http://gcmd.nasa.gov/r/l/TermsOfUse 9.1.5 2020-03-26 22:07:25 GCMD - Platforms GLONASS GLONASS or "Global Navigation Satellite System", is a space-based satellite navigation system operating in the radionavigation-satellite service. It provides an alternative to GPS and is the second navigational system in operation with global coverage and of comparable precision. Manufacturers of GPS devices say that adding GLONASS made more satellites available to them, meaning positions can be fixed more quickly and accurately, especially in built-up areas where the view to some GPS satellites is obscured by buildings. Smartphones generally tend to use the same chipsets and the versions used since 2015 receive GLONASS signals and positioning information along with GPS. Since 2012, GLONASS was the second most used positioning system in mobile phones after GPS. The system has the advantage that smartphone users receive a more accurate reception identifying location to within 2 meters. 2017-08-15 13:58:44.0 [tstevens] update Definition (GLONASS or "Global Navigation Satellite System", is a space-based satellite navigation system operating in the radionavigation-satellite service. It provides an alternative to GPS and is the second navigational system in operation with global coverage and of comparable precision. Manufacturers of GPS devices say that adding GLONASS made more satellites available to them, meaning positions can be fixed more quickly and accurately, especially in built-up areas where the view to some GPS satellites is obscured by buildings. Smartphones generally tend to use the same chipsets and the versions used since 2015 receive GLONASS signals and positioning information along with GPS. Since 2012, GLONASS was the second most used positioning system in mobile phones after GPS. The system has the advantage that smartphone users receive a more accurate reception identifying location to within 2 meters.); update Definition (https://www.glonass-iac.ru/en/); SENTINEL-1 PREFERRED TERMS: 1A, S1B, S1C, S1D, Sentinel-1 DEFINITION Sentinel-1 is the European Radar Observatory, representing the first new space component of the GMES (Global Monitoring for Environment and Security) satellite family, designed and developed by ESA and funded by the EC (European Commission). The Copernicus missions (Sentinel-1, -2, and -3) represent the EU contribution to GEOSS (Global Earth Observation System of Systems). Sentinel-1 is composed of a constellation of two satellites, Sentinel-1A and Sentinel-1B, sharing the same orbital plane with a 180° orbital phasing difference. The mission provides an independent operational capability for continuous radar mapping of the Earth with enhanced revisit frequency, coverage, timeliness and reliability for operational services and applications requiring long time series. BROADER CONCEPT: Earth Observation Satellite ENTRY TERMS: SENTINEL-1 NOTE: A,B,C,D HOSTS: SAR URI: https://earth.esa.int/concept/sentinel-1 2018-11-05 12:39:39.0 [mmorahan] update Definition (PREFERRED TERMS: 1A, S1B, S1C, S1D, Sentinel-1 DEFINITION Sentinel-1 is the European Radar Observatory, representing the first new space component of the GMES (Global Monitoring for Environment and Security) satellite family, designed and developed by ESA and funded by the EC (European Commission). The Copernicus missions (Sentinel-1, -2, and -3) represent the EU contribution to GEOSS (Global Earth Observation System of Systems). Sentinel-1 is composed of a constellation of two satellites, Sentinel-1A and Sentinel-1B, sharing the same orbital plane with a 180° orbital phasing difference. The mission provides an independent operational capability for continuous radar mapping of the Earth with enhanced revisit frequency, coverage, timeliness and reliability for operational services and applications requiring long time series. BROADER CONCEPT: Earth Observation Satellite ENTRY TERMS: SENTINEL-1 NOTE: A,B,C,D HOSTS: SAR URI: https://earth.esa.int/concept/sentinel-1); 2018-11-05 12:39:08.0 [mmorahan] update Definition (PREFERRED TERMS: 1A, S1B, S1C, S1DSentinel-1 DEFINITION Sentinel-1 is the European Radar Observatory, representing the first new space component of the GMES (Global Monitoring for Environment and Security) satellite family, designed and developed by ESA and funded by the EC (European Commission). The Copernicus missions (Sentinel-1, -2, and -3) represent the EU contribution to GEOSS (Global Earth Observation System of Systems). Sentinel-1 is composed of a constellation of two satellites, Sentinel-1A and Sentinel-1B, sharing the same orbital plane with a 180° orbital phasing difference. The mission provides an independent operational capability for continuous radar mapping of the Earth with enhanced revisit frequency, coverage, timeliness and reliability for operational services and applications requiring long time series. BROADER CONCEPT: Earth Observation Satellite ENTRY TERMS: SENTINEL-1 NOTE: A,B,C,D HOSTS: SAR URI: https://earth.esa.int/concept/sentinel-1); 2018-11-05 12:30:01.0 [mmorahan] Move Concepts delete broader relation (null); add broader relation (SENTINEL-1 [007c3084-89db-458e-8387-14e192b6cb8e,367691] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761]); 2018-11-05 12:29:33.0 [mmorahan] Cut Concepts delete broader relation (null); add broader relation (SENTINEL-1 [007c3084-89db-458e-8387-14e192b6cb8e,367691] - Trash Can/Platforms [6089b3e5-7db9-46e1-b73b-2d679f34abb4,354203]); 2018-11-02 21:16:54.0 [mmorahan] insert Definition (id: null text: The mission is composed of a constellation of two satellites, SENTINEL-1A and SENTINEL-1B, sharing the same orbital plane. SENTINEL-1 is designed to work in a pre-programmed, conflict-free operation mode, imaging all global landmasses, coastal zones and shipping routes at high resolution and covering the global ocean with vignettes. This ensures the reliability of service required by operational services and a consistent long term data archive built for applications based on long time series. Source: https://sentinel.esa.int/web/sentinel/missions/sentinel-1 Group: Platform_Details Entry_ID: SENTINEL-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: Sentinel GMES Short_Name: SENTINEL-1 End_Group Group: Platform_Associated_Instruments Short_Name: SENTINEL-1 C-SAR End_Group Group: Orbit Orbit_Altitude: 693 km Orbit_Type: LEO > LOW EARTH ORBIT > POLAR SUN-SYNCHRONOUS End_Group Creation_Date: 2009-12-18 Online_Resource: https://sentinel.esa.int/web/sentinel/missions/sentinel-1 Sample_Image: http://www.esa.int/images/sentinel2_alcatel_M.gif Group: Platform_Logistics Launch_Date: 2014-04-03 Launch_Site: KOUROU, FRENCH GUIANA Design_Life: 7 Years Primary_Sponsor: ESA/EU End_Group End_Group language code: en); 2018-06-12 19:27:23.0 [mmorahan] Rename Concept update PrefLabel (SENTINEL-1); 2018-06-12 19:26:21.0 [mmorahan] Move Concepts delete broader relation (null); add broader relation (Sentinel-1 [007c3084-89db-458e-8387-14e192b6cb8e,367691] - Sentinel GMES [2c9f1fcc-d9c8-4c6d-b701-45c97cee511f,344719]); 2018-06-12 19:15:52.0 [mmorahan] Move Concepts add narrower relation (Sentinel-1 [007c3084-89db-458e-8387-14e192b6cb8e,367691] - SENTINEL-1B [9940dbad-1a9a-4858-a0e8-af35b21277e2,345451]); 2018-06-12 19:15:42.0 [mmorahan] Move Concepts add narrower relation (Sentinel-1 [007c3084-89db-458e-8387-14e192b6cb8e,367691] - SENTINEL-1A [c7279e54-f7c1-4ee7-a957-719d6021a3f6,345757]); 2018-06-12 19:14:57.0 [mmorahan] Insert Concept add broader relation (Sentinel-1 [007c3084-89db-458e-8387-14e192b6cb8e,367691] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761]); MICOM 2015-08-10 18:49:03.0 [epneff] added long name insert AltLabel (id: null text: Miami Isopycnic Coordinate Ocean Model language code: en); 2015-08-10 18:48:31.0 [epneff] Insert Concept add broader relation (MICOM [00f8ab1f-040f-40b4-ba64-9f6a4c2ca7ed,158235] - Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215]); STS-62 Space Transport System STS-62 Mission Objectives: The 14-day mission is the latest in a series of Extended Duration Orbiter (EDO) flights which will provide additional information for on-going medical studies that assess the impact of long-duration spaceflight, 10 or more days, on astronaut health, identify any operational medical concerns and test countermeasures for the adverse effects of weightlessness on human physiology. The United States Microgravity Payload (USMP) will be making its second flight aboard the Space Shuttle. The USMP flights are regularly scheduled on Shuttle missions to permit scientists access to space for microgravity and fundamental science experiments which cannot be duplicated on Earth and provide the foundation for advanced scientific investigations that will be done on the international space station. The Office of Aeronautics and Space Technology (OAST-2) payload contains six experiments that will obtain technology data to support future needs for advanced satellites, sensors, microcircuits and the space station. Data gathered by the OAST-2 experiments could lead to satellites and spacecraft that are cheaper, more reliable and able to operate more efficiently. STS-62 will help scientists calibrate sensitive ozone- detecting instruments with the sixth flight of the Shuttle Solar Backscatter Ultraviolet (SSBUV) Instrument. This highly calibrated tool is used to check data from ozone-measuring instruments on free-flying satellites -- NASA's Total Ozone Mapping Spectrometer (TOMS) and Upper Atmosphere Research Satellite (UARS) and the National Oceanic and Atmospheric Administration NOAA-9 and NOAA-11 satellites. The Protein Crystal Growth (PCG) experiments and the Commercial Protein Crystal Growth (CPCG) experiments aboard Columbia will help scientists understand the growth of crystals to study the complex molecular structures of important proteins. By knowing the structure of specific proteins, scientists can design new drug treatments for humans and animals and develop new or better food crops. NASA's efforts in the important field of biotechnology are represented by the fourth flight of the Physiological Systems Experiment which is designed to evaluate pharmaceutical, agricultural or biotechnological products, and the first flight of the Biotechnology Specimen Temperature Controller (BSTC), designed to test the performance of a temperature control device being developed for use with the Bioreactor, a cell- culture growth device. Also flying again on the Shuttle is the Commercial Generic Bioprocessing Apparatus (CGBA) payload which will support more than 15 commercial life science investigations that have application in biomaterials, biotechnology, medicine and agriculture. The Middeck 0-Gravity Dynamics Experiment (MODE) will make its second flight on STS-62. MODE investigates how the microgravity of space flight influences the behavior of large space structures. The MODE test article can be configured in different shapes typical of space structural forms-- the truss of a space station, for example -- to help engineers develop and verify an analytical modeling capability for predicting the linear and nonlinear modal characteristics of space structures in a microgravity environment. MODE also will gather force measurements of nominal, crew-induced disturbance loads on the Shuttle. Astronauts will demonstrate a new magnetic end effector and grapple fixture design for the Shuttle's Canadian-built robot arm that engineers believe will increase the arm's dexterity and alignment accuracy, provide operators with a sense of touch and allow the use of more compact "handles" on satellites and other Shuttle payloads. Additional information available at "http://science.ksc.nasa.gov/shuttle/missions/sts-62/mission-sts-62.html" [Summary provided by NASA] CALIPSO [Source: NASA Science Missions Directorate] The CALIPSO satellite was developed to help scientists answer significant questions and provide new information about the effects of clouds and aerosols (airborne particles) on changes in the Earth's climate. Understanding these components will provide the international science community with a more comprehensive data set that is essential for a better understanding of the Earth's climatic processes. Accurate climate model predictions will provide international and national leaders accurate information to make more informed policy decisions about global climate change. CALIPSO flies a 3-channel lidar with a suite of passive instruments in formation with Aqua to obtain coincident observations of radiative fluxes and atmospheric conditions. This enables new observationally based assessments of the radiative effects of aerosol and clouds that will greatly improve out ability to predict future climate change. CloudSat also flies in formation with CALIPSO to provide a comprehensive characterization of the structure and composition of clouds and their effects on climate under all weather conditions. This comprehensive set of measurements is essential for accurate quantification of global aerosol and cloud radiative effects to understand their role in formation and variation of Earth's climate. This is a cooperative mission with France. For more information on CALIPSO, see: https://www-calipso.larc.nasa.gov/ Group: Platform_Details Entry_ID: CALIPSO Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: EOS (Earth Observing System) Short_Name: CALIPSO Long_Name: Cloud-Aerosol Lidar and Infrared Pathfinder Satellite Observations End_Group Group: Platform_Associated_Instruments Short_Name: WFC Short_Name: CALIOP Short_Name: IIR End_Group Group: Orbit Orbit_Altitude: 705 km Orbit_Inclination: 98.2 degrees Period: 99 minutes Repeat_Cycle: 16 days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-04-17 Online_Resource: https://www-calipso.larc.nasa.gov Online_Resource: https://eosweb.larc.nasa.gov/project/calipso/calipso_table nline_Resource: https://www.nasa.gov/mission_pages/calipso/ Group: Platform_Logistics Launch_Date: 2006-04-28 Launch_Site: Vandenberg Air Force Base, USA Design_Life: 3 years Primary_Sponsor: USA/NASA Primary_Sponsor: FRANCE/CNES Primary_Sponsor: Alcatel End_Group End_Group 2020-01-02 22:47:02.0 [sritz] update Definition ([Source: NASA Science Missions Directorate] The CALIPSO satellite was developed to help scientists answer significant questions and provide new information about the effects of clouds and aerosols (airborne particles) on changes in the Earth's climate. Understanding these components will provide the international science community with a more comprehensive data set that is essential for a better understanding of the Earth's climatic processes. Accurate climate model predictions will provide international and national leaders accurate information to make more informed policy decisions about global climate change. CALIPSO flies a 3-channel lidar with a suite of passive instruments in formation with Aqua to obtain coincident observations of radiative fluxes and atmospheric conditions. This enables new observationally based assessments of the radiative effects of aerosol and clouds that will greatly improve out ability to predict future climate change. CloudSat also flies in formation with CALIPSO to provide a comprehensive characterization of the structure and composition of clouds and their effects on climate under all weather conditions. This comprehensive set of measurements is essential for accurate quantification of global aerosol and cloud radiative effects to understand their role in formation and variation of Earth's climate. This is a cooperative mission with France. For more information on CALIPSO, see: https://www-calipso.larc.nasa.gov/ Group: Platform_Details Entry_ID: CALIPSO Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: EOS (Earth Observing System) Short_Name: CALIPSO Long_Name: Cloud-Aerosol Lidar and Infrared Pathfinder Satellite Observations End_Group Group: Platform_Associated_Instruments Short_Name: WFC Short_Name: CALIOP Short_Name: IIR End_Group Group: Orbit Orbit_Altitude: 705 km Orbit_Inclination: 98.2 degrees Period: 99 minutes Repeat_Cycle: 16 days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-04-17 Online_Resource: https://www-calipso.larc.nasa.gov Online_Resource: https://eosweb.larc.nasa.gov/project/calipso/calipso_table nline_Resource: https://www.nasa.gov/mission_pages/calipso/ Group: Platform_Logistics Launch_Date: 2006-04-28 Launch_Site: Vandenberg Air Force Base, USA Design_Life: 3 years Primary_Sponsor: USA/NASA Primary_Sponsor: FRANCE/CNES Primary_Sponsor: Alcatel End_Group End_Group); 2020-01-02 22:39:48.0 [sritz] delete Resource (null); 2018-03-12 18:51:11.0 [sritz] update Definition ([Source: NASA Science Missions Directorate] The CALIPSO satellite was developed to help scientists answer significant questions and provide new information about the effects of clouds and aerosols (airborne particles) on changes in the Earth's climate. Understanding these components will provide the international science community with a more comprehensive data set that is essential for a better understanding of the Earth's climatic processes. Accurate climate model predictions will provide international and national leaders accurate information to make more informed policy decisions about global climate change. CALIPSO flies a 3-channel lidar with a suite of passive instruments in formation with Aqua to obtain coincident observations of radiative fluxes and atmospheric conditions. This enables new observationally based assessments of the radiative effects of aerosol and clouds that will greatly improve out ability to predict future climate change. CloudSat also flies in formation with CALIPSO to provide a comprehensive characterization of the structure and composition of clouds and their effects on climate under all weather conditions. This comprehensive set of measurements is essential for accurate quantification of global aerosol and cloud radiative effects to understand their role in formation and variation of Earth's climate. This is a cooperative mission with France. For more information on CALIPSO, see: https://www-calipso.larc.nasa.gov/ Group: Platform_Details Entry_ID: CALIPSO Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: EOS (Earth Observing System) Short_Name: CALIPSO Long_Name: Cloud-Aerosol Lidar and Infrared Pathfinder Satellite Observations End_Group Group: Platform_Associated_Instruments Short_Name: WFC Short_Name: CALIOP Short_Name: IIR End_Group Group: Orbit Orbit_Altitude: 705 km Orbit_Inclination: 98.2 degrees Period: 99 minutes Repeat_Cycle: 16 days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-04-17 Online_Resource: https://www-calipso.larc.nasa.gov Online_Resource: https://eosweb.larc.nasa.gov/project/calipso/calipso_table Sample_Image: https://www-calipso.larc.nasa.gov/about/images/A-Train_Mar02_01.jpg Group: Platform_Logistics Launch_Date: 2006-04-28 Launch_Site: Vandenberg Air Force Base, USA Design_Life: 3 years Primary_Sponsor: USA/NASA Primary_Sponsor: FRANCE/CNES Primary_Sponsor: Alcatel End_Group End_Group); 2018-03-12 15:21:29.0 [sritz] update Definition ([Source: NASA Science Missions Directorate, https://nasascience.nasa.gov/missions/calipso ] The CALIPSO satellite was developed to help scientists answer significant questions and provide new information about the effects of clouds and aerosols (airborne particles) on changes in the Earth's climate. Understanding these components will provide the international science community with a more comprehensive data set that is essential for a better understanding of the Earth's climatic processes. Accurate climate model predictions will provide international and national leaders accurate information to make more informed policy decisions about global climate change. CALIPSO flies a 3-channel lidar with a suite of passive instruments in formation with Aqua to obtain coincident observations of radiative fluxes and atmospheric conditions. This enables new observationally based assessments of the radiative effects of aerosol and clouds that will greatly improve out ability to predict future climate change. CloudSat also flies in formation with CALIPSO to provide a comprehensive characterization of the structure and composition of clouds and their effects on climate under all weather conditions. This comprehensive set of measurements is essential for accurate quantification of global aerosol and cloud radiative effects to understand their role in formation and variation of Earth's climate. This is a cooperative mission with France. For more information on CALIPSO, see: https://www-calipso.larc.nasa.gov/ Group: Platform_Details Entry_ID: CALIPSO Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: EOS (Earth Observing System) Short_Name: CALIPSO Long_Name: Cloud-Aerosol Lidar and Infrared Pathfinder Satellite Observations End_Group Group: Platform_Associated_Instruments Short_Name: WFC Short_Name: CALIOP Short_Name: IIR End_Group Group: Orbit Orbit_Altitude: 705 km Orbit_Inclination: 98.2 degrees Period: 99 minutes Repeat_Cycle: 16 days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-04-17 Online_Resource: https://www-calipso.larc.nasa.gov Online_Resource: https://eosweb.larc.nasa.gov/project/calipso/calipso_table Sample_Image: https://www-calipso.larc.nasa.gov/about/images/A-Train_Mar02_01.jpg Group: Platform_Logistics Launch_Date: 2006-04-28 Launch_Site: Vandenberg Air Force Base, USA Design_Life: 3 years Primary_Sponsor: USA/NASA Primary_Sponsor: FRANCE/CNES Primary_Sponsor: Alcatel End_Group End_Group); 2018-03-12 15:20:40.0 [sritz] update Definition ([Source: NASA Science Missions Directorate, http://nasascience.nasa.gov/missions/calipso ] The CALIPSO satellite was developed to help scientists answer significant questions and provide new information about the effects of clouds and aerosols (airborne particles) on changes in the Earth's climate. Understanding these components will provide the international science community with a more comprehensive data set that is essential for a better understanding of the Earth's climatic processes. Accurate climate model predictions will provide international and national leaders accurate information to make more informed policy decisions about global climate change. CALIPSO flies a 3-channel lidar with a suite of passive instruments in formation with Aqua to obtain coincident observations of radiative fluxes and atmospheric conditions. This enables new observationally based assessments of the radiative effects of aerosol and clouds that will greatly improve out ability to predict future climate change. CloudSat also flies in formation with CALIPSO to provide a comprehensive characterization of the structure and composition of clouds and their effects on climate under all weather conditions. This comprehensive set of measurements is essential for accurate quantification of global aerosol and cloud radiative effects to understand their role in formation and variation of Earth's climate. This is a cooperative mission with France. For more information on CALIPSO, see: http://www-calipso.larc.nasa.gov/ Group: Platform_Details Entry_ID: CALIPSO Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: EOS (Earth Observing System) Short_Name: CALIPSO Long_Name: Cloud-Aerosol Lidar and Infrared Pathfinder Satellite Observations End_Group Group: Platform_Associated_Instruments Short_Name: WFC Short_Name: CALIOP Short_Name: IIR End_Group Group: Orbit Orbit_Altitude: 705 km Orbit_Inclination: 98.2 degrees Period: 99 minutes Repeat_Cycle: 16 days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-04-17 Online_Resource: https://www-calipso.larc.nasa.gov Online_Resource: https://eosweb.larc.nasa.gov/project/calipso/calipso_table Sample_Image: https://www-calipso.larc.nasa.gov/about/images/A-Train_Mar02_01.jpg Group: Platform_Logistics Launch_Date: 2006-04-28 Launch_Site: Vandenberg Air Force Base, USA Design_Life: 3 years Primary_Sponsor: USA/NASA Primary_Sponsor: FRANCE/CNES Primary_Sponsor: Alcatel End_Group End_Group); update Resource (image); update Resource (https://www-calipso.larc.nasa.gov/about/images/A-Train_Mar02_01.jpg); METEOSAT-10 2013-12-13 20:31:03.0 [saritz] Insert Concept add broader relation (METEOSAT-10 [01ee202c-22c5-442d-b4fd-65f424057ea3,106033] - METEOSAT [28eac19a-5500-4a21-af30-ab7a364ff8d0,73589]); Deep Discoverer Remotely operated vehicle (ROV) Deep Discoverer is owned by the NOAA Office of Ocean Exploration and Research and was built and continues to be maintained and operated by the Global Foundation for Ocean Exploration (GFOE) . Also known as “D2,” the vehicle is operated off NOAA Ship Okeanos Explorer with its sister vehicle, Seirios. Capable of diving to depths of 3.7 miles (6,000 meters), D2 provides scientists unprecedented access to the deep ocean. The main capability of Deep Discoverer is the ability to capture high-definition video, with the vehicle’s primary camera able to zoom in on a three-inch long organism from 10 feet away. D2’s 20 LED lights provide 150,000 lumens of light, illuminating the otherwise dark depths of the ocean. Equipped with two manipulator arms, Deep Discoverer is capable of collecting both biological and geological samples. The ROV is also outfitted with a variety of sensors to measure parameters such as salinity, water temperature, depth, and dissolved oxygen, providing additional information about the deep-ocean environment. Also available are five 1.7-liter Niskin bottles for water collection and a rotary suction sampler with six 4-liter sample jars for collecting more delicate biological samples. As a “remotely” operated vehicle, D2 carries no passengers. The vehicle is connected to Seirios and Okeanos Explorer via a long cable and is piloted by GFOE engineers on the ship. Thanks to telepresence technology, live video from D2 travels from the seafloor to the ship and then via satellite connection to scientists located on shore who use the real-time video to provide guidance to the pilots on where to go and which samples to collect. The live video is also broadcast to the Internet, allowing members of the public to join in on D2’s adventures. From delivering stunning high-definition video and gathering physical data about surrounding waters to allowing the collection of biological and geological samples, D2 is delivering data needed by scientists to better understand an ecosystem in its entirety, meaning we can make better decisions about an area's management as well as its protection. 2020-01-21 17:51:14.0 [tstevens] insert Definition (id: null text: Remotely operated vehicle (ROV) Deep Discoverer is owned by the NOAA Office of Ocean Exploration and Research and was built and continues to be maintained and operated by the Global Foundation for Ocean Exploration (GFOE) . Also known as “D2,” the vehicle is operated off NOAA Ship Okeanos Explorer with its sister vehicle, Seirios. Capable of diving to depths of 3.7 miles (6,000 meters), D2 provides scientists unprecedented access to the deep ocean. The main capability of Deep Discoverer is the ability to capture high-definition video, with the vehicle’s primary camera able to zoom in on a three-inch long organism from 10 feet away. D2’s 20 LED lights provide 150,000 lumens of light, illuminating the otherwise dark depths of the ocean. Equipped with two manipulator arms, Deep Discoverer is capable of collecting both biological and geological samples. The ROV is also outfitted with a variety of sensors to measure parameters such as salinity, water temperature, depth, and dissolved oxygen, providing additional information about the deep-ocean environment. Also available are five 1.7-liter Niskin bottles for water collection and a rotary suction sampler with six 4-liter sample jars for collecting more delicate biological samples. As a “remotely” operated vehicle, D2 carries no passengers. The vehicle is connected to Seirios and Okeanos Explorer via a long cable and is piloted by GFOE engineers on the ship. Thanks to telepresence technology, live video from D2 travels from the seafloor to the ship and then via satellite connection to scientists located on shore who use the real-time video to provide guidance to the pilots on where to go and which samples to collect. The live video is also broadcast to the Internet, allowing members of the public to join in on D2’s adventures. From delivering stunning high-definition video and gathering physical data about surrounding waters to allowing the collection of biological and geological samples, D2 is delivering data needed by scientists to better understand an ecosystem in its entirety, meaning we can make better decisions about an area's management as well as its protection. language code: en); 2020-01-21 17:21:50.0 [tstevens] Insert Concept add broader relation (Deep Discoverer [023cf280-8fd9-4a4d-8e18-54fac3f6dbbb,559711] - ROV [da6420b6-48ec-4ae2-98c7-0ef0538815a0,542741]); ERS-1 The first European Remote Sensing Satellite ERS-1, launched on 17 July 1991 at 01.46 UTC, operates in a sun-synchronous, near-polar orbit at an altitude of 785 km and an inclination of 98.5 degrees, known as the reference orbit. ERS-1 was conceived as an orbiting platform that would be capable of measuring, on a global scale, the Earth's atmospheric and surface properties with a high degree of accuracy. In fact it uses advanced microwave techniques to collect global measurements and images (much of the data are collected from remote areas such as the southern oceans and the Antarctic) independently of time of day and weather conditions. It also undertakes the measurement of many parameters that are not covered by existing satellite systems, including those of sea state, sea surface winds, ocean circulation and sea/ice levels. Satellite characteristics: -------- Platform: based on the SPOT Multimission Platform Power supply: 4 x 24 Ah batteries; 1.8 kW from solar array Attitude control: 3-axis stabilised earth pointing, with option of 9.5 degrees offset in Roll-Tilt Mode (RTM) Total mass: 2400 kg (at beginning of mission) Overall length: 11.8 m Solar array: 11.7 m x 2.4 m SAR antenna: 10.0 m x 1.0 m Scatterometer antennas: fore/aft 3.6 m x 0.25 m; mid: 2.3 m x 0.35 m Radar Altimeter antenna: 1.2 m diameter Design lifetime: 2-3 years --------- ERS-1 carries on-board a number of instruments consisting of a core set of active microwave sensors supported by additional, complementary instruments: the Active Microwave Instrument (AMI), which combines a Synthetic Aperture Radar (SAR) operating in image or wave mode and a wind scatterometer, the Radar Altimeter (RA), the Along-Track Scanning Radiometer and Microwave Sounder (ATSR), the Precise Range and Range-rate Equipment (PRARE) and Laser Retroreflectors (LRR). The primary objective of the ERS-1 mission is the monitoring of oceans and sea ice providing essential data for: - improved representation of oceans/atmosphere interactions in climatic models - major advances in the knowledge of ocean circulation and transfer of energy - more reliable estimates of the mass balance of the Arctic and Antarctic ice sheets - better monitoring of pollution and dynamic coastal processes - improved detection and management of land use change The ability of ERS-1 to acquire vast global data sets of ocean, atmosphere, ice and land phenomena contributes to the following fields of study: - Ocean/Ice: ocean circulation, global wind/wave relationships, sea ice and iceberg monitoring, etc. - Physical Earth: accurate determination of the ocean geoid, forestry, glaciology, geology and agriculture studies, etc. - Climate: contribution to the World Climate Research Programme and to the World Ocean Circulation Experiment - Weather and Sea: short and medium-term weather forecasting, sea surface state forecasting, wind speed and direction, location of pelagic fish through the monitoring of temperature fronts Relation between ERS-1 instruments and mission objectives ------------------------------------------------------------ Weather forecasting: AMI wind mode Sea-state forecasting: AMI, wave and wind modes Offshore activity: Altimeter, ATSR, AMI in wave and wind modes Ship routing: Altimeter, ATSR, AMI in wave and wind modes Fisheries (fish location): (Altimeter), (ATSR), AMI in wind mode Sea and iceberg monitoring: Altimeter, ATSR, AMI in image mode Oil and pollution detection: ATSR, AMI in image mode Coastal process: ATSR, AMI in image mode Land applications: (Altimeter), ATSR Ocean circulation: Altimeter(1), ATSR, (AMI in wave mode) Ocean tides: Altimeter(2) Wind fields(3): Altimeter, AMI (in image mode), in wave and wind mode Wave fields(3): Altimeter, AMI (in image mode), in wave and wind mode Polar oceans: Altimeter, ATSR, AMI in all modes. Land ice: Altimeter, AMI (in image mode) Sea-surface temperature: ATSR Marine biology: (ATSR) ------------------------------------------------------------ ( ) indicates limited applicability (1) For large-scale circulation, accurate orbit determination over short arcs is required (2) For solar tides, measurements from other satellites in complementary orbits are required (3) The altimeter and active microwave instrumentation are mutually supportive in deriving the wind and wave fields The complexity of the ERS-1 mission, which effectively consists of a combination of several different missions, requires a very careful approach when planning the mission operations. Taking into account the different mission objectives, and attempting to satisfy them in a quasi-optimal way in the course of ERS-1's lifetime, has held to the definition of phases of activity during the mission: - Phase 0: Orbit acquisition, initial switch-on and functional check-out (2 weeks after the launch) - Phase A: The Commisioning phase, using a 3 day repeat cycle (25 July 1991-10 December 1991) - Phase B : The first ice phase, using a 3 day repeat cycle (28 December 1991-1 April 1992) - Phase R: The Roll-Tilt phase, using a 35 day repeat cycle (2 April 1992-14 April 1992) - Phase C: The first multi-disciplinary phase, using a 35 day repeat cycle (14 April 1992-23 December 1993) - Phase D: The second ice phase, using a 3 day repeat cycle (23 December 1993-10 April 1994) - Phase E: The first geodetic phase, using a 172 day repeat cycle (10 April 1994-28 September 1994) - Phase F: The second Geodetic Phase, using a 172 day repeat cycle (28 September 1994-21 March 1995) - Phase G: The second Multi-Disciplinary Phase, using a 35 day repeat cycle (21 March 1995-10 March 2000) In the first half of April 1992, the satellite was operated in a Roll-tilt-mode (RTM) to allow SAR imaging at a different view angle. In fact by rotating the satellite body around its velocity vector (so-called 'Roll-tilt mode') the angle at which all the instruments look at the Earth can be varied. This allows experimentation with the SAR at an incidence angle of 35 degrees instead of the standard 23 degrees, thereby permitting analysis of a totally different set of signatures from objects on the Earth's surface, including in particular vegetation. Related URL: The ERS Missions: http://earth.esa.int/ers ERS-1 Design: http://earth.esa.int/ers/satconc For any query, please refer to: ESA/ESRIN Earth Observation Help Desk http://earth.esa.int Group: Platform_Details Entry_ID: ERS-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: ERS Earth Resource Satellite Short_Name: ERS-1 Long_Name: European Remote Sensing Satellite-1 End_Group Group: Synonymous_Platform_Names Short_Name: ERS-1 End_Group Group: Platform_Associated_Instruments Short_Name: ATSR Short_Name: RA Short_Name: SAR Short_Name: AMI End_Group Group: Orbit Orbit_Altitude: 782 to 785 km Orbit_Inclination: 98.52 deg Period: 100 min Repeat_Cycle: 3-day, 35-day and 176-day Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-09-14 Online_Resource: http://earth.esa.int/ers/satconc/ Online_Resource: http://earth.esa.int/ers/ Online_Resource: http://www.astronautix.com/craft/ers12.htm Sample_Image: http://earth.esa.int/icons/eeo/_ers-1_fully_deployed.gif Group: Platform_Logistics Launch_Date: 1991-07-17 Launch_Site: Kourou, French Guiana Design_Life: 2-3 YRS Primary_Sponsor: ESA End_Group End_Group MTSAT-2 MTSAT2 2016-06-09 18:50:11.0 [epneff] added altLabel insert AltLabel (id: null text: MTSAT2 language code: en); 2015-11-13 21:40:11.0 [mpmorahan] insert AltLabel (id: null text: The Multi-functional Transport Satellite 2 language code: en); 2012-08-07 19:04:22.0 [mpmorahan] Insert Concept add broader relation (MTSAT-2 [02db0949-495c-4579-8ff5-d1a9079c88b7,40467] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,31221]); CBERS-1 [Source: INPE CBERS home page, http://www.cbers.inpe.br/ingles/ ] The first satellite to be developed, CBERS-1, was launched with great success by the Chinese Long March 4B launcher, from the Taiyuan Launch Base, on Oct. 14, 1999. Launch occurred at 1:15 AM (Brasilia local time). Two modules compose the satellite. The first one is the payload module, where 3 cameras are located (CCD Camera, IRMSS Camera and WFI Camera) and a Transponder for the Brazilian Environmental Data Collection System. The second one is the service module, containing the equipment for power supply, control, telecommunications and remaining functions necessary to the satellite operation. Its orbit is Helios-synchronous, at a 778 km altitude. It performs about 14 revolutions a day and obtains a complete coverage of the Earth in 26 days. Group: Platform_Details Entry_ID: CBERS-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: CBERS (China-Brazil Earth Resources Satellite) Short_Name: CBERS-1 Long_Name: China-Brazil Earth Resource Satellite 1 End_Group Group: Synonymous_Platform_Names Short_Name: SJ 3 Short_Name: Shijian 3 Short_Name: 25940 End_Group Group: Platform_Associated_Instruments Short_Name: HRCCD Short_Name: WFI (CBERS 1,2) Short_Name: IRMSS End_Group Group: Orbit Orbit_Inclination: 98.6° Period: 99.6 minutes Perigee: 733.0 km Apogee: 745.0 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-08-29 Online_Resource: http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1999-057A Online_Resource: http://www.cbers.inpe.br/ingles/ Sample_Image: http://www.skyrocket.de/space/img_sat/cbers-1__1.jpg Group: Platform_Logistics Launch_Date: 1999-10-14 Launch_Site: Taiyuan Space Launch Center, China Primary_Sponsor: Brazil Primary_Sponsor: China End_Group End_Group DMSP 5D-2/F6 SOLRAD-7A Solrad 7A Characteristics: Designation: 00730 / 64001D Launch date: 11 Jan 1964 Country of origin: United States Mission: Scientific Perigee/Apogee: 900/921 km Inclination: 69.9 degrees Period: 103.2 min Launch vehicle: Thor Agena Launch site: Vandenberg Group: Platform_Details Entry_ID: SOLRAD-7A Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Platform_Series_or_Entity: SOLRAD Short_Name: SOLRAD-7A Long_Name: Solar Radiation-7A End_Group Group: Synonymous_Platform_Names Short_Name: solrad-7a End_Group Group: Platform_Associated_Instruments Short_Name: SXP End_Group Group: Orbit Orbit_Inclination: 69.9 degrees Period: 103.2 minutes Perigee: 900 km Apogee: 921 km End_Group Creation_Date: 2008-01-14 Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/experimentDisplay.do?id=1964-001D-01 Group: Platform_Logistics Launch_Date: 1964-01-11 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: NASA End_Group End_Group F/V GREAT PACIFIC UK-DMC-2 The Disaster Monitoring Constellation (DMC) is an international programme initially proposed in 1996 and led by SSTL (Surrey Satellite Technology Ltd) from the United Kingdom, to construct a network of five affordable Low Earth Orbit (LEO) microsatellites. The objective is to provide a daily global imaging capability at medium resolution (30-40 m), in 3-4 spectral bands, for rapid-response disaster monitoring and mitigation. 2019-07-24 16:32:38.0 [mmorahan] insert Definition (id: null text: The Disaster Monitoring Constellation (DMC) is an international programme initially proposed in 1996 and led by SSTL (Surrey Satellite Technology Ltd) from the United Kingdom, to construct a network of five affordable Low Earth Orbit (LEO) microsatellites. The objective is to provide a daily global imaging capability at medium resolution (30-40 m), in 3-4 spectral bands, for rapid-response disaster monitoring and mitigation. language code: en); insert WeightedRelation (id: null related concept uuid: 6a3c8a54-48ae-4357-8bbc-bd2c48ede3a7 relationship type: null relationship value: null generated by: null); 2019-07-24 16:28:01.0 [mmorahan] Insert Concept add broader relation (UK-DMC-2 [03afbb23-76cc-4241-b5a3-853367f8461f,368969] - DMC-2G (Disaster Monitoring Constellation- 2nd Generation) [e5184d15-eec8-4703-8318-243748ddbd0e,368737]); PIPER AZTEC The Piper PA-23, named Apache and later Aztec, was an American twin-engined monoplane, the first twin-engine aircraft built by Piper Aircraft. Originally to be named the "Twin-Stinson" and designed as a four-seater low-wing all-metal monoplane with a twin tail, the prototype first flew 2 March 1952. The prototype was then named the PA-21 to conform to Piper's numerical nomenclature[1] It was redesigned with a single vertical stabilizer and an all-metal rear fuselage and renamed to Apache 150 when it entered production in 1954; 1,231 were built. In 1958, the Apache 160 was produced by upgrading the engines to 160 hp (119 kW), and 816 were built before being superseded by the Apache 235, which went to 235 hp (175 kW) engines and swept tail surfaces (119 built). Declining sales of the Apache prompted the redesign dubbed PA-23-250 Aztec, with 250 hp (186 kW) Lycoming. The first models were delivered with O-540 Lycoming carburetor engines. These first models came in a five-seat configuration which became available in 1959. The later models of the Aztec were equipped with IO-540 fuel-injected engines and six-seat capacity, and continued in production until 1982. There were also turbocharged versions of the later models, which were able to fly at higher altitudes. [Text provided by: http://en.wikipedia.org/wiki/Piper_Aztec ] [Photo provided by: http://wikipedia.org ] Group: Platform_Details Entry_ID: PIPER AZTEC Group: Platform_Identification Platform_Category: Aircraft Short_Name: PIPER AZTEC End_Group Creation_Date: 2008-07-14 Online_Resource: http://en.wikipedia.org/wiki/Piper_Aztec Online_Resource: http://www.newpiper.com/ Sample_Image: http://upload.wikimedia.org/wikipedia/commons/c/cc/PiperAztecToronto.jpg End_Group R/V PALMETTO The R/V Palmetto is part of a fleet of vessels operated by the South Carolina Department of Natural Resources (SCDNR), Marine Resources Research Institute. The research vessel is used primarily for fishery surveys of natural and man-made fish habitats. The Palmetto conducts fishery and oceanographic surveys from Cape Hatteras, North Carolina to Palm Beach, Florida, and offshore to 100 miles. The ship is outfitted primarily for oceanographic and fishery and surveys including tag and release survival rate studies. It is equipped with three winches for deploying hydrographic gear (CTDs), underwater television and remotely operated vehicles (ROVs), fishing gear (longlines, traps, small trawls), and other sampling gear (e.g. plankton nets). Group: Platform_Details Entry_ID: R/V PALMETTO Group: Platform_Identification Platform_Category: In Situ Ocean-based Platforms Platform_Series_or_Entity: SHIPS Short_Name: R/V PALMETTO End_Group Creation_Date: 2012-07-19 Online_Resource: http://oceanexplorer.noaa.gov/technology/vessels/palmetto/palmetto.html Sample_Image: http://oceanexplorer.noaa.gov/technology/vessels/palmetto/palmetto_220.jpg End_Group JPSS-2 JPSS-2 will provide operational continuity of satellite-based observations and products for NOAA Polar-Orbiting Environmental Satellites (POES) and Suomi NPP satellite and ground systems. The baseline plan for JPSS Ground System will be sustained to support JPSS-2, similar to JPSS-1. The JPSS-2 spacecraft will host the following instruments: (1) VIIRS, (2) CrIS, (3) ATMS, (4) OMPS-N, and (5) RBI. More Information: https://www.jpss.noaa.gov 2019-10-04 19:37:40.0 [sritz] update Definition (JPSS-2 will provide operational continuity of satellite-based observations and products for NOAA Polar-Orbiting Environmental Satellites (POES) and Suomi NPP satellite and ground systems. The baseline plan for JPSS Ground System will be sustained to support JPSS-2, similar to JPSS-1. The JPSS-2 spacecraft will host the following instruments: (1) VIIRS, (2) CrIS, (3) ATMS, (4) OMPS-N, and (5) RBI. More Information: https://www.jpss.noaa.gov); 2019-10-04 19:36:24.0 [sritz] update Definition (Source: NOAA JPSS, https://www.jpss.noaa.gov/mission_and_instruments.html); 2018-02-02 17:12:47.0 [sritz] update WeightedRelation (Platform-Instrument); update WeightedRelation (1); 2018-02-02 17:12:20.0 [sritz] insert WeightedRelation (id: null related concept uuid: de7e08db-86f1-4593-ba9e-288f9f7b063e relationship type: null relationship value: null generated by: null); 2018-01-30 22:34:45.0 [sritz] delete WeightedRelation (null); insert WeightedRelation (id: null related concept uuid: 91923fed-61c3-4125-b69d-1eeccafce52c relationship type: null relationship value: null generated by: null); 2018-01-30 22:32:47.0 [sritz] insert WeightedRelation (id: null related concept uuid: 2ab4ba32-0bb3-4e4e-bac6-1ff4a3baf0df relationship type: null relationship value: null generated by: null); 2018-01-30 22:32:17.0 [sritz] insert WeightedRelation (id: null related concept uuid: 10adce36-ce10-4ae6-94f9-211911c7dd15 relationship type: null relationship value: null generated by: null); 2018-01-30 22:09:12.0 [sritz] insert WeightedRelation (id: null related concept uuid: dd7c719e-5767-4ceb-b83a-66c1401dab4a relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 5ad54972-6d91-4860-aea4-7914fe7ef823 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 9a68e783-b54c-41f2-82ce-da975af38359 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 6af7a52e-094d-4ba7-9174-ed967260939c relationship type: null relationship value: null generated by: null); 2016-07-19 19:03:37.0 [saritz] update Definition (Source: NOAA JPSS, http://www.jpss.noaa.gov/mission_and_instruments.html); 2016-07-19 19:03:02.0 [saritz] update WeightedRelation (Similar); update WeightedRelation (1); update WeightedRelation (Similar); update WeightedRelation (1); 2016-07-19 19:02:21.0 [saritz] update WeightedRelation (Similar); update WeightedRelation (1); 2016-07-19 18:59:30.0 [saritz] insert WeightedRelation (id: null related concept uuid: 5c2364ca-c01a-4f69-8808-282c3854b2f6 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 586db0b3-5f94-466e-b7c1-a2dbedc0c1fc relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 85a52725-e6a1-430a-8506-c08c59ef31c7 relationship type: null relationship value: null generated by: null); 2016-07-19 18:54:17.0 [saritz] insert Definition (id: null text: JPSS-2 will provide operational continuity of satellite-based observations and products for NOAA Polar-Orbiting Environmental Satellites (POES) and Suomi NPP satellite and ground systems. The baseline plan for JPSS Ground System will be sustained to support JPSS-2, similar to JPSS-1. The JPSS-2 spacecraft will host the following instruments: (1) VIIRS, (2) CrIS, (3) ATMS, (4) OMPS-N, and (5) RBI. language code: en); 2016-07-19 18:46:38.0 [saritz] Insert Concept add broader relation (JPSS-2 [043dc242-1014-4e9a-91ee-c472b791b026,247449] - Joint Polar Satellite System (JPSS) [5c2364ca-c01a-4f69-8808-282c3854b2f6,226695]); COSMOS 1500 The Cosmos-1500 spacecraft was launched on 28 September 1983, in Plesetsk, U.S.S.R.. Cosmos-1500 was a precursor to the operational Russian Okean ("Ocean") series of oceanographic remote sensing missions. Cosmos-1500 was launched into a 649 x 679 km orbit at 82.6 deg. inclination. The Cosmos-1500 tested new sensors and methods of data collection and processing. Cosmos-1500 had the capability of overlapping and processing images from its sensors. Data from Cosmos-1500 were sent directly to ships or automated data receiving stations and was applied in navigation in northern oceans. The instrument complement was highlighted by an all-weather X-band Side-Looking Real Aperature radar (SLRAR) operating at 9.5 GHz. other instruments included a multispectral scanner (MSL), a scanning high-frequency radiometer (SHF), and transponders for collecting data from ice and buoy transmitters. Group: Platform_Details Entry_ID: COSMOS 1500 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: COSMOS Short_Name: COSMOS 1500 End_Group Group: Synonymous_Platform_Names Short_Name: COSMOS 1500 End_Group Group: Orbit Orbit_Inclination: 82.5 degrees Period: 95.8 min Perigee: 546 km Apogee: 565 km End_Group Creation_Date: 2007-09-12 Online_Resource: http://www.n2yo.com/satellite.php?s=14372 Group: Platform_Logistics Launch_Date: 1983-09-28 Primary_Sponsor: Russia End_Group End_Group QUICKBIRD QUICKBIRD (DIGITALGLOBE'S QUICKBIRD) The QuickBird satellite is the first in a constellation of spacecraft that DigitalGlobe is developing that offers highly accurate, commercial high-resolution imagery of Earth. QuickBird's global collection of panchromatic and multispectral imagery is designed to support applications ranging from map publishing to land and asset management to insurance risk assessment. Today, DigitalGlobe's QuickBird is the only spacecraft able to offer sub-meter resolution imagery, industry-leading geolocational accuracy, large on-board data storage, and an imaging footprint 2 to 10 times larger than any other commercial high-resolution satellite. QuickBird was designed and built by our strategic partners, Ball Aerospace & Technologies Corp., Kodak, and Fokker Space, all leaders in their fields. By utilizing proven technology from each supplier, we have developed a state-of-the-art, satellite system built from space-qualified components. This system successfully meets DigitalGlobe's demanding performance requirements for high image quality, robust image collection, and long mission life. Group: Platform_Details Entry_ID: QUICKBIRD Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: QUICKBIRD Long_Name: DigitalGlobe's QuickBird End_Group Group: Synonymous_Platform_Names Short_Name: Quickbird End_Group Group: Orbit Orbit_Altitude: 450 km Orbit_Inclination: 98 degree Repeat_Cycle: 2-3 days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-11-28 Online_Resource: http://www.digitalglobe.com/index.php/85/QuickBird Sample_Image: http://www.digitalglobe.com/image.php?id=93 Group: Platform_Logistics Launch_Date: 2001-10-18 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: DigitalGlobe End_Group End_Group 2016-06-09 19:00:52.0 [epneff] added altLabel insert AltLabel (id: null text: QUICKBIRD (DIGITALGLOBE'S QUICKBIRD) language code: en); PROFS Prototype Regional Observing and Forecasting Service (PROFS) is a program responsible for improving local weather service capability through application of recent technological advances in high speed communication and computers. This program has worked closely with the National Weather Service (NWS) and the National Earth Satellite Service (NESS) to develop a highly sophisticated system (Brown, 1983) which integrates information from radar, satellites, national weather circuits, and a network of 22 automated surface observing stations spread over the northern Front Range and the eastern plains of Colorado. That network, hereafter referred to as the mesonet, provides real-time wind, temperature, humidity, pressure, rainfall, isolation and visual range data, offering the forecaster details of meteorological fields unavailable from other sources. Group: Platform_Details Entry_ID: PROFS Group: Platform_Identification Platform_Category: In Situ Land-based Platforms Platform_Series_or_Entity: WEATHER STATIONS/NETWORKS Short_Name: PROFS Long_Name: Program for Regional Observing and Forecast Systems Mesonet End_Group Group: Synonymous_Platform_Names Short_Name: PROFS End_Group Creation_Date: 2007-12-12 Online_Resource: http://www.fsl.noaa.gov/its/papers/GeoData/pm7-98g.html End_Group OCEAN STATE ESTIMATION major goal of oceanography is to combine all of the theoretical understanding we have about how a global fluid behaves with all of the observations pertaining to it. For anyone trying to understand climate, that means using the best ocean general circulation models, the best models of sea ice—which has a major high latitude influence on the ocean, and the best available estimates of the interacting meteorological fields. 2019-11-25 18:16:06.0 [mmorahan] insert Definition (id: null text: major goal of oceanography is to combine all of the theoretical understanding we have about how a global fluid behaves with all of the observations pertaining to it. For anyone trying to understand climate, that means using the best ocean general circulation models, the best models of sea ice—which has a major high latitude influence on the ocean, and the best available estimates of the interacting meteorological fields. language code: en); 2019-11-25 18:11:58.0 [mmorahan] Insert Concept add broader relation (OCEAN STATE ESTIMATION [04d24dfe-c9f7-43b6-8bd8-8f2613767257,423567] - Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,405101]); C-185 AES Atmospheric Environment Service: Certain ships of Canadian registry are fitted with this equipment on a loan basis. The cup wheel and wind vane are mounted on either end of a U - shaped arm. This U - arm is mounted as high and as forward on the ship as possible, so that the unit is in a flow of air relatively undisturbed by the ship's superstructure. The instrument requires 115 volt, 60 cycle power to operate the direction unit. The speed unit supplies its own power by means of a small permanent magnet generator which is operated by the rotating cup wheel. The wind speed and direction dials are mounted in a small cabinet located conveniently in the chart room or wheel house. The wind speed dial is calibrated in nautical miles per hour, from 0 to 1 00 knots. The wind direction dial is calibrated in tens of degrees from 01 0? to 360?. The direction indicated by the dial will be the direction of the apparent wind in relation to the heading of the ship, and not to north. Thus an indication of 360? represents an apparent wind from dead ahead; 090?, a wind on the starboard beam; 180?, a wind from dead astern; and 270?, a wind from the port beam. [Source: MID] FOKKER F27 The Fokker F27 Friendship is a turboprop airliner designed and built by the Dutch aircraft manufacturer Fokker. Design of the Fokker F27 started in the 1950s as a replacement to the successful DC-3 airliner. The manufacturer evaluated a number of different configurations before finally deciding on a high wing twin Rolls-Royce Dart engine layout with a pressurised cabin for 28 passengers. The first prototype, registered PH-NIV, first flew on 24 November 1955. The second prototype and initial production machines were 3 ft (0.9 m) longer, addressing the first aircraft's slightly tail-heavy handling and also providing space for more (32) passengers. These aircraft also used the more powerful Dart Mk 528 engine. The first production model, the F27-100, was delivered to Aer Lingus in September 1958. In 1956 Fokker signed a licensing deal with the US aircraft manufacturer Fairchild for the latter to construct the F27 in the USA. The first U.S.-built aircraft flew on 12 April 1958. Fairchild also independently developed a stretched version, called the FH-227. At the end of the Fokker F27s production in 1987, 793 units had been built (including 207 in the USA by Fairchild), which makes it the most successful western European civil turboprop airliner. Many aircraft have been modified from passenger service to cargo or express-package freighter roles. In the early 1980s, Fokker developed a successor to the Friendship, the Fokker 50. Although based on the F27-500 airframe, the Fokker 50 is virtually a new aircraft with Pratt & Whitney Canada engines and modern systems. Its general performance and passenger comfort were improved over the F27. [Text provided by: http://en.wikipedia.org/wiki/Fokker_F27 ] [Photo provided by: http://www.zap16.com/ ] Group: Platform_Details Entry_ID: FOKKER F27 Group: Platform_Identification Platform_Category: Aircraft Short_Name: FOKKER F27 End_Group Creation_Date: 2008-07-14 Online_Resource: http://en.wikipedia.org/wiki/Fokker_F27 Sample_Image: http://www.zap16.com/images/maac_f27_cf-jsd.jpg End_Group GEOSAT - Spacecraft Brief Description - The GEOdetic SATellite (GEOSAT) was a dedicated US Navy military oceanographic satellite consisting of a radar altimeter designed to obtain closely spaced, precise mapping of the earth's geoid over the ocean. On November 8, 1986, the satellite was moved into an Exact Repeat Mission (ERM) orbit with a repeat cycle of 17.05 days. The GEOSAT mission was originally managed by the Office of Naval Research (ONR). During the development phase, the program responsibility was transferred to the Naval Electronics Systems Command, now called the Space and Naval Warfare Systems Command (SPAWAR) in Washington, D.C. The Applied Physics Laboratory (APL) was the prime contractor for the spacecraft and radar altimeter and performed spacecraft command and control operations and collected the satellite data. The data was distributed to the Naval Surface Weapons Center (NSWC), the Naval Ocean Research and Development Activity (NORDA), and NOAA. An arrangement was made with the National Ocean Service of NOAA to obtain the classified GEOSAT geophysical data records (GDR) providing wind, wave and sea-level products and made available to the user community. NASA obtained GEOSAT data for extensive waveform modeling and ice sheet research.The basic structure of the GEOSAT is similar to the GEOS-3 satellite: The design consists of a conical structure below the core for the structural attachment of the velocity control system. The GEOSAT attitude control subsystem was designed to point the radar altimeter to within 1 degree of nadir 98 percent of the time. The system components were a 20-foot scissors boom with 100-pound end mass, redundant momentum wheels for roll and yaw stiffness, and pitch and roll attitude control thrusters. Attitude sensing was provided through the use of three digital sun-attitude detectors and a three-axis vector magnetometer. Spacecraft command was accomplished via a VHF uplink from the APL ground station. The telemetry subsystem consisted of two S-band transmitters, two tape recorders, and two encryption units. The GEOSAT was equipped with two Odetics dual-track high-density tape recorders that independently recorded the 10.205 kbps telemetry stream and played it back at 833 kbps for transmission to the ground. The GEOSAT also included redundant Doppler beacons for continuous tracking by a network of ground stations within the Defense Mapping Agency (DMA) and for a source of accurate timing to the radar altimeter and the telemetry subsystem. A C-band transponder was also included on GEOSAT. See Jensen,J.J. and F.R.Wooldridge, 'The Navy GEOSAT Mission: An Introduction'; McConathy, D.R. and C.C.Kilgus, 'The Navy GEOSAT Mission: An Overview', and Frain,W.E., M.H.Barbagallo, and R.J.Harvey,'The Design and Operation of GEOSAT', all in Johns Hopkins APL Technical Digest, Volume 8, Number 2 (1987). - Auxiliary Information - Launch Date and Time : 1985-03-12 Epoch Date and Time : Apogee (km or AU): 814. Perigee (km or AU): 757. Inclination (degree) : 108.1 Orbit Type : Information last updated on 1992-05-20 Group: Platform_Details Entry_ID: GEOSAT Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: GEOSAT Short_Name: GEOSAT Long_Name: Geodetic Satellite End_Group Group: Synonymous_Platform_Names Short_Name: GEOSAT End_Group Group: Platform_Associated_Instruments Short_Name: RADAR ALTIMETERS End_Group Group: Orbit Repeat_Cycle: 17 DAYS End_Group Creation_Date: 2007-09-26 Online_Resource: http://msl.jpl.nasa.gov/QuickLooks/geosatQL.html Online_Resource: http://leonardo.jpl.nasa.gov/msl/QuickLooks/geosatQL.html Online_Resource: http://nasascience.nasa.gov/missions/geosat Sample_Image: http://msl.jpl.nasa.gov/QuickLooks/pictures/geosat.gif Group: Platform_Logistics Launch_Date: 1985-03-13 Primary_Sponsor: USA/NASA Primary_Sponsor: United State Department of Defense End_Group End_Group Swarm-A Swarm is the fifth Earth Explorer mission approved in ESA's Living Planet Programme, and was successfully launched on 22 November 2013. As part of the Third Party Missions programme, the e-POP instrument of the Canadian Space Agency's CASSIOPE mission joined the constellation in February 2018. The research objectives of the Swarm mission is to provide the best-ever survey of the geomagnetic field and its temporal evolution as well as the electric field in the atmosphere using a constellation of 3 identical satellites carrying sophisticated magnetometers and electric field instruments. 2019-02-22 21:37:56.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: 5e95a04f-e746-4b55-b0f0-76631bb197fe relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: e5fde4c4-15cd-4278-b922-005488df096f relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 2380ecc6-b5ae-4ad8-a56a-9740166465aa relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 03d748ff-7398-4ea8-87e7-38d0ef3e6167 relationship type: null relationship value: null generated by: null); 2019-02-22 21:33:34.0 [mmorahan] insert Definition (id: null text: Swarm is the fifth Earth Explorer mission approved in ESA's Living Planet Programme, and was successfully launched on 22 November 2013. As part of the Third Party Missions programme, the e-POP instrument of the Canadian Space Agency's CASSIOPE mission joined the constellation in February 2018. The research objectives of the Swarm mission is to provide the best-ever survey of the geomagnetic field and its temporal evolution as well as the electric field in the atmosphere using a constellation of 3 identical satellites carrying sophisticated magnetometers and electric field instruments. language code: en); insert Resource (id: null type: image url: https://earth.esa.int/documents/10174/121731/swarm_constellation_120/5af5f840-f588-4537-a3e1-255391d50516?t=1331027602371); insert WeightedRelation (id: null related concept uuid: b7bc737c-15de-4b67-9bc3-5fa7c2b651d5 relationship type: null relationship value: null generated by: null); 2018-06-13 12:05:50.0 [mmorahan] Insert Concept add broader relation (Swarm-A [054787a6-0c47-43af-a4ee-05c572dd1705,367699] - Swarm [1d6d5f82-acd5-4bd2-9324-12884718b353,367695]); BEIJING-1 SSTL has developed the BEIJING-1 microsatellite bus for the Beijing Landview Mapping Information Technology Ltd (BLMIT). The BEIJING-1 enhanced microsatellite is an Earth observation spacecraft that combines SSTLs standard Disaster Monitoring Constellation (DMC) multispectral camera with a high resolution panchromatic imager. The customised microsatellite has specific enhancements to provide accommodation for the two imagers: a 32m multispectral imager currently flown on AlSAT-1, UK-DMC and NigeriaSat-1, plus a new 4m panchromatic imager developed under contract to SIRA Electro-Optics Ltd. The satellite bus provides highly agile attitude control to provide accurate pointing and the knowledge necessary for the mapping requirements of the mission. BEIJING-1 is supported by SSTL S-band telemetry, telecommand and an 8Mbps data retrieval ground station and is further supported by a customer furnished X-band data retrieval ground station and reflector subsystem. The Satellite was Launched on October 27th 2005 following a 24-month spacecraft development programme and is presently undergoing in orbit commissioning. Group: Platform_Details Entry_ID: BEIJING-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: BEIJING-1 End_Group Group: Synonymous_Platform_Names Short_Name: Tsinghua-1 Short_Name: China DMC+4 End_Group Group: Platform_Associated_Instruments Short_Name: BJ-1 PAN Short_Name: BJ-1 MSI End_Group Group: Orbit Orbit_Altitude: 686 km Orbit_Inclination: 98.1 degrees Equator_Crossing: 10:15 Period: 98.6 min Perigee: 683 km Apogee: 703 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2008-06-02 Online_Resource: http://eo.belspo.be/Directory/SatelliteDetail.aspx?satId=22 Online_Resource: http://www.sstl.co.uk/Missions/Beijing-1--Launched-2005/Beijing-1/Beijing-1--The-Mission Group: Platform_Logistics Launch_Date: 2005-10-27 Launch_Site: Plesetsk Cosmodrome, Russia Primary_Sponsor: China Primary_Sponsor: SSTL End_Group End_Group 2019-02-11 20:55:51.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: 6a3c8a54-48ae-4357-8bbc-bd2c48ede3a7 relationship type: null relationship value: null generated by: null); CBERS-3 [Summary provided by the Brazil National Institute for Space Research (INPE), http://www.cbers.inpe.br/en/programas/cbers3-4.htm ] Due to the success of CBERS-1 and 2, the two governments decided, in November 2002, to give continuity to the CBERS program by signing a new agreement for the development and launch of two more satellites, CBERS-3 and 4. Brazilian participation in this program will be enlarged up to 50%, thus taking Brazil to a condition of equality with its partner. CBERS-3 is expected to be launched in 2009, CBERS-4 in 2011. CBERS-3 and 4 satellites represent an evolution of CBERS-1 and 2. Four cameras will be present in the payload module, with improved geometrical and radiometric performance. They are: PanMux Camera-PANMUX, Multi-spectral Camera-MUXCAM, Scanning Medium Resolution Scanner-IRSCAM and Wide Field Imaging Camera-WFICAM. The orbits of the two satellites will be the same as for CBERS-1 and 2. Group: Platform_Details Entry_ID: CBERS-3 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: CBERS (China-Brazil Earth Resources Satellite) Short_Name: CBERS-3 Long_Name: China-Brazil Earth Resource Satellite 3 End_Group Group: Platform_Associated_Instruments Short_Name: IRS (CBERS) Short_Name: WFI (CBERS 3,4) Short_Name: PANMUX Short_Name: MUXCAM End_Group Group: Orbit Orbit_Altitude: 778 km Orbit_Inclination: 98.5 degrees Repeat_Cycle: 26 days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2008-08-19 Online_Resource: http://www.cbers.inpe.br/en/programas/cbers3-4.htm Sample_Image: http://space.skyrocket.de/img_sat/cbers-3__1.jpg Group: Platform_Logistics Launch_Date: 2009-01-01 Launch_Site: Taiyuan Space Launch Center, China Primary_Sponsor: Brazil National Institute for Space Research (INPE) Primary_Sponsor: China National Space Administration End_Group End_Group DMSP 5D-2/F15 DMSP 5D-1/F3 [Source: National Space Science Data Center, http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1978-042A ] DMSD 5D-1/F3 was one of a series of meteorological satellites developed and operated by the Air Force under the Defense Meteorological Satellite Program (DMSP). This program, previously known as DAPP (Data Acquisition and Processing Program), was classified until March 1973. The objectives of this program were to provide global visual and infrared cloudcover data and specialized environmental data to support Department of Defense requirements. Operationally, the program consisted of two satellites in sun-synchronous polar orbits, with the ascending node of one satellite in early morning and the other at local noon. The 5.4-m-long spacecraft was separated into four sections: (1) a precision mounting platform (PMP) for sensors and equipment requiring precise alignment; (2) an equipment support module (ESM) containing the electronics, reaction wheels, and some meteorological sensors; (3) a reaction control equipment (RCE) support structure (including the third-stage motor and hydrazine reaction control system); and (4) a 9.29-sq-m solar cell panel. The spacecraft stabilization was controlled by a combination flywheel and magnetic control coil system so sensors could be maintained in the desired "earth-looking" mode. One feature was the precision-pointing accuracy of the primary imager to 0.01 deg provided by a star sensor and an updated ephemeris navigation system. This allowed automatic geographical mapping of the digital imagery to the nearest picture element. The operational linescan system (OLS), built by Westinghouse, was the primary data acquisition system that provided real-time or stored, multi-orbit, day-and-night visual and infrared imagery of clouds, and provided with the data calibration, timing, and other auxiliary signals to the spacecraft for digital transmission to the ground. A supplementary meterological sensor, the special sensor H (SSH), a step-scanning radiometer, was the infrared temperature-humidity-ozone sounder. Either recorded or real-time data were transmitted to ground-receiving sites by two redundant S-band transmitters. Recorded data were read out to tracking sites located at Fairchild AFB, Wash., and Loring AFB, Maine, and relayed by SATCOM to Air Force Global Weather Central, Offutt AFB, Nebraska. Real-time data were read out at mobile tactical sites located around the world. A more complete description of the satellite can be found in the report, D. A. Nichols, "The Defense Meteorological Satellite Program," Optical Engineering, v. 14, n. 4, July-August 1975. Group: Platform_Details Entry_ID: DMSP 5D-1/F3 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: DMSP (Defense Meteorological Satellite Program) Short_Name: DMSP 5D-1/F3 Long_Name: Defense Meteorological Satellite Program-F3 End_Group Group: Synonymous_Platform_Names Short_Name: DMSP 14537 Short_Name: DMSP-F3 Short_Name: 10820 End_Group Group: Platform_Associated_Instruments Short_Name: GAMMA RAY DETECTOR (SSB) Short_Name: PES (SSJ/3) Short_Name: MFR/SSH Short_Name: OLS End_Group Group: Orbit Orbit_Inclination: 97.6° Period: 96.89 minutes Perigee: 564.0 km Apogee: 653.0 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Online_Resource: http://www.ngdc.noaa.gov/dmsp/index.html Online_Resource: http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/dmsp.html Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1978-042A Group: Platform_Logistics Launch_Date: 1978-05-01 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: Department of Defense-Department of the Air Force (United States) End_Group End_Group HELICOPTER An aircraft that derives its lift from blades that rotate about an approximately vertical central axis. [Source: The American Heritage? Dictionary of the English Language, Fourth Edition Copyright ? 2000 by Houghton Mifflin Company.] FDSN The Federation of Digital Broad-Band Seismograph Networks (FDSN) is a global organization. Its membership is comprised of groups responsible for the installation and maintenance of broad-band seismographs either within their geographic borders or globally. Membership in the FDSN is open to all organizations that operate more than one broadband station. Members agree to coordinate station siting and provide free and open access to their data. This cooperation helps scientists all over the world to further the advancement of earth science and particularly the study of global seismic activity. The FDSN goals related to station siting and instrumentation are to provide stations with good geographic distribution, recording data with 24 bits of resolution in continuous time series with at least a 20 sample per second sampling rate. The FDSN was also instrumental in development of a universal standard for distribution of broadband waveform data and related parametric information. The Standard for Exchange of Earthquake DATA (SEED) format is the result of that effort. View the Seismic Monitor at "http://www.iris.edu/seismon/" [Source: IRIS Consortium] Group: Platform_Details Entry_ID: FDSN Group: Platform_Identification Platform_Category: In Situ Land-based Platforms Platform_Series_or_Entity: GEOPHYSICAL STATIONS/NETWORKS Short_Name: FDSN Long_Name: Federation of Digital Seismographic Networks End_Group Group: Synonymous_Platform_Names Short_Name: FDSN End_Group Creation_Date: 2007-12-05 Online_Resource: http://www.iris.edu/seismon/ Sample_Image: http://www.fdsn.org/FDSNmeetings/2002/A17-DMS_files/image020.gif End_Group Environmental Modeling 2015-06-04 14:32:09.0 [aaleman] Insert Concept add narrower relation (Environmental Modeling [079610fb-e4cf-4e2c-9a92-86a9b798a7d5,157997] - Soil Characteristics [252a24e5-6f62-40df-86b3-59ef0d38283f,158001]); 2015-06-04 14:31:33.0 [aaleman] Insert Concept add broader relation (Environmental Modeling [079610fb-e4cf-4e2c-9a92-86a9b798a7d5,157997] - Data Analysis [73c1df3f-b389-4cc0-98eb-0fbc4f071f98,157993]); METEOSAT-9 2013-12-13 20:30:41.0 [saritz] Insert Concept add broader relation (METEOSAT-9 [07dfead6-2cbc-4703-8533-c4d07e2ec67c,106029] - METEOSAT [28eac19a-5500-4a21-af30-ab7a364ff8d0,73589]); ORBITER ALOUETTE-2 Alouette-2 was a small space based ionospheric observatory instrumented with a sweep-frequency ionospheric sounder (radio transmitter), a VLF radio receiver, an energetic particle detector experiment, a cosmic radio noise experiment, and an electrostatic plasma probe. EXTERIOR ANTENNAS: The spacecraft used two long dipole antennas (73 meter and 22.8 meter, respectively) for the sounder, VLF, and radio cosmic noise experiments. SPACECRAFT ROTATION (SPIN): The satellite was spin-stabilized at about 2.25 rpm after antenna deployment. End plates on the 73 meter antenna corrected the rapid despin that had occurred on the predecessor spacecraft, Alouette 1, and which was believed to result from thermal distortion of the antenna and from radiation pressure. DATA ACQUISITION: There was no onboard tape recorder, so that data were available to the ground receiving station only when the spacecraft was in direct line of sight of telemetry stations. Telemetry stations were located so that primary data coverage was near the 80 degrees West meridan plus areas near Hawaii, Singapore, Australia, England, India, Norway and Central Africa. Initially data were recorded about 8 hours per day. Degradation of the power supply system had, by June 1975, reduced the operating time to about 1/2 hour per day. Routine operations were terminated in July 1975. The spacecraft was also successfully reactivated on November 28 and 29, 1975, in order to obtain data on its 10th anniversary. Group: Platform_Details Entry_ID: ALOUETTE-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: ALOUETTE Short_Name: ALOUETTE-2 End_Group Group: Synonymous_Platform_Names Short_Name: ALOUETTE-B Short_Name: 01804 End_Group Group: Platform_Associated_Instruments Short_Name: STEP FREQUENCY RADIOMETERS Short_Name: ELECTROSTATIC ANALYZERS End_Group Creation_Date: 2007-08-22 Online_Resource: http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1965-098A Group: Platform_Logistics Launch_Date: 1965-11-29 Primary_Sponsor: NASA End_Group End_Group NLDN NATIONAL LIGHTNING DETECTION NETWORK Vaisala's U.S. National Lightning Detection Network (NLDN) is the most scientifically accurate and reliable lightning information system, monitoring cloud-to-ground lightning activity across the continental United States, 24 hours a day, 365 days a year. NLDN information includes date and time, location, cloud type, polarity, peak amplitude, and error ellipse. Also, NLDN can deliver information in real-time or near real-time. Group: Platform_Details Entry_ID: NLDN Group: Platform_Identification Platform_Category: In Situ Land-based Platforms Platform_Series_or_Entity: WEATHER STATIONS/NETWORKS Short_Name: NLDN Long_Name: National Lightning Detection Network End_Group Creation_Date: 2011-12-15 Online_Resource: http://www.vaisala.com/en/products/thunderstormandlightningdetectionsystems/Pages/NLDN.aspx End_Group 2016-06-09 18:54:47.0 [epneff] added altLabel insert AltLabel (id: null text: NATIONAL LIGHTNING DETECTION NETWORK language code: en); SPOT-5 [Text Source: NASA/NSSDC, http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=2002-021A ] Spot 5 is a French (CNES), Earth-imaging, three tonne satellite that was launched by an Ariane 42P rocket from Kourou at 00:31:00 UT on 4 May 2002. Its planar and stereoscopic relief images at about three meter resolution will be marketed for civilian and military uses, for cartographic and vegetation analyses. Panchromatic (at 2.5 m resolution) as well as multispectral images (at 10 m resolution) could be obtained. The position of the satellite, and hence the location of the images could be determined at 15 m accuracy by means of the DORIS position determination instrument. Extensive information on the instruments and data products is available via http://www.spotimage.com/ Group: Platform_Details Entry_ID: SPOT-5 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: SPOT Short_Name: SPOT-5 Long_Name: Systeme Probatoire Pour l'Observation de la Terre-5 End_Group Group: Synonymous_Platform_Names Short_Name: SPOT-5 End_Group Group: Platform_Associated_Instruments Short_Name: DORIS Short_Name: VEGETATION-2 Short_Name: HRS Short_Name: HRG-2 Short_Name: HRG-1 End_Group Group: Orbit Orbit_Altitude: 822 km Orbit_Inclination: 98.8° Equator_Crossing: 10:30 AM (descending node) Period: 101.4 minutes Repeat_Cycle: 2-3 days, depending on latitude Perigee: 825.0 km Apogee: 826.0 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-11-14 Online_Resource: http://smsc.cnes.fr/SPOT/index.htm Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=2002-021A Online_Resource: http://www.spot.com/ Online_Resource: http://www.satimagingcorp.com/satellite-sensors/spot-5.html Sample_Image: http://smsc.cnes.fr/IcSPOT/spot5.jpg Group: Platform_Logistics Launch_Date: 2002-05-04 Launch_Site: Kourou, French Guiana Primary_Sponsor: France/CNES End_Group End_Group MERRA-2 2015-06-22 19:09:40.0 [saritz] insert AltLabel (id: null text: The second Modern-Era Retrospective analysis for Research and Applications language code: en); 2015-06-22 19:09:06.0 [saritz] Insert Concept add broader relation (MERRA-2 [09294834-bc5d-4937-ba1a-3a62b4329948,158051] - Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215]); Catchment-LSM 2014-07-30 01:28:06.0 [saritz] insert AltLabel (id: null text: Catchment Land Surface Model language code: en); 2014-07-30 01:27:32.0 [saritz] Insert Concept add broader relation (Catchment-LSM [09ef7548-5e64-4296-8129-0ab625e15721,106525] - Models [113ecbc2-ab36-4d58-a96c-a6ce0106e749,73395]); SOYUZ SPOT 4 is the fourth member of the SPOT family. SPOT 4 was placed in orbit on March 24 1998 on an Ariane launcher. Designed and developed by the French space agency CNES (Centre National d'Études Spatiales), the SPOT system is the world leader in civil earth observation. The SPOT system comprises three satellites (SPOT 1, SPOT 2 and SPOT 4), an orbit and mission control ground segment, a global network of receiving and processing stations, and an international product distribution and marketing network. Specifications on SPOT 4 Prime contractor: Matra Marconi Space Platform: Spot Mk 2 Mass at launch: 2755 kg Dry mass: 2600 kg Payload mass: 1390 kg Dimension: 2.5 x 2.5 x 5.35 m Solar array: 4 x 8 m Stabilization: 3-axis DC power: EOL (2200 W) Design lifetime: 5 years Additional inforamtion avaialble at "http://spot4.cnes.fr/" [Summary provided by CNES] ECHO ICESat-2 [Text Source: NASA ICESat-2, https://icesat-2.gsfc.nasa.gov/ ] ICESat-2 will provide scientists with height measurements that create a global portrait of Earth’s 3rd dimension, gathering data that can precisely track changes of terrain including glaciers, sea ice, forests and more. While many of ICESat-2’s discoveries are yet to be imagined, the satellite mission has four science objectives: Measure melting ice sheets and investigate how this effects sea level rise, Measure and investigate changes in the mass of ice sheets and glaciers, Estimate and study sea ice thickness, Measure the height of vegetation in forests and other ecosystems worldwide. Group: Platform_Details Entry_ID: ICESAT-II Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NASA Decadal Survey Short_Name: ICESAT-II Long_Name: Ice, Cloud and Land Elevation Satellite-II End_Group Creation_Date: 2009-02-25 Online_Resource: https://icesat-2.gsfc.nasa.gov/ Group: Platform_Logistics Launch_Date: 2018 Primary_Sponsor: USA/NASA End_Group End_Group 2020-01-03 23:48:27.0 [sritz] update Definition ([Text Source: NASA ICESat-2, https://icesat-2.gsfc.nasa.gov/ ] ICESat-2 will provide scientists with height measurements that create a global portrait of Earth’s 3rd dimension, gathering data that can precisely track changes of terrain including glaciers, sea ice, forests and more. While many of ICESat-2’s discoveries are yet to be imagined, the satellite mission has four science objectives: Measure melting ice sheets and investigate how this effects sea level rise, Measure and investigate changes in the mass of ice sheets and glaciers, Estimate and study sea ice thickness, Measure the height of vegetation in forests and other ecosystems worldwide. Group: Platform_Details Entry_ID: ICESAT-II Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NASA Decadal Survey Short_Name: ICESAT-II Long_Name: Ice, Cloud and Land Elevation Satellite-II End_Group Creation_Date: 2009-02-25 Online_Resource: https://icesat-2.gsfc.nasa.gov/ Group: Platform_Logistics Launch_Date: 2018 Primary_Sponsor: USA/NASA End_Group End_Group); update Definition (NASA ICESat-2, https://icesat-2.gsfc.nasa.gov/); 2018-04-24 20:41:37.0 [sritz] update Definition ([Text Source: NASA Science Mission Directorate, https://icesat-2.gsfc.nasa.gov/mission ] The Ice, Cloud, and Land Elevation Satellite-2, or ICESat-2, will measure the height of a changing Earth, one laser pulse at a time, 10,000 laser pulses a second. Slated for launch in 2018, ICESat-2 will carry a photon-counting laser altimeter that will allow scientists to measure the elevation of ice sheets, glaciers, sea ice and more - all in unprecedented detail. Our planet's frozen and icy areas, called the cryosphere, are a key focus of NASA's Earth science research. ICESat-2 will help scientists investigate why, and how much, our cryosphere is changing in a warming climate. The satellite will also measure heights across Earth's temperate and tropical regions, and take stock of the vegetation in forests worldwide. Group: Platform_Details Entry_ID: ICESAT-II Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NASA Decadal Survey Short_Name: ICESAT-II Long_Name: Ice, Cloud and Land Elevation Satellite-II End_Group Creation_Date: 2009-02-25 Online_Resource: https://icesat-2.gsfc.nasa.gov/mission Group: Platform_Logistics Launch_Date: 2018 Primary_Sponsor: USA/NASA End_Group End_Group); 2018-04-24 20:40:02.0 [sritz] update PrefLabel (ICESat-2); 2018-03-05 15:02:08.0 [sritz] update Definition ([Text Source: NASA Science Mission Directorate, https://icesat-2.gsfc.nasa.gov/mission ] The Ice, Cloud, and Land Elevation Satellite-2, or ICESat-2, will measure the height of a changing Earth, one laser pulse at a time, 10,000 laser pulses a second. Slated for launch in 2018, ICESat-2 will carry a photon-counting laser altimeter that will allow scientists to measure the elevation of ice sheets, glaciers, sea ice and more - all in unprecedented detail. Our planet's frozen and icy areas, called the cryosphere, are a key focus of NASA's Earth science research. ICESat-2 will help scientists investigate why, and how much, our cryosphere is changing in a warming climate. The satellite will also measure heights across Earth's temperate and tropical regions, and take stock of the vegetation in forests worldwide. Group: Platform_Details Entry_ID: ICESAT-II Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NASA Decadal Survey Short_Name: ICESAT-II Long_Name: Ice, Cloud and Land Elevation Satellite-II End_Group Creation_Date: 2009-02-25 Online_Resource: https://icesat-2.gsfc.nasa.gov/mission Online_Resource: https://decadal.gsfc.nasa.gov/icesat2.html Group: Platform_Logistics Launch_Date: 2018 Primary_Sponsor: USA/NASA End_Group End_Group); 2016-08-10 17:31:16.0 [aaleman] update to short name and long name requested by data provider update AltLabel (Ice, Cloud, and land Elevation Satellite-2); update PrefLabel (ICESAT-2); WIND WIND was launched on November 1, 1994 and is the first of two NASA spacecraft in the Global Geospace Science initiative and part of the ISTP Project. WIND was positioned in a sunward, multiple double-lunar swingby orbit with a maximum apogee of 250Re during the first two years of operation. This was followed by a halo orbit at the Earth-Sun L1 point. The science objectives of the WIND mission are: - Provide conplete plasma, energetic particle, and magnetic field input for magnetospheric and ionospheric studies. - Determine the magnetospheric output to interplanetary space in the up-stream region - Investigate basic plasma processes occuring in the near-Earth solar wind - Provide baseline ecliptic plane observations to be used in heliospheric latitudes from ULYSSES. WIND carries the following instruments: Radio and Plasma Wave experiment (WAVES) Energetic Particle Acceleration, Composition, and Transport (EPACT) Solar Wind Experiment (SWE) Solar Wind and Suprathermal Ion Composition Studies (SWICS/MASS/STICS) Magnetic Fields Investigation (MFI) 3-D Plasma and Energetic Particle Analyzer (3DP) Transient Gamma-Ray Spectrometer (TGRS) Gamma Ray Burst Studies (KONUS) For more information, see: http://pwg.gsfc.nasa.gov/wind.shtml and http://ssed.gsfc.nasa.gov/waves/ Group: Platform_Details Entry_ID: WIND Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Short_Name: WIND End_Group Group: Synonymous_Platform_Names Short_Name: GGS/Wind Short_Name: ISTP/Wind Short_Name: Wind/GGS Short_Name: Wind/ISTP Short_Name: 23333 Short_Name: 1994-071A End_Group Group: Platform_Associated_Instruments Short_Name: SWIMS Short_Name: KONUS Short_Name: TGRS Short_Name: 3DP Short_Name: MFI Short_Name: SMS Short_Name: SWE Short_Name: EPACT Short_Name: WAVES End_Group Group: Orbit Perigee: 235 ER Apogee: 265 ER Orbit_Type: LPO > L1 > Lissajous Orbit > Halo Orbit End_Group Online_Resource: http://ssed.gsfc.nasa.gov/waves/ Sample_Image: http://nssdc.gsfc.nasa.gov/image/spacecraft/wind.jpg Group: Platform_Logistics Launch_Date: 1994-11-01 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: NASA End_Group End_Group COSMOS Nimbus-7 The Nimbus 7 research-and-development satellite served as a stabilized, earth-oriented platform for the testing of advanced systems for sensing and collecting data in the pollution, oceanographic and meteorological disciplines. The polar-orbiting spacecraft consisted of three major structures: (1) a hollow torus-shaped sensor mount, (2) solar paddles, and (3) a control housing unit that was connected to the sensor mount by a tripod truss structure. Configured somewhat like an ocean buoy, Nimbus-7 was nearly 3.04 m tall, 1.52 m in diameter at the base, and about 3.96 m wide with solar paddles extended. The sensor mount that formed the satellite base housed the electronics equipment and battery modules. The lower surface of the torus provided mounting space for sensors and antennas. A box-beam structure mounted within the center of the torus provided support for the larger sensor experiments. Mounted on the control housing unit, which was located on top of the spacecraft, were sun sensors, horizon scanners, and a command antenna. The spacecraft spin axis was pointed at the earth. An advanced attitude-control system permitted the spacecraft's orientation to be controlled to within plus or minus 1 deg in all three axes (pitch, roll, and yaw). Eight experiments were selected: (1) Limb Infrared Monitoring of the Stratosphere (LIMS), (2) Stratospheric And Mesopheric Sounder (SAMS), (3) Coastal-Zone Color Scanner (CZCS), (4) Stratospheric Aerosol Measurement II (SAM II), (5) Earth Radiation Budget (ERB), (6) Scanning Multichannel Microwave Radiometer (SMMR), (7) Solar Backscatter UV and Total Ozone Mapping Spectrometer (SBUV/TOMS), and (8) Temperature-Humidity Infrared Radiometer (THIR). These sensors were capable of observing several parameters at and below the mesospheric levels. The Nimbus-7 spacecraft was turned off in 1994 after 16 years of service. Group: Platform_Details Entry_ID: NIMBUS-7 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NIMBUS Short_Name: NIMBUS-7 End_Group Group: Synonymous_Platform_Names Short_Name: Nimbus-G End_Group Group: Platform_Associated_Instruments Short_Name: CZCS Short_Name: TOMS Short_Name: SBUV Short_Name: LIMS Short_Name: THIR Short_Name: SAMS Short_Name: SMMR Short_Name: ERB End_Group Group: Orbit Orbit_Altitude: 955 km Orbit_Inclination: 99.1 degree Equator_Crossing: 12:00 PM for ascending and 12:00 AM for descending Period: 104.15 min. Repeat_Cycle: 6 days End_Group Creation_Date: 2007-10-17 Online_Resource: http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1978-098A Online_Resource: http://nasascience.nasa.gov/missions/nimbus Sample_Image: http://toms.gsfc.nasa.gov/n7toms/images/n7c100small.gif Group: Platform_Logistics Launch_Date: 1978-10-24 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: USA/NASA End_Group End_Group 2015-05-12 16:55:17.0 [saritz] update PrefLabel (Nimbus-7); AGBFM The Advanced Ground Based Field Mill (AGBFM) network consists of 34 field mills of which, as of May 29, 1997, only 31 are presently working. These data are used in real time detecting the electrostatic field strength overhead the instrument using stainless steel plates, which are alternatively shielded and exposed to the existing atmospheric electric field by a grounded rotor. 2017-09-11 17:55:39.0 [tstevens] insert AltLabel (id: null category: primary text: Advanced Ground Based Field Mill language code: en); insert Definition (id: null text: The Advanced Ground Based Field Mill (AGBFM) network consists of 34 field mills of which, as of May 29, 1997, only 31 are presently working. These data are used in real time detecting the electrostatic field strength overhead the instrument using stainless steel plates, which are alternatively shielded and exposed to the existing atmospheric electric field by a grounded rotor. language code: en); 2017-09-11 17:54:55.0 [tstevens] Insert Concept add broader relation (AGBFM [0b011fe7-4a05-4e04-92f6-fa23b9e85e1a,310155] - WEATHER STATIONS/NETWORKS [57b7373d-5c21-4abb-8097-a410adc2a074,287833]); IRS-1C The fourth in the IRS series, IRS - 1C was launched from Baikanur cosmodrome, Kazakhstan on May 19, 1995. It operates in a near polar, sun- synchronous orbit at an altitude of 817km. Its local equatorial crossing time is 10:30 A.M in the descending node. The satellite payload consists of three sensors, namely Panchromatic camera (PAN), Linear Imaging and Self-Scanning Sensor (LISS - III) and Wide Field Sensor (WiFS). The PAN camera provides data with a spatial resolution of 5.8m and a ground swath of 70 km at nadir view. This camera can be steered up to +/- 26 degrees, which can be used to acquire stereo pairs and this also improves the revisit capability to 5 days. LISS - III camera provides multi-spectral data in 4 bands. The spatial resolution for visible (two bands) and near infrared (one band) is 23.5m with a ground swath of 141 km. The fourth band (short wave infrared band) has a spatial resolution of 70.5m with a ground swath of 148 km. The repetivity of LISS - III is 24 days. WiFS camera collects data in two spectral bands with a spatial resolution of 188m and a ground swath of 810 km. By virtue of its wide swath there is huge side lap between adjacent paths. A repetivity of 3 days can be achieved by suitably combining paths. The satellite is equipped with an On Board Tape Recorder (OBTR) with a capacity of 62 Gb, for collecting data outside the visibility region of any ground station. The OBTR was capable of storing data collected for 24 minutes. The OBTR was functional during 1995-1998. [Summary provided by the Indian Remote Sensing Agency.] Group: Platform_Details Entry_ID: IRS-1C Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: IRS (Indian Remote Sensing Satellite) Short_Name: IRS-1C Long_Name: Indian Remote Sensing Satellite-1C End_Group Group: Platform_Associated_Instruments Short_Name: PAN Short_Name: LISS-III Short_Name: WIFS End_Group Group: Orbit Orbit_Altitude: 817 km Orbit_Inclination: 98.69 deg Equator_Crossing: 10:30 A.M Period: 101.35 min Repeat_Cycle: 24 Days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2008-08-12 Online_Resource: http://www.isro.gov.in/satellites/irs-1c.aspx Sample_Image: http://www.isro.gov.in/satellites/images/irs1c_img.gif Group: Platform_Logistics Launch_Date: 1995-05-19 Launch_Site: Baikonur Cosmodrome, Tyuratam, Russia Primary_Sponsor: India End_Group End_Group CONVAIR CV-580 CV-580 CV580 While Convair (based in San Diego like the Classic Airliner Page) was quite successful with its piston powered CV-240/340/440 series of twins, it recognized as early as 1950 that turboprop engines offered some clear advantages over the "round engines". Instead of building a new plane, Convair decided that those very Convair-Liners could be re-engined instead. An experimental installation of Allison T56 engines into a CV-240 in 1950 was quite successful, but the first commercial conversion did not take place until 1954, and then with British Napier Elands. [Text provided by: http://www.calclassic.com/580.htm ] [Photo provided by: http://images3.jetphotos.net/ ] Group: Platform_Details Entry_ID: CONVAIR CV-580 Group: Platform_Identification Platform_Category: Aircraft Short_Name: CONVAIR CV-580 End_Group Creation_Date: 2008-07-14 Online_Resource: http://www.calclassic.com/580.htm Sample_Image: http://images3.jetphotos.net/img/2/4/6/2/79826_1215091264.jpg End_Group 2016-06-09 17:25:13.0 [epneff] added altLabel insert AltLabel (id: null text: CV-580 language code: en); insert AltLabel (id: null text: CV580 language code: en); WWLLN The World Wide Lightning Location Network (WWLLN) is a global, ground-based lightning sensor network operated by the University of Washington in Seattle. This network monitors and maps global lightning activity. 2017-09-11 17:49:21.0 [tstevens] insert AltLabel (id: null category: primary text: World Wide Lightning Location Network language code: en); insert Definition (id: null text: The World Wide Lightning Location Network (WWLLN) is a global, ground-based lightning sensor network operated by the University of Washington in Seattle. This network monitors and maps global lightning activity. language code: en); 2017-09-11 17:48:29.0 [tstevens] Insert Concept add broader relation (WWLLN [0b6bafa6-1cc4-47eb-9925-f72c6d6008fc,310147] - WEATHER STATIONS/NETWORKS [57b7373d-5c21-4abb-8097-a410adc2a074,287833]); ETALON-1 Etalon are a Russian family (Etalon-1, Etalon-2) of passive geodetic satellites dedicated to satellite laser ranging. Etalon-1 was the first geodynamic satellite launched by the former Soviet Union. The Etalon spacecraft were launched in 1989 in conjunction with a pair of GLObal'naya NAvigatisionnay Sputnikovaya Sistema (GLONASS) satellites. The mission objectives were to determine a high accuracy terrestrial reference frame and earth rotation parameters, to improve the gravity field, and to improve the gravitational constant. [Summary provided by NASA.] Group: Platform_Details Entry_ID: ETALON-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: ETALON Short_Name: ETALON-1 End_Group Group: Synonymous_Platform_Names Short_Name: ETALON-1 End_Group Group: Platform_Associated_Instruments Short_Name: RIS End_Group Group: Orbit Orbit_Inclination: 64.8 deg Period: 676 min Perigee: 19400 km Apogee: 19400 km Orbit_Type: HEO > Highly Elliptical Orbit End_Group Creation_Date: 2007-09-26 Online_Resource: http://ilrs.gsfc.nasa.gov/satellite_missions/list_of_satellites/eta1_general.html Sample_Image: http://ilrs.gsfc.nasa.gov/images/etalon.gif Group: Platform_Logistics Launch_Date: 1989-01-10 Primary_Sponsor: Russia End_Group End_Group ALOS ALOS (Advanced Land Observing Satellite) http://earth.esa.int/object/index.cfm?fobjectid=3738 http://www.jaxa.jp/projects/sat/alos/index_e.html ALOS is a Japanese Earth-Observation satellite, developed by JAXA. The objective of the mission is to provide the user community with data of sufficient resolution to be able to generate 1:25,000 scale maps. ALOS mission objectives as set by JAXA are to: - Develop digital elevation models (DEMs) and related geographic data products - Perform regional observation for 'sustainable development' (harmonization between Earth environment and development) - Conduct disaster monitoring around the world - Survey natural resources - Develop sensor and satellite technology for future Earth-observing satellites The mission includes optical and an active L-band microwave sensor payload whose high-resolution data may be used for environmental and hazard monitoring. ESA will provide the European/African node for data distribution. [Summary provided by JAXA] Group: Platform_Details Entry_ID: ALOS Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: ALOS Long_Name: Advanced Land Observing Satellite End_Group Group: Synonymous_Platform_Names Short_Name: ALOS End_Group Group: Platform_Associated_Instruments Short_Name: AVNIR-2 Short_Name: PALSAR Short_Name: PRISM End_Group Group: Orbit Orbit_Altitude: 691.65 km Orbit_Inclination: 98.16 deg Repeat_Cycle: 46 days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-11-14 Online_Resource: http://www.jaxa.jp/projects/sat/alos/index_e.html Sample_Image: http://www.eorc.jaxa.jp/ALOS/images/configuration.gif Group: Platform_Logistics Launch_Date: 2006-01-24 Launch_Site: Tanegashima Island, Japan Design_Life: 3-5 years Primary_Sponsor: JAPAN/JAXA End_Group End_Group 2016-06-09 14:28:36.0 [epneff] added altLabel insert AltLabel (id: null text: ALOS (Advanced Land Observing Satellite) language code: en); GMS-5 The Geostationary Meteorological Satellite series are spin-stabilized satellites. They have been developed to contribute to the improvement of Japan's meteorological services and the development of weather satellite technology. The satellites consist of a despun section which holds the earth-oriented antennas and a 100-rpm rotating spin section which contains the Visible and Infrared Spin Scan Radiometer (VISSR), electronic devices, etc. They have been used for the World Meteorological Organization's world Weather Watch Program which is sustained by five geostationary satellites. GMS-5 made its final observation at 00 UTC on 22 May 2003 and is temporarily replaced by the United States' geostationary meteorological satellite GOES-9. MTSAT-1R, the successor to GMS-5, will be launched in the early coming winter (January and February, 2004). Characteristics: Dimensions: Cylindrical, Diameter : 214.6cm Height: (before AKM separation) 444.1cm (after AKM separation) 353.9cm Weight: 747kg (at launch) 344kg (beginning of life) Attitude control: Spin-stabilized Design life: 5 years Reliability: More than 0.5 after 5 years (Specification) Launch Vehicle: H-II Launch site: Tanegashima Space Center, Kagoshima, Japan Launch date: Early 1995 Final Observation: 22 May 2003 Orbit: Geostationary orbit, 140deg. E. longitude Group: Platform_Details Entry_ID: GMS-5 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: GMS (Japan Geostationary Meteorological Satellite) Short_Name: GMS-5 Long_Name: Geostationary Meteorological Satellite-5 End_Group Group: Synonymous_Platform_Names Short_Name: GMS-5 End_Group Group: Platform_Associated_Instruments Short_Name: VISSR-GMS End_Group Group: Orbit Orbit_Altitude: 36,000 km Orbit_Type: GEO > Geosynchronous > Geostationary End_Group Creation_Date: 2007-10-01 Online_Resource: http://www.jaxa.jp/projects/sat/gms/index_e.html Online_Resource: http://psbcw1.nesdis.noaa.gov/terascan/home_basic/geosats_sensors_tables.html#GMS%20Sensor Group: Platform_Logistics Launch_Date: 1995-03-18 Launch_Site: Tanegashima Island, Japan Design_Life: 5 YEARS Primary_Sponsor: JAPAN/JAXA End_Group End_Group EXPLORER DMSP 5D-2/F11 DMSP-F11 [Source: National Space Science Data Center, http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1991-082A ] DMSP 5D-2/F11 is one of a series of meteorological satellites developed and operated by the Air Force under the Defense Meteorological Satellite Program (DMSP). This program, previously known as DAPP (Data Acquisition and Processing Program), was classified until March 1973. The objective of this program is to provide global visual and infrared cloudcover data and specialized environmental data to support Department of Defense operational weather analysis and forecasting requirements. Operationally, the program consists of two satellites in sun-synchronous polar orbits, with the ascending node of one satellite in early morning and the other at local noon. The 6.4-m-long spacecraft is separated into four sections: (1) a precision mounting platform for sensors and equipment requiring precise alignment; (2) an equipment support module containing the electronics, reaction wheels, and some meteorological sensors; (3) a reaction control equipment support structure containing the third-stage rocket motor and supporting the ascent phase reaction control equipment; and (4) a 9.29-sq-m solar cell panel. The spacecraft stabilization is controlled by a combination flywheel and magnetic control coil system so that sensors are maintained in the desired earth-looking mode. One feature is the precision-pointing accuracy of the primary imager to 0.01 deg provided by a star sensor and an updated ephemeris navigation system. This allows automatic geographical mapping of the digital imagery to the nearest picture element. The operational linescan system is the primary data acquisition system that provides real-time or stored, multi-orbit, day-and-night, visual and infrared imagery of clouds. A supplementary sensor package contains five special sensors: (1) a microwave temperature sounder, (2) an X-ray spectrometer, (3) an ionospheric/scintillation monitor, (4) a precipitating electron/ion spectrometer, and (5) a microwave imager. Either recorded or real-time data are transmitted to ground-receiving sites by two redundant S-band transmitters. Recorded data are read out to tracking sites located at Fairchild AFB, Washington, and at Loring AFB, Maine, and relayed by SATCOM to Air Force Global Weather Central, Offutt AFB, Nebraska. Real-time data are read out at mobile tactical sites located around the world. Additional information concerning this satellite can be found in the report by D. A. Nichols, "The Defense Meteorological Satellite Program," Optical Engineering, v. 14, n. 4, p. 273, July-August 1975. Group: Platform_Details Entry_ID: DMSP 5D-2/F11 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: DMSP (Defense Meteorological Satellite Program) Short_Name: DMSP 5D-2/F11 Long_Name: Defense Meteorological Satellite Program-F11 End_Group Group: Synonymous_Platform_Names Short_Name: DMSP-F11 Short_Name: USA 73 Short_Name: 21798 End_Group Group: Platform_Associated_Instruments Short_Name: OLS Short_Name: SSM/I Short_Name: SSJ/4 Short_Name: SSI/ES Short_Name: SSM/T Short_Name: SSB/X Short_Name: SSM/T-2 End_Group Group: Orbit Orbit_Inclination: 98.9° Period: 101.9 minutes Perigee: 846.0 km Apogee: 870.0 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1991-082A Online_Resource: http://www.ngdc.noaa.gov/dmsp/index.html Online_Resource: http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/dmsp.html Group: Platform_Logistics Launch_Date: 1991-11-28 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: Department of Defense-Department of the Air Force (United States) End_Group End_Group 2016-06-09 14:34:34.0 [epneff] added altLabel insert AltLabel (id: null text: DMSP-F11 language code: en); LANDSAT-4 LANDSAT-4 (LAND REMOTE-SENSING SATELLITE-4) Landsat 4 is the fourth satellite of the Landsat program. It was launched on July 16th, 1982, with the primary goal of providing a global archive of satellite photos. Although the Landsat Program is managed by NASA, data from Landsat 4 was collected and distributed by the USGS. Landsat 4 is no longer in operation, due to technical failure. It finally ceased transmission in 1993, far beyond its designed life expectancy of five years. The satellite orbit continues to be maintained by NASA. Landsat 4 had a maximum transmission bandwidth of 85 Mbit/s, and carried an updated Multi-Spectral Scanner used on previous Landsats, and a Thematic Mapper. It had a maximum 30 m resolution. Shortly after launch, the satellite lost half of its solar power, prompting fears the satellite would fail sooner than expected. This prompted the early launch of Landsat 5, a satellite identical in specification to Landsat 4. [Summary provided by NASA.] Group: Platform_Details Entry_ID: LANDSAT-4 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: LANDSAT Short_Name: LANDSAT-4 End_Group Group: Platform_Associated_Instruments Short_Name: MSS Short_Name: TM End_Group Group: Orbit Orbit_Altitude: 705 km Orbit_Inclination: 98.2 degree Equator_Crossing: 9:45 AM (&#177;15 min.) local time (descending node) Period: 99 minutes Repeat_Cycle: 16 days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-02-01 Online_Resource: https://landsat.gsfc.nasa.gov/landsat-4/ Online_Resource: https://www.usgs.gov/land-resources/nli/landsat/landsat-4 Group: Platform_Logistics Launch_Date: 1982-07-16 Launch_Site: Vandenberg Air Force Base, USA Design_Life: 5 Years Primary_Sponsor: NASA Primary_Sponsor: USGS End_Group End_Group 2019-12-31 21:25:25.0 [sritz] update Definition (Landsat 4 is the fourth satellite of the Landsat program. It was launched on July 16th, 1982, with the primary goal of providing a global archive of satellite photos. Although the Landsat Program is managed by NASA, data from Landsat 4 was collected and distributed by the USGS. Landsat 4 is no longer in operation, due to technical failure. It finally ceased transmission in 1993, far beyond its designed life expectancy of five years. The satellite orbit continues to be maintained by NASA. Landsat 4 had a maximum transmission bandwidth of 85 Mbit/s, and carried an updated Multi-Spectral Scanner used on previous Landsats, and a Thematic Mapper. It had a maximum 30 m resolution. Shortly after launch, the satellite lost half of its solar power, prompting fears the satellite would fail sooner than expected. This prompted the early launch of Landsat 5, a satellite identical in specification to Landsat 4. [Summary provided by NASA.] Group: Platform_Details Entry_ID: LANDSAT-4 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: LANDSAT Short_Name: LANDSAT-4 End_Group Group: Platform_Associated_Instruments Short_Name: MSS Short_Name: TM End_Group Group: Orbit Orbit_Altitude: 705 km Orbit_Inclination: 98.2 degree Equator_Crossing: 9:45 AM (&#177;15 min.) local time (descending node) Period: 99 minutes Repeat_Cycle: 16 days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-02-01 Online_Resource: https://landsat.gsfc.nasa.gov/landsat-4/ Online_Resource: https://www.usgs.gov/land-resources/nli/landsat/landsat-4 Group: Platform_Logistics Launch_Date: 1982-07-16 Launch_Site: Vandenberg Air Force Base, USA Design_Life: 5 Years Primary_Sponsor: NASA Primary_Sponsor: USGS End_Group End_Group); update Definition (https://landsat.gsfc.nasa.gov/landsat-4/); delete Resource (null); 2016-06-09 15:32:03.0 [epneff] added altLabel insert AltLabel (id: null text: LANDSAT-4 (LAND REMOTE-SENSING SATELLITE-4) language code: en); SENTINEL-6 Jason-CS/Sentinel-6 Michael Freilich The main purpose of the SENTINEL-6 mission will provide long-term continuity of the satellite altimetry measurement (sea surface height) from the TOPEX/POSEIDON, JASON-1, JASON-2, and JASON-3 missions and to extend the climate data record whilst improving measurement precision and accuracy. The SENTINEL-6 Mission Guide provides a high-level description of the mission objectives; satellite description, including payloads, orbit characteristics, coverage and data products. It also covers an introduction to heritage missions. The mission is being developed by a multi-agency partnership comprising ESA, EU, EUMETSAT, NASA-JPL, NOAA and CNES. ESA is responsible for the SENTINEL-6 (JASON-CS) space segment development with Airbus Space and Defence GmbH as a prime contractor. This Mision Guide provides imformation on the following areas: Overview This section gives a brief description of the spacecraft, including its payload, the heritage missions (TOPEX/POSEIDON and JASON missions), the main improvements compared to previous altimeters, the main thematic areas and services (e.g. ocean, land) and a summary of the complete mission details. It also provides information about the different agencies involved in the mission. Mission Objectives This section describes the primary and secondary objectives of the SENTINEL-6 mission. Satellite Orbit and geographical coverage This section describes orbit characteristics and the geographical coverage. Ground Segment This section describes the Sentinel Core Ground Segment and its main facilities. Instrumental Payload This section describes the main instruments of the SENTINEL-6 mission: Synthetic Aperture Radar Altimeter (POSEIDON-4), MicroWave Radiometer (AMR-C) and Precise Orbit Determination (POD) instruments (DORIS and GNSS-POD) and the secondary GNSS-RO for radio occultation instrument. Data Products This section defines all data products planned for the SENTINEL-6 mission. 2020-03-06 18:27:10.0 [mmorahan] insert AltLabel (id: null category: null text: Jason-CS/Sentinel-6 Michael Freilich language code: en); insert Definition (id: null text: The main purpose of the SENTINEL-6 mission will provide long-term continuity of the satellite altimetry measurement (sea surface height) from the TOPEX/POSEIDON, JASON-1, JASON-2, and JASON-3 missions and to extend the climate data record whilst improving measurement precision and accuracy. The SENTINEL-6 Mission Guide provides a high-level description of the mission objectives; satellite description, including payloads, orbit characteristics, coverage and data products. It also covers an introduction to heritage missions. The mission is being developed by a multi-agency partnership comprising ESA, EU, EUMETSAT, NASA-JPL, NOAA and CNES. ESA is responsible for the SENTINEL-6 (JASON-CS) space segment development with Airbus Space and Defence GmbH as a prime contractor. This Mision Guide provides imformation on the following areas: Overview This section gives a brief description of the spacecraft, including its payload, the heritage missions (TOPEX/POSEIDON and JASON missions), the main improvements compared to previous altimeters, the main thematic areas and services (e.g. ocean, land) and a summary of the complete mission details. It also provides information about the different agencies involved in the mission. Mission Objectives This section describes the primary and secondary objectives of the SENTINEL-6 mission. Satellite Orbit and geographical coverage This section describes orbit characteristics and the geographical coverage. Ground Segment This section describes the Sentinel Core Ground Segment and its main facilities. Instrumental Payload This section describes the main instruments of the SENTINEL-6 mission: Synthetic Aperture Radar Altimeter (POSEIDON-4), MicroWave Radiometer (AMR-C) and Precise Orbit Determination (POD) instruments (DORIS and GNSS-POD) and the secondary GNSS-RO for radio occultation instrument. Data Products This section defines all data products planned for the SENTINEL-6 mission. language code: en); 2020-03-06 18:24:43.0 [mmorahan] Insert Concept add broader relation (SENTINEL-6 [0df95c0e-77a5-46b5-94f4-3e5ae1391450,559847] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,541501]); AD-A AD-A Atmospheric Dynamics A (Explorer 19) Explorer 19 was the second in a series of 3.66-m inflatable spheres placed into orbit to determine atmospheric densities. Explorer 19 was launched while Explorer 9, the first satellite in the series, was still active, so that densities in two different portions of the atmosphere were sampled simultaneously. The satellite consisted of alternating layers of aluminum foil and plastic film. Uniformly distributed over the aluminum outer surface were 5.1-cm dots of white paint for thermal control. A 136.620-MHz tracking beacon, which was powered by four solar cells and was mounted on the spacecraft skin, used the electrically separated hemispheres of the balloon as an antenna. The spacecraft was successfully orbited, but its apogee was lower than planned. The beacon did not have sufficient power to be received by ground tracking stations, making it necessary to rely solely on the SAO Baker-Nunn camera network for tracking. Group: Platform_Details Entry_ID: AD-A Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: AD (Atmospheric Dynamics) Short_Name: AD-A Long_Name: Atmosphere Dynamics A (Explorer 19) End_Group Group: Synonymous_Platform_Names Short_Name: EXPLORER 19 End_Group Group: Platform_Associated_Instruments Short_Name: OPTICAL BEACON End_Group Group: Orbit Orbit_Inclination: 78.6 degrees Period: 115.9 min Perigee: 597 km Apogee: 2391 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-08-22 Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/masterCatalog.do?sc=1963-053A Group: Platform_Logistics Launch_Date: 1963-12-19 Primary_Sponsor: NASA End_Group End_Group PAM-II Portable Automated Mesonet II (PAM-II) stations was installed 10 meters to the west of the mobile laboratory (measuring trace gases) and consisted of a 10 meter tower with the required sensors, master control electronics box, and antenna to transmit station data to the satellite. The station, via the satellite data link, transmitted the data to NCAR in Boulder, Colorado, where the data were archived by the NCAR/SSSF DEC MicroVAX computer. [Source: NCAR] Group: Platform_Details Entry_ID: PAM-II Group: Platform_Identification Platform_Category: In Situ Land-based Platforms Platform_Series_or_Entity: MOBILE STATIONS/VEHICLES Short_Name: PAM-II Long_Name: Portable Automated Mesonet II End_Group Group: Synonymous_Platform_Names Short_Name: PAM II End_Group Creation_Date: 2007-12-10 Online_Resource: http://ams.allenpress.com/perlserv/?request=get-abstract&issn=1520-0426&volume=003&issue=04&page=0573 Sample_Image: http://www.eol.ucar.edu/dir_off/ASR/FY1996/images/ATDSSSF_pam_scms.jpg End_Group ISIS-1 - Spacecraft Brief Description - ISIS 1 was an ionospheric observatory instrumented with sweep- and fixed-frequency ionosondes, a VLF receiver, energetic and soft particle detectors, an ion mass spectrometer, an electrostatic probe, an electrostatic analyzer, a beacon transmitter, and a cosmic noise experiment. The sounder used two dipole antennas (73 and 18.7 m long). The satellite was spin-stabilized at about 2.9 rpm after antenna deployment. Some control was exercised over the spin rate and attitude by using magnetically induced torques to change the spin rate and to precess the spin axis. A tape recorder with 1-h capacity was included on the satellite. The satellite could be programmed to take recorded observations for four different time periods for each full recording period. The recorder data were dumped only at Ottawa. For non-tape-recorded observations, data for the satellite and subsatellite regions could be acquired and telemetered when the spacecraft was in the line of sight of telemetry stations. The selected telemetry stations were in areas that provided primary data coverage near the 80-deg-W meridian and in areas near Hawaii, Singapore, Australia, England, Norway, India, Japan, Antarctica, New Zealand, and Central Africa. NASA support of the ISIS project was terminated on October 1, 1979. A significant amount of experimental data, however, was acquired after this date by the Canadian project team. ISIS 1 operations were terminated in Canada on March 9, 1984. The Radio Research Laboratories (Tokyo, Japan) then requested and received permission to reactivate ISIS 1. Regular ISIS 1 operations were started from Kashima, Japan, in early August 1984. ISIS 1 was deactivated effective January 24, 1990. - Auxiliary Information - Launch Date and Time : 1969-01-30 06:43:00 Epoch Date and Time : 1969-02-04 Apogee (km or AU): 3526. Perigee (km or AU): 578. Inclination (degree) : 88.42 Orbit Type : Geocentric Information last updated on 1992-03-09 Group: Platform_Details Entry_ID: ISIS-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: ISIS (International Satellite for Ionospheric S Short_Name: ISIS-1 Long_Name: International Satellite for Ionospheric Studies-1 End_Group Group: Synonymous_Platform_Names Short_Name: ISIS-A End_Group Group: Platform_Associated_Instruments Short_Name: LASER SPECTROMETER Short_Name: VLF RECEIVERS End_Group Group: Orbit Orbit_Inclination: 88.4 Period: 128.4 min Perigee: 578 km Apogee: 3526 km End_Group Creation_Date: 2007-10-05 Online_Resource: http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1969-009A Sample_Image: http://www.space.gc.ca/asc/img/I-1_ISIS1-photo.jpg Group: Platform_Logistics Launch_Date: 1969-01-30 Primary_Sponsor: NASA End_Group End_Group NCEP-FNL 2015-08-10 18:56:18.0 [epneff] Added long name insert AltLabel (id: null text: NCEP Final Global Data Assimilation System language code: en); 2015-08-10 18:56:01.0 [epneff] Insert Concept add broader relation (NCEP-FNL [0ea8022d-e6bf-48e0-86ce-e1e7a886b7b1,158255] - Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215]); Pisces V The Pisces V is a three-person, battery-powered, submersible with an operating depth range of 2000 m. Along with its sister submersible, the Pisces IV, the Pisces V weighs 13 tons and has a payload of 200 pounds. The personnel sphere of each sub is 7 feet in diameter and is made of HY 100 steel. 2020-01-23 12:24:22.0 [tstevens] update Definition (The Pisces V is a three-person, battery-powered, submersible with an operating depth range of 2000 m. Along with its sister submersible, the Pisces IV, the Pisces V weighs 13 tons and has a payload of 200 pounds. The personnel sphere of each sub is 7 feet in diameter and is made of HY 100 steel.); update Definition (https://www.soest.hawaii.edu/soestwp/tech/watercraft/pisces-5/); 2020-01-21 20:00:28.0 [tstevens] insert Definition (id: null text: language code: en); 2020-01-21 17:35:39.0 [tstevens] Insert Concept add broader relation (Pisces V [0f50133b-1ef8-4c67-97a3-ac0604a41fc8,559791] - HOV [63c8aa1d-6efc-4943-8891-3a1cd520dde0,559759]); IRS-P2 Indian Remote Sensing (IRS) P2 was launched in 1994. This satellite carries one imaging sensor: Linear Imaging Self Scanner (LISS) 2. This satellite has a polar, circular, sun-synchronous 817-km orbit with a 24-day repeat cycle. Like the IRS-1A and -1B platforms, IRS-P2 has two identical LISS 2, but with a resolution of 32 m across-track and 37 m along-track. The total swath width on the IRS-P2 is 131 km. Group: Platform_Details Entry_ID: IRS-P2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: IRS (Indian Remote Sensing Satellite) Short_Name: IRS-P2 Long_Name: Indian Remote Sensing Satellite-P2 End_Group Group: Platform_Associated_Instruments Short_Name: LISS-II End_Group Group: Orbit Orbit_Inclination: 98.4 degrees Period: 101.2 min Perigee: 821.6 km Apogee: 822.9 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2008-09-10 Online_Resource: http://www.isro.gov.in/satellites/irs-p2.aspx Sample_Image: http://www.isro.gov.in/satellites/images/irsp2_img.gif Group: Platform_Logistics Launch_Date: 1994-10-15 Launch_Site: Sriharikota Island, India Primary_Sponsor: India End_Group End_Group C-131A The C-131 was a military transport version of the Convair-Liner 240 built by General Dynamics. It was the first pressurized, twin engine transport ordered by the Military Air Transport Service. The T-29 version of this aircraft filled the back of the plane with student stations and was used to train bombardiers, navigators and electronic warfare officers. [Text and Photo provided by: http://www.marchfield.org/c131d.htm ] Group: Platform_Details Entry_ID: C-131A Group: Platform_Identification Platform_Category: Aircraft Short_Name: C-131A Long_Name: Convair C-131 Samaritan End_Group Creation_Date: 2008-07-14 Online_Resource: http://aeroweb.brooklyn.cuny.edu/specs/convair/c-131a.htm Online_Resource: http://www.marchfield.org/c131d.htm Sample_Image: http://www.marchfield.org/c131z262.jpg End_Group RM-OBS/PU Hybrid of NCEP/NCAR Reanalysis Model and Observations by Princeton University 2018-10-15 18:35:47.0 [sritz] insert AltLabel (id: null category: primary text: Hybrid of NCEP/NCAR Reanalysis Model and Observations by Princeton University language code: en); insert Definition (id: null text: Hybrid of NCEP/NCAR Reanalysis Model and Observations by Princeton University language code: en); 2018-10-15 18:35:09.0 [sritz] Insert Concept add broader relation (RM-OBS/PU [0fb44090-a3e4-4820-aad5-dafbd76ae1b4,368179] - Merged Analysis [6acce314-322f-4d58-9dcb-1f93457a9d86,345119]); GEODYNAMIC STATIONS Stations that make geodynmaic observations about the Earth. JPSS-4 JPSS-4, scheduled to launch in 2031, is the fifth spacecraft within NOAA's next generation of polar-orbiting satellites. Similar to previous JPSS spacecrafts missions, JPSS-4 will host five instruments: (1) VIIRS, (2) CrIS, (3) ATMS, (4) OMPS-N, and (5) RBI. More Information: https://www.jpss.noaa.gov 2019-10-04 19:38:08.0 [sritz] update Definition (JPSS-4, scheduled to launch in 2031, is the fifth spacecraft within NOAA's next generation of polar-orbiting satellites. Similar to previous JPSS spacecrafts missions, JPSS-4 will host five instruments: (1) VIIRS, (2) CrIS, (3) ATMS, (4) OMPS-N, and (5) RBI. More Information: https://www.jpss.noaa.gov); update Definition (Source: NOAA JPSS, https://www.jpss.noaa.gov/mission_and_instruments.html); 2018-02-02 17:15:04.0 [sritz] update WeightedRelation (Platform-Instrument); update WeightedRelation (1); 2018-02-02 17:14:13.0 [sritz] insert WeightedRelation (id: null related concept uuid: de7e08db-86f1-4593-ba9e-288f9f7b063e relationship type: null relationship value: null generated by: null); 2018-01-30 22:35:38.0 [sritz] delete WeightedRelation (null); insert WeightedRelation (id: null related concept uuid: 91923fed-61c3-4125-b69d-1eeccafce52c relationship type: null relationship value: null generated by: null); 2018-01-30 22:29:14.0 [sritz] insert WeightedRelation (id: null related concept uuid: dd7c719e-5767-4ceb-b83a-66c1401dab4a relationship type: null relationship value: null generated by: null); 2018-01-30 22:17:14.0 [sritz] insert WeightedRelation (id: null related concept uuid: 5ad54972-6d91-4860-aea4-7914fe7ef823 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 9a68e783-b54c-41f2-82ce-da975af38359 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 6af7a52e-094d-4ba7-9174-ed967260939c relationship type: null relationship value: null generated by: null); 2016-07-19 19:16:57.0 [saritz] update WeightedRelation (Similar); update WeightedRelation (1); update WeightedRelation (Similar); update WeightedRelation (1); update WeightedRelation (Similar); update WeightedRelation (1); update WeightedRelation (Similar); update WeightedRelation (1); update WeightedRelation (Similar); update WeightedRelation (1); 2016-07-19 19:14:56.0 [saritz] insert WeightedRelation (id: null related concept uuid: 2ab4ba32-0bb3-4e4e-bac6-1ff4a3baf0df relationship type: null relationship value: null generated by: null); 2016-07-19 19:14:21.0 [saritz] insert WeightedRelation (id: null related concept uuid: 043dc242-1014-4e9a-91ee-c472b791b026 relationship type: null relationship value: null generated by: null); 2016-07-19 19:13:20.0 [saritz] insert Definition (id: null text: JPSS-4, scheduled to launch in 2031, is the fifth spacecraft within NOAA's next generation of polar-orbiting satellites. Similar to previous JPSS spacecrafts missions, JPSS-4 will host five instruments: (1) VIIRS, (2) CrIS, (3) ATMS, (4) OMPS-N, and (5) RBI. language code: en); insert WeightedRelation (id: null related concept uuid: 5c2364ca-c01a-4f69-8808-282c3854b2f6 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 586db0b3-5f94-466e-b7c1-a2dbedc0c1fc relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 85a52725-e6a1-430a-8506-c08c59ef31c7 relationship type: null relationship value: null generated by: null); 2016-07-19 18:47:05.0 [saritz] Insert Concept add broader relation (JPSS-4 [10adce36-ce10-4ae6-94f9-211911c7dd15,247457] - Joint Polar Satellite System (JPSS) [5c2364ca-c01a-4f69-8808-282c3854b2f6,226695]); MONITOR-E Monitor-E is a Russian Earth observation mission of KhSC (Khrunichev Space Center) on a small-class generic satellite series. The spacecraft was also designed and developed by KhSC of Moscow. The Monitor-E mission represents the first operational use of the newly developed modular and multipurpose Yakhta platform, intended for use in various remote sensing, communications, and space research applications. Spacecraft: The spacecraft is 3-axis stabilized using the generic Yakhta platform with a launch mass of 750 kg. The attitude pointing accuracy is 0.1º, the attitude rate control accuracy is 0.001º/s (angular drift). Power of 1200 W (max at EOL) is provided by two solar panels. The spacecraft features a cross-track pointing capability of ±30º from nadir by using a flywheel system, thereby providing a FOR (Field of Regard) for observation coverage considerably beyond that of the nominal swath width. This new S/C agility is provided by the introduction of a CMG (Control Moment Gyro) subsystem, an actuator within the ADCS (Attitude Determination and Control Subsystem), developed by Russian industry. KhSC refers to the ADCS as ICS (Integrated Control System). The S/C system design life is 5 years. Note: The Monitor-E spacecraft is of Monitor-E heritage (same name of previous and current missions) which was launched on June 30, 2003 from Plesetsk on a Rockot KS vehicle. On this flight, Monitor-E functioned as a mock-up (or prototype) spacecraft of KhSC with a mass of 700 kg. The spacecraft Monitor-E remained attached to the upper stage of the launch vehicle, it was used for demonstration purposes. RF communications: The payload data are being received in X-band by ground stations of federal, regional, and local levels in Russia. An effort is being made to acquire the data in near real-time in support of fast reaction response applications. Orbit: Sun-synchronous near-circular orbit: mean altitude = 540 km, inclination = 97.5º. Launch: A launch of Monitor-E took place on Aug. 26, 2005 on a Rockot Breeze-KM launch vehicle of Eurockot Launch Services from the Plesetsk Cosmodrome, Russia. Mission status: Monitor-E is operational as of 2007. So far, the spacecraft has collected imagery of more than 80 million km2. • After launch and orbit insertion, the spacecraft experienced initial attitude control problems (flight controllers lost contact with the satellite). However, the flight controllers have regained control of Monitor-E, all systems are operating nominally and the spacecraft is in the commissioning phase as of early November 2005 (the checkout phase is estimated to last for up to 6 months to test the new components of the platform and the payload - and to conduct various operational experiments). • In Sept. 2006, Monitor-E experienced a malfunction of its ADCS (Attitude Determination and Control Subsystem). After analysis of the problem nature, a software work-around procedure was developed and successfully installed onboard. Information obtained from http://www.eoportal.org/ Group: Platform_Details Entry_ID: MONITOR-E Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: MONITOR-E-1 End_Group Group: Synonymous_Platform_Names Short_Name: Monitor Experimental End_Group Group: Platform_Associated_Instruments Short_Name: CAMERAS Short_Name: MS End_Group Group: Orbit Orbit_Altitude: 540 km Orbit_Inclination: 97.5 degrees Period: 95.2 minutes Perigee: 532.0 km Apogee: 539.2 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2008-07-10 Online_Resource: http://directory.eoportal.org/get_announce.php?an_id=11116 Group: Platform_Logistics Launch_Date: 2005-08-26 Launch_Site: Plesetsk Cosmodrome, Russia Design_Life: 5 years Primary_Sponsor: Khrunichev Space Center, Russia End_Group End_Group Models/Analyses A schematic description of a system, theory, or phenomenon that accounts for its known or inferred properties and may be used for further study of its characteristics [Source: The Free Dictionary] Group: Platform_Details Entry_ID: Models/Analyses Group: Platform_Identification Platform_Category: Models/Analyses Short_Name: Models/Analyses End_Group End_Group 2019-11-25 18:11:58.0 [mmorahan] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,405101] - OCEAN STATE ESTIMATION [04d24dfe-c9f7-43b6-8bd8-8f2613767257,423567]); 2019-11-25 17:58:47.0 [mmorahan] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,405101] - MITgcm [3fd56bd8-0e40-4401-9033-97df9a552001,423563]); 2019-06-25 14:11:29.0 [tstevens] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,344529] - TMPA [eff6fbfa-3ccf-4848-89a2-b0b0e65e3524,368909]); 2018-12-28 21:49:22.0 [sritz] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,344529] - NASA-GISS-3D-Tracer-Transport [16ddc50b-7bb0-4a13-adef-dbdd5e2e2bcd,368403]); 2018-12-28 21:00:38.0 [sritz] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,344529] - NASA-GISS-Dust-Transport [ac82f543-df04-4301-b5fa-dae2800197d6,368399]); 2018-11-28 17:47:55.0 [tstevens] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,344529] - WRF [6fb2817f-c3e3-4332-85ad-79f74227e6bc,368277]); 2018-08-09 17:53:39.0 [sritz] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,344529] - GEOS-5 [42ad1501-744a-439c-a394-258db03d0304,368047]); 2018-08-09 17:43:43.0 [sritz] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,344529] - MODELE [8ad656db-1324-4e92-8273-5a765ca29282,368043]); 2016-12-07 14:47:01.0 [sritz] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,256331] - Merged Analysis [6acce314-322f-4d58-9dcb-1f93457a9d86,278533]); 2016-10-27 20:51:31.0 [saritz] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,256331] - GEOS-Chem [4773815f-2a76-425e-86cc-0bfd4c3b75c2,278467]); 2016-04-08 18:21:59.0 [saritz] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215] - NOBM [b63e0078-74a3-431d-92f7-8853c10474e4,158897]); 2016-03-31 13:54:06.0 [saritz] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215] - GEOS-4 [b42aa64a-6b63-4fd0-b953-4abf7558008c,158769]); 2015-11-24 18:04:57.0 [epneff] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215] - Observation Based Analyses [bb5002a8-6ff2-43dd-b0c9-8f9a76e11cb5,158503]); 2015-09-01 13:49:25.0 [gee-cee] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215] - CMORPH [1810678e-9c36-4260-b9a2-eb69eda1ffe4,158335]); 2015-08-10 18:57:11.0 [epneff] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215] - NCEP-MRF [6426710e-8498-4308-845e-c9c543bcc17e,158259]); 2015-08-10 18:56:01.0 [epneff] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215] - NCEP-FNL [0ea8022d-e6bf-48e0-86ce-e1e7a886b7b1,158255]); 2015-08-10 18:54:57.0 [epneff] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215] - NCEP-CFSV2 [86ee0e30-96d0-4bb4-9ee6-a24aa0e0234b,158251]); 2015-08-10 18:54:18.0 [epneff] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215] - NCEP-CFSR [929347c6-e7d9-4e72-a6c8-8926a369cb6b,158247]); 2015-08-10 18:51:41.0 [epneff] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215] - NCEP/NCAR-RM [b1c1ea44-000a-4535-8e90-d8dd447371d4,158243]); 2015-08-10 18:50:49.0 [epneff] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215] - NCEP/DOE-R2M [7c4302ef-0fca-4987-9515-d059b9e0bb95,158239]); 2015-08-10 18:48:31.0 [epneff] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215] - MICOM [00f8ab1f-040f-40b4-ba64-9f6a4c2ca7ed,158235]); 2015-08-10 18:47:07.0 [epneff] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215] - FSL-MAPS [f065f97b-a10e-4204-8807-dc904c409b51,158231]); 2015-08-10 18:45:43.0 [epneff] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215] - ETA [2ecfc2b9-118b-4462-9352-9193eef0a1dc,158227]); 2015-08-10 18:43:04.0 [epneff] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215] - ERA40DAS [260c784e-c422-4279-97fa-9c7a348118fa,158223]); 2015-08-10 18:42:27.0 [epneff] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215] - ERA15DAS [d022dc0f-0ce8-471a-ac6c-aabb48542cf4,158219]); 2015-08-10 18:41:36.0 [epneff] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215] - ECMWFIFS [47ee8305-57b9-4df1-84ce-f563df48cf69,158215]); 2015-08-10 18:39:48.0 [epneff] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215] - CESM [1b492235-f1fa-47d9-aae5-278812d29e7d,158211]); 2015-08-10 14:42:15.0 [gee-cee] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215] - CLIMATE MODELS [8680cb49-1637-4a47-a5fd-f39d4e618e45,158205]); 2015-08-10 14:41:43.0 [gee-cee] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215] - REANALYSIS MODELS [e804fb28-786b-460f-969c-7005b0803cde,158201]); 2015-08-10 14:41:19.0 [gee-cee] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215] - OPERATIONAL MODELS [9f95a56a-2669-427e-a785-de9162ffe133,158197]); 2015-08-10 14:40:28.0 [gee-cee] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215] - MODELS [26d3953e-be79-46e4-b746-efb1983c3f5c,158193]); 2015-06-22 19:09:06.0 [saritz] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215] - MERRA-2 [09294834-bc5d-4937-ba1a-3a62b4329948,158051]); 2015-06-21 23:16:17.0 [saritz] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215] - MERRA [5a147bc8-abc3-4c79-bbba-0a64bf888b41,158047]); 2015-06-04 14:32:22.0 [aaleman] Move Concepts delete narrower relation (null); 2015-06-04 14:30:43.0 [aaleman] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215] - DATA ANALYSIS [73c1df3f-b389-4cc0-98eb-0fbc4f071f98,157993]); 2015-05-27 18:05:57.0 [saritz] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215] - CONUS-Soil [e798b5b2-e34b-41bf-97f8-f1efd6a93300,157965]); 2015-03-05 16:05:17.0 [epneff] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,73395] - NCEP-GFS [53b3429a-d915-4d1c-b600-bf3e37874839,106787]); 2015-03-05 16:03:59.0 [epneff] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,73395] - NCEP-NAM [4cbc6cbe-50a2-4464-acd9-395379753d4e,106783]); 2015-03-05 15:37:53.0 [epneff] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,73395] - NCEP-GODAS [4201d98f-7f8a-46bf-b823-47385bbc7fed,106779]); 2015-01-07 22:49:43.0 [saritz] Remove Concepts delete narrower relation (null); 2015-01-07 22:36:38.0 [saritz] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,73395] - Reanalysis [033d5136-ed48-4ef0-9000-d657ded62cba,106689]); 2014-11-07 15:40:23.0 [epneff] Insert Concept add narrower relation (Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,73395] - RASI [2d0c75bf-49bc-4a76-bd77-b179ea677bc2,106665]); 2014-11-07 15:39:25.0 [epneff] Expanded to include Analyses at request of GHRC update PrefLabel (Models/Analyses); 2014-07-30 01:27:32.0 [saritz] Insert Concept add narrower relation (Models [113ecbc2-ab36-4d58-a96c-a6ce0106e749,73395] - Catchment-LSM [09ef7548-5e64-4296-8129-0ab625e15721,106525]); 2014-06-13 13:44:18.0 [tbs1979] Insert Concept add narrower relation (Models [113ecbc2-ab36-4d58-a96c-a6ce0106e749,73395] - GOCART [bacbb5ad-9269-48ce-8da2-c22d73b9a5f2,106473]); 2014-05-30 09:18:12.0 [128.183.164.42] Insert Concept add narrower relation (Models [113ecbc2-ab36-4d58-a96c-a6ce0106e749,73395] - Mosaic-LSM [8c1eb362-072d-4763-b6f3-6b706b257e6a,106441]); 2014-05-30 09:16:49.0 [128.183.164.42] Insert Concept add narrower relation (Models [113ecbc2-ab36-4d58-a96c-a6ce0106e749,73395] - Noah-LSM [d92e3dca-7aeb-4cc1-9dc0-571844337222,106437]); 2014-05-30 09:16:04.0 [128.183.164.42] Insert Concept add narrower relation (Models [113ecbc2-ab36-4d58-a96c-a6ce0106e749,73395] - VIC-LSM [87a9b8ff-5da4-4a9e-815b-2564a1af2719,106433]); 2014-05-30 09:14:58.0 [128.183.164.42] Insert Concept add narrower relation (Models [113ecbc2-ab36-4d58-a96c-a6ce0106e749,73395] - CLM-LSM [d8e67ddc-abaf-469b-8e84-f1549c1ca70d,106429]); 2014-05-30 09:14:04.0 [128.183.164.42] Insert Concept add narrower relation (Models [113ecbc2-ab36-4d58-a96c-a6ce0106e749,73395] - Forcing-LSM [862e790e-d42f-433a-8561-107562aceb64,106425]); 2014-05-21 18:10:25.0 [128.183.164.42] Insert Concept add narrower relation (Models [113ecbc2-ab36-4d58-a96c-a6ce0106e749,73395] - LSM [73cef3bc-0a2c-4c10-9e5b-d0c64bca038f,106403]); 2014-02-03 12:00:34.0 [tbs1979] Remove Concepts delete narrower relation (null); 2014-02-03 11:59:57.0 [tbs1979] Insert Concept add narrower relation (Models [113ecbc2-ab36-4d58-a96c-a6ce0106e749,73395] - TEST [66d14514-c38f-4a5e-a2aa-18ed7a07efe1,106129]); 2014-01-31 16:26:47.0 [tbs1979] Remove Concepts delete narrower relation (null); 2014-01-31 16:26:42.0 [tbs1979] Remove Concepts delete narrower relation (null); 2014-01-31 16:26:38.0 [tbs1979] Remove Concepts delete narrower relation (null); 2014-01-31 16:26:07.0 [tbs1979] Insert Concept add narrower relation (Models [113ecbc2-ab36-4d58-a96c-a6ce0106e749,73395] - TEST4 [db03fbe5-ad2d-498b-8a3d-9aa3259fdfeb,106121]); 2014-01-31 13:17:02.0 [tbs1979] Insert Concept add narrower relation (Models [113ecbc2-ab36-4d58-a96c-a6ce0106e749,73395] - TEST3 [7ca187b6-1aa8-4812-91f4-06251e7c5f11,106117]); 2014-01-31 13:16:49.0 [tbs1979] Rename Concept update PrefLabel (Models); 2014-01-31 13:16:43.0 [tbs1979] Undo delete add narrower relation (TEST3 [113ecbc2-ab36-4d58-a96c-a6ce0106e749,73395] - TEST2 [702d7d3a-eea8-4011-864d-7e78075db879,106113]); 2014-01-31 13:16:30.0 [tbs1979] Remove Concepts delete narrower relation (null); 2014-01-31 13:16:21.0 [tbs1979] Rename Concept update PrefLabel (TEST3); 2014-01-31 13:03:01.0 [tbs1979] Insert Concept add narrower relation (Models [113ecbc2-ab36-4d58-a96c-a6ce0106e749,73395] - TEST2 [702d7d3a-eea8-4011-864d-7e78075db879,106113]); 2014-01-30 14:53:53.0 [tbs1979] Insert Concept add narrower relation (Models [113ecbc2-ab36-4d58-a96c-a6ce0106e749,73395] - POM [45d0ab0d-19d4-4fc4-8f69-9f6b4529a430,106109]); 2013-07-03 15:06:26.0 [saritz] Insert Concept add narrower relation (Models [113ecbc2-ab36-4d58-a96c-a6ce0106e749,73395] - CRM [57441436-5372-484e-983c-f96cbc51ef72,105257]); ATS-2 ATS 2 was launched in April 1967 and was a medium altitude, gravity-gradient-stabilized spacecraft designed to (1) test new concepts in spacecraft design, propulsion, and stabilization, (2) take high-quality cloudcover pictures, (3) provide in situ measurements of the aerospace environment, and (4) test improved communication systems. The cylindrically-shaped spacecraft measured 142 cm in diameter and 183 cm in length. The primary structural members were a corrugated thrust tube with honeycombed bulkheads secured to each end. Equipment components and payload were externally mounted on the outer surface of the thrust tube as well as on a structure that slid into the interior of the thrust tube. Electric power was provided by two solar arrays mounted on either end of the spacecraft's outer shell and by two rechargeable nickel-cadmium batteries. Extending radially outward from the side of the spacecraft were four 28.2 m adjustable gravity-gradient booms. The spacecraft telemetry system consisted of four 2.1-W transmitters (two at 136.47 MHz and two at 137.35 MHz), in addition to a microwave communications experiment. This satellite carried a particle telescope, omnidirectional proton and electron detectors, advanced vidicon camera system, and a electron magnetic deflection spectrometer. The second stage of the ATS 2 launch vehicle failed to ignite resulting in an unplanned elliptical orbit. Stresses induced by this orbit eventually induced spacecraft tumbling. In spite of these conditions useful data were obtained from some of the experiments, most notably the cosmic-ray and particle experiments and the field detection experiments. The satellite reentered the atmosphere on September 2, 1969. Group: Platform_Details Entry_ID: ATS-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: ATS (Advanced Technology Satellite) Short_Name: ATS-2 Long_Name: Advanced Technology Satellite-2 End_Group Creation_Date: 2007-09-08 Online_Resource: http://www.astronautix.com/craft/ats2.htm Sample_Image: http://www.astronautix.com/graphics/a/ats2.jpg Group: Platform_Logistics Launch_Date: 1967-04-06 Design_Life: 3 YEARS Primary_Sponsor: NASA End_Group End_Group ADEOS (Advanced Earth Observing Satellite) ROPOS The Remotely Operated Platform for Ocean Science (ROPOS) is a remotely operated vehicle (ROV) which is able to dive down to depths of 3.1 miles (5,000 meters). The vehicle is managed and operated by the Canadian Scientific Submersible Facility , a nationally registered not-for-profit corporation established in 1995 specifically to oversee the ROPOS system. While ROPOS is used for a variety of different types of deployments, the ROV specializes in supporting science-based missions and carries a suite of “core” observation tools to assist with these missions. These tools include a number of video and still cameras and robust lighting to capture the otherwise dark underwater environment; two manipulator arms that can be fitted with different tools for collecting biologic and geologic samples; a multibeam system for mapping the seafloor; and much more. In fact, for each mission, ROPOS can be outfitted with up to eight additional custom-designed observation tools. ROPOS is an unmanned submersible, controlled from a surface vessel through an armored electrical-optical umbilical cable. This means that the ROV can spend as much time underwater as needed to accomplish a mission. To date, the longest dive recorded by ROPOS lasted over 99 hours! ROPOS and its crew conduct missions all over the world and have explored in the Pacific, Atlantic, and Indian Oceans as well as the sub-Arctic and Antarctica. 2020-01-21 18:05:22.0 [tstevens] insert Definition (id: null text: The Remotely Operated Platform for Ocean Science (ROPOS) is a remotely operated vehicle (ROV) which is able to dive down to depths of 3.1 miles (5,000 meters). The vehicle is managed and operated by the Canadian Scientific Submersible Facility , a nationally registered not-for-profit corporation established in 1995 specifically to oversee the ROPOS system. While ROPOS is used for a variety of different types of deployments, the ROV specializes in supporting science-based missions and carries a suite of “core” observation tools to assist with these missions. These tools include a number of video and still cameras and robust lighting to capture the otherwise dark underwater environment; two manipulator arms that can be fitted with different tools for collecting biologic and geologic samples; a multibeam system for mapping the seafloor; and much more. In fact, for each mission, ROPOS can be outfitted with up to eight additional custom-designed observation tools. ROPOS is an unmanned submersible, controlled from a surface vessel through an armored electrical-optical umbilical cable. This means that the ROV can spend as much time underwater as needed to accomplish a mission. To date, the longest dive recorded by ROPOS lasted over 99 hours! ROPOS and its crew conduct missions all over the world and have explored in the Pacific, Atlantic, and Indian Oceans as well as the sub-Arctic and Antarctica. language code: en); 2020-01-21 17:25:27.0 [tstevens] Insert Concept add broader relation (ROPOS [127be6b4-50ad-496d-939b-5c1dc47ac4ff,559731] - ROV [da6420b6-48ec-4ae2-98c7-0ef0538815a0,542741]); SAC-C SAC-C is an international cooperative mission between NASA, the Argentine Commission on Space Activities (CONAE), Centre National d'Etudes Spatiales (CNES or the French Space Agency), Instituto Nacional De Pesquisas Espaciais (Brazilian Space Agency), Danish Space Research Institute, and Agenzia Spaziale Italiana (Italian Space Agency). SAC-C was developed through the partnership of its senior partners, CONAE and NASA with contributions from Brazil, Denmark, France, and Italy. SAC-C will provide multispectral imaging of terrestrial and coastal environments. The spacecraft will study the structure and dynamics of the Earth?s atmosphere, ionosphere and geomagnetic field. SAC-C will seek to measure the space radiation in the environment and its influence on advanced electronic components. The satellite will determine the migration route of the Franca whale and verify autonomous methods of attitude and orbit determination. CONAE is responsible for development of the spacecraft and several instruments. The Brazilian Space Agency provided the testing facilities for SAC-C. The Italian Space Agency has partnered with CONAE to supply both solar panels and two GPS receivers. The Danish Space Research Institute provided the Magnetic Mapping Payload which carries a NASA Supplied Helium Magnetometer, and CNES is contributing an experiment to test the response of electronic circuitry to space radiation. The launch vehicle and some science instruments are provided by NASA. NASA's Goddard Space Flight Center, Greenbelt, Md. is responsible for overall project management. [Summary provided by NASA] Group: Platform_Details Entry_ID: SAC-C Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: SAC Short_Name: SAC-C Long_Name: Satelite de Aplicaciones Cientifico - C End_Group Group: Platform_Associated_Instruments Short_Name: MOBLAS Short_Name: MMRS Short_Name: IST Short_Name: INES Short_Name: ICARE Short_Name: HRTC Short_Name: HCS Short_Name: GOLPE End_Group Group: Orbit Orbit_Altitude: 702 km Orbit_Inclination: 98.2 degree Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-11-13 Online_Resource: http://www.conae.gov.ar/satelites/sac-c.html Sample_Image: http://space.skyrocket.de/img_sat/sac-c__2.jpg Group: Platform_Logistics Launch_Date: 2000-11-21 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: Argentina/CoNAE Primary_Sponsor: USA/NASA End_Group End_Group LANDSAT-8 [Update, 2013-02-11] The Landsat Data Continuity Mission spacecraft is safely in orbit and sending telemetry back to Earth after a 1:02 p.m. EST liftoff aboard a United Launch Alliance Atlas V 401 rocket. The on-time liftoff followed a smooth countdown at Vandenberg Air Force Base Space Launch Complex 3. [Text Source: NASA LDCM Mission Homepage, http://www.nasa.gov/mission_pages/landsat/main/index.html ] Landsat 8 (formerly called the Landsat Data Continuity Mission, or LDCM) is NASA’s eighth satellite in the Landsat series and continues the Landsat program’s critical role in monitoring, understanding and managing the resources needed for human sustainment such as food, water and forests. As our population surpasses seven billion people, the impact of human society on the planet will increase, and Landsat monitors those impacts as well as environmental changes. With the longest unbroken data stream of Earth’s surface as seen from space, NASA’s Earth-observing Landsat fleet has provided the world with unprecedented information on land cover changes and their residual effects since 1972. The knowledge gained from 40 years of continuous data contributes to research on climate, carbon cycle, ecosystems, water cycle, biogeochemistry and changes to Earth’s surface, as well as our understanding of visible human effects on land surfaces. Building off that research, the Landsat imaging data set has, over time, led to the improvement of human and biodiversity health, energy and water management, urban planning, disaster recovery and agriculture monitoring, all resulting in incalculable benefits to the United States and world economy. Landsat 8 joined the Landsat 7 satellite in orbit and produces stunning pictures of Earth’s surface along with a wealth of scientific data. Landsat 8 measures Earth’s surfaces in the visible, near-infrared, short wave infrared and thermal infrared, with a moderate-resolution of 15 to 100 meters, depending on spectral frequency. Landsat 8 is a collaboration between NASA and the U.S. Geological Survey (USGS). Group: Platform_Details Entry_ID: LANDSAT-8 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: LANDSAT Short_Name: LANDSAT-8 End_Group Group: Synonymous_Platform_Names Short_Name: LDCM Short_Name: Landsat Data Continuity Mission End_Group Group: Platform_Associated_Instruments Short_Name: TIRS Short_Name: OLI End_Group Group: Orbit Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2009-02-25 Online_Resource: https://landsat.gsfc.nasa.gov/landsat-8/ Online_Resource: https://www.usgs.gov/land-resources/nli/landsat/landsat-8 Group: Platform_Logistics Launch_Date: 2013-02-11 Launch_Site: VANDENBERG AIR FORCE BASE, USA Primary_Sponsor: USA/USGS Primary_Sponsor: USA/NASA End_Group End_Group 2019-12-31 21:53:25.0 [sritz] update Definition ([Update, 2013-02-11] The Landsat Data Continuity Mission spacecraft is safely in orbit and sending telemetry back to Earth after a 1:02 p.m. EST liftoff aboard a United Launch Alliance Atlas V 401 rocket. The on-time liftoff followed a smooth countdown at Vandenberg Air Force Base Space Launch Complex 3. [Text Source: NASA LDCM Mission Homepage, http://www.nasa.gov/mission_pages/landsat/main/index.html ] Landsat 8 (formerly called the Landsat Data Continuity Mission, or LDCM) is NASA’s eighth satellite in the Landsat series and continues the Landsat program’s critical role in monitoring, understanding and managing the resources needed for human sustainment such as food, water and forests. As our population surpasses seven billion people, the impact of human society on the planet will increase, and Landsat monitors those impacts as well as environmental changes. With the longest unbroken data stream of Earth’s surface as seen from space, NASA’s Earth-observing Landsat fleet has provided the world with unprecedented information on land cover changes and their residual effects since 1972. The knowledge gained from 40 years of continuous data contributes to research on climate, carbon cycle, ecosystems, water cycle, biogeochemistry and changes to Earth’s surface, as well as our understanding of visible human effects on land surfaces. Building off that research, the Landsat imaging data set has, over time, led to the improvement of human and biodiversity health, energy and water management, urban planning, disaster recovery and agriculture monitoring, all resulting in incalculable benefits to the United States and world economy. Landsat 8 joined the Landsat 7 satellite in orbit and produces stunning pictures of Earth’s surface along with a wealth of scientific data. Landsat 8 measures Earth’s surfaces in the visible, near-infrared, short wave infrared and thermal infrared, with a moderate-resolution of 15 to 100 meters, depending on spectral frequency. Landsat 8 is a collaboration between NASA and the U.S. Geological Survey (USGS). Group: Platform_Details Entry_ID: LANDSAT-8 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: LANDSAT Short_Name: LANDSAT-8 End_Group Group: Synonymous_Platform_Names Short_Name: LDCM Short_Name: Landsat Data Continuity Mission End_Group Group: Platform_Associated_Instruments Short_Name: TIRS Short_Name: OLI End_Group Group: Orbit Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2009-02-25 Online_Resource: https://landsat.gsfc.nasa.gov/landsat-8/ Online_Resource: https://www.usgs.gov/land-resources/nli/landsat/landsat-8 Group: Platform_Logistics Launch_Date: 2013-02-11 Launch_Site: VANDENBERG AIR FORCE BASE, USA Primary_Sponsor: USA/USGS Primary_Sponsor: USA/NASA End_Group End_Group); update Definition (https://landsat.gsfc.nasa.gov/landsat-8/); delete Resource (null); 2013-06-03 18:18:52.0 [tbs1979] delete AltLabel (null); 2013-06-03 18:16:25.0 [tbs1979] update AltLabel (); update AltLabel (false); 2013-06-03 18:16:05.0 [tbs1979] update AltLabel (LANDSAT-8); update PrefLabel (LANDSAT-8); DIADEM-1D Diademe-1 D1C and Diadème-2 D1D were launched by CNES, one week apart in February 1967 into elliptical orbits. Both Diadème satellites were geodetic missions. These satellites were magnetically stabilized which limited their trackability in the southern hemisphere. Group: Platform_Details Entry_ID: DIADEM-1D Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: DIADEM Short_Name: DIADEM-1D End_Group Group: Synonymous_Platform_Names Short_Name: DIADEM-1C End_Group Group: Platform_Associated_Instruments Short_Name: DOPPLER BEACONS End_Group Group: Orbit Orbit_Inclination: 39.5 degrees Period: 108 minutes Perigee: 570 km Orbit_Type: HEO > Highly Elliptical Orbit End_Group Creation_Date: 2007-09-12 Online_Resource: http://ilrs.gsfc.nasa.gov/satellite_missions/list_of_satellites/di1d_general.html Sample_Image: http://ilrs.gsfc.nasa.gov/satellite_missions/slr_sats_pics/diadem.gif Group: Platform_Logistics Launch_Date: 1967-02-15 Primary_Sponsor: CNES End_Group End_Group BILSAT-1 [Source: Gunter's Space Page, http://space.skyrocket.de/index_frame.htm?http://www.skyrocket.de/space/doc_sdat/bilsat-1.htm ] The Disaster Monitoring Constellation (DMC) is a novel international co-operation in space, led by SSTL bringing together organisations from seven countries: Algeria, China, Nigeria, Thailand, Turkey, the United Kingdom and Vietnam. The DMC Consortium is forming the first-ever microsatellite constellation bringing remarkable Earth observation capabilities both nationally to the individual satellite owners, and internationally to benefit world-wide humanitarian aid efforts. BILSAT experiments include two payloads designed and built by SSTL's Turkish customer, TUBITAK-ODTU-BILTEN. - The first, named COBAN, is a nine-band low resolution multi-spectral imager. - The second, named GEZGIN, is a DSP based image processing module that uses the JPEG2000 algorithm to compress images taken by BILSAT-1's on board cameras. Both of these payloads were designed and built by BILTEN engineers in the context of the KHTT (Know How Training and Transfer) programme that ran in parallel with the BILSAT project. Group: Platform_Details Entry_ID: BILSAT-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: DMC-1G (Disaster Monitoring Constellation- 1st Generation) Short_Name: BILSAT-1 End_Group Group: Platform_Associated_Instruments Short_Name: COBAN End_Group Creation_Date: 2008-08-18 Online_Resource: http://www.sstl.co.uk/Missions/BILSAT-1--Launched-2003/BILSAT-1/BILSAT-1--The-Mission Online_Resource: http://space.skyrocket.de/doc_sdat/bilsat-1.htm Sample_Image: http://www.skyrocket.de/space/img_sat/bilsat-1__1.jpg Group: Platform_Logistics Launch_Date: 2003-09-27 Launch_Site: Plesetsk Cosmodrome, Russia Design_Life: Fulfilled mission life time in August 2006 Primary_Sponsor: Turkey/BILTEN End_Group End_Group 2019-05-06 13:34:27.0 [mmorahan] update Resource (image); insert WeightedRelation (id: null related concept uuid: 534f6bde-acc9-4ba3-b3d9-06cd61060026 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 15d09d38-78d5-484c-93b4-3bf27e036dff relationship type: null relationship value: null generated by: null); MOORINGS STELLA Stella was a 48 kg French satellite that was launched along with SPOT 3. It was a dense sphere of uranium alloy with 60 laser reflectors on the surface. Reflected laser beams enabled accurate geodetic measurements for the determination, with an accuracy of 1 cm, of the geoid, of oceanic and terrestrial tides, and of tectonic movements. It joined its still operational twin, Starlette, that was launched in 1975. [Summary provided by NASA0 ATS (Advanced Technology Satellite) CORONA CORONA is the first operational space photo reconnaissance satellite. President Dwight David Eisenhower approved the project in Febuary 1958. The project was conceived to take pictures in space of the Soviet Bloc countries and de-orbit the photographic film for processing and exploitation. Satellite Characteristics: OBJECTIVES: - Annual and Semi-Annual Search - Priority Targets - Mapping, Charting and Geodesy PAYLOAD DATA: - Two convergent, F/3.5, 24. in FL Pan Cameras - Stellar-Terrain Camera - 2 1,500 FT x 70mm FILM - Frame Size 7.4 x 119 NM - Resolution 6-10 FT - Coverage 7 Million SQ NM/Mission - Two Recovery Vehicles ORBITAL DATA: - Inclination 60-110 DEG - Average Perigee 100 NM - Average Apogee 150 NM - Mission Life: 10 days BOOSTER: - Thorad / Agenda Additional inforamtion available at "http://www.nro.gov/corona/sysinfo2.htm" [Summary provided by the National Reconnaissance Office] Navigation Platforms Platforms such as GPS, NAVSTAR, and GLONASS whose purpose is for ascertaining one's position and planning and following a route. Group: Platform_Details Entry_ID: Navigation Platforms Group: Platform_Identification Platform_Category: Navigation Platforms Short_Name: Navigation Platforms End_Group End_Group 2017-08-14 19:24:51.0 [tstevens] Insert Concept add narrower relation (Navigation Platforms [1506fb17-7ac4-44ce-bde5-074885bdb2d2,287403] - SBAS (Satellite-Based Augmentation System) [612454e6-06ce-4bd3-b4f2-6db85f49a013,309927]); 2017-08-14 19:23:49.0 [tstevens] Insert Concept add narrower relation (Navigation Platforms [1506fb17-7ac4-44ce-bde5-074885bdb2d2,287403] - IRNSS (India’s Regional Navigation Satellite System) [bad22a08-f8ab-49b3-b266-005b21496626,309919]); 2017-08-14 19:22:50.0 [tstevens] Insert Concept add narrower relation (Navigation Platforms [1506fb17-7ac4-44ce-bde5-074885bdb2d2,287403] - QZSS (Japan’s Quasi-Zenith Satellite System) [225fb800-22b1-4d06-88ac-2bb391ac0906,309911]); 2017-08-14 19:21:42.0 [tstevens] Insert Concept add narrower relation (Navigation Platforms [1506fb17-7ac4-44ce-bde5-074885bdb2d2,287403] - Beidou (China’s Satellite Navigation System) [ef679d6a-a05b-4976-a236-ce2158b758ea,309903]); 2017-08-14 18:59:55.0 [tstevens] Insert Concept add narrower relation (Navigation Platforms [1506fb17-7ac4-44ce-bde5-074885bdb2d2,287403] - Galileo [b1c1ecfd-eb6c-4a51-b86e-2ae64babc27d,309895]); WEATHER STATIONS Weather Stations are facilities or locations where meteorological data are gathered, recorded, and released. Such stations are of the first order when they make observations of all the important elements either hourly or by self-registering instruments; of the second order when only important observations are taken; of the third order when simpler work is done, as to record rainfall and maximum and minimum temperatures. [Source: Webster's Revised Unabridged Dictionary, ? 1996, 1998 MICRA, Inc] OV-105 Endeavour, the newest addition to the four-orbiter fleet, is named after the first ship commanded by James Cook, the 18th century British explorer, navigator and astronomer. For the first time, a national competition involving students in elementary and secondary schools produced the name of the new orbiter; it was announced by President George Bush in 1989. The Space Shuttle orbiter Endeavour was delivered to Kennedy Space Center in May 1991, and flew its first mission, highlighted by the dramatic rescue of a stranded communications satellite, a year later in May 1992. Endeavour features new hardware designed to improve and expand orbiter capabilities. Most of this equipment was later incorporated into the other three orbiters during out-of-service major inspection and modification programs. Endeavour's upgrades include: -A 40-foot diameter drag chute that is expected to reduce the orbiter's rollout distance by 1,000 to 2,000 feet. -The plumbing and electrical connections needed for Extended Duration Orbiter (EDO) modifications to allow up to 28-day missions. -Updated avionics systems that include advanced general purpose computers, improved inertial measurement units and tactical air navigation systems, enhanced master events controllers and multiplexer-demultiplexers, a solid-state star tracker and improved nose wheel steering mechanisms. -An improved version of the Auxiliary Power Units (APU's) that provide power to operate the Shuttle's hydraulic systems. [Summary provided by NASA] Group: Platform_Details Entry_ID: OV-105 Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Platform_Series_or_Entity: SPACE SHUTTLE Short_Name: OV-105 Long_Name: Endeavour Space Shuttle End_Group Group: Synonymous_Platform_Names Short_Name: Endeavour End_Group Creation_Date: 2008-01-25 Online_Resource: http://science.ksc.nasa.gov/shuttle/resources/orbiters/endeavour.html Sample_Image: http://www-pao.ksc.nasa.gov/kscpao/images/medium/02pd0590-m.jpg Group: Platform_Logistics Launch_Date: 1992-05-07 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: USA/NASA End_Group End_Group MIR I The MIR deep sea submersibles operate from the RV Akademik Keldysh. The Akademik Keldysh is the most advanced deep diving support vessel in the world. The operation is owned and operated by the PP Shirshov Institute, Russian Academy of Sciences. Its crew of scientists and technicians have worked together for over 20 years, participating in deep dive expeditions all over the world with both Pisces and MIR submersibles. Our expedition is only made possible with the support and expertise of Captain Yuriy Gorbach, his Keldysh crew and the MIR support team lead by Dr. Anatoly Sagalevitch. They are a highly skilled, professional team running one of the most unique and safest underwater operations in the world. The Keldysh and MIR I and II have been used for National Geographic photo and film projects, and director James Cameron's epic motion picture Titanic. In addition to its 17 laboratories, the Keldysh features a specialized library covering underwater geology, oceanography and deep-sea exploration. The habitation sphere (pressure hull) of the MIR submersible is 6 feet 10 inches (2.1 meters) in diameter and is specifically designed to carry three people -- in our case one expert pilot and two participants/observers. Inside the sphere it is "one atmosphere," just like a room in your home. Around the inside of the sphere are many controls, instruments, and electrical circuits. At the forward end of the sphere are three viewports, each providing a forward and a partial peripheral viewing arc. There are two couches/mattresses for the two participants/observers who can lay along these with their faces close to the viewing portholes (you can also sit or stand up to stretch and relax). The pilot sits or kneels at a central control console and guides the submersible using the main central porthole. There is no vision directly to the sides or the aft end of the submersible. 2020-01-21 19:41:32.0 [tstevens] insert Definition (id: null text: The MIR deep sea submersibles operate from the RV Akademik Keldysh. The Akademik Keldysh is the most advanced deep diving support vessel in the world. The operation is owned and operated by the PP Shirshov Institute, Russian Academy of Sciences. Its crew of scientists and technicians have worked together for over 20 years, participating in deep dive expeditions all over the world with both Pisces and MIR submersibles. Our expedition is only made possible with the support and expertise of Captain Yuriy Gorbach, his Keldysh crew and the MIR support team lead by Dr. Anatoly Sagalevitch. They are a highly skilled, professional team running one of the most unique and safest underwater operations in the world. The Keldysh and MIR I and II have been used for National Geographic photo and film projects, and director James Cameron's epic motion picture Titanic. In addition to its 17 laboratories, the Keldysh features a specialized library covering underwater geology, oceanography and deep-sea exploration. The habitation sphere (pressure hull) of the MIR submersible is 6 feet 10 inches (2.1 meters) in diameter and is specifically designed to carry three people -- in our case one expert pilot and two participants/observers. Inside the sphere it is "one atmosphere," just like a room in your home. Around the inside of the sphere are many controls, instruments, and electrical circuits. At the forward end of the sphere are three viewports, each providing a forward and a partial peripheral viewing arc. There are two couches/mattresses for the two participants/observers who can lay along these with their faces close to the viewing portholes (you can also sit or stand up to stretch and relax). The pilot sits or kneels at a central control console and guides the submersible using the main central porthole. There is no vision directly to the sides or the aft end of the submersible. language code: en); 2020-01-21 17:35:19.0 [tstevens] Insert Concept add broader relation (MIR I [15f4ae34-a5c9-43e0-84d6-246690648fca,559783] - HOV [63c8aa1d-6efc-4943-8891-3a1cd520dde0,559759]); R/V ARANDA [Adapted from "Presentation of R/V Aranda", "http://www.fimr.fi/en/aranda/laiva.html"] The modern Aranda was launched in Helsinki in June 1989. It is first research vessel which is owned by the Finnish Institute of Marine Research, and its home port is Helsinki. The length of the ship is 59,2 m, its beam 13,8 m and gross register weight 1734 GT. The ship accomodates a research staff of 25 - 30 persons. Aranda is a modern, ice-reinforced research vessel. She was planned for Baltic Sea research, but in principle, she is able to operate in all seas. Aranda has made scientific expeditions i.a. to Antarctic waters and the Northern Atlantic. The vessel is adapted to year-round multidisciplinary marine research, including biology, physics, chemistry and geology of the sea. The well-equipped laboratories and advanced computer systems facilitate sample treatment and data analysis under way. Interplanetary Spacecraft A spacecraft designed for interplanetary flight. Group: Platform_Details Entry_ID: Interplanetary Spacecraft Group: Platform_Identification Platform_Category: Interplanetary Spacecraft Short_Name: Interplanetary Spacecraft End_Group End_Group EP-TOMS The Earth Probe TOMS (EP-TOMS) spacecraft was launched on July 2, 1996 from a Pegasus XL rocket and placed into a polar orbit with the following characteristics: Apogee Altitude : 515.2 km Perigee Altitude : 490.5 km Orbit Inclination : 97.432 deg. Period : 94.6 min The satellite was built by TRW for NASA's Goddard Space Flight Center. TOMS is part of NASA's Mission to Planet Earth a long term, coordinated research effort to study the Earth as a global environmental system. Using the unique perspective available from space, NASA will observe, monitor and assess large-scale environmental processes, focusing on climate change. MTPE satellite data, complemented by aircraft and ground data, will allow humans to better understand natural environmental changes and to distinguish natural changes from human induced changes. MTPE data, which NASA will distribute to researchers worldwide, is essential to humans making informed decisions about their environment. The goal of the Total Ozone Mapping Spectrometer (TOMS) Earth Probe mission (part of NASA's Mission To Planet Earth (MTPE) Phase I program) was to continue the high-resolution global mapping of total ozone on a daily basis (begun with the Nimbus 7 SBUV/TOMS) as well as to detect global ozone trends to verify depletion predicted by atmospheric chemistry models. The TOMS-Earth Probe (TOMS-EP), the first of a series of NASA Earth Probe missions, was one of three TOMS missions which included METEOR 3/TOMS2 (launched 1991) and ADEOS/TOMS (launched 1995). The TOMS-EP carried only one instrument: the Total Ozone Mapping Spectrometer (TOMS). The TOMS-EP spacecraft was based on the TRW/DSI Eagle bus developed under the USAF STEP program. The spacecraft was three-axis stabilized so that the TOMS instrument was nadir-pointed with about 0.5 degree control and about 0.1 degree knowledge from measured altitude data. The TOMS-EP spacecraft bus was designed to accomodate all of the TOMS instrument requirements to support a two-year lifetime with a three-year lifetime goal. The EP-TOMS Home Page is located at: http://eospso.nasa.gov/missions/total-ozone-mapping-spectrometer-earth-probe Group: Platform_Details Entry_ID: EP-TOMS Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: EP-TOMS Long_Name: Earth Probe-TOMS End_Group Group: Synonymous_Platform_Names Short_Name: SMEX/TOMS-Earth Probe Short_Name: Small Explorer/TOMS-Earth Probe Short_Name: TOMS-EP96 Short_Name: TOMS-Earth Probe End_Group Group: Platform_Associated_Instruments Short_Name: TOMS End_Group Group: Orbit Orbit_Altitude: 740 km Orbit_Inclination: 98.385 degrees Period: 99.6 minutes Perigee: 490.5 km Apogee: 515.2 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-05-01 Online_Resource: http://eospso.nasa.gov/missions/total-ozone-mapping-spectrometer-earth-probe Online_Resource: http://science.nasa.gov/missions/toms/ Online_Resource: http://disc.sci.gsfc.nasa.gov/acdisc/TOMS Online_Resource: https://ozoneaq.gsfc.nasa.gov/missions Group: Platform_Logistics Launch_Date: 1996-07-02 Launch_Site: Vandenberg Air Force Base, USA Design_Life: 2 years Primary_Sponsor: NASA End_Group End_Group GMS-4 The Geostationary Meteorological Satellite series are spin-stabilized satellites. They have been developed to contribute to the improvement of Japan's meteorological services and the development of weather satellite technology. The satellites consist of a despun section which holds the earth-oriented antennas and a 100-rpm rotating spin section which contains the Visible and Infrared Spin Scan Radiometer (VISSR), electronic devices, etc. They have been used for the World Meteorological Organization's world Weather Watch Program which is sustained by five geostationary satellites. Characteristics: Dimensions: Cylindrical, Diameter 214.6cm Height (before AKM separation) 444.1cm (after AKM separation) 345.1cm Initial Weight after stationing: 325kg Attitude control: Spin-stabilized Design life: 5 years Reliability More than 0.5 after 5 years (Specification) Launch vehicle: H-I Launch Vehicle Launch site: Tanegashima Space Center, Kagoshima , Japan Launch date: September 6, 1989 Orbit Geostationary orbit, 140deg. E. longitude 296kg Group: Platform_Details Entry_ID: GMS-4 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: GMS (Japan Geostationary Meteorological Satellite) Short_Name: GMS-4 Long_Name: Geostationary Meteorological Satellite-4 End_Group Group: Synonymous_Platform_Names Short_Name: GMS 4 End_Group Group: Platform_Associated_Instruments Short_Name: VISSR-GMS End_Group Group: Orbit Orbit_Altitude: 36,000 km Orbit_Type: GEO > Geosynchronous > Geostationary End_Group Creation_Date: 2007-10-01 Online_Resource: http://space.skyrocket.de/doc_sdat/gms-2.htm Online_Resource: http://www.jaxa.jp/projects/sat/gms/index_e.html Group: Platform_Logistics Launch_Date: 1989-09-06 Launch_Site: Tanegashima Island, Japan Primary_Sponsor: JAPAN/JAXA End_Group End_Group NASA-GISS-3D-Tracer-Transport NASA GISS 3-Dimensional (3-D) Global Tracer Transport Model 2018-12-28 21:50:08.0 [sritz] insert AltLabel (id: null category: null text: NASA GISS 3-Dimensional (3-D) Global Tracer Transport Model language code: en); 2018-12-28 21:49:22.0 [sritz] Insert Concept add broader relation (NASA-GISS-3D-Tracer-Transport [16ddc50b-7bb0-4a13-adef-dbdd5e2e2bcd,368403] - Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,344529]); CARTOSAT-2A IRS-P8 CartoSat-2A is a follow-up optical imaging mission of CartoSat-2 (launch Jan. 10, 2007), representing India's first dedicated military satellite (funding by the Ministry of Defense of the Government of India). The overall objective is to provide scene-specific spot imagery in high resolution to the Indian Armed Forces - which is in the process of establishing an Aerospace Command. The spacecraft and its payload, built by ISRO, is practically an identical copy of the CartoSat-2 spacecraft of ISRO. It features a lightweight and compact bus structure using the BMU (Bus Management Unit) for integrated bus functions (of the AOCS, TT&C, etc.). The spacecraft is 3-axis stabilized using high torque reaction wheels, magnetic torquers, and hydrazine thrusters. Attitude sensing is provided by a high performance star sensor and by an improved IRU (Inertial Reference Unit). The satellite is very agile providing a body-pointing capability in along-track and cross-track of up to ±45º (this supports a revisit capability of certain target regions within 4 days). Also use of the SPS (Satellite Positioning System), an 8-channel GPS receiver (C/A code) on-board for the provision of instantaneous state vectors (state vector using pseudo range and range rate measurements) for the spacecraft. The fixed solar arrays (triple-junction solar cells) provide a power of 900 W when pointed toward the sun; two NiCd batteries of 18 Ah capacity are being used for ecliptic phase bridging. CartoSat-2A has a launch mass of 690 kg and a design life of 5 years. Launch: The launch of CartoSat-2A took place on April 28, 2008 on a PSLV launcher. The launch was conducted from the Satish Dhawan Space Centre (SDSC) SHAR, Sriharikota space station in southern India. Next to the primary payload of CartoSat-2A, the PSLV-C9 vehicle successfully launched the IMS-1 (Indian Microsatellite-1) of 83 kg and eight nanosatellites for international customers. Sensor complement: PAN Camera (Panchromatic Camera). The objective is to provide imagery for cartographic applications. The optical system is designed with two mirror Ritchey-Chretien on-axis obscured reflective telescope system with a concave hyperboloidal primary mirror and convex hyperboloid secondary mirrors and the field correcting relay optics. The mirrors are made of special Zerodur glass and are light-weighted to about 60% as in CartoSat-1 series. The mirrors are mounted inside the telescope cylinder made of CFRP with special MFDs (Mirror Fixation Devices) and the whole telescope assembly is mounted to the spacecraft structure through a special suspension arrangement. The optical system is designed to provide < 1 m resolution across track. The along track GSD of < 1 m is achieved by apparent velocity reduction by a factor of 2.5. The spacecraft can be suitably biased to provide various modes of imaging: 1) Continuous strip monoscopic mode 2) Spot scene imaging (strips on either side of the ground track can be imaged) 3) Paint brush mode of imaging. This mode is used to increase the total swath. Both roll tilt and pitch tilt is employed. The PAN Camera is a nadir-pointing pushbroom CCD instrument (detector line array of 12, 288 pixels), observing in the visible spectral range of 0.5-0.85 µm with a GSD (Ground Sample Distance) of < 1 m, and a swath width of 9.6 km at nadir. The spacecraft is being monitored and controlled from the ISRO mission control center in Bangalore, India using the ISTRAC network of stations at Bangalore, Lucknow, Mauritius, Bearslake in Russia, Biak in Indonesia and Svalbard in Norway. Group: Platform_Details Entry_ID: CARTOSAT-2A Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: CARTOSAT-2A End_Group Group: Platform_Associated_Instruments Short_Name: PAN End_Group Group: Orbit Orbit_Altitude: 635 km Orbit_Inclination: 97.94 degrees Period: 97.4 minutes Repeat_Cycle: 4 days Perigee: 628.7 km Apogee: 653.2 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2008-06-27 Online_Resource: http://directory.eoportal.org/get_announce.php?an_id=10000443 Online_Resource: http://www.isro.org/pslv-c9/cartosat2a.htm Sample_Image: http://directory.eoportal.org/presentations/7336/CartoSat2A_Auto2.jpeg Group: Platform_Logistics Launch_Date: 2008-04-28 Launch_Site: Sriharikota Island, India Design_Life: 5 YEARS Primary_Sponsor: Ministry of Defense of the Government of India End_Group End_Group 2019-02-20 21:02:52.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: 86402184-15ee-435c-933f-d70eb986c715 relationship type: null relationship value: null generated by: null); 2018-06-12 10:34:11.0 [mmorahan] update AltLabel (IRS-P8); 2018-06-12 10:33:36.0 [mmorahan] insert AltLabel (id: null category: null text: IRS-P7 language code: en); update Resource (image); SATELLITES SATELLITE Satellites are objects launched to orbit Earth or another celestial body. [Source: The American Heritage® Dictionary] 2016-06-09 17:17:26.0 [epneff] added altLabel insert AltLabel (id: null text: SATELLITE language code: en); FAST The Fast Auroral SnapshoT Explorer (FAST), the second mission in NASA's Small Explorer Satellite Program (SMEX), is a satellite designed to study Earth's aurora. This highly successful spacecraft has helped scientists answer fundamental questions about the causes and makeup of the aurora. FAST was launched on August 21, 1996 from a Pegasus rocket into a highly elliptical orbit. It crosses Earth's auroral zones (donut shaped regions centered on the poles) four times each orbit, and only collects high-resolution data ("snapshots") while in those zones. It ventures high into the charged particle environment of the aurora to measure the electric and magnetic fields, plasma waves, energetic electrons and ions, ion mass composition, and thermal plasma density and temperature. The FAST instrument set consists of sixteen electrostatic analyzers, four electric field langmuir probes suspended on 30 m wire booms, two electric field langmuir probes on 3 m extendible booms, searchcoil and fluxgate magnetometers and a time-of-flight mass spectrometer. The science investigation makes extremely temporal and spatial resolution measurements of the auroral plasma at apogee altitude. The instrument hardware consists of the sensor assemblies and an instrument data processor. The instrument electronics include a 32-bit data processing unit that performs the science data processing and recording in a one gigabit, solid-state memory. The stored data are transferred to the ground at one of three selectable high data rates of 900 Kbps, 1.5 Mbps or 2.25 Mbps. The instruments weigh 51 kg; the total observatory mass is 191 kg. The FAST mission is in a 351 x 4175 km orbit with an 83? inclination. The FAST observatory is a 12 rpm, spin-stabilized spacecraft with its spin axis oriented parallel to the orbit axis. Spin rate and spin-axis orientation are maintained by two magnetic torquer coils, one spinning Sun sensor, one horizon crossing indicator and a spacecraft magnetometer. The Attitude Control System (ACS) provides closed-loop spin-rate control. Spin-axis precession is performed open loop and is closed via ground commands. After computation on the ground, attitude knowledge is accurate to within one degree. The body-mounted solar array contains 5.6 m2 of solar cells that can distribute 52 W of orbit average power to the spacecraft and instruments. The orbit average power consumption of the spacecraft hardware is 33 W. The instruments consume 19 W orbit average power, 39 W when operating. Instruments are frequently powered off in order to maintain a positive energy balance. The data system for the FAST mission consists of dual 8085, 8-bit spacecraft computers. The spacecraft computers perform health and safety functions, power distribution, data encoding/decoding and launch vehicle interface. A multi-element micropatch antenna mounted on a boom above the spacecraft supports ground communications. Commands are uplinked at 2 Kbps. Health and safety data is telemetered to the ground at 4 Kbps. A Transportable Orbital Tracking Station (TOTS) was placed in Alaska to collect real-time science telemetry while the spacecraft is passing through the northern aurora. TOTS is highly automated and portable; it has an 8 m antenna with 200 W of uplink power and can be packed for shipment in three ISO containers. The FAST instruments consist of: Electric Field Experiment: The electric field experiment is composed of three orthogonal boom pairs. Spherical sensors deployed on radial wire and axial stacer booms will provide information on the plasma density and electron temperature. Magnetic Field Experiment: The magnetic field experiment consists of two magnetometers mounted 180? apart on deployable graphite epoxy booms. The search coil magnetometer uses a three-axis sensor system to provide magnetic field data over the frequency range of 10 Hz to 2.5 kHz. The flux gate magnetometer is a three-axis system using high, stable, low noise, ring core sensors to provide magnetic field information for DC to 100 Hz. Time-of-Flight Energy Angle Mass Spectrograph (TEAMS): The TEAMS instrument is a high sensitivity, mass-resolving spectrometer that measures full three-dimension distribution functions of the major ion species with one spin of the spacecraft. The TEAMS experiment covers the core of all plasma distributions of importance in the auroral region. Electrostatic Analyzers (ESA): Sixteen ESAs configured in four stacks will be used for both electron and ion measurements. The four stacks are placed around the spacecraft such that the entire package is provided a full 360? field of view. The ESAs can provide a 64-step energy sweep, covering approximately 3 eV to 30 KeV up to 16 times per second. For more information, see: http://sprg.ssl.berkeley.edu/fast/ Group: Platform_Details Entry_ID: FAST Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Short_Name: FAST Long_Name: Fast Auroral Snapshot Explorer End_Group Group: Synonymous_Platform_Names Short_Name: Explorer 70 Short_Name: SMEX/FAST Short_Name: Small Explorer/FAST Short_Name: 24285 Short_Name: 1996-049A End_Group Group: Platform_Associated_Instruments Short_Name: MFS/FAST Short_Name: EFS/FAST Short_Name: ESA/FAST Short_Name: TEAMS End_Group Group: Orbit Orbit_Inclination: 83 degrees Period: 133 m Perigee: 350 km Apogee: 4175 km Orbit_Type: HEO > Highly Elliptical Orbit End_Group Online_Resource: http://sprg.ssl.berkeley.edu/fast/intro.html Sample_Image: http://sprg.ssl.berkeley.edu/fast/graphics/fast.gif Group: Platform_Logistics Launch_Date: 1996-08-21 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: NASA End_Group End_Group NAVSTAR The Navstar Global Positioning System (GPS) is a constellation of orbiting satellites that provides navigation data to military and civilian users all over the world. The system is operated and controlled by the 50th Space Wing, located at Schriever Air Force Base, Colo. Navigating Services Features: Extremely accurate, three-dimensional location information (latitude, longitude and altitude), velocity and precise time A worldwide common grid that is easily converted to any local grid Passive all-weather operations Continuous real-time information Support to an unlimited number of users and areas Support to civilian users at a slightly less accurate level Characteristics: Primary Function: Precise navigation, timing and velocity information worldwide Primary Contractors: Block I and II/IIA, Rockwell International (Boeing North American); Block IIR, Lockheed Martin; Block IIF, Boeing North American Power Plant: Solar panels generating 800 watts Weight: Block IIA, 3,670 pounds (1,816 kilograms); Block IIR, 4,480 pounds (2,217 kilograms) Height: Block IIA, 136 inches (3.4 meters); Block IIR, 70 inches (1.7 meters) Width (includes wingspan): Block IIA, 208.6 inches (5.3 meters); Block IIR, 449 inches (11.4 meters) Design life: Block II/IIA, 7.5 years; Block IIR, 10 years Date of First Launch: 1978 Launch vehicle: Delta II Date Constellation Operational: July 1995 (at full operational capacity) Contact Information: Air Force Space Command Public Affairs Office 150 Vandenberg, Suite 1105 Peterson AFB, Colo. 80914-4500 692-3731 or (719) 554-3731. Additional information available at: "http://131.84.1.31/news/factsheets/NAVSTAR_Global_Positioning_Sy.html" [Summary provided by United States Air Force] CMORPH CMORPH (CPC MORPHing technique) produces global precipitation analyses at very high spatial and temporal resolution. This technique uses precipitation estimates that have been derived from low orbiter satellite microwave observations exclusively, and whose features are transported via spatial propagation information that is obtained entirely from geostationary satellite IR data. http://www.cpc.ncep.noaa.gov/products/janowiak/cmorph_description.html 2015-09-01 13:50:43.0 [gee-cee] added definition from GHRC insert Definition (id: null text: CMORPH (CPC MORPHing technique) produces global precipitation analyses at very high spatial and temporal resolution. This technique uses precipitation estimates that have been derived from low orbiter satellite microwave observations exclusively, and whose features are transported via spatial propagation information that is obtained entirely from geostationary satellite IR data. http://www.cpc.ncep.noaa.gov/products/janowiak/cmorph_description.html language code: en); 2015-09-01 13:49:25.0 [gee-cee] Insert Concept add broader relation (CMORPH [1810678e-9c36-4260-b9a2-eb69eda1ffe4,158335] - Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215]); EXPLORER SEISMOLOGICAL STATIONS Seismological stations: Stations that measure seismic activity. [Source: The American Heritage? Dictionary of the English Language, Fourth Edition Copyright ? 2000 by Houghton Mifflin Company.] SRL-1 The Space Radar Laboratory - 1 (SRL-1) was launched onboard the Space Shuttle "Endeavor" (STS-59) on April 9, 1994. The SRL-1 consists of two elements: a suite of radar instruments called the Spaceborne Imaging Radar-C/X-Band Synthetic Aperture Radar (SIR-C/X-SAR) jointly developed by NASA and DARA of Germany and ASI of Italy, and the Measurement of Air Pollution from Satellite (MAPS) instrument to measure atmospheric air pollution. SRL-1 is the first in a series of flights of this payload designed to (1) acquire radar imagery of the Earth's surface for studies in geology, geography, hydrology, oceanography, agronomy, and botany; (2) gather data for future space-borne radar systems; and (3) provide measurements of the global distribution of carbon monoxide (CO) in the troposphere. Instruments on board include the Shuttle Imaging Radar-C (SIR-C) with multi-frequency (C- and L-Bands), multi-polarization (HH, VV, HV, VH), and multi-incidence angle (15 to 55 degrees) capabilities thus lending itself to a wide range of earth surface applications; the X-band Synthetic Aperture Radar (X-SAR), an X-band, VV-polarized imaging radar system, built by Dornier (Germany) and Alenia (Italy) for the German Space Agency (DARA)/German Aerospace Research Establishment (DLR) and the Italian Space Agency (ASI); and, the Mapping Air Pollution from Space (MAPS) instrument for the study of global air pollution. The MAPS instrument, from NASA Langley Research Center (LaRC) is part of NASA's Mission to Planet Earth (MtPE) Program. Four 45-Mbps data channels were recorded on special high data rate tape recorders and real-time data was transmitted to ground stations. About 50 hours each of SIR-C and X-SAR data were recorded during the mission. The combined SIR-C/X-SAR Science Team was made up of 49 members and 3 associates representing 13 countries. SIR-C/X-SAR data collection was focused on several worldwide supersites and correlated with ground and aircraft measurements. Radar data was also calibrated to allow comparisons with other operating spaceborne radars (ERS-1 SAR, JERS-1 SAR). Both SIR-C and X-SAR will use on-board tape recorders to store data as well as limited real-time transmissions to the ground. Each radar has its own on-board data handling system and each radar can have its data routed through the TDRSS for real-time transmission (Ku-band). SIR-C data are recorded in parallel and X-SAR data is recorded serially. SIR-C and X-SAR data will be preprocessed at the Payload Operations Control Center (POCC) at NASA/JSC before delivery to JPL and operations centers in Germany and Italy. Commands are sent to the SRL-1 from POCC. At mission end, data tapes recorded on-board are sent to the PI sites. The SIR-C/X-SAR part of the SRL-1 mission is expected to collect over 50 hours of data, both recorded and real-time. Real-time raw data will be pre-processed by the instrument PIs and science teams and stored at the PI sites at JPL, in Germany, and in Italy for analysis. SIR-C data will be processed at JPL using the JPL advanced digital SAR processor, leading to processed SAR images on 8-mm digital tape and on film. Plans include the production of CD-ROMs with 100 m resolution images. X-SAR data will be pre-processed within 3 months. Image products will be made available to X-SAR investigators. Both Germany and Italy will operate separate archives and processing facilities for X-SAR data. SIR-C processed data will eventually be be archived with the EOSDIS DAAC at EROS Data Center. All processed MAPS data is expected to be archived with the EOSDIS DAAC at NASA/Langley. Two additional flights of SRL are planned (August 1994 and 1995). Some SIR-C and X-SAR images are publically available on the Jet Propulsion Laboratory (JPL) FTP site: jplinfo.jpl.nasa.gov in the directory /sircxsar. The images are also available through the World Wide Web (WWW) at http://www.jpl.nasa.gov/. Both servers also have extensive information about the mission. Group: Platform_Details Entry_ID: SRL-1 Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Platform_Series_or_Entity: SPACE SHUTTLE Short_Name: SRL-1 Long_Name: Space Radar Laboratory-1 End_Group Group: Synonymous_Platform_Names Short_Name: SRL-1 End_Group Group: Platform_Associated_Instruments Short_Name: X-SAR End_Group Creation_Date: 2008-01-28 Online_Resource: http://www-pao.ksc.nasa.gov/kscpao/chron/sts-59.htm Group: Platform_Logistics Launch_Date: 1994-04-09 Primary_Sponsor: NASA End_Group End_Group GCOM-C SHIKISAI The Second generation GLobal Imager (SGLI) on GCOM-C1 is an optical sensor capable of multi-channel observation at wavelengths from near-UV to thermal infrared wavelengths (380nm to 12µm.) SGLI also has polarimetry and forward / backward observation functions at red and near infrared wavelengths. SGLI obtains global observation data once every 2 or 3 days, with resolutions of 250m to 1km. The SGLI observations will improve our understanding of climate change mechanisms through long-term monitoring of aerosols and clouds, as well as vegetation and temperatures, in the land and ocean regions. These observations will also contribute to enhancing the prediction accuracy of future environmental changes by improving sub-processes in numerical climate models. SGLI-derived phytoplankton and aerosol distributions are also used for mapping fisheries and for monitoring the transport of yellow dust and/or wildfire smoke. 2019-12-31 18:51:14.0 [sritz] insert AltLabel (id: null category: null text: SHIKISAI language code: en); 2018-11-13 11:15:59.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: 8891b8a8-a469-411f-8f84-71a94da19f02 relationship type: null relationship value: null generated by: null); 2018-11-13 11:03:55.0 [mmorahan] insert AltLabel (id: null category: primary text: Global Change Observation Mission – Climate language code: en); insert Definition (id: null text: The Second generation GLobal Imager (SGLI) on GCOM-C1 is an optical sensor capable of multi-channel observation at wavelengths from near-UV to thermal infrared wavelengths (380nm to 12µm.) SGLI also has polarimetry and forward / backward observation functions at red and near infrared wavelengths. SGLI obtains global observation data once every 2 or 3 days, with resolutions of 250m to 1km. The SGLI observations will improve our understanding of climate change mechanisms through long-term monitoring of aerosols and clouds, as well as vegetation and temperatures, in the land and ocean regions. These observations will also contribute to enhancing the prediction accuracy of future environmental changes by improving sub-processes in numerical climate models. SGLI-derived phytoplankton and aerosol distributions are also used for mapping fisheries and for monitoring the transport of yellow dust and/or wildfire smoke. language code: en); 2018-11-13 11:00:52.0 [mmorahan] Insert Concept add broader relation (GCOM-C [18512c09-2590-4804-8b43-dd9caea53b5d,368261] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761]); GPS-35 The Global Position System (GPS), counterpart to the Russian Global Navigation System (GLONASS), is a United States Department of Defense (DoD) developed, worldwide, satellite-based radionavigation system that will be the DoD's primary radionavigation system well into the next century. The constellation consists of 24 operational satellites. The U.S. Air Force Space Command (AFSC) formally declared the GPS satellite constellation as having met the requirement for Full Operational Capability (FOC) as of April 27, 1995. Requirements include 24 operational satellites functioning in their assigned orbits and successful testing completed for operational military functionality. GPS consists of three segments, the SPACE, CONTROL and USER Segment: 1. The SPACE segment consists of 24 operational satellites in six orbital planes, (four satellites in each plane). The satellites operate in circular 20,200 km orbits at an inclination angle of 55 degrees and with a 12-hour period. The position is therefore the same at the same sidereal time each day, i.e. the satellites appear four minutes earlier each day. 2. The CONTROL segment consists of five Monitor Stations, three Ground Antennas, and a Master Control Station (MCS) located at Falcon AFB in Colorado. The monitor stations passively track all satellites in view, accumulating ranging data. This information is processed at the MCS to determine satellite orbits and to update each satellite's navigation message. Updated information is transmitted to each satellite via the Ground Antennas. 3. The USER segment consists of antennas and receiver-processors that provide positioning, velocity and precise timing to the user. GPS provides two levels of service, Standard Positioning Service and the Precise Positioning Service. The Standard Positioning Service (SPS) is a positioning and timing service which will be available to all GPS users on a continuous, worldwide basis with no direct charge. The Precise Positioning Service (PPS) is a highly accurate military positioning, velocity and timing service which will be available on a continuous, worldwide basis to users authorized by the U.S. [Summary provided by NASA] Group: Platform_Details Entry_ID: GPS-35 Group: Platform_Identification Platform_Category: Navigation Platforms Platform_Series_or_Entity: GPS (Global Positioning System) Short_Name: GPS-35 Long_Name: Global Positioning System Satellites-35 End_Group Group: Platform_Associated_Instruments Short_Name: GPS Short_Name: GPS RECEIVERS End_Group Group: Orbit Orbit_Inclination: 64.8 degrees Period: 718 minutes Perigee: 20,195 km Orbit_Type: MEO > Semi-Synchronous > Navigation End_Group Creation_Date: 2007-02-12 Online_Resource: http://ilrs.gsfc.nasa.gov/cgi-bin/satellite_missions/select.cgi?order=by_name&sat_code=GP35&sat_name=GPS-35&sat_no=9305401&tab_id=general Sample_Image: http://ilrs.gsfc.nasa.gov/images/gps.gif Group: Platform_Logistics Launch_Date: 1993-08-30 Design_Life: 7 Years Primary_Sponsor: U.S. Department of Defense End_Group End_Group STS-41G The 13th flight of the Space Shuttle (STS 41-G) carried the OSTA-3 (Office of Space and Terrestrial Applications) payload designed for conducting experiments in earth remote sensing. This experiment payload consisted of 1) a Shuttle Imaging Radar (SIR-B) for studies of the earth's surface, 2) a Large Format Camera (LFC) for cartographic mappings of the earth, 3) a Measurement of Air Pollution from Satellite (MAPS) experiment to determine the distribution of CO in the atmosphere, and 4) a Feature Identification and Location Experiment (FILE) for classification of surface materials. The SIR-B was an upgraded version of the SIR-A flown on the OSTA-1 payload during the STS-2 mission (NSSDC ID 81-111A-01). The MAPS and FILE sensors were the reflies of those same instruments on the OSTA-1 payload (NSSDC ID 81-111A-04 and 81-111A-03). The mission lasted 8 days and, except for SIR-B, all instruments met their pre launch requirements. Group: Platform_Details Entry_ID: STS-41G Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Platform_Series_or_Entity: SPACE SHUTTLE Short_Name: STS-41G Long_Name: Space Transport System STS-41G End_Group Group: Synonymous_Platform_Names Short_Name: Challenger (6) End_Group Group: Orbit Orbit_Inclination: 57 degrees Perigee: 216 km Apogee: 229 km End_Group Creation_Date: 2008-01-29 Online_Resource: http://www.spacefacts.de/mission/english/sts-41g.htm Sample_Image: http://www.ksc.nasa.gov/mirrors/images/images/pao/STS41G/10061805.jpg Group: Platform_Logistics Launch_Date: 1984-10-05 Primary_Sponsor: NASA End_Group End_Group UC-12B The NASA Langley Beechcraft UC-12B Huron (NASA 528) is an all-metal, twin-turboprop research aircraft. The UC-12B aircraft is a military version of a Beechcraft B200 King Air. NASA Langley acquired this aircraft in 2007 from the U.S. Marine Corps. The aircraft has been modified with two nadir-viewing ports: 29.5 x 29.5-in. in the forward section of the passenger cabin and 26.75 x 22.5 in. in the aft section. These downward-looking portals allow the use of a wide variety of optical, laser, or R-F based devices that might require a nadir look angle out of the aircraft. Research-supporting subsystems, such as electrical power distribution, TCAS, GPS and satellite phone communications also have been installed. The UC-12B aircraft also has a cargo door in the aft left side of the passenger cabin that can accommodate payloads up to 51.5 in. wide. In past operations, the cargo door has allowed a forklift with a boom attachment to place large, heavy payloads directly into the aircraft cabin. In its current configuration, the aircraft serves as the primary flight platform for a suite of aerosol and cloud remote-sensing instruments, including the NASA Langley Doppler Aerosol Wind LIDAR (DAWN). The aircraft is fully IFR capable. 2017-07-18 21:33:23.0 [sritz] New Keyword requested by ASDC insert AltLabel (id: null category: primary text: NASA Langley Beechcraft UC-12B Huron language code: en); insert Definition (id: null text: The NASA Langley Beechcraft UC-12B Huron (NASA 528) is an all-metal, twin-turboprop research aircraft. The UC-12B aircraft is a military version of a Beechcraft B200 King Air. NASA Langley acquired this aircraft in 2007 from the U.S. Marine Corps. The aircraft has been modified with two nadir-viewing ports: 29.5 x 29.5-in. in the forward section of the passenger cabin and 26.75 x 22.5 in. in the aft section. These downward-looking portals allow the use of a wide variety of optical, laser, or R-F based devices that might require a nadir look angle out of the aircraft. Research-supporting subsystems, such as electrical power distribution, TCAS, GPS and satellite phone communications also have been installed. The UC-12B aircraft also has a cargo door in the aft left side of the passenger cabin that can accommodate payloads up to 51.5 in. wide. In past operations, the cargo door has allowed a forklift with a boom attachment to place large, heavy payloads directly into the aircraft cabin. In its current configuration, the aircraft serves as the primary flight platform for a suite of aerosol and cloud remote-sensing instruments, including the NASA Langley Doppler Aerosol Wind LIDAR (DAWN). The aircraft is fully IFR capable. language code: en); 2017-07-18 21:32:10.0 [sritz] Insert Concept add broader relation (UC-12B [18cb3d65-a7ab-4220-b7e3-38b98ce04ac7,309831] - Aircraft [227d9c3d-f631-402d-84ed-b8c5a562fc27,287509]); GOES-5 GOES 5 was launched in May 1981 and was a NASA-developed, NOAA-operated, geosynchronous, and operational spacecraft. The cylindrically shaped spacecraft measured 190.5 cm in diameter and 230 cm in length, exclusive of a magnetometer that extended an additional 83 cm beyond the cylinder shell. The primary structural members were a honeycombed equipment shelf and thrust tube. The VISSR telescope was mounted on the equipment shelf and viewed the Earth through a special aperture in the side of the spacecraft. A support structure extended radially out from the thrust tube and was affixed to the solar panels, which formed the outer walls of the spacecraft and provided the primary source of electrical power. Located in the annulus-shaped space between the thrust tube and the solar panels were stationkeeping and dynamics control equipment, batteries, and most of the SEM equipment. Proper spacecraft attitude and spin rate (approximately 100 rpm) were maintained by two separate sets of jet thrusters mounted around the spacecraft equator and activated by ground command. The spacecraft used both UHF-band and S-band frequencies in its telemetry and command subsystem. A low-power VHF transponder provided telemetry and command during launch and then served as a backup for the primary subsystem once the spacecraft attained orbit. The spin-stabilized spacecraft carried a visible infrared spin-scan radiometer atmospheric sounder, meteorological data collection and transmission system, space environment monitor, and a biaxial fluxgate magnetometer. It operated at at 75 degrees West as GOES-EAST, but on July 30, 1984, GOES 5 VAS experienced a failure, thus NOAA had to relocate GOES 6 to a more central 98 degrees West position, and to reactivate GOES 1 and GOES 4 for the acquisition and relay of VISSR information, respectively, from the western U.S. For more information on GOES satellites: http://www.ospo.noaa.gov/Operations/GOES/index.html 2017-09-01 17:05:32.0 [sritz] insert Definition (id: null text: GOES 5 was launched in May 1981 and was a NASA-developed, NOAA-operated, geosynchronous, and operational spacecraft. The cylindrically shaped spacecraft measured 190.5 cm in diameter and 230 cm in length, exclusive of a magnetometer that extended an additional 83 cm beyond the cylinder shell. The primary structural members were a honeycombed equipment shelf and thrust tube. The VISSR telescope was mounted on the equipment shelf and viewed the Earth through a special aperture in the side of the spacecraft. A support structure extended radially out from the thrust tube and was affixed to the solar panels, which formed the outer walls of the spacecraft and provided the primary source of electrical power. Located in the annulus-shaped space between the thrust tube and the solar panels were stationkeeping and dynamics control equipment, batteries, and most of the SEM equipment. Proper spacecraft attitude and spin rate (approximately 100 rpm) were maintained by two separate sets of jet thrusters mounted around the spacecraft equator and activated by ground command. The spacecraft used both UHF-band and S-band frequencies in its telemetry and command subsystem. A low-power VHF transponder provided telemetry and command during launch and then served as a backup for the primary subsystem once the spacecraft attained orbit. The spin-stabilized spacecraft carried a visible infrared spin-scan radiometer atmospheric sounder, meteorological data collection and transmission system, space environment monitor, and a biaxial fluxgate magnetometer. It operated at at 75 degrees West as GOES-EAST, but on July 30, 1984, GOES 5 VAS experienced a failure, thus NOAA had to relocate GOES 6 to a more central 98 degrees West position, and to reactivate GOES 1 and GOES 4 for the acquisition and relay of VISSR information, respectively, from the western U.S. For more information on GOES satellites: http://www.ospo.noaa.gov/Operations/GOES/index.html language code: en); 2017-09-01 16:45:17.0 [sritz] update PrefLabel (GOES-5); 2017-09-01 16:44:58.0 [sritz] Insert Concept add broader relation (GOEs-5 [18ceff7d-c5cd-4a72-86af-9a3ac0a884c4,310091] - GOES [6e332c25-caeb-4917-afb6-af757bcecd72,310071]); AIRBOAT C/NOFS The Communications/Navigation Outage Forecasting System (C/NOFS) is a prototype operational system designed to monitor and forecast ionospheric scintillation in real-time and on a global scale. Timely location of scintillation outage regions would enable the warfighter to modify mission plans and prevent potential mission failures by optimizing and tailoring communications routes, paths, and/or priorities and effectively use satellite communications, navigation, and surveillance assets. It will include three critical elements. The first is a space-borne sensor system consisting of seven proven sensors to provide data for global, real-time specification, and 4 hour forecast capability. The second is a series of regional ground networks that augment the space based sensors for real time, high resolution coverage in theater. The third is a forecasting/decision aid software package that produces tailored space environmental forecasts and warnings in the form of outage maps for the warfighter. Information provided by http://www.fas.org/spp/military/program/nssrm/initiatives/cnofs.htm Group: Platform_Details Entry_ID: C/NOFS Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Short_Name: C/NOFS Long_Name: Communication and Navigation Outage Forecast System End_Group Group: Synonymous_Platform_Names Short_Name: C/NOFS End_Group Group: Platform_Associated_Instruments Short_Name: GPS End_Group Group: Orbit Orbit_Type: MEO > Semi-Synchronous > Navigation End_Group Creation_Date: 2007-08-13 Online_Resource: http://www.fas.org/spp/military/program/nssrm/initiatives/cnofs.htm End_Group CYGNSS The CYGNSS mission will use eight micro-satellites to measure wind speeds over Earth's oceans, increasing the ability of scientists to understand and predict hurricanes. Each satellite will take information based on the signals from four GPS satellites. More information: https://www.nasa.gov/cygnss http://clasp-research.engin.umich.edu/missions/cygnss/ 2016-12-09 20:31:22.0 [sritz] insert Definition (id: null text: The CYGNSS mission will use eight micro-satellites to measure wind speeds over Earth's oceans, increasing the ability of scientists to understand and predict hurricanes. Each satellite will take information based on the signals from four GPS satellites. More information: https://www.nasa.gov/cygnss http://clasp-research.engin.umich.edu/missions/cygnss/ language code: en); 2016-12-09 20:29:13.0 [sritz] insert AltLabel (id: null text: Cyclone Global Navigation Satellite System language code: en); 2016-12-09 20:28:43.0 [sritz] Insert Concept add broader relation (CYGNSS [18fd52d4-c60c-4ef5-b39a-960ae9916472,278541] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,256549]); EO-1 Earth Observing 1 (NMP) EO-1 (EARTH OBSERVING 1) NMP [Mission completed 2017-03-30. Information for archival purposes.] Earth Observing-1 (EO-1) is an advanced land-imaging mission that will demonstrate new instruments and spacecraft systems. EO-1 will validate technologies contributing to the significant reduction in cost of follow-on Landsat missions. Launched on a Delta 7320 from Vandenberg Air Force Base, California, November 21, 2000. EO-1 has a 1-year primary mission but was designed to operate for an additional year. The NMP EO-1 mission includes three advanced land imaging instruments and five revolutionary cross cutting spacecraft technologies. The hyperspectral instrument is the first of its kind to provide images of land-surface in more than 220 spectral colors. The Hyperion will demonstrate the ability to perform detailed spectral mapping with high radiometric accuracy. In the future, an operational version of the Hyperion will allow complex land ecosystems to be imaged and accurately classified. The Advanced Land Imager (ALI) instrument yields almost four times better performance at only one-fourth the cost and weight of the Landsat ETM+. Finally the Linear Etalon Imaging Spectral Array/Atmospheric Corrector (LEISA/AC) is an infrared camera, which can be used to remove the effects of the atmosphere from surface pictures obtained by instruments such as the ALI on EO-1 and Landsat. This instrument will provide scientific return both in terms of improved imagery and hyperspectral sensing capabilities. It will also test a number of new technologies. Because the AC is small and adaptable to different spacecraft configurations, it is a bolt-on instrument, which can be attached to any future Earth imaging spacecraft. The three advanced imaging instruments will lead to a new generation of lighter weight, higher performance and lower cost Landsat-type Earth surface imaging instruments. Key EO-1 Facts: Orbit Type: Sun-synchronous Equatorial Crossing: 10:01 a.m. Altitude: 705 km Inclination: 98.2° Period: 98.8 minutes Repeat Cycle: 16 days Dimensions: 2 m height × 2.5 m diameter Mass: 529 kg Power: 300 W Design Life: 18 months; EO-1 is well beyond its planned mission life and is still functioning Downlink: X-Band (105 Mbps), Sioux Falls, Svalbard, Alaska, Hobart (Australia) Note: Part of the Morning Constellation of satellites, lags one minute behind Landsat 7 Contributors ALI: MIT/Lincoln Laboratory, NASA GSFC Hyperion: TRW, NASA GSFC LAC: NASA GSFC Applied Engineering and Technology Directorate (AETD) [Summary provided by NASA] More Information: https://eospso.nasa.gov/missions/earth-observing-1 Group: Platform_Details Entry_ID: EO-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: EO-1 Long_Name: Earth Observing 1 End_Group Group: Synonymous_Platform_Names Short_Name: New Millennium Program Earth Observing-1 (NMP EO-1) End_Group Group: Platform_Associated_Instruments Short_Name: LAC Short_Name: ALI Short_Name: HYPERION End_Group Group: Orbit Orbit_Altitude: 705 km Orbit_Inclination: 98.2° Equator_Crossing: 10:01 a.m. Period: 98.8 minutes Repeat_Cycle: 16 days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-02-06 Online_Resource: https://eospso.nasa.gov/missions/earth-observing-1 Online_Resource: https://eo1.gsfc.nasa.gov/ Group: Platform_Logistics Launch_Date: 2000-11-21 Launch_Site: Vandenberg Air Force Base, California Design_Life: 18 months Primary_Sponsor: NASA End_Group End_Group 2020-02-20 22:15:55.0 [sritz] update Definition ([Mission completed 2017-03-30. Information for archival purposes.] Earth Observing-1 (EO-1) is an advanced land-imaging mission that will demonstrate new instruments and spacecraft systems. EO-1 will validate technologies contributing to the significant reduction in cost of follow-on Landsat missions. Launched on a Delta 7320 from Vandenberg Air Force Base, California, November 21, 2000. EO-1 has a 1-year primary mission but was designed to operate for an additional year. The NMP EO-1 mission includes three advanced land imaging instruments and five revolutionary cross cutting spacecraft technologies. The hyperspectral instrument is the first of its kind to provide images of land-surface in more than 220 spectral colors. The Hyperion will demonstrate the ability to perform detailed spectral mapping with high radiometric accuracy. In the future, an operational version of the Hyperion will allow complex land ecosystems to be imaged and accurately classified. The Advanced Land Imager (ALI) instrument yields almost four times better performance at only one-fourth the cost and weight of the Landsat ETM+. Finally the Linear Etalon Imaging Spectral Array/Atmospheric Corrector (LEISA/AC) is an infrared camera, which can be used to remove the effects of the atmosphere from surface pictures obtained by instruments such as the ALI on EO-1 and Landsat. This instrument will provide scientific return both in terms of improved imagery and hyperspectral sensing capabilities. It will also test a number of new technologies. Because the AC is small and adaptable to different spacecraft configurations, it is a bolt-on instrument, which can be attached to any future Earth imaging spacecraft. The three advanced imaging instruments will lead to a new generation of lighter weight, higher performance and lower cost Landsat-type Earth surface imaging instruments. Key EO-1 Facts: Orbit Type: Sun-synchronous Equatorial Crossing: 10:01 a.m. Altitude: 705 km Inclination: 98.2° Period: 98.8 minutes Repeat Cycle: 16 days Dimensions: 2 m height × 2.5 m diameter Mass: 529 kg Power: 300 W Design Life: 18 months; EO-1 is well beyond its planned mission life and is still functioning Downlink: X-Band (105 Mbps), Sioux Falls, Svalbard, Alaska, Hobart (Australia) Note: Part of the Morning Constellation of satellites, lags one minute behind Landsat 7 Contributors ALI: MIT/Lincoln Laboratory, NASA GSFC Hyperion: TRW, NASA GSFC LAC: NASA GSFC Applied Engineering and Technology Directorate (AETD) [Summary provided by NASA] More Information: https://eospso.nasa.gov/missions/earth-observing-1 Group: Platform_Details Entry_ID: EO-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: EO-1 Long_Name: Earth Observing 1 End_Group Group: Synonymous_Platform_Names Short_Name: New Millennium Program Earth Observing-1 (NMP EO-1) End_Group Group: Platform_Associated_Instruments Short_Name: LAC Short_Name: ALI Short_Name: HYPERION End_Group Group: Orbit Orbit_Altitude: 705 km Orbit_Inclination: 98.2° Equator_Crossing: 10:01 a.m. Period: 98.8 minutes Repeat_Cycle: 16 days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-02-06 Online_Resource: https://eospso.nasa.gov/missions/earth-observing-1 Online_Resource: https://eo1.gsfc.nasa.gov/ Group: Platform_Logistics Launch_Date: 2000-11-21 Launch_Site: Vandenberg Air Force Base, California Design_Life: 18 months Primary_Sponsor: NASA End_Group End_Group); update Definition (https://eospso.nasa.gov/missions/earth-observing-1); 2020-02-20 22:09:58.0 [sritz] insert AltLabel (id: null category: null text: NMP language code: en); 2020-02-20 22:09:33.0 [sritz] delete Resource (null); 2018-04-24 20:26:40.0 [sritz] insert AltLabel (id: null category: null text: Earth Observing 1 (NMP) language code: en); update Resource (image); 2016-06-09 14:39:28.0 [epneff] added altLabel insert AltLabel (id: null text: EO-1 (EARTH OBSERVING 1) language code: en); NOAA-10 NOAA-10 (NATIONAL OCEANIC & ATMOSPHERIC ADMINISTRATION-10) NOAA-10 (ATN series) was launched on September 17, 1986 and is a third-generation operational meteorological satellite. The satellite design provides an economical and stable sun-synchronous platform. This platform enables the satellite to carry advanced operational instruments that measure the earth's atmosphere, its surface and cloud cover, and the near-space environment. The satellite is based upon the Block 5D spacecraft bus developed for the U.S. Air Force, and is capable of maintaining an earth-pointing accuracy of better than plus or minus 0.1 degree with a motion rate of less than 0.035 degree/second. Primary sensors include (1) an Advanced Very High Resolution Radiometer (AVHRR), (2) TIROS Operational Vertical Sounder (TOVS), (3) Earth Radiation Budget Experiment (ERBE), and (4) a Solar Backscatter Ultraviolet Spectrometer (SBUV/2). Secondary experiments consist of a Space Environment Monitor (SEM), and a Data Collection System (DCS). A Search and Rescue (SAR) system is also carried on NOAA-10. Orbital Characteristics- Orbital Period: 101.50 m Inclination: 98.59 degrees Eccentricity: 0.00256 Periapsis: 833.00 km Apoapsis: 870.00 km For more information about the NOAA POES satellite series link to the URL: "http://www.ncdc.noaa.gov/psguide/satellite/noaasat.html" To view a 3D orbit, observe the J track satellite tracking web page: "http://liftoff.msfc.nasa.gov/RealTime/JTrack/" ___________ Taken from the NSSDC System for Information Retrieval and Storage (SIRS). For more information contact the NSSDC Coordinated Request and User Support Office, 301-286-6695 (NASA Goddard Space Flight Center, Code 933.4, Greenbelt, Maryland 20771, USA, "http://nssdc.gsfc.nasa.gov/"). Group: Platform_Details Entry_ID: NOAA-10 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NOAA POES (Polar Orbiting Environmental Satellites) Short_Name: NOAA-10 Long_Name: National Oceanic & Atmospheric Administration-10 End_Group Group: Platform_Associated_Instruments Short_Name: SEM Short_Name: TOVS Short_Name: SBUV/2 Short_Name: ERBE Short_Name: AVHRR End_Group Group: Orbit Orbit_Inclination: 98.59 deg Period: 101.50 m Perigee: 833 km Apogee: 870 km End_Group Creation_Date: 2007-10-17 Online_Resource: http://www2.ncdc.noaa.gov/docs/podug/html/c1/sec1-46.htm Sample_Image: http://asd-www.larc.nasa.gov/erbe/noaasat.gif Group: Platform_Logistics Launch_Date: 1986-09-17 Primary_Sponsor: NASA End_Group End_Group 2016-06-09 17:12:21.0 [epneff] added altLabel insert AltLabel (id: null text: NOAA-10 (NATIONAL OCEANIC & ATMOSPHERIC ADMINISTRATION-10) language code: en); OSO (Orbiting Solar Observatory) ENTLN The Earth Networks Total Lightning Network (ENTLN) is an integrated in-cloud (IC) lightning and cloud-to-ground (CG) detection network deployed on a global basis capable of detecting long range in-cloud lightning at high efficiencies critical for the advanced prediction of severe weather phenomena. Group: Platform_Details Entry_ID: ENTLN Group: Platform_Identification Platform_Category: Aircraft Short_Name: ENTLN Long_Name: Earth Networks Total Lightning Network (ENTLN) End_Group Group: Platform_Associated_Instruments Short_Name: ENLS End_Group Creation_Date: 2014-01-23 End_Group 2014-01-23 16:12:38.0 [saritz] Added Primary Alternate Label and Definition. insert AltLabel (id: null text: Earth Networks Total Lightning Network (ENTLN) language code: en); insert Definition (id: null text: The Earth Networks Total Lightning Network (ENTLN) is an integrated in-cloud (IC) lightning and cloud-to-ground (CG) detection network deployed on a global basis capable of detecting long range in-cloud lightning at high efficiencies critical for the advanced prediction of severe weather phenomena. language code: en); 2014-01-23 16:11:11.0 [saritz] Insert Concept add broader relation (ENTLN [1ab2e0db-8911-434d-a6ba-3917730e83a6,106101] - WEATHER STATIONS/NETWORKS [57b7373d-5c21-4abb-8097-a410adc2a074,73471]); PML The Plymouth Marine Laboratory (PML) provides capability for observing, modelling, understanding and forecasting marine ecosystems, to underpin evidence-based environmental solutions to societal challenges. PML do so by applying world-leading, integrated, scientific understanding, focused on the interactions between the marine environment and society, in estuarine, coastal and shelf waters, as well as the upper layers of the global ocean. PML’s science is concerned with: - increasing knowledge and understanding of the marine environment and - designing tools and evidence based solutions for its practical management. Group: Platform_Details Entry_ID: PML Group: Platform_Identification Platform_Category: In Situ Land-based Platforms Short_Name: PML Long_Name: Plymouth Marine Laboratory End_Group Creation_Date: 2012-07-18 Online_Resource: www.pml.ac.uk/default.aspx End_Group CESM 2015-08-10 18:40:14.0 [epneff] Added long name insert AltLabel (id: null text: NCAR Community Earth System Model language code: en); 2015-08-10 18:39:48.0 [epneff] Insert Concept add broader relation (CESM [1b492235-f1fa-47d9-aae5-278812d29e7d,158211] - Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215]); SHIPS SHIP Ships: A vessel of considerable size for sailing and deep-water navigation. [Source: The American Heritage Dictionary of the English Language, Fourth Edition Copyright 2000 by Houghton Mifflin Company.] Group: Platform_Details Entry_ID: SHIPS Group: Platform_Identification Platform_Category: In Situ Ocean-based Platforms Platform_Series_or_Entity: SHIPS Short_Name: SHIPS End_Group Group: Synonymous_Platform_Names Short_Name: SHIPS End_Group Creation_Date: 2007-12-12 Online_Resource: http://en.wikipedia.org/wiki/Ship Sample_Image: http://www.nasa.gov/images/content/145634main_booster.jpg End_Group 2016-06-09 18:33:53.0 [epneff] added altLabel insert AltLabel (id: null text: SHIP language code: en); DE-2 The DE 2 spacecraft (low-altitude mission) complemented the high-altitude mission DE 1 and was placed into an orbit with a perigee sufficiently low to permit measurements of neutral composition, temperature, and wind. The apogee was high enough to permit measurements above the interaction regions of suprathermal ions, and also plasma flow measurements at the feet of the magnetospheric field lines. The general form of the spacecraft was a short polygon 137 cm in diameter and 115 cm high. The triaxial antennas were 23 m tip-to-tip. One 6-m boom was provided for remote measurements. The spacecraft weight was 403 kg. Power was supplied by a solar cell array, which charged two 6-ampere-hour nickel-cadmium batteries. The spacecraft was three-axis stabilized with the yaw axis aligned toward the center of the earth to within 1 deg. The spin axis was normal to the orbit plane within 1 deg with a spin rate of one revolution per orbit. A single-axis scan platform was included in order to mount the low-altitude plasma instrument (81-070B-08). The platform rotated about the spin axis. A pulse code modulation telemetry data system was used that operated in real time or in a tape-recorder mode. Data were acquired on a science-problem-oriented basis, with closely coordinated operations of the various instruments, both satellites, and supportive experiments. Measurements were temporarily stored on tape recorders before transmission at an 8:1 playback-to-record ratio. Since commands were also stored in a command memory unit, spacecraft operations were not real time. Group: Platform_Details Entry_ID: DE-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: DE (Dynamics Explorer) Short_Name: DE-2 Long_Name: Dynamics Explorer-2 End_Group Group: Synonymous_Platform_Names Short_Name: DE 2 Short_Name: DE-B Short_Name: Dynamics Explorer-B Short_Name: Explorer 63 Short_Name: 12625 End_Group Group: Platform_Associated_Instruments Short_Name: RPA Short_Name: VECTOR MAGNETOGRAPHS End_Group Group: Orbit Period: 98 min. End_Group Creation_Date: 2007-09-12 Online_Resource: http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1981-070Bdata.html Group: Platform_Logistics Launch_Date: 1981-08-03 Primary_Sponsor: NASA End_Group End_Group BT-67 The BT-67 is a world-class transport aircraft with an impressive resume of performance. Its robust airframe and state-of-the-art components stand ready to deliver a range of special mission capabilities that will provide unlimited opportunities. Group: Platform_Details Entry_ID: BT-67 Group: Platform_Identification Platform_Category: Aircraft Short_Name: BT-67 Long_Name: Basler BT-67 End_Group Creation_Date: 2012-07-23 Online_Resource: http://www.baslerturbo.com/bt_overview.aspx End_Group SEASAT 1 SEASAT-1 [Source NASA Space Science Data Center, http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1978-064A ] The Ocean Dynamics Satellite (Seasat 1) was designed to provide measurements of sea-surface winds, sea-surface temperatures, wave heights, internal waves, atmospheric liquid water content, sea ice features, ocean features, ocean topography, and the marine geoid. Seasat 1 provided 95% global coverage every 36 h. The instrument payload consisted of (1) an X-band compressed pulse radar altimeter (ALT), (2) a coherent synthetic aperture radar (SAR), (3) a Seasat-A scatterometer system (SASS), (4) a scanning multichannel microwave radiometer (SMMR), and (5) a visible and infrared radiometer (VIRR). The accuracies obtained were distance between spacecraft and ocean surface to 10 cm, wind speeds to 2 m/s, and surface temperatures to 1 deg C. For more information about Seasat 1, see "Seasat mission overview," Science, v. 204, pp. 1405-1424, 1979, and a special issue on the Seasat 1 sensors, IEEE J. of Oceanic Eng., v. OE-5, 1980. On October 10, 1978, Seasat 1 failed due to a massive short circuit in its electrical system. During most of its 105 days in orbit, Seasat 1 returned a unique and extensive set of observations of the earth's oceans. Group: Platform_Details Entry_ID: SEASAT 1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: SEASAT 1 Long_Name: Ocean Dynamics Satellite End_Group Group: Synonymous_Platform_Names Short_Name: Seasat-A Short_Name: 10967 End_Group Group: Platform_Associated_Instruments Short_Name: LT (SEASAT 1) Short_Name: VIRR Short_Name: SMMR Short_Name: SASS Short_Name: SAR Short_Name: ALT End_Group Group: Orbit Orbit_Inclination: 108.0° Period: 100.7 minutes Perigee: 769.0 km Apogee: 799.0 km End_Group Creation_Date: 2009-02-27 Online_Resource: http://southport.jpl.nasa.gov/scienceapps/seasat.html Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1978-064A Online_Resource: http://nasascience.nasa.gov/missions/seasat-1 Online_Resource: http://nsidc.org/data/docs/daac/seasat_platform.gd.html Group: Platform_Logistics Launch_Date: 1978-06-27 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: USA/NASA End_Group End_Group 2016-06-09 17:18:23.0 [epneff] added altLabel insert AltLabel (id: null text: SEASAT-1 language code: en); GEMINI-3 GEMINI 3 was the first manned Earth-orbiting spacecraft of the GEMINI series. Its primary objective was to demonstrate the manned qualifications of the GEMINI spacecraft. A synergistic effect of zero-g and radiation on white blood cells experiment, a sea urchin egg growth under zero-g experiment, and one technological experiment were conducted. Several of the photographs taken by the astronauts were later considered suitable for synoptic terrain studies. After 5 hours, the spacecraft successfully reentered the atmosphere and landed 60 n.m. (111 km) from the target area. Group: Platform_Details Entry_ID: GEMINI-3 Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Platform_Series_or_Entity: GEMINI Short_Name: GEMINI-3 End_Group Group: Synonymous_Platform_Names Short_Name: TITAN II (3) End_Group Group: Orbit Orbit_Inclination: 33 degrees Perigee: 160 km Apogee: 240 km End_Group Creation_Date: 2008-01-23 Online_Resource: http://science.ksc.nasa.gov/history/gemini/gemini-3/gemini-3.html Sample_Image: http://science.ksc.nasa.gov/history/gemini/gemini-3/gemini-3-patch-small.gif Group: Platform_Logistics Launch_Date: 1965-03-23 Primary_Sponsor: NASA End_Group End_Group R/V LMG [Adapted from "R/V Laurence M. Gould", "http://www.nsf.gov/od/opp/support/gould.htm"] The R/V Laurence M.Gould is 76 meters in length, and is ice-strengthened (Ice class ABS A1). The Gould, a multi-disciplinary research platform, is designed for year-round polar operations and can accomodate 26 research scientists for missions up to 75 days long. Its primary mission is to support research in the Antarctic Peninsula region and to resupply and transport researchers and staff between Palmer Station and South American ports. VOYAGER 1 Voyager 1 was one of a pair of spacecraft launched to explore the planets of the outer solar system and the interplanetary environment. Each Voyager had as its major objectives at each planet to: (1) investigate the circulation, dynamics, structure, and composition of the planet's atmosphere; (2) characterize the morphology, geology, and physical state of the satellites of the planet; (3) provide improved values for the mass, size, and shape of the planet, its satellites, and any rings; and, (4) determine the magnetic field structure and characterize the composition and distribution of energetic trapped particles and plasma therein. Originally planned as a Grand Tour of the outer planets, including dual launches to Jupiter, Saturn, and Pluto in 1976-77 and dual launches to Jupiter, Uranus, and Neptune in 1979, budgetary constraints caused a dramatic rescoping of the project to two spacecraft, each of which would go to only Jupiter and Saturn. The new mission was called Mariner Jupiter/Saturn, or MJS. It was subsequently renamed Voyager about six months prior to launch. The rescoped mission was estimated to cost $250 million (through the end of Saturn operations), only a third of what the Grand Tour design would have cost. Originally scheduled to launch twelve days after Voyager 2, Voyager 1's launch was delayed twice to prevent the occurrence of problems which Voyager 2 experienced after launch. Voyager 1's launch finally happened on 05 Sept. 1977 and was termed "flawless and accurate". Although launched sixteen days after Voyager 2, Voyager 1's trajectory was the quicker one to Jupiter. On 15 Dec. 1977, while both spacecraft were in the asteroid belt, Voyager 1 surpassed Voyager 2's distance from the Sun. Voyager 1 then proceeded to Jupiter (making its closest approach on 05 March 1979) and Saturn (with closest approach on 12 Nov. 1980). Both prior to and after planetary encounters observations were made of the interplanetary medium. Some 18,000 images of Jupiter and its satellites were taken by Voyager 1. In addition, roughly 16,000 images of Saturn, its rings and satellites were obtained. After its encounter with Saturn, Voyager 1 remained relatively quiescent, continuing to make in situ observations of the interplanetary environment and UV observations of stars. After nearly nine years of dormancy, Voyager 1's cameras were once again turned on to take a series of pictures. On 14 Feb. 1990, Voyager 1 looked back from whence it came and took the first "family portrait" of the solar system, a mosaic of 60 frames of the Sun and six of the planets (Venus, Earth, Jupiter, Saturn, Uranus, and Neptune) as seen from "outside" the solar system. After this final look back, the cameras on Voyager 1 were once again turned off. Group: Platform_Details Entry_ID: VOYAGER 1 Group: Platform_Identification Platform_Category: Interplanetary Spacecraft Platform_Series_or_Entity: FLYBY Short_Name: VOYAGER 1 End_Group Group: Synonymous_Platform_Names Short_Name: Mariner Jupiter/Saturn A Short_Name: 10321 Short_Name: 1977-084A End_Group Creation_Date: 2007-03-06 Online_Resource: http://www.nasa.gov/mission_pages/voyager/index.html Online_Resource: http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1977-084A Sample_Image: http://nssdc.gsfc.nasa.gov/image/spacecraft/voyager.jpg Group: Platform_Logistics Launch_Date: 1977-09-05 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: NASA End_Group End_Group FLYBY DMSP (Defense Meteorological Satellite Program) 2014-05-28 14:35:18.0 [128.183.164.42] Insert Concept add narrower relation (DMSP (Defense Meteorological Satellite Program) [1cf8cbcd-c1be-4c78-9272-b62adad59aa1,73429] - DMSP 5D-3/F19 [d1ad8ea7-b460-44b2-a96a-1040d156eeb4,106417]); 2014-05-28 14:35:01.0 [128.183.164.42] Remove Concepts delete narrower relation (null); 2014-05-28 14:34:22.0 [128.183.164.42] Insert Concept add narrower relation (DMSP (Defense Meteorological Satellite Program) [1cf8cbcd-c1be-4c78-9272-b62adad59aa1,73429] - DMSP 5D-3/F18 [66c23b2e-7a41-4b54-8cc8-fcaff3e90053,106413]); GEOSTAR GEophysical and Oceanographic STation for Abyssal Research. The Observatory (also named "Bottom Station") is a four-leg marine aluminium frame (overall dimension 3.50m x 3.50m x 3.30m) supporting all equipment and vessels constituting the scientific and operative payload. In the design of the station particular care is paid to ensure correct installation and positioning of the various sensors, taking into account their specific requirements and sensitivity to interferences, induced noise, correct alignment, etc. Group: Platform_Details Entry_ID: GEOSTAR Group: Platform_Identification Platform_Category: In Situ Ocean-based Platforms Platform_Series_or_Entity: OCEAN PLATFORM/OCEAN STATIONS Short_Name: GEOSTAR End_Group Group: Synonymous_Platform_Names Short_Name: GEophysical and Oceanographic STation for Abyssal Research End_Group Creation_Date: 2010-11-23 Online_Resource: http://roma2.rm.ingv.it/en/facilities/seafloor_multidisciplinary_observatories/1/geostar Sample_Image: http://roma2.rm.ingv.it/userfiles/image/risorse/OsservatoriSottomarini/GEOSTAR.jpg End_Group Swarm Swarm is the fifth Earth Explorer mission approved in ESA's Living Planet Programme, and was successfully launched on 22 November 2013. As part of the Third Party Missions programme, the e-POP instrument of the Canadian Space Agency's CASSIOPE mission joined the constellation in February 2018. The research objectives of the Swarm mission is to provide the best-ever survey of the geomagnetic field and its temporal evolution as well as the electric field in the atmosphere using a constellation of 3 identical satellites carrying sophisticated magnetometers and electric field instruments. 2019-07-25 08:54:12.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: 5e95a04f-e746-4b55-b0f0-76631bb197fe relationship type: null relationship value: null generated by: null); 2019-07-25 08:52:40.0 [mmorahan] insert Definition (id: null text: Swarm is the fifth Earth Explorer mission approved in ESA's Living Planet Programme, and was successfully launched on 22 November 2013. As part of the Third Party Missions programme, the e-POP instrument of the Canadian Space Agency's CASSIOPE mission joined the constellation in February 2018. The research objectives of the Swarm mission is to provide the best-ever survey of the geomagnetic field and its temporal evolution as well as the electric field in the atmosphere using a constellation of 3 identical satellites carrying sophisticated magnetometers and electric field instruments. language code: en); insert WeightedRelation (id: null related concept uuid: b7bc737c-15de-4b67-9bc3-5fa7c2b651d5 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 47d0c7c0-683c-42a9-b53b-53b684972b52 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 2380ecc6-b5ae-4ad8-a56a-9740166465aa relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: d1deab09-3edf-493b-a7ef-a3811b89e59d relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 03d748ff-7398-4ea8-87e7-38d0ef3e6167 relationship type: null relationship value: null generated by: null); 2018-06-13 12:07:25.0 [mmorahan] Insert Concept add narrower relation (Swarm [1d6d5f82-acd5-4bd2-9324-12884718b353,367695] - Swarm-C [769a52d4-7db1-4b8e-8d39-6fee4e74d34f,367707]); 2018-06-13 12:06:37.0 [mmorahan] Insert Concept add narrower relation (Swarm [1d6d5f82-acd5-4bd2-9324-12884718b353,367695] - Swarm-B [ab7f9a64-ca5d-4795-94ff-fd5367d39f9f,367703]); 2018-06-13 12:05:50.0 [mmorahan] Insert Concept add narrower relation (Swarm [1d6d5f82-acd5-4bd2-9324-12884718b353,367695] - Swarm-A [054787a6-0c47-43af-a4ee-05c572dd1705,367699]); 2018-06-13 12:02:46.0 [mmorahan] Insert Concept add broader relation (Swarm [1d6d5f82-acd5-4bd2-9324-12884718b353,367695] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761]); IRS-P5 The CARTOSAT-1 (IRS-P5) is envisaged as a mission to meet the stereo data requirements of the user community. The objectives of the mission are : -To design, develop, launch and operate an advanced space based mission with enhanced spatial resolution (2.5m) with along track stereo viewing capability for large scale mapping applications (up to 1:5000 scale) -To further stimulate newer areas of cartographic applications, urban management, disaster assessment, relief planning and management, environmental impact assessment and GIS applications. CARTOSAT-1 is a global mission. The nominal life of the mission is planned to be five years. The satellite was launched by the indigenously built Polar Satellite Launch Vehicle on May 05, 2005. [Summary provided by the Indian Remote Sensing Agency.] Group: Platform_Details Entry_ID: IRS-P5 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: IRS (Indian Remote Sensing Satellite) Short_Name: IRS-P5 Long_Name: Indian Remote Sensing Satellite-P5 (CARTOSAT-1) End_Group Group: Synonymous_Platform_Names Short_Name: CARTOSAT-1 End_Group Group: Platform_Associated_Instruments Short_Name: PAN Short_Name: CAMERAS Short_Name: CCD IMAGER End_Group Group: Orbit Orbit_Altitude: 618 km Orbit_Inclination: 97.87 degrees Equator_Crossing: 10:30 A.M Period: 97 minutes Repeat_Cycle: 5 days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2008-08-12 Online_Resource: http://www.nrsa.gov.in/satellites/irs-p5.html Sample_Image: http://www.skyrocket.de/space/img_sat/irs-p5__1.jpg Group: Platform_Logistics Launch_Date: 2005-05-05 Launch_Site: Sriharikota Island, India Design_Life: 5 Years Primary_Sponsor: India End_Group End_Group LUNOKHOD Luna 17 was launched from an earth parking orbit towards the Moon and entered lunar orbit on November 15, 1970. The spacecraft soft landed on the Moon in the Sea of Rains. The spacecraft had dual ramps by which the payload, Lunokhod 1, descended to the lunar surface. Lunokhod 1 was a lunar vehicle formed of a tub-like compartment with a large convex lid on eight independently powered wheels. Lunokhod was equipped with a cone-shaped antenna, a highly directional helical antenna, four television cameras, and special extendable devices to impact the lunar soil for soil density and mechanical property tests. An x-ray spectrometer, an x-ray telescope, cosmic-ray detectors, and a laser device were also included. The vehicle was powered by a solar cell array mounted on the underside of the lid. Lunokhod was intended to operate through three lunar days but actually operated for eleven lunar days. The operations of Lunokhod officially ceased on October 4, 1971, the anniversary of Sputnik 1. Lunokhod had traveled 10,540 m and had transmitted more than 20,000 TV pictures and more than 200 TV panoramas. It had also conducted more than 500 lunar soil tests. Group: Platform_Details Entry_ID: LUNOKHOD Group: Platform_Identification Platform_Category: Interplanetary Spacecraft Short_Name: LUNOKHOD Long_Name: Lunar Retroreflector Array End_Group Group: Synonymous_Platform_Names Short_Name: Luna 17 Short_Name: Lunik 17 Short_Name: Lunokhod 1 Short_Name: 04691 End_Group Creation_Date: 2012-07-18 Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1970-095A Sample_Image: http://nssdc.gsfc.nasa.gov/thumbnail/spacecraft/luna17.gif Group: Platform_Logistics Launch_Date: 1970-11-10 Launch_Site: Baikonur Cosmodrome, Tyuratam, Russia Primary_Sponsor: U.S.S.R End_Group End_Group ESSA-9 TOS-G The ESSA-9 satellite replaced ESSA-7 and provided cloud-cover photography to the US's National Meteorological Center for the purpose of preparing operational weather analyses and forecasts. The spacecraft was an 18-sided polygon, 42 inches in diameter, 22 inches high and weighed 320 pounds. The craft was made of aluminum alloy and stainless steel then covered with 10,020 solar cells. The solar cells served to charge the 63 nickel-cadmium batteries. The two cameras were mounted 180-degrees opposite each other along the side of the cylindrical craft. The "cartwheel" configuration of the TIROS-9 was selected as the orbital configuration of the operational series of ESSA satellites. Therefore, a camera could be pointed at some point on Earth every time the satellite rotated along its axis. The spacecraft operating system was the same as on the TIROS-9. The craft was placed in its planned Sun-synchronous 102-degree inclination retrograde orbit. The satellite spin axis was rotated using the magnetic attitude control system into an alignment perpendicular to the orbital plane and tangent to the Earth's surface. The ESSA-7 system transmitted images covering 2000-square mile areas with 2-mile resolution from every location once per day. Two arrays of radiometer sensors were also mounted 180-degrees apart to measure the global distribution of solar radiation reflected by the Earth and the Earth's atmosphere, as well as the long wave emissions from the Earth (a contribution from the NIMBUS program). ESSA-9 stats: Launch Date: February 26, 1969 Operational Period: 1,726 days until deactivated by NASA on November 15, 1972 Launch Vehicle: Three stage, thrust augmented, improved Delta Launch Site: Cape Canaveral, FL Type: Weather Satellite Top of Page | Back to Missions Phase: Past Full Name: Environmental Science Services Administration Satellite Program Launch Date: February 03, 1966 2018-11-14 15:40:55.0 [sritz] insert AltLabel (id: null category: null text: TOS-G language code: en); 2018-11-14 15:40:23.0 [sritz] insert AltLabel (id: null category: primary text: Environmental Science Services Administration Satellite 9 language code: en); 2018-10-30 17:05:27.0 [sritz] insert Definition (id: null text: The ESSA-9 satellite replaced ESSA-7 and provided cloud-cover photography to the US's National Meteorological Center for the purpose of preparing operational weather analyses and forecasts. The spacecraft was an 18-sided polygon, 42 inches in diameter, 22 inches high and weighed 320 pounds. The craft was made of aluminum alloy and stainless steel then covered with 10,020 solar cells. The solar cells served to charge the 63 nickel-cadmium batteries. The two cameras were mounted 180-degrees opposite each other along the side of the cylindrical craft. The "cartwheel" configuration of the TIROS-9 was selected as the orbital configuration of the operational series of ESSA satellites. Therefore, a camera could be pointed at some point on Earth every time the satellite rotated along its axis. The spacecraft operating system was the same as on the TIROS-9. The craft was placed in its planned Sun-synchronous 102-degree inclination retrograde orbit. The satellite spin axis was rotated using the magnetic attitude control system into an alignment perpendicular to the orbital plane and tangent to the Earth's surface. The ESSA-7 system transmitted images covering 2000-square mile areas with 2-mile resolution from every location once per day. Two arrays of radiometer sensors were also mounted 180-degrees apart to measure the global distribution of solar radiation reflected by the Earth and the Earth's atmosphere, as well as the long wave emissions from the Earth (a contribution from the NIMBUS program). ESSA-9 stats: Launch Date: February 26, 1969 Operational Period: 1,726 days until deactivated by NASA on November 15, 1972 Launch Vehicle: Three stage, thrust augmented, improved Delta Launch Site: Cape Canaveral, FL Type: Weather Satellite Top of Page | Back to Missions Phase: Past Full Name: Environmental Science Services Administration Satellite Program Launch Date: February 03, 1966 language code: en); 2018-10-30 15:45:36.0 [sritz] Insert Concept add broader relation (ESSA-9 [1dc828a8-8502-479d-b7c4-d5139c06029a,368211] - ESSA [65cb3e7c-d4d8-46df-a5fc-aec63e58e8df,345109]); NigeriaSat-2 The Disaster Monitoring Constellation (DMC) is an international programme initially proposed in 1996 and led by SSTL (Surrey Satellite Technology Ltd) from the United Kingdom, to construct a network of five affordable Low Earth Orbit (LEO) microsatellites. The objective is to provide a daily global imaging capability at medium resolution (30-40 m), in 3-4 spectral bands, for rapid-response disaster monitoring and mitigation. 2019-05-02 15:49:13.0 [mmorahan] insert Definition (id: null text: The Disaster Monitoring Constellation (DMC) is an international programme initially proposed in 1996 and led by SSTL (Surrey Satellite Technology Ltd) from the United Kingdom, to construct a network of five affordable Low Earth Orbit (LEO) microsatellites. The objective is to provide a daily global imaging capability at medium resolution (30-40 m), in 3-4 spectral bands, for rapid-response disaster monitoring and mitigation. language code: en); 2019-05-02 15:45:03.0 [mmorahan] Insert Concept add broader relation (NigeriaSat-2 [1dda5116-4079-445e-ae1c-614e49879cf3,368741] - DMC-2G (Disaster Monitoring Constellation- 2nd Generation) [e5184d15-eec8-4703-8318-243748ddbd0e,368737]); DC-6 The Douglas DC-6 was one of the first airplanes to fly a regularly scheduled around-the-world route. With its higher performance, increased accommodation, greater payload and pressurized cabin, it was a natural evolution of the DC-4. Although the DC-6 had the same wingspan as the DC-4, its engines helped it fly 90 mph faster than the DC-4, carry 3,000 pounds more payload and fly 850 miles farther. The DC-6 could maintain the cabin pressure of 5,000 feet while flying at 20,000 feet. American Airlines and United Airlines ordered the commercial DC-6 in 1946, and Pan American Airways used the DC-6 to start tourist-class service across the North Atlantic. The 29th DC-6 was ordered by the Air Force, adapted as the presidential aircraft and designated the VC-118. It was delivered on July 1, 1947, and called The Independence after President Harry Truman's hometown, Independence, Mo. The larger, all-cargo DC-6A first flew Sept. 29, 1949; the larger capacity DC-6B, which could seat up 102 people, first flew Feb. 10, 1951. After the Korean War broke out in 1951, the military ordered DC-6As modified as either C-118A "Liftmaster" personnel carriers, as the Navy's R6D transports or as MC-118As for aeromedical evacuation. Between 1947 and 1959, Douglas built a total of 704 DC-6s, 167 of them military versions. By 1998, the DC-6 was still flying with smaller airlines around the world. Group: Platform_Details Entry_ID: DC-6 Group: Platform_Identification Platform_Category: Aircraft Short_Name: DC-6 Long_Name: Douglas DC-6 End_Group Creation_Date: 2012-07-18 Online_Resource: http://www.boeing.com/history/mdc/dc-6.htm Sample_Image: http://www.boeing.com/history/mdc/images/D4E-535482_n.jpg Group: Platform_Logistics Launch_Date: 1946-02-15 Primary_Sponsor: Boeing End_Group End_Group AUVS Self powered systems designed for oceanographic research that operate without a physical connection to the surface. These platforms use extremley modest energy requirements using changes in buoyancy for thrust coupled with a stable, low-drag, hydrodynamic shape. For further description see "http://marine.rutgers.edu/cool/glider/webpage/tutorialGlider.html". Group: Platform_Details Entry_ID: AUVS Group: Platform_Identification Platform_Category: In Situ Ocean-based Platforms Short_Name: AUVS Long_Name: Autonomous Underwater Vehicles End_Group Group: Synonymous_Platform_Names Short_Name: AUVS End_Group Creation_Date: 2007-12-13 Online_Resource: http://marine.rutgers.edu/cool/glider/webpage/tutorialGlider.html Sample_Image: http://www.bluefinrobotics.com/images/isovan/AUVs-in-Container_500.jpg End_Group GEMINI Gemini (GPS-based Orbit Estimation and Laser Metrology for Intersatellite Navigation) is a technology mission, proposed by DLR?s German Space Operations Center (GSOC), Astrium GmbH, and Vectronic Aerospace GmbH. aiming The major Gemini mission objective is the controlled establishment of a satellite formation in a low-Earth orbit. To that end, advanced in-orbit technologies will be demonstrated based on laser metrology, as well as innovative GPS-based approaches to relative navigation. As part of its technological objectives, the Gemini formation control will entirely be based on an autonomous orbit control approach. Secondary mission objectives concern the separation concept from the launcher, the drift stop and the development of a controlled formation acquisition strategy. As a technology demonstration mission, emphasis is given to an independent verification of the relative distance by means of a laser radar sensor. To allow a formation flying demonstration for a wide ran ge of applications, the technologies for the control of the relative distance cover both the regime of close and wide formations ranging from several hundreds of meters up to 100 km. In contrast to the relaxed orbit control requirements of nowadays formations, Gemini aims at a relative position keeping of several cm to several meters, that is expected to be of significance for many of the upcoming formation flying missions and, in addition, paves the way for even more advanced requirements, such as for SMART 2. To achieve that level of control accuracy, the Gemini sensors have to provide relative position measurements in the range of millimeters or better, that may not be achievable solely using a spaceborne GPS receiver. METEOSAT-8 2013-12-13 20:30:24.0 [saritz] Insert Concept add broader relation (METEOSAT-8 [1ef73a04-e012-4389-9646-cdeb7c04dc92,106025] - METEOSAT [28eac19a-5500-4a21-af30-ab7a364ff8d0,73589]); GRO The Compton Gamma Ray Observatory (GRO) was the second of NASA's Great Observatories. Compton, at 17 tons, was the heaviest astrophysical payload ever flown at the time of its launch on April 5, 1991 aboard the space shuttle Atlantis. Compton was safely deorbited and re-entered the Earth's atmosphere on June 4, 2000. The objective of the Compton GRO was to make comprehensive observations of gamma ray sources throughout the Universe. The observatory carried four scientific instruments that made gamma ray energy measurements from 0.1 million electron volts to 30,000 million electron volts. The end of life was in June 2000. The failure of 1 gyroscope requires the deorbitation of the satellite in order to make sure it will not fall in a populated area. It is too large to completely burn in the atmosphere. Specifications: Prime contractor: TRW Dimension: 7.7 x 5.5 x 4.6 m Mass at launch: 15622 kg Dry mass: 13800 kg Solar array: 21.5 m Stabilization: 3-axis DC power: EOL: 3980 W Design lifetime: 2 years (min) Additional information available at "http://cossc.gsfc.nasa.gov/" [Summary provided by NASA and The Satellite Encyclopedia] Group: Platform_Details Entry_ID: GRO Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Short_Name: GRO Long_Name: Gamma-Ray Observatory End_Group Group: Synonymous_Platform_Names Short_Name: CGRO Short_Name: GRO Short_Name: 1991-027B Short_Name: 20225 End_Group Group: Platform_Associated_Instruments Short_Name: BATSE End_Group Group: Orbit Orbit_Inclination: 28.5 degrees Period: 90 m Perigee: 362 km Apogee: 457 km Orbit_Type: LEO > Low Earth Orbit > Inclined Non-Polar End_Group Online_Resource: http://cossc.gsfc.nasa.gov/docs/cgro/index.html Sample_Image: http://nssdc.gsfc.nasa.gov/image/spacecraft/cgro.jpg Group: Platform_Logistics Launch_Date: 1991-04-05 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: NASA End_Group End_Group ODIN ODIN is a Swedish small satellite project for Astronomical and Atmospheric Research. The Aeronomy research will address scientific problem areas in the stratosphere and mesosphere by making measurements of various trace species. The scientific goals can be summarized as follows: 1. Stratospheric ozone science: To elucidate the geographical extent of and mechanisms responsible for ozone depletion in the "ozone hole" region and to study dilution effects and possible heterogeneous chemistry even outside of the polar regions due to sulphate aerosols 2. Mesospheric ozone science: To establish the relative role of odd hydrogen chemistry and the effects of ordered and turbulent transport and corpuscular radiation. 3. Summer mesospheric science: To establish the variability of mesospheric water vapor including an assessment of the required fluxes for aerosol formation in the polar mesosphere. 4. Coupling of atmospheric regions: To study some of the mechanisms that provide coupling between the upper and lower atmosphere, eg downward transport of aurorally enhanced NO with its effects on ozone photo chemistry and the vertical exchange of minor species such as odd oxygen, CO and H2O. Odin will work in unexplored bands of the electromagnetic spectrum, around wavelengths of 0.5 mm and 3 mm. These contain emission lines from important molecules such as water vapor, molecular oxygen, ozone and carbon monoxide. The lines will be used as tools to study processes in the Earth's atmosphere and in astronomical objects. Complementary information on the atmosphere will come from spectral lines at ultraviolet and optical wavelengths. Major scientific issues relate to star formation processes interstellar chemistry and atmospheric ozone balance. Additional information available at http://www.ssc.se/ssd/ssat/odin.html [Summary provided by Swedish Space Corporation] 2019-02-22 13:35:47.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: 598b6dc4-aff0-4e14-b7b7-039e58560dd0 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: c143ee20-1d14-4003-9043-f028c19f0265 relationship type: null relationship value: null generated by: null); GEOMAGNETIC STATIONS Stations that make geomegnetic observations (observations on the Earth's magnetism). ARWS Automatic Weather Stations provide a continuous stream of high-quality data over a great range of meteorological and hydrological parameters. Basic sensors measure wind velocity and direction, air pressure, temperature, relative humidity and precipitation. Other measurements available on some stations include multilevel soil temperature, soil moisture, solar radiation, net radiation, water level and temperature. [Source: National Weather Service] MIR-PRIRODA The Russian space station MIR was launched in 1986, providing opportunities in many scientific areas. Planning for an environmental remote sensing module began in the mid-1980's which was later called PRIRODA (Russian for "Nature"). The PRIRODA module was launched from Baykonur Cosmodrome, Kazakhstan aboard a Proton-K rocket on April 23, 1996. The PRIRODA module docked with the MIR space station on April 26, 1996. The PRIRODA module consists of a passive microwave package (IKAR) consisting of 3 instuments: IKAR-N, IKAR-D, and IKAR-P; an active microwave Synthetic Aperture Radar (SAR); and the following optical instruments: an infrared ISTOK-1 from Russia, Czechia, MOS-A and MOSD-B imaging radiometers from Germany, MOMS-2P high resolution multispectral ans stereo scanner from Germany, MSU-SK and MSU-E multispectral scanners from Russia, a TV-camera, and an OZONE-M ozone profiler. The PRIRODA mission is conducted by the Russian Space Agency (RKA), the Institute for Radioelectronics of the Russian Acadamy of Sciences, and RKK ENERGIA. International participants include Belorussia, Bulgaria, France, Germany, Italy, Poland, Russia, Switzerland, Ukraine, and USA. Group: Platform_Details Entry_ID: MIR-PRIRODA Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Short_Name: MIR-PRIRODA Long_Name: PRIRODA Module of MIR Space Station End_Group Group: Synonymous_Platform_Names Short_Name: mir-priroda End_Group Creation_Date: 2008-01-31 Online_Resource: http://www.astronautix.com/craft/priroda.htm Group: Platform_Logistics Launch_Date: 1996-04-23 Primary_Sponsor: Russia End_Group End_Group AC-500S The Rockwell Aero Commander (AC-500S) is a versatile and stable high-winged twin piston-engine aircraft that is suitable for a variety of missions. Standard configuration allows for mission equipment and two pilots. However, with the scientific packages removed, seating for five additional passengers may be installed. NOAA's two aero commanders are utilized primarily as aerial survey platforms for visual verification of aeronautical charts, high-resolution aerial photography, and snow water equivalent and soil moisture content measurements. Additionally, the aircraft has been used in biological investigations, such as algal bloom measurements and sea turtle population assessments, and post-hurricane and severe flood damage assessment photography. [Photo and Text provided by NOAA's Aircraft Operations Center (AOC) home page, http://www.aoc.noaa.gov/aircraft_rockwell.htm ] Group: Platform_Details Entry_ID: AC-500S Group: Platform_Identification Platform_Category: Aircraft Short_Name: AC-500S Long_Name: Rockwell Aero Commander AC-500S End_Group Creation_Date: 2008-07-15 Online_Resource: http://www.aoc.noaa.gov/aircraft_rockwell.htm Sample_Image: http://www.aoc.noaa.gov/images/Shrike-Overwater3.jpg End_Group HCMM The Heat Capacity Mapping Mission (HCMM) spacecraft was the first of a series of Applications Explorer Missions (AEM). The objective of the HCMM was to provide comprehensive, accurate, high-spatial-resolution thermal surveys of the surface of the earth. The HCMM spacecraft was made of two distinct modules: (1) an instrument module, containing the heat capacity mapping radiometer and its supporting gear, and (2) a base module, containing the data handling, power, communications, command, and attitude control subsystems required to support the instrument module. The spacecraft was spin stabilized at a rate of 14 rpm. The HCMM circular sun-synchronous orbit allowed the spacecraft to sense surface temperatures near the maximum and minimum of the diurnal cycle. The orbit had a daylight ascending node with nominal equatorial crossing time of 2:00 p.m. Since there was no inclination adjustment capacity, the spacecraft drifted from this crossing time by about 1 hour earlier per year. There was no on-board data storage capability, so only real-time data were transmitted when the satellite came within reception range of seven ground stations. The repeat cycle of the spacecraft was 16 days. Day/night coverage over a given area between the latitudes of 85 deg N and 85 deg S occurred at intervals ranging from 12 to 36 h (once every 16 days). During February 21-23, 1980, the HCMM orbital altitude was lowered from 620 km to 540 km to stop the drift of the orbit plane to unfavorable sun angles which in turn reduced the power collection capability of the solar panels. The operations of the spacecraft were terminated on September 30, 1980. More detailed information can be found in the &#039;Heat Capacity Mapping Mission Users&#039; Guide&#039; (TRF B30282), available from NSSDC. __________ Taken from the NSSDC System for Information Retrieval and Storage (SIRS). For more information contact the NSSDC Coordinated Request and User Support Office, 301-286-6695 (NASA Goddard Space Flight Center, Code 933.4, Greenbelt, Maryland 20771, USA) Group: Platform_Details Entry_ID: HCMM Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: HCMM Long_Name: Heat Capacity Mapping Mission End_Group Group: Synonymous_Platform_Names Short_Name: HCMM Short_Name: AEM-A Short_Name: Explorer 58 Short_Name: 10818 End_Group Group: Orbit Orbit_Inclination: 97.6 degrees Period: 96.67 min Perigee: 560 km Apogee: 641 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-11-19 Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/masterCatalog.do?sc=1978-041A Sample_Image: http://www.daviddarling.info/images/HCMM.jpg Group: Platform_Logistics Launch_Date: 1978-04-26 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: NASA End_Group End_Group Meteor-M N2 Meteorological Satellite Meteor-M N2 Group: Platform_Details Entry_ID: Meteor-M N2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: Meteor-M N2 Long_Name: Meteorological Satellite Meteor-M N2 End_Group Group: Platform_Associated_Instruments Short_Name: MTVZA Short_Name: MSU-MR Short_Name: KMSS Short_Name: IKFS Short_Name: GGAK-M Short_Name: BRLK Short_Name: DCS End_Group Group: Orbit Orbit_Altitude: 835 km Orbit_Inclination: 98.8 degrees Equator_Crossing: 9:30 a.m. Local time: e.g. Period: 101 minutes Orbit_Type: LEO > LOW EARTH ORBIT > POLAR SUN-SYNCHRONOUS End_Group Creation_Date: 2015-01-26 Online_Resource: http://www.federalspace.ru/20746/ Online_Resource: http://www.vniiem.ru/ru/index.php?option=com_content&view=article&id=610:-l-r-2-2-1-2-2&catid=82:--l-3r&Itemid=62 Online_Resource: https://directory.eoportal.org/documents/163813/1637389/MeteorM2_AutoB.jpeg Sample_Image: http://www.federalspace.ru/media/img/site/2014/image003.jpg Group: Platform_Logistics Launch_Date: 2014-07-08 Design_Life: 5 years End_Group End_Group 2015-08-03 12:33:51.0 [mpmorahan] insert AltLabel (id: null text: Meteorological Satellite Meteor-M N2 language code: en); 2015-08-03 12:07:10.0 [mpmorahan] Insert Concept add broader relation (Meteor-M N2 [20e6f8e4-f60d-4ffb-ab85-0423c5078a52,158111] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,143415]); Balloons/Rockets Balloons : a nonporous bag of light material that can be inflated especially with air or gas. A bag that is filled with heated air or a gas lighter than air so as to rise and float in the atmosphere and that usually carries a suspended load (as a gondola with passengers). Rockets: A jet engine that operates on the same principle as the firework rocket, consists essentially of a combustion chamber and an exhaust nozzle, carries either liquid or solid propellants which provide the fuel and oxygen needed for combustion and thus make the engine independent of the oxygen of the air, and is used especially for the propulsion of a missile (as a bomb or shell) or a vehicle (as an airplane). A rocket-propelled bomb, missile, projectile, or vehicle. Group: Platform_Details Entry_ID: Balloons/Rockets Group: Platform_Identification Platform_Category: Balloons/Rockets Short_Name: Balloons/Rockets End_Group End_Group 2019-09-06 12:43:40.0 [tstevens] update Definition (Balloons : a nonporous bag of light material that can be inflated especially with air or gas. A bag that is filled with heated air or a gas lighter than air so as to rise and float in the atmosphere and that usually carries a suspended load (as a gondola with passengers). Rockets: A jet engine that operates on the same principle as the firework rocket, consists essentially of a combustion chamber and an exhaust nozzle, carries either liquid or solid propellants which provide the fuel and oxygen needed for combustion and thus make the engine independent of the oxygen of the air, and is used especially for the propulsion of a missile (as a bomb or shell) or a vehicle (as an airplane). A rocket-propelled bomb, missile, projectile, or vehicle. Group: Platform_Details Entry_ID: Balloons/Rockets Group: Platform_Identification Platform_Category: Balloons/Rockets Short_Name: Balloons/Rockets End_Group End_Group); 2015-12-01 20:41:51.0 [gee-cee] Insert Concept add narrower relation (Balloons/Rockets [2196cc92-a5da-4233-9509-5523385da1d7,143329] - Titan IIID [a044e8ff-8225-4bba-85c4-80ea394e007b,158535]); 2015-12-01 20:41:40.0 [gee-cee] Insert Concept add narrower relation (Balloons/Rockets [2196cc92-a5da-4233-9509-5523385da1d7,143329] - Titan 34D [9e9e86b0-d613-4069-abe2-8291a6fac3ef,158531]); VENERA-13 VENERA Mission Description: Venera 13 and 14 were identical spacecraft built to take advantage of the 1981 Venus launch opportunity and launched 5 days apart. The Venera 13 mission consisted of a bus (81-106A) and an attached descent craft (81-106D). The Venera 13 descent craft/lander was a hermetically sealed pressure vessel, which contained most of the instrumentation and electronics, mounted on a ring-shaped landing platform and topped by an antenna. The design was similar to the earlier Venera 9-12 landers. It carried instruments to take chemical and isotopic measurements, monitor the spectrum of scattered sunlight, and record electric discharges during its descent phase through the Venusian atmosphere. The spacecraft utilized a camera system, an X-ray fluorescence spectrometer, a screw drill and surface sampler, a dynamic penetrometer, and a seismometer to conduct investigations on the surface. After launch and a four month cruise to Venus, the descent vehicle separated from the bus and plunged into the Venus atmosphere on 1 March 1982. After entering the atmosphere a parachute was deployed. At an altitude of 47 km the parachute was released and simple airbraking was used the rest of the way to the surface. Venera 13 landed about 950 km northeast of Venera 14 at 7 deg 30 min S, 303 E, just east of the eastern extension of an elevated region known as Phoebe Regio. The area was composed of bedrock outcrops surrounded by dark, fine-grained soil. After landing an imaging panorama was started and a mechanical drilling arm reached to the surface and obtained a sample, which was deposited in a hermetically sealed chamber, maintained at 30 degrees C and a pressure of about .05 atmospheres. The composition of the sample determined by the X-ray flourescence spectrometer put it in the class of weakly differentiated melanocratic alkaline gabbroids. The lander survived for 127 ! minutes (the planned design life was 32 minutes) in an environment with a temperature of 457 degrees C and a pressure of 84 Earth atmospheres. The descent vehicle transmitted data to the bus, which acted as a data relay as it flew by Venus. More info at http://nssdc.gsfc.nasa.gov/imgcat/html/mission_page/VN_Venera_13_Lander_page1.html [Source: NASA] Group: Platform_Details Entry_ID: VENERA-13 Group: Platform_Identification Platform_Category: Interplanetary Spacecraft Platform_Series_or_Entity: LANDER Short_Name: VENERA-13 End_Group Group: Synonymous_Platform_Names Short_Name: VENERA 13 End_Group Group: Platform_Associated_Instruments Short_Name: FLUORESCENCE SPECTROSCOPY End_Group Creation_Date: 2007-12-13 Online_Resource: http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/venera1314.html Sample_Image: http://nssdc.gsfc.nasa.gov/imgcat/midres/v13_vg261_262.gif Group: Platform_Logistics Launch_Date: 1981-10-30 Launch_Site: Baikonur Cosmodrome, Tyuratam, Russia Primary_Sponsor: Russia End_Group End_Group FIXED OBSERVATION STATIONS Fixed Observation Stations: A fixed, somewhat permanent point from which measurements or surveys are made. [Source: The American Heritage? Dictionary of the English Language, Fourth Edition Copyright ? 2000 by Houghton Mifflin Company.] QZSS (Japan's Quasi-Zenith Satellite System) QZSS is a three-satellite regional positioning and time transfer system and satellite-based augmentation system for GPS receivable within Japan. 2017-08-15 13:43:15.0 [tstevens] insert Definition (id: null text: QZSS is a three-satellite regional positioning and time transfer system and satellite-based augmentation system for GPS receivable within Japan. language code: en); 2017-08-15 11:34:59.0 [tstevens] update PrefLabel (QZSS (Japan's Quasi-Zenith Satellite System)); 2017-08-14 19:23:01.0 [tstevens] Insert Concept add narrower relation (QZSS (Japan’s Quasi-Zenith Satellite System) [225fb800-22b1-4d06-88ac-2bb391ac0906,309911] - QZSS [9f9d2fac-92f3-4bc5-80ea-e68da85dd352,309915]); 2017-08-14 19:22:50.0 [tstevens] Insert Concept add broader relation (QZSS (Japan’s Quasi-Zenith Satellite System) [225fb800-22b1-4d06-88ac-2bb391ac0906,309911] - Navigation Platforms [1506fb17-7ac4-44ce-bde5-074885bdb2d2,287403]); Aircraft 2019-10-07 16:49:50.0 [sritz] Insert Concept add narrower relation (Aircraft [227d9c3d-f631-402d-84ed-b8c5a562fc27,344663] - G-LiHT [f4dbe34b-a93e-439f-bdbb-4167c833aba6,369229]); 2018-05-23 15:35:22.0 [sritz] Insert Concept add narrower relation (Aircraft [227d9c3d-f631-402d-84ed-b8c5a562fc27,344663] - NSF/NCAR GV HIAPER [879d697c-381f-45df-a48d-2d9095bc5c54,367611]); 2018-01-05 19:55:16.0 [sritz] Insert Concept add narrower relation (Aircraft [227d9c3d-f631-402d-84ed-b8c5a562fc27,287509] - AS355-F2 [770c3b12-d083-4df9-8b36-27a4786794bb,310519]); 2018-01-05 19:54:59.0 [sritz] Insert Concept add narrower relation (Aircraft [227d9c3d-f631-402d-84ed-b8c5a562fc27,287509] - AS350-B2 [50ce4651-516f-4b05-a5e0-864617ec26eb,310515]); 2018-01-05 19:54:46.0 [sritz] Insert Concept add narrower relation (Aircraft [227d9c3d-f631-402d-84ed-b8c5a562fc27,287509] - AS350-B3 [ad1d4887-ac0d-43a0-9e9b-b42172befebc,310511]); 2017-08-29 21:02:04.0 [aaleman] Insert Concept add narrower relation (Aircraft [227d9c3d-f631-402d-84ed-b8c5a562fc27,287509] - NP-3C Orion [fb9f4171-b9b6-4627-9c79-1d3b5890dfc4,310067]); 2017-07-18 21:32:10.0 [sritz] Insert Concept add narrower relation (Aircraft [227d9c3d-f631-402d-84ed-b8c5a562fc27,287509] - UC-12B [18cb3d65-a7ab-4220-b7e3-38b98ce04ac7,309831]); 2017-07-07 18:28:13.0 [sritz] Insert Concept add narrower relation (Aircraft [227d9c3d-f631-402d-84ed-b8c5a562fc27,287509] - NSF/NCAR C-130 [3a59dbd3-86c4-47dd-aeb1-935c657aa544,309791]); 2017-07-07 16:48:51.0 [tstevens] Remove Concepts delete narrower relation (null); 2017-06-26 11:38:58.0 [tstevens] Insert Concept add narrower relation (Aircraft [227d9c3d-f631-402d-84ed-b8c5a562fc27,287509] - TEST [3cc1c6b0-cdfa-49d4-b32b-9c14fe5ffe92,309675]); 2017-04-25 19:49:14.0 [sritz] Insert Concept add narrower relation (Aircraft [227d9c3d-f631-402d-84ed-b8c5a562fc27,287509] - Cessna Pelican [c97d09d4-4966-42ed-a6c7-4330a1e76edf,309547]); 2017-02-08 18:31:23.0 [aaleman] Insert Concept add narrower relation (Aircraft [227d9c3d-f631-402d-84ed-b8c5a562fc27,256457] - HU-25A [d77685bd-aa94-4717-bd97-632699d999b5,278645]); 2016-08-05 18:17:55.0 [gee-cee] Insert Concept add narrower relation (Aircraft [227d9c3d-f631-402d-84ed-b8c5a562fc27,256457] - C-23 Sherpa [abe97ffb-af51-43b2-a1d4-a922ddf9bc6e,277807]); 2016-03-15 18:26:41.0 [saritz] Insert Concept add narrower relation (Aircraft [227d9c3d-f631-402d-84ed-b8c5a562fc27,143335] - NASA GLOBAL HAWK 872 AIRCRAFT [8f3ab728-820e-4723-8807-c1f1e6e4a1b0,158663]); 2015-12-24 17:54:53.0 [aaleman] Insert Concept add narrower relation (Aircraft [227d9c3d-f631-402d-84ed-b8c5a562fc27,143335] - RQ-4 [e5aedd55-cce6-417c-97c0-595448406ad5,158567]); 2015-09-02 11:10:41.0 [tbs1979] Remove Concepts delete narrower relation (null); 2015-09-01 18:09:53.0 [tbs1979] Insert Concept add narrower relation (Aircraft [227d9c3d-f631-402d-84ed-b8c5a562fc27,143335] - TEST [e4f5ffb4-0708-4619-9fe2-6adbb33f05b3,158351]); 2014-03-13 09:57:10.0 [aaleman] Insert Concept add narrower relation (Aircraft [227d9c3d-f631-402d-84ed-b8c5a562fc27,73411] - P-3A ORION [29564e60-e0d6-4d5d-9999-97b9cd16a034,106229]); 2013-07-02 20:59:48.0 [saritz] Insert Concept add narrower relation (Aircraft [227d9c3d-f631-402d-84ed-b8c5a562fc27,73411] - UWKA [64b518f5-2026-4c5b-9bae-9fa55b5b5778,105253]); 2013-05-21 14:36:54.0 [aaleman] Insert Concept add narrower relation (Aircraft [227d9c3d-f631-402d-84ed-b8c5a562fc27,73411] - G-V [924c4b23-30f0-451f-baa2-b6de47c94e58,105145]); 2013-05-21 14:35:57.0 [aaleman] Insert Concept add narrower relation (Aircraft [227d9c3d-f631-402d-84ed-b8c5a562fc27,73411] - HU-25C [47b6caf1-e14c-458c-84a1-ec64cf29b534,105141]); 2012-10-17 01:30:33.0 [saritz] Move Concepts add narrower relation (Aircraft [227d9c3d-f631-402d-84ed-b8c5a562fc27,31205] - UND CITATION II [7f2883c4-bbaf-4150-93d8-dc48716476ca,61305]); 2012-07-05 21:00:20.0 [saritz] Remove Concepts delete narrower relation (null); 2012-07-05 20:59:33.0 [saritz] Insert Concept add narrower relation (Aircraft [227d9c3d-f631-402d-84ed-b8c5a562fc27,31205] - OWEN CESSNA SKYCAT [d301492d-0514-4b1f-bae7-15ce6f2776c1,40305]); TRITON The Japan Marine Science and Technology Center (JAMSTEC) is developing a surface moored buoy network named TRITON (TRIangle Trans-Ocean Buoy Network) for observing oceanic and atmospheric variability in the Pacific Ocean and its adjacent seas in cooperation interested Japanese and foreign agencies and institutions. The principal scientific objective is to understand variations of ocean circulation and heat/salt transports with emphasis on ENSO, the Asian monsoon, and decadal scale variability that influences world wide climate change. In its first phase, the TRITON array will be established mainly in the western tropical pacific Ocean, and harmonized with TAO array which are presently maintained by Pacific Marine Environmental Laboratory (PMEL), NOAA. The fundamental functions of TRITON are (1) basin scale ENSO monitoring, and (2) measurements of heat, freshwater, momentum fluxes for improving modeling capability. The TRITON (Triangle Trans-Ocean buoy network) is a series of buoys for measuring surface meteorology and upper ocean. The buoys will be deployed by JAMSTEC in collaboration with many countries in and around the Pacific Ocean as part of international climate research programs. The buoys measure wind, air temperature, humidity, precipitation, short wave radiation, water temperature, salinity and current. The water temperature and will be measured down to 750m depth. The data will be transmitted via satellite near real time and provided to researchers in the world. See: http://www.jamstec.go.jp/jamstec/TRITON/stream/index.html Group: Platform_Details Entry_ID: TRITON Group: Platform_Identification Platform_Category: In Situ Ocean-based Platforms Platform_Series_or_Entity: BUOYS Short_Name: TRITON Long_Name: TRIangle Trans-Ocean Buoy Network End_Group Group: Synonymous_Platform_Names Short_Name: Triton End_Group Creation_Date: 2007-12-12 Online_Resource: http://www.jamstec.go.jp/jamstec/TRITON/stream/index.html Sample_Image: http://www.jamstec.go.jp/jamstec/OCEAN/TRITON/buoy-photo-s.jpg End_Group GOES-9 GOES 9 was launched on May 23, 1995. GOES-9, which is currently partially operational, is being provided to the Japanese Meteorological Agency to replace their failing geostationary satellite. GOES I-M represents the next generation of meteorological satellites and introduces two new features. The first feature, flexible scan, offers small-scale area imaging that lets meteorologists take pictures of local weather trouble spots. This allows them to improve short-term forecasts over local areas. The second feature, simultaneous and independent imaging and sounding, is designed to allow weather forecasters to use multiple measurements of weather phenomena to increase the accuracy of their forecasts. Each satellite in the series carries two major instruments: an Imager and a Sounder. These instruments acquire high resolution visible and infrared data, as well as temperature and moisture profiles of the atmosphere. They continuously transmit these data to ground terminals where the data are processed for rebroadcast to primary weather services both in the United States and around the world, including the global research community. The GOES I-M mission is scheduled to run from the mid-1990s into the first decade of the 21st century. Each element of the mission has been designed to meet all in-orbit performance requirements for at least five years. The GOES I-M system performs the following basic functions: + Acquisition, processing, and dissemination of imaging and sounding data. + Acquisition and dissemination of Space Environment Monitor (SEM) data. + Reception and relay of data from ground-based Data Collection Platforms (DCPs) that are situated in carefully selected urban and remote areas to the NOAA Command and Data Acquisition (CDA) station. + Continuous relay of Weather Facsimile (WEFAX) and other data to users, independent of all other functions. + Relay of distress signals from people, aircraft, or marine vessels to the search and rescue ground stations of the Search and Rescue Satellite Aided Tracking (SARSAT) system. GOES provides the instantaneous relay functions for the SARSAT system. A dedicated search and rescue transponder on board GOES is designed to detect emergency distress signals originating from Earth-based sources. These unique identification signals are normally combined with signals received by a low-Earth orbiting satellite system and relayed to a search and rescue ground terminal. The combined data are used to perform effective search and rescue operations. The GOES I-M system serves a region covering the central and eastern Pacific Ocean; North, Central, and South America; and the central and western Atlantic Ocean. Pacific coverage includes Hawaii and the Gulf of Alaska. This is accomplished by two satellites, GOES West located at 135 west longitude and GOES East at 75 west longitude. A common ground station, the CDA station located at Wallops, Virginia, supports the interface to both satellites. The NOAA Satellite Operations Control Center (SOCC), in Suitland, Maryland, provides spacecraft scheduling, health and safety monitoring, and engineering analyses. Delivery of products involves ground processing of the raw instrument data for radiometric calibration and Earth location information, and retransmission to the satellite for relay to the data user community. The processed data are received at the control center and disseminated to the National Weather Service's (NWS) National Meteorological Center, Camp Springs, Maryland, and NWS forecast offices, including the National Hurricane Center, Miami, Florida, and the National Severe Storms Forecast Center, Kansas City, Missouri. Processed data are also received by Department of Defense installations, universities, and numerous private commercial users. *The GOES-9 satellite was replaced by GOES-10 in July 1998* MAIN SPACECRAFT DESIGN ELEMENTS Mission life 5 years, minimum Dimensions Main body 2 meter (7 foot) cube Deployed length 27 meters (88 feet) Weight 2100 kg (4600 lb) Orbit Geosynchronous Altitude 36,000 km (22,000 mi) Longitude 75W and 135W Latitude equatorial, within 0.5 degree Power 1050 watts &#64 42 volts, solar array; battery backup Launch vehicle Atlas-I/Centaur (GOES-I/K), Atlas-II/Centaur (GOES-L/M) Communications Imager and Sounder in GVAR format at 2.1 Mbits/sec GOES-I/M IMAGER The GOES Imager is a multi-channel instrument designed to sense radiant and solar-reflected energy from sampled areas of the Earth. The multi-element spectral channels simultaneously sweep east-west and west-east along a north-to-south path by means of a two-axis mirror scan system. The instrument can produce full-Earth disc images, sector images that contain the edges of the Earth, and various sizes of area scans completely enclosed within the Earth scene using a new flexible scan system. Scan selection permits rapid continuous viewing of local areas for monitoring of mesoscale (regional) phenomena and accurate wind determination. IMAGER CHANNELS AND PRODUCTS CHANNEL 1 2* 3* 4 5* WAVELENGTH (um) 0.65 3.9 6.7 11 12 PRODUCT Clouds x x x x x Water Vapor* x x x Surface Temp. o x o Winds x x x Albedo + IR Flux x o x o Fires + Smoke x x o o KEY: * = new operational data x = primary channel o = secondary channel GOES-I/M SOUNDER The GOES Sounder is a 19-channel discrete-filter radiometer covering the spectral range from the visible channel wavelengths to 15 microns. It is designed to provide data from which atmospheric temperature and moisture profiles, surface and cloud-top temperatures, and ozone distribution can be deduced by mathematical analysis. It operates independently of and simultaneously with the Imager, using a similarly flexible scan system. The Sounder's multi-element detector array assemblies simultaneously sample four separate fields or atmospheric columns. A rotating filter wheel, which brings spectral filters into the optical path of the detector array, provides the infrared channel definition. PRODUCTS, RESOLUTION AND ACCURACY RESOLUTION (km) ACCURACY Vert. Horiz. Absolute Relative PRODUCT TEMPERATURE Profile 3-5 50 2-3 K 1 K Land --- 10 2 K 1 K Sea --- 10 1 K 0.5 K MOISTURE Profile 2-4 50 30% 20% Total --- 10 20% 10% Motion 3 layers 50 6 m/sec 3 m/sec CLOUD Height 2 layers 10 50 mb 25 mb Amount total 10 15% 5% OZONE* Total --- 50 30% 15% Motion 1 layer 50 10 m/sec 5 m/sec IR Flux* total 50 10 W/m^2 3 W/m^2 KEY: * = potential future product GOES 9 information is available at: "http://www.oso.noaa.gov/goes/" To view a 3D orbit, observe the J Track satellite tracking web page at: "http://liftoff.msfc.nasa.gov/realtime/Jtrack/" Group: Platform_Details Entry_ID: GOES-9 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: GOES (Geostationary Operational Environmental Satellite) Short_Name: GOES-9 Long_Name: Geostationary Operational Environmental Satellite 9 End_Group Group: Synonymous_Platform_Names Short_Name: GOES J End_Group Group: Platform_Associated_Instruments Short_Name: GOES I-M IMAGER Short_Name: GOES I-M SOUNDER End_Group Group: Orbit Orbit_Type: GEO > Geosynchronous > Geostationary End_Group Creation_Date: 2007-10-04 Online_Resource: http://liftoff.msfc.nasa.gov/realtime/Jtrack/ Group: Platform_Logistics Launch_Date: 1995-05-23 Primary_Sponsor: USA/NASA Primary_Sponsor: USA/NOAA End_Group End_Group MARINER 2 The Mariner 2 spacecraft was the second of a series of spacecraft used for planetary exploration in the flyby, or nonlanding, mode and the first spacecraft to successfully encounter another planet. Mariner 2 was a backup for the Mariner 1 mission which failed shortly after launch to Venus. The objective of the Mariner 2 mission was to fly by Venus and return data on the planet's atmosphere, magnetic field, charged particle environment, and mass. It also made measurements of the interplanetary medium during its cruise to Venus and after the flyby. Spacecraft and Subsystems Mariner 2 consisted of a hexagonal base, 1.04 meters across and 0.36 meters thick, which contained six magnesium chassis housing the electronics for the science experiments, communications, data encoding, computing, timing, and attitude control, and the power control, battery, and battery charger, as well as the attitude control gas bottles and the rocket engine. On top of the base was a tall pyramid-shaped mast on which the science experiments were mounted which brought the total height of the spacecraft to 3.66 meters. Attached to either side of the base were rectangular solar panel wings with a total span of 5.05 meters and width of 0.76 meters. Attached by an arm to one side of the base and extending below the spacecraft was a large directional dish antenna. The Mariner 2 power system consisted of the two solar cell wings, one 183 cm by 76 cm and the other 152 cm by 76 cm (with a 31 cm dacron extension (a solar sail) to balance the solar pressure on the panels) which powered the craft directly or recharged a 1000 Watt-hour sealed silver-zinc cell battery, which was used before the panels were deployed, when the panels were not illuminated by the Sun, and when loads were heavy. A power-switching and booster regulator device controlled the power flow. Communications consisted of a 3 Watt transmitter capable of continuous telemetry operation, the large high gain directional dish antenna, a cylindrical omnidirectional antenna at the top of the instrument mast, and two command antennas, one on the end of either solar panel, which received instructions for midcourse maneuvers and other functions. Propulsion for midcourse maneuvers was supplied by a monopropellant (anhydrous hydrazine) 225 N retro-rocket. The hydrazine was ignited using nitrogen tetroxide and aluminum oxide pellets, and thrust direction was controlled by four jet vanes situated below the thrust chamber. Attitude control with a 1 degree pointing error was maintained by a system of nitrogen gas jets. The Sun and Earth were used as references for attitude stabilization. Overall timing and control was performed by a digital Central Computer and Sequencer. Thermal control was achieved through the use of passive reflecting and absorbing surfaces, thermal shields, and movable louvers. The scientific experiments were mounted on the instrument mast and base. A magnetometer was attached to the top of the mast below the omnidirectional antenna. Particle detectors were mounted halfway up the mast, along with the cosmic ray detector. A cosmic dust detector and solar plasma spectrometer detector were attached to the top edges of the spacecraft base. A microwave radiometer and an infrared radiometer and the radiometer reference horns were rigidly mounted to a 48 cm diameter parabolic radiometer antenna mounted near the bottom of the mast. All instruments were operated throughout the cruise and encounter modes except the radiometers, which were only used in the immediate vicinity of Venus. Group: Platform_Details Entry_ID: MARINER 2 Group: Platform_Identification Platform_Category: Interplanetary Spacecraft Platform_Series_or_Entity: FLYBY Short_Name: MARINER 2 End_Group Group: Synonymous_Platform_Names Short_Name: Mariner-Venus 1962 Short_Name: 00374 End_Group Group: Platform_Associated_Instruments Short_Name: MAGNETOMETERS End_Group Creation_Date: 2007-08-13 Online_Resource: http://www.jpl.nasa.gov/missions/past/mariner1-2.html Sample_Image: http://nssdc.gsfc.nasa.gov/image/spacecraft/mariner02.gif Group: Platform_Logistics Launch_Date: 1962-08-27 Primary_Sponsor: NASA End_Group End_Group COSMIC/FORMOSAT-3 [Source: COSMIC Home Page at UCAR, http://www.cosmic.ucar.edu/about.html ] FORMOSAT-3/COSMIC Overview FORMOSAT-3/COSMIC (F3C) is a joint Taiwan/US science mission for weather, climate, space weather and geodetic research. The F3C mission was successfully launched on 15 April 2006. Six identical micro satellites, each carrying an advanced GPS radio occultation (RO) receiver, a Tiny Ionospheric Photometer (TIP) and a Tri Band Beacon (TBB) were deployed. The satellites have since been raised by Taiwan's National Space Organization (NSPO) to their final orbit altitude at 800km to achieve an operational constellation of six orbital planes separated by 30 degrees. The payload science data are currently being downloaded every orbit via two NOAA TT&C stations (in Alaska and Norway) and one NSF/NASA station in McMurdo, Antarctica and transferred to the COSMIC Data Analysis and Archival Center (CDAAC) at UCAR in Boulder. The CDAAC currently processes the COSMIC science data in near real time - Ninety percent of RO profiles are delivered to operational weather centers within 3 hours of observation. CDAAC also reprocesses data in a more accurate post-processed mode (within 6 weeks of observation) for COSMIC as well as other missions including GPS/MET, CHAMP, SAC-C, and GRACE. COSMIC is currently providing between 1000-2500 daily RO profiles in the neutral atmosphere, 1000-2500 daily electron density profiles and total electron content arcs, and TIP radiance products. The data have already demonstrated their value for operational weather forecasting, hurricane forecasting, and investigations of the atmospheric boundary layer. The data have been used extensively to test ionospheric models and their use in operational space weather models is under development. COSMIC GPS RO data also have the potential to be of great benefit to climate studies due to their demonstrated high precision and global and diurnal sampling coverage. Group: Platform_Details Entry_ID: COSMIC/FORMOSAT-3 Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Short_Name: COSMIC/FORMOSAT-3 Long_Name: Constellation Observing System for Meteorology, Ionosphere and Climate End_Group Group: Synonymous_Platform_Names Short_Name: FORMSAT 3A Short_Name: FORMSAT 3B Short_Name: FORMSAT 3C Short_Name: FORMSAT 3D Short_Name: FORMSAT 3E Short_Name: FORMSAT 3F Short_Name: 2006-011A Short_Name: 2006-011B Short_Name: 2006-011C Short_Name: 2006-011D Short_Name: 2006-011E Short_Name: 2006-011F End_Group Group: Platform_Associated_Instruments Short_Name: RO Short_Name: TBB Short_Name: TIP End_Group Group: Orbit Orbit_Inclination: 72 degrees Period: 95 m Perigee: 496 km Apogee: 540 km Orbit_Type: LEO > Low Earth Orbit > Inclined Non-Polar End_Group Online_Resource: http://www.cosmic.ucar.edu/ Online_Resource: http://cosmic-io.cosmic.ucar.edu/cdaac/ Online_Resource: http://www.nspo.org.tw/2008e/projects/project3/hot.shtml?right=no Sample_Image: http://www.cosmic.ucar.edu/images/rocksat.jpg Group: Platform_Logistics Launch_Date: 2006-04-15 Launch_Site: Vandenberg Air Force Base, USA Design_Life: 5 years Primary_Sponsor: USA/NSF/UCAR Primary_Sponsor: TAIWAN/NSPO Primary_Sponsor: USA/NASA Primary_Sponsor: USA/DOD/USAF Primary_Sponsor: USA/NOAA Primary_Sponsor: USA/DOD/ONR End_Group End_Group AD-C Explorer 39 was an inflatable sphere, 3.6 m in diameter. It was orbited to make atmospheric density determinations. The spacecraft was successfully launched into a nearly polar, highly elliptical orbit. It was folded and carried into orbit, together with ejection and inflation equipment, as part of the payload of Explorer 40. Two density experiments were performed. One involved the study of systematic density variation, and the other was concerned with nonsystematic density changes. The upper atmospheric densities were derived from sequential observations of the sphere by use of an attached 136.620-MHz radio tracking beacon and by optical tracking. The radio beacon ceased transmitting in June 1971. Since that time it has been necessary to rely solely on the SAO Baker-Nunn camera network for tracking. Explorer 39 had an expected orbital lifetime of 50 years. http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1968-066A Group: Platform_Details Entry_ID: AD-C Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: AD (Atmospheric Dynamics) Short_Name: AD-C Long_Name: Atmosphere Dynamics C (Explorer 39) End_Group Group: Synonymous_Platform_Names Short_Name: EXPLORER 39 Short_Name: 03337 End_Group Group: Platform_Associated_Instruments Short_Name: OPTICAL BEACON End_Group Group: Orbit Orbit_Inclination: 80.6 degrees Period: 118.2 minutes Perigee: 670 km Apogee: 2538 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-08-22 Online_Resource: http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1968-066A Group: Platform_Logistics Launch_Date: 1968-08-08 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: NASA End_Group End_Group R/V MILLER FREEMAN Miller Freeman is a 215-foot fisheries and oceanographic research vessel and is one of the largest research trawlers in the United States. Miller Freeman's primary mission is to provide a working platform for the study of the ocean's living resources. Miller Freeman is homeported at the Marine Operations Center-Pacific in Newport, Oregon. With a 12,578 mile / 31 day endurance, Miller Freeman is capable of operating in any waters of the world. Group: Platform_Details Entry_ID: R/V MILLER FREEMAN Group: Platform_Identification Platform_Category: In Situ Ocean-based Platforms Platform_Series_or_Entity: SHIPS Short_Name: R/V MILLER FREEMAN End_Group Creation_Date: 2012-07-19 Online_Resource: http://www.moc.noaa.gov/mf/ Sample_Image: http://www.moc.noaa.gov/mf/mfunderway.jpg End_Group TOPSAT TopSat is a micro-satellite designed and built by a QinetiQ-led consortium of British firms. Images from the satellite are provided free of charge to relief agencies responding to disasters anywhere in world. TopSat was designed and built by a consortium of British companies led by QinetiQ, whose role included systems design and technical authority, provision of payload electronics units, project and operations management and data reception. Other consortium members are Surrey Satellite Technology Ltd (SSTL), Rutherford Appleton Laboratory (RAL) designed and Infoterra. The satellite is designed to return its data directly to a mobile ground station immediately after collecting an image, allowing far more timely delivery of the information which it collects than standard satellites. The system is specifically designed to meet operational timescales, whether for disaster relief, news-gathering, or other applications where speed of response is vital. TopSat received the Aviation and Space Grand Award – the top award for aerospace technology, from Popular Science, the best selling science and technology magazine in the world. The magazine’s editors concluded that TopSat is an innovation that has the potential to change satellite and space reconnaissance technology. TopSat weighs just 120 kg, but carries an optical camera capable of delivering panchromatic images with a spatial resolution at nadir of 2.8 metres covering a 17x17 km area, and simultaneous three-band multi-spectral images, (red, green, blue), with a resolution of 5.6 metres. This is thought to represent the best resolution per mass of any satellite launched to date. This camera is integrated with an agile micro-satellite platform to permit pitch compensation manoeuvres, allowing imaging of low illumination scenes. TopSat has been in operation since its launch from Plesetsk in Russia on 27th October 2005. The satellite can be reprogrammed in orbit, and the consortium is exploiting this to enhance its performance. In addition to actively pursuing experiments for the MOD and BNSC, the consortium is also seeking new applications to which the technology can be applied. In the future, a constellation of three or four TopSat satellites could image almost any point on the Earth at least once a day, further opening up the potential for quick response imagery which is extremely cost effective to deliver. [Information from QinetiQ Ltd.] Group: Platform_Details Entry_ID: TOPSAT Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: TOPSAT End_Group Group: Platform_Associated_Instruments Short_Name: CAMERAS End_Group Group: Orbit Orbit_Inclination: 98.1 Period: 98.6 Repeat_Cycle: 4 Perigee: 688.4 Apogee: 714 Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2008-06-18 Online_Resource: http://www.qinetiq.com/home/defence/defence_solutions/space/topsat.html Online_Resource: http://earth.esa.int/object/index.cfm?fobjectid=5135 Group: Platform_Logistics Launch_Date: 2005-10-27 Launch_Site: Plesetsk Cosmodrome, Russia Primary_Sponsor: QinetiQ Ltd. Primary_Sponsor: Surrey Satellite Technology Ltd. (SSTL) Primary_Sponsor: UK Ministry of Defense (MOD) End_Group End_Group RADIOSONDES The radiosonde is a balloon-borne instrument platform with radio transmitting capabilities. Originally named a radio-meteorograph, the instrument is now referred to as a radiosonde, a name apparently derived by H. Hergesell from a combination of the words "radio" for the onboard radio transmitter and "sonde", which is messenger from old English. The radiosonde contains instruments capable of making direct in-situ measurements of air temperature, humidity and pressure with height, typically to altitudes of approximately 30 km. These observed data are transmitted immediately to the ground station by a radio transmitter located within the instrument package. The ascent of a radiosonde provides an indirect measure of the wind speed and direction at various levels throughout the troposphere. Ground based radio direction finding antenna equipment track the motion of the radiosonde during its ascent through the air. The recorded elevation and azimuth information are converted to wind speed and direction at various levels by triangulation techniques. [Source: University of Wisconsin, Atmospheric and Ocean Sciences] Group: Platform_Details Entry_ID: RADIOSONDES Group: Platform_Identification Platform_Category: Balloons/Rockets Short_Name: RADIOSONDES End_Group Group: Platform_Associated_Instruments Short_Name: RADIOSONDES End_Group Creation_Date: 2007-08-21 Online_Resource: http://www.erh.noaa.gov/gyx/weather_balloons.htm Sample_Image: http://www.ua.nws.noaa.gov/images/sondes.gif Group: Platform_Logistics Primary_Sponsor: USA/NOAA End_Group End_Group Soil Characteristics 2019-07-31 11:58:17.0 [tstevens] Remove Concepts delete narrower relation (null); 2015-06-04 14:32:22.0 [aaleman] Move Concepts add narrower relation (Soil Characteristics [252a24e5-6f62-40df-86b3-59ef0d38283f,158001] - CONUS-Soil [e798b5b2-e34b-41bf-97f8-f1efd6a93300,157965]); 2015-06-04 14:32:09.0 [aaleman] Insert Concept add broader relation (Soil Characteristics [252a24e5-6f62-40df-86b3-59ef0d38283f,158001] - Environmental Modeling [079610fb-e4cf-4e2c-9a92-86a9b798a7d5,157997]); HST The Hubble Space Telescope (HST) is a cooperative program of the European Space Agency (ESA) and the National Aeronautics and Space Administration (NASA) to operate a long-lived space-based observatory for the benefit of the international astronomical community. HST is an observatory first dream of in the 1940s, designed and built in the 1970s and 80s, and operational only in the 1990s. Since its preliminary inception, HST was designed to be a different type of mission for NASA -- a long-term space-based observatory. To accomplish this goal and protect the spacecraft against instrument and equipment failures, NASA had always planned on regular servicing missions. Hubble has special grapple fixtures, 76 handholds, and stabilized in all three axes. HST is a 2.4-meter reflecting telescope, which was deployed, in low-Earth orbit (600 kilometers) by the crew of the space shuttle Discovery (STS-31) on 25 April 1990. Additional information available at http://www.stsci.edu/hst/HST_overview/ [Source: Space Telescope Science Institute] Group: Platform_Details Entry_ID: HST Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Short_Name: HST Long_Name: Hubble Space Telescope End_Group Group: Synonymous_Platform_Names Short_Name: Hubble Space Telescope Short_Name: 1990-037B Short_Name: Space Telescope Short_Name: 20580 End_Group Group: Orbit Orbit_Altitude: 575 km Orbit_Inclination: 28.48 degrees Period: 96.66 m Perigee: 586.47 km Apogee: 610.44 km Orbit_Type: LEO > Low Earth Orbit > Inclined Non-Polar End_Group Creation_Date: 2008-01-14 Online_Resource: http://www.stsci.edu/hst/HST_overview/ Online_Resource: http://hubble.nasa.gov/ Online_Resource: http://hubblesite.org/ Sample_Image: http://hubble.nasa.gov/art/zzcover/hubble_earth_horz.jpg Group: Platform_Logistics Launch_Date: 1990-04-25 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: NASA Primary_Sponsor: ESA End_Group End_Group ERA40DAS 2015-08-10 18:43:26.0 [epneff] Added long name insert AltLabel (id: null text: ERA40 Data Assimilation System language code: en); 2015-08-10 18:43:04.0 [epneff] Insert Concept add broader relation (ERA40DAS [260c784e-c422-4279-97fa-9c7a348118fa,158223] - Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215]); MODELS COMPUTER MODELS MODEL Models/Analyses 2016-06-09 17:28:38.0 [epneff] added altLabel insert AltLabel (id: null text: MODEL language code: en); insert AltLabel (id: null text: Models/Analyses language code: en); insert AltLabel (id: null text: COMPUTER MODELS language code: en); 2015-08-10 14:40:28.0 [gee-cee] Insert Concept add broader relation (MODELS [26d3953e-be79-46e4-b746-efb1983c3f5c,158193] - Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215]); CBERS-2B [Source: NASA National Space Science Data Center (NSSDC), http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=2007-042A ] CBERS 2B (China-Brazil Earth Resources Satellite 2B), also known as Zi Yuan 2B, is a China-Brazil joint craft that was launched by a Long March 4B rocket from Taiyuan Satellite Launch Center in Shanxi province at 03:26 UT on 19 September 2007. The 1.5 tonne, 1.8 m x 2.0 m x 2.2 m, triaxially-stabilized craft carries a low 20 m resolution, and a higher 2.5 m resolution camera. The data will help in crop estimation, urban planning, water resource management, and military intelligence. Group: Platform_Details Entry_ID: CBERS-2B Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: CBERS (China-Brazil Earth Resources Satellite) Short_Name: CBERS-2B Long_Name: China-Brazil Earth Resource Satellite 2B End_Group Group: Platform_Associated_Instruments Short_Name: HRCCD Short_Name: HRPC Short_Name: WFI (CBERS 1,2) End_Group Group: Orbit Orbit_Inclination: 98.6° Perigee: 773.0 km Apogee: 774.0 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2008-08-25 Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=2007-042A Online_Resource: http://www.cbers.inpe.br/ingles/ Group: Platform_Logistics Launch_Date: 2007-09-19 Launch_Site: Taiyuan Space Launch Center, China Design_Life: 2 Years Primary_Sponsor: China-Brazil joint spacecraft End_Group End_Group IRS-1D On 29th September, 1996, Indian Space Research Organization (ISRO) proved its launch vehicle capability by launching the Indian Remote Sensing Satellite, IRS-1D, using Polar Satellite Launch Vehicle, PSLV-C1, from Sriharikota. This added one more member to the existing IRS constellation. It carries payloads similar to its predecessor, IRS-1C. Like IRS-1C, IRS-1D has LISS III, PAN, WiFS sensors onboard. [Summary provided by the Indian Remote Sensing Agency.] Group: Platform_Details Entry_ID: IRS-1D Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: IRS (Indian Remote Sensing Satellite) Short_Name: IRS-1D End_Group Group: Platform_Associated_Instruments Short_Name: WIFS Short_Name: PAN Short_Name: LISS-III End_Group Group: Orbit Orbit_Altitude: 737 km Orbit_Inclination: 98.53 deg Equator_Crossing: 10.30 A.M to 10.47 A.M Period: 100.56 minutes Repeat_Cycle: 25 days Perigee: 737 km Apogee: 821 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2008-07-09 Online_Resource: http://www.isro.gov.in/satellites/irs-1d.aspx Sample_Image: http://www.isro.gov.in/satellites/images/irs1d_img.gif Group: Platform_Logistics Launch_Date: 1996-09-29 Launch_Site: Sriharikota Island, India Primary_Sponsor: India End_Group End_Group METEOSAT 2018-07-27 20:53:32.0 [sritz] Insert Concept add narrower relation (METEOSAT [28eac19a-5500-4a21-af30-ab7a364ff8d0,344695] - METEOSAT-11 [bc69ef64-c468-4e8a-9a41-3b421e79cc90,368007]); 2013-12-13 20:31:03.0 [saritz] Insert Concept add narrower relation (METEOSAT [28eac19a-5500-4a21-af30-ab7a364ff8d0,73589] - METEOSAT-10 [01ee202c-22c5-442d-b4fd-65f424057ea3,106033]); 2013-12-13 20:30:41.0 [saritz] Insert Concept add narrower relation (METEOSAT [28eac19a-5500-4a21-af30-ab7a364ff8d0,73589] - METEOSAT-9 [07dfead6-2cbc-4703-8533-c4d07e2ec67c,106029]); 2013-12-13 20:30:24.0 [saritz] Insert Concept add narrower relation (METEOSAT [28eac19a-5500-4a21-af30-ab7a364ff8d0,73589] - METEOSAT-8 [1ef73a04-e012-4389-9646-cdeb7c04dc92,106025]); 2012-09-18 16:35:22.0 [saritz] Cut Concepts delete narrower relation (null); 2012-09-18 16:35:03.0 [saritz] Cut Concepts delete narrower relation (null); TIROS-M The ITOS (Improved Tiros Operational Satellite) series (TIROS-M was the prototype spacecraft) were the second generation of operational sun-synchronous meteorological spacecraft. Operational satellites were renamed NOAA. The primary objective of ITOS was to provide improved operational infrared and visual observations of earth cloud cover for use in weather analysis and forecasting. Secondary objectives included providing both solar proton and global heat balance data on a regular daily basis. To accomplish these tasks, the spacecraft carried: -two television cameras for Automatic Picture Transmission (APT) and -two Advanced Vidicon Camera System (AVCS) cameras. It also carried -a low-resolution Flat Plate Radiometer (FPR), -a Solar Proton Monitor (SPM), and -two scanning radiometers that not only measured emitted infrared radiation, but also served as a backup system for the APT and AVCS cameras. The nearly cubical spacecraft measured 1 by 1 by 1.2 m. The TV cameras and infrared sensors were mounted on the satellite baseplate with their optical axes directed verticially earthward. The satellite was equipped with three curved solar panels that were folded during launch and deployed after orbit was achieved. Each panel measured over 4.2 m in length when unfolded and was covered with 3420 solar cells, each measuring 2 by 2 cm. The ITOS dynamics and attitude control system maintained desired spacecraft orientation through gyroscopic principles incorporated into the satellite design. Earth orientation of the satellite body was maintained by taking advantage of the precession induced from a momentum flywheel so that the satellite body precession rate of one revolution per orbit provided the desired 'earth looking' attitude. Minor adjustments in attitude and orientation were made by means of magnetic coils and by varying the speed of the momentum flywheel. Additional information available at "http://www.skyrocket.de/space/doc_sdat/noaa_itos-a.htm" Group: Platform_Details Entry_ID: TIROS-M Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: TIROS Short_Name: TIROS-M Long_Name: Television Infrared Observation Satellite-M End_Group Group: Synonymous_Platform_Names Short_Name: ITOS End_Group Group: Platform_Associated_Instruments Short_Name: HRIR End_Group Creation_Date: 2007-11-14 Online_Resource: http://www.skyrocket.de/space/doc_sdat/noaa_itos-a.htm Sample_Image: http://www.photolib.noaa.gov/700s/spac0170.jpg Group: Platform_Logistics Launch_Date: 1970-01-23 Primary_Sponsor: NASA End_Group End_Group CODAR SeaSonde The SeaSonde HF radar system by CODAR Ocean Sensors is your solution for making continuous, wide-area ocean observations. The SeaSonde will provide you with years of real-time data over large coverage areas, with ranges up to 200 km -- This is not possible with any other technology! The SeaSonde is a compact, non-contact surface current and wave measurement system that can be deployed and maintained easily, and will perform even during extreme weather conditions such as hurricanes. 2017-12-28 19:13:35.0 [sritz] Requested by Artem Moiseev insert Definition (id: null text: The SeaSonde HF radar system by CODAR Ocean Sensors is your solution for making continuous, wide-area ocean observations. The SeaSonde will provide you with years of real-time data over large coverage areas, with ranges up to 200 km -- This is not possible with any other technology! The SeaSonde is a compact, non-contact surface current and wave measurement system that can be deployed and maintained easily, and will perform even during extreme weather conditions such as hurricanes. language code: en); 2017-12-28 19:11:49.0 [sritz] Move Concepts delete broader relation (null); add broader relation (CODAR SeaSonde [294cc889-28bc-4a33-b630-8225f559c3e7,310507] - OCEAN PLATFORM/OCEAN STATIONS [62e9613a-6e40-41cf-838a-ed6ac0d4871b,287905]); 2017-12-28 19:11:17.0 [sritz] Insert Concept add broader relation (CODAR SeaSonde [294cc889-28bc-4a33-b630-8225f559c3e7,310507] - In Situ Land-based Platforms [4f396ff6-7bea-4ba4-afa3-198ebd914a4a,287781]); P-3A ORION P-3A The P-3A ORION is the Chilean Armada P-3 aircraft used during the 2002, 2004 and 2008 NASA missions that included Airborne Topographic Mapper (ATM) instrument data used in the recent Level 4 IceBridge derived data product. Group: Platform_Details Entry_ID: P-3A ORION Group: Platform_Identification Platform_Category: Aircraft Short_Name: P-3A ORION Long_Name: Lockheed P-3A Orion End_Group Creation_Date: 2014-03-13 End_Group 2016-06-09 18:34:41.0 [epneff] added altLabel insert AltLabel (id: null text: P-3A language code: en); 2014-03-13 09:58:00.0 [aaleman] added new platform insert AltLabel (id: null text: Lockheed P-3A Orion language code: en); 2014-03-13 09:57:10.0 [aaleman] Insert Concept add broader relation (P-3A ORION [29564e60-e0d6-4d5d-9999-97b9cd16a034,106229] - Aircraft [227d9c3d-f631-402d-84ed-b8c5a562fc27,73411]); GMS-1 The Geostationary Meteorological Satellite (GMS-1) was Japan's contribution to the international GARP (Global Atmospheric Research Program). One major objective of GARP was to obtain synoptic global meteorological data sets for one year's duration (to include two optimized observing periods of a few weeks each). These data served as raw material to optimize computer models for meteorological prediction. It was hoped that determination could be made of the time limitation for short-term modeling. The GMS series has been used for the World Meteorological Organization's World Weather Watch. The satellite was spin-stabilized with a despun earth-pointing antenna. The GMS series carried the Visible and Spin Scan Radiometer (VISSR). Launched by a US Delta rocket in July 1977, the satellite was positioned near 140 deg E. Designed to operate for 5 years, the satellite was turned off in 1981 after 4 1/2 years in orbit. __________ Taken from the NSSDC System for Information Retrieval and Storage (SIRS). For more information contact the NSSDC Coordinated Request and User Support Office, 301-286-6695 (NASA Goddard Space Flight Center, Code 933.4, Greenbelt, Maryland 20771, USA). WWW: http://nssdc.gsfc.nasa.gov/ Technical contact: Yukio Haruyama, Earth Observation program office director, Program plannig and management department, National space development agency of Japan Head office Hamamatsu-cho, Minato-ku, Tokyo, Japan Phone: 81-3-5470-4252 Group: Platform_Details Entry_ID: GMS-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: GMS (Japan Geostationary Meteorological Satellite) Short_Name: GMS-1 Long_Name: Geostationary Meteorological Satellite-1 End_Group Group: Synonymous_Platform_Names Short_Name: GMS-1 End_Group Group: Platform_Associated_Instruments Short_Name: VISSR-GMS End_Group Group: Orbit Orbit_Altitude: 36,000 km Orbit_Type: GEO > Geosynchronous > Geostationary End_Group Creation_Date: 2007-10-01 Online_Resource: http://www.jaxa.jp/projects/sat/gms/index_e.html Online_Resource: http://space.skyrocket.de/doc_sdat/gms-1.htm Group: Platform_Logistics Launch_Date: 1977-07-14 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: Japan/JAXA End_Group End_Group FORMOSAT-2 ROCSat-2 is an NSPO (National Space Program Office) of Taiwan Earth imaging satellite with the objective to collect high-resolution panchromatic (2 m) and multispectral (8 m) imagery for a great variety of applications such as in land use, agriculture and forestry, environmental monitoring, natural disaster evaluation, and in support of research interests, in particular with the ISUAL instrument. Daily image coverage of Taiwan and the surrounding region is required. Background: A contract was signed in May 1999 between NSPO and DASA/DSS (Dornier Satelliten Systeme GmbH) of Germany to build a high-resolution optical imaging satellite. However, the German government refused to give DASA/DSS an export licence for the S/C (the People's Republic of China was protesting the deal). The stalemate was resolved in Dec. 1999 when NSPO signed a new contract with MMS (now Astrium SAS of France). Quick approval of the export of ROCSat-2 was provided by the French government. The ROCSat program is part of a long-term effort in Taiwan to develop an autonomous space capability. Note: A public naming competition took place in Taiwan in 2004 with regard to the ROCSat satellite program. At the end of this contest, the ROCSat program was given the new name of FormoSat in December 2004. Hence, ROCSat-2 became FormoSat-2. Spacecraft: The spacecraft bus has been built by EADS Astrium SAS (prime contractor) of Vélizy, France, based on the Leostar 500 XO family. There were also contributions from Taiwanese industry (including satellite computers, S-band antennas, and sun sensors). The S/C structure consists basically of a hexagonal body of 1.6 m side length (diameter), 2.4 m in height. The satellite is three-axis stabilized. The upper deck of the platform carries the payload (RSI and ISUAL) and also part of AOCS (Attitude and Orbit Control Subsystem), namely the star sensors and gyroscopes. The lower deck carries the four reaction wheels and the autonomous propulsion module. The pointing accuracy is &lt; 0.7 km (0.12º); the position knowledge is &lt; 70 m (0.02º). The fixed solar array uses GaAs cells and consists of two deployable flaps. The entire S/C architecture is designed in such a way as to provide a low roll inertia, a key factor for satellite agility and instrument line-of-sight stability. The S/C provides a body-pointing capability of ±45º in roll and pitch (45º pitch in 60 s, 10º roll in 25 s, 30º roll in 60 s, respectively). The S/C wet mass is about 746 kg with 81 kg of propellant (N2H4) mass. The design life is five years or better. Launch: A launch of ROCSat-2 took place on May 20, 2004 (UTC) on a Taurus-XL vehicle of OSC (Orbital Sciences Corporation) from VAFB, CA (maiden flight of Taurus-XL configuration which offers greater lift capability compared to previous versions of the Taurus rocket). Orbit: Sun-synchronous circular orbit, mean altitude = 888 km, inclination = 99.14º, period of 102.9 minutes, the LTDN (Local Time of Descending Node) is 9:26 AM (14 orbits/day). The agility of the spacecraft provides a daily revisit capability for event/disaster monitoring. Note: Following the early-orbit checkout, the initial satellite orbit has been raised from 728 km to 888 km altitude in the period May 23 to June 2, 2004. A total of 32 burns were performed by the propulsion module with 4 burns for inclination change, to enter into the mission orbit with an altitude of 891 km and an inclination of 99.14º. Ground segment: The basic elements of the ROCSat-2 ground segment are the MMC (Multi Mission Center) and the XAS (X-band Acquisition System) located in Hsinchu, Taiwan. MMC in turn consists of MOC (Mission Operations Center), MCC (Mission Control Center), SCC (Science Control Center), FDF (Flight Dynamics Facility), and GCN (Ground Communications Network). ROCSat-2 X-band imagery reception is also made available to third parties (international partners) with their own ground stations through cooperative agreements. Mission status: The spacecraft and its payload are operating nominally as of 2007. Mission operations started in June 2004 (the checkout and performance verification for satellite bus and RSI were started on May 21 and completed through June 2004; all performance requirements of FormoSat-2 had been successfully verified in orbit). Besides providing imagery for the domestic needs of Taiwan, the S/C is frequently being used to deliver high-resolution imagery for event monitoring (coverage of the Tsunami in Asia on Dec. 26, 2004 and thereafter, coverage of Hurricane Katarina in Aug. 2005, coverage of Typhoons on the Pacific, coverage of earthquake regions, etc.). The spacecraft is operating nominally as of 2006. 7) 8) 9) 10) • NSPO has contracted to SPOT Image S.A. for the international distribution of FORMOSAT-2 images since June 2004 • On 4 July 2004, ISUAL successfully observed the first images of sprites, sprite halo, and elves. • In April 2005, NSPO implemented a terminal in Kiruna, Sweden, to serve as an additional receiving station • In May 2006, NSPO implemented a F2T (FormoSat-2 Terminal) in Svalbard, Norway, to extend the data acquisition capability of the mission. SOH (State-of-Health) trending during two years of mission operations (May 2004-May 2006) on five major subsystems, including AOCS and EPS (Electric Propulsion Subsystem), and one major payload have been conducted. All parameters were well within specifications. The C&amp;DH and the TT&amp;C do not exhibit any SOH problems so far. RSI (Remote Sensing Instrument), built by EADS Astrium SAS, France. RSI is made up of the camera and IPU (Instrument Processing Unit). The camera itself consists of the optical subassembly, the secondary structure, and the FPA (Focal Plane Assembly). The Korsch telescope (mirrors &amp; structure) design and the focal plane structure are being made of SiC (Silicon Carbide). The video electronics, sequencer, DC/DC converter, and compression cards comprise the IPU. RSI utilizes the agility of the satellite bus for stereo imaging over a specific region, continuous imaging over a slender region, and mosaic imaging over a large region. The imaging capability is 8 minutes per orbit, and the imaging areas during one cycle can be one 3000 km x 24 km continuous strip, two 100 km x 24 km stereo pairs, four 100 km x 24 km strips, or eight scenes. ISUAL (Imager of Sprites: Upper Atmospheric Lightning). ISUAL is a joint international research program of NSPO, UCB (University of California at Berkeley), National Cheng Kung University of Taiwan, and Tohoku University, Japan. The objective is to observe the natural upward lightning discharge phenomena toward the ionosphere on top of the troposphere, referred to as TLEs (Transient Luminous Events). The requirements call for: 14) • To determine the location and timing of luminous phenomena above thunder clouds to investigate their spatial, temporal and spectral properties • To obtain a global survey of upper atmospheric optical flash transients (sprites, elves, blue jets, gigantic jets, etc.). The instrument consists of four elements: a) intensified sprite imager, b) a six-channel spectrophotometer, c) a two-channel array photometer, and d) an electronics package. The imager is a staring-type frame CCD camera, taking 180 frames/s with a resolution of 512 x 80 pixels in a FOV of 20º x 3.15º. In Figure 8, the large disk of the ISUAL instrument contains six color filters, which can be rotated to select wavelength for measuring the emission spectrum of red sprites. ISUAL is operated in three modes: • The sprite continuous mode to take images with a sample rate of 100 Hz • The sprite burst mode with a sample rate of 1000 Hz • The auroral mode at a constant rate of 1 sample/s. Information obtained from http://www.eoportal.org/ Group: Platform_Details Entry_ID: FORMOSAT-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: FORMOSAT-2 End_Group Group: Synonymous_Platform_Names Short_Name: ROCSat-2 End_Group Group: Platform_Associated_Instruments Short_Name: CAMERAS Short_Name: MS End_Group Group: Orbit Orbit_Altitude: 888 km Orbit_Inclination: 99.14 degrees Equator_Crossing: 9:30 am Period: 103 minutes Repeat_Cycle: 1 Orbit_Type: LEO &gt; Low Earth Orbit &gt; Polar Sun-Synchronous End_Group Creation_Date: 2008-07-09 Online_Resource: http://www.nspo.org.tw/2008e/projects/project2/intro.htm Online_Resource: http://www.spotimage.com/web/en/977--formosat-2-images.php Online_Resource: http://www.satimagingcorp.com/satellite-sensors/formosat-2.html Group: Platform_Logistics Launch_Date: 2004-05-20 Launch_Site: Vandenberg Air Force Base, USA Design_Life: 5 years Primary_Sponsor: National Space Program Office (NSPO), China End_Group End_Group 2019-02-19 17:35:33.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: 90818762-d67c-4404-8563-5938c0493d2d relationship type: null relationship value: null generated by: null); UK-DMC SSTL developed the UK-DMC-1 satellite (also known as BNSCsat-1) for the British National Space Centre (BNSC) under a grant from the Microsatellite Applications in Collaboration (MOSAIC) programme. Through UK-DMC, BNSC became the anchor tenant for the SSTL-led Disaster Monitoring Constellation (DMC), accelerating the formation of a full international consortium. UK-DMC is a satellite of the standard Disaster Monitoring Constellation (DMC) design, with added research and development payloads. Like all of the standard DMC satellites, it carries an optical imaging payload developed by SSTL to provide 32-m ground resolution with an exceptionally wide swath width of over 640 km. The payload uses green, red and near infrared bands equivalent to Landsat TM+ bands 2, 3 and 4. In comparison to the other DMC satellites, UK-DMC features increased on-board data storage, with 1.5 gigabyte capacity. Images are returned to the SSTL mission operations centre using the Internet Protocol over an 8-Mbps S-band downlink. UK-DMC also contains a commercial Internet router from Cisco Systems, which builds on the use of the Internet Protocol by the DMC satellites to experiment with Internet packet routing to and in space. UK-DMC has also provided an opportunity for SSTL to test a new concept in remote sensing, GPS reflectometry. This technique, which measures the signals from the GPS navigation system after they are reflected off the sea, could revolutionize oceanographic remote sensing. If UK-DMC validates theories of GPS reflectometry, the technique could one day enable satellites to measure the height of waves on the high seas, providing important data to ship owners and operators. SSTL is using imagery from the UK-DMC to investigate the full range of uses for large-coverage images with medium spatial resolution and high temporal resolution. The UK-DMC satellite will also operate as part of a constellation providing images to disaster relief agencies worldwide in times of need. Group: Platform_Details Entry_ID: UK-DMC Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: UK-DMC End_Group Group: Synonymous_Platform_Names Short_Name: BNSCSAT End_Group Group: Platform_Associated_Instruments Short_Name: GPS Short_Name: SLIM-6 End_Group Group: Orbit Orbit_Altitude: 686 Km Orbit_Inclination: 98.0 degrees Period: 98.4 min Perigee: 675 Apogee: 692 Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2008-06-04 Online_Resource: https://earth.esa.int/web/guest/missions/3rd-party-missions/current-missions/uk-dmc Online_Resource: https://directory.eoportal.org/web/eoportal/satellite-missions/u/uk-dmc-2 Group: Platform_Logistics Launch_Date: 2003-09-27 Launch_Site: Plesetsk Cosmodrome, Russia Primary_Sponsor: British National Space Centre (BNSC) Primary_Sponsor: Surrey Satellite Technology Ltd. (SSTL) End_Group End_Group JPSS-3 JPSS-3 is the fourth spacecraft within NOAA's next generation of polar-orbiting satellites. It is scheduled to launch in 2026. Benefiting from on the success of previous JPSS spacecrafts, JPSS-3 contains five similar instruments: (1) VIIRS, (2) CrIS, (3) ATMS, (4) OMPS-N, and (5) RBI. More Information: https://www.jpss.noaa.gov 2019-10-04 19:37:12.0 [sritz] update Definition (JPSS-3 is the fourth spacecraft within NOAA's next generation of polar-orbiting satellites. It is scheduled to launch in 2026. Benefiting from on the success of previous JPSS spacecrafts, JPSS-3 contains five similar instruments: (1) VIIRS, (2) CrIS, (3) ATMS, (4) OMPS-N, and (5) RBI. More Information: https://www.jpss.noaa.gov); update Definition (Source: NOAA JPSS, https://www.jpss.noaa.gov/mission_and_instruments.html); 2018-02-02 17:13:46.0 [sritz] update WeightedRelation (Platform-Instrument); update WeightedRelation (1); 2018-02-02 17:13:14.0 [sritz] insert WeightedRelation (id: null related concept uuid: de7e08db-86f1-4593-ba9e-288f9f7b063e relationship type: null relationship value: null generated by: null); 2018-01-30 22:35:08.0 [sritz] delete WeightedRelation (null); insert WeightedRelation (id: null related concept uuid: 91923fed-61c3-4125-b69d-1eeccafce52c relationship type: null relationship value: null generated by: null); 2018-01-30 22:12:49.0 [sritz] insert WeightedRelation (id: null related concept uuid: dd7c719e-5767-4ceb-b83a-66c1401dab4a relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 5ad54972-6d91-4860-aea4-7914fe7ef823 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 9a68e783-b54c-41f2-82ce-da975af38359 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 6af7a52e-094d-4ba7-9174-ed967260939c relationship type: null relationship value: null generated by: null); 2016-07-19 19:16:06.0 [saritz] update WeightedRelation (Similar); update WeightedRelation (1); update WeightedRelation (Similar); update WeightedRelation (1); update WeightedRelation (Similar); update WeightedRelation (1); update WeightedRelation (Similar); update WeightedRelation (1); update WeightedRelation (Similar); update WeightedRelation (1); 2016-07-19 19:08:23.0 [saritz] insert WeightedRelation (id: null related concept uuid: 10adce36-ce10-4ae6-94f9-211911c7dd15 relationship type: null relationship value: null generated by: null); 2016-07-19 19:07:51.0 [saritz] insert WeightedRelation (id: null related concept uuid: 043dc242-1014-4e9a-91ee-c472b791b026 relationship type: null relationship value: null generated by: null); 2016-07-19 19:07:04.0 [saritz] insert WeightedRelation (id: null related concept uuid: 5c2364ca-c01a-4f69-8808-282c3854b2f6 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 586db0b3-5f94-466e-b7c1-a2dbedc0c1fc relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 85a52725-e6a1-430a-8506-c08c59ef31c7 relationship type: null relationship value: null generated by: null); 2016-07-19 19:05:54.0 [saritz] insert Definition (id: null text: JPSS-3 is the fourth spacecraft within NOAA's next generation of polar-orbiting satellites. It is scheduled to launch in 2026. Benefiting from on the success of previous JPSS spacecrafts, JPSS-3 contains five similar instruments: (1) VIIRS, (2) CrIS, (3) ATMS, (4) OMPS-N, and (5) RBI. language code: en); 2016-07-19 18:46:51.0 [saritz] Insert Concept add broader relation (JPSS-3 [2ab4ba32-0bb3-4e4e-bac6-1ff4a3baf0df,247453] - Joint Polar Satellite System (JPSS) [5c2364ca-c01a-4f69-8808-282c3854b2f6,226695]); Sonsub Innovator The Innovator is Sonsub’s new in-house manufactured, high-specification, high reliability, 3500 meter depth-rated, 150 HP ROV, capable of performing demanding deep-water construction and drill support tasks. The Innovator has many ground-breaking features which serve to minimize the amount of optical and electrical subsea equipment necessary for operations, while improving performance, flexibility, and reliability of the key components. The versatility of the Innovator allows it to perform a variety of functions as well as act as a platform for the operation of a suite of task specific, Sonsub built tools and equipment. 2020-01-21 18:08:31.0 [tstevens] insert Definition (id: null text: The Innovator is Sonsub’s new in-house manufactured, high-specification, high reliability, 3500 meter depth-rated, 150 HP ROV, capable of performing demanding deep-water construction and drill support tasks. The Innovator has many ground-breaking features which serve to minimize the amount of optical and electrical subsea equipment necessary for operations, while improving performance, flexibility, and reliability of the key components. The versatility of the Innovator allows it to perform a variety of functions as well as act as a platform for the operation of a suite of task specific, Sonsub built tools and equipment. language code: en); 2020-01-21 17:25:56.0 [tstevens] Insert Concept add broader relation (Sonsub Innovator [2adc78b1-be95-4cec-82a9-603f6a493d5b,559735] - ROV [da6420b6-48ec-4ae2-98c7-0ef0538815a0,542741]); GOES-11 [Update 2011-12-12: GOES-15 replaced GOES-11 as the GOES-West operational spacecraft on 2011-12-06, Source: http://noaasis.noaa.gov/NOAASIS/ml/status.html ] [Text For Archival Purposes only] GOES-11 (GOES-L) was launched May 3, 2000 from Cape Canaveral Air Station. The spacecraft will continue the long term geostationary monitoring of U.S. weather. The spacecraft will monitor hurricanes, severe thunderstorms, flash floods, and other severe weather as well as provide short-term weather forecasting or nowcasting. Combined with Doppler radar and automated surface weather stations, real-time GOES data will greatly aid weather foecasters in providing better warnings of severe weather. NOAA's National Environmmental Satellite, Data, and Information Service will operate GOES. The instrument package includes a GOES I-M Imager and GOES I-M Sounder. For more information see: http://www.oso.noaa.gov/goes/ Group: Platform_Details Entry_ID: GOES-11 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: GOES (Geostationary Operational Environmental Satellite) Short_Name: GOES-11 Long_Name: Geostationary Operational Environmental Satellite 11 End_Group Group: Synonymous_Platform_Names Short_Name: GOES-L Short_Name: GOES-NEXT Short_Name: 26352 End_Group Group: Platform_Associated_Instruments Short_Name: GOES I-M IMAGER Short_Name: GOES I-M SOUNDER End_Group Group: Orbit Perigee: 35.790 (km) Apogee: 35.7917 (km) Orbit_Type: GEO > Geosynchronous > Geostationary End_Group Creation_Date: 2007-10-03 Online_Resource: http://www.oso.noaa.gov/goes/ Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=2000-022A Online_Resource: http://goes.gsfc.nasa.gov/ Sample_Image: http://www.noaanews.noaa.gov/stories/images/goes-spacecraft.gif Group: Platform_Logistics Launch_Date: 2000-05-03 Primary_Sponsor: USA/NASA Primary_Sponsor: USA/NOAA End_Group End_Group CBERS (China-Brazil Earth Resources Satellite) Elektro-L N3 Elektro-L No.3 3rd flight unit of the Electro-L series. Mission: operational meteorology. Substantial contribution to space weather. Launch Date: 2019-12-24 More Information: https://www.wmo-sat.info/oscar/satellites/view/474 https://www.nasaspaceflight.com/2019/12/russian-proton-m-new-geostationary-weather-satellite/ 2019-12-31 17:36:54.0 [sritz] update Definition (3rd flight unit of the Electro-L series. Mission: operational meteorology. Substantial contribution to space weather. Launch Date: 2019-12-24 More Information: https://www.wmo-sat.info/oscar/satellites/view/474 https://www.nasaspaceflight.com/2019/12/russian-proton-m-new-geostationary-weather-satellite/); 2019-12-31 17:31:49.0 [sritz] update Definition (3rd flight unit of the Electro-L series. Mission: operational meteorology. Substantial contribution to space weather. Launch Date: 2019-12-24 More Information: https://www.wmo-sat.info/oscar/satellites/view/474); 2019-12-31 17:30:35.0 [sritz] update Definition (3rd flight unit of the Electro-L series. Mission: operational meteorology. Substantial contribution to space weather. More Information: https://www.wmo-sat.info/oscar/satellites/view/474); 2019-12-31 17:29:24.0 [sritz] insert AltLabel (id: null category: null text: Elektro-L No.3 language code: en); insert Definition (id: null text: https://www.wmo-sat.info/oscar/satellites/view/474 language code: en); 2019-12-31 17:24:56.0 [sritz] Insert Concept add broader relation (Elektro-L N3 [2c780dff-fce3-4625-8b89-a7cd2d64d6ec,559585] - Elektro-L [882c16a9-0bc6-4773-8066-e25ea8de3c9d,559581]); GEOSTATIONARY SATELLITES Geostationary satellites are satellites that travel above Earth's equator from west to east at an altitude of approximately 35,900 kilometers (22,300 miles) and at a speed matching that of Earth's rotation, thus remaining stationary in relation to Earth. [Source: The American Heritageý Dictionary of the English Language, Fourth Edition Copyright ý 2000 by Houghton Mifflin Company.] GOES-7 [Source: NASA NSSDC, http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1987-022A ] GOES 7 was launched in February 1987 and was a NASA-developed, NOAA-operated, geosynchronous, and operational spacecraft. The cylindrically shaped spacecraft measured 190.5 cm in diameter and 230 cm in length, exclusive of a magnetometer that extended an additional 83 cm beyond the cylinder shell. The primary structural members were a honeycombed equipment shelf and thrust tube. The VISSR telescope was mounted on the equipment shelf and viewed the Earth through a special aperture in the side of the spacecraft. A support structure extended radially out from the thrust tube and was affixed to the solar panels, which formed the outer walls of the spacecraft and provided the primary source of electrical power. Located in the annulus-shaped space between the thrust tube and the solar panels were stationkeeping and dynamics control equipment, batteries, and most of the SEM equipment. Proper spacecraft attitude and spin rate (approximately 100 rpm) were maintained by two separate sets of jet thrusters mounted around the spacecraft equator and activated by ground command. The spacecraft used both UHF-band and S-band frequencies in its telemetry and command subsystem. A low-power VHF transponder provided telemetry and command during launch and then served as a backup for the primary subsystem once the spacecraft attained orbit. The spin-stabilized spacecraft carried a visible infrared spin-scan radiometer atmospheric sounder, meteorological data collection and transmission system, space environment monitor, energetic particle monitor, and a magnetic field monitor. GOES 7 was positioned at 98 degrees West in the summer (Atlantic hurricane season) and 108 degrees West in the winter (Pacific storm season). For more information on GOES satellites: http://www.oso.noaa.gov/goes/ Group: Platform_Details Entry_ID: GOES-7 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: GOES (Geostationary Operational Environmental Satellite) Short_Name: GOES-7 Long_Name: Geostationary Operational Environmental Satellite 7 End_Group Group: Synonymous_Platform_Names Short_Name: GOES H Short_Name: PEACESAT Short_Name: 17561 End_Group Group: Platform_Associated_Instruments Short_Name: SXM Short_Name: EPM Short_Name: VAS End_Group Group: Orbit Orbit_Inclination: 0.10000000149011612° Period: 1440.0 minutes Perigee: 35788.0 km Apogee: 35788.0 km Orbit_Type: GEO > GEOSYNCHRONOUS > GEOSTATIONARY End_Group Creation_Date: 2007-10-04 Online_Resource: http://www.oso.noaa.gov/goes/ Online_Resource: http://goespoes.gsfc.nasa.gov/goes/ Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1987-022A Sample_Image: http://library01.gsfc.nasa.gov/gdprojs/images/goes_2.jpg Group: Platform_Logistics Launch_Date: 1987-02-26 Launch_Site: CAPE CANAVERAL/KENNEDY SPACE CENTER, USA Primary_Sponsor: USA/NASA Primary_Sponsor: USA/NOAA End_Group End_Group SENTINEL-2 The Sentinel-2 mission is a land monitoring constellation of two satellites that provide high resolution optical imagery and provide continuity for the current SPOT and Landsat missions. The orbit is an average height of 785 km and the presence of two satellites in the mission allow repeated surveys every 5 days at the equator and every 2-3 days at middle latitudes. The satellites are equipped with the state-of-the-art MSI (Multispectral Imager) instrument for surveying with a resolution of 10 to 60 m in the visible, near infrared (VNIR), and short-wave infrared (SWIR) spectral zones, including 13 spectral channels, which ensures the capture of differences in vegetation state, including temporal changes, and also minimizes impact on the quality of atmospheric photography. Sentinel-2A was launched June 23, 2015. 2020-02-12 16:40:58.0 [sritz] Move Concepts add narrower relation (SENTINEL-2 [2ce20983-98b2-40b9-bb0e-a08074fb93b3,541455] - SENTINEL-2A [6f1c359b-b1a6-47c1-979e-0689e637fbdc,559807]); 2020-02-12 16:40:48.0 [sritz] Move Concepts add narrower relation (SENTINEL-2 [2ce20983-98b2-40b9-bb0e-a08074fb93b3,541455] - SENTINEL-2B [f2445400-1981-4ef3-bf7c-f4aa35923ae9,559803]); 2020-02-12 16:39:59.0 [sritz] Rename Concept update PrefLabel (SENTINEL-2); 2020-02-12 16:39:34.0 [sritz] Move Concepts delete broader relation (null); add broader relation (SENTINEL-2A [2ce20983-98b2-40b9-bb0e-a08074fb93b3,541455] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,541501]); 2020-02-12 16:38:22.0 [sritz] Move Concepts delete broader relation (null); add broader relation (SENTINEL-2A [2ce20983-98b2-40b9-bb0e-a08074fb93b3,541455] - SENTINEL-2 [6f1c359b-b1a6-47c1-979e-0689e637fbdc,559807]); 2020-01-30 16:00:02.0 [tstevens] Move Concepts delete broader relation (null); add broader relation (SENTINEL-2A [2ce20983-98b2-40b9-bb0e-a08074fb93b3,541455] - SENTINEL-2 [6f1c359b-b1a6-47c1-979e-0689e637fbdc,559807]); 2020-01-29 12:31:31.0 [tstevens] update PrefLabel (SENTINEL-2A); update Definition (The Sentinel-2 mission is a land monitoring constellation of two satellites that provide high resolution optical imagery and provide continuity for the current SPOT and Landsat missions. The orbit is an average height of 785 km and the presence of two satellites in the mission allow repeated surveys every 5 days at the equator and every 2-3 days at middle latitudes. The satellites are equipped with the state-of-the-art MSI (Multispectral Imager) instrument for surveying with a resolution of 10 to 60 m in the visible, near infrared (VNIR), and short-wave infrared (SWIR) spectral zones, including 13 spectral channels, which ensures the capture of differences in vegetation state, including temporal changes, and also minimizes impact on the quality of atmospheric photography. Sentinel-2A was launched June 23, 2015.); update Definition (https://earth.esa.int/web/guest/missions/esa-operational-eo-missions/sentinel-2); 2018-11-29 19:10:56.0 [mmorahan] delete AltLabel (null); 2018-11-05 12:46:30.0 [mmorahan] update Definition (PREFERRED TERMS: 2A, S2B, S2C, S2D, Sentinel-2 DEFINITION The Sentinel-2 mission is a land monitoring constellation of two satellites that provide high resolution optical imagery and provide continuity for the current SPOT and Landsat missions. The mission provides a global coverage of the Earth's land surface every 10 days with one satellite and 5 days with 2 satellites, making the data of great use in on-going studies. The satellites are equipped with the state-of-the-art MSI (Multispectral Imager) instrument, that offers high-resolution optical imagery. BROADER CONCEPT: Earth Observation Satellite ENTRY TERMS: SENTINEL-2 NOTE: A,B,C,D HOSTS: MSI URI: https://earth.esa.int/concept/sentinel-2); 2018-11-05 12:31:17.0 [mmorahan] Move Concepts delete broader relation (null); add broader relation (SENTINEL-2 [2ce20983-98b2-40b9-bb0e-a08074fb93b3,344721] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761]); 2018-11-05 12:31:03.0 [mmorahan] Cut Concepts delete broader relation (null); add broader relation (SENTINEL-2 [2ce20983-98b2-40b9-bb0e-a08074fb93b3,344721] - Trash Can/Platforms [6089b3e5-7db9-46e1-b73b-2d679f34abb4,354203]); 2018-10-23 10:25:45.0 [mmorahan] insert AltLabel (id: null category: primary text: Sentinel-2 Multispectral Imager language code: en); update Resource (image); insert WeightedRelation (id: null related concept uuid: fc57a9a0-a287-4bcf-a517-20811b55596b relationship type: null relationship value: null generated by: null); 2018-06-12 19:26:01.0 [mmorahan] Move Concepts delete broader relation (null); add broader relation (SENTINEL-2 [2ce20983-98b2-40b9-bb0e-a08074fb93b3,344721] - Sentinel GMES [2c9f1fcc-d9c8-4c6d-b701-45c97cee511f,344719]); 2018-06-12 19:18:56.0 [mmorahan] Move Concepts delete broader relation (null); add broader relation (SENTINEL-2 [2ce20983-98b2-40b9-bb0e-a08074fb93b3,344721] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761]); 2018-06-12 19:18:11.0 [mmorahan] Cut Concepts delete broader relation (null); add broader relation (SENTINEL-2 [2ce20983-98b2-40b9-bb0e-a08074fb93b3,344721] - Trash Can/Platforms [6089b3e5-7db9-46e1-b73b-2d679f34abb4,354203]); 2018-06-12 19:16:50.0 [mmorahan] Move Concepts delete broader relation (null); add broader relation (SENTINEL-2 [2ce20983-98b2-40b9-bb0e-a08074fb93b3,344721] - Sentinel GMES [2c9f1fcc-d9c8-4c6d-b701-45c97cee511f,344719]); RASI Regional Air-Sea Interaction Regional Air-Sea Interaction analyses Group: Platform_Details Entry_ID: RASI Group: Platform_Identification Platform_Category: MODELS/ANALYSES Short_Name: RASI Long_Name: REGIONAL AIR-SEA INTERACTION End_Group Creation_Date: 2014-11-07 End_Group 2014-11-07 15:41:04.0 [epneff] added RASI keyword at request of GHRC insert AltLabel (id: null text: Regional Air-Sea Interaction language code: en); 2014-11-07 15:40:23.0 [epneff] Insert Concept add broader relation (RASI [2d0c75bf-49bc-4a76-bd77-b179ea677bc2,106665] - Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,73395]); ESSA-7 TOS-E The ESSA-7 satellite replaced ESSA-5 and provided cloud cover photography to the US's National Meteorological Center for the purpose of preparing operational weather analyses and forecasts. The spacecraft was an 18-sided polygon, 42 inches in diameter, 22 inches high and weighed 320 pounds. The craft was made of aluminum alloy and stainless steel then covered with 9100 solar cells. The solar cells served to charge the 63 nickel-cadmium batteries. The two cameras were mounted 180-degrees opposite each other along the side of the cylindrical craft. The "cartwheel" configuration of the TIROS-9 was selected as the orbital configuration of the operational series of ESSA satellites. Therefore, a camera could be pointed at some point on Earth every time the satellite rotated along its axis. The spacecraft operating system was the same as on the TIROS-9. The craft was placed in its planned Sun-synchronous 102-degree inclination retrograde orbit. The satellite spin axis was rotated using the magnetic attitude control system into an alignment perpendicular to the orbital plane and tangent to the Earth's surface. The ESSA-7 system transmitted images covering 2000-square mile areas with 2-mile resolution from every location once per day. Two arrays of radiometer sensors were also mounted 180-degrees apart to measure the global distribution of solar radiation reflected by the Earth and the Earth's atmosphere, as well as the long wave emissions from the Earth (a contribution from the NIMBUS program). ESSA-7 Stats: Launch Date: August 16, 1968 Operational Period: 571 days until deactivated by NASA on March 10, 1970 Launch Vehicle: Two stage long tank Delta Launch Site: Vandenberg Air Force Base, CA Type: Weather Satellite 2018-11-14 15:40:00.0 [sritz] insert AltLabel (id: null category: null text: TOS-E language code: en); 2018-11-14 15:39:34.0 [sritz] insert AltLabel (id: null category: primary text: Environmental Science Services Administration Satellite 7 language code: en); 2018-10-30 17:04:01.0 [sritz] insert Definition (id: null text: The ESSA-7 satellite replaced ESSA-5 and provided cloud cover photography to the US's National Meteorological Center for the purpose of preparing operational weather analyses and forecasts. The spacecraft was an 18-sided polygon, 42 inches in diameter, 22 inches high and weighed 320 pounds. The craft was made of aluminum alloy and stainless steel then covered with 9100 solar cells. The solar cells served to charge the 63 nickel-cadmium batteries. The two cameras were mounted 180-degrees opposite each other along the side of the cylindrical craft. The "cartwheel" configuration of the TIROS-9 was selected as the orbital configuration of the operational series of ESSA satellites. Therefore, a camera could be pointed at some point on Earth every time the satellite rotated along its axis. The spacecraft operating system was the same as on the TIROS-9. The craft was placed in its planned Sun-synchronous 102-degree inclination retrograde orbit. The satellite spin axis was rotated using the magnetic attitude control system into an alignment perpendicular to the orbital plane and tangent to the Earth's surface. The ESSA-7 system transmitted images covering 2000-square mile areas with 2-mile resolution from every location once per day. Two arrays of radiometer sensors were also mounted 180-degrees apart to measure the global distribution of solar radiation reflected by the Earth and the Earth's atmosphere, as well as the long wave emissions from the Earth (a contribution from the NIMBUS program). ESSA-7 Stats: Launch Date: August 16, 1968 Operational Period: 571 days until deactivated by NASA on March 10, 1970 Launch Vehicle: Two stage long tank Delta Launch Site: Vandenberg Air Force Base, CA Type: Weather Satellite language code: en); 2018-10-30 15:45:23.0 [sritz] Insert Concept add broader relation (ESSA-7 [2e4252b9-5b53-41bb-8212-1e63a540181f,368207] - ESSA [65cb3e7c-d4d8-46df-a5fc-aec63e58e8df,345109]); Publications 2018-08-23 18:24:33.0 [sritz] Insert Concept add broader relation (Publications [2e555886-1baa-4f05-899b-1d14ab69fe62,368087] - In Situ Land-based Platforms [4f396ff6-7bea-4ba4-afa3-198ebd914a4a,344951]); GRACE [Source: NASA Science Mission Directorate, https://www.nasa.gov/mission_pages/Grace/ ] The primary goal of the GRACE mission is to accurately map variations in the Earth's gravity field over its 5-year lifetime. The GRACE mission has two identical spacecrafts flying about 220 kilometers apart in a polar orbit 500 kilometers above the Earth. It maps the Earth's gravity fields by making accurate measurements of the distance between the two satellites, using geodetic quality Global Positioning System (GPS) receivers and a microwave ranging system. This provides scientists from all over the world with an efficient and cost-effective way to map the Earth's gravity fields with unprecedented accuracy. The results from this mission yield crucial information about the distribution and flow of mass within the Earth and it's surroundings. The gravity variations that GRACE studies include: changes due to surface and deep currents in the ocean; runoff and ground water storage on land masses; exchanges between ice sheets or glaciers and the oceans; and variations of mass within the Earth. Another goal of the mission is to create a better profile of the Earth's atmosphere. The results from GRACE make a huge contribution to NASA's Earth science goals, Earth Observation System (EOS) and global climate change studies. GRACE is a joint partnership between the NASA in the United States and Deutsche Forschungsanstalt fur Luft und Raumfahrt (DLR) in Germany. Dr. Byron Tapley of The University of Texas Center for Space Research (UTCSR) is the Principal Investigator (PI), and Dr. Christoph Reigber of the GeoForschungsZentrum (GFZ) Potsdam is the Co-Principal Investigator (Co-PI). Project management and systems engineering activities are carried out by the Jet Propulsion Laboratory. Group: Platform_Details Entry_ID: GRACE Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: GRACE Long_Name: Gravity Recovery and Climate Experiment End_Group Group: Platform_Associated_Instruments Short_Name: BLACKJACK Short_Name: GPS Short_Name: GPS RECEIVERS Short_Name: GRACE LRR Short_Name: IPU Short_Name: KBR Short_Name: MAGNETOMETERS Short_Name: MTQ Short_Name: OBDH Short_Name: SCA Short_Name: SCS Short_Name: SLR Short_Name: SUPERSTAR Short_Name: THR Short_Name: TNK Short_Name: USO End_Group Group: Orbit Orbit_Inclination: 89 degrees Period: 94.5 minutes Perigee: 483.0 km Apogee: 508.0 km Orbit_Type: LEO > Low Earth Orbit > Polar Non-Sun-Synchronous End_Group Creation_Date: 2007-05-01 Online_Resource: https://www.nasa.gov/mission_pages/Grace/ Online_Resource: https://grace.jpl.nasa.gov/ Online_Resource: http://www2.csr.utexas.edu/grace/ Online_Resource: https://podaac.jpl.nasa.gov/grace/ Online_Resource: https://www.gfz-potsdam.de/grace/ Online_Resource: https://earthobservatory.nasa.gov/Features/GRACE/ Group: Platform_Logistics Launch_Date: 2002-03-17 Launch_Site: Plesetsk Cosmodrome, Russia Design_Life: 5 years Primary_Sponsor: USA/NASA Primary_Sponsor: Germany/DLR Primary_Sponsor: Potsdam/GFZ Primary_Sponsor: UTexas/Center for Space Research End_Group End_Group 2020-01-02 22:45:11.0 [sritz] update Definition ([Source: NASA Science Mission Directorate, https://www.nasa.gov/mission_pages/Grace/ ] The primary goal of the GRACE mission is to accurately map variations in the Earth's gravity field over its 5-year lifetime. The GRACE mission has two identical spacecrafts flying about 220 kilometers apart in a polar orbit 500 kilometers above the Earth. It maps the Earth's gravity fields by making accurate measurements of the distance between the two satellites, using geodetic quality Global Positioning System (GPS) receivers and a microwave ranging system. This provides scientists from all over the world with an efficient and cost-effective way to map the Earth's gravity fields with unprecedented accuracy. The results from this mission yield crucial information about the distribution and flow of mass within the Earth and it's surroundings. The gravity variations that GRACE studies include: changes due to surface and deep currents in the ocean; runoff and ground water storage on land masses; exchanges between ice sheets or glaciers and the oceans; and variations of mass within the Earth. Another goal of the mission is to create a better profile of the Earth's atmosphere. The results from GRACE make a huge contribution to NASA's Earth science goals, Earth Observation System (EOS) and global climate change studies. GRACE is a joint partnership between the NASA in the United States and Deutsche Forschungsanstalt fur Luft und Raumfahrt (DLR) in Germany. Dr. Byron Tapley of The University of Texas Center for Space Research (UTCSR) is the Principal Investigator (PI), and Dr. Christoph Reigber of the GeoForschungsZentrum (GFZ) Potsdam is the Co-Principal Investigator (Co-PI). Project management and systems engineering activities are carried out by the Jet Propulsion Laboratory. Group: Platform_Details Entry_ID: GRACE Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: GRACE Long_Name: Gravity Recovery and Climate Experiment End_Group Group: Platform_Associated_Instruments Short_Name: BLACKJACK Short_Name: GPS Short_Name: GPS RECEIVERS Short_Name: GRACE LRR Short_Name: IPU Short_Name: KBR Short_Name: MAGNETOMETERS Short_Name: MTQ Short_Name: OBDH Short_Name: SCA Short_Name: SCS Short_Name: SLR Short_Name: SUPERSTAR Short_Name: THR Short_Name: TNK Short_Name: USO End_Group Group: Orbit Orbit_Inclination: 89 degrees Period: 94.5 minutes Perigee: 483.0 km Apogee: 508.0 km Orbit_Type: LEO > Low Earth Orbit > Polar Non-Sun-Synchronous End_Group Creation_Date: 2007-05-01 Online_Resource: https://www.nasa.gov/mission_pages/Grace/ Online_Resource: https://grace.jpl.nasa.gov/ Online_Resource: http://www2.csr.utexas.edu/grace/ Online_Resource: https://podaac.jpl.nasa.gov/grace/ Online_Resource: https://www.gfz-potsdam.de/grace/ Online_Resource: https://earthobservatory.nasa.gov/Features/GRACE/ Group: Platform_Logistics Launch_Date: 2002-03-17 Launch_Site: Plesetsk Cosmodrome, Russia Design_Life: 5 years Primary_Sponsor: USA/NASA Primary_Sponsor: Germany/DLR Primary_Sponsor: Potsdam/GFZ Primary_Sponsor: UTexas/Center for Space Research End_Group End_Group); delete Resource (null); 2018-03-13 18:28:47.0 [sritz] update Definition ([Source: NASA Science Mission Directorate, https://www.nasa.gov/mission_pages/Grace/ ] The primary goal of the GRACE mission is to accurately map variations in the Earth's gravity field over its 5-year lifetime. The GRACE mission has two identical spacecrafts flying about 220 kilometers apart in a polar orbit 500 kilometers above the Earth. It maps the Earth's gravity fields by making accurate measurements of the distance between the two satellites, using geodetic quality Global Positioning System (GPS) receivers and a microwave ranging system. This provides scientists from all over the world with an efficient and cost-effective way to map the Earth's gravity fields with unprecedented accuracy. The results from this mission yield crucial information about the distribution and flow of mass within the Earth and it's surroundings. The gravity variations that GRACE studies include: changes due to surface and deep currents in the ocean; runoff and ground water storage on land masses; exchanges between ice sheets or glaciers and the oceans; and variations of mass within the Earth. Another goal of the mission is to create a better profile of the Earth's atmosphere. The results from GRACE make a huge contribution to NASA's Earth science goals, Earth Observation System (EOS) and global climate change studies. GRACE is a joint partnership between the NASA in the United States and Deutsche Forschungsanstalt fur Luft und Raumfahrt (DLR) in Germany. Dr. Byron Tapley of The University of Texas Center for Space Research (UTCSR) is the Principal Investigator (PI), and Dr. Christoph Reigber of the GeoForschungsZentrum (GFZ) Potsdam is the Co-Principal Investigator (Co-PI). Project management and systems engineering activities are carried out by the Jet Propulsion Laboratory. Group: Platform_Details Entry_ID: GRACE Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: GRACE Long_Name: Gravity Recovery and Climate Experiment End_Group Group: Platform_Associated_Instruments Short_Name: BLACKJACK Short_Name: GPS Short_Name: GPS RECEIVERS Short_Name: GRACE LRR Short_Name: IPU Short_Name: KBR Short_Name: MAGNETOMETERS Short_Name: MTQ Short_Name: OBDH Short_Name: SCA Short_Name: SCS Short_Name: SLR Short_Name: SUPERSTAR Short_Name: THR Short_Name: TNK Short_Name: USO End_Group Group: Orbit Orbit_Inclination: 89 degrees Period: 94.5 minutes Perigee: 483.0 km Apogee: 508.0 km Orbit_Type: LEO > Low Earth Orbit > Polar Non-Sun-Synchronous End_Group Creation_Date: 2007-05-01 Online_Resource: https://www.nasa.gov/mission_pages/Grace/index.html Online_Resource: https://grace.jpl.nasa.gov/ Online_Resource: http://www2.csr.utexas.edu/grace/ Online_Resource: https://podaac.jpl.nasa.gov/grace/ Online_Resource: https://www.gfz-potsdam.de/grace/ Online_Resource: https://earthobservatory.nasa.gov/Features/GRACE/ Group: Platform_Logistics Launch_Date: 2002-03-17 Launch_Site: Plesetsk Cosmodrome, Russia Design_Life: 5 years Primary_Sponsor: USA/NASA Primary_Sponsor: Germany/DLR Primary_Sponsor: Potsdam/GFZ Primary_Sponsor: UTexas/Center for Space Research End_Group End_Group); update Resource (image); NCEP-ETA 2015-08-10 18:49:54.0 [epneff] added long name update PrefLabel (NCEP-ETA); 2015-08-10 18:46:05.0 [epneff] added long name insert AltLabel (id: null text: NCEP Eta Model language code: en); 2015-08-10 18:45:43.0 [epneff] Insert Concept add broader relation (ETA [2ecfc2b9-118b-4462-9352-9193eef0a1dc,158227] - Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215]); DMSP 5D-3/F16 [Source: National Space Science Data Center, http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=2003-048A ] DMSP F16 (USA 172) was launched by a Titan 2 rocket from Vandenberg AFB at 16:17 UT on 18 October 2003. The Defense Meteorological Satellite Program (DMSP) is a Department of Defense (DoD) program run by the Air Force Space and Missle Systems Center (SMC). The program designs, builds, launches, and maintains satellites monitoring the meteorological, oceanographic, and solar-terrestrial physics environments. Each DMSP satellite has a 101 minute, sun-synchronous near-polar orbit at an altitude of 830km above the surface of the earth. The visible and infrared sensors (OLS) collect images across a 3000 km swath, providing global coverage twice per day. The combination of day/night and dawn/dusk satellites allows monitoring of global information such as clouds every 6 hours. The microwave imager (SSMI) and sounders (SSMT1, SSMT2) cover one half the width of the visible and infrared swath. These instruments cover polar regions at least twice and the equatorial region once per day. The space environment sensors (SSJ, SSM, SSIES) record along-track plasma densities, velocities, composition and drifts (SS stands for Special Sensor). DMSP F16 carries two new experiments: the limb scanning ultraviolet imager/spectrometer SSULI built by the Naval Research Laboratory and the nadir scanning ultaviolet imager/spectrometer and photometer SSUSI built by the Applied Physics Laboratory at Johns Hopkins University. It also carried new versions of the Special Sensor for Ions, Electrons and Scintillations (SSIES-13) and of the precipitating ion and electron monitor (SSJ-5) The data from the DMSP satellites are received and used at operational centers continuously. The data are sent to the National Geophysical Data Center's Solar Terrestrial Physics Division (NGDC/STP) by the Air Force Weather Agency (AFWA) for creation of an archive. Group: Platform_Details Entry_ID: DMSP 5D-3/F16 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: DMSP (Defense Meteorological Satellite Program) Short_Name: DMSP 5D-3/F16 Long_Name: Defense Meteorological Satellite Program-F16 End_Group Group: Synonymous_Platform_Names Short_Name: DMSP-F16 Short_Name: USA 172 Short_Name: 28054 End_Group Group: Platform_Associated_Instruments Short_Name: SSULI Short_Name: OLS Short_Name: SSM/T Short_Name: SSIES Short_Name: SSJ/4 Short_Name: SSM/I Short_Name: SSM/T-2 Short_Name: SSM End_Group Group: Orbit Orbit_Altitude: 830km Orbit_Inclination: 98.9° Period: 101.9 minutes Perigee: 843.0 km Apogee: 853.0 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2008-10-31 Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=2003-048A Online_Resource: http://www.ngdc.noaa.gov/dmsp/ Group: Platform_Logistics Launch_Date: 2003-10-18 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: Department of Defense-Department of the Air Force (United States) End_Group End_Group FY-3A Storm III (FY-3) satellite is China's second-generation polar orbit meteorological satellite, which is the basis of FY-1 meteorological satellite technology on the development and improvement in function and technology a big step forward with qualitative change, specific requirements to solve the three-dimensional atmospheric detection, ability to obtain substantial increase in global data to further enhance the cloud and surface characteristics of remote sensing capabilities, enabling access to global, all-weather, three-dimensional, quantitative, multi-spectral atmosphere, surface and sea surface parameters. FY-3 meteorological satellite applications for purposes such as four aspects: ● the provision of global numerical weather prediction for the medium-term resolution of the meteorological parameters uniform. ● study of global change, including climate variation, climate prediction for the variety of meteorological and geophysical parameters. ● monitoring of large-scale natural disasters and the surface environment. ● for a variety of professional activities (aviation, maritime, etc.) of any region to provide global weather information, meteorological support services for the military. FY-3 research and production is divided into two batches, 01 batches of two satellites, FY-3A has been on 7 May 2008 successfully launched. 02 star award in 2010 after the launch, and some remote sensing instruments for the addition, replacement and performance improvements, FY-3 satellites will apply 15 years. Group: Platform_Details Entry_ID: FY-3A Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: FY-3A Long_Name: FengYun-3A End_Group Group: Platform_Associated_Instruments Short_Name: SIM Short_Name: IRAS Short_Name: MWTS Short_Name: MWRI Short_Name: MWHS Short_Name: TOU Short_Name: MERSI Short_Name: VIRR Short_Name: SBUS Short_Name: ERM End_Group Group: Orbit Orbit_Altitude: 836 km Orbit_Inclination: 98.75 Equator_Crossing: descending node local time 10:00 AM ~ 10:20 AM Local time: e.g. Period: 101 Orbit_Type: LEO > LOW EARTH ORBIT > POLAR NON-SUN-SYNCHRONOUS End_Group Creation_Date: 2011-02-09 Online_Resource: http://www.nsmc.cma.gov.cn/NewSite/NSMC_EN/Channels/100184.html Online_Resource: http://satellite.cma.gov.cn/ArssEn/Ord/Satellite.aspx Group: Platform_Logistics Launch_Date: 2008-05-27 Launch_Site: TAIYUAN SPACE LAUNCH CENTER, CHINA Primary_Sponsor: China/NSMC End_Group End_Group GOES-8 GOES 8 (GOES-I) was launched on April 13, 1994. On Tuesday April 1, 2003 GOES-12 (Formerly Referred to as GOES-M) replaced GOES-8 as the operational GOES East Satellite. NOAA deactivated the satellite on May 5, 2004 and will boost it into an orbit 350 kilometers above its original geostationary position, where it will be disposed safely in three controlled burns. GOES I-M represented the next generation of meteorological satellites and introduces two new features. The first feature, flexible scan, offers small-scale area imaging that lets meteorologists take pictures of local weather trouble spots. This allows them to improve short-term forecasts over local areas. The second feature, simultaneous and independent imaging and sounding, is designed to allow weather forecasters to use multiple measurements of weather phenomena to increase the accuracy of their forecasts. Each satellite in the series carries two major instruments: an Imager and a Sounder. These instruments acquire high resolution visible and infrared data, as well as temperature and moisture profiles of the atmosphere. They continuously transmit these data to ground terminals where the data are processed for rebroadcast to primary weather services both in the United States and around the world, including the global research community. The GOES I-M mission ran from the mid-1990s into the first decade of the 21st century. Each element of the mission has been designed to meet all in-orbit performance requirements for at least five years. The GOES I-M system performed the following basic functions: + Acquisition, processing, and dissemination of imaging and sounding data. + Acquisition and dissemination of Space Environment Monitor (SEM) data. + Reception and relay of data from ground-based Data Collection Platforms (DCPs) that are situated in carefully selected urban and remote areas to the NOAA Command and Data Acquisition (CDA) station. + Continuous relay of Weather Facsimile (WEFAX) and other data to users, independent of all other functions. + Relay of distress signals from people, aircraft, or marine vessels to the search and rescue ground stations of the Search and Rescue Satellite Aided Tracking (SARSAT) system. GOES provides the instantaneous relay functions for the SARSAT system. A dedicated search and rescue transponder on board GOES is designed to detect emergency distress signals originating from Earth-based sources. These unique identification signals are normally combined with signals received by a low-Earth orbiting satellite system and relayed to a search and rescue ground terminal. The combined data are used to perform effective search and rescue operations. The GOES I-M system serves a region covering the central and eastern Pacific Ocean; North, Central, and South America; and the central and western Atlantic Ocean. Pacific coverage includes Hawaii and the Gulf of Alaska. This is accomplished by two satellites, GOES West located at 135 west longitude and GOES East at 75 west longitude. A common ground station, the CDA station located at Wallops, Virginia, supports the interface to both satellites. The NOAA Satellite Operations Control Center (SOCC), in Suitland, Maryland, provides spacecraft scheduling, health and safety monitoring, and engineering analyses. Delivery of products involves ground processing of the raw instrument data for radiometric calibration and Earth location information, and retransmission to the satellite for relay to the data user community. The processed data are received at the control center and disseminated to the National Weather Service's (NWS) National Meteorological Center, Camp Springs, Maryland, and NWS forecast offices, including the National Hurricane Center, Miami, Florida, and the National Severe Storms Forecast Center, Kansas City, Missouri. Processed data are also received by Department of Defense installations, universities, and numerous private commercial users. MAIN SPACECRAFT DESIGN ELEMENTS Mission life 5 years, minimum Dimensions Main body 2 meter (7 foot) cube Deployed length 27 meters (88 feet) Weight 2100 kg (4600 lb) Orbit Geosynchronous Altitude 36,000 km (22,000 mi) Longitude 75W and 135W Latitude equatorial, within 0.5 degree Power 1050 watts @ 42 volts, solar array; battery backup Launch vehicle Atlas-I/Centaur (GOES-I/K), Atlas-II/Centaur (GOES-L/M) Communications Imager and Sounder in GVAR format at 2.1 Mbits/sec GOES-I/M IMAGER The GOES Imager is a multi-channel instrument designed to sense radiant and solar-reflected energy from sampled areas of the Earth. The multi-element spectral channels simultaneously sweep east-west and west-east along a north-to-south path by means of a two-axis mirror scan system. The instrument can produce full-Earth disc images, sector images that contain the edges of the Earth, and various sizes of area scans completely enclosed within the Earth scene using a new flexible scan system. Scan selection permits rapid continuous viewing of local areas for monitoring of mesoscale (regional) phenomena and accurate wind determination. IMAGER CHANNELS AND PRODUCTS CHANNEL 1 2* 3* 4 5* WAVELENGTH (um) 0.65 3.9 6.7 11 12 PRODUCT Clouds x x x x x Water Vapor* x x x Surface Temp. o x o Winds x x x Albedo + IR Flux x o x o Fires + Smoke x x o o KEY: * = new operational data x = primary channel o = secondary channel GOES-I/M SOUNDER The GOES Sounder is a 19-channel discrete-filter radiometer covering the spectral range from the visible channel wavelengths to 15 microns. It is designed to provide data from which atmospheric temperature and moisture profiles, surface and cloud-top temperatures, and ozone distribution can be deduced by mathematical analysis. It operates independently of and simultaneously with the Imager, using a similarly flexible scan system. The Sounder's multi-element detector array assemblies simultaneously sample four separate fields or atmospheric columns. A rotating filter wheel, which brings spectral filters into the optical path of the detector array, provides the infrared channel definition. PRODUCTS, RESOLUTION AND ACCURACY RESOLUTION (km) ACCURACY Vert. Horiz. Absolute Relative PRODUCT TEMPERATURE Profile 3-5 50 2-3 K 1 K Land --- 10 2 K 1 K Sea --- 10 1 K 0.5 K MOISTURE Profile 2-4 50 30% 20% Total --- 10 20% 10% Motion 3 layers 50 6 m/sec 3 m/sec CLOUD Height 2 layers 10 50 mb 25 mb Amount total 10 15% 5% OZONE* Total --- 50 30% 15% Motion 1 layer 50 10 m/sec 5 m/sec IR Flux* total 50 10 W/m^2 3 W/m^2 KEY: * = potential future product GOES 8 information is available at: http://www.ospo.noaa.gov/Operations/GOES/index.html 2017-09-01 17:09:41.0 [sritz] insert Definition (id: null text: GOES 8 (GOES-I) was launched on April 13, 1994. On Tuesday April 1, 2003 GOES-12 (Formerly Referred to as GOES-M) replaced GOES-8 as the operational GOES East Satellite. NOAA deactivated the satellite on May 5, 2004 and will boost it into an orbit 350 kilometers above its original geostationary position, where it will be disposed safely in three controlled burns. GOES I-M represented the next generation of meteorological satellites and introduces two new features. The first feature, flexible scan, offers small-scale area imaging that lets meteorologists take pictures of local weather trouble spots. This allows them to improve short-term forecasts over local areas. The second feature, simultaneous and independent imaging and sounding, is designed to allow weather forecasters to use multiple measurements of weather phenomena to increase the accuracy of their forecasts. Each satellite in the series carries two major instruments: an Imager and a Sounder. These instruments acquire high resolution visible and infrared data, as well as temperature and moisture profiles of the atmosphere. They continuously transmit these data to ground terminals where the data are processed for rebroadcast to primary weather services both in the United States and around the world, including the global research community. The GOES I-M mission ran from the mid-1990s into the first decade of the 21st century. Each element of the mission has been designed to meet all in-orbit performance requirements for at least five years. The GOES I-M system performed the following basic functions: + Acquisition, processing, and dissemination of imaging and sounding data. + Acquisition and dissemination of Space Environment Monitor (SEM) data. + Reception and relay of data from ground-based Data Collection Platforms (DCPs) that are situated in carefully selected urban and remote areas to the NOAA Command and Data Acquisition (CDA) station. + Continuous relay of Weather Facsimile (WEFAX) and other data to users, independent of all other functions. + Relay of distress signals from people, aircraft, or marine vessels to the search and rescue ground stations of the Search and Rescue Satellite Aided Tracking (SARSAT) system. GOES provides the instantaneous relay functions for the SARSAT system. A dedicated search and rescue transponder on board GOES is designed to detect emergency distress signals originating from Earth-based sources. These unique identification signals are normally combined with signals received by a low-Earth orbiting satellite system and relayed to a search and rescue ground terminal. The combined data are used to perform effective search and rescue operations. The GOES I-M system serves a region covering the central and eastern Pacific Ocean; North, Central, and South America; and the central and western Atlantic Ocean. Pacific coverage includes Hawaii and the Gulf of Alaska. This is accomplished by two satellites, GOES West located at 135 west longitude and GOES East at 75 west longitude. A common ground station, the CDA station located at Wallops, Virginia, supports the interface to both satellites. The NOAA Satellite Operations Control Center (SOCC), in Suitland, Maryland, provides spacecraft scheduling, health and safety monitoring, and engineering analyses. Delivery of products involves ground processing of the raw instrument data for radiometric calibration and Earth location information, and retransmission to the satellite for relay to the data user community. The processed data are received at the control center and disseminated to the National Weather Service's (NWS) National Meteorological Center, Camp Springs, Maryland, and NWS forecast offices, including the National Hurricane Center, Miami, Florida, and the National Severe Storms Forecast Center, Kansas City, Missouri. Processed data are also received by Department of Defense installations, universities, and numerous private commercial users. MAIN SPACECRAFT DESIGN ELEMENTS Mission life 5 years, minimum Dimensions Main body 2 meter (7 foot) cube Deployed length 27 meters (88 feet) Weight 2100 kg (4600 lb) Orbit Geosynchronous Altitude 36,000 km (22,000 mi) Longitude 75W and 135W Latitude equatorial, within 0.5 degree Power 1050 watts @ 42 volts, solar array; battery backup Launch vehicle Atlas-I/Centaur (GOES-I/K), Atlas-II/Centaur (GOES-L/M) Communications Imager and Sounder in GVAR format at 2.1 Mbits/sec GOES-I/M IMAGER The GOES Imager is a multi-channel instrument designed to sense radiant and solar-reflected energy from sampled areas of the Earth. The multi-element spectral channels simultaneously sweep east-west and west-east along a north-to-south path by means of a two-axis mirror scan system. The instrument can produce full-Earth disc images, sector images that contain the edges of the Earth, and various sizes of area scans completely enclosed within the Earth scene using a new flexible scan system. Scan selection permits rapid continuous viewing of local areas for monitoring of mesoscale (regional) phenomena and accurate wind determination. IMAGER CHANNELS AND PRODUCTS CHANNEL 1 2* 3* 4 5* WAVELENGTH (um) 0.65 3.9 6.7 11 12 PRODUCT Clouds x x x x x Water Vapor* x x x Surface Temp. o x o Winds x x x Albedo + IR Flux x o x o Fires + Smoke x x o o KEY: * = new operational data x = primary channel o = secondary channel GOES-I/M SOUNDER The GOES Sounder is a 19-channel discrete-filter radiometer covering the spectral range from the visible channel wavelengths to 15 microns. It is designed to provide data from which atmospheric temperature and moisture profiles, surface and cloud-top temperatures, and ozone distribution can be deduced by mathematical analysis. It operates independently of and simultaneously with the Imager, using a similarly flexible scan system. The Sounder's multi-element detector array assemblies simultaneously sample four separate fields or atmospheric columns. A rotating filter wheel, which brings spectral filters into the optical path of the detector array, provides the infrared channel definition. PRODUCTS, RESOLUTION AND ACCURACY RESOLUTION (km) ACCURACY Vert. Horiz. Absolute Relative PRODUCT TEMPERATURE Profile 3-5 50 2-3 K 1 K Land --- 10 2 K 1 K Sea --- 10 1 K 0.5 K MOISTURE Profile 2-4 50 30% 20% Total --- 10 20% 10% Motion 3 layers 50 6 m/sec 3 m/sec CLOUD Height 2 layers 10 50 mb 25 mb Amount total 10 15% 5% OZONE* Total --- 50 30% 15% Motion 1 layer 50 10 m/sec 5 m/sec IR Flux* total 50 10 W/m^2 3 W/m^2 KEY: * = potential future product GOES 8 information is available at: http://www.ospo.noaa.gov/Operations/GOES/index.html language code: en); 2017-09-01 16:46:07.0 [sritz] Insert Concept add broader relation (GOES-8 [2fa330c6-862b-408a-bdea-cc0eb502f3d2,310103] - GOES [6e332c25-caeb-4917-afb6-af757bcecd72,310071]); MIR II The MIR deep sea submersibles operate from the RV Akademik Keldysh. The Akademik Keldysh is the most advanced deep diving support vessel in the world. The operation is owned and operated by the PP Shirshov Institute, Russian Academy of Sciences. Its crew of scientists and technicians have worked together for over 20 years, participating in deep dive expeditions all over the world with both Pisces and MIR submersibles. Our expedition is only made possible with the support and expertise of Captain Yuriy Gorbach, his Keldysh crew and the MIR support team lead by Dr. Anatoly Sagalevitch. They are a highly skilled, professional team running one of the most unique and safest underwater operations in the world. The Keldysh and MIR I and II have been used for National Geographic photo and film projects, and director James Cameron's epic motion picture Titanic. In addition to its 17 laboratories, the Keldysh features a specialized library covering underwater geology, oceanography and deep-sea exploration. The habitation sphere (pressure hull) of the MIR submersible is 6 feet 10 inches (2.1 meters) in diameter and is specifically designed to carry three people -- in our case one expert pilot and two participants/observers. Inside the sphere it is "one atmosphere," just like a room in your home. Around the inside of the sphere are many controls, instruments, and electrical circuits. At the forward end of the sphere are three viewports, each providing a forward and a partial peripheral viewing arc. There are two couches/mattresses for the two participants/observers who can lay along these with their faces close to the viewing portholes (you can also sit or stand up to stretch and relax). The pilot sits or kneels at a central control console and guides the submersible using the main central porthole. There is no vision directly to the sides or the aft end of the submersible. 2020-01-21 19:42:35.0 [tstevens] insert Definition (id: null text: The MIR deep sea submersibles operate from the RV Akademik Keldysh. The Akademik Keldysh is the most advanced deep diving support vessel in the world. The operation is owned and operated by the PP Shirshov Institute, Russian Academy of Sciences. Its crew of scientists and technicians have worked together for over 20 years, participating in deep dive expeditions all over the world with both Pisces and MIR submersibles. Our expedition is only made possible with the support and expertise of Captain Yuriy Gorbach, his Keldysh crew and the MIR support team lead by Dr. Anatoly Sagalevitch. They are a highly skilled, professional team running one of the most unique and safest underwater operations in the world. The Keldysh and MIR I and II have been used for National Geographic photo and film projects, and director James Cameron's epic motion picture Titanic. In addition to its 17 laboratories, the Keldysh features a specialized library covering underwater geology, oceanography and deep-sea exploration. The habitation sphere (pressure hull) of the MIR submersible is 6 feet 10 inches (2.1 meters) in diameter and is specifically designed to carry three people -- in our case one expert pilot and two participants/observers. Inside the sphere it is "one atmosphere," just like a room in your home. Around the inside of the sphere are many controls, instruments, and electrical circuits. At the forward end of the sphere are three viewports, each providing a forward and a partial peripheral viewing arc. There are two couches/mattresses for the two participants/observers who can lay along these with their faces close to the viewing portholes (you can also sit or stand up to stretch and relax). The pilot sits or kneels at a central control console and guides the submersible using the main central porthole. There is no vision directly to the sides or the aft end of the submersible. language code: en); 2020-01-21 17:35:28.0 [tstevens] Insert Concept add broader relation (MIR II [2fcdab81-7527-4344-a26c-632746e94423,559787] - HOV [63c8aa1d-6efc-4943-8891-3a1cd520dde0,559759]); FY-2D NOAA-9 NOAA-9 (ATN series) was launched on December 12, 1984 and was a third-generation operational meteorological satellite. The satellite design provided an economical and stable sun-synchronous platform. This platform enables the satellite to carry advanced operational instruments to measure the earth's atmosphere, its surface and cloud cover, and the near-space environment. The satellite was based upon the Block 5D spacecraft bus developed for the U.S. Air Force, and was capable of maintaining an earth-pointing accuracy of better than plus or minus 0.1 degree with a motion rate of less than 0.035 degree/second. Primary sensors included (1) an Advanced Very High Resolution Radiometer (AVHRR), (2) a TIROS Operational Vertical Sounder (TOVS), (3) an Earth Radiation Budget Experiment (ERBE), and (4) a Solar Backscatter Ultraviolet Radiometer (SBUV/2). The secondary experiment was a Data Collection and Platform Location System (DCPLS). A Search and Rescue Satellite Aided Tracking (SARSAT) system was also carried on NOAA-9. Orbital Characteristics- Orbital Period: 102.00 m Inclination: 99.17 degrees Eccentricity: 0.00145 Periapsis: 841.00 km Apoapsis: 862.00 km To view a 3D orbit, observe the J track satellite tracking web page: "http://liftoff.msfc.nasa.gov/RealTime/JTrack" __________ Taken from the NSSDC System for Information Retrieval and Storage (SIRS). For more information contact the NSSDC Coordinated Request and User Support Office, 301-286-6695 (NASA Goddard Space Flight Center, Code 933.4, Greenbelt, Maryland 20771, USA, "http://nssdc.gsfc.nasa.gov/"). Group: Platform_Details Entry_ID: NOAA-9 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NOAA POES (Polar Orbiting Environmental Satellites) Short_Name: NOAA-9 Long_Name: National Oceanic & Atmospheric Administration-9 End_Group Group: Synonymous_Platform_Names Short_Name: NOAA-9 End_Group Group: Platform_Associated_Instruments Short_Name: AVHRR Short_Name: TOVS Short_Name: ERBE End_Group Group: Orbit Orbit_Inclination: 99.17 deg Period: 102 min Perigee: 841 km Apogee: 862 km End_Group Creation_Date: 2007-11-09 Online_Resource: http://nssdc.gsfc.nasa.gov/ Sample_Image: http://liftoff.msfc.nasa.gov/RealTime/JTrack Group: Platform_Logistics Launch_Date: 1984-12-12 Primary_Sponsor: NASA End_Group End_Group R/V YUZ RSS JAMES CLARK ROSS 2015-06-09 06:16:34.0 [aaleman] added new keyword insert AltLabel (id: null text: RSS JAMES CLARK ROSS language code: en); 2015-06-09 06:15:58.0 [aaleman] Insert Concept add broader relation (RSS JAMES CLARK ROSS [30585903-f838-4b9c-86c2-8778559475f7,158019] - SHIPS [82a67b12-e99d-4c90-8a6a-a6f79d4c3c7b,143897]); SOLAR RADIATION STATIONS Solar Radiation Stations: Stations that measure radiation from the sun. [Source: WordNet ? 1.6, ? 1997 Princeton University] STS-34 Space Transport System STS-34 Mission Objectives: Space Shuttle mission STS-34 will deploy the Galileo planetary exploration spacecraft into low-Earth orbit starting Galileo on its journey to explore Jupiter. Galileo will be the second planetary probe deployed from the Shuttle this year following Atlantis' successful launch of Magellan toward Venus exploration in May. [Summary provided by NASA] Group: Platform_Details Entry_ID: STS-34 Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Platform_Series_or_Entity: SPACE SHUTTLE Short_Name: STS-34 Long_Name: Space Transport System STS-34 End_Group Group: Synonymous_Platform_Names Short_Name: Atlantis End_Group Group: Orbit Orbit_Altitude: 185 Orbit_Inclination: 34.3 Period: 39 Repeat_Cycle: 4 End_Group Creation_Date: 2008-01-28 Online_Resource: http://science.ksc.nasa.gov/shuttle/missions/sts-34/mission-sts-34.html Sample_Image: http://www.ksc.nasa.gov/mirrors/images/images/pao/STS34/10063739.jpg Group: Platform_Logistics Launch_Date: 1989-10-23 Primary_Sponsor: NASA End_Group End_Group Sea Ice Mass Balance Station 2018-10-12 18:51:51.0 [sritz] Insert Concept add broader relation (Sea Ice Mass Balance Station [31e96f2f-9b8e-454f-a1f8-e8d791c13a33,368171] - OCEAN PLATFORM/OCEAN STATIONS [6ee1cf85-aa14-4fe9-a915-a8022830d8a7,345157]); SPACELAB-1 The first Spacelab mission was a joint NASA and European Space Agency (ESA) mission. Spacelab 1 consisted of a pressurized compartment (module) for housing equipment and flight personnel and a space-exposed platform to accommodate instruments. The compartment and platform were flown into space and returned inside the payload compartment of the Space Shuttle. The mission lasted 10 days, and while in space, the Shuttle payload compartment doors were opened to allow viewing of the earth, sun, and deep space. Spacelab 1 was a multidiscipline mission comprising five broad areas of investigation: Atmospheric Physics and Earth Observations, Space Plasma Physics, Astronomy and Solar Physics, Material Sciences and Technology, and Life Sciences. The Atmospheric Physics investigations conducted studies of the earth's environment through surveys of temperature, composition, and motion of the atmosphere. The Earth Observations investigations used and evaluated the capability of advanced measuring systems for making topographic and thematic maps from high-resolution photographs and from remote-sensing data. Investigations in the Space Plasma Physics group studied the charged particle or plasma environment of the earth. The Astronomy investigations studied astronomical sources of radiation in the ultraviolet and X-ray wavelengths. The Solar Physics investigations measured the total energy output of the sun using three different methods with the instruments cross calibrated so that meaningful comparisons could be made. The Material Sciences and Technology investigations took advantage of the microgravity conditions to perform studies in such areas as crystal growth, metallurgy, tribology, fluid physics, and ceramics technology. The Life Sciences investigations were concerned with the effects of the space environment (zero gravity and high-energy radiation) on human physiology and on the growth, development, and organization of biological systems. The mission was considered very successful. Group: Platform_Details Entry_ID: SPACELAB-1 Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Platform_Series_or_Entity: SPACE SHUTTLE Short_Name: SPACELAB-1 End_Group Group: Orbit Orbit_Inclination: 57 degrees Perigee: 242 km Apogee: 254 km End_Group Creation_Date: 2008-01-25 Online_Resource: http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/spacelab1.html Online_Resource: http://imagine.gsfc.nasa.gov/docs/sats_n_data/missions/spacelab1.html Sample_Image: http://upload.wikimedia.org/wikipedia/commons/thumb/6/61/Leroy_Chiao_inside_Destiny_space_lab.jpg/800px-Leroy_Chiao_inside_Destiny_space_lab.jpg Group: Platform_Logistics Launch_Date: 1983-11-28 Primary_Sponsor: NASA End_Group End_Group MESONET Mesoscale Meteorological Network (MESONET) are world-class network of environmental monitoring stations that gather current meteorological observations and send the data to their corresponding centers. Group: Platform_Details Entry_ID: MESONET Group: Platform_Identification Platform_Category: In Situ Land-based Platforms Platform_Series_or_Entity: WEATHER STATIONS/NETWORKS Short_Name: MESONET Long_Name: Mesoscale Meteorological Network End_Group Group: Synonymous_Platform_Names Short_Name: Mesonet End_Group Creation_Date: 2007-12-12 Online_Resource: http://en.wikipedia.org/wiki/Mesonet Sample_Image: http://www.srh.noaa.gov/mlb/digest/issue23/mesonet-map.jpg End_Group R/V XUELONG GPM [Text Source: NASA Science Missions Directorate Homepage, https://pmm.nasa.gov/GPM ] GPM Constellation is a joint mission with the Japan Aerospace Exploration Agency (JAXA) and other international partners. Building upon the success of the Tropical Rainfall Measuring Mission (TRMM), it will initiate the measurement of global precipitation, a key climate factor. Its science objectives are: to improve ongoing efforts to predict climate by providing near-global measurement of precipitation, its distribution, and physical processes; to improve the accuracy of weather and precipitation forecasts through more accurate measurement of rain rates and latent heating; and to provide more frequent and complete sampling of the Earth's precipitation. GPM Constellation is envisioned to consist of a core spacecraft to measure precipitation structure and to provide a calibration standard for the constellation spacecraft, an international constellation of NASA and contributed spacecraft to provide frequent precipitation measurements on a global basis, calibration/validation sites distributed globally with a broad array of precipitation-measuring instrumentation, and a global precipitation data system to produce and distribute global rain maps and climate research products. The GPM Core Observatory carries the first space-borne Ku/Ka-band Dual-frequency Precipitation Radar (DPR) and a multi-channel GPM Microwave Imager (GMI). The DPR instrument, which provides three dimensional measurements of precipitation structure over 78 and 152 mile (125 and 245 km) swaths, consists of a Ka-band precipitation radar (KaPR) operating at 35.5 GHz and a Ku-band precipitation radar (KuPR) operating at 13.6 GHz. Relative to the TRMM precipitation radar, the DPR is more sensitive to light rain rates and snowfall. In addition, simultaneous measurements by the overlapping of Ka/Ku-bands of the DPR can provide new information on particle drop size distributions over moderate precipitation intensities. In addition, by providing new microphysical measurements from the DPR to complement cloud and aerosol observations, GPM is expected to provide further insights into how precipitation processes may be affected by human activities. The GMI instrument is a conical-scanning multi-channel microwave radiometer covering a swath of 550 miles (885 km) with thirteen channels ranging in frequency from 10 GHz to 183 GHz. The GMI uses a set of frequencies that have been optimized over the past two decades to retrieve heavy, moderate and light precipitation using the polarization difference at each channel as an indicator of the optical thickness and water content. Group: Platform_Details Entry_ID: GPM Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: GPM Long_Name: Global Precipitation Measurement End_Group Group: Platform_Associated_Instruments Short_Name: GMI Short_Name: DPR End_Group Group: Orbit Orbit_Type: LEO > Low Earth Orbit > Polar Non-Sun-Synchronous End_Group Creation_Date: 2009-02-25 Online_Resource: https://pmm.nasa.gov/GPM Online_Resource: http://global.jaxa.jp/projects/sat/gpm/index.html Online_Resource: http://www.eorc.jaxa.jp/GPM/index_e.htm Group: Platform_Logistics Launch_Date: 2014-01-25 Launch_Site: TANEGASHIMA ISLAND, JAPAN Primary_Sponsor: USA/NASA Primary_Sponsor: JAPAN/JAXA End_Group End_Group 2018-04-24 20:32:35.0 [sritz] update Definition ([Text Source: NASA Science Missions Directorate Homepage, https://pmm.nasa.gov/GPM ] GPM Constellation is a joint mission with the Japan Aerospace Exploration Agency (JAXA) and other international partners. Building upon the success of the Tropical Rainfall Measuring Mission (TRMM), it will initiate the measurement of global precipitation, a key climate factor. Its science objectives are: to improve ongoing efforts to predict climate by providing near-global measurement of precipitation, its distribution, and physical processes; to improve the accuracy of weather and precipitation forecasts through more accurate measurement of rain rates and latent heating; and to provide more frequent and complete sampling of the Earth's precipitation. GPM Constellation is envisioned to consist of a core spacecraft to measure precipitation structure and to provide a calibration standard for the constellation spacecraft, an international constellation of NASA and contributed spacecraft to provide frequent precipitation measurements on a global basis, calibration/validation sites distributed globally with a broad array of precipitation-measuring instrumentation, and a global precipitation data system to produce and distribute global rain maps and climate research products. The GPM Core Observatory carries the first space-borne Ku/Ka-band Dual-frequency Precipitation Radar (DPR) and a multi-channel GPM Microwave Imager (GMI). The DPR instrument, which provides three dimensional measurements of precipitation structure over 78 and 152 mile (125 and 245 km) swaths, consists of a Ka-band precipitation radar (KaPR) operating at 35.5 GHz and a Ku-band precipitation radar (KuPR) operating at 13.6 GHz. Relative to the TRMM precipitation radar, the DPR is more sensitive to light rain rates and snowfall. In addition, simultaneous measurements by the overlapping of Ka/Ku-bands of the DPR can provide new information on particle drop size distributions over moderate precipitation intensities. In addition, by providing new microphysical measurements from the DPR to complement cloud and aerosol observations, GPM is expected to provide further insights into how precipitation processes may be affected by human activities. The GMI instrument is a conical-scanning multi-channel microwave radiometer covering a swath of 550 miles (885 km) with thirteen channels ranging in frequency from 10 GHz to 183 GHz. The GMI uses a set of frequencies that have been optimized over the past two decades to retrieve heavy, moderate and light precipitation using the polarization difference at each channel as an indicator of the optical thickness and water content. Group: Platform_Details Entry_ID: GPM Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: GPM Long_Name: Global Precipitation Measurement End_Group Group: Platform_Associated_Instruments Short_Name: GMI Short_Name: DPR End_Group Group: Orbit Orbit_Type: LEO > Low Earth Orbit > Polar Non-Sun-Synchronous End_Group Creation_Date: 2009-02-25 Online_Resource: https://pmm.nasa.gov/GPM Online_Resource: http://global.jaxa.jp/projects/sat/gpm/index.html Online_Resource: http://www.eorc.jaxa.jp/GPM/index_e.htm Group: Platform_Logistics Launch_Date: 2014-01-25 Launch_Site: TANEGASHIMA ISLAND, JAPAN Primary_Sponsor: USA/NASA Primary_Sponsor: JAPAN/JAXA End_Group End_Group); 2018-04-24 20:29:16.0 [sritz] update Definition ([Text Source: NASA Science Missions Directorate Homepage, http://science.nasa.gov/missions/gpm/ ] GPM Constellation is a joint mission with the Japan Aerospace Exploration Agency (JAXA) and other international partners. Building upon the success of the Tropical Rainfall Measuring Mission (TRMM), it will initiate the measurement of global precipitation, a key climate factor. Its science objectives are: to improve ongoing efforts to predict climate by providing near-global measurement of precipitation, its distribution, and physical processes; to improve the accuracy of weather and precipitation forecasts through more accurate measurement of rain rates and latent heating; and to provide more frequent and complete sampling of the Earth's precipitation. GPM Constellation is envisioned to consist of a core spacecraft to measure precipitation structure and to provide a calibration standard for the constellation spacecraft, an international constellation of NASA and contributed spacecraft to provide frequent precipitation measurements on a global basis, calibration/validation sites distributed globally with a broad array of precipitation-measuring instrumentation, and a global precipitation data system to produce and distribute global rain maps and climate research products. The GPM Core Observatory carries the first space-borne Ku/Ka-band Dual-frequency Precipitation Radar (DPR) and a multi-channel GPM Microwave Imager (GMI). The DPR instrument, which provides three dimensional measurements of precipitation structure over 78 and 152 mile (125 and 245 km) swaths, consists of a Ka-band precipitation radar (KaPR) operating at 35.5 GHz and a Ku-band precipitation radar (KuPR) operating at 13.6 GHz. Relative to the TRMM precipitation radar, the DPR is more sensitive to light rain rates and snowfall. In addition, simultaneous measurements by the overlapping of Ka/Ku-bands of the DPR can provide new information on particle drop size distributions over moderate precipitation intensities. In addition, by providing new microphysical measurements from the DPR to complement cloud and aerosol observations, GPM is expected to provide further insights into how precipitation processes may be affected by human activities. The GMI instrument is a conical-scanning multi-channel microwave radiometer covering a swath of 550 miles (885 km) with thirteen channels ranging in frequency from 10 GHz to 183 GHz. The GMI uses a set of frequencies that have been optimized over the past two decades to retrieve heavy, moderate and light precipitation using the polarization difference at each channel as an indicator of the optical thickness and water content. Group: Platform_Details Entry_ID: GPM Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: GPM Long_Name: Global Precipitation Measurement End_Group Group: Platform_Associated_Instruments Short_Name: GMI Short_Name: DPR End_Group Group: Orbit Orbit_Type: LEO > Low Earth Orbit > Polar Non-Sun-Synchronous End_Group Creation_Date: 2009-02-25 Online_Resource: https://pmm.nasa.gov/GPM Online_Resource: https://science.nasa.gov/missions/gpm/ Online_Resource: http://global.jaxa.jp/projects/sat/gpm/index.html Online_Resource: http://www.eorc.jaxa.jp/GPM/index_e.htm Group: Platform_Logistics Launch_Date: 2014-01-25 Launch_Site: TANEGASHIMA ISLAND, JAPAN Primary_Sponsor: USA/NASA Primary_Sponsor: JAPAN/JAXA End_Group End_Group); delete Resource (null); AE-E The Atmospheric Explorer-E (AE-E) spacecraft (Designation: 08440 / 75107A) was designed as a multi- sided polyhedron shaped frame with a mean diameter of 1.4 meters. AE-E was similar in construction and instrumentation to AE-C. AE-E was launched on 1975-11-20 and decayed on 1981-06-10. The purpose of the AE-C mission was to investigate the uppermost layer of the earth's atmosphere, the thermosphere, with emphasis on energy transfer and other controlling processes. Photochemical processes related to the absorption of solar UV radiation were studied by making coordinated measurements of reacting constituents and the solar input. Simultaneous two-spacecraft sampling was carried out at higher latitudes by the AE-D and AE-E spacecraft until the failure of AE-D on January 29, 1976, and then by (the re-activated) AE-C and AE-E spacecraft until AE-C re-entered the earth's atmosphere on December 12, 1978. The AE-E perigee swept through more than six full latitude cycles and two local time cycles during the first year after launch when the orbit was elliptical, and the perigee height was varied between 130 and 400 km. The circularization of the orbit around 390 km was made on November 20, 1976, and the spacecraft perigee was raised to this height whenever it had decayed to about 250 km. AE-E re-entered the earth's atmosphere on June 10, 1981 thus terminating the operations. The payload included instrumentation to measure: Solar UV Fluxes, the Composition of Positive Ions and Neutral Particles, the Density and Temperature of neutral particles, positive ions and electrons, Atmospheric airglow emissions, Photoelectron Energy Spectra, Proton and Electron Fluxes with particle energy up to 25 keV, and a backscatter UV spectrometer to monitor the atmospheric ozone content. Power was supplied by a solar cell array. The spacecraft used a PCM telemetry data system that operated in real time or using a tape recorder. Group: Platform_Details Entry_ID: AE-E Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: AE (Atmosphere Explorer) Short_Name: AE-E Long_Name: Atmosphere Explorer E (Explorer 55) End_Group Group: Synonymous_Platform_Names Short_Name: Explorer 55 Short_Name: 08440 End_Group Group: Platform_Associated_Instruments Short_Name: UV SPECTROMETER End_Group Group: Orbit Perigee: 130 to 400 km End_Group Creation_Date: 2007-08-22 Online_Resource: http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1975-107A Group: Platform_Logistics Launch_Date: 1975-11-20 Primary_Sponsor: NASA End_Group End_Group WORLDVIEW-4 2017-11-02 17:46:15.0 [aaleman] Insert Concept add broader relation (WORLDVIEW-4 [341b5eb7-19bd-4337-83f3-885730103df1,310277] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,287601]); Earth Observation Satellites Earth observation satellites are satellites specifically designed to observe Earth from orbit, similar to spy satellites but intended for non-military uses such as environmental monitoring, meteorology, map making etc. Source: Wikipedia, http://en.wikipedia.org/wiki/Earth_observation_satellite Group: Platform_Details Entry_ID: Earth Observation Satellites Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: Earth Observation Satellites End_Group End_Group 2020-03-06 18:24:43.0 [mmorahan] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,541501] - SENTINEL-6 [0df95c0e-77a5-46b5-94f4-3e5ae1391450,559847]); 2020-02-12 16:40:58.0 [sritz] Move Concepts delete narrower relation (null); 2020-02-12 16:39:34.0 [sritz] Move Concepts add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,541501] - SENTINEL-2A [2ce20983-98b2-40b9-bb0e-a08074fb93b3,541455]); 2020-01-30 16:00:22.0 [tstevens] Move Concepts delete narrower relation (null); 2020-01-30 16:00:02.0 [tstevens] Move Concepts delete narrower relation (null); 2020-01-29 12:36:30.0 [tstevens] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,541501] - SENTINEL-2 [6f1c359b-b1a6-47c1-979e-0689e637fbdc,559807]); 2020-01-29 12:34:29.0 [tstevens] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,541501] - SENTINEL-2B [f2445400-1981-4ef3-bf7c-f4aa35923ae9,559803]); 2020-01-04 00:19:19.0 [sritz] Move Concepts delete narrower relation (null); 2019-12-31 17:24:12.0 [sritz] Move Concepts delete narrower relation (null); 2019-12-31 17:23:43.0 [sritz] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,541501] - Elektro-L [882c16a9-0bc6-4773-8066-e25ea8de3c9d,559581]); 2019-12-19 14:10:27.0 [mmorahan] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,541501] - CFOSAT [7c3fab1c-d17e-4e5c-870e-994793c2594e,559573]); 2019-05-10 21:10:34.0 [sritz] Remove Concepts delete narrower relation (null); 2019-05-10 21:10:12.0 [sritz] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761] - Jason-class Altimeter [fbc0ccf8-81ef-4f9d-9714-155032271cf2,368813]); 2019-05-02 19:36:37.0 [mmorahan] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761] - Spire [da278af5-097b-47e7-903d-4deac395c4de,368757]); 2019-05-02 19:26:59.0 [mmorahan] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761] - SkySat [e9611632-822d-468b-9748-a392991a0718,368753]); 2019-05-02 16:04:56.0 [mmorahan] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761] - PlanetScope [6fffd5bf-1d22-487a-8b4c-495992ef3b28,368749]); 2019-05-02 15:41:59.0 [mmorahan] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761] - DMC-2G [e5184d15-eec8-4703-8318-243748ddbd0e,368737]); 2019-04-30 16:17:43.0 [sritz] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761] - PACE [eb4175de-3ee7-4897-bbbe-590ad7e09b4f,368729]); 2019-04-26 15:57:42.0 [mmorahan] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761] - ICEYE [42c6ff80-849b-4ef5-b6ff-fd9416b8cf33,368717]); 2019-04-26 12:56:04.0 [mmorahan] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761] - FLEX [acfdfa87-7490-47db-a1dd-94a3bfb6a16d,368709]); 2019-04-25 11:10:05.0 [mmorahan] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761] - CASSIOPE [66f5d236-40fb-4a41-96a4-761d48103765,368665]); 2018-11-13 11:00:52.0 [mmorahan] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761] - GCOM-C [18512c09-2590-4804-8b43-dd9caea53b5d,368261]); 2018-11-09 12:56:53.0 [tstevens] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761] - HEXAGON KH-9 [7d97b6ca-83de-44e1-8d3b-f45755e38a8d,368257]); 2018-11-05 12:33:23.0 [mmorahan] Remove Concepts delete narrower relation (null); 2018-11-05 12:32:05.0 [mmorahan] Move Concepts add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761] - SENTINEL-3 [8a19f309-46ee-424b-be9f-e7e57e5b8ca0,345357]); 2018-11-05 12:31:17.0 [mmorahan] Move Concepts add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761] - SENTINEL-2 [2ce20983-98b2-40b9-bb0e-a08074fb93b3,344721]); 2018-11-05 12:30:01.0 [mmorahan] Move Concepts add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761] - SENTINEL-1 [007c3084-89db-458e-8387-14e192b6cb8e,367691]); 2018-10-30 17:18:11.0 [sritz] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761] - ITOS [80e95a88-b44e-444e-bd79-2e6dbb56b170,368215]); 2018-10-11 20:09:41.0 [mmorahan] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761] - FireBIRD [9b165321-e03c-44dc-bb9c-d10c32c93ab6,368159]); 2018-10-04 18:31:20.0 [mmorahan] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761] - Sentinel-5P [77e9a75e-2c3b-428b-8b21-b6a902dd8fee,368151]); 2018-08-10 18:54:04.0 [sritz] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761] - HY-2B [7ef45b8e-ac63-41b2-9e8b-7becfa7d7431,368067]); 2018-08-10 18:47:59.0 [sritz] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761] - HY2-A [fe07a2e4-a6cd-401c-af3e-433bbc8c2c98,368063]); 2018-08-10 18:31:28.0 [sritz] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761] - JASON-3 [bffa816a-c210-46ed-81cb-ffdf3310c1a5,368059]); 2018-07-19 16:45:56.0 [sritz] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761] - LARES [ef053df7-ff76-47f3-a335-5d4e87e51b92,367855]); 2018-06-13 12:02:46.0 [mmorahan] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761] - Swarm [1d6d5f82-acd5-4bd2-9324-12884718b353,367695]); 2018-06-12 19:26:21.0 [mmorahan] Move Concepts delete narrower relation (null); 2018-06-12 19:26:14.0 [mmorahan] Move Concepts delete narrower relation (null); 2018-06-12 19:26:01.0 [mmorahan] Move Concepts delete narrower relation (null); 2018-06-12 19:20:10.0 [mmorahan] Move Concepts add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761] - SENTINEL-3 [8a19f309-46ee-424b-be9f-e7e57e5b8ca0,345357]); 2018-06-12 19:18:56.0 [mmorahan] Move Concepts add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761] - SENTINEL-2 [2ce20983-98b2-40b9-bb0e-a08074fb93b3,344721]); 2018-06-12 19:14:57.0 [mmorahan] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761] - Sentinel-1 [007c3084-89db-458e-8387-14e192b6cb8e,367691]); 2018-06-12 16:36:10.0 [mmorahan] Move Concepts delete narrower relation (null); 2018-06-12 16:36:02.0 [mmorahan] Move Concepts delete narrower relation (null); 2018-06-12 16:35:36.0 [mmorahan] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761] - KOMPSAT [9abdb7c0-7b8e-426b-8bc7-57ea4a30d82c,367679]); 2018-06-12 16:20:35.0 [mmorahan] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761] - KOMPSAT-1 [caf7cd97-6a64-4e31-9b7e-d96854eb9b6a,367675]); 2018-06-12 10:15:03.0 [mmorahan] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761] - EarthCARE [bf66ef8c-acc5-4c2f-b519-db0cbee37c99,367671]); 2018-06-12 09:14:20.0 [mmorahan] Move Concepts delete narrower relation (null); 2018-06-12 09:10:05.0 [mmorahan] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761] - Deimos [f122ab59-266b-4be9-99ad-4c2172bcf97c,367663]); 2018-06-12 08:47:45.0 [mmorahan] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761] - Aeolus [e31c4750-9903-4de7-95ef-faa9610f3a63,367659]); 2018-04-24 20:47:39.0 [sritz] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761] - OCO-3 [da687fb4-016d-4b4d-92c2-380640ca5640,367551]); 2018-03-12 16:26:34.0 [sritz] Remove Concepts delete narrower relation (null); 2018-02-27 19:11:42.0 [sritz] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,287601] - ICON [4a3988a7-f1c6-4c0a-a93b-9221adbca49b,310603]); 2018-02-26 20:52:22.0 [sritz] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,287601] - COMS [ec484699-009f-4f39-93aa-d11379b4288a,310595]); 2018-01-26 21:35:39.0 [sritz] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,287601] - SES-14 [8dd76819-1baa-4ccd-8544-23c2923f2d84,310531]); 2017-11-30 15:53:56.0 [sritz] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,287601] - SWOT [20de05fc-7088-4cf5-87aa-a8e2ceb3abd6,310419]); 2017-11-02 17:46:55.0 [aaleman] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,287601] - QUICKBIRD-2 [4240f2ff-8d4a-438d-bbae-f62ae3504922,310281]); 2017-11-02 17:46:15.0 [aaleman] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,287601] - WORLDVIEW-4 [341b5eb7-19bd-4337-83f3-885730103df1,310277]); 2017-09-27 20:38:22.0 [sritz] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,287601] - Himawari [d8b7fc7d-9cf3-4020-947d-f33d712b64ab,310213]); 2017-09-14 18:32:28.0 [sritz] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,287601] - NISAR [a6fddcb3-881b-484a-bbc9-39591b6359ab,310183]); 2017-05-05 13:35:50.0 [mmorahan] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,287601] - Proba-V [6f507389-2c7c-41b4-a638-95bdc73b63a3,309567]); 2017-04-25 21:31:43.0 [aaleman] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,287601] - TDX [6c21f29b-5dd4-4e96-a6fb-44e4788d1973,309555]); 2017-03-02 21:12:21.0 [aaleman] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,256549] - WORLDVIEW-3 [dfb49f10-0755-464f-96b1-fc037802c86d,278669]); 2016-12-09 20:28:43.0 [sritz] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,256549] - CYGNSS [18fd52d4-c60c-4ef5-b39a-960ae9916472,278541]); 2016-08-15 15:40:53.0 [mpmorahan] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,256549] - SARAL [4e62dd32-7776-4646-ae8d-b85d97df415a,277815]); 2016-03-21 20:43:23.0 [saritz] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,143415] - MTSAT [e3679e9e-5a95-46f4-a856-e51d459469fd,158711]); 2015-12-08 13:10:23.0 [mpmorahan] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,143415] - PLEIADES [516a9bb2-0171-4ad2-8d4f-3f7d1219d393,158543]); 2015-08-20 20:35:32.0 [mpmorahan] Remove Concepts delete narrower relation (null); 2015-08-20 20:19:09.0 [mpmorahan] Remove Concepts delete narrower relation (null); 2015-08-03 13:03:55.0 [mpmorahan] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,143415] - Elektro-L N1 [6d0d4c3e-acfb-4bfd-ab0d-4478e18e4b19,158135]); 2015-08-03 12:57:15.0 [mpmorahan] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,143415] - Kanopus-V [a93bb213-7862-4aa5-a113-38669e557a76,158131]); 2015-08-03 12:47:01.0 [mpmorahan] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,143415] - Resurs DK 1 [ff2141a6-5682-44da-88fc-9a4e78de35ad,158127]); 2015-08-03 12:41:31.0 [mpmorahan] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,143415] - Resurs-P N1 [a7560954-fe13-4e8a-bb12-1289154a3a24,158123]); 2015-08-03 12:38:06.0 [mpmorahan] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,143415] - Resurs-P N2 [b00d17a2-b509-4b42-86fd-d50bf50cfc3c,158119]); 2015-08-03 12:20:22.0 [mpmorahan] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,143415] - Meteor-M N1 [34e29a6e-63ef-4701-9f03-4dd233f146f6,158115]); 2015-08-03 12:07:10.0 [mpmorahan] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,143415] - Meteor-M N2 [20e6f8e4-f60d-4ffb-ab85-0423c5078a52,158111]); 2015-03-11 18:50:11.0 [saritz] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,73425] - MMS [76673a7f-44c8-4dde-83c2-1104b060061f,106791]); 2015-02-12 20:04:43.0 [saritz] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,73425] - STPSat-3 [b5e24e20-f99f-423f-83ac-d3eb5989ac48,106733]); 2014-06-18 17:08:45.0 [saritz] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,73425] - MT1 [9e09177b-bc72-41e9-921a-a4546f89e20a,106481]); 2013-05-07 19:00:54.0 [aaleman] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,73425] - WORLDVIEW-2 [ff0ed18d-c476-4dc4-a248-d42ad74bb4a1,105099]); 2013-03-28 19:31:33.0 [mpmorahan] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,73425] - AQUARIUS_SAC-D [e13d801e-19a3-4516-a64c-27f003b3d963,83227]); 2013-01-09 14:32:48.0 [mpmorahan] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,73425] - Coriolis [bac2e743-1d02-4868-8bd6-b8b8741e3794,82059]); 2012-09-19 13:43:39.0 [saritz] Remove Concepts delete narrower relation (null); 2012-09-18 16:35:12.0 [saritz] Move Concepts add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,31221] - METOP [8c192c86-d07c-4e7b-af8f-92aa4b40fca7,31825]); 2012-09-05 20:58:23.0 [mpmorahan] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,31221] - GCOM-W1 [6314fc1f-507f-4a59-a8f2-0d3cdc9c59a2,40571]); 2012-09-05 20:54:15.0 [mpmorahan] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,31221] - GCOM-W1 [7599828f-8793-4a17-b845-b0341729507e,40567]); 2012-09-05 20:54:13.0 [mpmorahan] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,31221] - GCOM-W1 [8781da14-5ced-4d64-81cd-8daa10a1c30d,40563]); 2012-08-07 19:04:22.0 [mpmorahan] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,31221] - MTSAT-2 [02db0949-495c-4579-8ff5-d1a9079c88b7,40467]); 2012-07-25 17:24:30.0 [mpmorahan] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,31221] - HJ1B [3edef6e1-db0b-4806-b586-8869a7c986ba,40375]); 2012-07-25 12:28:41.0 [mpmorahan] Insert Concept add narrower relation (Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,31221] - HJ1A [d65fc363-e9b4-410a-b5e3-8dbd87b510b4,40355]); Meteor-M N1 Meteorological Satellite Meteor-M N1 Group: Platform_Details Entry_ID: Meteor-M N1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: Meteor-M N1 Long_Name: Meteorological Satellite Meteor-M N1 End_Group Group: Synonymous_Platform_Names Short_Name: Meteor-M N1 End_Group Group: Platform_Associated_Instruments Short_Name: DCS Short_Name: GGAK-M Short_Name: KMSS Short_Name: MSU-MR Short_Name: MTVZA Short_Name: Severjanin End_Group Group: Orbit Orbit_Altitude: 832 km Orbit_Inclination: 98.8 degrees Equator_Crossing: 9:30 a.m. Local time: e.g. Period: 101 Orbit_Type: LEO > LOW EARTH ORBIT > POLAR SUN-SYNCHRONOUS End_Group Creation_Date: 2012-03-14 Online_Resource: http://www.vniiem.ru/ru/index.php?option=com_content&view=article&id=604:-l-r-1&catid=82:--l-3r&Itemid=62 Online_Resource: http://www.vniiem.ru/ru/index.php?option=com_content&view=article&id=605:-l-r-1&catid=82:--l-3r&Itemid=62 Sample_Image: http://planet.iitp.ru/spacecraft/img/meteor-m-600.jpg Group: Platform_Logistics Launch_Date: 2009-09-17 Design_Life: 6 years End_Group End_Group 2015-08-03 12:31:03.0 [mpmorahan] insert AltLabel (id: null text: Meteorological Satellite Meteor-M N1 language code: en); 2015-08-03 12:20:22.0 [mpmorahan] Insert Concept add broader relation (Meteor-M N1 [34e29a6e-63ef-4701-9f03-4dd233f146f6,158115] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,143415]); AE-D The Atmospheric Explorer-D (AE-D) spacecraft (designation: 08353 / 75096A ) was designed as a multi- sided polyhedron shaped frame with a mean diameter of about 1.4 meters. AE-D was in most respects similar to AE-C. The AE-D was launched on 1975-10-6 and decayed 1976-03-12. The purpose of the AE-D mission was a direct continuation of the EA-C mission: to investigate the chemical and physical processes in the uppermost layer of the earth's atmosphere, the thermosphere, with emphasis on energy transfer and other controlling processes. Photochemical processes related to the absorption of solar UV radiation were studied by making coordinated measurements of reacting constituents and the solar input in the region of high absorption of solar energy. The payload included instrumentation to measure: Solar UV Fluxes, the Composition of Positive Ions and Neutral Particles, the Density and Temperature of neutral particles, positive ions and electrons, Atmospheric airglow emissions, Photoelectron Energy Spectra, and Proton and Electron Fluxes with particle energy up to 25 keV. This mission was planned to sample the high latitude regions at the same time that the AE-E mission was sampling the equatorial and low latitude regions. The same type of spacecraft as AE-C was used, and the payload consisted of the same types of instruments except for deletion of the extreme solar UV monitor and the Bennett ion mass spectrometer both of which were part of the AE-E payload. AE-D was placed in a high inclination (polar) orbit. The polar orbit provided sampling of all latitudes, the perigee moved through all latitudes in 3 months, and all local times in 4 months. Unfortunately, a failure in the solar power panels resulted in the termination of AE-D operations on January 29, 1976, after slightly less than 4 months of useful spacecraft life. However, all the regions at the perigee altitudes were sampled during this time. The AE-D spacecraft re-entered the earth's atmosphere about 1 month after the cessation of telemetry. To continue the correlated observations with the AE-E mission, the earlier AE-C spacecraft was then reactivated on February 28, 1976 as replacecment for AE-D. Power to AE-D was supplied by a solar cell array. The spacecraft used a PCM telemetry data system that operated in real time or using a tape recorder. Group: Platform_Details Entry_ID: AE-D Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: AE (Atmosphere Explorer) Short_Name: AE-D Long_Name: Atmosphere Explorer D (Explorer 54) End_Group Group: Synonymous_Platform_Names Short_Name: Explorer 54 Short_Name: 08353 End_Group Group: Platform_Associated_Instruments Short_Name: MASS SPECTROMETERS End_Group Creation_Date: 2007-08-22 Online_Resource: http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1975-096A Group: Platform_Logistics Launch_Date: 1975-10-06 Primary_Sponsor: NASA End_Group End_Group VOYAGER 2 Voyager 2 was one of a pair of spacecraft launched to explore the planets of the outer solar system and the interplanetary environment. Each Voyager had as its major objectives at each planet to: (1) investigate the circulation, dynamics, structure, and composition of the planet's atmosphere; (2) characterize the morphology, geology, and physical state of the satellites of the planet; (3) provide improved values for the mass, size, and shape of the planet, its satellites, and any rings; and, (4) determine the magnetic field structure and characterize the composition and distribution of energetic trapped particles and plasma therein. Originally planned as a Grand Tour of the outer planets, including dual launches to Jupiter, Saturn, and Pluto in 1976-77 and dual launches to Jupiter, Uranus, and Neptune in 1979, budgetary constraints caused a dramatic rescoping of the project to two spacecraft, each of which would go to only Jupiter and Saturn. The new mission was called Mariner Jupiter/Saturn, or MJS. It was subsequently renamed Voyager about six months prior to launch. The rescoped mission was estimated to cost $250 million (through the end of Saturn operations), only a third of what the Grand Tour design would have cost. Voyager 2 was the first of the two spacecraft to be launched, with liftoff occurring 20 Aug. 1977. What was at first an auspicious launch, however, proved to be the beginning of a number of problems. The primary cause of the initial problems were attributed to commanding by the AACS, including difficulty in determining the full deployment of the science boom. These problems resulted in a delay of four days in the launch of Voyager 1 to ensure they wouldn't occur for it. Although launched sixteen days after Voyager 2, Voyager 1's trajectory was the quicker one to Jupiter. On 15 Dec. 1977, while both spacecraft were in the asteroid belt, Voyager 1 surpassed Voyager 2's distance from the Sun. Several months after launch, in April 1978, Voyager 2's primary radio receiver failed, automatically kicking in the backup receiver which proved to be faulty. Attempts to recover the use of the primary receiver failed and the backup receiver was used for the remainder of the mission. Although use of the backup receiver made communication with the spacecraft more difficult, engineers were able to find workarounds. Voyager 2 proceeded with its primary mission and flew by Jupiter (closest approach on 09 July 1979) and Saturn (05 Aug. 1981). During these flybys, Voyager 2 obtained images roughly equal in number to Voyager 1 (18,000 at Jupiter, 16,000 at Saturn). Voyager 2's launch date had preserved one part of the original Grand Tour design, i.e. the possibility of an extended mission to Uranus and Neptune. Despite the difficulties encountered, scientists and engineers had been able to make Voyager enormously successful. As a result, approval was granted to extend the mission, first to Uranus, then to Neptune and later to continue observations well past Neptune. Voyager 2 made successful flybys of Uranus (24 Jan. 1986) and Neptune (25 Aug. 1989). Because of the additional distance of these two planets, adaptations had to made to accomodate the lower light levels and decreased communications. Voyager 2 was successfully able to obtain about 8,000 images of Uranus and its satellites. Additional improvements in the on-board software and use of image compression techniques allowed about 10,000 images of Neptune and its satellites to be taken. All of the experiments on Voyager 2 have produced useful data. Group: Platform_Details Entry_ID: VOYAGER 2 Group: Platform_Identification Platform_Category: Interplanetary Spacecraft Platform_Series_or_Entity: FLYBY Short_Name: VOYAGER 2 End_Group Group: Synonymous_Platform_Names Short_Name: Mariner Jupiter/Saturn B Short_Name: 10271 Short_Name: 1977-076A End_Group Creation_Date: 2007-03-06 Online_Resource: http://www.nasa.gov/mission_pages/voyager/index.html Online_Resource: http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1977-076A Sample_Image: http://nssdc.gsfc.nasa.gov/image/spacecraft/voyager.jpg Group: Platform_Logistics Launch_Date: 1977-08-20 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: NASA End_Group End_Group ADEOS-I ADEOS-1 ADEOS (ADvanced Earth Observation Satellite), developed by the Japanese space agency JAXA. It was the largest satellite Japan has ever developed, having dimensions of 4 x 4 x 5 m. When antenna and the solar array paddle (approx. 3 x 24 m) were deployed, it had a span of 11m in the flight direction and 29 m in the perpendicular direction.It had a launch mass of approximatly 3500 kg and an in-orbit power generation capability of approximatly 4500W. The spacecraft consisted of a mission module and a bus module.The bus module was made of thermally, electrically and mechanically independent units, including the Communications and Data Handling Subsystem, the Electrical Power Subsystem (EPS), the Attitude and Orbital Control Subsystem (AOCS) and the reaction Control Subsystem (RCS) for orbital maneuvers. The mission module carried 8 instruments : Two core sensor developped by JAXA : AVNIR (Advanced Visible and Near Infrared Radiometer) and OCTS (Ocean Color and Temperature Temperature Sensor).Six Annoncement of Opportunity (AO) sensors : NSACT (NASA SCATterometer), TOMS (Total Ozone Mapping Spectometer), POLDER (POlarization and Directionality of the Earth'Reflectance), IMG (Interferometric Monitor for Greenhouse Gases), ILAS (Improved Limb Atmospheric Spectrometer), RIS (Retroreflector In Space).ADEOS-1 has been launched in August 1996 by H-II launcher from Tanegashima Space Center. Ninety seconds after liftoff, the solid rocket boosters separated from the H-II vehicle and 6 minutes after liftoff, the first stage separated. Then 16 minutes after liftoff, ADEOS-1 separated from the second stage. ADEOS-1 was lost on June 1997, the 30th, due to a solar panel cable breaking.[http://smsc.cnes.fr/POLDER/index.htm] Group: Platform_Details Entry_ID: ADEOS-I Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: ADEOS (Advanced Earth Observing Satellite) Short_Name: ADEOS-I Long_Name: Advanced Earth Observing Satellite-I End_Group Group: Platform_Associated_Instruments Short_Name: POLDER-1 Short_Name: TOMS Short_Name: RIS Short_Name: OCTS Short_Name: NSCAT Short_Name: IMG Short_Name: ILAS Short_Name: AVNIR End_Group Group: Orbit Orbit_Inclination: 98.6 degrees Period: 101 minutes Perigee: 797 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-08-22 Online_Resource: http://ilrs.gsfc.nasa.gov/satellite_missions/list_of_satellites/ade1_general.html#instrument Sample_Image: http://ilrs.gsfc.nasa.gov/images/adeos1.gif Group: Platform_Logistics Launch_Date: 1996-08-17 Design_Life: 3 years Primary_Sponsor: Japan Aerospace Exploration Agency End_Group End_Group 2016-06-09 14:27:20.0 [epneff] Added altLabel insert AltLabel (id: null text: ADEOS-1 language code: en); 2015-05-08 18:23:33.0 [saritz] update PrefLabel (ADEOS-I); 2014-02-27 14:44:09.0 [mpmorahan] Rename Concept update PrefLabel (ADEOS-1); NigeriaSat-X The Disaster Monitoring Constellation (DMC) is an international programme initially proposed in 1996 and led by SSTL (Surrey Satellite Technology Ltd) from the United Kingdom, to construct a network of five affordable Low Earth Orbit (LEO) microsatellites. The objective is to provide a daily global imaging capability at medium resolution (30-40 m), in 3-4 spectral bands, for rapid-response disaster monitoring and mitigation. 2019-05-02 16:01:23.0 [mmorahan] insert Definition (id: null text: The Disaster Monitoring Constellation (DMC) is an international programme initially proposed in 1996 and led by SSTL (Surrey Satellite Technology Ltd) from the United Kingdom, to construct a network of five affordable Low Earth Orbit (LEO) microsatellites. The objective is to provide a daily global imaging capability at medium resolution (30-40 m), in 3-4 spectral bands, for rapid-response disaster monitoring and mitigation. language code: en); 2019-05-02 15:57:44.0 [mmorahan] Insert Concept add broader relation (NigeriaSat-X [35cafb99-393d-4727-a89d-5472512b2fdf,368745] - DMC-2G (Disaster Monitoring Constellation- 2nd Generation) [e5184d15-eec8-4703-8318-243748ddbd0e,368737]); PIONEER 7 Identical to Pioneer 6, Pioneer 7 was put into heliocentric orbit at 0.814 x 0.985 AU to study the solar magnetic field, the solar wind, and cosmic rays at widely separated points in solar orbit. On 7 September 1968, the spacecraft was correctly aligned with the Sun and Earth to begin studying Earth's magnetic tail. In 1977, eleven years after its launch, Pioneer 7 registered the magnetic tail 19.3 million kilometers out, three times further into space than recorded previously. On 20 March 1986, the spacecraft flew within 12.3 million kilometers of Halley's Comet and monitored the interaction between the cometary hydrogen tail and the solar wind. As with Pioneer 6 and Pioneer 8, NASA continues to maintain intermittent contact with Pioneer 7, more than thirty years after its mission began. On 31 March 1995, for example, the plasma analyzer was turned on during 2 hours of contact with the ground. Information provided by http://solarsystem.nasa.gov/missions/profile.cfm?Sort=Alpha&Alias=Pioneer%207&Letter=P&Display=ReadMore Group: Platform_Details Entry_ID: PIONEER 7 Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Short_Name: PIONEER 7 End_Group Group: Platform_Associated_Instruments Short_Name: FLUXGATE MAGNETOMETERS Short_Name: PROBES End_Group Creation_Date: 2007-08-20 Online_Resource: http://solarsystem.nasa.gov/missions/profile.cfm?Sort=Alpha&Letter=P&Alias=Pioneer%207 Sample_Image: http://solarsystem.nasa.gov/missions/images/miss-pioneer_07.gif Group: Platform_Logistics Launch_Date: 1966-08-17 Primary_Sponsor: NASA End_Group End_Group GULFSTREAM 1000 (695A) The Gulfstream Jet Prop Commander 1000 (AC-695A) is a stable high-wing, pressurized, twin-engine turboprop aircraft that is suitable for a variety of missions. Standard configuration allows for mission equipment, two pilots and one observer. However, the aircraft can be configured for two scientists/observers and mission equipment in the cabin. NOAA’s AC-695A Jet Prop Commander is typically utilized by the National Weather Service (NWS) National Operational Hydrologic Remote Sensing Center (NOHRSC). [Text and Photo provided by NOAA, http://www.aoc.noaa.gov/aircraft_jet_prop.htm ] Group: Platform_Details Entry_ID: GULFSTREAM 1000 (695A) Group: Platform_Identification Platform_Category: Aircraft Short_Name: GULFSTREAM 1000 (695A) Long_Name: Gulfstream Jet Prop Commander 1000 (695a) End_Group Creation_Date: 2008-07-14 Online_Resource: http://www.gulfstream.com/ Online_Resource: http://www.aoc.noaa.gov/aircraft_jet_prop.htm Sample_Image: http://www.aoc.noaa.gov/images/Gulfstream%20Jet%20Prop%20Cdr/IMG_1493%20smaller.JPG End_Group R/V FERRELL Owned by Reservoir Geophysical, the R/V Ferrel is a 146 ft. oceanographic vessel used for sampling marine environments and other marine experiments. The R/V Ferrel houses two laboratories and 24 rooms for staff and crew. Group: Platform_Details Entry_ID: R/V FERRELL Group: Platform_Identification Platform_Category: In Situ Ocean-based Platforms Platform_Series_or_Entity: SHIPS Short_Name: R/V FERRELL End_Group Creation_Date: 2012-07-23 Online_Resource: http://www.reservoirgeophysical.com/reservoirgeophysical_files/Page1054.htm End_Group NOAA-18 [Source: NOAA-N Project home page, http://www.nasa.gov/mission_pages/noaa-n/main/index.html ] NOAA-N is the latest polar-orbiting satellite developed by NASA for the National Oceanic and Atmospheric Administration (NOAA). NOAA-N will collect information about Earth's atmosphere and environment to improve weather prediction and climate research across the globe. NOAA-N is the 15th in a series of polar-orbiting satellites dating back to 1978. NOAA uses two satellites, a morning and afternoon satellite, to ensure every part of the Earth is observed at least twice every 12 hours. Severe weather is monitored and reported to the National Weather Service which broadcasts the findings to the global community. With the early warning, effects of catastrophic weather events can be minimized. NOAA-N also has instruments to support an international search-and-rescue program. The Search and Rescue Satellite-Aided Tracking System, called COPAS-SARSAT, transmits to ground stations the location of emergency beacons from ships, aircraft and people in distress around the world. The program, in place since 1982, has saved about 18,000 lives. NOAA-N is the first in a series of polar-orbiting satellites to be part of a joint cooperation project with the European Organisation for the Exploitation of Meteorological Satellites (EUMESTAT). Group: Platform_Details Entry_ID: NOAA-18 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NOAA POES (Polar Orbiting Environmental Satellites) Short_Name: NOAA-18 Long_Name: National Oceanic & Atmospheric Administration-18 End_Group Group: Synonymous_Platform_Names Short_Name: NOAA-N End_Group Group: Platform_Associated_Instruments Short_Name: SARR Short_Name: SEM-2 Short_Name: AVHRR-3 Short_Name: HIRS/4 Short_Name: AMSU-A Short_Name: MHS Short_Name: SBUV/2 End_Group Group: Orbit Orbit_Inclination: 98.74 deg Period: 102.1 min Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-11-08 Online_Resource: http://goespoes.gsfc.nasa.gov/poes/spacecraft/noaan_spacecraft.html Online_Resource: http://www2.ncdc.noaa.gov/docs/klm/nnpsupp.htm Online_Resource: http://www.nasa.gov/mission_pages/noaa-n/main/index.html Online_Resource: http://nasascience.nasa.gov/missions/noaa-n Sample_Image: http://www.orbit.nesdis.noaa.gov/smcd/spb/mirs/img/NOAA18.gif Group: Platform_Logistics Launch_Date: 2005-05-20 Launch_Site: Vandenberg Air Force Base, USA Design_Life: Greater than 2 years Primary_Sponsor: USA/NASA Primary_Sponsor: USA/NOAA End_Group End_Group Space Stations/Manned Spacecraft Space Stations: A space station is an artificial structure designed for humans to live and work in outer space for a period of time. [Source: http://en.wikipedia.org/wiki/Space_station ] Manned Spacecraft: A vehicle, vessel or machine designed to (transport) humans in outer space. [Source: Wikipedia, http://en.wikipedia.org/wiki/Spacecraft ] Group: Platform_Details Entry_ID: Space Stations/Manned Spacecraft Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Short_Name: Space Stations/Manned Spacecraft End_Group End_Group SMS The SMS satellite series (1 and 2) were spin-stabilized (100 rpm) and operated in a West-to-East, geo-synchronous orbit at an altitude of 35,800 km (22,300 mi) above the equator. These were the first and second prototypes for the GOES satellite series. At this altitude it circled the axis of the Earth once in 24 hours, making its speed synonymous with the Earth's rotation, so that the satellite remained essentially stationary over a given geographical point. The two SMS satellites were employed to provide overlapping coverage that centers on the U.S. and extends over the eastern Atlantic Ocean and the western Pacific Ocean. The scanning system consisted of a mirror that is stepped mechanically to provide North to South viewing, while the rotation of the satellite provided West to East scanning. The mirror is stepped following each West to East scan, with each step resulting in a change in scan angle of 192 microradians, or 7 km near nadir. A sequence of 1821 scans is performed to provide a 'full disk' view from the Northern to the Southern Earth horizon. At the rotation rate of 100 rpm, 18.21 minutes are required to complete one full North to South view of the Earth. The VISSR field of view provides a ground resolution of 0.9km in the visible, and 3.0km in the infrared. Entry taken from: Cornillon, P., A Guide to Environmental Satellite Data, University of Rhode Island Marine Technical Report 79, 1982. Data Catalog Series for Space Science and Applications Flight Missions, National Space Science Data Center/World Data Center A for Rockets and Satellites, Volume 2A, September 1982. Data Catalog Series for Space Science and Applications Flight Missions, National Space Science Data Center/World Data Center A for Rockets and Satellites, Volume 4A, July 1985. Rao, P.K., S.J. Holmes, R.K. Anderson, J.S. Winston, and P.E. Lehr, Weather Satellites: Systems, Data, and Environmental Applications, American Metorological Society, Boston, 1990. ISBN 0-933876-66-1 The GOES Data Users Guide, 1984. Group: Platform_Details Entry_ID: SMS Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: SMS (Synchronous Meteorological Satellites) Short_Name: SMS Long_Name: Synchronous Meteorological Satellites End_Group Group: Synonymous_Platform_Names Short_Name: SMS End_Group Creation_Date: 2007-11-13 Online_Resource: http://goespoes.gsfc.nasa.gov/goes/project/history.html Sample_Image: http://goespoes.gsfc.nasa.gov/goes/project/images/SMS.jpg Group: Platform_Logistics Launch_Date: 1966-12-07 Primary_Sponsor: NASA End_Group End_Group OGO-5 The fifth Orbiting Geophysical Observatory, OGO-5, was launched on 4 March 1968. The satellite, primarily devoted to Earth observation, was in a highly elliptical initial orbit with a 272 km perigee and an 148,228 km apogee. The orbital inclination was 31.1 degrees. The satellite took 3796 minutes to complete one orbit. Two experiments aboard OGO-5 produced cosmic high- energy results, although their intended target was the Sun. The spacecraft attitude control failed on 6 August 1971 and it was placed in a standby mode on 8 October 1971. Three experiments (none of which were related to cosmic high-energy detection) were reactivated from 1 June to 13 July 1972. Operation of OGO 5 terminated completely on 14 July 1972. The Anderson et al. (University of California, Berkeley) Energetic Radiations from Solar Flares experiment was operational from March 1968 - June 1971. Primarily devoted to solar observations, it detected at least 11 cosmic X-ray bursts in time coincidence with gamma-ray bursts seen by other instruments. The detector was a 0.5 cm thick NaI(Tl) crystal with a 9.5 sq-cm area. Data were accumulated into energy ranges of: 9.6-19.2, 19.2-32, 32-48, 48-64, 64-80, 80-104, 104-128, and > 128 keV. The data were sampled for 1. 15 seconds once every 2.3 seconds. The gamma-ray instrument on-board, sensitive to energies from 25-100 MeV, was a six gap spark chamber with an effective area of ~ 100 sq-cm. It was called the Energetic Photons in Primary Cosmic Rays experiment (Hutchinson et al., Southampton University). It had an angular resolution of ~ 30 degrees (FWHM). The satellite was Earth-pointing and passed regularly through the radiation belts, which led to severe restrictions on the sky regions which could be examined by the gamma-ray instrument. Other problems, such as an efficiency reduction in the anti-coincidence shield and data system difficulties, severely degraded the scientific return from the experiment. Data collection ceased altogether after 5 months. Gamma-ray emission from the galactic plane was monitored. No point sources were detected. [Summary provided by NASA.] Group: Platform_Details Entry_ID: OGO-5 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: OGO (Orbiting Geophysical Observatory) Short_Name: OGO-5 Long_Name: Orbiting Geophysical Observatory-5 End_Group Group: Synonymous_Platform_Names Short_Name: OGO-E Short_Name: 03138 End_Group Group: Platform_Associated_Instruments Short_Name: MAGNETOMETERS Short_Name: SPECTROMETERS Short_Name: GAMMA RADIATION DETECTOR End_Group Group: Orbit Orbit_Inclination: 31.1 degrees Repeat_Cycle: 3796 minutes Perigee: 272 km Apogee: 148,228 km Orbit_Type: HEO > Highly Elliptical Orbit End_Group Creation_Date: 2007-02-13 Online_Resource: http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/ogo.html Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1968-014A Sample_Image: http://heasarc.gsfc.nasa.gov/Images/ogo/ogo.gif Group: Platform_Logistics Launch_Date: 1968-03-04 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: NASA End_Group End_Group G-I Grumman developed the Gulfstream I turbine powered executive transport to replace the many hundred war surplus piston twins performing such missions in the mid 1950s. Design work began in 1956, with first flight of the Gulfstream I prototype occurring on August 14 1958. FAA Type certification was awarded on May 21 1959 and deliveries of production aircraft followed from that June. Notably, the Gulfstream I was the first US twin engined corporate transport to be certificated to cruise at 30,000ft. [Text and Photo provided by Airliners.net: http://www.airliners.net/aircraft-data/stats.main?id=236 ] Group: Platform_Details Entry_ID: GULFSTREAM I Group: Platform_Identification Platform_Category: Aircraft Short_Name: GULFSTREAM I End_Group Creation_Date: 2008-07-14 Online_Resource: http://en.wikipedia.org/wiki/Grumman_Gulfstream_I Online_Resource: http://www.gulfstream.com/ Sample_Image: http://cdn-www.airliners.net/aviation-photos/middle/1/2/0/0236021.jpg End_Group 2014-07-02 15:10:30.0 [aaleman] fixed typo update PrefLabel (G-I); 2014-07-02 15:07:56.0 [aaleman] edited keyword at NSIDC request insert AltLabel (id: null text: GULFSTREAM I language code: en); update PrefLabel (G-1); STS-72 The primary objective of the STS-72 mission is to capture and return to Earth a Japanese microgravity research spacecraft known as Space Flyer Unit (SFU). The 7,885lbs SFU spacecraft was launched by Japan's National Space Development Agency (NASDA) from Tanegashima Space Center in Japan at 8:01 UT on March 18, 1995 aboard a Japanese H-II rocket (HII-3). The STS-72 mission will also deploy (for about 50 hours) and then retrieve the Office of Aeronautics and Space Technology Flyer (OAST-Flyer) spacecraft. OAST-Flyer is the seventh in a series of missions aboard reuseable free-flying Spartan carriers. It consists of four experiments: Return Flux Experiment (REFLEX), Global Positioning System Attitude Determination and Control Experiment (GADACS), Solar Exposure to Laser Ordnance Device (SELODE) and the University of Maryland Spartan Packet Radio Experiment (SPRE). Other experiments onboard STS-72 include the Shuttle Solar Backscatter Ultraviolet Experiment (SSBUV-8) (previously flown on STS-34, STS-41, STS-43, STS-45, STS-56, STS-62 and STS-66), EDFT-03, Shuttle Laser Altimeter Payload (SLA-01/GAS(5)), VDA-2, National Institutes of Health NIH-R3 Experiment, Space Tissue Loss Experiment (STL/NIH-C), Pool Boiling Experiment (PBE) (hardware previously flown on STS-47, STS-57 and STS-60) and the Thermal Energy Storage (TES-2) experiment (previously flown on STS-69). Get Away Special payloads include the United States Air Force Academy G-342 Flexible Beam Experiment (FLEXBEAM-2), Society of Japanese Aerospace Companies' G-459 - Protein Crystal Growth Experiment and the Jet Propulsion Laboratory GAS Ballast Can with Sample Return Experiment. Endeavour's 10th flight also includes two 6.5 hour spacewalks by three astronauts to test hardware and tools that will be used in the assembly of the International Space Station starting in late 1997. EVA-1 on flight day five consists of Crewmembers Leroy Chiao (EV1) and Dan Barry (EV2) while EVA-2 on Flight Day 7 consists of Leroy Chiao (EV1) and Winston Scott (EV2). [Summary provided by NASA] Group: Platform_Details Entry_ID: STS-72 Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Platform_Series_or_Entity: SPACE SHUTTLE Short_Name: STS-72 Long_Name: Space Transport System STS-72 End_Group Group: Synonymous_Platform_Names Short_Name: Endeavour End_Group Group: Orbit Orbit_Altitude: 250 nm (288 statute miles) Orbit_Inclination: 28.45 degrees End_Group Creation_Date: 2008-01-30 Online_Resource: http://science.ksc.nasa.gov/shuttle/missions/sts-72/mission-sts-72.html Sample_Image: http://www.nasa.gov/images/content/134518main_sts-72-crew-sm.jpg Group: Platform_Logistics Launch_Date: 1996-01-11 Primary_Sponsor: NASA End_Group End_Group AJISAI AJISAI: Experimental Geodetic Satellite (Japanese EGS) Characteristics: Launch: August 13, 1986 H-I Launch Vehicle Tanegashima Space Center Orbit: 1500km(alt.) circular 50 deg. inclination 116 min. period Weight: 685kg Dimensions: 215cm(D) sphere with solar ray and laser beam reflectors Description: The short-range objective was testing NASDA's H-I'(2-stage) launch vehicle. The long-range applications included a survery aimed at rectifying Japan's demestic geodetic triangular net - determining the exact position of many isolated Japanese islands and establishing Japan's geodetic point of origin. The survey was conducted by the Geographical Survey Institute of the Ministry of Construction and the Hydrography Department of the Maritime Safety Agency, Ministry of Transport. For additional information, link to: http://www.jaxa.jp/projects/sat/egs/index_e.html [Source: National Space Development Agency of Japan] Group: Platform_Details Entry_ID: AJISAI Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: AJISAI Long_Name: Experimental Geodetic Satellite (Japanese EGS) End_Group Group: Synonymous_Platform_Names Short_Name: AJISAI End_Group Group: Platform_Associated_Instruments Short_Name: LRA End_Group Group: Orbit Orbit_Inclination: 50 deg Period: 116 min Perigee: 1490 km End_Group Creation_Date: 2007-11-14 Online_Resource: http://www.jaxa.jp/projects/sat/egs/index_e.html Online_Resource: http://ilrs.gsfc.nasa.gov/satellite_missions/list_of_satellites/ajis_general.html Sample_Image: http://ilrs.gsfc.nasa.gov/images/ajisai.gif Group: Platform_Logistics Launch_Date: 1986-08-13 Launch_Site: Tanegashima Island, Japan Primary_Sponsor: JAXA End_Group End_Group NSF/NCAR C-130 FAQs, Investigator Handbook and other materials related to capabilities of the NSF/NCAR C-130 C-130 is a versatile airborne research platform that is well suited for studies of the middle troposphere.With its 13,000 lbs payload capability and 10 hour endurance, the C-130 is well suited for a variety of research tasks that do not require reaching altitudes in excess of 26,000 feet. With excellent low altitude performance the C-130 is used extensively for studies of the planetary boundary layer, flying as low as 100 feet above the surface of the ocean. 2017-07-07 18:29:42.0 [sritz] insert AltLabel (id: null category: primary text: NSF/NCAR Hercules C130 Aircraft language code: en); insert Definition (id: null text: FAQs, Investigator Handbook and other materials related to capabilities of the NSF/NCAR C-130 C-130 is a versatile airborne research platform that is well suited for studies of the middle troposphere.With its 13,000 lbs payload capability and 10 hour endurance, the C-130 is well suited for a variety of research tasks that do not require reaching altitudes in excess of 26,000 feet. With excellent low altitude performance the C-130 is used extensively for studies of the planetary boundary layer, flying as low as 100 feet above the surface of the ocean. language code: en); 2017-07-07 18:28:13.0 [sritz] Insert Concept add broader relation (NSF/NCAR C-130 [3a59dbd3-86c4-47dd-aeb1-935c657aa544,309791] - Aircraft [227d9c3d-f631-402d-84ed-b8c5a562fc27,287509]); PA-12 From August 9 to December 10, 1947, Clifford Evans and George Truman circled the globe in their Piper Super Cruisers, covering 35,897 kilometers (22,436 miles), the first time light personal aircraft accomplished such a feat. Evans flew the City of Washington while Truman flew the City of The Angels, now at the Piper Aviation Museum in Lock Haven, Pennsylvania. The PA-12 was a more powerful J-5 Cruiser, with an electric starter, navigation lights, and a cabin heater. For the flight, Piper Aircraft arranged for second-hand planes and extra fuel tanks while radio and navigation equipment were also donated. Evans built a drift meter for each aircraft. Flags of each nation they visited were hand-painted on the fuselages' left sides and 53 of 55 city stops on the right sides. Group: Platform_Details Entry_ID: PA-12 Group: Platform_Identification Platform_Category: Aircraft Short_Name: PA-12 Long_Name: Piper PA-12 Super Cruiser End_Group Creation_Date: 2012-07-23 Online_Resource: http://airandspace.si.edu/collections/artifact.cfm?id=A19500101000 Sample_Image: http://airandspace.si.edu/images/collections/media/previews/A19500101000cp02.jpg End_Group GEMINI-5 Gemini 5, manned with two astronauts, was the third earth-orbiting spacecraft of the Gemini series. The cone-shaped spacecraft was 3.05 m in diameter at the largest end, which was the rear of the craft. The major objectives of this mission were to demonstrate (1) a long-duration manned flight using a fuel cell power system, (2) rendezvous capabilities, and (3) rendezvous maneuvers. scientific studies included zodiacal light, synoptic terrain, synoptic weather photography, and a cloud top spectrometer experiment. In addition, five medical and seven technological experiments were performed during the mission. The 120-orbit flight lasted 8 days, returning to earth on august 29, 1965. The mission was considered successful. Group: Platform_Details Entry_ID: GEMINI-5 Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Platform_Series_or_Entity: GEMINI Short_Name: GEMINI-5 End_Group Group: Synonymous_Platform_Names Short_Name: TITAN II (5) End_Group Group: Orbit Orbit_Inclination: 32.61 degrees Perigee: 197 km Apogee: 303 km End_Group Creation_Date: 2008-01-24 Online_Resource: http://science.ksc.nasa.gov/history/gemini/gemini-v/gemini-v.html Sample_Image: http://science.ksc.nasa.gov/history/gemini/gemini-v/gemini-v-patch-small.gif Group: Platform_Logistics Launch_Date: 1965-08-21 Primary_Sponsor: NASA End_Group End_Group OSO-2 The objectives of the OSO satellite series were to perform solar physics experiments above the atmosphere during a complete solar cycle and to map the celestial sphere for direction and intensity of UV light, X-rays, and gamma radiation. General Information: Designation: 00987 / 65007A Launch date: 3 Feb 1965 Country of origin: United States Mission: Scientific (Sun observation) Perigee/Apogee: 294/306 km Inclination: 32.8? Period: 90.5 min Launch vehicle: Thor Delta #29 Decay: 9 Aug 1989 [Summary provided by The Satellite Encyclopedia] Group: Platform_Details Entry_ID: OSO-2 Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Platform_Series_or_Entity: OSO (Orbiting Solar Observatory) Short_Name: OSO-2 Long_Name: Orbiting Solar Observatory-2 End_Group Group: Synonymous_Platform_Names Short_Name: OSO 2 End_Group Group: Platform_Associated_Instruments Short_Name: GAMMA RAY SPECTROMETERS End_Group Group: Orbit Orbit_Inclination: 32.8 degrees Period: 90.5 min Perigee: 294 km Apogee: 306 km End_Group Creation_Date: 2007-12-14 Online_Resource: http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/images/oso_images.html Sample_Image: http://heasarc.gsfc.nasa.gov/Images/oso/oso2.gif Group: Platform_Logistics Launch_Date: 1965-02-03 Primary_Sponsor: NASA End_Group End_Group SOUNDING ROCKETS Sounding rockets are sub-orbital rockets that carry a payload above the Earth's atmosphere for period of up to 15 minutes, but which do not place the payload into orbit around the Earth. [Source: Penn State Department of Astronomy and Astrophysics] ERS Earth Resource Satellite GEMINI-12 Gemini 12 was the tenth and final flight of the Gemini series, which bridged the Mercury and Apollo programs. This mission was scheduled to perform rendezvous and docking with the Agena target vehicle, to conduct three extravehicular activity (EVA) operations, and to conduct a tethered station keeping exercise. There were also 14 scientific, medical, and technological experiments on board. The successfully performed scientific experiments were (1) frog egg growth under zero-g, (2) synoptic terrain photography, (3) synoptic weather photography, (4) nuclear emulsions, (5) airglow horizon photography, (6) UV astronomical photography, and (7) dim sky photography. Two micrometeorite collection experiments, as well as three space phenomena photography experiments, were not fully completed. There were fuel cell and attitude control thruster problems during the mission, which was otherwise highly successful. Reentry was accomplished after 59 orbits, with the spacecraft under automatic control. It landed within 4.8 km of the intended impact point on november 15, 1966. Group: Platform_Details Entry_ID: GEMINI-12 Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Platform_Series_or_Entity: GEMINI Short_Name: GEMINI-12 End_Group Group: Synonymous_Platform_Names Short_Name: gemini-12 End_Group Group: Orbit Orbit_Inclination: 28.78 degrees Perigee: 243 km Apogee: 310 km End_Group Creation_Date: 2007-01-23 Online_Resource: http://www.astronautix.com/flights/gemini12.htm Sample_Image: http://www.astronautix.com/graphics/0/10074584.jpg Group: Platform_Logistics Launch_Date: 1966-11-11 Primary_Sponsor: NASA End_Group End_Group SORCE [Description for archival purposes only. SORCE ended its mission on 2020-02-25.] SORCE is a NASA-sponsored satellite mission that will provide state-of-the-art measurements of incoming x-ray, ultraviolet, visible, near-infrared, and total solar radiation. SORCE represents the merging of the EOS Solar Stellar Irradiance Comparison Experiment (SOLSTICE) and the Total Solar Irradiance Mission (TSIM). The measurements provided by SORCE specifically address long-term climate change, natural variability and enhanced climate prediction, and atmospheric ozone and UV-B radiation. These measurements are critical to studies of the Sun, its effect on our Earth system, and its influence on humankind. Solar radiation is the dominant, direct energy input into the terrestrial ecosystem, and it affects all physical, chemical, and biological processes. The Sun provides a natural influence on the Earth's atmosphere and climate. In order to understand mankind's roles in climate change, the Sun's impact must first be understood. SORCE measures the Sun's output with the use of state-of-the-art radiometers, spectrometers, photodiodes, detectors, and bolometers engineered into instruments mounted on a satellite observatory. The SORCE satellite orbits around the Earth accumulating solar data. Spectral measurements identify the irradiance of the Sun by characterizing the Sun's energy and emissions in the form of color that can then be translated into quantities and elements of matter. Data obtained by the SORCE experiment will be used to model the Sun's output and to explain and predict the effect of the Sun's radiation on the Earth's atmosphere and climate. Website: http://lasp.colorado.edu/sorce/ [Summary provided by NASA] Group: Platform_Details Entry_ID: SORCE Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Short_Name: SORCE Long_Name: Solar Radiation and Climate Experiment End_Group Group: Synonymous_Platform_Names Short_Name: 2003-004A Short_Name: 27651 End_Group Group: Platform_Associated_Instruments Short_Name: XPS Short_Name: SOLSTICE Short_Name: SIM Short_Name: TIM End_Group Group: Orbit Orbit_Altitude: 630 km Orbit_Inclination: 40 degrees Period: 97 minutes Perigee: 612.8 km Apogee: 652.5 km Orbit_Type: LEO > Low Earth Orbit > Polar Non-Sun-Synchronous End_Group Creation_Date: 2007-12-14 Online_Resource: http://lasp.colorado.edu/sorce/ Online_Resource: https://www.nasa.gov/directorates/heo/scan/services/missions/solarsystem/SORCE.html Online_Resource: https://eospso.nasa.gov/missions/solar-radiation-and-climate-experiment Group: Platform_Logistics Launch_Date: 2003-01-25 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Design_Life: 5 years Primary_Sponsor: LASP-CU Primary_Sponsor: OSC Primary_Sponsor: NASA End_Group End_Group 2020-03-04 17:18:20.0 [sritz] update Definition ([Description for archival purposes only. SORCE ended its mission on 2020-02-25.] SORCE is a NASA-sponsored satellite mission that will provide state-of-the-art measurements of incoming x-ray, ultraviolet, visible, near-infrared, and total solar radiation. SORCE represents the merging of the EOS Solar Stellar Irradiance Comparison Experiment (SOLSTICE) and the Total Solar Irradiance Mission (TSIM). The measurements provided by SORCE specifically address long-term climate change, natural variability and enhanced climate prediction, and atmospheric ozone and UV-B radiation. These measurements are critical to studies of the Sun, its effect on our Earth system, and its influence on humankind. Solar radiation is the dominant, direct energy input into the terrestrial ecosystem, and it affects all physical, chemical, and biological processes. The Sun provides a natural influence on the Earth's atmosphere and climate. In order to understand mankind's roles in climate change, the Sun's impact must first be understood. SORCE measures the Sun's output with the use of state-of-the-art radiometers, spectrometers, photodiodes, detectors, and bolometers engineered into instruments mounted on a satellite observatory. The SORCE satellite orbits around the Earth accumulating solar data. Spectral measurements identify the irradiance of the Sun by characterizing the Sun's energy and emissions in the form of color that can then be translated into quantities and elements of matter. Data obtained by the SORCE experiment will be used to model the Sun's output and to explain and predict the effect of the Sun's radiation on the Earth's atmosphere and climate. Website: http://lasp.colorado.edu/sorce/ [Summary provided by NASA] Group: Platform_Details Entry_ID: SORCE Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Short_Name: SORCE Long_Name: Solar Radiation and Climate Experiment End_Group Group: Synonymous_Platform_Names Short_Name: 2003-004A Short_Name: 27651 End_Group Group: Platform_Associated_Instruments Short_Name: XPS Short_Name: SOLSTICE Short_Name: SIM Short_Name: TIM End_Group Group: Orbit Orbit_Altitude: 630 km Orbit_Inclination: 40 degrees Period: 97 minutes Perigee: 612.8 km Apogee: 652.5 km Orbit_Type: LEO > Low Earth Orbit > Polar Non-Sun-Synchronous End_Group Creation_Date: 2007-12-14 Online_Resource: http://lasp.colorado.edu/sorce/ Online_Resource: https://www.nasa.gov/directorates/heo/scan/services/missions/solarsystem/SORCE.html Online_Resource: https://eospso.nasa.gov/missions/solar-radiation-and-climate-experiment Group: Platform_Logistics Launch_Date: 2003-01-25 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Design_Life: 5 years Primary_Sponsor: LASP-CU Primary_Sponsor: OSC Primary_Sponsor: NASA End_Group End_Group); delete Resource (null); GOES-13 GOES-13 (GOES-N) lifted off aboard a Boeing Delta IV rocket from Space Launch Complex 37 at Cape Canaveral Air Force Station, Florida at 6:11 pm EDT on May 25, 2006. GOES-13 (GOES-N) is the latest in a series of Earth monitoring satellites. Geostationary Operational Environmental Satellites (GOES) provide the kind of continuous monitoring necessary for intensive data analysis. Geostationary describes an orbit in which a satellite is always in the same position with respect to the rotating Earth. This allows GOES to hover continuously over one position on the Earth's surface, appearing stationary. As a result, GOES provide a constant vigil for the atmospheric "triggers" for severe weather conditions such as tornadoes, flash floods, hail storms, and hurricanes. Orbit: Altitude: 36000 km Geo-Synchronous Vital Statistics: Weight 3200 kg Size: 4.2 meters (l) x 1.88 meters (w) Power: 2300 watts Mission Life: 5 years Instruments: Sounder Imager SEM (Space Environment Monitor) S and R (Search and Rescue) For more information, see: http://www.nasa.gov/mission_pages/goes-n/main/index.html [Summary provided by NASA.] Group: Platform_Details Entry_ID: GOES-13 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: GOES (Geostationary Operational Environmental Satellite) Short_Name: GOES-13 Long_Name: Geostationary Operational Environmental Satellite 13 End_Group Group: Synonymous_Platform_Names Short_Name: GOES 13 Short_Name: GOES-N End_Group Group: Platform_Associated_Instruments Short_Name: GOES N-P IMAGER Short_Name: GOES N-P SOUNDER Short_Name: SEM Short_Name: SXI End_Group Group: Orbit Orbit_Type: GEO > Geosynchronous > Geostationary End_Group Creation_Date: 2007-10-04 Online_Resource: http://www.nasa.gov/mission_pages/goes-n/main/index.html Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=2006-018A Group: Platform_Logistics Launch_Date: 2006-05-25 Launch_Site: CAPE CANAVERAL/KENNEDY SPACE CENTER, USA Design_Life: 5 YEARS Primary_Sponsor: USA/NASA Primary_Sponsor: USA/NOAA End_Group End_Group BUOYS BUOY Buoys, in the oceanographic context, are platforms whose defining characteristic is that they float at a predetermined depth in the ocean. Most often BUOYS float on the surface of the ocean. Typically, BUOYS are divided into two categories: drifting and moored buoys. Moored BUOYS are floats fixed in water to mark a location, warn of danger, or indicate a navigational channel. They can also take scientific measurements of the water including temperature and water quality measurements. Drifting BUOYS are exclusively scientific platforms that drift along the surface of the ocean following the ocean currents and/or the surface winds depending on their configuration. Along the trajectory, they collect oceanographic or meteorological data. Group: Platform_Details Entry_ID: BUOYS Group: Platform_Identification Platform_Category: In Situ Ocean-based Platforms Platform_Series_or_Entity: BUOYS Short_Name: BUOYS End_Group End_Group 2016-06-09 18:33:02.0 [epneff] added altLabel insert AltLabel (id: null text: BUOY language code: en); SOON The Solar Observing Optical Network (SOON), maintained and operated by the U.S. Air Force, monitors solar activity. The SOON sites are given below. Name Location Description Holloman N32 E254 Holloman AFB, New Mexico, USA Learmonth S22 E114 Learmonth, Australia Palehua N21 E202 Palehua, Hawaii, USA Ramey N18 E293 Ramey AFB, Puerto Rico San Vito N46 E013 San Vito, Italy IDN_Node: USA/NASA AERIAL PHOTOGRAPHS AERIAL PHOTOGRAPH Air Photographs or aerial photography are photographs of a portion of the Earth's surface, often from taken from airplanes. [Source: About Geography] Group: Platform_Details Entry_ID: AERIAL PHOTOGRAPHS Group: Platform_Identification Platform_Category: Maps/Charts/Photographs Short_Name: AERIAL PHOTOGRAPHS End_Group Group: Synonymous_Platform_Names Short_Name: Aerial Photographs End_Group Creation_Date: 2007-12-13 Online_Resource: http://erg.usgs.gov/isb/pubs/booklets/aerial/aerial.html Sample_Image: http://erg.usgs.gov/isb/pubs/booklets/aerial/graphics/fig4.gif End_Group 2016-06-09 18:37:13.0 [epneff] added altLabel insert AltLabel (id: null text: AERIAL PHOTOGRAPH language code: en); SMS-1 SMS-1 was launched in May 1974 and was a NASA-developed, NOAA-operated, prototype spacecraft for the geosynchronous series of meteorological satellites. The cylindrically shaped spacecraft measured 190.5 cm in diameter and 230 cm in length, exclusive of a magnetometer that extended an additional 83 cm beyond the cylinder shell. The primary structural members were a honeycombed equipment shelf and thrust tube. The VISSR telescope was mounted on the equipment shelf and viewed the Earth through a special aperture in the side of the spacecraft. A support structure extended radially from the thrust tube and was affixed to the solar panels, which formed the outer walls of the spacecraft and provided the primary source of electrical power. Located in the annulus-shaped space between the thrust tube and the solar panels were stationkeeping and dynamics control equipment, batteries, and most of the SEM equipment. Proper spacecraft attitude and spin rate (approximately 100 rpm) were maintained by two separate sets of jet thrusters mounted around the spacecraft equator and activated by ground command. The spacecraft used both UHF-band and S-band frequencies in its telemetry and command subsystem. A low-power VHF transponder provided telemetry and command during launch and then served as a backup for the primary subsystem once the spacecraft attained orbit. This spin-stabilized spacecraft carried a visible infrared spin-scan radiometer, meteorological data collection and relay system, space environment monitor, and a biaxial fluxgate magnetometer. Throughout its 7 year history, it operated at 45, 75 and 92 degrees West. __________ Taken from the NSSDC System for Information Retrieval and Storage (SIRS). For more information contact the NSSDC Coordinated Request and User Support Office, 301-286-6695 (NASA Goddard Space Flight Center, Code 933.4, Greenbelt, Maryland 20771, USA,"http://nssdc.gsfc.nasa.gov/"). Group: Platform_Details Entry_ID: SMS-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: SMS (Synchronous Meteorological Satellites) Short_Name: SMS-1 Long_Name: Synchronous Meteorological Satellite 1 End_Group Group: Synonymous_Platform_Names Short_Name: SMS-1 End_Group Group: Platform_Associated_Instruments Short_Name: SXM Short_Name: EPM Short_Name: VISSR Short_Name: SEM Short_Name: DCS Short_Name: Magnetic Field Monitor End_Group Creation_Date: 2007-11-13 Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1974-033A Sample_Image: http://goespoes.gsfc.nasa.gov/goes/project/images/SMS.jpg Group: Platform_Logistics Launch_Date: 1974-05-17 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: USA/NASA Primary_Sponsor: USA/NOAA End_Group End_Group LABORATORY A laboratory is a room or building equipped for scientific experimentation or research. (Source: The American Heritage Dictionary) LANDSAT 2019-12-31 21:59:57.0 [sritz] Insert Concept add narrower relation (LANDSAT [3cc4a1e8-3b94-4567-90b3-32137aec2d9e,541561] - LANDSAT-9 [5d3ce672-39fb-4dd5-be5e-55f81fb7f40f,559589]); 2018-06-12 16:53:34.0 [mmorahan] Insert Concept add narrower relation (LANDSAT [3cc4a1e8-3b94-4567-90b3-32137aec2d9e,344819] - LANDSAT-6 [b912164c-36a5-4d93-9638-1afb3e4c4354,367683]); R/V ONNURI 2013-05-24 19:51:13.0 [aaleman] Insert Concept add broader relation (R/V ONNURI [3ccb3423-b471-437e-87d0-e964702bd90f,105161] - SHIPS [82a67b12-e99d-4c90-8a6a-a6f79d4c3c7b,73407]); WESTPAC WESTPAC (Western Pacific Laser Satellite) was an Australia geodetic satellite for the joint venture between Australia's Electro Optics and the Russian Space Agency. It was spherical in shape with laser reflectors. It served as a target for the Western Pacific Laser Tracking Network. For additional Information, view the WESTPAC report at http://ilrs.gsfc.nasa.gov/docs/Westpac_final.doc [Summary provided by NASA] Group: Platform_Details Entry_ID: WESTPAC Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: WESTPAC Long_Name: Western Pacific Laser Satellite End_Group Group: Synonymous_Platform_Names Short_Name: WESTPAC Short_Name: 25398 End_Group Group: Platform_Associated_Instruments Short_Name: SLR End_Group Group: Orbit Orbit_Altitude: 835 km Orbit_Inclination: 98.8° Period: 101.3 minutes Perigee: 817.0 km Apogee: 845.0 km End_Group Creation_Date: 2007-11-30 Online_Resource: http://ilrs.gsfc.nasa.gov/docs/Westpac_final.doc Group: Platform_Logistics Launch_Date: 1998-07-10 Launch_Site: Baikonur Cosmodrome, Tyuratam, Russia Primary_Sponsor: Australia Primary_Sponsor: Russia End_Group End_Group NDBC MOORED BUOY 2012-08-07 19:42:12.0 [mpmorahan] Insert Concept add broader relation (NDBC MOORED BUOY [3d83b3e3-1be0-4ab8-9cf5-3b7ade27586e,40471] - In Situ Ocean-based Platforms [e50b2a1a-7d9d-4c09-ac7e-dc29f0c08fc7,31421]); NOAA-4 NOAA-4 was launched in November 1974 and was one in a series of reconfigured ITOS satellites launched with new meteorological sensors onboard to expand the operational capability of the ITOS system. The primary objective was to provide global daytime and nighttime direct readout real-time cloudcover data on a daily basis. The sun-synchronous spacecraft was also capable of supplying global atmospheric temperature soundings and very high resolution infrared cloudcover data for selected areas in either a direct readout or a tape-recorder mode. A secondary objective was to obtain global solar-proton flux data on a real-time daily basis. The sensors were mounted on the satellite baseplate with their optical axes directed vertically earthward. The nearly cubical spacecraft measured 1 by 1 by 1.2 m. The satellite was equipped with three curved solar panels that were folded during launch and deployed after orbit was achieved. Each panel measured over 4.2 m in length when unfolded and was covered with approximately 3500 solar cells measuring 2 by 2 cm. The dynamics and attitude control system maintained desired spacecraft orientation through gyroscopic principles incorporated into the satellite design. Earth orientation of the satellite body was maintained by taking advantage of the precession induced from a momentum flywheel so that the satellite body precession rate of one revolution per orbit provided the desired 'earth-looking' attitude. Minor adjustments in attitude and orientation were made by means of magnetic coils and by varying the speed of the momentum flywheel. The primary sensors consisted of a Very High Resolution Radiometer (VHRR), Vertical Temperature Profile Radiometer (VTPR), and a Scanning Radiometer (SR). __________ Taken from the NSSDC System for Information Retrieval and Storage (SIRS). For more information contact the NSSDC Coordinated Request and User Support Office, 301-286-6695 (NASA Goddard Space Flight Center, Code 933.4, Greenbelt, Maryland 20771, USA, "http://nssdc.gsfc.nasa.gov/). LAPAN-TUBSAT LAPAN-TUBSAT is a cooperation between TU Berlin and the National Institute of Aeronautics and Space of Indonesia (Lembaga Penerbangan dan Antariksa Nasional/LAPAN). It was launched with an Indian PSLV on Jan. 10, 2007. It's design follows the TUBSAT family with dimensions of 45x45x27cm and a mass of about 56kg. Mission goals: -Technology Demonstrators -Earth Observation -Attitude Control Experiments Summary provided by: http://www.ilr.tu-berlin.de/RFA/sat/lapan/content.htm Group: Platform_Details Entry_ID: LAPAN-TUBSAT Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: LAPAN-TUBSAT End_Group Group: Platform_Associated_Instruments Short_Name: CAMERAS End_Group Group: Orbit Orbit_Inclination: 97.9° Period: 97.3 minutes Perigee: 620.0 km Apogee: 638.0 km End_Group Creation_Date: 2008-07-24 Online_Resource: http://www.ilr.tu-berlin.de/RFA/sat/lapan/content.htm Sample_Image: http://www.ilr.tu-berlin.de/RFA/sat/lapan/img/lapan-view-01.gif Group: Platform_Logistics Launch_Date: 2007-01-10 Launch_Site: Sriharikota Island, India Primary_Sponsor: Indonesia Primary_Sponsor: Germany End_Group End_Group OCO [Source: NASA Home Page] NASA’s Orbiting Carbon Observatory satellite failed to reach orbit after its 4:55 a.m. EST liftoff Feb. 24 (2009) from California’s Vandenberg Air Force Base. Preliminary indications are that the fairing on the Taurus XL launch vehicle failed to separate. The fairing is a clamshell structure that encapsulates the satellite as it travels through the atmosphere. The spacecraft did not reach orbit and likely landed in the Pacific Ocean near Antarctica, said John Brunschwyler, the program manager for the Taurus XL. A Mishap Investigation Board is to determine the cause of the launch failure. [Source: NASA OCO Project Home Page, https://oco.jpl.nasa.gov/ ] The Orbiting Carbon Observatory (OCO) is a new Earth orbiting mission sponsored by NASA's Earth System Science Pathfinder Project (ESSP) Program. The ESSP Program funds competitively selected, low to moderate cost Earth Science missions. These highly focused missions acquire exploratory measurements of the atmosphere, the oceans, the land surface and the solid Earth. These missions share a common goal of improving the capability of Earth scientists to predict changes in weather, climate and natural hazards. After launch in 2009, the OCO mission will collect precise global measurements of carbon dioxide (CO2) in the Earth's atmosphere. Scientists will analyze OCO data to improve our understanding of the natural processes and human activities that regulate the abundance and distribution of this important greenhouse gas. This improved understanding will enable more reliable forecasts of future changes in the abundance and distribution of CO2 in the atmosphere and the effect that these changes may have on the Earth's climate. The Jet Propulsion Laboratory will lead the OCO effort. Orbital Sciences Corporation and Hamilton Sundstrand Sensor Systems will partner with JPL to realize this vital mission. Group: Platform_Details Entry_ID: OCO Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: OCO Long_Name: Orbiting Carbon Observatory End_Group Group: Platform_Associated_Instruments Short_Name: OCO SPECTROMETERS Short_Name: NEAR-INFRARED SPECTROMETER End_Group Group: Orbit Orbit_Altitude: 705 km Orbit_Inclination: 98.2 degrees Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-05-21 Online_Resource: https://oco.jpl.nasa.gov/ Group: Platform_Logistics Design_Life: 2 years Primary_Sponsor: USA/NASA End_Group End_Group 2019-05-03 17:59:49.0 [sritz] update Definition ([Source: NASA Home Page] NASA’s Orbiting Carbon Observatory satellite failed to reach orbit after its 4:55 a.m. EST liftoff Feb. 24 (2009) from California’s Vandenberg Air Force Base. Preliminary indications are that the fairing on the Taurus XL launch vehicle failed to separate. The fairing is a clamshell structure that encapsulates the satellite as it travels through the atmosphere. The spacecraft did not reach orbit and likely landed in the Pacific Ocean near Antarctica, said John Brunschwyler, the program manager for the Taurus XL. A Mishap Investigation Board is to determine the cause of the launch failure. [Source: NASA OCO Project Home Page, https://oco.jpl.nasa.gov/ ] The Orbiting Carbon Observatory (OCO) is a new Earth orbiting mission sponsored by NASA's Earth System Science Pathfinder Project (ESSP) Program. The ESSP Program funds competitively selected, low to moderate cost Earth Science missions. These highly focused missions acquire exploratory measurements of the atmosphere, the oceans, the land surface and the solid Earth. These missions share a common goal of improving the capability of Earth scientists to predict changes in weather, climate and natural hazards. After launch in 2009, the OCO mission will collect precise global measurements of carbon dioxide (CO2) in the Earth's atmosphere. Scientists will analyze OCO data to improve our understanding of the natural processes and human activities that regulate the abundance and distribution of this important greenhouse gas. This improved understanding will enable more reliable forecasts of future changes in the abundance and distribution of CO2 in the atmosphere and the effect that these changes may have on the Earth's climate. The Jet Propulsion Laboratory will lead the OCO effort. Orbital Sciences Corporation and Hamilton Sundstrand Sensor Systems will partner with JPL to realize this vital mission. Group: Platform_Details Entry_ID: OCO Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: OCO Long_Name: Orbiting Carbon Observatory End_Group Group: Platform_Associated_Instruments Short_Name: OCO SPECTROMETERS Short_Name: NEAR-INFRARED SPECTROMETER End_Group Group: Orbit Orbit_Altitude: 705 km Orbit_Inclination: 98.2 degrees Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-05-21 Online_Resource: https://oco.jpl.nasa.gov/ Group: Platform_Logistics Design_Life: 2 years Primary_Sponsor: USA/NASA End_Group End_Group); 2018-04-24 20:58:37.0 [sritz] update WeightedRelation (Similar); update WeightedRelation (1); update WeightedRelation (Similar); update WeightedRelation (1); 2018-04-24 20:56:34.0 [sritz] insert WeightedRelation (id: null related concept uuid: da687fb4-016d-4b4d-92c2-380640ca5640 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 6d5f222a-7750-4fd3-aa14-3c0d0059bc85 relationship type: null relationship value: null generated by: null); IRS (Indian Remote Sensing Satellite) 2020-01-24 14:27:50.0 [mmorahan] Insert Concept add narrower relation (IRS (Indian Remote Sensing Satellite) [3e8bc0c6-f599-4e23-9535-449af00edd61,541575] - IRS-R2A [56535da7-3b47-41e2-a3a9-b88a6abbc5ef,559799]); 2016-04-05 14:41:06.0 [mpmorahan] Insert Concept add narrower relation (IRS (Indian Remote Sensing Satellite) [3e8bc0c6-f599-4e23-9535-449af00edd61,143483] - IRS-RS2 [fd710ee8-797c-490a-9f90-064a38141f99,158885]); 2015-09-14 14:15:50.0 [mpmorahan] Insert Concept add narrower relation (IRS (Indian Remote Sensing Satellite) [3e8bc0c6-f599-4e23-9535-449af00edd61,143483] - K1 [87daf1d5-4f7c-40e9-8d31-4c816c320029,158397]); 2012-10-25 13:03:29.0 [mpmorahan] Insert Concept add narrower relation (IRS (Indian Remote Sensing Satellite) [3e8bc0c6-f599-4e23-9535-449af00edd61,74275] - IRS-O2 [df967339-0096-4445-8732-0071f1de9e27,81983]); AC-680E The Aero Commander 500 is the first in a series of light twin-engined aircraft originally built by the Aero Design and Engineering Company in the late 1940s. It later became the Aero Commander division of Rockwell International. The initial production version was the Aero Commander 520. Versions manufactured after 1967 are known as the Shrike Commander. [Photo and Text provided by Wikipedia, http://en.wikipedia.org/wiki/Aero_Commander_500 ] Group: Platform_Details Entry_ID: AC-680E Group: Platform_Identification Platform_Category: Aircraft Short_Name: AC-680E Long_Name: Rockwell Aero Commander AC-680E End_Group Creation_Date: 2008-07-15 Online_Resource: http://en.wikipedia.org/wiki/Aero_Commander_500 Sample_Image: http://upload.wikimedia.org/wikipedia/en/6/6f/AeroCommander680AtKCOS.JPG End_Group HJ1B Disaster and Environment Monitoring and Forecast Small Satellite Constellation B Launch Date: 06 Sep 2008 EOL Date: 01 Sep 2011 Type: Sun-synchronous Altitude: 649 km Period: Inclination: 97.9 deg Repeat cycle: 31 days LST: 10:30 Asc/desc: Descending URL: http://www.cresda.com/ Group: Platform_Details Entry_ID: HJ1B Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: HJ1B Long_Name: HuanJing 1B Satellite End_Group Group: Synonymous_Platform_Names Short_Name: HJ-1B End_Group Group: Platform_Associated_Instruments Short_Name: IRS (HuanJing 1B) Short_Name: CCD2 (HuanJing 1B) Short_Name: CCD1 (HuanJing 1B) End_Group Group: Orbit Orbit_Altitude: 649 km Orbit_Inclination: 97.9 deg Equator_Crossing: 10:30 AM Local time: e.g. Repeat_Cycle: 31 days Orbit_Type: LEO > LOW EARTH ORBIT > POLAR SUN-SYNCHRONOUS End_Group Creation_Date: 2012-07-25 Online_Resource: http://www.cresda.com/n16/n92006/n92066/n98627/index.html Group: Platform_Logistics Launch_Date: 2008-09-06 Launch_Site: TAIYUAN SPACE LAUNCH CENTER, CHINA Primary_Sponsor: CRESDA, CAST, NRSCC End_Group End_Group 2012-07-25 17:24:30.0 [mpmorahan] Insert Concept add broader relation (HJ1B [3edef6e1-db0b-4806-b586-8869a7c986ba,40375] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,31221]); SPACE SHUTTLE MOS-1B - Spacecraft Brief Description - The Japanese Marine Observation Satellite-1b (MOS-1b) was the second Earth resources satellite in the MOS series to be launched by NASDA to monitor atmospheric water vapor, ocean currents, sea surface temperature, ice floe dynamics, chlorophyll concentration in the oceans, and vegetation and agricultural land applications. The MOS-1b carried the same three sensors as the MOS-1a: a Multi-spectrum Electronic Self-Scanning Radiometer (MESSR), a Visible and Thermal Infrared Radiometer (VTIR), and a Microwave Scanning Radiometer (MSR). Data was transmitted real-time to the Hatoyama Earth Observation Center for processing and is available through the Data Service Department, Remote Sensing Technology Center of Japan (RESTEC). The satellite also included a Data Collection System (DCS) Transponder designed to be a forerunner of the Japanese TDRSS, used to collect and relay information from surface Data Collection Platforms (DCPs) and locate DCPs based on the Doppler frequency of received signals. The satellite is a 1.26 x 1.48 x 2.4 meter high box-shape of aluminium honeycomb construction with a single solar array of three 1.51 meter wide panels. The satellite is controlled in three axes by momentum wheels and four IN hydrazine thrusters. Other MOS satellites are planned throughout the 1990's. - Auxiliary Information - Launch Date and Time : 1990-02-07 Epoch Date and Time : Apogee (km or AU): 940. Perigee (km or AU): 909. Inclination (degree) : 99. Orbit Type : Geocentric Information last updated on 1992-06-09 Group: Platform_Details Entry_ID: MOS-1B Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: MOS (Japan Marine Observation Satellite) Short_Name: MOS-1B Long_Name: Japanese Marine Observation Satellite-1B End_Group Group: Synonymous_Platform_Names Short_Name: Momo-1b End_Group Group: Platform_Associated_Instruments Short_Name: MSR Short_Name: VTIR Short_Name: MESSR End_Group Online_Resource: http://www.jaxa.jp/projects/sat/mos1/index_e.html Online_Resource: http://nasascience.nasa.gov/missions/mos Group: Platform_Logistics Launch_Date: 1990-02-07 Launch_Site: Tanegashima Island, Japan Design_Life: 2 Years Primary_Sponsor: Japan/JAXA End_Group End_Group B/O MYTILUS The B/O Mytilus was built in hopes to fulfill the need of a maritime vessel in Ecuador. The Mytilus holds various laboratories and instruments to assist in research. Group: Platform_Details Entry_ID: B/O MYTILUS Group: Platform_Identification Platform_Category: In Situ Ocean-based Platforms Platform_Series_or_Entity: SHIPS Short_Name: B/O MYTILUS End_Group Creation_Date: 2012-07-19 Online_Resource: http://www.iim.csic.es/~waldo/Index.html Sample_Image: http://www.iim.csic.es/~waldo/fotos/mytilus/mytilus-circu.gif End_Group R/V PANDALUS The goals of the sampling from the Pandalus are to determine the distribution and abundance of surface fishes, sample surface zooplankton, measure water temperature, salinity, and fluorescence in the water column, and collect zooplankton for later studies. Samples will be taken at specific station locations along the Seward hydrographic transect (GAK line). Group: Platform_Details Entry_ID: R/V PANDALUS Group: Platform_Identification Platform_Category: In Situ Ocean-based Platforms Platform_Series_or_Entity: SHIPS Short_Name: R/V PANDALUS End_Group Creation_Date: 2012-07-19 Online_Resource: http://www.ims.uaf.edu/salmon/research/mesoscale/outreach/pandalus.htm Sample_Image: http://www.ims.uaf.edu/salmon/research/mesoscale/outreach/pictures/pandalus.jpg End_Group GEMINI-10 This spacecraft, an ATLAS/AGENA vehicle, was successfully launched from Cape Kennedy on July 18, 1966. It was the GEMINI X AGENA target vehicle (GATV10) with which the GEMINI 10 crew of young and collins successfully docked on July 21, 1966, 5 hr, 21 min after GEMINI 10 was launched. during rendezvous and docking, three midcourse maneuvers were effected using the GATV secondary propulsion system. In maneuver 1, the orbital apogee was changed from 163 n.m. to 414 n.m., the perigee from 158 to 160 n.m., the period from 90.4 to 94.9 min, and the inclination from 2887 to 2888 deg. During maneuver 2, the apogee was changed from 414 to 206 n.m., the perigee from 160 to 160 n.m., the period from 94.9 to 91.2 min, and the inclination from 2888 to 2886 deg. During maneuver 3, the apogee was changed from 206 to 209 n.m., the perigee from 160 to 204 n.m., the period from 91.2 to 92.0 min, and the inclination from 2886 to 2884 deg. Group: Platform_Details Entry_ID: GEMINI-10 Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Platform_Series_or_Entity: GEMINI Short_Name: GEMINI-10 End_Group Group: Synonymous_Platform_Names Short_Name: TITAN II Short_Name: EVA Short_Name: Pad LC-19 End_Group Group: Orbit Orbit_Inclination: 28.9 degrees Period: 92 minutes Perigee: 160 km Apogee: 206 km End_Group Creation_Date: 2008-01-18 Online_Resource: http://science.ksc.nasa.gov/history/gemini/gemini-x/gemini-x.html Sample_Image: http://science.ksc.nasa.gov/history/gemini/gemini-x/gemini-x-patch-small.gif Group: Platform_Logistics Launch_Date: 1966-07-18 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: NASA End_Group End_Group FASTSAT-1 [Source: Mark Boudreaux, Edward Montgomery, Joseph Casas "A Fast, Affordable, Science and Technology SATellite (FASTSAT) and the Small Satellite Market Development Environment", NASA, Huntsville, Alabama USA ] The National Aeronautics and Space Administration at Marshall Space Flight Center and the National Space Science and Technology Center in Huntsville Alabama USA, are jointly developing a new class of science and technology mission small satellites. The Fast, Affordable, Science and Technology SATellite (FASTSAT) was designed and developed using a new collaborative and best practices approach. The FASTSAT development, along with the new class of low cost vehicles currently being developed, would allow performance of ~ 30 kg payload mass missions for a cost of less than 10 million US dollars. Group: Platform_Details Entry_ID: FASTSAT-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: FASTSAT-1 Long_Name: Fast, Affordable, Science and Technology SATellite, 1 End_Group Creation_Date: 2009-10-23 Online_Resource: http://www.google.com/url?sa=t&source=web&ct=res&cd=1&ved=0CAoQFjAA&url=http%3A%2F%2Fntrs.nasa.gov%2Farchive%2Fnasa%2Fcasi.ntrs.nasa.gov%2F20080036190_2008036047.pdf&ei=BgfiSsn_I5OuMPnW0bYB&usg=AFQjCNHZ6N43VBkE4WvahXScylTbIEH_jw&sig2=Q7Ps8w9mdQtbZT7JWHLgbw Online_Resource: http://science.nasa.gov/headlines/y2007/19nov_fastsat.htm Online_Resource: http://www.nasa.gov/mission_pages/smallsats/fastsat/ Group: Platform_Logistics Primary_Sponsor: USA/NASA End_Group End_Group MITgcm numerical model designed for study of the atmosphere, ocean, and climate, MITgcm’s flexible non-hydrostatic formulation enables it to efficiently simulate fluid phenomena over a wide range of scales; its adjoint capabilities enable it to be applied to sensitivity questions and to parameter and state estimation problems. By employing fluid equation isomorphisms, a single dynamical kernel can be used to simulate flow of both the atmosphere and ocean. The model is developed to perform efficiently on a wide variety of computational platforms. 2019-11-25 18:00:12.0 [mmorahan] insert Definition (id: null text: numerical model designed for study of the atmosphere, ocean, and climate, MITgcm’s flexible non-hydrostatic formulation enables it to efficiently simulate fluid phenomena over a wide range of scales; its adjoint capabilities enable it to be applied to sensitivity questions and to parameter and state estimation problems. By employing fluid equation isomorphisms, a single dynamical kernel can be used to simulate flow of both the atmosphere and ocean. The model is developed to perform efficiently on a wide variety of computational platforms. language code: en); 2019-11-25 17:58:47.0 [mmorahan] Insert Concept add broader relation (MITgcm [3fd56bd8-0e40-4401-9033-97df9a552001,423563] - Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,405101]); OGO-2 OGO 2 was a large observatory instrumented with 20 experiments designed to make simultaneous, correlative observations of aurora and airglow emissions, energetic particles, magnetic field variations, ionospheric properties, etc., especially over the polar areas. OGO 2 consisted of a main body, generally parallelepipedal in form, two rectangular solar panels, each with a solar-oriented experiment package (SOEP), and two orbital plane experiment packages (OPEP). It also included six experiment packages (EP-1,-2,-3,-4,-5, and -6) mounted on booms extending generally fore and aft of the spacecraft along the Y axis. Antenna and attitude control fixtures also extended from separate and/or EP booms. The main body was attitude-controlled by use of horizon scanners and gas jets and was designed to point toward the earth (Z axis). The axis connecting the two solar panels (X axis) was designed to oscillate in order to remain perpendicular to the earth-sun-spacecraft plane. The solar panels activated by sun sensors could rotate about this X axis in order to obtain maximum radiation for the solar cells and concurrently orient the SOEP properly. The OPEPs were reoriented on either end of an axis that was parallel to the Z axis and attached to the forward end of the main body. These OPEP sensors normally were maintained looking forward in the orbital plane of the satellite. To maintain this orientation, the OPEP axis could rotate over 90 deg. In addition, an angular difference of over 90 deg was possible between the orientation of the upper and lower OPEP packages. The SOEP contained four experiments, and the OPEP contained five experiments. Soon after achieving orbit, difficulties in maintaining earth lock with horizon scanners caused exhaustion of attitude control gas by October 23, 1965, 10 days after launch. At this time, the spacecraft entered a spin mode (about 0.11 rpm) with a large coning angle about the previously vertical axis. Five experiments became useless when the satellite went into this spin mode. Six additional experiments were degraded by this loss of attitude control. By April 1966, both batteries had failed, so subsequent observations were limited to sunlit portions of the orbit. By December 1966, only eight experiments were operational, five of which were not degraded by the spin mode operation. By April 1967, the tape recorders had malfunctioned and only one third of the recorded data could be processed. Spacecraft power and periods of operational scheduling conflicts created six large data gaps so that data were observed on a total of about 306 days of the 2-yr, 18-day total span of observed satellite data to November 1, 1967. The data gaps were (a) October 24, 1965, to November 5, 1965, (b) December 6, 1965, to January 7, 1966, (c) April 9, 1966, to June 21, 1966, (d) September 2, 1966, to November 18, 1966, (e) December 27, 1966, to April 11, 1967, and (f) May 9, 1967, to September 19, 1967. The spacecraft was shut down on November 1, 1967, with eight experiments still operational. It was reactivated for 2 weeks in February 1968 to operate experiment 65-081A-05. [Summary provided by NASA.] Group: Platform_Details Entry_ID: OGO-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: OGO (Orbiting Geophysical Observatory) Short_Name: OGO-2 Long_Name: Orbiting Geophysical Observatory-2 End_Group Group: Synonymous_Platform_Names Short_Name: OGO-C Short_Name: POGO 1 Short_Name: 01620 End_Group Group: Platform_Associated_Instruments Short_Name: SPECTROMETERS Short_Name: MAGNETOMETERS End_Group Group: Orbit Orbit_Inclination: 87.4 degrees Period: 104.0 minutes Perigee: 414.0 km Apogee: 1510.0 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-02-13 Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1965-081A Sample_Image: http://heasarc.gsfc.nasa.gov/Images/ogo/ogo.gif Group: Platform_Logistics Launch_Date: 1965-10-14 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: NASA End_Group End_Group GLORY [2011-03-04, NASA's Glory Satellite Fails To Reach Orbit] [Source: NASA Press Release 11-050, http://www.nasa.gov/home/hqnews/2011/mar/HQ_11-050_N0_Glory.html ] WASHINGTON -- NASA's Glory mission launched from Vandenberg Air Force Base in California Friday at 5:09:45 a.m. EST failed to reach orbit. Telemetry indicated the fairing, the protective shell atop the Taurus XL rocket, did not separate as expected about three minutes after launch. // [Source: Glory Science Home Page, http://glory.giss.nasa.gov/ ] Glory is a remote-sensing Earth-orbiting observatory designed to achieve two separate mission objectives. One is to collect data on the chemical, microphysical, and optical properties, and spatial and temporal distributions of aerosols. The other is to continue collection of total solar irradiance data for the long-term climate record. The Glory mission's scientific objectives are met by implementing two separate science instruments, one with the ability to collect polarimetric measurements along the satellite ground track within the solar reflective spectral region (0.4 to 2.4 micrometers) and one with the ability to monitor changes in sunlight incident on the Earth's atmosphere by collecting high accuracy, high precision measurements of total solar irradiance. Glory accomplishes these objectives by deploying two instruments aboard a low earth orbit satellite, the Aerosol Polarimetry Sensor (APS) and the Total Irradiance Monitor (TIM). Additionally, a cloud camera system will provide images that allow the APS scans along the spacecraft ground track to be put into spatial context and to facilitate determination of cloud occurrence within the APS instantaneous field of view. Group: Platform_Details Entry_ID: GLORY Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: GLORY End_Group Group: Platform_Associated_Instruments Short_Name: TIM Short_Name: CC GLORY Short_Name: APS GLORY End_Group Group: Orbit Orbit_Altitude: 705 km +/- 30 km Orbit_Inclination: 98.2 Degrees +/- 0.15 Degrees Equator_Crossing: 1:35 p.m. Period: 99 Minutes Repeat_Cycle: 16 Days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-11-09 Online_Resource: http://glory.giss.nasa.gov/ Online_Resource: http://glory.gsfc.nasa.gov/ Sample_Image: http://glory.gsfc.nasa.gov/images/gloryinorbit-s.jpg Group: Platform_Logistics Launch_Date: 2011-03-04 Launch_Site: VANDENBERG AIR FORCE BASE, USA Design_Life: + 3 years; 5 year goal Primary_Sponsor: USA/NASA End_Group End_Group R/V L'ASTRO SENTINEL-3B The Sentinel-3 (S3) mission of ESA and the EC is one of the elements of the GMES (Global Monitoring for Environment and Security) program, which responds to the requirements for operational and near-real-time monitoring of ocean, land and ice surfaces over a period of 20 years. The topography element of this mission will serve primarily the marine operational users but will also allow the monitoring of sea ice and land ice, as well as inland water surfaces, using novel observation techniques.The Sentinel-3 mission is designed as a constellation of two identical polar orbiting satellites, separated by 180º, for the provision of long-term operational marine and land monitoring services. The operational character of this mission implies a high level of availability of the data products and fast delivery time, which have been important design drivers for the mission. https://directory.eoportal.org/web/eoportal/satellite-missions/c-missions/copernicus-sentinel-3 https://www.wmo-sat.info/oscar/satellites/view/401 2019-03-26 21:12:07.0 [sritz] update WeightedRelation (Platform-Instrument); update WeightedRelation (1); 2019-03-26 21:10:10.0 [sritz] insert WeightedRelation (id: null related concept uuid: 7b6e3162-1314-4441-b33a-e2b68ae85bcd relationship type: null relationship value: null generated by: null); 2019-03-26 21:08:54.0 [sritz] update WeightedRelation (Platform-Instrument); update WeightedRelation (1); 2019-03-26 21:06:33.0 [sritz] insert WeightedRelation (id: null related concept uuid: 7204c4d5-b7d0-41af-ba90-61d47c6dc610 relationship type: null relationship value: null generated by: null); 2019-03-26 21:05:22.0 [sritz] update WeightedRelation (Platform-Instrument); update WeightedRelation (1); 2019-03-26 21:03:58.0 [sritz] insert WeightedRelation (id: null related concept uuid: 65ed042c-df53-4afb-8b6a-1ea16958015d relationship type: null relationship value: null generated by: null); 2019-03-26 20:55:50.0 [sritz] update WeightedRelation (Platform-Instrument); update WeightedRelation (1); 2019-03-26 20:53:12.0 [sritz] insert WeightedRelation (id: null related concept uuid: d81fc4e3-c0b4-4205-82b2-ef2161c169a3 relationship type: null relationship value: null generated by: null); 2019-03-26 20:50:11.0 [sritz] update WeightedRelation (Platform-Instrument); update WeightedRelation (1); 2019-03-26 20:48:24.0 [sritz] insert WeightedRelation (id: null related concept uuid: 4b941002-170e-413b-aee4-860155b891e3 relationship type: null relationship value: null generated by: null); 2019-03-26 20:47:12.0 [sritz] update WeightedRelation (Platform-Instrument); update WeightedRelation (1); update WeightedRelation (Platform-Instrument); update WeightedRelation (1); 2019-03-26 20:45:15.0 [sritz] insert WeightedRelation (id: null related concept uuid: 029feed6-79dc-4316-b8ac-be8f1e557f89 relationship type: null relationship value: null generated by: null); 2019-03-26 20:44:20.0 [sritz] insert WeightedRelation (id: null related concept uuid: 9bfd9ff7-b838-4834-bd47-0127384c79f7 relationship type: null relationship value: null generated by: null); 2019-03-26 20:23:19.0 [sritz] update Definition (The Sentinel-3 (S3) mission of ESA and the EC is one of the elements of the GMES (Global Monitoring for Environment and Security) program, which responds to the requirements for operational and near-real-time monitoring of ocean, land and ice surfaces over a period of 20 years. The topography element of this mission will serve primarily the marine operational users but will also allow the monitoring of sea ice and land ice, as well as inland water surfaces, using novel observation techniques.The Sentinel-3 mission is designed as a constellation of two identical polar orbiting satellites, separated by 180º, for the provision of long-term operational marine and land monitoring services. The operational character of this mission implies a high level of availability of the data products and fast delivery time, which have been important design drivers for the mission. https://directory.eoportal.org/web/eoportal/satellite-missions/c-missions/copernicus-sentinel-3 https://www.wmo-sat.info/oscar/satellites/view/401); update Definition (https://directory.eoportal.org/web/eoportal/satellite-missions/c-missions/copernicus-sentinel-3 https://www.wmo-sat.info/oscar/satellites/view/401); 2019-03-26 20:22:38.0 [sritz] insert Definition (id: null text: The Sentinel-3 (S3) mission of ESA and the EC is one of the elements of the GMES (Global Monitoring for Environment and Security) program, which responds to the requirements for operational and near-real-time monitoring of ocean, land and ice surfaces over a period of 20 years. The topography element of this mission will serve primarily the marine operational users but will also allow the monitoring of sea ice and land ice, as well as inland water surfaces, using novel observation techniques.The Sentinel-3 mission is designed as a constellation of two identical polar orbiting satellites, separated by 180º, for the provision of long-term operational marine and land monitoring services. The operational character of this mission implies a high level of availability of the data products and fast delivery time, which have been important design drivers for the mission. https://directory.eoportal.org/web/eoportal/satellite-missions/c-missions/copernicus-sentinel-3 language code: en); 2019-03-26 20:18:45.0 [sritz] Insert Concept add broader relation (SENTINEL-3B [41163801-6aac-43e5-aed7-9f52613a6a73,368597] - SENTINEL-3 [8a19f309-46ee-424b-be9f-e7e57e5b8ca0,345357]); NOT APPLICABLE 2015-09-01 17:47:55.0 [tbs1979] Insert Concept add narrower relation (NOT APPLICABLE [41d72eb0-9554-48a7-8821-dec569503da3,158307] - NOT APPLICABLE [76b8f939-8558-4a10-8139-c7f8a0162102,158343]); 2015-08-19 13:45:13.0 [tbs1979] Insert Concept add broader relation (NOT APPLICABLE [41d72eb0-9554-48a7-8821-dec569503da3,158307] - Platforms [f3261de5-34c1-4980-af22-f9d7e7206d12,144559]); NAVSTAR NCEP-GODAS GODAS depends on continuous real-time data from the Global Ocean Observing System. This project is to deliver routine ocean monitoring products, and is being implemented by CPC in cooperation with NOAA Ocean Climate Observation Program (OCO) Website: http://www.cpc.ncep.noaa.gov/products/GODAS/ 2015-03-05 15:40:21.0 [epneff] insert AltLabel (id: null text: NCEP Global Ocean Data Assimilation System language code: en); insert Definition (id: null text: GODAS depends on continuous real-time data from the Global Ocean Observing System. This project is to deliver routine ocean monitoring products, and is being implemented by CPC in cooperation with NOAA Ocean Climate Observation Program (OCO) Website: http://www.cpc.ncep.noaa.gov/products/GODAS/ language code: en); 2015-03-05 15:37:53.0 [epneff] Insert Concept add broader relation (NCEP-GODAS [4201d98f-7f8a-46bf-b823-47385bbc7fed,106779] - Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,73395]); QUICKBIRD-2 QuickBird, launched in October 2001, was an imaging satellite of DigitalGlobe Inc. of Longmont, CO, USA. The spacecraft was in a sun-synchronous orbit with an operating altitude of 450 km. It completed one revolution every 93.4 minutes and absolved more than 15 revolutions per day. 2019-02-22 17:25:31.0 [mmorahan] insert Definition (id: null text: QuickBird, launched in October 2001, was an imaging satellite of DigitalGlobe Inc. of Longmont, CO, USA. The spacecraft was in a sun-synchronous orbit with an operating altitude of 450 km. It completed one revolution every 93.4 minutes and absolved more than 15 revolutions per day. language code: en); insert WeightedRelation (id: null related concept uuid: 9cd4b512-57e4-4369-9070-8618a92fb8ce relationship type: null relationship value: null generated by: null); 2017-11-02 17:47:46.0 [aaleman] re-added keyword insert AltLabel (id: null category: primary text: DigitalGlobe's QuickBird-2 language code: en); 2017-11-02 17:46:55.0 [aaleman] Insert Concept add broader relation (QUICKBIRD-2 [4240f2ff-8d4a-438d-bbae-f62ae3504922,310281] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,287601]); GPS-36 The Global Position System (GPS), counterpart to the Russian Global Navigation System (GLONASS), is a United States Department of Defense (DoD) developed, worldwide, satellite-based radionavigation system that will be the DoD's primary radionavigation system well into the next century. The constellation consists of 24 operational satellites. The U.S. Air Force Space Command (AFSC) formally declared the GPS satellite constellation as having met the requirement for Full Operational Capability (FOC) as of April 27, 1995. Requirements include 24 operational satellites functioning in their assigned orbits and successful testing completed for operational military functionality. GPS consists of three segments, the SPACE, CONTROL and USER Segment: 1. The SPACE segment consists of 24 operational satellites in six orbital planes, (four satellites in each plane). The satellites operate in circular 20,200 km orbits at an inclination angle of 55 degrees and with a 12-hour period. The position is therefore the same at the same sidereal time each day, i.e. the satellites appear four minutes earlier each day. 2. The CONTROL segment consists of five Monitor Stations, three Ground Antennas, and a Master Control Station (MCS) located at Falcon AFB in Colorado. The monitor stations passively track all satellites in view, accumulating ranging data. This information is processed at the MCS to determine satellite orbits and to update each satellite's navigation message. Updated information is transmitted to each satellite via the Ground Antennas. 3. The USER segment consists of antennas and receiver-processors that provide positioning, velocity and precise timing to the user. GPS provides two levels of service, Standard Positioning Service and the Precise Positioning Service. The Standard Positioning Service (SPS) is a positioning and timing service which will be available to all GPS users on a continuous, worldwide basis with no direct charge. The Precise Positioning Service (PPS) is a highly accurate military positioning, velocity and timing service which will be available on a continuous, worldwide basis to users authorized by the U.S. [Summary provided by NASA.] Group: Platform_Details Entry_ID: GPS-36 Group: Platform_Identification Platform_Category: Navigation Platforms Platform_Series_or_Entity: GPS (Global Positioning System) Short_Name: GPS-36 Long_Name: Global Positioning System Satellites-36 End_Group Group: Platform_Associated_Instruments Short_Name: GPS Short_Name: GPS RECEIVERS End_Group Group: Orbit Orbit_Altitude: 20,200 km Orbit_Inclination: 64.8 degrees Period: 718 minutes Perigee: 20,030 km Orbit_Type: MEO > Semi-Synchronous > Navigation End_Group Creation_Date: 2007-02-12 Online_Resource: http://ilrs.gsfc.nasa.gov/cgi-bin/satellite_missions/select.cgi?order=by_name&sat_code=GP36&sat_name=GPS-36&sat_no=9401601&tab_id=general Sample_Image: http://ilrs.gsfc.nasa.gov/images/gps.gif Group: Platform_Logistics Launch_Date: 1994-04-10 Primary_Sponsor: U.S. Department of Defense End_Group End_Group GEOS-5 The Goddard Earth Observing System Model, Version 5 (GEOS-5) model consists of a group of model components that can be connected in a flexible manner in order to address questions related to different aspects of Earth Science. GEOS-5 model development adheres to the modular architecture of the Earth System Modeling Framework (ESMF). This modular structure simplifies the management of both the model code and the model configurations, to enable progress with forefront applications of coupled processes in the Earth System. GMAO’s work with GEOS-5 spans a large range of space and time scales and encompasses the representation of dynamical, physical, chemical and biological processes. 2018-08-09 17:57:09.0 [sritz] insert Definition (id: null text: The Goddard Earth Observing System Model, Version 5 (GEOS-5) model consists of a group of model components that can be connected in a flexible manner in order to address questions related to different aspects of Earth Science. GEOS-5 model development adheres to the modular architecture of the Earth System Modeling Framework (ESMF). This modular structure simplifies the management of both the model code and the model configurations, to enable progress with forefront applications of coupled processes in the Earth System. GMAO’s work with GEOS-5 spans a large range of space and time scales and encompasses the representation of dynamical, physical, chemical and biological processes. language code: en); 2018-08-09 17:56:21.0 [sritz] insert AltLabel (id: null category: primary text: Goddard EOS Data Assimilation System-5 language code: en); 2018-08-09 17:53:39.0 [sritz] Insert Concept add broader relation (GEOS-5 [42ad1501-744a-439c-a394-258db03d0304,368047] - Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,344529]); ICEYE ICEYE's overall mission is to enable better decision making for everyone by providing timely and reliable Earth observation data. To achieve that goal, the company is developing its own synthetic-aperture radar (SAR) sensor technologies suitable for satellites under 100kg in weight. ICEYE is building a constellation of 18 SAR satellite by end of 2020 and that will enable a 3 hour on average revisit rate around the globe. 2019-04-26 16:06:39.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: 285c90fb-0b3f-487f-a094-40d6dea7948e relationship type: null relationship value: null generated by: null); 2019-04-26 16:02:09.0 [mmorahan] insert Definition (id: null text: ICEYE's overall mission is to enable better decision making for everyone by providing timely and reliable Earth observation data. To achieve that goal, the company is developing its own synthetic-aperture radar (SAR) sensor technologies suitable for satellites under 100kg in weight. ICEYE is building a constellation of 18 SAR satellite by end of 2020 and that will enable a 3 hour on average revisit rate around the globe. language code: en); 2019-04-26 15:57:42.0 [mmorahan] Insert Concept add broader relation (ICEYE [42c6ff80-849b-4ef5-b6ff-fd9416b8cf33,368717] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761]); GEOMET The USGS Desert Winds Geologic/Meteorological Ground Stations (GEOMET) provide a long-term data base for understanding the range of environmental conditions that can be expected to occur normally in arid and semiarid areas of the desert southwest, baseline data to assess changes in the desert such as changes in vegetation, migration of sand, and increased dust storms that may occur due to climate change in desert regions, and data for field-checking remotely sensed image data of various surfaces so that regional models can be developed for monitoring the land surface changes over time. More info at "http://geochange.er.usgs.gov/sw/impacts/biology/geomet/" [Source: USGS] Group: Platform_Details Entry_ID: GEOMET Group: Platform_Identification Platform_Category: In Situ Land-based Platforms Platform_Series_or_Entity: GEOPHYSICAL STATIONS/NETWORKS Short_Name: GEOMET Long_Name: USGS Desert Winds Geological/Meteorological Ground Station End_Group Group: Synonymous_Platform_Names Short_Name: GEOMET End_Group Group: Platform_Associated_Instruments Short_Name: WL/CR End_Group Creation_Date: 2007-12-05 Online_Resource: http://geochange.er.usgs.gov/sw/impacts/biology/geomet/ Sample_Image: http://geochange.er.usgs.gov/sw/impacts/biology/geomet/precip3.gif End_Group STS-51F - Spacecraft Brief Description - Spacelab 2, a NASA developed payload, had a configuration that included an igloo attached to a lead pallet, with the Instrument Pointing Subsystem (IPS) mounted on it, a two pallet train, and an experiment special support structure. The flight objective was to demonstrate Spacelab's capabilities through a multidisciplinary research program and to verify system performance. Investigations in the field of astrophysics and solar astronomy included a sky survey for extended infrared sources, x-ray imaging of cluster galaxies, cosmic ray measurements, studies of small-scale structures on the sun's surface, and a measurement of the coronal helium abundance. In addition, there were measurements of: the solar ultraviolet flux; the plasma environment and plasma processes near the Orbiter; and zero-gravity effects on technology processes and on the behavior of liquid helium. Life sciences problems investigated included bone demineralization in humans and lignin formation in plants. - Auxiliary Information - Launch Date and Time : 1985-07-29 21:00:00 Epoch Date and Time : Apogee (km or AU): 321. Perigee (km or AU): 312. Inclination (degree) : 49.5 Orbit Type : Geocentric Information last updated on 1992-06-19 NOAA-13 NOAA-13 (National Oceanic & Atmospheric Administration) Weather Satellite: Objective: To continue the Advanced TIROS-N program by working as a companion with NOAA-10, 11 and 12 in order to provide continuous coverage of the Earth and to provide high-resolution global meteorological data. Description: The spacecraft was launched on August 9, 1993 at Vandenberg Air Force Base, California on board the Atlas E. The spacecraft was rectangularly shaped (166" long by 74" high) and powered by a 191" by 94" solar array. The satellite was Earth oriented, three-axis stabilized and weighed approximately 2200 pounds. NOAA-13 was the sixth operational satellite in the Advanced TIROS-N series. The satellite carried the AVHRR, TOVS, and the solar proton monitor. All of which were present on previous NOAA satellites. The ERBE instruments, the SBUV radiometer and the SARSAT systems were also flown on this satellite. NOAA-13 was placed in a near circular, (470nm) polar orbit. The spacecraft and its systems operated successfully for 12 days until a circuit failure resulted in a power loss aboard the craft. At this time the spacecraft is still in its polar orbit; however, no data is being received. Specifications: Prime contractor: GE Astro Platform: evolved from NOAA 2nd generation Mass at launch: 1420 kg Mass in orbit: ~1050 kg Dimension: 4.18 m long x 1.88 m diameter Stabilization: 3-axis Design lifetime: 3 years APT downlink freq: 137.620 MHz (standby) HRPT downlink freq: 1698.0 MHz Beacon: 136.770 MHz Payload: AVHRR (Advanced Very High Resolution Radiometer: Wavebands: 0.58-0.68 µm (visible): cloud, snow and ice monitoring 0.725-1.10 µm (near IR): water, vegetation and agriculture surveys 3.55-3.93 µm (near IR): sea surface temperature, volcano, forest fire activity 10.3-11.3 µm (thermal IR): sea surface temperature, soil moisture 11.3-12.5 µm (thermal IR): sea surface temperature, soil moisture Resolution: 1.1 km Swath width: 3000 km TOVS (Tiros Operational Vertical Sounder): HIRS/2 (High Resolution IR Sounder): 20 channels in the 0.69 - 14 - 95 µm band; 17.4 km resolution SSU (Stratospheric Sounding Unit): step-scanned far IR spectrometer with 3 channels in the CO² absorption band (15 µm);147.3 km resolution MSU (Microwave Sounding Unit): passive 4-channel radiometer operating around 55 GHz; 109 km resolution PARTICIPANTS: NASA, USAF, ITT, Martin Marietta AstroSpace, Ball Aerospace, Marconi, JPL, Loral, NOAA, National Weather Service. [Summary provided by NOAA and The Satellite Encyclopedia] Group: Platform_Details Entry_ID: NOAA-13 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NOAA POES (Polar Orbiting Environmental Satellites) Short_Name: NOAA-13 Long_Name: National Oceanic & Atmospheric Administration-13 End_Group Group: Synonymous_Platform_Names Short_Name: ATLES E End_Group Group: Platform_Associated_Instruments Short_Name: TOVS Short_Name: HIRS/2 Short_Name: MSU Short_Name: SSU End_Group Group: Orbit Period: 12 days End_Group Creation_Date: 2007-11-05 Online_Resource: http://www2.ncdc.noaa.gov/docs/podug/html/c1/sec1-49.htm Sample_Image: http://www2.ncdc.noaa.gov/docs/podug/images/guide/f149-3.gif Group: Platform_Logistics Launch_Date: 1993-08-09 Launch_Site: Vandenberg Air Force Base, USA Design_Life: 3-years Primary_Sponsor: NASA End_Group End_Group CLUSTER-II The aim of the Cluster mission is to study small-scale structures of the magnetosphere and its environment in three dimensions. To achieve this, Cluster is constituted of four identical spacecraft that will flight in a tetrahedral configuration. The separation distances between the spacecraft will be varied between 600 km and 20 000 km, according to the key scientific regions. The first Cluster mission was launched on 4 June 1996, but the launch vehicle exploded 37 seconds into the flight. Cluster II was launched from Baikonur Cosmodrome in Kazakhstan on 16 July 2000 and 9 August 2000. The four satellites were put into orbit, in pairs, by two Soyuz rockets provided by the Russian-French Starsem company. Starsem has four shareholders - Aerospatiale, Arianespace, the Russian Space Agency and TsSKB Samara, the manufacturer of the Soyuz vehicle. Each of the four spacecraft carries an identical set of 11 instruments to investigate charged particles, electrical and magnetic fields. These were built by European and American instrument teams led by Principal Investigators. FGM-Fluxgate Magnetometer EDI -Electron Drift Instrument ASPOC-Active Spacecraft Potential Control experiment STAFF -Spatio-Temporal Analysis of Field Fluctuation experiment EFW-Electric Field and Wave experiment DWP-Digital Wave Processing experiment WHISPER-Waves of High frequency and Sounder for Probing of Electron density by Relaxation experiment WBD-Wide Band Data instrument PEACE-Plasma Electron And Current Experiment CIS-Cluster Ion Spectrometry experiment RAPID-Research with Adaptive Particle Imaging Detectors See: http://clusterlaunch.esa.int/science-e/www/area/index.cfm?fareaid=8 Group: Platform_Details Entry_ID: CLUSTER-II Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Short_Name: CLUSTER-II Long_Name: CLUSTER-II End_Group Group: Synonymous_Platform_Names Short_Name: Cluster-2 Short_Name: FM6 Short_Name: FM5 Short_Name: FM7 Short_Name: FM8 Short_Name: Salsa Short_Name: 26411 Short_Name: 26463 Short_Name: 26410 Short_Name: 26464 Short_Name: Samba Short_Name: Rumba Short_Name: Tango Short_Name: 2000-045B Short_Name: 2000-041A Short_Name: 2000-041B Short_Name: 2000-045A End_Group Group: Platform_Associated_Instruments Short_Name: EFW Short_Name: FGM Short_Name: EDI Short_Name: ASPOC Short_Name: STAFF Short_Name: DWP Short_Name: WHISPER Short_Name: WBD Short_Name: PEACE Short_Name: CIS Short_Name: RAPID End_Group Group: Orbit Orbit_Inclination: 90.7 degrees Period: 620 m Perigee: 19,000 km Apogee: 119,000 km Orbit_Type: HEO > Highly Elliptical Orbit End_Group Online_Resource: http://sci.esa.int/science-e/www/area/index.cfm?fareaid=8 Sample_Image: http://sci.esa.int/science-e-media/img/2e/hires_36654.JPG Group: Platform_Logistics Launch_Date: 2000-07-16 Launch_Site: Baikonur Cosmodrome, Tyuratam, Russia Design_Life: 9 years Primary_Sponsor: ESA Primary_Sponsor: NASA End_Group End_Group TRACE The Transition Region and Coronal Explorer (TRACE) is a NASA Small Explorer (SMEX) mission to image the solar corona and transition region at high angular and temporal resolution. TRACE was launched on a Pegasus launch vehicle from Vandenberg Air Force Base in April 1998. The launch was scheduled to allow joint observations with SOHO during the rising phase of the solar cycle to sunspot maximum. No transition region or coronal imager has witnessed the onset and rise of a solar cycle. For more information, see: http://trace.lmsal.com/ Group: Platform_Details Entry_ID: TRACE Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Platform_Series_or_Entity: NASA Small Explorer (SMEX) Short_Name: TRACE Long_Name: Transition Region and Coronal Explorer End_Group Group: Synonymous_Platform_Names Short_Name: Explorer 73 Short_Name: SMEX/TRACE Short_Name: Small Explorer/TRACE Short_Name: 25280 Short_Name: 1998-020A End_Group Group: Platform_Associated_Instruments Short_Name: TRACE IMAGING TELESCOPE End_Group Group: Orbit Orbit_Altitude: 700 km Orbit_Inclination: 97.84 degrees Period: 95.48 m Perigee: 520.0 km Apogee: 547.2 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2008-01-17 Online_Resource: http://trace.lmsal.com/ Online_Resource: http://explorers.gsfc.nasa.gov/ Sample_Image: http://nssdc.gsfc.nasa.gov/image/spacecraft/trace.jpg Group: Platform_Logistics Launch_Date: 1998-04-02 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: USA/NASA Primary_Sponsor: Lockheed Martin Solar and Astrophysics Labs End_Group End_Group RAPIDEYE RapidEye is a commercial multispectral remote sensing satellite mission being designed and implemented by MDA for RapidEye AG. The RapidEye sensor images five optical bands in the 400-850nm range and provides 6.5m pixel size at nadir. Rapid delivery and short revisit times are provided through the use of a five-satellite constellation. It provides products for the following applications: -Agriculture - crop monitoring and mapping, yield prediction, etc. -Forestry - tree species separation, stem volume estimation, etc. -Security & Emergency - disaster management etc. -Energy & Infrastructure - pipeline monitoring, landcover classification etc. -Environment - change detection etc. -Cartography - satellite based maps, ortho photos, etc. -Other Markets - natural disaster assessment, 3D-visualization, etc. The satellites will be placed equally spaced in a single sun-synchronous orbit to ensure consistent imaging conditions and a short revisit time. The RapidEye system can access any area on Earth within a day and cover the entire agricultural areas of North America and Europe within five days. The RapidEye satellite platforms has been constructed by Surrey Satellite Technology Ltd (SSTL). [1] This makes RapidEye the second multiple-satellite imaging constellation that SSTL has been involved with, after building and launching the Disaster Monitoring Constellation. Group: Platform_Details Entry_ID: RAPIDEYE Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: RAPIDEYE Long_Name: RapidEye End_Group Group: Orbit Orbit_Altitude: 630 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2008-08-11 Online_Resource: http://www.rapideye.de/ Online_Resource: http://www.rapideye.de/upload/documents/Standard_Image_Product_USLetter.pdf Sample_Image: http://www.dappolonia-research.com/invesatwiki/images/thumb/180px-Rapid_Eye.jpg Group: Platform_Logistics Launch_Site: Baikonur Cosmodrome, Tyuratam, Russia Primary_Sponsor: Germany End_Group End_Group PAGEOS 1 Spacecraft Brief Description The PAGEOS (Passive Geodetic Earth Orbiting Satellite) spacecraft was a 30.48-m inflatable sphere, and had no instrumentation on board. It was the second (following GEOS 1) NASA satellite in the National Geodetic Satellites Program. PAGEOS 1 was made up of 84 gores and 2 pole caps of 0.0127-mm aluminized mylar film. The gores were 48 m long with maximum width of 1.24 m and the pole caps were 1.02 m in diameter. The primary purpose of the satellite was to provide a tracking target for geodetic purposes. It had a specular reflectance of 0.862, and a diffuse reflectance of 0.029, providing a reflecting light source whose brightness was relatively independent of observer-satellite-sun phase angle. The surface was also 97% reflectant for microwave energy in the range from 17 to 4E5 kHz. The launch, orbit, separation, inflation and initial operation were nominal, with more than 40 ground stations participating in the observation program. The orbit was generally considered too high for drag-density study, although some work was done in this area by the Smithsonian Astrophysical Observatory. For a more detailed description, see David E. Bowker, 'PAGEOS Project Compilation of Information for Use of Experimenter' (TRF B01718), NASA-TM-X-1344, 1967. Auxiliary Information Launch Date and Time : 1966-06-24 00:14:00 Epoch Date and Time : 1966-06-24 Orbit Type : Geocentric Apogee(km) : 4271. Perigee(km) : 4207. Inclination : 87.14 Date of last update : 1985-07-17 Group: Platform_Details Entry_ID: PAGEOS 1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: PAGEOS 1 Long_Name: Passive Geodetic Earth Orbiting Satellite 1 End_Group Group: Synonymous_Platform_Names Short_Name: PAGEOS 1 End_Group Group: Orbit Orbit_Inclination: 85.40 deg Period: 177.10 min Perigee: 3,913 km Apogee: 4,220 km End_Group Creation_Date: 2007-11-21 Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/masterCatalog.do?sc=1966-056A Sample_Image: http://celebrating200years.noaa.gov/foundations/satellite_geodesy/pageos_500.jpg Group: Platform_Logistics Launch_Date: 1966-06-24 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: NASA End_Group End_Group SOHO The SOHO (Solar & Heliospheric Observatory) project is being carried out by the European Space Agency (ESA) and the US National Aeronautics and Space Administration (NASA) as a cooperative effort between the two agencies in the framework of the Solar Terrestrial Science Program (STSP) comprising SOHO and CLUSTER, and the International Solar-Terrestrial Physics Program (ISTP), with Geotail (ISAS-Japan), Wind, and Polar. SOHO was launched on December 2, 1995. The SOHO spacecraft was built in Europe by an industry team led by Matra, and instruments were provided by European and American scientists. There are nine European Principal Investigators (PI's) and three American ones. Large engineering teams and more than 200 co-investigators from many institutions supported the PI's in the development of the instruments and in the preparation of their operations and data analysis. NASA was responsible for the launch and is now responsible for mission operations. Large radio dishes around the world which form NASA's Deep Space Network are used to track the spacecraft beyond the Earth's orbit. Mission control is based at Goddard Space Flight Center in Maryland. Additional information available at "http://sohowww.nascom.nasa.gov/" [Summary provided by NASA] Group: Platform_Details Entry_ID: SOHO Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Short_Name: SOHO Long_Name: Solar and Heliospheric Observatory End_Group Group: Synonymous_Platform_Names Short_Name: Solar and Heliospheric Observatory Short_Name: 23726 Short_Name: 1995-065A End_Group Group: Platform_Associated_Instruments Short_Name: VIRGO Short_Name: UVCS Short_Name: SWAN Short_Name: SUMER Short_Name: MDI Short_Name: LASCO Short_Name: GOLF Short_Name: ERNE Short_Name: EIT Short_Name: COSTEP Short_Name: CELIAS Short_Name: CDS End_Group Group: Orbit Apogee: 1.5 million km Orbit_Type: LPO > L1 > Lissajous Orbit > Halo Orbit End_Group Creation_Date: 2008-01-17 Online_Resource: http://sohowww.nascom.nasa.gov/ Online_Resource: http://www.nasa.gov/mission_pages/soho/index.html Online_Resource: http://sci.esa.int/science-e/www/area/index.cfm?fareaid=14 Sample_Image: http://sohowww.nascom.nasa.gov/gallery/Posters/images/large/soho-poster.gif Group: Platform_Logistics Launch_Date: 1995-12-02 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: NASA Primary_Sponsor: ESA End_Group End_Group GEMINI EQUATOR-S EQUATOR-S is a low-cost mission designed to study the Earth's equatorial magnetosphere out to distances of 67000 km and it forms an element of the closely-coordinated fleet of satellites that comprise the IASTP program (http://www-istp.gsfc.nasa.gov/istp/sci_operations/www-sites.html) . It is based on a simple spacecraft design and carries a science payload consisting of advanced instruments that were developed for other IASTP missions. Unique features of EQUATOR-S are its nearly equatorial orbit and its high spin rate. It was launched as an auxiliary payload on an Ariane-4 on December 2nd, 1997. The mission is intended for a two-year lifetime. The idea of an equatorial satellite dates back to NASA's GGS (Global Geospace Science) program originally conceived in 1980. When the equatorial element of the program was abandoned in 1986 and several subsequent attempts to rescue the mission had failed, the Max-Planck-Institut f?r extraterrestrische Physik (MPE) decided in 1991 to fill this gap in the GGS (and in the international IASTP) program because of its interest in the global magnetospheric science, and because it provided an opportunity for a test of an advanced instrument, EDI, to measure electric fields with dual electron beams. The realization of EQUATOR-S was possible through a grant from the German Space Agency DARA (meanwhile part of DLR), that was approved in late 1994, but also through MPE-internal funds and personnel. For more information, see: http://www.mpe-garching.mpg.de/EQS/eq-s-spacecraft.html Group: Platform_Details Entry_ID: EQUATOR-S Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Short_Name: EQUATOR-S End_Group Group: Synonymous_Platform_Names Short_Name: EQUATOR-S End_Group Group: Platform_Associated_Instruments Short_Name: MAGNETOMETERS End_Group Creation_Date: 2008-01-14 Online_Resource: http://www.mpe-garching.mpg.de/EQS/ Sample_Image: http://www.mpe-garching.mpg.de/EQS/PIFICONS/eqs-spacecraft.gif End_Group GONG NETWORK The Global Oscillation Network Group (GONG) is a community-based project to conduct a detailed study of solar internal structure and dynamics using helioseismology. In order to exploit this new technique, GONG has developed a six-station network of extremely sensitive, and stable velocity imagers located around the Earth to obtain nearly continuous observations of the SUN's "five-minute" oscillations, or pulsations. The site comprising the GONG Network are: Big Bear, California Cerro Tololo, Chile Learmonth, Australia Mauna Loa, Hawaii Udaipur, India Observatorio del Teide, Canary Islands The five-minute oscillation is a subtle effect. Individual modes may exhibit velocities of less than 0.2 meters/second, while the sum of all of the modes is only a few hundred meters/second. The ultimate intention is to have the measurements be limited by the Sun's ``random'' surface motions. This means developing six stable instruments capable of making imaged velocity measurements with a precision of significantly less than one meter/second - one part in ten million! A low technological risk instrument based on a Michelson interferometer was selected, and it will be supported by a highly automated, portable installation, somewhat reminiscent of a spacecraft experiment. Each station in the network will produce more than 200 megabytes of data every day. Over the three year observing run, the raw data will exceed one terabyte, and the various processed data sets will exceed this several-fold. To keep up with the data flow, a pipe-line capable of roughly 6 Megaflops has be established to do the bulk processing and provide subsets of the data for the scientific community. Because of the widespread scientific participation, distributed data, software and analysis tools will be provided. Thus, in addition to a central facility, participating scientists will have access to readily transportable data archives and software, as well as shared analysis programs at their home institutions. Group: Platform_Details Entry_ID: GONG NETWORK Group: Platform_Identification Platform_Category: In Situ Land-based Platforms Platform_Series_or_Entity: SOLAR/SPACE MONITORING STATIONS Short_Name: GONG NETWORK Long_Name: Global Oscillation Network Group End_Group Group: Synonymous_Platform_Names Short_Name: GONG End_Group Group: Platform_Associated_Instruments Short_Name: INTERFEROMETERS End_Group Creation_Date: 2007-12-10 Online_Resource: http://gong.nso.edu/info/ Sample_Image: http://gong.nso.edu/instrument/outside_shelter.jpg End_Group ACE (DECADAL SURVEY) [Source: NASA ACE Mission, https://acemission.gsfc.nasa.gov/ ] ACE will assist in answering fundamental science questions associated with aerosols, clouds, and ocean ecosystems, by making improved and more comprehensive measurements through the use of innovative and advanced remote sensing technologies. Aerosols measured by ACE include those of both man-made and natural origins, the latter of which is contributed significantly by ocean ecosystems. Group: Platform_Details Entry_ID: ACE (DECADAL SURVEY) Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NASA Decadal Survey Short_Name: ACE (DECADAL SURVEY) Long_Name: Aerosol - Cloud - Ecosystems End_Group Group: Orbit Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2010-05-04 Online_Resource: https://acemission.gsfc.nasa.gov/ Group: Platform_Logistics Primary_Sponsor: USA/NASA End_Group End_Group 2020-01-03 22:16:38.0 [sritz] update Definition ([Source: NASA ACE Mission, https://acemission.gsfc.nasa.gov/ ] ACE will assist in answering fundamental science questions associated with aerosols, clouds, and ocean ecosystems, by making improved and more comprehensive measurements through the use of innovative and advanced remote sensing technologies. Aerosols measured by ACE include those of both man-made and natural origins, the latter of which is contributed significantly by ocean ecosystems. Group: Platform_Details Entry_ID: ACE (DECADAL SURVEY) Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NASA Decadal Survey Short_Name: ACE (DECADAL SURVEY) Long_Name: Aerosol - Cloud - Ecosystems End_Group Group: Orbit Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2010-05-04 Online_Resource: https://acemission.gsfc.nasa.gov/ Group: Platform_Logistics Primary_Sponsor: USA/NASA End_Group End_Group); 2020-01-03 22:14:33.0 [sritz] update Definition (https://acemission.gsfc.nasa.gov/); 2020-01-03 22:14:03.0 [sritz] update Definition ([Source: NASA Earth Science Decadal Survey Studies home page, https://acemission.gsfc.nasa.gov/ ] Mission objectives: * Cloud and aerosol height * Organic material in surface ocean layers * Aerosol and cloud types and properties * Improved climate models * Prediction of local climate change * Measure ocean productivity and health * Air-quality models and forecasts ACE is a tier 2 Decadal Survey mission focusing on clouds and aerosols as well as ocean ecosystem. ACE will help to answer emerging fundamental science questions associated with aerosols, clouds, air quality and global ocean ecosystems. [Source: https://acemission.gsfc.nasa.gov/ ] The ACE instrument requirements are under study. Please refer to the ACE home page for updated requirements: http://dsm.gsfc.nasa.gov/ace/payload.html . Group: Platform_Details Entry_ID: ACE (DECADAL SURVEY) Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NASA Decadal Survey Short_Name: ACE (DECADAL SURVEY) Long_Name: Aerosol - Cloud - Ecosystems End_Group Group: Orbit Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2010-05-04 Online_Resource: https://acemission.gsfc.nasa.gov/ Group: Platform_Logistics Primary_Sponsor: USA/NASA End_Group End_Group); MIPS The MIPS2 is a mobile profiling system with several components and capabilities. 1. Radian: (915 MHz 5-beam Doppler profiling radar) collects Doppler spectra, calculates the spectrum moments, determines wind profiles at 1-60 min intervals, acquires, vertically-pointing data at 40-60 times resolution and 60, 105, or 210 m vertical resolution. 2. Radian: (2 kHz Doppler sodar) determines wind profiles w and backscatter power at 20 s time resolution and 25 m vertical resolution. 3. Radio Acoustic Sounding System (RASS): using the sodar as the acoustic source, the profile of T can be determined fro ~120 m to 0.5-1.5 km AGL, dependent on water vapor content, wind speed and turbulence. 4. Vailalla: (0.906 um lidar ceilometer) determines cloud base and provides a good estimate of the lidar backscatter (or extinction coefficient) from aerosols, clouds, and precipitation. 5. Radiometrics: (12 channel microwave radiometer) measures profiles of T, water vapor, cloud water, and column integrated values of water vapor and cloud water, at 10 min intervals up to 10 km, with highest vertical resolution oat low levels. This system also includes an infrared pyranometer, which measures cloud base temperature. 6. Zenith cloud imaging system: This will consist of an upward directed computer controlled, digital camera system that will provide visible images of the sky at user-selected levels. 7. Surface Instrumentation: T, relative humidity, wind, pressure, solar radiation, and rainfall rate, all at 1-s resolution, An improved aspiration system designed for rainy high wind conditions has been designed for accurate measurements of T and RH. More info at "http://www.atd.ucar.edu/dir_off/projects/2002/IHOPinst/mips_desc.pdf" [Source: MIPS report] Group: Platform_Details Entry_ID: MIPS Group: Platform_Identification Platform_Category: In Situ Land-based Platforms Platform_Series_or_Entity: WEATHER STATIONS/NETWORKS Short_Name: MIPS Long_Name: Mobile Integrated Profiling System End_Group Group: Synonymous_Platform_Names Short_Name: MIPS End_Group Creation_Date: 2007-12-12 Online_Resource: http://www.atd.ucar.edu/dir_off/projects/2002/IHOPinst/mips_desc.pdf Sample_Image: http://www.ucar.edu/communications/newsreleases/2003/mipspayload.small.jpg End_Group NASA P-3 The P-3B is a specialized aircraft operated as an airborne “platform” in support of NASA’s Science Mission Directorate. The aircraft supports scientific investigations by NASA and visiting scientists from universities, other agencies and organizations worldwide. With instruments installed, the aircraft serves an economical test bed for studying the Earth and for new concepts in satellite design. The aircraft supports scientific studies across all disciplines of Earth Science such as forest ecology, atmospherics, ocean and ice dynamics, land processes and many more. The P-3 aircraft can carry instrument payloads consisting of one to several at once while supporting Earth studies all over the globe. Scientific instrument installations on the aircraft generally consist of external components such as a sensors, antennas or probes while inside the aircraft the supporting control and data analysis computers are installed in specially designed rack modules. Multiple instrument payloads are an economical way for cooperating scientists to intercompare data when studying Earth processes. A diverse mix of engineers, technicians, scientists, pilots and managers all team together to safely complete the aircraft-instrument integration designs and hardware fabrications and conduct the flight portions of studies. Once designed, all components can be quickly and economically Group: Platform_Details Entry_ID: NASA P-3 Group: Platform_Identification Platform_Category: Aircraft Short_Name: NASA P-3 End_Group Creation_Date: 2012-07-18 Online_Resource: https://www.nasa.gov/pdf/219397main_P-3B_fact_sheet.pdf End_Group 2020-03-26 22:07:15.0 [sritz] update WeightedRelation (Undefined); 2020-03-26 22:05:15.0 [sritz] update WeightedRelation (Similar); 2020-03-26 21:48:16.0 [sritz] update WeightedRelation (Platform-Instrument); update WeightedRelation (1.0); 2020-03-26 21:47:40.0 [sritz] insert WeightedRelation (id: null related concept uuid: 5e573a56-b485-4a7f-a652-6d941e7d0ce0 relationship type: null relationship value: null generated by: null); 2019-06-26 19:56:42.0 [sritz] update Definition (The P-3B is a specialized aircraft operated as an airborne “platform” in support of NASA’s Science Mission Directorate. The aircraft supports scientific investigations by NASA and visiting scientists from universities, other agencies and organizations worldwide. With instruments installed, the aircraft serves an economical test bed for studying the Earth and for new concepts in satellite design. The aircraft supports scientific studies across all disciplines of Earth Science such as forest ecology, atmospherics, ocean and ice dynamics, land processes and many more. The P-3 aircraft can carry instrument payloads consisting of one to several at once while supporting Earth studies all over the globe. Scientific instrument installations on the aircraft generally consist of external components such as a sensors, antennas or probes while inside the aircraft the supporting control and data analysis computers are installed in specially designed rack modules. Multiple instrument payloads are an economical way for cooperating scientists to intercompare data when studying Earth processes. A diverse mix of engineers, technicians, scientists, pilots and managers all team together to safely complete the aircraft-instrument integration designs and hardware fabrications and conduct the flight portions of studies. Once designed, all components can be quickly and economically Group: Platform_Details Entry_ID: NASA P-3 Group: Platform_Identification Platform_Category: Aircraft Short_Name: NASA P-3 End_Group Creation_Date: 2012-07-18 Online_Resource: https://www.nasa.gov/pdf/219397main_P-3B_fact_sheet.pdf End_Group); POM 2014-01-30 14:54:31.0 [tbs1979] insert AltLabel (id: null text: Princeton Ocean Model language code: en); 2014-01-30 14:53:53.0 [tbs1979] Insert Concept add broader relation (POM [45d0ab0d-19d4-4fc4-8f69-9f6b4529a430,106109] - Models [113ecbc2-ab36-4d58-a96c-a6ce0106e749,73395]); STS-39 Space Transport System STS-39 Mission Objectives: Mission STS-39 is the first unclassified Department of Defense- dedicated Space Shuttle mission, highlighted by around-the-clock observations of the atmosphere, gas releases, Shuttle engine firings, subsatellite gas releases and the Shuttle's orbital environment in wavelengths ranging from infrared to the far ultraviolet. Additional information available at "http://science.ksc.nasa.gov/shuttle/missions/sts-39/mission-sts-39.html [Summary provided by NASA] NPOESS (National Polar-orbiting Operational Environmental Satellite System ) ALTUS The ALTUS II, the first of the two craft to be completed, made its first flight on May 1, 1996. With its engine at first augmented by a single-stage turbocharger, the ALTUS II reached an altitude of 37,000 ft during its first series of development flights at Dryden in August, 1996. In October of that year, the ALTUS II was flown in an Atmospheric Radiation Measurement (ARM-UAV) study in Oklahoma conducted by Sandia National Laboratories for the Department of Energy (DOE). During the course of those flights, the ALTUS II set a single-flight endurance record for remotely operated aircraft of more than 26 hours. The ALTUS I, completed in 1997, flew a series of development flights at Dryden that summer. Those test flights saw the craft reach an altitude of 43,500 ft while carrying a simulated 300-lb payload, a record for a remotely operated aircraft powered by a piston engine augmented with a single-stage turbocharger. After major modifications and upgrades, including installation of a two-stage turbocharger in place of its original single-stage unit, a larger fuel tank and additional intercooling capacity, the ALTUS II returned to flight status in the summer of 1998. The goal of its development test flights was to reach one of the major Level 2 performance milestones within NASA's ERAST program: to fly a gasoline-fueled, piston-engine remotely piloted aircraft for several hours at an altitude at or near 60,000 feet. On March 5, 1999, The ALTUS II maintained flight at or above 55,000 feet for three hours, reaching a maximum density altitude of 57,300 feet during the mission. Later that spring, the ALTUS II flew another series of Atmospheric Radiation Measurement missions conducted by Sandia National Laboratories for the DOE. Hard-to-measure properties of high-level cirrus clouds that may affect global warming were recorded using specially designed instruments while the Altus flew at 50,000 feet altitude off the Hawaiian island of Kaua'i. Clouds both reflect incoming solar energy back to space, and absorb warm longwave radiation from the Earth's surface, keeping that heat in the atmosphere. Data from the study will help scientists better understand how these dual roles of clouds in reflecting and absorbing solar energy work, and build more accurate global climate models. In September, 2001, ALTUS II served as the UAV platform for a flight demonstration of remote sensoring and imaging capabilities that could detect hot spots in wildfires and relay that data in near- real time via the Internet to firefighting commanders below. The demonstration, led by NASA Ames Research Center, was flown over GA-ASI's El Mirage development facility in Southern California. In the summer of 2002, The Altus II served as the airborne platform for the Altus Cumulus Electrification Study (ACES), led by Dr. Richard Blakeslee of NASA Marshall Space Flight Center. The ACES experiment focused on the collection of electrical, magnetic and optical measurements of thunderstorms. Data collected will help scientists understand the development and life cycles of thunderstorms, which in turn may allow meteorologists to more accurately predict when destructive storms may hit. For more information on the ACES study, visit the National Space Science and Technology Center web site at the NASA Marshall Space Flight Center: http://aces.msfc.nasa.gov. information provided by http://www.nasa.gov/centers/dryden/news/FactSheets/FS-058-DFRC.html Group: Platform_Details Entry_ID: ALTUS Group: Platform_Identification Platform_Category: Aircraft Short_Name: ALTUS End_Group Group: Synonymous_Platform_Names Short_Name: ALTUS End_Group Creation_Date: 2007-08-13 Online_Resource: http://www.nasa.gov/centers/dryden/news/FactSheets/FS-058-DFRC.html Sample_Image: http://www.nasa.gov/centers/dryden/images/content/106304main_altus.jpg Group: Platform_Logistics Launch_Date: 1996-05-01 Primary_Sponsor: NASA End_Group End_Group Global Explorer It’s critically important for the research on this expedition that we collect live animals in excellent condition, and Deep Sea Systems Global Explorer remotely operated vehicle (ROV) will allow us to do so. Remotely operated means that the vehicle is tethered to the ship with a long fiber-optic cable, and operations are controlled by skilled pilots on shipboard while the ROV is deep in the ocean. About the size of a mini-van, the Global Explorer has a seven-function manipulator arm, which can be used to gently collect organisms and place them in a BioBox. 2020-01-21 17:53:22.0 [tstevens] insert Definition (id: null text: It’s critically important for the research on this expedition that we collect live animals in excellent condition, and Deep Sea Systems Global Explorer remotely operated vehicle (ROV) will allow us to do so. Remotely operated means that the vehicle is tethered to the ship with a long fiber-optic cable, and operations are controlled by skilled pilots on shipboard while the ROV is deep in the ocean. About the size of a mini-van, the Global Explorer has a seven-function manipulator arm, which can be used to gently collect organisms and place them in a BioBox. language code: en); 2020-01-21 17:23:04.0 [tstevens] Insert Concept add broader relation (Global Explorer [464643c0-4600-4d38-9927-9587fa8904bb,559715] - ROV [da6420b6-48ec-4ae2-98c7-0ef0538815a0,542741]); PMS Permafrost Monitoring Stations measure the underlying state of permafrost. These fully automated stations continuously monitor: -Air temperature -Snow Depth -Solar radiation -Shallow permafrost temperature (at several depths) [Source: USGS] Group: Platform_Details Entry_ID: PMS Group: Platform_Identification Platform_Category: In Situ Land-based Platforms Platform_Series_or_Entity: HYDROLOGICAL STATIONS Short_Name: PMS Long_Name: Permafrost Monitoring Stations End_Group Group: Synonymous_Platform_Names Short_Name: PMS End_Group Creation_Date: 2007-12-07 End_Group GEOS-Chem 2016-10-27 20:52:36.0 [saritz] update AltLabel (Global 3-D chemical transport model (CTM) for atmospheric composition driven by meteorological input from the Goddard > Earth Observing System (GEOS) of the NASA Global Modeling and Assimilation Office); 2016-10-27 20:52:04.0 [saritz] insert AltLabel (id: null text: Global 3-D chemical transport model (CTM) for atmospheric > composition driven by meteorological input from the Goddard > Earth Observing System (GEOS) of the NASA Global Modeling > and Assimilation Office language code: en); 2016-10-27 20:51:31.0 [saritz] Insert Concept add broader relation (GEOS-Chem [4773815f-2a76-425e-86cc-0bfd4c3b75c2,278467] - Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,256331]); GEOEYE-1 GeoEye-1, formerly known as OrbView-5, is the next-generation high-resolution imaging mission of GeoEye, Dulles, VA, USA. In January 2006, the commercial imaging company GeoEye was formed, made up of former Orbimage of Dulles VA, and of former Space Imaging of Thornton, CO (Orbimage acquired Space Imaging in 2005 and gave the merged company the new name of GeoEye). The newly formed GeoEye company is the world's largest commercial satellite imagery provider. On Sept. 30, 2004, OrbImage was awarded a NextView vendor contract of NGA (National Geospatial-Intelligence Agency). The contract, referred to as NextView OrbImage, provides long-term revenue commitments as well as capital for the development of OrbView-5. NGA's NextView program is designed to give US commercial imaging satellite operators the financing to build their satellites for high-resolution imaging. GeoEye's principal partners for the development and launch of the GeoEye-1 satellite include General Dynamics (formerly Spectrum Astro), ITT Industries (imager), and Boeing Launch Services. GeoEye's partners for the ground segment include IBM and MDA (MacDonald, Dettwiler and Associates) of Richmond, BC, Canada. he GeoEye-1 spacecraft is being designed and developed at General Dynamics/C4 Systems of Gilbert, AZ (formerly Spectrum Astro) as prime contractor. The contract was award in Dec. 2004. The spacecraft design is based on the SA-200HP standard modular bus (of Coriolis and SWIFT heritage). The spacecraft is 3-axis stabilized with a sophisticated attitude control system to provide a highly stable, while also highly agile imaging platform. A body-pointing capability of up to ± 60º is being provided, made possible by enhanced reaction wheels (low jitter). The image geolocation accuracy is ≤ 3 m. The spacecraft mass is 1955 kg (bus mass = 1260 kg), the S/C design is fully redundant with an operational life of 7 years (the expected life is 10 years). Orbit: Sun-synchronous circular orbit, altitude = 684 km, inclination = 98º, period = 98 minutes, local equatorial crossing at 10:30 hours, effective revisit time capability ≤ 3 days. Launch: A launch of GeoEye-1 is scheduled for August 2008 on a Delta-2 (7420-10) vehicle from VAFB, CA. The launch provider is ULA (United Launch Alliance). The launch delay from the fall of 2007 is due to a launch congestion at VAFB. RF communications: The source data are being stored on solid-state onboard recorders of 1.2 Tbit capacity. The downlink of imagery in X-band at 740 Mbit/s (or at 150 Mbit/s), the TT&C data are in S-band. The S/C is being operated from the command and control facility at GeoEye headquarters in Dulles, VA, along with an imagery acquisition station. Three other acquisition stations will be operated or leased by GeoEye in Barrow, AK, Tromsø, Norway and Troll, Antarctica (the TrollSat station is located at 72º S and 2º E). The latter two stations are being leased from KSAT (Kongsberg Satellite Services) of Tromsø, Norway. A total of four stations are needed to handle primary data reception due to the large volume of data that will be captured by the satellite. In addition, GeoEye will continue to support a network of receiving stations owned and operated by local business partners, referred to as Regional Affiliates and Regional Distributors. Ground segment: GeoEye has built a fully integrated receiving, processing, and distribution network for delivering high-quality imagery products to customers around the world. In late 2006, GeoEye purchased high-bandwidth, high-performance compute technology from SGI (Silicon Graphics Inc.). Four SGI Altix systems were installed at the Dulles (VA) ground station for data processing, distribution, and archiving services. Sensor complement: (GIS) The requirements of GeoEye-1 call for panchromatic imagery with a resolution of 0.41 m and multispectral imagery with a resolution of 1.64 m. The imager is being designed and developed by ITT Space Systems Division, formerly Kodak Remote Sensing Systems of Rochester, New York, which built also the sensor for Ikonos-2 (launch April 27, 1999). In January 2007, the GeoEye-1 imager system was delivered to General Dynamics for integration into the spacecraft. GIS (GeoEye Imager System). GIS is a pushbroom imaging system whose basic elements are the optics subsystem (telescope assembly), the focal plane assembly (CCD detector), and the digital electronics subsystem. The optics subsystem employs a TMA (Three Mirror Anastigmatic) telescope design with a primary mirror aperture of 1.1 m in diameter. Three mirrors are used to image and focus the light, and two additional mirrors to direct the image to the FPA (Focal Plane Assembly). The telescope is designed to give a near-perfect (diffraction limited) image to the FPA and to convert the analog pixels into digitized signals. The FPA consists of an array of CCD detectors with 8 µm pixel size for PAN and 32 µm pixel size for multispectral imagery. ITT has included an outer barrel and door assembly to help protect the telescope and maintain its thermal environment. Group: Platform_Details Entry_ID: GEOEYE-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: GEOEYE-1 End_Group Group: Synonymous_Platform_Names Short_Name: ORBVIEW-5 End_Group Group: Platform_Associated_Instruments Short_Name: CCD IMAGER End_Group Group: Orbit Orbit_Altitude: 684 km Orbit_Inclination: 98 degrees Equator_Crossing: 10:30 AM Period: 98 minutes Repeat_Cycle: 3 days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2008-06-27 Online_Resource: http://launch.geoeye.com/LaunchSite/about/fact_sheet.aspx Online_Resource: http://directory.eoportal.org/get_announce.php?an_id=13708 Sample_Image: http://launch.geoeye.com/LaunchSite/assets/images/about/satellite.gif Group: Platform_Logistics Launch_Date: 2008-08-22 Design_Life: 10 YEARS Primary_Sponsor: US National Geospatial-Intelligence Agency End_Group End_Group 2019-02-19 17:47:38.0 [mmorahan] update Resource (image); insert WeightedRelation (id: null related concept uuid: 992cb370-d2d0-4a9f-a4d4-179f140f505a relationship type: null relationship value: null generated by: null); HU-25C 2016-01-11 20:05:06.0 [aaleman] revised keyword at NSIDC request update AltLabel (Dassault HU-25C Guardian); 2013-05-21 14:36:34.0 [aaleman] created new platform insert AltLabel (id: null text: Dassault HU-25C Falcon language code: en); 2013-05-21 14:35:57.0 [aaleman] Insert Concept add broader relation (HU-25C [47b6caf1-e14c-458c-84a1-ec64cf29b534,105141] - Aircraft [227d9c3d-f631-402d-84ed-b8c5a562fc27,73411]); ECMWFIFS 2015-08-10 18:42:01.0 [epneff] Added long name insert AltLabel (id: null text: ECMWF Integrated Forecast System language code: en); 2015-08-10 18:41:36.0 [epneff] Insert Concept add broader relation (ECMWFIFS [47ee8305-57b9-4df1-84ce-f563df48cf69,158215] - Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215]); Okeanos Explorer NOAA Ship Okeanos Explorer is the only federal vessel dedicated to exploring our largely unknown ocean for the purpose of discovery and the advancement of knowledge about the deep ocean. 2019-11-19 20:57:24.0 [sritz] update AltLabel (NOAA Ship Okeanos Explorer); 2019-11-19 20:55:39.0 [sritz] Rename Concept update PrefLabel (Okeanos Explorer); 2019-08-28 16:09:05.0 [sritz] update AltLabel (Okeanos Explorer); 2019-08-28 16:08:27.0 [sritz] insert AltLabel (id: null category: primary text: OKEANOS Explorer language code: en); 2019-08-28 16:03:07.0 [sritz] insert Definition (id: null text: NOAA Ship Okeanos Explorer is the only federal vessel dedicated to exploring our largely unknown ocean for the purpose of discovery and the advancement of knowledge about the deep ocean. language code: en); 2019-08-28 16:01:09.0 [sritz] update PrefLabel (R/V Okeanos); 2019-08-28 15:57:41.0 [sritz] Insert Concept add broader relation (Okeanos [4838472f-2b4c-4107-bd9e-3bf78a7c5562,369077] - SHIPS [82a67b12-e99d-4c90-8a6a-a6f79d4c3c7b,345297]); Nimbus-2 Nimbus-2 was launched in May 1966 and was the second in a series of second-generation meteorological research-and-development satellites that was designed to serve as a stabilized, earth-oriented platform for the testing of advanced meteorological sensor systems and for collecting meteorological data. The polar-orbiting spacecraft consisted of three major elements: (1) a sensory ring, (2) solar paddles, and (3) the control system housing. The solar paddles and the control system housing were connected to the sensory ring by a truss structure, giving the satellite the appearance of an ocean buoy. Nimbus-2 was nearly 3.7 m tall, 1.5 m in diameter at the base, and about 3 m across with solar paddles extended. The sensory ring, which formed the satellite base, housed the electronics equipment and battery modules. The lower surface of the torus-shaped sensory ring provided mounting space for sensors and telemetry antennas. An H-frame structure mounted within the center of the torus provided support for the larger experiments and tape recorders. Mounted on the control system housing, which was located on top of the spacecraft, were sun sensors, horizon scanners, gas nozzles for attitude control, and a command antenna. Use of a stabilization and control system permitted the spacecraft's orientation to be controlled to within plus or minus 1 degree for all three axes (pitch, roll, and yaw). The spacecraft carried an advanced vidicon camera system for recording and storing remote cloudcover pictures, an automatic picture transmission camera for providing real-time cloudcover pictures, and both high- and medium-resolution infrared radiometers (HRIR and MRIR) for measuring the intensity and distribution of electromagnetic radiation emitted by and reflected from the earth and its atmosphere. The spacecraft and experiments performed normally after launch until July 26, 1966, when the spacecraft tape recorder failed. Its function was taken over by the HRIR tape recorder until November 15, 1966, when it also failed. Some real-time data were collected until January 17, 1969, when the spacecraft mission was terminated owing to deterioration of the horizon scanner used for earth reference. __________ Taken from the NSSDC System for Information Retrieval and Storage (SIRS). For more information contact the NSSDC Coordinated Request and User Support Office, 301-286-6695 (NASA Goddard Space Flight Center, Code 933.4, Greenbelt, Maryland 20771, USA). Nimbus-2 Users' Guide. Group: Platform_Details Entry_ID: NIMBUS-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NIMBUS Short_Name: NIMBUS-2 End_Group Group: Synonymous_Platform_Names Short_Name: Nimbus-C Short_Name: 02173 End_Group Group: Platform_Associated_Instruments Short_Name: AVCS NIMBUS-2 Short_Name: APT NIMBUS-2 Short_Name: MRIR NIMBUS-2 Short_Name: HRIR NIMBUS-2 End_Group Group: Orbit Orbit_Inclination: 100.3499984741211 Degrees Period: 108 minutes Perigee: 1103.0 km Apogee: 1179.0 km Orbit_Type: GEO > Geosynchronous > Geostationary End_Group Creation_Date: 2007-10-11 Online_Resource: http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1966-040A Online_Resource: http://nasascience.nasa.gov/missions/nimbus Online_Resource: http://atmospheres.gsfc.nasa.gov/nimbus/ Sample_Image: http://tbn0.google.com/images?q=tbn:3-Xfyn-FEFls8M:http://library01.gsfc.nasa.gov/gdprojs/images/nimbus_ii.jpg Group: Platform_Logistics Launch_Date: 1966-05-15 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: USA/NASA End_Group End_Group 2015-05-12 16:53:34.0 [saritz] update PrefLabel (Nimbus-2); DMSP 5D-2/F13 DMSP-F13 DMSP Satellite F13 was built by General Electrics Astro-Space Division (now part of Martin Marietta Astro Space). It was launched on March 24, 1995 from Vandenberg AFB, California using an Atlas E rocket. The spacecraft is 3.7 meters in length with a diameter of 1.2 meters with an on-orbit mass of 831 kilograms. It has a design lifetime of 48 months. Power is provided though a 9.29 sq-m solar cell panel. Attitude is controlled using momentum wheels and magnetic coils using a strap-down star sensor and gyros as the reference. Characteristics: Maximum Altitude: 856 km Minimum Altitude: 844 km Inclination: 98.8 deg Period: 102.0 minutes Eccentricity: 0.00083 Ascending Equator Crossing Time (Local Time): At Launch: 17:42 Current (09/02/95): 17:43 Swath Width: Visible and Infrared Imagery - 3000 km Microwave Imagery - 1400 km Temperature Sounder - 1500 km Water Vapor Profiler - 1500 km Launch Date - March 24, 1995 End Mission (Operational Support - F13 is currently (9/02/95) providing primary support with sensors OLS, SSM/I, SSM/T, SSM/T-2, SSJ/4, SSIES2, SSM, SSB/X and SSZ still providing data. Additional information available at "http://ghrc.msfc.nasa.gov:5721/source_documents/dmsp_f13.html" and "http://dmsp.ngdc.noaa.gov/dmsp.html" [Summary provided by GHRC] Group: Platform_Details Entry_ID: DMSP 5D-2/F13 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: DMSP (Defense Meteorological Satellite Program) Short_Name: DMSP 5D-2/F13 Long_Name: Defense Meteorological Satellite Program-F13 End_Group Group: Synonymous_Platform_Names Short_Name: DMSP-F13 Short_Name: USA 109 Short_Name: 23533 End_Group Group: Platform_Associated_Instruments Short_Name: SSM Short_Name: SSM/T-2 Short_Name: OLS Short_Name: SSI/ES2 Short_Name: SSJ/4 Short_Name: SSM/I Short_Name: SSB/X2 Short_Name: SSM/T Short_Name: SSJ End_Group Group: Orbit Orbit_Inclination: 98.8° Period: 101.9 minutes Perigee: 845.0 km Apogee: 851.0 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1995-015A Online_Resource: http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/dmsp.html Online_Resource: http://ghrc.msfc.nasa.gov:5721/source_documents/dmsp_f13.html Online_Resource: http://dmsp.ngdc.noaa.gov/dmsp.html Group: Platform_Logistics Launch_Date: 1995-03-24 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: Department of Defense-Department of the Air Force (United States) End_Group End_Group 2016-06-09 14:35:44.0 [epneff] added altLabel insert AltLabel (id: null text: DMSP-F13 language code: en); Deimos-2 Deimos-2 is a very-high resolution (75cm pan-sharpened) multispectral optical satellite, fully owned and operated by Deimos Imaging, an UrtheCast company. The Deimos-2 end-to-end system has been designed to provide a costeffective yet highly responsive service to customers worldwide. Deimos-2 is the second satellite of the Deimos Earth Observation system, following Deimos-1, which was launched in 2009 and provides mid-resolution, very-wide-swath imagery. Deimos-2 has been launched on 19 June 2014, with a mission lifetime of at least seven years. It operates from a Sun-synchronous orbit at a mean altitude of 620 km, with a local time of ascending node (LTAN) of 10h30, which allows an average revisit time of two days worldwide (one day at mid-latitudes). The spacecraft design is based on an agile platform for fast and precise off-nadir imaging (up to 30º over nominal scenarios and up to 45º in emergency cases), and it carries a push-broom very-high resolution camera with 5 spectral channels (1 panchromatic, 4 multispectral). 2018-07-04 13:17:45.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: d7fbb6b1-1925-4a32-b399-c578435db47c relationship type: null relationship value: null generated by: null); 2018-06-12 09:24:50.0 [mmorahan] insert Definition (id: null text: Deimos-2 is a very-high resolution (75cm pan-sharpened) multispectral optical satellite, fully owned and operated by Deimos Imaging, an UrtheCast company. The Deimos-2 end-to-end system has been designed to provide a costeffective yet highly responsive service to customers worldwide. Deimos-2 is the second satellite of the Deimos Earth Observation system, following Deimos-1, which was launched in 2009 and provides mid-resolution, very-wide-swath imagery. Deimos-2 has been launched on 19 June 2014, with a mission lifetime of at least seven years. It operates from a Sun-synchronous orbit at a mean altitude of 620 km, with a local time of ascending node (LTAN) of 10h30, which allows an average revisit time of two days worldwide (one day at mid-latitudes). The spacecraft design is based on an agile platform for fast and precise off-nadir imaging (up to 30º over nominal scenarios and up to 45º in emergency cases), and it carries a push-broom very-high resolution camera with 5 spectral channels (1 panchromatic, 4 multispectral). language code: en); 2018-06-12 09:18:45.0 [mmorahan] Insert Concept add broader relation (Deimos-2 [48e0f5f2-08fb-4739-8c5f-f53e24003f8c,367667] - Deimos [f122ab59-266b-4be9-99ad-4c2172bcf97c,367663]); GOES-10 The Geostationary Operational Environmental Satellite GOES 10 is the third satellite in a series of next generation geosynchronous spacecraft, referred to as GOES-NEXT and represented by the GOES I through GOES M spacecraft. The GOES-NEXT series is a joint effort on the part of NASA and NOAA to provide continued operational monitoring of weather systems primarily over the United States, distribute meteorological data to regional and national weather offices within the USA, contribute to the development of an environmental data collection network, contribute to the search and rescue program, improve the capability for forcasting and provide real-time warnings of solar distrubances, and to extend knowledge and understanding of atmospheric processes to improve short and long-term weather forecasts. The GOES-NEXT series extends the capabilities of the previous GOES 1-7 spacecraft. The GOES I-M spacecraft will be placed over the equator at 135 deg West or 75 deg West. The design allows unobstructed views of the Earth for operational coverage by the spacecraft sensors. The spacecraft configuration is a compact box-shaped main body that carries the Earth-observing instruments, a continuous-drive solar array attached to the south panel through a yoke assembly, and a solar pointing instrument gimbal mounted on the solar panel yoke. The main body accomodates the sensors, electronics, and support subsystems. The communication antennas, except the Tracking, Telemetry, and Command (TT&C) antenna, are hard-mounted to the Earth-facing panel. The Propulsion Module consists of the fuel and oxidizer tanks for the bipropellant propulsion subsystem mounted on the central cylinder. The Attitude and Orbit Control Substem (AOCS) provides attitude control of the spacecraft. The AOCS consists of the sensors, electronics, and the actuators. The GOES power is generated from the solar array and two 12 A-hr batteries. Power is automatically regulated during solar eclipses. A conical shaped solar sail at the end of a 58-foot boom balances torque caused by solar radiation. The main body of the spacecraft is a 2-meter cube. In its deployed orbit configuration, the overall length is about 27 meters. Initial mass was about 4640 pounds, including fuel. Design lifetime is about five years. The Image Navigation/Registration (INR) system provides Imager and Sounder data products in real-time to users. The Communications, Command, and Data Handling subsystem is comprised of antennas, receivers, transponders, transmitters, data encoders and encryptors and multiplexers. The Tracking Telemetry and Command (TT&C) subsystem provides the necessary monitor and command link between the spacecraft and the ground stations. The GOES-NEXT instruments consist of the following: (1) Earth Imaging System, a 5-channel visible and infrared radiometer which provides Earth imagery 24 hours a day; (2) Sounding System, a 19-channel discrete-filter radiometer for obtaining atmospheric temperature and moisture soundings; (3) a Space Environment Monitor (SEM), which consists of a magnetic field sensor, a solar X-ray sensor, an energetic particle sensor (EPS), and a High Energy Proton and Alpha Detector (HEPAD); (4) a Search and Rescue subsystem (SARSAT), which receives signals from 406 MHz distress beacons and relays them to the ground; (5) a Data Collection System (DCS) for collecting and relaying real-time information from Data Collection Platforms (DCPs) such as buoys, balloons, remote weather stations, ships, and aircraft; and (6) a Weather Facsimile (WEFAX) system which relays processed weather imagary from the Wallops Island station to the user community. The SEC package has been frequently eratic during 2003. 2017-09-01 16:50:58.0 [sritz] update Definition (The Geostationary Operational Environmental Satellite GOES 10 is the third satellite in a series of next generation geosynchronous spacecraft, referred to as GOES-NEXT and represented by the GOES I through GOES M spacecraft. The GOES-NEXT series is a joint effort on the part of NASA and NOAA to provide continued operational monitoring of weather systems primarily over the United States, distribute meteorological data to regional and national weather offices within the USA, contribute to the development of an environmental data collection network, contribute to the search and rescue program, improve the capability for forcasting and provide real-time warnings of solar distrubances, and to extend knowledge and understanding of atmospheric processes to improve short and long-term weather forecasts. The GOES-NEXT series extends the capabilities of the previous GOES 1-7 spacecraft. The GOES I-M spacecraft will be placed over the equator at 135 deg West or 75 deg West. The design allows unobstructed views of the Earth for operational coverage by the spacecraft sensors. The spacecraft configuration is a compact box-shaped main body that carries the Earth-observing instruments, a continuous-drive solar array attached to the south panel through a yoke assembly, and a solar pointing instrument gimbal mounted on the solar panel yoke. The main body accomodates the sensors, electronics, and support subsystems. The communication antennas, except the Tracking, Telemetry, and Command (TT&C) antenna, are hard-mounted to the Earth-facing panel. The Propulsion Module consists of the fuel and oxidizer tanks for the bipropellant propulsion subsystem mounted on the central cylinder. The Attitude and Orbit Control Substem (AOCS) provides attitude control of the spacecraft. The AOCS consists of the sensors, electronics, and the actuators. The GOES power is generated from the solar array and two 12 A-hr batteries. Power is automatically regulated during solar eclipses. A conical shaped solar sail at the end of a 58-foot boom balances torque caused by solar radiation. The main body of the spacecraft is a 2-meter cube. In its deployed orbit configuration, the overall length is about 27 meters. Initial mass was about 4640 pounds, including fuel. Design lifetime is about five years. The Image Navigation/Registration (INR) system provides Imager and Sounder data products in real-time to users. The Communications, Command, and Data Handling subsystem is comprised of antennas, receivers, transponders, transmitters, data encoders and encryptors and multiplexers. The Tracking Telemetry and Command (TT&C) subsystem provides the necessary monitor and command link between the spacecraft and the ground stations. The GOES-NEXT instruments consist of the following: (1) Earth Imaging System, a 5-channel visible and infrared radiometer which provides Earth imagery 24 hours a day; (2) Sounding System, a 19-channel discrete-filter radiometer for obtaining atmospheric temperature and moisture soundings; (3) a Space Environment Monitor (SEM), which consists of a magnetic field sensor, a solar X-ray sensor, an energetic particle sensor (EPS), and a High Energy Proton and Alpha Detector (HEPAD); (4) a Search and Rescue subsystem (SARSAT), which receives signals from 406 MHz distress beacons and relays them to the ground; (5) a Data Collection System (DCS) for collecting and relaying real-time information from Data Collection Platforms (DCPs) such as buoys, balloons, remote weather stations, ships, and aircraft; and (6) a Weather Facsimile (WEFAX) system which relays processed weather imagary from the Wallops Island station to the user community. The SEC package has been frequently eratic during 2003.); update Definition (https://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1997-019A); 2017-09-01 16:50:28.0 [sritz] insert Definition (id: null text: [Source: NASA NSSDC, https://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1997-019A ] The Geostationary Operational Environmental Satellite GOES 10 is the third satellite in a series of next generation geosynchronous spacecraft, referred to as GOES-NEXT and represented by the GOES I through GOES M spacecraft. The GOES-NEXT series is a joint effort on the part of NASA and NOAA to provide continued operational monitoring of weather systems primarily over the United States, distribute meteorological data to regional and national weather offices within the USA, contribute to the development of an environmental data collection network, contribute to the search and rescue program, improve the capability for forcasting and provide real-time warnings of solar distrubances, and to extend knowledge and understanding of atmospheric processes to improve short and long-term weather forecasts. The GOES-NEXT series extends the capabilities of the previous GOES 1-7 spacecraft. The GOES I-M spacecraft will be placed over the equator at 135 deg West or 75 deg West. The design allows unobstructed views of the Earth for operational coverage by the spacecraft sensors. The spacecraft configuration is a compact box-shaped main body that carries the Earth-observing instruments, a continuous-drive solar array attached to the south panel through a yoke assembly, and a solar pointing instrument gimbal mounted on the solar panel yoke. The main body accomodates the sensors, electronics, and support subsystems. The communication antennas, except the Tracking, Telemetry, and Command (TT&C) antenna, are hard-mounted to the Earth-facing panel. The Propulsion Module consists of the fuel and oxidizer tanks for the bipropellant propulsion subsystem mounted on the central cylinder. The Attitude and Orbit Control Substem (AOCS) provides attitude control of the spacecraft. The AOCS consists of the sensors, electronics, and the actuators. The GOES power is generated from the solar array and two 12 A-hr batteries. Power is automatically regulated during solar eclipses. A conical shaped solar sail at the end of a 58-foot boom balances torque caused by solar radiation. The main body of the spacecraft is a 2-meter cube. In its deployed orbit configuration, the overall length is about 27 meters. Initial mass was about 4640 pounds, including fuel. Design lifetime is about five years. The Image Navigation/Registration (INR) system provides Imager and Sounder data products in real-time to users. The Communications, Command, and Data Handling subsystem is comprised of antennas, receivers, transponders, transmitters, data encoders and encryptors and multiplexers. The Tracking Telemetry and Command (TT&C) subsystem provides the necessary monitor and command link between the spacecraft and the ground stations. The GOES-NEXT instruments consist of the following: (1) Earth Imaging System, a 5-channel visible and infrared radiometer which provides Earth imagery 24 hours a day; (2) Sounding System, a 19-channel discrete-filter radiometer for obtaining atmospheric temperature and moisture soundings; (3) a Space Environment Monitor (SEM), which consists of a magnetic field sensor, a solar X-ray sensor, an energetic particle sensor (EPS), and a High Energy Proton and Alpha Detector (HEPAD); (4) a Search and Rescue subsystem (SARSAT), which receives signals from 406 MHz distress beacons and relays them to the ground; (5) a Data Collection System (DCS) for collecting and relaying real-time information from Data Collection Platforms (DCPs) such as buoys, balloons, remote weather stations, ships, and aircraft; and (6) a Weather Facsimile (WEFAX) system which relays processed weather imagary from the Wallops Island station to the user community. The SEC package has been frequently eratic during 2003. language code: en); 2017-09-01 16:46:28.0 [sritz] Insert Concept add broader relation (GOES-10 [49178ef5-a003-4de2-9553-066f629bb072,310111] - GOES [6e332c25-caeb-4917-afb6-af757bcecd72,310071]); GROUND STATIONS GROUND STATION Ground Stations: A precise point along the ground or surface where measurements or surveys are made. [Source: The American Heritage Dictionary of the English Language, Fourth Edition Copyright 2000 by Houghton Mifflin Company] Group: Platform_Details Entry_ID: GROUND STATIONS Group: Platform_Identification Platform_Category: In Situ Land-based Platforms Short_Name: GROUND STATIONS End_Group End_Group 2016-06-09 18:42:25.0 [epneff] added altLabel insert AltLabel (id: null text: GROUND STATION language code: en); DIADEM EXPLORER-31 (DME-A) The Direct Measurement Explorer-A (DME-A) satellite was launched in November 1965 into a near-earth orbit ranging between altitudes of 500 and 3000 km to sample and measure charged particles. The attitude control system is used to keep the spin axis aligned with the orbit normal and to maintain the spin rate. Spin axis control is achieved by a chargeable permanent magnet system which is operated upon command and reacts with the earth's field to produce precession of several degrees per minute. With this system the spin axis was kept within 10 degrees of the orbit normal for several weeks at a time, although larger deviations have been tolerated. The spin rate was observed to decay at 0.05 rpm per day. Periodic use of the spin rate control system has compensated for spin decay. This system is analogous to a DC motor in which the entire satellite is the armature. Group: Platform_Details Entry_ID: EXPLORER-31 (DME-A) Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Platform_Series_or_Entity: EXPLORER Short_Name: EXPLORER-31 (DME-A) End_Group Group: Synonymous_Platform_Names Short_Name: Explorer-A Short_Name: Explorer 31 Short_Name: 01806 End_Group Group: Platform_Associated_Instruments Short_Name: SPHERICAL MASS SPECTROMETER Short_Name: ELECTROSTATIC ANALYZERS Short_Name: ENERGETIC ELECTRON CURRENT MONITOR Short_Name: ELECTRON TEMPERATURE PROBE Short_Name: MAGNETIC ION-MASS SPECTROMETER End_Group Group: Orbit Orbit_Inclination: 79.80 degrees Period: 119.70 min Perigee: 505 km Apogee: 2833 km End_Group Creation_Date: 2007-12-14 Online_Resource: http://stinet.dtic.mil/oai/oai?verb=getRecord&metadataPrefix=html&identifier=AD0656730 Sample_Image: http://www.daviddarling.info/images/DME.jpg Group: Platform_Logistics Launch_Date: 1965-11-29 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: NASA End_Group End_Group ICON The Ionospheric Connection Explorer will study the frontier of space: the dynamic zone high in our atmosphere where terrestrial weather from below meets space weather above. In this region, the tenuous gases are anything but quiet, as a mix of neutral and charged particles travel through in giant winds. These winds can change on a wide variety of time scales -- due to Earth's seasons, the day's heating and cooling, and incoming bursts of radiation from the sun. This region of space and its changes have practical repercussions, given our ever-increasing reliance on technology -- this is the area through which radio communications and GPS signals travel. Variations there can result in distortions or even complete disruption of signals. In order to understand this complicated region of near-Earth space, called the ionosphere, NASA has developed the ICON mission. To understand what drives variability in the ionosphere requires a careful look at a complicated system that is driven by both terrestrial and space weather. ICON will help determine the physics of our space environment and pave the way for mitigating its effects on our technology, communications systems and society. Additional Information: https://www.nasa.gov/icon 2019-10-08 19:20:28.0 [sritz] update Definition (The Ionospheric Connection Explorer will study the frontier of space: the dynamic zone high in our atmosphere where terrestrial weather from below meets space weather above. In this region, the tenuous gases are anything but quiet, as a mix of neutral and charged particles travel through in giant winds. These winds can change on a wide variety of time scales -- due to Earth's seasons, the day's heating and cooling, and incoming bursts of radiation from the sun. This region of space and its changes have practical repercussions, given our ever-increasing reliance on technology -- this is the area through which radio communications and GPS signals travel. Variations there can result in distortions or even complete disruption of signals. In order to understand this complicated region of near-Earth space, called the ionosphere, NASA has developed the ICON mission. To understand what drives variability in the ionosphere requires a careful look at a complicated system that is driven by both terrestrial and space weather. ICON will help determine the physics of our space environment and pave the way for mitigating its effects on our technology, communications systems and society. Additional Information: https://www.nasa.gov/icon); 2018-02-27 19:14:13.0 [sritz] insert Resource (id: null type: provider url: https://www.nasa.gov/icon); 2018-02-27 19:12:57.0 [sritz] insert Definition (id: null text: The Ionospheric Connection Explorer will study the frontier of space: the dynamic zone high in our atmosphere where terrestrial weather from below meets space weather above. In this region, the tenuous gases are anything but quiet, as a mix of neutral and charged particles travel through in giant winds. These winds can change on a wide variety of time scales -- due to Earth's seasons, the day's heating and cooling, and incoming bursts of radiation from the sun. This region of space and its changes have practical repercussions, given our ever-increasing reliance on technology -- this is the area through which radio communications and GPS signals travel. Variations there can result in distortions or even complete disruption of signals. In order to understand this complicated region of near-Earth space, called the ionosphere, NASA has developed the ICON mission. To understand what drives variability in the ionosphere requires a careful look at a complicated system that is driven by both terrestrial and space weather. ICON will help determine the physics of our space environment and pave the way for mitigating its effects on our technology, communications systems and society. language code: en); 2018-02-27 19:12:15.0 [sritz] insert AltLabel (id: null category: primary text: Ionospheric Connection Explorer language code: en); 2018-02-27 19:11:42.0 [sritz] Insert Concept add broader relation (ICON [4a3988a7-f1c6-4c0a-a93b-9221adbca49b,310603] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,287601]); DEM DEM (DIGITAL ELEVATION MODEL) DIGITAL ELEVATION MODEL Digital Elevation Models (DEM) are digital files consisting of terrain elevations for ground positions at regularly spaced horizontal intervals. [Source: USGS] Group: Platform_Details Entry_ID: DEM Group: Platform_Identification Platform_Category: Models Short_Name: DEM Long_Name: Digital Elevation Model End_Group Group: Synonymous_Platform_Names Short_Name: DEM End_Group Creation_Date: 2007-12-13 Online_Resource: http://rmmcweb.cr.usgs.gov/elevation/dpi_dem.html Sample_Image: http://edc.usgs.gov/images/dem.jpg End_Group 2016-06-09 17:26:13.0 [epneff] added altLabel insert AltLabel (id: null text: DEM (DIGITAL ELEVATION MODEL) language code: en); insert AltLabel (id: null text: DIGITAL ELEVATION MODEL language code: en); IMP-8 IMP-8 (Interplanetary Monitoring Platform-8) was launched by NASA on October 26, 1973 to measure the magnetic fields, plasmas, and energetic charged particles (e.g., cosmic rays) of the Earth's magnetotail and magnetosheath and of the near-Earth solar wind. IMP-8, the last of ten IMP (Interplanetary Monitoring Platform) or AIMP (Anchored-IMP) spacecraft launched in 10 years, continues to operate to this day in its near-circular, 35 Earth Radii, 12-day orbit. It is an important adjunct to the International Solar Terrestrial Physics program, provides in-ecliptic, one Astronomical Unit baseline data for the deep space Voyager and Ulysses missions, and continues to accumulate a long-timeseries database useful in understanding long-term solar processes. http://nssdc.gsfc.nasa.gov/space/imp-8.html [Source: NASA.] IRNSS IRNSS is an independent regional navigation satellite system being developed by India. It is designed to provide accurate position information service to users in India as well as the region extending up to 1500 km from its boundary, which is its primary service area. An Extended Service Area lies between primary service area and area enclosed by the rectangle from Latitude 30 deg South to 50 deg North, Longitude 30 deg East to 130 deg East. IRNSS will provide two types of services, namely, Standard Positioning Service (SPS) which is provided to all the users and Restricted Service (RS), which is an encrypted service provided only to the authorised users. The IRNSS System is expected to provide a position accuracy of better than 20 m in the primary service area. 2017-08-15 13:32:47.0 [tstevens] insert Definition (id: null text: IRNSS is an independent regional navigation satellite system being developed by India. It is designed to provide accurate position information service to users in India as well as the region extending up to 1500 km from its boundary, which is its primary service area. An Extended Service Area lies between primary service area and area enclosed by the rectangle from Latitude 30 deg South to 50 deg North, Longitude 30 deg East to 130 deg East. IRNSS will provide two types of services, namely, Standard Positioning Service (SPS) which is provided to all the users and Restricted Service (RS), which is an encrypted service provided only to the authorised users. The IRNSS System is expected to provide a position accuracy of better than 20 m in the primary service area. language code: en); 2017-08-14 19:24:16.0 [tstevens] insert AltLabel (id: null category: primary text: India’s Regional Navigation Satellite System Satellites language code: en); 2017-08-14 19:23:59.0 [tstevens] Insert Concept add broader relation (IRNSS [4c93cc0b-ca0e-4421-ac60-559b6390b89b,309923] - IRNSS (India’s Regional Navigation Satellite System) [bad22a08-f8ab-49b3-b266-005b21496626,309919]); NCEP-NAM 2015-03-05 16:04:51.0 [epneff] insert AltLabel (id: null text: NCEP North American Model language code: en); 2015-03-05 16:03:59.0 [epneff] Insert Concept add broader relation (NCEP-NAM [4cbc6cbe-50a2-4464-acd9-395379753d4e,106783] - Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,73395]); DASH-2 The Dash (Density And Scale Height) satellites were 2.5-m-diameter balloons used to measure air densities at altitudes of approximately 3500 km. The area-to-mass ratio for the spacecraft was 40 sq cm/g. The orbit, originally circular, increased in eccentricity rapidly under the action of solar radiation pressure. This experiment used the variations in orbit characteristics of the Dash balloon satellite to deduce neutral air densities and to study the effect of solar radiation pressure. Other effects, such as terrestrial radiation pressure, lunar gravity, and solar gravity were also observable. Dash 2 reentered the earth's atmosphere on April 12, 1971. Additional information available at "http://www.skyrocket.de/space/doc_sdat/dash-1.htm" Group: Platform_Details Entry_ID: DASH-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: DASH-2 End_Group Group: Synonymous_Platform_Names Short_Name: DASH-2 End_Group Creation_Date: 2007-11-19 Online_Resource: http://www.skyrocket.de/space/doc_sdat/dash-1.htm Group: Platform_Logistics Launch_Date: 1963-07-19 Primary_Sponsor: NASA End_Group End_Group GEOPHYSICAL STATIONS/NETWORKS 2019-03-01 20:39:47.0 [sritz] Insert Concept add narrower relation (GEOPHYSICAL STATIONS/NETWORKS [4ce2e520-9a55-44fe-8f2c-93d64f4eef63,344937] - Analytical Lab [ac63eed1-779d-4085-92f8-5743ec64a942,368521]); METEOSAT-3 Meteosat-P2 (Meteosat 3) was launched on June 15, 1988 from Kourou, French Guiana. Meteosat 3 is a refurbished protoype of Meteosat-2. In general, the design, the instrumentation, and the operation are similar to SMS/GOES. The cylindrically shaped spacecraft measures 210 cm in diameter and 430 cm in length, including the apogee boost motor. The primary structural members are an equipment platform and a central tube. The radiometer telescope is mounted on the equipment platform and views the earth through a special aperture in the side of the spacecraft. A support structure extends radially out from the central tube and is affixed to the solar panels, which form the outer walls of the spacecraft. These solar panels provide the primary source of electrical power. Located in the annulus-shaped space between the central tube and the solar panels are station-keeping and dynamics control equipment and batteries. Proper spacecraft attitude and spin rate (approximately 100 rpm) are maintained by jet thrusters mounted on the spacecraft and activated by ground command. The spacecraft uses both UHF-band and S-band frequencies in the telemetry and command systems. During launch, a lower power VHF transponder provides telemetry and command. After launch, the VHF transponder then serves as a backup for the primary subsystem once the spacecraft attains synchronous orbit. The spin-stabilized, geostationary spacecraft carries (1) a visible-IR radiometer to provide high-quality, day/night cloud-cover data and to take radiance temperatures of the earth/atmosphere system, and (2) a meteorological data collection system to disseminate image data to user stations, to collect data from various earth-based platforms, and to relay data from polar-orbiting satellites. Orbital Characteristics- Orbital Period: 1439.00 m Inclination: 0.50 degrees Eccentricity: 0.00110 Periapsis: 35796.00 km Apoapsis: 35889.00 km For information on the European Space Agency (ESA) and the Meteosat Program, see the URL: http://www.esrin.esa.it To view a 3D orbit, observe the J Track satellite tracking web page: http://liftoff.msfc.nasa.gov/RealTime/JTrack/ ----------------- Entry taken from: Taken from the NSSDC System for Information Retrieval and Storage (SIRS). For more information contact the NSSDC Coordinated Request and User Support Office, 301-286-6695 (NASA Goddard Space Flight Center, Code 933.4, Greenbelt, Maryland 20771, USA, http://nssdc.gsfc.nasa.gov/). Group: Platform_Details Entry_ID: METEOSAT-3 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: METEOSAT Short_Name: METEOSAT-3 End_Group End_Group DMSP 5D-3/F15 DMSP-F15 [Source: National Space Science Data Center, http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1999-067A ] MSP F15 (USA 147) was launched by a Titan rocket from Vandenberg AFB on December 12, 1999 into a 101 minute, sun-synchronous near-polar orbit at an altitude of 840km and with the Local Time nodes of 21:10 and 9:10. The Defense Meteorological Satellite Program (DMSP) is a Department of Defense (DoD) program run by the Air Force Space and Missle Systems Center (SMC). The program designs, builds, launches, and maintains satellites monitoring the meteorological, oceanographic, and solar-terrestrial physics environments. Each DMSP satellite has a above the surface of the earth. The visible and infrared sensors (OLS) collect images across a 3000 km swath, providing global coverage twice per day. The combination of day/night and dawn/dusk satellites allows monitoring of global information such as clouds every 6 hours. The microwave imager (MI) and sounders (T1, T2) cover one half the width of the visible and infrared swath. These instruments cover polar regions at least twice and the equatorial region once per day. The space environment sensors (J4, M, IES) record along-track plasma densities, velocities, composition and drifts. The data from the DMSP satellites are received and used at operational centers continuously. The data are sent to the National Geophysical Data Center's Solar Terrestrial Physics Division (NGDC/STP) by the Air Force Weather Agency (AFWA) for creation of an archive. Group: Platform_Details Entry_ID: DMSP 5D-3/F15 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: DMSP (Defense Meteorological Satellite Program) Short_Name: DMSP 5D-3/F15 Long_Name: Defense Meteorological Satellite Program-F15 End_Group Group: Platform_Associated_Instruments Short_Name: GAMMA RAY DETECTOR (SSB) Short_Name: OLS Short_Name: SSM/T Short_Name: SSI/ES Short_Name: SSJ/4 Short_Name: SSM/I Short_Name: SSM/T-2 Short_Name: SSM End_Group Group: Orbit Orbit_Inclination: 98.9° Period: 101.8 minutes Perigee: 837.0 km Apogee: 851.0 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2008-10-31 Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1999-067A Online_Resource: http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/dmsp.html Online_Resource: http://www.ngdc.noaa.gov/dmsp/ Group: Platform_Logistics Launch_Date: 1999-12-12 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: Department of Defense-Department of the Air Force (United States) End_Group End_Group 2016-06-09 14:38:03.0 [epneff] added altLabel insert AltLabel (id: null text: DMSP-F15 language code: en); SME The Solar Mesosphere Explorer (SME) mission objective was primarily to investigate the processes that create and destroy ozone in the Earth's mesosphere and upper stratosphere. Some specific goals were (1) to determine the nature and magnitude of changes in mesospheric ozone densities resulting from changes in the solar ultraviolet flux; (2) to determine the interrelationship between solar flux, ozone, and the temperature of the upper stratosphere and mesosphere; (3) to determine the interrelationship between ozone and water vapor; and (4) to determine the interrelationship between nitrogen dioxide and ozone. The satellite experiment complement consisted of a solar ultraviolet spectrometer, an ultraviolet ozone spectrometer, an infrared radiometer, a 1.27-micrometer spectrometer, and a nitrogen dioxide spectrometer. In addition, a solar proton alarm detector was carried on board to measure the integrated solar flux in the range 30 to 500 MeV. Spin stabilized at 5 rpm, the satellite moved in a 3 a.m. to 3 p.m. sun-synchronous orbit. The spacecraft body was a cylinder approximately 1.7 by 1.25 m and consisted of two major modules: the observatory module that housed the scientific instruments, and the spacecraft bus. The spin axis was oriented normal to the orbital plane. The command system was capable of executing commands in real time or from stored program control. Power was supplied by a solar cell array. The telemetry system was used either in a real-time or in a tape-recorder mode. Further details and some measurement results are written in C. A. Barth et al., 'Solar mesosphere explorer: scientific objectives and results,' Geophys. Res. Lett., v. 10, no. 4, p. 237, 1983. All instruments on board the SME were turned off in December 1988 because of energy considerations. - Auxiliary Information - Launch Date and Time : 1981-10-06 11:27:00 Epoch Date and Time : 1981-10-16 Apogee (km or AU): 551. Perigee (km or AU): 535. Inclination (degree) : 97.5 Orbit Type : Geocentric IDN_Node: USA/NASA Group: Platform_Details Entry_ID: SME Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: SME Long_Name: Solar Mesospheric Explorer End_Group Group: Synonymous_Platform_Names Short_Name: SME End_Group Group: Orbit Orbit_Inclination: 97.5 Perigee: 535 Apogee: 551 End_Group Creation_Date: 2007-11-28 Online_Resource: http://lasp.colorado.edu/sme/ Sample_Image: http://lasp.colorado.edu/sme/gifs/sme.gif Group: Platform_Logistics Launch_Date: 1981-09-06 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: NASA End_Group End_Group SARAL 2016-08-15 15:43:23.0 [mpmorahan] insert AltLabel (id: null text: Satellite with ARgos and ALtiKa language code: en); 2016-08-15 15:40:53.0 [mpmorahan] Insert Concept add broader relation (SARAL [4e62dd32-7776-4646-ae8d-b85d97df415a,277815] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,256549]); SRL-2 During the 10 day mission, the Space Radar Laboratory (SRL) payload in Endeavour's cargo bay will make its second flight. The SRL payload, which first flew during STS-59 in April 1994, will again give scientists highly detailed information that will help them distinguish between human-induced environmental changes and other natural forms of change. SRL-2 will take radar images of the Earth's surface for Earth system sciences studies, including geology, geography, hydrology, oceanography, agronomy and botany. The SRL payload is comprised of the Spaceborne Imaging Radar-C/X-Band Synthetic Aperture Radar (SIR-C/X-SAR), and the Measurement of Air Pollution from Satellite (MAPS). The German Space Agency (DARA) and the Italian Space Agency (ASI) are providing the X-SAR instrument. The imaging radar of the SIR-C/X-SAR instruments has the ability to make measurements over virtually any region at any time, regardless of weather or sunlight conditions. The radar waves can penetrate clouds, and under certain conditions, also can "see" through vegetation, ice and extremely dry sand. In many cases, radar is the only way scientists can explore inaccessible regions of the Earth's surface. The SIR-C/X-SAR radar data provide information about how many of Earth's complex systems - those processes that control the movement of land, water, air and life - work together to make this a livable planet. The science team particularly wants to study the amount of vegetation coverage, the extent of snow packs, wetlands areas, geologic features such as rock types and their distribution, volcanic activity, ocean wave heights and wind speed. STS-68 will fly over the same sites that STS-59 observed so that scientists will be able to study seasonal changes that may have occurred in those areas between the missions. An international team of 49 science investigators and three associates will conduct the SIR-C/X-SAR experiments. Thirteen nations are represented: Australia, Austria, Brazil, Canada, China, the United Kingdom, France, Germany, Italy, Japan, Mexico, Saudi Arabia and the United States. The MAPS experiment will measure the global distribution of carbon monoxide in the troposphere, or lower atmosphere. Measurements of carbon monoxide, an important element in several chemical cycles, provide scientists with indications of how well the atmosphere can cleanse itself of "greenhouse gases," chemicals that can increase the atmosphere's temperature. STS-68 provided a continuation of NASA's Get Away Special (GAS) experiments program. The project gives a person or organization a chance to perform experiments in space on a Shuttle mission. Two universities, North Carolina A&T State University and University of Alabama in Huntsville, and the Swedish Space Corp., Soina, Sweden, will have small self-contained payloads flying during the STS-68 mission. Other GAS hardware in Endeavour's payload bay will carry 500,000 commemorative stamps for the U.S. Postal Service in recognition of the 25th anniversary of the Apollo 11 Moon landing. Other payloads aboard Endeavour include the Biological Research in Canister (BRIC) which will fly for the first time, and the Military Applications of Ship Tracks (MAST) which will be making its second flight. BRIC experiments, sponsored by NASA's Office of Life and Microgravity Sciences and Applications, are designed to examine the effects of microgravity on a wide range of physiological processes in higher order plants and arthropod animals (e.g., insects, spiders, centipedes, crustaceans). MAST is an experiment sponsored by the Office of Naval Research (ONR) and is part of a five-year research program developed by ONR to examine the effects of ships on the marine environment. The Commercial Protein Crystal Growth (CPCG) experiment, the Chromosome and Plant Cell Division in Space Experiment (CHROMEX) and the Cosmic Radiation Effects and Activation Monitor (CREAM) experiment also will be carried aboard Endeavour. [Summary provided by NASA] Group: Platform_Details Entry_ID: SRL-2 Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Platform_Series_or_Entity: SPACE SHUTTLE Short_Name: SRL-2 Long_Name: Space Radar Laboratory-2 End_Group Group: Synonymous_Platform_Names Short_Name: SRL-2 End_Group Group: Platform_Associated_Instruments Short_Name: X-SAR End_Group Creation_Date: 2008-01-28 Online_Resource: http://www-pao.ksc.nasa.gov/shuttle/missions/backup%2010-5/sts-68/ Group: Platform_Logistics Launch_Date: 1994-09-30 Primary_Sponsor: NASA End_Group End_Group JASON-1 Jason maps ocean surface topography. The data collected provide information on ocean surface current velocity and heights which, when combined with ocean models, can lead to a four-dimensional description of ocean circulation. Data from Jason are also extending ocean surface topography into the 21st century, providing a 5-year view of global ocean surface topography, increasing understanding of ocean circulation, improving forecasting of climate events, and measuring global sea-level change. Key Jason Facts Joint with France Dimensions: Satellite support module: 95.4 cm ý 95.4 cm ý 100.0 cm; Payload module 95.4 cm ý 95.4 cm ý 121.8 cm; Solar array span: Two wings with four 1.5 m ý 0.8 m panels per wing; total surface of 9.8 m2 Mass: 500 kg Power: 2100 W Downlink: Jason telemetry downlink is 0.7 Mbps (700 Kbps) S-Band to JPL, Wallops Island, Virginia, Poker Flats, Alaska, and Aussaguel, France Group: Platform_Details Entry_ID: JASON-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: EOS (Earth Observing System) Short_Name: JASON-1 End_Group Group: Synonymous_Platform_Names Short_Name: JASON End_Group Group: Platform_Associated_Instruments Short_Name: TRSR Short_Name: POSEIDON-2 Short_Name: LRA Short_Name: JMR Short_Name: DORIS End_Group Group: Orbit Orbit_Altitude: 1336 km Orbit_Inclination: 66 degrees Period: 112.4 minutes Repeat_Cycle: 9.9156 days Perigee: 1,332 km (827 mi) Apogee: 1,344 km (835 mi) Orbit_Type: LEO > Low Earth Orbit > Polar Non-Sun-Synchronous End_Group Creation_Date: 2007-04-16 Online_Resource: http://sealevel.jpl.nasa.gov/mission/jason-1.html Online_Resource: http://www.aviso.oceanobs.com/ Online_Resource: http://nasascience.nasa.gov/missions/jason-1 Online_Resource: http://www.nasa.gov/centers/jpl/missions/jason.html Online_Resource: http://www.cnes.fr/web/1441-jason.php Sample_Image: http://sealevel.jpl.nasa.gov/mission/images/jason-1-in-space.gif Group: Platform_Logistics Launch_Date: 2001-12-07 Launch_Site: Vandenberg Air Force Base, USA Design_Life: 3-year primary mission; 2-year extended mission Primary_Sponsor: USA/NASA Primary_Sponsor: France/CNES End_Group End_Group 2019-02-21 09:29:03.0 [mmorahan] update Resource (image); insert WeightedRelation (id: null related concept uuid: e7c3b01c-0739-487b-adbb-59d84c559375 relationship type: null relationship value: null generated by: null); In Situ Land-based Platforms Fixed and mobile land-based platforms. Group: Platform_Details Entry_ID: In Situ Land-based Platforms Group: Platform_Identification Platform_Category: In Situ Land-based Platforms Short_Name: In Situ Land-based Platforms End_Group End_Group 2018-11-07 21:50:54.0 [sritz] Insert Concept add narrower relation (In Situ Land-based Platforms [4f396ff6-7bea-4ba4-afa3-198ebd914a4a,344951] - Ice Shelf [dd445d5a-14d5-4813-b1cb-243799a044f7,368249]); 2018-08-23 18:24:50.0 [sritz] Insert Concept add narrower relation (In Situ Land-based Platforms [4f396ff6-7bea-4ba4-afa3-198ebd914a4a,344951] - Data Collections [c10044b3-6ebc-413a-99b7-2be30c08e507,368091]); 2018-08-23 18:24:33.0 [sritz] Insert Concept add narrower relation (In Situ Land-based Platforms [4f396ff6-7bea-4ba4-afa3-198ebd914a4a,344951] - Publications [2e555886-1baa-4f05-899b-1d14ab69fe62,368087]); 2017-12-28 19:11:49.0 [sritz] Move Concepts delete narrower relation (null); 2017-12-28 19:11:17.0 [sritz] Insert Concept add narrower relation (In Situ Land-based Platforms [4f396ff6-7bea-4ba4-afa3-198ebd914a4a,287781] - CODAR SeaSonde [294cc889-28bc-4a33-b630-8225f559c3e7,310507]); 2017-11-22 15:24:51.0 [tstevens] Insert Concept add narrower relation (In Situ Land-based Platforms [4f396ff6-7bea-4ba4-afa3-198ebd914a4a,287781] - TRIPOD [9c44243f-3122-4f7f-98b1-fb4e729418e0,310389]); 2016-10-28 19:56:48.0 [gee-cee] Insert Concept add narrower relation (In Situ Land-based Platforms [4f396ff6-7bea-4ba4-afa3-198ebd914a4a,256725] - GREAT WALL STATION [92aae4b1-cd4c-41b8-b931-4c2b70790baf,278483]); ALOUETTE-1 Alouette-1 was a small ionospheric space based observatory instrumented with an ionospheric sounder (radio transmitter), a VLF radio wave receiver, an energetic particle detector, and a cosmic radio noise experiment. EXTERIOR EQUIPMENT: Extended from the satellite skin (shell) were two dipole antennas (45.7-meter and 22.8-meter long, respectively) which were shared by three of the experiments on this spacecraft. SPACECRAFT ROTATION (SPIN): The satellite was spin-stabilized at about 1.4 rpm after antenna extension. After about 500 days in orbit, the ALOUETTE-1 spin rate slowed more than had been expected, to about 0.6 rpm when satellite spin-stabilization failed. It is now believed that the satellite gradually progressed towards a gravity gradient stabilization with the longer antenna pointing earthward. Attitude information was deduced from a single onboard magnetometer only, and aided by temperature measurements on the upper and lower heat shields. DATA ACQUISITION: Alouette-1 was an early space era satellite, and there was no onboard tape recorder so data were available to the ground stations only from the immediate vicinity of the telemetry stations. The ground telemetry stations were located to provide primary data coverage near the 80 degrees West meridian and in areas near Hawaii, Singapore, Australia, Europe and Central Africa. Initially, data were recorded for about 6 hours per day. In September 1972, spacecraft operations were terminated. Group: Platform_Details Entry_ID: ALOUETTE-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: ALOUETTE Short_Name: ALOUETTE-1 End_Group Group: Synonymous_Platform_Names Short_Name: ALOUETTE-A Short_Name: 00424 End_Group Group: Platform_Associated_Instruments Short_Name: TELEMETER Short_Name: MAGNETOMETERS Short_Name: PARTICLE DETECTORS End_Group Creation_Date: 2007-08-22 Online_Resource: http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1962-049A Group: Platform_Logistics Launch_Date: 1962-09-29 Primary_Sponsor: NASA End_Group End_Group LAGEOS (Laser Geodetic Satellite) ESSA-4 TOS-B The ESSA-4 satellite replaced ESSA-2 and provided direct readout cloud-cover photography to ground stations worldwide using APT. The spacecraft was an 18-sided polygon, 42 inches in diameter, 22 inches high and weighed 290 pounds; it was made of aluminum alloy and stainless steel, then covered with 9100 solar cells. The solar cells served to charge the 63 nickel-cadmium batteries. The two cameras were mounted 180-degrees opposite each other along the side of the cylindrical craft. The "cartwheel" configuration of the TIROS-9 was selected as the orbital configuration of the ESSA satellites. Therefore, a camera could be pointed at some point on Earth every time the satellite rotated along its axis. The spacecraft operating system was the same as on the TIROS-9. The craft was placed in its planned Sun-synchronous 101-degree inclination retrograde orbit. The APT system was designed to transmit an image every 352 seconds, each photo covering a 2000-square mile area with 2-mile resolution. ESSA-4 was able to transmit two to three images daily to individual ground stations regardless of their location. ESSA-4 Stats: Launch Date: January 26, 1967 Operational Period: 465 days until deactivated by NASA on May 5, 1968 Launch Vehicle: Thrust Augmented Three-Stage Delta Launch Site: Vandenberg Air Force Base, CA Type: Weather Satellite 2018-11-14 15:41:57.0 [sritz] insert AltLabel (id: null category: null text: TOS-B language code: en); 2018-11-14 15:38:47.0 [sritz] update AltLabel (Environmental Science Services Administration Satellite 4); 2018-11-14 15:37:44.0 [sritz] insert AltLabel (id: null category: primary text: Environmental Science Services Administration 4 language code: en); 2018-10-30 17:02:05.0 [sritz] insert Definition (id: null text: The ESSA-4 satellite replaced ESSA-2 and provided direct readout cloud-cover photography to ground stations worldwide using APT. The spacecraft was an 18-sided polygon, 42 inches in diameter, 22 inches high and weighed 290 pounds; it was made of aluminum alloy and stainless steel, then covered with 9100 solar cells. The solar cells served to charge the 63 nickel-cadmium batteries. The two cameras were mounted 180-degrees opposite each other along the side of the cylindrical craft. The "cartwheel" configuration of the TIROS-9 was selected as the orbital configuration of the ESSA satellites. Therefore, a camera could be pointed at some point on Earth every time the satellite rotated along its axis. The spacecraft operating system was the same as on the TIROS-9. The craft was placed in its planned Sun-synchronous 101-degree inclination retrograde orbit. The APT system was designed to transmit an image every 352 seconds, each photo covering a 2000-square mile area with 2-mile resolution. ESSA-4 was able to transmit two to three images daily to individual ground stations regardless of their location. ESSA-4 Stats: Launch Date: January 26, 1967 Operational Period: 465 days until deactivated by NASA on May 5, 1968 Launch Vehicle: Thrust Augmented Three-Stage Delta Launch Site: Vandenberg Air Force Base, CA Type: Weather Satellite language code: en); 2018-10-30 15:44:06.0 [sritz] Insert Concept add broader relation (ESSA-4 [50992afe-f79e-47fc-a1a2-126dc2c42c9a,368199] - ESSA [65cb3e7c-d4d8-46df-a5fc-aec63e58e8df,345109]); STS-45 Studies of the sun, the upper reaches of Earth's atmosphere and astronomical objects using an international array of instruments in Atlantis' cargo bay will highlight Shuttle Mission STS-45. Atlantis will carry the Atmospheric Laboratory for Applications and Science-1 (ATLAS-1), 12 instruments from the United States, France, Germany, Belgium, Switzerland, the Netherlands and Japan, that will conduct 13 experiments to study the chemistry of the atmosphere, solar radiation, space plasma physics and ultraviolet astronomy. ATLAS-1 is planned to be the first of several ATLAS flights designed to cover an entire 11-year solar cycle, the regular period of energetic activity by the sun. Co- manifested with ATLAS-1 is the Shuttle Solar Backscatter Ultraviolet Instrument (SSBUV), which provides highly calibrated measurements of ozone to fine-tune measurements made by other NASA and NOAA satellites. [Summary provided by NASA] Group: Platform_Details Entry_ID: STS-45 Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Platform_Series_or_Entity: SPACE SHUTTLE Short_Name: STS-45 Long_Name: Space Transport System STS-45 End_Group Group: Synonymous_Platform_Names Short_Name: Atlantis End_Group Group: Orbit Orbit_Altitude: 160nm Orbit_Inclination: 57.0 degrees End_Group Creation_Date: 2008-01-29 Online_Resource: http://science.ksc.nasa.gov/shuttle/missions/sts-45/mission-sts-45.html Sample_Image: http://www.nasa.gov/images/content/134440main_sts-45-crew-sm.jpg Group: Platform_Logistics Launch_Date: 1992-03-24 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: NASA End_Group End_Group AS350-B2 2018-01-05 19:56:53.0 [sritz] Requested by NSIDC DAAC update AltLabel (Helicopter AS350-B2); 2018-01-05 19:55:55.0 [sritz] insert AltLabel (id: null category: primary text: Helicopter AS350-B3 language code: en); 2018-01-05 19:54:59.0 [sritz] Insert Concept add broader relation (AS350-B2 [50ce4651-516f-4b05-a5e0-864617ec26eb,310515] - Aircraft [227d9c3d-f631-402d-84ed-b8c5a562fc27,287509]); ASCENDS [Source: NASA ASCENDS, https://www-air.larc.nasa.gov/missions/ascends/] The Active Sensing of CO2 Emissions over Nights, Days, and Seasons (ASCENDS) mission objective is to make global atmospheric column carbon dioxide (CO2) measurements without a seasonal, latitudinal, or diurnal bias. The three science objectives are to (1) quantify global spatial distributions of atmospheric CO2 on scales of weather models in the 2010-2020 era; (2) quantify the current global spatial distribution of terrestrial and oceanic sources and sinks of CO2 on 1-degree grids at weekly resolution; and (3) provide a scientific basis for future projections of CO2 sources and sinks through data-driven enhancements of Earth system process modeling. Entry_ID: ASCENDS Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NASA Decadal Survey Short_Name: ASCENDS Long_Name: Active Sensing of CO2 Emissions over Nights, Days, and Seasons End_Group Group: Orbit Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2009-12-23 Online_Resource: https://www-air.larc.nasa.gov/missions/ascends/ Group: Platform_Logistics Primary_Sponsor: USA/NASA End_Group End_Group 2020-01-03 22:28:59.0 [sritz] update Definition ([Source: NASA ASCENDS, https://www-air.larc.nasa.gov/missions/ascends/] The Active Sensing of CO2 Emissions over Nights, Days, and Seasons (ASCENDS) mission objective is to make global atmospheric column carbon dioxide (CO2) measurements without a seasonal, latitudinal, or diurnal bias. The three science objectives are to (1) quantify global spatial distributions of atmospheric CO2 on scales of weather models in the 2010-2020 era; (2) quantify the current global spatial distribution of terrestrial and oceanic sources and sinks of CO2 on 1-degree grids at weekly resolution; and (3) provide a scientific basis for future projections of CO2 sources and sinks through data-driven enhancements of Earth system process modeling. Entry_ID: ASCENDS Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NASA Decadal Survey Short_Name: ASCENDS Long_Name: Active Sensing of CO2 Emissions over Nights, Days, and Seasons End_Group Group: Orbit Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2009-12-23 Online_Resource: https://www-air.larc.nasa.gov/missions/ascends/ Group: Platform_Logistics Primary_Sponsor: USA/NASA End_Group End_Group); 2020-01-03 22:26:32.0 [sritz] update Definition ([Source: NASA ASCENDS, https://www-air.larc.nasa.gov/missions/ascends/] Mission objectives: * Measure the number density of Carbon Dioxide (CO2) in the column of air beneath the aircraft * Measure length of the column using a laser altimeter * Measure ambient air pressure and temperature. ASCENDS will provide improved ability to predict/model long-term changes in the climate cycle based both on the understanding of the natural processes driving the variability of natural carbon sources and sinks, and on the transport of carbon through the atmosphere. Group: Platform_Details Entry_ID: ASCENDS Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NASA Decadal Survey Short_Name: ASCENDS Long_Name: Active Sensing of CO2 Emissions over Nights, Days, and Seasons End_Group Group: Orbit Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2009-12-23 Online_Resource: https://www-air.larc.nasa.gov/missions/ascends/ Group: Platform_Logistics Primary_Sponsor: USA/NASA End_Group End_Group); AWOS Automated Surface Observing Systems (ASOS) have been installed at over 850 locations throughout the U.S. The ASOS program is a joint effort of the National Weather Service (NWS), the Federal Aviation Administration (FAA), and the Department of Defense (DOD). ASOS systems serve as the nation's primary surface weather observing network. ASOS is designed to support weather forecast activities and aviation operations and, at the same time, support the needs of the meteorological, hydrological, and climatological research communities. ASOS Features: 1. Reports basic weather elements -sky conditions -visibility -basic present weather information (type and intensity for rain, snow, ect) -obstructions to vision (fog, haze) -pressure -ambient tempetature, dew point temperature -wind (direction, speed and character -precipitation accumulation -selected significant remarks [Source: NOAA] Group: Platform_Details Entry_ID: AWOS Group: Platform_Identification Platform_Category: In Situ Land-based Platforms Platform_Series_or_Entity: WEATHER STATIONS/NETWORKS Short_Name: AWOS Long_Name: Automated Weather Observing System End_Group Group: Synonymous_Platform_Names Short_Name: AWI/AWOS End_Group Group: Platform_Associated_Instruments Short_Name: AWS End_Group Creation_Date: 2007-12-05 Online_Resource: http://www.allweatherinc.com/aviation/awos_dom.html Sample_Image: http://www.allweatherinc.com/images/awos_img_wc.jpg End_Group INSAT-1A INSAT-1 Spacecraft Brief Description The Insat-1 satellite program incorporated two three-axis stabilized spacecraft in geostationary orbit (Insat-1A at 74 degrees E and Insat-1B at 94 degrees E) with a host of ground stations throughout India. The Insat-1A satellite, built by the Ford Aerospace and Communications Corporation, was designed to provide combined telecommunications, direct TV broadcast, and meteorological service to India's civilian community over a 7-year-in-orbit lifespan. The telecommunications package provided two-way, long distance telephone circuits and direct radio and TV broadcasting to the remotest areas of India. The meteorology package was composed of a scanning very-high-resolution, two-channel radiometer (VHRR) to provide full-frame, full-earth coverage every 30 minutes. The visual channel (0.55-0.75 micrometer) had a 2.75-km resolution while the IR channel (10.5-12.5 micrometers) had an 11-km resolution. Using the Insat TV capability, early warnings of impending disasters (i.e., floods, storms, etc.) could directly reach the civilian population, even in remote areas. The Insat-1A also had a data channel for relaying meteorological, hydrological, and oceanographic data from unattended land-based or ocean-based data collection and transmission platforms. *Insat-1A was abandoned in September 1983 when its attitude control propellant was exhausted* Auxiliary Information Launch Date and Time : 1982-04-10 06:47:00 Epoch Date and Time : 1982-04-11 Orbit Type : Geocentric Apogee(km) : 35784. Perigee(km) : 225. Inclination : 28.1 Date of last update : 1998-10-07 More information about the INSAT Satellite Series is available at: "http://www.bharat-rakshak.com/SPACE/space-satellite3.html" Group: Platform_Details Entry_ID: INSAT-1A Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: INSAT (Indian National Satellite) Short_Name: INSAT-1A Long_Name: Indian National Satellite-1A End_Group Group: Synonymous_Platform_Names Short_Name: INSAT-1A End_Group Group: Platform_Associated_Instruments Short_Name: VHRR End_Group Group: Orbit Orbit_Inclination: 28.1 Perigee: 225 km Apogee: 35784 km End_Group Creation_Date: 2007-10-04 Online_Resource: http://www.bharat-rakshak.com/SPACE/space-satellite3.html Sample_Image: http://www.bharat-rakshak.com/SPACE/Images/Insat-1A.jpg Group: Platform_Logistics Launch_Date: 1982-04-10 Primary_Sponsor: India End_Group End_Group 2016-06-09 14:49:01.0 [epneff] added altLabel insert AltLabel (id: null text: INSAT-1 language code: en); PLEIADES Pleiades is the optical component of the ORFEO system developed in cooperation with Italy. The Pleiades system is an optical observation system with a metric resolution designed to offer a high acquisition capability with a revisit lower than 24 hours to satisfy both civilian and military needs. Moreover, to meet the needs for detailed mapping, especially in urban areas and to complement aerial photography, Pleiades will offer instantaneous stereoscopic acquisition and the capability to cover large areas. For applications such as forestry, geology and marine environment, and using its spectral characteristics and its tree-dimensional characterization of surfaces, Pleiades should complete the information supplied by other sensors, such as Spot 5, by offering information with a better spatial resolution. Lastly, to meet the defence and civil security missions, the Pleiades system is expected to: Supply the information in a very short time-frame (usually less than 24 hours). Ensure to defence users a priority in the daily programming of the 50 acquisition requests. Ensure to defence users the confidentiality of their requests and communications. Enable priority acquisitions on a predefined area with a "crisis" mode implementation. For this, the Pleiades system is constituted of a constellation of two optical satellites (visible and near infrared domain) on a Sun-synchronous orbit at 694 km. This number of satellites is essential to guarantee the accessibility and revisit frequency required to operationally answer to defence and civil security missions. With its two agile satellites, the Pleiades system will offer: a daily access to every point on Earth, a resolution of 0.7 m in vertical viewing in panchromatic, four spectral bands (blue, green, red and near infrared) with a resolution of 2.8 m in vertical viewing, a field of view of 20 km, an acquisition of a 120 km x 120 km image mosaic in the same orbit, the acquisition of nearly instantaneous stereoscopic couples (or even triplet) of 20 km by 300 km, the acquisition of cloud free images covering 2 500 000 km² per year, a very accurate localization of the images (<1 m with ground control points) enabling an optimal use of the data in the Geographical Information Systems (GIS). Moreover, the great agility of the satellites will enable to minimize the programming conflicts, particularly during the dual use, and to better meet the users' needs. 2018-06-14 13:02:52.0 [mmorahan] insert Definition (id: null text: Pleiades is the optical component of the ORFEO system developed in cooperation with Italy. The Pleiades system is an optical observation system with a metric resolution designed to offer a high acquisition capability with a revisit lower than 24 hours to satisfy both civilian and military needs. Moreover, to meet the needs for detailed mapping, especially in urban areas and to complement aerial photography, Pleiades will offer instantaneous stereoscopic acquisition and the capability to cover large areas. For applications such as forestry, geology and marine environment, and using its spectral characteristics and its tree-dimensional characterization of surfaces, Pleiades should complete the information supplied by other sensors, such as Spot 5, by offering information with a better spatial resolution. Lastly, to meet the defence and civil security missions, the Pleiades system is expected to: Supply the information in a very short time-frame (usually less than 24 hours). Ensure to defence users a priority in the daily programming of the 50 acquisition requests. Ensure to defence users the confidentiality of their requests and communications. Enable priority acquisitions on a predefined area with a "crisis" mode implementation. For this, the Pleiades system is constituted of a constellation of two optical satellites (visible and near infrared domain) on a Sun-synchronous orbit at 694 km. This number of satellites is essential to guarantee the accessibility and revisit frequency required to operationally answer to defence and civil security missions. With its two agile satellites, the Pleiades system will offer: a daily access to every point on Earth, a resolution of 0.7 m in vertical viewing in panchromatic, four spectral bands (blue, green, red and near infrared) with a resolution of 2.8 m in vertical viewing, a field of view of 20 km, an acquisition of a 120 km x 120 km image mosaic in the same orbit, the acquisition of nearly instantaneous stereoscopic couples (or even triplet) of 20 km by 300 km, the acquisition of cloud free images covering 2 500 000 km² per year, a very accurate localization of the images (<1 m with ground control points) enabling an optimal use of the data in the Geographical Information Systems (GIS). Moreover, the great agility of the satellites will enable to minimize the programming conflicts, particularly during the dual use, and to better meet the users' needs. language code: en); 2018-06-14 13:00:44.0 [mmorahan] Insert Concept add narrower relation (PLEIADES [516a9bb2-0171-4ad2-8d4f-3f7d1219d393,344967] - Pleiades-1B [92bdb34f-5df0-498d-b3c9-477ff3a1f80a,367719]); 2018-06-14 13:00:05.0 [mmorahan] Insert Concept add narrower relation (PLEIADES [516a9bb2-0171-4ad2-8d4f-3f7d1219d393,344967] - Pleiades-1A [a0b1f332-41b9-4eec-8a9e-67778193a679,367715]); 2015-12-08 13:10:23.0 [mpmorahan] Insert Concept add broader relation (PLEIADES [516a9bb2-0171-4ad2-8d4f-3f7d1219d393,158543] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,143415]); TIROS-N TIROS-N was launched in October 1978 and was a third generation operational meteorological satellite for use in the National Operational Environmental Satellite System (NOESS) and for the support of the Global Atmospheric Research Program (GARP) during 1978-84. The satellite design provided an economical and stable sun-synchronous platform for advanced operational instruments to measure the earth's atmosphere, its surface and cloud cover, and the near-space environment. The satellite was based upon the Block 5D spacecraft bus developed for the U.S. Air Force, and it was capable of maintaining an earth-pointing accuracy of better than plus or minus 0.1 degree with a motion rate of less than 0.035 degree/second. Primary sensors included an Advanced Very High Resolution Radiometer (AVHRR) and a TIROS Operational Vertical Sounder (TOVS). Secondary experiments consisted of a Space Environment Monitor (SEM) and a Data Collection System (DCS). __________ Taken from the NSSDC System for Information Retrieval and Storage (SIRS). For more information contact the NSSDC Coordinated Request and User Support Office, 301-286-6695 (NASA Goddard Space Flight Center, Code 933.4, Greenbelt, Maryland 20771, USA, "http://nssdc.gsfc.nasa.gov/"). Schwalb, A., 'The TIROS-N/NOAA A-G Satellite Series,' NOAA Tech. Mem., NESS 95, 1978. Group: Platform_Details Entry_ID: TIROS-N Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: TIROS Short_Name: TIROS-N Long_Name: Television Infrared Observation Satellite-N End_Group Group: Synonymous_Platform_Names Short_Name: TIROS-N End_Group Group: Platform_Associated_Instruments Short_Name: TOVS Short_Name: AVHRR End_Group Group: Orbit Orbit_Inclination: 98.70 deg Period: 101.70 min Perigee: 829 km Apogee: 845 km End_Group Creation_Date: 2007-11-14 Online_Resource: http://nssdc.gsfc.nasa.gov/ Sample_Image: http://www.nasm.si.edu/exhibitions/lae/images/tirosn.jpg Group: Platform_Logistics Launch_Date: 1978-10-13 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: NASA End_Group End_Group SEAGLIDER A long-range Autonomous Underwater Vehicle (AUV) for oceanographic research. A suite of miniaturized physical and bio-optical instruments, which measure in situ water properties including temperature, salinity, and the absorption and scattering of light in the water column, have been and are currently under development for placement in the glider&#039;s science payload bay. Seagliders fly through the water with extremely modest energy requirements using changes in buoyancy for thrust coupled with a stable, low-drag, hydrodynamic shape. Designed to operate at depths up to 1000 meters, the hull compresses as it sinks, matching the compressibility of seawater. For further description see http://www.apl.washington.edu/projects/seaglider/summary.html. Group: Platform_Details Entry_ID: SEAGLIDER Group: Platform_Identification Platform_Category: In Situ Ocean-based Platforms Short_Name: SEAGLIDER End_Group Group: Synonymous_Platform_Names Short_Name: Seaglider End_Group Creation_Date: 2007-12-13 Online_Resource: http://www.apl.washington.edu/projects/seaglider/summary.html End_Group NOAA-2 NOAA-2 was launched in October 1972 and was the first in a series of reconfigured ITOS satellites launched with new meteorological sensors onboard to expand the operational capability of the ITOS system. NOAA-2 was not equipped with conventional TV cameras. It was the first operational weather satellite to rely solely upon radiometric imaging to obtain cloudcover data. The primary objective was to provide global daytime and nighttime direct readout real-time cloudcover data on a daily basis. The sun-synchronous spacecraft was also capable of supplying global atmospheric temperature soundings and very high resolution infrared cloudcover data for selected areas in either a direct readout or a tape-recorder mode. A secondary objective was to obtain global solar-proton flux data on a real-time daily basis. The sensors were mounted on the satellite baseplate with their optical axes directed vertically earthward. The nearly cubical spacecraft measured 1 by 1 by 1.2 m. The satellite was equipped with three curved solar panels that were folded during launch and deployed after orbit was achieved. Each panel measured over 4.2 m in length when unfolded and was covered with approximately 3500 solar cells measuring 2 by 2 cm. The dynamics and attitude control system maintained desired spacecraft orientation through gyroscopic principles incorporated into the satellite design. Earth orientation of the satellite body was maintained by taking advantage of the precession induced from a momentum flywheel so that the satellite body precession rate of one revolution per orbit provided the desired 'earth-looking' attitude. Minor adjustments in attitude and orientation were made by means of magnetic coils and by varying the speed of the momentum flywheel. The primary sensors consisted of a Very High Resolution Radiometer (VHRR), Vertical Temperature Profile Radiometer (VTPR), and a Scanning Radiometer (SR). The spacecraft operated satisfactorily until March 18, 1974, when the VTPR failed. NOAA-2 was then placed in a marginal standby mode from March 19 to July 1, 1974. It was then used as the operational NOAA satellite until October 16, 1974, when it was again placed in a marginal standby mode. The spacecraft was deactivated on January 30, 1975. More Information about NOAA-2: https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1972-082A __________ Taken from the NSSDC System for Information Retrieval and Storage (SIRS). For more information contact the NSSDC Coordinated Request and User Support Office, 301-286-6695 (NASA Goddard Space Flight Center, Code 933.4, Greenbelt, Maryland 20771, USA, https://nssdca.gsfc.nasa.gov/). Group: Platform_Details Entry_ID: NOAA-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NOAA POES (Polar Orbiting Environmental Satellites) Short_Name: NOAA-2 Long_Name: National Oceanic & Atmospheric Administration-2 End_Group Group: Platform_Associated_Instruments Short_Name: IKAR End_Group Creation_Date: 2007-11-08 Online_Resource: https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1972-082A Group: Platform_Logistics Launch_Date: 1972-10-01 Primary_Sponsor: NASA End_Group End_Group 2019-11-22 22:44:18.0 [sritz] update Definition (NOAA-2 was launched in October 1972 and was the first in a series of reconfigured ITOS satellites launched with new meteorological sensors onboard to expand the operational capability of the ITOS system. NOAA-2 was not equipped with conventional TV cameras. It was the first operational weather satellite to rely solely upon radiometric imaging to obtain cloudcover data. The primary objective was to provide global daytime and nighttime direct readout real-time cloudcover data on a daily basis. The sun-synchronous spacecraft was also capable of supplying global atmospheric temperature soundings and very high resolution infrared cloudcover data for selected areas in either a direct readout or a tape-recorder mode. A secondary objective was to obtain global solar-proton flux data on a real-time daily basis. The sensors were mounted on the satellite baseplate with their optical axes directed vertically earthward. The nearly cubical spacecraft measured 1 by 1 by 1.2 m. The satellite was equipped with three curved solar panels that were folded during launch and deployed after orbit was achieved. Each panel measured over 4.2 m in length when unfolded and was covered with approximately 3500 solar cells measuring 2 by 2 cm. The dynamics and attitude control system maintained desired spacecraft orientation through gyroscopic principles incorporated into the satellite design. Earth orientation of the satellite body was maintained by taking advantage of the precession induced from a momentum flywheel so that the satellite body precession rate of one revolution per orbit provided the desired 'earth-looking' attitude. Minor adjustments in attitude and orientation were made by means of magnetic coils and by varying the speed of the momentum flywheel. The primary sensors consisted of a Very High Resolution Radiometer (VHRR), Vertical Temperature Profile Radiometer (VTPR), and a Scanning Radiometer (SR). The spacecraft operated satisfactorily until March 18, 1974, when the VTPR failed. NOAA-2 was then placed in a marginal standby mode from March 19 to July 1, 1974. It was then used as the operational NOAA satellite until October 16, 1974, when it was again placed in a marginal standby mode. The spacecraft was deactivated on January 30, 1975. More Information about NOAA-2: https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1972-082A __________ Taken from the NSSDC System for Information Retrieval and Storage (SIRS). For more information contact the NSSDC Coordinated Request and User Support Office, 301-286-6695 (NASA Goddard Space Flight Center, Code 933.4, Greenbelt, Maryland 20771, USA, https://nssdca.gsfc.nasa.gov/). Group: Platform_Details Entry_ID: NOAA-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NOAA POES (Polar Orbiting Environmental Satellites) Short_Name: NOAA-2 Long_Name: National Oceanic & Atmospheric Administration-2 End_Group Group: Platform_Associated_Instruments Short_Name: IKAR End_Group Creation_Date: 2007-11-08 Online_Resource: https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1972-082A Group: Platform_Logistics Launch_Date: 1972-10-01 Primary_Sponsor: NASA End_Group End_Group); 2019-11-22 22:30:09.0 [sritz] update Definition (NOAA-2 was launched in October 1972 and was the first in a series of reconfigured ITOS satellites launched with new meteorological sensors onboard to expand the operational capability of the ITOS system. NOAA-2 was not equipped with conventional TV cameras. It was the first operational weather satellite to rely solely upon radiometric imaging to obtain cloudcover data. The primary objective was to provide global daytime and nighttime direct readout real-time cloudcover data on a daily basis. The sun-synchronous spacecraft was also capable of supplying global atmospheric temperature soundings and very high resolution infrared cloudcover data for selected areas in either a direct readout or a tape-recorder mode. A secondary objective was to obtain global solar-proton flux data on a real-time daily basis. The sensors were mounted on the satellite baseplate with their optical axes directed vertically earthward. The nearly cubical spacecraft measured 1 by 1 by 1.2 m. The satellite was equipped with three curved solar panels that were folded during launch and deployed after orbit was achieved. Each panel measured over 4.2 m in length when unfolded and was covered with approximately 3500 solar cells measuring 2 by 2 cm. The dynamics and attitude control system maintained desired spacecraft orientation through gyroscopic principles incorporated into the satellite design. Earth orientation of the satellite body was maintained by taking advantage of the precession induced from a momentum flywheel so that the satellite body precession rate of one revolution per orbit provided the desired 'earth-looking' attitude. Minor adjustments in attitude and orientation were made by means of magnetic coils and by varying the speed of the momentum flywheel. The primary sensors consisted of a Very High Resolution Radiometer (VHRR), Vertical Temperature Profile Radiometer (VTPR), and a Scanning Radiometer (SR). The spacecraft operated satisfactorily until March 18, 1974, when the VTPR failed. NOAA-2 was then placed in a marginal standby mode from March 19 to July 1, 1974. It was then used as the operational NOAA satellite until October 16, 1974, when it was again placed in a marginal standby mode. The spacecraft was deactivated on January 30, 1975. More Information on the NOAA satellite series: https://www.noaa.gov/satellites __________ Taken from the NSSDC System for Information Retrieval and Storage (SIRS). For more information contact the NSSDC Coordinated Request and User Support Office, 301-286-6695 (NASA Goddard Space Flight Center, Code 933.4, Greenbelt, Maryland 20771, USA, https://nssdca.gsfc.nasa.gov/). Group: Platform_Details Entry_ID: NOAA-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NOAA POES (Polar Orbiting Environmental Satellites) Short_Name: NOAA-2 Long_Name: National Oceanic & Atmospheric Administration-2 End_Group Group: Platform_Associated_Instruments Short_Name: IKAR End_Group Creation_Date: 2007-11-08 Online_Resource: https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1972-082A Group: Platform_Logistics Launch_Date: 1972-10-01 Primary_Sponsor: NASA End_Group End_Group); delete Resource (null); HINOTORI The main objective of the HINOTORI mission was the detailed study of solar flares during solar maximum. Principal investigations were (1) imaging of solar flare X rays in the range 10 to 40 keV by means of rotating modulation collimators and (2) spectroscopy of X-ray emission lines from highly ionized iron in solar flares in the range 1.7 to 2.0 A by means of a Bragg spectrometer. Wavelength scanning was achieved by the spacecraft revolution, with an offset pointing of the spin axis with respect to the sun. Investigations (1) and (2) each had a time resolution of 6 s. In addition, the following investigations were included: three solar flare X-ray monitors that recorded the time profile and spectrum of the X-ray flares in the range 2 to 20 keV, a solar flare gamma-ray detector for the range 0.2 to 9.0 MeV, a particle detector that monitored electron flux above 100 keV, and plasma probes for the measurement of electron density and temperature. Information provided by http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1981-017A Group: Platform_Details Entry_ID: HINOTORI Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Short_Name: HINOTORI End_Group Group: Synonymous_Platform_Names Short_Name: ASTRO-A Short_Name: Astronomical Satellite-A Short_Name: 12307 End_Group Group: Platform_Associated_Instruments Short_Name: PARTICLE DETECTORS Short_Name: BCS End_Group Creation_Date: 2007-08-13 Online_Resource: http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1981-017A Sample_Image: http://jda.jaxa.jp/jda/get_image.php?f_id=1414&type=L Group: Platform_Logistics Launch_Date: 1981-02-21 Primary_Sponsor: Institute of Space and Aeronautical Science, U of Tokyo/Japan End_Group End_Group AEROS OGO-3 The Orbiting Geophysical Observatory 3 (OGO 3) was launched on 7 June 1966 and put into orbit of 295 x 122,219 km at 31 degrees inclination. All 21 experiments returned good data. At the time, this was the largest experimental complement ever put into orbit. There were 4 cosmic ray instruments (1 of which included a gamma-ray spectrometer), 4 plasma, 2 trapped radiation, 2 magnetic fields, 5 ionosphere, 3 radio/optical, and 1 micrometeoroid detectors. Again, the GSFC positron search and gamma-ray spectrometer was included. The experiment was essentially identical to what was flown on OGO 1, with the PMTs being replaced by an improved variety. This time, the experiment was successful in achieving all of its objectives. OGO 3 maintained 3-axis stabilization for 46 days. At that point, an attitude controller failed and the spacecraft was put into a spin on 23 July 1966. The spin period varied from 90-125 seconds. By June 1969, data acquisition was limited to 50% of the orbital path. Routine operation was discontinued on 1 December 1969, and complete termination occurred on 29 February 1972. [Summary provided by NASA.] Group: Platform_Details Entry_ID: OGO-3 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: OGO (Orbiting Geophysical Observatory) Short_Name: OGO-3 Long_Name: Orbiting Geophysical Observatory-3 End_Group Group: Synonymous_Platform_Names Short_Name: EOGO 3 Short_Name: OGO-B Short_Name: 02195 End_Group Group: Platform_Associated_Instruments Short_Name: GAMMA RAY SPECTROMETERS End_Group Group: Orbit Orbit_Inclination: 31 degrees Period: 2913.0 minutes Perigee: 295.0 km Apogee: 122219.0 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-02-13 Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1966-049A Sample_Image: http://heasarc.gsfc.nasa.gov/Images/ogo/ogo.gif Group: Platform_Logistics Launch_Date: 1966-06-07 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: NASA End_Group End_Group GOES-14 The GOES-O satellite lifted off from Launch Complex 37 at Cape Canaveral Air Force Station in Florida at 6:51 p.m. EDT [2009-06-27] atop a Delta IV rocket. From a position about 22,300 miles above Earth, the advanced weather satellite will keep an unblinking eye on atmospheric conditions in the Eastern United States and Atlantic Ocean. Geostationary Operational Environmental Satellite (GOES)-O represents a continuation of the newest generation of environmental satellites built by Boeing for the National Oceanic and Atmospheric Administration (NOAA) under the technical guidance and project management of NASA's Goddard Space Flight Center, Greenbelt, MD. GOES satellites provide the familiar weather pictures seen on United States television newscasts every day. The GOES imaging and sounding instruments (built by ITT) feature flexible scans for small-scale area viewing in regions of the visible and infrared spectrum allowing meteorologists to improve short-term forecasts. GOES provides nearly continuous imaging and sounding, which allow forecasters to better measure changes in atmospheric temperature and moisture distributions and hence increase the accuracy of their forecasts. GOES environmental information is used for a host of applications, including weather monitoring and prediction models, ocean temperatures and moisture locations, climate studies, cryosphere (ice, snow, glaciers) detection and extent, land temperatures and crop conditions, and hazards detection. The GOES-O&P Imagers have improved resolution in the 13 micrometer channel from 8 km to 4 km. The finer spatial resolution allows an improved cloud-top product, height of atmospheric motion vectors and volcanic ash detection. GOES-O continues the improved image navigation and registration, additional power and fuel lifetime capability, space weather, solar x-ray imaging, search and rescue, and communication services as provided on GOES-13. GOES-P is also in ground storage following the completion of environmental testing and is prepared for an April 2009 launch readiness with a July 2010, engineering handover date requirement. 2017-09-01 16:58:23.0 [sritz] update Definition (The GOES-O satellite lifted off from Launch Complex 37 at Cape Canaveral Air Force Station in Florida at 6:51 p.m. EDT [2009-06-27] atop a Delta IV rocket. From a position about 22,300 miles above Earth, the advanced weather satellite will keep an unblinking eye on atmospheric conditions in the Eastern United States and Atlantic Ocean. Geostationary Operational Environmental Satellite (GOES)-O represents a continuation of the newest generation of environmental satellites built by Boeing for the National Oceanic and Atmospheric Administration (NOAA) under the technical guidance and project management of NASA's Goddard Space Flight Center, Greenbelt, MD. GOES satellites provide the familiar weather pictures seen on United States television newscasts every day. The GOES imaging and sounding instruments (built by ITT) feature flexible scans for small-scale area viewing in regions of the visible and infrared spectrum allowing meteorologists to improve short-term forecasts. GOES provides nearly continuous imaging and sounding, which allow forecasters to better measure changes in atmospheric temperature and moisture distributions and hence increase the accuracy of their forecasts. GOES environmental information is used for a host of applications, including weather monitoring and prediction models, ocean temperatures and moisture locations, climate studies, cryosphere (ice, snow, glaciers) detection and extent, land temperatures and crop conditions, and hazards detection. The GOES-O&P Imagers have improved resolution in the 13 micrometer channel from 8 km to 4 km. The finer spatial resolution allows an improved cloud-top product, height of atmospheric motion vectors and volcanic ash detection. GOES-O continues the improved image navigation and registration, additional power and fuel lifetime capability, space weather, solar x-ray imaging, search and rescue, and communication services as provided on GOES-13. GOES-P is also in ground storage following the completion of environmental testing and is prepared for an April 2009 launch readiness with a July 2010, engineering handover date requirement.); 2017-09-01 16:57:27.0 [sritz] insert Definition (id: null text: The GOES-O satellite lifted off from Launch Complex 37 at Cape Canaveral Air Force Station in Florida at 6:51 p.m. EDT [2009-06-27] atop a Delta IV rocket. From a position about 22,300 miles above Earth, the advanced weather satellite will keep an unblinking eye on atmospheric conditions in the Eastern United States and Atlantic Ocean. [Source: GOES project Office NASA Goddard Space Flight Center, http://goespoes.gsfc.nasa.gov/goes/spacecraft/goes_o_spacecraft.html ] Geostationary Operational Environmental Satellite (GOES)-O represents a continuation of the newest generation of environmental satellites built by Boeing for the National Oceanic and Atmospheric Administration (NOAA) under the technical guidance and project management of NASA's Goddard Space Flight Center, Greenbelt, MD. GOES satellites provide the familiar weather pictures seen on United States television newscasts every day. The GOES imaging and sounding instruments (built by ITT) feature flexible scans for small-scale area viewing in regions of the visible and infrared spectrum allowing meteorologists to improve short-term forecasts. GOES provides nearly continuous imaging and sounding, which allow forecasters to better measure changes in atmospheric temperature and moisture distributions and hence increase the accuracy of their forecasts. GOES environmental information is used for a host of applications, including weather monitoring and prediction models, ocean temperatures and moisture locations, climate studies, cryosphere (ice, snow, glaciers) detection and extent, land temperatures and crop conditions, and hazards detection. The GOES-O&P Imagers have improved resolution in the 13 micrometer channel from 8 km to 4 km. The finer spatial resolution allows an improved cloud-top product, height of atmospheric motion vectors and volcanic ash detection. GOES-O continues the improved image navigation and registration, additional power and fuel lifetime capability, space weather, solar x-ray imaging, search and rescue, and communication services as provided on GOES-13. GOES-P is also in ground storage following the completion of environmental testing and is prepared for an April 2009 launch readiness with a July 2010, engineering handover date requirement. language code: en); 2017-09-01 16:47:13.0 [sritz] Insert Concept add broader relation (GOES-14 [530c0bf3-28b9-4cb7-ad4e-979ad7444933,310127] - GOES [6e332c25-caeb-4917-afb6-af757bcecd72,310071]); NOAA-16 NOAA-16 previously NOAA-L was launched on Spetember 21, 2000 on a Titan2 launch vehicle. General Information: Designation - 26536 / 00055A Launch date - 21 Sep 2000 Country of origin - United States Mission - Meteorology Perigee/Apogee - 870 km Inclination - 98.70 Period - 102 min Launch vehicle - Titan 2 #22 More Information: "http://www.tbs-satellite.com/tse/online/sat_noaa_16.html" "http://www.osd.noaa.gov/" Track NOAA-16: "http://liftoff.msfc.nasa.gov/RealTime/JTrack/" Group: Platform_Details Entry_ID: NOAA-16 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NOAA POES (Polar Orbiting Environmental Satellites) Short_Name: NOAA-16 Long_Name: National Oceanic & Atmospheric Administration-16 End_Group Group: Synonymous_Platform_Names Short_Name: NOAA-L End_Group Group: Platform_Associated_Instruments Short_Name: AMSU-B Short_Name: AMSU-A End_Group Group: Orbit Orbit_Inclination: 99 deg Period: 102.1 min End_Group Creation_Date: 2007-11-08 Online_Resource: http://www.oso.noaa.gov/poesstatus/spacecraftStatusSummary.asp?spacecraft=16 Sample_Image: http://www.noaanews.noaa.gov/stories/images/noaa-l.jpg Group: Platform_Logistics Launch_Date: 2000-09-21 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: NASA End_Group End_Group NCEP-GFS 2015-03-05 16:05:36.0 [epneff] insert AltLabel (id: null text: NCEP Global Forecast System language code: en); 2015-03-05 16:05:17.0 [epneff] Insert Concept add broader relation (NCEP-GFS [53b3429a-d915-4d1c-b600-bf3e37874839,106787] - Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,73395]); OKEAN-O OKEAN - Russian-Ukrainian mission, data were collected during OKEAN scientific program from board of OKEAN-O1 satellite, processed in NC OMZ (Scientific Center of Operational Monitoring of Earth of Russian Aerospace Agency), and stored in IRE CPSSI (Center of Processing and Storing the Space Information in Institute of Radioengineering and Electronics of Russian Academy of Sciences). MSU-SK - visible and IR scanner with medium resolution, optico-mechanical scanner. MSU-SK stands for Multispectral Scanners with Conical Scanning. MSU-SK has 6 spectral channels in 0.5-0.6, 0.6-0.7, 0.7-0.8, 0.8-1.1, 3.5-4.1, and 10.0-12.5 mkm spectral bands. Its spatial resolutions are 157x245 m (for visible and near infrared channels in 0.5-1.1 mkm band ) and 590x820 m (for infrared channels above 3.5 mkm). Group: Platform_Details Entry_ID: OKEAN-O Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: OKEAN-O Long_Name: Ukranian-Russian Ocean Remote Sensing System End_Group Group: Synonymous_Platform_Names Short_Name: OKEAN-O End_Group Group: Orbit Orbit_Inclination: 98 deg Perigee: 660 km Apogee: 663 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-11-20 Online_Resource: http://www.astronautix.com/craft/okeano.htm Sample_Image: http://www.astronautix.com/graphics/o/okeano2.jpg Group: Platform_Logistics Launch_Date: 1999-07-17 Launch_Site: Baikonur Cosmodrome, Tyuratam, Russia Primary_Sponsor: Russian-Ukrainian End_Group End_Group EOS (Earth Observing System) SCISAT-1/ACE Launched on August 12, 2003, SCISAT helps a team of Canadian and international scientists improve their understanding of the depletion of the ozone layer, with a special emphasis on the changes occurring over Canada and in the Arctic. SCISAT focuses its attention in the stratosphere, where the ozone layer is located. SCISAT is providing the most accurate measurements to date of chemicals that affect ozone, which blocks the sun's biologically damaging ultraviolet radiation and prevents most of it from reaching the Earth's surface. http://www.nasa.gov/missions/earth/scisat.html Group: Platform_Details Entry_ID: SCISAT-1/ACE Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: SCISAT-1/ACE Long_Name: Atmospheric Chemistry Experiment End_Group Group: Synonymous_Platform_Names Short_Name: SCISAT End_Group Group: Orbit Orbit_Type: HEO > Highly Elliptical Orbit End_Group Creation_Date: 2007-11-28 Online_Resource: http://earth.esa.int/SCISAT-1ACE/ Online_Resource: http://www.nasa.gov/missions/earth/scisat.html Sample_Image: http://www.space.gc.ca/asc/img/scisat_061213_thum.jpg Group: Platform_Logistics Launch_Date: 2003-08-12 Primary_Sponsor: Canada/CSA End_Group End_Group IRIS-GSN The IRIS Global Seismographic Network (GSN) is one of the four major components of the IRIS Consortium. The goal of the GSN is to deploy 128 permanent seismic recording stations uniformly over the earth's surface. Stations: As of 2003 the IRIS GSN was made up of over 128 stations with affiliations to USGS, UCSD/IDA, GEOFON, Pacific21, NCDSN, GEOSCOPE, MedNet, BGR, BFO, USNSN, BDSN, TriNet, AFTAC and several other national and international networks. Eight new stations are planned for completion in 2003-2005. The IRIS GSN stations continuously record seismic data from very broad band seismometers at 20 samples per second, and to provide for high-frequency (40 sps) and strong-motion (1 and 100 sps) sensors where scientifically warranted. It is also the goal of the GSN to provide for real-time access to its data via Internet or satellite. Over 75% of the IRIS GSN stations meet this goal. More information at"http://www.iris.edu/about/GSN/" [Source: IRIS] SENTINEL-3A Mission Details Launch Date: Sentinel-3A - 16 February 2016 Sentinel-3B - 25 April 2018 Operational lifepsan: 7 years (With consumables for 12) Mission objectives: Measuring sea-surface topography, sea-surface height and significant wave height Measuring ocean and land-surface temperature Measuring ocean and land-surface colour Monitoring sea and land ice topography Sea-water quality and pollution monitoring Inland water monitoring, including rivers and lakes Aid ocean forecasts with acquired data Climate monitoring and modelling Land-use change monitoring Forest cover mapping Fire detection Weather forecasting Measuring Earth's thermal radiation for atmospheric applications Mission Orbit: Orbit Type: Sun-synchronous Orbit Height: 814 km Inclination: 98.6o Repeat Cycle: 27 days Payload: OLCI (Ocean and Land Colour Instrument) SLSTR (Sea and Land Surface Temperature Radiometer) SRAL (Synthetic Aperture Radar Altimeter) MWR (Microwave Radiometer) DORIS LRR (Laser Retroreflector) GNSS (Global Navigation Satellite System) Resolution and Swath Width: OLCI - 1270 km SLSTR - 1420 km Configuration: In addition to the observation instruments, the Sentinel-3 spacecraft will carry the GNSS (Global Navigation Satellite System) and LRR (Laser Retro Reflector) instruments. GNSS will provide precise orbit determination and can track multiple satellites simultaneously. LRR will be used to accurately locate the satellite in orbit using a laser ranging system. The dimensions of the craft are: 3.7 x 2.2 x 2.2 m with a weight (at time of launch) of 1250 kg. Launch vehicle: Rockot (Sentinel-3A and -3B) Operator: EUMETSAT Contractors: Thales Alenia Space is the prime contractor, responsible for constructing the spacecraft and the SRAL instrument, as well as contributing to the supply of the SLSTR instrument. Many European companies are involved in supplying the SLSTR instrument, including SELEX Galileo, RAL (Rutherford Appleton Laboratory), Jena-Optronik, Thales Alenia Space, ABSL and ESA-ESTEC. EADS CASA Espacio is contracted to provide the MWR instrument. CNES is contracted to provide the DORIS instrument. Eurockot and Arianespace are contracted to launch the spacecraft. 2019-02-22 19:10:03.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: 7204c4d5-b7d0-41af-ba90-61d47c6dc610 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 7b6e3162-1314-4441-b33a-e2b68ae85bcd relationship type: null relationship value: null generated by: null); 2019-02-22 19:08:42.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: 9bfd9ff7-b838-4834-bd47-0127384c79f7 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: be02e58f-ce2f-448f-8a81-74bcc4eb7056 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: d81fc4e3-c0b4-4205-82b2-ef2161c169a3 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 65ed042c-df53-4afb-8b6a-1ea16958015d relationship type: null relationship value: null generated by: null); 2018-11-05 12:56:19.0 [mmorahan] Rename Concept update PrefLabel (SENTINEL-3A); 2018-11-05 12:55:14.0 [mmorahan] insert Definition (id: null text: Mission Details Launch Date: Sentinel-3A - 16 February 2016 Sentinel-3B - 25 April 2018 Operational lifepsan: 7 years (With consumables for 12) Mission objectives: Measuring sea-surface topography, sea-surface height and significant wave height Measuring ocean and land-surface temperature Measuring ocean and land-surface colour Monitoring sea and land ice topography Sea-water quality and pollution monitoring Inland water monitoring, including rivers and lakes Aid ocean forecasts with acquired data Climate monitoring and modelling Land-use change monitoring Forest cover mapping Fire detection Weather forecasting Measuring Earth's thermal radiation for atmospheric applications Mission Orbit: Orbit Type: Sun-synchronous Orbit Height: 814 km Inclination: 98.6o Repeat Cycle: 27 days Payload: OLCI (Ocean and Land Colour Instrument) SLSTR (Sea and Land Surface Temperature Radiometer) SRAL (Synthetic Aperture Radar Altimeter) MWR (Microwave Radiometer) DORIS LRR (Laser Retroreflector) GNSS (Global Navigation Satellite System) Resolution and Swath Width: OLCI - 1270 km SLSTR - 1420 km Configuration: In addition to the observation instruments, the Sentinel-3 spacecraft will carry the GNSS (Global Navigation Satellite System) and LRR (Laser Retro Reflector) instruments. GNSS will provide precise orbit determination and can track multiple satellites simultaneously. LRR will be used to accurately locate the satellite in orbit using a laser ranging system. The dimensions of the craft are: 3.7 x 2.2 x 2.2 m with a weight (at time of launch) of 1250 kg. Launch vehicle: Rockot (Sentinel-3A and -3B) Operator: EUMETSAT Contractors: Thales Alenia Space is the prime contractor, responsible for constructing the spacecraft and the SRAL instrument, as well as contributing to the supply of the SLSTR instrument. Many European companies are involved in supplying the SLSTR instrument, including SELEX Galileo, RAL (Rutherford Appleton Laboratory), Jena-Optronik, Thales Alenia Space, ABSL and ESA-ESTEC. EADS CASA Espacio is contracted to provide the MWR instrument. CNES is contracted to provide the DORIS instrument. Eurockot and Arianespace are contracted to launch the spacecraft. language code: en); 2018-11-05 12:50:49.0 [mmorahan] Insert Concept add broader relation (Sentinel 3A [5449d87b-5573-450f-8acb-2fdfeab3c8ce,368235] - SENTINEL-3 [8a19f309-46ee-424b-be9f-e7e57e5b8ca0,345357]); GOES-3 [Source: NASA NSSDC, http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1978-062A ] GOES 3 was launched in June 1978 and was a NASA-developed, NOAA-operated, geosynchronous, and operational spacecraft. The cylindrically shaped spacecraft measured 190.5 cm in diameter and 230 cm in length, exclusive of a magnetometer that extended an additional 83 cm beyond the cylinder shell. The primary structural members were a honeycombed equipment shelf and thrust tube. The VISSR telescope was mounted on the equipment shelf and viewed the Earth through a special aperture in the side of the spacecraft. A support structure extended radially out from the thrust tube and was affixed to the solar panels, which formed the outer walls of the spacecraft and provided the primary source of electrical power. Located in the annulus-shaped space between the thrust tube and the solar panels were stationkeeping and dynamics control equipment, batteries, and most of the SEM equipment. Proper spacecraft attitude and spin rate (approximately 100 rpm) were maintained by two separate sets of jet thrusters mounted around the spacecraft equator and activated by ground command. The spacecraft used both UHF-band and S-band frequencies in its telemetry and command subsystem. A low-power VHF transponder provided telemetry and command during launch and then served as a backup for the primary subsystem once the spacecraft attained orbit. The spin-stabilized spacecraft carried a visible infrared spin-scan radiometer, meteorological data collection and transmission system, space environment monitor, and a biaxial fluxgate magnetometer. It operated at 135 degrees West as GOES-WEST. For more information on GOES satellites: http://www.oso.noaa.gov/goes/ Group: Platform_Details Entry_ID: GOES-3 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: GOES (Geostationary Operational Environmental Satellite) Short_Name: GOES-3 Long_Name: Geostationary Operational Environmental Satellite 3 End_Group Group: Synonymous_Platform_Names Short_Name: GOES C Short_Name: 10953 End_Group Group: Platform_Associated_Instruments Short_Name: SXM Short_Name: VISSR Short_Name: SEM Short_Name: MAGNETOMETERS End_Group Group: Orbit Orbit_Type: GEO > Geosynchronous > Geostationary End_Group Creation_Date: 2007-10-04 Online_Resource: http://www.oso.noaa.gov/goes/ Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1978-062A Sample_Image: http://library01.gsfc.nasa.gov/gdprojs/images/goes.jpg Group: Platform_Logistics Launch_Date: 1978-06-16 Launch_Site: CAPE CANAVERAL/KENNEDY SPACE CENTER, USA Primary_Sponsor: USA/NASA Primary_Sponsor: USA/NOAA End_Group End_Group NOAA-5 NOAA-5 was launched in July 1976 and was one in a series of reconfigured ITOS satellites launched with new meteorological sensors onboard to expand the operational capability of the ITOS system. The primary objective was to provide global daytime and nighttime direct readout real-time cloudcover data on a daily basis. The sun-synchronous spacecraft was also capable of supplying global atmospheric temperature soundings and very high resolution infrared cloudcover data for selected areas in either a direct readout or a tape-recorder mode. A secondary objective was to obtain global solar-proton flux data on a real-time daily basis. The sensors were mounted on the satellite baseplate with their optical axes directed vertically earthward. The nearly cubical spacecraft measured 1 by 1 by 1.2 m. The satellite was equipped with three curved solar panels that were folded during launch and deployed after orbit was achieved. Each panel measured over 4.2 m in length when unfolded and was covered with approximately 3500 solar cells measuring 2 by 2 cm. The dynamics and attitude control system maintained desired spacecraft orientation through gyroscopic principles incorporated into the satellite design. Earth orientation of the satellite body was maintained by taking advantage of the precession induced from a momentum flywheel so that the satellite body precession rate of one revolution per orbit provided the desired 'earth-looking' attitude. Minor adjustments in attitude and orientation were made by means of magnetic coils and by varying the speed of the momentum flywheel. The primary sensors consisted of a Very High Resolution Radiometer (VHRR), Vertical Temperature Profile Radiometer (VTPR), and a Scanning Radiometer (SR). The spacecraft was placed in a sun-synchronous orbit with equatorial crossing of the ascending node near 8:30 a.m. local time. __________ Taken from the NSSDC System for Information Retrieval and Storage (SIRS). For more information contact the NSSDC Coordinated Request and User Support Office, 301-286-6695 (NASA Goddard Space Flight Center, Code 933.4, Greenbelt, Maryland 20771, USA, "http://nssdc.gsfc.nasa.gov/"). Group: Platform_Details Entry_ID: NOAA-5 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NOAA POES (Polar Orbiting Environmental Satellites) Short_Name: NOAA-5 Long_Name: National Oceanic & Atmospheric Administration-5 End_Group Group: Synonymous_Platform_Names Short_Name: NOAA-5 End_Group Creation_Date: 2007-11-08 Online_Resource: http://nssdc.gsfc.nasa.gov/ Group: Platform_Logistics Launch_Date: 1976-07-29 Primary_Sponsor: NASA End_Group End_Group GOMS The Planeta-C Meteorological Space System includes the Geostationary Operational Meteorological Satellite GOMS (launched on October 31, 1994) located in orbit at stationary point over 76° 50' E. Onboard instruments package allows: 1. obtaining in real time visible and infrared images of the Earth surface and cloud cover within a radius of 60° 50' centred at subsatellite point 2. providing continious observation of the dinamics of varying atmosheric processes 3. detecting, on an operational basis, hazardous natural phenomena 4. determining wind velocity and directions at several levels, sea surface temperature 5. obtaining information on fluxes of solar and galactic particles, electromagnetic ultraviolet and X-ray radiation, variations in the vector of magnetic field General Information: Designation: 23327 / 94069A Launch date: 31 Oct 1994 Country of origin: CIS Mission: Meteorology Launch vehicle: Proton #228 Out of service: Sep 1998? Cause: end of life Location: Begin End Position L: 31 Oct 1994 Sep 1998 76.5°E Mar 1999 66°E drifting Aug 1999 72°E drifting Oct 1999 76°E drifting May 2000 84°E For more information, link to "http://sputnik.infospace.ru/goms/engl/goms_e.htm" [Summary provided by the SPUTNIK Server] Group: Platform_Details Entry_ID: GOMS Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: GOMS Long_Name: Geostationary Operational Meteorological Satellite End_Group Group: Synonymous_Platform_Names Short_Name: GOMS Short_Name: 23327 Short_Name: Electro End_Group Group: Orbit Orbit_Altitude: 36 000km Orbit_Inclination: 0.5 deg Orbit_Type: GEO > Geosynchronous > Geostationary End_Group Creation_Date: 2007-11-19 Online_Resource: http://sputnik.infospace.ru/goms/engl/goms_1.htm Group: Platform_Logistics Launch_Date: 1994-10-31 Launch_Site: Baikonur Cosmodrome, Tyuratam, Russia Primary_Sponsor: Russia End_Group End_Group SPOT 2018-02-20 09:37:48.0 [mmorahan] Insert Concept add narrower relation (SPOT [5615d18d-4217-42a0-a53d-77298834fc2e,287827] - SPOT-7 [5993e605-b045-43fb-bd9b-928892b7386d,310583]); 2018-02-20 09:37:30.0 [mmorahan] Insert Concept add narrower relation (SPOT [5615d18d-4217-42a0-a53d-77298834fc2e,287827] - SPOT-6 [b5b5a3c9-a393-4766-a7d6-ef6c97969e78,310579]); IRS-R2A Today, the array of Indian Earth Observation (EO) Satellites with imaging capabilities in visible, infrared, thermal and microwave regions of the electromagnetic spectrum, including hyper-spectral sensors, have helped the country in realising major operational applications. The imaging sensors have been providing spatial resolution ranging from 1 km to better than 1m; repeat observation (temporal imaging) from 22 days to every 15 minutes and radiometric ranging from 7 bit to 12 bit, which has significantly helped in several applications at national level. In the coming years, the Indian EO satellites are heading towards further strengthened and improved technologies, taking cognizance of the learnings/ achievements made in the yester years, while addressing newer observational requirements and the technological advancements including high agility spacecrafts. 2020-01-24 14:59:13.0 [mmorahan] insert Definition (id: null text: Today, the array of Indian Earth Observation (EO) Satellites with imaging capabilities in visible, infrared, thermal and microwave regions of the electromagnetic spectrum, including hyper-spectral sensors, have helped the country in realising major operational applications. The imaging sensors have been providing spatial resolution ranging from 1 km to better than 1m; repeat observation (temporal imaging) from 22 days to every 15 minutes and radiometric ranging from 7 bit to 12 bit, which has significantly helped in several applications at national level. In the coming years, the Indian EO satellites are heading towards further strengthened and improved technologies, taking cognizance of the learnings/ achievements made in the yester years, while addressing newer observational requirements and the technological advancements including high agility spacecrafts. language code: en); 2020-01-24 14:29:01.0 [mmorahan] insert AltLabel (id: null category: primary text: Indian Remote Sensing Satellite-R2A language code: en); 2020-01-24 14:27:50.0 [mmorahan] Insert Concept add broader relation (IRS-R2A [56535da7-3b47-41e2-a3a9-b88a6abbc5ef,559799] - IRS (Indian Remote Sensing Satellite) [3e8bc0c6-f599-4e23-9535-449af00edd61,541575]); Alvin Alvin, which is operated by Woods Hole Oceanographic Institution, has been in operation since 1964. The human occupied vehicle is capable of reaching depths of 4,500 meters, carrying two scientists and one pilot for each dive. Image courtesy of Luis Lamar, Woods Hole Oceanographic Institution. Alvin, which is operated by Woods Hole Oceanographic Institution, has been in operation since 1964. The human occupied vehicle is capable of reaching depths of 4,500 meters, carrying two scientists and one pilot for each dive. Image courtesy of Luis Lamar, Woods Hole Oceanographic Institution. Download larger version (jpg, 476 KB). The human-occupied vehicle (HOV) Alvin enables direct data collection and observation by two scientists of the seafloor and water column to depths reaching 2.8 miles (4,500 meters) on dives lasting up to 10 hours with the support of an experienced, multi-talented support team. The Alvin Group and their equipment meet the highest safety and reliability standards as a result of decades of operational and engineering expertise. Continual innovation and the application of the latest technological advancements puts Alvin at the forefront of expeditionary research. Its seven reversible thrusters permit Alvin to hover in the water, maneuver over rugged topography, or rest on the seafloor. With an experienced pilot at the controls, it can collect data throughout the water column, produce a variety of maps, and perform photographic surveys. Alvin also has two robotic arms that can manipulate instruments and obtain samples ranging from hard-rock geology to delicate biology, and its sampling basket can be reconfigured daily based on the needs of each dive. Alvin is a proven and reliable platform capable of diving for up to 30 days in a row before requiring a scheduled maintenance day. Recent collaborations with autonomous vehicles such as Sentry have proven expansive, allowing research teams to visit promising sites to collect samples and data in-person within hours of being discovered, and University-National Oceanographic Laboratory System (UNOLS)-driven technological advances have improved the ability for scientific outreach and collaboration via telepresence. Currently rated to 4,500 meters, Alvin gives researchers in-person access to about two-thirds of the ocean floor. The sub’s most recent upgrade, completed in 2014, increased the depth rating of many of the vehicle’s systems, putting it just steps away from having a depth rating of 4.04 miles (6,500 meters) that would provide access to approximately 98 percent of the seafloor. 2020-01-21 19:18:54.0 [tstevens] insert Definition (id: null text: Alvin, which is operated by Woods Hole Oceanographic Institution, has been in operation since 1964. The human occupied vehicle is capable of reaching depths of 4,500 meters, carrying two scientists and one pilot for each dive. Image courtesy of Luis Lamar, Woods Hole Oceanographic Institution. Alvin, which is operated by Woods Hole Oceanographic Institution, has been in operation since 1964. The human occupied vehicle is capable of reaching depths of 4,500 meters, carrying two scientists and one pilot for each dive. Image courtesy of Luis Lamar, Woods Hole Oceanographic Institution. Download larger version (jpg, 476 KB). The human-occupied vehicle (HOV) Alvin enables direct data collection and observation by two scientists of the seafloor and water column to depths reaching 2.8 miles (4,500 meters) on dives lasting up to 10 hours with the support of an experienced, multi-talented support team. The Alvin Group and their equipment meet the highest safety and reliability standards as a result of decades of operational and engineering expertise. Continual innovation and the application of the latest technological advancements puts Alvin at the forefront of expeditionary research. Its seven reversible thrusters permit Alvin to hover in the water, maneuver over rugged topography, or rest on the seafloor. With an experienced pilot at the controls, it can collect data throughout the water column, produce a variety of maps, and perform photographic surveys. Alvin also has two robotic arms that can manipulate instruments and obtain samples ranging from hard-rock geology to delicate biology, and its sampling basket can be reconfigured daily based on the needs of each dive. Alvin is a proven and reliable platform capable of diving for up to 30 days in a row before requiring a scheduled maintenance day. Recent collaborations with autonomous vehicles such as Sentry have proven expansive, allowing research teams to visit promising sites to collect samples and data in-person within hours of being discovered, and University-National Oceanographic Laboratory System (UNOLS)-driven technological advances have improved the ability for scientific outreach and collaboration via telepresence. Currently rated to 4,500 meters, Alvin gives researchers in-person access to about two-thirds of the ocean floor. The sub’s most recent upgrade, completed in 2014, increased the depth rating of many of the vehicle’s systems, putting it just steps away from having a depth rating of 4.04 miles (6,500 meters) that would provide access to approximately 98 percent of the seafloor. language code: en); 2020-01-21 17:34:12.0 [tstevens] Insert Concept add broader relation (Alvin [57323291-3348-4292-812e-7436d6a0781a,559767] - HOV [63c8aa1d-6efc-4943-8891-3a1cd520dde0,559759]); CRM 2013-07-03 15:16:27.0 [saritz] insert AltLabel (id: null text: Cloud Resolving Model language code: en); 2013-07-03 15:06:26.0 [saritz] Insert Concept add broader relation (CRM [57441436-5372-484e-983c-f96cbc51ef72,105257] - Models [113ecbc2-ab36-4d58-a96c-a6ce0106e749,73395]); EXOS-A - Spacecraft Brief Description - This satellite was a part of Japan's contribution to the International Magnetospheric Study. The mission objectives were to observe the aurora borealis, study aurora-related phenomena, and study the ionosphere and magnetosphere. The main body of the spacecraft was a cylinder 0.946 m in diameter with shallow truncated cones attached at both ends. Most of the surface was covered with solar cells that produced 35 W. Two booms of roughly 1.9 m each extended outward from the equator of the main body. At the tip of each boom was a permanent magnet to provide alignment of the spacecraft center axis along the local geomagnetic field line. Two sets of circularly polarized quadrupole antennas, one for UHF (400 MHz) and another for VHF, extended from opposite ends of the spacecraft. The VHF antenna was diplexed for telemetry (136 MHz) and command (148 MHz). Other attitude sensors included a vector magnetometer and a solar sensor. The spacecraft contained a tape recorder to store 160 min of data at 512 bps or 40 min at 2048 bps, with readout in 10 min at 8192 bps. Besides the solar cells, there was a nickel-cadmium battery for nighttime operation. - Auxiliary Information - Launch Date and Time : 1978-02-04 07:00:00 Epoch Date and Time : 1978-02-06 Apogee (km or AU): 3978. Perigee (km or AU): 642. Inclination (degree) : 65.4 Orbit Type : Geocentric Information last updated on 1991-11-15 Group: Platform_Details Entry_ID: EXOS-A Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: EXOS-A End_Group Group: Synonymous_Platform_Names Short_Name: EXOS-A End_Group Group: Orbit Orbit_Inclination: 65.4 deg Perigee: 642 km Apogee: 3978 km End_Group Creation_Date: 2007-11-19 Online_Resource: http://www.oma.be/sevem/EXOS-A.html Sample_Image: http://edu.jaxa.jp/materialDB/display/large-67262.jpg Group: Platform_Logistics Launch_Date: 1978-02-04 Launch_Site: Uchinoura Space Center, Japan Primary_Sponsor: JAXA End_Group End_Group WEATHER STATIONS/NETWORKS 2017-09-11 17:54:55.0 [tstevens] Insert Concept add narrower relation (WEATHER STATIONS/NETWORKS [57b7373d-5c21-4abb-8097-a410adc2a074,287833] - AGBFM [0b011fe7-4a05-4e04-92f6-fa23b9e85e1a,310155]); 2017-09-11 17:52:21.0 [tstevens] Insert Concept add narrower relation (WEATHER STATIONS/NETWORKS [57b7373d-5c21-4abb-8097-a410adc2a074,287833] - LDAR [af4130b5-af02-4602-9e05-81405cfe6dc5,310151]); 2017-09-11 17:48:29.0 [tstevens] Insert Concept add narrower relation (WEATHER STATIONS/NETWORKS [57b7373d-5c21-4abb-8097-a410adc2a074,287833] - WWLLN [0b6bafa6-1cc4-47eb-9925-f72c6d6008fc,310147]); 2014-01-23 16:11:11.0 [saritz] Insert Concept add narrower relation (WEATHER STATIONS/NETWORKS [57b7373d-5c21-4abb-8097-a410adc2a074,73471] - ENTLN [1ab2e0db-8911-434d-a6ba-3917730e83a6,106101]); NOAA-20 JPSS-1 NOAA-20, which launched into space on November 18, 2017, is the first spacecraft of NOAA's next generation of polar-orbiting satellites. Capitalizing on the success of Suomi NPP, NOAA-20 features five similar instruments: (1) VIIRS, (2) CrIS, (3) ATMS, (4) OMPS-N, and (5) CERES-FM6. NOAA-20 has a design life of seven years and it will circle the Earth in the same orbit as Suomi NPP, although the two satellites will be separated in time and space by 50 minutes. Additional information available at: https://www.jpss.noaa.gov/ Group: Platform_Details Entry_ID: JPSS-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: Joint Polar Satellite System (JPSS) Short_Name: NOAA-20 Long_Name: Joint Polar Satellite System - 1 End_Group Group: Synonymous_Platform_Names Short_Name: C-1 Short_Name: Defense Weather Satellite System Short_Name: DWSS End_Group Group: Platform_Associated_Instruments Short_Name: CERES-FM5 Short_Name: A-DCS Short_Name: ATMS Short_Name: CRIMSS Short_Name: CRIS Short_Name: MIS Short_Name: OMPS Short_Name: SEM-N Short_Name: VIIRS End_Group Group: Orbit Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-11-09 Online_Resource: https://www.jpss.noaa.gov/ Group: Platform_Logistics Launch_Date: 2017-11-18 Primary_Sponsor: USA/NOAA Primary_Sponsor: USA/NASA End_Group End_Group 2019-10-03 15:16:47.0 [sritz] update Definition (NOAA-20, which launched into space on November 18, 2017, is the first spacecraft of NOAA's next generation of polar-orbiting satellites. Capitalizing on the success of Suomi NPP, NOAA-20 features five similar instruments: (1) VIIRS, (2) CrIS, (3) ATMS, (4) OMPS-N, and (5) CERES-FM6. NOAA-20 has a design life of seven years and it will circle the Earth in the same orbit as Suomi NPP, although the two satellites will be separated in time and space by 50 minutes. Additional information available at: https://www.jpss.noaa.gov/ Group: Platform_Details Entry_ID: JPSS-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: Joint Polar Satellite System (JPSS) Short_Name: NOAA-20 Long_Name: Joint Polar Satellite System - 1 End_Group Group: Synonymous_Platform_Names Short_Name: C-1 Short_Name: Defense Weather Satellite System Short_Name: DWSS End_Group Group: Platform_Associated_Instruments Short_Name: CERES-FM5 Short_Name: A-DCS Short_Name: ATMS Short_Name: CRIMSS Short_Name: CRIS Short_Name: MIS Short_Name: OMPS Short_Name: SEM-N Short_Name: VIIRS End_Group Group: Orbit Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-11-09 Online_Resource: https://www.jpss.noaa.gov/ Group: Platform_Logistics Launch_Date: 2017-11-18 Primary_Sponsor: USA/NOAA Primary_Sponsor: USA/NASA End_Group End_Group); 2019-10-01 16:15:46.0 [sritz] update Definition (NOAA-20, which launched into space on November 18, 2017, is the first spacecraft of NOAA's next generation of polar-orbiting satellites. Capitalizing on the success of Suomi NPP, NOAA-20 features five similar instruments: (1) VIIRS, (2) CrIS, (3) ATMS, (4) OMPS-N, and (5) CERES-FM6. NOAA-20 has a design life of seven years and it will circle the Earth in the same orbit as Suomi NPP, although the two satellites will be separated in time and space by 50 minutes. Additional information available at: https://www.jpss.noaa.gov/ Group: Platform_Details Entry_ID: JPSS-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NOAA POES (Polar Orbiting Environmental Satellites) Short_Name: NOAA-20 Long_Name: Joint Polar Satellite System - 1 End_Group Group: Synonymous_Platform_Names Short_Name: C-1 Short_Name: Defense Weather Satellite System Short_Name: DWSS End_Group Group: Platform_Associated_Instruments Short_Name: CERES-FM5 Short_Name: A-DCS Short_Name: ATMS Short_Name: CRIMSS Short_Name: CRIS Short_Name: MIS Short_Name: OMPS Short_Name: SEM-N Short_Name: VIIRS End_Group Group: Orbit Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-11-09 Online_Resource: https://www.jpss.noaa.gov/ Group: Platform_Logistics Launch_Date: 2017-11-18 Primary_Sponsor: USA/NOAA Primary_Sponsor: USA/NASA End_Group End_Group); 2019-09-30 20:45:27.0 [sritz] update Definition (NOAA-20, which launched into space on November 18, 2017, is the first spacecraft of NOAA's next generation of polar-orbiting satellites. Capitalizing on the success of Suomi NPP, NOAA-20 features five similar instruments: (1) VIIRS, (2) CrIS, (3) ATMS, (4) OMPS-N, and (5) CERES-FM6. NOAA-20 has a design life of seven years and it will circle the Earth in the same orbit as Suomi NPP, although the two satellites will be separated in time and space by 50 minutes. Additional information available at: https://www.jpss.noaa.gov/ Group: Platform_Details Entry_ID: JPSS-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NOAA POES (Polar Orbiting Environmental Satellites) Short_Name: JPSS-1 Long_Name: Joint Polar Satellite System End_Group Group: Synonymous_Platform_Names Short_Name: C-1 Short_Name: Defense Weather Satellite System Short_Name: DWSS End_Group Group: Platform_Associated_Instruments Short_Name: CERES-FM5 Short_Name: A-DCS Short_Name: ATMS Short_Name: CRIMSS Short_Name: CRIS Short_Name: MIS Short_Name: OMPS Short_Name: SEM-N Short_Name: VIIRS End_Group Group: Orbit Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-11-09 Online_Resource: https://www.jpss.noaa.gov/ Group: Platform_Logistics Launch_Date: 2017-11-18 Primary_Sponsor: USA/NOAA Primary_Sponsor: USA/NASA End_Group End_Group); 2018-04-11 21:28:37.0 [sritz] update WeightedRelation (Platform-Instrument); update WeightedRelation (1); 2018-04-11 21:28:11.0 [sritz] insert WeightedRelation (id: null related concept uuid: b6bcacb0-f88c-440e-9401-61dfb8aa2e0d relationship type: null relationship value: null generated by: null); 2018-02-02 17:11:41.0 [sritz] update WeightedRelation (Platform-Instrument); update WeightedRelation (1); 2018-02-02 17:11:14.0 [sritz] insert WeightedRelation (id: null related concept uuid: de7e08db-86f1-4593-ba9e-288f9f7b063e relationship type: null relationship value: null generated by: null); 2017-11-27 17:19:09.0 [sritz] Move Concepts delete broader relation (null); add broader relation (NOAA-20 [586db0b3-5f94-466e-b7c1-a2dbedc0c1fc,287835] - Joint Polar Satellite System (JPSS) [5c2364ca-c01a-4f69-8808-282c3854b2f6,287871]); 2017-11-27 17:10:52.0 [sritz] update Definition ([Text provided by NASA, http://eospso.gsfc.nasa.gov/eos_homepage/mission_profiles/show_mission.php?id=71&mission_cat_id=17 ] The Joint Polar Satellite System (JPSS) is the restructured civilian portion of the National Polar-orbiting Operational Environmental Satellite System (NPOESS) that will make afternoon observations as it orbits Earth. The system includes the satellites and sensors supporting civil weather and climate measurements and a shared ground infrastructure with the Department of Defense weather satellite system. NOAA is responsible for the JPSS program. NASA is the program’s procurement agent, and the agency’s Goddard Space Flight Center in Greenbelt, Md., is the lead for acquisition. Data and imagery obtained from JPSS will increase the timeliness, accuracy and cost-effectiveness of public warnings and forecasts of climate and weather events, reducing the potential loss of human life and property. Polar-orbiting satellites observe Earth from space and collect and disseminate data on Earth’s weather, atmosphere, oceans, land, and near-space environment and are able to monitor the entire planet and provide data for long-range weather and climate forecasts. Additional information available at: http://eospso.gsfc.nasa.gov/eos_homepage/mission_profiles/show_mission.php?id=71&mission_cat_id=17 Group: Platform_Details Entry_ID: JPSS-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NOAA POES (Polar Orbiting Environmental Satellites) Short_Name: JPSS-1 Long_Name: Joint Polar Satellite System End_Group Group: Synonymous_Platform_Names Short_Name: C-1 Short_Name: Defense Weather Satellite System Short_Name: DWSS End_Group Group: Platform_Associated_Instruments Short_Name: CERES-FM5 Short_Name: A-DCS Short_Name: ATMS Short_Name: CRIMSS Short_Name: CRIS Short_Name: MIS Short_Name: OMPS Short_Name: SEM-N Short_Name: VIIRS End_Group Group: Orbit Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-11-09 Online_Resource: http://www.nesdis.noaa.gov/jpss/ Online_Resource: https://jointmission.gsfc.nasa.gov/ Group: Platform_Logistics Launch_Date: 2017-11-18 Primary_Sponsor: USA/NOAA Primary_Sponsor: USA/NASA End_Group End_Group); 2017-11-27 17:03:54.0 [sritz] update Definition ([Text provided by NASA, http://eospso.gsfc.nasa.gov/eos_homepage/mission_profiles/show_mission.php?id=71&mission_cat_id=17 ] The Joint Polar Satellite System (JPSS) is the restructured civilian portion of the National Polar-orbiting Operational Environmental Satellite System (NPOESS) that will make afternoon observations as it orbits Earth. The system includes the satellites and sensors supporting civil weather and climate measurements and a shared ground infrastructure with the Department of Defense weather satellite system. NOAA is responsible for the JPSS program. NASA is the program’s procurement agent, and the agency’s Goddard Space Flight Center in Greenbelt, Md., is the lead for acquisition. Data and imagery obtained from JPSS will increase the timeliness, accuracy and cost-effectiveness of public warnings and forecasts of climate and weather events, reducing the potential loss of human life and property. Polar-orbiting satellites observe Earth from space and collect and disseminate data on Earth’s weather, atmosphere, oceans, land, and near-space environment and are able to monitor the entire planet and provide data for long-range weather and climate forecasts. Additional information available at: http://eospso.gsfc.nasa.gov/eos_homepage/mission_profiles/show_mission.php?id=71&mission_cat_id=17 Group: Platform_Details Entry_ID: JPSS-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NOAA POES (Polar Orbiting Environmental Satellites) Short_Name: JPSS-1 Long_Name: Joint Polar Satellite System End_Group Group: Synonymous_Platform_Names Short_Name: C-1 Short_Name: Defense Weather Satellite System Short_Name: DWSS End_Group Group: Platform_Associated_Instruments Short_Name: CERES-FM5 Short_Name: A-DCS Short_Name: ATMS Short_Name: CRIMSS Short_Name: CRIS-NPOESS Short_Name: MIS Short_Name: OMPS Short_Name: SEM-N Short_Name: VIIRS End_Group Group: Orbit Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-11-09 Online_Resource: http://www.nesdis.noaa.gov/jpss/ Online_Resource: http://www.ipo.noaa.gov/ Online_Resource: http://nasascience.nasa.gov/missions/npoes Online_Resource: http://npp.gsfc.nasa.gov/ Online_Resource: http://projects.osd.noaa.gov/NDE/ Group: Platform_Logistics Launch_Date: 2017-11-18 Primary_Sponsor: USA/NOAA Primary_Sponsor: USA/NASA End_Group End_Group); 2017-11-27 17:02:11.0 [sritz] update Definition ([Text provided by NASA, http://eospso.gsfc.nasa.gov/eos_homepage/mission_profiles/show_mission.php?id=71&mission_cat_id=17 ] The Joint Polar Satellite System (JPSS) is the restructured civilian portion of the National Polar-orbiting Operational Environmental Satellite System (NPOESS) that will make afternoon observations as it orbits Earth. The system includes the satellites and sensors supporting civil weather and climate measurements and a shared ground infrastructure with the Department of Defense weather satellite system. NOAA is responsible for the JPSS program. NASA is the program’s procurement agent, and the agency’s Goddard Space Flight Center in Greenbelt, Md., is the lead for acquisition. Data and imagery obtained from JPSS will increase the timeliness, accuracy and cost-effectiveness of public warnings and forecasts of climate and weather events, reducing the potential loss of human life and property. Polar-orbiting satellites observe Earth from space and collect and disseminate data on Earth’s weather, atmosphere, oceans, land, and near-space environment and are able to monitor the entire planet and provide data for long-range weather and climate forecasts. Additional information available at: http://eospso.gsfc.nasa.gov/eos_homepage/mission_profiles/show_mission.php?id=71&mission_cat_id=17 Group: Platform_Details Entry_ID: JPSS-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NOAA POES (Polar Orbiting Environmental Satellites) Short_Name: JPSS-1 Long_Name: Joint Polar Satellite System End_Group Group: Synonymous_Platform_Names Short_Name: C-1 Short_Name: Defense Weather Satellite System Short_Name: DWSS End_Group Group: Platform_Associated_Instruments Short_Name: CERES-FM5 Short_Name: A-DCS Short_Name: ATMS Short_Name: CRIMSS Short_Name: CRIS-NPOESS Short_Name: MIS Short_Name: OMPS Short_Name: SEM-N Short_Name: VIIRS End_Group Group: Orbit Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-11-09 Online_Resource: http://npoess.noaa.gov/ Online_Resource: http://www.nesdis.noaa.gov/jpss/ Online_Resource: http://www.ipo.noaa.gov/ Online_Resource: http://nasascience.nasa.gov/missions/npoes Online_Resource: http://npp.gsfc.nasa.gov/ Online_Resource: http://projects.osd.noaa.gov/NDE/ Group: Platform_Logistics Launch_Date: 2017-11-18 Primary_Sponsor: USA/NOAA Primary_Sponsor: USA/NASA Primary_Sponsor: USA/DOD End_Group End_Group); 2017-11-27 16:47:27.0 [sritz] insert AltLabel (id: null category: null text: JPSS-1 language code: en); update PrefLabel (NOAA-20); 2017-11-27 16:46:53.0 [sritz] Move Concepts delete broader relation (null); add broader relation (JPSS-1 [586db0b3-5f94-466e-b7c1-a2dbedc0c1fc,287835] - NOAA POES (Polar Orbiting Environmental Satellites) [e8baa3a4-ef5a-455a-bf25-d61e59fc9bb3,288767]); DMC-1G (Disaster Monitoring Constellation- 1st Generation) OV-104 Atlantis, the fourth orbiter to become operational at Kennedy Space Center, was named after the primary research vessel for the Woods Hole Oceanographic Institute in Massachusetts from 1930 to 1966. The spaceship Atlantis has carried on the spirit of the sailing vessel with several important voyages of its own, including the Galileo planetary explorer mission in 1989 and the deployment of the Arthur Holley Compton Gamma Ray Observatory in 1991. Atlantis benefited from lessons learned in the construction and testing of Enterprise, Columbia and Challenger. At rollout, its weight was some 6,974 pounds less than Columbia. The Experience gained during the Orbiter assembly process also enabled Atlantis to be completed with a 49.5 percent reduction in man hours (compared to Columbia). Much of this decrease can be attributed to the greater use of thermal protection blankets on the upper orbiter body instead of tiles. During the construction of Discovery and Atlantis, NASA opted to have the various contractors manufacture a set of 'structural spares' to facilitate the repair of an Orbiter if one was damaged during an accident. This contract was valued at &#36389 million and consisted of a spare aft-fuselage, mid-fuselage, forward fuselage halves, vertical tail and rudder, wings, elevons and a body flap. These spares were later assembled into the orbiter Endeavour. Atlantis was shipped to California to undergo upgrades and modifications. These modifications include a drag chute, new plumbing lines that configure the orbiter for extended duration, more than 800 new heat protection tiles and blankets and new insulation for the main landing gear. [Summary provided by NASA] Group: Platform_Details Entry_ID: OV-104 Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Platform_Series_or_Entity: SPACE SHUTTLE Short_Name: OV-104 Long_Name: Atlantis Space Shuttle End_Group Group: Synonymous_Platform_Names Short_Name: Atlantis End_Group Creation_Date: 2008-01-25 Online_Resource: http://science.ksc.nasa.gov/shuttle/resources/orbiters/atlantis.html Sample_Image: http://www.centralfloridavillaholiday.com/images/nasa_shuttle_launch.jpg Group: Platform_Logistics Launch_Date: 1985-10-03 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: NASA End_Group End_Group ALOUETTE SPOT-7 TECHNICAL FEATURES With SPOT 6 and SPOT 7, Astrium not only secures mission continuity of the SPOT series, which has been collecting an archive of more than 30 million of scenes since 1986: this new generation of optical satellites also features technological improvements and advanced system performance that increase reactivity and acquisition capacity as well as simplifying data access. Space segment: SPOT 6 and SPOT 7 will provide 1.5metre resolution products over broad areas until 2024. Number of satellites 2 Launch periods SPOT 6: September 12th, 2012 SPOT 7: June 30th, 2014 Design lifetime 10 years Size Body: ~ 1.55 x 1.75 x 2.7 m Solar array wingspan 5,4 m2 Launch mass 712 kg Altitude 694 km Onboard Storage 1 Tbits end of life (Solid State Mass Memory) Orbital characteristics and viewing capability: SPOT 6 and SPOT 7 missions are designed to achieve efficiently both collection of large coverage and collection of individual targets that are possible thanks to the extreme agility of the satellite. Orbit Sun-synchronous; 10:00 AM local time at descending node Period 98.79 minutes Cycle 26 days Viewing angle Standard: +/- 30° in roll | Extended: +/- 45° in roll Revisit • 1 day with SPOT 6 and SPOT 7 operating simultaneously • Between 1 and 3 days with only one satellite in operation (note 1) Pointing agility Control Moment Gyroscopes allowing quick maneuvers in all directions for targeting several areas of interest on the same pass (30° in 14s, including stabilization time) Acquisition capacity Up to 6 million sq.km daily with SPOT 6 and SPOT 7 when operating simultaneously Nominal Imaging Mode 60km-swath strips oriented along North-South axis; up to 600km length Stereo capability Fore and aft mode; Single pass stereo and tri-stereo Note1: Depends on the latitude of the area of interest Instruments: Optical system One instrument made of 2 identical Korsch telescopes, each with a 200 mm aperture, delivering the expected swath. Detectors PAN array assembly: 28,000 pixels MS array assembly: 4 x 7000 pixels Spectral bands Panchromatic: 0.450-0.745 µm Blue: 0.450-0.520 µm Green: 0.530-0.590 µm Red: 0.625-0.695 µm Near Infrared: 0.760-0.890 µm The 5 bands are always acquired simultaneously. Swath 60km at nadir Dynamic range at acquisition 12 bits per pixel Location accuracy specification • 35m CE 90 without GCP within a 30° viewing angle cone • 10m CE90 for Ortho products where Reference3D is available Instrument telemetry link rate X-band channel - 300 Mbits/s Ground segment: Main receiving stations • Toulouse (France) • Kiruna (Sweden) S-Band uplink stations • Kiruna (Sweden) • Inuvik (Canada) Programming centre Astrium GEO-Information Service – Toulouse (France) Astrium GEO-Information Service – Chantilly VA (USA) Production centre Astrium GEO-Information Service – Toulouse (France) Tasking plans refresh frequency 6 times/day/satellite Update of weather forecast 4 times/day – fully automatic process Satellite control centre Astrium Satellite – Toulouse (France) 2018-02-20 09:51:01.0 [mmorahan] insert AltLabel (id: null category: primary text: Systeme Probatoire Pour l'Observation de la Terre-7 language code: en); insert Definition (id: null text: TECHNICAL FEATURES With SPOT 6 and SPOT 7, Astrium not only secures mission continuity of the SPOT series, which has been collecting an archive of more than 30 million of scenes since 1986: this new generation of optical satellites also features technological improvements and advanced system performance that increase reactivity and acquisition capacity as well as simplifying data access. Space segment: SPOT 6 and SPOT 7 will provide 1.5metre resolution products over broad areas until 2024. Number of satellites 2 Launch periods SPOT 6: September 12th, 2012 SPOT 7: June 30th, 2014 Design lifetime 10 years Size Body: ~ 1.55 x 1.75 x 2.7 m Solar array wingspan 5,4 m2 Launch mass 712 kg Altitude 694 km Onboard Storage 1 Tbits end of life (Solid State Mass Memory) Orbital characteristics and viewing capability: SPOT 6 and SPOT 7 missions are designed to achieve efficiently both collection of large coverage and collection of individual targets that are possible thanks to the extreme agility of the satellite. Orbit Sun-synchronous; 10:00 AM local time at descending node Period 98.79 minutes Cycle 26 days Viewing angle Standard: +/- 30° in roll | Extended: +/- 45° in roll Revisit • 1 day with SPOT 6 and SPOT 7 operating simultaneously • Between 1 and 3 days with only one satellite in operation (note 1) Pointing agility Control Moment Gyroscopes allowing quick maneuvers in all directions for targeting several areas of interest on the same pass (30° in 14s, including stabilization time) Acquisition capacity Up to 6 million sq.km daily with SPOT 6 and SPOT 7 when operating simultaneously Nominal Imaging Mode 60km-swath strips oriented along North-South axis; up to 600km length Stereo capability Fore and aft mode; Single pass stereo and tri-stereo Note1: Depends on the latitude of the area of interest Instruments: Optical system One instrument made of 2 identical Korsch telescopes, each with a 200 mm aperture, delivering the expected swath. Detectors PAN array assembly: 28,000 pixels MS array assembly: 4 x 7000 pixels Spectral bands Panchromatic: 0.450-0.745 µm Blue: 0.450-0.520 µm Green: 0.530-0.590 µm Red: 0.625-0.695 µm Near Infrared: 0.760-0.890 µm The 5 bands are always acquired simultaneously. Swath 60km at nadir Dynamic range at acquisition 12 bits per pixel Location accuracy specification • 35m CE 90 without GCP within a 30° viewing angle cone • 10m CE90 for Ortho products where Reference3D is available Instrument telemetry link rate X-band channel - 300 Mbits/s Ground segment: Main receiving stations • Toulouse (France) • Kiruna (Sweden) S-Band uplink stations • Kiruna (Sweden) • Inuvik (Canada) Programming centre Astrium GEO-Information Service – Toulouse (France) Astrium GEO-Information Service – Chantilly VA (USA) Production centre Astrium GEO-Information Service – Toulouse (France) Tasking plans refresh frequency 6 times/day/satellite Update of weather forecast 4 times/day – fully automatic process Satellite control centre Astrium Satellite – Toulouse (France) language code: en); 2018-02-20 09:37:48.0 [mmorahan] Insert Concept add broader relation (SPOT-7 [5993e605-b045-43fb-bd9b-928892b7386d,310583] - SPOT [5615d18d-4217-42a0-a53d-77298834fc2e,287827]); INSAT-3D INSAT-3D is an advanced weather satellite of India configured with improved Imaging System and Atmospheric Sounder. INSAT-3D is designed for enhanced meteorological observations, monitoring of land and ocean surfaces, generating vertical profile of the atmosphere in terms of temperature and humidity for weather forecasting and disaster warning. It carries four payloads - a) 6 channel multi-spectral Imager b) 19 channel Sounder c) Data Relay Transponder (DRT) d) Search and Rescue Transponder The payloads of INSAT-3D provides continuity and further augment the capability to provide various meteorological as well as search and rescue services. Group: Platform_Details Entry_ID: INSAT-3D Group: Platform_Identification Platform_Category: EARTH OBSERVATION SATELLITES Platform_Series_or_Entity: INSAT (INDIAN NATIONAL SATELLITE) Short_Name: INSAT-3D End_Group Group: Synonymous_Platform_Names Short_Name: INSAT-3D End_Group Group: Platform_Associated_Instruments Short_Name: 3D-IMAGER Short_Name: INSAT-3D SOUNDER End_Group Group: Orbit Orbit_Altitude: 36000 Orbit_Inclination: 0.23 Period: 1428 Perigee: 35469 Apogee: 35799 Orbit_Type: GEO > GEOSYNCHRONOUS > GEOSTATIONARY End_Group Creation_Date: 2014-06-11 Online_Resource: http://www.isro.gov.in/satellites/insat-3d.aspx Sample_Image: http://www.isro.gov.in/satellites/images/insat-3d_img.jpg Group: Platform_Logistics Launch_Date: 2013-07-26 Launch_Site: KOUROU, FRENCH GUIANA Design_Life: 07 years Primary_Sponsor: ISRO End_Group End_Group 2014-06-12 13:46:25.0 [mpmorahan] Insert Concept add broader relation (INSAT-3D [5999e653-21ea-49ef-977a-13b5fe40fa36,106461] - INSAT (Indian National Satellite) [949ab40f-3954-4c81-a063-275d0e13a14e,73981]); GOES-2 [Source: NASA Space Science Data Center (NSSDC), http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1977-048A ] GOES 2 was a NASA-developed, NOAA-operated, geosynchronous, and operational spacecraft. The spin-stabilized spacecraft carried (1) a visible infrared spin-scan radiometer (VISSR) to provide high-quality day/night cloudcover data and to take radiance-derived temperatures of the earth/atmosphere system, (2) a meteorological data collection and transmission system to relay processed data from central weather facilities to APT-equipped regional stations and to collect and retransmit data from remotely located earth-based platforms, and (3) a space environment monitor (SEM) system to measure proton, electron, and solar X-ray fluxes and magnetic fields. The cylindrically shaped spacecraft measured 190.5 cm in diameter and 230 cm in length, exclusive of a magnetometer that extended an additional 83 cm beyond the cylinder shell. The primary structural members were a honeycombed equipment shelf and thrust tube. The VISSR telescope was mounted on the equipment shelf and viewed the earth through a special aperture in the side of the spacecraft. A support structure extended radially out from the thrust tube and was affixed to the solar panels, which formed the outer walls of the spacecraft and provided the primary source of electrical power. Located in the annulus-shaped space between the thrust tube and the solar panels were stationkeeping and dynamics control equipment, batteries, and most of the SEM equipment. Proper spacecraft attitude and spin rate (approximately 100 rpm) were maintained by two separate sets of jet thrusters mounted around the spacecraft equator and activated by ground command. The spacecraft used both UHF-band and S-band frequencies in its telemetry and command subsystem. A low-power VHF transponder provided telemetry and command during launch and then served as a backup for the primary subsystem once the spacecraft attained synchronous orbit. For more detailed information, see "The GOES/SMS User's Guide" (TRF B28599), available from NSSDC. Group: Platform_Details Entry_ID: GOES-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: GOES (Geostationary Operational Environmental Satellite) Short_Name: GOES-2 Long_Name: Geostationary Operational Environmental Satellite 2 End_Group Group: Synonymous_Platform_Names Short_Name: GOES-B Short_Name: 10061 End_Group Group: Platform_Associated_Instruments Short_Name: SXM Short_Name: VISSR Short_Name: SEM Short_Name: MAGNETOMETERS End_Group Group: Orbit Orbit_Type: GEO > Geosynchronous > Geostationary End_Group Creation_Date: 2007-10-04 Online_Resource: http://www.oso.noaa.gov/goes/ Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1977-048A Group: Platform_Logistics Launch_Date: 1977-06-16 Launch_Site: CAPE CANAVERAL/KENNEDY SPACE CENTER, USA Primary_Sponsor: USA/NASA Primary_Sponsor: USA/NOAA End_Group End_Group Aura NASA's Aura is a mission to understand and protect the air we breathe. With the launch of Aura NASA has begun to make the most comprehensive measurements of the Earth's atmosphere. It also caps off a 15-year international effort to establish the world's most comprehensive Earth Observing System, whose overarching goal is to determine the extent, causes, and regional consequences of global change. Aura's objective is to study the chemistry and dynamics of the Earth's atmosphere with emphasis on the upper troposphere and lower stratosphere (0-30km) by employing multiple instruments on a single satellite. The satellite's measurements enable scientists to investigate questions about ozone trends, air quality changes and their linkages to climate change. These observations provide accurate data for predictive models and provide useful information for local and national government agencies. Website: https://aura.gsfc.nasa.gov/ [Summary provided by NASA] Group: Platform_Details Entry_ID: AURA Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: EOS (Earth Observing System) Short_Name: AURA Long_Name: Aura End_Group Group: Synonymous_Platform_Names Short_Name: EOS Chemistry-1 End_Group Group: Platform_Associated_Instruments Short_Name: TES Short_Name: OMI Short_Name: MLS Short_Name: HIRDLS End_Group Group: Orbit Orbit_Altitude: 705 km Orbit_Inclination: 98.2 Degrees Equator_Crossing: 1:45 p.m. Period: 100 Minutes Repeat_Cycle: 16 Days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-04-17 Online_Resource: https://aura.gsfc.nasa.gov/ Sample_Image: https://gcmd.gsfc.nasa.gov/KeywordSearch/default/images/aura.gif Group: Platform_Logistics Launch_Date: 2004-07-15 Launch_Site: Vandenberg Air Force Base, USA Design_Life: Nominal mission lifetime of 5 years, with a goal of 6 years of operation. Primary_Sponsor: USA/NASA Primary_Sponsor: Joint with United States of America, Netherlands, Finland, and UK End_Group End_Group 2018-04-05 19:53:27.0 [sritz] delete AltLabel (null); insert AltLabel (id: null category: outdated text: AURA language code: en); 2018-04-05 19:52:59.0 [sritz] update PrefLabel (Aura); 2018-02-22 22:58:11.0 [sritz] update Definition (NASA's Aura is a mission to understand and protect the air we breathe. With the launch of Aura NASA has begun to make the most comprehensive measurements of the Earth's atmosphere. It also caps off a 15-year international effort to establish the world's most comprehensive Earth Observing System, whose overarching goal is to determine the extent, causes, and regional consequences of global change. Aura's objective is to study the chemistry and dynamics of the Earth's atmosphere with emphasis on the upper troposphere and lower stratosphere (0-30km) by employing multiple instruments on a single satellite. The satellite's measurements enable scientists to investigate questions about ozone trends, air quality changes and their linkages to climate change. These observations provide accurate data for predictive models and provide useful information for local and national government agencies. Website: https://aura.gsfc.nasa.gov/ [Summary provided by NASA] Group: Platform_Details Entry_ID: AURA Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: EOS (Earth Observing System) Short_Name: AURA Long_Name: Aura End_Group Group: Synonymous_Platform_Names Short_Name: EOS Chemistry-1 End_Group Group: Platform_Associated_Instruments Short_Name: TES Short_Name: OMI Short_Name: MLS Short_Name: HIRDLS End_Group Group: Orbit Orbit_Altitude: 705 km Orbit_Inclination: 98.2 Degrees Equator_Crossing: 1:45 p.m. Period: 100 Minutes Repeat_Cycle: 16 Days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-04-17 Online_Resource: https://aura.gsfc.nasa.gov/ Sample_Image: https://gcmd.gsfc.nasa.gov/KeywordSearch/default/images/aura.gif Group: Platform_Logistics Launch_Date: 2004-07-15 Launch_Site: Vandenberg Air Force Base, USA Design_Life: Nominal mission lifetime of 5 years, with a goal of 6 years of operation. Primary_Sponsor: USA/NASA Primary_Sponsor: Joint with United States of America, Netherlands, Finland, and UK End_Group End_Group); 2018-02-22 22:54:54.0 [sritz] update Definition (NASA's Aura is a mission to understand and protect the air we breathe. With the launch of Aura NASA has begun to make the most comprehensive measurements of the Earth's atmosphere. It also caps off a 15-year international effort to establish the world's most comprehensive Earth Observing System, whose overarching goal is to determine the extent, causes, and regional consequences of global change. Aura's objective is to study the chemistry and dynamics of the Earth's atmosphere with emphasis on the upper troposphere and lower stratosphere (0-30km) by employing multiple instruments on a single satellite. The satellite's measurements enable scientists to investigate questions about ozone trends, air quality changes and their linkages to climate change. These observations provide accurate data for predictive models and provide useful information for local and national government agencies. Website: http://www.nasa.gov/mission_pages/aura/main/index.html [Summary provided by NASA] Group: Platform_Details Entry_ID: AURA Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: EOS (Earth Observing System) Short_Name: AURA Long_Name: Aura End_Group Group: Synonymous_Platform_Names Short_Name: EOS Chemistry-1 End_Group Group: Platform_Associated_Instruments Short_Name: TES Short_Name: OMI Short_Name: MLS Short_Name: HIRDLS End_Group Group: Orbit Orbit_Altitude: 705 km Orbit_Inclination: 98.2 Degrees Equator_Crossing: 1:45 p.m. Period: 100 Minutes Repeat_Cycle: 16 Days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-04-17 Online_Resource: https://aura.gsfc.nasa.gov/ Online_Resource: http://www.nasa.gov/mission_pages/aura/main/index.html Online_Resource: http://science.nasa.gov/missions/aura/ Online_Resource: http://disc.gsfc.nasa.gov/Aura/ Online_Resource: http://www.nasa.gov/mission_pages/aura/spacecraft/index.html Sample_Image: http://gcmd.gsfc.nasa.gov/KeywordSearch/default/images/aura.gif Group: Platform_Logistics Launch_Date: 2004-07-15 Launch_Site: Vandenberg Air Force Base, USA Design_Life: Nominal mission lifetime of 5 years, with a goal of 6 years of operation. Primary_Sponsor: USA/NASA Primary_Sponsor: Joint with United States of America, Netherlands, Finland, and UK End_Group End_Group); update Resource (image); update Resource (https://gcmd.gsfc.nasa.gov/KeywordSearch/default/images/aura.gif); 2016-10-13 20:39:46.0 [saritz] update AltLabel (Aura); update PrefLabel (AURA); 2016-09-13 21:43:51.0 [saritz] update AltLabel (AURA); update PrefLabel (Aura); 2016-06-09 14:30:31.0 [epneff] added altLabel insert AltLabel (id: null text: Aura language code: en); 2014-05-21 17:54:51.0 [128.183.164.42] update AltLabel (Earth Observing System, Aura); 2014-05-21 17:18:25.0 [128.183.164.42] Updated to be consistent with other EOS platform names. update AltLabel (Earth Observing System (EOS), Aura); DE-1 The Dynamics Explorer (DE) mission's general objective is to investigate the strong interactive processes coupling the hot, tenuous, convecting plasmas of the magnetosphere and the cooler, denser plasmas and gases corotating in the earth's ionosphere, upper atmosphere, and plasmasphere. Two satellites, DE 1 and DE 2, were launched together and were placed in polar coplanar orbits, permitting simultaneous measurements at high and low altitudes in the same field-line region. The DE 1 spacecraft (high-altitude mission) uses an elliptical orbit selected to allow (1) measurements extending from the hot magnetospheric plasma through the plasmasphere to the cool ionosphere; (2) global auroral imaging, wave measurements in the heart of the magnetosphere, and crossing of auroral field lines at several earth radii; and (3) measurements for significant periods along a magnetic field flux tube. The spacecraft approximated a short polygon 137 cm in diameter and 115 cm high. The antennas in the X-Y plane measured 200-m tip-to-tip, and on the Z-axis are 9 meters tip-to-tip. Two six-meter booms are provided for remote measurements. Power is supplied by a solar cell array, mounted on the side and end panels. The spacecraft is spin stabilized, with the spin axis normal to the orbital plane, and the spin rate at ten plus or minus 0.1 rpm. A pulse code modulation (PCM) telemetry data system is used that operates in real time or in a tape-recorder mode. Data have been acquired on a science-problem-oriented basis, with closely coordinated operations of the various instruments, both satellites, and supportive experiments. Data acquired from the instruments are temporarily stored on tape recorders before transmission at an 8:1 playback-to-record ratio. Additional operational flexibility allows a playback-to-record ratio of 4:1. The primary data rate is 16,384 bits per second. Since commands are stored in a command memory unit, spacecraft operations are not real time, except for the transmission of the wideband analog data from the Plasma Wave Instrument (81-070A-02). On October 22, 1990 science operations were terminated. On February 28, 1991 Dynamics Explorer 1 operations were offically terminated. Group: Platform_Details Entry_ID: DE-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: DE (Dynamics Explorer) Short_Name: DE-1 Long_Name: Dynamics Explorer-1 End_Group Group: Synonymous_Platform_Names Short_Name: DE 1 Short_Name: DE-A Short_Name: Dynamics Explorer-A Short_Name: Explorer 62 Short_Name: 12624 End_Group Group: Platform_Associated_Instruments Short_Name: MAGNETOMETERS End_Group Creation_Date: 2007-09-12 Online_Resource: http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1981-070A Sample_Image: http://www-pi.physics.uiowa.edu/sai/gallery/destack.jpg Group: Platform_Logistics Launch_Date: 1981-08-03 Primary_Sponsor: NASA End_Group End_Group METEOSAT-2 Meteosat-2 was launched in June 1981 and was a geostationary spacecraft that served as part of European Space Agency's (ESA) contribution to the Global Atmospheric Research Program (GARP). As part of GARP, the satellite helped to supply data required for global data sets used in improvement of machine weather forecasts. In general, the spacecraft design, instrumentation, and operation were similar to SMS/GOES. The cylindrically shaped spacecraft measured 210 cm in diameter and 430 cm in length, including the apogee boost motor. The primary structural members were an equipment platform and a central tube. The radiometer telescope was mounted on the equipment platform and viewed the earth through a special aperture in the side of the spacecraft. A support structure extended radially out from the central tube and was affixed to the solar panels, which formed the outer walls of the spacecraft and provided the primary source of electrical power. Located in the annulus-shaped space between the central tube and the solar panels were station-keeping and dynamics control equipment and batteries. Proper spacecraft attitude and spin rate (approximately 100 rpm) were maintained by jet thrusters mounted on the spacecraft and activated by ground command. The spacecraft used both UHF-band and S-band frequencies in its telemetry and command subsystems. A low-power VHF transponder provided telemetry and command during launch and then served as a backup for the primary subsystem once the spacecraft attained synchronous orbit. The spin-stabilized spacecraft carried (1) a visible-IR radiometer to provide high-quality day/night cloudcover data and to take radiance temperatures of the earth/atmosphere system, and (2) a meteorological data collection system to disseminate image data to user stations, to collect data from various earth-based platforms, and to relay data from polar-orbiting satellites. Meteosat-1 was maintained on station between 1 degree East and 1 degree West. For information on the European Space Agency (ESA) and the Meteosat Program, see the URL: http://www.esrin.esa.it ----------------- Entry taken from: Taken from the NSSDC System for Information Retrieval and Storage (SIRS). For more information contact the NSSDC Coordinated Request and User Support Office, 301-286-6695 (NASA Goddard Space Flight Center, Code 933.4, Greenbelt, Maryland 20771, USA, http://nssdc.gsfc.nasa.gov/). Group: Platform_Details Entry_ID: METEOSAT-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: METEOSAT Short_Name: METEOSAT-2 End_Group End_Group Galileo Galileo is the European Union's Global Satellite Navigation System (GNSS). Sometimes called the 'European GPS, Galileo provides accurate positioning and timing information. Galileo is a programme under civilian control and its data can be used for a broad range of applications. It is autonomous but also interoperable with existing satellite navigation systems. At the moment, the Galileo constellation consists of 18 satellites. 2017-08-15 13:23:56.0 [tstevens] insert Definition (id: null text: Galileo is the European Union's Global Satellite Navigation System (GNSS). Sometimes called the 'European GPS, Galileo provides accurate positioning and timing information. Galileo is a programme under civilian control and its data can be used for a broad range of applications. It is autonomous but also interoperable with existing satellite navigation systems. At the moment, the Galileo constellation consists of 18 satellites. language code: en); 2017-08-14 19:20:37.0 [tstevens] insert AltLabel (id: null category: primary text: Galileo Satellites language code: en); 2017-08-14 19:20:04.0 [tstevens] Insert Concept add broader relation (Galileo [59fae923-a986-41e5-8fe2-30bd3b9cb625,309899] - Galileo (European Satellite Navigation System) [b1c1ecfd-eb6c-4a51-b86e-2ae64babc27d,309895]); MERRA 2015-06-21 23:17:32.0 [saritz] S. Ritz added new keyword. insert AltLabel (id: null text: Modern-Era Retrospective Analysis for Research and Applications language code: en); 2015-06-21 23:16:17.0 [saritz] Insert Concept add broader relation (MERRA [5a147bc8-abc3-4c79-bbba-0a64bf888b41,158047] - Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215]); AE-A 00564 Atmosphere Explorer-A Explorer 17 S 6 Explorer 17 was a spin-stabilized sphere 0.95 m in diameter. The spacecraft was vacuum sealed in order to prevent contamination of the local atmosphere. Explorer 17 carried four pressure gauges for the measurement of total neutral particle density, two mass spectrometers for the measurement of certain neutral particle concentrations, and two electrostatic probes for ion concentration and electron temperature measurements. Battery power failed on July 10, 1963. Three of the four pressure gauges and both electrostatic probes operated normally. One spectrometer malfunctioned, and the other operated intermittently. https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1963-009A Group: Platform_Details Entry_ID: AE-A Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: AE (Atmosphere Explorer) Short_Name: AE-A Long_Name: Atmosphere Explorer A (Explorer 17) End_Group Group: Synonymous_Platform_Names Short_Name: Explorer 17 Short_Name: S 6 Short_Name: 00564 End_Group Group: Platform_Associated_Instruments Short_Name: SPECTROMETERS End_Group Group: Orbit Orbit_Inclination: 57.6 degrees Perigee: 255 km Apogee: 916 km End_Group Creation_Date: 2007-08-22 Online_Resource: https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1963-009A Group: Platform_Logistics Launch_Date: 1963-04-03 Primary_Sponsor: NASA End_Group End_Group 2019-09-17 21:25:39.0 [sritz] insert AltLabel (id: null category: null text: Explorer 17 language code: en); insert AltLabel (id: null category: null text: S 6 language code: en); insert AltLabel (id: null category: null text: Atmosphere Explorer-A language code: en); insert AltLabel (id: null category: null text: 00564 language code: en); 2019-09-17 21:24:37.0 [sritz] update Definition (Explorer 17 was a spin-stabilized sphere 0.95 m in diameter. The spacecraft was vacuum sealed in order to prevent contamination of the local atmosphere. Explorer 17 carried four pressure gauges for the measurement of total neutral particle density, two mass spectrometers for the measurement of certain neutral particle concentrations, and two electrostatic probes for ion concentration and electron temperature measurements. Battery power failed on July 10, 1963. Three of the four pressure gauges and both electrostatic probes operated normally. One spectrometer malfunctioned, and the other operated intermittently. https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1963-009A Group: Platform_Details Entry_ID: AE-A Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: AE (Atmosphere Explorer) Short_Name: AE-A Long_Name: Atmosphere Explorer A (Explorer 17) End_Group Group: Synonymous_Platform_Names Short_Name: Explorer 17 Short_Name: S 6 Short_Name: 00564 End_Group Group: Platform_Associated_Instruments Short_Name: SPECTROMETERS End_Group Group: Orbit Orbit_Inclination: 57.6 degrees Perigee: 255 km Apogee: 916 km End_Group Creation_Date: 2007-08-22 Online_Resource: https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1963-009A Group: Platform_Logistics Launch_Date: 1963-04-03 Primary_Sponsor: NASA End_Group End_Group); Meteor-3M METEOR-3M Mission: The Meteor-3M satellite mission is a joint partnership between NASA and the Russian Aviation and Space Agency (RASA). It was initiated by the Gore-Chernomyrdin Commission in 1994 and extends a long-term working relationship between the United States and Russia to understand Earth's environment. Spacecraft Information: The Meteor-3M spacecraft is an advanced model of the Meteor spacecraft that was developed over 30 years ago. The payload includes SAGE III and other instruments. Measurements Taken: 1. temperature and humidity profiles 2. clouds, 3. surface properties 4. high energy particles in the upper atmosphere. Solar measurements are collected twice each orbit when the satellite ascends or descends from behind the Earth. Lunar measurements are collected when at least 50% of the moon is visible and the sun is not. Additional information available at: https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=2001-056A [Summary provided by NASA] Group: Platform_Details Entry_ID: METEOR-3M Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: METEOR Short_Name: METEOR-3M End_Group Group: Synonymous_Platform_Names Short_Name: SAGE III/Meteor 3M Short_Name: 26701 End_Group Group: Platform_Associated_Instruments Short_Name: SAGE III End_Group Group: Orbit Orbit_Inclination: 99.7° Period: 105.0 minutes Perigee: 996.0 km Apogee: 1016.0 km End_Group Creation_Date: 2009-02-27 Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=2001-056A Group: Platform_Logistics Launch_Date: 2001-12-10 Launch_Site: Baikonur Cosmodrome, Tyuratam, Russia Primary_Sponsor: Russia Primary_Sponsor: USA/NASA End_Group End_Group 2019-05-31 17:11:26.0 [sritz] update Definition (METEOR-3M Mission: The Meteor-3M satellite mission is a joint partnership between NASA and the Russian Aviation and Space Agency (RASA). It was initiated by the Gore-Chernomyrdin Commission in 1994 and extends a long-term working relationship between the United States and Russia to understand Earth's environment. Spacecraft Information: The Meteor-3M spacecraft is an advanced model of the Meteor spacecraft that was developed over 30 years ago. The payload includes SAGE III and other instruments. Measurements Taken: 1. temperature and humidity profiles 2. clouds, 3. surface properties 4. high energy particles in the upper atmosphere. Solar measurements are collected twice each orbit when the satellite ascends or descends from behind the Earth. Lunar measurements are collected when at least 50% of the moon is visible and the sun is not. Additional information available at: https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=2001-056A [Summary provided by NASA] Group: Platform_Details Entry_ID: METEOR-3M Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: METEOR Short_Name: METEOR-3M End_Group Group: Synonymous_Platform_Names Short_Name: SAGE III/Meteor 3M Short_Name: 26701 End_Group Group: Platform_Associated_Instruments Short_Name: SAGE III End_Group Group: Orbit Orbit_Inclination: 99.7° Period: 105.0 minutes Perigee: 996.0 km Apogee: 1016.0 km End_Group Creation_Date: 2009-02-27 Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=2001-056A Group: Platform_Logistics Launch_Date: 2001-12-10 Launch_Site: Baikonur Cosmodrome, Tyuratam, Russia Primary_Sponsor: Russia Primary_Sponsor: USA/NASA End_Group End_Group); 2019-05-31 17:09:31.0 [sritz] update WeightedRelation (Similar); update WeightedRelation (1); update WeightedRelation (Instrument-Sensor); update WeightedRelation (1); 2019-05-31 17:08:33.0 [sritz] insert WeightedRelation (id: null related concept uuid: b9f2cf4a-c2f0-4e78-847f-71fbbbce2f24 relationship type: null relationship value: null generated by: null); 2019-05-31 17:02:34.0 [sritz] insert WeightedRelation (id: null related concept uuid: 1c0794e7-622d-47bf-9ca1-1da7232193df relationship type: null relationship value: null generated by: null); 2015-05-08 18:51:16.0 [saritz] update PrefLabel (Meteor-3M); OCEAN PLATFORMS OCEAN PLATFORMS/OCEAN STATIONS Ocean Platforms are platforms that are elevated over the surface of the ocean for ocean observations and drilling. Group: Platform_Details Entry_ID: OCEAN PLATFORMS Group: Platform_Identification Platform_Category: In Situ Ocean-based Platforms Platform_Series_or_Entity: OCEAN PLATFORM/OCEAN STATIONS Short_Name: OCEAN PLATFORMS End_Group Group: Synonymous_Platform_Names Short_Name: Ocean Platforms End_Group Creation_Date: 2007-12-12 Online_Resource: http://www.freepatentsonline.com/4829928.html Sample_Image: http://www.alaska-in-pictures.com/data/media/17/monopod-oil-platform_3221.jpg End_Group 2016-06-09 18:35:24.0 [epneff] added altLabel insert AltLabel (id: null text: OCEAN PLATFORMS/OCEAN STATIONS language code: en); WP-3D ORION Two of the world's premier research aircraft, the renowned NOAA WP-3D Orions, participate in a wide variety of national and international meteorological, oceanographic and environmental research programs in addition to their widely known use in hurricane research and reconnaissance. These versatile turboprop aircraft are equipped with an unprecedented variety of scientific instrumentation, radars and recording systems for both in-situ and remote sensing measurements of the atmosphere, the earth and its environment. Obtained as new aircraft from the Lockheed production line in the mid-70's, these robust and well maintained aircraft have led NOAA's continuing effort to monitor and study hurricanes and other severe storms, the quality of the atmosphere, the state of the ocean and its fish population, and climate trends. [Photo and text provided by NOAA, http://www.aoc.noaa.gov/aircraft_lockheed.htm ] Group: Platform_Details Entry_ID: WP-3D ORION Group: Platform_Identification Platform_Category: Aircraft Short_Name: WP-3D ORION Long_Name: Lockheed WP-3D Orion End_Group Creation_Date: 2008-07-14 Online_Resource: http://www.aoc.noaa.gov/aircraft_lockheed.htm Online_Resource: http://en.wikipedia.org/wiki/WP-3D Online_Resource: http://www.aoml.noaa.gov/hrd/aircraft.html Sample_Image: http://www.aoc.noaa.gov/images/lockheed1.jpg End_Group MSG MSG02 Meteosat Second Generation (MSG) has been chosen as the name for the new family of Meteorological Satellites. Twenty-five years after the rollout of the first meteorological satellite in 1977, some six other Meteosats later, MSG is now a completely new series of geostationary meteorological satellites with three pieces already being produced and others that may follow within the next decade. MSG is a joint project between ESA and Eumetsat, the organization set up in 1986 to establish, maintain and operate a European system of meteorological satellites. Three satellites are planned at present and a ground segment. ESA is responsible for designing and developing the first satellite - now already in orbit - and for procuring the other three on behalf of Eumetsat. Eumetsat is responsible for defining the payload based on user needs, procuring the ground segment and launchers, and operating the system. With the launch of MSG-2, at any one time, two MSG satellites will be functional in geostationary orbit, the operational one being at 0 degrees longitude which is above equatorial west Africa, the other being on stand-by with 10 degrees of separation. The first satellite, MSG-1 has been launched on board an Ariane 5 launcher in August 2002. MSG-2 will follow later. MSG-3 will be built and put in storage until it is required to take over as the operational MSG nears the end of its life. Each satellite will have a nominal seven-year lifetime. A fourth MSG satellite of the same design is foreseen to ensure continuity of service until the end of the next decade. Additional information can be found at "http://www.esa.int/SPECIALS/MSG/" Group: Platform_Details Entry_ID: MSG Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: METEOSAT Short_Name: MSG Long_Name: Meteosat Second Generation End_Group Group: Synonymous_Platform_Names Short_Name: Meteosat-9 Short_Name: Meteosat-8 Short_Name: MSG-1 Short_Name: MSG-2 End_Group Group: Platform_Associated_Instruments Short_Name: GERB Short_Name: SEVIRI End_Group Group: Orbit Orbit_Altitude: 35,800 km Orbit_Inclination: 0 degrees Orbit_Type: GEO > Geosynchronous > Geostationary End_Group Creation_Date: 2008-07-29 Online_Resource: http://www.esa.int/esaMI/MSG/SEMQSCULWFE_0.html Group: Platform_Logistics Launch_Date: 2005-12-25 Launch_Site: Kourou, French Guiana Design_Life: 7 years Primary_Sponsor: EUMETSAT End_Group End_Group 2016-06-09 15:34:01.0 [epneff] added altLabel insert AltLabel (id: null text: MSG02 language code: en); QUIKSCAT [Text Source: NASA Science Mission Directorate Homepage, https://www.jpl.nasa.gov/missions/quick-scatterometer-quikscat/ ] QuikSCAT mission is intended to record sea-surface wind speed and direction data under all weather and cloud conditions over Earth's oceans. QuikSCAT was initiated as a "quick recovery" mission to help reduce the ocean-wind vector data gap created by the loss of the NASA Scatterometer (NSCAT) on the Japanese Advanced Earth Observing Satellite (ADEOS), which ceased functioning when ADEOS failed on June 30, 1997. QuikSCAT was launched from Vandenberg Air Force Base, Calif., aboard a Titan II vehicle, reducing the data gap by about one-half. QuikSCAT operates in a near polar orbit. It flies in a circular orbit at an altitude of approximately 800 km (500 miles) above Earth's surface. It completes a full orbit in about 101 minutes, which translates to a little more than 14 orbits per day. SeaWinds is the main instrument on the QuikSCAT satellite. SeaWinds is an active radar scatterometer. This scatterometer operates by transmitting high-frequency microwave pulses to the ocean surface and measuring the echoed radar pulses bounced back to the satellite. The scatterometer estimates wind speed and direction over the Earth's oceans at 10 m above the surface of the water. The instrument collects data over ocean, land, and ice in a continuous, 1,800-kilometer-wide band, making approximately 400,000 measurements and covering 90% of Earth's surface in one day. QuikSCAT can acquire hundreds of times more observations of surface wind velocity each day than can ships and buoys, and can provide continuous, accurate and high-resolution measurements of both wind speeds and direction regardless of weather conditions. This data is vital for global climate research, operational weather forecasting, and storm warning. The SeaWinds scatterometer is providing unprecedented, frequent surface wind speed and direction measurements over the global oceans. Coupled with other satellite measurements of cloud patterns, water vapor and rain, the data are contributing to scientists' ability to predict the intensity, location and movements of hurricanes and other severe marine weather patterns. Group: Platform_Details Entry_ID: QUIKSCAT Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: QUIKSCAT Long_Name: Quick Recovery Scatterometer End_Group Group: Synonymous_Platform_Names Short_Name: QUIKSCAT End_Group Group: Platform_Associated_Instruments Short_Name: SEAWINDS End_Group Group: Orbit Orbit_Altitude: 803 km Orbit_Inclination: 98.6 degrees Equator_Crossing: 6:00 p.m. Period: 101 minutes Perigee: 804 km (499 mi) Apogee: 806 km (500 mi) Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-04-16 Online_Resource: https://www.jpl.nasa.gov/missions/quick-scatterometer-quikscat/ Online_Resource: [Text Source: NASA Science Mission Directorate Homepage, https://www.jpl.nasa.gov/missions/quick-scatterometer-quikscat/ ] QuikSCAT mission is intended to record sea-surface wind speed and direction data under all weather and cloud conditions over Earth's oceans. QuikSCAT was initiated as a "quick recovery" mission to help reduce the ocean-wind vector data gap created by the loss of the NASA Scatterometer (NSCAT) on the Japanese Advanced Earth Observing Satellite (ADEOS), which ceased functioning when ADEOS failed on June 30, 1997. QuikSCAT was launched from Vandenberg Air Force Base, Calif., aboard a Titan II vehicle, reducing the data gap by about one-half. QuikSCAT operates in a near polar orbit. It flies in a circular orbit at an altitude of approximately 800 km (500 miles) above Earth's surface. It completes a full orbit in about 101 minutes, which translates to a little more than 14 orbits per day. SeaWinds is the main instrument on the QuikSCAT satellite. SeaWinds is an active radar scatterometer. This scatterometer operates by transmitting high-frequency microwave pulses to the ocean surface and measuring the echoed radar pulses bounced back to the satellite. The scatterometer estimates wind speed and direction over the Earth's oceans at 10 m above the surface of the water. The instrument collects data over ocean, land, and ice in a continuous, 1,800-kilometer-wide band, making approximately 400,000 measurements and covering 90% of Earth's surface in one day. QuikSCAT can acquire hundreds of times more observations of surface wind velocity each day than can ships and buoys, and can provide continuous, accurate and high-resolution measurements of both wind speeds and direction regardless of weather conditions. This data is vital for global climate research, operational weather forecasting, and storm warning. The SeaWinds scatterometer is providing unprecedented, frequent surface wind speed and direction measurements over the global oceans. Coupled with other satellite measurements of cloud patterns, water vapor and rain, the data are contributing to scientists' ability to predict the intensity, location and movements of hurricanes and other severe marine weather patterns. Group: Platform_Details Entry_ID: QUIKSCAT Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: QUIKSCAT Long_Name: Quick Recovery Scatterometer End_Group Group: Synonymous_Platform_Names Short_Name: QUIKSCAT End_Group Group: Platform_Associated_Instruments Short_Name: SEAWINDS End_Group Group: Orbit Orbit_Altitude: 803 km Orbit_Inclination: 98.6 degrees Equator_Crossing: 6:00 p.m. Period: 101 minutes Perigee: 804 km (499 mi) Apogee: 806 km (500 mi) Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-04-16 Online_Resource: https://winds.jpl.nasa.gov/missions/quikscat/index.cfm Online_Resource: https://www.jpl.nasa.gov/missions/quick-scatterometer-quikscat/ Group: Platform_Logistics Launch_Date: 1999-06-19 Launch_Site: Vandenberg Air Force Base, USA Design_Life: 3 years (exceeded) Primary_Sponsor: USA/NASA End_Group End_Group Group: Platform_Logistics Launch_Date: 1999-06-19 Launch_Site: Vandenberg Air Force Base, USA Design_Life: 3 years (exceeded) Primary_Sponsor: USA/NASA End_Group End_Group 2020-01-31 22:13:30.0 [sritz] update Definition ([Text Source: NASA Science Mission Directorate Homepage, https://www.jpl.nasa.gov/missions/quick-scatterometer-quikscat/ ] QuikSCAT mission is intended to record sea-surface wind speed and direction data under all weather and cloud conditions over Earth's oceans. QuikSCAT was initiated as a "quick recovery" mission to help reduce the ocean-wind vector data gap created by the loss of the NASA Scatterometer (NSCAT) on the Japanese Advanced Earth Observing Satellite (ADEOS), which ceased functioning when ADEOS failed on June 30, 1997. QuikSCAT was launched from Vandenberg Air Force Base, Calif., aboard a Titan II vehicle, reducing the data gap by about one-half. QuikSCAT operates in a near polar orbit. It flies in a circular orbit at an altitude of approximately 800 km (500 miles) above Earth's surface. It completes a full orbit in about 101 minutes, which translates to a little more than 14 orbits per day. SeaWinds is the main instrument on the QuikSCAT satellite. SeaWinds is an active radar scatterometer. This scatterometer operates by transmitting high-frequency microwave pulses to the ocean surface and measuring the echoed radar pulses bounced back to the satellite. The scatterometer estimates wind speed and direction over the Earth's oceans at 10 m above the surface of the water. The instrument collects data over ocean, land, and ice in a continuous, 1,800-kilometer-wide band, making approximately 400,000 measurements and covering 90% of Earth's surface in one day. QuikSCAT can acquire hundreds of times more observations of surface wind velocity each day than can ships and buoys, and can provide continuous, accurate and high-resolution measurements of both wind speeds and direction regardless of weather conditions. This data is vital for global climate research, operational weather forecasting, and storm warning. The SeaWinds scatterometer is providing unprecedented, frequent surface wind speed and direction measurements over the global oceans. Coupled with other satellite measurements of cloud patterns, water vapor and rain, the data are contributing to scientists' ability to predict the intensity, location and movements of hurricanes and other severe marine weather patterns. Group: Platform_Details Entry_ID: QUIKSCAT Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: QUIKSCAT Long_Name: Quick Recovery Scatterometer End_Group Group: Synonymous_Platform_Names Short_Name: QUIKSCAT End_Group Group: Platform_Associated_Instruments Short_Name: SEAWINDS End_Group Group: Orbit Orbit_Altitude: 803 km Orbit_Inclination: 98.6 degrees Equator_Crossing: 6:00 p.m. Period: 101 minutes Perigee: 804 km (499 mi) Apogee: 806 km (500 mi) Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-04-16 Online_Resource: https://www.jpl.nasa.gov/missions/quick-scatterometer-quikscat/ Online_Resource: [Text Source: NASA Science Mission Directorate Homepage, https://www.jpl.nasa.gov/missions/quick-scatterometer-quikscat/ ] QuikSCAT mission is intended to record sea-surface wind speed and direction data under all weather and cloud conditions over Earth's oceans. QuikSCAT was initiated as a "quick recovery" mission to help reduce the ocean-wind vector data gap created by the loss of the NASA Scatterometer (NSCAT) on the Japanese Advanced Earth Observing Satellite (ADEOS), which ceased functioning when ADEOS failed on June 30, 1997. QuikSCAT was launched from Vandenberg Air Force Base, Calif., aboard a Titan II vehicle, reducing the data gap by about one-half. QuikSCAT operates in a near polar orbit. It flies in a circular orbit at an altitude of approximately 800 km (500 miles) above Earth's surface. It completes a full orbit in about 101 minutes, which translates to a little more than 14 orbits per day. SeaWinds is the main instrument on the QuikSCAT satellite. SeaWinds is an active radar scatterometer. This scatterometer operates by transmitting high-frequency microwave pulses to the ocean surface and measuring the echoed radar pulses bounced back to the satellite. The scatterometer estimates wind speed and direction over the Earth's oceans at 10 m above the surface of the water. The instrument collects data over ocean, land, and ice in a continuous, 1,800-kilometer-wide band, making approximately 400,000 measurements and covering 90% of Earth's surface in one day. QuikSCAT can acquire hundreds of times more observations of surface wind velocity each day than can ships and buoys, and can provide continuous, accurate and high-resolution measurements of both wind speeds and direction regardless of weather conditions. This data is vital for global climate research, operational weather forecasting, and storm warning. The SeaWinds scatterometer is providing unprecedented, frequent surface wind speed and direction measurements over the global oceans. Coupled with other satellite measurements of cloud patterns, water vapor and rain, the data are contributing to scientists' ability to predict the intensity, location and movements of hurricanes and other severe marine weather patterns. Group: Platform_Details Entry_ID: QUIKSCAT Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: QUIKSCAT Long_Name: Quick Recovery Scatterometer End_Group Group: Synonymous_Platform_Names Short_Name: QUIKSCAT End_Group Group: Platform_Associated_Instruments Short_Name: SEAWINDS End_Group Group: Orbit Orbit_Altitude: 803 km Orbit_Inclination: 98.6 degrees Equator_Crossing: 6:00 p.m. Period: 101 minutes Perigee: 804 km (499 mi) Apogee: 806 km (500 mi) Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-04-16 Online_Resource: https://winds.jpl.nasa.gov/missions/quikscat/index.cfm Online_Resource: https://www.jpl.nasa.gov/missions/quick-scatterometer-quikscat/ Group: Platform_Logistics Launch_Date: 1999-06-19 Launch_Site: Vandenberg Air Force Base, USA Design_Life: 3 years (exceeded) Primary_Sponsor: USA/NASA End_Group End_Group Group: Platform_Logistics Launch_Date: 1999-06-19 Launch_Site: Vandenberg Air Force Base, USA Design_Life: 3 years (exceeded) Primary_Sponsor: USA/NASA End_Group End_Group); 2019-12-31 18:58:24.0 [sritz] update Definition ([Text Source: NASA Science Mission Directorate Homepage, https://www.jpl.nasa.gov/missions/quick-scatterometer-quikscat/ ] QuikSCAT mission is intended to record sea-surface wind speed and direction data under all weather and cloud conditions over Earth's oceans. QuikSCAT was initiated as a "quick recovery" mission to help reduce the ocean-wind vector data gap created by the loss of the NASA Scatterometer (NSCAT) on the Japanese Advanced Earth Observing Satellite (ADEOS), which ceased functioning when ADEOS failed on June 30, 1997. QuikSCAT was launched from Vandenberg Air Force Base, Calif., aboard a Titan II vehicle, reducing the data gap by about one-half. QuikSCAT operates in a near polar orbit. It flies in a circular orbit at an altitude of approximately 800 km (500 miles) above Earth's surface. It completes a full orbit in about 101 minutes, which translates to a little more than 14 orbits per day. SeaWinds is the main instrument on the QuikSCAT satellite. SeaWinds is an active radar scatterometer. This scatterometer operates by transmitting high-frequency microwave pulses to the ocean surface and measuring the echoed radar pulses bounced back to the satellite. The scatterometer estimates wind speed and direction over the Earth's oceans at 10 m above the surface of the water. The instrument collects data over ocean, land, and ice in a continuous, 1,800-kilometer-wide band, making approximately 400,000 measurements and covering 90% of Earth's surface in one day. QuikSCAT can acquire hundreds of times more observations of surface wind velocity each day than can ships and buoys, and can provide continuous, accurate and high-resolution measurements of both wind speeds and direction regardless of weather conditions. This data is vital for global climate research, operational weather forecasting, and storm warning. The SeaWinds scatterometer is providing unprecedented, frequent surface wind speed and direction measurements over the global oceans. Coupled with other satellite measurements of cloud patterns, water vapor and rain, the data are contributing to scientists' ability to predict the intensity, location and movements of hurricanes and other severe marine weather patterns. Group: Platform_Details Entry_ID: QUIKSCAT Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: QUIKSCAT Long_Name: Quick Recovery Scatterometer End_Group Group: Synonymous_Platform_Names Short_Name: QUIKSCAT End_Group Group: Platform_Associated_Instruments Short_Name: SEAWINDS End_Group Group: Orbit Orbit_Altitude: 803 km Orbit_Inclination: 98.6 degrees Equator_Crossing: 6:00 p.m. Period: 101 minutes Perigee: 804 km (499 mi) Apogee: 806 km (500 mi) Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-04-16 Online_Resource: https://www.jpl.nasa.gov/missions/quick-scatterometer-quikscat/ Online_Resource: [Text Source: NASA Science Mission Directorate Homepage, https://www.jpl.nasa.gov/missions/quick-scatterometer-quikscat/ ] QuikSCAT mission is intended to record sea-surface wind speed and direction data under all weather and cloud conditions over Earth's oceans. QuikSCAT was initiated as a "quick recovery" mission to help reduce the ocean-wind vector data gap created by the loss of the NASA Scatterometer (NSCAT) on the Japanese Advanced Earth Observing Satellite (ADEOS), which ceased functioning when ADEOS failed on June 30, 1997. QuikSCAT was launched from Vandenberg Air Force Base, Calif., aboard a Titan II vehicle, reducing the data gap by about one-half. QuikSCAT operates in a near polar orbit. It flies in a circular orbit at an altitude of approximately 800 km (500 miles) above Earth's surface. It completes a full orbit in about 101 minutes, which translates to a little more than 14 orbits per day. SeaWinds is the main instrument on the QuikSCAT satellite. SeaWinds is an active radar scatterometer. This scatterometer operates by transmitting high-frequency microwave pulses to the ocean surface and measuring the echoed radar pulses bounced back to the satellite. The scatterometer estimates wind speed and direction over the Earth's oceans at 10 m above the surface of the water. The instrument collects data over ocean, land, and ice in a continuous, 1,800-kilometer-wide band, making approximately 400,000 measurements and covering 90% of Earth's surface in one day. QuikSCAT can acquire hundreds of times more observations of surface wind velocity each day than can ships and buoys, and can provide continuous, accurate and high-resolution measurements of both wind speeds and direction regardless of weather conditions. This data is vital for global climate research, operational weather forecasting, and storm warning. The SeaWinds scatterometer is providing unprecedented, frequent surface wind speed and direction measurements over the global oceans. Coupled with other satellite measurements of cloud patterns, water vapor and rain, the data are contributing to scientists' ability to predict the intensity, location and movements of hurricanes and other severe marine weather patterns. Group: Platform_Details Entry_ID: QUIKSCAT Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: QUIKSCAT Long_Name: Quick Recovery Scatterometer End_Group Group: Synonymous_Platform_Names Short_Name: QUIKSCAT End_Group Group: Platform_Associated_Instruments Short_Name: SEAWINDS End_Group Group: Orbit Orbit_Altitude: 803 km Orbit_Inclination: 98.6 degrees Equator_Crossing: 6:00 p.m. Period: 101 minutes Perigee: 804 km (499 mi) Apogee: 806 km (500 mi) Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-04-16 Online_Resource: http://winds.jpl.nasa.gov/missions/quikscat/index.cfm Online_Resource: https://www.jpl.nasa.gov/missions/quick-scatterometer-quikscat/ Group: Platform_Logistics Launch_Date: 1999-06-19 Launch_Site: Vandenberg Air Force Base, USA Design_Life: 3 years (exceeded) Primary_Sponsor: USA/NASA End_Group End_Group Group: Platform_Logistics Launch_Date: 1999-06-19 Launch_Site: Vandenberg Air Force Base, USA Design_Life: 3 years (exceeded) Primary_Sponsor: USA/NASA End_Group End_Group); 2019-12-31 18:56:12.0 [sritz] update Definition ([Text Source: NASA Science Mission Directorate Homepage, https://www.jpl.nasa.gov/missions/quick-scatterometer-quikscat/ ] QuikSCAT mission is intended to record sea-surface wind speed and direction data under all weather and cloud conditions over Earth's oceans. QuikSCAT was initiated as a "quick recovery" mission to help reduce the ocean-wind vector data gap created by the loss of the NASA Scatterometer (NSCAT) on the Japanese Advanced Earth Observing Satellite (ADEOS), which ceased functioning when ADEOS failed on June 30, 1997. QuikSCAT was launched from Vandenberg Air Force Base, Calif., aboard a Titan II vehicle, reducing the data gap by about one-half. QuikSCAT operates in a near polar orbit. It flies in a circular orbit at an altitude of approximately 800 km (500 miles) above Earth's surface. It completes a full orbit in about 101 minutes, which translates to a little more than 14 orbits per day. SeaWinds is the main instrument on the QuikSCAT satellite. SeaWinds is an active radar scatterometer. This scatterometer operates by transmitting high-frequency microwave pulses to the ocean surface and measuring the echoed radar pulses bounced back to the satellite. The scatterometer estimates wind speed and direction over the Earth's oceans at 10 m above the surface of the water. The instrument collects data over ocean, land, and ice in a continuous, 1,800-kilometer-wide band, making approximately 400,000 measurements and covering 90% of Earth's surface in one day. QuikSCAT can acquire hundreds of times more observations of surface wind velocity each day than can ships and buoys, and can provide continuous, accurate and high-resolution measurements of both wind speeds and direction regardless of weather conditions. This data is vital for global climate research, operational weather forecasting, and storm warning. The SeaWinds scatterometer is providing unprecedented, frequent surface wind speed and direction measurements over the global oceans. Coupled with other satellite measurements of cloud patterns, water vapor and rain, the data are contributing to scientists' ability to predict the intensity, location and movements of hurricanes and other severe marine weather patterns. Group: Platform_Details Entry_ID: QUIKSCAT Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: QUIKSCAT Long_Name: Quick Recovery Scatterometer End_Group Group: Synonymous_Platform_Names Short_Name: QUIKSCAT End_Group Group: Platform_Associated_Instruments Short_Name: SEAWINDS End_Group Group: Orbit Orbit_Altitude: 803 km Orbit_Inclination: 98.6 degrees Equator_Crossing: 6:00 p.m. Period: 101 minutes Perigee: 804 km (499 mi) Apogee: 806 km (500 mi) Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-04-16 Online_Resource: http://winds.jpl.nasa.gov/missions/quikscat/index.cfm Online_Resource: http://nasascience.nasa.gov/missions/quikscat Group: Platform_Logistics Launch_Date: 1999-06-19 Launch_Site: Vandenberg Air Force Base, USA Design_Life: 3 years (exceeded) Primary_Sponsor: USA/NASA End_Group End_Group); update Definition (https://www.jpl.nasa.gov/missions/quick-scatterometer-quikscat/); TIMED NASA's Thermosphere, Ionosphere, Mesosphere Energetics and Dynamics (TIMED) spacecraft was launched on December 7, 2001 from Vandenberg AFB. The spacecraft was built by The Johns Hopkins University Applied Physics Laboratory (APL) and shares the same launch vehicle as NASA's Jason-1 spacecraft. TIMED is the first mission in NASA's Solar Terrestrial Probes Program and will study the influences of the sun and humans on the mesosphere and Lower Thermosphere/Ionosphere (MLTI). TIMED will focus on a portion of the atmosphere between 60-180 km above the surface. TIMED's payload consists of four instruments: - Global Ultraviolet Imager (GUVI): a spatial scanning ultraviolet spectrograph designed to measure the composition and temperature profiles of the MLTI region, as well as its auroral energy inputs. - Solar Extreme Ultraviolet Experiment (SEE): comprised of a spectrometer and a suite of photometers designed to measure the solar soft X-ray, extreme ultraviolet and far-ultraviolet radiation in the MLTI region. - TIMED Doppler Interferometer (TIDI): designed to measure the wind and temperature profiles of the MLTI region. - Sounding of the Atmosphere using Broadband Emission Radiometry (SABER): designed to measure the pressure, temperature, key gases in the oxygen and hydrogen families, infrared cooling, and effects of solar and chemical heating of the MLTI region. TIMED is sponsored by NASA's Office of Space Science and is managed by NASA's Goddard Space Flight Center's Solar Terrestrial Probes program Office. The Johns Hopkins Applied Physics Laboratory operates the spacecraft and leads the science effort. For more information, see: http://www.timed.jhuapl.edu Group: Platform_Details Entry_ID: TIMED Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: TIMED Long_Name: Thermosphere, Ionosphere, Mesosphere Energetics and Dynamics End_Group Group: Synonymous_Platform_Names Short_Name: 26998 Short_Name: 2001-055B End_Group Group: Platform_Associated_Instruments Short_Name: TIDI Short_Name: SEE Short_Name: SABER Short_Name: GUVI End_Group Group: Orbit Orbit_Altitude: 625 km Orbit_Inclination: 74.1 degrees Period: 97.3 m Perigee: 627 km Apogee: 628 km Orbit_Type: LEO > Low Earth Orbit > Inclined Non-Polar End_Group Online_Resource: http://www.timed.jhuapl.edu/WWW/index.php Sample_Image: http://nssdc.gsfc.nasa.gov/image/spacecraft/timed.jpg Group: Platform_Logistics Launch_Date: 2001-12-07 Launch_Site: Vandenberg Air Force Base, USA Design_Life: 2 years Primary_Sponsor: NASA Primary_Sponsor: Johns Hopkins University/Applied Physics Lab End_Group End_Group OV-102 Columbia, the oldest orbiter in the Shuttle fleet, is named after the Boston, Massachusetts based sloop captained by American Robert Gray. The spaceship Columbia has continued the pioneering legacy of its forebears, becoming the first Space Shuttle to fly into Earth orbit in 1981. Four sister ships joined the fleet over the next 10 years: Challenger, arriving in 1982 but destroyed four years later; Discovery, 1983; Atlantis, 1985; and Endeavour, built as a replacement for Challenger, 1991. A test vehicle, the Enterprise, was used for suborbital approach and landing tests and did not fly in space. Columbia was the first on-line orbiter to undergo the scheduled inspection and retrofit program. It was transported August 10, 1991, after its completion of mission STS-40, to prime Shuttle contractor Rockwell International's Palmdale, California assembly plant. The oldest orbiter in the fleet underwent approximately 50 modifications, including the addition of carbon brakes, drag chute, improved nose wheel steering, removal of development flight instrumentation and an enhancement of its thermal protection system. The orbiter returned to KSC February 9, 1992 to begin processing for mission STS-50 in June of that year. On October 8, 1994, Columbia was transported to Palmdale California for its first ODMP. Approximately 90 modifications and upgrades were made to Columbia during this 6 month period. Modifications included upgrades to the main landing gear thermal barrier, tire pressure monitoring system and radiator drive circuitry. (Reference KSC Press Release 113-94 and Shuttle Status Report 10/10/94) On September 24, 1999, Columbia was transported to Palmdale California for its second ODMP. While in California, workers will perform more than 100 modifications on the vehicle. Columbia will be the second orbiter outfitted with the multi-functional electronic display system (MEDS) or "glass cockpit". Last year, Shuttle Atlantis had the full-color, flat-panel displays installed on its flight deck during an OMDP. The new system improves crew interaction with the orbiter during flight and reduces the high cost of maintaining the outdated electromechanical cockpit displays currently onboard. (Reference KSC Press Release 74-99). On February 1, 2003, Columbia was lost during re-entry into Earth's atmosphere. [Summary provided by NASA] Group: Platform_Details Entry_ID: OV-102 Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Platform_Series_or_Entity: SPACE SHUTTLE Short_Name: OV-102 Long_Name: Columbia Space Shuttle End_Group Group: Synonymous_Platform_Names Short_Name: Columbia End_Group Creation_Date: 2008-01-24 Online_Resource: http://science.ksc.nasa.gov/shuttle/resources/orbiters/columbia.html Sample_Image: http://science.ksc.nasa.gov/shuttle/resources/orbiters/columbia-logo.gif Group: Platform_Logistics Primary_Sponsor: NASA End_Group End_Group Joint Polar Satellite System (JPSS) The Joint Polar Satellite System (JPSS) is the Nation's new generation polar-orbiting operational environmental satellite system. JPSS is a collaborative program between the National Oceanic and Atmospheric Administration (NOAA) and its acquisition agent, National Aeronautics and Space Administration (NASA). This interagency effort is the latest generation of U.S. polar-orbiting, non-geosynchronous environmental satellites. More Information: https://www.jpss.noaa.gov 2019-10-04 19:39:39.0 [sritz] insert Definition (id: null text: The Joint Polar Satellite System (JPSS) is the Nation's new generation polar-orbiting operational environmental satellite system. JPSS is a collaborative program between the National Oceanic and Atmospheric Administration (NOAA) and its acquisition agent, National Aeronautics and Space Administration (NASA). This interagency effort is the latest generation of U.S. polar-orbiting, non-geosynchronous environmental satellites. More Information: https://www.jpss.noaa.gov language code: en); 2017-11-27 17:19:09.0 [sritz] Move Concepts add narrower relation (Joint Polar Satellite System (JPSS) [5c2364ca-c01a-4f69-8808-282c3854b2f6,287871] - NOAA-20 [586db0b3-5f94-466e-b7c1-a2dbedc0c1fc,287835]); 2017-11-27 16:46:53.0 [sritz] Move Concepts delete narrower relation (null); 2016-07-19 19:28:26.0 [saritz] insert WeightedRelation (id: null related concept uuid: 586db0b3-5f94-466e-b7c1-a2dbedc0c1fc relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 043dc242-1014-4e9a-91ee-c472b791b026 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 2ab4ba32-0bb3-4e4e-bac6-1ff4a3baf0df relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 10adce36-ce10-4ae6-94f9-211911c7dd15 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 85a52725-e6a1-430a-8506-c08c59ef31c7 relationship type: null relationship value: null generated by: null); 2016-07-19 18:47:05.0 [saritz] Insert Concept add narrower relation (Joint Polar Satellite System (JPSS) [5c2364ca-c01a-4f69-8808-282c3854b2f6,226695] - JPSS-4 [10adce36-ce10-4ae6-94f9-211911c7dd15,247457]); 2016-07-19 18:46:51.0 [saritz] Insert Concept add narrower relation (Joint Polar Satellite System (JPSS) [5c2364ca-c01a-4f69-8808-282c3854b2f6,226695] - JPSS-3 [2ab4ba32-0bb3-4e4e-bac6-1ff4a3baf0df,247453]); 2016-07-19 18:46:38.0 [saritz] Insert Concept add narrower relation (Joint Polar Satellite System (JPSS) [5c2364ca-c01a-4f69-8808-282c3854b2f6,226695] - JPSS-2 [043dc242-1014-4e9a-91ee-c472b791b026,247449]); LEARJET The Learjet started life as an abortive Swiss ground-attack fighter aircraft, the FFA P-16. Development started in 1952 and prototypes were ordered the next year. The first prototypes flew in 1955 and construction and testing continued until 1958 when an order for 100 was placed. This was reversed soon after due to a crash of the third prototype. Two additional prototypes were finished, the last in 1960, but the project was ended at this point. The basic structure of this aircraft was seen by Bill Lear and his team as a good starting point to the development of a business jet, which was originally intended to be called the SAAC-23. The wing with its distinctive tip fuel tanks and landing gear of the first Learjets were little changed from those used by the fighter prototypes. The tooling for building the aircraft was purchased and moved to Wichita, Kansas in 1962. On February 7, assembly of the first Learjet began. The next year, the company was renamed the Lear Jet Corporation. [Text provided by: http://en.wikipedia.org/wiki/Learjet ] [Photo provided by: http://www.aerospace-technology.com ] Group: Platform_Details Entry_ID: LEARJET Group: Platform_Identification Platform_Category: Aircraft Short_Name: LEARJET End_Group Creation_Date: 2008-07-14 Online_Resource: http://www.learjet.com/ Online_Resource: http://en.wikipedia.org/wiki/Learjet Sample_Image: http://www.aerospace-technology.com/projects/learjet/images/Learjet45_2.jpg End_Group 2020-03-26 22:06:06.0 [sritz] update WeightedRelation (Undefined); 2020-03-26 21:50:08.0 [sritz] update WeightedRelation (Platform-Instrument); update WeightedRelation (1.0); 2020-03-26 21:49:26.0 [sritz] update Resource (image); insert WeightedRelation (id: null related concept uuid: 5e573a56-b485-4a7f-a652-6d941e7d0ce0 relationship type: null relationship value: null generated by: null); ADEOS-II ADEOS-2 ADEOS (ADvanced Earth Observation Satellite), developed by the Japanese space agency JAXA. ADEOS-II, the successor to ADEOS, has been developed to advance Earth observation technologies. It acquires data to help researchers understand the mechanism of the global environmental changes such as global warming and to support meteorology and fishery activities.It is equipped with two JAXA sensors (AMSR and GLI) and three sensors provided by international and domestic partners (ILAS-II, SeaWinds Scatterometer and POLDER).ADEOS-II is expected to provide the data necessary for us to understand the circulation of water, energy, and carbon in order to contribute to studies on global environmental changes. ADEOS-II has been launched in December 2002 by H-II launcher from Tanegashima Space Center and was lost on October 2003, the 24th.[http://smsc.cnes.fr/POLDER/index.htm] Group: Platform_Details Entry_ID: ADEOS-II Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: ADEOS (Advanced Earth Observing Satellite) Short_Name: ADEOS-II Long_Name: Advanced Earth Observing Satellite-II End_Group Group: Synonymous_Platform_Names Short_Name: Midori 2 Short_Name: 27597 End_Group Group: Platform_Associated_Instruments Short_Name: SEAWINDS Short_Name: POLDER-2 Short_Name: ILAS II Short_Name: GLI Short_Name: AMSR Short_Name: ACATS End_Group Group: Orbit Orbit_Altitude: 802.92km Orbit_Inclination: 98.62 degrees Period: 101 minutes Repeat_Cycle: 4 days Perigee: 806.0 km Apogee: 807.0 km Orbit_Type: MEO > SEMI-SYNCHRONOUS > GEODETIC/SPACE ENVIRONMENT End_Group Creation_Date: 2007-08-22 Online_Resource: http://sharaku.eorc.jaxa.jp/ADEOS2/ Online_Resource: http://www-ilas2.nies.go.jp/en/project/adeos2.html Online_Resource: http://winds.jpl.nasa.gov/missions/seawinds/index.cfm Online_Resource: http://nasascience.nasa.gov/missions/seawinds Sample_Image: http://sharaku.eorc.jaxa.jp/ADEOS2/over/image/adeos22.gif Group: Platform_Logistics Launch_Date: 2002-12-14 Launch_Site: Tanegashima Island, Japan Design_Life: 3 years Primary_Sponsor: Japan/JAXA End_Group End_Group 2016-06-09 14:27:58.0 [epneff] added altLabel insert AltLabel (id: null text: ADEOS-2 language code: en); 2015-05-08 18:23:53.0 [saritz] update PrefLabel (ADEOS-II); 2014-02-27 14:45:32.0 [mpmorahan] Rename Concept update PrefLabel (ADEOS-2); HELIOS 2 Helios 2 was launched into a solar orbit on 15 January 1976. It had a perihelion of 0.29 AU and an aphelion of 1 AU. Its orbit made it an ideal platform for making long baseline time-of-arrival measurements to obtain source direction. The satellite rotated with a ~ 1-s spin period. The mission ended in 1981. Information provided by http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/helios2.html Group: Platform_Details Entry_ID: HELIOS 2 Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Short_Name: HELIOS 2 End_Group Group: Synonymous_Platform_Names Short_Name: HELIOS 2 Short_Name: 08582 End_Group Group: Platform_Associated_Instruments Short_Name: SCINTILLATION COUNTERS End_Group Group: Orbit Orbit_Inclination: 0.0° Period: 185.6 days End_Group Creation_Date: 2007-08-13 Online_Resource: http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/helios2.html Online_Resource: http://www.cnes.fr/web/CNES-en/2743-helios-ii-a-new-generation-of-military-satellites.php Sample_Image: http://heasarc.gsfc.nasa.gov/Images/misc_missions/helios2.gif Group: Platform_Logistics Launch_Date: 1976-01-15 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: USA/NASA Primary_Sponsor: Germany End_Group End_Group LANDSAT-9 Landsat 9—a partnership between NASA and the U.S. Geological Survey— will continue the Landsat program’s critical role in monitoring, understanding and managing the land resources needed to sustain human life. Today’s increased rates of global land cover and land use change have profound consequences for weather and climate change, ecosystem function and services, carbon cycling and sequestration, resource management, the national and global economy, human health, and society. Landsat is the only U.S. satellite system designed and operated to repeatedly observe the global land surface at a moderate scale that shows both natural and human-induced change. Landsat 9 has been fast-tracked for a December 2020 launch. More Information: https://landsat.gsfc.nasa.gov/landsat-9/ https://www.usgs.gov/land-resources/nli/landsat/landsat-9 2019-12-31 22:01:32.0 [sritz] insert Definition (id: null text: Landsat 9—a partnership between NASA and the U.S. Geological Survey— will continue the Landsat program’s critical role in monitoring, understanding and managing the land resources needed to sustain human life. Today’s increased rates of global land cover and land use change have profound consequences for weather and climate change, ecosystem function and services, carbon cycling and sequestration, resource management, the national and global economy, human health, and society. Landsat is the only U.S. satellite system designed and operated to repeatedly observe the global land surface at a moderate scale that shows both natural and human-induced change. Landsat 9 has been fast-tracked for a December 2020 launch. More Information: https://landsat.gsfc.nasa.gov/landsat-9/ https://www.usgs.gov/land-resources/nli/landsat/landsat-9 language code: en); 2019-12-31 21:59:57.0 [sritz] Insert Concept add broader relation (LANDSAT-9 [5d3ce672-39fb-4dd5-be5e-55f81fb7f40f,559589] - LANDSAT [3cc4a1e8-3b94-4567-90b3-32137aec2d9e,541561]); SOLAR OBSERVATORY STATIONS ALSAT-1 AlSAT-1 is part of an international (BNSC-UK, China, Nigeria and Thailand) disaster-monitoring constellation (DMC) of 6 micro-satellites dedicated for monitoring disasters throughout the earth, such as floods, fires, earthquakes, volcanoes, large-scale industrial accidents and civil strife. When there are no disasters, AlSAT-1 will be used for Algerian purposes such as monitoring desertification, industrial and marine pollution, agricultural monitoring, geophysics mapping and fire detection. The nature of the mission is that the 6 micro-satellites, when coordinated together, can produce a daily revisit with a 32 m resolution multi-spectral imaging and 600 km ground track. AlSAT-1 uses the flight proven modular SSTL bus from previous missions but will carry a push broom imager for the first time on SSTL micro-satellites. As a part of the constellation and to maintain a daily coverage, AlSAT-1 is equipped with a propulsion system for orbit corrections. AlSAT-1's main payload a multi-spectral earth observation imager. Digital store and forward communications can be experienced between two points and autonomous GPS positioning techniques also accomplished. The Algerian satellite is one of SSTL’s new generation microsatellites in a sense that it carries a new type of push broom sensors. These types of sensors can previously only be found in larger commercial satellites. Because of the advance in electronics and semiconductor integration on a single chip, nowadays these sensors are being implemented by SSTL on microsatellites. AlSAT-1 is designed to view the earth surface with a 32 m resolution in three spectral bands (R, G, NIR) and a ground track of 600 km. The spectral bands were chosen to correspond to those used by commercial satellites in the following wavelengths (in micrometer) 0.5-0.6 micrometer, 0.6-0.7 , 0.7-0.8 ). The imaging system comprises two cameras for each spectral band and two sensors with 10 000 pixels each. This represents a huge quantity of data for the electronics on board (processors, SSDR, fast clocks) to deal with. The cameras provide 32 m ground resolution in 3 spectral bands capable of giving detailed information on earth resources, land use and effects of pollution and natural disasters using 2x10 000 pixels linear array detectors digitized to 8 bits radiometric resolution (256 levels). The image swath width is 600 km and the imager can collect images continuously along the flight track. The images are stored on board the microsatellite via the On Board Computer (OBC) and Controller Area Network (CAN) in the 2x512 Mbytes Solid State Data Recorder (SSDR) for later transmission to ground via digital packet error controlled links at 8 Mbit/s in S-band. However, on the satellite there will be an option to do “windowing”. By using this technique, we can take images of 100x100 km and thus extend the track range. Group: Platform_Details Entry_ID: ALSAT-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: ALSAT-1 End_Group Group: Platform_Associated_Instruments Short_Name: SLIM-6 End_Group Group: Orbit Orbit_Altitude: 700 Orbit_Inclination: 98 Period: 98.4 Perigee: 676 Apogee: 691 Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2008-06-02 Online_Resource: https://directory.eoportal.org/web/eoportal/satellite-missions/a/alsat-2 Group: Platform_Logistics Launch_Date: 2002-11-28 Launch_Site: Plesetsk Cosmodrome, Russia Primary_Sponsor: Algeria End_Group End_Group DIADEM-1C Diadème-1 D1C and Diadème-2 D1D were launched by CNES, one week apart in February 1967 into elliptical orbits. Both Diadème satellites were geodetic missions. These satellites were magnetically stabilized which limited their trackability in the southern hemisphere. Group: Platform_Details Entry_ID: DIADEM-1C Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: DIADEM Short_Name: DIADEM-1C End_Group Group: Synonymous_Platform_Names Short_Name: Diadem-1C End_Group Group: Platform_Associated_Instruments Short_Name: DOPPLER BEACONS End_Group Group: Orbit Orbit_Inclination: 39.9 degrees Period: 101 minutes Perigee: 550 km Orbit_Type: HEO > Highly Elliptical Orbit End_Group Creation_Date: 2007-09-12 Online_Resource: http://ilrs.gsfc.nasa.gov/satellite_missions/list_of_satellites/di1d_general.html Sample_Image: http://ilrs.gsfc.nasa.gov/satellite_missions/slr_sats_pics/diadem.gif Group: Platform_Logistics Launch_Date: 1967-02-08 Primary_Sponsor: CNES End_Group End_Group NSRN The NOAA Solar Radiation Network is a collection of stations that provides solar radiations information, specifically, the amount of energy a user can expect from the Sun. History: NOAA and its predecessor agencies, the Environmental Science Services Administration and the Weather Bureau, have had the Federal civilian responsibilities for monitoring and documenting the climate of the United States, including solar radiation and many other weather elements required by the solar energy technology user. The solar radiation monitoring network has existed for about 75 years with varying numbers of stations. In the 1960's about 60 NOAA stations and 30 cooperative stations were reporting solar radiation data to the National Climatic Center (NCC) in Asheville, N.C. In addition, State, local, and private organizations were making measurements with varying degrees of regularity and quality. These non-NOAA networks continue and, if anything, have increased in number, and with DOE help some of their data will be archived and published by the NCC. Network Centers: The current network consists of 39 stations of which 35 are in the contiguous U.S. The remaining are in Alaska, Hawaii, Puerto Rico, and Guam. All stations are equipped to operate both a pyranometer and pyrheliometer. Fairbanks, AK Montgomery, AL Phoenix, AZ Fresno, CA Los Angeles, CA Boulder, CO Grand Junction, CO Miami, FL Tallahassee, FL Honolulu, HI Boise, ID Indianapolis, IN Dodge City, KS Lake Charles, LA Blue Hill, MA Caribou, ME Columbia, MO Great Falls, MT Raleigh, NC Bismark, ND Omaha, NE Albuquerque, NM Ely, NV Las Vegas, NV Medford, OR Pittsburgh, PA Nashville, TN Brownsville, TX El Paso, TX Midland, TX Salt Lake City, UT Sterling, VA Burlington, VT Seattle-Tacoma, WA Madison, WI Lander, WY Guam, Marianas Isl. San Juan, PR Desert Rock, NV [Source: Renewable Resource Data Center] ATS-1 ATS 1 was launched in December 1966 and was the first in a series of geostationary satellites to be used in a research mode, while also demonstrating communications satellite technology. It was designed for the purpose of (1) testing new concepts in spacecraft design, propulsion, and stabilization, (2) collecting high-quality cloudcover pictures and relaying processed meteorological data via an earth-synchronous satellite, (3) providing in situ measurements of the aerospace environment, and (4) testing improved communication systems. The spin-stabilized spacecraft was cylindrically shaped and measured 135 cm long and 142 cm in diameter. The primary structural members were a honeycombed equipment shelf and thrust tube. Support rods extended radially outward from the thrust tube. Solar panels were affixed to the support rods and formed the outer walls of the spacecraft. In addition to solar panels, the spacecraft was equipped with two rechargeable nickel-cadmium batteries to provide electrical power. Equipment components and payload were mounted in the annular space between the thrust tube and solar panels. This satellite carried a spin scan cloudcover camera, particle telescope, biaxal fluxgate magnetometer, suprathermal ion detector, omnidirectional spectrometer, weather facsimile data relay system, and VHF, telemetry and command antennas. Spacecraft guidance and orbital corrections were accomplished by a 2.3 kg hydrogen peroxide and hydrazine thrusters, which were activated by ground command. The satellite was initially placed at 151.16 degrees West over the Pacific Ocean in a geosynchronous orbit. In general, most of the experiments were successful. Data coverage was nominal until about 1970, after which limited real-time data acquisition was carried out by NOAA until the May 1974 launch of SMS 1. Limited ATS 1 data acquisition was started by NASA at about that time for ATS 1 - ATS 6 correlative studies. The spacecraft served as a communications satellite for a number of state, federal, and public organizations. It continued to operate at its final longitude of 164 degress East until September 1983, when the spacecraft was moved out of the geostationary orbit. __________ Taken from the NSSDC System for Information Retrieval and Storage (SIRS). For more information contact the NSSDC Coordinated Request and User Support Office, 301-286-6695 (NASA Goddard Space Flight Center, Code 933.4, Greenbelt, Maryland 20771, USA). SPOT-4 SPOT-4 (SYSTEME PROBATOIRE POUR L'OBSERVATION DE LA TERRE-4) SPOT (Satellite Probatoire d'Observation de la Terre) is the French government sponsored civil Earth observation program, with support from Belgium and Sweden. A single SPOT satellite provides complete coverage of the Earth every 26 days. Image products from SPOT are handled by a commercial entity, SPOT-Image Corp. Spacecraft: 3-Axis stabilized. Single 5-panel solar array, each panel is 2.6 x 1.9 m. Hydrazine propulsion system provides orbit maintenance. Payload: Two HRVIR (High Resolution Visible - Infrared) pushbrrom imaging instruments are carried. HRVIR is derived from the HRV instruments on SPOT 1-3. This system will provide 10 m resolution in the panchromatic band and 20 m resolution in the multispectral bands. HRVIR includes a new medium IR channel to support vegetation analysis and harvest forecasting. The HRVIRs are steerable to within 27 deg off-nadir. Each HRVIR has a swath width of 60 km. The Vegetation Monitoring instrument has 1 km resolution in the same bands as the HRVIR. PASTEL optical link terminal supports laser crosslink experiments. DORIS (Doppler Orbitography and Radiopositioning Integrated by Satellite) precision orbit determination system. Additional information available at "http://samadhi.jpl.nasa.gov/msl/QuickLooks/spot4QL.html" [Summary provided by NASA] Group: Platform_Details Entry_ID: SPOT-4 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: SPOT Short_Name: SPOT-4 Long_Name: Systeme Probatoire Pour l'Observation de la Terre-4 End_Group Group: Synonymous_Platform_Names Short_Name: 25260 End_Group Group: Platform_Associated_Instruments Short_Name: DORIS Short_Name: VEGETATION-1 Short_Name: POAM III Short_Name: HRVIR Short_Name: HRV End_Group Group: Orbit Orbit_Altitude: 832 km Orbit_Inclination: 98.8° Equator_Crossing: 10:30 local solar time Period: 100.9 minutes Repeat_Cycle: 26 days Perigee: 791.0 km Apogee: 811.0 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2008-08-20 Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1998-017A Online_Resource: http://www.astrium-geo.com/ Online_Resource: http://earth.esa.int/object/index.cfm?fobjectid=4074 Sample_Image: http://ceos.cnes.fr:8100/cdrom-98/ceos1/satellit/spotsys/spot4_gb/images/orbite/spot4044.gif Group: Platform_Logistics Launch_Date: 1998-03-24 Launch_Site: Kourou, French Guiana Design_Life: 4 Years Primary_Sponsor: France/CNES End_Group End_Group 2016-06-09 17:20:14.0 [epneff] added altLabel insert AltLabel (id: null text: SPOT-4 (SYSTEME PROBATOIRE POUR L'OBSERVATION DE LA TERRE-4) language code: en); ZODIACS Small, inflatable, powered rubber boats used in some marine science investigations. Group: Platform_Details Entry_ID: ZODIACS Group: Platform_Identification Platform_Category: In Situ Ocean-based Platforms Platform_Series_or_Entity: SHIPS Short_Name: ZODIACS End_Group Group: Synonymous_Platform_Names Short_Name: Zodiacs End_Group Creation_Date: 2007-12-12 Online_Resource: http://www.zodiacmarineusa.com/ Sample_Image: http://www.quebecweb.com/croisieres2001/photos/Zodiac01.jpg End_Group Saildrone Saildrone (https://www.saildrone.com) is a state-of-the-art, wind and solar powered unmanned surface vehicle (USV) capable of long distance deployments lasting up to 12 months. The drone is autonomous in that it may be guided remotely from land while being completely wind driven. This novel sampling platform is equipped with a suite of instruments and sensors providing high quality, georeferenced, near real-time, multi-parameter surface ocean and atmospheric observations while transiting at typical speeds of 3-5 knots. Instruments are customizable depending on the mission, but typically include anemometer, barometer, thermosalinograph, CTD, IR pyrometer, fluorometer, and CO2/dissolved oxygen sensors. Saildrones have additionally been deployed with Acoustic Doppler Current Profilers (ADCP), passive acoustic sensors and echo sounders to measure along-track 3D current velocities and biological acoustic backscatter. Saildrone adopts a service model approach to the design and implementation of missions and the delivery of data products to customers. Current deployments include the Tropical and North Pacific, with a focus on future deployments in the Arctic. Data from Saildrone are providing information being used to support NASA satellite cal/val and ocean science studies, including the improvement of salinity and SST retrievals at high latitudes and closer to the coast. https://podaac.jpl.nasa.gov/saildrone 2019-01-18 20:52:08.0 [sritz] insert Definition (id: null text: Saildrone (https://www.saildrone.com) is a state-of-the-art, wind and solar powered unmanned surface vehicle (USV) capable of long distance deployments lasting up to 12 months. The drone is autonomous in that it may be guided remotely from land while being completely wind driven. This novel sampling platform is equipped with a suite of instruments and sensors providing high quality, georeferenced, near real-time, multi-parameter surface ocean and atmospheric observations while transiting at typical speeds of 3-5 knots. Instruments are customizable depending on the mission, but typically include anemometer, barometer, thermosalinograph, CTD, IR pyrometer, fluorometer, and CO2/dissolved oxygen sensors. Saildrones have additionally been deployed with Acoustic Doppler Current Profilers (ADCP), passive acoustic sensors and echo sounders to measure along-track 3D current velocities and biological acoustic backscatter. Saildrone adopts a service model approach to the design and implementation of missions and the delivery of data products to customers. Current deployments include the Tropical and North Pacific, with a focus on future deployments in the Arctic. Data from Saildrone are providing information being used to support NASA satellite cal/val and ocean science studies, including the improvement of salinity and SST retrievals at high latitudes and closer to the coast. https://podaac.jpl.nasa.gov/saildrone language code: en); 2019-01-18 20:50:46.0 [sritz] Insert Concept add broader relation (Saildrone [6077a16e-dc27-47ba-b2b8-6ae731615925,368435] - USV [bf17bbac-0fc9-48b3-9b03-bd780ffe1eb0,368431]); GEOS (Geodetic Earth Orbiting Satellite) TIROS The objectives of TIROS (Television Infrared Observation Satellite) was to test experimental television techniques designed to develop a worldwide meteorological satellite information system. The spacecraft was 42 inches in diameter, 19 inches high and weighed 270 pounds. The craft was made of aluminum alloy and stainless steel which was then covered by 9200 solar cells. The solar cells served to charge the on-board batteries. Three pairs of solid-propellant spin rockets were mounted on the base plate. Two television cameras were housed in the craft, one low-resolution and one high-resolution. A magnetic tape recorder for each camera was supplied for storing photographs while the satellite was out of range of the ground station network. The antennas consisted of four rods from the base plate to serve as transmitters and one vertical rod from the center of the top plate to serve as a receiver. The craft was spin-stabilized and space-oriented (not Earth-oriented). Therefore, the cameras were only operated while they were pointing at the Earth when that portion of the Earth was in sunlight. The video systems relayed thousands of pictures containing cloud-cover views of the Earth. Early photographs provided information concerning the structure of large-scale cloud regimes. For more information, link to "http://www.earth.nasa.gov/history/tiros/tiros1.html" [Summary provided by NASA] Group: Platform_Details Entry_ID: TIROS Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: TIROS Short_Name: TIROS Long_Name: Television Infrared Observation Satellite End_Group Group: Synonymous_Platform_Names Short_Name: TIROS-1 End_Group Creation_Date: 2007-11-14 Online_Resource: http://www.earth.nasa.gov/history/tiros/tiros1.html Sample_Image: http://www.nasm.si.edu/exhibitions/lae/images/LE410L8.jpg Group: Platform_Logistics Launch_Date: 1960-04-01 Primary_Sponsor: NASA End_Group End_Group DMSP 5D-2/F12 DMSP-F12 [Source: National Space Science Data Center, http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1994-057A ] DMSP 5D-2/F12, also known as USA 106, is one of a series of meteorological satellites developed and operated by the Air Force under the Defense Meteorological Satellite Program (DMSP). This program, previously known as DAPP (Data Acquisition and Processing Program), was classified until March 1973. The objective of this program is to provide global visual and infrared cloudcover data and specialized environmental data to support Department of Defense operational weather analysis and forecasting requirements. Operationally, the program consists of two satellites in sun-synchronous polar orbits, with the ascending node of one satellite in early morning and the other at local noon. The 6.4-m-long spacecraft is separated into four sections: (1) a precision mounting platform for sensors and equipment requiring precise alignment; (2) an equipment support module containing the electronics, reaction wheels, and some meteorological sensors; (3) a reaction control equipment support structure containing the third-stage rocket motor and supporting the ascent phase reaction control equipment; and (4) a 9.29-sq-m solar cell panel. The spacecraft stabilization is controlled by a combination flywheel and magnetic control coil system so that sensors are maintained in the desired earth-looking mode. One feature is the precision-pointing accuracy of the primary imager to 0.01 deg provided by a star sensor and an updated ephemeris navigation system. This allows automatic geographical mapping of the digital imagery to the nearest picture element. The operational linescan system is the primary data acquisition system and provides real-time or stored, multi-orbit, day-and-night, visual and infrared imagery of clouds. A supplementary sensor package contains: (1) a microwave imager; (2) a microwave temperature sounder; (3) a microwave water vapor profiler; (4) an ion and electron scintillation monitor; (5) a precipitating electron/ion spectrometer; (6) a gamma/X-ray detector, and (7) a magnetometer. Data are transmitted to ground receiving sites by two redundant S-band transmitters. Real-time data are received at tactical sites world-wide. Recorded data are transmitted to and processed by the Air Force Global Weather Central (AFGWC), Offutt AFB, Nebraska, and the Fleet Numerical Meteorology and Oceanography Center (FNMOC), Monterey, California. Both AFGWC and FNMOC relay the SSM/I, SSM/T, and SSM/T2 data to the National Environmental Satellite Data and Information System (NESDIS). AFGWC also sends the entire data stream to the National Geophysical Data Center, Boulder, Colorado. Additional information concerning can be found in the report by D. A. Nichols, "The Defense Meteorological Satellite Program," Optical Engineering, v. 14, n. 4, p. 273, July-August 1975. Group: Platform_Details Entry_ID: DMSP 5D-2/F12 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: DMSP (Defense Meteorological Satellite Program) Short_Name: DMSP 5D-2/F12 Long_Name: Defense Meteorological Satellite Program-F12 End_Group Group: Synonymous_Platform_Names Short_Name: DMSP-F12 Short_Name: USA 106 Short_Name: 23233 End_Group Group: Platform_Associated_Instruments Short_Name: SSM Short_Name: SSM/T-2 Short_Name: SSB/X2 Short_Name: SSM/I Short_Name: SSJ/4 Short_Name: OLS Short_Name: SSM/T Short_Name: SSI/ES2 End_Group Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1994-057A Online_Resource: http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/dmsp.html Online_Resource: http://www.ngdc.noaa.gov/dmsp/index.html Group: Platform_Logistics Launch_Date: 1994-08-29 Primary_Sponsor: Department of Defense-Department of the Air Force (United States) End_Group End_Group 2016-06-09 14:35:21.0 [epneff] added altLabel insert AltLabel (id: null text: DMSP-F12 language code: en); DMSP 5D-1/F5 METOP-C Global Data Service. Regional Data Service. Direct Readout Service. Real-time Imagery. Launch planned in September 2018 2019-02-21 21:43:55.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: e64e83bd-02b3-4a47-830d-00e1aa4b04d3 relationship type: null relationship value: null generated by: null); 2018-06-12 17:28:30.0 [mmorahan] insert Definition (id: null text: Global Data Service. Regional Data Service. Direct Readout Service. Real-time Imagery. Launch planned in September 2018 language code: en); 2018-06-12 17:26:49.0 [mmorahan] Insert Concept add broader relation (METOP-C [6120cea0-c943-4c7c-bddd-8d8648d58022,367687] - METOP [8c192c86-d07c-4e7b-af8f-92aa4b40fca7,345373]); SBAS (Satellite-Based Augmentation System) SBAS is a satellite-based augmentation system that supports wide-area or reginal augmentation through the use of additional satellite broadcast messages. There are several SBAS systems around the world, such as WAAS in the U.S. and EGNOS in Europe. 2017-08-15 13:52:35.0 [tstevens] insert Definition (id: null text: SBAS is a satellite-based augmentation system that supports wide-area or reginal augmentation through the use of additional satellite broadcast messages. There are several SBAS systems around the world, such as WAAS in the U.S. and EGNOS in Europe. language code: en); 2017-08-14 19:25:01.0 [tstevens] Insert Concept add narrower relation (SBAS (Satellite-Based Augmentation System) [612454e6-06ce-4bd3-b4f2-6db85f49a013,309927] - SBAS [6c37b37f-44f3-4cfd-859d-44f9266d97cb,309931]); 2017-08-14 19:24:51.0 [tstevens] Insert Concept add broader relation (SBAS (Satellite-Based Augmentation System) [612454e6-06ce-4bd3-b4f2-6db85f49a013,309927] - Navigation Platforms [1506fb17-7ac4-44ce-bde5-074885bdb2d2,287403]); NOAA-3 NOAA-4 was launched in November 1974 and was one in a series of reconfigured ITOS satellites launched with new meteorological sensors onboard to expand the operational capability of the ITOS system. The primary objective was to provide global daytime and nighttime direct readout real-time cloudcover data on a daily basis. The sun-synchronous spacecraft was also capable of supplying global atmospheric temperature soundings and very high resolution infrared cloudcover data for selected areas in either a direct readout or a tape-recorder mode. A secondary objective was to obtain global solar-proton flux data on a real-time daily basis. The sensors were mounted on the satellite baseplate with their optical axes directed vertically earthward. The nearly cubical spacecraft measured 1 by 1 by 1.2 m. The satellite was equipped with three curved solar panels that were folded during launch and deployed after orbit was achieved. Each panel measured over 4.2 m in length when unfolded and was covered with approximately 3500 solar cells measuring 2 by 2 cm. The dynamics and attitude control system maintained desired spacecraft orientation through gyroscopic principles incorporated into the satellite design. Earth orientation of the satellite body was maintained by taking advantage of the precession induced from a momentum flywheel so that the satellite body precession rate of one revolution per orbit provided the desired 'earth-looking' attitude. Minor adjustments in attitude and orientation were made by means of magnetic coils and by varying the speed of the momentum flywheel. The primary sensors consisted of a Very High Resolution Radiometer (VHRR), Vertical Temperature Profile Radiometer (VTPR), and a Scanning Radiometer (SR). More information about NOAA-4: https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1973-086A __________ Taken from the NSSDC System for Information Retrieval and Storage (SIRS). For more information contact the NSSDC Coordinated Request and User Support Office, https://nssdca.gsfc.nasa.gov/). 2019-11-22 22:42:19.0 [sritz] update Definition (NOAA-4 was launched in November 1974 and was one in a series of reconfigured ITOS satellites launched with new meteorological sensors onboard to expand the operational capability of the ITOS system. The primary objective was to provide global daytime and nighttime direct readout real-time cloudcover data on a daily basis. The sun-synchronous spacecraft was also capable of supplying global atmospheric temperature soundings and very high resolution infrared cloudcover data for selected areas in either a direct readout or a tape-recorder mode. A secondary objective was to obtain global solar-proton flux data on a real-time daily basis. The sensors were mounted on the satellite baseplate with their optical axes directed vertically earthward. The nearly cubical spacecraft measured 1 by 1 by 1.2 m. The satellite was equipped with three curved solar panels that were folded during launch and deployed after orbit was achieved. Each panel measured over 4.2 m in length when unfolded and was covered with approximately 3500 solar cells measuring 2 by 2 cm. The dynamics and attitude control system maintained desired spacecraft orientation through gyroscopic principles incorporated into the satellite design. Earth orientation of the satellite body was maintained by taking advantage of the precession induced from a momentum flywheel so that the satellite body precession rate of one revolution per orbit provided the desired 'earth-looking' attitude. Minor adjustments in attitude and orientation were made by means of magnetic coils and by varying the speed of the momentum flywheel. The primary sensors consisted of a Very High Resolution Radiometer (VHRR), Vertical Temperature Profile Radiometer (VTPR), and a Scanning Radiometer (SR). More information about NOAA-4: https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1973-086A __________ Taken from the NSSDC System for Information Retrieval and Storage (SIRS). For more information contact the NSSDC Coordinated Request and User Support Office, https://nssdca.gsfc.nasa.gov/).); 2019-11-22 22:41:25.0 [sritz] update Definition (NOAA-4 was launched in November 1974 and was one in a series of reconfigured ITOS satellites launched with new meteorological sensors onboard to expand the operational capability of the ITOS system. The primary objective was to provide global daytime and nighttime direct readout real-time cloudcover data on a daily basis. The sun-synchronous spacecraft was also capable of supplying global atmospheric temperature soundings and very high resolution infrared cloudcover data for selected areas in either a direct readout or a tape-recorder mode. A secondary objective was to obtain global solar-proton flux data on a real-time daily basis. The sensors were mounted on the satellite baseplate with their optical axes directed vertically earthward. The nearly cubical spacecraft measured 1 by 1 by 1.2 m. The satellite was equipped with three curved solar panels that were folded during launch and deployed after orbit was achieved. Each panel measured over 4.2 m in length when unfolded and was covered with approximately 3500 solar cells measuring 2 by 2 cm. The dynamics and attitude control system maintained desired spacecraft orientation through gyroscopic principles incorporated into the satellite design. Earth orientation of the satellite body was maintained by taking advantage of the precession induced from a momentum flywheel so that the satellite body precession rate of one revolution per orbit provided the desired 'earth-looking' attitude. Minor adjustments in attitude and orientation were made by means of magnetic coils and by varying the speed of the momentum flywheel. The primary sensors consisted of a Very High Resolution Radiometer (VHRR), Vertical Temperature Profile Radiometer (VTPR), and a Scanning Radiometer (SR). More information about NOAA-4: https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1973-086A __________ Taken from the NSSDC System for Information Retrieval and Storage (SIRS). For more information contact the NSSDC Coordinated Request and User Support Office, 301-286-6695 (NASA Goddard Space Flight Center, Code 933.4, Greenbelt, Maryland 20771, USA, https://nssdca.gsfc.nasa.gov/).); 2019-11-22 22:34:12.0 [sritz] update Definition (NOAA-3 was launched in November 1973 and was one in a series of reconfigured ITOS satellites launched with new meteorological sensors onboard to expand the operational capability of the ITOS system. The primary objective was to provide global daytime and nighttime direct readout real-time cloudcover data on a daily basis. The sun-synchronous spacecraft was also capable of supplying global atmospheric temperature soundings and very high resolution infrared cloudcover data for selected areas in either a direct readout or a tape-recorder mode. A secondary objective was to obtain global solar-proton flux data on a real-time daily basis. The sensors were mounted on the satellite baseplate with their optical axes directed vertically earthward. The nearly cubical spacecraft measured 1 by 1 by 1.2 m. The satellite was equipped with three curved solar panels that were folded during launch and deployed after orbit was achieved. Each panel measured over 4.2 m in length when unfolded and was covered with approximately 3500 solar cells measuring 2 by 2 cm. The dynamics and attitude control system maintained desired spacecraft orientation through gyroscopic principles incorporated into the satellite design. Earth orientation of the satellite body was maintained by taking advantage of the precession induced from a momentum flywheel so that the satellite body precession rate of one revolution per orbit provided the desired 'earth-looking' attitude. Minor adjustments in attitude and orientation were made by means of magnetic coils and by varying the speed of the momentum flywheel. The primary sensors consisted of a Very High Resolution Radiometer (VHRR), Vertical Temperature Profile Radiometer (VTPR), and a Scanning Radiometer (SR). The spacecraft became the operational ITOS spacecraft on March 19, 1974. Operations terminated in August 1976. More information about the NOAA satellite series: https://www.noaa.gov/satellites __________ Taken from the NSSDC System for Information Retrieval and Storage (SIRS). For more information contact the NSSDC Coordinated Request and User Support Office, 301-286-6695 (NASA Goddard Space Flight Center, Code 933.4, Greenbelt, Maryland 20771, USA, https://nssdca.gsfc.nasa.gov/). Group: Platform_Details Entry_ID: NOAA-3 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NOAA POES (Polar Orbiting Environmental Satellites) Short_Name: NOAA-3 Long_Name: National Oceanic & Atmospheric Administration-3 End_Group Group: Synonymous_Platform_Names Short_Name: NOAA-3 End_Group Creation_Date: 2007-11-08 Online_Resource: https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1973-086A Group: Platform_Logistics Launch_Date: 1973-11-06 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: NASA End_Group End_Group); delete Resource (null); AEROS-1 The purpose of the AEROS spacecraft mission was to study the state and behavior of the upper atmosphere (thermosphere) and the ionospheric F-region. Of particular interest was the influence of solar ultraviolet radiation on the structure, photochemistry and dynamics of the atmosphere above 100 km altitude. INSTRUMENTATION: Five experiments provided data on the temperature and density of F-region electrons, ions and neutral particles, on the composition of ions and neutral particles, and on the solar ultraviolet flux incident on the topside ionosphere. SPACECRAFT: The AEROS satellite had a circular cylindrical shape with a diameter of 0.914 meter and a height of 0.710 meter. ORBIT: AEROS was launched into an elliptical, polar, and nearly sun-synchronous earth orbit. The spacecraft was spin stabilized at 10 rpm and was oriented with the spin axis toward the sun. Group: Platform_Details Entry_ID: AEROS-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: AEROS Short_Name: AEROS-1 End_Group Group: Synonymous_Platform_Names Short_Name: AEROS-A Short_Name: 06315 End_Group Group: Platform_Associated_Instruments Short_Name: MASS SPECTROMETERS Short_Name: RPA Short_Name: Quadrupole Mass Analyzer Short_Name: Impedance Probe Short_Name: Grating Spectrometer Short_Name: Solar Collimator Short_Name: Photomultiplier End_Group Group: Orbit Orbit_Inclination: 96.9 degrees Period: 95.6 minutes Perigee: 223.0 km Apogee: 867.0 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-08-22 Online_Resource: http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1972-100A Group: Platform_Logistics Launch_Date: 1972-12-16 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: NASA Primary_Sponsor: GERMANY End_Group End_Group OCEAN PLATFORM/OCEAN STATIONS 2017-12-28 19:11:49.0 [sritz] Move Concepts add narrower relation (OCEAN PLATFORM/OCEAN STATIONS [62e9613a-6e40-41cf-838a-ed6ac0d4871b,287905] - CODAR SeaSonde [294cc889-28bc-4a33-b630-8225f559c3e7,310507]); ZEIA Mission Objectives: The Zeya satellite is a Russian Military Communications satellite launched on March 4, 1997. Zeya is named after the Zeya River, which is very close to it's launch site, Cosmodrome Svobodniy. This was the first satellite launched from this new Russian launch site in far eastern Russia. Note: Sometimes also spelled Zeia. ILRS Mission Support Status: Satellite laser ranging was used for precision orbit determination for this spacecraft and used for calibration of GPS and GLONASS navigation equipment aboard the satellite. This satellite was only tracked for 6 months by the international laser ranging network. SLR tracking support was discontinued on 29 July 1997. Instrumentation: Zeya has the following instrumentation onboard: 1) Radio equipment 2) GPS receiver 3) GLONASS receiver 4) Laser retroreflector array RetroReflector Array (RRA) Characteristics: The retro-reflector array is a box array of 20 corner cubes, which are optimized at 532 nanometers. Twenty retroreflectors operating with principle "not more than one reflectors works in any direction" are installed on the satellite. Each retroreflector has field of view of 35 arc degrees. Retroreflectors ensure reflection of laser light within 47% of 4 steradian. Satellite's design provides accuracy of link of range measurements to the center of mass with root mean square error of about 5 mm. Systematic correction is 419 mm. The satellite is spinning around Y axis with angular velocity about 30 revolutions per minute. Additional information available at "http://ilrs.gsfc.nasa.gov/satellite_missions/list_of_satellites/zeya/" [Summary provided by NASA] SWOT The Surface Water & Ocean Topography (SWOT) mission brings together two communities focused on a better understanding of the world's oceans and its terrestrial surface waters. U.S. and French oceanographers and hydrologists and international partners have joined forces to develop this new space mission to make the first global survey of Earth's surface water, observe the fine details of the ocean's surface topography, and measure how water bodies change over time. SWOT was one of 15 missions listed in the 2007 National Research Council Decadal Survey of Earth science as missions that NASA should implement in the coming decade. More information: https://swot.jpl.nasa.gov/ 2019-05-10 21:13:35.0 [sritz] insert WeightedRelation (id: null related concept uuid: 3f392e56-af78-451b-a1ba-c577aa728a4c relationship type: null relationship value: null generated by: null); 2019-05-10 20:54:18.0 [sritz] insert WeightedRelation (id: null related concept uuid: e5c4d64f-fb76-40e1-84f0-d3019b70642d relationship type: null relationship value: null generated by: null); 2019-05-10 20:42:50.0 [sritz] delete Resource (null); 2018-03-12 16:33:34.0 [sritz] update Definition (The Surface Water & Ocean Topography (SWOT) mission brings together two communities focused on a better understanding of the world's oceans and its terrestrial surface waters. U.S. and French oceanographers and hydrologists and international partners have joined forces to develop this new space mission to make the first global survey of Earth's surface water, observe the fine details of the ocean's surface topography, and measure how water bodies change over time. SWOT was one of 15 missions listed in the 2007 National Research Council Decadal Survey of Earth science as missions that NASA should implement in the coming decade. More information: https://swot.jpl.nasa.gov/); 2017-11-30 16:14:04.0 [sritz] update Definition (The Surface Water & Ocean Topography (SWOT) mission brings together two communities focused on a better understanding of the world's oceans and its terrestrial surface waters. U.S. and French oceanographers and hydrologists and international partners have joined forces to develop this new space mission to make the first global survey of Earth's surface water, observe the fine details of the ocean's surface topography, and measure how water bodies change over time. SWOT was one of 15 missions listed in the 2007 National Research Council Decadal Survey of Earth science as missions that NASA should implement in the coming decade.); update Definition (https://swot.jpl.nasa.gov/); update Resource (image); update Resource (https://swot.jpl.nasa.gov/images/swot/swot_v4_lowres_cropped_200.jpg); GMS-2 The Geostationary Meteorological Satellites (GMS) were Japan's contribution to the international Global Atmospheric Research Program (GARP). The GMS series carried the Visible and Spin Scan Radiometer (VISSR). The satellite was spin-stabilized with a despun earth-pointing antenna. Launched by a Japan N-2 rocket in a August 1981, the satellite was positioned near 140 deg E and was designed to operate for 5 years. This was a follow-on GMS type spacecraft launched and controlled by NASDA of Japan. The spacecraft was launched in August 1981, and turned off in September 1984. __________ Taken from the NSSDC System for Information Retrieval and Storage (SIRS). For more information contact the NSSDC Coordinated Request and User Support Office, 301-286-6695 (NASA Goddard Space Flight Center, Code 933.4, Greenbelt, Maryland 20771, USA). WWW: http://nssdc.gsfc.nasa.gov/ Technical contact: Yukio Haruyama, Earth Observation program office director, Program planning and management department, National space development agency of Japan Head office Hamamatsu-cho, Minato-ku, Tokyo, Japan Phone: 81-3-5470-4252 Group: Platform_Details Entry_ID: GMS-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: GMS (Japan Geostationary Meteorological Satellite) Short_Name: GMS-2 Long_Name: Geostationary Meteorological Satellite-2 End_Group Group: Synonymous_Platform_Names Short_Name: GMS-2 End_Group Group: Platform_Associated_Instruments Short_Name: VISSR-GMS End_Group Group: Orbit Orbit_Altitude: 36,000 km Orbit_Type: GEO > Geosynchronous > Geostationary End_Group Creation_Date: 2007-10-01 Online_Resource: http://space.skyrocket.de/doc_sdat/gms-2.htm Online_Resource: http://www.jaxa.jp/projects/sat/gms/index_e.html Group: Platform_Logistics Launch_Date: 1981-08-10 Launch_Site: Tanegashima Island, Japan Design_Life: 5 YEARS Primary_Sponsor: Japan/JAXA End_Group End_Group HOV 2020-01-21 17:35:39.0 [tstevens] Insert Concept add narrower relation (HOV [63c8aa1d-6efc-4943-8891-3a1cd520dde0,559759] - Pisces V [0f50133b-1ef8-4c67-97a3-ac0604a41fc8,559791]); 2020-01-21 17:35:28.0 [tstevens] Insert Concept add narrower relation (HOV [63c8aa1d-6efc-4943-8891-3a1cd520dde0,559759] - MIR II [2fcdab81-7527-4344-a26c-632746e94423,559787]); 2020-01-21 17:35:19.0 [tstevens] Insert Concept add narrower relation (HOV [63c8aa1d-6efc-4943-8891-3a1cd520dde0,559759] - MIR I [15f4ae34-a5c9-43e0-84d6-246690648fca,559783]); 2020-01-21 17:35:05.0 [tstevens] Insert Concept add narrower relation (HOV [63c8aa1d-6efc-4943-8891-3a1cd520dde0,559759] - Johnson-Sea-Link II [cb5ab3cc-48d1-4b0c-b72b-700a6faee11e,559779]); 2020-01-21 17:34:52.0 [tstevens] Insert Concept add narrower relation (HOV [63c8aa1d-6efc-4943-8891-3a1cd520dde0,559759] - Johnson-Sea-Link I [ae078302-17ab-4cc5-ba7d-7a8a0102c01b,559775]); 2020-01-21 17:34:22.0 [tstevens] Insert Concept add narrower relation (HOV [63c8aa1d-6efc-4943-8891-3a1cd520dde0,559759] - Clelia [78c6cfd9-0df5-435e-9bb1-d14322db928f,559771]); 2020-01-21 17:34:12.0 [tstevens] Insert Concept add narrower relation (HOV [63c8aa1d-6efc-4943-8891-3a1cd520dde0,559759] - Alvin [57323291-3348-4292-812e-7436d6a0781a,559767]); 2020-01-21 17:31:24.0 [tstevens] Insert Concept add narrower relation (HOV [63c8aa1d-6efc-4943-8891-3a1cd520dde0,559759] - DeepWorker 2000 [caa8300a-560a-4190-b257-6f8d33f6f134,559763]); 2020-01-21 17:30:55.0 [tstevens] insert AltLabel (id: null category: primary text: Human Occupied Vehicle language code: en); 2020-01-21 17:30:18.0 [tstevens] Insert Concept add broader relation (HOV [63c8aa1d-6efc-4943-8891-3a1cd520dde0,559759] - In Situ Ocean-based Platforms [e50b2a1a-7d9d-4c09-ac7e-dc29f0c08fc7,542811]); R/V PROFESSOR KHROMOV 2012-06-29 19:59:25.0 [aaleman] Insert Concept add broader relation (R/V PROFESSOR KHROMOV [5650f8fe-8db8-4bb1-927a-54a214d30ca1,40281] - SHIPS [82a67b12-e99d-4c90-8a6a-a6f79d4c3c7b,31201]); NCEP-MRF 2015-08-10 18:57:30.0 [epneff] Added long name insert AltLabel (id: null text: NCEP Medium Range Forecast Model language code: en); 2015-08-10 18:57:11.0 [epneff] Insert Concept add broader relation (NCEP-MRF [6426710e-8498-4308-845e-c9c543bcc17e,158259] - Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215]); STS-56 A variety of scientific questions will be addressed when NASA conducts Shuttle mission STS-56 in late March 1993. The crew on Space Shuttle Discovery will gather data on the relationship between sun's energy output and Earth's middle-atmosphere chemical make-up and how these factors affect the Earth's ozone level. The crew will use the Atmospheric Laboratory for Science and Applications (ATLAS 2) and Shuttle Backscatter Ultraviolet (SSBUV) payloads aboard Discovery to gather this information. The source of solar wind and the possible applications a microgravity environment can provide for research in drug development and the changes which occur in muscles and bones in a weightless condition are some of the other areas to be investigated during the STS-56 mission. {Summary provided by NASA] Group: Platform_Details Entry_ID: STS-56 Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Platform_Series_or_Entity: SPACE SHUTTLE Short_Name: STS-56 Long_Name: Space Transport System STS-56 End_Group Group: Synonymous_Platform_Names Short_Name: DISCOVERY End_Group Group: Orbit Orbit_Altitude: 160nm Orbit_Inclination: 57 degrees End_Group Creation_Date: 2008-01-30 Online_Resource: http://science.ksc.nasa.gov/shuttle/missions/sts-56/mission-sts-56.html Sample_Image: http://science.ksc.nasa.gov/shuttle/missions/sts-56/sts-56-patch-small.gif Group: Platform_Logistics Launch_Date: 1993-04-08 Primary_Sponsor: NASA End_Group End_Group UWKA [Source: http://www.uwyo.edu/atsc/flightcenter/ ] The University of Wyoming Beechcraft King Air 200T (N2UW) is the third atmospheric research aircraft we have operated since the mid 1960's. Click here for photos. Click here for driving instructions to the facility. Group: Platform_Details Entry_ID: UWKA Group: Platform_Identification Platform_Category: Aircraft Short_Name: UWKA Long_Name: University of Wyoming King Air End_Group Group: Platform_Associated_Instruments Short_Name: WCR End_Group Creation_Date: 2013-07-02 Online_Resource: http://www.uwyo.edu/atsc/flightcenter/ Group: Platform_Logistics Primary_Sponsor: University of Wyoming End_Group End_Group 2013-07-02 21:02:52.0 [saritz] Added definition. insert Definition (id: null text: The University of Wyoming Beechcraft King Air 200T (N2UW) is the third atmospheric research aircraft we have operated since the mid 1960's. Click here for photos. Click here for driving instructions to the facility. language code: en); insert AltLabel (id: null text: University of Wyoming King Air language code: en); 2013-07-02 21:00:43.0 [saritz] Added primary preferred label. insert AltLabel (id: null text: University of Wyoming King Air language code: en); 2013-07-02 20:59:48.0 [saritz] Insert Concept add broader relation (UWKA [64b518f5-2026-4c5b-9bae-9fa55b5b5778,105253] - Aircraft [227d9c3d-f631-402d-84ed-b8c5a562fc27,73411]); DMSP The Defense Meteorological Satellite Program (DMSP) is a Department of Defense (DoD) program run by the Air Force Space and Missle Systems Center (SMC). The DMSP designs, builds, launches, and maintains satellites monitoring the meteorological, oceanographic, and solar-terrestrial physics environments. Each DMSP satellite has a 101 minute, sun-synchronous near-polar orbit at an altitude of 830km above the surface of the earth. The visible and infrared sensors (OLS) collect images across a 3000km swath, providing global coverage twice per day. The combination of day/night and dawn/dusk satellites allows monitoring of global information such as clouds every 6 hours. The microwave imager (MI) and sounders (T1, T2) cover one half the width of the visible and infrared swath. These instruments cover polar regions at least twice and the equatorial region once per day. The space environment sensors (J4, M, IES) record along-track plasma densities, velocities, composition and drifts. The data from the DMSP satellites are received and used at operational centers continuously. The data are sent to the National Geophysical Data Center's Solar Terrestrial Physics Division (NGDC/STP) by the Air Force Weather Agency (AFWA) for creation of an archive. Additional information available at http://dmsp.ngdc.noaa.gov/dmsp.html [Summary provided by NOAA] Group: Platform_Details Entry_ID: DMSP Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: DMSP (Defense Meteorological Satellite Program) Short_Name: DMSP Long_Name: Defense Meteorological Satellite Program End_Group Group: Platform_Associated_Instruments Short_Name: GAMMA RADIATION DETECTOR End_Group Group: Orbit Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-09-12 Online_Resource: http://www.ngdc.noaa.gov/dmsp/index.html Sample_Image: http://heasarc.gsfc.nasa.gov/Images/misc_missions/dmsp_sat.gif Group: Platform_Logistics Launch_Date: 1972-12-01 Primary_Sponsor: NOAA End_Group End_Group GOES-8 GOES-8 (GEOSTATIONARY OPERATIONAL ENVIRONMENTAL SATELLITE-8) GOES 8 (GOES-I) was launched on April 13, 1994. On Tuesday April 1, 2003 GOES-12 (Formerly Referred to as GOES-M) replaced GOES-8 as the operational GOES East Satellite. NOAA deactivated the satellite on May 5, 2004 and will boost it into an orbit 350 kilometers above its original geostationary position, where it will be disposed safely in three controlled burns. GOES I-M represented the next generation of meteorological satellites and introduces two new features. The first feature, flexible scan, offers small-scale area imaging that lets meteorologists take pictures of local weather trouble spots. This allows them to improve short-term forecasts over local areas. The second feature, simultaneous and independent imaging and sounding, is designed to allow weather forecasters to use multiple measurements of weather phenomena to increase the accuracy of their forecasts. Each satellite in the series carries two major instruments: an Imager and a Sounder. These instruments acquire high resolution visible and infrared data, as well as temperature and moisture profiles of the atmosphere. They continuously transmit these data to ground terminals where the data are processed for rebroadcast to primary weather services both in the United States and around the world, including the global research community. The GOES I-M mission ran from the mid-1990s into the first decade of the 21st century. Each element of the mission has been designed to meet all in-orbit performance requirements for at least five years. The GOES I-M system performed the following basic functions: + Acquisition, processing, and dissemination of imaging and sounding data. + Acquisition and dissemination of Space Environment Monitor (SEM) data. + Reception and relay of data from ground-based Data Collection Platforms (DCPs) that are situated in carefully selected urban and remote areas to the NOAA Command and Data Acquisition (CDA) station. + Continuous relay of Weather Facsimile (WEFAX) and other data to users, independent of all other functions. + Relay of distress signals from people, aircraft, or marine vessels to the search and rescue ground stations of the Search and Rescue Satellite Aided Tracking (SARSAT) system. GOES provides the instantaneous relay functions for the SARSAT system. A dedicated search and rescue transponder on board GOES is designed to detect emergency distress signals originating from Earth-based sources. These unique identification signals are normally combined with signals received by a low-Earth orbiting satellite system and relayed to a search and rescue ground terminal. The combined data are used to perform effective search and rescue operations. The GOES I-M system serves a region covering the central and eastern Pacific Ocean; North, Central, and South America; and the central and western Atlantic Ocean. Pacific coverage includes Hawaii and the Gulf of Alaska. This is accomplished by two satellites, GOES West located at 135 west longitude and GOES East at 75 west longitude. A common ground station, the CDA station located at Wallops, Virginia, supports the interface to both satellites. The NOAA Satellite Operations Control Center (SOCC), in Suitland, Maryland, provides spacecraft scheduling, health and safety monitoring, and engineering analyses. Delivery of products involves ground processing of the raw instrument data for radiometric calibration and Earth location information, and retransmission to the satellite for relay to the data user community. The processed data are received at the control center and disseminated to the National Weather Service's (NWS) National Meteorological Center, Camp Springs, Maryland, and NWS forecast offices, including the National Hurricane Center, Miami, Florida, and the National Severe Storms Forecast Center, Kansas City, Missouri. Processed data are also received by Department of Defense installations, universities, and numerous private commercial users. MAIN SPACECRAFT DESIGN ELEMENTS Mission life 5 years, minimum Dimensions Main body 2 meter (7 foot) cube Deployed length 27 meters (88 feet) Weight 2100 kg (4600 lb) Orbit Geosynchronous Altitude 36,000 km (22,000 mi) Longitude 75W and 135W Latitude equatorial, within 0.5 degree Power 1050 watts @ 42 volts, solar array; battery backup Launch vehicle Atlas-I/Centaur (GOES-I/K), Atlas-II/Centaur (GOES-L/M) Communications Imager and Sounder in GVAR format at 2.1 Mbits/sec GOES-I/M IMAGER The GOES Imager is a multi-channel instrument designed to sense radiant and solar-reflected energy from sampled areas of the Earth. The multi-element spectral channels simultaneously sweep east-west and west-east along a north-to-south path by means of a two-axis mirror scan system. The instrument can produce full-Earth disc images, sector images that contain the edges of the Earth, and various sizes of area scans completely enclosed within the Earth scene using a new flexible scan system. Scan selection permits rapid continuous viewing of local areas for monitoring of mesoscale (regional) phenomena and accurate wind determination. IMAGER CHANNELS AND PRODUCTS CHANNEL 1 2* 3* 4 5* WAVELENGTH (um) 0.65 3.9 6.7 11 12 PRODUCT Clouds x x x x x Water Vapor* x x x Surface Temp. o x o Winds x x x Albedo + IR Flux x o x o Fires + Smoke x x o o KEY: * = new operational data x = primary channel o = secondary channel GOES-I/M SOUNDER The GOES Sounder is a 19-channel discrete-filter radiometer covering the spectral range from the visible channel wavelengths to 15 microns. It is designed to provide data from which atmospheric temperature and moisture profiles, surface and cloud-top temperatures, and ozone distribution can be deduced by mathematical analysis. It operates independently of and simultaneously with the Imager, using a similarly flexible scan system. The Sounder's multi-element detector array assemblies simultaneously sample four separate fields or atmospheric columns. A rotating filter wheel, which brings spectral filters into the optical path of the detector array, provides the infrared channel definition. PRODUCTS, RESOLUTION AND ACCURACY RESOLUTION (km) ACCURACY Vert. Horiz. Absolute Relative PRODUCT TEMPERATURE Profile 3-5 50 2-3 K 1 K Land --- 10 2 K 1 K Sea --- 10 1 K 0.5 K MOISTURE Profile 2-4 50 30% 20% Total --- 10 20% 10% Motion 3 layers 50 6 m/sec 3 m/sec CLOUD Height 2 layers 10 50 mb 25 mb Amount total 10 15% 5% OZONE* Total --- 50 30% 15% Motion 1 layer 50 10 m/sec 5 m/sec IR Flux* total 50 10 W/m^2 3 W/m^2 KEY: * = potential future product GOES 8 information is available at: http://www.oso.noaa.gov/goes/ Group: Platform_Details Entry_ID: GOES-8 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: GOES (Geostationary Operational Environmental Satellite) Short_Name: GOES-8 Long_Name: Geostationary Operational Environmental Satellite 8 End_Group Group: Synonymous_Platform_Names Short_Name: GOES I Short_Name: GOES-NEXT Short_Name: 23051 End_Group Group: Platform_Associated_Instruments Short_Name: SXM Short_Name: VAS Short_Name: GOES I-M IMAGER Short_Name: GOES I-M SOUNDER Short_Name: EPM End_Group Group: Orbit Orbit_Type: GEO > Geosynchronous > Geostationary End_Group Creation_Date: 2007-10-04 Online_Resource: http://www.oso.noaa.gov/goes/ Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1994-022A Online_Resource: http://goes.gsfc.nasa.gov/ Group: Platform_Logistics Launch_Date: 1994-04-13 Launch_Site: CAPE CANAVERAL/KENNEDY SPACE CENTER, USA Primary_Sponsor: USA/NASA Primary_Sponsor: USA/NOAA End_Group End_Group 2016-06-09 14:48:10.0 [epneff] added altLabel insert AltLabel (id: null text: GOES-8 (GEOSTATIONARY OPERATIONAL ENVIRONMENTAL SATELLITE-8) language code: en); THEMIS [Source: NASA THEMIS Mission Home Page, http://www.nasa.gov/mission_pages/themis/mission/ ] NASA's Time History of Events and Macroscale Interactions during Substorms (THEMIS) aims to resolve one of the oldest mysteries in space physics, namely to determine what physical process in near-Earth space initiates the violent eruptions of the aurora that occur during substorms in the Earth's magnetosphere. THEMIS is a 2-year mission consisting of 5 identical probes that will study the violent colorful eruptions of Auroras. For the first time NASA will launch a constellation of five satellites to study substorms. The THEMIS probes will line up over North America once every four days. Over the mission’s two-year lifetime, the probes should be able to observe some 30 substorms. THEMIS is the fifth medium-class mission under NASA's Explorer Program, which was conceived to provide frequent flight opportunities for world-class scientific investigations from space within the Heliophysics and Astrophysics science areas. The Explorers Program Office at Goddard Space Flight Center, Greenbelt, Md., manages this NASA-funded mission. The University of California, Berkeley's Space Sciences Laboratory and Swales Aerospace, Beltsville, Md., built the THEMIS probes. Group: Platform_Details Entry_ID: THEMIS Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Platform_Series_or_Entity: NASA Medium Class Explorers (MIDEX) Short_Name: THEMIS Long_Name: Time History of Events and Macroscale Interactions During Substorms End_Group Group: Platform_Associated_Instruments Short_Name: THEMIS-SST Short_Name: THEMIS-ESA Short_Name: THEMIS-FGM Short_Name: THEMIS-EFI Short_Name: SCM End_Group Group: Orbit Orbit_Type: HEO > Highly Elliptical Orbit End_Group Creation_Date: 2008-07-17 Online_Resource: http://www.nasa.gov/mission_pages/themis/main/ Online_Resource: http://themis.ssl.berkeley.edu/ Online_Resource: http://www.atk.com/Customer_Solutions_SpaceSystems/cs_ss_spacesys_ssp_ppcs-themis.asp Sample_Image: http://www.nasa.gov/images/content/164405main_THEMIS-Spacecraft_bus2.jpg Group: Platform_Logistics Launch_Date: 2007-02-17 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: USA/NASA End_Group End_Group Hercules Owned and operated by the Ocean Exploration Trust , Hercules is a remotely operated vehicle (ROV) equipped with special features that allow it to perform intricate tasks while descending to depths of 2.5 miles (4,000 meters). Hercules operates off Exploration Vessel (E/V) Nautilus and always with its tandem vehicle, Argus. Hercules carries an array of lighting, cameras, and acoustic sensors that are used to gather video and other data during each dive. Hercules’ four HMI lights and high-definition video camera allow scientists to closely examine a dive site and monitor operations. Video is streamed up a fiber-optic cable to a control van on Nautilus and then out to the world on the Internet . Two manipulator arms allow Hercules to collect biological and geological samples and to recover artifacts. Other sensors measure pressure, depth, water temperature, oxygen concentration, and salinity. As a remotely operated vehicle, Hercules is controlled (remotely) by pilots located in a mission control room aboard E/V Nautilus, who use the vehicle’s six thrusters to "fly" the ROV in any direction. 2020-01-21 18:11:50.0 [tstevens] insert Definition (id: null text: Owned and operated by the Ocean Exploration Trust , Hercules is a remotely operated vehicle (ROV) equipped with special features that allow it to perform intricate tasks while descending to depths of 2.5 miles (4,000 meters). Hercules operates off Exploration Vessel (E/V) Nautilus and always with its tandem vehicle, Argus. Hercules carries an array of lighting, cameras, and acoustic sensors that are used to gather video and other data during each dive. Hercules’ four HMI lights and high-definition video camera allow scientists to closely examine a dive site and monitor operations. Video is streamed up a fiber-optic cable to a control van on Nautilus and then out to the world on the Internet . Two manipulator arms allow Hercules to collect biological and geological samples and to recover artifacts. Other sensors measure pressure, depth, water temperature, oxygen concentration, and salinity. As a remotely operated vehicle, Hercules is controlled (remotely) by pilots located in a mission control room aboard E/V Nautilus, who use the vehicle’s six thrusters to "fly" the ROV in any direction. language code: en); 2020-01-21 17:26:19.0 [tstevens] Insert Concept add broader relation (Hercules [654fb060-af2f-4d5d-af89-2216ef7939ca,559739] - ROV [da6420b6-48ec-4ae2-98c7-0ef0538815a0,542741]); AE-B 02183 Atmosphere Explorer-B Explorer 32 S 6A Explorer 32 was an aeronomy satellite which was designed to directly measure temperatures, composition, densities, and pressures in the upper atmosphere on a global basis. The satellite was a stainless steel, vacuum-sealed sphere, 0.889 m in diameter. The experimental payload included one ion and two neutral mass spectrometers, three magnetron density gauges, and two electrostatic probes. Additional equipment included optical and magnetic aspect sensors, magnetic attitude and spin rate control systems, and a tape recorder for data acquisition at locations remote from ground receiving stations. Power was supplied by silver-zinc batteries and a solar cell array mounted on the satellite exterior. Two identical pulse-modulated telemetry systems and a canted turnstile antenna were employed. The two neutral-particle mass spectrometers failed about 6 days after launch. The remaining experiments operated satisfactorily and provided useful data for most of the 10-month satellite lifetime. The spacecraft ceased to function due to battery failures which resulted from depressurization of the sphere. https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1966-044A Group: Platform_Details Entry_ID: AE-B Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: AE (Atmosphere Explorer) Short_Name: AE-B Long_Name: Atmosphere Explorer B (Explorer 32) End_Group Group: Synonymous_Platform_Names Short_Name: Explorer 32 Short_Name: 02183 End_Group Group: Platform_Associated_Instruments Short_Name: MASS SPECTROMETERS Short_Name: ELECTROSTATIC ANALYZERS End_Group Group: Orbit Orbit_Inclination: 64.67 degrees Perigee: 276 km Apogee: 2725 km End_Group Creation_Date: 2007-08-22 Online_Resource: https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1966-044A Group: Platform_Logistics Launch_Date: 1966-05-25 Primary_Sponsor: NASA End_Group End_Group 2019-09-17 21:30:17.0 [sritz] insert AltLabel (id: null category: null text: S 6A language code: en); insert AltLabel (id: null category: null text: 02183 language code: en); insert AltLabel (id: null category: null text: Atmosphere Explorer-B language code: en); insert AltLabel (id: null category: null text: Explorer 32 language code: en); update Definition (Explorer 32 was an aeronomy satellite which was designed to directly measure temperatures, composition, densities, and pressures in the upper atmosphere on a global basis. The satellite was a stainless steel, vacuum-sealed sphere, 0.889 m in diameter. The experimental payload included one ion and two neutral mass spectrometers, three magnetron density gauges, and two electrostatic probes. Additional equipment included optical and magnetic aspect sensors, magnetic attitude and spin rate control systems, and a tape recorder for data acquisition at locations remote from ground receiving stations. Power was supplied by silver-zinc batteries and a solar cell array mounted on the satellite exterior. Two identical pulse-modulated telemetry systems and a canted turnstile antenna were employed. The two neutral-particle mass spectrometers failed about 6 days after launch. The remaining experiments operated satisfactorily and provided useful data for most of the 10-month satellite lifetime. The spacecraft ceased to function due to battery failures which resulted from depressurization of the sphere. https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1966-044A Group: Platform_Details Entry_ID: AE-B Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: AE (Atmosphere Explorer) Short_Name: AE-B Long_Name: Atmosphere Explorer B (Explorer 32) End_Group Group: Synonymous_Platform_Names Short_Name: Explorer 32 Short_Name: 02183 End_Group Group: Platform_Associated_Instruments Short_Name: MASS SPECTROMETERS Short_Name: ELECTROSTATIC ANALYZERS End_Group Group: Orbit Orbit_Inclination: 64.67 degrees Perigee: 276 km Apogee: 2725 km End_Group Creation_Date: 2007-08-22 Online_Resource: https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1966-044A Group: Platform_Logistics Launch_Date: 1966-05-25 Primary_Sponsor: NASA End_Group End_Group); ESSA The world's first operational weather satellite system was placed into service with the launching of the Environmental Science Services Administration (which in 1970 became the National Oceanic and Atmospheric Administration, NOAA) satellites, ESSA-1, on February 3, 1966, and ESSA-2, on February 28, 1966. The objective of this program, also called the TIROS Operational System (TOS), was to acquire global observational data routinely on a daily basis. This system consisted of a pair of ESSA satellites in sun-synchronous (polar) orbit. The odd numbered satellites (ESSA-1, 3, 5, 7, and 9) utilized the Advanced Vidicon Camera System (AVCS) to obtain global imagery which were transmitted to the ESSA Command and Data Acquition (CDA) stations at Wallops, Virginia, and Fairbanks, Alaska. The CDA stations relayed the data to the National Environmental Satellite Service (NESS), which later became the National Environmental Satellite, Data, and Information Service (NESDIS), located in Suitland, Maryland, for processing and distribution to forecasting centers of the U.S. and other nations. The even numbered satellites (ESSA-2, 4, 6, and 8) were equipped with Automatic Picture Transmission (APT) TV cameras which transmitted television pictures directly to ground stations worldwide. ----------------- Entry taken from: Rao, P.K., S.J. Holmes, R.K. Anderson, J.S. Winston, and P.E. Lehr, Weather Satellites: Systems, Data, and Environmental Applications, American Meteorological Society, Boston, 1990. ISBN 0-933876-66-1 Group: Platform_Details Entry_ID: ESSA Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: ESSA Long_Name: Environmental Science Services Administration End_Group Group: Synonymous_Platform_Names Short_Name: ESSA End_Group Creation_Date: 2007-11-19 Online_Resource: https://science.nasa.gov/missions/essa Group: Platform_Logistics Launch_Date: 1966-02-28 Primary_Sponsor: USA/NASA End_Group End_Group 2018-10-30 15:45:36.0 [sritz] Insert Concept add narrower relation (ESSA [65cb3e7c-d4d8-46df-a5fc-aec63e58e8df,345109] - ESSA-9 [1dc828a8-8502-479d-b7c4-d5139c06029a,368211]); 2018-10-30 15:45:23.0 [sritz] Insert Concept add narrower relation (ESSA [65cb3e7c-d4d8-46df-a5fc-aec63e58e8df,345109] - ESSA-7 [2e4252b9-5b53-41bb-8212-1e63a540181f,368207]); 2018-10-30 15:45:08.0 [sritz] Insert Concept add narrower relation (ESSA [65cb3e7c-d4d8-46df-a5fc-aec63e58e8df,345109] - ESSA-5 [8b67c88a-b62f-4585-a5d3-8e0005f42fd0,368203]); 2018-10-30 15:44:06.0 [sritz] Insert Concept add narrower relation (ESSA [65cb3e7c-d4d8-46df-a5fc-aec63e58e8df,345109] - ESSA-4 [50992afe-f79e-47fc-a1a2-126dc2c42c9a,368199]); 2018-10-30 15:43:43.0 [sritz] Insert Concept add narrower relation (ESSA [65cb3e7c-d4d8-46df-a5fc-aec63e58e8df,345109] - ESSA--3 [c7706afe-079a-4966-8a9e-6a688ca9b880,368195]); 2018-10-30 15:42:52.0 [sritz] update Definition (The world's first operational weather satellite system was placed into service with the launching of the Environmental Science Services Administration (which in 1970 became the National Oceanic and Atmospheric Administration, NOAA) satellites, ESSA-1, on February 3, 1966, and ESSA-2, on February 28, 1966. The objective of this program, also called the TIROS Operational System (TOS), was to acquire global observational data routinely on a daily basis. This system consisted of a pair of ESSA satellites in sun-synchronous (polar) orbit. The odd numbered satellites (ESSA-1, 3, 5, 7, and 9) utilized the Advanced Vidicon Camera System (AVCS) to obtain global imagery which were transmitted to the ESSA Command and Data Acquition (CDA) stations at Wallops, Virginia, and Fairbanks, Alaska. The CDA stations relayed the data to the National Environmental Satellite Service (NESS), which later became the National Environmental Satellite, Data, and Information Service (NESDIS), located in Suitland, Maryland, for processing and distribution to forecasting centers of the U.S. and other nations. The even numbered satellites (ESSA-2, 4, 6, and 8) were equipped with Automatic Picture Transmission (APT) TV cameras which transmitted television pictures directly to ground stations worldwide. ----------------- Entry taken from: Rao, P.K., S.J. Holmes, R.K. Anderson, J.S. Winston, and P.E. Lehr, Weather Satellites: Systems, Data, and Environmental Applications, American Meteorological Society, Boston, 1990. ISBN 0-933876-66-1 Group: Platform_Details Entry_ID: ESSA Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: ESSA Long_Name: Environmental Science Services Administration End_Group Group: Synonymous_Platform_Names Short_Name: ESSA End_Group Creation_Date: 2007-11-19 Online_Resource: https://science.nasa.gov/missions/essa Group: Platform_Logistics Launch_Date: 1966-02-28 Primary_Sponsor: USA/NASA End_Group End_Group); delete Resource (null); DMSP 5D-1/F4 [Source: Nationa Space Science Data Center, http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1979-050A ] DMSP 5D-1/F4 was one of a series of meteorological satellites developed and operated by the Air Force under the Defense Meteorological Satellite Program (DMSP). This program, previously known as DAAP (Data Acquisition and Processing Program), was classified until March 1973. The objectives of this program are to provide global visual and infrared cloud-cover data and specialized environmental data to support Department of Defense requirements. Operationally, the program consisted of two satellites in planned 830-km sun-synchronous polar orbits, with the ascending node of one satellite in early morning and the other at local noon. The 5.4-m long spacecraft was separated into four sections: (1) a precision mounting platform (PMP) for sensors and equipment requiring precise alignment, (2) an equipment support module (ESM) containing the electronics, reaction wheels, and some meteorological sensors, (3) a reaction control equipment (RCE) support structure (including the third-stage motor, hydrazine reaction control system) that supported (4) a 9.29 sq m solar cell panel. The spacecraft stabilization was controlled by a combination flywheel and magnetic control coil system, so that sensors were maintained in the desired 'earth-looking' mode. One feature was the precision-pointing accuracy of the primary imager to 0.01 deg provided by a star sensor and an updated ephemeris navigation system. This allowed automatic geographical mapping of the digital imagery to the nearest picture element. The operational line scan system (OLS) built by Westinghouse, was the primary data acquisition system that provided real-time or stored, multi-orbit, day-and-night visual and infrared imagery at 1/3 nautical mile resolution for all major land masses, 1-1/2 nautical mile resolution for complete global coverage, and provided with this data calibration, timing, and other auxiliary signals to the spacecraft for digital transmission to the ground. A supplementary sensor package, the special sensor H (SSH), a step-scanning radiometer, was the infrared temperature-humidity-ozone sounder. The data processing system, which included three high-density tape recorders, was capable of storing a total of 400 min of data, each allowing full global coverage twice daily. Either recorded or real-time data were transmitted to ground-receiving sites by two redundant S-band transmitters. Recorded data were read out to tracking sites located at Fairchild AFB, WA, and Loring AFB, ME, and relayed by SATCOM to Air Fource Global Weather Central, Offutt AFB, NE. Real-time data were read out at mobile tactical sites located around the world. A more complete description of the satellite can be found in the report `The Defense Meteorological Satellite Program,' D.A. Nichols, Optical Engineering, 14, 4, July - August 1975. Group: Platform_Details Entry_ID: DMSP 5D-1/F4 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: DMSP (Defense Meteorological Satellite Program) Short_Name: DMSP 5D-1/F4 Long_Name: Defense Meteorological Satellite Program-F4 End_Group Group: Synonymous_Platform_Names Short_Name: DMSP 15539 Short_Name: DMSP-F4 Short_Name: 11389 End_Group Group: Platform_Associated_Instruments Short_Name: SSC Short_Name: OLS Short_Name: MFR/SSH Short_Name: PES (SSJ/3) Short_Name: PASSIVE IONOSPHERIC MONITOR Short_Name: SSI/E Short_Name: SSM/T Short_Name: SSD End_Group Group: Orbit Orbit_Inclination: 98.7° Period: 101.4 minutes Perigee: 817.0 km Apogee: 839.0 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1979-050A Online_Resource: http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/dmsp.html Online_Resource: http://www.ngdc.noaa.gov/dmsp/index.html Group: Platform_Logistics Launch_Date: 1979-06-06 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: Department of Defense-Department of the Air Force (United States) End_Group End_Group CASSIOPE CASSIOPE (Cascade SmallSat and Ionospheric Polar Explorer)is a new generation of small-satellite and multifunctional platform technology demonstration program of CSA (Canadian Space Agency) with the goal to serve both, namely scientific and commercial support applications in a variety of future Canadian space missions. The science mission, called ePOP (Enhanced Polar Outflow Probe), is comprised of eight instruments. The objective is to measure the interaction of the Earth's upper atmosphere with the solar wind (space weather monitoring with greatly improved prediction capability). 2019-05-06 14:05:48.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: f1f8384c-3846-443b-8bd1-18b7696aafd4 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 1c03710e-1898-49ec-84bb-c064e7a358d0 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 02a50e11-e6ee-4b05-a157-32cf57a74adf relationship type: null relationship value: null generated by: null); 2019-05-06 13:51:35.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: a96885e0-9dc1-4edb-bc29-1cdb320d50f2 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: ee53dfb1-6495-405e-953b-63434a2ec27e relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 0c439fcf-b55c-430e-baee-ae047032df46 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: e0134cc6-79d0-492d-9e9a-6320e04ed972 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: eb47a4c5-5ab5-4803-9395-f58de828499c relationship type: null relationship value: null generated by: null); 2019-04-25 11:15:18.0 [mmorahan] insert AltLabel (id: null category: primary text: Cascade SmallSat and Ionospheric Polar Explorer language code: en); insert Definition (id: null text: CASSIOPE (Cascade SmallSat and Ionospheric Polar Explorer)is a new generation of small-satellite and multifunctional platform technology demonstration program of CSA (Canadian Space Agency) with the goal to serve both, namely scientific and commercial support applications in a variety of future Canadian space missions. The science mission, called ePOP (Enhanced Polar Outflow Probe), is comprised of eight instruments. The objective is to measure the interaction of the Earth's upper atmosphere with the solar wind (space weather monitoring with greatly improved prediction capability). language code: en); 2019-04-25 11:10:05.0 [mmorahan] Insert Concept add broader relation (CASSIOPE [66f5d236-40fb-4a41-96a4-761d48103765,368665] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761]); TET-1 TET-1 (Technologie Erprobungs Träger-1) is a German technology demonstration microsatellite of DLR (German Aerospace Center) within its OOV (On-Orbit Verification) program. Project funding is provided by the German Ministry for Economics and Technology (Bundesministerium für Wirtschaft und Technologie). The overall objective is to provide industry and research institutes with adequate means for the in-flight validation of space technology. Certain programmatic rules were established for the space segment and the ground segment to realize TET-1 as a low-cost mission within a relatively short timeframe under the leadership of an industrial space company as prime contractor. Flight opportunities for technology demonstration and verification should ideally be provided on a regular basis in a cost efficient and safe manner. A market survey of German industries' and institutes' technologies has shown that about 75% of the experiments can be verified using a microsatellite. The OOV-Program is thus structured into two main parts with respect to the flight opportunities offered. The first comprises the microsatellites TET with a planned flight opportunity every two years. For payloads which do not fit on TET microsatellite concept, DLR will cooperate with national and international partners to provide flight opportunities on other carriers. 2019-03-11 17:32:55.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: e9d9df16-ebbf-4f6d-838f-225716619ff9 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 7c6ddfcd-00e3-4194-be91-9a9648f9d30b relationship type: null relationship value: null generated by: null); 2018-10-11 20:36:06.0 [mmorahan] insert AltLabel (id: null category: primary text: Technology Experiment Carrier-1 language code: en); 2018-10-11 20:32:16.0 [mmorahan] insert Definition (id: null text: TET-1 (Technologie Erprobungs Träger-1) is a German technology demonstration microsatellite of DLR (German Aerospace Center) within its OOV (On-Orbit Verification) program. Project funding is provided by the German Ministry for Economics and Technology (Bundesministerium für Wirtschaft und Technologie). The overall objective is to provide industry and research institutes with adequate means for the in-flight validation of space technology. Certain programmatic rules were established for the space segment and the ground segment to realize TET-1 as a low-cost mission within a relatively short timeframe under the leadership of an industrial space company as prime contractor. Flight opportunities for technology demonstration and verification should ideally be provided on a regular basis in a cost efficient and safe manner. A market survey of German industries' and institutes' technologies has shown that about 75% of the experiments can be verified using a microsatellite. The OOV-Program is thus structured into two main parts with respect to the flight opportunities offered. The first comprises the microsatellites TET with a planned flight opportunity every two years. For payloads which do not fit on TET microsatellite concept, DLR will cooperate with national and international partners to provide flight opportunities on other carriers. language code: en); 2018-10-11 20:28:51.0 [mmorahan] Insert Concept add broader relation (TET-1 [67e5bbab-0c9b-40e5-acf7-054671f35d2b,368163] - FireBIRD [9b165321-e03c-44dc-bb9c-d10c32c93ab6,368159]); STEREO A STEREO (Solar TErrestrial RElations Observatory) is a 2-year NASA mission employing two nearly identical space-based observatories to provide the very first, 3-D "stereo" images of the sun to study the nature of coronal mass ejections. These powerful solar eruptions are a major source of the magnetic disruptions on Earth and a key component of space weather, which can greatly affect satellite operations, communications, power systems, the lives of humans in space, and global climate. STEREO is the third mission in NASA's Solar Terrestrial Probes Program. The twin observatories launched aboard a single Boeing Delta II rocket from Cape Canaveral Air Force Station, Fla., on Oct. 25, 2006, at 8:52 p.m. EDT. STEREO is sponsored by NASA Headquarters' Science Mission Directorate, Washington, D.C. NASA Goddard Space Flight Center's Solar Terrestrial Probes Program Office, in Greenbelt, Md., manages the mission, instruments and science center. The Johns Hopkins University Applied Physics Laboratory (APL), in Laurel, Md., designed and built the spacecraft and will operate the twin observatories for NASA during the mission. The two spacecraft are launched to drift slowly away from the Earth in opposite directions at about 10 degrees per year for the lagging spacecraft and 20 degrees per year for the leading one. Optimal longitudinal separation of about sixty degrees is achieved after two years. Afterwards the separation gradually increases beyond the design lifetime of two years with the possibility of extended mission observations at larger angles. Science instruments selected for STEREO include the Sun Earth Connection Coronal and Heliospheric Investigation (SECCHI) for extreme ultraviolet (EUV), white-light coronographic, and heliospheric imaging, the STEREO/WAVES (SWAVES) interplanetary radio burst tracker, the In situ Measurements of Particles and CME Transients (IMPACT) investigation for in-situ sampling the 3-D distribution and plasma characteristics of solar energetic particles and the interplanetary magnetic field, and the PLAsma and SupraThermal Ion and Composition (PLASTIC) experiment to measure elemental and charge composition of ambient and CME plasma ions. STEREO data recorded and stored onboard each spacecraft will be downlinked through the NASA Deep Space Network on a daily schedule. Real-time space weather data will be continuously transmitted through a separate beacon system to NASA and non-NASA receiving stations. Group: Platform_Details Entry_ID: STEREO A Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Short_Name: STEREO A Long_Name: Solar Terrestrial Relations Observatory A End_Group Group: Synonymous_Platform_Names Short_Name: STEREO East Short_Name: STEREO Lag Short_Name: Solar Terrestrial Relations Observatory A Short_Name: 29510 Short_Name: 2006-047A End_Group Group: Platform_Associated_Instruments Short_Name: SWAVES Short_Name: SECCHI Short_Name: PLASTIC Short_Name: IMPACT End_Group Creation_Date: 2007-02-13 Online_Resource: http://www.nasa.gov/mission_pages/stereo/main/ Online_Resource: http://stereo.gsfc.nasa.gov/ Online_Resource: http://stereo.jhuapl.edu/ Online_Resource: http://stereo-ssc.nascom.nasa.gov/ Sample_Image: http://stereo.jhuapl.edu/gallery/images/artistConcepts/tn/PanelsDeploy_tn.jpg Group: Platform_Logistics Launch_Date: 2006-10-26 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Design_Life: 2 years Primary_Sponsor: USA/NASA Primary_Sponsor: Johns Hopkins/APL End_Group End_Group MSTI-2 MSTI 2 (Miniature Sensor Technology Integration 2) was a US Department of Defense spacecraft launched from the Vandenberg AFB by a Scout rocket. It was the last of the now discontinued Scout series. The primary mission of MSTI 2 was to demonstrate theater ballistic missible (TBM) tracking and was intended to last for six months. It successfully spotted and locked onto a test Minuteman-3 launched from Vandenberg AFB. More than three million short wavelength infrared (SWIR) and medium wavelength infrared (MWIR) image frames were obtained during the mission. General Characteristics: Launch date: May 9, 1994 Country of origin: United States Perigee/Apogee: 411/427 km Inclination: 97.1° Period: 92.9 min Launch vehicle Scout #118 End of Life: Out of service: September 1994 Decay: November 28, 1998 Additional Resources: "http://www.actgate.com/msti3/msti2.html" [Summary provided by The Satellite Encyclopedia] ATS-3 ATS 3 was launched in November 1967 and was one of a series of spacecraft designed to demonstrate the utility and feasibility of a variety of technological and scientific activities that could be carried out by an earth-synchronous spacecraft. Of the 11 experiments on board, 8 were technological engineering experiments concerned with navigation, communications, and spacecraft operation equipment; 2 were photographic imaging experiments that produced near real-time daylight pictures of the earth-atmosphere system; and the remaining experiment was an ionospheric beacon. The spin-stabilized spacecraft was cylindrically shaped and measured 180 cm in length and 142 cm in diameter. The primary structural members were a honeycombed equipment shelf and thrust tube. Support rods extended radially outward from the thrust tube and were affixed to solar panels which formed the outer walls of the spacecraft. Equipment components and payload were mounted in the annular space between the thrust tube and solar panels. In addition to solar panels, the spacecraft was equipped with two rechargeable nickel-cadmium batteries to provide electrical power. This satellite supported an image dissector camera, multicolor spin scan cloud cover camera, weather facsimile data relay system, omega position and location equipment designed to demonstrate the feasibility of using the NAVY's Omega Navigation System, and VHF, telemetry, and command antennas. Spacecraft guidance and orbital corrections were accomplished by 2.3 kg hydrogen peroxide and hydrazine thrusters, which were activated by ground command. Initially placed at 48 degrees West over the Atlantic Ocean in a geosynchronous orbit, the satellite position later varied between 45 and 95 degrees West in support of meteorological operations. In general, the various experiments were successful. Group: Platform_Details Entry_ID: ATS-3 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: ATS (Advanced Technology Satellite) Short_Name: ATS-3 Long_Name: Advanced Technology Satellite-3 End_Group Group: Synonymous_Platform_Names Short_Name: Advanced Tech. Sat. 3 Short_Name: 03029 End_Group Creation_Date: 2007-08-29 Online_Resource: http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1967-111A Group: Platform_Logistics Launch_Date: 1967-11-05 Primary_Sponsor: NASA End_Group End_Group Merged Analysis 2018-10-15 18:35:09.0 [sritz] Insert Concept add narrower relation (Merged Analysis [6acce314-322f-4d58-9dcb-1f93457a9d86,345119] - RM-OBS/PU [0fb44090-a3e4-4820-aad5-dafbd76ae1b4,368179]); 2016-12-07 14:47:29.0 [sritz] Insert Concept add narrower relation (Merged Analysis [6acce314-322f-4d58-9dcb-1f93457a9d86,278533] - LANDMET [e951dc1d-eeb5-4d67-ad77-e60ee469486c,278537]); 2016-12-07 14:47:01.0 [sritz] Insert Concept add broader relation (Merged Analysis [6acce314-322f-4d58-9dcb-1f93457a9d86,278533] - Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,256331]); NOAA-12 NOAA-12 (NATIONAL OCEANIC & ATMOSPHERIC ADMINISTRATION-12) [Source: National Space Science Data Center (NSSDC), http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1991-032A ] NOAA-12 (NOAA-D before launch) is a third-generation operational meteorological satellite for use in the National Environmental Satellite, Data, and Information Service (NESDIS). The satellite design provides an economical and stable sun-synchronous (morning equator-crossing) platform for advanced operational instruments to measure the earth's atmosphere, its surface and cloud cover, and the near-space environment. Primary sensors include an Advanced Very High Resolution Radiometer (AVHRR) for observing daytime and nighttime global radiances and temperatures and a TIROS Operational Vertical Sounder (TOVS) for obtaining temperature and water vapor profiles through the earth's atmosphere. Secondary experiments consist of a Space Environment Monitor (SEM), which measures the proton and electron fluxes near the earth, and an ARGOS Data Collection and Location System, which processes and relays to central data acquisition stations the various meteorological data received from free-floating balloons and ocean buoys distributed around the globe. The satellite is based upon the Block 5D spacecraft bus developed for the U.S. Air Force, and it is capable of maintaining an earth-pointing accuracy of better than plus or minus 0.1 deg with a motion rate of less than 0.035 deg/s. NOAA 12 operations were closed as of April 2001. Group: Platform_Details Entry_ID: NOAA-12 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NOAA POES (Polar Orbiting Environmental Satellites) Short_Name: NOAA-12 Long_Name: National Oceanic & Atmospheric Administration-12 End_Group Group: Synonymous_Platform_Names Short_Name: NOAA-D Short_Name: 21263 End_Group Group: Platform_Associated_Instruments Short_Name: AVHRR Short_Name: ADCS Short_Name: HIRS Short_Name: TOVS Short_Name: SEM End_Group Group: Orbit Orbit_Inclination: 98.70 deg Period: 101.3 minutes Perigee: 821.0 km Apogee: 841.0 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-11-05 Online_Resource: http://www.oso.noaa.gov/poes/index.htm Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1991-032A Online_Resource: http://noaasis.noaa.gov/NOAASIS/ml/genlsatl.html Group: Platform_Logistics Launch_Date: 1991-05-14 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: USA/NASA Primary_Sponsor: USA/NOAA End_Group End_Group 2016-06-09 17:13:26.0 [epneff] added altLabel insert AltLabel (id: null text: NOAA-12 (NATIONAL OCEANIC & ATMOSPHERIC ADMINISTRATION-12) language code: en); Nimbus-4 Nimbus-4 was launched in April 1970 and was the fourth in a series of second-generation meteorological research-and-development satellites that was designed to serve as a stabilized, earth-oriented platform for the testing of advanced meteorological sensor systems and for collecting meteorological data. The polar-orbiting spacecraft consisted of three major structures: (1) a ring-shaped sensor mount, (2) solar paddles, and (3) the control system housing. The solar paddles and the control system were connected to the sensor mount by a truss structure, giving the satellite the appearance of an ocean buoy. Nimbus-4 was nearly 3.7 m tall, 1.45 m in diameter at the base, and about 3 m across with solar paddles extended. The torus-shaped sensor mount, which formed the satellite base, housed the electronics equipment and battery modules. The lower surface of the torus ring provided mounting space for sensors and telemetry antennas. An H-frame structure mounted within the center of the torus provided support for the larger experiments and tape recorders. Mounted on the control system housing, which was on top of the spacecraft, were sun sensors, horizon scanners, gas nozzles for attitude control, and a command antenna. Use of an advanced attitude-control subsystem permitted the spacecraft's orientation to be controlled to within plus or minus 1 degree for all three axes (pitch, roll, and yaw). Primary experiments consisted of an image dissector camera system for providing daytime cloudcover pictures both in real-time and recorded modes, temperature-humidity infrared radiometer (THIR) for measuring daytime and nighttime surface and cloudtop temperatures as well as the water vapor content of the upper atmosphere, infrared interferometer spectrometer (IRIS) for measuring the emission spectra of the earth/atmosphere system, satellite infrared spectrometer (SIRS) for determining the vertical profiles of temperature and water vapor in the atmosphere, a monitor of ultraviolet solar energy (MUSE) for detecting solar UV radiation, a backscatter ultraviolet (BUV) detector for monitoring the vertical distribution and total amount of atmospheric ozone on a global scale, a filter wedge spectrometer (FWS) for accurate measurement of IR radiance as a function of wavelength from the earth/atmosphere system, a selective chopper radiometer (SCR) for determining the temperatures of six successive 10-km layers in the atmosphere from absorption measurements in the 15-micrometer CO2 band, and an interrogation, recording, and location system (IRLS) for locating, interrogating, recording, and retransmitting meteorological and geophysical data from remote collection stations. The spacecraft performed well until April 14, 1971, when attitude problems started. The experiments then operated on a limited time basis until September 30, 1980. __________ Taken from the NSSDC System for Information Retrieval and Storage (SIRS). For more information contact the NSSDC Coordinated Request and User Support Office, 301-286-6695 (NASA Goddard Space Flight Center, Code 933.4, Greenbelt, Maryland 20771, USA). Nimbus-4 User's Guide. Group: Platform_Details Entry_ID: NIMBUS-4 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NIMBUS Short_Name: NIMBUS-4 End_Group Group: Synonymous_Platform_Names Short_Name: NIMBUS-D End_Group Group: Platform_Associated_Instruments Short_Name: NEAR-INFRARED SPECTROMETER Short_Name: BUV End_Group Creation_Date: 2007-10-11 Online_Resource: http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1970-025A Online_Resource: http://nasascience.nasa.gov/missions/nimbus Sample_Image: http://space.skyrocket.de/img_sat/nimbus-4__1.jpg Group: Platform_Logistics Launch_Date: 1970-04-08 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: USA/NASA End_Group End_Group 2019-03-26 21:35:45.0 [sritz] update WeightedRelation (Platform-Instrument); update WeightedRelation (1); 2019-03-26 21:35:02.0 [sritz] update Resource (image); insert WeightedRelation (id: null related concept uuid: 7bf9f69e-3bc7-45ad-9224-969676d36d78 relationship type: null relationship value: null generated by: null); 2015-05-12 16:54:13.0 [saritz] update PrefLabel (Nimbus-4); GOES GOES (NOAA GEOSTATIONARY OPERATIONAL ENVIRONMENTAL SATELLITES) GOES satellites provide the kind of continuous monitoring necessary for intensive data analysis. They circle the Earth in a geosynchronous orbit, which means they orbit the equatorial plane of the Earth at a speed matching the Earth's rotation. This allows them to hover continuously over one position on the surface. The geosynchronous plane is about 35,800 km (22,300 miles) above the Earth, high enough to allow the satellites a full-disc view of the Earth. Because they stay above a fixed spot on the surface, they provide a constant vigil for the atmospheric "triggers" for severe weather conditions such as tornadoes, flash floods, hail storms, and hurricanes. When these conditions develop the GOES satellites are able to monitor storm development and track their movements. GOES satellite imagery is also used to estimate rainfall during the thunderstorms and hurricanes for flash flood warnings, as well as estimates snowfall accumulations and overall extent of snow cover. Such data help meteorologists issue winter storm warnings and spring snow melt advisories. Satellite sensors also detect ice fields and map the movements of sea and lake ice. NASA launched the first GOES for NOAA in 1975 and followed it with another in 1977. Currently, the United States is operating GOES-10 and GOES-12. (GOES-9, which is partially operational, is being provided to the Japanese Meteorological Agency to replace their failing geostationary satellite.) GOES-11 is being stored in orbit as a replacement for GOES-12 or GOES-10 in the event of failure. Additional Information on GOES Satellites: "http://www.oso.noaa.gov/goes/" To view a 3D orbit of GOES satellites, observe the J Track satellite tracking web page at: "http://liftoff.msfc.nasa.gov/realtime/jtrack/" [Summary Extracted from the NOAA Office of Satellite Operations Home Page] Group: Platform_Details Entry_ID: GOES Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: GOES (Geostationary Operational Environmental Satellite) Short_Name: GOES Long_Name: NOAA Geostationary Operational Environmental Satellites End_Group Group: Synonymous_Platform_Names Short_Name: GOES-1 Short_Name: GOES-2 Short_Name: GOES-3 Short_Name: GOES-4 Short_Name: GOES-5 Short_Name: GOES-6 Short_Name: GOES-7 Short_Name: GOES-8 Short_Name: GOES-9 Short_Name: GOES-10 Short_Name: GOES-11 Short_Name: GOES-12 Short_Name: GOES-13 Short_Name: GOES-N End_Group Group: Platform_Associated_Instruments Short_Name: SEM Short_Name: SAR Short_Name: HEPAD Short_Name: MAGNETOMETERS Short_Name: VAS Short_Name: VISSR Short_Name: GOES I-M SOUNDER Short_Name: GOES I-M IMAGER Short_Name: SXI End_Group Group: Orbit Orbit_Altitude: 35,800 km (22,300 miles) Orbit_Inclination: 0.41 degrees Period: 1,436 minutes Repeat_Cycle: GOES flies in an orbit above the equator at the same rate as the equator turns -- one cycle per day. Apogee: 400 000 km (240 000 mi) Orbit_Type: GEO > Geosynchronous > Geostationary End_Group Creation_Date: 2007-05-08 Online_Resource: http://www.oso.noaa.gov/goes/ Online_Resource: http://www.goes.noaa.gov/ Online_Resource: http://goes.gsfc.nasa.gov/ Online_Resource: http://goespoes.gsfc.nasa.gov/goes/index.html Online_Resource: http://rsd.gsfc.nasa.gov/goes/text/goes.databook.html Online_Resource: http://goes.gsfc.nasa.gov/text/goesfaq.html Sample_Image: http://goes.gsfc.nasa.gov/images/thenextgeneration.gif Group: Platform_Logistics Launch_Site: Cape Canaveral/Kennedy Space Center, USA Design_Life: 7 to 11 years Primary_Sponsor: USA/NASA Primary_Sponsor: USA/NOAA End_Group End_Group 2016-06-09 14:43:57.0 [epneff] added altLabel insert AltLabel (id: null text: GOES (NOAA GEOSTATIONARY OPERATIONAL ENVIRONMENTAL SATELLITES) language code: en); Nimbus-6 Nimbus-6 was launched in June 1975 and was a research-and-development satellite serving as a stabilized, earth-oriented platform for testing advanced systems for sensing and collecting meteorological data on a global scale. The polar-orbiting spacecraft consisted of three major structures: (1) a hollow torus-shaped sensor mount, (2) solar paddles, and (3) a control housing unit connected to the sensor mount by a tripod truss structure. Configured somewhat like an ocean buoy, Nimbus-6 was nearly 3.7 m tall, 1.5 m in diameter at the base, and about 3 m wide with solar paddles extended. The sensor mount that formed the satellite base housed the electronics equipment and battery modules. The lower surface of the torus provided mounting space for sensors and antennas. A box-beam structure mounted within the center of the torus supported the larger sensor experiments. Mounted on the control housing unit, which was located on top of the spacecraft, were sun sensors, horizon scanners, and a command antenna. The spacecraft spin axis was pointed at the earth. An advanced attitude-control system permitted the spacecraft's orientation to be controlled to within plus or minus 1 degree in all three axes (pitch, roll, and yaw). The experiments selected for Nimbus-6 were the earth radiation budget (ERB), electrically scanning microwave radiometer (ESMR), high-resolution infrared radiation sounder (HIRS), limb radiance inversion radiometer (LRIR), pressure modulated radiometer (PMR), scanning microwave spectrometer (SCAMS), temperature-humidity infrared radiometer (THIR), tracking and data relay experiment (T+DRE), and the tropical wind energy conversion and reference level experiment (TWERLE). This complement of advanced sensors was capable of mapping tropospheric temperature, water vapor abundance, and cloud water content; providing vertical profiles of temperature, ozone, and water vapor; transmitting real-time data to a geostationary spacecraft (ATS 6); and yielding data on the earth's radiation budget. __________ Taken from the NSSDC System for Information Retrieval and Storage (SIRS). For more information contact the NSSDC Coordinated Request and User Support Office, 301-286-6695 (NASA Goddard Space Flight Center, Code 933.4, Greenbelt, Maryland 20771, USA). Nimbus-6 User's Guide. Group: Platform_Details Entry_ID: NIMBUS-6 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NIMBUS Short_Name: NIMBUS-6 End_Group Group: Synonymous_Platform_Names Short_Name: NIMBUS-F End_Group Group: Platform_Associated_Instruments Short_Name: ESMR Short_Name: THIR Short_Name: HIRS End_Group Creation_Date: 2007-10-15 Online_Resource: http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1975-052A Online_Resource: http://nasascience.nasa.gov/missions/nimbus Group: Platform_Logistics Launch_Date: 1975-06-12 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: USA/NASA End_Group End_Group 2015-05-12 16:54:51.0 [saritz] update PrefLabel (Nimbus-6); AEROSONDE AEROSONDE: Small robotic aircraft for long-range environmental monitoring and surveillance. It has been developed especially for meteorological and environmental reconnaissance over oceanic and remote areas and in harsh conditions, for which its economy and flexibility will allow routine operations on a much wider scale than has been possible in the past. It has been extended to surveillance and other reconnaissance applications. The Aerosonde is being deployed to fill chronic gaps in the global upper-air sounding network, to conduct systematic surveillance of tropical cyclones and other severe weather, to undertake offshore surveillance and agricultural/biological surveys, and to obtain specialist observations, such as volcanic plumes. Miniaturisation and flexibility, fully robotic operation and remote command are the key factors in the Aerosonde success. We have proven that an aircraft weighing less than 15 kg can undertake completely autonomous missions of several thousand kilometres and several days duration. Technical Specifications: Aerosonde Robotic Aircraft Mark 3 Specifications Weight, wing span: 13-14 kg, 2.9 m Engine: 24 cc, Premium Unleaded Petrol, 1kw, fuel injected Navigation: GPS, DGPS, automatic storm/front tracking Operation Staff for Launch and Recovery 2-3: Controller, Engineer, Pilot/Maintenance Staff for Flight Operations: 1 Person for up to 3 aircraft Ground Equipment: Proprietary Staging Box, Personal Computer, GPS Antenna Flight: Fully autonomous, under Base Command Launch and Recovery: Launch from car roof rack (catapult option), land on belly, Autonomous or with pilot Ground & air communications: UHF or SatComms to Aerosonde, VHF to field staff and other aircraft , internet to command centre and customers. Performance Speed, Climb: 18 ? >32 ms-1, Climb >2.5 ms-1 Range, Endurance: >3000 km , >30Hrs Altitude Range: 100 m ? >6000 m (intermediate weight) Payload: Maximum 2 kg with full fuel load Standard Instrumentation Temperature, Pressure, Humidity, Wind 3 More info at "http://www.aerosonde.com/index.php" [Information provided by AEROSONDE] Group: Platform_Details Entry_ID: AEROSONDE Group: Platform_Identification Platform_Category: Aircraft Short_Name: AEROSONDE End_Group Creation_Date: 2007-08-21 Online_Resource: http://www.aerosonde.com/ Sample_Image: http://www.aerosonde.com/images/featurepics/snow.jpg Group: Platform_Logistics Launch_Date: 1998-08-21 End_Group End_Group GEMINI-6 - Spacecraft Brief Description - GEMINI 6 was the fifth manned earth-orbiting spacecraft of the GEMINI series, having been launched after GEMINI 7. the mission priorities were to demonstrate on-time launch procedures, closed-loop rendezvous capabilities, and stationkeeping techniques with GEMINI 7. the crew conducted three scientific experiments -- (1) synoptic terrain photography, (2) synoptic weather photography, and (3) dim light photography. The mission was successfully completed after 25 hours of flight. The spacecraft landed within 11 km of the target point on December 16, 1965. - Auxiliary Information - Launch Date and Time : 1965-12-15 13:40:00 Epoch Date and Time : 1965-12-15 Apogee (km or AU): 271. Perigee (km or AU): 258. Inclination (degree) : 28.89 Orbit Type : Geocentric Additional information available at "http://science.ksc.nasa.gov/history/gemini/gemini-vi-a/gemini-vi-a.html" TDX [SOURCE: http://www.dlr.de/dlr/en/desktopdefault.aspx/tabid-10378/566_read-426/#/gallery/345] The main objective of the TanDEM-X mission is to generate an accurate three-dimensional image of Earth that is homogeneous in quality and unprecedented in accuracy. At present, the elevation models that are available for large parts of Earth are of low resolution, inconsistent or incomplete. In addition, they are commonly based on different data sources and survey methods. TanDEM-X, TerraSAR-X add-on for Digital Elevation Measurement, is designed to close these gaps and deliver a homogenous elevation model that should prove indispensable for many scientific and commercial applications. Orbiting Earth at an altitude of around 500 kilometres, the two nearly-identical radar satellites have begun mapping its surface. The first of the two, TerraSAR-X, has been operating since 2007. Three years years on, it has been joined by its twin satellite, TanDEM-X. Flying in close formation only a few hundred metres apart, the two satellites are imaging the terrain below them simultaneously, from different angles. These images are processed into accurate elevation maps with a 12-metre resolution and a vertical accuracy better than 2 metres. The amount of data generated by the satellites will grow to 1.5 petabytes within three years, corresponding to a storage capacity of almost 200,000 DVDs. Like the TerraSAR-X mission, TanDEM-X is a project developed under a public-private partnership between the German Aerospace Center, DLR, and Astrium GmbH based in Friedrichshafen, Germany. The TanDEM-X mission The TanDEM-X mission will survey all 150 million square kilometres of Earth's land surface several times over during its three-year mission. Apart from its high measuring-point density (a 12-metre grid) and high vertical accuracy (better than two metres), the elevation model generated by TanDEM-X will have another unrivalled advantage – being entirely homogenous, it will serve as a basis for maps that are globally consistent. Conventional maps are often fragmented along national borders, or difficult to reconcile as they are based on different survey methods or because of time lags between survey campaigns. Together TanDEM-X and TerraSAR-X are form the first configurable synthetic aperture radar interferometer in space. Besides this primary goal, the mission has several secondary objectives based on new and innovative methods such as along-track interferometry, polarimetric synthetic aperture radar interferometry, digital beamforming and bistatic radar. The TanDEM-X satellite follows the TerraSAR-X design with minor modifications such as an additional cold gas propulsion system (powered by high-pressure nitrogen gas) to enable fine-tuning of its relative position during formation flying and an additional S-band receiver to receive status and position information sent by TerraSAR-X. The TanDEM-X satellite has been designed for a nominal lifetime of five years and has a planned overlap with TerraSAR-X of three years. TerraSAR-X holds consumables and resources for up to seven years of operation however, potentially allowing for a prolongation of the overlap and the duration of the TanDEM-X mission 2019-03-18 16:36:50.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: ab70584d-30b9-49c1-b1d6-b05cd8c9cbb0 relationship type: null relationship value: null generated by: null); 2017-04-25 21:33:33.0 [aaleman] added new keyword at NSIDC request insert AltLabel (id: null text: TanDEM-X language code: en); insert Definition (id: null text: [SOURCE: http://www.dlr.de/dlr/en/desktopdefault.aspx/tabid-10378/566_read-426/#/gallery/345] The main objective of the TanDEM-X mission is to generate an accurate three-dimensional image of Earth that is homogeneous in quality and unprecedented in accuracy. At present, the elevation models that are available for large parts of Earth are of low resolution, inconsistent or incomplete. In addition, they are commonly based on different data sources and survey methods. TanDEM-X, TerraSAR-X add-on for Digital Elevation Measurement, is designed to close these gaps and deliver a homogenous elevation model that should prove indispensable for many scientific and commercial applications. Orbiting Earth at an altitude of around 500 kilometres, the two nearly-identical radar satellites have begun mapping its surface. The first of the two, TerraSAR-X, has been operating since 2007. Three years years on, it has been joined by its twin satellite, TanDEM-X. Flying in close formation only a few hundred metres apart, the two satellites are imaging the terrain below them simultaneously, from different angles. These images are processed into accurate elevation maps with a 12-metre resolution and a vertical accuracy better than 2 metres. The amount of data generated by the satellites will grow to 1.5 petabytes within three years, corresponding to a storage capacity of almost 200,000 DVDs. Like the TerraSAR-X mission, TanDEM-X is a project developed under a public-private partnership between the German Aerospace Center, DLR, and Astrium GmbH based in Friedrichshafen, Germany. The TanDEM-X mission The TanDEM-X mission will survey all 150 million square kilometres of Earth's land surface several times over during its three-year mission. Apart from its high measuring-point density (a 12-metre grid) and high vertical accuracy (better than two metres), the elevation model generated by TanDEM-X will have another unrivalled advantage – being entirely homogenous, it will serve as a basis for maps that are globally consistent. Conventional maps are often fragmented along national borders, or difficult to reconcile as they are based on different survey methods or because of time lags between survey campaigns. Together TanDEM-X and TerraSAR-X are form the first configurable synthetic aperture radar interferometer in space. Besides this primary goal, the mission has several secondary objectives based on new and innovative methods such as along-track interferometry, polarimetric synthetic aperture radar interferometry, digital beamforming and bistatic radar. The TanDEM-X satellite follows the TerraSAR-X design with minor modifications such as an additional cold gas propulsion system (powered by high-pressure nitrogen gas) to enable fine-tuning of its relative position during formation flying and an additional S-band receiver to receive status and position information sent by TerraSAR-X. The TanDEM-X satellite has been designed for a nominal lifetime of five years and has a planned overlap with TerraSAR-X of three years. TerraSAR-X holds consumables and resources for up to seven years of operation however, potentially allowing for a prolongation of the overlap and the duration of the TanDEM-X mission language code: en); 2017-04-25 21:31:43.0 [aaleman] Insert Concept add broader relation (TDX [6c21f29b-5dd4-4e96-a6fb-44e4788d1973,309555] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,287601]); SBAS SBAS is a satellite-based augmentation system that supports wide-area or reginal augmentation through the use of additional satellite broadcast messages. There are several SBAS systems around the world, such as WAAS in the U.S. and EGNOS in Europe. 2017-08-15 13:53:02.0 [tstevens] insert Definition (id: null text: SBAS is a satellite-based augmentation system that supports wide-area or reginal augmentation through the use of additional satellite broadcast messages. There are several SBAS systems around the world, such as WAAS in the U.S. and EGNOS in Europe. language code: en); 2017-08-14 19:25:25.0 [tstevens] insert AltLabel (id: null category: primary text: Satellite-Based Augmentation System Satellites language code: en); 2017-08-14 19:25:01.0 [tstevens] Insert Concept add broader relation (SBAS [6c37b37f-44f3-4cfd-859d-44f9266d97cb,309931] - SBAS (Satellite-Based Augmentation System) [612454e6-06ce-4bd3-b4f2-6db85f49a013,309927]); IKHANA NASA's Ikhana / Predator B has a wingspan of 66 feet and is 36 feet long. More than 400 pounds of sensors can be carried internally and over 2,000 pounds in external under-wing pods. Ikhana is powered by a Honeywell TPE 331-10T turbine engine and is capable of reaching altitudes above 40,000 feet. The Ikhana is the first production Predator B equipped with a digital electronic engine controller developed by Honeywell and GA-ASI that will make Ikhana five to 10 percent more fuel efficient than earlier versions of the aircraft. Group: Platform_Details Entry_ID: IKHANA Group: Platform_Identification Platform_Category: Aircraft Short_Name: IKHANA Long_Name: Ikhana Unmanned Science and Research Aircraft System End_Group Creation_Date: 2012-07-23 Online_Resource: http://www.nasa.gov/centers/dryden/news/FactSheets/FS-097-DFRC.html Sample_Image: http://www.nasa.gov/centers/dryden/images/content/258832main_ED07-0038-052c_226-170.jpg End_Group GLONASS-40-82 GLONASS Satellites Characteristics: Satellite name/other name/full name: GLONASS / / Russian GLObal NAvigation Satellite System GLONASS Launch date: set into orbit since 1982 Satellite Number: see previous page under COSPAR IDs Perigee Height: 19 100 km Apogee Height: 19 100 km Eccentricity: roughly circular Inclination: 64.8 degrees Semi-major axis: 25 440 km Comment: The space segment of GLONASS is formed by 24 satellites located on three orbital planes. Each satellite is identified by its slot number, which defines the orbital plane (1-8, 9-16, 17-24) and the location within the plane. The three orbital planes are separated 120 degrees, and the satellites within the the same orbital plane by 45 degrees. Group: Platform_Details Entry_ID: GLONASS-40-82 Group: Platform_Identification Platform_Category: Navigation Platforms Platform_Series_or_Entity: GLONASS Short_Name: GLONASS-40-82 Long_Name: Global Navigation Satellite System 40-82 End_Group Group: Platform_Associated_Instruments Short_Name: GPS End_Group Group: Orbit Orbit_Altitude: 19,100 km Orbit_Inclination: 64.8 degrees Repeat_Cycle: 11 hours 15 minutes Perigee: 19,100 km Apogee: 19, 100 km End_Group Creation_Date: 2007-02-12 Online_Resource: http://www.glonass-ianc.rsa.ru/pls/htmldb/f?p=202:1:2884436078431393054 Sample_Image: http://ilrs.gsfc.nasa.gov/images/glonass.gif Group: Platform_Logistics Launch_Date: 1982-10-12 Primary_Sponsor: Russia End_Group End_Group R/V ITALICA 2012-07-30 19:46:25.0 [aaleman] Insert Concept add broader relation (R/V ITALICA [6cf9a0ac-18c6-492a-b302-62ad4c918fcf,40425] - SHIPS [82a67b12-e99d-4c90-8a6a-a6f79d4c3c7b,31201]); Elektro-L N1 Geostationary Operational Meteorological Satellite (Elektro-L N1) Group: Platform_Details Entry_ID: Elektro-L N1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: Elektro-L N1 Long_Name: Geostationary Operational Meteorological Satellite End_Group Group: Platform_Associated_Instruments Short_Name: DCS Short_Name: GGAK-E Short_Name: MSU-GS End_Group Group: Orbit Orbit_Altitude: 36000 km Orbit_Inclination: 0 degrees Period: 1436 minutes Repeat_Cycle: 1 day Orbit_Type: GEO > GEOSYNCHRONOUS > GEOSTATIONARY End_Group Creation_Date: 2015-01-26 Online_Resource: http://www.laspace.ru/rus/electro.php Sample_Image: http://www.federalspace.ru/media/img/site/elektro001.jpg Group: Platform_Logistics Launch_Date: 2011-01-20 Design_Life: 10 years End_Group End_Group 2019-12-31 17:24:12.0 [sritz] Move Concepts delete broader relation (null); add broader relation (Elektro-L N1 [6d0d4c3e-acfb-4bfd-ab0d-4478e18e4b19,541909] - Elektro-L [882c16a9-0bc6-4773-8066-e25ea8de3c9d,559581]); 2015-08-03 13:06:30.0 [mpmorahan] insert AltLabel (id: null text: Geostationary Operational Meteorological Satellite language code: en); 2015-08-03 13:03:55.0 [mpmorahan] Insert Concept add broader relation (Elektro-L N1 [6d0d4c3e-acfb-4bfd-ab0d-4478e18e4b19,158135] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,143415]); OCO-2 OCO-2 is designed to provide space-based global measurements of atmospheric carbon dioxide (CO2) with the precision and resolution needed to identify and characterize the processes that regulate this important greenhouse gas. With its three high-resolution grating spectrometers, data collected by OCO-2 could be combined with meteorological observations and ground-based CO2 measurement to help characterize CO2 sources and sinks on regional scales at monthly intervals for 2 years. More Information: https://oco.jpl.nasa.gov/ Summary provided by NASA Group: Platform_Details Entry_ID: OCO-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: OCO-2 Long_Name: Orbiting Carbon Observatory-2 End_Group Group: Platform_Associated_Instruments Short_Name: OCO SPECTROMETERS End_Group Creation_Date: 2010-09-10 Online_Resource: https://oco.jpl.nasa.gov/ Online_Resource: https://science.jpl.nasa.gov/projects/OCO/ Online_Resource: https://www.nasa.gov/mission_pages/oco2/ Group: Platform_Logistics Launch_Date: 2014-07-02 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: USA/NASA End_Group End_Group 2020-01-02 22:51:04.0 [sritz] update Definition (OCO-2 is designed to provide space-based global measurements of atmospheric carbon dioxide (CO2) with the precision and resolution needed to identify and characterize the processes that regulate this important greenhouse gas. With its three high-resolution grating spectrometers, data collected by OCO-2 could be combined with meteorological observations and ground-based CO2 measurement to help characterize CO2 sources and sinks on regional scales at monthly intervals for 2 years. More Information: https://oco.jpl.nasa.gov/ Summary provided by NASA Group: Platform_Details Entry_ID: OCO-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: OCO-2 Long_Name: Orbiting Carbon Observatory-2 End_Group Group: Platform_Associated_Instruments Short_Name: OCO SPECTROMETERS End_Group Creation_Date: 2010-09-10 Online_Resource: https://oco.jpl.nasa.gov/ Online_Resource: https://science.jpl.nasa.gov/projects/OCO/ Online_Resource: https://www.nasa.gov/mission_pages/oco2/ Group: Platform_Logistics Launch_Date: 2014-07-02 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: USA/NASA End_Group End_Group); 2019-05-06 11:06:31.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: 6d5f222a-7750-4fd3-aa14-3c0d0059bc85 relationship type: null relationship value: null generated by: null); 2018-04-24 20:55:43.0 [sritz] update WeightedRelation (Similar); update WeightedRelation (1); update WeightedRelation (Similar); update WeightedRelation (1); 2018-04-24 20:52:42.0 [sritz] insert WeightedRelation (id: null related concept uuid: da687fb4-016d-4b4d-92c2-380640ca5640 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 3e77610e-bb50-4c45-a62a-c50194ec16c2 relationship type: null relationship value: null generated by: null); 2018-03-14 18:16:21.0 [sritz] update Definition (OCO-2 is designed to provide space-based global measurements of atmospheric carbon dioxide (CO2) with the precision and resolution needed to identify and characterize the processes that regulate this important greenhouse gas. With its three high-resolution grating spectrometers, data collected by OCO-2 could be combined with meteorological observations and ground-based CO2 measurement to help characterize CO2 sources and sinks on regional scales at monthly intervals for 2 years. More Information: https://oco.jpl.nasa.gov/ Summary provided by NASA Group: Platform_Details Entry_ID: OCO-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: OCO-2 Long_Name: Orbiting Carbon Observatory-2 End_Group Group: Platform_Associated_Instruments Short_Name: OCO SPECTROMETERS End_Group Creation_Date: 2010-09-10 Online_Resource: https://oco.jpl.nasa.gov/ Online_Resource: https://science.jpl.nasa.gov/projects/OCO/ Online_Resource: https://www.nasa.gov/mission_pages/oco2/index.html Group: Platform_Logistics Launch_Date: 2014-07-02 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: USA/NASA End_Group End_Group); 2018-03-13 18:36:19.0 [sritz] update Definition (OCO-2 is designed to provide space-based global measurements of atmospheric carbon dioxide (CO2) with the precision and resolution needed to identify and characterize the processes that regulate this important greenhouse gas. With its three high-resolution grating spectrometers, data collected by OCO-2 could be combined with meteorological observations and ground-based CO2 measurement to help characterize CO2 sources and sinks on regional scales at monthly intervals for 2 years. Summary provided by NASA Group: Platform_Details Entry_ID: OCO-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: OCO-2 Long_Name: Orbiting Carbon Observatory-2 End_Group Group: Platform_Associated_Instruments Short_Name: OCO SPECTROMETERS End_Group Creation_Date: 2010-09-10 Online_Resource: https://oco.jpl.nasa.gov/ Online_Resource: https://science.jpl.nasa.gov/projects/OCO/ Online_Resource: https://www.nasa.gov/mission_pages/oco2/index.html Group: Platform_Logistics Launch_Date: 2014-07-02 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: USA/NASA End_Group End_Group); GEMINI-11 Spacecraft Brief Description Gemini 11 was the ninth manned earth-orbiting spacecraft of the Gemini series. The 3-day mission was designed to achieve a first orbit rendezvous and docking with the agena target vehicle, to accomplish two extravehicular activity (EVA) tests, and to perform spacecraft maneuvers. There were also eight scientific and four technological experiments on board. The scientific experiments were (1) synergistic effect of zero-g and radiation on white blood cells, (2) synoptic terrain photography, (3) synoptic weather photography, (4) nuclear emulsions, (5) airglow horizon photography, (6) UV astronomical photography, (7) Gemini ion wake measurement, and (8) dim sky photography. The experiments and the other mission objectives were successfully completed. Reentry occurred after 44 orbits using the first closed-loop automatic reentry mode. The spacecraft landed within 4.8 km of the planned impact point on september 15, 1966. Auxiliary Information Launch Date and Time : 1966-09-12 14:38:00 Epoch Date and Time : 1966-09-12 Orbit Type : Geocentric Apogee(km) : 280. Perigee(km) : 161. Inclination : 28.83 Date of last update : 1992-05-11 Additional information available at "http://www.friends-partners.ru/partners/mwade/flights/gemini11.htm" Group: Platform_Details Entry_ID: GEMINI-11 Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Platform_Series_or_Entity: GEMINI Short_Name: GEMINI-11 End_Group Group: Synonymous_Platform_Names Short_Name: TITAN II End_Group Group: Orbit Orbit_Inclination: 28.8 Perigee: 161 Apogee: 280 End_Group Creation_Date: 2008-01-18 Online_Resource: http://www.friends-partners.ru/partners/mwade/flights/gemini11.htm Sample_Image: http://science.ksc.nasa.gov/history/gemini/gemini-xi/gemini-xi-patch-small.gif Group: Platform_Logistics Launch_Date: 1966-09-12 Primary_Sponsor: NASA End_Group End_Group GOES-10 [Source: NASA NSSDC, http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1997-019A ] The Geostationary Operational Environmental Satellite GOES 10 is the third satellite in a series of next generation geosynchronous spacecraft, referred to as GOES-NEXT and represented by the GOES I through GOES M spacecraft. The GOES-NEXT series is a joint effort on the part of NASA and NOAA to provide continued operational monitoring of weather systems primarily over the United States, distribute meteorological data to regional and national weather offices within the USA, contribute to the development of an environmental data collection network, contribute to the search and rescue program, improve the capability for forcasting and provide real-time warnings of solar distrubances, and to extend knowledge and understanding of atmospheric processes to improve short and long-term weather forecasts. The GOES-NEXT series extends the capabilities of the previous GOES 1-7 spacecraft. The GOES I-M spacecraft will be placed over the equator at 135 deg West or 75 deg West. The design allows unobstructed views of the Earth for operational coverage by the spacecraft sensors. The spacecraft configuration is a compact box-shaped main body that carries the Earth-observing instruments, a continuous-drive solar array attached to the south panel through a yoke assembly, and a solar pointing instrument gimbal mounted on the solar panel yoke. The main body accomodates the sensors, electronics, and support subsystems. The communication antennas, except the Tracking, Telemetry, and Command (TT&C) antenna, are hard-mounted to the Earth-facing panel. The Propulsion Module consists of the fuel and oxidizer tanks for the bipropellant propulsion subsystem mounted on the central cylinder. The Attitude and Orbit Control Substem (AOCS) provides attitude control of the spacecraft. The AOCS consists of the sensors, electronics, and the actuators. The GOES power is generated from the solar array and two 12 A-hr batteries. Power is automatically regulated during solar eclipses. A conical shaped solar sail at the end of a 58-foot boom balances torque caused by solar radiation. The main body of the spacecraft is a 2-meter cube. In its deployed orbit configuration, the overall length is about 27 meters. Initial mass was about 4640 pounds, including fuel. Design lifetime is about five years. The Image Navigation/Registration (INR) system provides Imager and Sounder data products in real-time to users. The Communications, Command, and Data Handling subsystem is comprised of antennas, receivers, transponders, transmitters, data encoders and encryptors and multiplexers. The Tracking Telemetry and Command (TT&C) subsystem provides the necessary monitor and command link between the spacecraft and the ground stations. The GOES-NEXT instruments consist of the following: (1) Earth Imaging System, a 5-channel visible and infrared radiometer which provides Earth imagery 24 hours a day; (2) Sounding System, a 19-channel discrete-filter radiometer for obtaining atmospheric temperature and moisture soundings; (3) a Space Environment Monitor (SEM), which consists of a magnetic field sensor, a solar X-ray sensor, an energetic particle sensor (EPS), and a High Energy Proton and Alpha Detector (HEPAD); (4) a Search and Rescue subsystem (SARSAT), which receives signals from 406 MHz distress beacons and relays them to the ground; (5) a Data Collection System (DCS) for collecting and relaying real-time information from Data Collection Platforms (DCPs) such as buoys, balloons, remote weather stations, ships, and aircraft; and (6) a Weather Facsimile (WEFAX) system which relays processed weather imagary from the Wallops Island station to the user community. The SEC package has been frequently eratic during 2003. Group: Platform_Details Entry_ID: GOES-10 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: GOES (Geostationary Operational Environmental Satellite) Short_Name: GOES-10 Long_Name: Geostationary Operational Environmental Satellite 10 End_Group Group: Synonymous_Platform_Names Short_Name: GOES-10 Short_Name: 24786 End_Group Group: Platform_Associated_Instruments Short_Name: GOES I-M IMAGER Short_Name: GOES I-M SOUNDER End_Group Group: Orbit Orbit_Type: GEO > Geosynchronous > Geostationary End_Group Creation_Date: 2007-10-03 Online_Resource: http://www.oso.noaa.gov/goes/ Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1997-019A Online_Resource: http://goes.gsfc.nasa.gov/ Sample_Image: http://library01.gsfc.nasa.gov/gdprojs/images/goes_2.jpg Group: Platform_Logistics Launch_Date: 1997-04-25 Launch_Site: CAPE CANAVERAL/KENNEDY SPACE CENTER, USA Primary_Sponsor: USA/NASA Primary_Sponsor: USA/NOAA End_Group End_Group ECHO-2 The Echo 2 spacecraft was a 41-m balloon of aluminum foil-mylar laminate. Echo 2 was designed as a rigidized passive communications spacecraft for testing propagation, tracking, and communication techniques. Instrumentation included a beacon telemetry system that provided a tracking signal, monitored spacecraft skin temperature between -120 deg C and +16 deg C, and measured the internal pressure of the spacecraft between 5E-5 mm of mercury and 0.5 mm of mercury, especially during the initial inflation stages. This system, which consisted of two beacon assemblies, used solar cell panels for power and had a minimum power output of 45 mW at 136.17 MHz and 136.02 MHz. In addition to fulfilling its communications mission, the spacecraft was used for global geometric geodesy. The spacecraft re-entered the atmosphere on June 7, 1969. [Summary provided by NASA.] Group: Platform_Details Entry_ID: ECHO-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: ECHO Short_Name: ECHO-2 End_Group Group: Orbit Orbit_Inclination: 81.5 degrees Perigee: 1029 km Apogee: 1316 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2008-10-24 Online_Resource: http://msl.jpl.nasa.gov/QuickLooks/echoQL.html Group: Platform_Logistics Launch_Date: 1964-01-25 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: NASA End_Group End_Group GOES 2017-09-01 16:47:27.0 [sritz] Insert Concept add narrower relation (GOES [6e332c25-caeb-4917-afb6-af757bcecd72,310071] - GOES-15 [f9649a77-f89c-4b3a-a5e5-624ccfccf97d,310131]); 2017-09-01 16:47:13.0 [sritz] Insert Concept add narrower relation (GOES [6e332c25-caeb-4917-afb6-af757bcecd72,310071] - GOES-14 [530c0bf3-28b9-4cb7-ad4e-979ad7444933,310127]); 2017-09-01 16:47:01.0 [sritz] Insert Concept add narrower relation (GOES [6e332c25-caeb-4917-afb6-af757bcecd72,310071] - GOES-13 [98685a1b-9825-43c0-b0d9-6a65f8cb8c7c,310123]); 2017-09-01 16:46:52.0 [sritz] Insert Concept add narrower relation (GOES [6e332c25-caeb-4917-afb6-af757bcecd72,310071] - GOES-12 [ccc4869c-ff0c-41ef-b621-eaeae1ffb79b,310119]); 2017-09-01 16:46:41.0 [sritz] Insert Concept add narrower relation (GOES [6e332c25-caeb-4917-afb6-af757bcecd72,310071] - GOES-11 [d1c98f16-ae13-45a0-b1bf-de4fd2a5b1c7,310115]); 2017-09-01 16:46:28.0 [sritz] Insert Concept add narrower relation (GOES [6e332c25-caeb-4917-afb6-af757bcecd72,310071] - GOES-10 [49178ef5-a003-4de2-9553-066f629bb072,310111]); 2017-09-01 16:46:18.0 [sritz] Insert Concept add narrower relation (GOES [6e332c25-caeb-4917-afb6-af757bcecd72,310071] - GOES-9 [8651726e-1f93-4a65-9e09-4be1e3075e5d,310107]); 2017-09-01 16:46:07.0 [sritz] Insert Concept add narrower relation (GOES [6e332c25-caeb-4917-afb6-af757bcecd72,310071] - GOES-8 [2fa330c6-862b-408a-bdea-cc0eb502f3d2,310103]); 2017-09-01 16:45:49.0 [sritz] Insert Concept add narrower relation (GOES [6e332c25-caeb-4917-afb6-af757bcecd72,310071] - GOES-7 [e8fbbfce-0ba2-431c-8533-a1ec9347efd1,310099]); 2017-09-01 16:45:35.0 [sritz] Insert Concept add narrower relation (GOES [6e332c25-caeb-4917-afb6-af757bcecd72,310071] - GOES-6 [b048b823-7125-4426-b25d-121c85044bb4,310095]); 2017-09-01 16:44:58.0 [sritz] Insert Concept add narrower relation (GOES [6e332c25-caeb-4917-afb6-af757bcecd72,310071] - GOEs-5 [18ceff7d-c5cd-4a72-86af-9a3ac0a884c4,310091]); 2017-09-01 16:44:49.0 [sritz] Insert Concept add narrower relation (GOES [6e332c25-caeb-4917-afb6-af757bcecd72,310071] - GOES-4 [79de5661-cfa3-491d-bb30-4414452676e8,310087]); 2017-09-01 16:36:33.0 [sritz] Insert Concept add narrower relation (GOES [6e332c25-caeb-4917-afb6-af757bcecd72,310071] - GOES-3 [a520a517-f8da-4bf7-9dec-5e8758dad38a,310083]); 2017-09-01 16:36:21.0 [sritz] Insert Concept add narrower relation (GOES [6e332c25-caeb-4917-afb6-af757bcecd72,310071] - GOES-2 [f2b36444-124d-4f32-97c7-dc8a09b2d0f0,310079]); 2017-09-01 16:36:06.0 [sritz] Insert Concept add narrower relation (GOES [6e332c25-caeb-4917-afb6-af757bcecd72,310071] - GOES-1 [f86fcbce-178c-410a-8e6e-380c0bc392ad,310075]); 2017-09-01 16:35:23.0 [sritz] Move Concepts add narrower relation (GOES [6e332c25-caeb-4917-afb6-af757bcecd72,310071] - GOES-16 [72ebfb29-14dd-4306-a28c-ecfc25fc8ad6,287987]); 2017-09-01 16:33:01.0 [sritz] insert AltLabel (id: null category: primary text: Geostationary Operational Environmental Satellite language code: en); 2017-09-01 16:30:29.0 [sritz] Insert Concept add broader relation (GOES [6e332c25-caeb-4917-afb6-af757bcecd72,310071] - Solar/Space Observation Satellites [8e8b7689-0a8e-47a4-9c68-5f6a207104d5,288197]); FLOATS OCEAN PLATFORM/OCEAN STATIONS 2018-10-12 18:51:51.0 [sritz] Insert Concept add narrower relation (OCEAN PLATFORM/OCEAN STATIONS [6ee1cf85-aa14-4fe9-a915-a8022830d8a7,345157] - Sea Ice Mass Balance Station [31e96f2f-9b8e-454f-a1f8-e8d791c13a33,368171]); 2013-11-11 19:18:22.0 [aaleman] Insert Concept add narrower relation (OCEAN PLATFORM/OCEAN STATIONS [6ee1cf85-aa14-4fe9-a915-a8022830d8a7,73557] - SN-2 [d227bc01-e09a-4356-89d3-84cae164eeec,105917]); 2013-02-21 21:58:53.0 [aaleman] Insert Concept add narrower relation (OCEAN PLATFORM/OCEAN STATIONS [6ee1cf85-aa14-4fe9-a915-a8022830d8a7,73557] - SN-4 [85e347f2-d65d-4941-a252-0b0c55653b37,82691]); 2013-02-21 21:30:01.0 [aaleman] Insert Concept add narrower relation (OCEAN PLATFORM/OCEAN STATIONS [6ee1cf85-aa14-4fe9-a915-a8022830d8a7,73557] - NEMO-SN1 [83212677-16fc-42ab-9a23-cdbbacfa1d18,82687]); SENTINEL-2A The Sentinel-2 mission is a land monitoring constellation of two satellites that provide high resolution optical imagery and provide continuity for the current SPOT and Landsat missions. The mission provides a global coverage of the Earth's land surface every 10 days with one satellite and 5 days with 2 satellites, making the data of great use in on-going studies. The satellites are equipped with the state-of-the-art MSI (Multispectral Imager) instrument, that offers high-resolution optical imagery. 2020-02-12 16:40:58.0 [sritz] Move Concepts delete broader relation (null); add broader relation (SENTINEL-2A [6f1c359b-b1a6-47c1-979e-0689e637fbdc,559807] - SENTINEL-2 [2ce20983-98b2-40b9-bb0e-a08074fb93b3,541455]); 2020-02-12 16:40:48.0 [sritz] Move Concepts delete narrower relation (null); 2020-02-12 16:40:30.0 [sritz] Rename Concept update PrefLabel (SENTINEL-2A); 2020-02-12 16:39:34.0 [sritz] Move Concepts delete narrower relation (null); 2020-02-12 16:38:22.0 [sritz] Move Concepts delete narrower relation (null); 2020-02-12 16:38:22.0 [sritz] Move Concepts add narrower relation (SENTINEL-2 [6f1c359b-b1a6-47c1-979e-0689e637fbdc,559807] - SENTINEL-2A [2ce20983-98b2-40b9-bb0e-a08074fb93b3,541455]); 2020-01-30 16:00:22.0 [tstevens] Move Concepts add narrower relation (SENTINEL-2 [6f1c359b-b1a6-47c1-979e-0689e637fbdc,559807] - SENTINEL-2B [f2445400-1981-4ef3-bf7c-f4aa35923ae9,559803]); 2020-01-30 16:00:02.0 [tstevens] Move Concepts add narrower relation (SENTINEL-2 [6f1c359b-b1a6-47c1-979e-0689e637fbdc,559807] - SENTINEL-2A [2ce20983-98b2-40b9-bb0e-a08074fb93b3,541455]); 2020-01-29 12:37:53.0 [tstevens] insert Definition (id: null text: The Sentinel-2 mission is a land monitoring constellation of two satellites that provide high resolution optical imagery and provide continuity for the current SPOT and Landsat missions. The mission provides a global coverage of the Earth's land surface every 10 days with one satellite and 5 days with 2 satellites, making the data of great use in on-going studies. The satellites are equipped with the state-of-the-art MSI (Multispectral Imager) instrument, that offers high-resolution optical imagery. language code: en); 2020-01-29 12:36:30.0 [tstevens] Insert Concept add broader relation (SENTINEL-2 [6f1c359b-b1a6-47c1-979e-0689e637fbdc,559807] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,541501]); Proba-V The Proba-V satellite may only be slightly larger than a washing machine, but it is tasked with a full-scale mission. This miniature satellite is designed to map land cover and vegetation growth across the entire globe every two days. Over the last decade 'Proba' has become synonymous with small high-performance satellites, designed around innovation. The two previous satellites in the series were demonstration missions to give promising technologies an early chance to fly in space. They were overseen by ESA’s Directorate of Technical and Quality Management. Although designed as a demonstration mission, the success of the first Proba satellite led to it being operated as an Earth observation Third Party Mission. Proba-1 carries a high-resolution imaging spectrometer. Proba-V, however is different from the outset: this new mission will start serving as an operational Earth observation mission as soon as its six-month commissioning phase is complete, supplying data to an existing – and eagerly waiting – user community. The 'V' stands for Vegetation – a lighter but fully functional redesign of the ‘Vegetation’ imaging instrument previously flown on France’s full-sized Spot-4 and Spot-5 satellites. Launched on 7 May 2013, Proba-V has been designed to continue the supply of this much needed imagery for applications such as climate impact assessments, water resource management, agricultural monitoring and food security estimates. 2019-02-22 17:06:35.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: 88094b8c-c68c-4e4f-a4d9-1d5b6e15ba5b relationship type: null relationship value: null generated by: null); 2017-05-05 13:40:39.0 [mmorahan] insert Definition (id: null text: The Proba-V satellite may only be slightly larger than a washing machine, but it is tasked with a full-scale mission. This miniature satellite is designed to map land cover and vegetation growth across the entire globe every two days. Over the last decade 'Proba' has become synonymous with small high-performance satellites, designed around innovation. The two previous satellites in the series were demonstration missions to give promising technologies an early chance to fly in space. They were overseen by ESA’s Directorate of Technical and Quality Management. Although designed as a demonstration mission, the success of the first Proba satellite led to it being operated as an Earth observation Third Party Mission. Proba-1 carries a high-resolution imaging spectrometer. Proba-V, however is different from the outset: this new mission will start serving as an operational Earth observation mission as soon as its six-month commissioning phase is complete, supplying data to an existing – and eagerly waiting – user community. The 'V' stands for Vegetation – a lighter but fully functional redesign of the ‘Vegetation’ imaging instrument previously flown on France’s full-sized Spot-4 and Spot-5 satellites. Launched on 7 May 2013, Proba-V has been designed to continue the supply of this much needed imagery for applications such as climate impact assessments, water resource management, agricultural monitoring and food security estimates. language code: en); 2017-05-05 13:35:50.0 [mmorahan] Insert Concept add broader relation (Proba-V [6f507389-2c7c-41b4-a638-95bdc73b63a3,309567] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,287601]); METEOSAT-6 The Meteosat Operational Programme (MOP-3) satellite, launched on November 20, 1993, was the third operational geostationary Meteosat satellite following 3 pre-operational Meteosat satellites (Meteosat-1,-2,-3/P2). The primary goal of the MOP satellites were (1) to provide visible and IR day/night cloudcover data and radiances and (2) disseminate image data to users through the Data Collection Platform (DCP). MOP-3 (or Meteosat 6) is a 2.1 m diameter, 3.195 m high stepped cylindrical body with solar cells on six main body panels. The spacecraft is spin-stabilized at 100 rpm around the main axis aligned almost parallel to the Earth's axis with spin regulated by two small hydrazine thrusters. Spin access control and east-west stationkeeping is provided by two pairs of large thrusters. Attitude information is provided by Earth horizon and Sun-lit sensors. A radiating diplole antenna directs S-band (333 kbs) transmission of DCP image data to the Data Acquisition, Telemetry, and Tracking Station at Odenwald, Germany for relay to the Meteosat Ground Computer System and Meteosat Operations Control center at ESA's European Space Operations Center (ESOC). The MOP-3 carries a single imaging radiometer in visible/infrared wavelengths in addition to the Data Collection Platform. To view a 3D orbit, observe the J Track satellite tracking web page: http://liftoff.msfc.nasa.gov/RealTime/JTrack/ For more information on the European Space Agency (ESA) and the Meteosat Program, see the URL: http://www.esrin.esa.it Group: Platform_Details Entry_ID: METEOSAT-6 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: METEOSAT Short_Name: METEOSAT-6 Long_Name: Meteosat Operational Programme 3 (MOP-3) End_Group End_Group WRF The Weather Research and Forecasting (WRF) Model is a next-generation mesoscale numerical weather prediction system designed for both atmospheric research and operational forecasting applications. It features two dynamical cores, a data assimilation system, and a software architecture supporting parallel computation and system extensibility. The model serves a wide range of meteorological applications across scales from tens of meters to thousands of kilometers. 2018-11-28 17:51:30.0 [tstevens] insert Definition (id: null text: The Weather Research and Forecasting (WRF) Model is a next-generation mesoscale numerical weather prediction system designed for both atmospheric research and operational forecasting applications. It features two dynamical cores, a data assimilation system, and a software architecture supporting parallel computation and system extensibility. The model serves a wide range of meteorological applications across scales from tens of meters to thousands of kilometers. language code: en); 2018-11-28 17:48:54.0 [tstevens] insert AltLabel (id: null category: primary text: Weather Research and Forecasting (WRF) Model language code: en); 2018-11-28 17:47:55.0 [tstevens] Insert Concept add broader relation (WRF [6fb2817f-c3e3-4332-85ad-79f74227e6bc,368277] - Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,344529]); PlanetScope The PlanetScope satellite constellation consists of multiple launches of groups of individual satellites (DOVEs). Therefore, on-orbit capacity is constantly improving in capability or quantity, with technology improvements deployed at a rapid pace. Each DOVE satellite is a CubeSat 3U form factor (10 cm by 10 cm by 30 cm). The complete PlanetScope constellation of approximately 150 active satellites is able to image the entire land surface of the Earth every day (equating to a daily collection capacity of 350 million km²/day). The constellation is constantly "on" and does not require ordering or acquisition planning. 2019-05-06 11:33:25.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: ccae4c79-b985-4be6-b146-5c1a1a395e03 relationship type: null relationship value: null generated by: null); 2019-05-02 16:06:31.0 [mmorahan] insert Definition (id: null text: The PlanetScope satellite constellation consists of multiple launches of groups of individual satellites (DOVEs). Therefore, on-orbit capacity is constantly improving in capability or quantity, with technology improvements deployed at a rapid pace. Each DOVE satellite is a CubeSat 3U form factor (10 cm by 10 cm by 30 cm). The complete PlanetScope constellation of approximately 150 active satellites is able to image the entire land surface of the Earth every day (equating to a daily collection capacity of 350 million km²/day). The constellation is constantly "on" and does not require ordering or acquisition planning. language code: en); 2019-05-02 16:04:56.0 [mmorahan] Insert Concept add broader relation (PlanetScope [6fffd5bf-1d22-487a-8b4c-495992ef3b28,368749] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761]); NASA WB-57F The NASA Johnson Space Center (JSC) in Houston, Texas is the home of the NASA WB-57 High Altitude Research Program. Two fully operational WB-57 aircraft are based near JSC at Ellington Field. Both aircraft have been flying research missions since the early 1960's, and continue to be an asset to the scientific community with professional, reliable, customer-oriented service designed to meet all scientific objectives. [Text and Photo provided by: https://jsc-aircraft-ops.jsc.nasa.gov/wb-57.html ] Group: Platform_Details Entry_ID: NASA WB-57F Group: Platform_Identification Platform_Category: Aircraft Short_Name: NASA WB-57F End_Group Group: Platform_Associated_Instruments Short_Name: ACATS Short_Name: HIRAD End_Group Creation_Date: 2008-07-14 Online_Resource: https://jsc-aircraft-ops.jsc.nasa.gov/wb-57.html End_Group 2019-06-26 20:11:52.0 [sritz] update Definition (The NASA Johnson Space Center (JSC) in Houston, Texas is the home of the NASA WB-57 High Altitude Research Program. Two fully operational WB-57 aircraft are based near JSC at Ellington Field. Both aircraft have been flying research missions since the early 1960's, and continue to be an asset to the scientific community with professional, reliable, customer-oriented service designed to meet all scientific objectives. [Text and Photo provided by: https://jsc-aircraft-ops.jsc.nasa.gov/wb-57.html ] Group: Platform_Details Entry_ID: NASA WB-57F Group: Platform_Identification Platform_Category: Aircraft Short_Name: NASA WB-57F End_Group Group: Platform_Associated_Instruments Short_Name: ACATS Short_Name: HIRAD End_Group Creation_Date: 2008-07-14 Online_Resource: https://jsc-aircraft-ops.jsc.nasa.gov/wb-57.html End_Group); delete Resource (null); RADARSAT SPACELAB-3 The Spacelab 3 mission was the second flight of Spacelab, the reusable and versatile space laboratory developed for NASA by the European Space Agency (ESA); it was also the first NASA-dedicated Spacelab mission. The SL-3 crew consisted of Commander Robert F. Overmyer, Pilot Frederick D. Gregory, Mission Specialists Don L. Lind, Norman E. Thagard, and William E. Thornton, and Payload Specialists Lodewijk van den Berg and Taylor G. Wang. Rather than carrying experiments covering a broad range of disciplines as did Spacelab 1, the SL-3 payload investigations focused mainly on microgravity and included experiments in life sciences, materials science, fluid mechanics, and atmospheric and astronomical observations. Additional information available at "http://lsda.jsc.nasa.gov/scripts/cf/miss.cfm?mis_index=11" [Summary provided by NASA] ICESat ICESAT-1 [Source: NASA ICESat home page] ICESat (Ice, Cloud,and land Elevation Satellite) is the benchmark Earth Observing System mission for measuring ice sheet mass balance, cloud and aerosol heights, as well as land topography and vegetation characteristics. From 2003 to 2009, the ICESat mission provided multi-year elevation data needed to determine ice sheet mass balance as well as cloud property information, especially for stratospheric clouds common over polar areas. It also provided topography and vegetation data around the globe, in addition to the polar-specific coverage over the Greenland and Antarctic ice sheets. Group: Platform_Details Entry_ID: ICESAT Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: ICESAT Long_Name: Ice, Cloud and Land Elevation Satellite End_Group Group: Synonymous_Platform_Names Short_Name: ICESAT End_Group Group: Platform_Associated_Instruments Short_Name: GLAS End_Group Group: Orbit Orbit_Altitude: ~600 km Orbit_Inclination: 94 degrees Period: ~97 minutes Repeat_Cycle: 91 days with ~33 days subcycle Perigee: 593 km (368 mi) Apogee: 610 km (379 mi) Orbit_Type: LEO > Low Earth Orbit > Polar Non-Sun-Synchronous End_Group Creation_Date: 2007-04-16 Online_Resource: https://icesat.gsfc.nasa.gov/ Online_Resource: http://www.csr.utexas.edu/glas/atbd.html Group: Platform_Logistics Launch_Date: 2003-01-12 Launch_Site: Vandenberg Air Force Base, USA Design_Life: 3 years Primary_Sponsor: USA/NASA End_Group End_Group 2018-04-24 20:39:09.0 [sritz] update Definition ([Source: NASA ICESat home page] ICESat (Ice, Cloud,and land Elevation Satellite) is the benchmark Earth Observing System mission for measuring ice sheet mass balance, cloud and aerosol heights, as well as land topography and vegetation characteristics. From 2003 to 2009, the ICESat mission provided multi-year elevation data needed to determine ice sheet mass balance as well as cloud property information, especially for stratospheric clouds common over polar areas. It also provided topography and vegetation data around the globe, in addition to the polar-specific coverage over the Greenland and Antarctic ice sheets. Group: Platform_Details Entry_ID: ICESAT Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: ICESAT Long_Name: Ice, Cloud and Land Elevation Satellite End_Group Group: Synonymous_Platform_Names Short_Name: ICESAT End_Group Group: Platform_Associated_Instruments Short_Name: GLAS End_Group Group: Orbit Orbit_Altitude: ~600 km Orbit_Inclination: 94 degrees Period: ~97 minutes Repeat_Cycle: 91 days with ~33 days subcycle Perigee: 593 km (368 mi) Apogee: 610 km (379 mi) Orbit_Type: LEO > Low Earth Orbit > Polar Non-Sun-Synchronous End_Group Creation_Date: 2007-04-16 Online_Resource: https://icesat.gsfc.nasa.gov/ Online_Resource: http://www.csr.utexas.edu/glas/atbd.html Group: Platform_Logistics Launch_Date: 2003-01-12 Launch_Site: Vandenberg Air Force Base, USA Design_Life: 3 years Primary_Sponsor: USA/NASA End_Group End_Group); delete Resource (null); 2018-04-24 20:34:29.0 [sritz] update PrefLabel (ICESat); update Resource (image); 2016-06-09 18:43:38.0 [epneff] added altLabel insert AltLabel (id: null text: ICESAT-1 language code: en); CARTOSAT-2 IRS-P7 Cartosat-2 Series Satellite is the primary satellite carried by PSLV-C40. This remote sensing satellite is similar in configuration to earlier satellites in the series and is intended to augment data services to the users. The imagery sent by satellite will be useful for cartographic applications, urban and rural applications, coastal land use and regulation, utility management like road network monitoring, water distribution, creation of land use maps, change detection to bring out geographical and manmade features and various other Land Information System (LIS) as well as Geographical Information System (GIS) applications. PSLV-C40/Cartosat-2 Series Satellite Mission was launched on Jan 12, 2018 at 09:29 Hrs (IST) from SDSC SHAR, Sriharikota. 2019-02-20 19:07:08.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: 3a3c2498-8e0e-4138-b5a2-7c2a80e1b598 relationship type: null relationship value: null generated by: null); 2018-06-14 09:28:21.0 [mmorahan] insert AltLabel (id: null category: null text: IRS-P7 language code: en); 2018-06-13 19:07:44.0 [mmorahan] delete AltLabel (null); 2018-06-13 15:47:59.0 [mmorahan] insert AltLabel (id: null category: null text: IRS-P7 language code: en); insert Definition (id: null text: Cartosat-2 Series Satellite is the primary satellite carried by PSLV-C40. This remote sensing satellite is similar in configuration to earlier satellites in the series and is intended to augment data services to the users. The imagery sent by satellite will be useful for cartographic applications, urban and rural applications, coastal land use and regulation, utility management like road network monitoring, water distribution, creation of land use maps, change detection to bring out geographical and manmade features and various other Land Information System (LIS) as well as Geographical Information System (GIS) applications. PSLV-C40/Cartosat-2 Series Satellite Mission was launched on Jan 12, 2018 at 09:29 Hrs (IST) from SDSC SHAR, Sriharikota. language code: en); 2018-06-13 15:45:50.0 [mmorahan] Insert Concept add broader relation (CARTOSAT-2 [71ccf8e3-7b1f-418d-9bc0-0ead78ec75ee,367711] - CARTOSAT [b65c6b10-a648-4a7c-9af1-71506ed9bb13,345679]); ULYSSES The primary objectives of Ulysses, formerly the International Solar Polar Mission (ISPM), are to investigate, as a function of solar latitude, the properties of the solar wind and the interplanetary magnetic field, of galactic cosmic rays and neutral interstellar gas, and to study energetic particle composition and acceleration. The 55 kg payload includes two magnetometers, two solar wind plasma instruments, a unified radio/plasma wave instrument, three energetic charged particle instruments, an interstellar neutral gas sensor, a solar X-ray/cosmic gamma-ray burst detector, and a cosmic dust sensor. The communications systems is also used to study the solar corona and to search for gravitational waves. Secondary objectives included interplanetary and planetary physics investigations during the initial Earth-Jupiter phase and investigations in the Jovian magnetosphere. The spacecraft used a Jupiter swingby in Feb. 1992 to transfer to a heliospheric orbit with high heliocentric inclination, and will pass over the rotational south pole of the sun in mid-1994 at 2 AU, and over the north pole in mid-1995. A second solar orbit will take Ulysses again over the south and north poles in years 2000 and 2001, respectively. The spacecraft is powered by a single radio-isotope generator. It is spin stabilized at a rate of 5 rpm and its high-gain antenna points continuously to the earth. Group: Platform_Details Entry_ID: ULYSSES Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Short_Name: ULYSSES End_Group Group: Synonymous_Platform_Names Short_Name: International Solar Polar Mission Short_Name: Solar Polar Short_Name: 20842 Short_Name: 1990-090B End_Group Group: Platform_Associated_Instruments Short_Name: EPAC Short_Name: FGM-U Short_Name: DUST Short_Name: URAP Short_Name: SWOOPS Short_Name: SWICS-U Short_Name: HI-SCALE Short_Name: COSPIN Short_Name: GRB End_Group Group: Orbit Period: 2264 days Perigee: 1.35 AU Apogee: 5.4 AU End_Group Creation_Date: 2007-03-05 Online_Resource: http://ulysses.jpl.nasa.gov/index.html Online_Resource: http://helio2.estec.esa.nl/ulysses_/ Sample_Image: http://nssdc.gsfc.nasa.gov/image/spacecraft/ulysses_test.jpg Group: Platform_Logistics Launch_Date: 1990-10-06 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: ESA Primary_Sponsor: NASA End_Group End_Group GOES-16 The Geostationary Operational Environmental Satellite-R Series (GOES-R) is the nation’s next generation of geostationary weather satellites. The GOES-R series will significantly improve the detection and observation of environmental phenomena that directly affect public safety, protection of property and our nation’s economic health and prosperity. 2017-09-01 17:01:10.0 [sritz] insert Definition (id: null text: The Geostationary Operational Environmental Satellite-R Series (GOES-R) is the nation’s next generation of geostationary weather satellites. The GOES-R series will significantly improve the detection and observation of environmental phenomena that directly affect public safety, protection of property and our nation’s economic health and prosperity. language code: en); 2017-09-01 16:35:23.0 [sritz] Move Concepts delete broader relation (null); add broader relation (GOES-16 [72ebfb29-14dd-4306-a28c-ecfc25fc8ad6,287987] - GOES [6e332c25-caeb-4917-afb6-af757bcecd72,310071]); 2017-04-14 16:36:48.0 [sritz] Insert Concept add broader relation (GOES-16 [72ebfb29-14dd-4306-a28c-ecfc25fc8ad6,278801] - Solar/Space Observation Satellites [8e8b7689-0a8e-47a4-9c68-5f6a207104d5,257137]); FEDSAT FedSat is an Australian scientific microsatellite mission, a 58cm cube weighing approximately 50 kg. It was launched in early 2002 from Japan by Japan's National Space Development Agency. The purpose of FedSat is to: Establish Australian capability in microsatellite technologies Develop expertise necessary for sustaining those industries and profiting from them Test and develop Australian-developed intellectual property Provide a research platform for Australian space science, communication and GPS studies. FedSat was developed by the Cooperative Research Centre for Satellite Systems, which combines the resources and skills of 12 Australian organizations. Contributions from each of the partner organizations are doubled by the Commonwealth Government, under its Commonwealth Government's Cooperative Research Center?s Program. The total budget of the Centre is approximately &#3660 million over 7 years, with &#3620 million of that allocated for the FedSat mission. Much of FedSat was developed in Australia by the CRCSS. Three of the six main payloads have been fully developed by the CRCSS, and the other three have been supplied by overseas organizations in consultation with the CRCSS. The satellite platform, the structure that houses and maintains the payloads, is being provided by overseas organizations. CRCSS engineers could have developed an Australian platform, but given the time available from project-start to launch, that was not practical. CRCSS opted to contract an overseas platform supplier, avoiding the need to reinvent established technologies. Payloads: 1. GPS Receiver: The GPS, Global Positioning System, is an American network of satellites that transmit radio signals containing time and orbit-position codes. GPS receivers decode the signals, and by comparing signals of up to 4 satellites with known positions, they can derive their own locations by triangulation. The system was designed for mainly military use, but now GPS provides many scientific and civilian applications. 2. NewMag: The NewMag magnetometer is a very sensitive and rapid-sampling device for measuring the strength of the Earth's magnetic field. Earth is like a big bar magnet, with magnetic field lines emerging from the poles and far out into space. FedSat's polar orbit crosses all these lines, so NewMag can effectively gain a window into the whole magnetosphere region. NewMag can also measure vibrations simultaneously with ground- based magnetometers, so investigating the dynamics of the magnetosphere (changes in it shape due to variations in the Sun), and study magnetospheric wave-propagation. 3. High performance computing: The FedSat high performance computing payload is the world's first use of reconfigurable computing technology in space. Reconfigurable computers permit change of their physical circuits via software control; new physical circuits can be installed into a reconfigurable computer module by remote command. For spacecraft, this technology means that satellites can be rewired without having to retrieve them. 4. Ka-band transponder: The FedSat Ka-band transponder is designed to handle the new experimental high- frequency and high-capacity Ka part of the radio spectrum. The transponder processes signals to and from the ground in the frequency band. The transponder incorporates CRCSS-designed Gallium Arsenide monolithic microwave circuits; FedSat will space qualify these for the first time. 5. Baseband processor The baseband processor provides on-board computer processing of the Ka- and UHF- band payloads. It has been designed and built by the CRCSS, to operate as a low power single modem with flexible operation. It will also provide the channel for satellite operations commands. 6. UHF communications payload: The Ultra High Frequency band payload will introduce a new type of packet data service for Low Earth Orbiting satellites to obtain environmental data. For example, ocean buoys may transmit their data using this means to orbiting satellites, which are retransmitted back to the lab for analysis. 7. CD ROM: FedSat also carries a compact disc mounted on the side, containing the audio messages members of the Australian public recorded to go into space from March to August 2000. The disc also contains a copy of the song From Little Things, Big Things Grow, by Paul Kelly, with kind permission of the writers (Kev Carmody/Paul Kelly) and publishers (Larrikin Music, Mushroon Records). Additional information available at "http://www.crcss.csiro.au/overview.htm" and "http://www.crcss.csiro.au/launch/launch.html" [Summary provided by CSIRO] GEOS-3 The mission of GEOS 3 (Geodynamics Experimental Ocean Satellite) was to provide the stepping stone between the National Geodetic Satellite Program (NGSP) and the Earth and Ocean Physics Application Program. It provided data to refine the geodetic and geophysical results of the NGSP and served as a test for new systems. A major achievment was the flight of a radar altimeter. Further mission objectives: intercomparison of tracking systems, investigation of solid-earth dynamic phenomena through precision laser tracking, refinement of orbit determination techniques, determination of interdatum ties and gravity models, and support of the calibration and position determination of NASA Spaceflight Tracking and Data Network (STDN) S-band tracking stations. For more details, see special reports on the GEOS 3 in J. Geophys. Res., v. 84, n. B8, 1979. __________ Taken from the NSSDC System for Information Retrieval and Storage (SIRS). For more information contact the NSSDC Coordinated Request and User Support Office, 301-286-6695 (NASA Goddard Space Flight Center, Code 933.4, Greenbelt, Maryland 20771, USA) Group: Platform_Details Entry_ID: GEOS-3 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: GEOS (Geodetic Earth Orbiting Satellite) Short_Name: GEOS-3 Long_Name: Geodetic Earth Orbiting Satellite-3 End_Group Group: Synonymous_Platform_Names Short_Name: GEOS-3 End_Group Group: Platform_Associated_Instruments Short_Name: DOPPLER BEACONS Short_Name: ALTIMETERS End_Group Group: Orbit Orbit_Inclination: 115 deg Period: 102 min Perigee: 824 km End_Group Creation_Date: 2007-09-26 Online_Resource: http://ilrs.gsfc.nasa.gov/satellite_missions/list_of_satellites/geos_general.html Sample_Image: http://ilrs.gsfc.nasa.gov/images/geos3.gif Group: Platform_Logistics Launch_Date: 1975-04-09 Primary_Sponsor: NASA End_Group End_Group OSO-5 The objectives of the OSO satellite series were to perform solar physics experiments above the atmosphere during a complete solar cycle and to map the celestial sphere for direction and intensity of UV light, X-rays, and gamma radiation. General Information: Designation: 03663 / 69006A Launch date: 22 Jan 1969 Country of origin: United States Mission: Scientific (Sun observation) Perigee/Apogee: 538/559 km Inclination: 33° Period: 95.6 min Launch vehicle: Thor Delta #64 Out of service: Jul 1975 Decay: 2 Apr 1984 Additional information available at "http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/oso5.html" Group: Platform_Details Entry_ID: OSO-5 Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Platform_Series_or_Entity: OSO (Orbiting Solar Observatory) Short_Name: OSO-5 Long_Name: Orbiting Solar Observatory-5 End_Group Group: Synonymous_Platform_Names Short_Name: OSO-5 End_Group Group: Platform_Associated_Instruments Short_Name: GAMMA RADIATION DETECTOR End_Group Group: Orbit Orbit_Inclination: 33 degrees Period: 95.6 min Perigee: 538 km Apogee: 559 km End_Group Creation_Date: 2007-12-14 Online_Resource: http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/oso5.html Sample_Image: http://heasarc.gsfc.nasa.gov/Images/oso/oso5_wheel.gif Group: Platform_Logistics Launch_Date: 1969-01-22 Primary_Sponsor: NASA End_Group End_Group Data Analysis 2015-06-04 14:31:33.0 [aaleman] Insert Concept add narrower relation (Data Analysis [73c1df3f-b389-4cc0-98eb-0fbc4f071f98,157993] - Environmental Modeling [079610fb-e4cf-4e2c-9a92-86a9b798a7d5,157997]); 2015-06-04 14:31:08.0 [aaleman] added new keyword update PrefLabel (Data Analysis); 2015-06-04 14:30:43.0 [aaleman] Insert Concept add broader relation (DATA ANALYSIS [73c1df3f-b389-4cc0-98eb-0fbc4f071f98,157993] - Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215]); LSM 2014-05-21 18:10:54.0 [128.183.164.42] insert AltLabel (id: null text: Land Surface Model language code: en); 2014-05-21 18:10:25.0 [128.183.164.42] Insert Concept add broader relation (LSM [73cef3bc-0a2c-4c10-9e5b-d0c64bca038f,106403] - Models [113ecbc2-ab36-4d58-a96c-a6ce0106e749,73395]); HYDROLOGICAL STATIONS SID Sudden Ionospheric Disturbance Stations (SID) consists of solar observers who monitor very low frequency (VLF) radio stations for sudden enhancements of their signals. Earth's ionosphere reacts to the intense x-ray and ultraviolet radiation released during a solar flare. The ionospheric disturbance enhances VLF radio propagation. By monitoring the signal strength of a distant VLF transmitter, sudden ionospheric disturbances (SIDs) are recorded and indicate a recent solar flare event. All SID monitoring stations are homebuilt by the observers. Instructions for constructing the VLF receiver and antenna can be obtained from the AAVSO Solar Division chairman. The receiver design has progressed remarkably as the SID program participants have been inspired to improve signal sensitivity and noise rejection. Recent SID station receivers follow a design developed by SID Technical Coordinator Art Stokes. The Stokes Gyrator receiver can be built and tuned by anyone with simple soldering skills. A small indoor loop antenna captures the radio wave for amplification and rectification by the receiver. The SID station operates unattended until the end of each month. Recordings are then analyzed for the beginning, end, and duration of SID events. More info available at http://www.aavso.org/committees/solar/sid.stm [Source: AAVSO] Group: Platform_Details Entry_ID: SID Group: Platform_Identification Platform_Category: In Situ Land-based Platforms Platform_Series_or_Entity: SOLAR/SPACE MONITORING STATIONS Short_Name: SID Long_Name: Sudden Ionospheric Disturbance Stations End_Group Group: Synonymous_Platform_Names Short_Name: SID End_Group Creation_Date: 2007-12-10 Online_Resource: http://www.aavso.org/committees/solar/sid.stm End_Group SPAS-II The SPAS (Shuttle Pallet Satellite) satellite was a reusable free-flying vehicle built by Messerschmitt-Bolkow-Blohm.which could be deployed and then retrieved by the US Space Shuttle's Remote Manipulator System arm. The original SPAS, with materials processing and SDI-related sensor payloads, was used on several missions (STS-7, STS-11, STS-39). An experiment-carrying truss (USS) based on the original SPAS structure (but without the avionics and attitude control) was flown on the Spacelab D-1 and D-2 missions. The shuttle was launched on April 28, 1991 and landed May 6, 1991. Unclassified payload included the Infrared Background Signature Survey (IBSS) with Critical Ionization Velocity (CIV), Chemical Release Observation (CRO) and Shuttle Pallet Satellite-II (SPAS-II) experiments; and Space Test Payload-1 (STP-1). Classified payload consisted of Multi-Purpose Release Canister (MPEC). Also on board was Radiation Monitoring Equipment III (RME III) and Cloud Logic to Optimize Use of Defense Systems-1A (CLOUDS-1). [Summary provided by NASA] Group: Platform_Details Entry_ID: SPAS-II Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Platform_Series_or_Entity: SPACE SHUTTLE Short_Name: SPAS-II Long_Name: Shuttle Pallet Satellite-II End_Group Group: Synonymous_Platform_Names Short_Name: ORFEUS II End_Group Creation_Date: 2008-01-25 Online_Resource: http://www-pao.ksc.nasa.gov/kscpao/chron/sts-39.htm Group: Platform_Logistics Launch_Date: 1991-04-28 Primary_Sponsor: NASA End_Group End_Group NOAA-15 NOAA 15, also known as NOAA-K before launch, was an operational, polar orbiting, meteorological satellite operated by the National Oceanic and Atmospheric Administration (NOAA). It was the latest in the Advanced TIROS-N (ATN) series and the design was based on the Defense Meteorological Satellite Program (DMSP). Launched by the Titan II rocket from Vandenberg AFB, NOAA-K replaced the decommissioned NOAA 12 in an afternoon equator-crossing orbit. It provided support to environmental monitoring by complementing the NOAA/NESS geostationary meteorological satellite program (GOES). Instruments were flown for imaging and measurement of the Earth's atmosphere, its surface, and cloud cover, including Earth radiation, atmospheric ozone, aerosol distribution, sea surface temperature, vertical temperature and water profiles in the troposphere and stratosphere; measurement of proton and electron flux at orbit altitude, and remote platform data collection, and for SARSAT. They included (1) an improved six-channel Advanced Very High Resolution Radiometer/3 (AVHRR/3); (2) an improved High Resolution Infrared Radiation Sounder (HIRS/3); (3) the Search and Rescue Satellite Aided Tracking System (S&R), which consists of the Search and Rescure Repeater (SARR) and the Search and Rescue Processor (SARP-2); (4) the French/CNES-provided improved ARGOS Data Collection System (DCS-2); and (5) the Advanced Microwave Sounding Units (AMSUs), which replaced the previous MSU and SSU instruments to become the first in the NOAA series to support dedicated microwave measurements of temperature, moisture, surface and hydrological studies in cloudy regions where visible and infrared instruments have decreased capability. Additional Information: http://www2.ncdc.noaa.gov/docs/intro.htm To view a 3D orbit, observe the J track satellite tracking web page: http://liftoff.msfc.nasa.gov/RealTime/JTrack/ NOAA-K CHARACTERISTICS Main Body: 4.2m long, 1.88m diameter Solar Array: 2.73 by 6.14 m Weight: At liftoff 2231.7 kg (includes 756.7 kg of expendable fuel) Lifetime: Greater than 2 years Load Power Requirements: 833 Watts for 0 degree sun angle 750 Watts for 80 degree sun angle Orbital Characteristics- Orbital Period: 101.20 m Inclination: 98.70 degrees Periapsis: 808.00 km Apoapsis: 824.00 km Information was adopted from NSSDC Master Catalog and the J Track Liftoff web pages. Group: Platform_Details Entry_ID: NOAA-15 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NOAA POES (Polar Orbiting Environmental Satellites) Short_Name: NOAA-15 Long_Name: National Oceanic & Atmospheric Administration-15 End_Group Group: Platform_Associated_Instruments Short_Name: AMSU-B Short_Name: AMSU-A End_Group Group: Orbit Orbit_Altitude: 807 km Orbit_Inclination: 98.5 deg Period: 101.1 End_Group Creation_Date: 2007-11-07 Online_Resource: http://www.oso.noaa.gov/poesstatus/spacecraftStatusSummary.asp?spacecraft=15 Group: Platform_Logistics Launch_Date: 1998-05-13 Primary_Sponsor: NASA End_Group End_Group Jason In advance of DEEP SEARCH 2019’s first remotely operated vehicle (ROV) dive today, Woods Hole Oceanographic Institution (WHOI) has shared the following overview about ROV Jason. Check back soon for our impressions of the first dive of the cruise. We’ll be diving at Richardson Hills and are expecting to see some spectacular coral habitats! Jason is an ROV system designed and built by WHOI’s National Deep Submergence Laboratory and funded by the National Science Foundation. Its design gives scientists access to most of the globe’s seafloor, often for days at a time, without leaving the deck of a ship. The vehicle can operate as either a two-body (with ROV Medea) or a single-body system, depending on mission requirements. A 10-kilometer (6-mile) reinforced fiber-optic cable delivers electrical power and control signals from the ship to the vehicle and returns data and live video imagery throughout a dive. When Medea is used, it acts as a “shock absorber” shielding Jason from the movement of the ship and cable. For the DEEP SEARCH mission, Jason will be operated in single-body mode with a series of floats attached to the cable to dampen the influence of the surface swell. Jason is equipped with sonars, video and still imaging systems, lighting, and a flexible payload of sensors and sampling systems. The vehicle’s manipulator arms collect samples just by picking them up, or by deploying sampling gear provided by the science team, such as push cores and mussel pots. The samples are then placed in the vehicle’s basket or on “elevator” platforms that float samples to the surface, permitting Jason to stay submerged for as much as a week at a time. 2020-01-21 17:54:41.0 [tstevens] insert Definition (id: null text: In advance of DEEP SEARCH 2019’s first remotely operated vehicle (ROV) dive today, Woods Hole Oceanographic Institution (WHOI) has shared the following overview about ROV Jason. Check back soon for our impressions of the first dive of the cruise. We’ll be diving at Richardson Hills and are expecting to see some spectacular coral habitats! Jason is an ROV system designed and built by WHOI’s National Deep Submergence Laboratory and funded by the National Science Foundation. Its design gives scientists access to most of the globe’s seafloor, often for days at a time, without leaving the deck of a ship. The vehicle can operate as either a two-body (with ROV Medea) or a single-body system, depending on mission requirements. A 10-kilometer (6-mile) reinforced fiber-optic cable delivers electrical power and control signals from the ship to the vehicle and returns data and live video imagery throughout a dive. When Medea is used, it acts as a “shock absorber” shielding Jason from the movement of the ship and cable. For the DEEP SEARCH mission, Jason will be operated in single-body mode with a series of floats attached to the cable to dampen the influence of the surface swell. Jason is equipped with sonars, video and still imaging systems, lighting, and a flexible payload of sensors and sampling systems. The vehicle’s manipulator arms collect samples just by picking them up, or by deploying sampling gear provided by the science team, such as push cores and mussel pots. The samples are then placed in the vehicle’s basket or on “elevator” platforms that float samples to the surface, permitting Jason to stay submerged for as much as a week at a time. language code: en); 2020-01-21 17:24:23.0 [tstevens] Insert Concept add broader relation (Jason [74995db1-1047-4e0b-b0c9-b4b9f7bdd6b6,559719] - ROV [da6420b6-48ec-4ae2-98c7-0ef0538815a0,542741]); DE (Dynamics Explorer) BE (Beacon Explorer) RESURS-O1 There are two types of remote sensing instrument on board RESURS-O1. The MSU-E is comparable with instruments on other satellites, such as Landsat, while the MSU-SK offers perspectives of the Earth that have never been available before. It has a wide swath and medium resolution, and bridges the enormous gap in coverage and detail between SPOT/Landsat TM and NOAA AVHRR. It makes it an ideal complement to both of these data sets, better defining the regional context of a local study, or giving focus at regional scales to a continental survey. Technical Information: launch date: 4 November 1994 orbit: sun-synchronous, circular average altitude: 678 km inclination: 98.04 eccentricity: 0.0128 argument of perigee: 88.93 cycle: 21 days orbit period: 98 minutes satellite mass: 1950 kg scientific payload mass: 550 kg attitude control: orbital, triaxial, active data transfer rate: 7.68 Mbits/s down-link frequency: 8192 MHz design lifetime: 2 years launched from: Baikonur carrier Zenit [Summary provided by the Sputnik Server] Group: Platform_Details Entry_ID: RESURS-O1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: RESURS-O1 End_Group Group: Synonymous_Platform_Names Short_Name: RESURS-01 End_Group Group: Platform_Associated_Instruments Short_Name: MSU-SK End_Group Group: Orbit Orbit_Altitude: 678 Orbit_Inclination: 98.04 Period: 98 Repeat_Cycle: 21 Perigee: 88.93 Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-11-28 Online_Resource: http://sputnik.infospace.ru/resurs/engl/resurs.htm Group: Platform_Logistics Launch_Date: 1994-11-04 Design_Life: 2 YEARS Primary_Sponsor: Russia End_Group End_Group TIROS METEOSAT-7 The METOSAT-7 satellite is part of the METOSAT series of satellites whose goal is to provide weather oriented imaging of the Earth's globe at both visible and infra-red wavelenghts. General Characteristics: Launch date: September 2, 1997 Country of origin: Europe Launch vehicle Ariane V99 Specifications: Prime contractor: Aerospatiale Mass at launch: 690 kg Mass in orbit: 320 kg Dry mass: 281 kg Dimension: 4.23 m height x 2.10 m diameter Stabilization: spin stabilized (90/100 rpm) DC power: BOL: 240 W EOL: 225 W Design lifetime: 5 years More Information: http://www.esa.int/Our_Activities/Observing_the_Earth/Meteosat [Information provided by The Satellite Encyclopedia] Group: Platform_Details Entry_ID: METEOSAT-7 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: METEOSAT Short_Name: METEOSAT-7 End_Group Group: Platform_Associated_Instruments Short_Name: MVIRI Short_Name: A-DCS End_Group Group: Orbit Orbit_Altitude: 35786 km Orbit_Inclination: 8.78124 deg Orbit_Type: GEO > Geosynchronous > Geostationary End_Group Online_Resource: http://www.eumetsat.int/website/home/Satellites/CurrentSatellites/Meteosat/index.html Online_Resource: http://www.esa.int/Our_Activities/Observing_the_Earth/Meteosat Online_Resource: http://www.wmo-sat.info/oscar/satellites/view/535 Sample_Image: http://www.emgo.cz/obrazky/met7sat.jpg Group: Platform_Logistics Launch_Date: 1997-09-02 Launch_Site: KOUROU, FRENCH GUIANA Design_Life: 2006-12-05 Primary_Sponsor: EUMETSAT End_Group End_Group MMS The Magnetospheric Multiscale (MMS) mission is a Solar Terrestrial Probes mission comprising four identically instrumented spacecraft that will use Earth’s magnetosphere as a laboratory to study the microphysics of three fundamental plasma processes: magnetic reconnection, energetic particle acceleration, and turbulence. These processes occur in all astrophysical plasma systems but can be studied in situ only in our solar system and most efficiently only in Earth’s magnetosphere, where they control the dynamics of the geospace environment and play an important role in the processes known as “space weather.” 2015-03-11 18:52:49.0 [saritz] insert Definition (id: null text: The Magnetospheric Multiscale (MMS) mission is a Solar Terrestrial Probes mission comprising four identically instrumented spacecraft that will use Earth’s magnetosphere as a laboratory to study the microphysics of three fundamental plasma processes: magnetic reconnection, energetic particle acceleration, and turbulence. These processes occur in all astrophysical plasma systems but can be studied in situ only in our solar system and most efficiently only in Earth’s magnetosphere, where they control the dynamics of the geospace environment and play an important role in the processes known as “space weather.” language code: en); 2015-03-11 18:52:17.0 [saritz] insert AltLabel (id: null text: Magnetospheric Multiscale language code: en); 2015-03-11 18:50:11.0 [saritz] Insert Concept add broader relation (MMS [76673a7f-44c8-4dde-83c2-1104b060061f,106791] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,73425]); Swarm-C Primary objectives: * studies of core dynamics, geodynamo processes and core-mantle interaction * mapping of the lithospheric magnetisation and its geological interpretation * determination of the 3D electrical conductivity of the mantle * investigation of electric currents flowing in the magnetosphere and ionosphere * identifying the ocean circulation by its magnetic signature * quantifying the magnetic forcing of the upper atmosphere 2019-02-22 21:48:47.0 [mmorahan] insert Definition (id: null text: Primary objectives: * studies of core dynamics, geodynamo processes and core-mantle interaction * mapping of the lithospheric magnetisation and its geological interpretation * determination of the 3D electrical conductivity of the mantle * investigation of electric currents flowing in the magnetosphere and ionosphere * identifying the ocean circulation by its magnetic signature * quantifying the magnetic forcing of the upper atmosphere language code: en); 2019-02-22 21:44:33.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: b7bc737c-15de-4b67-9bc3-5fa7c2b651d5 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 5e95a04f-e746-4b55-b0f0-76631bb197fe relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: e5fde4c4-15cd-4278-b922-005488df096f relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 2380ecc6-b5ae-4ad8-a56a-9740166465aa relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 03d748ff-7398-4ea8-87e7-38d0ef3e6167 relationship type: null relationship value: null generated by: null); 2018-06-13 12:07:25.0 [mmorahan] Insert Concept add broader relation (Swarm-C [769a52d4-7db1-4b8e-8d39-6fee4e74d34f,367707] - Swarm [1d6d5f82-acd5-4bd2-9324-12884718b353,367695]); NOT APPLICABLE 2015-09-01 17:55:40.0 [tbs1979] Insert Concept add narrower relation (NOT APPLICABLE [76b8f939-8558-4a10-8139-c7f8a0162102,158343] - NOT APPLICABLE [cffdd7e9-e25d-4c85-86ae-ff651532f02e,158347]); 2015-09-01 17:47:55.0 [tbs1979] Insert Concept add broader relation (NOT APPLICABLE [76b8f939-8558-4a10-8139-c7f8a0162102,158343] - NOT APPLICABLE [41d72eb0-9554-48a7-8821-dec569503da3,158307]); AIR MONITORING STATIONS/NETWORKS ACRIMSAT The purpose of the Active Cavity Radiometer Irradiance Monitor III (ACRIM III) instrument is to study total solar Irradiance from the Sun. The ACRIM III package is flying on a spacecraft called ACRIMSAT. The spacecraft was launched on December 20, 1999 as a secondary payload on a Taurus launch vehicle. ACRIM III, third in a series of long-term solar-monitoring tools built for NASA by the Jet Propulsion Laboratory, will continue to extend the database first created by ACRIM I, which was launched in 1980 on the Solar Maximum Mission (SMM) spacecraft. ACRIM II followed on the Upper Atmosphere Research Satellite (UARS) in 1991. ACRIMSAT data will be correlated with possible global warming data, ice cap shrinkage data, and ozone layer depletion data. It is theorized that as much as 25 percent of the Earth's total global warming may be solar in origin due to small increases in the Sun's total energy output since the last century. By measuring incoming solar radiation and adding measurements of ocean and atmosphere currents and temperatures, as well as surface temperatures, climatologists will be able to improve their predictions of climate and global warming over the next century. Energy forecasting, carbon management, public health. Launch: Launched: December 20, 1999 Launch Vehicle: Taurus Launch Site: Western Test Range, Vandenberg Air Force Base Orbit: Altitude: 680 km Inclination: 98.13 degrees Sun-Synchronous Vital Statistics: Weight: 13 kg Power: 49 watts Design Life: 5 years Instruments: Active Cavity Radiometer (ACR) instrument (4 Shuttle) SMM/ACRIM I SMM/ACRIM II Website: https://www.jpl.nasa.gov/missions/active-cavity-irradiance-monitor-satellite-acrimsat/ [Summary provided by NASA.] Group: Platform_Details Entry_ID: ACRIMSAT Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Short_Name: ACRIMSAT Long_Name: Active Cavity Radiometer Irradiance Monitor Satellite End_Group Group: Synonymous_Platform_Names Short_Name: 1999-070B Short_Name: 26033 End_Group Group: Platform_Associated_Instruments Short_Name: ACRIM III End_Group Group: Orbit Orbit_Altitude: 685 km Orbit_Inclination: 98.13 degrees Equator_Crossing: 10:50 AM descending node Period: 99 m Perigee: 683 km Apogee: 727 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Online_Resource: https://www.jpl.nasa.gov/missions/active-cavity-irradiance-monitor-satellite-acrimsat/ Online_Resource: https://eospso.nasa.gov/missions/active-cavity-radiometer-irradiance-monitor-satellite Online_Resource: https://www.nasa.gov/centers/jpl/missions/acrimsat.html Group: Platform_Logistics Launch_Date: 1999-12-20 Launch_Site: Vandenberg Air Force Base, USA Design_Life: 5 years Primary_Sponsor: NASA End_Group End_Group 2020-02-20 22:03:07.0 [sritz] update WeightedRelation (Platform-Instrument); update WeightedRelation (1); 2020-02-20 22:02:17.0 [sritz] insert WeightedRelation (id: null related concept uuid: 2cd4dc41-07f3-4c0d-a4fe-235fdd7cbc29 relationship type: null relationship value: null generated by: null); 2020-02-13 21:44:41.0 [sritz] update Definition (https://www.jpl.nasa.gov/missions/active-cavity-irradiance-monitor-satellite-acrimsat/); 2020-02-13 21:43:54.0 [sritz] update Definition (The purpose of the Active Cavity Radiometer Irradiance Monitor III (ACRIM III) instrument is to study total solar Irradiance from the Sun. The ACRIM III package is flying on a spacecraft called ACRIMSAT. The spacecraft was launched on December 20, 1999 as a secondary payload on a Taurus launch vehicle. ACRIM III, third in a series of long-term solar-monitoring tools built for NASA by the Jet Propulsion Laboratory, will continue to extend the database first created by ACRIM I, which was launched in 1980 on the Solar Maximum Mission (SMM) spacecraft. ACRIM II followed on the Upper Atmosphere Research Satellite (UARS) in 1991. ACRIMSAT data will be correlated with possible global warming data, ice cap shrinkage data, and ozone layer depletion data. It is theorized that as much as 25 percent of the Earth's total global warming may be solar in origin due to small increases in the Sun's total energy output since the last century. By measuring incoming solar radiation and adding measurements of ocean and atmosphere currents and temperatures, as well as surface temperatures, climatologists will be able to improve their predictions of climate and global warming over the next century. Energy forecasting, carbon management, public health. Launch: Launched: December 20, 1999 Launch Vehicle: Taurus Launch Site: Western Test Range, Vandenberg Air Force Base Orbit: Altitude: 680 km Inclination: 98.13 degrees Sun-Synchronous Vital Statistics: Weight: 13 kg Power: 49 watts Design Life: 5 years Instruments: Active Cavity Radiometer (ACR) instrument (4 Shuttle) SMM/ACRIM I SMM/ACRIM II Website: https://www.jpl.nasa.gov/missions/active-cavity-irradiance-monitor-satellite-acrimsat/ [Summary provided by NASA.] Group: Platform_Details Entry_ID: ACRIMSAT Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Short_Name: ACRIMSAT Long_Name: Active Cavity Radiometer Irradiance Monitor Satellite End_Group Group: Synonymous_Platform_Names Short_Name: 1999-070B Short_Name: 26033 End_Group Group: Platform_Associated_Instruments Short_Name: ACRIM III End_Group Group: Orbit Orbit_Altitude: 685 km Orbit_Inclination: 98.13 degrees Equator_Crossing: 10:50 AM descending node Period: 99 m Perigee: 683 km Apogee: 727 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Online_Resource: https://www.jpl.nasa.gov/missions/active-cavity-irradiance-monitor-satellite-acrimsat/ Online_Resource: https://eospso.nasa.gov/missions/active-cavity-radiometer-irradiance-monitor-satellite Online_Resource: https://www.nasa.gov/centers/jpl/missions/acrimsat.html Group: Platform_Logistics Launch_Date: 1999-12-20 Launch_Site: Vandenberg Air Force Base, USA Design_Life: 5 years Primary_Sponsor: NASA End_Group End_Group); delete Resource (null); AS355-F2 2018-01-05 19:57:55.0 [sritz] Requested by NSIDC DAAC. insert AltLabel (id: null category: primary text: Helicopter AS355-F2 language code: en); 2018-01-05 19:55:16.0 [sritz] Insert Concept add broader relation (AS355-F2 [770c3b12-d083-4df9-8b36-27a4786794bb,310519] - Aircraft [227d9c3d-f631-402d-84ed-b8c5a562fc27,287509]); SAMPEX SAMPEX is the first of SMEX'es (SMall EXplorers). SAMPEX was launched in July 1992 from Western Test Range (Lompoc,CA) at 1419 UT on July 3, 1992. SAMPEX orbits at an altitude 520 by 670 Km and 82 degrees inclination and carries four instruments on board. SAMPEX measures energetic electrons as well as ion composition of particle populations from ~0.4 MeV/nucleon to hundreds of MeV/nucleon from a zenith-oriented satellite in a near polar orbit. The Payload combines some of the most sensitive particle sensors ever flown in space. Information provided by http://lasp.colorado.edu/sampex/sampex.html Group: Platform_Details Entry_ID: SAMPEX Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Short_Name: SAMPEX Long_Name: SolarAnomalous and Magnetospheric Particle Explorer End_Group Group: Synonymous_Platform_Names Short_Name: sampex End_Group Group: Platform_Associated_Instruments Short_Name: ION CHROMATOGRAPHS Short_Name: SOLAR TELESCOPES End_Group Group: Orbit Orbit_Altitude: 520 by 670 Km Orbit_Inclination: 82 degrees End_Group Creation_Date: 2007-08-21 Online_Resource: http://lasp.colorado.edu/sampex/sampex.html Sample_Image: http://lasp.colorado.edu/sampex/sampex.html Group: Platform_Logistics Launch_Date: 1992-07-03 Primary_Sponsor: NASA End_Group End_Group LANDSAT LANDSAT (LAND REMOTE-SENSING SATELLITE) Since 1972, the joint NASA/ U.S. Geological Survey Landsat series of Earth Observation satellites have continuously acquired space-based images of the Earth’s land surface, providing uninterrupted data to help land managers and policymakers make informed decisions about our natural resources and the environment. Landsat is a part of the USGS National Land Imaging (NLI) Program. More Information: https://www.usgs.gov/land-resources/nli/landsat 2019-12-31 22:07:19.0 [sritz] update Definition (Since 1972, the joint NASA/ U.S. Geological Survey Landsat series of Earth Observation satellites have continuously acquired space-based images of the Earth’s land surface, providing uninterrupted data to help land managers and policymakers make informed decisions about our natural resources and the environment. Landsat is a part of the USGS National Land Imaging (NLI) Program. More Information: https://www.usgs.gov/land-resources/nli/landsat); update Definition (https://www.usgs.gov/land-resources/nli/landsat https://landsat.gsfc.nasa.gov/); delete Resource (null); 2016-06-09 15:31:07.0 [epneff] added altLabel insert AltLabel (id: null text: LANDSAT (LAND REMOTE-SENSING SATELLITE) language code: en); Sentinel-5P A precursor satellite mission, Sentinel-5P aims to fill in the data gap and provide data continuity between the retirement of the Envisat satellite and NASA's Aura mission and the launch of Sentinel-5. The mission will perform atmospheric monitoring and was launched in October 2017. Launch Date: 13 October 2017 Operational lifespan: 7 years Mission Objectives: The Sentinel-5 Precursor objectives are to provide operational space-borne observations in support to the operational monitoring of: Air Quality Ozone and Surface UV Climate It will provide measurements of: Ozone NO_2 SO_2 Formaldehyde Aerosol Carbonmonoxide Methane Clouds Mission Orbit: Orbit Type: Sun-synchronous, polar Orbit Height: 824 km Inclination: 98.74° Repeat Cycle: 16 days Mean LST: 13:30 at Ascending Node Sentinel-5 Precursor is foreseen to operate in loose formation with Suomi-NPP Payload: The TROPOMI instrument is a UV-VIS-NIR-SWIR push-broom grating spectrometer. Spectral range: 270-495 nm, 710-775 nm, 2305-2385 nm Spectral resolution: 0.25-0.55 nm Observation mode: nadir pointing, global daily coverage, 7x7 km^2 ground Payload Mass: 200kg Configuration: The spacecraft launch mass is ~900 kg Launch vehicle: ROCKOT Contractors: Prime Contractor: Airbus Defence & Space TROPOMI contract: Dutch Ministry of Economic Affairs 2019-02-22 20:03:26.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: 74ee2866-0e9e-4c20-8003-0621af6552f3 relationship type: null relationship value: null generated by: null); 2018-10-04 18:35:15.0 [mmorahan] insert Definition (id: null text: A precursor satellite mission, Sentinel-5P aims to fill in the data gap and provide data continuity between the retirement of the Envisat satellite and NASA's Aura mission and the launch of Sentinel-5. The mission will perform atmospheric monitoring and was launched in October 2017. Launch Date: 13 October 2017 Operational lifespan: 7 years Mission Objectives: The Sentinel-5 Precursor objectives are to provide operational space-borne observations in support to the operational monitoring of: Air Quality Ozone and Surface UV Climate It will provide measurements of: Ozone NO_2 SO_2 Formaldehyde Aerosol Carbonmonoxide Methane Clouds Mission Orbit: Orbit Type: Sun-synchronous, polar Orbit Height: 824 km Inclination: 98.74° Repeat Cycle: 16 days Mean LST: 13:30 at Ascending Node Sentinel-5 Precursor is foreseen to operate in loose formation with Suomi-NPP Payload: The TROPOMI instrument is a UV-VIS-NIR-SWIR push-broom grating spectrometer. Spectral range: 270-495 nm, 710-775 nm, 2305-2385 nm Spectral resolution: 0.25-0.55 nm Observation mode: nadir pointing, global daily coverage, 7x7 km^2 ground Payload Mass: 200kg Configuration: The spacecraft launch mass is ~900 kg Launch vehicle: ROCKOT Contractors: Prime Contractor: Airbus Defence & Space TROPOMI contract: Dutch Ministry of Economic Affairs language code: en); 2018-10-04 18:31:20.0 [mmorahan] Insert Concept add broader relation (Sentinel-5P [77e9a75e-2c3b-428b-8b21-b6a902dd8fee,368151] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761]); Clelia As of 2010, Clelia has been retired from active deployment and placed on display at the Georgia Aquarium as the centerpiece of their deep sea research methods exhibit. Owned and operated by Harbor Branch Oceanographic Institution, Clelia is a PC 1204 submersible built by Perry Oceanographics in 1976 and refitted in 1992 by Harbor Branch to address the needs of the shallow water scientific community. At 23 ft long, 8 ft 3 in wide and 9 ft 7 in high, the Clelia travels at a maximum speed of 3 knots and is classed and certified to a maximum operating depth of 1,000 feet by the American Bureau of Shipping (ABS). The vehicle can accommodate two scientists/observers and a pilot allowing excellent visibility through the forward acrylic hemisphere. The proximity of the occupants to the bottom (approximately 18") allows tasks to be completed in areas of low visibility. Researchers are afforded an excellent view of the ocean environment through 10 view ports. A hemispheric, 3-ft-diameter window is located at the front end of the sub. Eight 8-in diameter ports are equally spaced around the conning tower of the sub, and one upward view port is in the center of the overhead hatch. Clelia is outfitted with active sonar, still and video cameras, as well as a seven-function hydraulic manipulator equipped with a suction sampler, clam bucket scoop and jaws capable of handling bottom cores and other sampling devices. The manipulator can lift up to 150 lbs. The various collections are placed in the rotating sampler that allows for both quantitative and qualitative sampling. The Clelia is equipped with still and video cameras. Two 500-watt metal halide lights, ideal for photography, can illuminate an area to near-daylight conditions. The highly maneuverable submersible is ideally suited for multiple short dives as well as longer duration, more complex dives. The Clelia can be balanced midwater to absolutely neutral buoyancy, providing an extremely stable platform from which to observe, collect samples and shoot photographs and video. Typical applications include benthic and/or mid-water observations, photo/video documentation and collection of organisms; dump site inspections and monitoring; punch and box coring; search and recovery; bottom surveys; photogrammetric surveys; archaeological site documentation and recovery; and environmental impact studies. Maintained and operated by experienced and expert pilots and crew, it is further supported by an in-house engineering staff. Working with the support staff, researchers also can add their own equipment, usually other cameras or sampling equipment, to the Clelia. The additional equipment, however, must be tested and certified that it can withstand deep-sea pressures. Harbor Branch also requires that researchers provide their equipment ahead of time to ensure that it can be interfaced properly with the Clelia’s existing equipment. 2020-01-21 19:21:06.0 [tstevens] insert Definition (id: null text: As of 2010, Clelia has been retired from active deployment and placed on display at the Georgia Aquarium as the centerpiece of their deep sea research methods exhibit. Owned and operated by Harbor Branch Oceanographic Institution, Clelia is a PC 1204 submersible built by Perry Oceanographics in 1976 and refitted in 1992 by Harbor Branch to address the needs of the shallow water scientific community. At 23 ft long, 8 ft 3 in wide and 9 ft 7 in high, the Clelia travels at a maximum speed of 3 knots and is classed and certified to a maximum operating depth of 1,000 feet by the American Bureau of Shipping (ABS). The vehicle can accommodate two scientists/observers and a pilot allowing excellent visibility through the forward acrylic hemisphere. The proximity of the occupants to the bottom (approximately 18") allows tasks to be completed in areas of low visibility. Researchers are afforded an excellent view of the ocean environment through 10 view ports. A hemispheric, 3-ft-diameter window is located at the front end of the sub. Eight 8-in diameter ports are equally spaced around the conning tower of the sub, and one upward view port is in the center of the overhead hatch. Clelia is outfitted with active sonar, still and video cameras, as well as a seven-function hydraulic manipulator equipped with a suction sampler, clam bucket scoop and jaws capable of handling bottom cores and other sampling devices. The manipulator can lift up to 150 lbs. The various collections are placed in the rotating sampler that allows for both quantitative and qualitative sampling. The Clelia is equipped with still and video cameras. Two 500-watt metal halide lights, ideal for photography, can illuminate an area to near-daylight conditions. The highly maneuverable submersible is ideally suited for multiple short dives as well as longer duration, more complex dives. The Clelia can be balanced midwater to absolutely neutral buoyancy, providing an extremely stable platform from which to observe, collect samples and shoot photographs and video. Typical applications include benthic and/or mid-water observations, photo/video documentation and collection of organisms; dump site inspections and monitoring; punch and box coring; search and recovery; bottom surveys; photogrammetric surveys; archaeological site documentation and recovery; and environmental impact studies. Maintained and operated by experienced and expert pilots and crew, it is further supported by an in-house engineering staff. Working with the support staff, researchers also can add their own equipment, usually other cameras or sampling equipment, to the Clelia. The additional equipment, however, must be tested and certified that it can withstand deep-sea pressures. Harbor Branch also requires that researchers provide their equipment ahead of time to ensure that it can be interfaced properly with the Clelia’s existing equipment. language code: en); 2020-01-21 17:34:22.0 [tstevens] Insert Concept add broader relation (Clelia [78c6cfd9-0df5-435e-9bb1-d14322db928f,559771] - HOV [63c8aa1d-6efc-4943-8891-3a1cd520dde0,559759]); SMART-R The Shared Mobile Atmospheric Research and Teaching Radar (SMART-R) is a new mobile radar built with partners Texas A&M University, Texas Tech University and the University of Oklahoma. SMART-R is the first mobile 5 cm radar in the United States. It was designed using the latest computer and radar signal processing hardware and software. With the capability to see through an entire thunderstorm or hurricane, it can observe precipitation over a larger area than other mobile radars. [Source: NOAA] Group: Platform_Details Entry_ID: SMART-R Group: Platform_Identification Platform_Category: In Situ Land-based Platforms Platform_Series_or_Entity: WEATHER STATIONS/NETWORKS Short_Name: SMART-R Long_Name: Shared Mobile Atmospheric Research and Teaching Radar End_Group Group: Synonymous_Platform_Names Short_Name: SMARTR End_Group Creation_Date: 2007-12-12 Online_Resource: http://www.nssl.noaa.gov/smartradars/ Sample_Image: http://www.nssl.noaa.gov/stories/images/SMARTR_832.jpg End_Group AEM-3 AEM-3 (Applications Explorer Mission-3) Designation: 11604 / 79094A Launch date: 30 Oct 1979 Country of origin: United States Mission Scientific: Earth magnetic field study Perigee/Apogee: 352/561 km Inclination: 96.8ý Period: 93.7 min Launch vehicle: Scout #101 Decay: 11 Jun 1980 Group: Platform_Details Entry_ID: AEM-3 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: AEM (Applications Explorer Mission) Short_Name: AEM-3 Long_Name: Applications Explorer Mission-3 End_Group Group: Synonymous_Platform_Names Short_Name: Magsat End_Group Group: Platform_Associated_Instruments Short_Name: MAGNETOMETERS End_Group Group: Orbit Orbit_Inclination: 96.8 degrees Period: 93.7 min Perigee: 352 km Apogee: 561 km End_Group Creation_Date: 2007-08-22 Sample_Image: http://space.skyrocket.de/img_sat/magsat__2.jpg Group: Platform_Logistics Launch_Date: 1979-10-30 Primary_Sponsor: NASA End_Group End_Group GEMINI-4 GEMINI 4 was the second manned mission of the GEMINI series and carried J. A. Mcdivitt and E. H. White on a 4-day, 62-orbit, 98-hr flight from June 3 to June 7, 1965. The spacecraft was conical and had a diameter of 3.05 m at the large end, which was the rear of the spacecraft and which was covered by a fiberglass heat shield to protect the craft during reentry. The objective of the mission was to test the performance of the astronauts and capsule for an extended length of time in space. The spacecraft was transported to space with a titan rocket. White performed a 23-min eva (walk) in space attached to the spacecraft by an 8-m tether. Medical and engineering experiments were performed. The scientific experiments performed were visual and photographic. The experiments performed were electrostatic charge (msc-1), proton-electron spectrometer (msc-2), triaxial magnetometer (msc-3), two-color earth limb photos (msc-10), inflight exerciser (m-3), inflight phonocardiogram (m-4), bone demineralization (m-6), synoptic terrain photos (s-5), synoptic weather photos (s-6), dim and twilight phenomena (s-28), radiation (d-8), and simple navigation (d-9). The mission was successful, and the spacecraft landed in the pacific on June 7, 1965. Group: Platform_Details Entry_ID: GEMINI-4 Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Platform_Series_or_Entity: GEMINI Short_Name: GEMINI-4 End_Group Group: Synonymous_Platform_Names Short_Name: Titan-II (4) End_Group Group: Orbit Orbit_Inclination: 32.53 degrees Period: 56 minutes Repeat_Cycle: 4 days Perigee: 162 km Apogee: 281 km End_Group Creation_Date: 2008-01-23 Online_Resource: http://science.ksc.nasa.gov/history/gemini/gemini-iv/gemini-iv.html Sample_Image: http://science.ksc.nasa.gov/history/gemini/gemini-iv/gemini-iv-patch-small.gif Group: Platform_Logistics Launch_Date: 1965-06-03 Primary_Sponsor: NASA End_Group End_Group GOES-4 GOES 4 was launched in September 1980 and was a NASA-developed, NOAA-operated, geosynchronous, and operational spacecraft. The cylindrically shaped spacecraft measured 190.5 cm in diameter and 230 cm in length, exclusive of a magnetometer that extended an additional 83 cm beyond the cylinder shell. The primary structural members were a honeycombed equipment shelf and thrust tube. The VISSR telescope was mounted on the equipment shelf and viewed the Earth through a special aperture in the side of the spacecraft. A support structure extended radially out from the thrust tube and was affixed to the solar panels, which formed the outer walls of the spacecraft and provided the primary source of electrical power. Located in the annulus-shaped space between the thrust tube and the solar panels were stationkeeping and dynamics control equipment, batteries, and most of the SEM equipment. Proper spacecraft attitude and spin rate (approximately 100 rpm) were maintained by two separate sets of jet thrusters mounted around the spacecraft equator and activated by ground command. The spacecraft used both UHF-band and S-band frequencies in its telemetry and command subsystem. A low-power VHF transponder provided telemetry and command during launch and then served as a backup for the primary subsystem once the spacecraft attained orbit. The spin-stabilized spacecraft carried a visible infrared spin-scan radiometer atmospheric sounder, meteorological data collection and transmission system, space environment monitor, and a biaxial fluxgate magnetometer. It operated at 100 degrees West initially, but replaced GOES 3 at 135 degrees West in March 1981. When GOES 5 VAS experienced a failure on July 30, 1984, GOES 4 was reactivated by NOAA to provide GOES 1 VISSR data relay services to western users. More information about GOES Satellites: http://www.ospo.noaa.gov/Operations/GOES/index.html 2017-09-01 17:04:38.0 [sritz] insert Definition (id: null text: GOES 4 was launched in September 1980 and was a NASA-developed, NOAA-operated, geosynchronous, and operational spacecraft. The cylindrically shaped spacecraft measured 190.5 cm in diameter and 230 cm in length, exclusive of a magnetometer that extended an additional 83 cm beyond the cylinder shell. The primary structural members were a honeycombed equipment shelf and thrust tube. The VISSR telescope was mounted on the equipment shelf and viewed the Earth through a special aperture in the side of the spacecraft. A support structure extended radially out from the thrust tube and was affixed to the solar panels, which formed the outer walls of the spacecraft and provided the primary source of electrical power. Located in the annulus-shaped space between the thrust tube and the solar panels were stationkeeping and dynamics control equipment, batteries, and most of the SEM equipment. Proper spacecraft attitude and spin rate (approximately 100 rpm) were maintained by two separate sets of jet thrusters mounted around the spacecraft equator and activated by ground command. The spacecraft used both UHF-band and S-band frequencies in its telemetry and command subsystem. A low-power VHF transponder provided telemetry and command during launch and then served as a backup for the primary subsystem once the spacecraft attained orbit. The spin-stabilized spacecraft carried a visible infrared spin-scan radiometer atmospheric sounder, meteorological data collection and transmission system, space environment monitor, and a biaxial fluxgate magnetometer. It operated at 100 degrees West initially, but replaced GOES 3 at 135 degrees West in March 1981. When GOES 5 VAS experienced a failure on July 30, 1984, GOES 4 was reactivated by NOAA to provide GOES 1 VISSR data relay services to western users. More information about GOES Satellites: http://www.ospo.noaa.gov/Operations/GOES/index.html language code: en); 2017-09-01 16:44:49.0 [sritz] Insert Concept add broader relation (GOES-4 [79de5661-cfa3-491d-bb30-4414452676e8,310087] - GOES [6e332c25-caeb-4917-afb6-af757bcecd72,310071]); OrbView-1 MICROLAB-1 MicroLab 1, also known as OrbView 1 was launched on April 3, 1995, OrbView-1 provides the world's first broad-area cloud-to-cloud lightning data. OrbView-1's payload consists of two sensors: -an Optical Transient Detector (OTD) provided by NASA's Marshall Space Flight Center, and -an atmospheric monitoring instrument (GPS/MET) sponsored by the National Science Foundation and the University Consortium for Atmospheric Research. The OTD sensor maps atmospheric lighting strikes and has provided NASA with information important to the understanding of severe weather patterns. The GPS/MET sensor has proven that the signals from the GPS satellite constellation used for precision navigation can also be used to provide important atmospheric data. The success of the GPS/MET sensor has further validated the concept of using space-based sensors to improve worldwide weather prediction. The OrbView-1 program is the result of a unique government-industry partnership between ORBIMAGE and NASA. Under this arrangement, NASA provided the OTD sensor for use on OrbView-1 and ORBIMAGE agreed to conduct an initial six-month experiment of the sensor. NASA's cost for data under this program over the past five years has totaled approximately &#367.2 million. Additional information available at https://space.skyrocket.de/doc_sdat/orbview-1.htm Group: Platform_Details Entry_ID: MICROLAB-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: MICROLAB-1 Long_Name: OSC Microlab-1 Satellite End_Group Group: Synonymous_Platform_Names Short_Name: OrbView-1 End_Group Group: Platform_Associated_Instruments Short_Name: GPS Short_Name: OTD End_Group Creation_Date: 2007-11-20 Online_Resource: https://space.skyrocket.de/doc_sdat/orbview-1.htm Sample_Image: http://space.skyrocket.de/img_sat/orbview-1.jpg Group: Platform_Lsogistics Launch_Date: 1995-04-03 Primary_Sponsor: NASA End_Group End_Group 2020-01-29 22:01:42.0 [sritz] update Definition (MicroLab 1, also known as OrbView 1 was launched on April 3, 1995, OrbView-1 provides the world's first broad-area cloud-to-cloud lightning data. OrbView-1's payload consists of two sensors: -an Optical Transient Detector (OTD) provided by NASA's Marshall Space Flight Center, and -an atmospheric monitoring instrument (GPS/MET) sponsored by the National Science Foundation and the University Consortium for Atmospheric Research. The OTD sensor maps atmospheric lighting strikes and has provided NASA with information important to the understanding of severe weather patterns. The GPS/MET sensor has proven that the signals from the GPS satellite constellation used for precision navigation can also be used to provide important atmospheric data. The success of the GPS/MET sensor has further validated the concept of using space-based sensors to improve worldwide weather prediction. The OrbView-1 program is the result of a unique government-industry partnership between ORBIMAGE and NASA. Under this arrangement, NASA provided the OTD sensor for use on OrbView-1 and ORBIMAGE agreed to conduct an initial six-month experiment of the sensor. NASA's cost for data under this program over the past five years has totaled approximately &#367.2 million. Additional information available at https://space.skyrocket.de/doc_sdat/orbview-1.htm Group: Platform_Details Entry_ID: MICROLAB-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: MICROLAB-1 Long_Name: OSC Microlab-1 Satellite End_Group Group: Synonymous_Platform_Names Short_Name: OrbView-1 End_Group Group: Platform_Associated_Instruments Short_Name: GPS Short_Name: OTD End_Group Creation_Date: 2007-11-20 Online_Resource: https://space.skyrocket.de/doc_sdat/orbview-1.htm Sample_Image: http://space.skyrocket.de/img_sat/orbview-1.jpg Group: Platform_Lsogistics Launch_Date: 1995-04-03 Primary_Sponsor: NASA End_Group End_Group); update Resource (image); update Resource (https://space.skyrocket.de/img_sat/orbview-1.jpg); 2016-07-26 20:57:08.0 [saritz] S. Ritz updated keyword at the request of UAH. insert AltLabel (id: null text: MICROLAB-1 language code: en); update PrefLabel (OrbView-1); SCD The satellites of the SCD (Satelites de Coleta de Dados) series are equipped to collect and transmit meteorological and environmental data collected by automatic platforms (PCD) installed on land or on oceanic buoys. The data is relayed to one or more ground stations. The INPE is responsible for development, production and operation of this series of 4 satellites, the SCD-1, SCD-2, SCD-2A and SCD-3. SCD-1 was placed in orbit in February 1993 by a Pegasus and is operating until today, with a useful life beyond the period, initially foreseen, of one year. The SCD-2 was launched successfully in 1998, by a Pegasus-H vehicle, from Cape Canaveral. Currently it operates jointly form with SCD-1. The SCD-2A was lost in the inaugural launching of the VLS-1, in 1997. SCD 3 is a new design, which will be launched into a higher orbit to enlarge the area covered by the satellite. Group: Platform_Details Entry_ID: SCD Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: SCD Long_Name: Satellites de Coleta de Dados End_Group Group: Synonymous_Platform_Names Short_Name: SCD End_Group Group: Orbit Orbit_Inclination: 25 Period: 98.8 End_Group Creation_Date: 2007-11-28 Online_Resource: http://en.wikipedia.org/wiki/Sat%C3%A9lite_de_Coleta_de_Dados Group: Platform_Logistics Launch_Date: 1993-02-09 Design_Life: 1 years Primary_Sponsor: Brazil/INPE End_Group End_Group FY-1 FY-1 is China's meteorological satellite. Multichannel Visible and IR Scan Radiometer (MVISR) is the major sensor of FY- 1. The total number of channels of the sensor is increased from 5 channels in FY-1 A and B to 10 channels in FY-1 C and D. These channels include 4 VIS channels, 3 near IR channels, 1 short wave IR channel and 2 long wave IR channels. The instantaneous field of view of the sensor is 1.2 microrad and the resolution at subpoint is 1.1 Km. The scan rate of MVISR is still 6 lines/second and total pixel of every scan line is 20480. The High Resolution Picture Transmission of FY-1 C and D is named CHRPT. It is considered that the system which receives and processes HRPT/NOAA- Now data can receive and process CHRPT with updating as few as possible. The scan rate of MVISR is 6 lines/second. The words of every channel are 2048 and the total words of 10 channels are 20480. Plus the sync and auxiliary information there are 22180 words every scan line and 10 bits every word. The bit rate is 1.3308 Mbps, just twice as many as the bit rate of HRPT/NOAA-Now. The modulation of CHRPT data is PSK and bit format is split phase. The transmission frequency of CHRPT will be 1700.5MHz and the data format will be similar to the HRPT/NOAA-Now data format. Therefore, it will to be easy to process CHRPT data with HRPT/NOAA-Now data processing system. Additional information available at "http://nsmc.cma.gov.cn/fy1e.html" [Summary provided by China's National Satellite Meteorological Center] Group: Platform_Details Entry_ID: FY-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: FY (Feng-Yun) Short_Name: FY-1 Long_Name: China's Meteorological Satellite-1 End_Group Group: Platform_Associated_Instruments Short_Name: MVISR - Multichannel Visible and Infrared Scan Radiometer Short_Name: CHRPT - The High Resolution Picture Transmission of FY-1 C End_Group Group: Orbit Orbit_Altitude: 863 km Orbit_Inclination: 98.8 degrees Equator_Crossing: 8:53 AM Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Online_Resource: http://nsmc.cma.gov.cn/item/fy_demo2.asp Group: Platform_Logistics Launch_Date: 1988-09-06 Launch_Site: Taiyuan Space Launch Center, China Primary_Sponsor: China National Meteorology Center End_Group End_Group STREAMFLOW STATION The USGS, in cooperation with more than 800 state, local and other federal agencies, operates approximately 7,000 continuously active streamflow measurement and data collection sites, called streamgages. Almost 5,000 of the USGS's approximately 7,000 streamgages are equipped with telemetry that transmits a reading of stream depth ("stage") to a district office via satellite or telephone. This "realtime" data is used for a multiplicity of purposes: including flood hazard mitigation by the National Weather Service, the U.S. Army Corps of Engineers, and the Federal Emergency Management Agency; and for resource planning, and infrastructure design of reservoirs and dams. Group: Platform_Details Entry_ID: STREAMFLOW STATION Group: Platform_Identification Platform_Category: In Situ Land-based Platforms Platform_Series_or_Entity: HYDROLOGICAL STATIONS Short_Name: STREAMFLOW STATION End_Group Creation_Date: 2012-07-18 Online_Resource: http://www.nationalatlas.gov/articles/water/a_streamflow.html End_Group IMP-I IMP-6 (IMP-I or Explorer 43, NSSDC ID: 71-019A) was a 16-sided drum-shaped spacecraft of dimensions: 1.8212 meter high and 1.3564 meter in diameter. Its mass was 635 kg. The spacecraft spin axis was perpendicular to the ecliptic plane with a spin rate of 5 rpm, giving it a spin period of 12 seconds. IMP-6 continued the study, begun by earlier IMPs, of the interplanetary and outer magnetospheric regions by measuring energetic particles, plasma, and electric and magnetic fields. A radio astronomy experiment was also included in the spacecraft payload. The initial apogee point was near the earth-sun line. The solar-cell and chemical- battery powered spacecraft carried two transmitters. One continuously transmitted PCM encoder data at a 1600-bps information bit rate. The second transmitter was used for transmission of VLF data and for ranging information. Three orthogonal pairs of dipole antennas were used for the electric fields experiments, and one of these pairs was also used for the radio astronomy experiment. The members of the antenna pair along the spacecraft spin axis extended 2.9 meter, the members of the antennal pair used in both the electric field and radio astronomy experiments extended 45.5 meter, and the members of the third pair were slightly unbalanced, extending 24.4 meter and 27.6 meter, respectively. All four elements perpendicular to the spin axis were to have extended 45.5 meter. The spacecraft reentered the earth's atmosphere on October 2, 1974, after a highly successful mission. The IMP (Interplanetary Monitoring Platform) spacecraft exploration program was carried out by the United States. _____________________________________________________________ Entry taken from: Hills, H. K., R. G. Littlefield, N. J. Schofield and J. I. Vette: 'Data Catalog Series for Space Science and Applications Flight Missions', Vol. 3A, NSSDC/WDC-A, NASA / Goddard Space Flight Center, September 1982. _________________________________________________________________ See also: Fairfield, D. H., Journal of Geophysical Research, 79, 1368, 1974. Frank, L. A. et al., Journal of Geophysical Research, 82, 129, 1977. Armstrong, T. and S. M. Krimigis, Journal of Geophysical Research, 81, 677, 1976. Williams, D. J., NOAA Technical Report, ERL 393-SEL 40, U.S. Department of Commerce, Boulder, Colorado, USA, October 1977. PIONEER 11 Pioneer 11 was launched on 5 April 1973, like Pioneer 10, on top of an Atlas/Centaur/TE364-4 launch vehicle. After safe passage through the Asteroid belt on 19 April 1974, the Pioneer 11 thrusters were fired to add another 63.7 m/sec (210 ft/sec) to the spacecraft's velocity. This adjusted the aiming point at Jupiter to 43,000 km (26,725 miles) above the cloudtops. The close approach also allowed the spacecraft to be accelerated by Jupiter to a velocity 55 times that of the muzzle velocity of a high speed rifle bullet - 173,000 km/hr (108,000 mph) - so that it would be carried across the Solar System some 2.4 billion kilometers (1.5 billion miles) to Saturn. During its flyby of Jupiter on 2 December 1974, Pioneer 11 obtained dramatic images of the Great Red Spot, made the first observation of the immense polar regions, and determined the mass of Jupiter's moon, Callisto. Looping high above the ecliptic plane and across the Solar System, Pioneer 11 raced toward its appointment with Saturn on 1 September 1979. Pioneer 11 flew to within 13,000 miles of Saturn and took the first close-up pictures of the planet. Instruments located two previously undiscovered small moons and an additional ring, charted Saturn's magnetosphere and magnetic field and found its planet-size moon, Titan, to be too cold for life. Hurtling underneath the ring plane, Pioneer 11 sent back amazing pictures of Saturn's rings. The rings, which normally seem bright when observed from Earth, appeared dark in the Pioneer pictures, and the dark gaps in the rings seen from Earth appeared as bright rings. Following its encounter with Saturn, Pioneer 11 explored the outer regions of our Solar system, studying energetic particles from our Sun (Solar Wind) and cosmic rays entering our portion of the Milky Way. In September 1995, Pioneer 11 was at a distance of 6.5 billion km (4 billion miles) from Earth. At that distance, it takes over 6 hours for the radio signal (which is traveling at the speed of light) to reach Earth. However, by September 1995, Pioneer 11 could no longer make any scientific observations. On 30 September 1995, routine daily mission operations were stopped. Intermittent contact continued until November 1995, at which time the last communication with Pioneer 11 took place. There have been no communications with Pioneer 11 since. The Earth's motion has carried it out of the view of the spacecraft antenna. The spacecraft cannot be maneuvered to point back at the Earth. It is not known whether the spacecraft is still transmitting a signal. No further tracks of Pioneer 11 are scheduled. Group: Platform_Details Entry_ID: PIONEER 11 Group: Platform_Identification Platform_Category: Interplanetary Spacecraft Platform_Series_or_Entity: FLYBY Short_Name: PIONEER 11 End_Group Group: Synonymous_Platform_Names Short_Name: Pioneer-G Short_Name: 06421 Short_Name: 1973-019A End_Group Creation_Date: 2007-02-05 Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1973-019A Sample_Image: http://nssdc.gsfc.nasa.gov/image/spacecraft/pioneer10-11.jpg Group: Platform_Logistics Launch_Date: 1973-04-05 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: NASA/Ames Primary_Sponsor: TRW End_Group End_Group TIPS The TIPS satellite was deployed on 20 June 1996 at an altitude of 1,022 kilometers (552 nautical miles). This experiment is designed to increase knowledge about gravity-gradient tether dynamics and the survivability of tethers in space. (Tethers can be severed by space debris.) The National Reconnaissance Office (NRO) is a sponsor of the TiPS program. While tethers have been theoretically studied as a means for satellite stabilization, propulsion, and electricity generation for some time, TiPS is among the first successful tether deployments in space and is the first experiment designed for long duration. Additional information available at http://projects.nrl.navy.mil/tips/ [Summary provided by U.S. Military] Group: Platform_Details Entry_ID: TIPS Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: TIPS Long_Name: Tether Physics and Survivability End_Group Group: Synonymous_Platform_Names Short_Name: TIPS End_Group Group: Platform_Associated_Instruments Short_Name: RIS End_Group Group: Orbit Orbit_Altitude: 1,022 km Orbit_Inclination: 63.4 deg Period: 105 min Orbit_Type: LEO > Low Earth Orbit > Inclined Non-Polar End_Group Creation_Date: 2007-11-28 Online_Resource: http://projects.nrl.navy.mil/tips/ Sample_Image: http://code8100.nrl.navy.mil/programs/images/tips2_corner_lg.jpg Group: Platform_Logistics Launch_Date: 1996-06-20 Primary_Sponsor: NASA End_Group End_Group Megha-Tropiques GPS (Global Positioning System) CFOSAT CFOSAT is a joint mission of the Chinese (CNSA) and French (CNES) space agencies with the goal to monitor the ocean surface winds and waves and to provide information on related ocean and atmospheric science and applications. The primary objective of CFOSAT is to monitor on a global scale the wind and waves at the ocean surface in order to improve: • The wind and wave forecast for marine meteorology (including severe events) • The ocean dynamics modeling and prediction • Our knowledge of climate variability • Fundamental knowledge on surface processes linked to wind and waves. An operational demonstration objective of CFOSAT is to provide observations over the ocean in near-real-time for assimilation in meteorological and wave forecast models. Wind and wave products must be available in operational centers within 3 hours after acquisition. CFOSAT will also be used to complement other satellite missions for the estimation of land surface parameters (in particular soil moisture and soil roughness), and polar ice sheet characteristics. 2019-12-19 14:13:09.0 [mmorahan] insert AltLabel (id: null category: primary text: Chinese-French Oceanography Satellite language code: en); insert Definition (id: null text: CFOSAT is a joint mission of the Chinese (CNSA) and French (CNES) space agencies with the goal to monitor the ocean surface winds and waves and to provide information on related ocean and atmospheric science and applications. The primary objective of CFOSAT is to monitor on a global scale the wind and waves at the ocean surface in order to improve: • The wind and wave forecast for marine meteorology (including severe events) • The ocean dynamics modeling and prediction • Our knowledge of climate variability • Fundamental knowledge on surface processes linked to wind and waves. An operational demonstration objective of CFOSAT is to provide observations over the ocean in near-real-time for assimilation in meteorological and wave forecast models. Wind and wave products must be available in operational centers within 3 hours after acquisition. CFOSAT will also be used to complement other satellite missions for the estimation of land surface parameters (in particular soil moisture and soil roughness), and polar ice sheet characteristics. language code: en); insert WeightedRelation (id: null related concept uuid: 55694771-4eee-455d-87db-135627949cf5 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 1c7fb7a4-cedd-4328-b785-5b0774cf1990 relationship type: null relationship value: null generated by: null); 2019-12-19 14:10:27.0 [mmorahan] Insert Concept add broader relation (CFOSAT [7c3fab1c-d17e-4e5c-870e-994793c2594e,559573] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,541501]); NCEP/DOE-R2M 2015-08-10 18:51:16.0 [epneff] Added long name insert AltLabel (id: null text: NCEP/DOE Reanalysis 2 Model language code: en); 2015-08-10 18:50:49.0 [epneff] Insert Concept add broader relation (NCEP/DOE-R2M [7c4302ef-0fca-4987-9515-d059b9e0bb95,158239] - Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215]); GEOTAIL The GEOTAIL mission is a collaborative project undertaken by the Institute of Space and Astronautical Science (ISAS) and the National Aeronautics and Space Administration (NASA). Its primary objective is to study the dynamics of the Earth's magnetotail over a wide range of distance, extending from the near-Earth region (8 Earth radii (Re) from the Earth) to the distant tail (about 200 Re). The GEOTAIL spacecraft was designed and built by ISAS and was launched on July 24, 1992. The Geotail mission measures global energy flow and transformation in the magnetotail to increase understanding of fundamental magnetospheric processes. This will include the physics of the magnetopause, the plasma sheet, and reconnection and neutral line formation (i.e., the mechanisms of input, transport, storage, release and conversion of energy in the magnetotail). Geotail, together with Wind, Polar, SOHO, and Cluster projects, constitute a cooperative scientific satellite project designated the International Solar-Terrestrial Physics (ISTP) program which aims at gaining improved understanding of the physics of solar terrestrial relations. Geotail is a spin-stabilized spacecraft utilizing mechanically despun antennas with a design lifetime of about four years. The nominal spin rate of the spacecraft is about 20 rpm around a spin axis maintained between 85 and 89 deg to the ecliptic plane. Geotail is cylindrical, approximately 2.2 m in diameter and 1.6 m high with body-mounted solar cells. Geotail also has a two-hour back-up battery subsystem which operates when the spacecraft is in the Earth's shadow. Real-time telemetry data transmitted in the X-band are received at the Usuda Deep Space Center (UDSC) in Japan. There are two tape recorders on board, each with a capacity of 450 Mbit which allow daily 24-hour data coverage. The data are collected in playback mode by the NASA Deep Space Network (DSN). The Geotail mission is divided into two phases. During the two-year initial phase, the orbit apogee was kept on the nightside of the Earth by using the Moon's gravity in a series of double-lunar swing-by maneuvers that result in the spacecraft spending most of its time in the distant magnetotail (maximum apogee about 200 Earth radii) with a period varying from one to four months. Then, starting in November 1994, there were a series of maneuvers to bring the spacecraft into its near-Earth orbit. This transition orbit lasted about three months with the apogee varying from 50 RE to 30 RE. The second phase is dedicated to the study of near-Earth magnetospheric processes, including neutral line formation. The GEOTAIL mission consists of the following experiments: - Comprehensive Plasma Investigation (CPI) - Electric Fields Detector (EFD) - Energetic Particle and Ion Composition (EPIC) - High-Energy Particles (HEP) - Low-Energy Particles (LEP) - Magnetic Field Experiment - Plasma Waves Investigation (PWI) For more information, see: http://pwg.gsfc.nasa.gov/geotail.shtml Group: Platform_Details Entry_ID: GEOTAIL Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Short_Name: GEOTAIL End_Group Group: Synonymous_Platform_Names Short_Name: GGS/Geotail Short_Name: GTL Short_Name: Geomagnetic Tail Lab Short_Name: ISTP/Geotail Short_Name: 22049 Short_Name: 1992-044A End_Group Group: Platform_Associated_Instruments Short_Name: MFE Short_Name: PWI Short_Name: LEP Short_Name: HEP Short_Name: EPIC Short_Name: EFD Short_Name: CPI-G End_Group Group: Orbit Orbit_Inclination: 5.15 degrees - 7.45 degrees Period: 43 days - 49 days Perigee: 47,835 km - 51,024 km Apogee: 869,421 km - 191,340 km Orbit_Type: HEO > Highly Elliptical Orbit End_Group Online_Resource: http://pwg.gsfc.nasa.gov/geotail.shtml Online_Resource: http://www.stp.isas.ac.jp/geotail/ Sample_Image: http://nssdc.gsfc.nasa.gov/image/spacecraft/geotail.jpg Group: Platform_Logistics Launch_Date: 1992-07-24 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: ISAS, Japan Primary_Sponsor: NASA End_Group End_Group R/V POLARSTERN The Polarstern spends almost 310 days a year at sea. Between November and March it usually sails to and around the waters of the Antarctic, while the northern summer months are spent in Arctic waters. The ship is equipped for biological, geological, geophysical, glaciological, chemical, oceanographic and meteorological research, and contains nine research laboratories. Additional laboratory containers may be stowed on and below deck. Refrigerated rooms and aquaria permit the transport of samples and living marine fauna. Group: Platform_Details Entry_ID: R/V POLARSTERN Group: Platform_Identification Platform_Category: In Situ Ocean-based Platforms Platform_Series_or_Entity: SHIPS Short_Name: R/V POLARSTERN End_Group Creation_Date: 2012-07-19 Online_Resource: http://www.awi.de/en/infrastructure/ships/polarstern/ End_Group HEXAGON KH-9 2018-11-09 12:57:53.0 [tstevens] insert AltLabel (id: null category: primary text: HEXAGON KH-9 Reconnaissance Satellite language code: en); 2018-11-09 12:56:53.0 [tstevens] Insert Concept add broader relation (HEXAGON KH-9 [7d97b6ca-83de-44e1-8d3b-f45755e38a8d,368257] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761]); GMCC The NOAA Geophysical Monitoring for Climatic Change Stations (GMCC) measure and observe atmospheric aerosols. The goals of this regional-scale monitoring program are to characterize means, variability, and trends of climate-forcing properties of different types of aerosols, and to understand the factors that control these properties. Additional information available at "http://www.cmdl.noaa.gov/aero/" [Summary provided by NOAA] Group: Platform_Details Entry_ID: GMCC Group: Platform_Identification Platform_Category: In Situ Land-based Platforms Platform_Series_or_Entity: AIR MONITORING STATIONS/NETWORKS Short_Name: GMCC Long_Name: NOAA Geophysical Monitoring for Climatic Change Stations End_Group Group: Synonymous_Platform_Names Short_Name: GMCC End_Group Creation_Date: 2007-11-30 Online_Resource: http://www.fdsn.org/FDSNintro.htm Sample_Image: http://www.esrl.noaa.gov/gmd/hats/flask/bull_flk.jpg End_Group RCV-150 The RCV-150 ROV was a remotely operated robotic submersible that was operated by HURL between 1998 and 2011. It was piloted from a shipboard station, receiving power and commands from the surface control console via a steel armored electro-mechanical fiber optical cable. The vehicle could operate to depths of 914 meters (3000 ft). It was equipped with two color video cameras with lights and a CTD which sent data directly up the wire. RCV-150 was primarily used as a video survey tool that could acquire extremely close-up views because of its small size and maneuverability. 2020-01-23 12:26:25.0 [tstevens] insert Definition (id: null text: The RCV-150 ROV was a remotely operated robotic submersible that was operated by HURL between 1998 and 2011. It was piloted from a shipboard station, receiving power and commands from the surface control console via a steel armored electro-mechanical fiber optical cable. The vehicle could operate to depths of 914 meters (3000 ft). It was equipped with two color video cameras with lights and a CTD which sent data directly up the wire. RCV-150 was primarily used as a video survey tool that could acquire extremely close-up views because of its small size and maneuverability. language code: en); 2020-01-21 17:26:55.0 [tstevens] Insert Concept add broader relation (RCV-150 [7ec61a93-3c42-4af1-adca-8f26d22d3d27,559747] - ROV [da6420b6-48ec-4ae2-98c7-0ef0538815a0,542741]); SKYVAN The Skyvan is a 19-seater twin turboprop aircraft manufactured by Short Brothers, at the time Short Brothers & Harland Ltd, and used mainly for short-haul freight and skydiving. The Skyvan is a high wing twin engined all-metal monoplane with a high cantilever tailplane with twin rudders. The first flight of the Skyvan, the Skyvan 1, was on 17 January 1963. [Text provided by Wikipedia, http://en.wikipedia.org/wiki/Shorts_SC.7_Skyvan ] [Photo provided by Arctic Circle Air, http://www.arctic-circle-air.com/skyvan%20front%20view%20small.jpg ] Group: Platform_Details Entry_ID: SKYVAN Group: Platform_Identification Platform_Category: Aircraft Short_Name: SKYVAN End_Group Creation_Date: 2008-07-14 Online_Resource: http://en.wikipedia.org/wiki/Shorts_SC.7_Skyvan Sample_Image: http://www.arctic-circle-air.com/skyvan%20front%20view%20small.jpg End_Group DMSP 5B/F3 DMSP-5B-F3 [Source: National Space Science Data Center, http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1972-089A ] DMSP (72-089A), also known as DMSP 6530, was one of a series of meteorological satellites developed and operated by the Air Force under the Defense Meteorological Satellite Program. The program, previously known as Data Acquisition and Processing Program (DAPP), was classified until March 1973. The objective of this program was to provide global visual and infrared (IR) cloudcover data and specialized environmental data to support Department of Defense requirements. Operationally, the program consisted of two satellites in 830 km sun-synchronous polar orbits, with the ascending node of one satellite near the sunrise terminator and the other near local noon. The satellite, shaped like the frustum of a polyhedron, consisted of four subassemblies -- (1) a solar array hat, (2) a base-plate assembly, (3) a sensor AVE (Aerospace Vehicle Electronics) package (SAP), and (4) a data processing system. The primary sensor (SAP) was a four channel scanning radiometer. Secondary sensors included a vertical temperature profile radiometer (supplementary sensor E -SSE) and an electron spectrograph (supplementary sensor J/2 - SSJ/2), which were mounted, along with the primary sensor, on the base-plate assembly. Spacecraft stabilization was controlled by a combination flywheel and magnetic control coil system so that the sensors were maintained in the desired earth-looking mode. The data processing system included three tape recorders capable of storing a total of 440 min of data, which allowed full global coverage twice daily. Either recorded or real-time data were transmitted to ground receiving sites via an s-band transmitter. Recorded data were read out to tracking sites located at Fairchild AFB, Wa, and Loring AFB, ME, and relayed to Air Force Global Weather Central, Offutt AFB, NE. Real-time data were read out a mobile tactical sites located around the world. Group: Platform_Details Entry_ID: DMSP 5B/F3 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: DMSP (Defense Meteorological Satellite Program) Short_Name: DMSP 5B/F3 Long_Name: Defense Meteorological Satellite Program-F3 End_Group Group: Synonymous_Platform_Names Short_Name: DMSP 6530 Short_Name: 06275 End_Group Group: Platform_Associated_Instruments Short_Name: SSJ Short_Name: VTPR Short_Name: SR End_Group Group: Orbit Orbit_Inclination: 98.7° Period: 101.8 minutes Perigee: 813.0 km Apogee: 872.0 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1972-089A Online_Resource: http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/dmsp.html Online_Resource: http://www.ngdc.noaa.gov/dmsp/index.html Group: Platform_Logistics Launch_Date: 1972-11-09 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: Department of Defense-Department of the Air Force (United States) End_Group End_Group 2016-06-09 14:33:07.0 [epneff] added altLabel insert AltLabel (id: null text: DMSP-5B-F3 language code: en); SMAP [Source: NASA SMAP, https://smap.jpl.nasa.gov ] [SMAP was launched on 2015-01-31] The Soil Moisture Active-Passive (SMAP) mission has been recommended by the NRC Earth Science Decadal Survey Panel for 'launch in 2015. SMAP will use a combined radiometer and high-resolution radar to measure surface soil moisture and freeze-thaw state, providing for scientific advances and societal benefits. Direct measurements of soil moisture and freeze/thaw state are needed to improve our understanding of regional water cycles, ecosystem productivity, and processes that link the water, energy, and carbon cycles. Soil moisture information at high resolution enables improvements in weather forecasts, flood and drought forecasts, and predictions of agricultural productivity and climate change. The National Polar-orbiting Operational Environmental Satellite System (NPOESS) Integrated Program Office (IPO) has developed a tri-agency set of requirements for the next generation of polar-orbiting operational environmental satellites. A novel approach combining radar-radiometer and L-band mapping of global soil moisture will allow SMAP to far exceed the NPOESS soil moisture threshold (minimum performance) requirements for sensing depth and spatial resolution. With "fast-track" development, it is possible that SMAP could provide critical gap-filling soil moisture measurements for NPOESS, which were lost when the Conical Microwave Imager/Sounder was cancelled from the first NPOESS platform. Group: Platform_Details Entry_ID: SMAP Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NASA Decadal Survey Short_Name: SMAP Long_Name: Soil Moisture Active and Passive Observatory End_Group Group: Platform_Associated_Instruments Short_Name: SMAP L-BAND RADIOMETER Short_Name: SMAP L-BAND RADAR End_Group Creation_Date: 2009-09-17 Online_Resource: https://smap.jpl.nasa.gov/ Group: Platform_Logistics Launch_Date: 2015-01-31 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: USA/NASA End_Group End_Group 2019-09-16 21:45:13.0 [sritz] update Definition ([Source: NASA SMAP, https://smap.jpl.nasa.gov ] [SMAP was launched on 2015-01-31] The Soil Moisture Active-Passive (SMAP) mission has been recommended by the NRC Earth Science Decadal Survey Panel for 'launch in 2015. SMAP will use a combined radiometer and high-resolution radar to measure surface soil moisture and freeze-thaw state, providing for scientific advances and societal benefits. Direct measurements of soil moisture and freeze/thaw state are needed to improve our understanding of regional water cycles, ecosystem productivity, and processes that link the water, energy, and carbon cycles. Soil moisture information at high resolution enables improvements in weather forecasts, flood and drought forecasts, and predictions of agricultural productivity and climate change. The National Polar-orbiting Operational Environmental Satellite System (NPOESS) Integrated Program Office (IPO) has developed a tri-agency set of requirements for the next generation of polar-orbiting operational environmental satellites. A novel approach combining radar-radiometer and L-band mapping of global soil moisture will allow SMAP to far exceed the NPOESS soil moisture threshold (minimum performance) requirements for sensing depth and spatial resolution. With "fast-track" development, it is possible that SMAP could provide critical gap-filling soil moisture measurements for NPOESS, which were lost when the Conical Microwave Imager/Sounder was cancelled from the first NPOESS platform. Group: Platform_Details Entry_ID: SMAP Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NASA Decadal Survey Short_Name: SMAP Long_Name: Soil Moisture Active and Passive Observatory End_Group Group: Platform_Associated_Instruments Short_Name: SMAP L-BAND RADIOMETER Short_Name: SMAP L-BAND RADAR End_Group Creation_Date: 2009-09-17 Online_Resource: https://smap.jpl.nasa.gov/ Group: Platform_Logistics Launch_Date: 2015-01-31 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: USA/NASA End_Group End_Group); HY2-B The HY-2 satellite is an oceanographic remote sensing satellite series developed by China's National Satellite Ocean Application Service (NSOAS); four satellites are planned: HY-2A (2011), HY-2B (2012), HY-2C (2015), HY-2D (2019). The objective of HY-2 is to monitor the dynamic ocean environment with radar sensors to measure sea surface wind field, sea surface height and sea surface temperature. It will include a dual-frequency radar altimeter in Ku and C-bands, a Ku-band rotating scatterometer and microwave imager. The orbit is sun-synchronous: the first 2 years with a 14-day cycle, then one year with geodetic orbit (168-day cycle, 5-day approx. subcycle). 2018-08-10 18:56:52.0 [sritz] insert Definition (id: null text: The HY-2 satellite is an oceanographic remote sensing satellite series developed by China's National Satellite Ocean Application Service (NSOAS); four satellites are planned: HY-2A (2011), HY-2B (2012), HY-2C (2015), HY-2D (2019). The objective of HY-2 is to monitor the dynamic ocean environment with radar sensors to measure sea surface wind field, sea surface height and sea surface temperature. It will include a dual-frequency radar altimeter in Ku and C-bands, a Ku-band rotating scatterometer and microwave imager. The orbit is sun-synchronous: the first 2 years with a 14-day cycle, then one year with geodetic orbit (168-day cycle, 5-day approx. subcycle). language code: en); 2018-08-10 18:55:12.0 [sritz] insert AltLabel (id: null category: primary text: Haiyang-2B language code: en); 2018-08-10 18:54:34.0 [sritz] update PrefLabel (HY2-B); 2018-08-10 18:54:04.0 [sritz] Insert Concept add broader relation (HY-2B [7ef45b8e-ac63-41b2-9e8b-7becfa7d7431,368067] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761]); GAW The Global Atmosphere Watch (GAW) programme of WMO is a partnership involving 80 countries, which provides reliable scientific data and information on the chemical composition of the atmosphere, its natural and anthropogenic change, and helps to improve the understanding of interactions between the atmosphere, the oceans and the biosphere. [Source: GAW Home Page, http://www.wmo.int/pages/prog/arep/gaw/gaw_home_en.html ] Group: Platform_Details Entry_ID: GAW Group: Platform_Identification Platform_Category: In Situ Land-based Platforms Platform_Series_or_Entity: WEATHER STATIONS/NETWORKS Short_Name: GAW Long_Name: Global Atmospheric Stations End_Group Creation_Date: 2010-06-15 Online_Resource: http://www.wmo.int/pages/prog/arep/gaw/gaw_home_en.html End_Group WORLDVIEW-1 he next-generation commercial imaging satellite of DigitalGlobe Inc. (Longmont, CO, USA) is called WorldView-1, a successor of QuickBird-2 (launch Oct. 18, 2001 - and fully operational as of 2007). In Oct. 2003, DigitalGlobe was awarded a sizeable contract by NGA (National Geospatial-Intelligence Agency) of Washington DC, formerly NIMA (National Imaging and Mapping Agency), to provide high-resolution imagery from the next-generation commercial imaging satellites. The NGA requirements call for imagery with a spatial resolution of 0.5 m panchromatic and 2 m MS (Multispectral) data. The contract award was made within NGA's NextView program, designed to give the US commercial imaging satellite operators the financing to build their satellites for high-resolution imaging. The WorldView mission is intended to provide imaging services to NGA as well as to the commercial customer base of DigitalGlobe. Spacecraft: BATC (Ball Aerospace and Technologies Corporation) of Boulder, CO, is the prime contractor and integrator of the spacecraft, providing the S/C bus (Ball Commercial Platform BCP-5000) and a WorldView-60 camera. A new feature of the WorldView spacecraft are CMG (Control Moment Gyroscopes) actuators for precise and highly responsive pointing control. The BCP-5000 bus provides increased power, stability, agility, data storage and transmission (over the BCP-2000 bus) as the demand for Earth remote-sensing information becomes more comprehensive. The S/C is 3-axis stabilized. The ADCS (Attitude Determination and Control Subsystem) employs star trackers, IRU (Inertial Reference Unit) and GPS for attitude sensing, and CMGs as actuators. A S/C body-pointing range of ±40º about nadir is provided corresponding to a FOR (Field of Regard) of 775 km in cross-track. An instantaneous pointing accuracy of ≤ 500 m is provided at any start and stop of an imaging sequence. On the ground, the geolocation accuracy of the imagery is 5.8 to 7.6 m without GPCs (Ground Control Points) and 2 m with GPCs (3σ). The agile S/C provides retargeting at a rate of 4.5º/s with an acceleration of 2.5º/s2; it takes 9 s to slew the S/C over a ground distance of 300 km. S/C power of 3.2 kW (EOL) is provided by the solar panels; the battery capacity is 100 Ah. The solar arrays are being articulated into the sun (normal pointing into the sun). The rotational drive assemblies and drive control electronics, referred to as QuAD (Quiet Array Drive), are being provided by Starsys, a subsidiary of SpaceDev, Poway, CA. Unlike traditional stepper motor solar array drives, the QuAD technology provides low disturbance actuation, allowing spacecraft images to be captured at the same time that the solar arrays are being pointed. The S/C bus has dimensions of 3.6 m (high) and 2.5 m in diameter, the span of the deployed panels measures 7.1 m. WorldView-1 has a launch mass of 2500 kg. The mission design life is 7.25 years. Launch: A launch of the WorldView-1 spacecraft took place on Sept. 18, 2007 on a Delta-2920 vehicle from VAFB, CA. Orbit: Sun-synchronous circular orbit, altitude = 496 km (nominal), inclination = 97.2º. The equator crossing time is at 10:30 hours on a descending node. The period is 94.6 minutes. Note: While the low-altitude orbit selection offers better spatial resolutions than a higher one, it requires also more frequent reboosts to maintain the low orbit due to atmospheric drag influences. RF communications: The command data are in S-band at 2 or 64 kbit/s. The housekeeping telemetry and tracking is in X-band at 4, 16, or 32 kbit/s of real-time data, or 524 kbit/s of stored data. The imagery is downlinked in X-band at 800 Mbit/s. The S/C provides a data storage capacity of 2.2 Tbit in solid state memory with EDAC (Error Detection and Correction). A total of 331 Gbit of imagery per orbit may be collected. In addition, direct (real-time) downlinks to customer sites are available using the same high-speed 800 Mbit/s X-band link. Mission status: In early January 2008, DigitalGlobe announced the general availability of WorldView-1 imagery to its customers after all check-out aspects of the spacecraft and its payload had been completed. 6) • DigitalGlobe delivered its first sample set of high-resolution images on Oct. 15, 2007 and began supplying imagery to the National Geospatial-Intelligence Agency (NGA) on Nov. 26, 2007 (the S/C reached already full operating capacity on Nov. 17. 2007). Informaiton obtained from http://www.eoportal.org/ Group: Platform_Details Entry_ID: WORLDVIEW-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: WORLDVIEW-1 End_Group Group: Platform_Associated_Instruments Short_Name: CAMERAS Short_Name: MS End_Group Group: Orbit Orbit_Altitude: 496 Orbit_Inclination: 97.2 Period: 94.5 Repeat_Cycle: 1.7 Perigee: 499.7 Apogee: 500.8 Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2008-07-10 Online_Resource: http://directory.eoportal.org/get_announce.php?an_id=12389 Online_Resource: http://www.digitalglobe.com/index.php/86/WorldView-1 Group: Platform_Logistics Launch_Date: 2007-09-18 Launch_Site: Vandenberg Air Force Base, USA Design_Life: 7.25 years Primary_Sponsor: National Geospatial-Intelligence Agency, USA End_Group End_Group 2019-02-22 22:03:08.0 [mmorahan] delete WeightedRelation (null); insert WeightedRelation (id: null related concept uuid: d8ff2cc4-d922-4661-8bba-fd78c7672ce9 relationship type: null relationship value: null generated by: null); NASA S-3B VIKING The Lockheed S-3 Viking is a jet aircraft originally used by the United States Navy to identify, track, and destroy enemy submarines. In the late 1990s, the S-3B's mission focus shifted to surface warfare and aerial refueling. After the retirement of the A-6 Intruder and A-7 Corsair II, the Viking was the only airborne refueling platform organic to the Carrier Air Wing(s) until the fielding of the F/A-18E/F Super Hornet... One aircraft was transformed into a state-of-the-art NASA research aircraft. The Navy's Fleet Readiness Center - Southeast and a Boeing facility in Fla. enhanced the plane by adding commercial satellite communications, global positioning navigation and weather radar systems. They installed research equipment racks in what was once the plane's bomb bay. NASA's S-3B Viking is equipped to conduct science and aeronautics missions, such as environmental monitoring, satellite communications testing and aviation safety research. [Text provided by: Wikipedia, http://en.wikipedia.org/wiki/S-3_Viking ] [Photo provided by: https://www.nasa.gov/centers/glenn ] Group: Platform_Details Entry_ID: NASA S-3B VIKING Group: Platform_Identification Platform_Category: Aircraft Short_Name: NASA S-3B VIKING End_Group Creation_Date: 2008-07-15 Online_Resource: https://www.nasa.gov/topics/aeronautics/features/s3_viking.html Online_Resource: http://en.wikipedia.org/wiki/S-3_Viking Online_Resource: https://www.nasa.gov/centers/glenn/aeronautics/aero_overview.html End_Group 2019-06-26 20:14:31.0 [sritz] update Definition (The Lockheed S-3 Viking is a jet aircraft originally used by the United States Navy to identify, track, and destroy enemy submarines. In the late 1990s, the S-3B's mission focus shifted to surface warfare and aerial refueling. After the retirement of the A-6 Intruder and A-7 Corsair II, the Viking was the only airborne refueling platform organic to the Carrier Air Wing(s) until the fielding of the F/A-18E/F Super Hornet... One aircraft was transformed into a state-of-the-art NASA research aircraft. The Navy's Fleet Readiness Center - Southeast and a Boeing facility in Fla. enhanced the plane by adding commercial satellite communications, global positioning navigation and weather radar systems. They installed research equipment racks in what was once the plane's bomb bay. NASA's S-3B Viking is equipped to conduct science and aeronautics missions, such as environmental monitoring, satellite communications testing and aviation safety research. [Text provided by: Wikipedia, http://en.wikipedia.org/wiki/S-3_Viking ] [Photo provided by: https://www.nasa.gov/centers/glenn ] Group: Platform_Details Entry_ID: NASA S-3B VIKING Group: Platform_Identification Platform_Category: Aircraft Short_Name: NASA S-3B VIKING End_Group Creation_Date: 2008-07-15 Online_Resource: https://www.nasa.gov/topics/aeronautics/features/s3_viking.html Online_Resource: http://en.wikipedia.org/wiki/S-3_Viking Online_Resource: https://www.nasa.gov/centers/glenn/aeronautics/aero_overview.html End_Group); 2019-06-26 19:59:16.0 [sritz] update Definition (The Lockheed S-3 Viking is a jet aircraft originally used by the United States Navy to identify, track, and destroy enemy submarines. In the late 1990s, the S-3B's mission focus shifted to surface warfare and aerial refueling. After the retirement of the A-6 Intruder and A-7 Corsair II, the Viking was the only airborne refueling platform organic to the Carrier Air Wing(s) until the fielding of the F/A-18E/F Super Hornet... One aircraft was transformed into a state-of-the-art NASA research aircraft. The Navy's Fleet Readiness Center - Southeast and a Boeing facility in Fla. enhanced the plane by adding commercial satellite communications, global positioning navigation and weather radar systems. They installed research equipment racks in what was once the plane's bomb bay. NASA's S-3B Viking is equipped to conduct science and aeronautics missions, such as environmental monitoring, satellite communications testing and aviation safety research. [Text provided by: Wikipedia, http://en.wikipedia.org/wiki/S-3_Viking ] [Photo provided by: https://www.nasa.gov/centers/glenn ] Group: Platform_Details Entry_ID: NASA S-3B VIKING Group: Platform_Identification Platform_Category: Aircraft Short_Name: NASA S-3B VIKING End_Group Creation_Date: 2008-07-15 Online_Resource: https://www.nasa.gov/topics/aeronautics/features/s3_viking.html Online_Resource: http://en.wikipedia.org/wiki/S-3_Viking Online_Resource: https://www.nasa.gov/centers/glenn/aeronautics/aero_overview.html Sample_Image: https://www.nasa.gov/centers/glenn/images/content/235804main_S-3B_featured_image_4x3_800-600.jpg End_Group); update Definition (http://en.wikipedia.org/wiki/S-3_Viking); delete Resource (null); UND CITATION II The University of North Dakota owns and operates a Cessna Citation II aircraft for the purpose of atmospheric research. This aircraft type has a number of design and performance characteristics that make it an ideal platform for a wide range of atmospheric studies. The Citation II is a twin-engine fanjet with an operating ceiling of 43,000 feet (13.1 km). The turbofan engines provide sufficient power to cruise at speeds of up to 340 knots (175 m s-1) or climb at 3300 feet per minute (16.8 m s-1). These high performance capabilities are accompanied by relatively low fuel consumption at all altitudes, giving the Citation an on-station time of 3-5 hours, depending on mission type. Long wings allow it to be operated out of relatively short airstrips and to be flown at the slower speeds (140 kts/72 m s-1) necessary for many types of measurements. The Citation is certified for flight into known icing conditions. Source: http://cumulus.atmos.und.edu/ Group: Platform_Details Entry_ID: UND CITATION II Group: Platform_Identification Platform_Category: Aircraft Short_Name: UND CITATION II End_Group Group: Platform_Associated_Instruments Short_Name: GNSS RECEIVER Short_Name: ACCELEROMETERS Short_Name: GPS End_Group Creation_Date: 2012-12-11 Online_Resource: http://cumulus.atmos.und.edu/ End_Group 2012-10-17 01:30:33.0 [saritz] Move Concepts delete broader relation (null); add broader relation (UND CITATION II [7f2883c4-bbaf-4150-93d8-dc48716476ca,61305] - Aircraft [227d9c3d-f631-402d-84ed-b8c5a562fc27,31205]); 2012-10-17 01:29:33.0 [saritz] Insert Concept add broader relation (UND CITATION II [7f2883c4-bbaf-4150-93d8-dc48716476ca,61305] - Platforms [f3261de5-34c1-4980-af22-f9d7e7206d12,31173]); VOLCANO OBSERVATORY Volcano Observatory is a building, place, or institution designed and equipped for making observations on volcanoes. There are many such global volcano observatories. [Source: The American Heritage? Dictionary of the English Language, Fourth Edition Copyright ? 2000 by Houghton Mifflin Company.] PIONEER 10 Pioneer 10 was launched on 2 March 1972 on top of an Atlas/Centaur/TE364-4 launch vehicle. The launch marked the first use of the Atlas-Centaur as a three-stage launch vehicle. The third stage was required to rocket Pioneer 10 to the speed of 51,810 kilometers per hour (32,400 mph) needed for the flight to Jupiter. This made Pioneer the fastest manmade object to leave the Earth, fast enough to pass the Moon in 11 hours and to cross the Mars orbit, about 80 million kilometers (50 million miles) away, in just 12 weeks. On 15 July 1972 Pioneer 10 entered the Asteroid Belt, a doughnut shaped area which measures some 280 million kilometers wide and 80 million kilometers thick. The material in the belts travels at speed about 20 km/sec. and ranges in size from dust particles to rock chunks as big as Alaska. After safely traversing the Asteroid Belt, Pioneer 10 headed toward Jupiter. Accelerated by the massive giant to a speed of 132,000 km/hr (82,000 mph), Pioneer 10 passed by Jupiter within 130,354 km (81,000 miles) of the cloudtops on December 3, 1973. During the passage by Jupiter, Pioneer 10 obtained the first close-up images of the planet, charted Jupiter's intense radiation belts, located the planet's magnetic field, and discovered that Jupiter is predominantly a liquid planet. Following its encounter with Jupiter, Pioneer 10 explored the outer regions of the Solar system, studying energetic particles from the Sun (Solar Wind), and cosmic rays entering our portion of the Milky Way. The spacecraft continued to make valuable scientific investigations in the outer regions of the solar system until its science mission ended on March 31, 1997. Since that time, Pioneer 10's weak signal has been tracked by the DSN as part of an advanced concept study of communication technology in support of NASA's future interstellar probe mission. The spacecraft had also been used to help train flight controllers how to acquire radio signals from space during the Lunar Prospector mission. The power source on Pioneer 10 finally degraded to the point where the signal to Earth dropped below the threshold for detection in its latest contact attempt on 7 February, 2003. The previous three contacts had very faint signals with no telemetry received. The last time a Pioneer 10 contact returned telemetry data was on 27 April 2002. Group: Platform_Details Entry_ID: PIONEER 10 Group: Platform_Identification Platform_Category: Interplanetary Spacecraft Platform_Series_or_Entity: FLYBY Short_Name: PIONEER 10 End_Group Group: Synonymous_Platform_Names Short_Name: Pioneer-F Short_Name: 05860 Short_Name: 1972-012A End_Group Creation_Date: 2007-02-05 Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1972-012A Sample_Image: http://nssdc.gsfc.nasa.gov/image/spacecraft/pioneer10-11.jpg Group: Platform_Logistics Launch_Date: 1972-03-02 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: NASA/Ames Primary_Sponsor: TRW End_Group End_Group C-MAN The Coastal-Marine Automated Network (C-MAN) was established by NDBC for the NWS in the early 1980's. The development of C-MAN was in response to a need to maintain meteorological observations in U. S. coastal areas. Such observations, which had been made previously by USCG personnel, would have been lost as many USCG navigational aids were automated under the Lighthouse Automation and Modernization Program (LAMPS). In all, approximately 60 stations make up C-MAN. C-MAN stations have been installed on lighthouses, at capes and beaches, on near shore islands, and on offshore platforms (see the NDBC station location map for all station locations). C-MAN station data typically include barometric pressure, wind direction, speed and gust, and air temperature; however, some C-MAN stations are designed to also measure sea water temperature, water level, waves, relative humidity, precipitation, and visibility. These data are processed and transmitted hourly to users in a manner almost identical to moored buoy data. In addition to the conventional method of data transmission, certain C-MAN stations are equipped with telephone modems that allow more frequent data acquisition, data quality checking, and remote payload reconfiguration or restarting. More info at http://www.ndbc.noaa.gov/cman.phtml [Source: NOAA] Group: Platform_Details Entry_ID: C-MAN Group: Platform_Identification Platform_Category: In Situ Ocean-based Platforms Platform_Series_or_Entity: OCEAN PLATFORM/OCEAN STATIONS Short_Name: C-MAN Long_Name: Coastal Marine Network End_Group Group: Synonymous_Platform_Names Short_Name: C-MAN End_Group Creation_Date: 2007-12-12 Online_Resource: http://www.ndbc.noaa.gov/cman.phtml Sample_Image: http://www.uruguaynatural.com.uy/nautica/notas/Boya-10metros-diametro.jpg End_Group PAM Portable Automated Mesonet (PAM) is a network of portable surface meteorological stations designed to support observational field research projects of the atmospheric science community. More info at "http://www.atd.ucar.edu/rtf/facilities/sssf_facility_descrip/ pamiii.specs.html" [Source: Tom Horst, NCAR] Group: Platform_Details Entry_ID: PAM Group: Platform_Identification Platform_Category: In Situ Land-based Platforms Platform_Series_or_Entity: MOBILE STATIONS/VEHICLES Short_Name: PAM Long_Name: Portable Automated Mesonet End_Group Group: Synonymous_Platform_Names Short_Name: PAM End_Group Creation_Date: 2007-12-10 Online_Resource: http://www.atd.ucar.edu/rtf/facilities/sssf_facility_descrip/ Sample_Image: http://www.ucar.edu/communications/ucar25/pg.14.jpg End_Group CESSNA 188 The Cessna 188 is a family of light agricultural airplanes produced between 1966 and 1983 by the Cessna Aircraft Company. The various versions of the 188 — the AGwagon, AGpickup, AGtruck and AGhusky, along with the AGcarryall variant of the 185, constituted Cessna's line of agricultural aircraft. In the early 1960s Cessna decided to expand their already wide line of light aircraft by entering the agricultural aircraft market. They surveyed pilots and operators of other brands of agricultural aircraft to see what features and capabilities these operators were looking for. The resulting aircraft was a conventional single-seat, piston-powered, strut-braced low-winged agricultural airplane. The 188 is the only single-engined Cessna design that does not have a high-wing. The Cessna 188 borrowed heavily from the Cessna 180, the initial version using the same tail cone and fin structure as well as the same Continental O-470-R 230hp (170kW) powerplant. The 188’s airframe is predominantly built from 2024-T3 aluminum, with the chemical hopper constructed from fibreglass. The fuselage is of semi-monocoque construction and is pressurized on later models (using the dynamic pressure resulting from the aircraft's forward speed) to reduce induction of chemicals into the airframe. The Cessna 188 was first flown on 19 February 1965. The aircraft was certified and entered production in February 1966, with 241 aircraft delivered the first year. The initial design of the Cessna 188 was so successful that over its 17-year production run the basic airframe remained unchanged. Only the engines and the agricultural products dispensing systems were upgraded, other than some minor changes to the ventilation systems. A total of 3967 Cessna 188s of all four variants were built during its production run. [Text and Photo provided by: http://en.wikipedia.org/wiki/Cessna_188 ] Group: Platform_Details Entry_ID: CESSNA 188 Group: Platform_Identification Platform_Category: Aircraft Short_Name: CESSNA 188 End_Group Creation_Date: 2008-07-14 Online_Resource: http://en.wikipedia.org/wiki/Cessna_188 Online_Resource: http://www.cessna.com/ Sample_Image: http://upload.wikimedia.org/wikipedia/commons/4/4e/CessnaA188BAGtruckC-GSWZ.jpg End_Group STS-7 Manned five crew. Deployed Anik C2, Palapa B1; deployed and retrieved SPAS platform. Payloads: Office of Space and Terrestrial Applications (OSTA)-2 experiments, deployment of PALAPA-B1 communications satellite for Indonesia with Payload Assist Module (PAM)-D and Telesat-F communications satellite for Canada with PAM-D, German Shuttle Pallet Satellite (SPAS)-01, seven getaway specials (GAS), Monodisperse Latex Reactor (MLR), Continuous Flow Electrophoresis System (CFES). [Summary provided by NASA] Group: Platform_Details Entry_ID: STS-7 Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Platform_Series_or_Entity: SPACE SHUTTLE Short_Name: STS-7 Long_Name: Space Transport System STS-7 End_Group Group: Synonymous_Platform_Names Short_Name: CHALLENGER End_Group Group: Platform_Associated_Instruments Short_Name: MOMS-01 End_Group Group: Orbit Orbit_Altitude: 160nm-170nm Orbit_Inclination: 28.5 degrees End_Group Creation_Date: 2008-01-30 Online_Resource: http://science.ksc.nasa.gov/shuttle/missions/sts-7/mission-sts-7.html Sample_Image: http://science.ksc.nasa.gov/shuttle/missions/sts-7/sts-7-patch-small.gif Group: Platform_Logistics Launch_Date: 1983-06-18 Primary_Sponsor: USA/NASA End_Group End_Group SPOT-1 The SPOT-1 (Satellite Pour l'Observation de la Terre) spacecraft was launched on February 22, 1986. SPOT-1 is an earth observation satellite with a greater ground resolution than that of the Landsat series satellites. The main applications for the images returned by the first SPOT mission are land-use studies, agriculture and forestry resources, mineral and oil resources, and cartography. The three-axis stabilized satellite operates in a circular sun-synchronous near-polar orbit for a design lifetime of 2 years. Orbital Characteristics- Orbital Period: 101.40 m Inclination: 98.70 degrees Eccentricity: 0.00101 Periapsis: 815.00 km Apoapsis: 829.60 km The spacecraft dimensions are 2 x 2 x 3.5 m and 15.60 m for the overall length of the deployed solar panel. SPOT-1 consists of two parts: (1) the bus, a standard multipurpose platform, and (2) the payload. The bus provides housekeeping information and an onboard computer. The payload is mounted on one of the side panels of the bus. SPOT-1 consists of two identical high-resolution visible (HRV) imaging instruments and a package comprising two magnetic-tape data recorders and a telemetry transmitter. The HRV imaging instrument observes in three spectral bands (in the visible and near infrared regions) with a ground resolution of 20 m, and/or in a broader spectral band (panchromatic black and white) with a ground resolution of 10 m. The pattern of successive ground tracks is repeated exactly at 26-day intervals. The SPOT-1 instrument package has the provision for off-nadir viewing which should be particularly useful for monitoring localized phenomena evolving on a relatively short timescale. SPOT-1, also, provides the capability for recording stereoscopic pairs of images of a given area during successive satellite passes. *NOTE-SPOT1 is used for technological experiments such as : refocusing, batteries, etc,... *NOTE-SPOT1 is no more used for commercial image acquisition. Group: Platform_Details Entry_ID: SPOT-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: SPOT Short_Name: SPOT-1 Long_Name: Systeme Probatoire Pour l'Observation de la Terre-1 End_Group Group: Synonymous_Platform_Names Short_Name: SPOT-1 Short_Name: SPOT-A Short_Name: 16613 End_Group Group: Platform_Associated_Instruments Short_Name: HRV End_Group Group: Orbit Orbit_Inclination: 98.7° Period: 101.4 minutes Perigee: 815.0 km Apogee: 829.6 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-11-13 Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1986-019A Online_Resource: http://www.cnes.fr/web/1417-spot-1-to-5.php Online_Resource: http://www.spot.com/ Sample_Image: http://msl.jpl.nasa.gov/QuickLooks/pictures/spot1.gif Group: Platform_Logistics Launch_Date: 1986-02-22 Launch_Site: Kourou, French Guiana Primary_Sponsor: France/CNES End_Group End_Group CBERS-2 [Source: INPE CBERS home page, http://www.cbers.inpe.br/ingles/ ] CBERS-2 is technically identical to CBERS-1. The second satellite developed jointly with China was launched successfully on Oct.21, 2003 from the Taiyuan Satellite Launch Center in China. The launch time was 11:16AM (Beijing local time), which corresponds to 1:16AM (Brasilia local time). The CBERS-2 was integrated and tested in the Integration and Test Laboratory of INPE. See a detail description of the activities done in Brazil. Group: Platform_Details Entry_ID: CBERS-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: CBERS (China-Brazil Earth Resources Satellite) Short_Name: CBERS-2 Long_Name: China-Brazil Earth Resource Satellite 2 End_Group Group: Platform_Associated_Instruments Short_Name: WFI (CBERS 1,2) Short_Name: IRMSS Short_Name: HRCCD End_Group Group: Orbit Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-08-29 Online_Resource: http://adsabs.harvard.edu/abs/2004ESASP.548..221O Online_Resource: http://www.cbers.inpe.br/ingles/ Sample_Image: http://www.skyrocket.de/space/img_sat/cbers-1__1.jpg Group: Platform_Logistics Launch_Date: 2003-10-21 Primary_Sponsor: Brazil Primary_Sponsor: China End_Group End_Group CESSNA CITATION II The Cessna Citation (CE-550) is a versatile twin-engine jet aircraft modified for acquiring remote sensing imagery. The aircraft is equipped with two equal sized camera ports which can support a wide variety of remote sensing configurations including large format aerial photography as well as data collection for digital cameras, hyperspectral, multispectral, and LIDAR systems. Standard configuration includes space for two pilots, two equipment operators, and a scientific equipment rack. The aircraft can accommodate additional passengers depending on the amount of scientific equipment. The aircraft's unique side-by-side sensor port modification allows two different sensors to collect data simultaneously. The sensor ports have glass optical flats that allow the cabin to remain pressurized. Additionally, two high-precision GPS antennas provide signals to user receivers. The Citation primarily supports the Remote Sensing Division of the National Geodetic Survey, collecting remote sensing data in support of coastal mapping and remote sensing research. Imagery acquired onboard the Citation is used for updating the shoreline and shore features on NOAA's nautical charts. The Citation also serves as an emergency responder during hurricane season by collecting digital photography of damaged areas caused by hurricane landfall. [Text and Photo provided by: http://www.aoc.noaa.gov/aircraft_cessna.htm ] Group: Platform_Details Entry_ID: CESSNA CITATION II Group: Platform_Identification Platform_Category: Aircraft Short_Name: CESSNA CITATION II End_Group Creation_Date: 2008-07-14 Online_Resource: http://en.wikipedia.org/wiki/Cessna_Citation Online_Resource: http://www.cessna.com/ Online_Resource: http://www.aoc.noaa.gov/aircraft_cessna.htm Sample_Image: http://www.aoc.noaa.gov/images/Cessna%20Citation%20Photos/aircraft_cessna_update_clip_image002.jpg End_Group ITOS The Improved TIROS Operational Satellite (ITOS) inaugurated the second generation of a space-based system to provide continuous, day-to-day observations of the Earth's weather systems. ITOS launched a total of six satellites from 1970 through 1976, continuing the mission of the TIROS and the TIROS Operational Satellite programs. ITOS flew in a polar, sun-synchronous orbit and used improved stabilization techniques that allowed the spacecraft always to point its cameras and other sensors at the Earth. The satellite carried Automatic Picture Transmission cameras to provide instant weather data to ground stations around the world; Advanced Vidicon Camera Subsystems for detailed observations; and scanning radiometers for imaging the earth at night. 2018-10-30 17:20:07.0 [sritz] insert Definition (id: null text: The Improved TIROS Operational Satellite (ITOS) inaugurated the second generation of a space-based system to provide continuous, day-to-day observations of the Earth's weather systems. ITOS launched a total of six satellites from 1970 through 1976, continuing the mission of the TIROS and the TIROS Operational Satellite programs. ITOS flew in a polar, sun-synchronous orbit and used improved stabilization techniques that allowed the spacecraft always to point its cameras and other sensors at the Earth. The satellite carried Automatic Picture Transmission cameras to provide instant weather data to ground stations around the world; Advanced Vidicon Camera Subsystems for detailed observations; and scanning radiometers for imaging the earth at night. language code: en); 2018-10-30 17:18:47.0 [sritz] Insert Concept add narrower relation (ITOS [80e95a88-b44e-444e-bd79-2e6dbb56b170,368215] - ITOS-1 [b080d2a3-c089-4ddf-bbfb-3e24495413b3,368219]); 2018-10-30 17:18:11.0 [sritz] Insert Concept add broader relation (ITOS [80e95a88-b44e-444e-bd79-2e6dbb56b170,368215] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761]); Terra AM-1 am-1 TERRA TERRA (MORNING EQUATORIAL CROSSING TIME SATELLITE) Terra is the flagship satellite of NASA's Earth observing systems. Terra is the first EOS (Earth Observing System) platform and provides global data on the state of the atmosphere, land, and oceans, as well as their interactions with solar radiation and with one another. Since the 1950's, it has become increasingly clear that human activities are modifying the composition of the atmosphere on a global scale. As the result of industrialization, the concentration of carbon dioxide has increased by about 20% during this period. More recently, the stratospheric concentrations of chemically-active gases containing chlorine, bromine, and fluorine have dramatically increased. These trends have created issues of global interest including global warming and declining levels of ozone (both globally and in the ozone &hole& in the Antarctic). It has become increasingly clear, however, that these processes do not occur independently of one another and can only be understood in the context of a global system. Accurate and precise measurements are needed to unravel complex and interactive relationships between chemical, radiative, and dynamical processes in the atmosphere, ocean, and on land. As a result, in 1991 NASA initiated a comprehensive program to understand the Earth's atmosphere, oceans, land, and cryosphere (ice and snow) as a single, complex, interactive system. NASA's Earth Observing System (EOS) consists of a series of spaceborne instruments to monitor crucial components of the Earth system, an advanced data handling system, and teams of scientists who will evaluate on-going climate change and predict future changes. Ultimately, EOS will produce scientifically sound recommendations for environmental policy to national and international bodies to mitigate or prepare for these changes. Key Terra Facts: Joint with Japan and Canada Orbit: Type: Near-polar, sun-synchronous Equatorial Crossing: 10:30 a.m. Altitude: 705 km Inclination: 98.1 degrees Period: 98.88 minutes Repeat Cycle: 16 days Dimensions: 2.7 m x 3.3 m x 6.8 m Mass: 5,190 kg Power: 2,530 W Design Life: 6 years Terra Status: Operating instruments: ASTER, CERES, MODIS, MISR, and MOPITT are operating well. ASTER Short Wave Infrared (SWIR) data is unavailable. Current life expectancy: Terra has far exceeded its design life and has a strong chance of operating successfully into the early 2020s. [Summary provided by NASA] Group: Platform_Details Entry_ID: Terra Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: Terra Long_Name: Earth Observing System, Terra (AM-1) End_Group Group: Synonymous_Platform_Names Short_Name: EOS AM-1 End_Group Group: Platform_Associated_Instruments Short_Name: MOPITT Short_Name: MODIS Short_Name: MISR Short_Name: CERES-FM2 Short_Name: CERES-FM1 Short_Name: ASTER End_Group Group: Orbit Orbit_Altitude: 705 km Orbit_Inclination: 98.2 degrees Equator_Crossing: 10:30 a.m. Period: 98.88 minutes Repeat_Cycle: 16 days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-02-06 Online_Resource: https://terra.nasa.gov/ Online_Resource: https://www.nasa.gov/mission_pages/terra/index.html Sample_Image: https://www.nasa.gov/mission_pages/terra/spacecraft/index.html Group: Platform_Logistics Launch_Date: 1999-12-18 Launch_Site: VANDENBERG AIR FORCE BASE, USA Design_Life: 6 years Primary_Sponsor: USA/NASA End_Group End_Group 2020-02-04 22:40:37.0 [sritz] update Definition (Terra is the flagship satellite of NASA's Earth observing systems. Terra is the first EOS (Earth Observing System) platform and provides global data on the state of the atmosphere, land, and oceans, as well as their interactions with solar radiation and with one another. Since the 1950's, it has become increasingly clear that human activities are modifying the composition of the atmosphere on a global scale. As the result of industrialization, the concentration of carbon dioxide has increased by about 20% during this period. More recently, the stratospheric concentrations of chemically-active gases containing chlorine, bromine, and fluorine have dramatically increased. These trends have created issues of global interest including global warming and declining levels of ozone (both globally and in the ozone &hole& in the Antarctic). It has become increasingly clear, however, that these processes do not occur independently of one another and can only be understood in the context of a global system. Accurate and precise measurements are needed to unravel complex and interactive relationships between chemical, radiative, and dynamical processes in the atmosphere, ocean, and on land. As a result, in 1991 NASA initiated a comprehensive program to understand the Earth's atmosphere, oceans, land, and cryosphere (ice and snow) as a single, complex, interactive system. NASA's Earth Observing System (EOS) consists of a series of spaceborne instruments to monitor crucial components of the Earth system, an advanced data handling system, and teams of scientists who will evaluate on-going climate change and predict future changes. Ultimately, EOS will produce scientifically sound recommendations for environmental policy to national and international bodies to mitigate or prepare for these changes. Key Terra Facts: Joint with Japan and Canada Orbit: Type: Near-polar, sun-synchronous Equatorial Crossing: 10:30 a.m. Altitude: 705 km Inclination: 98.1 degrees Period: 98.88 minutes Repeat Cycle: 16 days Dimensions: 2.7 m x 3.3 m x 6.8 m Mass: 5,190 kg Power: 2,530 W Design Life: 6 years Terra Status: Operating instruments: ASTER, CERES, MODIS, MISR, and MOPITT are operating well. ASTER Short Wave Infrared (SWIR) data is unavailable. Current life expectancy: Terra has far exceeded its design life and has a strong chance of operating successfully into the early 2020s. [Summary provided by NASA] Group: Platform_Details Entry_ID: Terra Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: Terra Long_Name: Earth Observing System, Terra (AM-1) End_Group Group: Synonymous_Platform_Names Short_Name: EOS AM-1 End_Group Group: Platform_Associated_Instruments Short_Name: MOPITT Short_Name: MODIS Short_Name: MISR Short_Name: CERES-FM2 Short_Name: CERES-FM1 Short_Name: ASTER End_Group Group: Orbit Orbit_Altitude: 705 km Orbit_Inclination: 98.2 degrees Equator_Crossing: 10:30 a.m. Period: 98.88 minutes Repeat_Cycle: 16 days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-02-06 Online_Resource: https://terra.nasa.gov/ Online_Resource: https://www.nasa.gov/mission_pages/terra/index.html Sample_Image: https://www.nasa.gov/mission_pages/terra/spacecraft/index.html Group: Platform_Logistics Launch_Date: 1999-12-18 Launch_Site: VANDENBERG AIR FORCE BASE, USA Design_Life: 6 years Primary_Sponsor: USA/NASA End_Group End_Group); 2018-04-26 01:24:09.0 [sritz] delete AltLabel (null); update AltLabel (Earth Observing System, Terra (AM-1)); 2018-03-26 20:20:40.0 [sritz] insert AltLabel (id: null category: null text: TERRA language code: en); update PrefLabel (Terra); 2018-03-06 20:50:02.0 [sritz] update Definition (Terra is the flagship satellite of NASA's Earth observing systems. Terra is the first EOS (Earth Observing System) platform and provides global data on the state of the atmosphere, land, and oceans, as well as their interactions with solar radiation and with one another. Since the 1950's, it has become increasingly clear that human activities are modifying the composition of the atmosphere on a global scale. As the result of industrialization, the concentration of carbon dioxide has increased by about 20% during this period. More recently, the stratospheric concentrations of chemically-active gases containing chlorine, bromine, and fluorine have dramatically increased. These trends have created issues of global interest including global warming and declining levels of ozone (both globally and in the ozone &hole& in the Antarctic). It has become increasingly clear, however, that these processes do not occur independently of one another and can only be understood in the context of a global system. Accurate and precise measurements are needed to unravel complex and interactive relationships between chemical, radiative, and dynamical processes in the atmosphere, ocean, and on land. As a result, in 1991 NASA initiated a comprehensive program to understand the Earth's atmosphere, oceans, land, and cryosphere (ice and snow) as a single, complex, interactive system. NASA's Earth Observing System (EOS) consists of a series of spaceborne instruments to monitor crucial components of the Earth system, an advanced data handling system, and teams of scientists who will evaluate on-going climate change and predict future changes. Ultimately, EOS will produce scientifically sound recommendations for environmental policy to national and international bodies to mitigate or prepare for these changes. Key Terra Facts: Joint with Japan and Canada Orbit: Type: Near-polar, sun-synchronous Equatorial Crossing: 10:30 a.m. Altitude: 705 km Inclination: 98.1 degrees Period: 98.88 minutes Repeat Cycle: 16 days Dimensions: 2.7 m x 3.3 m x 6.8 m Mass: 5,190 kg Power: 2,530 W Design Life: 6 years Terra Status: Operating instruments: ASTER, CERES, MODIS, MISR, and MOPITT are operating well. ASTER Short Wave Infrared (SWIR) data is unavailable. Current life expectancy: Terra has far exceeded its design life and has a strong chance of operating successfully into the early 2020s. [Summary provided by NASA] Group: Platform_Details Entry_ID: TERRA Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: TERRA Long_Name: Earth Observing System, TERRA (AM-1) End_Group Group: Synonymous_Platform_Names Short_Name: EOS AM-1 End_Group Group: Platform_Associated_Instruments Short_Name: MOPITT Short_Name: MODIS Short_Name: MISR Short_Name: CERES-FM2 Short_Name: CERES-FM1 Short_Name: ASTER End_Group Group: Orbit Orbit_Altitude: 705 km Orbit_Inclination: 98.2 degrees Equator_Crossing: 10:30 a.m. Period: 98.88 minutes Repeat_Cycle: 16 days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-02-06 Online_Resource: https://terra.nasa.gov/ Online_Resource: https://www.nasa.gov/mission_pages/terra/index.html Sample_Image: https://www.nasa.gov/mission_pages/terra/spacecraft/index.html Group: Platform_Logistics Launch_Date: 1999-12-18 Launch_Site: VANDENBERG AIR FORCE BASE, USA Design_Life: 6 years Primary_Sponsor: USA/NASA End_Group End_Group); delete Resource (null); insert Resource (id: null type: provider url: https://terra.nasa.gov/); 2016-10-13 20:47:56.0 [saritz] update AltLabel (Terra); update PrefLabel (TERRA); 2016-06-10 20:02:38.0 [saritz] update AltLabel (TERRA); update PrefLabel (Terra); 2016-04-22 18:24:32.0 [saritz] S. Ritz added alternate labels. insert AltLabel (id: null text: Terra language code: en); insert AltLabel (id: null text: TERRA (MORNING EQUATORIAL CROSSING TIME SATELLITE language code: en); 2016-04-22 18:19:15.0 [saritz] S. Ritz added alternate labels. insert AltLabel (id: null text: AM-1 language code: en); insert AltLabel (id: null text: GOES-12 (AQUA/TERRA) language code: en); insert AltLabel (id: null text: am-1 language code: en); 2015-01-22 00:51:41.0 [saritz] Added related concept update WeightedRelation (1); 2015-01-22 00:50:51.0 [saritz] Added related concept insert WeightedRelation (id: null related concept uuid: 437ff0d5-8eda-49cd-8ac2-2ebbfdffeff4 relationship type: null relationship value: null generated by: null); 2015-01-22 00:46:46.0 [gee-cee] Added Related Keyword update Definition (Terra is the flagship satellite of NASA's Earth observing systems. Terra is the first EOS (Earth Observing System) platform and provides global data on the state of the atmosphere, land, and oceans, as well as their interactions with solar radiation and with one another. Since the 1950&#039;s, it has become increasingly clear that human activities are modifying the composition of the atmosphere on a global scale. As the result of industrialization, the concentration of carbon dioxide has increased by about 20% during this period. More recently, the stratospheric concentrations of chemically-active gases containing chlorine, bromine, and fluorine have dramatically increased. These trends have created issues of global interest including global warming and declining levels of ozone (both globally and in the ozone &hole& in the Antarctic). It has become increasingly clear, however, that these processes do not occur independently of one another and can only be understood in the context of a global system. Accurate and precise measurements are needed to unravel complex and interactive relationships between chemical, radiative, and dynamical processes in the atmosphere, ocean, and on land. As a result, in 1991 NASA initiated a comprehensive program to understand the Earth&#039;s atmosphere, oceans, land, and cryosphere (ice and snow) as a single, complex, interactive system. NASA&#039;s Earth Observing System (EOS) consists of a series of spaceborne instruments to monitor crucial components of the Earth system, an advanced data handling system, and teams of scientists who will evaluate on-going climate change and predict future changes. Ultimately, EOS will produce scientifically sound recommendations for environmental policy to national and international bodies to mitigate or prepare for these changes. Key Terra Facts: Joint with Japan and Canada Orbit: Type: Near-polar, sun-synchronous Equatorial Crossing: 10:30 a.m. Altitude: 705 km Inclination: 98.1 degrees Period: 98.88 minutes Repeat Cycle: 16 days Dimensions: 2.7 m x 3.3 m x 6.8 m Mass: 5,190 kg Power: 2,530 W Design Life: 6 years [Summary provided by NASA] Group: Platform_Details Entry_ID: TERRA Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: TERRA Long_Name: Earth Observing System, TERRA End_Group Group: Synonymous_Platform_Names Short_Name: EOS AM-1 End_Group Group: Platform_Associated_Instruments Short_Name: MOPITT Short_Name: MODIS Short_Name: MISR Short_Name: CERES-FM2 Short_Name: CERES-FM1 Short_Name: ASTER End_Group Group: Orbit Orbit_Altitude: 705 km Orbit_Inclination: 98.2 degrees Equator_Crossing: 10:30 a.m. Period: 98.88 minutes Repeat_Cycle: 16 days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-02-06 Online_Resource: http://science.hq.nasa.gov/missions/satellite_52.htm Online_Resource: http://terra.nasa.gov/ Sample_Image: http://gcmd.gsfc.nasa.gov/KeywordSearch/default/images/terra.gif Group: Platform_Logistics Launch_Date: 1999-12-18 Launch_Site: VANDENBERG AIR FORCE BASE, USA Design_Life: 6 years Primary_Sponsor: USA/NASA End_Group End_Group); 2015-01-22 00:45:14.0 [gee-cee] Added Related Keyword update WeightedRelation (Platform-Instrument); update WeightedRelation (1); 2015-01-22 00:44:35.0 [gee-cee] Added Related Keyword insert WeightedRelation (id: null related concept uuid: 3d148e55-a196-4779-ad6e-71a6acb5ec92 relationship type: null relationship value: null generated by: null); R/V Ivan Petrov 2012-07-13 22:52:05.0 [aaleman] Insert Concept add broader relation (R/V Ivan Petrov [810bc419-c1ea-4f38-b05f-6471e3621274,40335] - SHIPS [82a67b12-e99d-4c90-8a6a-a6f79d4c3c7b,31201]); LAGEOS-1 Spacecraft Brief Description LAGEOS (Laser Geodetic Satellite) was a very dense (high mass-to-area ratio) laser retroreflector satellite which provided a permanent reference point in a very stable orbit for such precision earth-dynamics measurements as crustal motions, regional strains, fault motions, polar motion and earth-rotation variations, solid earth tides, and other kinematic and dynamic parameters associated with earthquake assessment and alleviation. In conjunction with appropriate laser-tracking systems, LAGEOS permitted extreme precision-ranging measurements for both geometric mode (multilateration) and orbital dynamic mode determinations of positions of points on the earth. It was the first spacecraft dedicated exclusively to high-precision laser ranging and provided the first opportunity to acquire laser-ranging data that were not degraded by errors originating in the target satellite. The high-accuracy range measurements from this permanent-orbiting reference point were used to accomplish many extreme precision earth-dynamics measurements required by the earthquake hazard assessment and alleviation objectives of the Earth and Ocean Physics Applications Program (EOPAP). The performance in orbit of LAGEOS was limited only by degradation of the retroreflectors, so many decades of useful life can be expected. The high mass-to-area ratio and the precise, stable (attitude-independent) geometry of the spacecraft, together with the orbit, made this satellite the most precise position reference available. Because it is visible in all parts of the world and has an extended operation life in orbit, LAGEOS can serve as a fundamental standard for decades. Auxiliary Information Launch Date and Time : 1976-05-04 08:00:00 Epoch Date and Time : 1976-05-05 Orbit Type : Geocentric Apogee(km) : 5946. Perigee(km) : 5837. Inclination : 109.8 Date of last update : 1992-03-09 Group: Platform_Details Entry_ID: LAGEOS-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: LAGEOS (Laser Geodetic Satellite) Short_Name: LAGEOS-1 Long_Name: Laser Geodetic Satellite-1 End_Group Group: Synonymous_Platform_Names Short_Name: LAGEOS-1 End_Group Group: Platform_Associated_Instruments Short_Name: LASER TRACKING REFLECTOR End_Group Group: Orbit Orbit_Inclination: 109.90 deg Period: 225.50 min Perigee: 5,837 km Apogee: 5,947 km End_Group Creation_Date: 2007-10-10 Online_Resource: http://msl.jpl.nasa.gov/QuickLooks/lageosQL.html Online_Resource: http://nasascience.nasa.gov/missions/lageos-1-2 Online_Resource: http://ilrs.gsfc.nasa.gov/satellite_missions/list_of_satellites/lag1_general.html Sample_Image: http://msl.jpl.nasa.gov/QuickLooks/pictures/lageos.gif Group: Platform_Logistics Launch_Date: 1976-05-04 Launch_Site: Vandenberg Air Force Base, USA Design_Life: 50 years Primary_Sponsor: USA/NASA End_Group End_Group APOLLO-SOYUZ The Apollo-Soyuz Test Project (ASTP) was the first human spaceflight mission managed jointly by two nations. It was designed to test the compatibility of rendezvous and docking systems for American and Soviet spacecraft in order to open the way for future joint human flights. There were a number of difficulties that both nations had to resolve in the mission design before they could assure a safe docking of both spacecraft and an on-orbit meeting of crewmembers. The technical challenges included different measuring systems, the different spacecraft and thus mating adapter designs, and different air pressures and mixtures. The Apollo spacecraft was the same design as those used on lunar exploration missions. Several modifications were made for the Apollo-Soyuz mission, however, including the addition of propellants for the reaction control system, heaters for temperature control, and extra equipment needed to operate the Docking Module. The Soyuz had been the Soviet's primary spacecraft since 1967. It consisted of three basic modules?Orbital, Descent, and Instrument?no major modifications were needed. The mission began with the Soyuz launch on July 15, 1975, followed by the Apollo launch seven hours later. The docking in space of, the two spacecraft took place at 2:17 p.m. U.S. central time on July 17. Two days worth of joint operations followed. After separation, the Soyuz remained in space for almost two days before landing in the U.S.S.R. on July 21. The Apollo spacecraft remained in space for another three days before splashing down near Hawaii on July 24. The mission was a resounding success for both Americans and Soviets. They achieved their goal of obtaining flight experience for rendezvous and docking of human spacecraft. In addition, they also demonstrated in-flight intervehicular crew transfer, as well as accomplished a series of scientific experiments. The ASTP mission was not only successful as a space effort, but the mutual confidence and trust it engendered made it a huge step in international cooperation during the Cold War. Additional information available at "http://science.ksc.nasa.gov/history/astp/astp.html" [Summary provided by NASA] METOP-A MetOp-A The MetOp-A satellite, developed by a consortium of European companies led by the main contractor EADS-Astrium, France, builds on the heritage gained from a successful series of European satellites, including the French Space Agency's (CNES) SPOT and ESA'S ERS and Envisat. The satellite consists of a Solar Array and two modules: the Payload Module (PLM) and the Service Module (SVM). The PLM accommodates the whole suite of instruments and associated support equipment. It includes advanced versions of the widely used scatterometer and ozone-monitoring instruments already flying onboard the ERS-2 satellite. The SVM, which interfaces with the launcher, provides the main satellite support functions, such as command and control, communications with the ground, power and orbit control and propulsion. MetOp-A carries a set of 'heritage' instruments, provided by the United States’ National Oceanic and Atmospheric Administration (NOAA) and the French Space Agency (CNES), and a new generation of European instruments offering precise sensing capabilities to both meteorologists and climatologists. http://www.esa.int/esaLP/LPmetop.html [Summary from the ESA MetOp Meteorological Missions home page] Group: Platform_Details Entry_ID: METOP-A Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: METOP Short_Name: METOP-A Long_Name: Meteorological Operational Satellite - A End_Group Group: Platform_Associated_Instruments Short_Name: SARR Short_Name: SEM-2 Short_Name: A-DCS Short_Name: AVHRR-3 Short_Name: HIRS/4 Short_Name: AMSU-B Short_Name: AMSU-A Short_Name: GOME-2 Short_Name: ASCAT Short_Name: GRAS Short_Name: MHS Short_Name: IASI End_Group Group: Orbit Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Online_Resource: http://www.esa.int/esaLP/LPmetop.html Group: Platform_Logistics Launch_Date: 2006-10-19 Launch_Site: Baikonur Cosmodrome, Tyuratam, Russia Primary_Sponsor: ESA End_Group End_Group 2016-06-09 19:16:18.0 [epneff] added altLabel insert AltLabel (id: null text: MetOp-A language code: en); 2012-09-18 16:35:53.0 [saritz] Move Concepts add broader relation (METOP-A [8143808e-1005-4fed-a469-c2bd5f1521bf,32245] - METOP [8c192c86-d07c-4e7b-af8f-92aa4b40fca7,31825]); delete broader relation (null); 2012-09-18 16:35:22.0 [saritz] Cut Concepts delete broader relation (null); add broader relation (METOP-A [8143808e-1005-4fed-a469-c2bd5f1521bf,32245] - Trash Can/Platforms [6089b3e5-7db9-46e1-b73b-2d679f34abb4,40307]); LANYARD LANYARD was a photo-reconnaissance satellite that was operation between March 1963-July 1963. The images were used to produce maps and charts for the Department of Defense and other Federal Government mapping programs. President Clinton signed an Executive Order on 24 February 1995, directing the declassification of intelligence imagery acquired by the first generation of United States photo-reconnaissance satellites, including the systems code-named CORONA, ARGON and LANYARD. Additional information available at "http://edc.usgs.gov/guides/disp1.html" [Summary provided by USGS] ETALON SHIPS 2019-08-28 15:57:41.0 [sritz] Insert Concept add narrower relation (SHIPS [82a67b12-e99d-4c90-8a6a-a6f79d4c3c7b,345297] - Okeanos [4838472f-2b4c-4107-bd9e-3bf78a7c5562,369077]); 2019-01-29 21:46:32.0 [sritz] Remove Concepts delete narrower relation (null); 2019-01-29 21:46:09.0 [sritz] Insert Concept add narrower relation (SHIPS [82a67b12-e99d-4c90-8a6a-a6f79d4c3c7b,345297] - ARAON (Icebreaker Research Vessel [e6d3a1a1-6774-4be2-8456-40025d745e08,368449]); 2015-06-09 06:15:58.0 [aaleman] Insert Concept add narrower relation (SHIPS [82a67b12-e99d-4c90-8a6a-a6f79d4c3c7b,143897] - RSS JAMES CLARK ROSS [30585903-f838-4b9c-86c2-8778559475f7,158019]); 2013-06-11 20:05:54.0 [aaleman] Insert Concept add narrower relation (SHIPS [82a67b12-e99d-4c90-8a6a-a6f79d4c3c7b,73407] - R/V AKADEMIK M.A. LAVRENTYEV [cdc27a9f-6118-4ab8-bf2c-d762e6dbbbdf,105209]); 2013-05-24 19:51:13.0 [aaleman] Insert Concept add narrower relation (SHIPS [82a67b12-e99d-4c90-8a6a-a6f79d4c3c7b,73407] - R/V ONNURI [3ccb3423-b471-437e-87d0-e964702bd90f,105161]); 2012-10-16 20:04:32.0 [aaleman] Move Concepts add narrower relation (SHIPS [82a67b12-e99d-4c90-8a6a-a6f79d4c3c7b,31201] - B/O SG [bccde7bb-3a29-4919-85ce-0b8f446d707d,31215]); 2012-07-30 19:46:27.0 [aaleman] Insert Concept add narrower relation (SHIPS [82a67b12-e99d-4c90-8a6a-a6f79d4c3c7b,31201] - R/V ITALIA [e2e59fcb-be11-4ff2-bd7f-eee34a76aa45,40429]); 2012-07-30 19:46:25.0 [aaleman] Insert Concept add narrower relation (SHIPS [82a67b12-e99d-4c90-8a6a-a6f79d4c3c7b,31201] - R/V ITALICA [6cf9a0ac-18c6-492a-b302-62ad4c918fcf,40425]); 2012-07-14 00:44:39.0 [aaleman] Insert Concept add narrower relation (SHIPS [82a67b12-e99d-4c90-8a6a-a6f79d4c3c7b,31201] - R/V HERITAGE [bbb476e8-9e6a-461f-882d-a213213705f2,40339]); 2012-07-13 22:52:05.0 [aaleman] Insert Concept add narrower relation (SHIPS [82a67b12-e99d-4c90-8a6a-a6f79d4c3c7b,31201] - R/V Ivan Petrov [810bc419-c1ea-4f38-b05f-6471e3621274,40335]); 2012-06-29 20:40:35.0 [aaleman] Insert Concept add narrower relation (SHIPS [82a67b12-e99d-4c90-8a6a-a6f79d4c3c7b,31201] - R/V LOUIS S. ST. LAURENT [0d34806c-5288-4939-96e7-afdda39342fb,40293]); 2012-06-29 20:35:34.0 [aaleman] Insert Concept add narrower relation (SHIPS [82a67b12-e99d-4c90-8a6a-a6f79d4c3c7b,31201] - R/V OSHORO-MARU [d4fa5a8e-39fe-4d3c-b832-9e06469e1cc8,40289]); 2012-06-29 20:26:43.0 [aaleman] Insert Concept add narrower relation (SHIPS [82a67b12-e99d-4c90-8a6a-a6f79d4c3c7b,31201] - R/V ARAON [b86ba8f3-1d11-4603-8d5a-5633be4529c8,40285]); 2012-06-29 19:59:25.0 [aaleman] Insert Concept add narrower relation (SHIPS [82a67b12-e99d-4c90-8a6a-a6f79d4c3c7b,31201] - R/V PROFESSOR KHROMOV [5650f8fe-8db8-4bb1-927a-54a214d30ca1,40281]); RAE-B Spacecraft Brief Description This RAE-B mission was the second of a pair of Radio Astronomy Explorer satellites. It was placed into lunar orbit on June 15, 1973, to provide radio astronomical measurements of the planets, the sun, and the galaxy over the frequency range of 25 kHz to 13.1 MHz. The experiment complement consisted of two Ryle-Vonberg radiometers (nine channels each), three swept-frequency burst receivers (32 channels each), and an impedance probe for calibration. The experiment antennas consisted of a 229-m upper V-antenna pointed away from the moon; a 183-m lower V-antenna pointed toward the moon; and a 37-m dipole antenna parallel to the lunar surface. The lower V-antenna was extended to its full 229-m length in November 1974. The spacecraft body was a truncated cylinder 36.25 in. in diameter and approximately 31-in. high, with four fixed solar paddles. The maneuvering system consisted of a hydrazine velocity correction package, a cold gas attitude control system, and a solid fuel lunar insertion motor. Data were returned to the earth via either a low power UHF/(400 MHz) transmitter, in real time, or stored in an onboard tape recorder and transmitted to earth via a high power UHF transmitter (400 MHz). Two tape recorders provided backup storage. A VHF transmitter served primarily for range and range-rate measurements and as a backup. Commands were received on a VHF (148 MHz) receiver, which also was a part of the range and range-rate system. Spacecraft attitude was determined by (1) a solar aspect system, (2) a horizon sensor system, and (3) a panoramic attitude sensor system, and was accurate to 1 deg. The spacecraft was gravity gradient oriented (Z axis parallel to local vertical) and was equipped with libration dampers to damp out oscillations. For additional information, see J. K. Alexander et al., Astron. & Astrophys., v. 40, p. 365, 1975. Auxiliary Information Launch Date and Time : 1973-06-10 14:13:00 Epoch Date and Time : 1973-06-21 00:00:00 Orbit Type : Geocentric Apogee(km) : 1063.84 Perigee(km) : 1052.98 Inclination : 55.7 Date of last update : 1992-03-09 *** Note: For datasets information under this source name, select option 1 *** from the MD_MAIN menu, and then search by source. R/V WECOMA Equipped with laboratories to accommodate the various maritime scientists, the R/V Wecoma has been used to conduct research on marine environments and species. Group: Platform_Details Entry_ID: R/V WECOMA Group: Platform_Identification Platform_Category: In Situ Ocean-based Platforms Platform_Series_or_Entity: SHIPS Short_Name: R/V WECOMA End_Group Creation_Date: 2012-07-19 Online_Resource: http://www.shipops.oregonstate.edu/ops/wecoma/ Sample_Image: http://www.shipops.oregonstate.edu/ops/wecoma/Wecoma_Departing.jpg End_Group NEMO-SN1 NEutrino Mediterranean Observatory - Submarine Network 1 Group: Platform_Details Entry_ID: NEMO-SN1 Group: Platform_Identification Platform_Category: In Situ Ocean-based Platforms Platform_Series_or_Entity: OCEAN PLATFORM/OCEAN STATIONS Short_Name: NEMO-SN1 Long_Name: NEutrino Mediterranean Observatory - Submarine Network 1 End_Group Creation_Date: 2012-12-13 Online_Resource: http://roma2.rm.ingv.it/en/facilities/seafloor_multidisciplinary_observatories/2/sn-1 Sample_Image: http://roma2.rm.ingv.it/userfiles/image/risorse/OsservatoriSottomarini/SN1/DSCF0010.JPG End_Group 2013-02-21 21:30:01.0 [aaleman] Insert Concept add broader relation (NEMO-SN1 [83212677-16fc-42ab-9a23-cdbbacfa1d18,82687] - OCEAN PLATFORM/OCEAN STATIONS [6ee1cf85-aa14-4fe9-a915-a8022830d8a7,73557]); FERMI [Source: FERMI Project, http://fermi.gsfc.nasa.gov/ ] The Universe is home to numerous exotic and beautiful phenomena, some of which can generate almost inconceivable amounts of energy. Supermassive black holes, merging neutron stars, streams of hot gas moving close to the speed of light ... these are but a few of the marvels that generate gamma-ray radiation, the most energetic form of radiation, billions of times more energetic than the type of light visible to our eyes. What is happening to produce this much energy? What happens to the surrounding environment near these phenomena? How will studying these energetic objects add to our understanding of the very nature of the Universe and how it behaves? The Fermi Gamma-ray Space Telescope, formerly GLAST, will open this high-energy world to exploration and help us to answer these questions. With Fermi, astronomers will at long last have a superior tool to study how black holes, notorious for pulling matter in, can accelerate jets of gas outward at fantastic speeds. Physicists will be able to study subatomic particles at energies far greater than those seen in ground-based particle accelerators. And cosmologists will gain valuable information about the birth and early evolution of the Universe. For this unique endeavor, one that brings together the astrophysics and particle physics communities, NASA is teaming up with the U.S. Department of Energy and institutions in France, Germany, Japan, Italy and Sweden. General Dynamics was chosen to build the spacecraft. Fermi was launched June 11, 2008 at 12:05 pm EDT. Mission Objectives - Explore the most extreme environments in the Universe, where nature harnesses energies far beyond anything possible on Earth. - Search for signs of new laws of physics and what composes the mysterious Dark Matter. - Explain how black holes accelerate immense jets of material to nearly light speed. - Help crack the mysteries of the stupendously powerful explosions known as gamma-ray bursts. - Answer long-standing questions across a broad range of topics, including solar flares, pulsars and the origin of cosmic rays. Group: Platform_Details Entry_ID: FERMI Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Short_Name: FERMI Long_Name: Fermi Gamma-ray Space Telescope End_Group Group: Synonymous_Platform_Names Short_Name: GLAST End_Group Group: Platform_Associated_Instruments Short_Name: LAT End_Group Creation_Date: 2009-09-14 Online_Resource: http://fermi.gsfc.nasa.gov/ Online_Resource: http://www.nasa.gov/mission_pages/GLAST/main/index.html Online_Resource: http://nasascience.nasa.gov/missions/glast Sample_Image: http://nasascience.nasa.gov/missions/glast/graphic Group: Platform_Logistics Launch_Date: 2008-06-11 Primary_Sponsor: USA/NASA End_Group End_Group COSMOS 49 The rocket was launched from Plesetsk Space Center, 800 kilometers northeast of Moscow, and successfully brought the satellites on board, including OHB?s micro-satellite RUBIN-4-dsi, into their respective orbits. OHB, via its subsidiary COSMOS International Satellitenstart GmbH, organized and carried out the services associated with the launch of South Korean research satellite KAISTSAT-4, which was also on board. The orbital telematics experiment Rubin-4-dsi developed by OHG is located on the upper stage of the COSMOS and transmits information on the rocket?s acceleration, vibration load and position. Rubin will transmit this information to earth via e-mail using the Orbcomm satellite communications system. In this way, it will be possible to track the rocket in orbit reliably and without any data loss. RUBIN-4-dsi is the fourth micro-satellite from the RUBIN series developed and maintained by OHB. The first was launched in July 2000 and transmitted approximately 1,600 e-mails with measuring data from outer space. RUBIN-2, a much more complex follow-up model, and RUBIN-3 came at the end of 2002. Among other things, RUBIN communications technology can in future be used for communicating with satellites orbiting close to the earth without any data loss. Moreover, RUBIN can provide early information on whether a satellite was successfully put into orbit. For further information please contact: Danela Sell OHB-System AG Communication & Public Relations fon: +49.421.2020-620 fax: +49.421.2020-700 mail: dsell&#64ohb-system.de Additional information available at "http://www.fuchs-gruppe.com/ohb-system/News/presse/2709_03.html" SOLRAD-9 This NRL satellite was one of the Solrad series that began in 1960 to provide continuous coverage of solar radiation with a set of standard photometers. Solrad 9 was a spin-stabilized satellite oriented with its spin axis perpendicular to the sun-satellite line so that the 14 solar X-ray and UV photometers pointing radially outward from its equatorial belt viewed the sun with each revolution. General Information: Designation: 03141 / 68017A Launch date: 5 Mar 1968 Country of origin: United States Mission: Scientific (Observation of the Sun) Perigee/Apogee: 353/433 km Inclination: 59.3° Period: 92.4 min Launch vehicle: Scout #60 Decay: 16 Nov 1990 [Summary provided by The Satellite Encyclopedia] Group: Platform_Details Entry_ID: SOLRAD-9 Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Platform_Series_or_Entity: SOLRAD Short_Name: SOLRAD-9 Long_Name: Solar Radiation-9 End_Group Group: Synonymous_Platform_Names Short_Name: SOLRAD-9 End_Group Group: Platform_Associated_Instruments Short_Name: SXP End_Group Group: Orbit Orbit_Inclination: 59.3 degrees Period: 92.4 minutes Perigee: 353 km Apogee: 433 km End_Group Creation_Date: 2008-01-14 Online_Resource: http://stinet.dtic.mil/oai/oai?verb=getRecord&metadataPrefix=html&identifier=AD0686019 Sample_Image: http://www.designation-systems.net/dusrm/app3/1968-017a.jpg Group: Platform_Logistics Launch_Date: 1968-03-15 Primary_Sponsor: NASA End_Group End_Group APOLLO The Apollo program was designed to land humans on the Moon and bring them safely back to Earth. Six of the missions (Apollos 11, 12, 14, 15, 16, and 17) achieved this goal. Apollos 7 and 9 were Earth orbiting missions to test the Command and Lunar Modules, and did not return lunar data. Apollos 8 and 10 tested various components while orbiting the Moon, and returned photography of the lunar surface. Apollo 13 did not land on the Moon due to a malfunction, but also returned photographs. The six missions that landed on the Moon returned a wealth of scientific data and almost 400 kilograms of lunar samples. Experiments included soil mechanics, meteoroids, seismic, heat flow, lunar ranging, magnetic fields, and solar wind experiments. [Summary provided by NASA] Group: Platform_Details Entry_ID: APOLLO Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Platform_Series_or_Entity: APOLLO Short_Name: APOLLO End_Group Group: Synonymous_Platform_Names Short_Name: Apollo End_Group Creation_Date: 2008-01-17 Online_Resource: http://history.nasa.gov/apollo.html Online_Resource: http://nssdc.gsfc.nasa.gov/planetary/lunar/apollo.html Online_Resource: http://spaceflight.nasa.gov/history/apollo/ Online_Resource: http://www-pao.ksc.nasa.gov/history/apollo/apollo.htm Sample_Image: http://nssdc.gsfc.nasa.gov/planetary/lunar/apollo1_crew.gif Group: Platform_Logistics Launch_Date: 1967-01-27 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: NASA End_Group End_Group EXPLORER-9 Explorer 9 was the first in a series of 3.66-m inflatable spheres placed into orbit solely for the determination of atmospheric densities. The spacecraft consisted of alternating layers of aluminum foil and plastic film. Uniformly distributed over the aluminum surface were 5.1-cm dots of white paint for thermal control. Explorer 9 carried a 136-MHz beacon for tracking purposes. The beacon failed on the first orbit however, and the SAO Baker-Nunn camera network had to be relied upon for tracking. The spacecraft reentered the earth's atmosphere on April 9, 1964. Group: Platform_Details Entry_ID: EXPLORER-9 Group: Platform_Identification Platform_Category: Balloons/Rockets Short_Name: EXPLORER 9 Long_Name: Air Density Balloon End_Group Group: Synonymous_Platform_Names Short_Name: Explorer-9 End_Group Group: Platform_Associated_Instruments Short_Name: OPTICAL BEACON Short_Name: OPTICAL TRACKING Short_Name: SATELLITE RADIO BEACON End_Group Group: Orbit Orbit_Inclination: 38.91degrees Perigee: 545 km Apogee: 2225 km End_Group Creation_Date: 2007-08-21 Online_Resource: http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1961-004A Group: Platform_Logistics Launch_Date: 1961-02-16 Launch_Site: Wallops Flight Facility, Wallops Island, USA Primary_Sponsor: NASA End_Group End_Group GFO-1 GFO The mission objectives of GFO-1 (GEOSAT FOLLOW-ON-1) program the U.S. Navy's initiative to develop an operational family of radar altimeters satellites to maintain continuous ocean observation from the GEOSAT exact repeat orbit. GFO-1 data will be used for precise measurement of both mesoscale and basin-scale oceanography. The length and time scales of these processes are too large for conventional in-the-water oceanographic instrumentation configurations to measure. Satellite altimetry is the only known method by which oceanographers can precisely measure sea surface topography. The shape of the sea surface is the only physical variable directly measurable from space that is directly and simply connected to the large-scale movement of water and the total mass and volume of the ocean. [Source: NASA] 2016-06-09 18:40:02.0 [epneff] added altLabel insert AltLabel (id: null text: GFO language code: en); THEOS The THEOS contract with the Thai Ministry of Science and Technology's Space Agency (GISTDA) includes the production and launch of one optical observation satellite, as well as the development of the ground segment necessary to operate and control the satellite directly from Thailand. This is accompanied by state of the art facilities for image archiving and processing. The THEOS satellite is based on EADS Astrium's new generation of high performance AstroSat optical Earth observation satellites and benefits from the company's extensive experience in this field which started with the SPOT and MetOp satellites. As part of the THEOS contract, Thai engineers will join the Astrium development team and attend intensive space programme training. The company firmly believes that this cooperation contract paves the way for further development of GISTDA and space activities in Thailand. The THEOS payload features both high resolution in panchromatic mode (2m) and wide field of view in multi-spectral mode and has been tailored to Thailand's specific needs with a worldwide imaging capability. It will be launched in 2008 on a sun synchronous orbit at an altitude of around 820km. THEOS will be fully owned and operated by GISTDA and will provide Thailand with worldwide geo-referenced image products and image processing capabilities for applications in cartography, land use, agricultural monitoring, forestry management, coastal zone monitoring and flood risk management. THEOS will provide access to any part of Thailand in less than two days. [Source: EADS Astrium Home Page, http://www.astrium.eads.net/families/daily-life-benefits/remote-sensing/theos ] Group: Platform_Details Entry_ID: THEOS Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: THEOS Long_Name: Thai Earth Observation System End_Group Group: Platform_Associated_Instruments Short_Name: MS Short_Name: PAN End_Group Group: Orbit Orbit_Altitude: 822 km Orbit_Inclination: 98.7 Equator_Crossing: 10:00 AM Period: 101.4 Repeat_Cycle: 26 Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2008-07-03 Online_Resource: http://www.astrium.eads.net/families/daily-life-benefits/remote-sensing/theos Online_Resource: http://www.space-risks.com/SpaceData/index.php?id_page=8&Satellite_Name=THEOS Sample_Image: http://earth.esa.int/earthnetmedia/img/0e/tm_theos.jpg Group: Platform_Logistics Launch_Date: 2008-10-01 Launch_Site: Yasny Launch Base, Russia Primary_Sponsor: Thailand End_Group End_Group CBERS-4 [Summary provided by the Brazil National Institute for Space Research (INPE), http://www.cbers.inpe.br/en/programas/cbers3-4.htm ] Due to the success of CBERS-1 and 2, the two governments decided, in November 2002, to give continuity to the CBERS program by signing a new agreement for the development and launch of two more satellites, CBERS-3 and 4. Brazilian participation in this program will be enlarged up to 50%, thus taking Brazil to a condition of equality with its partner. CBERS-3 is expected to be launched in 2009, CBERS-4 in 2011. CBERS-3 and 4 satellites represent an evolution of CBERS-1 and 2. Four cameras will be present in the payload module, with improved geometrical and radiometric performance. They are: PanMux Camera-PANMUX, Multi-spectral Camera-MUXCAM, Scanning Medium Resolution Scanner-IRSCAM and Wide Field Imaging Camera-WFICAM. The orbits of the two satellites will be the same as for CBERS-1 and 2. Group: Platform_Details Entry_ID: CBERS-4 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: CBERS (China-Brazil Earth Resources Satellite) Short_Name: CBERS-4 Long_Name: China-Brazil Earth Resource Satellite 4 End_Group Group: Platform_Associated_Instruments Short_Name: IRS (CBERS) Short_Name: WFI (CBERS 3,4) Short_Name: PANMUX Short_Name: MUXCAM End_Group Group: Orbit Orbit_Altitude: 778 km Orbit_Inclination: 98.5 degrees Repeat_Cycle: 26 days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2008-08-19 Online_Resource: http://www.cbers.inpe.br/en/programas/cbers3-4.htm Group: Platform_Logistics Launch_Date: 2011-01-01 Launch_Site: Taiyuan Space Launch Center, China Primary_Sponsor: Brazil National Institute for Space Research (INPE) Primary_Sponsor: China National Space Administration End_Group End_Group DMSP 5D-3/F18 [Text Source: NASA Spaceflight.com, "Atlas’ 600th Mission launches with DMSP F18 from Vandenberg", 2009-10-18, http://www.nasaspaceflight.com/2009/10/live-atlas-600th-mission-launch-dmsp-f18-vandenberg/ ] The Defense Meteorological Satellite Program F18 (DMSP F18) satellite will help the Air Force provide “strategic and tactical weather prediction … to aide the U.S. military in planning operations at sea, on land, and in the air,” notes the ULA mission over presentation. Furthermore, “DMSP is a space- and ground-based system to collect and disseminate timely global environmental data to the Department of Defense and other governmental agencies.” DMSP F18 will provide viable data on soil moisture, surface temperatures, and cloud cover around the globe via its multitude of onboard sensors and polar orbit. The presentation goes on to discuss some specifics of the DMSP satellite system, of which F18 is a part. “DMSP satellites ’see’ environmental features such as clouds, bodies of water, snow, fire, and pollution in the visual and infrared spectra.” The satellite system can monitor global water temperatures, cloud cover, water currents, and ocean surface characteristics during their 101-minute orbital period around Earth. This, coupled with their polar and “sun-synchronous” orbits, allows each DMSP weather satellite to monitor nearly the entire globe every six hours. The data collected by the satellites is transmitted to the ground where a team of meteorologists interpret the data and disseminate the information for the U.S. military, which in turn uses the data to plan and conduct U.S. military operations around the globe. In addition to DMSP F18, two more DMSP weather satellites are awaiting launch. These satellites are currently stored at Space Systems’ operations in Sunnyvale, California. They will be transported to Vandenberg upon the request of the Air Force for launch operations. Group: Platform_Details Entry_ID: DMSP 5D-3/F18 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: DMSP (Defense Meteorological Satellite Program) Short_Name: DMSP 5D-3/F18 Long_Name: Defense Meteorological Satellite Program-F18 End_Group Creation_Date: 2009-10-21 Online_Resource: http://www.nasaspaceflight.com/2009/10/live-atlas-600th-mission-launch-dmsp-f18-vandenberg/ Group: Platform_Logistics Launch_Date: 2009-10-18 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: Department of Defense-Department of the Air Force (United States) End_Group End_Group SUOMI-NPP NPP Suomi NPP [Text from the NPP Launch Blog, https://www.nasa.gov/mission_pages/NPP/launch/launch_blog.html ] The NPOESS Preparatory Project (NPP) spacecraft lifted off aboard a United Launch Alliance Delta II rocket from Space Launch Complex 2 at Vandenberg Air Force Base in California on Oct. 28, 2011 at 5:48 a.m. EDT. The NPP spacecraft will build on more than four decades Earth observation to help us better understand our climate. The National Polar-Orbiting Operational Environmental Satellite System (NPOESS) Preparatory Project (NPP) is a joint mission involving the National Aeronautics and Space Administration's (NASA) and the NPOESS Integrated Program Office (IPO). The NPP mission collects and distributes remotely-sensed land, ocean, and atmospheric data to the meteorological and global climate change communities as the responsibility for these measurements transitions from existing Earth-observing missions such as Aqua, Terra and Aura, to the NPOESS. It will provide atmospheric and sea surface temperatures, humidity sounding, land and ocean biological productivity, and cloud and aerosol properties. For the IPO, NPP provides risk reduction with an opportunity to demonstrate and validate new instruments and processing algorithms, as well as to demonstrate and validate aspects of the NPOESS command, control, communications and ground processing capabilities prior to the launch of the first NPOESS spacecraft. More Information: https://www.jpss.noaa.gov Group: Platform_Details Entry_ID: SUOMI-NPP Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: Joint Polar Satellite System (JPSS) Short_Name: SUOMI-NPP Long_Name: Suomi National Polar-orbiting Partnership End_Group Group: Platform_Associated_Instruments Short_Name: CRIMSS Short_Name: ATMS Short_Name: CRIS-NPOESS Short_Name: OMPS Short_Name: VIIRS Short_Name: CERES-FM5 End_Group Group: Orbit Repeat_Cycle: 16-day Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2009-02-27 Online_Resource: https://www.jpss.noaa.gov/ Online_Resource: https://www.nasa.gov/mission_pages/NPP/main/index.html Group: Platform_Logistics Launch_Date: 2011-10-28 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: USA/NASA Primary_Sponsor: USA/NOAA End_Group End_Group 2019-10-03 20:34:49.0 [sritz] update Definition ([Text from the NPP Launch Blog, https://www.nasa.gov/mission_pages/NPP/launch/launch_blog.html ] The NPOESS Preparatory Project (NPP) spacecraft lifted off aboard a United Launch Alliance Delta II rocket from Space Launch Complex 2 at Vandenberg Air Force Base in California on Oct. 28, 2011 at 5:48 a.m. EDT. The NPP spacecraft will build on more than four decades Earth observation to help us better understand our climate. The National Polar-Orbiting Operational Environmental Satellite System (NPOESS) Preparatory Project (NPP) is a joint mission involving the National Aeronautics and Space Administration's (NASA) and the NPOESS Integrated Program Office (IPO). The NPP mission collects and distributes remotely-sensed land, ocean, and atmospheric data to the meteorological and global climate change communities as the responsibility for these measurements transitions from existing Earth-observing missions such as Aqua, Terra and Aura, to the NPOESS. It will provide atmospheric and sea surface temperatures, humidity sounding, land and ocean biological productivity, and cloud and aerosol properties. For the IPO, NPP provides risk reduction with an opportunity to demonstrate and validate new instruments and processing algorithms, as well as to demonstrate and validate aspects of the NPOESS command, control, communications and ground processing capabilities prior to the launch of the first NPOESS spacecraft. More Information: https://www.jpss.noaa.gov Group: Platform_Details Entry_ID: SUOMI-NPP Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: Joint Polar Satellite System (JPSS) Short_Name: SUOMI-NPP Long_Name: Suomi National Polar-orbiting Partnership End_Group Group: Platform_Associated_Instruments Short_Name: CRIMSS Short_Name: ATMS Short_Name: CRIS-NPOESS Short_Name: OMPS Short_Name: VIIRS Short_Name: CERES-FM5 End_Group Group: Orbit Repeat_Cycle: 16-day Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2009-02-27 Online_Resource: https://www.jpss.noaa.gov/ Online_Resource: https://www.nasa.gov/mission_pages/NPP/main/index.html Group: Platform_Logistics Launch_Date: 2011-10-28 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: USA/NASA Primary_Sponsor: USA/NOAA End_Group End_Group); delete Resource (null); 2016-06-09 19:01:57.0 [epneff] added altLabel insert AltLabel (id: null text: Suomi NPP language code: en); insert AltLabel (id: null text: NPP language code: en); SN-4 2013-02-21 21:58:53.0 [aaleman] Insert Concept add broader relation (SN-4 [85e347f2-d65d-4941-a252-0b0c55653b37,82691] - OCEAN PLATFORM/OCEAN STATIONS [6ee1cf85-aa14-4fe9-a915-a8022830d8a7,73557]); Forcing-LSM 2014-05-30 09:14:35.0 [128.183.164.42] SR Added new model. insert AltLabel (id: null text: Forcing data for Land Surface Model language code: en); 2014-05-30 09:14:04.0 [128.183.164.42] Insert Concept add broader relation (Forcing-LSM [862e790e-d42f-433a-8561-107562aceb64,106425] - Models [113ecbc2-ab36-4d58-a96c-a6ce0106e749,73395]); GOES-9 GOES 9 was launched on May 23, 1995. GOES-9, which is currently partially operational, is being provided to the Japanese Meteorological Agency to replace their failing geostationary satellite. GOES I-M represents the next generation of meteorological satellites and introduces two new features. The first feature, flexible scan, offers small-scale area imaging that lets meteorologists take pictures of local weather trouble spots. This allows them to improve short-term forecasts over local areas. The second feature, simultaneous and independent imaging and sounding, is designed to allow weather forecasters to use multiple measurements of weather phenomena to increase the accuracy of their forecasts. Each satellite in the series carries two major instruments: an Imager and a Sounder. These instruments acquire high resolution visible and infrared data, as well as temperature and moisture profiles of the atmosphere. They continuously transmit these data to ground terminals where the data are processed for rebroadcast to primary weather services both in the United States and around the world, including the global research community. The GOES I-M mission is scheduled to run from the mid-1990s into the first decade of the 21st century. Each element of the mission has been designed to meet all in-orbit performance requirements for at least five years. The GOES I-M system performs the following basic functions: + Acquisition, processing, and dissemination of imaging and sounding data. + Acquisition and dissemination of Space Environment Monitor (SEM) data. + Reception and relay of data from ground-based Data Collection Platforms (DCPs) that are situated in carefully selected urban and remote areas to the NOAA Command and Data Acquisition (CDA) station. + Continuous relay of Weather Facsimile (WEFAX) and other data to users, independent of all other functions. + Relay of distress signals from people, aircraft, or marine vessels to the search and rescue ground stations of the Search and Rescue Satellite Aided Tracking (SARSAT) system. GOES provides the instantaneous relay functions for the SARSAT system. A dedicated search and rescue transponder on board GOES is designed to detect emergency distress signals originating from Earth-based sources. These unique identification signals are normally combined with signals received by a low-Earth orbiting satellite system and relayed to a search and rescue ground terminal. The combined data are used to perform effective search and rescue operations. The GOES I-M system serves a region covering the central and eastern Pacific Ocean; North, Central, and South America; and the central and western Atlantic Ocean. Pacific coverage includes Hawaii and the Gulf of Alaska. This is accomplished by two satellites, GOES West located at 135 west longitude and GOES East at 75 west longitude. A common ground station, the CDA station located at Wallops, Virginia, supports the interface to both satellites. The NOAA Satellite Operations Control Center (SOCC), in Suitland, Maryland, provides spacecraft scheduling, health and safety monitoring, and engineering analyses. Delivery of products involves ground processing of the raw instrument data for radiometric calibration and Earth location information, and retransmission to the satellite for relay to the data user community. The processed data are received at the control center and disseminated to the National Weather Service's (NWS) National Meteorological Center, Camp Springs, Maryland, and NWS forecast offices, including the National Hurricane Center, Miami, Florida, and the National Severe Storms Forecast Center, Kansas City, Missouri. Processed data are also received by Department of Defense installations, universities, and numerous private commercial users. *The GOES-9 satellite was replaced by GOES-10 in July 1998* MAIN SPACECRAFT DESIGN ELEMENTS Mission life 5 years, minimum Dimensions Main body 2 meter (7 foot) cube Deployed length 27 meters (88 feet) Weight 2100 kg (4600 lb) Orbit Geosynchronous Altitude 36,000 km (22,000 mi) Longitude 75W and 135W Latitude equatorial, within 0.5 degree Power 1050 watts @ 42 volts, solar array; battery backup Launch vehicle Atlas-I/Centaur (GOES-I/K), Atlas-II/Centaur (GOES-L/M) Communications Imager and Sounder in GVAR format at 2.1 Mbits/sec GOES-I/M IMAGER The GOES Imager is a multi-channel instrument designed to sense radiant and solar-reflected energy from sampled areas of the Earth. The multi-element spectral channels simultaneously sweep east-west and west-east along a north-to-south path by means of a two-axis mirror scan system. The instrument can produce full-Earth disc images, sector images that contain the edges of the Earth, and various sizes of area scans completely enclosed within the Earth scene using a new flexible scan system. Scan selection permits rapid continuous viewing of local areas for monitoring of mesoscale (regional) phenomena and accurate wind determination. IMAGER CHANNELS AND PRODUCTS CHANNEL 1 2* 3* 4 5* WAVELENGTH (um) 0.65 3.9 6.7 11 12 PRODUCT Clouds x x x x x Water Vapor* x x x Surface Temp. o x o Winds x x x Albedo + IR Flux x o x o Fires + Smoke x x o o KEY: * = new operational data x = primary channel o = secondary channel GOES-I/M SOUNDER The GOES Sounder is a 19-channel discrete-filter radiometer covering the spectral range from the visible channel wavelengths to 15 microns. It is designed to provide data from which atmospheric temperature and moisture profiles, surface and cloud-top temperatures, and ozone distribution can be deduced by mathematical analysis. It operates independently of and simultaneously with the Imager, using a similarly flexible scan system. The Sounder's multi-element detector array assemblies simultaneously sample four separate fields or atmospheric columns. A rotating filter wheel, which brings spectral filters into the optical path of the detector array, provides the infrared channel definition. PRODUCTS, RESOLUTION AND ACCURACY RESOLUTION (km) ACCURACY Vert. Horiz. Absolute Relative PRODUCT TEMPERATURE Profile 3-5 50 2-3 K 1 K Land --- 10 2 K 1 K Sea --- 10 1 K 0.5 K MOISTURE Profile 2-4 50 30% 20% Total --- 10 20% 10% Motion 3 layers 50 6 m/sec 3 m/sec CLOUD Height 2 layers 10 50 mb 25 mb Amount total 10 15% 5% OZONE* Total --- 50 30% 15% Motion 1 layer 50 10 m/sec 5 m/sec IR Flux* total 50 10 W/m^2 3 W/m^2 KEY: * = potential future product 2017-09-01 17:10:36.0 [sritz] insert Definition (id: null text: GOES 9 was launched on May 23, 1995. GOES-9, which is currently partially operational, is being provided to the Japanese Meteorological Agency to replace their failing geostationary satellite. GOES I-M represents the next generation of meteorological satellites and introduces two new features. The first feature, flexible scan, offers small-scale area imaging that lets meteorologists take pictures of local weather trouble spots. This allows them to improve short-term forecasts over local areas. The second feature, simultaneous and independent imaging and sounding, is designed to allow weather forecasters to use multiple measurements of weather phenomena to increase the accuracy of their forecasts. Each satellite in the series carries two major instruments: an Imager and a Sounder. These instruments acquire high resolution visible and infrared data, as well as temperature and moisture profiles of the atmosphere. They continuously transmit these data to ground terminals where the data are processed for rebroadcast to primary weather services both in the United States and around the world, including the global research community. The GOES I-M mission is scheduled to run from the mid-1990s into the first decade of the 21st century. Each element of the mission has been designed to meet all in-orbit performance requirements for at least five years. The GOES I-M system performs the following basic functions: + Acquisition, processing, and dissemination of imaging and sounding data. + Acquisition and dissemination of Space Environment Monitor (SEM) data. + Reception and relay of data from ground-based Data Collection Platforms (DCPs) that are situated in carefully selected urban and remote areas to the NOAA Command and Data Acquisition (CDA) station. + Continuous relay of Weather Facsimile (WEFAX) and other data to users, independent of all other functions. + Relay of distress signals from people, aircraft, or marine vessels to the search and rescue ground stations of the Search and Rescue Satellite Aided Tracking (SARSAT) system. GOES provides the instantaneous relay functions for the SARSAT system. A dedicated search and rescue transponder on board GOES is designed to detect emergency distress signals originating from Earth-based sources. These unique identification signals are normally combined with signals received by a low-Earth orbiting satellite system and relayed to a search and rescue ground terminal. The combined data are used to perform effective search and rescue operations. The GOES I-M system serves a region covering the central and eastern Pacific Ocean; North, Central, and South America; and the central and western Atlantic Ocean. Pacific coverage includes Hawaii and the Gulf of Alaska. This is accomplished by two satellites, GOES West located at 135 west longitude and GOES East at 75 west longitude. A common ground station, the CDA station located at Wallops, Virginia, supports the interface to both satellites. The NOAA Satellite Operations Control Center (SOCC), in Suitland, Maryland, provides spacecraft scheduling, health and safety monitoring, and engineering analyses. Delivery of products involves ground processing of the raw instrument data for radiometric calibration and Earth location information, and retransmission to the satellite for relay to the data user community. The processed data are received at the control center and disseminated to the National Weather Service's (NWS) National Meteorological Center, Camp Springs, Maryland, and NWS forecast offices, including the National Hurricane Center, Miami, Florida, and the National Severe Storms Forecast Center, Kansas City, Missouri. Processed data are also received by Department of Defense installations, universities, and numerous private commercial users. *The GOES-9 satellite was replaced by GOES-10 in July 1998* MAIN SPACECRAFT DESIGN ELEMENTS Mission life 5 years, minimum Dimensions Main body 2 meter (7 foot) cube Deployed length 27 meters (88 feet) Weight 2100 kg (4600 lb) Orbit Geosynchronous Altitude 36,000 km (22,000 mi) Longitude 75W and 135W Latitude equatorial, within 0.5 degree Power 1050 watts @ 42 volts, solar array; battery backup Launch vehicle Atlas-I/Centaur (GOES-I/K), Atlas-II/Centaur (GOES-L/M) Communications Imager and Sounder in GVAR format at 2.1 Mbits/sec GOES-I/M IMAGER The GOES Imager is a multi-channel instrument designed to sense radiant and solar-reflected energy from sampled areas of the Earth. The multi-element spectral channels simultaneously sweep east-west and west-east along a north-to-south path by means of a two-axis mirror scan system. The instrument can produce full-Earth disc images, sector images that contain the edges of the Earth, and various sizes of area scans completely enclosed within the Earth scene using a new flexible scan system. Scan selection permits rapid continuous viewing of local areas for monitoring of mesoscale (regional) phenomena and accurate wind determination. IMAGER CHANNELS AND PRODUCTS CHANNEL 1 2* 3* 4 5* WAVELENGTH (um) 0.65 3.9 6.7 11 12 PRODUCT Clouds x x x x x Water Vapor* x x x Surface Temp. o x o Winds x x x Albedo + IR Flux x o x o Fires + Smoke x x o o KEY: * = new operational data x = primary channel o = secondary channel GOES-I/M SOUNDER The GOES Sounder is a 19-channel discrete-filter radiometer covering the spectral range from the visible channel wavelengths to 15 microns. It is designed to provide data from which atmospheric temperature and moisture profiles, surface and cloud-top temperatures, and ozone distribution can be deduced by mathematical analysis. It operates independently of and simultaneously with the Imager, using a similarly flexible scan system. The Sounder's multi-element detector array assemblies simultaneously sample four separate fields or atmospheric columns. A rotating filter wheel, which brings spectral filters into the optical path of the detector array, provides the infrared channel definition. PRODUCTS, RESOLUTION AND ACCURACY RESOLUTION (km) ACCURACY Vert. Horiz. Absolute Relative PRODUCT TEMPERATURE Profile 3-5 50 2-3 K 1 K Land --- 10 2 K 1 K Sea --- 10 1 K 0.5 K MOISTURE Profile 2-4 50 30% 20% Total --- 10 20% 10% Motion 3 layers 50 6 m/sec 3 m/sec CLOUD Height 2 layers 10 50 mb 25 mb Amount total 10 15% 5% OZONE* Total --- 50 30% 15% Motion 1 layer 50 10 m/sec 5 m/sec IR Flux* total 50 10 W/m^2 3 W/m^2 KEY: * = potential future product language code: en); 2017-09-01 16:46:18.0 [sritz] Insert Concept add broader relation (GOES-9 [8651726e-1f93-4a65-9e09-4be1e3075e5d,310107] - GOES [6e332c25-caeb-4917-afb6-af757bcecd72,310071]); CLIMATE MODELS 2015-08-10 14:42:15.0 [gee-cee] Insert Concept add broader relation (CLIMATE MODELS [8680cb49-1637-4a47-a5fd-f39d4e618e45,158205] - Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215]); NCEP-CFSV2 2015-08-10 18:55:20.0 [epneff] Added long name insert AltLabel (id: null text: NCEP Climate Forecast System Version 2 language code: en); 2015-08-10 18:54:57.0 [epneff] Insert Concept add broader relation (NCEP-CFSV2 [86ee0e30-96d0-4bb4-9ee6-a24aa0e0234b,158251] - Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215]); CLARREO [Source: NASA Science Mission Homepage, https://clarreo.larc.nasa.gov/ ] The Climate Absolute Radiance and Refractivity Observatory (CLARREO) mission will monitor the pulse of the Earth to better understand climate change. The foundation for CLARREO is the ability to produce highly accurate and trusted climate records. These tested climate records can be used to lay the groundwork for informed decisions on mitigation and adaptation policies that address the effects of climate change on society. Group: Platform_Details Entry_ID: CLARREO Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NASA Decadal Survey Short_Name: CLARREO Long_Name: Climate Absolute Radiance and Refractivity Observatory End_Group Group: Platform_Associated_Instruments Short_Name: INFRARED INSTRUMENT SUITE Short_Name: GNSS-RO RECEIVER Short_Name: REFLECTED SOLAR SUITE End_Group Group: Orbit Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2009-02-25 Online_Resource: https://clarreo.larc.nasa.gov/ Group: Platform_Logistics Primary_Sponsor: USA/NASA End_Group End_Group 2020-01-03 22:46:11.0 [sritz] update Definition (https://clarreo.larc.nasa.gov/); 2020-01-03 22:45:34.0 [sritz] update Definition ([Source: NASA Science Mission Homepage, https://clarreo.larc.nasa.gov/ ] The Climate Absolute Radiance and Refractivity Observatory (CLARREO) mission will monitor the pulse of the Earth to better understand climate change. The foundation for CLARREO is the ability to produce highly accurate and trusted climate records. These tested climate records can be used to lay the groundwork for informed decisions on mitigation and adaptation policies that address the effects of climate change on society. Group: Platform_Details Entry_ID: CLARREO Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NASA Decadal Survey Short_Name: CLARREO Long_Name: Climate Absolute Radiance and Refractivity Observatory End_Group Group: Platform_Associated_Instruments Short_Name: INFRARED INSTRUMENT SUITE Short_Name: GNSS-RO RECEIVER Short_Name: REFLECTED SOLAR SUITE End_Group Group: Orbit Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2009-02-25 Online_Resource: https://clarreo.larc.nasa.gov/ Group: Platform_Logistics Primary_Sponsor: USA/NASA End_Group End_Group); GCOM-W1 SHIZUKU The GCOM-W mission aims to establish the global and long-term observation system to collect data, which is needed to understand mechanisms of climate and water cycle variations, and demonstrate its utilization. AMSR2 onboard the first generation of the GCOM-W satellite will continue Aqua/AMSR-E observations of water vapor, cloud liquid water, precipitation, SST, sea surface wind speed, sea ice concentration, snow depth, and soil moisture. More Information: http://global.jaxa.jp/projects/sat/gcom_w/ GCOM-W1/AMSR2 characteristics Scan and rate : Conical scan at 40 rpm Antenna : Offset parabola with 2.0m dia. Swath width : 1450km Incidence angle: Nominal 55 degrees Digitization : 12bits Dynamic range : 2.7-340K Polarization : Vertical and horizontal Group: Platform_Details Entry_ID: GCOM-W1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: GCOM-W1 Long_Name: Global Change Observation Mission 1st-Water End_Group Creation_Date: 2012-08-31 End_Group 2018-03-14 18:54:07.0 [sritz] insert AltLabel (id: null category: null text: SHIZUKU language code: en); 2018-03-14 18:53:27.0 [sritz] update Definition (The GCOM-W mission aims to establish the global and long-term observation system to collect data, which is needed to understand mechanisms of climate and water cycle variations, and demonstrate its utilization. AMSR2 onboard the first generation of the GCOM-W satellite will continue Aqua/AMSR-E observations of water vapor, cloud liquid water, precipitation, SST, sea surface wind speed, sea ice concentration, snow depth, and soil moisture. More Information: http://global.jaxa.jp/projects/sat/gcom_w/ GCOM-W1/AMSR2 characteristics Scan and rate : Conical scan at 40 rpm Antenna : Offset parabola with 2.0m dia. Swath width : 1450km Incidence angle: Nominal 55 degrees Digitization : 12bits Dynamic range : 2.7-340K Polarization : Vertical and horizontal Group: Platform_Details Entry_ID: GCOM-W1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: GCOM-W1 Long_Name: Global Change Observation Mission 1st-Water End_Group Creation_Date: 2012-08-31 End_Group); 2015-08-21 18:47:04.0 [mpmorahan] insert AltLabel (id: null text: Global Change Observation Mission 1st-Water language code: en); 2012-09-05 20:54:13.0 [mpmorahan] Insert Concept add broader relation (GCOM-W1 [8781da14-5ced-4d64-81cd-8daa10a1c30d,40563] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,31221]); SUNSAT [Text Source: University of Stellenbosch] [Image Source: NASA ILRS, http://ilrs.gsfc.nasa.gov/satellite_missions/list_of_satellites/suns_general.html ] Sunsat is a micro-satellite built by post-graduate engineering students in the Electronic Systems Laboratory, in the Department of Electrical and Electronic Engineering at the University of Stellenbosch.It was launched in 1999 on a Delta II Launch Vehicle. Payloads include NASA experiments, Radio Amateur communications, a high resolution imager, precision attitude control, and school experiments. SUNSAT was launched on the 11th attempt at 10h29:45 GMT on 23 February 1999 and went out of service on January 19, 2001 due to hardware failure. Additional information available at http://ilrs.gsfc.nasa.gov/satellite_missions/list_of_satellites/suns_general.html Group: Platform_Details Entry_ID: SUNSAT Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: SUNSAT Long_Name: Stellenbosch University Satellite End_Group Group: Synonymous_Platform_Names Short_Name: SUNSAT Short_Name: OSCAR 35 Short_Name: 25636 End_Group Group: Platform_Associated_Instruments Short_Name: MAGNETOMETERS Short_Name: GPS RECEIVERS End_Group Group: Orbit Orbit_Inclination: 96.5 degrees Period: 100.0 minutes Perigee: 644.0 km Apogee: 857.0 km End_Group Creation_Date: 2007-11-28 Online_Resource: http://ilrs.gsfc.nasa.gov/satellite_missions/list_of_satellites/suns_general.html Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1999-008C Sample_Image: http://ilrs.gsfc.nasa.gov/images/sunsat.gif Group: Platform_Logistics Launch_Date: 1999-02-23 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: Stellenbosch University Primary_Sponsor: Republic of South Africa End_Group End_Group NSF/NCAR GV HIAPER 2018-06-06 21:02:15.0 [sritz] insert WeightedRelation (id: null related concept uuid: 8f368c9f-5dd7-42f6-8cd1-086c23ef6cdd relationship type: null relationship value: null generated by: null); 2018-05-23 15:36:11.0 [sritz] insert AltLabel (id: null category: primary text: NSF/NCAR Gulfstream GV Aircraft language code: en); 2018-05-23 15:35:22.0 [sritz] Insert Concept add broader relation (NSF/NCAR GV HIAPER [879d697c-381f-45df-a48d-2d9095bc5c54,367611] - Aircraft [227d9c3d-f631-402d-84ed-b8c5a562fc27,344663]); VIC-LSM 2014-05-30 09:16:30.0 [128.183.164.42] SR Added new model. insert AltLabel (id: null text: Variable Infiltration Capacity (VIC) Land Surface Model language code: en); 2014-05-30 09:16:04.0 [128.183.164.42] Insert Concept add broader relation (VIC-LSM [87a9b8ff-5da4-4a9e-815b-2564a1af2719,106433] - Models [113ecbc2-ab36-4d58-a96c-a6ce0106e749,73395]); K1 2015-09-14 14:19:34.0 [mpmorahan] insert AltLabel (id: null text: Kalpana-1 language code: en); 2015-09-14 14:15:50.0 [mpmorahan] Insert Concept add broader relation (K1 [87daf1d5-4f7c-40e9-8d31-4c816c320029,158397] - IRS (Indian Remote Sensing Satellite) [3e8bc0c6-f599-4e23-9535-449af00edd61,143483]); Elektro-L 2019-12-31 17:24:56.0 [sritz] Insert Concept add narrower relation (Elektro-L [882c16a9-0bc6-4773-8066-e25ea8de3c9d,559581] - Elektro-L N3 [2c780dff-fce3-4625-8b89-a7cd2d64d6ec,559585]); 2019-12-31 17:24:12.0 [sritz] Move Concepts add narrower relation (Elektro-L [882c16a9-0bc6-4773-8066-e25ea8de3c9d,559581] - Elektro-L N1 [6d0d4c3e-acfb-4bfd-ab0d-4478e18e4b19,541909]); 2019-12-31 17:23:43.0 [sritz] Insert Concept add broader relation (Elektro-L [882c16a9-0bc6-4773-8066-e25ea8de3c9d,559581] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,541501]); Meteor-2 The Russian Meteor-2 series of spacecraft are polar-orbiting weather satellites designed to provide continuous daily coverage of the Earth's surface and weather patterns. The Meteor-2 provides global data on the distribution of clouds, snow and ice, radiation fluxes, atmospheric temperature, humidity sounding data, cloud-top heights and sea-surface temperature. The series has been of particular importance in providing information to Russian ships on weather systems and sea-ice conditions. Typically, two Meteor satellites are in orbit at the same time to cover almost 80% of the Earth's surface in 6 hours. The Meteor-2 instrumentation consists of (1) three television-type visible and infrared scanners, (2) an 8-channel scanning radiometer, and (3) a radiation-flux device for measuring radiation flux densities in near-space. The two visible scanners operate in the 0.5-0.7 micrometer region and has a swath width of 2100 and 2400 km at a resolution of 2 and 1 km, respectively. These scanners provide images and mosaics of arctic and antarctic oceans. The IR scanner operates in the 8-12 micrometer range with a swath width of 2600 km at a resolution of 8 km. The IR scanner provides imagery of clouds and surface. The 8-channel infrared radiometer operates in the 11.1 to 18.7 micrometer range with a swath of 1000 km at 30 km resolution. This instrument provides atmospheric sounding data and total ozone content. Group: Platform_Details Entry_ID: METEOR-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: METEOR Short_Name: METEOR-2 End_Group Group: Synonymous_Platform_Names Short_Name: METEOR-2 End_Group Group: Orbit Orbit_Inclination: 81.30 deg Period: 102.70 min Perigee: 876 km Apogee: 893 km End_Group Creation_Date: 2007-10-11 Online_Resource: http://www.astronautix.com/craft/meteor2.htm Sample_Image: http://www.astronautix.com/graphics/m/meteor2.jpg Group: Platform_Logistics Design_Life: 1 YEAR Primary_Sponsor: Russia End_Group End_Group 2015-05-08 18:51:57.0 [saritz] update PrefLabel (Meteor-2); KOMPSAT-2 KOMPSAT-2 (also referred to as Arirang-2 by South Korea) was developed by KARI (Korea Aerospace Research Institute) to continue the observation program of the KOMPSAT-1 mission. The main mission objectives of the KOMPSAT-2 are to provide a surveillance capability for large-scale disasters by acquiring high-resolution imagery for GIS (Geographic Information Systems) applications. The spacecraft design is based on the KOMPSAT-1 heritage making extensive use of existing hardware, software, tools, and facilities; it allows parallel integration of the payload, equipment, and propulsion modules. The KOMPSAT-2 bus structure consists of the five modules: SMS (Structure and Mechanisms Subsystem), TCS (Thermal ConTrol Subsystem), AOCS (Attitude and Orbit Control Subsystem), TC&R (Telemetry Command and Ranging) subsystem, EPS (Electrical Power Subsystem), PS (Propulsion Subsystem), and the FSW (Flight Software) element. The AOCS provides three-axis stabilization (3-axis control with zero momentum bias system) with high accuracy for roll, pitch and yaw pointing. Star trackers, gyro reference assemblies, three-axis magnetometers, magnetic torquers and reaction wheels are used for attitude sensing and control. The pointing accuracy is < 0.025º in roll and pitch, and 0.08º in yaw. The pointing knowledge is 0.020º in roll and pitch, and 0.045º in yaw. The spacecraft platform offers a cross-track body-pointing capability through roll maneuvers (up to ±45º). The propulsion subsystem makes use of re-used components (hydrazine monopropellant thrusters with blowdown pressure-feed system, 73 kg propellant). The spacecraft mass is 800 kg (including propellant), the S/C size is hexagonal: 1.85 m diameter x 2.6 m in height (6.8 m length in deployed configuration), the power is 955 W (EOL) provided by two solar arrays (GaAs cell technology). A super NiCd battery has a capacity of 30 Ah for eclipse phase support. The S/C design life is three years. EADS Astrium has been selected by KARI to support the platform development and manufacture of KOMPSAT-2. Launch: A launch of the KOMPSAT-2 spacecraft took place on July 28, 2006 with a Rockot-KM launch vehicle of Eurockot Launch Services from Plesetsk, Russia. Orbit: Sun-synchronous circular orbit, altitude = 685 km, inclination = 98.13º, period = 98.46 min, the mean local time of the ascending node is at 10:50 hours. The KOMPSAT-2 orbit is identical to that of KOMPSAT-1 but with a different phase (180º apart). RF communications: Onboard storage capacity of 96 Gbit (BOL) and 64 Gbit (EOL) for image data. S-band (TT&C) and X-band (payload data at 8.205 GHz downlink frequency) communications are provided for all data transmission to the ground (real-time and playback), the downlink data rate is 320 Mbit/s (QPSK modulation). Encryption of image data. The CCSDS communication protocols are implemented. The S-band data rates are: 2 kbit/s uplink and 1.5 Mbit/s downlink. Mission status: The KOMPSAT-2 spacecraft and its payload are operating nominally as of 2008. • KOMPSAT-2 completed its commissioning phase in late September 2006 and started its nominal operations phase in October 2006. • In August, 2006, KOMPSAT-2 had provided its first images. • On Oct. 24, 2005, KARI has made Spot Image (France) exclusive distributor of imagery from the KOMPSAT-2 Earth observation satellite - except for customers from Korea, the United States, and the Middle East, which are being serviced by KAI Image Inc. of Korea. Information obtained from http://www.eoportal.org/ KOMPSAT-2 Specifications Imaging mode: Panchromatic Multispectral Spatial Resolution: 1m 4m Swatch Width: 15km 15km Duty Cycle: >20% per Orbit Off-Nadir Imaging: Up to 45 degree Orbital Altitude: 685km, Sun-synchromous orbit Operation Life: Minimum 5 years ( Design Life :3years) Revisit Time: Less than 3 days Data Transmission: 320 Mbps Data Storage: 90 Gbits Dynamic Range: 10 bits per pixel Group: Platform_Details Entry_ID: KOMPSAT-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: KOMPSAT-2 End_Group Group: Synonymous_Platform_Names Short_Name: Arirang-2 End_Group Group: Platform_Associated_Instruments Short_Name: CAMERA Short_Name: MS End_Group Group: Orbit Orbit_Altitude: 685 Orbit_Inclination: 98.13 Period: 98.46 Repeat_Cycle: ~14 Perigee: 682.0 Apogee: 708.0 Orbit_Type: LEO > LOW EARTH ORBIT > POLAR SUN-SYNCHRONOUS End_Group Creation_Date: 2008-07-09 Online_Resource: http://directory.eoportal.org/get_announce.php?an_id=7483 Online_Resource: http://www.kaiimage.co.kr/eng/kompsat_b01.asp Group: Platform_Logistics Launch_Date: 2006-07-28 Launch_Site: PLESETSK COSMODROME, RUSSIA Design_Life: Minimum 5 years ( Design Life :3years) Primary_Sponsor: Korea Aerospace Research Institute (KARI), South Korea End_Group End_Group 2019-02-21 10:40:39.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: bf3e5771-7ca2-4083-a5e2-9be6a28fe588 relationship type: null relationship value: null generated by: null); 2018-06-12 16:36:10.0 [mmorahan] Move Concepts delete broader relation (null); add broader relation (KOMPSAT-2 [88d9cd91-a26e-467a-9554-c5d927540421,345347] - KOMPSAT [9abdb7c0-7b8e-426b-8bc7-57ea4a30d82c,367679]); DMSP 5D-2/F9 [Source: National Space Science Data Center, http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1988-006A ] DMSP 5D-2/F9 is one of a series of meteorological satellites developed and operated by the Air Force under the Defense Meteorological Satellite Program (DMSP). This program, previously known as DAPP (Data Acquisition and Processing Program), was classified until March 1973. The objective of this program is to provide global visual and infrared cloudcover data and specialized environmental data to support Department of Defense operational weather analysis and forecasting requirements. Operationally, the program consists of two satellites in planned 830-km, sun-synchronous polar orbits, with the ascending node of one satellite in early morning and the other at local noon. The 6.4-m-long spacecraft is separated into four sections: (1) a precision mounting platform for sensors and equipment requiring precise alignment; (2) an equipment support module containing the electronics, reaction wheels, and some meteorological sensors; (3) a reaction control equipment support structure containing the third-stage rocket motor and supporting the ascent phase reaction control equipment; and (4) a 9.29-sq-m solar cell panel. The spacecraft stabilization is controlled by a combination flywheel and magnetic control coil system so sensors are maintained in the desired "earth-looking" mode. One feature is the precision-pointing accuracy of the primary imager to 0.01 deg provided by a star sensor and an updated ephemeris navigation system. This allows automatic geographical mapping of the digital imagery to the nearest picture element. The operational linescan system is the primary data acquisition system that provides real-time or stored, multi-orbit, day-and-night visual and infrared imagery of clouds. A supplementary sensor package contains four special sensors: (1) an advanced X-ray spectrometer, (2) an ionospheric/scintillation monitor, (3) a precipitating electron/ion spectrometer, and (4) an infrared temperature and moisture sounder. Either recorded or real-time data are transmitted to ground-receiving sites by two redundant S-band transmitters. Recorded data are read out to tracking sites located at Fairchild AFB, Washington, and at Loring AFB, Maine, and relayed by SATCOM to Air Force Global Weather Center, Offutt AFB, Nebraska. Real-time data are read out at mobile tactical sites located around the world. Additional information concerning this satellite program can be found in the report by D.A. Nichols, "The Defense Meteorological Satellite Program," Optical Engineering, v. 14, n. 4, p. 273, July-August 1975. Group: Platform_Details Entry_ID: DMSP 5D-2/F9 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: DMSP (Defense Meteorological Satellite Program) Short_Name: DMSP 5D-2/F9 Long_Name: Defense Meteorological Satellite Program-F9 End_Group Group: Synonymous_Platform_Names Short_Name: DMSP-F9 Short_Name: USA 29 Short_Name: 18822 End_Group Group: Platform_Associated_Instruments Short_Name: SSH-2 Short_Name: SSB/X Short_Name: OLS Short_Name: SSI/ES Short_Name: SSJ/4 End_Group Group: Orbit Orbit_Inclination: 98.6° Period: 101.2 minutes Perigee: 818.8 km Apogee: 818.8 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1988-006A Online_Resource: http://www.ngdc.noaa.gov/dmsp/index.html Online_Resource: http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/dmsp.html Group: Platform_Logistics Launch_Date: 1988-02-03 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: Department of Defense-Department of the Air Force (United States) End_Group End_Group SOLRAD-10 Solrad 10, known as Explorer 44 before launch, was the third in a series of small satellites launched by the US Naval Research Laboratory to study the Sun. It went into orbit on 8 July 1971. It was in an eccentric orbit, with apogee 630 km, perigee 436 km, and inclination 51 degrees. The orbital period was just over 95 minutes. The satellite was spin stabilized at 60 rpm. The satellite spin axis was pointed toward the Sun. All of the solar X-ray and UV sensors were located on the Sun-facing end parallel to the spin axis. The satellite was 12 sided, with a diameter of 0.76 m and a height of 0.59 m. It weighed about 118 kg. Solrad 10's scientific instruments were dedicated to studying the solar electromagnetic radiation, specifically in the UV/X-ray region. However, it could be commanded to study radiations from other stellar sources. The spacecraft descended into the atmosphere on 15 December 1979. Additional information available at "http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/solrad10.html" [Summary provided by NASA] Group: Platform_Details Entry_ID: SOLRAD-10 Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Platform_Series_or_Entity: SOLRAD Short_Name: SOLRAD-10 Long_Name: Solar Radiation-10 End_Group Group: Synonymous_Platform_Names Short_Name: SOLRAD-10 End_Group Group: Platform_Associated_Instruments Short_Name: SXP End_Group Group: Orbit Orbit_Inclination: 51 degrees Perigee: 436 km Apogee: 630 km End_Group Creation_Date: 2008-01-14 Online_Resource: http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/solrad10.html Sample_Image: http://heasarc.gsfc.nasa.gov/Images/misc_missions/solrad10_small.gif Group: Platform_Logistics Launch_Date: 1971-07-08 Primary_Sponsor: NASA End_Group End_Group Phantom DHD2+2 The Phantom DHD2+2 is a dependable ROV for offshore inspection and light work tasks, for use in strong currents to depths of 600m (2000'), and accommodates cameras, sonar, tracking, manipulators and custom tooling. 2020-01-21 18:00:34.0 [tstevens] insert Definition (id: null text: The Phantom DHD2+2 is a dependable ROV for offshore inspection and light work tasks, for use in strong currents to depths of 600m (2000'), and accommodates cameras, sonar, tracking, manipulators and custom tooling. language code: en); 2020-01-21 17:25:15.0 [tstevens] Insert Concept add broader relation (Phantom DHD2+2 [897c4eed-6f5a-4b60-9780-a73362ec84f2,559727] - ROV [da6420b6-48ec-4ae2-98c7-0ef0538815a0,542741]); COASTAL STATIONS Coastal stations take observations near or at the coast. TRMM The Tropical Rainfall Measuring Mission (or TRMM) is a NASA satellite that provides more information both to test and to improve those models. TRMM is particularly devoted to determining rainfall in the tropics and subtropics of the Earth. These regions make up about two thirds of the total rainfall on Earth and are responsible for driving our weather and climate system. TRMM contributed to a better understanding of where and how much the winds blow, where the clouds form and rain occurs, where floods and droughts will occur, and how the winds drive the ocean currents. TRMM accomplished this not just by providing rainfall data but, more importantly, by providing information on heat released into the atmosphere as part of the process that leads to rain. TRMM was launched on November 27, 1997, on the Japanese H-II vehicle from the Tanegashima Space Center in Tanegashima, Japan. Continuous science data collection began December 8, 1997. Upon completion of the nominal 3-year prime mission, the decision was made to boost the mission from its original altitude of 350km to 402.5km, to reduce fuel consumption and extend the mission life. The TRMM boost was completed August 24, 2001, and the orbit was maintained until 2014, when fuel was depleted and the spacecraft began to descend. Mission operations were terminated in April 2015, the spacecraft re-entered the Earth’s atmosphere and mostly burned up in June 2015. TRMM exceeded its 3-year design goal by collecting 17 years of rainfall data, creating a benchmark rainfall climatology which is used to test, compare and improve global climate models. The TRMM dataset of rain distribution across the tropics has narrowed considerably the range of uncertainty in previous space-based rainfall estimates. The choice of a precessing, low-inclination orbit (35°) enabled the quantification of the diurnal cycle of precipitation and convective intensity over land and ocean tropics-wide on fine scales (0.25°). TRMM products have provided the first comprehensive estimates of how rainfall is directly related to latent heat release in the atmosphere, a key characteristic in understanding the impact of tropical rainfall on the general circulation of the atmosphere. Based on hydrometeor vertical structure information from the TRMM active and passive sensors, TRMM produced climatologies of latent heating profiles for analysis and comparison with global models. In addition, the lightning sensor delivered a detailed global map of lightning distribution, and combined with the rain data, led to quantifying the lightning/convection relation for land and ocean. Launch: Launched: November 27, 1997 Launch Site: Tanegashima Space Center, Japan Orbit: Altitude: 402 km Inclination: 35 degrees Period: 92.6 minutes Non-Sun-Synchronous Vital Statistics: Weight: 3512 kg Power: 1100 watts Design Life: 3 years Instruments: CERES (Clouds and the Earth Radiant Energy System LIS (Lightning Imaging Sensor) TMI (TRMM Microwave Radiometer) PR (RADAR) VIRS (Visible/Infrared Radiometer) Website: https://pmm.nasa.gov/trmm [Summary provided by NASA.] Group: Platform_Details Entry_ID: TRMM Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: TRMM Long_Name: Tropical Rainfall Measuring Mission End_Group Group: Synonymous_Platform_Names Short_Name: TRMM End_Group Group: Platform_Associated_Instruments Short_Name: CERES-PFM Short_Name: PR Short_Name: TMI Short_Name: VIRS Short_Name: LIS End_Group Group: Orbit Orbit_Altitude: 402 km Orbit_Inclination: 35 degrees Period: 92.6 minutes Orbit_Type: LEO > Low Earth Orbit > Inclined Non-Polar End_Group Creation_Date: 2007-11-28 Online_Resource: https://pmm.nasa.gov/trmm Group: Platform_Logistics Launch_Date: 1997-11-27 Launch_Site: Tanegashima Island, Japan Design_Life: 3 YEARS Primary_Sponsor: USA/NASA Primary_Sponsor: JAPAN/JAXA End_Group End_Group 2020-01-02 22:57:15.0 [sritz] update Definition (The Tropical Rainfall Measuring Mission (or TRMM) is a NASA satellite that provides more information both to test and to improve those models. TRMM is particularly devoted to determining rainfall in the tropics and subtropics of the Earth. These regions make up about two thirds of the total rainfall on Earth and are responsible for driving our weather and climate system. TRMM contributed to a better understanding of where and how much the winds blow, where the clouds form and rain occurs, where floods and droughts will occur, and how the winds drive the ocean currents. TRMM accomplished this not just by providing rainfall data but, more importantly, by providing information on heat released into the atmosphere as part of the process that leads to rain. TRMM was launched on November 27, 1997, on the Japanese H-II vehicle from the Tanegashima Space Center in Tanegashima, Japan. Continuous science data collection began December 8, 1997. Upon completion of the nominal 3-year prime mission, the decision was made to boost the mission from its original altitude of 350km to 402.5km, to reduce fuel consumption and extend the mission life. The TRMM boost was completed August 24, 2001, and the orbit was maintained until 2014, when fuel was depleted and the spacecraft began to descend. Mission operations were terminated in April 2015, the spacecraft re-entered the Earth’s atmosphere and mostly burned up in June 2015. TRMM exceeded its 3-year design goal by collecting 17 years of rainfall data, creating a benchmark rainfall climatology which is used to test, compare and improve global climate models. The TRMM dataset of rain distribution across the tropics has narrowed considerably the range of uncertainty in previous space-based rainfall estimates. The choice of a precessing, low-inclination orbit (35°) enabled the quantification of the diurnal cycle of precipitation and convective intensity over land and ocean tropics-wide on fine scales (0.25°). TRMM products have provided the first comprehensive estimates of how rainfall is directly related to latent heat release in the atmosphere, a key characteristic in understanding the impact of tropical rainfall on the general circulation of the atmosphere. Based on hydrometeor vertical structure information from the TRMM active and passive sensors, TRMM produced climatologies of latent heating profiles for analysis and comparison with global models. In addition, the lightning sensor delivered a detailed global map of lightning distribution, and combined with the rain data, led to quantifying the lightning/convection relation for land and ocean. Launch: Launched: November 27, 1997 Launch Site: Tanegashima Space Center, Japan Orbit: Altitude: 402 km Inclination: 35 degrees Period: 92.6 minutes Non-Sun-Synchronous Vital Statistics: Weight: 3512 kg Power: 1100 watts Design Life: 3 years Instruments: CERES (Clouds and the Earth Radiant Energy System LIS (Lightning Imaging Sensor) TMI (TRMM Microwave Radiometer) PR (RADAR) VIRS (Visible/Infrared Radiometer) Website: https://pmm.nasa.gov/trmm [Summary provided by NASA.] Group: Platform_Details Entry_ID: TRMM Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: TRMM Long_Name: Tropical Rainfall Measuring Mission End_Group Group: Synonymous_Platform_Names Short_Name: TRMM End_Group Group: Platform_Associated_Instruments Short_Name: CERES-PFM Short_Name: PR Short_Name: TMI Short_Name: VIRS Short_Name: LIS End_Group Group: Orbit Orbit_Altitude: 402 km Orbit_Inclination: 35 degrees Period: 92.6 minutes Orbit_Type: LEO > Low Earth Orbit > Inclined Non-Polar End_Group Creation_Date: 2007-11-28 Online_Resource: https://pmm.nasa.gov/trmm Group: Platform_Logistics Launch_Date: 1997-11-27 Launch_Site: Tanegashima Island, Japan Design_Life: 3 YEARS Primary_Sponsor: USA/NASA Primary_Sponsor: JAPAN/JAXA End_Group End_Group); delete Resource (null); SENTINEL-3 PREFERRED TERMS: 3A, S3B, S3C, S3D, Sentinel-3 DEFINITION The Sentinel-3 (S3) mission of ESA and the EC is one of the elements of the GMES (Global Monitoring for Environment and Security) program, which responds to the requirements for operational and near-real-time monitoring of ocean, land and ice surfaces over a period of 20 years. The topography element of this mission will serve primarily the marine operational users but will also allow the monitoring of sea ice and land ice, as well as inland water surfaces, using novel observation techniques.The Sentinel-3 mission is designed as a constellation of two identical polar orbiting satellites, separated by 180º, for the provision of long-term operational marine and land monitoring services. The operational character of this mission implies a high level of availability of the data products and fast delivery time, which have been important design drivers for the mission. BROADER CONCEPT: Earth Observation Satellite ENTRY TERMS: SENTINEL-3 NOTE: A,B,C,D HOSTS: DORIS, GNSS, MWR, OLCI, SLSTR, SRAL URI: https://earth.esa.int/concept/sentinel-3 2019-03-26 20:18:45.0 [sritz] Insert Concept add narrower relation (SENTINEL-3 [8a19f309-46ee-424b-be9f-e7e57e5b8ca0,345357] - SENTINEL-3B [41163801-6aac-43e5-aed7-9f52613a6a73,368597]); 2018-11-05 12:50:49.0 [mmorahan] Insert Concept add narrower relation (SENTINEL-3 [8a19f309-46ee-424b-be9f-e7e57e5b8ca0,345357] - Sentinel 3A [5449d87b-5573-450f-8acb-2fdfeab3c8ce,368235]); 2018-11-05 12:48:54.0 [mmorahan] update Definition (PREFERRED TERMS: 3A, S3B, S3C, S3D, Sentinel-3 DEFINITION The Sentinel-3 (S3) mission of ESA and the EC is one of the elements of the GMES (Global Monitoring for Environment and Security) program, which responds to the requirements for operational and near-real-time monitoring of ocean, land and ice surfaces over a period of 20 years. The topography element of this mission will serve primarily the marine operational users but will also allow the monitoring of sea ice and land ice, as well as inland water surfaces, using novel observation techniques.The Sentinel-3 mission is designed as a constellation of two identical polar orbiting satellites, separated by 180º, for the provision of long-term operational marine and land monitoring services. The operational character of this mission implies a high level of availability of the data products and fast delivery time, which have been important design drivers for the mission. BROADER CONCEPT: Earth Observation Satellite ENTRY TERMS: SENTINEL-3 NOTE: A,B,C,D HOSTS: DORIS, GNSS, MWR, OLCI, SLSTR, SRAL URI: https://earth.esa.int/concept/sentinel-3); 2018-11-05 12:32:05.0 [mmorahan] Move Concepts delete broader relation (null); add broader relation (SENTINEL-3 [8a19f309-46ee-424b-be9f-e7e57e5b8ca0,345357] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761]); 2018-11-05 12:31:54.0 [mmorahan] Cut Concepts delete broader relation (null); add broader relation (SENTINEL-3 [8a19f309-46ee-424b-be9f-e7e57e5b8ca0,345357] - Trash Can/Platforms [6089b3e5-7db9-46e1-b73b-2d679f34abb4,354203]); 2018-06-12 19:26:14.0 [mmorahan] Move Concepts delete broader relation (null); add broader relation (SENTINEL-3 [8a19f309-46ee-424b-be9f-e7e57e5b8ca0,345357] - Sentinel GMES [2c9f1fcc-d9c8-4c6d-b701-45c97cee511f,344719]); 2018-06-12 19:20:10.0 [mmorahan] Move Concepts delete broader relation (null); add broader relation (SENTINEL-3 [8a19f309-46ee-424b-be9f-e7e57e5b8ca0,345357] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761]); 2018-02-27 22:01:28.0 [sritz] insert Resource (id: null type: provider url: https://earth.esa.int/web/guest/missions/esa-eo-missions/sentinel-3); 2018-02-27 22:00:35.0 [sritz] update Definition (entinel-3 is primarily an ocean mission, however, the mission is also able to provide atmospheric and land applications. The mission provides data continuity for the ERS, Envisat and SPOT satellites. Sentinel-3 makes use of multiple sensing instruments to accomplish its objectives; SLSTR (Sea and Land Surface Temperature Radiometer), OLCI (Ocean and Land Colour Instrument), SRAL (SAR Altimeter), DORIS, and MWR (Microwave Radiometer). Group: Platform_Details Entry_ID: SENTINEL-3 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: Sentinel GMES Short_Name: SENTINEL-3 End_Group Group: Orbit Orbit_Altitude: 800 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2009-12-18 Online_Resource: https://earth.esa.int/web/guest/missions/esa-eo-missions/sentinel-3 Sample_Image: http://www.esa.int/images/sentinel_M.gif Group: Platform_Logistics Launch_Site: Kourou, French Guiana Design_Life: 7 years Primary_Sponsor: ESA/EU End_Group End_Group); update Definition (https://earth.esa.int/web/guest/missions/esa-eo-missions/sentinel-3); 2018-02-27 21:58:04.0 [sritz] update Definition (The ESA Sentinels will be the first series of noperational satellites to meet the Earth lobservation needs of the European Union ESA Global Monitoring for Environment and Security (GMES) programme. The pair of Sentinel-3 satellites will provide global, frequent and near-realtime ocean, ice and land monitoring. It continues Envisat’s altimetry, the multispectral, medium-resolution visible and infrared ocean and land-surface observations of ERS, Envisat and Spot, and includes enhancements to meet the operational revisit requirements and to facilitate new products and evolution of services. The first launch is expected in 2011/2012. Summary Source: http://www.esa.int/esapub/bulletin/bulletin131/bul131c_aguirre.pdf Group: Platform_Details Entry_ID: SENTINEL-3 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: Sentinel GMES Short_Name: SENTINEL-3 End_Group Group: Orbit Orbit_Altitude: 800 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2009-12-18 Online_Resource: http://www.esa.int/esaLP/SEMZHM0DU8E_LPgmes_0.html Online_Resource: http://www.esa.int/esaEO/SEMXK570A2G_environment_0.html Online_Resource: http://en.wikipedia.org/wiki/Sentinel_3 Online_Resource: http://ec.europa.eu/gmes/index_en.htm Sample_Image: http://www.esa.int/images/sentinel_M.gif Group: Platform_Logistics Launch_Site: Kourou, French Guiana Design_Life: 7 years Primary_Sponsor: ESA/EU End_Group End_Group); 2018-02-27 21:57:36.0 [sritz] update Resource (image); insert WeightedRelation (id: null related concept uuid: 65ed042c-df53-4afb-8b6a-1ea16958015d relationship type: null relationship value: null generated by: null); ModelE The current incarnation of the GISS series of coupled atmosphere-ocean models is available here. Called ModelE, it provides the ability to simulate many different configurations of Earth System Models — including interactive atmospheric chemistry, aerosols, carbon cycle and other tracers, as well as the standard atmosphere, ocean, sea ice and land surface components. 2018-08-09 17:50:02.0 [sritz] update PrefLabel (ModelE); 2018-08-09 17:44:40.0 [sritz] insert AltLabel (id: null category: primary text: GISS GCM ModelE language code: en); insert Definition (id: null text: The current incarnation of the GISS series of coupled atmosphere-ocean models is available here. Called ModelE, it provides the ability to simulate many different configurations of Earth System Models — including interactive atmospheric chemistry, aerosols, carbon cycle and other tracers, as well as the standard atmosphere, ocean, sea ice and land surface components. language code: en); 2018-08-09 17:43:43.0 [sritz] Insert Concept add broader relation (MODELE [8ad656db-1324-4e92-8273-5a765ca29282,368043] - Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,344529]); WC-130J The WC-130 Hercules is a high-wing, medium-range aircraft used in weather reconnaissance missions. This plane is a C-130 transport configured with palletized weather instrumentation for penetration of tropical disturbances and storms, hurricanes and winter storms to obtain data on movement, size and intensity. The WC-130 is the weather data collection platform for the 53rd Weather Reconnaissance Squadron. [Summary provided by Wikipedia, http://en.wikipedia.org/wiki/Lockheed_WC-130 ] [Photo provided by Lockheed Martin, http://www.lockheedmartin.com/data/assets/aeronautics/products/c130j/c130j_5.jpg ] Group: Platform_Details Entry_ID: WC-130J Group: Platform_Identification Platform_Category: Aircraft Short_Name: WC-130J Long_Name: Lockheed-Martin WC-130J Hercules End_Group Group: Synonymous_Platform_Names Short_Name: Hurricane Hunter End_Group Creation_Date: 2008-07-14 Online_Resource: http://www.403wg.afrc.af.mil/library/factsheets/factsheet.asp?id=7482 Online_Resource: http://en.wikipedia.org/wiki/Lockheed_WC-130 Sample_Image: http://www.lockheedmartin.com/data/assets/aeronautics/products/c130j/c130j_5.jpg End_Group Deimos-1 The Deimos-1 mission is fully owned and operated by Deimos Imaging (DMI), an UrtheCast company. Deimos-1 satellite was successfully launched on 29 July 2009 from the Baikonur Launch Complex (Kazakhstan) in the Russian-Ukrainian Dnepr launcher. The mission is fully dedicated to Earth Observation and captures images all around the world. Thus, currently the Deimos-1 system provides capabilities well above and beyond the design goals. The payload is a three-band multispectral imager system with 22m Ground Sample Distance (GSD) at nominal altitude (663 km) with 625 km swath, 8 or 10 bits radiometric depth available. Imager delivers data in three spectral bands, very close to the Near-Infrared (NIR), Red (R) and Green (G) bands in the Landsat series of US satellites. The satellite payload is a dual bank linear CCD push broom imager, so that banks are mounted at an angle to provide a wide imaging swath, one of the most characteristics Deimos-1 features. launch: July 2009 lifetime: 10 years orbit: Sun-Synchronous altitude: 650 Km weight: 100 Kg size: 60x60x60 cm comms: bands S/X bands: R,G,NIR resolution: 22 m swath: 650 km made by: SSTL Ltd. launcher: Dnepr – Baikonur 2019-07-24 16:25:05.0 [mmorahan] Move Concepts delete broader relation (null); add broader relation (Deimos-1 [8b35d386-0999-4b6e-ad12-f8501427b0ca,345361] - DMC-2G (Disaster Monitoring Constellation- 2nd Generation) [e5184d15-eec8-4703-8318-243748ddbd0e,368737]); 2019-02-14 20:21:38.0 [mmorahan] delete WeightedRelation (null); insert WeightedRelation (id: null related concept uuid: 6a3c8a54-48ae-4357-8bbc-bd2c48ede3a7 relationship type: null relationship value: null generated by: null); 2019-02-14 20:13:39.0 [mmorahan] update Definition (The Deimos-1 mission is fully owned and operated by Deimos Imaging (DMI), an UrtheCast company. Deimos-1 satellite was successfully launched on 29 July 2009 from the Baikonur Launch Complex (Kazakhstan) in the Russian-Ukrainian Dnepr launcher. The mission is fully dedicated to Earth Observation and captures images all around the world. Thus, currently the Deimos-1 system provides capabilities well above and beyond the design goals. The payload is a three-band multispectral imager system with 22m Ground Sample Distance (GSD) at nominal altitude (663 km) with 625 km swath, 8 or 10 bits radiometric depth available. Imager delivers data in three spectral bands, very close to the Near-Infrared (NIR), Red (R) and Green (G) bands in the Landsat series of US satellites. The satellite payload is a dual bank linear CCD push broom imager, so that banks are mounted at an angle to provide a wide imaging swath, one of the most characteristics Deimos-1 features. launch: July 2009 lifetime: 10 years orbit: Sun-Synchronous altitude: 650 Km weight: 100 Kg size: 60x60x60 cm comms: bands S/X bands: R,G,NIR resolution: 22 m swath: 650 km made by: SSTL Ltd. launcher: Dnepr – Baikonur); update Definition (https://earth.esa.int/web/guest/missions/3rd-party-missions/current-missions/deimos-1); insert Resource (id: null type: image url: https://earth.esa.int/image/image_gallery?img_id=19297); insert WeightedRelation (id: null related concept uuid: 24b58da6-ac1a-46d1-bbd3-6cdb0a0e1707 relationship type: null relationship value: null generated by: null); 2018-06-12 09:19:22.0 [mmorahan] Rename Concept update PrefLabel (Deimos-1); 2018-06-12 09:14:20.0 [mmorahan] Move Concepts delete broader relation (null); add broader relation (DEIMOS-1 [8b35d386-0999-4b6e-ad12-f8501427b0ca,345361] - Deimos [f122ab59-266b-4be9-99ad-4c2172bcf97c,367663]); STS-66 The Atmospheric Laboratory for Applications and Sciences - 3 (ATLAS-03) is the primary payload aboard STS-66. It will continue the series of Spacelab flights to study the energy of the sun and how it affects the Earth's climate and environment. The ATLAS 3 mission will make the first detailed measurements from the Shuttle of the Northern Hemisphere's middle atmosphere in late fall. The timing of the flight, when the Antarctic ozone hole is diminishing, allows scientists to study possible effects of the ozone hole on mid-latitudes, the way Antarctic air recovers, and how the northern atmosphere changes as the winter season approaches. In addition to the ATLAS-03 investigations, the mission will include deployment and retrieval of the Cryogenic Infrared Spectrometer Telescopefor Atmosphere, or CRISTA. Mounted on the Shuttle Pallet Satellite, the payload is designed to explore the variability of the atmosphere and provide measurements that will complement those obtained by the Upper Atmosphere Research Satellite launched aboard Discovery in 1991. CRISTA-SPAS is a joint U.S./German experiment. Other payloads in Atlantis cargo bay include the Shuttle Solar Backscatter Ultraviolet (SSBUV-7) payload and the Experiment on the Sun Complementing ATLAS (ESCAPE-II). Payloads located in the middeck include the Physiological & Anatomical Rodent Experiment (PARE/NIR-R), Protein Crystal Growth-Thermal Enclosure (PCG-TES), Protein Crystal Growth- Single Locker (PCG-STES), Space Tissue Loss/National Institute of Health (STL/NIH-C), Space Acceleration Measurement System (SAMS) and the Heat Pipe Performance-2 Experiment (HPP-2). [Summary provided by NASA] Group: Platform_Details Entry_ID: STS-66 Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Platform_Series_or_Entity: SPACE SHUTTLE Short_Name: STS-66 Long_Name: Space Transport System STS-66 End_Group Group: Synonymous_Platform_Names Short_Name: Atlantis End_Group Group: Orbit Orbit_Altitude: 164nm Orbit_Inclination: 57 degrees End_Group Creation_Date: 2008-01-30 Online_Resource: http://science.ksc.nasa.gov/shuttle/missions/sts-66/mission-sts-66.html Sample_Image: http://www.nasa.gov/images/content/134504main_sts-66-crew-sm.jpg Group: Platform_Logistics Launch_Date: 1994-11-03 Primary_Sponsor: NASA End_Group End_Group ESSA-5 TOS-C The ESSA-5 satellite replaced ESSA-3 and provided cloud-cover photography to the US's National Meteorological Center for the purpose of preparing weather analyses and forecasts. The spacecraft was an 18-sided polygon, 42 inches in diameter, 22 inches high and weighed 320 pounds; it was made of aluminum alloy and stainless steel then covered with 9100 solar cells, used to charge the 63 nickel-cadmium batteries. The two cameras were mounted 180 degrees opposite each other along the side of the cylindrical craft. The "cartwheel" configuration of the TIROS-9 was selected as the orbital configuration for the ESSA satellites. Therefore, a camera could be pointed at some point on Earth every time the satellite rotated along its axis. The spacecraft operating system was the same as on the TIROS-9. The craft was placed in its planned Sun-synchronous 102-degree inclination retrograde orbit. The ESSA-5 system transmitted images covering 2000-square mile areas with 2-mile resolution from every location once per day. The ESSA-5 satellite replaced ESSA-3 and provided cloud-cover photography to the US's National Meteorological Center for the purpose of preparing weather analyses and forecasts. The spacecraft was an 18-sided polygon, 42 inches in diameter, 22 inches high and weighed 320 pounds; it was made of aluminum alloy and stainless steel then covered with 9100 solar cells, used to charge the 63 nickel-cadmium batteries. The two cameras were mounted 180 degrees opposite each other along the side of the cylindrical craft. The "cartwheel" configuration of the TIROS-9 was selected as the orbital configuration for the ESSA satellites. Therefore, a camera could be pointed at some point on Earth every time the satellite rotated along its axis. The spacecraft operating system was the same as on the TIROS-9. The craft was placed in its planned Sun-synchronous 102-degree inclination retrograde orbit. The ESSA-5 system transmitted images covering 2000-square mile areas with 2-mile resolution from every location once per day. ESSA-5 Stats: Launch Date: April 20, 1967 Operational Period: 738 days until deactivated by NASA on February 20, 1970 Launch Vehicle: Thrust Augmented Three-Stage Delta Launch Site: Vandenberg Air Force Base, CA Type: Weather Satellite 2018-11-14 15:41:30.0 [sritz] insert AltLabel (id: null category: null text: TOS-C language code: en); 2018-11-14 15:39:12.0 [sritz] insert AltLabel (id: null category: primary text: Environmental Science Services Administration Satellite 5 language code: en); 2018-10-30 17:02:58.0 [sritz] insert Definition (id: null text: The ESSA-5 satellite replaced ESSA-3 and provided cloud-cover photography to the US's National Meteorological Center for the purpose of preparing weather analyses and forecasts. The spacecraft was an 18-sided polygon, 42 inches in diameter, 22 inches high and weighed 320 pounds; it was made of aluminum alloy and stainless steel then covered with 9100 solar cells, used to charge the 63 nickel-cadmium batteries. The two cameras were mounted 180 degrees opposite each other along the side of the cylindrical craft. The "cartwheel" configuration of the TIROS-9 was selected as the orbital configuration for the ESSA satellites. Therefore, a camera could be pointed at some point on Earth every time the satellite rotated along its axis. The spacecraft operating system was the same as on the TIROS-9. The craft was placed in its planned Sun-synchronous 102-degree inclination retrograde orbit. The ESSA-5 system transmitted images covering 2000-square mile areas with 2-mile resolution from every location once per day. The ESSA-5 satellite replaced ESSA-3 and provided cloud-cover photography to the US's National Meteorological Center for the purpose of preparing weather analyses and forecasts. The spacecraft was an 18-sided polygon, 42 inches in diameter, 22 inches high and weighed 320 pounds; it was made of aluminum alloy and stainless steel then covered with 9100 solar cells, used to charge the 63 nickel-cadmium batteries. The two cameras were mounted 180 degrees opposite each other along the side of the cylindrical craft. The "cartwheel" configuration of the TIROS-9 was selected as the orbital configuration for the ESSA satellites. Therefore, a camera could be pointed at some point on Earth every time the satellite rotated along its axis. The spacecraft operating system was the same as on the TIROS-9. The craft was placed in its planned Sun-synchronous 102-degree inclination retrograde orbit. The ESSA-5 system transmitted images covering 2000-square mile areas with 2-mile resolution from every location once per day. ESSA-5 Stats: Launch Date: April 20, 1967 Operational Period: 738 days until deactivated by NASA on February 20, 1970 Launch Vehicle: Thrust Augmented Three-Stage Delta Launch Site: Vandenberg Air Force Base, CA Type: Weather Satellite language code: en); 2018-10-30 15:45:08.0 [sritz] Insert Concept add broader relation (ESSA-5 [8b67c88a-b62f-4585-a5d3-8e0005f42fd0,368203] - ESSA [65cb3e7c-d4d8-46df-a5fc-aec63e58e8df,345109]); X-POW Mobile X-band Polarimetric Weather Radar on Wheels (X-POW)is a Doppler scanning radar operating at 9.3 GHz.with horizontal and vertical polarization. Used for detection and detailing surface rainfall rate and precipitation classification fields, 3D precipitation microphysical retrievals including water/frozen hydrometer contents and drop size distribution profiles, X-POW was located in the Florida Keys during the CAMEX-4 field experiment. Group: Platform_Details Entry_ID: X-POW Group: Platform_Identification Platform_Category: In Situ Land-based Platforms Platform_Series_or_Entity: WEATHER STATIONS/NETWORKS Short_Name: X-POW Long_Name: X-band Polarimetric Weather Radar End_Group Group: Synonymous_Platform_Names Short_Name: X-POW End_Group Creation_Date: 2007-12-12 Online_Resource: http://camex.nsstc.nasa.gov/camex4/instrument_documentation/xpow.pdf End_Group MAGSAT - Spacecraft Brief Description - The Magsat project was a joint NASA/United States Geological Survey (USGS) effort to measure near-earth magnetic fields on a global basis. Objectives included obtaining an accurate description of the earth's magnetic field, obtaining data for use in the update and refinement of world and regional magnetic charts, compilation of a global crustal magnetic anomaly map, and interpretation of that map in terms of geologic/geophysical models of the earth's crust. The spacecraft was launched into a low, near-polar, orbit by the Scout vehicle. The basic spacecraft was made up of two distinct parts: the instrument module that contained a vector and a scalar magnetometer and their unique supporting gear; and the base module that contained the necessary data-handling, power, communications, command, and attitude-control subsystems to support the instrument module. The base module complete with its subsystems was comprised of residual Small Astronomy Satellite (SAS-C) hardware. The magnetometers were deployed after launch to a position 6 m behind the spacecraft. At this distance, the influence of magnetic materials from the instrument and base module (chiefly from the star cameras) was less than 1 nT. - Auxiliary Information - Launch Date and Time : 1979-10-30 14:16:00 Epoch Date and Time : 1979-10-31 Apogee (km or AU): 578.4 Perigee (km or AU): 351.9 Inclination (degree) : 96.8 Orbit Type : Geocentric Information last updated on 1992-04-13 Group: Platform_Details Entry_ID: MAGSAT Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: MAGSAT End_Group Group: Synonymous_Platform_Names Short_Name: AEM-3 End_Group Group: Orbit Orbit_Inclination: 96.8 deg Perigee: 351.9 km Apogee: 578.4 km End_Group Creation_Date: 2007-11-20 Online_Resource: http://www.daviddarling.info/encyclopedia/M/Magsat.html Sample_Image: http://www.daviddarling.info/images/Magsat.jpg Group: Platform_Logistics Launch_Date: 1979-10-30 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: NASA End_Group End_Group AIRCRAFT An AIRCRAFT is a machine or device, such as an airplane, helicopter, glider, or dirigible, that is capable of atmospheric flight. Group: Platform_Details Entry_ID: AIRCRAFT Group: Platform_Identification Platform_Category: Aircraft Short_Name: AIRCRAFT End_Group Group: Platform_Associated_Instruments Short_Name: ROSEMOUNT PROBES Short_Name: PRESSURE TRANSDUCERS Short_Name: TEMPERATURE PROBES Short_Name: PITOT-STATIC SYSTEM Short_Name: INS End_Group End_Group SDO [Source: NASA Science Mission Directorate Home Page, http://nasascience.nasa.gov/ ] [SDO was successfully launched on 2010-02-11. Please follow the SDO home page for mission updates. http://sdo.gsfc.nasa.gov/ ] The Solar Dynamics Observatory (SDO) is the first mission to be launched for NASA's Living With a Star (LWS) Program, a program designed to understand the causes of solar variability and its impacts on Earth. SDO is designed to help us understand study the Sun's influence on Earth and Near-Earth space by studying observing the solar atmosphere on small scales of space and time and in many wavelengths simultaneously. SDO's goal is to understand, driving towards a predictive capability, the solar variations that influence life on Earth and humanity's technological systems by determining how the Sun's magnetic field is generated and structured how this stored magnetic energy is converted and released into the heliosphere and geospace in the form of solar wind, energetic particles, and variations in the solar irradiance. SDO data will help us to understand the cause the how and why of the Sun's magnetic activity changes. It will determine how the magnetic field is generated and structured, and how the stored magnetic energy is released into the heliosphere and geospace. SDO data and analysis will also help us develop the ability to predict the solar activity variations. that influence life on Earth and humanity's technological systems. SDO will observe different layers in solar atmosphere from visible surface, photosphere, to outer corona. measure the properties of the Sun and solar activity. There are few types of measurements but many of them will be taken. For example, Helioseismic and Magnetic Imager (HMI) will record maps of magnetic fields on entire visible solar hemisphere. HMI will also observe flows of plasma in the photosphere. These observations will be used to study motions throughout solar atmosphere: from the global scale (solar rotation), to small spatial scales (e.g. convective motions, which the surface velocity is measured by HMI. This data can be used for many different studies. One is the surface rotation rate, which must be removed to study the others. After subtracting the rotation, you have the oscillation and convective velocities. The latter look like billows of storm clouds covering the Sun. Hot gas moves outward at the center of the billows and downward at the edges—just like boiling water). Data from HMI will also allow us to study processes taking place underneath the visible surface. These studies will be conducted using methods of helioseismology, in the same manner as geologies on Earth study interior of our planet. Other SDO instruments, Atmospheric Imaging Assembly (AIA) will study hot outer layers of solar atmosphere, corona. AIA will take images and movies of corona in several wavelengths of ultraviolet light. The third SDO instrument, ), Extreme Ultraviolet Variability Experiment (EVE) will observe total every flux from the Sun, or irradiance. The variations in irradiance are important component of Earth's atmosphere and climate models. Group: Platform_Details Entry_ID: SDO Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Platform_Series_or_Entity: Living with a Star Short_Name: SDO Long_Name: Solar Dynamics Observatory End_Group Group: Synonymous_Platform_Names Short_Name: SDO End_Group Group: Platform_Associated_Instruments Short_Name: HMI-SDO Short_Name: AIA-SDO Short_Name: EVE-SDO End_Group Group: Orbit Orbit_Altitude: 36,000 km Orbit_Inclination: 28.5 degrees Orbit_Type: GEO > Geosynchronous > Non-Geostationary End_Group Creation_Date: 2009-04-24 Online_Resource: http://sdo.gsfc.nasa.gov/ Online_Resource: http://nasascience.nasa.gov/missions/sdo Sample_Image: http://www.nasa.gov/images/content/425451main_AV021-Launch425x.jpg Group: Platform_Logistics Launch_Date: 2010-02-11 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Design_Life: 5 years 3 months Primary_Sponsor: USA/NASA End_Group End_Group METOP The Meteorological Operational satellite programme (MetOp) is a European undertaking providing weather data services to monitor the climate and improve weather forecasts. The programme was jointly established by ESA and the European Organisation for the Exploitation of Meteorological Satellites (Eumetsat), forming the space segment of Eumetsat's Polar System (EPS). The programme also represents the European contribution to a cooperative venture with the United States’ National Oceanic and Atmospheric Administration (NOAA), which for the last 40 years has been delivering meteorological data from polar orbit, free of charge, to users worldwide. Information provided by http://www.esa.int/esaLP/SEMN1FAATME_LPmetop_0.html Group: Platform_Details Entry_ID: METOP Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: METEOSAT Short_Name: METOP Long_Name: Meteorological Operational Satelite End_Group Creation_Date: 2007-08-20 Online_Resource: http://www.esa.int/esaLP/SEMN1FAATME_LPmetop_0.html Sample_Image: http://www.esa.int/images/metop_flyby2_l.jpg Group: Platform_Logistics Primary_Sponsor: European Space Agency End_Group End_Group 2018-06-12 17:26:49.0 [mmorahan] Insert Concept add narrower relation (METOP [8c192c86-d07c-4e7b-af8f-92aa4b40fca7,345373] - METOP-C [6120cea0-c943-4c7c-bddd-8d8648d58022,367687]); 2012-09-18 21:35:41.0 [saritz] Remove Concepts delete narrower relation (null); 2012-09-18 21:18:56.0 [saritz] Insert Concept add narrower relation (METOP [8c192c86-d07c-4e7b-af8f-92aa4b40fca7,31825] - METOP-B [c9f84df0-e807-46e3-8fce-c33e9201fbc2,40601]); 2012-09-18 19:52:45.0 [saritz] Insert Concept add narrower relation (METOP [8c192c86-d07c-4e7b-af8f-92aa4b40fca7,31825] - METOP-B [944bdc0a-f753-425c-9ac7-1494c9b9d299,40597]); 2012-09-18 16:35:53.0 [saritz] Move Concepts add narrower relation (METOP [8c192c86-d07c-4e7b-af8f-92aa4b40fca7,31825] - METOP-A [8143808e-1005-4fed-a469-c2bd5f1521bf,32245]); 2012-09-18 16:35:12.0 [saritz] Move Concepts add broader relation (METOP [8c192c86-d07c-4e7b-af8f-92aa4b40fca7,31825] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,31221]); delete broader relation (null); 2012-09-18 16:35:03.0 [saritz] Cut Concepts add broader relation (METOP [8c192c86-d07c-4e7b-af8f-92aa4b40fca7,31825] - Trash Can/Platforms [6089b3e5-7db9-46e1-b73b-2d679f34abb4,40307]); delete broader relation (null); Mosaic-LSM 2014-05-30 09:18:55.0 [128.183.164.42] SR Added new model. insert AltLabel (id: null text: Mosaic Land Surface Model language code: en); 2014-05-30 09:18:12.0 [128.183.164.42] Insert Concept add broader relation (Mosaic-LSM [8c1eb362-072d-4763-b6f3-6b706b257e6a,106441] - Models [113ecbc2-ab36-4d58-a96c-a6ce0106e749,73395]); NCEP-RUC The NCEP Rapid Update Cycle (RUC) Model is a weather prediction system running every hour out to at least 18h comprised primarily of a numerical forecast model (using isentropic-sigma hybrid vertical coordinate) and an analysis/assimilation system to initialize that model. RUC was developed to serve users needing frequently updated short-range weather forecasts, including those in the US aviation community and US severe weather forecasting community. Group: Platform_Details Entry_ID: NCEP-RUC Group: Platform_Identification Platform_Category: Models Short_Name: NCEP-RUC Long_Name: NCEP Rapid Update Cycle Model End_Group Creation_Date: 2012-07-23 Online_Resource: http://ruc.noaa.gov/ Online_Resource: http://www.srh.noaa.gov/ssd/nwpmodel/html/ruc.htm End_Group LANDSAT-3 Landsat 3 is the third satellite of the Landsat program. It was launched on March 5th, 1978, with the primary goal of providing a global archive of satellite photos. Unlike later Landsats, Landsat 3 was managed solely by NASA. Landsat 3 is no longer in operation, due to technical failure. It finally ceased transmission on March 21st 1983, far beyond its designed life expectancy of one year. Landsat 3 had essentially the same design as Landsat 2. It carried a Multi-Spectral Scanner, which had a maximum 75m resolution. Unlike the previous two Landsat missions a thermal band was built into Landsat 3, but this instrument failed shortly after the satellite was deployed. [2] Landsat 3 was placed into a polar orbit at about 920 kilometers, and took 18 days to cover the entire Earth&#039;s surface. [Summary provided by NASA.] Group: Platform_Details Entry_ID: LANDSAT-3 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: LANDSAT Short_Name: LANDSAT-3 End_Group Group: Platform_Associated_Instruments Short_Name: MSS Short_Name: RBV End_Group Group: Orbit Orbit_Altitude: 900 km Orbit_Inclination: 99.2 degree Equator_Crossing: 9:42 AM mean local time Period: 103 minutes Repeat_Cycle: 18 days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-02-01 Online_Resource: https://landsat.gsfc.nasa.gov/landsat-3/ Online_Resource: https://www.usgs.gov/land-resources/nli/landsat/landsat-3 Group: Platform_Logistics Launch_Date: 1978-03-05 Launch_Site: Vandenberg AFB Design_Life: 1 Year Primary_Sponsor: NASA Primary_Sponsor: USGS End_Group End_Group 2019-12-31 21:20:37.0 [sritz] update Definition (Landsat 3 is the third satellite of the Landsat program. It was launched on March 5th, 1978, with the primary goal of providing a global archive of satellite photos. Unlike later Landsats, Landsat 3 was managed solely by NASA. Landsat 3 is no longer in operation, due to technical failure. It finally ceased transmission on March 21st 1983, far beyond its designed life expectancy of one year. Landsat 3 had essentially the same design as Landsat 2. It carried a Multi-Spectral Scanner, which had a maximum 75m resolution. Unlike the previous two Landsat missions a thermal band was built into Landsat 3, but this instrument failed shortly after the satellite was deployed. [2] Landsat 3 was placed into a polar orbit at about 920 kilometers, and took 18 days to cover the entire Earth&#039;s surface. [Summary provided by NASA.] Group: Platform_Details Entry_ID: LANDSAT-3 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: LANDSAT Short_Name: LANDSAT-3 End_Group Group: Platform_Associated_Instruments Short_Name: MSS Short_Name: RBV End_Group Group: Orbit Orbit_Altitude: 900 km Orbit_Inclination: 99.2 degree Equator_Crossing: 9:42 AM mean local time Period: 103 minutes Repeat_Cycle: 18 days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-02-01 Online_Resource: https://landsat.gsfc.nasa.gov/landsat-3/ Online_Resource: https://www.usgs.gov/land-resources/nli/landsat/landsat-3 Group: Platform_Logistics Launch_Date: 1978-03-05 Launch_Site: Vandenberg AFB Design_Life: 1 Year Primary_Sponsor: NASA Primary_Sponsor: USGS End_Group End_Group); update Definition (https://landsat.gsfc.nasa.gov/landsat-3/); delete Resource (null); MAPS A Map is a graphic representation of the Earth's surface. Maps can include street maps, world maps, country maps, state maps, historic maps and world maps. [Source: About Geography] Group: Platform_Details Entry_ID: MAPS Group: Platform_Identification Platform_Category: Maps/Charts/Photographs Short_Name: MAPS End_Group Group: Synonymous_Platform_Names Short_Name: maps End_Group Creation_Date: 2007-12-13 Online_Resource: http://en.wikipedia.org/wiki/Map Sample_Image: http://upload.wikimedia.org/wikipedia/commons/thumb/7/75/Planisph%C3%A6ri_c%C5%93leste.jpg/200px-Planisph%C3%A6ri_c%C5%93leste.jpg End_Group STS-68 During the 10 day mission, the Space Radar Laboratory (SRL) payload in Endeavour's cargo bay will make its second flight. The SRL payload, which first flew during STS-59 in April 1994, will again give scientists highly detailed information that will help them distinguish between human-induced environmental changes and other natural forms of change. SRL-2 will take radar images of the Earth's surface for Earth system sciences studies, including geology, geography, hydrology, oceanography, agronomy and botany. The SRL payload is comprised of the Spaceborne Imaging Radar-C/X-Band Synthetic Aperture Radar (SIR-C/X-SAR), and the Measurement of Air Pollution from Satellite (MAPS). The German Space Agency (DARA) and the Italian Space Agency (ASI) are providing the X-SAR instrument. The imaging radar of the SIR-C/X-SAR instruments has the ability to make measurements over virtually any region at any time, regardless of weather or sunlight conditions. The radar waves can penetrate clouds, and under certain conditions, also can "see" through vegetation, ice and extremely dry sand. In many cases, radar is the only way scientists can explore inaccessible regions of the Earth's surface. The SIR-C/X-SAR radar data provide information about how many of Earth's complex systems - those processes that control the movement of land, water, air and life - work together to make this a livable planet. The science team particularly wants to study the amount of vegetation coverage, the extent of snow packs, wetlands areas, geologic features such as rock types and their distribution, volcanic activity, ocean wave heights and wind speed. STS-68 will fly over the same sites that STS-59 observed so that scientists will be able to study seasonal changes that may have occurred in those areas between the missions. An international team of 49 science investigators and three associates will conduct the SIR-C/X-SAR experiments. Thirteen nations are represented: Australia, Austria, Brazil, Canada, China, the United Kingdom, France, Germany, Italy, Japan, Mexico, Saudi Arabia and the United States. The MAPS experiment will measure the global distribution of carbon monoxide in the troposphere, or lower atmosphere. Measurements of carbon monoxide, an important element in several chemical cycles, provide scientists with indications of how well the atmosphere can cleanse itself of "greenhouse gases," chemicals that can increase the atmosphere's temperature. STS-68 provided a continuation of NASA's Get Away Special (GAS) experiments program. The project gives a person or organization a chance to perform experiments in space on a Shuttle mission. Two universities, North Carolina A&T State University and University of Alabama in Huntsville, and the Swedish Space Corp., Soina, Sweden, will have small self-contained payloads flying during the STS-68 mission. Other GAS hardware in Endeavour's payload bay will carry 500,000 commemorative stamps for the U.S. Postal Service in recognition of the 25th anniversary of the Apollo 11 Moon landing. Other payloads aboard Endeavour include the Biological Research in Canister (BRIC) which will fly for the first time, and the Military Applications of Ship Tracks (MAST) which will be making its second flight. BRIC experiments, sponsored by NASA's Office of Life and Microgravity Sciences and Applications, are designed to examine the effects of microgravity on a wide range of physiological processes in higher order plants and arthropod animals (e.g., insects, spiders, centipedes, crustaceans). MAST is an experiment sponsored by the Office of Naval Research (ONR) and is part of a five-year research program developed by ONR to examine the effects of ships on the marine environment. The Commercial Protein Crystal Growth (CPCG) experiment, the Chromosome and Plant Cell Division in Space Experiment (CHROMEX) and the Cosmic Radiation Effects and Activation Monitor (CREAM) experiment also will be carried aboard Endeavour. [Summary provided by NASA] Group: Platform_Details Entry_ID: STS-68 Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Platform_Series_or_Entity: SPACE SHUTTLE Short_Name: STS-68 Long_Name: Space Transport System STS-68 End_Group Group: Synonymous_Platform_Names Short_Name: Endeavour End_Group Group: Orbit Orbit_Inclination: 57 End_Group Creation_Date: 2008-01-30 Online_Resource: http://science.ksc.nasa.gov/shuttle/missions/sts-68/mission-sts-68.html Sample_Image: http://www.nasa.gov/images/content/134508main_sts-68-crew-sm.jpg Group: Platform_Logistics Launch_Date: 1994-09-30 Primary_Sponsor: NASA End_Group End_Group SES-14 The C-band payload of SES-14 will replace NSS-806 and will support SES’s cable neighborhood in Latin America. The Ku-band payload augments the Ku-band capacity on NSS-806 with wide beams and high throughput spot beams covering the Americas and the North Atlantic Region. The Ku-band spot beams will allow SES to support the increasing demand for aeronautical and maritime mobility applications, cellular backhaul, broadband delivery, and VSAT services for enterprise and government segments. The Ku-band wide beams are designed to provide video and data services in Latin America, the Caribbean, and across the North Atlantic. SES-14 also carries the Global-Scale Observations of the Limb and Disk (GOLD) as a hosted payload for NASA. Read more at https://www.ses.com/our-coverage/satellites/369#pXjgoQTiElC2hApq.99 Launch date: 26 January 2018 Launch vehicle: Ariane 5 ECA Satellite manufacturer: Airbus Defense and Space Designed lifetime: 15 years 2018-01-29 16:32:31.0 [sritz] update WeightedRelation (Platform-Instrument); update WeightedRelation (1); 2018-01-29 16:31:58.0 [sritz] insert WeightedRelation (id: null related concept uuid: b68224a0-262d-4001-94b8-e10a3fd7e799 relationship type: null relationship value: null generated by: null); 2018-01-26 21:38:36.0 [sritz] update Definition (The C-band payload of SES-14 will replace NSS-806 and will support SES’s cable neighborhood in Latin America. The Ku-band payload augments the Ku-band capacity on NSS-806 with wide beams and high throughput spot beams covering the Americas and the North Atlantic Region. The Ku-band spot beams will allow SES to support the increasing demand for aeronautical and maritime mobility applications, cellular backhaul, broadband delivery, and VSAT services for enterprise and government segments. The Ku-band wide beams are designed to provide video and data services in Latin America, the Caribbean, and across the North Atlantic. SES-14 also carries the Global-Scale Observations of the Limb and Disk (GOLD) as a hosted payload for NASA. Read more at https://www.ses.com/our-coverage/satellites/369#pXjgoQTiElC2hApq.99 Launch date: 26 January 2018 Launch vehicle: Ariane 5 ECA Satellite manufacturer: Airbus Defense and Space Designed lifetime: 15 years); 2018-01-26 21:37:09.0 [sritz] insert Definition (id: null text: The C-band payload of SES-14 will replace NSS-806 and will support SES’s cable neighborhood in Latin America. The Ku-band payload augments the Ku-band capacity on NSS-806 with wide beams and high throughput spot beams covering the Americas and the North Atlantic Region. The Ku-band spot beams will allow SES to support the increasing demand for aeronautical and maritime mobility applications, cellular backhaul, broadband delivery, and VSAT services for enterprise and government segments. The Ku-band wide beams are designed to provide video and data services in Latin America, the Caribbean, and across the North Atlantic. SES-14 also carries the Global-Scale Observations of the Limb and Disk (GOLD) as a hosted payload for NASA. Read more at https://www.ses.com/our-coverage/satellites/369#pXjgoQTiElC2hApq.99 language code: en); 2018-01-26 21:35:39.0 [sritz] Insert Concept add broader relation (SES-14 [8dd76819-1baa-4ccd-8544-23c2923f2d84,310531] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,287601]); BIROS BIROS is a follow-on fire detection mission of DLR based on TET-1 (Technology Experiment Carrier-1). The BIROS satellite is part of DLR's FireBird constellation, which consists of two spacecraft, TET-1 and BIROS. The primary goal of this mission is the detection and monitoring of so called HTEs (High Temperature Events), e.g. forest fires or other hot spots. The secondary BIROS mission goals are: • The processing capabilities of the BIROS payload will be considerably upgraded. • BIROS will be equipped with OSIRIS (Optical Space Infrared Downlink System), a new onboard optical communication terminal, developed at DLR, to demonstrate the following capabilities: - three different laser systems for downlink communications at data rates up to 1 Gbit/s - four quadrant laser detector onboard for improved pointing accuracy - a beacon laser in uplink to support the BIROS attitude control; it may also be used for an optical uplink. • VAMOS (Verification of Autonomous Mission Planning On-board a Spacecraft). VAMOS is a DLR/GSOC software experiment with the objective to schedule and (re-)command tasks. • AVANTI (Autonomous Vision Approach Navigation and Target Identification), an optical navigation experiment. The goal is to demonstrate autonomous rendezvous to (and departure from) a non-cooperative client using vision-based navigation. 3) • BIROS will carry onboard the picosatellite BEESAT-4 (Berlin Experimental and Educational Satellite-4) of TU Berlin(1U CubeSat, 1 kg) and release it through a spring mechanism [ejection by SPL (Single Picosatellite Launcher ) after the successful check-out and commissioning of all relevant BIROS subsystems]. After separation, it will perform experimental proximity maneuvers in formation with the picosatellite solely based on optical navigation. 4) Spacecraft: For BIROS, the TET-X platform is being used, a slightly improved version of the existing TET-1 satellite bus. The TET-X bus shares the TET-1 bus envelope of 670 x 580 x 880 mm3 and 70 kg satellite bus mass with 460 x 460 x 428 mm3 payload volume and 50 kg payload mass. The three-axis attitude control system provides a pointing knowledge of 10 arcsec and a position accuracy of 10 m. But the TET-X bus contains a new power subsystem, new transmitters and OBC (OnBoard Computer), with same envelopes and masses as for TET-1. The BIROS spacecraft will be built again in a cooperation of DLR and AFW (Astro Feinwerktechnik GmbH), Berlin Adlershof. Both satellites (TET-1 and BIROS) are equipped with an identical main payload. These are the infrared cameras for Earth observation, especially hot spot detection. As part of the DLR FireBIRD mission, both satellites shall be used in a constellation for fire detection and monitoring. A special point in the design of the satellite bus was the interface between satellite bus and payload. To support different kinds of missions, the system contains the nominal satellite bus and a PSS (Payload Supply System). This payload supply system is on its payload interface side adaptable to the data (SpaceWire, RS422/485, CAN-Bus, etc.) and power interface requirements, data storage requirements and payload control requirements. The nominal satellite bus will remain unchanged for different missions, but of course can be adapted in parts, like an upgrade to X-band system if higher data rates are required. The PCBs (Printed Circuit Boards) of the PSS will be adapted for every new payload accommodation. 2019-03-11 17:31:15.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: e9d9df16-ebbf-4f6d-838f-225716619ff9 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 7c6ddfcd-00e3-4194-be91-9a9648f9d30b relationship type: null relationship value: null generated by: null); 2018-10-11 20:41:21.0 [mmorahan] insert AltLabel (id: null category: primary text: Bi-spectral InfraRed Optical System language code: en); insert Definition (id: null text: BIROS is a follow-on fire detection mission of DLR based on TET-1 (Technology Experiment Carrier-1). The BIROS satellite is part of DLR's FireBird constellation, which consists of two spacecraft, TET-1 and BIROS. The primary goal of this mission is the detection and monitoring of so called HTEs (High Temperature Events), e.g. forest fires or other hot spots. The secondary BIROS mission goals are: • The processing capabilities of the BIROS payload will be considerably upgraded. • BIROS will be equipped with OSIRIS (Optical Space Infrared Downlink System), a new onboard optical communication terminal, developed at DLR, to demonstrate the following capabilities: - three different laser systems for downlink communications at data rates up to 1 Gbit/s - four quadrant laser detector onboard for improved pointing accuracy - a beacon laser in uplink to support the BIROS attitude control; it may also be used for an optical uplink. • VAMOS (Verification of Autonomous Mission Planning On-board a Spacecraft). VAMOS is a DLR/GSOC software experiment with the objective to schedule and (re-)command tasks. • AVANTI (Autonomous Vision Approach Navigation and Target Identification), an optical navigation experiment. The goal is to demonstrate autonomous rendezvous to (and departure from) a non-cooperative client using vision-based navigation. 3) • BIROS will carry onboard the picosatellite BEESAT-4 (Berlin Experimental and Educational Satellite-4) of TU Berlin(1U CubeSat, 1 kg) and release it through a spring mechanism [ejection by SPL (Single Picosatellite Launcher ) after the successful check-out and commissioning of all relevant BIROS subsystems]. After separation, it will perform experimental proximity maneuvers in formation with the picosatellite solely based on optical navigation. 4) Spacecraft: For BIROS, the TET-X platform is being used, a slightly improved version of the existing TET-1 satellite bus. The TET-X bus shares the TET-1 bus envelope of 670 x 580 x 880 mm3 and 70 kg satellite bus mass with 460 x 460 x 428 mm3 payload volume and 50 kg payload mass. The three-axis attitude control system provides a pointing knowledge of 10 arcsec and a position accuracy of 10 m. But the TET-X bus contains a new power subsystem, new transmitters and OBC (OnBoard Computer), with same envelopes and masses as for TET-1. The BIROS spacecraft will be built again in a cooperation of DLR and AFW (Astro Feinwerktechnik GmbH), Berlin Adlershof. Both satellites (TET-1 and BIROS) are equipped with an identical main payload. These are the infrared cameras for Earth observation, especially hot spot detection. As part of the DLR FireBIRD mission, both satellites shall be used in a constellation for fire detection and monitoring. A special point in the design of the satellite bus was the interface between satellite bus and payload. To support different kinds of missions, the system contains the nominal satellite bus and a PSS (Payload Supply System). This payload supply system is on its payload interface side adaptable to the data (SpaceWire, RS422/485, CAN-Bus, etc.) and power interface requirements, data storage requirements and payload control requirements. The nominal satellite bus will remain unchanged for different missions, but of course can be adapted in parts, like an upgrade to X-band system if higher data rates are required. The PCBs (Printed Circuit Boards) of the PSS will be adapted for every new payload accommodation. language code: en); 2018-10-11 20:37:15.0 [mmorahan] Insert Concept add broader relation (BIROS [8e53aafe-f7a5-4629-893e-0a3ae1a6fe1d,368167] - FireBIRD [9b165321-e03c-44dc-bb9c-d10c32c93ab6,368159]); Explorer HC-130 The HC-130 is an extended-range, combat rescue version of the C-130 transport aircraft. Capable of independent employment in the no-to-low threat environment. Its primary mission is to provide air refueling for rescue helicopters. The HC-130 can perform extended searches in a permissive environment and has the capability to airdrop pararescuemen and survival equipment to isolated survivors when a delay in the arrival of a recovery vehicle is anticipated. Flights to air refueling areas or drop zones are accomplished at tactical low altitude to avoid threats. NVG-assisted, low-altitude air refueling and other operations in a low-threat environment are performed by specially trained crews. The crew can perform airborne mission commander (AMC) duties in a no-to-low threat environment when threat conditions permit. Group: Platform_Details Entry_ID: HC-130 Group: Platform_Identification Platform_Category: Aircraft Short_Name: HC-130 Long_Name: HC-130 End_Group Creation_Date: 2012-07-18 Online_Resource: http://www.globalsecurity.org/military/systems/aircraft/hc-130.htm End_Group Solar/Space Observation Satellites Satellites that observe the Earth's sun and the physical universe beyond the Earth's atmosphere. Group: Platform_Details Entry_ID: Solar/Space Observation Satellites Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Short_Name: Solar/Space Observation Satellites End_Group End_Group 2017-09-01 16:35:23.0 [sritz] Move Concepts delete narrower relation (null); 2017-09-01 16:30:29.0 [sritz] Insert Concept add narrower relation (Solar/Space Observation Satellites [8e8b7689-0a8e-47a4-9c68-5f6a207104d5,288197] - GOES [6e332c25-caeb-4917-afb6-af757bcecd72,310071]); 2017-04-14 16:36:48.0 [sritz] Insert Concept add narrower relation (Solar/Space Observation Satellites [8e8b7689-0a8e-47a4-9c68-5f6a207104d5,257137] - GOES-16 [72ebfb29-14dd-4306-a28c-ecfc25fc8ad6,278801]); 2014-05-07 12:41:20.0 [128.183.164.42] Insert Concept add narrower relation (Solar/Space Observation Satellites [8e8b7689-0a8e-47a4-9c68-5f6a207104d5,73505] - DSCOVR [d9cc74c9-34f5-48a4-a982-e4c6f8a5171c,106359]); NASA GLOBAL HAWK 872 AIRCRAFT Owner/Operator: NASA Armstrong (Dryden) Flight Research Center Type: UAS Duration: 30 hours (payload and weather dependent) Useful Payload: 1,900 lbs Gross Take-off Weight: 25,600 lbs Onboard Operators: 0 Max Altitude: 65,000 ft Air Speed: 345 knots Range: 11,000 Nmi Power: Rolls-Royce AE3007H turbofan NASA SMD User Fee: $60K/week or $250K/month for access $1800/Flt hour up to 150hrs/month 2019-06-26 19:54:43.0 [sritz] update Definition (Owner/Operator: NASA Armstrong (Dryden) Flight Research Center Type: UAS Duration: 30 hours (payload and weather dependent) Useful Payload: 1,900 lbs Gross Take-off Weight: 25,600 lbs Onboard Operators: 0 Max Altitude: 65,000 ft Air Speed: 345 knots Range: 11,000 Nmi Power: Rolls-Royce AE3007H turbofan NASA SMD User Fee: $60K/week or $250K/month for access $1800/Flt hour up to 150hrs/month); 2019-06-26 19:53:53.0 [sritz] insert Definition (id: null text: Owner/Operator: NASA Armstrong (Dryden) Flight Research Center Type: UAS Duration: 30 hours (payload and weather dependent) Useful Payload: 1,900 lbs Gross Take-off Weight: 25,600 lbs Onboard Operators: 0 Max Altitude: 65,000 ft Air Speed: 345 knots Range: 11,000 Nmi Power: Rolls-Royce AE3007H turbofan NASA SMD User Fee: $60K/week or $250K/month for access $1800/Flt hour up to 150hrs/month language code: en); 2016-03-15 18:27:13.0 [saritz] S. Ritz added keyword at the request of ASDC. insert AltLabel (id: null text: NASA unmanned Global Hawk aircraft number 872 language code: en); 2016-03-15 18:26:41.0 [saritz] Insert Concept add broader relation (NASA GLOBAL HAWK 872 AIRCRAFT [8f3ab728-820e-4723-8807-c1f1e6e4a1b0,158663] - Aircraft [227d9c3d-f631-402d-84ed-b8c5a562fc27,143335]); IRS-1A The Indian Remote Sensing Satellite-1A (IRS-1A) was launched on March 17, 1988. IRS-1A is the first of a series of semi-operational/ operational remote sensing satellites developed by Indian Space Research Organisation (ISRO) for land-based applications such as agriculture,forestry, geology, and hydrology. The three-axis-stabilized sun-synchronous satellite carries two linear imaging self-scanned sensors (LISS). LISS-1 and LISS-II perform "pushbroom" scanning in visible and near IR bands to acquire images of the earth. Both push-broom scanning sensors operate in the four spectral bands: 0.45-0.52, 0.52-0.59, 0.62-0.68, and 0.77-0.86 micrometer. Local equatorial crossing time is fixed at around 10 a.m. The spacecraft platform, measuring 1.56 m x 1.66 m x 1.10 m, has the payload module attached on the top and a deployable solar array stowed on either side. Attitude control is provided by four momentum wheels, two magnetic torques, and a thruster system. Together these mechanisms provide an estimated accuracy of plus or minus 0.10 deg in all three axes. Group: Platform_Details Entry_ID: IRS-1A Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: IRS (Indian Remote Sensing Satellite) Short_Name: IRS-1A Long_Name: Indian Remote Sensing Satellite-1A End_Group Group: Synonymous_Platform_Names Short_Name: IRS-1A End_Group Group: Platform_Associated_Instruments Short_Name: LISS-II Short_Name: LISS-I End_Group Group: Orbit Orbit_Altitude: 904 km Orbit_Inclination: 99.01 deg Period: 103.1minutes Repeat_Cycle: 22 days Perigee: 863 km Apogee: 917 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-10-05 Online_Resource: http://www.isro.gov.in/satellites/irs-1a.aspx Sample_Image: http://www.isro.gov.in/satellites/images/irs1a_img.gif Group: Platform_Logistics Launch_Date: 1988-03-17 Launch_Site: BAIKONUR COSMODROME, TYURATAM, RUSSIA Primary_Sponsor: India End_Group End_Group R/V AA SNOE SNOE ("snowy") was a small scientific satellite that measured the effects of energy from the sun and from the magnetosphere on the density of nitric oxide in the Earth's upper atmosphere. The spacecraft and its instruments were designed and built at LASP, the Laboratory for Atmospheric and Space Physics at the University of Colorado, Boulder. SNOE was launched on February 26, 1998, and was operated from the mission operations center at the LASP Space Technology Research building. SNOE re-entered the Earth's atmosphere on Dec. 13, 2003, completing a very successful mission. This site contains a description of the SNOE mission, spacecraft drawings and images, and provides access to the scientific data and publications. An archive of launch activities and development personnel have been retained. Information provided by http://lasp.colorado.edu/snoe/ Group: Platform_Details Entry_ID: SNOE Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Platform_Series_or_Entity: Explorer Short_Name: SNOE Long_Name: Student Nitric Oxide Explorer End_Group Group: Synonymous_Platform_Names Short_Name: SNOE Short_Name: Explorer 72 Short_Name: STEDI-SNOE Short_Name: Student Nitric Oxide Explorer Short_Name: UNEX/SNOE Short_Name: 25233 End_Group Group: Platform_Associated_Instruments Short_Name: AP Short_Name: GPS Short_Name: SXP Short_Name: UVS End_Group Group: Orbit Orbit_Altitude: 580 km Orbit_Inclination: 97.69999694824219° Degrees Period: 95.80000305175781 minutes Perigee: 535.0 km Apogee: 580.0 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-08-21 Online_Resource: http://nasascience.nasa.gov/missions/snoe Online_Resource: http://lasp.colorado.edu/snoe/ Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1998-012A Sample_Image: http://lasp.colorado.edu/snoe/images/UVS_New.gif Group: Platform_Logistics Launch_Date: 1998-02-26 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: USA/NASA Primary_Sponsor: University of Colorado End_Group End_Group G-V 2013-05-21 14:38:04.0 [aaleman] created new platform insert AltLabel (id: null text: Gulfstream V language code: en); 2013-05-21 14:36:54.0 [aaleman] Insert Concept add broader relation (G-V [924c4b23-30f0-451f-baa2-b6de47c94e58,105145] - Aircraft [227d9c3d-f631-402d-84ed-b8c5a562fc27,73411]); Living with a Star NCEP-CFSR 2015-08-10 18:54:37.0 [epneff] Added long name insert AltLabel (id: null text: NCEP Climate Forecast System Reanalysis language code: en); 2015-08-10 18:54:18.0 [epneff] Insert Concept add broader relation (NCEP-CFSR [929347c6-e7d9-4e72-a6c8-8926a369cb6b,158247] - Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215]); GREAT WALL STATION 2016-10-28 19:57:12.0 [gee-cee] insert AltLabel (id: null text: CHINESE GREAT WALL STATION language code: en); 2016-10-28 19:56:48.0 [gee-cee] Insert Concept add broader relation (GREAT WALL STATION [92aae4b1-cd4c-41b8-b931-4c2b70790baf,278483] - In Situ Land-based Platforms [4f396ff6-7bea-4ba4-afa3-198ebd914a4a,256725]); Pleiades-1B Pléiades 1A and Pléiades 1B operate as a constellation in the same orbit, phased 180° apart. The identical twin satellites deliver very-high-resolution optical data products in record time and offer a daily revisit capability to any point on the globe. The Pléiades constellation is designed to obtain data in double-quick time: Ability to acquire imagery anywhere in the world in less than 24 hrs. in response to a crisis or natural disaster. Regular monitoring, as often as every day if required. Three satellite work plans a day ensure easy handling of last-minute tasking requests. Twice the coverage and twice the chance of obtaining cloud-free imagery. 2018-06-14 13:07:29.0 [mmorahan] insert Definition (id: null text: Pléiades 1A and Pléiades 1B operate as a constellation in the same orbit, phased 180° apart. The identical twin satellites deliver very-high-resolution optical data products in record time and offer a daily revisit capability to any point on the globe. The Pléiades constellation is designed to obtain data in double-quick time: Ability to acquire imagery anywhere in the world in less than 24 hrs. in response to a crisis or natural disaster. Regular monitoring, as often as every day if required. Three satellite work plans a day ensure easy handling of last-minute tasking requests. Twice the coverage and twice the chance of obtaining cloud-free imagery. language code: en); 2018-06-14 13:00:44.0 [mmorahan] Insert Concept add broader relation (Pleiades-1B [92bdb34f-5df0-498d-b3c9-477ff3a1f80a,367719] - PLEIADES [516a9bb2-0171-4ad2-8d4f-3f7d1219d393,344967]); GEMINI-7 - Spacecraft Brief Description - GEMINI 7 was the fourth manned earth-orbiting spacecraft of the GEMINI series. its mission priorities were (1) to demonstrate a 2-week flight, (2) to perform stationkeeping with the GEMINI launch vehicle stage 2, (3) to evaluate the 'shirt sleeve' environment, (4) to act as a rendezvous target for GEMINI 6, and (5) to demonstrate controlled reentry to within 11 km of the landing point. The crew members had four scientific experiments to perform. These were synoptic terrain, synoptic weather, dim light photography, and visual acuity in the space environment. Four technological and eight medical experiments were also conducted. All experiments and mission objectives were successfully completed. The spacecraft reentered the atmosphere after 15 days in space and landed within 11 km of the target point. - Auxiliary Information - Launch Date and Time : 1965-12-04 19:26:00 Epoch Date and Time : 1965-12-12 Apogee (km or AU): 298. Perigee (km or AU): 292. Inclination (degree) : 28.9 Orbit Type : Geocentric Additional information available at "http://science.ksc.nasa.gov/history/gemini/gemini-vii/gemini-vii.html" COMPUTERS COMPUTER [Source: Mirriam-Webster, http://www.merriam-webster.com/dictionary/computer A programmable usually electronic device that can store, retrieve, and process data. Group: Platform_Details Entry_ID: COMPUTER Group: Platform_Identification Platform_Category: In Situ Land-based Platforms Short_Name: COMPUTER End_Group Group: Platform_Associated_Instruments Short_Name: RTMM End_Group Creation_Date: 2012-05-15 Online_Resource: http://en.wikipedia.org/wiki/Computer End_Group 2016-06-09 18:37:59.0 [epneff] added altLabel insert AltLabel (id: null text: COMPUTER language code: en); GEMINI-8 Spacecraft Brief Description Gemini 8 was the sixth manned earth-orbiting spacecraft of the Gemini series. The primary mission objectives were to perform rendezvous and four docking tests with the Agena target vehicle and to execute an extravehicular activity (EVA) experiment. Ten technological, medical, and scientific experiments were carried on board. Of the six scientific experiments only the Agena micrometeorite collection was successful. the others -- (1) zodiacal light photography, (2) frog egg growth, (3) synoptic terrain photography, (4) nuclear emulsions, and (5) spectrophotography of clouds -- were incomplete, owing to a large loss of fuel and early termination of the mission. The EVA docking and other maneuvers were canceled. The spacecraft reentered the earth's atmosphere after 6.5 orbits and landed in the pacific ocean on March 17, 1966. Auxiliary Information Launch Date and Time : 1966-03-16 16:48:00 Epoch Date and Time : 1966-03-17 Orbit Type : Geocentric Apogee(km) : 298. Perigee(km) : 285. Inclination : 28.88 Additional information available at "http://science.ksc.nasa.gov/history/gemini/gemini-viii/gemini-viii.html" ISS INTERNATIONAL SPACE STATION (ISS) The International Space Station is the largest and most complex international scientific project in history. The station represents a move of unprecedented scale off the home planet. Led by the United States, the International Space Station draws upon the scientific and technological resources of 16 nations: Canada, Japan, Russia, 11 nations of the European Space Agency and Brazil. The goals of the International Space Station are: 1. Find solutions to crucial problems in medicine, ecology and other areas of science. 2. Lay the foundation for developing space-based commerce and enterprise. 3. Create greater worldwide demand for space-related education at all levels by cultivating the excitement, wonder and discovery that the ISS symbolizes. 4. Foster world peace through high-profile, long-term international cooperation in space. [Summary provided by Boeing and NASA] Group: Platform_Details Entry_ID: ISS Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Short_Name: ISS Long_Name: International Space Station End_Group Group: Synonymous_Platform_Names Short_Name: ISS Short_Name: FGB Short_Name: MKS Short_Name: Space Station Short_Name: Unity Short_Name: Zarya Short_Name: 25544 End_Group Group: Platform_Associated_Instruments Short_Name: CATS End_Group Group: Orbit Orbit_Altitude: ~ 350 Km Orbit_Inclination: 51.6° Period: 92.0 minutes Perigee: 384.0 km Apogee: 396.0 km End_Group Creation_Date: 2008-01-30 Online_Resource: https://www.nasa.gov/mission_pages/station/main/index.html Online_Resource: http://en.wikipedia.org/wiki/International_Space_Station Sample_Image: http://www.our-picks.com/wp-content/uploads/2007/06/international-space-station.jpg Group: Platform_Logistics Launch_Date: 1998-11-20 Launch_Site: Baikonur Cosmodrome, Tyuratam, Russia Primary_Sponsor: USA/NASA Primary_Sponsor: Russia/RKA Primary_Sponsor: Canada/CSA Primary_Sponsor: Japan/JAXA Primary_Sponsor: ESA End_Group End_Group 2018-12-03 16:20:46.0 [sritz] update WeightedRelation (Platform-Instrument); update WeightedRelation (1); 2018-12-03 16:20:06.0 [sritz] update Definition (The International Space Station is the largest and most complex international scientific project in history. The station represents a move of unprecedented scale off the home planet. Led by the United States, the International Space Station draws upon the scientific and technological resources of 16 nations: Canada, Japan, Russia, 11 nations of the European Space Agency and Brazil. The goals of the International Space Station are: 1. Find solutions to crucial problems in medicine, ecology and other areas of science. 2. Lay the foundation for developing space-based commerce and enterprise. 3. Create greater worldwide demand for space-related education at all levels by cultivating the excitement, wonder and discovery that the ISS symbolizes. 4. Foster world peace through high-profile, long-term international cooperation in space. [Summary provided by Boeing and NASA] Group: Platform_Details Entry_ID: ISS Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Short_Name: ISS Long_Name: International Space Station End_Group Group: Synonymous_Platform_Names Short_Name: ISS Short_Name: FGB Short_Name: MKS Short_Name: Space Station Short_Name: Unity Short_Name: Zarya Short_Name: 25544 End_Group Group: Platform_Associated_Instruments Short_Name: CATS End_Group Group: Orbit Orbit_Altitude: ~ 350 Km Orbit_Inclination: 51.6° Period: 92.0 minutes Perigee: 384.0 km Apogee: 396.0 km End_Group Creation_Date: 2008-01-30 Online_Resource: https://www.nasa.gov/mission_pages/station/main/index.html Online_Resource: http://en.wikipedia.org/wiki/International_Space_Station Sample_Image: http://www.our-picks.com/wp-content/uploads/2007/06/international-space-station.jpg Group: Platform_Logistics Launch_Date: 1998-11-20 Launch_Site: Baikonur Cosmodrome, Tyuratam, Russia Primary_Sponsor: USA/NASA Primary_Sponsor: Russia/RKA Primary_Sponsor: Canada/CSA Primary_Sponsor: Japan/JAXA Primary_Sponsor: ESA End_Group End_Group); update Resource (image); insert WeightedRelation (id: null related concept uuid: 5218fe2e-bea7-4654-bc54-7b9ec5503b60 relationship type: null relationship value: null generated by: null); 2016-06-09 18:44:37.0 [epneff] added altLabel insert AltLabel (id: null text: INTERNATIONAL SPACE STATION (ISS) language code: en); GOES-6 [Source: NASA NSSDC, http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1983-041A ] GOES 6 was launched in April 1983 and was a NASA-developed, NOAA-operated, geosynchronous, and operational spacecraft. The cylindrically shaped spacecraft measured 190.5 cm in diameter and 230 cm in length, exclusive of a magnetometer that extended an additional 83 cm beyond the cylinder shell. The primary structural members were a honeycombed equipment shelf and thrust tube. The VISSR telescope was mounted on the equipment shelf and viewed the Earth through a special aperture in the side of the spacecraft. A support structure extended radially out from the thrust tube and was affixed to the solar panels, which formed the outer walls of the spacecraft and provided the primary source of electrical power. Located in the annulus-shaped space between the thrust tube and the solar panels were stationkeeping and dynamics control equipment, batteries, and most of the SEM equipment. Proper spacecraft attitude and spin rate (approximately 100 rpm) were maintained by two separate sets of jet thrusters mounted around the spacecraft equator and activated by ground command. The spacecraft used both UHF-band and S-band frequencies in its telemetry and command subsystem. A low-power VHF transponder provided telemetry and command during launch and then served as a backup for the primary subsystem once the spacecraft attained orbit. The spin-stabilized spacecraft carried a visible infrared spin-scan radiometer atmospheric sounder, meteorological data collection and transmission system, space environment monitor, and a biaxial fluxgate magnetometer. GOES 6 was moved from its 135 degrees West position to a more central 98 degrees West position when GOES 5 failed on July 29, 1984. For more information on GOES satellites: http://www.oso.noaa.gov/goes/ Group: Platform_Details Entry_ID: GOES-6 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: GOES (Geostationary Operational Environmental Satellite) Short_Name: GOES-6 Long_Name: Geostationary Operational Environmental Satellite 6 End_Group Group: Synonymous_Platform_Names Short_Name: GOES F Short_Name: 14050 End_Group Group: Platform_Associated_Instruments Short_Name: SXM Short_Name: VAS Short_Name: EPM End_Group Group: Orbit Orbit_Type: GEO > Geosynchronous > Geostationary End_Group Creation_Date: 2007-10-04 Online_Resource: http://www.oso.noaa.gov/goes/ Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1983-041A Group: Platform_Logistics Launch_Date: 1983-04-28 Launch_Site: CAPE CANAVERAL/KENNEDY SPACE CENTER, USA Primary_Sponsor: USA/NASA Primary_Sponsor: USA/NOAA End_Group End_Group INSAT (Indian National Satellite) 2014-06-12 13:46:25.0 [mpmorahan] Insert Concept add narrower relation (INSAT (Indian National Satellite) [949ab40f-3954-4c81-a063-275d0e13a14e,73981] - INSAT-3D [5999e653-21ea-49ef-977a-13b5fe40fa36,106461]); R/V OSHORO-MARU 2012-06-29 20:35:34.0 [aaleman] Insert Concept add broader relation (R/V OSHORO-MARU [d4fa5a8e-39fe-4d3c-b832-9e06469e1cc8,40289] - SHIPS [82a67b12-e99d-4c90-8a6a-a6f79d4c3c7b,31201]); Nimbus-5 Nimbus-5 was launched in December 1972 and was a research-and-development satellite designed to serve as a stabilized, earth-oriented platform for the testing of advanced meteorological sensor systems and collecting meteorological and geological data on a global scale. The polar-orbiting spacecraft consisted of three major structures: (1) a hollow, ring-shaped sensor mount, (2) solar paddles, and (3) a control system housing. The solar paddles and control system housing were connected to the sensor mount by a truss structure, giving the satellite the appearance of an ocean buoy. Nimbus-5 was nearly 3.7 m tall, 1.5 m in diameter at the base, and about 3 m wide with solar paddles extended. The torus-shaped sensor mount, which formed the satellite base, housed the electronics equipment and battery modules. The lower surface of the torus provided mounting space for sensors and antennas. A box-beam structure mounted within the center of the torus provided support for the larger sensor experiments. Mounted on the control system housing, which was located on top of the spacecraft, were sun sensors, horizon scanners, and a command antenna. An advanced attitude-control system permitted the spacecraft orientation to be controlled to within plus or minus 1 degree in all three axes (pitch, roll, and yaw). Primary experiments included a temperature-humidity infrared radiometer (THIR) for measuring day and night surface and cloudtop temperatures as well as the water vapor content of the upper atmosphere, electrically scanning microwave radiometer (ESMR) for mapping the microwave radiation from the earth's surface and atmosphere, infrared temperature profile radiometer (ITPR) for obtaining vertical profiles of temperature and moisture, Nimbus E microwave spectrometer (NEMS) for determining tropospheric temperature profiles, atmospheric water vapor abundances, and cloud liquid water contents, selective chopper radiometer (SCR) for observing the global temperature structure of the atmosphere, and a surface composition mapping radiometer (SCMR) for measuring the differences in the thermal emission characteristics of the earth's surface. __________ Taken from the NSSDC System for Information Retrieval and Storage (SIRS). For more information contact the NSSDC Coordinated Request and User Support Office, 301-286-6695 (NASA Goddard Space Flight Center, Code 933.4, Greenbelt, Maryland 20771, USA). Nimbus-5 User's Guide Group: Platform_Details Entry_ID: NIMBUS-5 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NIMBUS Short_Name: NIMBUS-5 End_Group Group: Platform_Associated_Instruments Short_Name: THIR Short_Name: SCR Short_Name: NEMS Short_Name: ITPR Short_Name: ESMR Short_Name: SCMR End_Group Group: Orbit Orbit_Altitude: 1020 km Orbit_Inclination: 100.10 degrees Period: 107.20 minutes Perigee: 1088 km Apogee: 1101 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1972-097A Online_Resource: http://nasascience.nasa.gov/missions/nimbus Group: Platform_Logistics Launch_Date: 1972-12-11 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: USA/NASA End_Group End_Group 2015-05-12 16:54:32.0 [saritz] update PrefLabel (Nimbus-5); EOLE Eole, a.k.a. CAS 1 (Cooperative Application Satellite), FR 2 (France), the second French experimental data relay satellite for meteorological data and the first launched by NASA under a cooperative agreement with the Centre National d'Etudes Spatiales (CNES), was designed to function primarily as a communications satellite to acquire and relay telemetered data on altitude, pressure, temperature, moisture, and upper atmospheric wind velocities from instrumented earth-circling constant density meteorological balloons. The octagonally shaped satellite measured 0.71 m across opposite corners and was 0.58 m long. Electrical power (20 W average) was supplied by eight rectangular solar panels deployed 45 deg from the EOLE 1 upper octagonal structure after orbital insertion, and by 15 rechargeable silver-cadmium batteries. Constant earth orientation was maintained by a deployable 10.06-m gravity gradient boom. Satellite spin was near zero rpm in orbit, and the attitude was programme! d to remain stable within 9 deg of local vertical. The data were stored on board the spacecraft and unloaded on command when the spacecraft was within range of the ground station. The onboard telemetry consisted of (1) a 136.350-MHz downlink transmitter for relaying balloon telemetry to ground stations and also to serve as a tracking beacon, (2) a 148.25-MHz receiver for receiving spacecraft commands and telemetry programs for balloon operations, and (3) a spacecraft-to-balloon transmitter (464.84 MHz) and receiver (401.7196 MHz). The satellite operation was successful with the exception of the inadvertent destruction of 71 balloons by an erroneous ground command. The last balloon ceased transmitting in January 1973. However, the spacecraft was subsequently used to track and receive data from ocean buoys, icebergs, and ships. More info at: "http://www.skyrocket.de/space/index_frame.htm?http://www.skyrocket.de /space/doc_sdat/eole.htm" [Source: Gunther's Space Page] IMAGE The IMAGE spacecraft was launched from Vandenberg AFB on March 25, 2000, at 20:34:43 UTC. IMAGE is the first satellite mission dedicated to imaging the Earth's magnetosphere, the region of space controlled by the Earth's magnetic field and containing extremely tenuous plasmas of both solar and terrestrial origin. Invisible to standard astronomical observing techniques, these populations of ions and electrons have traditionally been studied by means of localized measurements with charged particle detectors, magnetometers, and electric field instruments. Instead of such in-situ measurements, IMAGE employs a variety of imaging techniques to "see the invisible" and to produce the first comprehensive global images of the plasma populations in the inner magnetosphere. With these images, space scientists are able to observe, in a way never before possible, the large-scale dynamics of the magnetosphere and the interactions among its constituent plasma populations. Additional information available at "http://pluto.space.swri.edu/IMAGE/" Group: Platform_Details Entry_ID: IMAGE Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: IMAGE Long_Name: Imager for Magnetopause -to - Aurora Global Exploration End_Group Group: Synonymous_Platform_Names Short_Name: IMAGE End_Group Group: Platform_Associated_Instruments Short_Name: UVI End_Group Creation_Date: 2007-11-20 Online_Resource: http://image.gsfc.nasa.gov/ Sample_Image: http://image.gsfc.nasa.gov/image/image_launch_a5.jpg Group: Platform_Logistics Launch_Date: 2000-03-25 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: NASA End_Group End_Group VENERA-14 Venera 14 Mission Description: Venera 13 and 14 were identical spacecraft built to take advantage of the 1981 Venus launch opportunity and launched 5 days apart. The Venera 14 mission consisted of a bus (81-110A) and an attached descent craft (81-110D). The Venera 14 descent craft/lander was a hermetically sealed pressure vessel, which contained most of the instrumentation and electronics, mounted on a ring-shaped landing platform and topped by an antenna. The design was similar to the earlier Venera 9-12 landers. It carried instruments to take chemical and isotopic measurements, monitor the spectrum of scattered sunlight, and record electric discharges during its descent phase through the Venusian atmosphere. The spacecraft utilized a camera system, an X-ray fluorescence spectrometer, a screw drill and surface sampler, a dynamic penetrometer, and a seismometer to conduct investigations on the surface. After launch and a four month cruise to Venus, the descent vehicle separated from the bus and plunged into the Venus atmosphere on 5 March 1982. After entering the atmosphere a parachute was deployed. At an altitude of about 50 km the parachute was released and simple airbraking was used the rest of the way to the surface. Venera 14 landed about 950 km southwest of Venera 13 near the eastern flank of Phoebe Regio at 13 deg 15 min S by 310 E on a basaltic plain. After landing an imaging panorama was started and a mechanical drilling arm reached to the surface and obtained a sample, which was deposited in a hermetically sealed chamber, maintained at 30 degrees C and a pressure of about .05 atmospheres. The composition of the sample was determined by the X-ray flourescence spectrometer, showing it to be similar to oceanic tholeiitic basalts. The lander survived for 57 minutes (the planned design life was 32 minutes) in an environment with a temperature of 465 degrees C and a pr! essure of 94 Earth atmospheres. The descent vehicle transmitted data to the bus, which acted as a data relay as it. [Source: NASA] Group: Platform_Details Entry_ID: VENERA-14 Group: Platform_Identification Platform_Category: Interplanetary Spacecraft Platform_Series_or_Entity: LANDER Short_Name: VENERA-14 End_Group Online_Resource: http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/venera1314.html End_Group GLONASS (Russia's GLObal NAvigation Satellite System) Global'naya Navigatsionnay Sputnikovaya Sistema Satellites GLONASS or "Global Navigation Satellite System", is a space-based satellite navigation system operating in the radionavigation-satellite service. It provides an alternative to GPS and is the second navigational system in operation with global coverage and of comparable precision. Manufacturers of GPS devices say that adding GLONASS made more satellites available to them, meaning positions can be fixed more quickly and accurately, especially in built-up areas where the view to some GPS satellites is obscured by buildings. Smartphones generally tend to use the same chipsets and the versions used since 2015 receive GLONASS signals and positioning information along with GPS. Since 2012, GLONASS was the second most used positioning system in mobile phones after GPS. The system has the advantage that smartphone users receive a more accurate reception identifying location to within 2 meters. 2017-08-15 13:58:10.0 [tstevens] insert Definition (id: null text: GLONASS or "Global Navigation Satellite System", is a space-based satellite navigation system operating in the radionavigation-satellite service. It provides an alternative to GPS and is the second navigational system in operation with global coverage and of comparable precision. Manufacturers of GPS devices say that adding GLONASS made more satellites available to them, meaning positions can be fixed more quickly and accurately, especially in built-up areas where the view to some GPS satellites is obscured by buildings. Smartphones generally tend to use the same chipsets and the versions used since 2015 receive GLONASS signals and positioning information along with GPS. Since 2012, GLONASS was the second most used positioning system in mobile phones after GPS. The system has the advantage that smartphone users receive a more accurate reception identifying location to within 2 meters. language code: en); 2017-08-15 11:49:33.0 [tstevens] update AltLabel (Global'naya Navigatsionnay Sputnikovaya Sistema Satellites); 2017-08-15 11:33:32.0 [tstevens] update PrefLabel (GLONASS (Russia's GLObal NAvigation Satellite System)); 2017-08-14 19:12:15.0 [tstevens] insert AltLabel (id: null category: null text: Global’naya Navigatsionnay Sputnikovaya Sistema Satellites language code: en); 2017-08-14 19:11:19.0 [tstevens] update PrefLabel (GLONASS (Russia’s GLObal NAvigation Satellite System)); PROBA-3 AE (Atmosphere Explorer) COSMO-SKYMED COSMO-SkyMed (Constellation of Small Satellites for Mediterranean basin Observation) is a 4-spacecraft constellation, conceived by ASI (Agenzia Spaziale Italiana), and funded by the Italian Ministry of Research (MUR) and the Italian Ministry of Defense (MOD), Rome, Italy. The program is managed in cooperation by ASI and MOD. Each of the four satellites is equipped with a SAR (Synthetic Aperture Radar) instrument and is capable of operating in all visibility conditions at high resolution and in real time. The overall objective of this program is global Earth observation and the relevant data exploitation for the needs of the military community as well as for the civil (institutional, commercial) community. Sample applications of COSMO-SkyMed data are seen the following fields: • Defense and security applications: Surveillance, intelligence, mapping, damage assessment, vulnerability assessment, target detection/localization • Risk management applications: Floods, droughts, landslides, volcanic/seismic, forest fire, industrial hazards, water pollution • Other applications: Marine and coastal environments, agriculture, forestry, cartography, environment, geology and exploration, telecommunication, utilities and planning • Provision of commercial imaging services • The high revisit frequency offered by the four X-band SAR spacecraft is also expected to provide a unique potential to the operational meteorological user community through provision of ancillary data and/or data on meteo-correlated phenomena, in particular as regards sea ice monitoring and study of ocean wave patterns. Background: In 1996 the Italian Government provided initial funding for the realization of a national Earth observation program. In 1997 the general guidelines for the 1998-2002 Italian National Space Plan (PSN) were approved including the activities on Earth observation. The strategic element in this plan is the COSMO-SkyMed dual-use program of ASI. 1) 2) In the summer of 2001, the Italian Ministry of Defense became a partner in the COSMO-SkyMed program (a welcome funding partner for the Italian Ministry of Research). However, the dual-use nature of the COSMO-SkyMed program, i. e. civil (research and commercial) and military use of its data products, resulted in a virtually classified program. A great disadvantage of the new arrangement is that rather sparse technical information of the mission can only be made available to the public. Although the first constellation satellite SAR instruments (SAR-2000) will observe in X-band (9.6 GHz with a wavelength of 3.1 cm), multi-mode scenarios (X-, C- L- and P-band) are planned for the future. The overall system architecture is composed of a space segment, a constellation of SAR satellites, and a ground segment including full featured user services. The requirements call for the following general performance characteristics: 3) • Full global observation coverage with all weather, day/night acquisition capability • Collection capability of large areas within a single pass, with along-track stereo imaging during a single pass • High image quality, to allow a robust image interpretability at the requested scale of analysis (data sets are characterized by adequate spatial and spectral resolution suitable to perform analyses at different scales of detail) • Ground track repeatability: the satellites of the SAR constellation shall have a ground track repeatability of better than 1 km • Fast response times (from the data/service user request up to the data/service delivery to that requiring user). The SABRINA project was started in 2004/5. The COSMO-SkyMed space segment is composed of a constellation of four SAR satellites. The PRIMA \[Piattaforma Riconfigurabile Italiana Multi-Applicativa (Reconfigurable Italian Platform for Multiple Applications)\] bus of Alcatel Alenia Space is being employed. Alcatel Alenia Space is also the prime contractor of the space segment \[funding by ASI and I-AD (Ministry of Defense)\]. - Note: As of April 10, 2007, the EC approved the transfer to Thales of Alcatel-Lucent's shareholdings in the two space sector joint venture companies Alcatel Alenia Space and Telespazio. Hence, Alcatel Alenia Space was renamed to Thales Alenia Space. The S/C is three-axis stabilized, it consists of the main body (bus), two deployable solar arrays, and a SAR antenna. The bus provides all support functions like: AOCS, electrical power (power generation, storage and distribution), data handling, thermal control, RF communications, and on-orbit propulsion for orbit injection and maintenance. The platform mechanical configuration consists of two elements or modules, namely: • SVM (Service Module) at the bottom of the bus which contains all bus subsystems including the propulsion module • PLM (Payload Module) at the top, dedicated to the payload complement, the PDHT (Payload Data Handing and Transmission) subsystem, and the AOCS (Attitude and Orbit Control Subsystem) with star trackers gyros actuators. The bus structure material is CFRP (Carbon Fiber Reinforced Plastic) while SVM and PLM consist of aluminum alloys. The interfaces of the SAR antenna, star trackers and gyros are mounted on the CFRP structure for pointing precision and stability (a star tracker is being used as well as a high-quality GPS receiver). The SSTI (Satellite-to-Satellite Tracking Instrument) is the LAGRANGE GPS receiver of Laben SpA. The SAR antenna bore sight is pointing with an incidence angle about 38º to the right side of the S/C ground track. AOCS provides an antenna steering capability of ±2º in yaw as well as for a re-pointing capability to the left side of the ground track. Each S/C in the constellation features a RCT (Reaction Control Thruster) system for orbit maintenance. The mass of each spacecraft is about 1700 kg. The design life is 5 years. The S/C provides an onboard operational autonomy for a period of 24 hours. Launch: The launch of the first COSMO spacecraft in the constellation took place on June 8, 2007 (UTC). The launch was provided by the Boeing Company on a Delta-2 (7420-10 configuration) vehicle from VAFB, CA. This represented the first commercial Delta-2 launch since the formation of the United Launch Alliance (ULA) in December 2006. Circular sun-synchronous dawn-dusk orbit, nominal altitude = 619.6 km, inclination = 97.86º, period = 97.1 min, with LTAN (Local Time of Ascending Node) at 6:00 AM, 14.8125 rev./day (or 14 13/16). All spacecraft of the SAR constellation will be positioned in the same orbital plane with a phasing outlined in Table 2. The nominal repeat cycle is 16 days; however, each single satellite will have a near revisit time of 5 days. Satellite Launch date Nominal EOL (End Of Life) Extended lifetime CSK-1 8-Jun-07 Jun-14 7-Jun-16 CSK-2 9-Dec-07 Dec-14 8-Dec-16 CSK-3 25-Oct-08 Oct-15 25-Oct-16 CSK-4 6-Nov-10 Nov-17 6-Nov-17 COSMO-SKYMED Platform_Details Platform_Category: Earth Observation Satellites Platform_Associated_Instruments Short_Name: SAR Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous Primary_Sponsor: Italian Ministry of Defense (MOD) Primary_Sponsor: Agenzia Spaziale Italiana (ASI), Italy 2019-02-14 17:37:41.0 [mmorahan] update Definition (COSMO-SkyMed (Constellation of Small Satellites for Mediterranean basin Observation) is a 4-spacecraft constellation, conceived by ASI (Agenzia Spaziale Italiana), and funded by the Italian Ministry of Research (MUR) and the Italian Ministry of Defense (MOD), Rome, Italy. The program is managed in cooperation by ASI and MOD. Each of the four satellites is equipped with a SAR (Synthetic Aperture Radar) instrument and is capable of operating in all visibility conditions at high resolution and in real time. The overall objective of this program is global Earth observation and the relevant data exploitation for the needs of the military community as well as for the civil (institutional, commercial) community. Sample applications of COSMO-SkyMed data are seen the following fields: • Defense and security applications: Surveillance, intelligence, mapping, damage assessment, vulnerability assessment, target detection/localization • Risk management applications: Floods, droughts, landslides, volcanic/seismic, forest fire, industrial hazards, water pollution • Other applications: Marine and coastal environments, agriculture, forestry, cartography, environment, geology and exploration, telecommunication, utilities and planning • Provision of commercial imaging services • The high revisit frequency offered by the four X-band SAR spacecraft is also expected to provide a unique potential to the operational meteorological user community through provision of ancillary data and/or data on meteo-correlated phenomena, in particular as regards sea ice monitoring and study of ocean wave patterns. Background: In 1996 the Italian Government provided initial funding for the realization of a national Earth observation program. In 1997 the general guidelines for the 1998-2002 Italian National Space Plan (PSN) were approved including the activities on Earth observation. The strategic element in this plan is the COSMO-SkyMed dual-use program of ASI. 1) 2) In the summer of 2001, the Italian Ministry of Defense became a partner in the COSMO-SkyMed program (a welcome funding partner for the Italian Ministry of Research). However, the dual-use nature of the COSMO-SkyMed program, i. e. civil (research and commercial) and military use of its data products, resulted in a virtually classified program. A great disadvantage of the new arrangement is that rather sparse technical information of the mission can only be made available to the public. Although the first constellation satellite SAR instruments (SAR-2000) will observe in X-band (9.6 GHz with a wavelength of 3.1 cm), multi-mode scenarios (X-, C- L- and P-band) are planned for the future. The overall system architecture is composed of a space segment, a constellation of SAR satellites, and a ground segment including full featured user services. The requirements call for the following general performance characteristics: 3) • Full global observation coverage with all weather, day/night acquisition capability • Collection capability of large areas within a single pass, with along-track stereo imaging during a single pass • High image quality, to allow a robust image interpretability at the requested scale of analysis (data sets are characterized by adequate spatial and spectral resolution suitable to perform analyses at different scales of detail) • Ground track repeatability: the satellites of the SAR constellation shall have a ground track repeatability of better than 1 km • Fast response times (from the data/service user request up to the data/service delivery to that requiring user). The SABRINA project was started in 2004/5. The COSMO-SkyMed space segment is composed of a constellation of four SAR satellites. The PRIMA \[Piattaforma Riconfigurabile Italiana Multi-Applicativa (Reconfigurable Italian Platform for Multiple Applications)\] bus of Alcatel Alenia Space is being employed. Alcatel Alenia Space is also the prime contractor of the space segment \[funding by ASI and I-AD (Ministry of Defense)\]. - Note: As of April 10, 2007, the EC approved the transfer to Thales of Alcatel-Lucent's shareholdings in the two space sector joint venture companies Alcatel Alenia Space and Telespazio. Hence, Alcatel Alenia Space was renamed to Thales Alenia Space. The S/C is three-axis stabilized, it consists of the main body (bus), two deployable solar arrays, and a SAR antenna. The bus provides all support functions like: AOCS, electrical power (power generation, storage and distribution), data handling, thermal control, RF communications, and on-orbit propulsion for orbit injection and maintenance. The platform mechanical configuration consists of two elements or modules, namely: • SVM (Service Module) at the bottom of the bus which contains all bus subsystems including the propulsion module • PLM (Payload Module) at the top, dedicated to the payload complement, the PDHT (Payload Data Handing and Transmission) subsystem, and the AOCS (Attitude and Orbit Control Subsystem) with star trackers gyros actuators. The bus structure material is CFRP (Carbon Fiber Reinforced Plastic) while SVM and PLM consist of aluminum alloys. The interfaces of the SAR antenna, star trackers and gyros are mounted on the CFRP structure for pointing precision and stability (a star tracker is being used as well as a high-quality GPS receiver). The SSTI (Satellite-to-Satellite Tracking Instrument) is the LAGRANGE GPS receiver of Laben SpA. The SAR antenna bore sight is pointing with an incidence angle about 38º to the right side of the S/C ground track. AOCS provides an antenna steering capability of ±2º in yaw as well as for a re-pointing capability to the left side of the ground track. Each S/C in the constellation features a RCT (Reaction Control Thruster) system for orbit maintenance. The mass of each spacecraft is about 1700 kg. The design life is 5 years. The S/C provides an onboard operational autonomy for a period of 24 hours. Launch: The launch of the first COSMO spacecraft in the constellation took place on June 8, 2007 (UTC). The launch was provided by the Boeing Company on a Delta-2 (7420-10 configuration) vehicle from VAFB, CA. This represented the first commercial Delta-2 launch since the formation of the United Launch Alliance (ULA) in December 2006. Circular sun-synchronous dawn-dusk orbit, nominal altitude = 619.6 km, inclination = 97.86º, period = 97.1 min, with LTAN (Local Time of Ascending Node) at 6:00 AM, 14.8125 rev./day (or 14 13/16). All spacecraft of the SAR constellation will be positioned in the same orbital plane with a phasing outlined in Table 2. The nominal repeat cycle is 16 days; however, each single satellite will have a near revisit time of 5 days. Satellite Launch date Nominal EOL (End Of Life) Extended lifetime CSK-1 8-Jun-07 Jun-14 7-Jun-16 CSK-2 9-Dec-07 Dec-14 8-Dec-16 CSK-3 25-Oct-08 Oct-15 25-Oct-16 CSK-4 6-Nov-10 Nov-17 6-Nov-17 COSMO-SKYMED Platform_Details Platform_Category: Earth Observation Satellites Platform_Associated_Instruments Short_Name: SAR Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous Primary_Sponsor: Italian Ministry of Defense (MOD) Primary_Sponsor: Agenzia Spaziale Italiana (ASI), Italy); 2019-02-14 17:32:01.0 [mmorahan] update Definition (COSMO-SkyMed (Constellation of Small Satellites for Mediterranean basin Observation) is a 4-spacecraft constellation, conceived by ASI (Agenzia Spaziale Italiana), and funded by the Italian Ministry of Research (MUR) and the Italian Ministry of Defense (MOD), Rome, Italy. The program is managed in cooperation by ASI and MOD. Each of the four satellites is equipped with a SAR (Synthetic Aperture Radar) instrument and is capable of operating in all visibility conditions at high resolution and in real time. The overall objective of this program is global Earth observation and the relevant data exploitation for the needs of the military community as well as for the civil (institutional, commercial) community. Sample applications of COSMO-SkyMed data are seen the following fields: • Defense and security applications: Surveillance, intelligence, mapping, damage assessment, vulnerability assessment, target detection/localization • Risk management applications: Floods, droughts, landslides, volcanic/seismic, forest fire, industrial hazards, water pollution • Other applications: Marine and coastal environments, agriculture, forestry, cartography, environment, geology and exploration, telecommunication, utilities and planning • Provision of commercial imaging services • The high revisit frequency offered by the four X-band SAR spacecraft is also expected to provide a unique potential to the operational meteorological user community through provision of ancillary data and/or data on meteo-correlated phenomena, in particular as regards sea ice monitoring and study of ocean wave patterns. Background: In 1996 the Italian Government provided initial funding for the realization of a national Earth observation program. In 1997 the general guidelines for the 1998-2002 Italian National Space Plan (PSN) were approved including the activities on Earth observation. The strategic element in this plan is the COSMO-SkyMed dual-use program of ASI. 1) 2) In the summer of 2001, the Italian Ministry of Defense became a partner in the COSMO-SkyMed program (a welcome funding partner for the Italian Ministry of Research). However, the dual-use nature of the COSMO-SkyMed program, i. e. civil (research and commercial) and military use of its data products, resulted in a virtually classified program. A great disadvantage of the new arrangement is that rather sparse technical information of the mission can only be made available to the public. Although the first constellation satellite SAR instruments (SAR-2000) will observe in X-band (9.6 GHz with a wavelength of 3.1 cm), multi-mode scenarios (X-, C- L- and P-band) are planned for the future. The overall system architecture is composed of a space segment, a constellation of SAR satellites, and a ground segment including full featured user services. The requirements call for the following general performance characteristics: 3) • Full global observation coverage with all weather, day/night acquisition capability • Collection capability of large areas within a single pass, with along-track stereo imaging during a single pass • High image quality, to allow a robust image interpretability at the requested scale of analysis (data sets are characterized by adequate spatial and spectral resolution suitable to perform analyses at different scales of detail) • Ground track repeatability: the satellites of the SAR constellation shall have a ground track repeatability of better than 1 km • Fast response times (from the data/service user request up to the data/service delivery to that requiring user). The SABRINA project was started in 2004/5. The COSMO-SkyMed space segment is composed of a constellation of four SAR satellites. The PRIMA \[Piattaforma Riconfigurabile Italiana Multi-Applicativa (Reconfigurable Italian Platform for Multiple Applications)\] bus of Alcatel Alenia Space is being employed. Alcatel Alenia Space is also the prime contractor of the space segment \[funding by ASI and I-AD (Ministry of Defense)\]. - Note: As of April 10, 2007, the EC approved the transfer to Thales of Alcatel-Lucent's shareholdings in the two space sector joint venture companies Alcatel Alenia Space and Telespazio. Hence, Alcatel Alenia Space was renamed to Thales Alenia Space. The S/C is three-axis stabilized, it consists of the main body (bus), two deployable solar arrays, and a SAR antenna. The bus provides all support functions like: AOCS, electrical power (power generation, storage and distribution), data handling, thermal control, RF communications, and on-orbit propulsion for orbit injection and maintenance. The platform mechanical configuration consists of two elements or modules, namely: • SVM (Service Module) at the bottom of the bus which contains all bus subsystems including the propulsion module • PLM (Payload Module) at the top, dedicated to the payload complement, the PDHT (Payload Data Handing and Transmission) subsystem, and the AOCS (Attitude and Orbit Control Subsystem) with star trackers gyros actuators. The bus structure material is CFRP (Carbon Fiber Reinforced Plastic) while SVM and PLM consist of aluminum alloys. The interfaces of the SAR antenna, star trackers and gyros are mounted on the CFRP structure for pointing precision and stability (a star tracker is being used as well as a high-quality GPS receiver). The SSTI (Satellite-to-Satellite Tracking Instrument) is the LAGRANGE GPS receiver of Laben SpA. The SAR antenna bore sight is pointing with an incidence angle about 38º to the right side of the S/C ground track. AOCS provides an antenna steering capability of ±2º in yaw as well as for a re-pointing capability to the left side of the ground track. Each S/C in the constellation features a RCT (Reaction Control Thruster) system for orbit maintenance. The mass of each spacecraft is about 1700 kg. The design life is 5 years. The S/C provides an onboard operational autonomy for a period of 24 hours. Launch: The launch of the first COSMO spacecraft in the constellation took place on June 8, 2007 (UTC). The launch was provided by the Boeing Company on a Delta-2 (7420-10 configuration) vehicle from VAFB, CA. This represented the first commercial Delta-2 launch since the formation of the United Launch Alliance (ULA) in December 2006. Circular sun-synchronous dawn-dusk orbit, nominal altitude = 619.6 km, inclination = 97.86º, period = 97.1 min, with LTAN (Local Time of Ascending Node) at 6:00 AM, 14.8125 rev./day (or 14 13/16). All spacecraft of the SAR constellation will be positioned in the same orbital plane with a phasing outlined in Table 2. The nominal repeat cycle is 16 days; however, each single satellite will have a near revisit time of 5 days. Satellite Launch date Nominal EOL (End Of Life) Extended lifetime CSK-1 8-Jun-07 Jun-14 7-Jun-16 CSK-2 9-Dec-07 Dec-14 8-Dec-16 CSK-3 25-Oct-08 Oct-15 25-Oct-16 CSK-4 6-Nov-10 Nov-17 6-Nov-17 Group: Platform_Details Entry_ID: COSMO-SKYMED Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: COSMO-SKYMED End_Group Group: Platform_Associated_Instruments Short_Name: SAR End_Group Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous Primary_Sponsor: Italian Ministry of Defense (MOD) Primary_Sponsor: Agenzia Spaziale Italiana (ASI), Italy); update Definition (https://eoportal.org/web/eoportal/satellite-missions/c-missions/cosmo-skymed); 2019-02-13 13:48:52.0 [mmorahan] insert Resource (id: null type: image url: https://eoportal.org/documents/163813/3649508/COSMO_Auto32.jpeg); GFZ-1 GFZ-1 (GeoForschungsZentrum-1) is a geodetic satellite designed to improve the current knowledge of the Earth's gravity field. The satellite, a passive system with no onboard sensors or electronics, is covered with retroreflectors that reflect laser beams sent from ground stations. By measuring the round trip time of the transmitted light, the distance between the satellite and the station can be determined with approximately 1 centimeter. These measurements are used to determine variations in the rotational characteristics of the Earth and for measurement of the Earth's gravitational field. As the vehicle's orbit decays, the satellite's orbital motion will also be used calculate to atmospheric densities. Deployed from the Mir space station, GFZ-1 was the first non-Russian satellite launched from MIR. GFZ-1 was developed in under 12 months and cost approximately &#36700,000 (including design, fabrication, test, and launch). Data collection, distribution and evaluation is coor dinated by the project's scientists at the GeoForschungsZentrum Potsdam. Spacecraft The satellite consists of a spherical body made from brass with 60 corner cube reflectors distributed regularly over the satellite's surface. These retroreflectors are quartz prisms placed in special holders that are recessed in the satellite's body. External metallic surfaces are covered with white paint for thermal control purposes and to facilitate visual observation in space. The vehicle's size was limited by the maximum allowable dimensions of the Mir airlock (30 cm). The vehicle carries no electronics or sensors and is not attitude controlled. [Source: NASA Mission and Spacecraft Library] Group: Platform_Details Entry_ID: GFZ-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: GFZ-1 Long_Name: GeoForschungsZentrum-1 End_Group Group: Synonymous_Platform_Names Short_Name: GFZ-1 End_Group Group: Platform_Associated_Instruments Short_Name: SLR End_Group Group: Orbit Orbit_Altitude: 400 km End_Group Creation_Date: 2007-11-19 Online_Resource: http://www.gfz-potsdam.de/pb1/op/gfz1/index_GFZ1.html Sample_Image: http://www.gfz-potsdam.de/pb1/op/gfz1/GFZ1_1.small.gif Group: Platform_Logistics Launch_Date: 1995-04-09 Launch_Site: 1999-06-23 Design_Life: 3.5-5 years Primary_Sponsor: GeoForschungsZentrum Potsdam End_Group End_Group GOES-13 GOES-13 (GOES-N) lifted off aboard a Boeing Delta IV rocket from Space Launch Complex 37 at Cape Canaveral Air Force Station, Florida at 6:11 pm EDT on May 25, 2006. GOES-13 (GOES-N) is the latest in a series of Earth monitoring satellites. Geostationary Operational Environmental Satellites (GOES) provide the kind of continuous monitoring necessary for intensive data analysis. Geostationary describes an orbit in which a satellite is always in the same position with respect to the rotating Earth. This allows GOES to hover continuously over one position on the Earth's surface, appearing stationary. As a result, GOES provide a constant vigil for the atmospheric "triggers" for severe weather conditions such as tornadoes, flash floods, hail storms, and hurricanes. Orbit: Altitude: 36000 km Geo-Synchronous Vital Statistics: Weight 3200 kg Size: 4.2 meters (l) x 1.88 meters (w) Power: 2300 watts Mission Life: 5 years Instruments: Sounder Imager SEM (Space Environment Monitor) S and R (Search and Rescue) 2017-09-01 16:54:55.0 [sritz] insert Definition (id: null text: GOES-13 (GOES-N) lifted off aboard a Boeing Delta IV rocket from Space Launch Complex 37 at Cape Canaveral Air Force Station, Florida at 6:11 pm EDT on May 25, 2006. GOES-13 (GOES-N) is the latest in a series of Earth monitoring satellites. Geostationary Operational Environmental Satellites (GOES) provide the kind of continuous monitoring necessary for intensive data analysis. Geostationary describes an orbit in which a satellite is always in the same position with respect to the rotating Earth. This allows GOES to hover continuously over one position on the Earth's surface, appearing stationary. As a result, GOES provide a constant vigil for the atmospheric "triggers" for severe weather conditions such as tornadoes, flash floods, hail storms, and hurricanes. Orbit: Altitude: 36000 km Geo-Synchronous Vital Statistics: Weight 3200 kg Size: 4.2 meters (l) x 1.88 meters (w) Power: 2300 watts Mission Life: 5 years Instruments: Sounder Imager SEM (Space Environment Monitor) S and R (Search and Rescue) language code: en); 2017-09-01 16:47:01.0 [sritz] Insert Concept add broader relation (GOES-13 [98685a1b-9825-43c0-b0d9-6a65f8cb8c7c,310123] - GOES [6e332c25-caeb-4917-afb6-af757bcecd72,310071]); IMP (Interplanetary Monitoring Platform) OSTM/JASON-2 JASON-2 The Ocean Surface Topography Mission (OSTM)/Jason-2 was a follow-on altimetric mission to the very successful TOPEX/Poseidon mission and Jason-1. It was a joint mission between NASA and CNES (French space agency). It launched 20 June 2008 and began data collection on 12 July 2008. OSTM measured significant wave height, sigma naught (sigma0), dry and wet troposphere and ionosphere, which can be used to calculate sea surface height and anomalies and total electron content. https://podaac.jpl.nasa.gov/OSTM-JASON2 Group: Platform_Details Entry_ID: OSTM/JASON-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: OSTM/JASON-2 End_Group Group: Platform_Associated_Instruments Short_Name: AMR Short_Name: POSEIDON-3 Short_Name: GPSP Short_Name: LRA Short_Name: DORIS End_Group Group: Orbit Orbit_Altitude: 1336 km Orbit_Inclination: 66 degrees Repeat_Cycle: 10 Day Orbit_Type: LEO > Low Earth Orbit > Polar Non-Sun-Synchronous End_Group Creation_Date: 2008-06-11 Online_Resource: https://sealevel.jpl.nasa.gov/missions/ostmjason2/ Online_Resource: https://www.nasa.gov/mission_pages/ostm/main/index.html Online_Resource: https://www.aviso.altimetry.fr/en/missions/current-missions/jason-2.html Group: Platform_Logistics Launch_Date: 2008-06-20 Launch_Site: Vandenberg Air Force Base, USA Design_Life: 3 Years Primary_Sponsor: USA/NASA Primary_Sponsor: USA/NOAA Primary_Sponsor: France/CNES Primary_Sponsor: EUMETSAT End_Group End_Group 2020-01-29 22:08:37.0 [sritz] update Definition (The Ocean Surface Topography Mission (OSTM)/Jason-2 was a follow-on altimetric mission to the very successful TOPEX/Poseidon mission and Jason-1. It was a joint mission between NASA and CNES (French space agency). It launched 20 June 2008 and began data collection on 12 July 2008. OSTM measured significant wave height, sigma naught (sigma0), dry and wet troposphere and ionosphere, which can be used to calculate sea surface height and anomalies and total electron content. https://podaac.jpl.nasa.gov/OSTM-JASON2 Group: Platform_Details Entry_ID: OSTM/JASON-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: OSTM/JASON-2 End_Group Group: Platform_Associated_Instruments Short_Name: AMR Short_Name: POSEIDON-3 Short_Name: GPSP Short_Name: LRA Short_Name: DORIS End_Group Group: Orbit Orbit_Altitude: 1336 km Orbit_Inclination: 66 degrees Repeat_Cycle: 10 Day Orbit_Type: LEO > Low Earth Orbit > Polar Non-Sun-Synchronous End_Group Creation_Date: 2008-06-11 Online_Resource: https://sealevel.jpl.nasa.gov/missions/ostmjason2/ Online_Resource: https://www.nasa.gov/mission_pages/ostm/main/index.html Online_Resource: https://www.aviso.altimetry.fr/en/missions/current-missions/jason-2.html Group: Platform_Logistics Launch_Date: 2008-06-20 Launch_Site: Vandenberg Air Force Base, USA Design_Life: 3 Years Primary_Sponsor: USA/NASA Primary_Sponsor: USA/NOAA Primary_Sponsor: France/CNES Primary_Sponsor: EUMETSAT End_Group End_Group); 2016-06-09 17:15:52.0 [epneff] added altLabel insert AltLabel (id: null text: JASON-2 language code: en); CONTROL SURVEYS A control survey is a survey that provides positions (horizontal or vertical) of points to which supplementary surveys are adjusted. Group: Platform_Details Entry_ID: CONTROL SURVEYS Group: Platform_Identification Platform_Category: In Situ Land-based Platforms Short_Name: CONTROL SURVEYS End_Group Creation_Date: 2012-03-13 Online_Resource: http://www.britannica.com/EBchecked/topic/575433/surveying/51754/Basic-control-surveys End_Group PIPER NAVAJO CHIEFTAIN The PA-31 Navajo is a family of cabin-class, twin-engine aircraft designed and built by Piper Aircraft using Lycoming engines for the general aviation market. In the mid-1960s, an aircraft of this size was sorely needed and founder William T. Piper requested the type be developed. Targeted at small-scale cargo and feeder liner operations and the corporate market, the aircraft was a success. It continues to prove a popular choice, but due to greatly decreased demand across the general aviation sector in the 1980s, production of the PA-31 ceased. [Text and Photo provided by: http://en.wikipedia.org/wiki/Piper_PA-31_Navajo ] Group: Platform_Details Entry_ID: PIPER NAVAJO CHIEFTAIN Group: Platform_Identification Platform_Category: Aircraft Short_Name: PIPER NAVAJO CHIEFTAIN End_Group Creation_Date: 2008-07-14 Online_Resource: http://en.wikipedia.org/wiki/Piper_PA-31_Navajo Online_Resource: http://www.newpiper.com/ Sample_Image: http://upload.wikimedia.org/wikipedia/commons/a/af/Piper_PA-31_Navajo_St_Catharines_1.jpg End_Group SENTINEL-1B The SENTINEL-1 mission is the European Radar Observatory for the Copernicus joint initiative of the European Commission (EC) and the European Space Agency (ESA). Copernicus, previously known as GMES, is a European initiative for the implementation of information services dealing with environment and security. It is based on observation data received from Earth Observation satellites and ground-based information. The SENTINEL-1 mission includes C-band imaging operating in four exclusive imaging modes with different resolution (down to 5 m) and coverage (up to 400 km). It provides dual polarisation capability, very short revisit times and rapid product delivery. For each observation, precise measurements of spacecraft position and attitude are available. Synthetic Aperture Radar (SAR) has the advantage of operating at wavelengths not impeded by cloud cover or a lack of illumination and can acquire data over a site during day or night time under all weather conditions. SENTINEL-1, with its C-SAR instrument, can offer reliable, repeated wide area monitoring. The mission is composed of a constellation of two satellites, SENTINEL-1A and SENTINEL-1B, sharing the same orbital plane. SENTINEL-1 is designed to work in a pre-programmed, conflict-free operation mode, imaging all global landmasses, coastal zones and shipping routes at high resolution and covering the global ocean with vignettes. This ensures the reliability of service required by operational services and a consistent long term data archive built for applications based on long time series. Source: https://sentinel.esa.int/web/sentinel/missions/sentinel-1 Group: Platform_Details Entry_ID: SENTINEL-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: Sentinel GMES Short_Name: SENTINEL-1 End_Group Group: Platform_Associated_Instruments Short_Name: SENTINEL-1 C-SAR End_Group Group: Orbit Orbit_Altitude: 693 km Orbit_Type: LEO > LOW EARTH ORBIT > POLAR SUN-SYNCHRONOUS End_Group Creation_Date: 2009-12-18 Online_Resource: https://sentinel.esa.int/web/sentinel/missions/sentinel-1 Sample_Image: http://www.esa.int/images/sentinel2_alcatel_M.gif Group: Platform_Logistics Launch_Date: 2014-04-03 Launch_Site: KOUROU, FRENCH GUIANA Design_Life: 7 Years Primary_Sponsor: ESA/EU End_Group End_Group 2019-03-28 16:57:08.0 [mmorahan] delete WeightedRelation (null); 2019-02-22 18:55:58.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: 1c53d85e-3792-4081-9748-192fd3140aa6 relationship type: null relationship value: null generated by: null); 2019-02-22 17:50:34.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: ed400e7c-229e-48be-9a93-84f2fc864448 relationship type: null relationship value: null generated by: null); 2018-11-05 13:37:15.0 [tstevens] insert AltLabel (id: null category: primary text: SENTINEL-1B language code: en); 2018-11-02 21:18:00.0 [mmorahan] insert Definition (id: null text: The SENTINEL-1 mission is the European Radar Observatory for the Copernicus joint initiative of the European Commission (EC) and the European Space Agency (ESA). Copernicus, previously known as GMES, is a European initiative for the implementation of information services dealing with environment and security. It is based on observation data received from Earth Observation satellites and ground-based information. The SENTINEL-1 mission includes C-band imaging operating in four exclusive imaging modes with different resolution (down to 5 m) and coverage (up to 400 km). It provides dual polarisation capability, very short revisit times and rapid product delivery. For each observation, precise measurements of spacecraft position and attitude are available. Synthetic Aperture Radar (SAR) has the advantage of operating at wavelengths not impeded by cloud cover or a lack of illumination and can acquire data over a site during day or night time under all weather conditions. SENTINEL-1, with its C-SAR instrument, can offer reliable, repeated wide area monitoring. The mission is composed of a constellation of two satellites, SENTINEL-1A and SENTINEL-1B, sharing the same orbital plane. SENTINEL-1 is designed to work in a pre-programmed, conflict-free operation mode, imaging all global landmasses, coastal zones and shipping routes at high resolution and covering the global ocean with vignettes. This ensures the reliability of service required by operational services and a consistent long term data archive built for applications based on long time series. Source: https://sentinel.esa.int/web/sentinel/missions/sentinel-1 Group: Platform_Details Entry_ID: SENTINEL-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: Sentinel GMES Short_Name: SENTINEL-1 End_Group Group: Platform_Associated_Instruments Short_Name: SENTINEL-1 C-SAR End_Group Group: Orbit Orbit_Altitude: 693 km Orbit_Type: LEO > LOW EARTH ORBIT > POLAR SUN-SYNCHRONOUS End_Group Creation_Date: 2009-12-18 Online_Resource: https://sentinel.esa.int/web/sentinel/missions/sentinel-1 Sample_Image: http://www.esa.int/images/sentinel2_alcatel_M.gif Group: Platform_Logistics Launch_Date: 2014-04-03 Launch_Site: KOUROU, FRENCH GUIANA Design_Life: 7 Years Primary_Sponsor: ESA/EU End_Group End_Group language code: en); 2018-06-12 19:15:52.0 [mmorahan] Move Concepts delete broader relation (null); add broader relation (SENTINEL-1B [9940dbad-1a9a-4858-a0e8-af35b21277e2,345451] - Sentinel-1 [007c3084-89db-458e-8387-14e192b6cb8e,367691]); 2015-09-23 23:54:19.0 [saritz] Insert Concept add broader relation (SENTINEL-1B [9940dbad-1a9a-4858-a0e8-af35b21277e2,158413] - Sentinel GMES [2c9f1fcc-d9c8-4c6d-b701-45c97cee511f,143381]); SPOT-2 [Text Source: NSSDC, http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1990-005A ] The SPOT-B (Systeme Probatoire d'Observation de la Terre) spacecraft is an earth observation satellite with a ground resolution better than that of the Landsat series satellites. The main applications for the images returned by the second SPOT mission are land-use studies, agriculture and forestry resources, mineral and oil resources, and cartography. The three-axis stabilized satellite operates in a circular sun-synchronous near-polar orbit for a design lifetime of 2 years. The spacecraft dimensions are 2 x 2 x 3.5 m and 15.60 m for the overall length of the deployed solar panel. SPOT-B consists of two parts: (1) the bus, a standard multipurpose platform, and (2) the payload. The bus provides housekeeping information and an onboard computer. The payload is mounted on one of the side panels of the bus. It consists of two identical high-resolution visible (HRV) imaging instruments and a package comprising two magnetic-tape data recorders and a telemetry transmitter. The HRV imaging instrument observes in three spectral bands (in the visible and near infrared regions) with a ground resolution of 20 m, and/or in a broader spectral band (panchromatic black and white) with a ground resolution of 10 m. The pattern of successive ground tracks is repeated exactly at 26-day intervals. The SPOT-B instrument package has the provision for off-nadir viewing which should be particularly useful for monitoring localized phenomena evolving on a relatively short timescale. It also provides the capability for recording stereoscopic pairs of images of a given area during successive satellite passes. Group: Platform_Details Entry_ID: SPOT-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: SPOT Short_Name: SPOT-2 Long_Name: Systeme Probatoire Pour l'Observation de la Terre-2 End_Group Group: Synonymous_Platform_Names Short_Name: SPOT-2 Short_Name: SPOT-B Short_Name: 20436 End_Group Group: Platform_Associated_Instruments Short_Name: DORIS Short_Name: HRV End_Group Group: Orbit Orbit_Inclination: 98.7° Period: 100.9 minutes Perigee: 802 km Apogee: 831 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-11-13 Online_Resource: http://www.spotimage.fr/web/en/224-technical-information.php Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1990-005A Online_Resource: http://www.spot.com/ Sample_Image: http://www.space-risks.com/SpaceData/ImaSat/spot2.jpg Group: Platform_Logistics Launch_Date: 1990-01-22 Launch_Site: Kourou, French Guiana Primary_Sponsor: CNES End_Group End_Group GOES-1 [Source: NASA NSSDC, http://nssdc.gsfc.nasa.gov/ ] GOES-1 (SMS-C) was launched in October 1975 and was a NASA-developed, NOAA-operated, geosynchronous, and operational spacecraft. The cylindrically shaped spacecraft measured 190.5 cm in diameter and 230 cm in length, exclusive of a magnetometer that extended an additional 83 cm beyond the cylinder shell. The primary structural members were a honeycombed equipment shelf and thrust tube. The VISSR telescope was mounted on the equipment shelf and viewed the Earth through a special aperture in the side of the spacecraft. A support structure extended radially from the thrust tube and was affixed to the solar panels, which formed the outer walls of the spacecraft and provided the primary source of electrical power. Located in the annulus-shaped space between the thrust tube and the solar panels were stationkeeping and dynamics control equipment, batteries, and most of the SEM equipment. Proper spacecraft attitude and spin rate (approximately 100 rpm) were maintained by two separate sets of jet thrusters mounted around the spacecraft equator and activated by ground command. The spacecraft used both UHF-band and S-band frequencies in its telemetry and command subsystem. A low-power VHF transponder provided telemetry and command during launch and then served as a backup for the primary subsystem once the spacecraft attained orbit. This spin-stabilized spacecraft carried a visible infrared spin-scan radiometer, meteorological data collection and relay system, space environment monitor, and a biaxial fluxgate magnetometer. On December 1, 1978, responsibility for GOES 1 was turned over to ESA to be used as part of FGGE/GARP. It was stationed over the Indian Ocean and controlled by ESOC in Darmstadt, F.R.G. In December 1979, it was returned to the control of NOAA and positioned at 135 degrees West. When GOES 5 VAS experienced a failure on July 30, 1984, GOES 6 was moved east and GOES 1 was reactivated by NOAA to provide visible imaging capability over the western U.S. GOES 1 failed on February 3, 1985. Additional Information on GOES Satellites: http://www.oso.noaa.gov/goes/ Group: Platform_Details Entry_ID: GOES-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: GOES (Geostationary Operational Environmental Satellite) Short_Name: GOES-1 Long_Name: Geostationary Operational Environmental Satellite 1 End_Group Group: Synonymous_Platform_Names Short_Name: SMS-3 Short_Name: GOES-A Short_Name: SMS-C Short_Name: 8366 End_Group Group: Platform_Associated_Instruments Short_Name: SEM Short_Name: VISSR Short_Name: EPM Short_Name: SXM Short_Name: DCS Short_Name: Magnetic Field Monitor End_Group Group: Orbit Orbit_Type: GEO > Geosynchronous > Geostationary End_Group Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1975-100A Group: Platform_Logistics Launch_Date: 1975-10-16 Launch_Site: CAPE CANAVERAL/KENNEDY SPACE CENTER, USA Primary_Sponsor: USA/NASA Primary_Sponsor: USA/NOAA End_Group End_Group GRAVITY STATIONS Gravity stations make observations related to the Earth's gravity. SMS (Synchronous Meteorological Satellites) KOMPSAT 2018-06-12 16:36:10.0 [mmorahan] Move Concepts add narrower relation (KOMPSAT [9abdb7c0-7b8e-426b-8bc7-57ea4a30d82c,367679] - KOMPSAT-2 [88d9cd91-a26e-467a-9554-c5d927540421,345347]); 2018-06-12 16:36:02.0 [mmorahan] Move Concepts add narrower relation (KOMPSAT [9abdb7c0-7b8e-426b-8bc7-57ea4a30d82c,367679] - KOMPSAT-1 [caf7cd97-6a64-4e31-9b7e-d96854eb9b6a,367675]); 2018-06-12 16:35:36.0 [mmorahan] Insert Concept add broader relation (KOMPSAT [9abdb7c0-7b8e-426b-8bc7-57ea4a30d82c,367679] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761]); FireBIRD FireBIRD is an earth observation mission with the primary goal of monitoring fires from space. It involves the detection and measurement of so-called high-temperature events and the provision of remote sensing science data for research at DLR and for external partners. It is organized as a research and development project under the auspices of DLR’s Aerospace Research and Technology program division with solely science goals, and all aspects of the mission are under DLR control. The space segment consists of the two satellites TET-1 (Technology Experiment Carrier) and BIROS (Berlin InfraRed Optical System). The TET-1 satellite has been circling Earth in a polar orbit since July 2012 and has successfully concluded the first part of its mission as a technology testing platform. The BIROS satellite has the same bus as TET-1, but is additionally equipped with a propulsion system for active attitude and orbit control. BIROS was launched on 22 June 2016 at 05:55 CEST. The main payload for both satellites is a multispectral camera system. 2018-10-11 20:37:15.0 [mmorahan] Insert Concept add narrower relation (FireBIRD [9b165321-e03c-44dc-bb9c-d10c32c93ab6,368159] - BIROS [8e53aafe-f7a5-4629-893e-0a3ae1a6fe1d,368167]); 2018-10-11 20:28:51.0 [mmorahan] Insert Concept add narrower relation (FireBIRD [9b165321-e03c-44dc-bb9c-d10c32c93ab6,368159] - TET-1 [67e5bbab-0c9b-40e5-acf7-054671f35d2b,368163]); 2018-10-11 20:14:06.0 [mmorahan] insert Definition (id: null text: FireBIRD is an earth observation mission with the primary goal of monitoring fires from space. It involves the detection and measurement of so-called high-temperature events and the provision of remote sensing science data for research at DLR and for external partners. It is organized as a research and development project under the auspices of DLR’s Aerospace Research and Technology program division with solely science goals, and all aspects of the mission are under DLR control. The space segment consists of the two satellites TET-1 (Technology Experiment Carrier) and BIROS (Berlin InfraRed Optical System). The TET-1 satellite has been circling Earth in a polar orbit since July 2012 and has successfully concluded the first part of its mission as a technology testing platform. The BIROS satellite has the same bus as TET-1, but is additionally equipped with a propulsion system for active attitude and orbit control. BIROS was launched on 22 June 2016 at 05:55 CEST. The main payload for both satellites is a multispectral camera system. language code: en); 2018-10-11 20:09:41.0 [mmorahan] Insert Concept add broader relation (FireBIRD [9b165321-e03c-44dc-bb9c-d10c32c93ab6,368159] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761]); METEOROLOGICAL STATIONS METEOROLOGICAL STATION Meteorological Stations: stations that observe and monitor variabes such as temperature, atmospheric pressure, humidity, surface winds, precipitation, radiation, visibility, evaportation, and current conditions. [Source: METEO-TECHNOLOGY "http://www.meteo-technology.com/"] 2016-06-09 18:48:47.0 [epneff] added altLabel insert AltLabel (id: null text: METEOROLOGICAL STATION language code: en); ECHO-1 The Echo satellites were NASA's first experimental communications satellite project. Each spacecraft was a large metallized balloon designed to act as a passive communications reflector to bounce communication signals transmitted from one point on Earth to another. Following the failure of the launch vehicle carrying Echo 1, Echo 1A (commonly referred to as Echo 1) was successfully orbited, and was used to redirect transcontinental and intercontinental telephone, radio, and television signals. The success of Echo 1A proved that microwave transmission to and from satellites in space was understood and demonstrated the promise of communications satellites. The vehicle also provided data for the calculation of atmospheric density and solar pressure due to its large area-to-mass ratio. Echo 1A was visible to the unaided eye over most of the Earth (brighter than most stars) and was probably seen by more people than any other man-made object in space. Echo 2 continued the passive communications experiments, and also investigated the dynamics of large spacecraft and was used for global geometric geodesy. Although NASA abandonded passive communications systems in favor of active satellites following Echo 2, the Echo systems demonstrated several ground station and tracking technologies that would be used by active systems. Echo 1A reentered on May 24, 1968 followed by Echo 2 on June 7, 1969. Spacecraft 1, 1A: each was a 30.5 m diameter balloon made of 0.0127 mm thick mylar polyester film. A set of 107.9-MHz beacon transmitters were carried for telemetry. The transmitters were powered by five nickel-cadmium batteries that were charged by 70 solar cells mounted on the balloon. 2: a 41.1 m diameter mylar balloon that used an improved inflation system to improve the balloon's smoothness and sphericity. Instrumentation included temperature sensors to monitor the balloon's skin temperature and pressure sensors to monitor the balloon's internal pressure. A beacon system, consisting of two transmitter assemblies, provided tracking and telemetry signals. The beacon system used solar cell panels for power and had a minimum power output of 45 mW at 136.17 MHz and 136.02 MHz. [Summary provided by NASA.] Group: Platform_Details Entry_ID: ECHO-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: ECHO Short_Name: ECHO-1 End_Group Group: Orbit Orbit_Inclination: 47.1999 degrees Perigee: 1524 km Apogee: 1684 km End_Group Creation_Date: 2007-09-14 Online_Resource: http://msl.jpl.nasa.gov/QuickLooks/echoQL.html Sample_Image: http://msl.jpl.nasa.gov/QuickLooks/pictures/echo.gif Group: Platform_Logistics Launch_Date: 1960-08-12 Primary_Sponsor: NASA End_Group End_Group UAV Unmanned Aerial Vehicles (UAVs) are remotely piloted or self-piloted aircraft that can carry cameras, sensors, communications equipment or other payloads. They have been used in a reconnaissance and intelligence-gathering role since the 1950s, and more challenging roles are envisioned, including combat missions. Since 1964 the Defense Department has developed 11 different UAVs, though due to acquisition and development problems only 3 entered production. The US Navy has studyied the feasibility of operating VTOL UAVs since the early 1960s, the QH-50 Gyrodyne torpedo-delivery drone being an early example. However, high cost and technological immaturity have precluded acquiring and fielding operational VTOL UAV systems. By the early 1990s DOD sought UAVs to satisfy surveillance requirements in Close Range, Short Range or Endurance categories. Close Range was defined to be within 50 kilometers, Short Range was defined as within 200 kilometers and Endurance as anything beyond. By the late 1990s, the Close and Short Range categories were combined, and a separate Shipboard category emerged. The current classes of these vehicles are the Tactical UAV and the Endurance category. Group: Platform_Details Entry_ID: UAV Group: Platform_Identification Platform_Category: Aircraft Short_Name: UAV Long_Name: Unmanned Aerial Vehicle End_Group Creation_Date: 2010-08-31 Online_Resource: http://www.fas.org/irp/program/collect/uav.htm End_Group STARLETTE - Spacecraft Brief Description - The two primary goals of this satellite were to minimize the effects of non-gravitational forces and to obtain the highest possible accuracy for laser range measurements. The satellite was spherically shaped with a 12-cm radius. The core was an alloy of uranium 238 and 1.5% molybdenum. The skin consisted of 20 spherical caps made of an alloy of aluminum and 5% magnesium with triangular bases. Each cap contained three laser corner cubes. The corner cubes were fused silica trihedrons with circular apertures made of suprasil 1 with silver coatings covered by inconel. For Groupe de Recherches de Geodesie Spatiale (GRGS), the principal objective was to study earth and ocean tides by (1) the determination of the second harmonics (amplitude and phase) of the main semidiurnal oceanic tides (M and S) and, if possible, of the diurnal K, O, and P tides; and (2) the determination of the dissipation in the solid earth and in the oceans (Q). - Auxiliary Information - Launch Date and Time : 1975-02-06 Epoch Date and Time : 1975-02-20 Apogee (km or AU): 1108. Perigee (km or AU): 806. Inclination (degree) : 49.82 Orbit Type : Geocentric Information last updated on 1985-07-17 Group: Platform_Details Entry_ID: STARLETTE Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: STARLETTE End_Group Group: Synonymous_Platform_Names Short_Name: STARLETTE End_Group Group: Orbit Orbit_Inclination: 49.82 Perigee: 806 Apogee: 1108 End_Group Creation_Date: 2007-11-28 Group: Platform_Logistics Launch_Date: 1975-02-06 End_Group End_Group HELIOS 1 Helios 1 was a joint German- American deep space mission to study the main solar processes and solar-terrestrial relationships. Specifically, the spacecraft's instruments were designed to investigate phenomena such as solar wind, magnetic and electric fields, cosmic rays, and cosmic dust in regions between Earth's orbit and approximately 0.3 AU from the Sun. It was the largest bilateral project to date for NASA, with Germany paying about $180 million of the total $260-million cost. Germany provided the spacecraft and NASA the launch vehicles. After a successful launch, Helios 1 passed within 47 million kilometers of the Sun at a speed of 238,000 kilometers per hour on 15 March 1975, the closest any humanmade object had been to our nearest star. During its mission, the spacecraft spun once every second to evenly distribute the heat coming from the Sun, 90 percent of which was reflected by optical surface mirrors. Its data indicated the presence of fifteen times more micrometeorites close to the Sun than there are near Earth. Information provided by http://solarsystem.nasa.gov/missions/profile.cfm?Sort=Target&Target=Sun&MCode=Helios_01&Display=ReadMore Group: Platform_Details Entry_ID: HELIOS 1 Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Short_Name: HELIOS 1 End_Group Group: Synonymous_Platform_Names Short_Name: Helio 1 End_Group Group: Platform_Associated_Instruments Short_Name: WAVES Short_Name: 3DP End_Group Creation_Date: 2007-08-13 Online_Resource: http://solarsystem.nasa.gov/missions/profile.cfm?Sort=Target&Target=Sun&MCode=Helios_01&Display=ReadMore Sample_Image: http://solarsystem.nasa.gov/missions/images/miss-helios_01.gif Group: Platform_Logistics Launch_Date: 1974-11-10 Primary_Sponsor: NASA End_Group End_Group NASA Decadal Survey The Decadal Survey provides scientific priorities indirectly through a time sequencing of recommended missions. It is a first-ever comprehensive survey of all Earth sciences that could benefit from spaceborne observations. The study is requested and supported by NASA, NOAA, USGS. More Information: https://science.nasa.gov/earth-science/decadal-surveys 2020-01-04 00:05:16.0 [sritz] Remove Concepts delete narrower relation (null); 2020-01-03 23:57:07.0 [sritz] Remove Concepts delete narrower relation (null); 2020-01-03 23:54:54.0 [sritz] Remove Concepts delete narrower relation (null); 2020-01-03 23:30:36.0 [sritz] Remove Concepts delete narrower relation (null); 2020-01-03 23:27:38.0 [sritz] Remove Concepts delete narrower relation (null); 2020-01-03 22:34:17.0 [sritz] update Definition (The Decadal Survey provides scientific priorities indirectly through a time sequencing of recommended missions. It is a first-ever comprehensive survey of all Earth sciences that could benefit from spaceborne observations. The study is requested and supported by NASA, NOAA, USGS. More Information: https://science.nasa.gov/earth-science/decadal-surveys); update Definition (https://science.nasa.gov/earth-science/decadal-surveys); 2020-01-03 22:06:41.0 [sritz] Remove Concepts delete narrower relation (null); 2012-09-18 16:38:55.0 [saritz] Added decadel survey definition. insert Definition (id: null text: The Decadal Survey provides scientific priorities indirectly through a time sequencing of recommended missions. It is a first-ever comprehensive survey of all Earth sciences that could benefit from spaceborne observations. The study is requested and supported by NASA, NOAA, USGS. language code: en); POLAR The Polar spacecraft was launched on February 24, 1996, to obtain data from both high- and low-altitude perspectives of this active region of geospace. High above the poles the particles of the solar wind and the energy of the wind can find their way into the magnetosphere. At lesser altitudes energy is transferred from electric fields and electromagnetic waves to electrons that then plunge into the atmosphere to create the aurora. At mid-altitudes nearer the equator the satellite passes through the Earth's trapped radiation, the Van Allen belts. Out of the polar ionosphere flows plasma to populate the magnetosphere. Through this region particles and energy flow from the geomagnetic tail to the atmosphere. Thus the instruments on the Polar satellites see a lot of action in the various plasma parameters that they measure. Three of the twelve scientific instruments aboard the Polar satellite are used to image the aurora in various wavelengths when the satellite is near apogee, high over the northern polar region. The other nine instruments make measurements in-situ, at the location of the satellite, around the entire orbit. They measure the fluxes of charged particles, electrons and protons, as well as heavier ions, from thermal energies into MeV energies. They measure magnetic and electric fields, plus electromagnetic waves. They must make these measurements in great detail in order for scientists to be able to learn new things about the environment in the region over the poles of the Earth. The Polar satellite is in a highly elliptical orbit, with apogee at 9 earth radii and perigee at 1.8 earth radii geocentric. The inclination is 86 deg. and the period about 18 hours. Initially apogee was over the northern polar region, but apogee has been moving towards the equator at about 16 deg. per year. The nominal mission duration was two years, but a three year extended mission has been approved. Details on the POLAR mission and instrumentation are provided in Space Science Reviews (Vol. 71, Nos. 1-4, 1995) and reprinted in The Global Geospace Mission, edited by C. T. Russell (Kluwer, 1995). For more information, see: http://pwg.gsfc.nasa.gov/polar/ Group: Platform_Details Entry_ID: POLAR Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Short_Name: POLAR Long_Name: POLAR End_Group Group: Synonymous_Platform_Names Short_Name: GGS/Polar Short_Name: STP/Polar Short_Name: Polar Plasma Laboratory Short_Name: 23802 Short_Name: 1996-013A Short_Name: POLAR-EFI End_Group Group: Platform_Associated_Instruments Short_Name: MDI Short_Name: VIS Short_Name: UVI Short_Name: TIMAS Short_Name: TIDE Short_Name: SEPS Short_Name: PWI-P Short_Name: PIXIE Short_Name: MFE-P Short_Name: HYDRA Short_Name: EPI Short_Name: CEPPAD Short_Name: CAMMICE End_Group Group: Orbit Orbit_Inclination: 85.9 degrees Period: 938.1 min Perigee: 185 km Apogee: 50551 km Orbit_Type: HEO > Highly Elliptical Orbit End_Group Online_Resource: http://pwg.gsfc.nasa.gov/polar/ Sample_Image: http://nssdc.gsfc.nasa.gov/image/spacecraft/polar.jpg Group: Platform_Logistics Launch_Date: 1996-02-24 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: NASA End_Group End_Group TRIPOD 2017-11-22 15:24:51.0 [tstevens] Insert Concept add broader relation (TRIPOD [9c44243f-3122-4f7f-98b1-fb4e729418e0,310389] - In Situ Land-based Platforms [4f396ff6-7bea-4ba4-afa3-198ebd914a4a,287781]); VANGUARD - Spacecraft Brief Description - Vanguard 2 was an earth-orbiting satellite designed to measure cloud-cover distribution over the daylight portion of its orbit. The spacecraft was a 9.8 kg magnesium sphere 50.8 cm in diameter. It contained two optical telescopes with two photocells. The sphere was internally gold-plated and externally covered with an aluminum deposit coated with silicon oxide of sufficient thickness to provide thermal control for the instrumentation. Radio communication was provided by a 1-W, 108.03-MHz telemetry transmitter and a 10-mW, 108-MHz beacon transmitter that sent a continuous signal for tracking purposes. A command receiver was used to activate a tape recorder that relayed telescope experiment data to the telemetry transmitter. Both transmitters functioned normally for 19 days. The satellite was spin stabilized at 50 rpm, but telemetry data were poor because of an unsatisfactory orientation of the spin axis. The power supply for the instrumentation was provided by mercury batteries. - Auxiliary Information - Launch Date and Time : 1959-02-17 16:05:00 Epoch Date and Time : 1959-02-17 16:48:00 Apogee (km or AU): 3320. Perigee (km or AU): 559. Inclination (degree) : 32.88 Orbit Type : Geocentric Information last updated on 1992-04-14 Vanguard 3 was launched by a Vanguard rocket from the Eastern Test Range into a geocentric orbit. The objectives of the flight were to measure the earth's magnetic field, the solar X-ray radiation and its effects on the earth's atmosphere, and the near-earth micrometeoroid environment. Instrumentation included a proton magnetometer, X-ray ionization chambers, and various micrometeoroid detectors. The spacecraft was a 50.8-cm-diameter magnesium sphere. The magnetometer was housed in a glass fiber phenolic resin conical tube attached to the sphere. Data transmission stopped on December 11, 1959, after 84 days of operation. The data obtained provided a comprehensive survey of the earth's magnetic field over the area covered, defined the lower edge of the Van Allen radiation belt, and provided a count of micrometeoroid impacts. Vanguard 3 has an expected orbital lifetime of 300 yr. - Auxiliary Information - Launch Date and Time : 1959-09-18 05:16:00 Epoch Date and Time : 1959-09-18 14:24:00 Apogee (km or AU): 3744. Perigee (km or AU): 512. Inclination (degree) : 33.3 Orbit Type : Geocentric Information last updated on 1992-04-14 Group: Platform_Details Entry_ID: VANGUARD Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: VANGUARD End_Group Group: Synonymous_Platform_Names Short_Name: VANGUARD End_Group Creation_Date: 2007-11-30 Online_Resource: http://history.nasa.gov/SP-4202/toc2.html Sample_Image: http://history.nasa.gov/SP-4202/p0-ii.jpg Group: Platform_Logistics Launch_Date: 1959-02-17 Primary_Sponsor: United States Department of Defense End_Group End_Group GOES-14 [Source: NASA Home Page, http://www.nasa.gov/mission_pages/GOES-O/main/index.html ] The GOES-O satellite lifted off from Launch Complex 37 at Cape Canaveral Air Force Station in Florida at 6:51 p.m. EDT [2009-06-27] atop a Delta IV rocket. From a position about 22,300 miles above Earth, the advanced weather satellite will keep an unblinking eye on atmospheric conditions in the Eastern United States and Atlantic Ocean. [Source: GOES project Office NASA Goddard Space Flight Center, http://goespoes.gsfc.nasa.gov/goes/spacecraft/goes_o_spacecraft.html ] Geostationary Operational Environmental Satellite (GOES)-O represents a continuation of the newest generation of environmental satellites built by Boeing for the National Oceanic and Atmospheric Administration (NOAA) under the technical guidance and project management of NASA's Goddard Space Flight Center, Greenbelt, MD. GOES satellites provide the familiar weather pictures seen on United States television newscasts every day. The GOES imaging and sounding instruments (built by ITT) feature flexible scans for small-scale area viewing in regions of the visible and infrared spectrum allowing meteorologists to improve short-term forecasts. GOES provides nearly continuous imaging and sounding, which allow forecasters to better measure changes in atmospheric temperature and moisture distributions and hence increase the accuracy of their forecasts. GOES environmental information is used for a host of applications, including weather monitoring and prediction models, ocean temperatures and moisture locations, climate studies, cryosphere (ice, snow, glaciers) detection and extent, land temperatures and crop conditions, and hazards detection. The GOES-O&P Imagers have improved resolution in the 13 micrometer channel from 8 km to 4 km. The finer spatial resolution allows an improved cloud-top product, height of atmospheric motion vectors and volcanic ash detection. GOES-O continues the improved image navigation and registration, additional power and fuel lifetime capability, space weather, solar x-ray imaging, search and rescue, and communication services as provided on GOES-13. GOES-P is also in ground storage following the completion of environmental testing and is prepared for an April 2009 launch readiness with a July 2010, engineering handover date requirement. Summary provided by http://goespoes.gsfc.nasa.gov/goes/spacecraft/goes_o_spacecraft.html Group: Platform_Details Entry_ID: GOES-14 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: GOES (Geostationary Operational Environmental Satellite) Short_Name: GOES-14 Long_Name: Geostationary Operational Environmental Satellite 14 End_Group Group: Platform_Associated_Instruments Short_Name: SEM Short_Name: SXI Short_Name: GOES N-P IMAGER Short_Name: GOES N-P SOUNDER End_Group Group: Orbit Orbit_Type: GEO > GEOSYNCHRONOUS > GEOSTATIONARY End_Group Creation_Date: 2009-02-12 Online_Resource: http://goespoes.gsfc.nasa.gov/goes/spacecraft/goes_o_spacecraft.html Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=2009-033A Online_Resource: http://www.nasa.gov/mission_pages/GOES-O/main/index.html Online_Resource: http://nasascience.nasa.gov/missions/goes-n-o-p Online_Resource: http://www.oso.noaa.gov/goes Online_Resource: http://goes.gsfc.nasa.gov/ Sample_Image: http://goespoes.gsfc.nasa.gov/goes/launchinfo/images/GOESN_launch.jpg Group: Platform_Logistics Launch_Date: 2009-06-27 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: USA/NASA Primary_Sponsor: USA/NOAA End_Group End_Group 2018-04-05 19:25:48.0 [sritz] update WeightedRelation (Platform-Instrument); update WeightedRelation (1); 2018-04-05 19:25:18.0 [sritz] update Resource (image); insert WeightedRelation (id: null related concept uuid: 55461d90-0015-4d73-8ccc-16b25d9c925c relationship type: null relationship value: null generated by: null); INSAT-1B Spacecraft Brief Description The Insat 1B was the second spacecraft in the first generation Indian National Satellite System. The three-axis stabilized spacecraft, originally launched as an on-orbit backup, replaced Insat 1A, which failed in late 1982. It was positioned in a geosynchronous orbit at 74 deg E with a host of ground stations throughout India. The Insat 1B satellite, built by the Ford Aerospace and Communications Corporation, was designed to provide combined telecommunications, direct TV broadcast, and meteorological service to India's civilian community over a 7-year-in-orbit lifespan. The telecommunications package provided two-way, long-distance telephone circuits and direct radio and TV broadcasting to the remotest areas of India. The meteorology package was comprised of a scanning very-high-resolution, two-channel radiometer (VHRR) to provide full-frame, full-earth coverage every 30 min. The visual channel (0.55-0.75 micrometer) had a 2.75-km resolution while the IR channel (10.5-12.5 micrometers) had an 11-km resolution. Using the Insat TV capability, early warnings of impending disasters (i.e., floods, storms, etc.) can directly reach the civilian population, even in remote areas. The Insat 1B also had a data channel for relaying meteorological, hydrological, and oceanographic data from unattended land-based or ocean-based data collection and transmission platforms. * INSAT-1B was relegated to spare status on 17 July 1990 by the INSAT-1D. The INSAT-1B was finally removed from GEO in August 1993, after being replaced at 93.50E by INSAT-2B.* Auxiliary Information Launch Date and Time : 1983-08-31 07:49:00 Epoch Date and Time : 1983-10-15 Orbit Type : Geocentric Apogee(km) : 35680. Perigee(km) : 35680. Inclination : 0.0 Date of last update : 1998-10-07 More information about the INSAT Satellite Series is available at: "http://www.bharat-rakshak.com/SPACE/space-satellite3.html" Group: Platform_Details Entry_ID: INSAT-1B Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: INSAT (Indian National Satellite) Short_Name: INSAT-1B Long_Name: Indian National Satellite-1B End_Group Group: Synonymous_Platform_Names Short_Name: INSAT-1B End_Group Group: Platform_Associated_Instruments Short_Name: VHRR End_Group Group: Orbit Orbit_Inclination: 0.0 Perigee: 35680 Apogee: 35680 End_Group Creation_Date: 2007-10-05 Online_Resource: http://www.bharat-rakshak.com/SPACE/space-satellite3.html Group: Platform_Logistics Launch_Date: 1983-08-31 Primary_Sponsor: India End_Group End_Group STS-55 The 54th flight of the Space Shuttle will be devoted primarily to Germany for conducting a wide range of experiments in the microgravity environment of space flight. Columbia, the flagship of the Shuttle fleet, will make its 14th voyage into Earth orbit carrying a crew of seven, including two German payload specialists. STS-55's primary payload is Spacelab D2, for the second Shuttle mission dedicated to Germany. Spacelab D1 was flown in 1985. Spacelab is a self-contained, space-based research laboratory carried inside the Shuttle's 60- foot-long cargo bay. [Summary provided by NASA] Group: Platform_Details Entry_ID: STS-55 Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Platform_Series_or_Entity: SPACE SHUTTLE Short_Name: STS-55 Long_Name: Space Transport System STS-55 End_Group Group: Synonymous_Platform_Names Short_Name: COLUMBIA End_Group Creation_Date: 2008-01-30 Online_Resource: http://science.ksc.nasa.gov/shuttle/missions/sts-55/mission-sts-55.html Group: Platform_Logistics Launch_Date: 1993-04-26 Primary_Sponsor: NASA End_Group End_Group MT1 2014-06-18 17:09:20.0 [saritz] insert AltLabel (id: null text: Megha-Tropiques language code: en); 2014-06-18 17:08:45.0 [saritz] Insert Concept add broader relation (MT1 [9e09177b-bc72-41e9-921a-a4546f89e20a,106481] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,73425]); IRS-P4 Oceansat-1 The IRS-P4 (Oceansat-1), the eighth satellite built in India under the indigenous Indian Remote Sensing Satellite programme was successfully launched on May,26,1999 at 11.52 A.M from Sriharikota, India using the indigenously developed Polar Satellite Launch Vehicle (PSLV). IRS-P4 carries two sensors onboard, Ocean Color Monitor (OCM) and Multi-frequency Scanning Microwave Radiometer (MSMR). Several new technologies like Dual Cone Earth Sensor, improved Digital Sun Sensor and Satellite Positioning System (SPS) were introduced in the satellite. OCM data products are available to the User community acquired from July,01,1999 onwards. [Summary provided by the Indian Remote Sensing Agency.] Group: Platform_Details Entry_ID: IRS-P4 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: IRS (Indian Remote Sensing Satellite) Short_Name: IRS-P4 Long_Name: Indian Remote Sensing Satellite-P4 (OCEANSAT-1) End_Group Group: Synonymous_Platform_Names Short_Name: Oceansat-1 End_Group Group: Platform_Associated_Instruments Short_Name: OCM Short_Name: MIMR Short_Name: SMMR Short_Name: MR End_Group Group: Orbit Orbit_Altitude: 720 km Orbit_Inclination: 98.28 degree Equator_Crossing: 12 noon Period: 98 minutes Repeat_Cycle: 2 days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-08-13 Online_Resource: http://www.isro.gov.in/satellites/irs-p4_oceansat.aspx Sample_Image: http://www.isro.gov.in/satellites/images/irsp4ocsat_img.gif Group: Platform_Logistics Launch_Date: 1999-05-26 Launch_Site: Sriharikota Island, India Design_Life: 5 Years Primary_Sponsor: India End_Group End_Group 2018-06-12 17:35:12.0 [mmorahan] insert AltLabel (id: null category: null text: Oceansat-1 language code: en); update Resource (image); SUBMARINE Submarine: A vessel that is capable of operating submerged. [Source: Webster's Revised Unabridged Dictionary, 1996, 1998 MICRA, Inc.] Group: Platform_Details Entry_ID: SUBMARINE Group: Platform_Identification Platform_Category: In Situ Ocean-based Platforms Platform_Series_or_Entity: SHIPS Short_Name: SUBMARINE End_Group Group: Synonymous_Platform_Names Short_Name: Submarines End_Group Creation_Date: 2007-12-12 Online_Resource: http://en.wikipedia.org/wiki/Submarine Sample_Image: http://upload.wikimedia.org/wikipedia/commons/thumb/f/f6/ALVIN_submersible.jpg/180px-ALVIN_submersible.jpg End_Group Titan 34D 2015-12-01 20:41:40.0 [gee-cee] Insert Concept add broader relation (Titan 34D [9e9e86b0-d613-4069-abe2-8291a6fac3ef,158531] - Balloons/Rockets [2196cc92-a5da-4233-9509-5523385da1d7,143329]); LNOM [Source: NASA GHRC, http://ghrc.nsstc.nasa.gov/ ] LNOM The LNOM model is NASA software which combines detailed, flash-specific measurements of lightning with empirical laboratory results of lightning NOx production of Lightning Mapper Array and NLDN data to compute the vertical lightning NOx profile inside the analysis cylinder and the total NOx produced by each flash. Group: Platform_Details Entry_ID: LNOM Group: Platform_Identification Platform_Category: Models Short_Name: LNOM Long_Name: Lightning Nitrogen Oxides Model End_Group Creation_Date: 2012-01-30 End_Group OPERATIONAL MODELS 2015-08-10 14:41:19.0 [gee-cee] Insert Concept add broader relation (OPERATIONAL MODELS [9f95a56a-2669-427e-a785-de9162ffe133,158197] - Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215]); QZSS QZSS is a three-satellite regional positioning and time transfer system and satellite-based augmentation system for GPS receivable within Japan. 2017-08-15 13:47:26.0 [tstevens] insert Definition (id: null text: QZSS is a three-satellite regional positioning and time transfer system and satellite-based augmentation system for GPS receivable within Japan. language code: en); 2017-08-14 19:23:17.0 [tstevens] insert AltLabel (id: null category: primary text: Quasi-Zenith Satellite System Satellites language code: en); 2017-08-14 19:23:01.0 [tstevens] Insert Concept add broader relation (QZSS [9f9d2fac-92f3-4bc5-80ea-e68da85dd352,309915] - QZSS (Japan’s Quasi-Zenith Satellite System) [225fb800-22b1-4d06-88ac-2bb391ac0906,309911]); Titan IIID 2015-12-01 20:41:51.0 [gee-cee] Insert Concept add broader relation (Titan IIID [a044e8ff-8225-4bba-85c4-80ea394e007b,158535] - Balloons/Rockets [2196cc92-a5da-4233-9509-5523385da1d7,143329]); GEMINI-9 Gemini 9, manned with two astronauts, was the seventh earth-orbiting spacecraft of the Gemini series. The blunt, cone-shaped spacecraft was 3.048 cm in diameter at the rear of the craft. Primary mission objectives were to demonstrate (1) three rendezvous techniques, (2) an extravehicular activity (EVA) to test the astronaut maneuvering unit (AMU), and (3) precision landing capability. scientific objectives included obtaining zodiacal light and airglow horizon photographs. Two micrometeorite studies were to be carried out, and there were also one medical and two technological experiments. the agena target vehicle failed to achieve orbit, and the agena micrometeorite experiment hardware was lost. Other experiments functioned normally. The three rendezvous techniques were demonstrated, although docking could not be achieved due to a failure of the augmented target-docking shroud to jettison. The EVA was curtailed due to fogging of the visor and energy expended by the astronaut. Reentry was routinely accomplished after 47 orbits on june 6, 1966, within 3.2 km of the target point. Group: Platform_Details Entry_ID: GEMINI-9 Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Platform_Series_or_Entity: GEMINI Short_Name: GEMINI-9 End_Group Group: Synonymous_Platform_Names Short_Name: TITAN II (9) End_Group Group: Orbit Orbit_Inclination: 28.86 degrees Perigee: 270 km Apogee: 272 km End_Group Creation_Date: 2008-01-24 Online_Resource: http://www.astronautix.com/flights/gemini9.htm Sample_Image: http://www.astronautix.com/graphics/0/10074373.jpg Group: Platform_Logistics Launch_Date: 1966-06-03 Primary_Sponsor: NASA End_Group End_Group Pleiades-1A Pléiades 1A and Pléiades 1B operate as a constellation in the same orbit, phased 180° apart. The identical twin satellites deliver very-high-resolution optical data products in record time and offer a daily revisit capability to any point on the globe. The Pléiades constellation is designed to obtain data in double-quick time: Ability to acquire imagery anywhere in the world in less than 24 hrs. in response to a crisis or natural disaster. Regular monitoring, as often as every day if required. Three satellite work plans a day ensure easy handling of last-minute tasking requests. Twice the coverage and twice the chance of obtaining cloud-free imagery. 2018-06-14 13:05:26.0 [mmorahan] insert Definition (id: null text: Pléiades 1A and Pléiades 1B operate as a constellation in the same orbit, phased 180° apart. The identical twin satellites deliver very-high-resolution optical data products in record time and offer a daily revisit capability to any point on the globe. The Pléiades constellation is designed to obtain data in double-quick time: Ability to acquire imagery anywhere in the world in less than 24 hrs. in response to a crisis or natural disaster. Regular monitoring, as often as every day if required. Three satellite work plans a day ensure easy handling of last-minute tasking requests. Twice the coverage and twice the chance of obtaining cloud-free imagery. language code: en); 2018-06-14 13:00:05.0 [mmorahan] Insert Concept add broader relation (Pleiades-1A [a0b1f332-41b9-4eec-8a9e-67778193a679,367715] - PLEIADES [516a9bb2-0171-4ad2-8d4f-3f7d1219d393,344967]); SURFACE WATER WEIR OSO-1 The objectives of the OSO satellite series were to perform solar physics experiments above the atmosphere during a complete solar cycle and to map the celestial sphere for direction and intensity of UV light, X-rays, and gamma radiation. The OSO 1 was the first satellite to have pointed instruments and onboard tape recorders for data storage. The OSO 1 platform consisted of a sail section, which pointed two experiments continuously toward the sun, supplying power to the experiments from the solar batteries and rechargeable chemical batteries; and a wheel section, which spun about an axis perpendicular to the pointing direction of the sail and carried seven experiments. Attitude adjustment was performed by gas jets. Data were simultaneously recorded on tape and transmitted by FM telemetry. A command system provided for 10 ground-based commands. The spacecraft performed normally until the second onboard tape recorder failed May 15, 1962. The spacecraft provided real-time data until May 1964, when the power cells failed. General Information: Designation: 00255 / 62006A Launch date: 7 Mar 1962 Country of origin: United States Mission: Scientific (Sun observation) Perigee/Apogee: 522/553 km Inclination: 32.8° Period: 95.3 min Launch vehicle: Thor Delta #8 End of Life: Out of service Apr 1963 Decay 8 Oct 1981 Additional information available at "http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/oso1.html" [Summary provided by NASA and The Satellite Encyclopedia] Group: Platform_Details Entry_ID: OSO-1 Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Platform_Series_or_Entity: OSO (Orbiting Solar Observatory) Short_Name: OSO-1 Long_Name: Orbiting Solar Observatory-1 End_Group Group: Synonymous_Platform_Names Short_Name: OSO-1 End_Group Group: Orbit Orbit_Inclination: 32.8 degrees Period: 95.3 min Perigee: 522 km Apogee: 553 km End_Group Creation_Date: 2007-12-14 Online_Resource: http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/oso1.html Sample_Image: http://www.nasm.si.edu/spacecraft/images/SS-Astro/A19820270000d.jpg Group: Platform_Logistics Launch_Date: 1962-03-07 Primary_Sponsor: NASA End_Group End_Group SOLAR/SPACE MONITORING STATIONS 2019-08-26 18:28:47.0 [sritz] Insert Concept add narrower relation (SOLAR/SPACE MONITORING STATIONS [a143e5f5-4e4c-45cb-8053-5c9f6a099784,345507] - SURFRAD [d5456efc-ae6c-4c68-8b5e-66e40226d897,369065]); ENVISAT Envisat ENVISAT was successfully launched on March 1, 2002 from Kourou, French Guiana on Europe's Ariane 5 launcher. The ENVIronmental SATellite (ENVISAT) is an element of the European Space Agency (ESA) Columbus Programme. The ENVISAT satellite is part of the International Earth Observation System (IEOS). The ENVISAT is designed to study Earth's resources and to contribute to the study of land surface properties, atmospheric chemistry, aerosol distribution, ocean and ice processes, and marine biology. The ENVISAT spacecraft is based on the Polar Platform (PPF) concept and consists of a Service Module (SM) which provides main support functions, and a mission-specific Payload Module (PLM) which provides the instruments and payload support functions. The Payload Module consists of the Payload Equipment Bay (PEB) and the Payload Carrier (PLC). The Payload Data Management Subsystem performs instrument and support subsystems, data processing, telecommand and telemetry management, data-bus control, failure management, and instrument operations timeline management. Commonad and control is provided by the Payload Module Computer (PMC). Scientific data generated from the instruments will be processed by the High Speed Multiplexer (HSM) for recording or transmission to the ground. A set of four tape recorders provide a recording speed of 2 to 4 Mbps and a capacity of 25 Gbits. The communication subsystem uses an x-band link directly to the ground and a Ka-band bi-directional link via ESA's Data Relay Satellite (DRS). The Thermal Control Subsystem consists of a Heater Switching Unit (HSU), heaters, thermistors and thermostats. The Service Module (SM) consists of a carbon-fibre-reinforced plastic (CFRP) cone with a launcher interface at one end and a propulsion module at the other. The power subsystem consists of up to eight nickel-cadmium batteries (40 Ahr) and a modular solar array. The SM on-board data management is done by the Central Computer Unit (CCU). Command and contral are done via S-band communications direct to the ground or through the DRS. The Attitude and Orbit Control Subsystem (AOCS) provides three-axis stabilization. Altitude measurements will be provided by digital Sun sensors, Earth-horizon sensors and gyroscopes while altitude control will be provided by monopropellent thrusters. Fine pointing is accomplished through star sensors and gyroscopes, reaction wheels, and magneto-torquers. The ENVISAT consists of : (1) Advanced SAR (ASAR), (2) Global Ozone Monitoring by Occultation of Stars (GOMOS), (3) Medium Resolution Imaging Spectrometer (MERIS), (4) Michelson Interferometer for Passive Atmospheric Sounding (MIPAS), (5) Radar Altimeter-2 (RA-2), (6) Advanced Along Track Scanning Radiometer (AATSR), (7) Scanning Imaging Absorption Spectrometer for Atmospheric Cartography (SCIMACHY), (8) Microwave Radiometer (MWR), (9) Doppler Orbitography and Radiopositioning Integrated by Satellite (DORIS), and (10) a Laser Retroreflector (LRR) for tracking. Just weeks after celebrating its tenth year in orbit, communication with the Envisat satellite was suddenly lost on 8 April. Following rigorous attempts to re-establish contact and the investigation of failure scenarios, the end of the mission is being declared. Group: Platform_Details Entry_ID: ENVISAT Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: ENVISAT Long_Name: Environmental Satellite End_Group Group: Platform_Associated_Instruments Short_Name: RA-2 Short_Name: MWR Short_Name: MIPAS Short_Name: MERIS Short_Name: LRR Short_Name: GOMOS Short_Name: DORIS Short_Name: ASAR Short_Name: AATSR End_Group Group: Orbit Orbit_Altitude: 800-km Orbit_Inclination: 98.55 degrees Equator_Crossing: 10 am Local time: e.g. Repeat_Cycle: 35 days Orbit_Type: LEO > LOW EARTH ORBIT > POLAR SUN-SYNCHRONOUS End_Group Creation_Date: 2007-09-20 Online_Resource: http://envisat.esa.int/ Sample_Image: http://www.dutchspace.nl/uploadedImages/Business_Fields/Earth_observation/Envisat/Envisat-in-Orbit-512.jpg Group: Platform_Logistics Launch_Date: 2002-03-01 Launch_Site: KOUROU, FRENCH GUIANA Design_Life: 10 years Primary_Sponsor: European Space Agency End_Group End_Group 2019-02-15 18:12:10.0 [mmorahan] update Definition (http://fedeo.spacebel.be/thesaurus/en/page/envisat); update Resource (image); 2016-06-09 19:13:13.0 [epneff] added altLabel insert AltLabel (id: null text: Envisat language code: en); BALLOONS 1. A flexible bag designed to be inflated with hot air or with a gas, such as helium, that is lighter than the surrounding air, causing it to rise and float in the atmosphere. Such a bag with sufficient capacity to lift and transport a suspended gondola or other load. Such a bag shaped like a figure or object when inflated; an inflatable. [Source: The American Heritage? Dictionary of the English Language, Fourth Edition Copyright ? 2000 by Houghton Mifflin Company.] MAXIS MAXIS (MeV Auroral X-ray Imaging and Spectroscopy): Launched: January 12, 2000 Purpose of Flight: To study electron precipitation from the magnetosphere into the ionosphere. This electron precipitation creates the aurora (northern and southern lights) along with X-rays which can be observed with our balloon instrumentation. For this project, the University of Washington provided a bismuth germanate (BGO) X-ray spectrometer and two X-ray imaging cameras. One camera has a pinhole collimator and the other has a coded aperture mask collimator. Both cameras use scintillating crystals and photomultiplier tubes to detect X-rays which are produced in the aurora. The Berkeley balloon group provided a high resolution germanium X-ray spectrometer. All of these instruments flew on the INTERBOA campaign in 1996, where they observed an unusual relativistic electron precipitation event. The MAXIS balloon was terminated on January 30, 2000 at 22:13 UT after a successful 450 hour flight. Additional information available at "http://www.geophys.washington.edu/Space/SpaceExp/Balloon/Antarctica99/" [Source: University of Washington] Group: Platform_Details Entry_ID: MAXIS Group: Platform_Identification Platform_Category: Balloons/Rockets Short_Name: MAXIS Long_Name: MeV Auroral X-ray Imaging and Spectroscopy End_Group Group: Platform_Associated_Instruments Short_Name: BGO End_Group Creation_Date: 2007-08-21 Online_Resource: http://www.geophys.washington.edu/Space/SpaceExp/Balloon/Antarctica99/ Sample_Image: http://www.geophys.washington.edu/Space/SpaceExp/Balloon/Antarctica99/pictures/maxisinflate.jpg Group: Platform_Logistics Launch_Date: 2000-01-12 End_Group End_Group NASA Small Explorer (SMEX) METEOSAT-5 The Meteosat Operational Programme (MOP-2) satellite, launched on March 2,1991, was the second operational geostationary Meteosat satellite following 3 pre-operational Meteosat satellites (Meteosat-1,-2,-3/P2). The primary goal of the MOP satellites were (1) to provide visible and IR day/night cloudcover data and radiances and (2) disseminate image data to users through the Data Collection Platform (DCP). MOP-2 (or Meteosat 5) is a 2.1 m diameter, 3.195 m high stepped cylindrical body with solar cells on six main body panels. The spacecraft is spin-stabilized at 100 rpm around the main axis aligned almost parallel to the Earth's axis with spin regulated by two small hydrazine thrusters. Spin access control and east-west stationkeeping is provided by two pairs of large thrusters. Attitude information is provided by Earth horizon and Sun-lit sensors. A radiating dipole antenna directs S-band (333 kbs) transmission of DCP image data to the Data Acquisition, Telemetry, and Tracking Station at Odenwald, Germany for relay to the Meteosat Ground Computer System and Meteosat Operations Control center at ESA's European Space Operations Center(ESOC). The MOP-2 carries a single imaging radiometer invisible/infrared wavelengths in addition to the Data Collection Platform. To view a 3D orbit, observe the J Track satellite tracking web page: http://liftoff.msfc.nasa.gov/RealTime/JTrack/ For information on the European Space Agency (ESA) and the Meteosat Program, see the URL: http://www.esrin.esa.it Group: Platform_Details Entry_ID: METEOSAT-5 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: METEOSAT Short_Name: METEOSAT-5 Long_Name: Meteosat Operational Programme 2 (MOP-2) End_Group End_Group BE-200 The basic configuration of the Be-200 amphibious aircraft is indended for fighting the forest fires using the fire extinguishant fluids. While doing this, the aircraft can fulfill the following tasks: - stop and restrain the spread of the big forest fires by developing the protecting strip due to multiple drops on the fire edge; - extinguishing the small fire and fire which only starts to develop; - delivery of fire brigades and fire extingushing equipment to the fire region by landing on preselected water area of aifield, and return to the base. A particular feature of the Be-200 aircraft, when compared with the other amphibians, is that it has fully pressurized fuselage, which allows to fulfill a lot of missions. The aircraft is fitted with flight/navigation and communication equipment allowing the navigation and flight control at all flight phases in adverse weather conditions at any season, day and night. Group: Platform_Details Entry_ID: BE-200 Group: Platform_Identification Platform_Category: Aircraft Short_Name: BE-200 Long_Name: Beechcraft King Air BE-200 End_Group Creation_Date: 2008-07-14 Online_Resource: http://www.beriev.com/eng/Be-200_e/Be-200_e.html Sample_Image: http://upload.wikimedia.org/wikipedia/commons/thumb/8/8e/Beriew_Be-200_CH-S_l.jpg/800px-Beriew_Be-200_CH-S_l.jpg End_Group GOSAT [Source: ESA Earthnet Online, http://earth.esa.int/object/index.cfm?fobjectid=5096] GOSAT (Greenhouse gases Observing Satellite) is a JAXA (Japan Aerospace Exploration Agency) mission within the GCOM (Global Change Observation Mission) program of Japan. The GOSAT mission goals call for the study of the transport mechanisms of greenhouse gases such as carbon dioxide (CO2) and methane (CH4). The emphasis is on atmospheric monitoring to clarify the sources and sinks of CO2 on a sub-continental scale. The overall mission objective is to contribute to environmental administration by estimating the Green House Gases (GHGs) source and sink on a sub-continental scale and to support the Kyoto protocol that was adsorbed at COP3/UNFCCC (3rd session of the conference in the framework of climate change) in 1997. The protocol calls for a reduction of greenhouse gases, in particular CO2; it requires all parties to reduce their emissions by 5% below the level of the year 1990, for the period of 2008-2012 Group: Platform_Details Entry_ID: GOSAT Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: GOSAT Long_Name: Greenhouse Gases Observing Satellite End_Group Group: Synonymous_Platform_Names Short_Name: IBUKI Short_Name: 2009-002A End_Group Group: Platform_Associated_Instruments Short_Name: TANSO-FTS Short_Name: TANSO-CAI End_Group Group: Orbit Orbit_Altitude: 666 km Repeat_Cycle: 3 days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2010-08-24 Online_Resource: http://www.gosat.nies.go.jp/index_e.html Online_Resource: http://www.jaxa.jp/projects/sat/gosat/index_e.html Online_Resource: https://data.gosat.nies.go.jp/GosatUserInterfaceGateway/guig/GuigPage/open.do Online_Resource: http://earth.esa.int/object/index.cfm?fobjectid=5096 Sample_Image: http://www.jaxa.jp/projects/sat/gosat/img/photo-1_goast.jpg Group: Platform_Logistics Launch_Date: 2009-01-23 Launch_Site: Tanegashima Island, Japan Primary_Sponsor: JP/JAXA End_Group End_Group NOAA POES NOAA POES (Polar Orbiting Environmental Satellites) The world's first operational weather satellite system was placed into service with the launching of the Environmental Satellite Services Administration (which in 1970 became the National Oceanic and Atmospheric Administration, NOAA) satellites, ESSA-1, on February 3, 1966, and ESSA-2, on February 28, 1966. The objective of this program, called the TIROS Operational System (TOS), was to acquire global observational data routinely on a daily basis. This system consisted of a pair of ESSA satellites in sun synchronous (polar) orbit. The odd numbered satellites (ESSA-1, 3, 5, 7, and 9) utilized the Advanced Vidicon Camera System (AVCS) to obtain global imagery which were transmitted to the ESSA Command and Data Acquisition (CDA) stations at Wallops, Virginia, and Fairbanks, Alaska. The CDA stations relayed the data to the National Environmental Satellite Service (NESS), which later became the National Environmental Satellite, Data, and Information Service (NESDIS), located in Suitland, Maryland, for processing and distribution to forecasting centers of the U.S. and other nations. The even numbered satellites (ESSA-2, 4, 6, and 8) were equipped with Automatic Picture Transmission (APT) TV cameras which transmitted television pictures directly to ground stations worldwide. The ESSA satellites operated in orbits at altitudes of approximately 1450 km. The second generation operational polar orbiting satellites started with the ITOS-1 (Improved TIROS Operational System) mission launched on January 23, 1970 which combined the joint capabilities of two ESSA spacecraft; essentially, the direct readout APT system and the global stored images of the AVCS. The second generation objectives were to provide improved operational Infrared (IR) and Visible (VIS) observations of Earth cloud cover for use in weather analysis and forecasting and also to provide solar proton and global heat data on a daily basis. ITOS-1 also carried an operational 2 channel Scanning Radiometer (SR) providing day and night radiometric data for immediate transmission as well as acquisition data stored for delayed transmission to CDA stations. With an Infrared 5 channel scanner, global observation of the Earth atmosphere and surface areas was available once every 12 hours. A second ITOS spacecraft, the National Oceanic and Atmospheric Administration satellite, NOAA-1, was launched on December 11, 1970. The ITOS system evolved further with the development of the ITOS-D satellites, NOAA-2, 3, 4, and 5 and were placed into orbit in 1972, 1973, 1974, and 1975, respectively. These had a new sensor complement to provide day and night imaging by means of the Very High Resolution Radiometer (VHRR) along with the medium resolution Scanning Radiometer (SR). The Vertical Temperature Profile Radiometer (VTPR) for sounding the atmosphere and the Solar Proton Monitor (SPM) for measurements of solar proton and electron flux in the vicinity of the satellite were added. The first spacecraft in the third generation operational polar orbiting environmental satellite system was TIROS-N which was launched in 1978. The third generation objectives were to provide observations for the atmosphere, cloud cover, surface and near-surface. The TIROS-N type satellites that followed were NOAA-A (6), NOAA-B which failed to achieve useful orbit, NOAA-C (7), and NOAA-D. The TIROS-N system provided NOAA with the global meteorological and environmental data required for normal operations and for the experimental World Weather Watch (WWW) Program. The spacecraft had a new complement of data gathering instruments. The Advanced Very High Resolution Radiometer (AVHRR) provided day and night imaging in the Visible (VIS) and Infrared (IR), sea surface temperature (SST) determination, estimation of heat budget components, and identification of snow and sea ice. The TIROS Operational Vertical Sounder (TOVS) supplied improved estimates of the vertical structure of the atmosphere. The Data Collection System (DCS) gathered environmental data from fixed and moving platforms such as buoys and balloons, and transmitted the data to central stations for processing and relay to users. The Solar Environment Monitor (SEM) measured solar proton, electron, and alpha particle densities. The data collected were stored onboard the satellite for transmission to the NOAA central processing facility at Suitland, Maryland, through the Wallops and Fairbanks CDA stations. Satellite data also were transmitted in real time direct readout at VHF and S-band frequencies to remote stations worldwide. The Advanced TIROS-N (ATN) type satellites were NOAA-E (8), NOAA-F (9), NOAA-G (10), NOAA-H (11), NOAA-I (12), and NOAA-J (13), the latter two scheduled for launch in 1990 and 1991 respectively. The spacecraft was lengthened 0.5m and the solar array was enlarged to provide additional power. New systems were added starting with NOAA-8: the Search and Rescue (SAR) system; NOAA-9: the Earth Radiation Budget Experiment (ERBE) instruments and the Solar Backscatter UltraViolet (SBUV) radiometer; NOAA-10: ERBE instruments. For more information about the NOAA POES satellite series link to the ----------------- Entry taken from: Rao, P.K., S.J. Holmes, R.K. Anderson, J.S. Winston and P.E. Lehr, Weather Satellites: Systems, Data, and Environmental Applications, American Meteorological Society, Boston, 1990. ISBN 0-933876-66-1 Cornillon, P., A Guide to Environmental Satellite Data, University of Rhode Island Marine Technical Report 79, 1982. Group: Platform_Details Entry_ID: NOAA POES Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NOAA POES (Polar Orbiting Environmental Satellites) Short_Name: NOAA POES Long_Name: NOAA Polar Orbiting Environmental Satellites End_Group Group: Synonymous_Platform_Names Short_Name: NOAA POES End_Group Group: Platform_Associated_Instruments Short_Name: TOVS Short_Name: AVHRR End_Group Creation_Date: 2007-10-17 Online_Resource: http://www.oso.noaa.gov/poes/index.htm Sample_Image: http://www.oso.noaa.gov/poesstatus/images/poesSpacecraft.gif Group: Platform_Logistics Primary_Sponsor: NASA End_Group End_Group 2016-06-09 17:11:29.0 [epneff] added altLabel insert AltLabel (id: null text: NOAA POES (Polar Orbiting Environmental Satellites) language code: en); OSO-7 Spacecraft Brief Description The objectives of the OSO satellite series were to perform solar physics experiments above the atmosphere during a complete solar cycle and to map the entire celestial sphere for direction and intensity of UV light and X-ray and gamma radiation. The OSO 7 platform consisted of a sail section, which pointed two experiments continually toward the sun, and a wheel section, which spun about an axis perpendicular to the pointing direction of the sail and carried four experiments. Attitude adjustment was performed by gas jets and a magnetic torquing coil. A pointing control permitted the pointed experiments to scan the region of the solar disk in a 60- by 60-arc-min raster pattern. In addition, the pointed section could be commanded to select and scan any 7.5- by 5-arc-min region near the solar disk. Data were simultaneously recorded on tape and transmitted by PCM/PM telemetry. A command system provided for at least 155 ground-based commands. Only real-time data have been received since May 1973, when the second tape recorder failed. The spacecraft reentered the earth's atmosphere July 9, 1974. Auxiliary Information Launch Date and Time : 1971-09-29 09:50:00 Epoch Date and Time : 1971-09-30 Orbit Type : Geocentric Apogee(km) : 572. Perigee(km) : 321. Inclination : 33.1 Date of last update : 2003-01-28 Additional information available at "http://heasarc.gsfc.nasa.gov/docs/oso7/oso7.html" Group: Platform_Details Entry_ID: OSO-7 Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Platform_Series_or_Entity: OSO (Orbiting Solar Observatory) Short_Name: OSO-7 Long_Name: Orbiting Solar Observatory-7 End_Group Group: Synonymous_Platform_Names Short_Name: OSO-7 End_Group Group: Platform_Associated_Instruments Short_Name: GAMMA RADIATION DETECTOR End_Group Group: Orbit Orbit_Inclination: 33.1 degrees Perigee: 321 km Apogee: 572 km End_Group Creation_Date: 2007-12-14 Online_Resource: http://heasarc.gsfc.nasa.gov/docs/oso7/oso7.html Sample_Image: http://heasarc.gsfc.nasa.gov/Images/oso/oso7_flight.gif Group: Platform_Logistics Launch_Date: 1971-09-29 Primary_Sponsor: NASA End_Group End_Group OSO-6 The objectives of the OSO satellite series were to perform solar physics experiments above the atmosphere during a complete solar cycle and to map the celestial sphere for direction and intensity of UV light, X-rays, and gamma radiation. General Information: Designation: 04065 / 69068A Launch date: 9 Aug 1969 Country of origin: United States Mission Scientific: Sun observation Perigee/Apogee: 489/554 km Inclination: 32.9° Period: 95.1 min Launch vehicle: Thor Delta #72 Out of service: Jan 1972 Decay: 7 Mar 1981 Additional information available at "http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/oso6.html" [Summary provided by The Satellite Encyclopedia] Group: Platform_Details Entry_ID: OSO-6 Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Platform_Series_or_Entity: OSO (Orbiting Solar Observatory) Short_Name: OSO-6 Long_Name: Orbiting Solar Observatory-6 End_Group Group: Synonymous_Platform_Names Short_Name: OSO-6 End_Group Group: Platform_Associated_Instruments Short_Name: GAMMA RADIATION DETECTOR End_Group Group: Orbit Orbit_Inclination: 32.9 degrees Period: 95.1 min Perigee: 489 km Apogee: 554 km End_Group Creation_Date: 2007-12-14 Online_Resource: http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/oso6.html Sample_Image: http://heasarc.gsfc.nasa.gov/Images/oso/oso7.gif Group: Platform_Logistics Launch_Date: 1969-08-09 Primary_Sponsor: NASA End_Group End_Group ISIS-2 - Spacecraft Brief Description - ISIS 2 was an ionospheric observatory instrumented with a sweep- and a fixed-frequency ionosonde, a VLF receiver, energetic and soft particle detectors, an ion mass spectrometer, an electrostatic probe, a retarding potential analyzer, a beacon transmitter, a cosmic noise experiment, and two photometers. Two long crossed-dipole antennas (73 and 18.7 m) were used for the sounding, VLF, and cosmic noise experiments. The spacecraft was spin-stabilized to about 2 rpm after antenna deployment. There were two basic orientation modes for the spacecraft, cartwheel and orbit-aligned. The spacecraft operated approximately the same length of time in each mode, remaining in one mode typically 3 to 5 months. The cartwheel mode with the axis perpendicular to the orbit plane was made available to provide ram and wake data for some experiments for each spin period, rather than for each orbit period. Attitude and spin information was obtained from a three-axis magnetometer and a sun sensor. Control of attitude and spin was possible by means of magnetic torquing. The experiment package also included a programmable tape recorder with a 1-h capacity. For nonrecorded observations, data from satellite and subsatellite regions were telemetered when the spacecraft was in the line of sight of a telemetry station. Telemetry stations were located so that primary data coverage was near the 80-deg-W meridian and near Hawaii, Singapore, Australia, England, France, Norway, India, Japan, Antarctica, New Zealand, and Central Africa. NASA support of the ISIS project was terminated on October 1, 1979. A significant amount of experimental data, however, was acquired after this date by the Canadian project team. ISIS 2 operations were terminated in Canada on March 9, 1984. The Radio Research Laboratories (Tokyo, Japan) then requested and received permission to reactivate ISIS 2. Regular ISIS 2 operations were started from Kashima, Japan, in early August 1984. ISIS 2 was deactivated effective 24, 1990. - Auxiliary Information - Launch Date and Time : 1971-04-01 02:53:00 Epoch Date and Time : 1971-04-02 Apogee (km or AU): 1428. Perigee (km or AU): 1358. Inclination (degree) : 88.1 Orbit Type : Geocentric Information last updated on 1992-03-09 Group: Platform_Details Entry_ID: ISIS-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: ISIS (International Satellite for Ionospheric S Short_Name: ISIS-2 Long_Name: International Satellite for Ionospheric Studies-2 End_Group Group: Synonymous_Platform_Names Short_Name: ISIS-B End_Group Group: Platform_Associated_Instruments Short_Name: PHOTOMETERS Short_Name: PARTICLE DETECTORS Short_Name: VLF RECEIVERS End_Group Group: Orbit Orbit_Inclination: 88.1 deg Perigee: 1358 km Apogee: 1428 km End_Group Creation_Date: 2007-10-05 Online_Resource: http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1971-024A Group: Platform_Logistics Launch_Date: 1971-04-01 Primary_Sponsor: NASA End_Group End_Group DHC-6 The DeHavilland Twin Otter (DHC-6) is a highly maneuverable, versatile aircraft which can be flown slowly (80-160 knots/150-300 km/hr) and in tight circles. The Twin Otter is a high-winged, unpressurized, twin-engine turboprop aircraft equipped with color weather radar, radar altimeter, dual GPS/Loran-C navigation systems with scientific data drops, and camera ports in the nose and belly areas. A standard flight crew consists of two NOAA pilots. In support of NOAA or NOAA-related missions, this platform has conducted low-level slow speed aerial surveys of marine mammals, aerial video surveys of coastal erosion, various remote sensing missions, atmospheric air chemistry sampling, and atmospheric eddy flux and concentration gradient assessments. [Photo and text provided by NOAA, http://www.aoc.noaa.gov/aircraft_otter.htm ] Group: Platform_Details Entry_ID: DHC-6 Group: Platform_Identification Platform_Category: Aircraft Short_Name: DHC-6 Long_Name: DeHavilland Twin Otter End_Group Creation_Date: 2008-07-14 Online_Resource: http://www.aoc.noaa.gov/aircraft_otter.htm Sample_Image: http://www.aoc.noaa.gov/images/Otter_flying_over_beach.JPG End_Group GEOS-1 Spacecraft Brief Description The GEOS 1 (Geodetic Earth Orbiting Satellite) spacecraft was a gravity-gradient-stabilized, solar-cell powered unit designed exclusively for geodetic studies. It was the first successful active spacecraft of the National Geodetic Satellite Program. Instrumentation included (1) four optical beacons, (2) laser reflectors, (3) a radio range transponder, (4) Doppler beacons, and (5) a range and range rate transponder. These were designed to operate simultaneously to fulfill the objectives of locating observation points (geodetic control stations) in a three dimensional earth center-of-mass coordinate system within 10 m of accuracy, of defining the structure of the earth's irregular gravitational field and refining the locations and magnitudes of the large gravity anomalies, and of comparing results of the various systems onboard the spacecraft to determine the most accurate and reliable system. Acquisition and recording of data were the responsibility of the GSFC Space Tracking and Data Acquisitions Network (STADAN). Ten major observing networks were used. Auxiliary Information Launch Date and Time : 1965-11-06 18:43:00 Epoch Date and Time : 1978-12-30 Orbit Type : Geocentric Apogee(km) : 2275. Perigee(km) : 1113. Inclination : 59.4 Date of last update : 1992-04-21 Group: Platform_Details Entry_ID: GEOS-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: GEOS (Geodetic Earth Orbiting Satellite) Short_Name: GEOS-1 Long_Name: Geodetic Earth Orbiting Satellite-1 End_Group Group: Synonymous_Platform_Names Short_Name: GEOS-1 End_Group Group: Platform_Associated_Instruments Short_Name: TRANSPONDERS Short_Name: DOPPLER BEACONS Short_Name: RADIO TRANSPONDERS Short_Name: LASER REFLECTOR Short_Name: OPTICAL BEACON End_Group Group: Orbit Orbit_Inclination: 59.3 deg Period: 540 days Perigee: 1135 km Apogee: 2270 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-09-26 Online_Resource: http://cddis.nasa.gov/926/egm96/geos1.html Sample_Image: http://www1.cira.colostate.edu/ramm/hillger/ESA-GEOS-1_image.jpg Group: Platform_Logistics Launch_Date: 1977-04-20 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: NASA End_Group End_Group IMS-1 IMS-1, previously referred to as TWSat (Third World Satellite), is a low-cost microsatellite imaging mission of ISRO (Indian Space Research Organization). The overall objective is to provide medium-resolution imagery for developing countries for free. Around 50 data reception terminals will be installed by ISRO in selected Third World countries and also at some universities in India. he project started in 2005 with a definition phase of the mission. The ISRO approach was to develop two versions of a standard small spacecraft bus (SSB) design with the objective to provide a low-cost and a quick-response time approach to space. • A microsatellite version (first use by the IMS-1 mission) • A minisatellite version (first use by the SARAL mission) The main advantage of these "smallsats" is the fact that they can be launched by a PSLV vehicle as a piggyback payload on any one of the larger primary payloads (like IRS satellites). The modular design concept of the SSB is suited for series production making the bus a natural choice for constellation-flight applications. The design layout is such that the bus module and the payload module of each series may be integrated and tested separately (thus reducing the interdependency during the realization between both modules). Each SSB version is 3-axis stabilized. SSB is also designed to accommodate different types of payloads with minor modification from mission to mission. The SSB micro-bus uses aluminum honeycomb panels arranged in a cuboid structure with internal shear frames. This design is made to provide maximum area for mounting the packages while being sturdy. All the subsystem packages are mounted within the cuboid except sensors and antennas which are mounted outside. The structure includes a launch vehicle interface and solar panel interfaces. The payloads are mounted on the top deck, with optical axis towards the + yaw direction. The power subsystem consists of solar panels, battery, power conditioning and distribution units. There are two solar panels of size 0.81m x 0.72 m in the roll direction of the satellite. The panels are stowed during the launch and deployed after injection to the orbit. The satellite is nominally in sun-pointing mode with the solar panels facing the sun. For every payload operation, the satellite is maneuvered into an Earth-pointing mode and goes back to the sun-pointing mode after the imaging operation. Multi-junction solar cells are being used to provide higher efficiency of power conversion to generate about 230 W. A Li-ion battery is used with a capacity of 10.5 Ah, having a mass of about 3.5 kg. The power subsystem provides a single raw bus of 28 to 33 V. There are four DC/DC converters which provide the required secondary voltages for the payloads and bus subsystems. The AOCS (Attitude and Orbit Control Subsystem) uses sun sensors with 4π FOV providing an accuracy of 0.5º in all axes. The sun sensors are being used for sun acquisition and safe mode detection and recovery. A MEMS-based magnetometer is being used in the spacecraft de-tumbling support mode and in the momentum dumping of the reaction wheels. A star sensor, providing an inertial quaternion output, is used as prime sensor during 3-axis stabilization and during the maneuver support modes. The accuracy of the star sensor is < 40 arcsec in all axes. In addition, there are two miniaturized gyros which are dynamically tuned. A GPS-based SPS (Satellite Positioning System) is used to provide the satellite position to an accuracy of < 30 m. Actuation is provided by magnetic torquers (momentum dumping), micro reaction wheels,and an RCS (Reaction Control Subsystem). The reaction wheels have aan angular momentum capacity of 0.36 Nms and a torque of 0.015 Nm. The wheels are arranged in a tetrahedral configuration to provide enhanced torques about any axis. The RCS consists of a single tank (8 liter volume) containing a monopropellant fuel and a single 1N thruster. The thruster is primarily used for orbit corrections. BMU (Bus Management Unit): The BMU represents the heart of the satellite providing the functions of telecommand decoding, house keeping telemetry, data encoding, sensor processing, on/off control of the subsystems and heaters, command distribution, spacecraft control during initial acquisition, normal mode, safe mode etc., using the actuators. This subsystem is realized in a single PCB (Printed Circuit Board). Passive control methods (with elements like multi layer insulation blankets, optical surface reflectors, thermal paints and heaters wherever necessary.) are being used in the thermal control subsystem. Launch: A launch of IMS-1 as a secondary payload on a PSLV vehicle (PSLV-C9) took place on April 28, 2008 from the SDSC-SHAR launch site (Sriharikota, India) of ISRO. The primary payload on this flight was CartoSat-2A (launch mass of 690 kg), an Indian military high-resolution panchromatic imaging satellite (based on CartoSat-2 of ISRO). TWSat carries two payloads: the Mx-T (Multispectral Camera) and the HySI (Hyperspectral Imager). However, since the data of both imagers is rather high, only one of them will be powered on and data transmitted at any given time. Mx-T (Multispectral Camera). The instrument of modular design provides four spectral bands in VNIR, where each band employs an individual lens, a separate CCD detector, and separate front-end electronics. The camera operates in a pushbroom scanning mode to image the Earth. The spatial resolution at nadir is 36 m on a swath of 151 km. The 12 bit video output is coded to 10 bit with multi-linear gain. Mx-T has a mass of 5.5 kg and a power consumption of 18 W. All the front end electronics and the video processors are accommodated on the electro optical module (EOM) itself. Each band has one detector which gives out data in 4 ports with 10 bits per pixel. The source data (32 Mbit/s) is sent to the baseband data handling system of the microsatellite bus, compressed and stored in SSR (Solid State Recorder). The recorded data is transmitted to the ground in S-band at 8 Mbit/s. HySI-T (Hyperspectral Imager). The prototype instrument providing a total of 64 spectral bands in the VNIR region. Spectral separation is realized using the wedge filter technique. Detection is provided with a CMOS/APS (Active Pixel Sensor) area device. - The HySI-T data may be used for resource characterization and detailed studies. The HySI-T is being used on an experimental basis to obtain experience of such a payload and also of handling the hyperspectral data and generating the application models. Mission operations: While Mx-T serves the basic requirement of the imaging mission, the HySI-T is incorporated on an experimental basis. It is planned to operate the Mx-T instrument on for most of the orbits based on the user demands, while the HySI-T is operated over Indian ground stations for evaluation purposes. Either of the payloads will be operated at a time in order to conserve the available resources on board the microsatellite. The data from the two payloads is being downlinked separately. The Mx-T data is compressed at a ratio of 3.4:1, formatted, RS (Reed Solomon) encoded and stored on SSR (Solid Sate Recorder). The downlink is in near real-time via the S-band transmitter. The SSR has the storage capacity of 16 Gbit providing a maximum storage volume of 20 minutes data in segmented form. Group: Platform_Details Entry_ID: IMS-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: IMS-1 End_Group Group: Platform_Associated_Instruments Short_Name: MX-T Short_Name: CCD IMAGER End_Group Group: Orbit Orbit_Altitude: 635 km Orbit_Inclination: 98 km Period: 97.3 minutes Perigee: 626.5 km Apogee: 646.3 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2008-06-27 Online_Resource: http://directory.eoportal.org/get_announce.php?an_id=15158 Sample_Image: http://directory.eoportal.org/presentations/6100/IMS1_Auto9.jpeg Group: Platform_Logistics Launch_Date: 2008-04-28 Launch_Site: Sriharikota Island, India Primary_Sponsor: Indian Space Research Organization (ISRO) End_Group End_Group GOES-3 GOES 3 was launched in June 1978 and was a NASA-developed, NOAA-operated, geosynchronous, and operational spacecraft. The cylindrically shaped spacecraft measured 190.5 cm in diameter and 230 cm in length, exclusive of a magnetometer that extended an additional 83 cm beyond the cylinder shell. The primary structural members were a honeycombed equipment shelf and thrust tube. The VISSR telescope was mounted on the equipment shelf and viewed the Earth through a special aperture in the side of the spacecraft. A support structure extended radially out from the thrust tube and was affixed to the solar panels, which formed the outer walls of the spacecraft and provided the primary source of electrical power. Located in the annulus-shaped space between the thrust tube and the solar panels were stationkeeping and dynamics control equipment, batteries, and most of the SEM equipment. Proper spacecraft attitude and spin rate (approximately 100 rpm) were maintained by two separate sets of jet thrusters mounted around the spacecraft equator and activated by ground command. The spacecraft used both UHF-band and S-band frequencies in its telemetry and command subsystem. A low-power VHF transponder provided telemetry and command during launch and then served as a backup for the primary subsystem once the spacecraft attained orbit. The spin-stabilized spacecraft carried a visible infrared spin-scan radiometer, meteorological data collection and transmission system, space environment monitor, and a biaxial fluxgate magnetometer. It operated at 135 degrees West as GOES-WEST. For more information on GOES satellites: http://www.ospo.noaa.gov/Operations/GOES/index.html 2017-09-01 17:03:44.0 [sritz] update Definition (GOES 3 was launched in June 1978 and was a NASA-developed, NOAA-operated, geosynchronous, and operational spacecraft. The cylindrically shaped spacecraft measured 190.5 cm in diameter and 230 cm in length, exclusive of a magnetometer that extended an additional 83 cm beyond the cylinder shell. The primary structural members were a honeycombed equipment shelf and thrust tube. The VISSR telescope was mounted on the equipment shelf and viewed the Earth through a special aperture in the side of the spacecraft. A support structure extended radially out from the thrust tube and was affixed to the solar panels, which formed the outer walls of the spacecraft and provided the primary source of electrical power. Located in the annulus-shaped space between the thrust tube and the solar panels were stationkeeping and dynamics control equipment, batteries, and most of the SEM equipment. Proper spacecraft attitude and spin rate (approximately 100 rpm) were maintained by two separate sets of jet thrusters mounted around the spacecraft equator and activated by ground command. The spacecraft used both UHF-band and S-band frequencies in its telemetry and command subsystem. A low-power VHF transponder provided telemetry and command during launch and then served as a backup for the primary subsystem once the spacecraft attained orbit. The spin-stabilized spacecraft carried a visible infrared spin-scan radiometer, meteorological data collection and transmission system, space environment monitor, and a biaxial fluxgate magnetometer. It operated at 135 degrees West as GOES-WEST. For more information on GOES satellites: http://www.ospo.noaa.gov/Operations/GOES/index.html); update Definition (NASA NSSDC, https://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1978-062A); 2017-09-01 17:02:31.0 [sritz] insert Definition (id: null text: [Source: NASA NSSDC, https://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1978-062A ] GOES 3 was launched in June 1978 and was a NASA-developed, NOAA-operated, geosynchronous, and operational spacecraft. The cylindrically shaped spacecraft measured 190.5 cm in diameter and 230 cm in length, exclusive of a magnetometer that extended an additional 83 cm beyond the cylinder shell. The primary structural members were a honeycombed equipment shelf and thrust tube. The VISSR telescope was mounted on the equipment shelf and viewed the Earth through a special aperture in the side of the spacecraft. A support structure extended radially out from the thrust tube and was affixed to the solar panels, which formed the outer walls of the spacecraft and provided the primary source of electrical power. Located in the annulus-shaped space between the thrust tube and the solar panels were stationkeeping and dynamics control equipment, batteries, and most of the SEM equipment. Proper spacecraft attitude and spin rate (approximately 100 rpm) were maintained by two separate sets of jet thrusters mounted around the spacecraft equator and activated by ground command. The spacecraft used both UHF-band and S-band frequencies in its telemetry and command subsystem. A low-power VHF transponder provided telemetry and command during launch and then served as a backup for the primary subsystem once the spacecraft attained orbit. The spin-stabilized spacecraft carried a visible infrared spin-scan radiometer, meteorological data collection and transmission system, space environment monitor, and a biaxial fluxgate magnetometer. It operated at 135 degrees West as GOES-WEST. For more information on GOES satellites: http://www.oso.noaa.gov/goes/ language code: en); 2017-09-01 16:36:33.0 [sritz] Insert Concept add broader relation (GOES-3 [a520a517-f8da-4bf7-9dec-5e8758dad38a,310083] - GOES [6e332c25-caeb-4917-afb6-af757bcecd72,310071]); SOLRAD-7B The Solar Radiation (SOLRAD) series 1, 4, 6 - 10 collected solar X-ray and ultraviolet data during numerous intervals in the years 1960 - 1973. General Information: Designation: 01291 / 65016D Launch date: 9 Mar 1965 Country of origin: United States Mission: Scientific Perigee/Apogee: 900/928 km Inclination: 70.1° Period: 103.3 min Launch vehicle: Thor Agena D Launch site: Vandenberg [Summary provided by The Satellite Encyclopedia] Group: Platform_Details Entry_ID: SOLRAD-7B Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Platform_Series_or_Entity: SOLRAD Short_Name: SOLRAD-7B Long_Name: Solar Radiation-7B End_Group Group: Synonymous_Platform_Names Short_Name: solrad-7B End_Group Group: Platform_Associated_Instruments Short_Name: SXP End_Group Group: Orbit Orbit_Inclination: 70.1 degrees Period: 103.3 minutes Perigee: 900 km Apogee: 928 km End_Group Creation_Date: 2008-01-14 Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1965-016D Sample_Image: http://www.astronautix.com/graphics/z/zgrab.jpg Group: Platform_Logistics Launch_Date: 1965-03-09 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: United States Department of Defense End_Group End_Group TSX TERRASAR-X [Source: ASTRIUM GEOInformation Services, http://www.infoterra.de/terrasar-x-satellite ] TerraSAR-X was successfully launched on June 15th, 2007, from Baikonur in Kazakhstan and has been fully operational since early 2008. With its active antenna, the spacecraft acquires high-quality X-band radar images of the entire planet whilst circling Earth in a polar orbit at 514 km altitude. TerraSAR-X is designed to carry out its task for five years, independent of weather conditions and illumination, and reliably provides radar imagery with a resolution of up to 1m and a unique geometric accuracy. Key Technical Features Active phased array X-band SAR Single, dual and quad polarisation Side-looking acquisition geometry Sun-synchronous dawn-dusk repeat orbit Repetition rate: 11 days; due to swath overlay, a 2.5 day revisit time time (2 days at 95% probability) to any point on Earth can be achieved Orbit altitude range from 512 km to 530 km Operational imaging modes: HighResolution Spotlight: up to 1m resolution, 5 to 10 km x 5 km (width x length) SpotLight: up to 2m resolution, 10 km x 10 km (width x length) StripMap: up to 3m resolution, 30 km x 50 km ( width x length)* ScanSAR: up to 18 m resolution, 100 km x 150 km (width x length)* Group: Platform_Details Entry_ID: TSX Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: TSX Long_Name: TerraSAR-X End_Group Group: Synonymous_Platform_Names Short_Name: TSX End_Group Group: Platform_Associated_Instruments Short_Name: SAR End_Group Group: Orbit Orbit_Inclination: 97.44 degrees Period: 11 Days Perigee: 514 Km Orbit_Type: LEO > LOW EARTH ORBIT > POLAR SUN-SYNCHRONOUS End_Group Creation_Date: 2007-11-28 Online_Resource: http://www.infoterra.de/terrasar-x-satellite Online_Resource: http://www.terrasar.de/ Online_Resource: http://www.dlr.de/tsx/start_en.htm Online_Resource: http://ilrs.gsfc.nasa.gov/satellite_missions/list_of_satellites/tsar_general.html Group: Platform_Logistics Launch_Date: 2007-06-15 Launch_Site: BAIKONUR COSMODROME, TYURATAM, RUSSIA Design_Life: 5 years Primary_Sponsor: Germany/DLR End_Group End_Group 2019-03-18 16:38:38.0 [mmorahan] delete WeightedRelation (null); insert WeightedRelation (id: null related concept uuid: 4dc63a97-144f-49f7-8fe2-2202857543f7 relationship type: null relationship value: null generated by: null); 2019-02-22 21:51:25.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: 285c90fb-0b3f-487f-a094-40d6dea7948e relationship type: null relationship value: null generated by: null); 2016-06-09 17:22:04.0 [epneff] added altLabel insert AltLabel (id: null text: TERRASAR-X language code: en); NEUTRON MONITOR STATIONS ACE The Advanced Composition Explorer (ACE) is an Explorer mission that is being managed by the Office of Space Science Mission and Payload Development Division of the National Aeronautics and Space Administration (NASA). The primary purpose of ACE is to determine and compare the isotopic and elemental composition of several distinct samples of matter, including the solar corona, the interplanetary medium, the local interstellar medium, and Galactic matter. The spacecraft is 1.6 meters across and 1 meter high, not including the four solar arrays and the magnetometer booms attached to two of the solar panels. It will weigh 785 kg, which includes 189 kg of hydrazine fuel for orbit insertion and maintenance. The solar arrays will generate about 500 watts of power at the beginning of life. The spacecraft will spin at 5 rpm, with the spin axis generally pointed along the Earth-sun line and most of the scientific instruments on the top (sunward) deck. The instruments that are carried on ACE are as follows: Cosmic Ray Isotope Spectrometer (CRIS), Electon,Proton,and Alpha Monitor (EPAM), Magnetometer (MAG), Solar Energetic Particle Ionic Charge Analyzer (SEPICA), Solar Isotope Spectrometer (SIS), Solar Wind Electon, Proton, and Alpha Monitor (SWEPAM), Solar Wind Ionic Charge Spectrometer (SWICS), Solar Wind Ion Mass Spectrometer (SWIMS), and Ultra Low Energy Isotope Spectrometer (ULEIS). ACE launched on a McDonnell-Douglas Delta II 7920 launch vehicle on August 25, 1997 from the Kennedy Space Center in Florida. In order to get away from the effects of the Earth's magnetic field, the ACE spacecraft has travelled almost a million miles (1.5 million km) from the Earth to the Earth-sun libration point (L1). By orbiting the L1 point, ACE will stay in a relatively constant position with respect to the Earth as the Earth revolves around the sun. Group: Platform_Details Entry_ID: ACE Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Short_Name: ACE Long_Name: Advanced Composition Explorer (ACE) End_Group Group: Synonymous_Platform_Names Short_Name: Explorer 71 Short_Name: 1997-045A Short_Name: 24912 End_Group Group: Platform_Associated_Instruments Short_Name: MAG Short_Name: SWICS Short_Name: SEPICA Short_Name: SIS Short_Name: SWEPAM Short_Name: EPAM Short_Name: SWIMS Short_Name: ULEIS Short_Name: CRIS End_Group Group: Orbit Orbit_Altitude: 1.5 million km Orbit_Inclination: 28.7 degrees Perigee: 179 km Apogee: 1256768 km Orbit_Type: LPO > L1 > Lissajous Orbit > Halo Orbit End_Group Creation_Date: 2008-01-14 Online_Resource: http://www.srl.caltech.edu/ACE/ Online_Resource: http://sd-www.jhuapl.edu/ACE/ACE_FactSheet.html Sample_Image: http://nssdc.gsfc.nasa.gov/image/spacecraft/ace1.jpg Group: Platform_Logistics Launch_Date: 1997-08-25 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: NASA Primary_Sponsor: California Institute of Technology End_Group End_Group SMOS [Source: ESA, http://www.esa.int/esaLP/ESAMBA2VMOC_LPsmos_0.html ] ESA's Soil Moisture and Ocean Salinity (SMOS) mission has been designed to observe soil moisture over the Earth's landmasses and salinity over the oceans. Soil moisture data are urgently required for hydrological studies and data on ocean salinity are vital for improving our understanding of ocean circulation patterns. Launched on 2 November 2009, SMOS is the second Earth Explorer Opportunity mission to be developed as part of ESA's Living Planet Programme. As well as demonstrating the use of the new radiometer, the data acquired from this mission will contribute to furthering our knowledge of the Earth's water cycle. The data acquired from the SMOS mission will lead to better weather and extreme-event forecasting, and contribute to seasonal-climate forecasting. As a secondary objective, SMOS will also provide observations over regions of snow and ice, contributing to studies of the cryosphere. Facts and figures • Launch: 2 November 2009 • Orbit: Mean altitude of 758 km and inclination of 98.44°; low-Earth, polar, Sun-synchronous, quasi-circular, dusk-dawn, 23-day repeat cycle, 3-day sub-cycle • Lifetime: Three years (including a six-month commissioning phase) with a possible two-year extension • Instrument: Microwave Imaging Radiometer using Aperture Synthesis – MIRAS, 2D interferometric L-band radiometer operating at 1.4 GHz (21 cm wavelength), with 69 antenna receivers distributed on a Y-shaped deployable antenna array and central hub. H and V polarisations measured sequentially • Satellite: Proteus platform adapted to the needs of the SMOS mission • Satellite mass: 658 kg (platform: 275 kg, payload: 355 kg, fuel: 28 kg) • Dimensions at launch: Cylinder 2.4 m high and 2.3 m in diameter • Power: Deployable solar panels with Si-cells, Li-Ion battery. Maximum power available for satellite: 1065 W, maximum consumption for MIRAS payload: 511 W • Communication links: X-band downlink for science data to ESA’s European Space Astronomy Centre (ESAC) in Villafranca, Spain, complemented by an X-band station in Svalbard, Norway, for acquisition of near-realtime data products; S-band uplink (4 kbps) and downlink (722 kbps) to Kiruna, Sweden, for satellite telemetry and telecommand (generic Proteus ground station) • Launcher: Rockot (with Breeze-KM upper stage) by Eurockot Launch Services GmbH • Launch site: Plesetsk Cosmodrome, Russia • Mission control: CNES Proteus Control and Command Centre in Toulouse, France, via CNES S-band ground station network – Kiruna in Sweden, Aussaguel in France and Kourou in French Guiana • Data processing: Data Processing Centre at ESAC, long-term archive at Kiruna, and User Services via ESA’s Centre for Earth Observation ESRIN in Frascati, Italy Group: Platform_Details Entry_ID: SMOS Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: Earth Explorers Short_Name: SMOS Long_Name: Soil Moisture and Ocean Salinity (Earth Explorer Opportunity Mission) End_Group Group: Platform_Associated_Instruments Short_Name: MIRAS End_Group Group: Orbit Orbit_Altitude: 758 km Orbit_Inclination: 98.44 deg Repeat_Cycle: 23 days Orbit_Type: LEO > LOW EARTH ORBIT > POLAR SUN-SYNCHRONOUS End_Group Creation_Date: 2007-09-12 Online_Resource: http://earth.esa.int/SMOS/ Online_Resource: http://www.cnes.fr/web/CNES-en/8042-gp-smos-to-provide-a-unique-map.php Online_Resource: http://esamultimedia.esa.int/docs/SMOS/SMOS_factsheet_22Jun09.pdf Online_Resource: http://www.esa.int/esaLP/ESAMBA2VMOC_LPsmos_0.html Sample_Image: http://www.esa.int/images/smos_key-visual_FINAL_H.jpg Group: Platform_Logistics Launch_Date: 2009-11-02 Launch_Site: PLESETSK COSMODROME, RUSSIA Design_Life: 3 Years Primary_Sponsor: ESA Primary_Sponsor: France/CNES End_Group End_Group 2019-02-22 21:23:55.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: 8df8e3d1-6e77-4146-bd7e-59d64564595b relationship type: null relationship value: null generated by: null); 2019-02-22 21:23:19.0 [mmorahan] update Resource (image); NOAA-8 NOAA-8 was launched in March 1983 and was a third-generation operational meteorological satellite for use in the National Environmental Satellite Data and Information Service (NESDIS) of NOAA. NOAA-8 was the first spacecraft of the advanced TIROS-N (ATN) series. The satellite design provided an economical and stable sun-synchronous platform for advanced operational instruments to measure the earth's atmosphere, its surface and cloud cover, and the near-space environment. The satellite was based upon the Block 5D spacecraft bus developed for the U.S. Air Force, and it was capable of maintaining an earth-pointing accuracy of better than plus or minus 0.1 degree with a motion rate of less than 0.035 degree/second. Primary sensors included an Advanced Very High Resolution Radiometer (AVHRR) and a TIROS Operational Vertical Sounder (TOVS). Secondary experiments consisted of a Space Environment Monitor (SEM) and a Data Collection and Platform Location System (DCPLS). A Search and Rescue Satellite Aided Tracking (SARSAT) system was also included on NOAA-8. Although designed for a 2-year life span, NOAA-8 experienced a premature failure in June 1984. __________ Taken from the NSSDC System for Information Retrieval and Storage (SIRS). For more information contact the NSSDC Coordinated Request and User Support Office, 301-286-6695 (NASA Goddard Space Flight Center, Code 933.4, Greenbelt, Maryland 20771, USA,"http://nssdc.gsfc.nasa.gov/"). Group: Platform_Details Entry_ID: NOAA-8 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NOAA POES (Polar Orbiting Environmental Satellites) Short_Name: NOAA-8 Long_Name: National Oceanic & Atmospheric Administration-8 End_Group Group: Synonymous_Platform_Names Short_Name: NOAA-E End_Group Group: Platform_Associated_Instruments Short_Name: AVHRR Short_Name: TOVS End_Group Creation_Date: 2007-11-09 Online_Resource: http://nssdc.gsfc.nasa.gov/ Sample_Image: http://www.dk3wn.info/images/noaa.gif Group: Platform_Logistics Launch_Date: 1983-06-20 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: NASA End_Group End_Group NISAR The NASA-ISRO Synthetic Aperture Radar (SAR), or NISAR, Mission will make global integrated measurements of the causes and consequences of land surface changes. NISAR will provide a means of resolving highly spatial and temporally complex processes ranging from ecosystem disturbances, to ice sheet collapse and natural hazards including earthquakes, tsunamis, volcanoes, and landslides. 2020-21 (planned) More information: https://nisar.jpl.nasa.gov/ 2018-03-12 16:32:45.0 [sritz] update Definition (The NASA-ISRO Synthetic Aperture Radar (SAR), or NISAR, Mission will make global integrated measurements of the causes and consequences of land surface changes. NISAR will provide a means of resolving highly spatial and temporally complex processes ranging from ecosystem disturbances, to ice sheet collapse and natural hazards including earthquakes, tsunamis, volcanoes, and landslides. 2020-21 (planned) More information: https://nisar.jpl.nasa.gov/); 2017-09-14 18:48:26.0 [sritz] update Definition (The NASA-ISRO Synthetic Aperture Radar (SAR), or NISAR, Mission will make global integrated measurements of the causes and consequences of land surface changes. NISAR will provide a means of resolving highly spatial and temporally complex processes ranging from ecosystem disturbances, to ice sheet collapse and natural hazards including earthquakes, tsunamis, volcanoes, and landslides. 2020-21 (planned)); 2017-09-14 18:34:34.0 [sritz] insert AltLabel (id: null category: primary text: NASA-ISRO Synthetic Aperture Radar language code: en); insert Definition (id: null text: The NASA-ISRO Synthetic Aperture Radar (SAR), or NISAR, Mission will make global integrated measurements of the causes and consequences of land surface changes. NISAR will provide a means of resolving highly spatial and temporally complex processes ranging from ecosystem disturbances, to ice sheet collapse and natural hazards including earthquakes, tsunamis, volcanoes, and landslides. language code: en); 2017-09-14 18:32:28.0 [sritz] Insert Concept add broader relation (NISAR [a6fddcb3-881b-484a-bbc9-39591b6359ab,310183] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,287601]); STS-11 First untethered space walks by McCandless and Stewart, using manned maneuvering unit. WESTAR-VI and PALAPA-B2 satellites deployed, but failure of Payload Assist Module-D (PAM-D) rocket motors left them in radical low-Earth orbits. German-built Shuttle Pallet Satellite (SPAS), first flown on STS-7, became first satellite refurbished and flown again. SPAS remained in payload bay due to electrical problem with Remote Manipulator System (RMS). RMS manipulator foot restraint first used, practice procedures performed for Solar Maximum satellite retrieval and repair planned for next mission. Integrated Rendezvous Target (IRT) failed due to internal failure. Five Get Away Special canisters flown in cargo bay and Cinema-360 camera used by crew. Other payloads: Acoustic Containerless Experiment System (ACES); Monodisperse Latex Reactor (MLR); and Radiation Monitoring Equipment (RME), and Isoelectric Focusing (IEF) payload. [Summary provided by NASA] Group: Platform_Details Entry_ID: STS-11 Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Platform_Series_or_Entity: SPACE SHUTTLE Short_Name: STS-11 Long_Name: Space Transport System STS-11 End_Group Group: Synonymous_Platform_Names Short_Name: Challenger End_Group Group: Platform_Associated_Instruments Short_Name: MOMS-01 End_Group Creation_Date: 2008-01-28 Online_Resource: http://science.ksc.nasa.gov/shuttle/missions/41-b/mission-41-b.html Sample_Image: http://science.ksc.nasa.gov/mirrors/images/images/pao/STS41B/10061751.jpg Group: Platform_Logistics Launch_Date: 1984-02-03 Primary_Sponsor: USA/NASA End_Group End_Group Resurs-P N1 Environmental Satellite Resurs-P N1 Group: Platform_Details Entry_ID: Resurs-P N1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: Resurs-P N1 Long_Name: Environmental Satellite Resurs-P N1 End_Group Group: Platform_Associated_Instruments Short_Name: GSA Short_Name: SHMSA-VR Short_Name: SHMSA-SR Short_Name: Geoton-L1 (2) End_Group Group: Orbit Orbit_Altitude: 475 km Orbit_Inclination: 97 degrees Repeat_Cycle: 3 days Orbit_Type: LEO > LOW EARTH ORBIT > POLAR SUN-SYNCHRONOUS End_Group Creation_Date: 2015-01-26 Online_Resource: http://samspace.ru/products/earth_remote_sensing_satellites/ka_resurs_p/ Online_Resource: http://en.samspace.ru/products/earth_remote_sensing_satellites/ka_resurs_p/ Sample_Image: http://www.ntsomz.ru/img/resurs-p_scheme.jpg Group: Platform_Logistics Launch_Date: 2013-06-25 Design_Life: 5 years End_Group End_Group 2015-08-03 12:45:44.0 [mpmorahan] insert AltLabel (id: null text: Environmental Satellite Resurs-P N1 language code: en); 2015-08-03 12:41:31.0 [mpmorahan] Insert Concept add broader relation (Resurs-P N1 [a7560954-fe13-4e8a-bb12-1289154a3a24,158123] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,143415]); SPACE SHUTTLES A Space Shuttle is a reusable spacecraft with wings for controlled descent in the atmosphere, designed to transport astronauts between Earth and an orbiting space station and also used to deploy and retrieve satellites. [Source: The American Heritage] Group: Platform_Details Entry_ID: SPACE SHUTTLES Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Platform_Series_or_Entity: SPACE SHUTTLE Short_Name: SPACE SHUTTLES End_Group Creation_Date: 2008-01-25 Online_Resource: http://en.wikipedia.org/wiki/Space_Shuttle Sample_Image: http://www.aerospaceguide.net/spacepictures/shuttle_endeavour.jpg End_Group METEOSAT-1 Meteosat-1 was launched in November 1977 and was a geostationary spacecraft that served as part of European Space Agency's (ESA) contribution to the Global Atmospheric Research Program (GARP). As part of GARP, the satellite helped to supply data required for global data sets used in improvement of machine weather forecasts. In general, the spacecraft design, instrumentation, and operation were similar to SMS/GOES. The cylindrically shaped spacecraft measured 210 cm in diameter and 430 cm in length, including the apogee boost motor. The primary structural members were an equipment platform and a central tube. The radiometer telescope was mounted on the equipment platform and viewed the earth through a special aperture in the side of the spacecraft. A support structure extended radially out from the central tube and was affixed to the solar panels, which formed the outer walls of the spacecraft and provided the primary source of electrical power. Located in the annulus-shaped space between the central tube and the solar panels were station-keeping and dynamics control equipment and batteries. Proper spacecraftattitude and spin rate (approximately 100 rpm) were maintained by jet thrusters mounted on the spacecraft and activated by ground command. The spacecraft used both UHF-band and S-band frequencies in its telemetry and command subsystems. A low-power VHF transponder provided telemetry and command during launch and then served as a backup for the primary subsystem once the spacecraft attained synchronous orbit. The spin-stabilized spacecraft carried (1) a visible-IR radiometer to provide high-quality day/night cloudcover data and to take radiance temperatures of the earth/atmosphere system, and (2) a meteorological data collection system to disseminate image data to user stations, to collect data from various earth-based platforms, and to relay data from polar-orbiting satellites. Meteosat-1 was originally placed in a geosynchronous orbit near the prime meridian and was positioned later between 9 and 11 degrees East. For information on the European Space Agency (ESA) and the Meteosat Program, see the URL: "http://www.esrin.esa.it" ---------------- Entry taken from: Taken from the NSSDC System for Information Retrieval and Storage (SIRS). For more information contact the NSSDC Coordinated Request and User Support Office, 301-286-6695 (NASA Goddard Space Flight Center, Code 933.4, Greenbelt, Maryland 20771, USA, http://nssdc.gsfc.nasa.gov/). Group: Platform_Details Entry_ID: METEOSAT-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: METEOSAT Short_Name: METEOSAT-1 End_Group End_Group C-130 The C-130 Hercules primarily performs the intratheater portion of the airlift mission. The aircraft is capable of operating from rough, dirt strips and is the prime transport for paradropping troops and equipment into hostile areas. Basic and specialized versions perform a diversity of roles, including airlift support, DEW Line and Arctic ice resupply, aeromedical missions, aerial spray missions, fire-fighting duties for the US Forest Service, and natural disaster relief missions. In recent years, they have been used to bring humanitarian relief to many countries, including Haiti, Bosnia, Somalia, and Rwanda. Four decades have elapsed since the Air Force issued its original design specification, yet the remarkable C-130 remains in production. The turbo-prop, high-wing, versatile "Herc" has accumulated over 20 million flight hours. It is the preferred transport aircraft for many US Government services and over 60 foreign countries. The basic airframe has been modified to hundreds of different configurations to meet an ever-changing environment and mission requirement. The C-130 Hercules has unsurpassed versatility, performance, and mission effectiveness. Early C-130A, B, and D versions are now retired. [Text provided by: http://www.fas.org/man/dod-101/sys/ac/c-130.htm ] [Photo provided by: http://www.globalaircraft.org/ ] Group: Platform_Details Entry_ID: C-130 Group: Platform_Identification Platform_Category: Aircraft Short_Name: C-130 Long_Name: Lockheed C-130 Hercules End_Group Creation_Date: 2008-07-14 Online_Resource: http://en.wikipedia.org/wiki/C-130_Hercules Online_Resource: http://www.af.mil/factsheets/factsheet.asp?fsID=92 Sample_Image: http://www.globalaircraft.org/photos/planephotos/c-130_1.jpg End_Group AEM-2 The Stratospheric Aerosol and Gas Experiment (SAGE) spacecraft was the second of the Applications Explorer Missions (AEM). This small, versatile, and relatively low-cost spacecraft was made of two distinct parts: (1) The SAGE instrument module containing the detectors and the associated hardware, and (2) The base module containing the necessary data handling, power, communications, command, and the attitude control subsystem to support the instruments. The objective of the SAGE mission was to obtain stratospheric aerosol and ozone data on a global scale for a better understanding of the earth&#039;s environmental quality and the radiation budget. The SAGE spacecraft was designed for a 1-year life in orbit. Unfortunately, SAGE experienced power problems after May 15, 1979. Nevertheless, spacecraft operations continued until November 19, 1981. The signal from the spacecraft was last received on January 7, 1982 when the battery failed. [Source: NASA NSSDC] Group: Platform_Details Entry_ID: AEM-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: AEM (Applications Explorer Mission) Short_Name: AEM-2 Long_Name: Applications Explorer Mission-2 End_Group Group: Synonymous_Platform_Names Short_Name: SAGE Short_Name: AEM-B Short_Name: Explorer 60 Short_Name: Strat Aero and Gas Exp Short_Name: 11270 End_Group Group: Platform_Associated_Instruments Short_Name: AEROSOL/CLOUD PARTICLE SIZER Short_Name: AEROSOL MONITOR Short_Name: SAGE I End_Group Group: Orbit Orbit_Inclination: 54.9 degrees Period: 96.8 minutes Perigee: 547.5 km Apogee: 660.2 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-08-22 Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/masterCatalog.do?sc=1979-013A Sample_Image: http://space.skyrocket.de/img_sat/sage__1.jpg Group: Platform_Logistics Launch_Date: 1979-02-18 Launch_Site: Wallops Flight Facility, Wallops Island, USA Design_Life: 1 year Primary_Sponsor: NASA End_Group End_Group G-III A Grumman Gulfstream III (G-III) business jet has been modified and instrumented by NASA's Dryden Flight Research Center to serve as a multi-role cooperative research platform testbed for a variety of flight research experiments. The twin-turbofan aircraft provides long-term capability for efficient testing of subsonic flight experiments for NASA, the U.S. Air Force, other government agencies, academia, and private industry. The aircraft, which carried the military designation of C-20A, was obtained from the U.S. Air Force in 2003. NASA Dryden's G-III is equipped with a self-contained on-board Data Collection and Processing System (DCAPS). This embedded instrumentation system allows for automated configuration setups to reduce required engineering support for each mission. It includes primary and backup systems to assure mission reliability, with the backup system available for use concurrently as a slave system when needed. DCAPS is designed to allow easy upgrades, addition of add-on systems for expansion, and to operate in both autonomous and manual modes. [Text and Photo from the NASA Dryden Research Center home page, http://www.nasa.gov/centers/dryden/research/G-III/ ] Group: Platform_Details Entry_ID: GULFSTREAM III Group: Platform_Identification Platform_Category: Aircraft Short_Name: GULFSTREAM III End_Group Creation_Date: 2008-07-15 Online_Resource: http://www.nasa.gov/centers/dryden/research/G-III/index.html Online_Resource: http://www.gulfstream.com/ Sample_Image: http://www.nasa.gov/centers/dryden/images/content/140766main_G-III-1.jpg End_Group 2015-05-08 18:26:04.0 [saritz] update AltLabel (Gulfstream III); 2014-07-02 15:09:40.0 [aaleman] edited keyword at NSIDC request insert AltLabel (id: null text: GULFSTREAM III language code: en); update PrefLabel (G-III); ANTHMS KINGAIR GMS-3 The Geostationary Meteorological Satellites (GMS) were Japan&#039;s contribution to the international Global Atmospheric Research Program (GARP). The GMS series carried the Visible and Spin Scan Radiometer (VISSR). The satellite was spin-stabilized with a despun earth-pointing antenna. The satellite was positioned near 140 deg E and was designed to operate for 5 years. This was a follow-on GMS type spacecraft launched and controlled by NASDA of Japan. The spacecraft was launched in August 1984, and turned off in December 1989. __________ Taken from the NSSDC System for Information Retrieval and Storage (SIRS). For more information contact the NSSDC Coordinated Request and User Support Office, 301-286-6695 (NASA Goddard Space Flight Center, Greenbelt, Maryland 20771, USA). WWW: http://nssdc.gsfc.nasa.gov/ Technical contact: Yukio Haruyama, Earth Observation program office director, Program plannig and management department, National space development agency of Japan Head office Hamamatsu-cho, Minato-ku, Tokyo, Japan Phone: 81-3-5470-4252 Group: Platform_Details Entry_ID: GMS-3 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: GMS (Japan Geostationary Meteorological Satellite) Short_Name: GMS-3 Long_Name: Geostationary Meteorological Satellite-3 End_Group Group: Synonymous_Platform_Names Short_Name: GMS-3 End_Group Group: Platform_Associated_Instruments Short_Name: VISSR-GMS End_Group Group: Orbit Orbit_Altitude: 36,000 km Orbit_Type: GEO > Geosynchronous > Geostationary End_Group Creation_Date: 2007-10-01 Online_Resource: http://www.jaxa.jp/projects/sat/gms/index_e.html Online_Resource: http://space.skyrocket.de/doc_sdat/gms-2.htm Group: Platform_Logistics Launch_Date: 1984-08-03 Launch_Site: Tanegashima Island, Japan Primary_Sponsor: Japan/JAXA End_Group End_Group MIO The Mobile Ionospheric Observatory was developed to learn more about the vagaries of the ionosphere. It would become the first major project undertaken by the newly established Radio Propagation Laboratory. Group: Platform_Details Entry_ID: MIO Group: Platform_Identification Platform_Category: In Situ Land-based Platforms Platform_Series_or_Entity: SOLAR/SPACE MONITORING STATIONS Short_Name: MIO Long_Name: Mobile Ionospheric Observatory End_Group Group: Synonymous_Platform_Names Short_Name: MIO End_Group Creation_Date: 2007-12-10 Online_Resource: http://www.friendsofcrc.ca/Articles/Hansen-MobileObs/RPLMobileObservatory.html Sample_Image: http://www.friendsofcrc.ca/Articles/Hansen-MobileObs/RPL-Mobile-48-49-s.jpg End_Group CRYOSAT-2 Europe's first ice mission is an advanced radar altimeter specifically designed to monitor the most dynamic sections of Earth's cryosphere. It borrows synthetic aperture radar and interferometry techniques from standard imaging radar missions to sharpen its accuracy over rugged ice sheet margins and sea ice in polar waters. CryoSat-2 measures 'freeboard' - the difference in height between sea ice and adjacent water - as well as ice sheet altitude, tracking changes in ice thickness. Group: Platform_Details Entry_ID: CRYOSAT-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: Earth Explorers Short_Name: CRYOSAT-2 End_Group Group: Platform_Associated_Instruments Short_Name: LRR Short_Name: DORIS End_Group Group: Orbit Orbit_Altitude: 717 km Orbit_Inclination: 92 deg Repeat_Cycle: 369 days with 30 day sub-cycle Orbit_Type: LEO > Low Earth Orbit > Polar Non-Sun-Synchronous End_Group Creation_Date: 2010-05-07 Online_Resource: http://www.esa.int/esaLP/LPcryosat.html Sample_Image: http://esamultimedia.esa.int/images/EarthObservation/cryosat/4_sar_hz31_H.jpg Group: Platform_Logistics Launch_Date: 2010-04-08 Launch_Site: Plesetsk Cosmodrome, Russia Design_Life: 3 Years Primary_Sponsor: ESA End_Group End_Group 2019-02-13 13:25:15.0 [mmorahan] update Definition (Europe's first ice mission is an advanced radar altimeter specifically designed to monitor the most dynamic sections of Earth's cryosphere. It borrows synthetic aperture radar and interferometry techniques from standard imaging radar missions to sharpen its accuracy over rugged ice sheet margins and sea ice in polar waters. CryoSat-2 measures 'freeboard' - the difference in height between sea ice and adjacent water - as well as ice sheet altitude, tracking changes in ice thickness. Group: Platform_Details Entry_ID: CRYOSAT-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: Earth Explorers Short_Name: CRYOSAT-2 End_Group Group: Platform_Associated_Instruments Short_Name: LRR Short_Name: DORIS End_Group Group: Orbit Orbit_Altitude: 717 km Orbit_Inclination: 92 deg Repeat_Cycle: 369 days with 30 day sub-cycle Orbit_Type: LEO > Low Earth Orbit > Polar Non-Sun-Synchronous End_Group Creation_Date: 2010-05-07 Online_Resource: http://www.esa.int/esaLP/LPcryosat.html Sample_Image: http://esamultimedia.esa.int/images/EarthObservation/cryosat/4_sar_hz31_H.jpg Group: Platform_Logistics Launch_Date: 2010-04-08 Launch_Site: Plesetsk Cosmodrome, Russia Design_Life: 3 Years Primary_Sponsor: ESA End_Group End_Group); update Resource (image); delete WeightedRelation (null); insert WeightedRelation (id: null related concept uuid: 30787b9f-a407-47a5-b69b-5b9e1d1b1144 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 2380ecc6-b5ae-4ad8-a56a-9740166465aa relationship type: null relationship value: null generated by: null); NASA DC-8 [Source: https://www.nasa.gov/centers/armstrong/news/FactSheets/FS-050-DFRC.html ] NASA operates a highly modified Douglas DC-8 jetliner as a flying science laboratory. The aircraft, based at NASA's Dryden Aircraft Operations Facility in Palmdale, Calif., is used to collect data for experiments in support of projects serving the world's scientific community. Federal, state, academic and foreign investigators are among those who use NASA’s DC-8. Data gathered with the aircraft at flight altitude and by remote sensing have been used for studies in archaeology, ecology, geography, hydrology, meteorology, oceanography, volcanology, atmospheric chemistry, cryospheric science, soil science and biology. Four types of missions are flown with the DC-8: sensor development, satellite sensor verification, space vehicle launch or re-entry telemetry data retrieval and optical tracking, and basic research studies of Earth's surface and atmosphere. More information: https://www.nasa.gov/centers/armstrong/news/FactSheets/FS-050-DFRC.html Group: Platform_Details Entry_ID: NASA DC-8 Group: Platform_Identification Platform_Category: Aircraft Short_Name: NASA DC-8 Long_Name: NASA Douglas DC-8 End_Group Group: Platform_Associated_Instruments Short_Name: DAWN End_Group Creation_Date: 2012-05-01 Online_Resource: https://www.nasa.gov/centers/armstrong/news/FactSheets/FS-050-DFRC.html Group: Platform_Logistics Primary_Sponsor: USA/NASA End_Group End_Group 2019-10-08 16:30:59.0 [sritz] update WeightedRelation (Platform-Instrument); update WeightedRelation (1.0); 2019-10-08 16:29:31.0 [sritz] insert WeightedRelation (id: null related concept uuid: b0f93e6a-c766-4957-8762-5c7709487459 relationship type: null relationship value: null generated by: null); 2019-06-26 20:19:00.0 [sritz] update Definition ([Source: https://www.nasa.gov/centers/armstrong/news/FactSheets/FS-050-DFRC.html ] NASA operates a highly modified Douglas DC-8 jetliner as a flying science laboratory. The aircraft, based at NASA's Dryden Aircraft Operations Facility in Palmdale, Calif., is used to collect data for experiments in support of projects serving the world's scientific community. Federal, state, academic and foreign investigators are among those who use NASA’s DC-8. Data gathered with the aircraft at flight altitude and by remote sensing have been used for studies in archaeology, ecology, geography, hydrology, meteorology, oceanography, volcanology, atmospheric chemistry, cryospheric science, soil science and biology. Four types of missions are flown with the DC-8: sensor development, satellite sensor verification, space vehicle launch or re-entry telemetry data retrieval and optical tracking, and basic research studies of Earth's surface and atmosphere. More information: https://www.nasa.gov/centers/armstrong/news/FactSheets/FS-050-DFRC.html Group: Platform_Details Entry_ID: NASA DC-8 Group: Platform_Identification Platform_Category: Aircraft Short_Name: NASA DC-8 Long_Name: NASA Douglas DC-8 End_Group Group: Platform_Associated_Instruments Short_Name: DAWN End_Group Creation_Date: 2012-05-01 Online_Resource: https://www.nasa.gov/centers/armstrong/news/FactSheets/FS-050-DFRC.html Group: Platform_Logistics Primary_Sponsor: USA/NASA End_Group End_Group); GOES-12 GOES-12 (GEOSTATIONARY OPERATIONAL ENVIRONMENTAL SATELLITE-12) GOES-12 (GOES-M) was launched July 23, 2001 from Cape Canaveral Air Station. On Tuesday April 1, 2003 at approximately 1815 UTC, GOES-12 replaced GOES-8 as the operational GOES East Satellite. The spacecraft will perform long term geostationary monitoring of U.S. weather. GOES 12's mission is the monitoring of hurricanes, severe thunderstorms, flash floods, and other severe weather as well as providing short-term weather forecasting or nowcasting. Combined with Doppler radar and automated surface weather stations, real-time GOES data greatly aids weather foecasters in providing better warnings of severe weather. NOAA's National Environmmental Satellite, Data, and Information Service will operate GOES. The instrument package includes a GOES I-M Imager and GOES I-M Sounder. For more information see http://www.oso.noaa.gov/goes/ Group: Platform_Details Entry_ID: GOES-12 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: GOES (Geostationary Operational Environmental Satellite) Short_Name: GOES-12 Long_Name: Geostationary Operational Environmental Satellite 12 End_Group Group: Synonymous_Platform_Names Short_Name: GOES-12 Short_Name: 26871 End_Group Group: Platform_Associated_Instruments Short_Name: SXI Short_Name: GOES I-M SOUNDER Short_Name: GOES I-M IMAGER End_Group Group: Orbit Orbit_Type: GEO > GEOSYNCHRONOUS > GEOSTATIONARY End_Group Creation_Date: 2007-10-04 Online_Resource: http://www.oso.noaa.gov/goes/ Online_Resource: http://goes.gsfc.nasa.gov/ Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=2001-031A Group: Platform_Logistics Launch_Date: 2001-07-23 Launch_Site: CAPE CANAVERAL/KENNEDY SPACE CENTER, USA Primary_Sponsor: USA/NASA Primary_Sponsor: USA/NOAA End_Group End_Group 2016-06-09 14:44:50.0 [epneff] added altLabel insert AltLabel (id: null text: GOES-12 (GEOSTATIONARY OPERATIONAL ENVIRONMENTAL SATELLITE-12) language code: en); Kanopus-V Environmental Satellite Kanopus-V Group: Platform_Details Entry_ID: Kanopus-V Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: Kanopus-V Long_Name: Environmental Satellite Kanopus-V End_Group Group: Platform_Associated_Instruments Short_Name: PSS_RS Short_Name: MSS_RS End_Group Group: Orbit Orbit_Altitude: 510 km Orbit_Inclination: 97.4 degrees Period: 94.7 minutes Repeat_Cycle: 5 days Orbit_Type: LEO > LOW EARTH ORBIT > POLAR SUN-SYNCHRONOUS End_Group Creation_Date: 2015-08-19 Online_Resource: http://vniiem.ru/ru/index.php?option=com_content&view=article&id=622:-l-r-1-3-4-5-6&catid=85:--l-r&Itemid=62 Sample_Image: http://vniiem.ru/ru/uploads/images/kanopus_3b.jpg Group: Platform_Logistics Launch_Date: 2011-01-20 Design_Life: 10 years End_Group End_Group 2015-08-03 13:01:05.0 [mpmorahan] insert AltLabel (id: null text: Environmental Satellite Kanopus-V language code: en); 2015-08-03 12:57:15.0 [mpmorahan] Insert Concept add broader relation (Kanopus-V [a93bb213-7862-4aa5-a113-38669e557a76,158131] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,143415]); Meteor 2-21 [Source: NASA ILRS, http://ilrs.gsfc.nasa.gov/satellite_missions/list_of_satellites/fize_general.html ] Mission Objectives: Meteor 2-21 is the twenty-first and last in the Meteor-2 series of Russian meteorological satellites launched in 1993. The Meteor satellites were designed to monitor atmospheric and sea-surface temperatures, humidity, radiation, sea-ice conditions, snow-cover, and clouds. What makes Meteor 2-21 distinctive from the other meteorological satellites is its unique retroreflector array. Fizeau is named after a French physicist, Armand Fizeau, who in 1851 conducted an experiment which tested for the aether convection coefficient. SLR tracking of this satellite was used for precise orbit determination and the Experiment of Fizeau. The Fizeau Experiment tests the theory of special relativity-that distance events that are simultaneous for one observer will not be simultaneous for an observer in motion relative to the first. Mission Instrumentation: Meteor-2-21/Fizeau had the following instrumentation onboard: 1. Scanning telephotometer 2. Scanning infrared radiometers 3. Radiation measurement complex 4. Retroreflector array Additional information available at: http://ilrs.gsfc.nasa.gov/satellite_missions/list_of_satellites/fize_general.html Group: Platform_Details Entry_ID: METEOR 2-21 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: METEOR Short_Name: METEOR 2-21 End_Group Group: Synonymous_Platform_Names Short_Name: 22782 Short_Name: Meteor-2-21/FIZEAU End_Group Group: Platform_Associated_Instruments Short_Name: INFRARED RADIOMETERS End_Group Group: Orbit Orbit_Inclination: 82.5 degrees Period: 104.0 minutes Perigee: 945.0 km Apogee: 980.0 km End_Group Creation_Date: 2007-10-10 Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1993-055A Online_Resource: http://ilrs.gsfc.nasa.gov/satellite_missions/list_of_satellites/fize_general.html Sample_Image: http://ilrs.gsfc.nasa.gov/images/meteor2.gif Group: Platform_Logistics Launch_Date: 1993-05-31 Launch_Site: Plesetsk Cosmodrome, Russia Design_Life: 2 years Primary_Sponsor: Russia End_Group End_Group 2015-05-08 18:51:41.0 [saritz] update PrefLabel (Meteor 2-21); Biomass The Biomass mission will address a fundamental gap in our understanding of the land component of the Earth system, which is the status and the dynamics of Earth’s forests, as represented by the distribution of forest biomass and its changes. With accurate, frequent and global information on these forest properties at a spatial scale of 200 m, it will be possible to address a range of critical issues with far-reaching scientific and societal consequences. The Biomass mission will explore Earth’s surface for the first time at the P-band wavelength, making observations that could have a wide range of as yet unforeseen applications, such as for mapping subsurface geological features in deserts in support of palaeohydrological studies and in ice sheets, and the surface topography of areas covered by dense vegetation. 2019-04-25 10:43:12.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: 1715936c-434b-410c-aa94-c2f6b5c08c95 relationship type: null relationship value: null generated by: null); 2019-04-25 06:39:22.0 [mmorahan] insert AltLabel (id: null category: primary text: Biomass monitoring mission for Carbon Assessment language code: en); insert Definition (id: null text: The Biomass mission will address a fundamental gap in our understanding of the land component of the Earth system, which is the status and the dynamics of Earth’s forests, as represented by the distribution of forest biomass and its changes. With accurate, frequent and global information on these forest properties at a spatial scale of 200 m, it will be possible to address a range of critical issues with far-reaching scientific and societal consequences. The Biomass mission will explore Earth’s surface for the first time at the P-band wavelength, making observations that could have a wide range of as yet unforeseen applications, such as for mapping subsurface geological features in deserts in support of palaeohydrological studies and in ice sheets, and the surface topography of areas covered by dense vegetation. language code: en); 2019-04-25 06:26:18.0 [mmorahan] Insert Concept add broader relation (Biomass [a9b21edd-49b7-43be-8e35-8652bbc5559a,368657] - Earth Explorers [fe9b35e7-6243-44bb-ac42-ce8350e7a86f,346137]); R/V NBP [from NSF web page on R/V Nathaniel B. Palmer, "http://www.nsf.gov/od/opp/support/nathpalm.jsp"] In 1992, Edison Chouest Offshore Inc., Galliano, Louisiana, built and delivered a 94-meter research ship with icebreaking capability for use by the U.S. Antarctic Program for 10 years or more. The ship, Nathaniel B. Palmer, is a first-rate platform for global change studies, including biological, oceanographic, geological, and geophysical components. It can operate safely year-round in Antarctic waters that often are stormy or covered with sea ice. It accommodates 37 scientists, has a crew of 22, and is capable of 75-day missions. For ship deck layouts, lab photographs, schedules, equipment, ship user committee issues and a variety of other information regarding USAP research ships, go to the Raytheon Polar Services Company (RSPC) marine sciences web site. For specific information about cruises schedules, scientific equipment and other related science support information, see RSPC's the Nathaniel B. Palmer web page at "http://www.nsf.gov/od/opp/support/nathpalm.jspl". Group: Platform_Details Entry_ID: R/V NBP Group: Platform_Identification Platform_Category: In Situ Ocean-based Platforms Platform_Series_or_Entity: SHIPS Short_Name: R/V NBP Long_Name: R/V Nathaniel B. Palmer End_Group Creation_Date: 2007-08-31 Online_Resource: http://www.nsf.gov/od/opp/support/nathpalm.jsp Sample_Image: http://www.nsf.gov/od/opp/images/prss/nbpice.jpg End_Group IMS-2 IMS-2 Bus is evolved as a standard bus of 400 kg class which includes a payload capability of around 200kg. IMS-2 development is an important milestone as it is envisaged to be a work horse for different types of remote sensing applications. The first mission of IMS-2 is SARAL. SARAL is a co-operative mission between ISRO and CNES with payloads from CNES and spacecraft bus from ISRO. 2017-12-27 10:10:54.0 [mmorahan] insert AltLabel (id: null category: primary text: Indian Mini Satellite-2 language code: en); insert Definition (id: null text: IMS-2 Bus is evolved as a standard bus of 400 kg class which includes a payload capability of around 200kg. IMS-2 development is an important milestone as it is envisaged to be a work horse for different types of remote sensing applications. The first mission of IMS-2 is SARAL. SARAL is a co-operative mission between ISRO and CNES with payloads from CNES and spacecraft bus from ISRO. language code: en); 2017-12-27 10:08:51.0 [mmorahan] Insert Concept add broader relation (IMS-2 [aa137482-53a7-455d-b8d8-52d487380c2a,310491] - IMS [fecf6a37-ffa9-4e11-90cf-1abfeb95cb95,288895]); DMSP 5D-2/F10 DMSP-F10 [Source: National Space Science Data Center, http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1990-105A ] DMSP 5D-2/F10 is one of a series of meteorological satellites developed and operated by the Air Force under the Defense Meteorological Satellite Program (DMSP). This program, previously known as DAPP (Data Acquisition and Processing Program), was classified until March 1973. The objective of this program is to provide global visual and infrared cloudcover data and specialized environmental data to support Department of Defense operational weather analysis and forecasting requirements. Operationally, the program consists of two satellites in sun-synchronous polar orbits, with the ascending node of one satellite in early morning and the other at local noon. The 6.4-m-long spacecraft is separated into four sections: (1) a precision mounting platform for sensors and equipment requiring precise alignment; (2) an equipment support module containing the electronics, reaction wheels, and some meteorological sensors; (3) a reaction control equipment support structure containing the third-stage rocket motor and supporting the ascent phase reaction control equipment; and (4) a 9.29-sq-m solar cell panel. The spacecraft stabilization is controlled by a combination flywheel and magnetic control coil system so that sensors are maintained in the desired earth-looking mode. One feature is the precision-pointing accuracy of the primary imager to 0.01 deg provided by a star sensor and an updated ephemeris navigation system. This allows automatic geographical mapping of the digital imagery to the nearest picture element. The operational linescan system is the primary data acquisition system that provides real-time or stored, multi-orbit, day-and-night, visual and infrared imagery of clouds. A supplementary sensor package contains five special sensors: (1) a microwave temperature sounder, (2) an advanced X-ray detector, (3) an ionospheric/scintillation monitor, (4) a precipitating electron/ion spectrometer, and (5) a microwave imager. Either recorded or real-time data are transmitted to ground-receiving sites by two redundant S-band transmitters. Recorded data are read out to tracking sites located at Fairchild AFB, Washington, and at Loring AFB, Maine, and relayed by SATCOM to Air Force Global Weather Central, Offutt AFB, Nebraska. Real-time data are read out at mobile tactical sites located around the world. Additional information concerning this satellite can be found in the report by D. A. Nichols, "The Defense Meteorological Satellite Program," Optical Engineering, v. 14, n. 4, p. 273, July-August 1975. Group: Platform_Details Entry_ID: DMSP 5D-2/F10 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: DMSP (Defense Meteorological Satellite Program) Short_Name: DMSP 5D-2/F10 Long_Name: Defense Meteorological Satellite Program-F10 End_Group Group: Synonymous_Platform_Names Short_Name: DMSP-F10 Short_Name: USA 68 Short_Name: 20978 End_Group Group: Platform_Associated_Instruments Short_Name: SSB/X Short_Name: SSI/ES Short_Name: OLS Short_Name: SSM/T Short_Name: SSJ/4 Short_Name: SSM/I End_Group Group: Orbit Orbit_Inclination: 97.6° Period: 96.89 minutes Perigee: 564.0 km Apogee: 653.0 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1990-105A Online_Resource: http://ghrc.msfc.nasa.gov:5721/source_documents/dmsp_f10.html Online_Resource: http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/dmsp.html Online_Resource: http://www.ngdc.noaa.gov/dmsp/index.html Group: Platform_Logistics Launch_Date: 1990-12-01 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: Department of Defense-Department of the Air Force (United States) End_Group End_Group 2016-06-09 14:34:00.0 [epneff] added altLabel insert AltLabel (id: null text: DMSP-F10 language code: en); DC-8 When the world's first jet airliner, the De Havilland Comet, was introduced in 1949, Douglas held a commanding position in the aircraft market. Although Boeing had pointed the way to the modern all-metal airliner in 1933 with the 247, it was Douglas that, more than any other company, made the promise a reality. Douglas produced a succession of piston-engined commercial aircraft through the 1930s, 1940s and 1950s: 138 DC-2s, 10,928 DC-3s (mostly for military service in World War II), 1453 DC-4s, 537 DC-6s and 226 DC-7s. Given the success of their designs, Douglas took the view that there was no reason to rush into anything new, as did their rivals Lockheed and Convair. Most air transport manufacturers expected that there would be a gradual switch, from piston engines to turbines and that it would be to the more fuel-efficient turboprop engines rather than pure jets. In contrast, Boeing took the bold step of starting to plan a pure jet airliner as early as 1949. Boeing's military arm had gained extensive experience with large, long-range jets through the B-47 Stratojet (first flight 1947) and the B-52 Stratofortress (1952). With thousands of their big jet bombers on order or in service, Boeing had developed a close relationship with the U.S. Air Force Strategic Air Command (SAC), and could count on having preference when the time came to replace SAC's fleet of piston-engined KC-97 Stratotankers. For Boeing, this was an opportunity to build a jet aircraft for air-to-air refueling that could be turned into a commercial transport. [Text provided by: http://en.wikipedia.org/wiki/Douglas_DC-8 ] [Photo provided by: http://www.aerospaceweb.org/ ] Group: Platform_Details Entry_ID: DC-8 Group: Platform_Identification Platform_Category: Aircraft Short_Name: DC-8 Long_Name: Douglas DC-8 End_Group Group: Platform_Associated_Instruments Short_Name: CAPS Short_Name: PRESSURE TRANSDUCERS Short_Name: TEMPERATURE PROBES Short_Name: PITOT-STATIC SYSTEM Short_Name: INS Short_Name: ROSEMOUNT PROBES Short_Name: CDP Short_Name: PIP Short_Name: DC8 DROPSONDES Short_Name: DROPSONDES End_Group Creation_Date: 2008-07-14 Online_Resource: http://www1.nasa.gov/centers/dryden/news/FactSheets/FS-050-DFRC.html Sample_Image: http://www.aerospaceweb.org/aircraft/jetliner/dc8/dc8_06.jpg Group: Platform_Logistics Primary_Sponsor: NASA End_Group End_Group 2018-04-05 19:21:39.0 [sritz] update Resource (image); insert WeightedRelation (id: null related concept uuid: f59652c5-eaa8-49c0-b65f-a0166048b1dd relationship type: null relationship value: null generated by: null); G-IV The Gulfstream IV-SP (G-IV) is a high altitude, high speed, twin turbofan jet aircraft acquired by AOC in 1996. The G-IV is currently configured for operational support of the National Hurricane Center synoptic surveillance mission and is expected to provide support for NOAA programs for many years to come. This mission is designed to collect, process and transmit vertical atmospheric soundings in the environment of the hurricane. The principle tool used for this task is the GPS dropwindsonde. [Text and Photo provided by NOAA, http://www.aoc.noaa.gov/aircraft_g4.htm ] Group: Platform_Details Entry_ID: GULFSTREAM IV-SP Group: Platform_Identification Platform_Category: Aircraft Short_Name: GULFSTREAM IV-SP End_Group Creation_Date: 2008-07-14 Online_Resource: http://en.wikipedia.org/wiki/Gulfstream_IV Online_Resource: http://www.gulfstream.com/ Sample_Image: http://www.aoc.noaa.gov/images/g4-1.jpg End_Group 2014-07-02 15:11:27.0 [aaleman] edited keyword at NSIDC request insert AltLabel (id: null text: GULFSTREAM IV language code: en); update PrefLabel (G-IV); STS-41 Space Transport System STS-41 Mission Highlights: Three satellites deployed: Satellite Business System SBS-D, SYNCOM IV-2 (also known as LEASAT2) and TELSTAR. The 102- foot-tall, 13-loot-wide Office of Application and Space Technology (OAST-1) solar wing extended from payload bay. Wing carried different types of solar cells and extended to full height several times. It demonstrated large lightweight solar arrays for future in building large facilities in space such as Space Station. Other payloads: Continuous Flow Electrophoresis System (CFES) Ill; Radiation Monitoring Equipment (RME); Shuttle Student Involvement Program (SSIP) experiment; lMAX camera, being flown second time; and an Air Force experiment, Cloud Logic to Optimize Use of Defense Systems (CLOUDS). [Summary provided by NASA] Group: Platform_Details Entry_ID: STS-41 Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Platform_Series_or_Entity: SPACE SHUTTLE Short_Name: STS-41 Long_Name: Space Transport System STS-41 End_Group Group: Synonymous_Platform_Names Short_Name: discovery End_Group Group: Orbit Orbit_Inclination: 28.45 Repeat_Cycle: 4 End_Group Creation_Date: 2008-01-28 Online_Resource: http://science.ksc.nasa.gov/shuttle/missions/ Sample_Image: http://science.ksc.nasa.gov/shuttle/missions/sts-41/sts-41-patch-small.gif Group: Platform_Logistics Launch_Date: 1984-08-30 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: NASA End_Group End_Group Swarm-B Primary objectives: * studies of core dynamics, geodynamo processes and core-mantle interaction * mapping of the lithospheric magnetisation and its geological interpretation * determination of the 3D electrical conductivity of the mantle * investigation of electric currents flowing in the magnetosphere and ionosphere * identifying the ocean circulation by its magnetic signature * quantifying the magnetic forcing of the upper atmosphere 2019-02-22 21:49:27.0 [mmorahan] insert Definition (id: null text: Primary objectives: * studies of core dynamics, geodynamo processes and core-mantle interaction * mapping of the lithospheric magnetisation and its geological interpretation * determination of the 3D electrical conductivity of the mantle * investigation of electric currents flowing in the magnetosphere and ionosphere * identifying the ocean circulation by its magnetic signature * quantifying the magnetic forcing of the upper atmosphere language code: en); 2019-02-22 21:42:36.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: b7bc737c-15de-4b67-9bc3-5fa7c2b651d5 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 5e95a04f-e746-4b55-b0f0-76631bb197fe relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: e5fde4c4-15cd-4278-b922-005488df096f relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 2380ecc6-b5ae-4ad8-a56a-9740166465aa relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 03d748ff-7398-4ea8-87e7-38d0ef3e6167 relationship type: null relationship value: null generated by: null); 2018-06-13 12:06:37.0 [mmorahan] Insert Concept add broader relation (Swarm-B [ab7f9a64-ca5d-4795-94ff-fd5367d39f9f,367703] - Swarm [1d6d5f82-acd5-4bd2-9324-12884718b353,367695]); GSN The IRIS Global Seismographic Network (GSN) is one of the four major components of the IRIS Consortium. The goal of the GSN is to deploy 128 permanent seismic recording stations uniformly over the earth's surface. As of 2001 the GSN was made up of over 120 stations with affiliations to IRIS USGS, IRIS IDA, GEOFON, Pacific21, NCDSN, MedNet, BGR, BFO, USNSN, BDSN and several other national and international networks. Thirteen new stations are planned for completion in 2001/2002. The IRIS GSN stations continuously record seismic data from very broad band seismometers at 20 samples per second. It is also the goal of the GSN to record data with a dynamic range of 140 db (24 bit digitizers). Nearly all of the IRIS GSN stations meet this goal. More info at "http://www.iris.washington.edu/GSN/" [Source: The IRIS Consortium] C-23 Sherpa The NASA Goddard Space Flight Center’s (GSFC) Wallops Flight Facility (WFF) Aircraft Office operates the NASA C-23 Sherpa research aircraft available to support airborne science research. The C-23 is used to perform scientific research, provide logistics support on an as-needed basis to other airborne science missions, and can be used as a technology test bed for new airborne and satellite instrumentation. This aircraft is also available to support range surveillance and recovery operations as needed. The C-23 is a self-sufficient aircraft that can operate from short field civilian and military airports to remote areas of the world in support of scientific studies and other operations. The C-23 is a two-engine turboprop aircraft designed to operate efficiently, under the most arduous conditions, in a wide range of mission configurations. The large square-section cargo hold, with excellent access at both ends (4 side fuselage doors and aft cargo ramp), and a 7000 pound payload, offers ready flexibility to perform a variety of missions. The aircraft also has 22 cabin windows as well as a nose cargo area available for installations. An internal auxillary fuel tank is also available which is capable of extending the aircraft range to 1,000nm and 7 hours endurance. Group: Platform_Details Entry_ID: C-23 Sherpa Group: Platform_Identification Platform_Category: Aircraft Short_Name: C-23 Sherpa Long_Name: Short Brothers C-23 Sherpa End_Group Creation_Date: 2016-08-05 Online_Resource: https://airbornescience.nasa.gov/aircraft/C-23_Sherpa End_Group 2016-08-05 18:32:47.0 [gee-cee] insert Definition (id: null text: The NASA Goddard Space Flight Center’s (GSFC) Wallops Flight Facility (WFF) Aircraft Office operates the NASA C-23 Sherpa research aircraft available to support airborne science research. The C-23 is used to perform scientific research, provide logistics support on an as-needed basis to other airborne science missions, and can be used as a technology test bed for new airborne and satellite instrumentation. This aircraft is also available to support range surveillance and recovery operations as needed. The C-23 is a self-sufficient aircraft that can operate from short field civilian and military airports to remote areas of the world in support of scientific studies and other operations. The C-23 is a two-engine turboprop aircraft designed to operate efficiently, under the most arduous conditions, in a wide range of mission configurations. The large square-section cargo hold, with excellent access at both ends (4 side fuselage doors and aft cargo ramp), and a 7000 pound payload, offers ready flexibility to perform a variety of missions. The aircraft also has 22 cabin windows as well as a nose cargo area available for installations. An internal auxillary fuel tank is also available which is capable of extending the aircraft range to 1,000nm and 7 hours endurance. language code: en); 2016-08-05 18:18:22.0 [gee-cee] insert AltLabel (id: null text: Short Brothers C-23 Sherpa language code: en); 2016-08-05 18:17:55.0 [gee-cee] Insert Concept add broader relation (C-23 Sherpa [abe97ffb-af51-43b2-a1d4-a922ddf9bc6e,277807] - Aircraft [227d9c3d-f631-402d-84ed-b8c5a562fc27,256457]); EXPLORER-35 AIMP-2 (AIMP-E or IMP-E or Explorer 35, NSSDC ID: 76-070A) was a spin- stabilized 230 kg spacecraft instrumented for interplanetary studies at lunar distances. It was successfully 'anchored' to the earth's moon, and stayed that way during its operational life. The AIMP-2 sensors were designed to study the interplanetary plasmas, the magnetic fields, fluxes of energetic particles, and solar X-rays. The spacecraft was launched into an elliptical lunar orbit. The spin axis direction was nearly perpendicular to the ecliptic plane, and the AIMP-2 spin rate was 25.6 rpm, giving a spin period of 2.34 sec. The overall AIMP-2 mission objectives were achieved. After successful operation and data gathering for 6 years, the spacecraft was turned off on June 24, 1973. Group: Platform_Details Entry_ID: EXPLORER-35 Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Platform_Series_or_Entity: EXPLORER Short_Name: EXPLORER-35 Long_Name: Interplanetary Monitoring Platform D (IMP-E) End_Group Group: Synonymous_Platform_Names Short_Name: AIMP 2 Short_Name: AIMP-E Short_Name: IMP-E End_Group Creation_Date: 2007-12-14 Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/masterCatalog.do?sc=1967-070A Sample_Image: http://nssdc.gsfc.nasa.gov/image/spacecraft/explorer_35.jpg Group: Platform_Logistics Launch_Date: 1967-07-19 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: NASA End_Group End_Group Analytical Lab Analytical Geochemistry Laboratory 2019-03-01 20:40:59.0 [sritz] update AltLabel (Analytical Geochemistry Laboratory); 2019-03-01 20:40:16.0 [sritz] insert AltLabel (id: null category: null text: Analytical geochemistry laboratory language code: en); 2019-03-01 20:39:47.0 [sritz] Insert Concept add broader relation (Analytical Lab [ac63eed1-779d-4085-92f8-5743ec64a942,368521] - GEOPHYSICAL STATIONS/NETWORKS [4ce2e520-9a55-44fe-8f2c-93d64f4eef63,344937]); RHESSI The High Energy Solar Spectroscopic Imager (HESSI) mission consists of a single spin-stabilized spacecraft in a low-altitude orbit inclined 38 degrees to the Earth's equator. The only instrument on board is an imaging spectrometer with the ability to obtain high fidelity color movies of solar flares in X rays and gamma rays. It uses two new complementary technologies: fine grids to modulate the solar radiation, and germanium detectors to measure the energy of each photon very precisely. The HESSI was renamed the Reuven Ramaty High Energy Solar Spectroscopic Imager (RHESSI). RHESSI is a NASA Small Explorer satellite and was launched February 5, 2002. RHESSI's imaging capability is achieved with fine tungsten and/or molybdenum grids that modulate the solar X-ray flux as the spacecraft rotates at ~ 15 rpm. Up to 20 detailed images can be obtained per second. This is sufficient to track the electrons as they travel from their acceleration site, believed to be in the solar corona, and slow down on their way to the lower solar atmosphere. The high-resolution spectroscopy is achieved with 9 cooled germanium crystals that detect the X-ray and gamma-ray photons transmitted through the grids over the broad energy range of 3 keV to 20 MeV. Their fine energy resolution of about 1 keV is more than sufficient to reveal the detailed features of the X-ray and gamma-ray spectra, clues to the nature of the electron and ion acceleration processes. For more information, see; http://hesperia.gsfc.nasa.gov/hessi/index.html Group: Platform_Details Entry_ID: RHESSI Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Short_Name: RHESSI Long_Name: Reuven Ramaty High Energy Solar Spectroscopic Imager End_Group Group: Synonymous_Platform_Names Short_Name: HESSI Short_Name: Reuven Ramaty High Energy Solar Spectroscopic Imager Short_Name: SMEX/RHESSI Short_Name: Small Explorer/RHESSI Short_Name: 27370 Short_Name: 2002-004A End_Group Group: Platform_Associated_Instruments Short_Name: HESSI SPECTROMETER Short_Name: HESSI IMAGER End_Group Group: Orbit Orbit_Altitude: 600 km Orbit_Inclination: 38 degrees Period: 96.5 m Perigee: 579 km Apogee: 607 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Online_Resource: http://hesperia.gsfc.nasa.gov/hessi/ Sample_Image: http://hesperia.gsfc.nasa.gov/hessi/images/hessicraft.gif Group: Platform_Logistics Launch_Date: 2002-02-05 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Design_Life: 2 years Primary_Sponsor: NASA/GSFC End_Group End_Group NASA-GISS-Dust-Transport NASA GISS Globally Uniform Mineral Dust Model 2018-12-28 21:01:57.0 [sritz] insert AltLabel (id: null category: null text: NASA GISS Globally Uniform Mineral Dust Model language code: en); 2018-12-28 21:00:38.0 [sritz] Insert Concept add broader relation (NASA-GISS-Dust-Transport [ac82f543-df04-4301-b5fa-dae2800197d6,368399] - Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,344529]); Nimbus-3 Nimbus-3 was launched in April 1969 and was the third in a series of second-generation meteorological research-and-development satellites that was designed to serve as a stabilized, earth-oriented platform for the testing of advanced meteorological sensor systems and for collecting meteorological data. The polar-orbiting spacecraft consisted of three major elements: (1) a sensory ring, (2) solar paddles, and (3) the control system housing. The solar paddles and the control system housing were connected to the sensory ring by a truss structure, giving the satellite the appearance of an ocean buoy. Nimbus-3 was nearly 3.7 m tall, 1.5 m in diameter at the base, and about 3 m across with solar paddles extended. The torus-shaped sensory ring, which formed the satellite base, housed the electronics equipment and battery modules. The lower surface of the torus ring provided mounting space for sensors and telemetry antennas. An H-frame structure mounted within the center of the torus provided support for the larger experiments and tape recorders. Mounted on the control system housing, which was located on top of the spacecraft, were sun sensors, horizon scanners, gas nozzles for attitude control, and a command antenna. Use of the attitude control subsystem (ACS) permitted the spacecraft's orientation to be controlled to within plus or minus 1 degree for all three axes (pitch, roll, and yaw). Primary experiments consisted of a satellite infrared spectrometer (SIRS) for determining the vertical temperature profiles of the atmosphere, an infrared interferometer spectrometer (IRIS) for measuring the emission spectra of the earth-atmosphere system, both high- and medium-resolution infrared radiometers (HRIR and MRIR) for yielding information on the distribution and intensity of infrared radiation emitted and reflected by the earth and its atmosphere, monitor of ultraviolet solar energy (MUSE) for detecting solar UV radiation, image dissector camera system for providing daytime cloudcover pictures in both real-time mode using the real time transmission system and tape recorder mode using the high data rate storage system, radioisotope thermoelectric generator (RTG) SNAP-19 to assess the operational capability of radioisotope power for space applications, and an interrogation, recording and location system (IRLS) experiment designed to locate, interrogate, record, and retransmit meteorological and geophysical data from remote collection stations. Nimbus-3 was successful and performed normally until July 22, 1969, when the IRIS experiment failed. The HRIR and the SIRS experiments were terminated on January 25, 1970, and June 21, 1970, respectively. The remaining experiments continued operation until September 25, 1970, when the rear horizon scanner failed. Without this horizon scanner, it was impossible to maintain proper spacecraft attitude, thus making most experimental observations useless. All spacecraft operations were terminated on January 22, 1972. __________ Taken from the NSSDC System for Information Retrieval and Storage (SIRS). For more information contact the NSSDC Coordinated Request and User Support Office, 301-286-6695 (NASA Goddard Space Flight Center, Code 933.4, Greenbelt, Maryland 20771, USA). Nimbus-3 User's Guide. Group: Platform_Details Entry_ID: NIMBUS-3 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NIMBUS Short_Name: NIMBUS-3 End_Group Group: Synonymous_Platform_Names Short_Name: Nimbus-B2 Short_Name: 03890 End_Group Group: Platform_Associated_Instruments Short_Name: NEAR-INFRARED SPECTROMETER Short_Name: INFRARED RADIOMETERS Short_Name: HRIR NIMBUS-3 End_Group Group: Orbit Orbit_Inclination: 99.91000366210938 degrees Period: 107.4000015258789 minutes Perigee: 1075.0 km Apogee: 1135.0 km Orbit_Type: GEO > Geosynchronous > Geostationary End_Group Creation_Date: 2007-10-11 Online_Resource: http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1969-037A Online_Resource: http://nasascience.nasa.gov/missions/nimbus Online_Resource: http://atmospheres.gsfc.nasa.gov/nimbus/ Sample_Image: http://library01.gsfc.nasa.gov/gdprojs/images/nimbus_iii.jpg Group: Platform_Logistics Launch_Date: 1969-04-14 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: USA/NASA End_Group End_Group 2015-05-12 16:53:55.0 [saritz] update PrefLabel (Nimbus-3); GMS The Geostationary Meteorological Satellite series are spin-stabilized satellites. They have been developed to contribute to the improvement of Japan's meteorological services and the development of weather satellite technology. The satellites consist of a despun section which holds the earth-oriented antennas and a 100-rpm rotating spin section which contains the Visible and Infrared Spin Scan Radiometer (VISSR), electronic devices, etc. They have been used for the World Meteorological Organization's world Weather Watch Program which is sustained by five geostationary satellites. The first satellite in the series was launched by a U.S. Delta rocket in July 1977. The GMS-2,3 were launched by Japanese N-II rockets in August 1981 and 1984, and the GMS-4 was launched by Japanese H-I rocket in September. The following is a summary of the GMS series. NAME LAUNCHED ALTITUDE INCLINATION INSTRUMENT (KM) (DEG) ------- -------- -------- ----------- ---------- GMS-1 JULY 77 36,000 0 VISSR GMS-2 AUG. 81 36,000 0 VISSR GMS-3 AUG. 84 36,000 0 VISSR GMS-4 SEP. 89 36,000 0 VISSR GMS-5 1994 36,000 0 VISSR (to be launched) --------------- Contributed by: Tasuku Tanaka, Earth Observation Program Office Director, Program Planning and Management Department, National Space Development Agency of Japan Head Office, Hamamatsu-cho, Minato-ku, Tokyo, Japan. Group: Platform_Details Entry_ID: GMS Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: GMS (Japan Geostationary Meteorological Satellite) Short_Name: GMS Long_Name: Japan Geostationary Meteorological Satellite End_Group Group: Synonymous_Platform_Names Short_Name: Himawari End_Group Group: Platform_Associated_Instruments Short_Name: VISSR-GMS End_Group Online_Resource: http://www.jaxa.jp/projects/sat/gms/index_e.html End_Group FLEX The Earth Explorer - Fluorescence Explorer (FLEX) mission will map vegetation fluorescence to quantify photosynthetic activity. The conversion of atmospheric carbon dioxide and sunlight into energy-rich carbohydrates through photosynthesis is one of the most fundamental processes on Earth – and one on which we all depend. Information from FLEX will improve our understanding of the way carbon moves between plants and the atmosphere and how photosynthesis affects the carbon and water cycles. 2019-05-06 14:29:37.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: f6fcdea4-fdbd-4eaa-b696-2db4a893fbbc relationship type: null relationship value: null generated by: null); 2019-04-26 12:59:38.0 [mmorahan] insert AltLabel (id: null category: primary text: Fluorescence Explorer (FLEX) language code: en); insert Definition (id: null text: The Earth Explorer - Fluorescence Explorer (FLEX) mission will map vegetation fluorescence to quantify photosynthetic activity. The conversion of atmospheric carbon dioxide and sunlight into energy-rich carbohydrates through photosynthesis is one of the most fundamental processes on Earth – and one on which we all depend. Information from FLEX will improve our understanding of the way carbon moves between plants and the atmosphere and how photosynthesis affects the carbon and water cycles. language code: en); 2019-04-26 12:56:04.0 [mmorahan] Insert Concept add broader relation (FLEX [acfdfa87-7490-47db-a1dd-94a3bfb6a16d,368709] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761]); AS350-B3 2018-01-05 19:57:34.0 [sritz] Requested by NSIDC DAAC. insert AltLabel (id: null category: primary text: Helicopter AS350-B3 language code: en); 2018-01-05 19:54:46.0 [sritz] Insert Concept add broader relation (AS350-B3 [ad1d4887-ac0d-43a0-9e9b-b42172befebc,310511] - Aircraft [227d9c3d-f631-402d-84ed-b8c5a562fc27,287509]); STEREO B STEREO (Solar TErrestrial RElations Observatory) is a 2-year NASA mission employing two nearly identical space-based observatories to provide the very first, 3-D "stereo" images of the sun to study the nature of coronal mass ejections. These powerful solar eruptions are a major source of the magnetic disruptions on Earth and a key component of space weather, which can greatly affect satellite operations, communications, power systems, the lives of humans in space, and global climate. STEREO is the third mission in NASA's Solar Terrestrial Probes Program. The twin observatories launched aboard a single Boeing Delta II rocket from Cape Canaveral Air Force Station, Fla., on Oct. 25, 2006, at 8:52 p.m. EDT. STEREO is sponsored by NASA Headquarters' Science Mission Directorate, Washington, D.C. NASA Goddard Space Flight Center's Solar Terrestrial Probes Program Office, in Greenbelt, Md., manages the mission, instruments and science center. The Johns Hopkins University Applied Physics Laboratory (APL), in Laurel, Md., designed and built the spacecraft and will operate the twin observatories for NASA during the mission. The two spacecraft are launched to drift slowly away from the Earth in opposite directions at about 10 degrees per year for the lagging spacecraft and 20 degrees per year for the leading one. Optimal longitudinal separation of about sixty degrees is achieved after two years. Afterwards the separation gradually increases beyond the design lifetime of two years with the possibility of extended mission observations at larger angles. Science instruments selected for STEREO include the Sun Earth Connection Coronal and Heliospheric Investigation (SECCHI) for extreme ultraviolet (EUV), white-light coronographic, and heliospheric imaging, the STEREO/WAVES (SWAVES) interplanetary radio burst tracker, the In situ Measurements of Particles and CME Transients (IMPACT) investigation for in-situ sampling the 3-D distribution and plasma characteristics of solar energetic particles and the interplanetary magnetic field, and the PLAsma and SupraThermal Ion and Composition (PLASTIC) experiment to measure elemental and charge composition of ambient and CME plasma ions. STEREO data recorded and stored onboard each spacecraft will be downlinked through the NASA Deep Space Network on a daily schedule. Real-time space weather data will be continuously transmitted through a separate beacon system to NASA and non-NASA receiving stations. Group: Platform_Details Entry_ID: STEREO B Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Short_Name: STEREO B Long_Name: Solar Terrestrial Relations Observatory B End_Group Group: Synonymous_Platform_Names Short_Name: STEREO Lead Short_Name: STEREO West Short_Name: Solar Terrestrial Relations Observatory B Short_Name: 29511 Short_Name: 2006-047B End_Group Group: Platform_Associated_Instruments Short_Name: IMPACT Short_Name: PLASTIC Short_Name: SECCHI Short_Name: SWAVES End_Group Creation_Date: 2007-02-13 Online_Resource: http://www.nasa.gov/mission_pages/stereo/main/ Online_Resource: http://stereo.gsfc.nasa.gov/ Online_Resource: http://stereo.jhuapl.edu/ Online_Resource: http://stereo-ssc.nascom.nasa.gov/ Sample_Image: http://stereo.jhuapl.edu/gallery/images/artistConcepts/tn/PanelsDeploy_tn.jpg Group: Platform_Logistics Launch_Date: 2006-10-26 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Design_Life: 2 years Primary_Sponsor: USA/NASA Primary_Sponsor: Johns Hopkins/APL End_Group End_Group OBSERVATORIES Observatories: Buildings or places designed and equipped for making observations of astronomical, meteorological, or other natural phenomena. [Source: The American Heritage? Dictionary of the English Language, Fourth Edition] Johnson-Sea-Link I The Johnson-Sea-Link I and II were retired by Harbor Branch Oceanographic Institution in 2011 after their support ship the R/V Seward Johnson was sold to Cepemar Environmental Services of Brazil. The Johnson-Sea-Link (JSL) I and II are owned and operated by Harbor Branch Oceanographic Institution. At 23.6 ft long, 10.9 ft high and 8.3 ft wide, these highly maneuverable submersibles can dive to a depth of 3,000 ft and travel at a maximum speed of one knot. Edwin Albert Link, engineer, inventor, and friend of Harbor Branch founder Seward Johnson, working at Harbor Branch, designed and built the JSL in 1971, at Mr. Johnson’s request. Harbor Branch constructed the JSL II, which is virtually identical to the JSL I, in 1975. The JSL has two separate pressure hulls and can accommodate four people. Aft compartment occupants enter the sub through a bottom-facing 20 inch-wide hatch. The front chamber, which contains the sub’s controls, is a 5-ft-diameter sphere made of five-in thick, clear acrylic. It provides a panoramic view for the pilot and one observer. Because acrylic is a good insulator and hampers conductivity of cold ocean temperatures, the front compartment actually requires air conditioning. The second chamber, the stern compartment, houses another crew member and a second observer. The occupants have access to two side view ports and a video monitor. 2020-01-21 19:27:03.0 [tstevens] update Definition (The Johnson-Sea-Link I and II were retired by Harbor Branch Oceanographic Institution in 2011 after their support ship the R/V Seward Johnson was sold to Cepemar Environmental Services of Brazil. The Johnson-Sea-Link (JSL) I and II are owned and operated by Harbor Branch Oceanographic Institution. At 23.6 ft long, 10.9 ft high and 8.3 ft wide, these highly maneuverable submersibles can dive to a depth of 3,000 ft and travel at a maximum speed of one knot. Edwin Albert Link, engineer, inventor, and friend of Harbor Branch founder Seward Johnson, working at Harbor Branch, designed and built the JSL in 1971, at Mr. Johnson’s request. Harbor Branch constructed the JSL II, which is virtually identical to the JSL I, in 1975. The JSL has two separate pressure hulls and can accommodate four people. Aft compartment occupants enter the sub through a bottom-facing 20 inch-wide hatch. The front chamber, which contains the sub’s controls, is a 5-ft-diameter sphere made of five-in thick, clear acrylic. It provides a panoramic view for the pilot and one observer. Because acrylic is a good insulator and hampers conductivity of cold ocean temperatures, the front compartment actually requires air conditioning. The second chamber, the stern compartment, houses another crew member and a second observer. The occupants have access to two side view ports and a video monitor.); 2020-01-21 19:22:32.0 [tstevens] insert Definition (id: null text: The Johnson-Sea-Link I and II were retired by Harbor Branch Oceanographic Institution in 2011 after their support ship the R/V Seward Johnson was sold to Cepemar Environmental Services of Brazil. The Johnson-Sea-Link (JSL) I and II are owned and operated by Harbor Branch Oceanographic Institution. At 23.6 ft long, 10.9 ft high and 8.3 ft wide, these highly maneuverable submersibles can dive to a depth of 3,000 ft and travel at a maximum speed of one knot. Edwin Albert Link, engineer, inventor, and friend of Harbor Branch founder Seward Johnson, working at Harbor Branch, designed and built the JSL in 1971, at Mr. Johnson’s request. Harbor Branch constructed the JSL II, which is virtually identical to the JSL I, in 1975. The JSL has two separate pressure hulls and can accommodate four people. Aft compartment occupants enter the sub through a bottom-facing 20 inch-wide hatch. The front chamber, which contains the sub’s controls, is a 5-ft-diameter sphere made of five-in thick, clear acrylic. It provides a panoramic view for the pilot and one observer. Because acrylic is a good insulator and hampers conductivity of cold ocean temperatures, the front compartment actually requires air conditioning. The second chamber, the stern compartment, houses another crewmember and a second observer. The occupants have access to two side view ports and a video monitor. language code: en); 2020-01-21 17:34:52.0 [tstevens] Insert Concept add broader relation (Johnson-Sea-Link I [ae078302-17ab-4cc5-ba7d-7a8a0102c01b,559775] - HOV [63c8aa1d-6efc-4943-8891-3a1cd520dde0,559759]); DHC-3 The DeHavilland DHC-3 Otter's primary purpose is for utility and personnel transport. However, the DHC-3 was used by the U.S. Military and the Canadian Military as a search and rescue aircraft. Group: Platform_Details Entry_ID: DHC-3 Group: Platform_Identification Platform_Category: Aircraft Short_Name: DHC-3 Long_Name: DeHavilland DHC-3 Otter End_Group Creation_Date: 2012-07-23 Online_Resource: http://www.dhc3otter.com/profile.htm End_Group PARASOL Polarization and Anisotropy of Reflectances for Atmospheric Sciences coupled with Observations from a Lidar (PARASOL) is the second microsatellite in the Myriade series developed by CNES. It is carrying a wide-field imaging radiometer/polarimeter called POLDER (Polarization and Directionality of the Earth's Reflectances), designed in partnership with the LOA atmospheric optics laboratory in Lille (CNRS-USTL). POLDER is designed to improve our knowledge of the radiative and microphysical properties of clouds and aerosols by measuring the directionality and polarization of light reflected by the Earth-atmosphere system. [Summary provided by CNES.] Group: Platform_Details Entry_ID: PARASOL Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: EOS (Earth Observing System) Short_Name: PARASOL End_Group Group: Platform_Associated_Instruments Short_Name: POLDER End_Group Group: Orbit Orbit_Altitude: 705 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-05-21 Online_Resource: http://missions-scientifiques.cnes.fr/PARASOL/Fr/ Sample_Image: http://smsc.cnes.fr/IcPARASOL/satellite.gif Group: Platform_Logistics Launch_Date: 2004-12-18 Launch_Site: Kourou, French Guiana Design_Life: 1 Year Primary_Sponsor: CNES End_Group End_Group OrbView-2 SEASTAR OrbView-2 is an imaging satellite, developed, owned, managed and operated by Orbital Imaging Corporation (OrbImage) of Dulles, VA. The overall objective of the OrbView-2/SeaWiFS mission is to provide quantitative data on global ocean bio-optical properties to the Earth science community. The OrbView-2 satellite includes the SeaWiFS (Sea-Viewing Wide Field-of-View Sensor) imaging system, an 8-band multispectral imaging instrument with a one kilometer spatial resolution. 2020-01-29 21:58:54.0 [sritz] update Resource (https://oceancolor.gsfc.nasa.gov/SeaWiFS/IMAGES/seastar_orbit.jpg); 2019-02-22 14:00:15.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: 769780b8-ba0e-4cd2-9575-88953c1010a0 relationship type: null relationship value: null generated by: null); 2017-11-14 18:54:23.0 [tstevens] update Definition (OrbView-2 is an imaging satellite, developed, owned, managed and operated by Orbital Imaging Corporation (OrbImage) of Dulles, VA. The overall objective of the OrbView-2/SeaWiFS mission is to provide quantitative data on global ocean bio-optical properties to the Earth science community. The OrbView-2 satellite includes the SeaWiFS (Sea-Viewing Wide Field-of-View Sensor) imaging system, an 8-band multispectral imaging instrument with a one kilometer spatial resolution.); 2017-11-14 18:53:09.0 [tstevens] update AltLabel (SEASTAR ); update PrefLabel (OrbView-2); update Resource (image); 2016-06-09 17:19:17.0 [epneff] added altLabel insert AltLabel (id: null text: OrbView-2 language code: en); Maps/Charts/Photographs Map: Visual representations of an area – a symbolic depiction highlighting relationships between elements of that space such as objects, regions, and themes. [Source: Wikipedia, http://en.wikipedia.org/wiki/Map ] Chart: A sheet of information in the form of a table, graph, or diagram. [Source: Merriam Webster, http://www.merriam-webster.com/dictionary/charts Photograph: a picture or likeness obtained by photography. [Source: Merriam Webster, http://www.merriam-webster.com/dictionary/photographs ] Group: Platform_Details Entry_ID: Maps/Charts/Photographs Group: Platform_Identification Platform_Category: Maps/Charts/Photographs Short_Name: Maps/Charts/Photographs End_Group End_Group 2012-10-24 18:22:41.0 [saritz] Insert Concept add narrower relation (Maps/Charts/Photographs [af11dd2a-e514-4329-bbc5-0f36f2776a26,73527] - MISSION REPORTS [f9846838-fdbc-4aa0-86e9-b0e70e97d0e2,81979]); LDAR Located at the Kennedy Space Center, the Lightning Detection and Ranging (LDAR) system consists of seven antennas that detect electromagnetic pulses at 66 MHz, which allows it to detect 99% of all flashes (both intracloud and cloud-to-ground flashes) within 10 km of the antenna network. The accuracy of source locations is a function of position relative to the receiving array, generally decreasing (particularly along the radial axis with respect to the array center) with distance. The RMS error for LDAR lightning source locations varies from 100 meters inside the network to about 10 km at a range of 90 km (about 1/3 the width of the Florida peninsula). 2017-09-11 17:53:26.0 [tstevens] insert AltLabel (id: null category: primary text: Lightning Detection and Ranging language code: en); insert Definition (id: null text: Located at the Kennedy Space Center, the Lightning Detection and Ranging (LDAR) system consists of seven antennas that detect electromagnetic pulses at 66 MHz, which allows it to detect 99% of all flashes (both intracloud and cloud-to-ground flashes) within 10 km of the antenna network. The accuracy of source locations is a function of position relative to the receiving array, generally decreasing (particularly along the radial axis with respect to the array center) with distance. The RMS error for LDAR lightning source locations varies from 100 meters inside the network to about 10 km at a range of 90 km (about 1/3 the width of the Florida peninsula). language code: en); 2017-09-11 17:52:21.0 [tstevens] Insert Concept add broader relation (LDAR [af4130b5-af02-4602-9e05-81405cfe6dc5,310151] - WEATHER STATIONS/NETWORKS [57b7373d-5c21-4abb-8097-a410adc2a074,287833]); OV-099 Challenger, the second orbiter to become operational at Kennedy Space Center, was named after the British Naval research vessel HMS Challenger that sailed the Atlantic and Pacific oceans during the 1870's. The Apollo 17 lunar module also carried the name of Challenger. Like her historic predecessors, Space Shuttle Challenger and her crews made significant contributions to America's scientific growth. Challenger started out as a high-fidelity structural test article (STA-099). The airframe was completed by Rockwell and delivered to Lockheed Plant 42 for structural testing on 02/04/78. The orbiter structure had evolved under such weight-saving pressure that virtually all components of the air frame were required to handle significant structural stress. With such an optimized design, it was difficult to accurately predict mechanical and thermal loading with the computer software available at the time. The only safe approach was to submit the structural test article to intensive testing and analysis. STA-099 underwent 11 months of intensive vibration testing in a 43 ton steel rig built especially for the Space Shuttle Test Program. The rig consisted of 256 hydraulic jacks, distributed over 836 load application points. Under computer control, it was possible to simulate the expected stress levels of launch, ascent, on-orbit, reentry and landing. Three 1 million pound-force hyd raulic cylinders were used to simulate the thrust from the Space Shuttle Main Engines. Heating and thermal simulations were also done. On January 28, 1986, the Challenger and its seven-member crew were lost 73 seconds after launch when a booster failure resulted in the breakup of the vehicle. [Summary provided by NASA] Group: Platform_Details Entry_ID: OV-099 Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Platform_Series_or_Entity: SPACE SHUTTLE Short_Name: OV-099 Long_Name: Challenger Space Shuttle End_Group Group: Synonymous_Platform_Names Short_Name: challenger End_Group Creation_Date: 2008-01-24 Online_Resource: http://www-pao.ksc.nasa.gov/kscpao/shuttle/resources/orbiters/challenger.html Group: Platform_Logistics Primary_Sponsor: NASA End_Group End_Group ERS-2 ERS-2 (EUROPEAN REMOTE SENSING SATELLITE-2) The second European Remote Sensing Satellite ERS-2, launched on 20 April 1995, operates in a sun-synchronous, near-polar orbit at an altitude of 785 km and an inclination of 98.5 degrees ,known as the reference orbit. The mission consists of an only phase (phase A), using a 35 day repeat cycle, from 21 April 1995 to the present. ERS-2 is almost identical to the European Remote Sensing Satellite ERS-1 launched in 1991. ERS-2 is capable of measuring, on a global scale, the Earth's atmospheric and surface properties with a high degree of accuracy. In fact it uses advanced microwave techniques to collect global measurements and images (much of the data are collected from remote areas such as the southern oceans and the Antarctic) independent of time of day and weather conditions. It also undertakes the measurements of many parameters not covered by existing satellite systems, including those of sea state, sea surface winds, ocean circulation and sea and ice levels. ERS-2 carries on-board a number of instruments consisting of a core set of active microwave sensors supported by additional, complementary instruments: the Active Microwave Instrument (AMI), which combines a Synthetic Aperture Radar (SAR) operating in image or wave mode and a wind scatterometer, the Radar Altimeter (RA), the Along-Track Scanning Radiometer and Microwave Sounder (ATSR-2), the Precise Range and Range-rate Equipment (PRARE), the Global Ozone Monitoring Experiment (GOME), and Laser Retroreflectors (LRR). The primary objectives of the ERS-2 mission are the monitoring of the oceans and sea ice providing essential data for: - improved representation of oceans/atmosphere interactions in climatic models - major advances in the knowledge of ocean circulation and transfer of energy - more reliable estimates of the mass balance of the Arctic and Antarctic ice sheets - better monitoring of pollution and dynamic coastal processes - improved detection and management of land use change. The capability of ERS-2 to acquire vast global data sets of ocean, atmosphere, ice and land phenomena contributes to the following types of study and application: - Ocean/Ice: ocean circulation, global wind/wave relationships, sea ice and iceberg monitoring, etc. - Physical Earth: accurate determination of the ocean geoid, forestry, glaciology, geology and agriculture studies, etc. - Climate: contribution to the World Climate Research Programme and to the World Ocean Circulation Experiment - Weather and Sea: short and medium-term weather forecasting, sea surface State Forecasting wind speed and direction, location of pelagic fish through the monitoring of temperature fronts - Global Ozone: measures ozone, trace gases, and aerosols in the troposphere and stratosphere Group: Platform_Details Entry_ID: ERS-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: ERS Earth Resource Satellite Short_Name: ERS-2 Long_Name: European Remote Sensing Satellite-2 End_Group Group: Synonymous_Platform_Names Short_Name: ERS-2 End_Group Group: Platform_Associated_Instruments Short_Name: LRR Short_Name: GOME Short_Name: PRARE Short_Name: ATSR-2 Short_Name: RA Short_Name: SAR Short_Name: AMI End_Group Group: Orbit Orbit_Altitude: 785 km Orbit_Inclination: 98.5 deg Repeat_Cycle: 35 day End_Group Creation_Date: 2007-09-19 Online_Resource: http://earth.esa.int/ers/ Online_Resource: http://www.astronautix.com/craft/ers12.htm Sample_Image: http://southport.jpl.nasa.gov/polar/satgifs/ers1.gif Group: Platform_Logistics Launch_Date: 1995-04-21 Launch_Site: Kourou, French Guiana Primary_Sponsor: ESA End_Group End_Group 2016-06-09 14:40:16.0 [epneff] added altLabel insert AltLabel (id: null text: ERS-2 (EUROPEAN REMOTE SENSING SATELLITE-2) language code: en); NASA Medium Class Explorers (MIDEX) Resurs-P N2 Environmental Satellite Resurs-P N2 Group: Platform_Details Entry_ID: Resurs-P N2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: Resurs-P N2 Long_Name: Environmental Satellite Resurs-P N2 End_Group Group: Platform_Associated_Instruments Short_Name: Geoton-L1 (2) Short_Name: GSA (1) Short_Name: SHMSA-VR Short_Name: SHMSA-SR End_Group Group: Orbit Orbit_Altitude: 475 km Orbit_Inclination: 97 degrees Repeat_Cycle: 3 days Orbit_Type: LEO > LOW EARTH ORBIT > POLAR SUN-SYNCHRONOUS End_Group Creation_Date: 2015-01-26 Online_Resource: http://samspace.ru/products/earth_remote_sensing_satellites/ka_resurs_p/ Online_Resource: http://en.samspace.ru/products/earth_remote_sensing_satellites/ka_resurs_p/ Sample_Image: https://hi-tech.imgsmail.ru/hitech_img/source/a9/e4/60d9293c45c431051af8cf310903.jpg Group: Platform_Logistics Launch_Date: 2015-12-26 Design_Life: 5 years End_Group End_Group 2015-08-03 12:40:13.0 [mpmorahan] insert AltLabel (id: null text: Environmental Satellite Resurs-P N2 language code: en); 2015-08-03 12:38:06.0 [mpmorahan] Insert Concept add broader relation (Resurs-P N2 [b00d17a2-b509-4b42-86fd-d50bf50cfc3c,158119] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,143415]); BE-C BE-C (Explorer 27) was a small ionospheric research satellite instrumented with an electrostatic probe, radio beacons, a passive laser tracking reflector, and a Doppler navigation experiment. Its primary objective was to obtain worldwide observations of total electron content between the spacecraft and the earth. The satellite was initially spin stabilized, but it was despun after solar paddle erection. Subsequent stabilization oriented the satellite axis of symmetry with the local magnetic field by means of a strong bar magnet and damping rods. A three-axis magnetometer and sun sensors provided information on the satellite attitude and spin rate. There was no tape recorder aboard so that satellite performance data and electrostatic probe data were observed only when the satellite was within range of a ground telemetry station. Continuous transmitters operated at 162 and 324 MHz to permit precise tracking by 'Transit' tracking stations for navigation and geodetic studies. The satellite was turned off on July 20, 1973, due to frequency interference with higher priority spacecraft. Group: Platform_Details Entry_ID: BE-C Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: BE (Beacon Explorer) Short_Name: BE-C Long_Name: Beacon Explorer-C End_Group Group: Platform_Associated_Instruments Short_Name: DOPPLER BEACONS Short_Name: LASER TRACKING REFLECTOR Short_Name: RADIO TRANSPONDERS Short_Name: PROBES End_Group Group: Orbit Orbit_Inclination: 41.1 degrees Perigee: 1320 km Apogee: 940 km End_Group Creation_Date: 2007-08-29 Online_Resource: http://cddis.nasa.gov/926/egm96/bec.html Group: Platform_Logistics Launch_Date: 1965-04-29 Launch_Site: Wallops Flight Facility, Wallops Island, USA Primary_Sponsor: NASA End_Group End_Group GOES-6 GOES 6 was launched in April 1983 and was a NASA-developed, NOAA-operated, geosynchronous, and operational spacecraft. The cylindrically shaped spacecraft measured 190.5 cm in diameter and 230 cm in length, exclusive of a magnetometer that extended an additional 83 cm beyond the cylinder shell. The primary structural members were a honeycombed equipment shelf and thrust tube. The VISSR telescope was mounted on the equipment shelf and viewed the Earth through a special aperture in the side of the spacecraft. A support structure extended radially out from the thrust tube and was affixed to the solar panels, which formed the outer walls of the spacecraft and provided the primary source of electrical power. Located in the annulus-shaped space between the thrust tube and the solar panels were stationkeeping and dynamics control equipment, batteries, and most of the SEM equipment. Proper spacecraft attitude and spin rate (approximately 100 rpm) were maintained by two separate sets of jet thrusters mounted around the spacecraft equator and activated by ground command. The spacecraft used both UHF-band and S-band frequencies in its telemetry and command subsystem. A low-power VHF transponder provided telemetry and command during launch and then served as a backup for the primary subsystem once the spacecraft attained orbit. The spin-stabilized spacecraft carried a visible infrared spin-scan radiometer atmospheric sounder, meteorological data collection and transmission system, space environment monitor, and a biaxial fluxgate magnetometer. GOES 6 was moved from its 135 degrees West position to a more central 98 degrees West position when GOES 5 failed on July 29, 1984. For more information on GOES satellites: http://www.ospo.noaa.gov/Operations/GOES/index.html 2017-09-01 17:06:39.0 [sritz] insert Definition (id: null text: GOES 6 was launched in April 1983 and was a NASA-developed, NOAA-operated, geosynchronous, and operational spacecraft. The cylindrically shaped spacecraft measured 190.5 cm in diameter and 230 cm in length, exclusive of a magnetometer that extended an additional 83 cm beyond the cylinder shell. The primary structural members were a honeycombed equipment shelf and thrust tube. The VISSR telescope was mounted on the equipment shelf and viewed the Earth through a special aperture in the side of the spacecraft. A support structure extended radially out from the thrust tube and was affixed to the solar panels, which formed the outer walls of the spacecraft and provided the primary source of electrical power. Located in the annulus-shaped space between the thrust tube and the solar panels were stationkeeping and dynamics control equipment, batteries, and most of the SEM equipment. Proper spacecraft attitude and spin rate (approximately 100 rpm) were maintained by two separate sets of jet thrusters mounted around the spacecraft equator and activated by ground command. The spacecraft used both UHF-band and S-band frequencies in its telemetry and command subsystem. A low-power VHF transponder provided telemetry and command during launch and then served as a backup for the primary subsystem once the spacecraft attained orbit. The spin-stabilized spacecraft carried a visible infrared spin-scan radiometer atmospheric sounder, meteorological data collection and transmission system, space environment monitor, and a biaxial fluxgate magnetometer. GOES 6 was moved from its 135 degrees West position to a more central 98 degrees West position when GOES 5 failed on July 29, 1984. For more information on GOES satellites: http://www.ospo.noaa.gov/Operations/GOES/index.html language code: en); 2017-09-01 16:45:35.0 [sritz] Insert Concept add broader relation (GOES-6 [b048b823-7125-4426-b25d-121c85044bb4,310095] - GOES [6e332c25-caeb-4917-afb6-af757bcecd72,310071]); ITOS-1 The Improved TIROS Operational Satellite (ITOS) inaugurated the second generation of a space-based system to provide continuous, day-to-day observations of the Earth's weather systems. ITOS launched a total of six satellites from 1970 through 1976, continuing the mission of the TIROS and the TIROS Operational Satellite programs. ITOS flew in a polar, sun-synchronous orbit and used improved stabilization techniques that allowed the spacecraft always to point its cameras and other sensors at the Earth. The satellite carried Automatic Picture Transmission cameras to provide instant weather data to ground stations around the world; Advanced Vidicon Camera Subsystems for detailed observations; and scanning radiometers for imaging the earth at night. ITOS 1 had an operational life of 510 days, taking more than 100,000 images of the Earth. This artifact is a prototype of ITOS-1; NASA transferred it to the Museum in 1976. 2018-10-30 17:21:13.0 [sritz] insert Definition (id: null text: The Improved TIROS Operational Satellite (ITOS) inaugurated the second generation of a space-based system to provide continuous, day-to-day observations of the Earth's weather systems. ITOS launched a total of six satellites from 1970 through 1976, continuing the mission of the TIROS and the TIROS Operational Satellite programs. ITOS flew in a polar, sun-synchronous orbit and used improved stabilization techniques that allowed the spacecraft always to point its cameras and other sensors at the Earth. The satellite carried Automatic Picture Transmission cameras to provide instant weather data to ground stations around the world; Advanced Vidicon Camera Subsystems for detailed observations; and scanning radiometers for imaging the earth at night. ITOS 1 had an operational life of 510 days, taking more than 100,000 images of the Earth. This artifact is a prototype of ITOS-1; NASA transferred it to the Museum in 1976. language code: en); 2018-10-30 17:18:47.0 [sritz] Insert Concept add broader relation (ITOS-1 [b080d2a3-c089-4ddf-bbfb-3e24495413b3,368219] - ITOS [80e95a88-b44e-444e-bd79-2e6dbb56b170,368215]); MERCURY Initiated in 1958, completed in 1963, Project Mercury was the United States' first man-in-space program. The objectives of the program, which made six manned flights from 1961 to 1963, were specific: - To orbit a manned spacecraft around Earth - To investigate man's ability to function in space - To recover both man and spacecraft safely Group: Platform_Details Entry_ID: MERCURY Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Short_Name: MERCURY End_Group Creation_Date: 2012-07-18 Online_Resource: http://www.nasa.gov/mission_pages/mercury/missions/goals.html Sample_Image: http://www.nasa.gov/images/content/163519main_mercury-missions-sm.jpg Group: Platform_Logistics Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: NASA End_Group End_Group SKYLAB The Skylab (SL) was a manned, orbiting spacecraft composed of five parts: the Apollo telescope mount (ATM), the multiple docking adapter (MDA), the airlock module (AM), the instrument unit (IU), and the orbital workshop (OWS). The Skylab was in the form of a cylinder, with the ATM being positioned 90 degrees from the longitudinal axis after insertion into orbit. The ATM was a solar observatory, and it provided attitude control and experiment pointing for the rest of the cluster. The retrieval and installation of film used in the ATM was accomplished by astronauts during extravehicular activity (EVA). The MDA served as a dock for the command and service modules, which served as personnel taxies to the Skylab. The OWS was a modified Saturn 4B stage suitable for long duration manned habitation in orbit. It contained provisions and crew quarters necessary to support three-person crews for periods of up to 84 days each. All parts were also capable of unmanned, in-orbit storage, reactivation, and reuse. The Skylab itself was launched on May 14, 1973. It was first manned during the period May 25 to June 22, 1973, by the crew of the SL-2 mission. Next, it was manned during the period July 28 to September 25, 1973, by the crew of the SL-3 mission. The final manned period was from November 16, 1973, to February 8, 1974, when it was manned by the crew from the SL-4 mission. Group: Platform_Details Entry_ID: SKYLAB Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Short_Name: SKYLAB End_Group Group: Synonymous_Platform_Names Short_Name: skylab End_Group Creation_Date: 2008-01-31 Online_Resource: http://science.ksc.nasa.gov/history/skylab/skylab.html Sample_Image: http://www.nasa.gov/images/content/144461main_skylab_over_earth2.jpg Group: Platform_Logistics Launch_Date: 1973-05-14 Primary_Sponsor: NASA End_Group End_Group AEM (Applications Explorer Mission) DMSP 5D-2/F14 DMSP-F14 [Source: National Space Science Data Center, http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1997-012A ] DMSP 5D-2/F14, also named USA 131, is one of a series of meteorological satellites developed and operated by the Air Force under the Defense Meteorological Satellite Program (DMSP). This program, previously known as DAPP (Data Acquisition and Processing Program), was classified until March 1973. The objective of this program is to provide global visual and infrared cloudcover data and specialized environmental data to support Department of Defense operational weather analysis and forecasting requirements. Operationally, the program consists of two satellites in sun-synchronous polar orbits, with the ascending node of one satellite in early morning and the other at local noon. The 6.4-m-long spacecraft is separated into four sections: (1) a precision mounting platform for sensors and equipment requiring precise alignment; (2) an equipment support module containing the electronics, reaction wheels, and some meteorological sensors; (3) a reaction control equipment support structure containing the third-stage rocket motor and supporting the ascent phase reaction control equipment; and (4) a 9.29-sq-m solar cell panel. The spacecraft stabilization is controlled by a combination flywheel and magnetic control coil system so that sensors are maintained in the desired earth-looking mode. One feature is the precision-pointing accuracy of the primary imager to 0.01 deg provided by a star sensor and an updated ephemeris navigation system. This allows automatic geographical mapping of the digital imagery to the nearest picture element. The operational linescan system is the primary data acquisition system and provides real-time or stored, multi-orbit, day-and-night, visual and infrared imagery of clouds. A supplementary sensor package contains: (1) a microwave imager; (2) a microwave temperature sounder; (3) a microwave water vapor profiler; (4) an ion and electron scintillation monitor; (5) a precipitating electron/ion spectrometer; (6) a gamma/X-ray detector; (7) a magnetometer; and (8) a static earth-viewing sensor monitoring electromagnetic radiation. Additional information concerning the satellite can be found in the report by D. A. Nichols, "The Defense Meteorological Satellite Program," Optical Engineering, v. 14, n. 4, p. 273, July-August 1975. Group: Platform_Details Entry_ID: DMSP 5D-2/F14 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: DMSP (Defense Meteorological Satellite Program) Short_Name: DMSP 5D-2/F14 Long_Name: Defense Meteorological Satellite Program-F14 End_Group Group: Synonymous_Platform_Names Short_Name: DMSP-F14 Short_Name: USA 131 Short_Name: 24753 End_Group Group: Platform_Associated_Instruments Short_Name: SSI/ES2 Short_Name: SSM/T Short_Name: OLS Short_Name: SSM/T-2 Short_Name: SSJ/4 Short_Name: SSM/I Short_Name: SSB/X2 Short_Name: SSM End_Group Group: Orbit Orbit_Inclination: 98.9° Period: 101.8 minutes Perigee: 843.0 km Apogee: 854.0 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2008-10-30 Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1997-012A Online_Resource: http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/dmsp.html Online_Resource: http://www.ngdc.noaa.gov/dmsp/ Group: Platform_Logistics Launch_Date: 1997-04-04 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: Department of Defense-Department of the Air Force (United States) End_Group End_Group 2016-06-09 14:36:09.0 [epneff] added altLabel insert AltLabel (id: null text: DMSP-F14 language code: en); NASA ER-2 The ER-2 is a civilian version of the Air Force's U2-S reconnaissance platform. These high-altitude aircraft are used as platforms for investigations that cannot be accomplished by sensor platforms of the private sector. Aircraft and spacecraft have proven to be excellent platforms for remote and in situ sensing. The ER-2, flying at the edge of space, can scan shorelines, measure water levels, help fight forest fires, profile the atmosphere, assess flood damage, and sample the stratosphere. [Text and Photo provided by: http://www.nasa.gov/centers/dryden/research/AirSci/ER-2/ ] Group: Platform_Details Entry_ID: NASA ER-2 Group: Platform_Identification Platform_Category: Aircraft Short_Name: NASA ER-2 Long_Name: NASA Earth Resources-2 End_Group Group: Platform_Associated_Instruments Short_Name: COSMIR Short_Name: NAST-MTS Short_Name: NAST-M Short_Name: NAST-I End_Group Creation_Date: 2008-07-14 Online_Resource: http://www.nasa.gov/centers/dryden/research/AirSci/ER-2/ Online_Resource: http://www.nasa.gov/centers/dryden/news/FactSheets/FS-046-DFRC.html Sample_Image: http://www.nasa.gov/centers/dryden/images/content/85208main_EC99-45225-2.jpg Group: Platform_Logistics Primary_Sponsor: USA/NASA End_Group End_Group IRS-1B The Indian Remote Sensing Satellite-1B (IRS-1B) was launched on August 8, 1991, from Tyuratan, U.S.S.R.. IRS-1B continues the series of Earth resources remote sensing satellites developed by Indian Space Research Organisation (ISRO) for land-based applications such as agriculture, forestry, geology, and hydrology. The spacecraft is a box-shaped 1.6 x 1.56 x 1.1 meter bus with two Sun-tracking solar arrays of 8.5 square meters each. Two nickel cadmium batteries provide power during eclipses. The three-axis stabilize sun-synchronous satellite had a 0.4 degree pitch/roll and 0.5 degree yaw pointing accuracy provided by a zero-momentum reaction wheel system utilizing Earth/Sun/star sensors and gyros. The satellite carried three Linear Imaging Self-Scanning (LISS) push-broom CCD sensors operating in four spectral bands compatible with Landsat Thematic Mapper and Spor HRV data. The bands were 0.45 - 0.52, 0.52 - 0.59, 0.62 - 0.68, and 0.77 - 0.86 microns. The LISS 1 sensor had four 2048-element CCD imagers with a focal length of 162.2 cm generating a resolution of 72.5 meters and a 148 km swath width. The LISS 2A/B sensors had eight 2048-element CCD imagers with a focal length of 324.4 mm generating a ground resolution of 36.25 meters and a 74 km swath width. The two LISS 2 imagers bracketed the LISS 1 imager providing a 3 km overlap. Data from the LISS 1 were downlinked on S-band at 5.2 Mbps and from the LISS 2 A/B at 10.4 Mbps to the ground station at Shandnager, India. The satellite was controlled from Bangalore, India. Group: Platform_Details Entry_ID: IRS-1B Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: IRS (Indian Remote Sensing Satellite) Short_Name: IRS-1B Long_Name: Indian Remote Sensing Satellite-1B End_Group Group: Synonymous_Platform_Names Short_Name: IRS-IB End_Group Group: Platform_Associated_Instruments Short_Name: LISS-I Short_Name: LISS-II End_Group Group: Orbit Orbit_Altitude: 904 km Orbit_Inclination: 99 deg Period: 103 min Repeat_Cycle: 22 days Perigee: 887 km Apogee: 922 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-10-05 Online_Resource: http://www.isro.gov.in/satellites/irs-1b.aspx Sample_Image: http://www.isro.gov.in/satellites/images/irs-1b_img.gif Group: Platform_Logistics Launch_Date: 1991-08-08 Launch_Site: Baikonur Cosmodrome, Tyuratam, Russia Primary_Sponsor: India End_Group End_Group NASA ELECTRA Lockheed's Electra provided a number of airlines with their introduction to turbine powered aircraft. Today it remains popular with freight operators. The Lockheed L-188 Electra was developed to meet a 1954 American Airlines requirement for a domestic short to medium range 75 to 100 seat airliner. In June 1955 American awarded Lockheed an order for 35 such aircraft. Lockheed's design, the L-188, was a low wing, four turboprop powered aircraft. Many other airlines shared American's interest in the L-188, and by the time the first prototype flew on December 6 1957, the order book stood at 144. Service entry was with Eastern Airlines (due to a pilot's strike at American) on January 12 1959. However, any optimism Lockheed felt about a strong sales future would have been short lived, as a number of crashes in 1959 and 1960 (two of which where the aircraft broke up in flight) contributed to a number of order cancellations. As an interim measure following the crashes, speed restrictions were imposed on Electras. Investigations uncovered a design defect with the engine mountings where the wing would shake and eventually break up. Lockheed undertook a significant modification program where the nacelles, nacelle mountings and wing structure were strengthened, and the speed restrictions were eventually lifted in 1961. After that the Electra proved reliable and popular in service, but the damage had been done and production wound up in 1961 after 170 had been built. Lockheed built two basic versions of the Electra. The L-188A was the basic production aircraft, and accounted for most Electra sales. The L-188C entered service with KLM in 1959 and had greater fuel capacity and higher weights, and thus improved payload range performance. The Electra also forms the basis for the hugely successful P-3 Orion long range maritime surveillance aircraft of which more than 600 have been built. Most Electras currently in service are configured as freighters. From 1967 Lockheed converted 41 Electras to freighters or convertible freighter/passenger aircraft, fitting a strengthened floor and a large cargo door forward of the wing on the left side. Other companies have also converted Electras to freighters. However, a small number remain in passenger service. [Text provided by airliners.net: http://www.airliners.net/aircraft-data/stats.main?id=268 ] [Photo provided by: http://quest.arc.nasa.gov/ltc/astrobio/leonid/images/NCAR.gif ] Group: Platform_Details Entry_ID: NASA ELECTRA Group: Platform_Identification Platform_Category: Aircraft Short_Name: NASA ELECTRA End_Group Creation_Date: 2008-07-14 Online_Resource: http://www.airliners.net/aircraft-data/stats.main?id=268 Sample_Image: http://quest.arc.nasa.gov/ltc/astrobio/leonid/images/NCAR.gif End_Group NCEP/NCAR-RM 2015-08-10 18:52:00.0 [epneff] Added long name insert AltLabel (id: null text: NCEP/NCAR Reanalysis Model language code: en); 2015-08-10 18:51:41.0 [epneff] Insert Concept add broader relation (NCEP/NCAR-RM [b1c1ea44-000a-4535-8e90-d8dd447371d4,158243] - Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215]); Galileo (Europe's European Satellite Navigation System) Galileo is the European Union's Global Satellite Navigation System (GNSS). Sometimes called the 'European GPS, Galileo provides accurate positioning and timing information. Galileo is a programme under civilian control and its data can be used for a broad range of applications. It is autonomous but also interoperable with existing satellite navigation systems. At the moment, the Galileo constellation consists of 18 satellites. 2017-08-15 13:23:20.0 [tstevens] insert Definition (id: null text: Galileo is the European Union's Global Satellite Navigation System (GNSS). Sometimes called the 'European GPS, Galileo provides accurate positioning and timing information. Galileo is a programme under civilian control and its data can be used for a broad range of applications. It is autonomous but also interoperable with existing satellite navigation systems. At the moment, the Galileo constellation consists of 18 satellites. language code: en); 2017-08-15 11:32:37.0 [tstevens] update PrefLabel (Galileo (Europe's European Satellite Navigation System)); 2017-08-14 19:29:27.0 [tstevens] update PrefLabel (Galileo (Europe’s European Satellite Navigation System)); 2017-08-14 19:20:04.0 [tstevens] Insert Concept add narrower relation (Galileo (European Satellite Navigation System) [b1c1ecfd-eb6c-4a51-b86e-2ae64babc27d,309895] - Galileo [59fae923-a986-41e5-8fe2-30bd3b9cb625,309899]); 2017-08-14 19:19:17.0 [tstevens] update PrefLabel (Galileo (European Satellite Navigation System)); 2017-08-14 18:59:55.0 [tstevens] Insert Concept add broader relation (Galileo [b1c1ecfd-eb6c-4a51-b86e-2ae64babc27d,309895] - Navigation Platforms [1506fb17-7ac4-44ce-bde5-074885bdb2d2,287403]); DART The Deep-ocean Assessment and Reporting of Tsunamis (DART) real-time tsunami buoy system is comprised of two parts -- the Bottom Pressure Recorder (BPR) and the accompanying surface buoy with its related electronics. The BPR resides on the ocean bottom and monitors water pressure with a resolution of approximately 1 mm seawater. Samples integrated over a 15-second time window are recorded internally by the BPR and provide the base sampling interval for all real-time transmissions. Data are transmitted from the BPR to the surface buoy via an acoustic modem which in turn transmits the data to ground systems via Iridium satellites. Group: Platform_Details Entry_ID: DART Group: Platform_Identification Platform_Category: In Situ Ocean-based Platforms Short_Name: DART Long_Name: Deep-ocean Assessment and Reporting of Tsunamis End_Group Creation_Date: 2012-07-18 Online_Resource: http://nctr.pmel.noaa.gov/Dart/ End_Group NOAA-11 NOAA-11 (ATN series) was launched on September 24, 1988 and is a third-generation operational meteorological satellite for use in the National Operational Environmental Satellite System (NOESS). The satellite design provides an economical and stable sun-synchronous platform. This platform enables the satellite to carry advanced operational instruments to measure the earth's atmosphere, its surface and cloud cover, and the near-space environment. The satellite is based upon the Block 5D spacecraft bus developed for the U.S. Air Force, and is capable of maintaining an earth-pointing accuracy of better than plus or minus 0.1 degree with a motion rate of less than 0.035 degree/second. Primary sensors include (1) an Advanced Very High Resolution Radiometer (AVHRR), (2) TIROS Operational Vertical Sounder (TOVS), and (3) a Solar Backscatter Ultraviolet Spectrometer (SBUV/2). The secondary experiment is a Data Collection System (DCS). A Search and Rescue (SAR) system is also carried on NOAA-11. Orbital Characteristics- Orbital Period: 101.50 m Inclination: 99.00 degrees Eccentricity: 0.00256 Periapsis: 833.00 km Apoapsis: 870.00 km To view a 3D orbit, observe the J track satellite tracking web page: "http://liftoff.msfc.nasa.gov/RealTime/JTrack/" __________ Taken from the NSSDC System for Information Retrieval and Storage (SIRS). For more information contact the NSSDC Coordinated Request and User Support Office, 301-286-6695 (NASA Goddard Space Flight Center, Code 933.4, Greenbelt, Maryland 20771, USA, "http://nssdc.gsfc.nasa.gov/"). Group: Platform_Details Entry_ID: NOAA-11 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NOAA POES (Polar Orbiting Environmental Satellites) Short_Name: NOAA-11 Long_Name: National Oceanic & Atmospheric Administration-11 End_Group Group: Synonymous_Platform_Names Short_Name: NOAA-11 End_Group Group: Platform_Associated_Instruments Short_Name: TOVS Short_Name: AVHRR Short_Name: SBUV End_Group Group: Orbit Orbit_Inclination: 99 deg Perigee: 833 km Apogee: 870 km End_Group Creation_Date: 2007-10-17 Online_Resource: http://nssdc.gsfc.nasa.gov/ Group: Platform_Logistics Launch_Date: 1988-09-09 Primary_Sponsor: NASA End_Group End_Group Little Hercules Little Hercules is a 4000m depth rated Remotely Operated Vehicle (ROV), with an impressive past and most promising future. “Little Herc”, as he is widely referred to is just that; “little”. But as we all know, many good things come in small packages. Little Herc came to the Okeanos Explorer through collaboration between NOAA’s Office of Ocean Exploration and Research and Dr. Robert Ballard’s Institute for Exploration (IFE) at the University of Rhode Island (URI). With a major commitment to explore the waters off Indonesia, our Program’s much larger ROV could not be readied in time for our 2010 sailing date. As a result, Little Herc was chosen as our stand-in. Originally developed by a team of engineers at IFE, Little Herc first came into the spotlight when he gave the world the first and only images of John Kennedy’s PT Boat; PT-109. After several other successful missions for IFE, Little Herc stepped down, taking a back seat to the now much larger and spectacular, “Hercules”. After doing a short stint as an exhibit piece in the Mystic Aquarium, a proposal by the NOAA Office of Ocean Exploration has given new life to the veteran “Explorer”. Through a Joint Project Agreement (JPA) between NOAA, IFE and URI, a team of engineers from several institutions and companies once again went to work, this time recommissioning Little Herc. In a field where technology advances rapidly, it was necessary and appropriate that Little Herc receive a substantial upgrade before joining the ship. After an extensive 4 month overhaul, Little Herc boasted a new motor controller and power bottle system, an upgraded fiber optic multiplexer system, a new Ultra Short Baseline Tracking System (USBL), a full color imaging sonar, a new Conductivity-Temperature-Depth (CTD) sensor, two new single chip color CCD cameras, two new LED lights, two 400watt HMI Lights and a spectacular High Definition video camera. New tethers, new tether terminations, a new transformer, a new electrical junction box, new depth and altitude sensors, a new light bar and a new version of control software to make it all work was in order. Tested at the University of New Hampshire’s Center for Coastal and Ocean Mapping prior to arrival in Hawaii for field trails, Little Herc has now come full circle. Today, the beautiful images you are seeing are once again, Little Herc’s major contribution. Made possible by the generous support of our partners and engineers, Little Herc is back. Diving deeper, shining brighter and taking higher resolution imagery than ever before! And my thanks to everyone. 2020-01-21 18:12:55.0 [tstevens] insert Definition (id: null text: Little Hercules is a 4000m depth rated Remotely Operated Vehicle (ROV), with an impressive past and most promising future. “Little Herc”, as he is widely referred to is just that; “little”. But as we all know, many good things come in small packages. Little Herc came to the Okeanos Explorer through collaboration between NOAA’s Office of Ocean Exploration and Research and Dr. Robert Ballard’s Institute for Exploration (IFE) at the University of Rhode Island (URI). With a major commitment to explore the waters off Indonesia, our Program’s much larger ROV could not be readied in time for our 2010 sailing date. As a result, Little Herc was chosen as our stand-in. Originally developed by a team of engineers at IFE, Little Herc first came into the spotlight when he gave the world the first and only images of John Kennedy’s PT Boat; PT-109. After several other successful missions for IFE, Little Herc stepped down, taking a back seat to the now much larger and spectacular, “Hercules”. After doing a short stint as an exhibit piece in the Mystic Aquarium, a proposal by the NOAA Office of Ocean Exploration has given new life to the veteran “Explorer”. Through a Joint Project Agreement (JPA) between NOAA, IFE and URI, a team of engineers from several institutions and companies once again went to work, this time recommissioning Little Herc. In a field where technology advances rapidly, it was necessary and appropriate that Little Herc receive a substantial upgrade before joining the ship. After an extensive 4 month overhaul, Little Herc boasted a new motor controller and power bottle system, an upgraded fiber optic multiplexer system, a new Ultra Short Baseline Tracking System (USBL), a full color imaging sonar, a new Conductivity-Temperature-Depth (CTD) sensor, two new single chip color CCD cameras, two new LED lights, two 400watt HMI Lights and a spectacular High Definition video camera. New tethers, new tether terminations, a new transformer, a new electrical junction box, new depth and altitude sensors, a new light bar and a new version of control software to make it all work was in order. Tested at the University of New Hampshire’s Center for Coastal and Ocean Mapping prior to arrival in Hawaii for field trails, Little Herc has now come full circle. Today, the beautiful images you are seeing are once again, Little Herc’s major contribution. Made possible by the generous support of our partners and engineers, Little Herc is back. Diving deeper, shining brighter and taking higher resolution imagery than ever before! And my thanks to everyone. language code: en); 2020-01-21 17:26:43.0 [tstevens] Insert Concept add broader relation (Little Hercules [b3ef5a11-5c6d-4f14-a0bb-a90e8614a908,559743] - ROV [da6420b6-48ec-4ae2-98c7-0ef0538815a0,542741]); GEOS-4 2016-03-31 13:57:12.0 [saritz] insert AltLabel (id: null text: Goddard EOS Data Assimilation System-4 language code: en); 2016-03-31 13:54:06.0 [saritz] Insert Concept add broader relation (GEOS-4 [b42aa64a-6b63-4fd0-b953-4abf7558008c,158769] - Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215]); Beidou Compass The BeiDou Navigation Satellite System will provide global coverage with positioning, navigation and timing services, including two kinds of service modes: an open service and an authorized service. The open service is provided free of charge location, velocity and timing, with positioning accuracy of 10 meters, velocity accuracy of 0.2 meters / second and timing accuracy of 10 nanoseconds. The authorized service provides a more secure position, velocity, timing, and communications services as well as a higher level of integrity. In order to make BeiDou Navigation Satellite System work better for global service, strengthen compatibility and interoperability between BeiDou and other countries’satellite navigation systems,and promote satellite positioning, navigation and timing service application, China is willing to cooperate with other countries in developing satellite navigation industry. 2017-08-15 13:28:44.0 [tstevens] insert Definition (id: null text: The BeiDou Navigation Satellite System will provide global coverage with positioning, navigation and timing services, including two kinds of service modes: an open service and an authorized service. The open service is provided free of charge location, velocity and timing, with positioning accuracy of 10 meters, velocity accuracy of 0.2 meters / second and timing accuracy of 10 nanoseconds. The authorized service provides a more secure position, velocity, timing, and communications services as well as a higher level of integrity. In order to make BeiDou Navigation Satellite System work better for global service, strengthen compatibility and interoperability between BeiDou and other countries’satellite navigation systems,and promote satellite positioning, navigation and timing service application, China is willing to cooperate with other countries in developing satellite navigation industry. language code: en); 2017-08-14 19:26:01.0 [tstevens] insert AltLabel (id: null category: null text: Compass language code: en); 2017-08-14 19:22:22.0 [tstevens] insert AltLabel (id: null category: primary text: Beidou Satellites language code: en); 2017-08-14 19:22:02.0 [tstevens] Insert Concept add broader relation (Beidou [b4306421-a1b1-4d56-ad84-6f0c57806369,309907] - Beidou (China’s Satellite Navigation System) [ef679d6a-a05b-4976-a236-ce2158b758ea,309903]); MEGHA-TROPIQUES Introduction This mission was studied in France in the context of GEWEX (Global Energy and Water cycle Experiment). For understanding tropical meteorological and climatic processes, it appeared necessary to obtain reliable statistics on the water and energy budget of the tropical atmosphere and to describe the evolution of its systems (monsoons, cyclones, …) at appropriate time scales. In parallel, tropical atmospheric and oceanic missions were also studied in India, which is directly concerned by these phenomena. The first originality of MEGHA-TROPIQUES is to associate three radiometric instruments allowing to observe simultaneously three interrelated components of the atmospheric engine : water vapour, condensed water (clouds and precipitations), and radiative fluxes. The second is to privilege the sampling of the intertropical zone, accounting for the large time-space variability of the tropical phenomena. Moreover, the MEGHA-TROPIQUES microwave radiometer MADRAS could be one element complementing the constellation of mini-satellites of the Global Precipitation Mission . Scientific objectives - to improve the knowledge of the water cycle in the intertropical region, to evaluate its consequences on the energy budget, - to study the life cycle of tropical convective systems over ocean and continents, the environmental conditions for their appearance and evolution, their water budget, and the associated transports of water vapor. Applied objectives - to provide data about the processes leading to dramatic weather events affecting the Tropical countries, as hurricanes, systems producing heavy rainfalls, processes governing monsoons variability or droughts. Mission Scenario The key of this mission is the repetitivity of the measurement in the Tropics. The orbit of the platform must be in a low inclination on the equatorial plane. The altitude of the orbit has to be high enough to allow a wide swath of the instruments. Geophysical parameters to be retrieved: Atmospheric water cycle elements: Water vapor (integrated and vertical distribution), cloud condensed water content, ice/water, precipitation. Radiative budget elements: solar reflected and terrestrial emitted fluxes at the top of the atmosphere. Instrumental payload The instruments have to be complementary to what exists on geostationary satellites (VIS-IR imagers). Microwave instruments are then fundamental. The main payload instruments are: - A microwave imager (MADRAS) aimed mainly to study precipitation and cloud properties, including ice at the top of clouds (SSM/I type, with an additional channel at 157 GHz). - A microwave sounding instrument for the atmospheric water vapor (SAPHIR - 6 channels in the 183 GHz band). - A radiometer devoted to the measurement of outgoing radiative fluxes at the top of the atmosphere (ScaRaB). Group: Platform_Details Entry_ID: MEGHA-TROPIQUES Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: MEGHA-TROPIQUES End_Group Group: Platform_Associated_Instruments Short_Name: SAPHIR Short_Name: MADRAS Short_Name: SCARAB End_Group Group: Orbit Orbit_Altitude: 867 Orbit_Inclination: 20 Period: 102.16 minutes Orbit_Type: LEO > LOW EARTH ORBIT > INCLINED NON-POLAR End_Group Creation_Date: 2012-01-20 Online_Resource: http://meghatropiques.ipsl.polytechnique.fr/mission-description.html Sample_Image: http://upload.wikimedia.org/wikipedia/en/7/72/Megha_tropiques.jpg Group: Platform_Logistics Launch_Date: 2011-10-12 Launch_Site: SRIHARIKOTA ISLAND, INDIA Design_Life: 4 Primary_Sponsor: Indian Space Research Organisation (ISRO) Primary_Sponsor: Centre National d'Études Spatiales (CNES) End_Group End_Group PALACE FLOAT PALACE FLOATS measure profiles of ocean salinity and temperature. Measurements are made as the floats ascend to a drifting horizon. They do this by changing their buoyancy internally. Periodically, the floats rise to the surface, where the data is transmitted via satellite. Group: Platform_Details Entry_ID: PALACE FLOAT Group: Platform_Identification Platform_Category: In Situ Ocean-based Platforms Platform_Series_or_Entity: FLOATS Short_Name: PALACE FLOAT Long_Name: Profiling Autonomous Lagrangian Circulation Explorer End_Group Group: Synonymous_Platform_Names Short_Name: Palace Float End_Group Creation_Date: 2007-12-12 Online_Resource: http://hrp.whoi.edu/floats/spalace_overv.html Sample_Image: http://hrp.whoi.edu/floats/palace.gif End_Group NOAA-17 NOAA-17 (previously NOAA-M) was launched on June 24, 2002 from Vandenberg AFB, CA. NOAA-M POES (National Oceanic and Atmospheric Administration Polar-orbiting Operational Environmental Satellites) provides global coverage of numerous atmospheric and surface parameters for weather forecasting and meteorological research, as well as space environment monitors and an aircraft and maritime emergency beacon system. This is a reimbursable project for NOAA. NASA builds and launches the satellites. NOAA operates the satellites post commissioning and check-out period and uses the data in weather forecasts.??Energy forecasting, aviation safety, disaster management, public health, and air quality.??? Instruments include: * AMSU-B (Advanced Microwave Sounding Unit-B) * MHS (Microwave Humidity Sounder) * SBUV (Solar Backscatter Ultraviolet Radiometer) * DCS (Data Collection System) * S&R (Search and Rescue) * AVHRR (Advanced Very High Resolution Radiometer) * HIRS (High Resolution Infrared Radiometer Sounder) * AMSU-A (Advanced Microwave Sounding Unit-A) For more information, see: "http://poes.gsfc.nasa.gov/" Group: Platform_Details Entry_ID: NOAA-17 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NOAA POES (Polar Orbiting Environmental Satellites) Short_Name: NOAA-17 Long_Name: National Oceanic & Atmospheric Administration-17 End_Group Group: Synonymous_Platform_Names Short_Name: NOAA-M End_Group Group: Platform_Associated_Instruments Short_Name: AMSU-B Short_Name: AMSU-A End_Group Group: Orbit Orbit_Inclination: 98.7 deg Period: 101.2 min End_Group Creation_Date: 2007-11-08 Online_Resource: http://www.oso.noaa.gov/poesstatus/spacecraftStatusSummary.asp?spacecraft=17 Sample_Image: http://www.horizon.co.fk/images/weather/noaa-17-06220146-mcir-precip.jpg Group: Platform_Logistics Launch_Date: 2002-06-24 Primary_Sponsor: NASA End_Group End_Group Meteor-3 The Russian Meteor-3 series of meteorological satellites provides twice-daily weather information including data on clouds, ice and snow cover, atmospheric radiation and humidity sounding. The Meteor-3 class of satellites orbit in a higher altitude than the Meteor-2 class of satellites thus providing more complete coverage of the earth's surface. The Meteor-3 has the same payload as the Meteor-2 but also includes an advanced scanning radiometer with better spectral and spatial resolution and a spectrometer for determining total ozone content. The spacecraft incorporates three-axis stabilization (0.5 deg accuracy) and twin 10-m span solar panels. The orbit is adjusted by ion thrusters. Meteorological data is transmitted to four primary sites in the former Soviet Union in conjunction with about 80 other smaller sites. Internationally compatible Automatic Picture Transmission (APT) is made available on 137 - 138 MHz channels to ground workstations. The Meteor-3 has two 0.5 - 0.7 micron radiometers. The first provides direct relay with a swath width of 2600 km and a resolution of 1 x 2 km. The second stores data on an on-board data recorder providing global coverage with a swath width of 3100 km and a resolution of 0.7 x 1.4 km. The payload also includes a scanning IR radiometer at 10.5 - 12.5 microns with a swath width of 3100 km and resolution of 3 x 3 km and an 8-channel IR radiometer for atmospheric sounding at 9.65 - 18.7 micorns with a swath width of 2000 km and a resolution of 32 x 32 km. The Meteor-3 also includes a 4 channel UV ozone monitor (0.25 - 1.03 micron) at 2 km altitude resolution and a particle radiation detector (0.15 - 90 MeV). Group: Platform_Details Entry_ID: METEOR-3 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: METEOR Short_Name: METEOR-3 End_Group Group: Platform_Associated_Instruments Short_Name: TOMS Short_Name: PHOTOMETERS End_Group Creation_Date: 2007-10-11 Online_Resource: http://www.astronautix.com/craft/meteor3.htm Sample_Image: http://www.astronautix.com/graphics/m/meteor3e.jpg Group: Platform_Logistics Launch_Date: 1991-08-15 Launch_Site: Plesetsk Cosmodrome, Russia Design_Life: 2 Years Primary_Sponsor: Russia End_Group End_Group 2015-05-08 18:52:17.0 [saritz] update PrefLabel (Meteor-3); GOCE [Source: ESA GOCE Home page, http://www.esa.int/esaLP/ESAYEK1VMOC_LPgoce_0.html ] Launched on 17 March 2009 - End of mission 10 November 2013, ESA's Gravity field and steady-state Ocean Circulation Explorer (GOCE) was developed to bring about a whole new level of understanding of one of Earth's most fundamental forces of nature – the gravity field. Dubbed the 'Formula 1' of satellites, this sleek high-tech gravity satellite embodies many firsts in its design and use of new technology in space to map Earth's gravity field in unprecedented detail. As the most advanced gravity space mission to date, GOCE will realise a broad range of fascinating new possibilities for oceanography, solid Earth physics, geodesy and sea-level research, and significantly contribute to furthering our understanding of climate change. Although invisible, gravity is a complex force of nature that has an immeasurable impact on our everyday lives. It is often assumed that the force of gravity on the surface of the Earth has a constant value, but in fact the value of 'g' varies subtly from place to place. These variations are due to a number of factors such as the rotation of the Earth, the position of mountains and ocean trenches and variations in density of the Earth's interior. Over its life of about 20 months, GOCE will map these global variations in the gravity field with extreme detail and accuracy. This will result in a unique model of the 'geoid', which is the surface of equal gravitational potential defined by the gravity field – crucial for deriving accurate measurements of ocean circulation and sea-level change, both of which are affected by climate change. GOCE-derived data are also much needed to understand more about processes occurring inside the Earth and for use in practical applications such as surveying and levelling. Group: Platform_Details Entry_ID: GOCE Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: Earth Explorers Short_Name: GOCE Long_Name: Gravity Field and Steady-State Ocean Circulation Explorer End_Group Group: Platform_Associated_Instruments Short_Name: LRR Short_Name: EGG Short_Name: SSTI End_Group Group: Orbit Orbit_Altitude: 250 km (Hibernation 270 km) Orbit_Inclination: 96.7° Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2009-05-15 Online_Resource: http://www.esa.int/esaLP/LPgoce.html Online_Resource: http://ilrs.gsfc.nasa.gov/satellite_missions/list_of_satellites/goce_general.html Group: Platform_Logistics Launch_Date: 2009-03-17 Launch_Site: Plesetsk Cosmodrome, Russia Design_Life: 20 months Primary_Sponsor: ESA End_Group End_Group SPOT-6 TECHNICAL FEATURES With SPOT 6 and SPOT 7, Astrium not only secures mission continuity of the SPOT series, which has been collecting an archive of more than 30 million of scenes since 1986: this new generation of optical satellites also features technological improvements and advanced system performance that increase reactivity and acquisition capacity as well as simplifying data access. Space segment: SPOT 6 and SPOT 7 will provide 1.5metre resolution products over broad areas until 2024. Number of satellites 2 Launch periods SPOT 6: September 12th, 2012 SPOT 7: June 30th, 2014 Design lifetime 10 years Size Body: ~ 1.55 x 1.75 x 2.7 m Solar array wingspan 5,4 m2 Launch mass 712 kg Altitude 694 km Onboard Storage 1 Tbits end of life (Solid State Mass Memory) Orbital characteristics and viewing capability: SPOT 6 and SPOT 7 missions are designed to achieve efficiently both collection of large coverage and collection of individual targets that are possible thanks to the extreme agility of the satellite. Orbit Sun-synchronous; 10:00 AM local time at descending node Period 98.79 minutes Cycle 26 days Viewing angle Standard: +/- 30° in roll | Extended: +/- 45° in roll Revisit • 1 day with SPOT 6 and SPOT 7 operating simultaneously • Between 1 and 3 days with only one satellite in operation (note 1) Pointing agility Control Moment Gyroscopes allowing quick maneuvers in all directions for targeting several areas of interest on the same pass (30° in 14s, including stabilization time) Acquisition capacity Up to 6 million sq.km daily with SPOT 6 and SPOT 7 when operating simultaneously Nominal Imaging Mode 60km-swath strips oriented along North-South axis; up to 600km length Stereo capability Fore and aft mode; Single pass stereo and tri-stereo Note1: Depends on the latitude of the area of interest Instruments: Optical system One instrument made of 2 identical Korsch telescopes, each with a 200 mm aperture, delivering the expected swath. Detectors PAN array assembly: 28,000 pixels MS array assembly: 4 x 7000 pixels Spectral bands Panchromatic: 0.450-0.745 µm Blue: 0.450-0.520 µm Green: 0.530-0.590 µm Red: 0.625-0.695 µm Near Infrared: 0.760-0.890 µm The 5 bands are always acquired simultaneously. Swath 60km at nadir Dynamic range at acquisition 12 bits per pixel Location accuracy specification • 35m CE 90 without GCP within a 30° viewing angle cone • 10m CE90 for Ortho products where Reference3D is available Instrument telemetry link rate X-band channel - 300 Mbits/s Ground segment: Main receiving stations • Toulouse (France) • Kiruna (Sweden) S-Band uplink stations • Kiruna (Sweden) • Inuvik (Canada) Programming centre Astrium GEO-Information Service – Toulouse (France) Astrium GEO-Information Service – Chantilly VA (USA) Production centre Astrium GEO-Information Service – Toulouse (France) Tasking plans refresh frequency 6 times/day/satellite Update of weather forecast 4 times/day – fully automatic process Satellite control centre Astrium Satellite – Toulouse (France) 2018-02-20 09:55:51.0 [mmorahan] insert Definition (id: null text: TECHNICAL FEATURES With SPOT 6 and SPOT 7, Astrium not only secures mission continuity of the SPOT series, which has been collecting an archive of more than 30 million of scenes since 1986: this new generation of optical satellites also features technological improvements and advanced system performance that increase reactivity and acquisition capacity as well as simplifying data access. Space segment: SPOT 6 and SPOT 7 will provide 1.5metre resolution products over broad areas until 2024. Number of satellites 2 Launch periods SPOT 6: September 12th, 2012 SPOT 7: June 30th, 2014 Design lifetime 10 years Size Body: ~ 1.55 x 1.75 x 2.7 m Solar array wingspan 5,4 m2 Launch mass 712 kg Altitude 694 km Onboard Storage 1 Tbits end of life (Solid State Mass Memory) Orbital characteristics and viewing capability: SPOT 6 and SPOT 7 missions are designed to achieve efficiently both collection of large coverage and collection of individual targets that are possible thanks to the extreme agility of the satellite. Orbit Sun-synchronous; 10:00 AM local time at descending node Period 98.79 minutes Cycle 26 days Viewing angle Standard: +/- 30° in roll | Extended: +/- 45° in roll Revisit • 1 day with SPOT 6 and SPOT 7 operating simultaneously • Between 1 and 3 days with only one satellite in operation (note 1) Pointing agility Control Moment Gyroscopes allowing quick maneuvers in all directions for targeting several areas of interest on the same pass (30° in 14s, including stabilization time) Acquisition capacity Up to 6 million sq.km daily with SPOT 6 and SPOT 7 when operating simultaneously Nominal Imaging Mode 60km-swath strips oriented along North-South axis; up to 600km length Stereo capability Fore and aft mode; Single pass stereo and tri-stereo Note1: Depends on the latitude of the area of interest Instruments: Optical system One instrument made of 2 identical Korsch telescopes, each with a 200 mm aperture, delivering the expected swath. Detectors PAN array assembly: 28,000 pixels MS array assembly: 4 x 7000 pixels Spectral bands Panchromatic: 0.450-0.745 µm Blue: 0.450-0.520 µm Green: 0.530-0.590 µm Red: 0.625-0.695 µm Near Infrared: 0.760-0.890 µm The 5 bands are always acquired simultaneously. Swath 60km at nadir Dynamic range at acquisition 12 bits per pixel Location accuracy specification • 35m CE 90 without GCP within a 30° viewing angle cone • 10m CE90 for Ortho products where Reference3D is available Instrument telemetry link rate X-band channel - 300 Mbits/s Ground segment: Main receiving stations • Toulouse (France) • Kiruna (Sweden) S-Band uplink stations • Kiruna (Sweden) • Inuvik (Canada) Programming centre Astrium GEO-Information Service – Toulouse (France) Astrium GEO-Information Service – Chantilly VA (USA) Production centre Astrium GEO-Information Service – Toulouse (France) Tasking plans refresh frequency 6 times/day/satellite Update of weather forecast 4 times/day – fully automatic process Satellite control centre Astrium Satellite – Toulouse (France) language code: en); 2018-02-20 09:42:26.0 [mmorahan] insert AltLabel (id: null category: primary text: Systeme Probatoire Pour l'Observation de la Terre-6 language code: en); 2018-02-20 09:37:30.0 [mmorahan] Insert Concept add broader relation (SPOT-6 [b5b5a3c9-a393-4766-a7d6-ef6c97969e78,310579] - SPOT [5615d18d-4217-42a0-a53d-77298834fc2e,287827]); STPSat-3 STPSat-3 Mission: Launched from Wallops Flight Center Va., on Nov. 19, 2013 – three years to the day since STPSat-2 launched from Kodiak, Alaska. STPSat-3 is the primary satellite for the U.S. Air Force Operationally Responsive Space (ORS)-3 enabler mission. STPSat-3 was launched along with numerous28 CubeSats as part of the ORS-3 mission. The ORS-3 enabler mission is demonstrating, testing and verifying rapid response spacecraft technologies to decrease launch timelines and reduce mission costs. [Source: Ball Aerospace Home Page, http://www.ballaerospace.com/page.jsp?page=303 ] Group: Platform_Details Entry_ID: STPSat-3 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: STPSat-3 Long_Name: U.S. Air Force Space Test Program Satellite 3 End_Group Group: Synonymous_Platform_Names Short_Name: ORS-3 End_Group Group: Orbit Orbit_Altitude: 400 and 850 km altitude End_Group Creation_Date: 2015-03-01 Online_Resource: http://www.ballaerospace.com/page.jsp?page=303 Online_Resource: https://directory.eoportal.org/web/eoportal/satellite-missions/o/ors-3 Group: Platform_Logistics Launch_Date: 2013-11-19 Launch_Site: WALLOPS FLIGHT FACILITY, WALLOPS ISLAND, USA Primary_Sponsor: USA/DOD End_Group End_Group 2015-02-12 20:08:30.0 [saritz] update Definition (The ORS-3 mission is focused on breaking the constraining paradigms and procedures associated with the acquisition, coordination, range logistics, mission safety, technical management, and overall execution of an existing launch capability. 6) The launch will feature a primary payload, the STPSat-3 (Space Test Program Satellite-3) of the US Air Force SMC (Space and Missile Systems Center), and 27 additional experiments comprised of free-flying systems and non-separating components. ORS-3 will employ CubeSat wafers, which enable secondary payloads to take advantage of excess lift capacity unavailable to the primary trial. More Information: https://directory.eoportal.org/web/eoportal/satellite-missions/o/ors-3); 2015-02-12 20:07:26.0 [saritz] update Definition (The ORS-3 mission is focused on breaking the constraining paradigms and procedures associated with the acquisition, coordination, range logistics, mission safety, technical management, and overall execution of an existing launch capability. 6) The launch will feature a primary payload, the STPSat-3 (Space Test Program Satellite-3) of the US Air Force SMC (Space and Missile Systems Center), and 27 additional experiments comprised of free-flying systems and non-separating components. ORS-3 will employ CubeSat wafers, which enable secondary payloads to take advantage of excess lift capacity unavailable to the primary trial.); 2015-02-12 20:06:33.0 [saritz] insert Definition (id: null text: The ORS (Operationally Responsive Space) Office, a DoD program conceived to demonstrate space systems on leaner budgets and rapid schedules, is sponsoring the ORS-3 (Operationally Responsive Space) mission, which is planned to launch in 2013 from MARS (Mid-Atlantic Regional Spaceport), located at NASA's Wallops Flight Facility,Wallops Island, VA. language code: en); 2015-02-12 20:05:14.0 [saritz] insert AltLabel (id: null text: U.S. Air Force Space Test Program Satellite 3 language code: en); 2015-02-12 20:04:43.0 [saritz] Insert Concept add broader relation (STPSat-3 [b5e24e20-f99f-423f-83ac-d3eb5989ac48,106733] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,73425]); NOBM 2016-04-08 18:22:56.0 [saritz] S. Ritz added new model. Resquested by GES-DISC. insert AltLabel (id: null text: NASA Ocean Biogeochemical Model language code: en); 2016-04-08 18:21:59.0 [saritz] Insert Concept add broader relation (NOBM [b63e0078-74a3-431d-92f7-8853c10474e4,158897] - Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215]); CARTOSAT 2018-06-13 15:45:50.0 [mmorahan] Insert Concept add narrower relation (CARTOSAT [b65c6b10-a648-4a7c-9af1-71506ed9bb13,345679] - CARTOSAT-2 [71ccf8e3-7b1f-418d-9bc0-0ead78ec75ee,367711]); UARS Following the deployment of the Goddard Space Flight Center's (GSFC) Upper Atmosphere Research Satellite (UARS) on Sept. 15, 1991, from the Space Shuttle Discovery, scientists have gained a better understanding of the energy input, chemistry and dynamics of the upper atmosphere and the coupling between the upper and lower atmosphere. UARS, the first satellite dedicated to studying stratospheric science, focuses on the processes that lead to ozone depletion, complementing and amplifying the measurements of total ozone made by the Total Ozone Mapping Spectrometer (TOMS) onboard NASA's Nimbus-7 and the Russian Meteor-3 satellites. UARS also measures winds and temperatures in the stratosphere as well as the energy input from the Sun. Ten UARS instruments have provided the most complete data on upper atmospheric energy inputs, winds, and chemical composition ever gathered. Together, these observations constitute a highly integrated investigation of the nature of the upper atmosphere, and help define the role of the upper atmosphere in climate and climate variability. In its first two weeks of operation, UARS data confirmed the polar ozone-depletion theories by providing three-dimensional maps of ozone and chlorine monoxide near the South Pole during development of the 1991 ozone hole. UARS, developed and managed by GSFC, in Greenbelt, Md., provides information that nations around the world can use to guide decisions on environmental policies, according to scientists. Moreover, UARS collected data on the chemistry, dynamics, and radiative inputs to the upper atmosphere far beyond its designed lifetime, obtaining over 13 years of observations for many atmospheric constituents, temperature, winds, and external forcings. UARS was decommissioned in 2005. The United Kingdom and Canada both provided instruments for this mission. UARS is the first spacecraft launched as part of NASA's systematic, comprehensive study of the Earth system. Instruments: ISAMS (Improved Stratospheric and Mesospheric Sounder) MLS (Microwave Limb Sounder) HALOE (Halogen Occultation Experiment) HRDI (High Resolution Doppler Imager) WIND II (Wind Imaging Interferometer) SOLSTICE (Solar-stellar Irradiance Comparison Experiment) SUSIM (Solar Ultraviolet Spectral Irradiance Monitor) PEM (Particle Environment Monitor) ACRIM II (Active Cavity Radiometer Irradiance Monitor) CLAES (Cryogenic Limb Array Etalon Spectrometer) [Summary provided by NASA] Group: Platform_Details Entry_ID: UARS Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: UARS Long_Name: Upper Atmosphere Research Satellite End_Group Group: Platform_Associated_Instruments Short_Name: CLAES Short_Name: ISAMS Short_Name: MLS Short_Name: HALOE Short_Name: HRDI Short_Name: WINDII Short_Name: SOLSTICE Short_Name: SUSIM Short_Name: PEM Short_Name: ACRIM II End_Group Group: Orbit Orbit_Altitude: 585 km circular Orbit_Inclination: 57 deg Period: 96.7 min Perigee: 574 km (356 mi) Apogee: 582 km (361 mi) Orbit_Type: LEO > Low Earth Orbit > Polar Non-Sun-Synchronous End_Group Creation_Date: 2007-05-09 Online_Resource: http://umpgal.gsfc.nasa.gov/ Online_Resource: http://www.nasa.gov/mission_pages/uars/index.html Sample_Image: http://umpgal.gsfc.nasa.gov/uars-science/images/uars.jpg Group: Platform_Logistics Launch_Date: 1991-09-12 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Design_Life: 3 years Primary_Sponsor: NASA - Goddard Space Flight Center End_Group End_Group NOAA-19 [Source: NASA Portal, http://www.nasa.gov/mission_pages/NOAA-N-Prime/main/index.html ] The Delta II carrying NOAA-N Prime lifted off Feb. 6, 2009 at 2:22 a.m. Pacific time, 5:22 a.m. Eastern time from Space Launch Complex-2 at Vandenberg Air Force Base in California. [Image and Text Source: NOAA-N Prime Spacecraft web page, http://goespoes.gsfc.nasa.gov/poes/spacecraft/noaanprime_spacecraft.html ] NOAA-N Prime will be the last in the series of TIROS ATN. NOAA-N' has a planned launch date of February 2009 from Vandenberg AFB, CA by a Delta II launch vehicle. The spacecraft will continue to provide a polar-orbiting platform to support (1) environmental monitoring instruments for imaging and measuring the Earth's atmosphere, its surface, and cloud cover, including Earth radiation, atmospheric ozone, aerosol distribution, sea surface temperature, and vertical temperature and water profiles in the troposphere and stratosphere; (2) measurement of proton and electron flux at orbit altitude; (3) data collection from remote platforms; and (4) the Search and Rescue Satellite-Aided Tracking (SARSAT) system. Additionally, NOAA-N' will be the fifth in the series of support dedicated microwave instruments for the generation of temperature, moisture, surface, and hydrological products in cloudy regions where visible and infrared (IR) instruments have decreased capability. This spacecraft will carry an Advanced - DCS instead of the previous DCS. More Information: http://goespoes.gsfc.nasa.gov/poes/spacecraft/noaanprime_spacecraft.html Group: Platform_Details Entry_ID: NOAA-19 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NOAA POES (Polar Orbiting Environmental Satellites) Short_Name: NOAA-19 Long_Name: National Oceanic & Atmospheric Administration-19 End_Group Group: Platform_Associated_Instruments Short_Name: SARR Short_Name: SEM-2 Short_Name: SBUV/2 Short_Name: MHS Short_Name: HIRS/4 Short_Name: AVHRR-3 Short_Name: AMSU-A End_Group Group: Orbit Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2009-01-23 Online_Resource: http://goespoes.gsfc.nasa.gov/poes/index.html Online_Resource: http://www.osd.noaa.gov/POES/noaa_n_prime.htm Online_Resource: http://goespoes.gsfc.nasa.gov/poes/Goes_N_Prime.pdf Online_Resource: http://www2.ncdc.noaa.gov/docs/klm/nnpsupp.htm Online_Resource: http://www.nasa.gov/mission_pages/NOAA-N-Prime/main/index.html Sample_Image: http://goespoes.gsfc.nasa.gov/poes/gallery/N%20Prime/unpacking/Unpacking-5_800px.jpg Group: Platform_Logistics Launch_Date: 2009-02-06 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: USA/NASA Primary_Sponsor: USA/NOAA End_Group End_Group Jason II The remotely operated vehicle (ROV) Jason 2 is a robotic vehicle tethered to the ship by a fiber optic cable that is capable of working is water depths up to 6500 meters. This tether is only 2.1 cm in diameter and contains 3 copper conductors and 3 single-mode optical fibers. It is incredibly strong with a breaking strength of 18,600 kilograms. Jason is designed to conduct a diverse range of scientific investigations in the world's oceans. The ROV system also includes the vehicle Medea, which serves as a shock absorber and allows Jason to be decoupled from surface and ship motion. The fiber optic tether runs from the ship to Medea, and then down to Jason, to provide real-time communication to and from the vehicles. When Jason is in the water, it requires three people to operate it: a pilot (who operates the vehicle controls), an engineer (who monitors all of the systems and operates the winch that pays out/hauls in the fiber optic cable attached to Medea), and a navigator (who is responsible for positioning the ship so that the system operates in the desired locations). In addition to these three people during each 4-hour watch, 3 to 5 scientists will also be in the control van working with the Jason crew to accomplish the scientific goals of the cruise. 2020-01-21 17:56:24.0 [tstevens] insert Definition (id: null text: The remotely operated vehicle (ROV) Jason 2 is a robotic vehicle tethered to the ship by a fiber optic cable that is capable of working is water depths up to 6500 meters. This tether is only 2.1 cm in diameter and contains 3 copper conductors and 3 single-mode optical fibers. It is incredibly strong with a breaking strength of 18,600 kilograms. Jason is designed to conduct a diverse range of scientific investigations in the world's oceans. The ROV system also includes the vehicle Medea, which serves as a shock absorber and allows Jason to be decoupled from surface and ship motion. The fiber optic tether runs from the ship to Medea, and then down to Jason, to provide real-time communication to and from the vehicles. When Jason is in the water, it requires three people to operate it: a pilot (who operates the vehicle controls), an engineer (who monitors all of the systems and operates the winch that pays out/hauls in the fiber optic cable attached to Medea), and a navigator (who is responsible for positioning the ship so that the system operates in the desired locations). In addition to these three people during each 4-hour watch, 3 to 5 scientists will also be in the control van working with the Jason crew to accomplish the scientific goals of the cruise. language code: en); 2020-01-21 17:24:41.0 [tstevens] Insert Concept add broader relation (Jason II [b7831fc5-0da7-4c2a-b4d6-dae934648d95,559723] - ROV [da6420b6-48ec-4ae2-98c7-0ef0538815a0,542741]); GEOSAT OSO-4 The objectives of the OSO satellite series were to perform solar physics experiments above the atmosphere during a complete solar cycle and to map the celestial sphere for direction and intensity of UV light, X-rays, and gamma radiation. General Information: Designation: 03000 / 67100A Launch date: 18 Oct 1967 Country of origin: United States Mission: Scientific (Sun observation) Perigee/Apogee: 552/555 km Inclination: 32.9° Period: 95.7 min Launch vehicle: Thor Delta #53 Out of service: Dec 1971 Decay: 15 Jun 1982 Additional information available at "http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/oso4.html" [Summary provided by The Satellite Encyclopedia] Group: Platform_Details Entry_ID: OSO-4 Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Platform_Series_or_Entity: OSO (Orbiting Solar Observatory) Short_Name: OSO-4 Long_Name: Orbiting Solar Observatory-4 End_Group Group: Synonymous_Platform_Names Short_Name: OSO-4 End_Group Group: Platform_Associated_Instruments Short_Name: GAMMA RADIATION DETECTOR End_Group Group: Orbit Orbit_Inclination: 32.9 degrees Period: 95.7 min Perigee: 552 km Apogee: 555 km End_Group Creation_Date: 2007-12-14 Online_Resource: http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/oso4.html Sample_Image: http://heasarc.gsfc.nasa.gov/Images/oso/oso4.gif Group: Platform_Logistics Launch_Date: 1967-10-18 Primary_Sponsor: NASA End_Group End_Group OGO-1 The Orbiting Geophysical Observatory (OGO 1) was successfully launched from Cape Kennedy on 5 September 1964 and placed into an initial orbit of 281 x 149,385 km at 31 degrees inclination. Two experiment booms failed to properly deploy, with one of the booms obscuring a horizon scanner's view of earth. As a result, the spacecraft attitude could not be earth oriented and OGO 1 remained spin stabilized at 5 rpm. Nevertheless, data from all 20 experiments on board was received, although at a "less than expected capacity" from some of them. During September 1964, acceptable data were received over 70% of the orbital path. Spacecraft operation was restricted to Spring and Fall due to power supply limitations. There were 11 such 3-month periods prior to the spacecraft being put into stand-by mode on 25 November 1969. OGO 1 was completely terminated on 1 November 1971. On board was the Positron Search and Gamma-Ray Spectrum experiment of Cline et al. It was designed to determine whether low-energy (0-3 MeV) positrons are trapped temporarily or permanently in the Van Allen regions and whether low-energy solar and interplanetary positrons exist at the edge of the Earth's magnetic field. A secondary objective was to detect gamma-ray bursts from the Sun in the energy range 80 keV - 1 MeV. The experiment consisted of 3 CsI crystals surrounded by a plastic anti-coincidence shield. The output of the whole unit was monitored by 3 PMTs. Once every 18.5 seconds, integral intensity measurements were made in each of 16 energy channels which were equally spaced over the .08-1 MeV range. The experiment did not achieve its goals due to electrical interference and secular degradation of the PMT responses. However, searching back through the data after the discovery of cosmic gamma-ray bursts by the Vela satellites revealed the detection of one or more such events in the OGO 1 data. [Summary provided by NASA.] Group: Platform_Details Entry_ID: OGO-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: OGO (Orbiting Geophysical Observatory) Short_Name: OGO-1 Long_Name: Orbiting Geophysical Observatory-1 End_Group Group: Synonymous_Platform_Names Short_Name: EOGO 1 Short_Name: OGO-A Short_Name: 00879 End_Group Group: Platform_Associated_Instruments Short_Name: SPECTROMETERS Short_Name: MAGNETOMETERS End_Group Group: Orbit Orbit_Inclination: 31.2 degrees Period: 3839.0 minutes Perigee: 281.0 km Apogee: 149385.0 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-02-12 Online_Resource: http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1964-054A Online_Resource: http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/ogo.html#ogo1 Sample_Image: http://heasarc.gsfc.nasa.gov/Images/ogo/ogo.gif Group: Platform_Logistics Launch_Date: 1964-09-05 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: NASA End_Group End_Group NOAA-6 NOAA-6 was launched in June 1979 and was a third generation operational meteorological satellite for use in the National Operational Environmental Satellite System (NOESS) and for the support of the Global Atmospheric Research Program (GARP) during 1978-84. The satellite design provided an economical and stable sun-synchronous platform for advanced operational instruments to measure the earth's atmosphere, its surface and cloud cover, and the near-space environment. The satellite was based upon the Block 5D spacecraft bus developed for the U.S. Air Force, and it was capable of maintaining an earth-pointing accuracy of better than plus or minus 0.1 degree with a motion rate of less than 0.035 degree/second. Primary sensors included an Advanced Very High Resolution Radiometer (AVHRR) and a TIROS Operational Vertical Sounder (TOVS). Secondary experiments consisted of a Space Environment Monitor (SEM) and a Data Collection and Platform Location System (DCPLS). In early 1984, only one to two NOAA-6 passes were taken per day due to priorities for NOAA-7 and 8 data. However, when NOAA-8 failed in late June 1984, NOAA-6 was returned to full operational status to continue to provide morning orbit operational data. __________ Taken from the NSSDC System for Information Retrieval and Storage (SIRS). For more information contact the NSSDC Coordinated Request and User Support Office, 301-286-6695 (NASA Goddard Space Flight Center, Code 933.4, Greenbelt, Maryland 20771, USA, "http://nssdc.gsfc.nasa.gov/"). Group: Platform_Details Entry_ID: NOAA-6 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NOAA POES (Polar Orbiting Environmental Satellites) Short_Name: NOAA-6 Long_Name: National Oceanic & Atmospheric Administration-6 End_Group Group: Synonymous_Platform_Names Short_Name: NOAA-N End_Group Group: Platform_Associated_Instruments Short_Name: SEM Short_Name: AVHRR Short_Name: TOVS End_Group Group: Orbit Orbit_Inclination: 98.6 deg Period: 92.6 min Perigee: 382 km Apogee: 425 km End_Group Creation_Date: 2007-11-09 Online_Resource: http://nssdc.gsfc.nasa.gov/ Sample_Image: http://www.siloworld.com/MISSILE%20%20LAUNCHES/VAFB/SLC-3/19790627_025F_0568.JPG Group: Platform_Logistics Launch_Date: 1979-06-27 Primary_Sponsor: NASA End_Group End_Group DMSP 5D-2/F7 [Source: National Space Science Data Center, http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1983-113A ] DMSP 5D-2/F7 was one of a series of meteorological satellites developed and operated by the Air Force under the Defense Meteorological Satellite Program (DMSP). This program, previously known as DAPP (Data Acquisition and Processing Program), was classified until March 1973. The objective of this program was to provide global visual and infrared cloudcover data and specialized environmental data to support Department of Defense requirements. Operationally, the program consisted of two satellites in planned 830-km, sun-synchronous polar orbits, with the ascending node of one satellite in early morning and the other one at local noon. The 6.4-m-long spacecraft was divided into four sections: (1) a precision mounting platform for sensors and equipment requiring precise alignment; (2) an equipment support module containing the electronics, reaction wheels, and some meteorological sensors; (3) a reaction control equipment support structure containing the third-stage rocket motor and supporting the ascent phase reaction control equipment; and (4) a 9.29-sq-m solar cell panel. The spacecraft stabilization was controlled by a combination flywheel and magnetic control coil system so sensors were maintained in the desired "earth-looking" mode. One feature was the precision-pointing accuracy of the primary imager to 0.01 deg provided by a star sensor and an updated ephemeris navigation system. This allowed automatic geographical mapping of the digital imagery to the nearest picture element. The operational linescan system was the primary data acquisition system that provided real-time or stored, multi-orbit, day-and-night, visual and infrared imagery of the clouds. A supplementary sensor package contained six special sensors: (1) a microwave temperature sounder, (2) an X-ray spectrometer, (3) an ionospheric plasma monitor, (4) a precipitating electron/ion spectrometer, (5) a magnetometer, and (6) a space radiation dosimeter. Either recorded or real-time data were transmitted to ground-receiving sites by two redundant S-band transmitters. Recorded data were read out to tracking sites located at Fairchild AFB, Washington, and at Loring AFB, Maine, and relayed by SATCOM to Air Force Global Weather Central, Offutt AFB, Nebraska. Real-time data were read out at mobile tactical sites located around the world. A more complete description of the satellite can be found in the report by D. A. Nichols, "The Defense Meteorological Satellite Program," Optical Engineering, v. 14, n. 4, July-August 1975. Group: Platform_Details Entry_ID: DMSP 5D-2/F7 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: DMSP (Defense Meteorological Satellite Program) Short_Name: DMSP 5D-2/F7 Long_Name: Defense Meteorological Satellite Program-F7 End_Group Group: Synonymous_Platform_Names Short_Name: DMSP-F7 Short_Name: 14506 End_Group Group: Platform_Associated_Instruments Short_Name: SPACE RADIATION DOSIMETER Short_Name: SSM Short_Name: SSJ/4 Short_Name: SSI/E Short_Name: OLS Short_Name: SSB/S Short_Name: SSM/T End_Group Group: Orbit Orbit_Inclination: 98.7° Period: 101.3 minutes Perigee: 810.0 km Apogee: 829.0 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1983-113A Online_Resource: http://www.ngdc.noaa.gov/dmsp/index.html Online_Resource: http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/dmsp.html Group: Platform_Logistics Launch_Date: 1983-11-18 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: Department of Defense-Department of the Air Force (United States) End_Group End_Group ASOS The Automated Surface Observing Systems (ASOS) program is a joint effort of the National Weather Service (NWS), the Federal Aviation Administration (FAA), and the Department of Defense (DOD). The ASOS systems serves as the nation's primary surface weather observing network. ASOS is designed to support weather forecast activities and aviation operations and, at the same time, support the needs of the meteorological, hydrological, and climatological research communities. With the largest and most modern complement of weather sensors, ASOS has significantly expanded the information available to forecasters and the aviation community. The ASOS network has more than doubled the number of full-time surface weather observing locations. ASOS works non-stop, updating observations every minute, 24 hours a day, every day of the year. Elements Reported: 1. Sky condition:cloud height and amount (clear, scattered, broken, overcast) up to 12,000 feet 2. Visibility (to at least 10 statute miles) 3. Basic present weather information: type and intensity for rain, snow, and freezing rain 4. Obstructions to vision: fog, haze 5. Pressure: sea-level pressure, altimeter setting 6. Ambient temperature, dew point temperature 7. Wind: direction, speed and character (gusts, squalls) 8. Precipitation accumulation 9. Selected significant remarks including- variable cloud height, variable visibility, precipitation beginning/ending times, rapid pressure changes, pressure change tendency, wind shift, peak wind [Source: National Weather Service] Group: Platform_Details Entry_ID: ASOS Group: Platform_Identification Platform_Category: In Situ Land-based Platforms Platform_Series_or_Entity: WEATHER STATIONS/NETWORKS Short_Name: ASOS Long_Name: Automated Surface Observing System End_Group Group: Synonymous_Platform_Names Short_Name: ASOS End_Group Creation_Date: 2007-12-10 Online_Resource: http://cimss.ssec.wisc.edu/goes/asos/asos.html Sample_Image: http://www.crh.noaa.gov/ilx/images/asos.jpg End_Group LANDSAT-6 October 5, 1993 (did not achieve orbit) Participants NASA National Oceanic and Atmospheric Administration (NOAA) Department of the Interior (DOI) U.S. Geological Survey (USGS) Spacecraft bus: Lockheed Martin Missiles & Space Enhanced Thematic Mapper (ETM): Hughes Santa Barbara Research Center Launch Date: October 5, 1993 Vehicle: Titan II Launched by: NASA Site: Western Test Range at Vandenberg Air Force Base, California Spacecraft Power provided by a single sun-tracking solar array and two 50 Ampere-Hour (AHr), Nickel Cadmium (NiCd) batteries Attitude control provided through four reaction wheels (pitch, yaw, roll, and skew); three 2-channel gyros with celestial drift updating; a static Earth sensor; a 1750 processor; and torque rods and magnetometers for momentum uploading Orbit control and backup momentum unloading provided through a blow-down monopropellant hydrazine system with a single tank containing 270 pounds of hydrazine, associated plumbing, and twelve 1-pound-thrust jets Weight: approx. 4,800 lbs (2,200 kg) Length: 4.3 m (14 ft) Diameter: 2.8 m (9 ft) Communications Direct downlink with solid state recorders capable of storing 380 gigabits of data (100 scenes) Data rate: 85 Mbps Orbit (if obtained) Worldwide Reference System-2 (WRS-2) path/row system Sun-synchronous orbit at an altitude of 705 km (438 mi) Inclined 98.2° (slightly retrograde) Repeat cycle: 16 days Equatorial crossing time: 10:00 a.m. +/- 15 minutes https://www.usgs.gov/land-resources/nli/landsat/landsat-6 https://landsat.gsfc.nasa.gov/landsat-6/ 2019-12-31 21:45:31.0 [sritz] update Definition (October 5, 1993 (did not achieve orbit) Participants NASA National Oceanic and Atmospheric Administration (NOAA) Department of the Interior (DOI) U.S. Geological Survey (USGS) Spacecraft bus: Lockheed Martin Missiles & Space Enhanced Thematic Mapper (ETM): Hughes Santa Barbara Research Center Launch Date: October 5, 1993 Vehicle: Titan II Launched by: NASA Site: Western Test Range at Vandenberg Air Force Base, California Spacecraft Power provided by a single sun-tracking solar array and two 50 Ampere-Hour (AHr), Nickel Cadmium (NiCd) batteries Attitude control provided through four reaction wheels (pitch, yaw, roll, and skew); three 2-channel gyros with celestial drift updating; a static Earth sensor; a 1750 processor; and torque rods and magnetometers for momentum uploading Orbit control and backup momentum unloading provided through a blow-down monopropellant hydrazine system with a single tank containing 270 pounds of hydrazine, associated plumbing, and twelve 1-pound-thrust jets Weight: approx. 4,800 lbs (2,200 kg) Length: 4.3 m (14 ft) Diameter: 2.8 m (9 ft) Communications Direct downlink with solid state recorders capable of storing 380 gigabits of data (100 scenes) Data rate: 85 Mbps Orbit (if obtained) Worldwide Reference System-2 (WRS-2) path/row system Sun-synchronous orbit at an altitude of 705 km (438 mi) Inclined 98.2° (slightly retrograde) Repeat cycle: 16 days Equatorial crossing time: 10:00 a.m. +/- 15 minutes https://www.usgs.gov/land-resources/nli/landsat/landsat-6 https://landsat.gsfc.nasa.gov/landsat-6/); update Definition (https://www.usgs.gov/land-resources/nli/landsat/landsat-6 https://landsat.gsfc.nasa.gov/landsat-6/); 2018-06-12 17:01:51.0 [mmorahan] insert Definition (id: null text: October 5, 1993 (did not achieve orbit) Participants NASA National Oceanic and Atmospheric Administration (NOAA) Department of the Interior (DOI) U.S. Geological Survey (USGS) Spacecraft bus: Lockheed Martin Missiles & Space Enhanced Thematic Mapper (ETM): Hughes Santa Barbara Research Center Launch Date: October 5, 1993 Vehicle: Titan II Launched by: NASA Site: Western Test Range at Vandenberg Air Force Base, California Spacecraft Power provided by a single sun-tracking solar array and two 50 Ampere-Hour (AHr), Nickel Cadmium (NiCd) batteries Attitude control provided through four reaction wheels (pitch, yaw, roll, and skew); three 2-channel gyros with celestial drift updating; a static Earth sensor; a 1750 processor; and torque rods and magnetometers for momentum uploading Orbit control and backup momentum unloading provided through a blow-down monopropellant hydrazine system with a single tank containing 270 pounds of hydrazine, associated plumbing, and twelve 1-pound-thrust jets Weight: approx. 4,800 lbs (2,200 kg) Length: 4.3 m (14 ft) Diameter: 2.8 m (9 ft) Communications Direct downlink with solid state recorders capable of storing 380 gigabits of data (100 scenes) Data rate: 85 Mbps Orbit (if obtained) Worldwide Reference System-2 (WRS-2) path/row system Sun-synchronous orbit at an altitude of 705 km (438 mi) Inclined 98.2° (slightly retrograde) Repeat cycle: 16 days Equatorial crossing time: 10:00 a.m. +/- 15 minutes language code: en); 2018-06-12 16:53:34.0 [mmorahan] Insert Concept add broader relation (LANDSAT-6 [b912164c-36a5-4d93-9638-1afb3e4c4354,367683] - LANDSAT [3cc4a1e8-3b94-4567-90b3-32137aec2d9e,344819]); STS-64 The STS-64 mission will carry the LIDAR In-Space Technology Experiment (LITE), a project to measure atmospheric parameters from a space platform utilizing laser sensors, the Robot Operated Materials Processing System (ROMPS) to investigate robot handling of thin film samples, and the Shuttle Pointed Autonomous Research Tool for Astronomy (SPARTAN-201). SPARTAN is a free-flying retrievable platform with two telescopes to study the solar wind, a continuous stream of electrons, heavy protons and heavy ions ejected from the sun and traveling through space at speeds of almost 1 million miles per hour. The solar wind frequently causes problems on Earth by disrupting navigation, communications and electrical power. The STS-64 mission will also carry the Shuttle Plume Impingement Flight Experiment (SPIFEX). This experiment is designed to directly measure RCS plume loads in the far-field regime under actual on-orbit conditions. Discovery's payload bay also contains a GAS bridge assembly with 12 GAS canisters (G-178, G-254, G-312, G-325, G-417, G-453, G-454, G-456, G-485, G-506 and G-562). One additional experiment in the payload bay is the Trajectory Control Sensor (TCS) package positioned on an Adaptive Payload Carrier. It will provide relative trajectory data on a target vehicle operating in close proximity (less than 5000ft) of the Orbiter. The TCS will provide range and range rate data for target vehicles having a reflective surface. Additionally, the TCS provides bearing, bearing rate, attitude, and attitude rates for target vehicles utilizing special retro-reflectors. In Discovery's middeck area, STS-64 will carry the Simplified Aid for EVA Rescue (SAFER) system, the Solid Surface Combustion Experiment (SSCE), the Biological Research in Canister III (BRIC-III) experiment, the Radiation Monitoring Equipment III (RME-III) experiment. Other experiments onboard STS-64 include Military Application of Ship Trails (MAST), Shuttle Amateur Radio Experiment-II (SAREX-II) and Air Force Maui Optical Site Calibration Test (AMOS). [Summary provided by NASA] Group: Platform_Details Entry_ID: STS-64 Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Platform_Series_or_Entity: SPACE SHUTTLE Short_Name: STS-64 Long_Name: Space Transport System STS-64 End_Group Group: Synonymous_Platform_Names Short_Name: Discovery End_Group Group: Orbit Orbit_Altitude: 140 nm Orbit_Inclination: 57 degrees End_Group Creation_Date: 2008-01-30 Online_Resource: http://science.ksc.nasa.gov/shuttle/missions/sts-64/mission-sts-64.html Sample_Image: http://www.nasa.gov/images/content/134500main_sts-64-crew-sm.jpg Group: Platform_Logistics Launch_Date: 1994-09-09 Primary_Sponsor: NASA End_Group End_Group RADARSAT-2 The RADARSAT-2 satellite incorporates state-of-the-art technology and features the most advanced commercially available radar imagery in the world. The RADARSAT-2 program ensures the continuation of the original RADARSAT program and the development of Canada's Earth Observation business sector. RADARSAT-2 is a unique cooperation between the Canadian Space Agency (CSA) and MacDonald Dettwiler. The CSA is providing approximately 75% of the funding for the development of the satellite and MacDonald Dettwiler is investing the difference. MacDonald Dettwiler will own and operate the satellite and the CSA's investment will be recovered through the supply of imagery to a number of government agencies during the mission lifetime. The design of RADARSAT-2 has been driven by the needs of the emerging Earth Observation market, to provide users around the world with high-quality data products. RADARSAT-2 will be capable of imaging at spatial resolutions ranging from 3 to 100 meters with swath widths ranging from 20 to 500 kilometres. RADARSAT-2 is also the first commercial radar satellite to offer multi-polarization capability that aids in identifying a wide variety of surface features and targets. The satellite is scheduled for launch in 2005 and has a design life of 7 years. RADARSAT-2 is a truly world-class mission and the next step in MacDonald Dettwiler's goal to being a world-leading company in the delivery of a broad range of information products and services to manage the scope of human activities on our planet. Orbit Characteristics: Altitude (average): 798 km Inclination: 98.6° Period: 100.7 minutes Ascending Node: 18:00 hrs Sun-synchronous: 14 orbits per day Repeat Cycle: 24 days Additional information available at: http://www.radarsat2.info/ [Summary provided by MacDonald Dettwiler.] Group: Platform_Details Entry_ID: RADARSAT-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: RADARSAT Short_Name: RADARSAT-2 End_Group Group: Synonymous_Platform_Names Short_Name: RADARSAT-2 End_Group Group: Orbit Orbit_Altitude: 798 km Orbit_Inclination: 98.6 deg Period: 100.7 Repeat_Cycle: 24 days End_Group Creation_Date: 2007-11-13 Online_Resource: http://www.radarsat2.info/ Group: Platform_Logistics Launch_Date: 2007-12-08 Primary_Sponsor: Canada/CSA Primary_Sponsor: Canada/MDA End_Group End_Group STS-59 Scientists around the world will be provided a unique vantage point for studying how the Earth's global environment is changing when Space Shuttle Endeavour is launched on Shuttle mission STS-59. During the 9-day mission, the Space Radar Laboratory (SRL) payload in Endeavour's cargo bay will give scientists highly detailed information that will help them distinguish human-induced environmental changes from other natural forms of change. The Space Radar Laboratory (SRL) payload is comprised of the Spaceborne Imaging Radar-C/X-Band Synthetic Aperture Radar (SIR-C/X-SAR) and the Measurement of Air Pollution from Satellite (MAPS). The German Space Agency (DARA) and the Italian Space Agency (ASI) are providing the X-SAR instrument. The imaging radar of the SIR-C/X-SAR instruments have the ability to make measurements over virtually any region at any time, regardless of weather or sunlight conditions. The radar waves can penetrate clouds, and under certain conditions, can also "see" through vegetation, ice and extremely dry sand. In many cases, radar is the only way scientists can explore inaccessible regions of the Earth's surface. [Summary provided by NASA] Group: Platform_Details Entry_ID: STS-59 Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Platform_Series_or_Entity: SPACE SHUTTLE Short_Name: STS-59 Long_Name: Space Transport System STS-59 End_Group Group: Synonymous_Platform_Names Short_Name: Endeavour End_Group Group: Orbit Orbit_Altitude: 121nm Orbit_Inclination: 57 degrees End_Group Creation_Date: 2008-01-30 Online_Resource: http://science.ksc.nasa.gov/shuttle/missions/sts-59/mission-sts-59.html Sample_Image: http://www.nasa.gov/images/content/136249main_sts-59-crew-sm.jpg Group: Platform_Logistics Launch_Date: 1994-04-09 Primary_Sponsor: NASA End_Group End_Group A340-600 [Source: Wikipedia, http://en.wikipedia.org/wiki/Airbus_A340 ]. Designed as an early generation 747 replacement, the A340-600 flies 380 passengers in a three-class cabin layout (419 in 2 class) over 7,500 nautical miles (13,900 km). It provides similar passenger capacity to a 747 but with 25% more cargo volume, and at lower trip and seat costs. First flight of the A340-600 was made on 23 April 2001. Virgin Atlantic began commercial services in August 2002. The A340-600 is more than 10 m longer than a basic -300, making it the longest airliner currently in production; more than four metres longer than the Boeing 747-400. The Airbus A340-600 will continue to hold the record for being the worlds longest commercial aircraft until the first Boeing 747-8 Intercontinental is rolled out in 2010. It is powered by four 56,000 lbf (249 kN) thrust Rolls-Royce Trent 556 turbofans. It also has an additional four-wheel undercarriage on the fuselage center-line to cope with the increased MTOW. Airbus has made provisions for freeing additional upper deck main cabin space, by providing optional arrangements for additional facilities such as crew rest areas, galleys, and lavatories upon the "stretched" A340 aircraft's lower decks. Group: Platform_Details Entry_ID: A340-600 Group: Platform_Identification Platform_Category: Aircraft Short_Name: A340-600 Long_Name: Airbus A340-600 End_Group Creation_Date: 2009-05-14 Online_Resource: http://www.airbus.com/en/aircraftfamilies/a330a340/a340-600/ Online_Resource: http://www.airbus.com/en/aircraftfamilies/a330a340/a340-600/specifications.html Online_Resource: http://en.wikipedia.org/wiki/Airbus_A340 Group: Platform_Logistics Primary_Sponsor: Airbus End_Group End_Group 2017-06-27 16:23:58.0 [tstevens] update Definition ([Source: Wikipedia, http://en.wikipedia.org/wiki/Airbus_A340 ]. Designed as an early generation 747 replacement, the A340-600 flies 380 passengers in a three-class cabin layout (419 in 2 class) over 7,500 nautical miles (13,900 km). It provides similar passenger capacity to a 747 but with 25% more cargo volume, and at lower trip and seat costs. First flight of the A340-600 was made on 23 April 2001. Virgin Atlantic began commercial services in August 2002. The A340-600 is more than 10 m longer than a basic -300, making it the longest airliner currently in production; more than four metres longer than the Boeing 747-400. The Airbus A340-600 will continue to hold the record for being the worlds longest commercial aircraft until the first Boeing 747-8 Intercontinental is rolled out in 2010. It is powered by four 56,000 lbf (249 kN) thrust Rolls-Royce Trent 556 turbofans. It also has an additional four-wheel undercarriage on the fuselage center-line to cope with the increased MTOW. Airbus has made provisions for freeing additional upper deck main cabin space, by providing optional arrangements for additional facilities such as crew rest areas, galleys, and lavatories upon the "stretched" A340 aircraft's lower decks. Group: Platform_Details Entry_ID: A340-600 Group: Platform_Identification Platform_Category: Aircraft Short_Name: A340-600 Long_Name: Airbus A340-600 End_Group Creation_Date: 2009-05-14 Online_Resource: http://www.airbus.com/en/aircraftfamilies/a330a340/a340-600/ Online_Resource: http://www.airbus.com/en/aircraftfamilies/a330a340/a340-600/specifications.html Online_Resource: http://en.wikipedia.org/wiki/Airbus_A340 Group: Platform_Logistics Primary_Sponsor: Airbus End_Group End_Group); CORIOLIS The Coriolis satellite is a Naval Research Laboratory and Air Force Research Laboratory earth and space observation satellite launched from Vandenberg Air Force Base, on 2003-01-06 at 14:19 GMT. Instruments: Windsat: WINDSAT is a joint Integrated Program Office/Department of Defense demonstration project, intended to measure ocean surface wind speed and wind direction from space using a polarimetric radiometer. Solar Mass Ejection Imager (SMEI: The Solar Mass Ejection Imager (SMEI) is an instrument intended to detect disturbances in the solar wind by means of imaging scattered light from the free electrons in the plasma of the solar wind. To do this three CCD cameras observe sections of the sky of size 60 by 3 degree. As the SMEI instrument observers the whole sky, data generated has been used to observe periodic changes in the brightness of stars. This data be used to detect asteroseismological oscillation in giant stars, and for the detection of large eclipsing extra-solar planets. Group: Platform_Details Entry_ID: Coriolis Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: Coriolis End_Group Group: Platform_Associated_Instruments Short_Name: WINDSAT End_Group Group: Orbit Orbit_Inclination: 98.7 Period: 101.6 Perigee: 842 Apogee: 822 Orbit_Type: LEO > LOW EARTH ORBIT > POLAR SUN-SYNCHRONOUS End_Group Creation_Date: 2013-01-09 Group: Platform_Logistics Launch_Date: 2003-01-06 Launch_Site: VANDENBERG AIR FORCE BASE, USA Primary_Sponsor: Naval Research Laboratory Primary_Sponsor: Air Force Research Laboratory End_Group End_Group 2013-06-27 16:36:03.0 [saritz] Updated Primary Alternate label at GES-DISC Direction. update AltLabel (Coriolis); 2013-06-27 15:34:23.0 [saritz] Added long name at GES-DISC Direction insert AltLabel (id: null text: NRL and NPOESS Integrated Program Office (IPO), Coriolis language code: en); 2013-06-27 15:32:30.0 [saritz] Uppercased Preferred Label update PrefLabel (CORIOLIS); 2013-01-09 14:32:48.0 [mpmorahan] Insert Concept add broader relation (Coriolis [bac2e743-1d02-4868-8bd6-b8b8741e3794,82059] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,73425]); GOCART 2014-06-13 13:44:46.0 [tbs1979] insert AltLabel (id: null text: Goddard Chemistry Aerosol Radiation and Transport Model language code: en); 2014-06-13 13:44:18.0 [tbs1979] Insert Concept add broader relation (GOCART [bacbb5ad-9269-48ce-8da2-c22d73b9a5f2,106473] - Models [113ecbc2-ab36-4d58-a96c-a6ce0106e749,73395]); IRNSS (India's Regional Navigation Satellite System) IRNSS is an independent regional navigation satellite system being developed by India. It is designed to provide accurate position information service to users in India as well as the region extending up to 1500 km from its boundary, which is its primary service area. An Extended Service Area lies between primary service area and area enclosed by the rectangle from Latitude 30 deg South to 50 deg North, Longitude 30 deg East to 130 deg East. IRNSS will provide two types of services, namely, Standard Positioning Service (SPS) which is provided to all the users and Restricted Service (RS), which is an encrypted service provided only to the authorised users. The IRNSS System is expected to provide a position accuracy of better than 20 m in the primary service area. 2017-08-15 13:31:18.0 [tstevens] insert Definition (id: null text: IRNSS is an independent regional navigation satellite system being developed by India. It is designed to provide accurate position information service to users in India as well as the region extending up to 1500 km from its boundary, which is its primary service area. An Extended Service Area lies between primary service area and area enclosed by the rectangle from Latitude 30 deg South to 50 deg North, Longitude 30 deg East to 130 deg East. IRNSS will provide two types of services, namely, Standard Positioning Service (SPS) which is provided to all the users and Restricted Service (RS), which is an encrypted service provided only to the authorised users. The IRNSS System is expected to provide a position accuracy of better than 20 m in the primary service area. language code: en); 2017-08-15 11:34:37.0 [tstevens] update PrefLabel (IRNSS (India's Regional Navigation Satellite System)); 2017-08-14 19:23:59.0 [tstevens] Insert Concept add narrower relation (IRNSS (India’s Regional Navigation Satellite System) [bad22a08-f8ab-49b3-b266-005b21496626,309919] - IRNSS [4c93cc0b-ca0e-4421-ac60-559b6390b89b,309923]); 2017-08-14 19:23:49.0 [tstevens] Insert Concept add broader relation (IRNSS (India’s Regional Navigation Satellite System) [bad22a08-f8ab-49b3-b266-005b21496626,309919] - Navigation Platforms [1506fb17-7ac4-44ce-bde5-074885bdb2d2,287403]); OBSERVATION BASED 2015-11-30 22:45:06.0 [saritz] insert AltLabel (id: null text: OBSERVATION BASED ANALYSES language code: en); update PrefLabel (OBSERVATION BASED); 2015-11-24 18:06:57.0 [epneff] Rename Concept update PrefLabel (OBSERVATION BASED ANALYSES); 2015-11-24 18:04:57.0 [epneff] Insert Concept add broader relation (Observation Based Analyses [bb5002a8-6ff2-43dd-b0c9-8f9a76e11cb5,158503] - Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215]); R/V HERITAGE 2012-07-14 00:44:39.0 [aaleman] Insert Concept add broader relation (R/V HERITAGE [bbb476e8-9e6a-461f-882d-a213213705f2,40339] - SHIPS [82a67b12-e99d-4c90-8a6a-a6f79d4c3c7b,31201]); R/V LL The R/V Lady Lisa is a 75’ St. Augustine Trawler. Built in 1980, she is powered by a 415 HP, 12 cylinder Caterpillar Engine and is capable of towing two 80’ trawls. The vessel has accommodations for 3 crew members and 8 scientists, including a complete head and shower, as well as dry storage space for gear and cold storage space for samples. The R/V Lady Lisa is the primary sampling platform for several state and federal projects, working mostly in near coastal waters between Cape Hatteras, NC and Cape Canaveral, Florida. Group: Platform_Details Entry_ID: R/V LL Group: Platform_Identification Platform_Category: In Situ Ocean-based Platforms Platform_Series_or_Entity: SHIPS Short_Name: R/V LL Long_Name: R/V LADY LISA End_Group Creation_Date: 2012-07-23 Online_Resource: http://www.dnr.sc.gov/marine/mrri/vessels/ladylisa.html Sample_Image: http://www.dnr.sc.gov/marine/mrri/vessels/images/rvladylisa.jpg End_Group METEOSAT-11 Meteosat-11 is the prime operational geostationary satellite, positioned at 0 degrees and providing full disc imagery every 15 minutes. It also provides Search and Rescue monitoring and Data Collection Platform relay service. 2018-07-27 21:00:22.0 [sritz] insert Definition (id: null text: Meteosat-11 is the prime operational geostationary satellite, positioned at 0 degrees and providing full disc imagery every 15 minutes. It also provides Search and Rescue monitoring and Data Collection Platform relay service. language code: en); 2018-07-27 20:53:32.0 [sritz] Insert Concept add broader relation (METEOSAT-11 [bc69ef64-c468-4e8a-9a41-3b421e79cc90,368007] - METEOSAT [28eac19a-5500-4a21-af30-ab7a364ff8d0,344695]); B/O SG The new Oceanographic Vessel (B / O) Sarmiento de Gamboa, launched on January 30, 2006 in the presence of Her Majesty Queen Sofia, is considered of great scientific facility and incorporates the latest technology both in terms of system navigation (eg dynamic positioning) and its scientific equipment, besides being the first Spanish oceanographic ship that can work with ROV's (Remote Operated Vehicle) to great depths and AUV's (Autonomous Underwater Vehicle). Will be used primarily to do research and science in the Atlantic Ocean, so that its base of operations is a port of Galicia. Group: Platform_Details Entry_ID: B/O SG Group: Platform_Identification Platform_Category: In Situ Ocean-based Platforms Platform_Series_or_Entity: Ships Short_Name: B/O SG Long_Name: B/O SARMIENTO DE GAMBOA End_Group Creation_Date: 2012-07-19 Online_Resource: http://www.utm.csic.es/sarmiento.asp Sample_Image: http://www.utm.csic.es/imagenes/infraestructuras/sarmiento/sarmiento_179x116.jpg End_Group 2012-10-16 20:04:32.0 [aaleman] Move Concepts add broader relation (B/O SG [bccde7bb-3a29-4919-85ce-0b8f446d707d,31215] - SHIPS [82a67b12-e99d-4c90-8a6a-a6f79d4c3c7b,31201]); delete broader relation (null); HESSI The HESSI mission consists of a single spin-stabilized spacecraft in a low-altitude orbit inclined 38 degrees to the Earth's equator. The only instrument on board is an imaging spectrometer with the ability to obtain high fidelity color movies of solar flares in X rays and gamma rays. It uses two new complementary technologies: fine grids to modulate the solar radiation, and germanium detectors to measure the energy of each photon very precisely. HESSI's imaging capability is achieved with fine tungsten and/or molybdenum grids that modulate the solar X-ray flux as the spacecraft rotates at ~ 15 rpm. Up to 20 detailed images can be obtained per second. This is sufficient to track the electrons as they travel from their acceleration site, believed to be in the solar corona, and slow down on their way to the lower solar atmosphere. The high-resolution spectroscopy is achieved with 9 cooled germanium crystals that detect the X-ray and gamma-ray photons transmitted through the grids over the broad energy range of 3 keV to 20 MeV. Their fine energy resolution of about 1 keV is more than sufficient to reveal the detailed features of the X-ray and gamma-ray spectra, clues to the nature of the electron and ion acceleration processes. A spinning spacecraft pointing at or near Sun center provides a simple and reliable way to achieve the rotation required for the HESSI imaging technique. A low-altitude equatorial orbit that can be reached with a Pegasus launch vehicle is chosen to minimize damage to the germanium detectors from the charged particles in the Earth's radiation belts. Context observations from ground-based observatories and a theory program are also integral parts of the HESSI mission. Ground-based optical and radio telescopes will provide complementary data on the magnetic fields, electric currents, hot plasma, and the energetic electrons in the flaring regions where the X-ray and gamma-ray emissions are generated. Also, it is hoped that other spacecraft will provide additional simultaneous observations of the thermal and dynamic environment to further enhance our knowledge of the conditions in the flaring region. [Information provided by NASA.] Group: Platform_Details Entry_ID: HESSI Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Short_Name: HESSI Long_Name: High Energy Solar Spectroscopic Imager End_Group Group: Synonymous_Platform_Names Short_Name: HESSI End_Group Group: Platform_Associated_Instruments Short_Name: POLARIMETERS Short_Name: SPECTROGRAPHS Short_Name: WAVES Short_Name: VECTOR MAGNETOGRAPHS End_Group Group: Orbit Orbit_Altitude: 600 km Orbit_Inclination: 38 degrees End_Group Creation_Date: 2007-08-13 Online_Resource: http://hesperia.gsfc.nasa.gov/hessi/ Sample_Image: http://hesperia.gsfc.nasa.gov/hessi/images/hessicraft.gif Group: Platform_Logistics Launch_Date: 2002-02-05 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Design_Life: 2 years Primary_Sponsor: NASA End_Group End_Group DMSP 5D-3/F17 DMSP-F17 [Source: National Space Science Data Center (NSSDC), http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=2006-050A ] MSP F17, also known as DMSP 5D-3 F17 is an American (DoD/NOAA) military weather satellite that was launched by a Delta 4 rocket from Vandenberg AFB at 13:53 UT on 04 November 2006. It is presumed to carry a payload similar to those on DMSP F16 and F15, to provide infrared and visible light images, and some data of ionospheric and magnetospheric import. Group: Platform_Details Entry_ID: DMSP 5D-3/F17 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: DMSP (Defense Meteorological Satellite Program) Short_Name: DMSP 5D-3/F17 Long_Name: Defense Meteorological Satellite Program-F17 End_Group Group: Synonymous_Platform_Names Short_Name: DMSP-F17 Short_Name: 29522 End_Group Group: Orbit Orbit_Inclination: 98.80000305175781° Period: 102.0 minutes Perigee: 841.0 km Apogee: 855.0 km End_Group Creation_Date: 2009-12-23 Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=2006-050A Online_Resource: http://www.ngdc.noaa.gov/dmsp/ Group: Platform_Logistics Launch_Date: 2006-11-04 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: Department of Defense-Department of the Air Force (United States) End_Group End_Group 2016-06-09 14:38:24.0 [epneff] added altLabel insert AltLabel (id: null text: DMSP-F17 language code: en); GOES-17 GOES-S The Geostationary Operational Environmental Satellite (GOES) – R Series is the nation’s most advanced fleet of geostationary weather satellites. The GOES-R Series significantly improves the detection and observation of environmental phenomena that directly affect public safety, protection of property and our nation’s economic health and prosperity. The satellites provide advanced imaging with increased spatial resolution and faster coverage for more accurate forecasts, real-time mapping of lightning activity, and improved monitoring of solar activity and space weather. The GOES-R Series is a four-satellite program (GOES-R/S/T/U) that will extend the availability of the operational GOES satellite system through 2036. 2018-03-02 17:34:12.0 [tstevens] insert Definition (id: null text: The Geostationary Operational Environmental Satellite (GOES) – R Series is the nation’s most advanced fleet of geostationary weather satellites. The GOES-R Series significantly improves the detection and observation of environmental phenomena that directly affect public safety, protection of property and our nation’s economic health and prosperity. The satellites provide advanced imaging with increased spatial resolution and faster coverage for more accurate forecasts, real-time mapping of lightning activity, and improved monitoring of solar activity and space weather. The GOES-R Series is a four-satellite program (GOES-R/S/T/U) that will extend the availability of the operational GOES satellite system through 2036. language code: en); 2018-03-02 15:50:49.0 [tstevens] insert AltLabel (id: null category: null text: GOES-S language code: en); 2018-03-02 15:42:17.0 [tstevens] insert AltLabel (id: null category: primary text: Geostationary Operational Environmental Satellite 17 language code: en); 2018-03-02 15:41:19.0 [tstevens] Insert Concept add broader relation (GOES-17 [bec0b215-7fe0-46e8-855a-d1807779f004,310619] - GOES (Geostationary Operational Environmental Satellite) [e31e924e-9e50-4856-b85d-862ee3d084a4,288727]); USV Unmanned surface vehicles (USV) or autonomous surface vehicles (ASV) are vehicles that operate on the surface of the water (watercraft) without a crew. 2020-03-17 12:19:43.0 [tstevens] Insert Concept add narrower relation (USV [bf17bbac-0fc9-48b3-9b03-bd780ffe1eb0,542539] - Kingfisher [dba6c8ed-8444-4e18-965c-9c0e30186ac3,559867]); 2019-01-18 20:50:46.0 [sritz] Insert Concept add narrower relation (USV [bf17bbac-0fc9-48b3-9b03-bd780ffe1eb0,368431] - Saildrone [6077a16e-dc27-47ba-b2b8-6ae731615925,368435]); 2019-01-18 20:48:25.0 [sritz] insert AltLabel (id: null category: primary text: Unmanned Surface Vehicle language code: en); insert Definition (id: null text: Unmanned surface vehicles (USV) or autonomous surface vehicles (ASV) are vehicles that operate on the surface of the water (watercraft) without a crew. language code: en); 2019-01-18 20:44:27.0 [sritz] Insert Concept add broader relation (USV [bf17bbac-0fc9-48b3-9b03-bd780ffe1eb0,368431] - In Situ Ocean-based Platforms [e50b2a1a-7d9d-4c09-ac7e-dc29f0c08fc7,345973]); EarthCARE The EarthCARE satellite will carry four instruments for observations of clouds and aerosols with four synergistic sensing methodologies. The three-axis stabilised satellite platform was designed to accommodate the four instruments, which need unobstructed and very accurately collocated views of Earth as well as unobstructed views for solar calibration of the passive instruments. The satellite design meets these challenges by employing a fully customised carbon fibre-based platform with the radar, lidar and startrackers (used for determining the satellite’s attitude) positioned as close together as possible, thereby minimising alignment errors. The satellite is dominated by the large Cloud Profiling Radar (CPR) antenna, which is 2.5 m across. The long trailing solar panel at the rear gives the satellite an overall length of 19 m. The solar panel is made up of five sections and covers an area of 21 sq m and, at the satellite’s low orbital altitude, helps minimise atmospheric drag. EarthCARE will orbit Earth at an altitude of around 393 km. The altitude needs to be as low as possible to optimise the use of the lidar and radar, but not too low where atmospheric drag would impact fuel consumption and the life of the mission. Since global coverage is required, EarthCARE’s orbit is near-polar. It crosses the equator in the early afternoon, providing optimal illumination and minimal sun glint for the passive instruments. The system’s power demand is significant. The two active instruments, the Atmospheric Lidar (ATLID) and the CPR, require 2500 W. The size of the satellite (with solar panel and CPR antenna stowed for launch) and its mass of about 2000 kg plus fuel makes it compatible with both Soyuz and Zenit launchers. 2019-02-15 16:06:54.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: 485824e1-c539-45e6-8262-4e902b8542ed relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: f3c9a235-939d-4898-94f3-3dea5ad187e1 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 715d7cf7-0824-4fca-bdd8-1b651953b820 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 081f9b6e-d0a0-4f1d-ad8a-638189418480 relationship type: null relationship value: null generated by: null); 2018-06-12 10:17:34.0 [mmorahan] insert Definition (id: null text: The EarthCARE satellite will carry four instruments for observations of clouds and aerosols with four synergistic sensing methodologies. The three-axis stabilised satellite platform was designed to accommodate the four instruments, which need unobstructed and very accurately collocated views of Earth as well as unobstructed views for solar calibration of the passive instruments. The satellite design meets these challenges by employing a fully customised carbon fibre-based platform with the radar, lidar and startrackers (used for determining the satellite’s attitude) positioned as close together as possible, thereby minimising alignment errors. The satellite is dominated by the large Cloud Profiling Radar (CPR) antenna, which is 2.5 m across. The long trailing solar panel at the rear gives the satellite an overall length of 19 m. The solar panel is made up of five sections and covers an area of 21 sq m and, at the satellite’s low orbital altitude, helps minimise atmospheric drag. EarthCARE will orbit Earth at an altitude of around 393 km. The altitude needs to be as low as possible to optimise the use of the lidar and radar, but not too low where atmospheric drag would impact fuel consumption and the life of the mission. Since global coverage is required, EarthCARE’s orbit is near-polar. It crosses the equator in the early afternoon, providing optimal illumination and minimal sun glint for the passive instruments. The system’s power demand is significant. The two active instruments, the Atmospheric Lidar (ATLID) and the CPR, require 2500 W. The size of the satellite (with solar panel and CPR antenna stowed for launch) and its mass of about 2000 kg plus fuel makes it compatible with both Soyuz and Zenit launchers. language code: en); 2018-06-12 10:15:03.0 [mmorahan] Insert Concept add broader relation (EarthCARE [bf66ef8c-acc5-4c2f-b519-db0cbee37c99,367671] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761]); JASON-3 Jason-3 is the fourth mission in U.S.-European series of satellite missions that measure the height of the ocean surface. Launched on January 17, 2016, the mission will extend the time series of ocean surface topography measurements (the hills and valleys of the ocean surface) begun by the TOPEX/Poseidon satellite mission in 1992 and continuing through the Jason-1 (launched in 2001) and the currently operating OSTM/Jason-2 (launched in 2008) missions. These measurements provide scientists with critical information about circulation patterns in the ocean and about both global and regional changes in sea level and the climate implications of a warming world. 2018-08-10 18:33:01.0 [sritz] insert Definition (id: null text: Jason-3 is the fourth mission in U.S.-European series of satellite missions that measure the height of the ocean surface. Launched on January 17, 2016, the mission will extend the time series of ocean surface topography measurements (the hills and valleys of the ocean surface) begun by the TOPEX/Poseidon satellite mission in 1992 and continuing through the Jason-1 (launched in 2001) and the currently operating OSTM/Jason-2 (launched in 2008) missions. These measurements provide scientists with critical information about circulation patterns in the ocean and about both global and regional changes in sea level and the climate implications of a warming world. language code: en); 2018-08-10 18:31:28.0 [sritz] Insert Concept add broader relation (JASON-3 [bffa816a-c210-46ed-81cb-ffdf3310c1a5,368059] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761]); STS-2 Space Transport System STS-2 Mission Objectives: Demonstrate safe re-launch and safe return of the orbiter and crew. Verify the combined performance of the entire shuttle vehicle - orbiter, solid rocket boosters and external tank. Payloads included the Orbital Flight Test Pallet consisting of the Measurement of Air Pollution from Satellite (MAPS) experiment, the Shuttle Multispectral Infrared Radiometer (SMIRR) experiment, the Shuttle Imaging Radar (SIR-A) experiment, the Features Identification and Location Experiment (FILE) and the Ocean Color Experimetn (OCE). Also included was the 11,048 lb Development Flight Instrumentation (DFI) pallet, the Aerodynamic Coefficient Identification Package (ACIP), the Induced Environment Contamination Monitor (IECM) and the 5,395 lb Office of Space and Terrestrial Applications Pallet (OSTA-1). [Summary provided by NASA] Group: Platform_Details Entry_ID: STS-2 Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Platform_Series_or_Entity: SPACE SHUTTLE Short_Name: STS-2 Long_Name: Space Transport System STS-2 End_Group Group: Synonymous_Platform_Names Short_Name: columbia End_Group Group: Orbit Orbit_Altitude: 291 Orbit_Inclination: 38.03 End_Group Creation_Date: 2008-01-28 Online_Resource: http://science.ksc.nasa.gov/shuttle/missions/sts-2/mission-sts-2.html Sample_Image: http://science.ksc.nasa.gov/shuttle/missions/sts-2/sts-2-patch.jpg Group: Platform_Logistics Launch_Date: 1981-11-12 Primary_Sponsor: NASA End_Group End_Group PASSCAL Program for Array Seismic Studies of the Continental Lithosphere (PASSCAL) is one of two major instrumentation programs of IRIS (the other being the Global Seismic Network or GSN). PASSCAL operates a pool of over 400 portable seismic instruments to record active source reflection data, active source refraction data or natural source recordings of earthquakes. The instrumentation is housed and supported by an instrument center at New Mexico Tech, Socorro, New Mexico. PASSCAL Instruments and support are available to the academic research community according to the rules and policies set by the IRIS. More information at "http://www.passcal.nmt.edu/" [Source: IRIS] CRRES The Combined Release and Radiation Effects Satellite (CRRES) Program is comprised of several elements. One is the release of powdered and liquid chemicals during the first 45 to 60 days after launch, when the spacecraft is in its 300-km altitude circular orbit. These releases are used to study electric fields, neutral winds, and other phenomena in the upper atmosphere, the ionosphere, and the magnetosphere. The spacecraft spins at 20 rpm during the low altitude orbit phase of the program. After the chemical releases are completed, the satellite is boosted into a geosynchronous-transfer-type orbit and spun down to 2 rpm. The orbit parameters of this final orbit are as follows: apogee altitude - 35,800 km, perigee altitude - 400 km, period - 630 min, inclination - about 16 deg. As the satellite traverses the inner magnetosphere, a full complement of field, particle, and plasma instruments measures the radiation environment. A comprehensive set of state-of-the-art microelectronics devices and other spacecraft components are tested in orbit for radiation effects. A major segment of the CRRES payload is part of AFGL's Space Radiation Effects Program (SPACERAD). The SPACERAD Program is a comprehensive space and ground test effort to (a) measure radiation-induced single event upsets and total dose degradation of state-of-the-art microelectronics devices, including VHSIC and GaAs, in a known space environment; (b) perform laboratory radiation response and annealing characterization of parts identical to those flown on CRRES; (c) develop algorithms to relate space performance of microelectronic components to ground test procedures, and update existing radiation ground test guidelines to more accurately simulate the behavior of devices in space; (d) space qualify advanced technology devices for use in operational systems; (e) update the static models of the radiation belts; and (f) develop the first dynamic models of the high-energy particle populations. The on-orbit phase of SPACERAD lasts for about 3 years. In addition, there are other radiation belt experiments on CRRES provided by the Navy. The CRRES spacecraft has the shape of an octagonal prism with solar arrays on the top side. The prism is 1 m high and 3 m between opposite faces. Four of the eight compartments are for the chemical canisters and the other four house the SPACERAD and other experiments. The spin axis of CRRES is controlled so that it points at the sun. Spacecraft Orbit Information Launch Date and Time 07/25/90 Orbit Type Elliptical Anomalistic Period 591.9 Min Apogee(km) 33612. Perigee(km) 335. Inclination 18.2 Group: Platform_Details Entry_ID: CRRES Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: CRRES Long_Name: Combined Release and Radiation Effects Satellite End_Group Group: Synonymous_Platform_Names Short_Name: CRRES End_Group Group: Orbit Orbit_Inclination: 18.2 Period: 591.9 min Perigee: 335 km Apogee: 33612 km Orbit_Type: HEO > Highly Elliptical Orbit End_Group Creation_Date: 2007-11-19 Online_Resource: http://www.spenvis.oma.be/spenvis/help/models/databases/crres.html Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/masterCatalog.do?sc=1990-065A Sample_Image: http://library01.gsfc.nasa.gov/gdprojs/images/crres.jpg Group: Platform_Logistics Launch_Date: 1990-07-25 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: USA/NASA End_Group End_Group Data Collections 2018-08-23 18:24:50.0 [sritz] Insert Concept add broader relation (Data Collections [c10044b3-6ebc-413a-99b7-2be30c08e507,368091] - In Situ Land-based Platforms [4f396ff6-7bea-4ba4-afa3-198ebd914a4a,344951]); LANDER SOLRAD ACARS A digital datalink system for transmission of short, relatively simple messages between aircraft and ground stations via radio or satellite. The protocol, which was designed by ARINC to replace their VHF voice service and deployed in 1978, uses telex formats. SITA later augmented their worldwide ground data network by adding radio stations to provide ACARS service. Group: Platform_Details Entry_ID: ACARS Group: Platform_Identification Platform_Category: In Situ Land-based Platforms Short_Name: ACARS Long_Name: ACARS Ground Receiving Station End_Group Creation_Date: 2010-08-31 Online_Resource: http://www.arinc.com/ End_Group R/V RHB G-1 AIRCRAFT The G-1 is a large twin turboprop with performance characteristics of contemporary production aircraft. It is capable of measurements to altitudes approaching 30,000 feet over ranges of 1500 nautical miles, and can be operated at speeds that enable both relatively slow sampling and rapid deployment to field sites throughout the world. The aircraft is configured for versatile research applications. It accommodates a variety of external probes for aerosol, radiation, and turbulence measurements and internal sampling systems for a wide range of measurements. The G-1 has sufficient cabin volume, electrical power and payload capabilities, and flight characteristics to accommodate a variety of instrument systems and experimental equipment configurations. Internal instrumentation is mounted in removable racks to enable rapid reconfiguration as necessary. Data from most systems are acquired on a central computer that is tailored to airborne research data acquisition. In addition to acquiring the various analog and digital input signals, it can be configured to communicate with and/or control other systems onboard, and to provide time synchronization to other computers. Group: Platform_Details Entry_ID: G-1 AIRCRAFT Group: Platform_Identification Platform_Category: Aircraft Short_Name: G-1 AIRCRAFT Long_Name: G-1 Aircraft End_Group Creation_Date: 2012-02-17 Online_Resource: http://www.pnl.gov/atmospheric/programs/raf_g1.stm End_Group ROCKETS Rocket: A vehicle or device propelled by one or more rocket engines, especially such a vehicle designed to travel through space. [Source: The American Heritage? Dictionary of the English Language, Fourth Edition Copyright ? 2000 by Houghton Mifflin Company.] IRAS The Infrared Astronomy Satellite (IRAS)was a joint scientific project sponsored by the United Kingdom, the United States, and the Netherlands. IRAS was launched in January of 1983 and ended its mission ten months later. IRAS' mission was to map the entire sky at infrared wavelengths. It was equipped with a special infrared telescope to scan the sky. IRAS was the first satellite to discover a comet. The comet IRAS-Araki-Alcock was named for the probe and two co-discovering astronomers. During its lifespan, IRAS observed 20,000 galaxies, 130,000 stars and 90,000 other space objects and star clusters. IRAS detectors found a disk of dusty material and fine rock around the star Vega which may be an early stage in the formation of a new solar system. IRAS' most famous discovery was that of a new type of galaxy, a starburst galaxy. In starburst galaxies, new stars are forming more rapidly than in other types of galaxies. Additional information available at "http://lambda.gsfc.nasa.gov/product/iras/" Group: Platform_Details Entry_ID: IRAS Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Short_Name: IRAS Long_Name: Infrared Astronomy Satellite End_Group Group: Synonymous_Platform_Names Short_Name: IRAS End_Group Group: Platform_Associated_Instruments Short_Name: OPTICAL TELESCOPES Short_Name: LRS - Low Resolution Spectrometer Short_Name: CPC - Chopped Photometric Channel End_Group Group: Orbit Orbit_Inclination: 99 degrees Perigee: 884 km Apogee: 903 km End_Group Creation_Date: 2008-01-14 Online_Resource: http://www.daviddarling.info/encyclopedia/I/IRAS.html Sample_Image: http://www.daviddarling.info/images/IRAS.jpg Group: Platform_Logistics Launch_Date: 1983-01-23 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: NASA End_Group End_Group R/V UM Built in 1973, the R/V Umitaka Maru operates in the western central Pacific Ocean, the eastern Indian Ocean, and the Coral Sea. This Japanese marine vessel is mainly used for fisheries. Group: Platform_Details Entry_ID: R/V UM Group: Platform_Identification Platform_Category: In Situ Ocean-based Platforms Platform_Series_or_Entity: SHIPS Short_Name: R/V UM Long_Name: R/V UMITAKA MARU End_Group Creation_Date: 2012-07-23 Online_Resource: http://www.researchvessels.org/country/Japan/umitaka_maru.html End_Group RAE (Radio Astronomy Explorer) HINODE Solar-B (Hinode) is an international mission to study our nearest star, the sun. To accomplish this, the Solar-B mission includes a suite of three science instruments -- the Solar Optical Telescope, X-ray Telescope and Extreme Ultraviolet Imaging Spectrometer. SOLAR-B is the third solar physics satellite of JAXA which was approved as a successor of the highly successful Japan/US/UK YOHKOH (SOLAR-A) collaboration. Together, these instruments will study the generation, transport, and dissipation of magnetic energy from the photosphere to the corona and will record how energy stored in the sun's magnetic field is released, either gradually or violently, as the field rises into the sun?s outer atmosphere. Led by the Japan Aerospace Exploration Agency (JAXA), the Solar-B mission is a collaboration between the space agencies of Japan, the United States, the United Kingdom and Europe. NASA helped in the development, funding and assembly of the spacecraft?s three science instruments. Solar-B is part of the Solar Terrestrial Probes (STP) Program within the Heliophysics Division of NASA's Science Mission Directorate in Washington. The Solar Terrestrial Probes Program is managed at NASA's Goddard Space Flight Center in Greenbelt, Md. NASA's Marshall Space Flight Center in Huntsville, Ala., managed the development of instrument components provided by NASA, with additional support by academia and industry. Group: Platform_Details Entry_ID: HINODE Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Short_Name: HINODE Long_Name: Hinode (Solar-B) End_Group Group: Synonymous_Platform_Names Short_Name: Solar-B Short_Name: 29479 Short_Name: 2006-041A End_Group Group: Platform_Associated_Instruments Short_Name: SOT Short_Name: EIS Short_Name: XRT End_Group Group: Orbit Orbit_Inclination: 98.3 degrees Period: 94.54 m Perigee: 318 km Apogee: 675 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-02-15 Online_Resource: http://solar-b.nao.ac.jp/index_e.shtml Online_Resource: http://solarb.msfc.nasa.gov/ Online_Resource: http://www.isas.jaxa.jp/home/solar/ Online_Resource: http://www.isas.jaxa.jp/e/enterp/missions/hinode/index.shtml Sample_Image: http://nssdc.gsfc.nasa.gov/image/spacecraft/solar_b.jpg Group: Platform_Logistics Launch_Date: 2006-09-22 Launch_Site: Uchinoura Space Center, Japan Design_Life: 3 years Primary_Sponsor: NASA Primary_Sponsor: JAXA End_Group End_Group R/V ALPHA HELIX APOLLO SAGE-III The newest SAGE mission, SAGE III on ISS, is scheduled to launch in 2014. Plans include sending a copy of the SAGE III instrument to the International Space Station aboard a commercial Space X flight. SAGE III was a fourth generation, satellite-borne instrument and a crucial element in NASA's Earth Observing System (EOS) . The instrument was launched on the Russian Meteor-3M spacecraft in December 2001. The Meteor-3M mission, along with the SAGE III mission, was terminated on March 6, 2006, because of a power supply system failure resulting in loss of communication with the satellite. The SAGE III mission enhanced our understanding of natural and human-derived atmospheric processes by providing accurate measurements of the vertical structure of aerosols, ozone, water vapor, and other important trace gases in the upper troposphere and stratosphere. Human-derived changes in climate and ozone threaten the health of our planet. They also threaten global economic development and the use of new technologies like high-speed aircraft. By understanding the effect of human activities on the atmosphere, national and international leaders can make informed policy that mitigates or prepares for future climate change. The SAGE III-Meteor-3M Version 3 revised data set, which includes improvements to solar ozone, nitrogen dioxide and aerosol extinction products, is publicly available at NASA Langley's Atmospheric Science Data Center . The data set also includes the release of a cloud presence identifier and lunar data products. These data will cover the period 27 February 2002 - Present. IDL users will need to access the reader software that must be matched with this version of the data set. [Summary provided by NASA.] Group: Platform_Details Entry_ID: SAGE-III Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: SAGE-III Long_Name: Stratospheric Aerosol and Gas Experiment-III End_Group Group: Platform_Associated_Instruments Short_Name: ISS End_Group Creation_Date: 2012-01-27 Online_Resource: http://www-sage3.larc.nasa.gov/ Sample_Image: http://earthobservatory.nasa.gov/Features/SAGEIII/Images/SAGE_orbit.jpg Group: Platform_Logistics Design_Life: 3 Years Primary_Sponsor: NASA Primary_Sponsor: Russian Space Agency End_Group End_Group SENTINEL-1A The SENTINEL-1 mission is the European Radar Observatory for the Copernicus joint initiative of the European Commission (EC) and the European Space Agency (ESA). Copernicus, previously known as GMES, is a European initiative for the implementation of information services dealing with environment and security. It is based on observation data received from Earth Observation satellites and ground-based information. The SENTINEL-1 mission includes C-band imaging operating in four exclusive imaging modes with different resolution (down to 5 m) and coverage (up to 400 km). It provides dual polarisation capability, very short revisit times and rapid product delivery. For each observation, precise measurements of spacecraft position and attitude are available. Synthetic Aperture Radar (SAR) has the advantage of operating at wavelengths not impeded by cloud cover or a lack of illumination and can acquire data over a site during day or night time under all weather conditions. SENTINEL-1, with its C-SAR instrument, can offer reliable, repeated wide area monitoring. The mission is composed of a constellation of two satellites, SENTINEL-1A and SENTINEL-1B, sharing the same orbital plane. SENTINEL-1 is designed to work in a pre-programmed, conflict-free operation mode, imaging all global landmasses, coastal zones and shipping routes at high resolution and covering the global ocean with vignettes. This ensures the reliability of service required by operational services and a consistent long term data archive built for applications based on long time series. Source: https://sentinel.esa.int/web/sentinel/missions/sentinel-1 Group: Platform_Details Entry_ID: SENTINEL-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: Sentinel GMES Short_Name: SENTINEL-1 End_Group Group: Platform_Associated_Instruments Short_Name: SENTINEL-1 C-SAR End_Group Group: Orbit Orbit_Altitude: 693 km Orbit_Type: LEO > LOW EARTH ORBIT > POLAR SUN-SYNCHRONOUS End_Group Creation_Date: 2009-12-18 Online_Resource: https://sentinel.esa.int/web/sentinel/missions/sentinel-1 Sample_Image: http://www.esa.int/images/sentinel2_alcatel_M.gif Group: Platform_Logistics Launch_Date: 2014-04-03 Launch_Site: KOUROU, FRENCH GUIANA Design_Life: 7 Years Primary_Sponsor: ESA/EU End_Group End_Group 2019-03-28 16:56:35.0 [mmorahan] delete WeightedRelation (null); 2019-02-22 18:54:55.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: 1c53d85e-3792-4081-9748-192fd3140aa6 relationship type: null relationship value: null generated by: null); 2019-02-22 17:49:03.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: ed400e7c-229e-48be-9a93-84f2fc864448 relationship type: null relationship value: null generated by: null); 2018-11-05 13:36:01.0 [tstevens] insert AltLabel (id: null category: primary text: SENTINEL-1A language code: en); update Resource (image); 2018-06-12 19:15:42.0 [mmorahan] Move Concepts delete broader relation (null); add broader relation (SENTINEL-1A [c7279e54-f7c1-4ee7-a957-719d6021a3f6,345757] - Sentinel-1 [007c3084-89db-458e-8387-14e192b6cb8e,367691]); 2015-09-23 23:55:42.0 [saritz] Rename Concept update PrefLabel (SENTINEL-1A); MOBILE STATIONS/VEHICLES ESSA-3 TOS-A ESSA-3 satellite replaced ESSA-1. It provided cloud-cover photography to the US's National Meteorological Center for the purpose of preparing weather analyses and forecasts. The spacecraft was designed and configured exactly the same as NIMBUS-1. The total weight of the spacecraft was 912 pounds. The spacecraft was an 18-sided polygon, 42 inches in diameter, 22 inches high and weighed 320 pounds; it was made of aluminum alloy and stainless steel, then covered with 9100 solar cells. The solar cells served to charge the 63 nickel-cadmium batteries. The two cameras were mounted 180-degrees opposite each other along the side of the cylindrical craft. The "cartwheel" configuration of the TIROS-9 was selected as the orbital configuration for the ESSA satellites. Therefore, a camera could be pointed at some point on Earth every time the satellite rotated along its axis. The spacecraft operating system was the same as on the TIROS-9. The craft was placed in its planned Sun-synchronous 101 degree inclination retrograde orbit. The ESSA-3 system transmitted images covering 2000-square mile areas with 2-mile resolution from every location once per day. ESSA-3 Stats: Launch Date: October 02, 1966 Operational Period: 736 days until deactivated by NASA on December 02, 1968 Launch Vehicle: Thrust Augmented Three-Stage Delta Launch Site: Vandenberg Air Force Base, CA Type: Weather Satellite 2018-11-14 15:42:28.0 [sritz] insert AltLabel (id: null category: null text: TOS-A language code: en); 2018-11-14 15:38:27.0 [sritz] update AltLabel (Environmental Science Services Administration Satellite 3); 2018-11-14 15:37:23.0 [sritz] update AltLabel (Environmental Science Services Administration 3); 2018-11-14 15:37:02.0 [sritz] insert AltLabel (id: null category: primary text: Environmental Science Services Administration language code: en); insert AltLabel (id: null category: null text: TOS-E language code: en); 2018-10-30 17:00:59.0 [sritz] insert Definition (id: null text: ESSA-3 satellite replaced ESSA-1. It provided cloud-cover photography to the US's National Meteorological Center for the purpose of preparing weather analyses and forecasts. The spacecraft was designed and configured exactly the same as NIMBUS-1. The total weight of the spacecraft was 912 pounds. The spacecraft was an 18-sided polygon, 42 inches in diameter, 22 inches high and weighed 320 pounds; it was made of aluminum alloy and stainless steel, then covered with 9100 solar cells. The solar cells served to charge the 63 nickel-cadmium batteries. The two cameras were mounted 180-degrees opposite each other along the side of the cylindrical craft. The "cartwheel" configuration of the TIROS-9 was selected as the orbital configuration for the ESSA satellites. Therefore, a camera could be pointed at some point on Earth every time the satellite rotated along its axis. The spacecraft operating system was the same as on the TIROS-9. The craft was placed in its planned Sun-synchronous 101 degree inclination retrograde orbit. The ESSA-3 system transmitted images covering 2000-square mile areas with 2-mile resolution from every location once per day. ESSA-3 Stats: Launch Date: October 02, 1966 Operational Period: 736 days until deactivated by NASA on December 02, 1968 Launch Vehicle: Thrust Augmented Three-Stage Delta Launch Site: Vandenberg Air Force Base, CA Type: Weather Satellite language code: en); 2018-10-30 15:44:45.0 [sritz] Rename Concept update PrefLabel (ESSA-3); 2018-10-30 15:43:43.0 [sritz] Insert Concept add broader relation (ESSA--3 [c7706afe-079a-4966-8a9e-6a688ca9b880,368195] - ESSA [65cb3e7c-d4d8-46df-a5fc-aec63e58e8df,345109]); ESRL STATIONS The Global Monitoring Division (GMD) of the National Oceanic and Atmospheric Administration's Earth Science Research Laboratory (ESRL), conducts sustained observations and research related to source and sink strengths, trends and global distributions of atmospheric constituents that are capable of forcing change in the climate of Earth through modification of the atmospheric radiative environment, those that may cause depletion of the global ozone layer, and those that affect baseline air quality. ESRL accomplishes this mission primarily through long-term measurements of key atmospheric species at sites spanning the globe, including five fully-equipped Baseline Observatories. These key species include carbon dioxide, carbon monoxide, methane, nitrous oxide, surface and stratospheric ozone, halogenated compounds including CFC replacements, hydrocarbons, sulfur gases, aerosols, and solar and infrared radiation. The measurements are of the highest quality and accuracy possible, and document global ch! anges in key atmospheric species, which are all affected by mankind, identifying sources of interannual variability. In addition, research programs in key regions, utilizing an array of platforms including aircraft, balloons, ocean vessels and towers, complement the land-based information. ESRL's data are used to assess climate forcing, ozone depletion and baseline air quality, to develop and test diagnostic and predictive models, and to keep the public, policy makers, and scientists abreast of the current state of our chemical and radiative atmosphere. More info at http://www.esrl.noaa.gov/gmd/ [Source: NOAA] Group: Platform_Details Entry_ID: ESRL STATIONS Group: Platform_Identification Platform_Category: In Situ Land-based Platforms Platform_Series_or_Entity: AIR MONITORING STATIONS/NETWORKS Short_Name: ESRL STATIONS Long_Name: NOAA Earth Science Research Laboratory Stations End_Group Online_Resource: http://www.esrl.noaa.gov/gmd/ End_Group PIONEER VENUS The Pioneer Venus Orbiter was inserted into an elliptical orbit around Venus on December 4, 1978. The Orbiter was a flat cylinder 2.5 m in diameter and 1.2 m high. All instruments and spacecraft subsystems were mounted on the forward end of the cylinder, except the magnetometer, which was at the end of a 4.7 m boom. A solar array extended around the circumference of the cylinder. A 1.09 m despun dish antenna provided S and X band communication with Earth. The Pioneer Venus Orbiter carried 17 experiments (with a total mass of 45 kg): * a cloud photopolarimeter to measure the vertical distribution of the clouds * a surface radar mapper to determine topography and surface characteristics * an infrared radiometer to measure IR emissions from the Venus atmosphere * an airglow ultraviolet spectrometer to measure scattered and emitted UV light * a neutral mass spectrometer to determine the composition of the upper atmosphere * a solar wind plasma analyzer to measure properties of the solar wind * a magnetometer to characterize the magnetic field at Venus * an electric field detector to study the solar wind and its interactions * an electron temperature probe to study the thermal properties of the ionosphere * an ion mass spectrometer to characterize the ionospheric ion population * a charged particle retarding potential analyzer to study ionospheric particles * two radio science experiments to determine the gravity field of Venus * a radio occultation experiment to characterize the atmosphere * an atmospheric drag experiment to study the upper atmosphere * a radio science atmospheric and solar wind turbulence experiment * a gamma ray burst detector to record gamma ray burst events From Venus orbit insertion to July 1980, periapsis was held between 142 and 253 km (at 17 degrees north latitude) to facilitate radar and ionospheric measurements. The spacecraft was in a 24 hour orbit with an apoapsis of 66,900 km. Thereafter, the periapsis was allowed to rise (to 2290 km at maximum) and then fall, to conserve fuel. In 1991 the Radar Mapper was reactivated to investigate previously inaccessible southern portions of the planet. In May 1992 Pioneer Venus began the final phase of its mission, in which the periapsis was held between 150 and 250 km until the fuel ran out and atmospheric entry destroyed the spacecraft the following August. Group: Platform_Details Entry_ID: PIONEER VENUS Group: Platform_Identification Platform_Category: Interplanetary Spacecraft Platform_Series_or_Entity: ORBITER Short_Name: PIONEER VENUS End_Group Group: Synonymous_Platform_Names Short_Name: PVO Short_Name: Pioneer 12 Short_Name: Pioneer Venus 1 Short_Name: Pioneer Venus 1978 Orbiter Short_Name: 10911 Short_Name: 1978-051A End_Group Creation_Date: 2007-02-05 Online_Resource: http://www.nasa.gov/mission_pages/pioneer-venus/index.html Sample_Image: http://agile.gsfc.nasa.gov/Images/pvo/pvo.gif Group: Platform_Logistics Launch_Date: 1978-05-20 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: NASA End_Group End_Group LANDSAT-7 L7 LANDSAT-7 (LAND REMOTE-SENSING SATELLITE-7) Landsat 7 systematically provides well-calibrated, multispectral, moderate resolution, substantially cloud-free, sun-lit digital images of the Earth&#039;s continental and coastal areas with global coverage on a seasonal basis. It covers the United States every 16 days. Operations were transferred to USGS on Fall 2000. The Landsat Project is a joint initiative of the U.S. Geological Survey (USGS) and the NASA to gather Earth resource data using a series of satellites. NASA was responsible for developing and launching the spacecrafts, while the USGS is responsible for flight operations, maintenance, and management of all ground data reception, processing, archiving, product generation, and distribution. The primary objective of the Landsat Project is to ensure a collection of consistently calibrated Earth imagery. Landsat&#039;s Global Survey Mission is to establish and execute a data acquisition strategy that ensures repetitive acquisition of observations over the Earth&#039;s land mass, coastal boundaries, and coral reefs; and to ensure the data acquired are of maximum utility in supporting the scientific objectives of monitoring changes in the Earth&#039;s land surface and associated environment. Key Landsat 7 Facts [p. 176] Joint with U.S. Geological Survey (USGS) Heritage: Landsat 4, 5 Equatorial Crossing: 10:00 a.m. &#177; 15 mins Altitude: 705 km &#177; 5 km (at the equator) Inclination: 98.2&#176; &#177; 0.15&#176; Period: 98.9 min Repeat cycle: 16 days/233 orbits Dimensions: 4 m high, 2.7 m diameter Mass: 1982 kg Power: 1550 W Downlink: Three 150 Mbps wideband downlinks Antennas: 3 gimbaled X-band, 2 omni S-band Design Life: 5 years Spacecraft: Lockheed Martin ETM+: Raytheon Santa Barbara Remote Sensing Data Archival, Processing, Ground Operations: USGS National Center for Earth Resources Observation System (EROS) data center Spacecraft and Sensor Maintenance: NASA GSFC Calibration: EROS and GSFC Type: Circular, sun-synchronous [Summary provided by NASA.] Group: Platform_Details Entry_ID: LANDSAT-7 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: LANDSAT Short_Name: LANDSAT-7 End_Group Group: Platform_Associated_Instruments Short_Name: ETM+ End_Group Group: Orbit Orbit_Altitude: 705km Orbit_Inclination: 98.2 degree Equator_Crossing: nominally 10 AM Period: 99 minutes Repeat_Cycle: 16 days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-02-02 Online_Resource: https://landsat.gsfc.nasa.gov/landsat-7/ Online_Resource: https://www.usgs.gov/land-resources/nli/landsat/landsat-7 Group: Platform_Logistics Launch_Date: 1999-03-15 Design_Life: 5 Years Primary_Sponsor: USA/USGS Primary_Sponsor: USA/NASA End_Group End_Group 2019-12-31 21:48:51.0 [sritz] update Definition (Landsat 7 systematically provides well-calibrated, multispectral, moderate resolution, substantially cloud-free, sun-lit digital images of the Earth&#039;s continental and coastal areas with global coverage on a seasonal basis. It covers the United States every 16 days. Operations were transferred to USGS on Fall 2000. The Landsat Project is a joint initiative of the U.S. Geological Survey (USGS) and the NASA to gather Earth resource data using a series of satellites. NASA was responsible for developing and launching the spacecrafts, while the USGS is responsible for flight operations, maintenance, and management of all ground data reception, processing, archiving, product generation, and distribution. The primary objective of the Landsat Project is to ensure a collection of consistently calibrated Earth imagery. Landsat&#039;s Global Survey Mission is to establish and execute a data acquisition strategy that ensures repetitive acquisition of observations over the Earth&#039;s land mass, coastal boundaries, and coral reefs; and to ensure the data acquired are of maximum utility in supporting the scientific objectives of monitoring changes in the Earth&#039;s land surface and associated environment. Key Landsat 7 Facts [p. 176] Joint with U.S. Geological Survey (USGS) Heritage: Landsat 4, 5 Equatorial Crossing: 10:00 a.m. &#177; 15 mins Altitude: 705 km &#177; 5 km (at the equator) Inclination: 98.2&#176; &#177; 0.15&#176; Period: 98.9 min Repeat cycle: 16 days/233 orbits Dimensions: 4 m high, 2.7 m diameter Mass: 1982 kg Power: 1550 W Downlink: Three 150 Mbps wideband downlinks Antennas: 3 gimbaled X-band, 2 omni S-band Design Life: 5 years Spacecraft: Lockheed Martin ETM+: Raytheon Santa Barbara Remote Sensing Data Archival, Processing, Ground Operations: USGS National Center for Earth Resources Observation System (EROS) data center Spacecraft and Sensor Maintenance: NASA GSFC Calibration: EROS and GSFC Type: Circular, sun-synchronous [Summary provided by NASA.] Group: Platform_Details Entry_ID: LANDSAT-7 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: LANDSAT Short_Name: LANDSAT-7 End_Group Group: Platform_Associated_Instruments Short_Name: ETM+ End_Group Group: Orbit Orbit_Altitude: 705km Orbit_Inclination: 98.2 degree Equator_Crossing: nominally 10 AM Period: 99 minutes Repeat_Cycle: 16 days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-02-02 Online_Resource: https://landsat.gsfc.nasa.gov/landsat-7/ Online_Resource: https://www.usgs.gov/land-resources/nli/landsat/landsat-7 Group: Platform_Logistics Launch_Date: 1999-03-15 Design_Life: 5 Years Primary_Sponsor: USA/USGS Primary_Sponsor: USA/NASA End_Group End_Group); update Definition (https://landsat.gsfc.nasa.gov/landsat-7/); delete Resource (null); 2016-06-09 15:33:25.0 [epneff] added altLabel insert AltLabel (id: null text: LANDSAT-7 (LAND REMOTE-SENSING SATELLITE-7) language code: en); 2016-06-09 15:32:50.0 [epneff] added altLabel insert AltLabel (id: null text: L7 language code: en); FIELD INVESTIGATION INVESTIGATION Field investigations are primary observations and measurements that are taken from the place or location of what is being investigated. [Source: The American Heritage Dictionary.] Group: Platform_Details Entry_ID: FIELD INVESTIGATION Group: Platform_Identification Platform_Category: In Situ Land-based Platforms Short_Name: FIELD INVESTIGATION End_Group Group: Synonymous_Platform_Names Short_Name: Field Investigation End_Group Creation_Date: 2007-12-12 End_Group 2016-06-09 18:38:42.0 [epneff] added altLabel insert AltLabel (id: null text: INVESTIGATION language code: en); IKONOS IKONOS is the world's first commerical high resolution satellite and was launched into orbit on September 24, 1999 from Vandenberg Air Force Base, California on a Athena II rocket. The 1600-pound (720-kilogram) IKONOS was launched into a sun-synchronous, near-polar(98.1degrees), circular low-Earth orbit (423miles) at 11:21:08 a.m. PDT. (2:21:08 p.m. EDT). IKONOS satellite is operated by the Space Imaging Company in Thorton, Colorado. IKONOS has a panchromatic band with a resolution of 1meter and a multispectural band wit h a resolution of 4meters. The1 meter panchromatic band has a revisit time of 2.9 days and the 4m meter multispectural band has a revisit time of 1.5 days. Group: Platform_Details Entry_ID: IKONOS Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: IKONOS End_Group Group: Synonymous_Platform_Names Short_Name: IKONOS End_Group Group: Orbit Orbit_Altitude: 681 km Orbit_Inclination: 98.1 degree Equator_Crossing: 10:30 AM Repeat_Cycle: 3 days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-11-19 Online_Resource: http://www.satimagingcorp.com/satellite-sensors/ikonos.html Sample_Image: http://www.satimagingcorp.com/media/images/ikonos-satellite.jpg Group: Platform_Logistics Launch_Date: 1999-09-24 Launch_Site: Vandenberg Air Force Base, USA Design_Life: Over 7 years Primary_Sponsor: GeoEye Inc. End_Group End_Group LA-27 The Lake Renegade Seawolf (LA-27) is a rugged, adaptable, single turbo-charged piston engine amphibious aircraft designed for nearshore low-level surveys. The aircraft is equipped with external fuel tanks, bubble windows, and NATO hardpoints. A standard crew consists of one pilot and up to three scientists. The Lake aircraft has been used for biological surveys including red drum, sea turtle and marine mammal surveys, as well as on site terrain observations. [Photo and text provided by NOAA, http://www.aoc.noaa.gov/aircraft_lake.htm ] Group: Platform_Details Entry_ID: LA-27 Group: Platform_Identification Platform_Category: Aircraft Short_Name: LA-27 Long_Name: Lake Seawolf LA-27 End_Group Creation_Date: 2008-07-14 Online_Resource: http://www.aoc.noaa.gov/aircraft_lake.htm Sample_Image: http://www.aoc.noaa.gov/images/lake1.jpg End_Group STEREOGRAPHIC PHOTOGRAPHS Stereographic photographs are two slightly different photographs of the same scene that when viewed they produce a 3-dimensional image. [Source: The American Heritage Dictionary.] Group: Platform_Details Entry_ID: STEREOGRAPHIC PHOTOGRAPHS Group: Platform_Identification Platform_Category: Maps/Charts/Photographs Short_Name: STEREOGRAPHIC PHOTOGRAPHS End_Group Group: Synonymous_Platform_Names Short_Name: STEREOGRAPHIC PHOTOGRAPHS End_Group Creation_Date: 2007-12-13 Online_Resource: http://en.wikipedia.org/wiki/Stereoscopy Sample_Image: http://tbn0.google.com/images?q=tbn:h82VFTLdSWZoYM:http://www-user.uni-bremen.de/~i18m/ste4.jpg End_Group Cessna Pelican The Pelican is a highly-modified Cessna 337, O2, Skymaster originally developed by the Office of Naval Research for low-altitude, long-endurance atmospheric and oceanographic sampling. Through an SBIR program between Zivko Aeronautics and GA, the air vehicle was configured to operate as a true Predator UAV surrogate for the U.S. Navy. Pelican has supported several military exercises that require a UAV capability for the troops to work with, but where a real UAV wasn't practical to operate due to FAA restrictions. With Pelican, the US Military can realistically train with capabilities very close to those of the UAV's that they will work with on the battlefield. 2017-04-25 19:50:55.0 [sritz] insert Definition (id: null text: The Pelican is a highly-modified Cessna 337, O2, Skymaster originally developed by the Office of Naval Research for low-altitude, long-endurance atmospheric and oceanographic sampling. Through an SBIR program between Zivko Aeronautics and GA, the air vehicle was configured to operate as a true Predator UAV surrogate for the U.S. Navy. Pelican has supported several military exercises that require a UAV capability for the troops to work with, but where a real UAV wasn't practical to operate due to FAA restrictions. With Pelican, the US Military can realistically train with capabilities very close to those of the UAV's that they will work with on the battlefield. language code: en); 2017-04-25 19:49:14.0 [sritz] Insert Concept add broader relation (Cessna Pelican [c97d09d4-4966-42ed-a6c7-4330a1e76edf,309547] - Aircraft [227d9c3d-f631-402d-84ed-b8c5a562fc27,287509]); R/V TANGAROA RV Tangaroa is a deepwater research vessel that has been recently upgraded to enhance its ocean science and oil and gas exploration capabilities and extend its useable life. Key details are available at http://www.niwa.co.nz/our-science/vessels/tangaroa/specifications-and-principal-features#key-details. Group: Platform_Details Entry_ID: R/V TANGAROA Group: Platform_Identification Platform_Category: In Situ Ocean-based Platforms Platform_Series_or_Entity: SHIPS Short_Name: R/V TANGAROA End_Group Creation_Date: 2012-07-18 Online_Resource: http://www.niwa.co.nz/our-science/vessels/tangaroa End_Group PROTEUS Profile Telemetry of Upper Ocean Currents (PROTEUS)are current-meter moorings along the equator which measure air temperature, SST and subsurface temperature to 500 m and measures and telemeters current profiles in the upper 250 m from a downward-looking acoustic Doppler current meter mounted in the surface buoy. [Source: NOAA] Group: Platform_Details Entry_ID: PROTEUS Group: Platform_Identification Platform_Category: In Situ Ocean-based Platforms Platform_Series_or_Entity: FLOATS Short_Name: PROTEUS Long_Name: Profile Telemetry of Upper Ocean Currents End_Group Group: Synonymous_Platform_Names Short_Name: Proteus End_Group Creation_Date: 2007-12-12 Online_Resource: http://www.pmel.noaa.gov/pubs/outstand/cron1713/data.shtml Sample_Image: http://www.pmel.noaa.gov/pubs/outstand/cron1713/images/fig01.gif End_Group ETALON-2 Etalon are a Russian family (Etalon-1, Etalon-2) of passive geodetic satellites dedicated to satellite laser ranging. Etalon-1 was the first geodynamic satellite launched by the former Soviet Union. The Etalon spacecraft were launched in 1989 in conjunction with a pair of GLObal'naya NAvigatisionnay Sputnikovaya Sistema (GLONASS) satellites. The mission objectives were to determine a high accuracy terrestrial reference frame and earth rotation parameters, to improve the gravity field, and to improve the gravitational constant. [Summary provided by NASA.] Group: Platform_Details Entry_ID: ETALON-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: ETALON Short_Name: ETALON-2 End_Group Group: Synonymous_Platform_Names Short_Name: ETALON-2 End_Group Group: Platform_Associated_Instruments Short_Name: RIS End_Group Group: Orbit Orbit_Inclination: 65.5 deg Period: 675 min Perigee: 19120 km Apogee: 19120 km Orbit_Type: HEO > Highly Elliptical Orbit End_Group Creation_Date: 2007-09-26 Online_Resource: http://ilrs.gsfc.nasa.gov/satellite_missions/list_of_satellites/eta1_general.html Sample_Image: http://ilrs.gsfc.nasa.gov/images/etalon.gif Group: Platform_Logistics Launch_Date: 1989-05-31 Primary_Sponsor: Russia End_Group End_Group TAO The Tropical Atmosphere Ocean (TAO) network of moored ocean buoys provides real-time data for improved detection, understanding and prediction of El Niño and La Niña. Group: Platform_Details Entry_ID: TAO Group: Platform_Identification Platform_Category: IN SITU OCEAN-BASED PLATFORMS Platform_Series_or_Entity: BUOYS Short_Name: TAO Long_Name: TROPICAL ATMOSPHERE OCEAN End_Group Creation_Date: 2009-04-14 Online_Resource: http://www.pmel.noaa.gov/tao/ End_Group METOP-B [Text Source: ESA MetOp Meteorological Missions Homepage, http://www.esa.int/esaLP/SEMN1FAATME_LPmetop_0.html ] MetOp-B, the second satellite in the series,launched on 17 September 2012 and will operate in tandem with MetOp-A, increasing the wealth of data even further. The third and final satellite, MetOp-C will be launched in 2016. Launching a new satellite every 5–6 years guarantees a continuous delivery of high-quality data for medium- and long-term weather forecasting and climate monitoring until at least 2020. Group: Platform_Details Entry_ID: METOP-B Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: METOP Short_Name: METOP-B Long_Name: Meteorological Operational Satellite - B End_Group Group: Platform_Associated_Instruments Short_Name: SEM Short_Name: SARSAT Short_Name: MHS Short_Name: IASI Short_Name: HIRS/4 Short_Name: GRAS Short_Name: GOME-2 Short_Name: AVHRR-3 Short_Name: ASCAT Short_Name: ARGOS Short_Name: AMSU-A End_Group Group: Orbit Orbit_Altitude: 840 km Orbit_Inclination: 98.8 degrees Period: 101.7 minutes Repeat_Cycle: 29 days Orbit_Type: LEO > LOW EARTH ORBIT > POLAR SUN-SYNCHRONOUS End_Group Creation_Date: 2012-09-18 Online_Resource: http://www.esa.int/esaLP/SEMN1FAATME_LPmetop_0.html Online_Resource: http://www.nasa.gov/topics/earth/features/metop-b.html Group: Platform_Logistics Launch_Date: 2012-09-17 Launch_Site: BAIKONUR COSMODROME, TYURATAM, RUSSIA Design_Life: EOL July 2017 Primary_Sponsor: ESA Primary_Sponsor: EUMETSAT End_Group End_Group 2017-04-13 14:03:42.0 [mgenazzi] Alternate Label added insert AltLabel (id: null text: Meteorological Operational Satellite - B language code: en); 2012-09-18 21:18:56.0 [saritz] Insert Concept add broader relation (METOP-B [c9f84df0-e807-46e3-8fce-c33e9201fbc2,40601] - METOP [8c192c86-d07c-4e7b-af8f-92aa4b40fca7,31825]); EROS-A1 EROS-A (of Ofeq-3 heritage) is a high-resolution commercial imaging satellite of ImageSat International N.V. headquartered at Limassol, Cyprus, and designed and built by Israeli Aircraft Industries Ltd. (IAI). The overall objective is to launch and operate a constellation of high-resolution commercial satellites, primarily for intelligence and national security applications and to serve a global customer base. The spaceborne remote sensing technology for the EROS family was approved by the government of Israel in Oct. 1996. The EROS program offers a combination of services and products tailored to meet specific customer requirements and budgets: • The option to acquire exclusive imaging rights over a defined footprint or the ability to acquire imagery on an exclusive basis. • Rapid delivery of imagery to the customer, either through direct downlink, electronic transfer or courier. • Provision of low-cost imagery products to support applications in many fields. Spacecraft: The EROS-A satellite structure consists of low-mass composite material with passive thermal control, it is three-axis stabilized. Attitude control and navigation is performed using horizon sensors, sun sensors, gyros and magnetometer, four reaction wheels and thrusters. The pointing accuracy is <0.1º in all three axes, attitude stabilization is < 40 µrad/s, the jitter is < 0.2 µrad. S/C mass = 260 kg (178 kg S/C bus, 42 kg of instrument mass and 30 kg of hydrazine), solar panel power (silicon array, fixed panels) = 450 W (EOL), plus 14 Ah NiCd batteries for eclipse operation, the bus power consumption at imaging session is 300 W. S/C design life = 4 years, however the estimated operational life of the satellite is ten years. RF communications: Imagery is transmitted in X-band at a rate of 70 Mbit/s (RF downlink) to the ground receiving stations, using a 1.5 W transmitter and one of the two existing two-axis gimbaled directional antennas. The EROS satellites are monitored/operated in S-Band (TT&C) via a single ground control station (GCS), located at IAI/MBT in Israel (3 to 4 passes per day and per satellite are in station visibility). The S-band data rate is either 2.5 or 15 kbit/s selectable by the GCS. ImageSat has a global network of ground segment infrastructure, for real-time image data acquisition. This network is comprised of the ImageSat Central Ground Control Station, a network of EROS-compatible Ground Receiving Stations on 5 continents and EROS-compatible Ground Control Stations based at exclusive customers' premises (see SOP Program). The EROS A satellite has limited availability of onboard source data storage, as the satellite was designed to cater to customers acquiring real-time, exclusive imaging and download rights over a defined geographic footprint, in view of their own EROS-compatible GRS (Ground Receiving Stations). Operational capabilities/services primarily include: • Satellite Operating Partner (SOP) Program. This service provides a dedicated regional satellite with local customer tasking. SOP receiving ground stations are able to plan, to generate and to transmit imaging commands to the satellite and to download imagery in real-time. • PAS (Priority Acquisition Service) Program. The service provides highest priority tasking of the EROS satellite, in areas not previously acquired by SOP Customers. • Non-exclusive acquisitions. ImageSat sells EROS imagery on a non-exclusive basis to customers for civilian applications, such as mapping, disaster planning and monitoring, environmental management, homeland security and border control, and a range of development-related projects. aunch: EROS-A was launched on a Russian Start-1 launcher on Dec. 5, 2000 from the Svobodny Cosmodrome in eastern Siberia. Orbit for EROS-A: Circular sun-synchronous orbit, altitude 480 km, inclination = 97.3º, period = 94.7 minutes, local time of descending node at 10:00 hours. The revisit capability at at latitude of 10º within a 15º cone is within 10.5 days. A revisit period/satellite at latitude of 10º is 4.5 days within a 30º cone, and only 2.5 days within a 45º cone. Operational status of mission: The EROS-A spacecraft and all subsystems are operating nominally as of 2008. Operations are expected to last until 2010. Background on EROS program: EROS is a program of ImageSat International, N.V., formerly WIS (West Indian Space) Ltd., Cayman Islands. The name change took place in June 2000. ImageSat was re-incorporated in Curacao, Netherlands Antilles. ImageSat's ownership includes: Israel Aircraft Industries (IAI) of Tel-Aviv (owned by the Israeli government), Elbit Systems Ltd. of Haifa, and private investors from Europe and the United States. • EROS-B was launched on April 25, 2006 on a Start-1 launch vehicle from the Svobodny Cosmodrome in eastern Siberia • A third satellite, EROS C, will offer comparable panchromatic resolution to EROS B, as well as multispectral resolution of 2.8 m GSD; it is planned for launch in 2009. Information obtained from http://www.eoportal.org/ Group: Platform_Details Entry_ID: EROS-A1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: EROS-A1 End_Group Group: Synonymous_Platform_Names Short_Name: Earth Remote Observation System-A End_Group Group: Platform_Associated_Instruments Short_Name: CAMERAS End_Group Group: Orbit Orbit_Altitude: 480 Orbit_Inclination: 97.3 Period: 94.7 Perigee: 498.6 Apogee: 511.2 Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2008-07-09 Online_Resource: http://directory.eoportal.org/get_announce.php?an_id=10063 Group: Platform_Logistics Launch_Date: 2000-12-05 Launch_Site: Svobodny Cosmodrome, Russia Design_Life: 4 years Primary_Sponsor: ImageSat International, Israel End_Group End_Group SMS-2 SMS-2 was launched in February 1975 and was a NASA-developed, NOAA-operated, second prototype spacecraft for the geosynchronous series of meteorological satellites. The cylindrically shaped spacecraft measured 190.5 cm in diameter and 230 cm in length, exclusive of a magnetometer that extended an additional 83 cm beyond the cylinder shell. The primary structural members were a honeycombed equipment shelf and thrust tube. The VISSR telescope was mounted on the equipment shelf and viewed the Earth through a special aperture in the side of the spacecraft. A support structure extended radially from the thrust tube and was affixed to the solar panels, which formed the outer walls of the spacecraft and provided the primary source of electrical power. Located in the annulus-shaped space between the thrust tube and the solar panels were stationkeeping and dynamics control equipment, batteries, and most of the SEM equipment. Proper spacecraft attitude and spin rate (approximately 100 rpm) were maintained by two separate sets of jet thrusters mounted around the spacecraft equator and activated by ground command. The spacecraft used both UHF-band and S-band frequencies in its telemetry and command subsystem. A low-power VHF transponder provided telemetry and command during launch and then served as a backup for the primary subsystem once the spacecraft attained orbit. This spin-stabilized spacecraft carried a visible infrared spin-scan radiometer, meteorological data collection and relay system, space environment monitor, and a biaxial fluxgate magnetometer. Throughout its history, it operated at 75 (replaced SMS-1 in April 1979), 115, and 135 degrees West. __________ Taken from the NSSDC System for Information Retrieval and Storage (SIRS). For more information contact the NSSDC Coordinated Request and User Support Office, 301-286-6695 (NASA Goddard Space Flight Center, Code 933.4, Greenbelt, Maryland 20771, USA, "http://nssdc.gsfc.nasa.gov/"). Group: Platform_Details Entry_ID: SMS-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: SMS (Synchronous Meteorological Satellites) Short_Name: SMS-2 Long_Name: Synchronous Meteorological Satellite 2 End_Group Group: Synonymous_Platform_Names Short_Name: SMS-2 End_Group Group: Platform_Associated_Instruments Short_Name: SXM Short_Name: EPM Short_Name: VISSR Short_Name: DCS Short_Name: Magnetic Field Monitor End_Group Creation_Date: 2007-11-13 Online_Resource: http://goes.gsfc.nasa.gov/text/history/sms/sms2.html Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1975-011A Sample_Image: http://goes.gsfc.nasa.gov/text/history/sms/sms2.gif Group: Platform_Logistics Launch_Date: 1975-02-06 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: USA/NASA Primary_Sponsor: USA/NOAA End_Group End_Group DeepWorker 2000 The one-atmosphere DeepWorker 2000 submersible allows a pilot to go deeper and spend more time below the surface than traditional diving methods. The compact and lightweight DeepWorker 2000 is easy to operate and can be piloted with minimal training. Horizontal and vertical thrusters give unparalleled manoeuvrability; the DeepWorker 2000 can hover and ‘fly’ underwater. DeepWorker 2000 is also available in a 3300ft (1000m) configuration as a DeepWorker 3000. 2020-01-21 19:17:07.0 [tstevens] insert Definition (id: null text: The one-atmosphere DeepWorker 2000 submersible allows a pilot to go deeper and spend more time below the surface than traditional diving methods. The compact and lightweight DeepWorker 2000 is easy to operate and can be piloted with minimal training. Horizontal and vertical thrusters give unparalleled manoeuvrability; the DeepWorker 2000 can hover and ‘fly’ underwater. DeepWorker 2000 is also available in a 3300ft (1000m) configuration as a DeepWorker 3000. language code: en); 2020-01-21 17:31:24.0 [tstevens] Insert Concept add broader relation (DeepWorker 2000 [caa8300a-560a-4190-b257-6f8d33f6f134,559763] - HOV [63c8aa1d-6efc-4943-8891-3a1cd520dde0,559759]); DMSP 5D-1/F2 [Source: National Space Science Data Center, http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1977-044A ] DMSP 5D-1/F2 was one of a series of meteorological satellites developed and operated by the Air Force under the Defense Meteorological Satellite Program (DMSP). This program, previously known as DAPP (Data Acquisition and Processing Program), was classified until March 1973. The objectives of this program were to provide global visual and infrared cloud cover data and specialized environmental data to support Department of Defense requirements. Operationally, the program consisted of two satellites in planned 830-km sun-synchronous polar orbits, with the ascending node of one satellite in early morning and the other at local noon. The 5.4-m long spacecraft was separated into four sections: (1) a precision mounting platform (PMP) for sensors and equipment requiring precise alignment, (2) an equipment support module (ESM) containing the electronics, reaction wheels, and some meteorological sensors, (3) a reaction control equipment (RCE) support structure (that has the third-stage motor, hydrazine reaction control system) which supports (4) a 9.29 sq mm solar cell panel. The spacecraft stabilization was controlled by a combination flywheel and magnetic control coil system so sensors could be maintained in the desired `earth-looking' mode. One feature was the precision-pointing accuracy of the primary imager to 0.01 deg provided by a star sensor and an updated ephemeris navigation system. This allowed automatic geographical mapping of the digital imagery to the nearest picture element. The operational line scan system (OLS) built by Westinghouse, was the primary data acquisition system that provided real-time or stored, multi-orbit, day-and-night visual and infrared imagery at 1/3-nautical-mile resolution for all major land masses, 1-1/2-nautical-mile resolution for complete global coverage, and provided with this data calibration, timing, and other auxiliary signals to the spacecraft for digital transmission to the ground. A supplementary sensor package, the special sensor H (SSH), a step-scanning radiometer, was the infrared temperature-humidity-ozone sounder. The data processing system, which included three high-density tape recorders, was capable of storing a total of 400 min of data, each allowing full global coverage twice daily. Either recorded or real-time data were transmitted to ground-receiving sites via two redundant S-band transmitters. Recorded data were read out to tracking sites located at Fairchild AFB, WA, and Loring AFB, ME, and relayed via SATCOM to Air Force Global Weather Central, Offutt AFB, NE. Real-time data were read out at mobile tactical sites located around the world. A more complete description of the satellite can be found in the report, `The Defense Meteorological Satellite Program,' D. A. Nichols, Optical Engineering, 14, 4, July - August 1975. Group: Platform_Details Entry_ID: DMSP 5D-1/F2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: DMSP (Defense Meteorological Satellite Program) Short_Name: DMSP 5D-1/F2 Long_Name: Defense Meteorological Satellite Program-F2 End_Group Group: Synonymous_Platform_Names Short_Name: AMS 2 Short_Name: Advanced Meteorological Satellite 2 Short_Name: DMSP 13536 Short_Name: DMSP-F2 Short_Name: 10033 End_Group Group: Platform_Associated_Instruments Short_Name: SSB/O Short_Name: PASSIVE IONOSPHERIC MONITOR Short_Name: OLS Short_Name: MFR/SSH Short_Name: PES (SSJ/3) Short_Name: SSI/E End_Group Group: Orbit Orbit_Inclination: 99.0° Period: 101.7 minutes Perigee: 811.0 km Apogee: 869.0 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-09-14 Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1977-044A Online_Resource: http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/dmsp.html Online_Resource: http://www.ngdc.noaa.gov/dmsp/ Group: Platform_Logistics Launch_Date: 1977-06-05 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: Department of Defense-Department of the Air Force (United States) End_Group End_Group KOMPSAT-1 Kompsat-1 was a high resolution optical mission of Korea launched in 1999. Through a 3rd party mission agreement, ESA makes a sample dataset of European cities available from this satellite. The Kompsat program was initiated in 1995 as a major space investment in Korea. Its objective was the development of a national space segment in Earth observation along with an efficient infrastructure and ground segment to provide valuable services to remote sensing users in various fields of applications. 2019-02-21 10:06:02.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: a6c03baf-042d-412e-af18-3c5bd6fa8770 relationship type: null relationship value: null generated by: null); 2018-06-12 16:36:02.0 [mmorahan] Move Concepts delete broader relation (null); add broader relation (KOMPSAT-1 [caf7cd97-6a64-4e31-9b7e-d96854eb9b6a,367675] - KOMPSAT [9abdb7c0-7b8e-426b-8bc7-57ea4a30d82c,367679]); 2018-06-12 16:23:43.0 [mmorahan] insert Definition (id: null text: Kompsat-1 was a high resolution optical mission of Korea launched in 1999. Through a 3rd party mission agreement, ESA makes a sample dataset of European cities available from this satellite. The Kompsat program was initiated in 1995 as a major space investment in Korea. Its objective was the development of a national space segment in Earth observation along with an efficient infrastructure and ground segment to provide valuable services to remote sensing users in various fields of applications. language code: en); 2018-06-12 16:20:35.0 [mmorahan] Insert Concept add broader relation (KOMPSAT-1 [caf7cd97-6a64-4e31-9b7e-d96854eb9b6a,367675] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761]); AEM-1 AEM-1, also known as Heat Capacity Mapping Mission (HCMM), was the first of the Applications Explorer Missions. The objective of the HCMM was to provide comprehensive, accurate, high-spatial-resolution thermal surveys of the surface of the earth. More information can be found at: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1978-041A Group: Platform_Details Entry_ID: AEM-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: AEM (Applications Explorer Mission) Short_Name: AEM-1 Long_Name: Applications Explorer Mission-1 End_Group Group: Synonymous_Platform_Names Short_Name: HCMM Short_Name: AEM-A End_Group Group: Platform_Associated_Instruments Short_Name: RADIOMETERS End_Group Creation_Date: 2012-01-27 Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1978-041A Group: Platform_Logistics Launch_Date: 1978-04-26 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: NASA-Office of Space and Terrestrial Applications End_Group End_Group Johnson-Sea-Link II The Johnson-Sea-Link I and II were retired by Harbor Branch Oceanographic Institution in 2011 after their support ship the R/V Seward Johnson was sold to Cepemar Environmental Services of Brazil. The Johnson-Sea-Link (JSL) I and II are owned and operated by Harbor Branch Oceanographic Institution. At 23.6 ft long, 10.9 ft high and 8.3 ft wide, these highly maneuverable submersibles can dive to a depth of 3,000 ft and travel at a maximum speed of one knot. Edwin Albert Link, engineer, inventor, and friend of Harbor Branch founder Seward Johnson, working at Harbor Branch, designed and built the JSL in 1971, at Mr. Johnson’s request. Harbor Branch constructed the JSL II, which is virtually identical to the JSL I, in 1975. The JSL has two separate pressure hulls and can accommodate four people. Aft compartment occupants enter the sub through a bottom-facing 20 inch-wide hatch. The front chamber, which contains the sub’s controls, is a 5-ft-diameter sphere made of five-in thick, clear acrylic. It provides a panoramic view for the pilot and one observer. Because acrylic is a good insulator and hampers conductivity of cold ocean temperatures, the front compartment actually requires air conditioning. The second chamber, the stern compartment, houses another crew member and a second observer. The occupants have access to two side view ports and a video monitor. 2020-01-21 19:26:31.0 [tstevens] insert Definition (id: null text: The Johnson-Sea-Link I and II were retired by Harbor Branch Oceanographic Institution in 2011 after their support ship the R/V Seward Johnson was sold to Cepemar Environmental Services of Brazil. The Johnson-Sea-Link (JSL) I and II are owned and operated by Harbor Branch Oceanographic Institution. At 23.6 ft long, 10.9 ft high and 8.3 ft wide, these highly maneuverable submersibles can dive to a depth of 3,000 ft and travel at a maximum speed of one knot. Edwin Albert Link, engineer, inventor, and friend of Harbor Branch founder Seward Johnson, working at Harbor Branch, designed and built the JSL in 1971, at Mr. Johnson’s request. Harbor Branch constructed the JSL II, which is virtually identical to the JSL I, in 1975. The JSL has two separate pressure hulls and can accommodate four people. Aft compartment occupants enter the sub through a bottom-facing 20 inch-wide hatch. The front chamber, which contains the sub’s controls, is a 5-ft-diameter sphere made of five-in thick, clear acrylic. It provides a panoramic view for the pilot and one observer. Because acrylic is a good insulator and hampers conductivity of cold ocean temperatures, the front compartment actually requires air conditioning. The second chamber, the stern compartment, houses another crew member and a second observer. The occupants have access to two side view ports and a video monitor. language code: en); 2020-01-21 17:35:05.0 [tstevens] Insert Concept add broader relation (Johnson-Sea-Link II [cb5ab3cc-48d1-4b0c-b72b-700a6faee11e,559779] - HOV [63c8aa1d-6efc-4943-8891-3a1cd520dde0,559759]); BAPMON Background Air Pollution Monitoring Network (BAPMoN): A network of stations that collect rain water samples which are sent to the Central Chemical Laboratory at Pune for complete chemical analysis. Acidity of rain and mineral deposition is determined from these. Atmospheric turbidity which indicates the columnar aerosol load of the atmosphere, is also measured at these stations using sunphotmeters. These data are important for identifying the current levels of pollution as well as for study of the long term trends in the concentration of trace constituents of the atmosphere which may affect the environment and induce a climate change. ATS-4 ATS 4 was launched in August 1968 and was a gravity-gradient-stabilized spacecraft designed to (1) test new concepts in spacecraft design, propulsion, and stabilization, (2) take high-quality cloud cover pictures, (3) provide in situ measurements of the aerospace environment, and (4) test improved communication systems while in earth-synchronous orbit. The cylindrically-shaped spacecraft measured 142 cm in diameter and 183 cm in length. The primary structural members were a corrugated thrust tube with honeycombed bulkheads secured to each end. Equipment components and payload were externally mounted on the outer surface of the thrust tube as well as on a structure that slid into the interior of the thrust tube. Electric power was provided by two solar arrays mounted on either end of the spacecraft's outer shell and by two rechargeable nickel-cadmium batteries. Extending radially outward from the side of the spacecraft were four 28.2 m adjustable gravity-gradient booms. The spacecraft telemetry system consisted of four 2.1-W transmitters, (two at 136.47 MHz and two at 137.35 MHz), in addition to a microwave communications experiment. This satellite featured an image orthicon (day/night) camera for the purpose of determining the feasibility of simultaneous day/night imaging of cloud cover patterns from an earth-synchronous spacecraft. The second stage of the launch vehicle failed to to ignite, and the planned synchronous orbit was not achieved. The spacecraft and its Centaur booster rocket were left attached together in a parking orbit. In spite of the anomalistic attitude, some of the experiments did perform successfully before the satellite and its attached rocket booster reentered the earth's atmosphere on October 17, 1968. The primary objective of inserting a gravity-gradient-stabilized spacecraft into a geosynchronous orbit was not accomplished. Group: Platform_Details Entry_ID: ATS-4 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: ATS (Advanced Technology Satellite) Short_Name: ATS-4 Long_Name: Advanced Technology Satellite-4 End_Group Creation_Date: 2007-08-29 Online_Resource: http://www.astronautix.com/craft/ats4.htm Group: Platform_Logistics Launch_Date: 1968-08-10 Primary_Sponsor: NASA End_Group End_Group GOES-16 GOES-R The Geostationary Operational Environmental Satellite-R Series (GOES-R) is the nation’s next generation of geostationary weather satellites. The GOES-R series will significantly improve the detection and observation of environmental phenomena that directly affect public safety, protection of property and our nation’s economic health and prosperity. 2017-06-28 20:52:01.0 [sritz] insert WeightedRelation (id: null related concept uuid: ec7681c4-fbcd-4c58-8f0b-5a9b59b0b56d relationship type: null relationship value: null generated by: null); 2017-06-28 20:44:46.0 [sritz] insert WeightedRelation (id: null related concept uuid: 12a671f6-d18d-405a-9ff5-432ef2b94135 relationship type: null relationship value: null generated by: null); 2016-12-01 17:33:26.0 [saritz] S. Ritz changed name to GOES-16 following NOAA protocol. insert Definition (id: null text: The Geostationary Operational Environmental Satellite-R Series (GOES-R) is the nation’s next generation of geostationary weather satellites. The GOES-R series will significantly improve the detection and observation of environmental phenomena that directly affect public safety, protection of property and our nation’s economic health and prosperity. language code: en); 2016-12-01 17:30:28.0 [saritz] S. Ritz changed name to GOES-16 following NOAA protocol. update AltLabel (Geostationary Operational Environmental Satellite 16); 2016-12-01 16:51:30.0 [saritz] S. Ritz changed name to GOES-16 following NOAA protocol. insert AltLabel (id: null text: GOES-R language code: en); update PrefLabel (GOES-16); GEO-CAPE [Source: NASA GEO-CAPE, https://geo-cape.larc.nasa.gov/] The GEOstationary Coastal and Air Pollution Events (GEO-CAPE) mission was recommended by the NRC's Earth Science Decadal Survey to measure tropospheric trace gases and aerosols and coastal ocean phytoplankton, water quality and biogeochemistry from geostationary orbit, providing multiple daily observations within the field of view. Multiple observations per day are required to explore the physical, chemical, and dynamical processes that determine tropospheric composition and air quality over spatial scales ranging from urban to continental, and over temporal scales ranging from diurnal to seasonal. Likewise, high frequency satellite observations are critical to studying and quantifying biological, chemical, and physical processes within the coastal ocean and beyond. Group: Platform_Details Entry_ID: GEO-CAPE Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NASA Decadal Survey Short_Name: GEO-CAPE Long_Name: Geostationary Coastal and Air Pollution Events End_Group Group: Orbit Orbit_Type: GEO > GEOSYNCHRONOUS > GEOSTATIONARY End_Group Creation_Date: 2010-05-04 Online_Resource: https://geo-cape.larc.nasa.gov/ Group: Platform_Logistics Primary_Sponsor: USA/NASA End_Group End_Group 2020-01-03 23:36:25.0 [sritz] update Definition ([Source: NASA GEO-CAPE, https://geo-cape.larc.nasa.gov/] The GEOstationary Coastal and Air Pollution Events (GEO-CAPE) mission was recommended by the NRC's Earth Science Decadal Survey to measure tropospheric trace gases and aerosols and coastal ocean phytoplankton, water quality and biogeochemistry from geostationary orbit, providing multiple daily observations within the field of view. Multiple observations per day are required to explore the physical, chemical, and dynamical processes that determine tropospheric composition and air quality over spatial scales ranging from urban to continental, and over temporal scales ranging from diurnal to seasonal. Likewise, high frequency satellite observations are critical to studying and quantifying biological, chemical, and physical processes within the coastal ocean and beyond. Group: Platform_Details Entry_ID: GEO-CAPE Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NASA Decadal Survey Short_Name: GEO-CAPE Long_Name: Geostationary Coastal and Air Pollution Events End_Group Group: Orbit Orbit_Type: GEO > GEOSYNCHRONOUS > GEOSTATIONARY End_Group Creation_Date: 2010-05-04 Online_Resource: https://geo-cape.larc.nasa.gov/ Group: Platform_Logistics Primary_Sponsor: USA/NASA End_Group End_Group); update Definition (NASA GEO-CAPE, https://geo-cape.larc.nasa.gov/); GOES-5 [Source: NSSDC, http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-049A ] GOES 5 was launched in May 1981 and was a NASA-developed, NOAA-operated, geosynchronous, and operational spacecraft. The cylindrically shaped spacecraft measured 190.5 cm in diameter and 230 cm in length, exclusive of a magnetometer that extended an additional 83 cm beyond the cylinder shell. The primary structural members were a honeycombed equipment shelf and thrust tube. The VISSR telescope was mounted on the equipment shelf and viewed the Earth through a special aperture in the side of the spacecraft. A support structure extended radially out from the thrust tube and was affixed to the solar panels, which formed the outer walls of the spacecraft and provided the primary source of electrical power. Located in the annulus-shaped space between the thrust tube and the solar panels were stationkeeping and dynamics control equipment, batteries, and most of the SEM equipment. Proper spacecraft attitude and spin rate (approximately 100 rpm) were maintained by two separate sets of jet thrusters mounted around the spacecraft equator and activated by ground command. The spacecraft used both UHF-band and S-band frequencies in its telemetry and command subsystem. A low-power VHF transponder provided telemetry and command during launch and then served as a backup for the primary subsystem once the spacecraft attained orbit. The spin-stabilized spacecraft carried a visible infrared spin-scan radiometer atmospheric sounder, meteorological data collection and transmission system, space environment monitor, and a biaxial fluxgate magnetometer. It operated at at 75 degrees West as GOES-EAST, but on July 30, 1984, GOES 5 VAS experienced a failure, thus NOAA had to relocate GOES 6 to a more central 98 degrees West position, and to reactivate GOES 1 and GOES 4 for the acquisition and relay of VISSR information, respectively, from the western U.S. For more information on GOES satellites: http://www.oso.noaa.gov/goes/ Group: Platform_Details Entry_ID: GOES-5 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: GOES (Geostationary Operational Environmental Satellite) Short_Name: GOES-5 Long_Name: Geostationary Operational Environmental Satellite 5 End_Group Group: Synonymous_Platform_Names Short_Name: GOES E Short_Name: 12472 End_Group Group: Platform_Associated_Instruments Short_Name: SXM Short_Name: VAS End_Group Group: Orbit Orbit_Type: GEO > Geosynchronous > Geostationary End_Group Creation_Date: 2007-10-04 Online_Resource: http://www.oso.noaa.gov/goes/ Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-049A Group: Platform_Logistics Launch_Date: 1981-05-22 Launch_Site: CAPE CANAVERAL/KENNEDY SPACE CENTER, USA Primary_Sponsor: USA/NASA Primary_Sponsor: USA/NOAA End_Group End_Group STS-99 The primary objective of the STS-99 mission was to complete high resolution mapping of large sections of the Earth's surface using the Shuttle Radar Topography Mission (SRTM), a specially modified radar system. This radar system produced unrivaled 3-D images of the Earth's Surface. The mission was launched at 1231 on February 11, 2000 onboard the space shuttle Endeavour, and led by Commander Kevin Kregel. The crew was Pilot Dominic L. Pudwill Gorie and Mission Specialists Janet L. Kavandi, Janice E. Voss, Mamoru Mohri from the National Space Development Agency (Japanese Space Agency), and Gerhard P. J. Thiele from DARA (German Space Agency). This videotape shows a press briefing about a mechanical problem that the shuttle was having. There was discussion about possibly scrubbing the launch due to the problem with the Enhanced Master Events Controller. A problem with a fuel pump part had also become evident and there was discussion about the impact that this could have on the flight. Group: Platform_Details Entry_ID: STS-99 Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Platform_Series_or_Entity: SPACE SHUTTLE Short_Name: STS-99 Long_Name: Space Transport System STS-99 End_Group Group: Platform_Associated_Instruments Short_Name: CAMERAS Short_Name: SRTM End_Group Group: Orbit Orbit_Altitude: 126 nm Orbit_Inclination: 57 degrees End_Group Creation_Date: 2007-08-21 Online_Resource: http://science.ksc.nasa.gov/shuttle/missions/sts-99/mission-sts-99.html Group: Platform_Logistics Launch_Date: 2000-02-11 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: USA/NASA End_Group End_Group 2018-09-18 20:38:54.0 [sritz] update WeightedRelation (Platform-Instrument); update WeightedRelation (1); 2018-09-18 20:38:21.0 [sritz] insert WeightedRelation (id: null related concept uuid: 7b241f5e-a68a-491a-830b-22ecf48a57e3 relationship type: null relationship value: null generated by: null); MIDAS 2 The MIDAS 2 (Missile Defense Alarm System) satellite was an earth-orbiting satellite designed to measure IR background and define IR sources. In addition, the satellite carried experiments to measure cosmic radiation, atmospheric density, thermal emission and reflected solar radiation from the earth, and micrometeorites. A plasma probe was included too. The spacecraft was chemical-battery powered. IR radiation data were received for the lifetime of the battery pack, which powered the final transmission on May 26, 1960. __________ Taken from the NSSDC System for Information Retrieval and Storage (SIRS). For more information contact the NSSDC Coordinated Request and User Support Office, 301-286-6695 (NASA Goddard Space Flight Center, Code 933.4, Greenbelt, Maryland 20771, USA). FIELD SURVEYS FIELD SURVEY Field Surveys Field Surveys are surveys carried out in the field rather than in a laboratory or headquarters. [Source: WordNet 1.6, 1997 Princeton University] Group: Platform_Details Entry_ID: FIELD SURVEYS Group: Platform_Identification Platform_Category: In Situ Land-based Platforms Short_Name: FIELD SURVEYS End_Group Group: Synonymous_Platform_Names Short_Name: Field Surveys End_Group Creation_Date: 2007-12-12 End_Group 2016-06-09 18:39:20.0 [epneff] added altLabel insert AltLabel (id: null text: FIELD SURVEY language code: en); insert AltLabel (id: null text: Field Surveys language code: en); GOES-12 OES-12 (GOES-M) was launched July 23, 2001 from Cape Canaveral Air Station. On Tuesday April 1, 2003 at approximately 1815 UTC, GOES-12 replaced GOES-8 as the operational GOES East Satellite. The spacecraft will perform long term geostationary monitoring of U.S. weather. GOES 12's mission is the monitoring of hurricanes, severe thunderstorms, flash floods, and other severe weather as well as providing short-term weather forecasting or nowcasting. Combined with Doppler radar and automated surface weather stations, real-time GOES data greatly aids weather foecasters in providing better warnings of severe weather. NOAA's National Environmental Satellite, Data, and Information Service will operate GOES. The instrument package includes a GOES I-M Imager and GOES I-M Sounder. 2017-09-01 16:53:20.0 [sritz] insert Definition (id: null text: OES-12 (GOES-M) was launched July 23, 2001 from Cape Canaveral Air Station. On Tuesday April 1, 2003 at approximately 1815 UTC, GOES-12 replaced GOES-8 as the operational GOES East Satellite. The spacecraft will perform long term geostationary monitoring of U.S. weather. GOES 12's mission is the monitoring of hurricanes, severe thunderstorms, flash floods, and other severe weather as well as providing short-term weather forecasting or nowcasting. Combined with Doppler radar and automated surface weather stations, real-time GOES data greatly aids weather foecasters in providing better warnings of severe weather. NOAA's National Environmental Satellite, Data, and Information Service will operate GOES. The instrument package includes a GOES I-M Imager and GOES I-M Sounder. language code: en); 2017-09-01 16:46:52.0 [sritz] Insert Concept add broader relation (GOES-12 [ccc4869c-ff0c-41ef-b621-eaeae1ffb79b,310119] - GOES [6e332c25-caeb-4917-afb6-af757bcecd72,310071]); DRILLING PLATFORMS A drilling platform is a horizontal surface raised above the level of the adjacent area where a drill can be erected. [Source: The American Heritage Dictionary.] IRS-P6 The RESOURCESAT-1 (IRS-P6) is envisaged as the continuity mission to IRS-1C/1D, with enhanced capabilities both in the payload and the platform, to meet the increasing demands of the user community. The objectives of the mission are : -To provide continued remote sensing data services on an operational basis for integrated land and water resources management at micro level, with enhanced spectral and spatial coverage and stereo imaging. -To further carry out studies in advanced areas of user applications like improved crop discrimination, crop yield, crop stress, pest/disease surveillance, disaster management etc.,. The life of the mission is planned to be five years. The satellite was launched by the indigenously built Polar Satellite Launch Vehicle on October 17, 2003. The orbit parameters of IRS-P6 are same as IRS-1C. [Summary provided by the Indian Remote Sensing Agency.] Group: Platform_Details Entry_ID: IRS-P6 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: IRS (Indian Remote Sensing Satellite) Short_Name: IRS-P6 Long_Name: Indian Remote Sensing Satellite-P6 End_Group Group: Synonymous_Platform_Names Short_Name: IRS-P6 Short_Name: ResourceSat-1 End_Group Group: Platform_Associated_Instruments Short_Name: LISS-IV Short_Name: LISS-III Short_Name: AWIFS End_Group Group: Orbit Orbit_Altitude: 817 km Orbit_Inclination: 98.69 deg Equator_Crossing: 10.30 A.M Period: 101.35 min Repeat_Cycle: 24 days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-10-05 Online_Resource: http://www.isro.gov.in/satellites/irs-p6resourcesat-1.aspx Sample_Image: http://www.isro.gov.in/satellites/images/irsp6_img.gif Group: Platform_Logistics Launch_Date: 2003-10-17 Launch_Site: Sriharikota Island, India Design_Life: 5 years Primary_Sponsor: India End_Group End_Group R/V AKADEMIK M.A. LAVRENTYEV 2013-06-11 20:05:54.0 [aaleman] Insert Concept add broader relation (R/V AKADEMIK M.A. LAVRENTYEV [cdc27a9f-6118-4ab8-bf2c-d762e6dbbbdf,105209] - SHIPS [82a67b12-e99d-4c90-8a6a-a6f79d4c3c7b,73407]); MOS-1 NASDA launched the Japanese Marine Observation Satellite 1(MOS-1) on February 19, 1987. The MOS-1 carries three instruments on board, the MESSR (Multispectrum Electronic Self Scanning Radiometer), VTIR (Visible and Thermal Infrared Radiometer) and MSR (Microwave Scanning Radiometer). MOS-1 is Japan's first earth observation satellite which has a sun-synchronous and sub-recurrent orbit at a nominal altitude of 909 km and an inclination of 99 deg. The local mean time at descending node is 10:00-11:00 AM. MOS-1/b, which carries the same sensors as MOS-1 was launched on February 7, 1990 to provide continuous data to users. The following is a summary of MOS-1 and MOS-1/b. NAME LAUNCHED ALTITUDE INCLINATION INSTRUMENTS (KM) (DEG) ------- --------- -------- ----------- -------------- MOS-1 19 FEB 87 909 99 MESSR, VTIR, MSR MOS-1/b 7 FEB 90 909 99 MESSR, VTIR, MSR --------------- Contributed by: Tasuku Tanaka, Earth Observation Program Office Director, Program Planning and Management Department, National Space Development Agency of Japan Head Office, Hamamatsu-cho, Minato-ku, Tokyo, Japan Takeshi Osugi, Earth Observation Center Director, National Space Development Agency of Japan, Ohashi Hatoyama-machi, Hiki-gun, Saitama pref, Japan Group: Platform_Details Entry_ID: MOS-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: MOS (Japan Marine Observation Satellite) Short_Name: MOS-1 Long_Name: Japanese Marine Observation Satellite 1 End_Group Group: Synonymous_Platform_Names Short_Name: Momo-1 End_Group Group: Platform_Associated_Instruments Short_Name: MSR Short_Name: VTIR Short_Name: MESSR End_Group Online_Resource: http://www.jaxa.jp/projects/sat/mos1/index_e.html Online_Resource: http://nasascience.nasa.gov/missions/mos Group: Platform_Logistics Launch_Date: 1987-02-19 Launch_Site: Tanegashima Island, Japan Primary_Sponsor: Japan/JAXA End_Group End_Group PROBA-2 EROS-B1 EROS-B is a high-resolution commercial imaging minisatellite mission of ImageSat International N.V. headquartered in the Netherlands Antilles (Cayman Islands), with offices in Limassol, Cyprus, and in Tel Aviv, Israel. The overall objective is to provide high-resolution imagery to the customer base. Spacecraft: The EROS-B series S/C structure is identical to that of EROS-A, based on the Ofeq platform of Israel's Defense Ministry, and designed and built by Israel Aircraft Industries Ltd. (IAI/MBT). The deployed S/C structure is 2.3 m high and 4.0 m wide. The S/C is is 3-axis stabilized and the light/rigid design of the EROS satellite family allows for a great degree of platform agility. The spacecraft is very agile, a body-pointing capability of ±45º from nadir is provided in all directions, supporting the daily data acquisition plan. The S/C attitude is sensed and controlled as done with EROS-A. In addition, there is a star sensor for the B satellite series. The nominal S/C design life is six years. The nominal S/C launch mass is ~290 kg; however, additional onboard fuel (up to 60 kg) is sufficient for S/C operations of up to 10 years. This increased the spacecraft launch mass to about 350 kg. Orbit: Sun-synchronous circular orbit, mean altitude = 500 km, inclination = 97.4º, local time of descending node (LTDN) at 14:00 hours. - Note: The orbits of EROS-A and EROS-B are phased in the same orbital plane thereby increasing the revisit time of the constellation. Launch: A launch of EROS-B took place on April 25, 2006 on a Start-1 launch vehicle from the Svobodny Cosmodrome in eastern Siberia (location at: 51.4º N, 128.3º E). 3) RF communications: Imagery is transmitted in X-band at a rate of 280 Mbit/s (downlink) to the ground receiving stations, using a 1.5 W transmitter and one of the two existing two-axis gimbaled directional antennas. The EROS satellites are monitored/operated in S-Band (TT&C) via a single ground control station (GCS), located at IAI/MBT in Israel (3 to 4 passes per day and per satellite are in station visibility). The S-band data rate is either 2.5 or 15 kbit/s selectable by the GCS. ImageSat has a global network of ground segment infrastructure, for real-time image data acquisition. This network is comprised of the ImageSat Central Ground Control Station, a network of EROS-compatible Ground Receiving Stations on 5 continents and EROS-compatible Ground Control Stations based at exclusive customers' premises. Sensor complement: (PIC-2) PIC-2 (Panchromatic Imaging Camera-2), designed and developed by ElOp (Electro Optical Industries) of Rehovot, Israel, a subsidiary of Elbit Systems Ltd. The EROS-B series imager instrument features CCD pushbroom technology in combination with a TDI (Time Delay Integration) scheme in its focal plane, a cumulative expose concept of each ground image line by a CCD detector array, to improve the SNR value (an important issue for high-resolution imaging). The instrument uses also a Cassegrain telescope with an aperture of 50 cm in diameter and a focal length of 5 m (folded optics). FOV = 1.5º. The PIC-2 instrument is rigidly mounted to the S/C structure looking into the nadir direction, thus permitting a body-pointing observation scheme. he CCD pushbroom detector array provides 10,000 pixels per line and a total of 96 lines for selectable TDI observation support. Pushbroom scanning is provided for panchromatic imagery only in the spectral range of 0.5 - 0.9 μm. The ground sampling distance (GSD) is 0.70 m, the swath width is 7 km at nadir. The data is quantized at 10 bit/sample. The imager instrument of EROS-B spacecraft can be operated in either asynchronous or in synchronous imaging mode. In synchronous mode, the S/C platform keeps a constant pointing angle toward the Earth's surface. In asynchronous mode, imaging by the detector array is performed in a "step-and-stare" fashion, i.e., by slewing the S/C platform in the along-track direction (this permits in particular the generation of mosaics as well as the support of stereo imaging of targets of interest). Information obtained from http://www.eoportal.org/ Group: Platform_Details Entry_ID: EROS-B1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: EROS-B1 End_Group Group: Platform_Associated_Instruments Short_Name: CAMERAS End_Group Group: Orbit Orbit_Altitude: 500 Orbit_Inclination: 97.4 Period: 94.7 Perigee: 503.5 Apogee: 514.7 Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2008-07-09 Online_Resource: http://directory.eoportal.org/get_announce.php?an_id=12460 Group: Platform_Logistics Launch_Date: 2006-04-25 Launch_Site: Svobodny Cosmodrome, Russia Design_Life: 10 years Primary_Sponsor: ImageSat International, Israel End_Group End_Group YOHKOH The YOHKOH satellite, also called "Sunbeam" was launched into space from the Kagoshima Space Center (KSC) in Southern Japan. This is a project of the Japanese Institute of Space and Astronautical Science (ISAS). The scientific objective has been to observe the energetic phenomena taking place on the Sun, specifically solar flares in x-ray and gamma-ray emissions. Instruments on the satellite: the Bragg Crystal Spectrometer (BCS) the Wide Band Spectrometer (WBS) the Soft X-Ray Telescope (SXT) the Hard X-Ray Telescope (HXT) Additional information available at "http://hesperia.gsfc.nasa.gov/sftheory/yohkoh.htm" [Summary provided by NASA] Group: Platform_Details Entry_ID: YOHKOH Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Short_Name: YOHKOH End_Group Group: Synonymous_Platform_Names Short_Name: Solar-A Short_Name: 1991-062A Short_Name: 21694 End_Group Group: Platform_Associated_Instruments Short_Name: WBS Short_Name: SXT Short_Name: BCS Short_Name: HXT End_Group Group: Orbit Orbit_Inclination: 31.3 degrees Period: 97.9 m Perigee: 517.9 km Apogee: 792.6 km Orbit_Type: LEO > Low Earth Orbit > Inclined Non-Polar End_Group Creation_Date: 2008-01-17 Online_Resource: http://solarscience.msfc.nasa.gov/Yohkoh.shtml Online_Resource: http://hesperia.gsfc.nasa.gov/sftheory/yohkoh.htm Online_Resource: http://umbra.nascom.nasa.gov/yohkoh_archive.html Sample_Image: http://solarscience.msfc.nasa.gov/images/yohkoh.jpg Group: Platform_Logistics Launch_Date: 1991-08-30 Launch_Site: Uchinoura Space Center, Japan Primary_Sponsor: JAXA Primary_Sponsor: NASA End_Group End_Group METEOSAT-4 Designation: 19876 / 89020B Launch date: 6 Mar 1989 Country of origin: Europe Mission: Meteorology Launch vehicle: Ariane V29 Prime contractor: Aerospatiale Mass at launch: 681 kg Mass in orbit: 316 kg Diameter: 2.1 m Height: 3.1 m Stabilization: Spin stabilized (100 rpm) DC power: BOL: 387 W EOL: 225 W Design lifetime: 5 years Additional information available at "http://www.tbs-satellite.com/tse/online/sat_meteosat_4.html" NIGERIASAT-1 SSTL developed the NigeriaSat-1 enhanced microsatellite during a know-how and technology transfer program for the Federal Ministry of Science and Technology (FMST) of Nigeria. NigeriaSat-1 is the first step in FMSTs plan to develop Nigerias national space infrastructure. The NigeriaSat-1 programme included the satellite, a mission control station in Abuja, Nigeria and hands-on training at Surrey for a team of Nigerian engineers. During the project, Nigeria formed a National Space Research and Development Agency (NASRDA), which now manages the NigeriaSat-1 program. NigeriaSat-1 is a satellite of the standard Disaster Monitoring Constellation (DMC) design. It carries an optical imaging payload developed by SSTL to provide 32-m ground resolution with an exceptionally wide swath width of over 640 km. The payload uses green, red and near infrared bands equivalent to Landsat TM+ bands 2, 3 and 4. Images are stored in a 1-gigabyte solid-state data recorder and returned via an 8-Mbps S-band downlink. NigeriaSat-1 can image scenes as large as 640 x 560 km, providing unparalleled wide-area, medium-resolution data. The data will be used within Nigeria to monitor pollution, land use and other medium-scale phenomena. . In addition, NASRDA have joined the Disaster Monitoring Constellation (DMC) Consortium, and images from NigeriaSat-1 will be available to disaster relief agencies world-wide through the DMC data sharing system. NigeriaSat-1 was launched in September 2003 from Pletsesk on a Kosmos launch vehicle, one of three satellites simultaneously launched to complete the first phase of the Disaster Monitoring Constellation, to provide medium-resolution imagery with daily worldwide revisit. The objective is to provide a daily global imaging capability at medium resolution (30-40 m), in 3-4 spectral bands, for rapid-response disaster monitoring and mitigation. Group: Platform_Details Entry_ID: NIGERIASAT-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: NIGERIASAT-1 End_Group Group: Platform_Associated_Instruments Short_Name: SLIM-6 End_Group Group: Orbit Orbit_Altitude: 686 km Orbit_Inclination: 98 degrees Period: 98.4 min Perigee: 675 km Apogee: 692 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2008-06-02 Online_Resource: http://www.dmcii.com/ Online_Resource: http://www.skyrocket.de/space/doc_sdat/nigeriasat-1.htm Online_Resource: https://directory.eoportal.org/web/eoportal/satellite-missions/n/nigeriasat-2 Group: Platform_Logistics Launch_Date: 2003-09-27 Launch_Site: Plesetsk Cosmodrome, Russia Primary_Sponsor: Nigeria Primary_Sponsor: SSTL End_Group End_Group NOT APPLICABLE 2015-09-01 17:55:40.0 [tbs1979] Insert Concept add broader relation (NOT APPLICABLE [cffdd7e9-e25d-4c85-86ae-ff651532f02e,158347] - NOT APPLICABLE [76b8f939-8558-4a10-8139-c7f8a0162102,158343]); ERA15DAS 2015-08-10 18:42:44.0 [epneff] Added long name insert AltLabel (id: null text: ERA15 Data Assimilation System language code: en); 2015-08-10 18:42:27.0 [epneff] Insert Concept add broader relation (ERA15DAS [d022dc0f-0ce8-471a-ac6c-aabb48542cf4,158219] - Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215]); STS-9 For the STS-9 mission Columbia was once again back in orbit.The launch occurred at ll a.m. EST, Nov. 28, 1983, after a 2-month delay because of a nozzle problem with one of the SRBs. This necessitated moving the vehicle back to the Vehicle Assembly Building where the nozzle was replaced. The 6-member crew -- a manned space flight record at the time -- included John W. Young, commander, on his second Shuttle flight; Brewster H. Shaw, pilot; Owen Garriott and Robert A. Parker, both mission specialists; and Byron K. Lichtenberg and Ulf Merbold payload specialists -- the first two non-astronauts to fly on the Shuttle. Merbold, a citizen of West Germany, also was the first foreign citizen to participate in a Shuttle flight. Lichtenberg was a researcher at Massachusetts Institute of Technology. [Summary provided by NASA] Group: Platform_Details Entry_ID: STS-9 Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Platform_Series_or_Entity: SPACE SHUTTLE Short_Name: STS-9 Long_Name: Space Transport System STS-9 End_Group Group: Synonymous_Platform_Names Short_Name: Columbia End_Group Group: Orbit Orbit_Altitude: 155nm Orbit_Inclination: 57.0 degrees End_Group Creation_Date: 2008-01-30 Online_Resource: http://science.ksc.nasa.gov/shuttle/missions/sts-9/mission-sts-9.html Sample_Image: http://science.ksc.nasa.gov/shuttle/missions/sts-9/sts-9-patch-small.gif Group: Platform_Logistics Launch_Date: 1983-11-28 Primary_Sponsor: NASA End_Group End_Group SMM The Solar Maximum Mission (SMM) was designed to provide coordinated observations of solar activity, in particular solar flares, during a period of maximum solar activity. The payload was made up of seven instruments, specifically selected to study the short-wavelength and coronal manifestations of flares. The total solar irradiance was measured by ACRIM, gamma rays by GRS, hard X-rays by the HXRBS, soft X-rays by XRP and HXIS, ultraviolet by UVSP, and the C/P imaged the corona 2-5 radii from the sun. Data were obtained on the storage and release of flare energy, particle acceleration, formation of hot plasma, and mass ejection. Complementary studies were made as part of the SMM guest investigator program, and coordinated in-situ measurements of flare particle emissions were made from the ISEE-3 spacecraft. The SMM observatory was of modular construction and measured approximately 4 m in length, fitting into a circular envelope 2.3 m in diameter. The instrument module occupied the top 2.3 m and contained all the solar payload instruments together with the fine-pointing Sun-sensor system. Below the instrument module was the Multimission Modular Spacecraft (MMS) containing the systems for attitude control, power, communication, and data handling. Between the instrument module and the MMS was the transition adaptor, supporting two fixed solar paddles that supplied between 1500 and 3000 W of power. Quick and coordinated responses to solar flares were considered essential for meeting the scientific objectives of the mission. Therefore, the ground system was designed to facilitate coordinated data evaluation, observation, planning, and command uplink to the onboard stored command processor. Onboard coordination of response to a flare was performed in real time. The attitude-control software allowed observatory repointings and slow scanning motions; there was also a special module for tracking a solar feature over many days. A repair mission by the space shuttle (STS-41C) was performed in 1984. During the repair mission the Shuttle astronauts rendezvoused with SMM and replaced successfully some hardware. As a result the coronagraph observations resumed until the end of mission. SMM collected data until Nov. 24, 1989, and re-entered on Dec. 2, 1989. For more details, see E. G. Chipman, Ap. J., v. 244, p. L113, 1981, and J. D. Bohlin et al., Solar Phys., v. 65, p. 5,1980. LAUNCH DATE- 02/14/80 ORBIT PARAMETERS ORBIT TYPE- GEOCENTRIC EPOCH DATE- 02/15/80 ORBIT PERIOD- 94.8 MIN INCLINATION- 28.5 DEG PERIAPSIS- 508. KM ALT APOAPSIS- 512. KM ALT Group: Platform_Details Entry_ID: SMM Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Short_Name: SMM Long_Name: Solar Maximum Mission End_Group Group: Synonymous_Platform_Names Short_Name: Solar Max Short_Name: Solar Maximum Mission Short_Name: 1980-014A Short_Name: 11703 End_Group Group: Platform_Associated_Instruments Short_Name: ACRIM Short_Name: UVSP Short_Name: HXRBS End_Group Group: Orbit Orbit_Inclination: 28.5 degrees Period: 94.8 m Perigee: 508 km Apogee: 512 km Orbit_Type: LEO > Low Earth Orbit > Inclined Non-Polar End_Group Online_Resource: http://umbra.nascom.nasa.gov/smm/ Sample_Image: http://nssdc.gsfc.nasa.gov/image/spacecraft/smm_capture.jpg Group: Platform_Logistics Launch_Date: 1980-02-14 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: NASA End_Group End_Group SOLRAD-8 The NRL Solrad 8 satellite was one of the Solrad series that began in 1960 to provide continuous coverage of solar radiation with a set of standard photometers. Solrad 8 was a spin-stabilized satellite oriented with its spin axis perpendicular to the sun-satellite line so that the 14 solar X-ray and ultraviolet photometers pointing radially outward from its equatorial belt viewed the sun with each revolution. Data were transmitted in real time by means of an FM/AM telemetry system and were recorded by the stations on the STADAN tracking network. The satellite performed normally except for the spin system, which failed to maintain 60 rpm (at spin rates below 10 rpm data reduction became difficult). The spin rate gradually decreased to 4 rpm on September 12, 1966. At that time, ground command succeeded in reactivating spinup to 78 rpm, which exhausted the gas supply. From this point, the spin rate gradually decreased to 10 rpm in August 1967, when data collection was substantially decreased. [Summary provided by Gunther's Space Page] Group: Platform_Details Entry_ID: SOLRAD-8 Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Platform_Series_or_Entity: SOLRAD Short_Name: SOLRAD-8 Long_Name: Solar Radiation-8 End_Group Group: Synonymous_Platform_Names Short_Name: SOLRAD-8 End_Group Group: Platform_Associated_Instruments Short_Name: SXP End_Group Creation_Date: 2008-01-14 Online_Resource: http://space.skyrocket.de/index_frame.htm?http://space.skyrocket.de/doc_sdat/explorer_se-a.htm Sample_Image: http://space.skyrocket.de/img_sat/se-a__explorer30__solrad-8__1.jpg Group: Platform_Logistics Launch_Date: 1966-05-20 Primary_Sponsor: NASA End_Group End_Group Meteor 2015-05-08 18:52:32.0 [saritz] update PrefLabel (Meteor); DMSP 5D-3/F19 A United Launch Alliance Atlas 5-401 rocket (AV-044) will be used to launch the Defense Meteorological Satellite Program Flight 19 military weather satellite for the U.S. Air Force. The polar orbiting satellite will collect global data on cloud movements, atmospheric profiles and the other ingredients needed by meteorologists to generate strike quality weather forecasts across the globe for the warfighter. The rocket stands 189 feet tall, weighs 737,000 pounds at launch and produces 860,000 pounds of sea-level thrust. The spacecraft is encapsulated in a 14-foot, diameter, 39-foot-tall aluminum payload fairing. 2014-05-28 14:38:16.0 [128.183.164.42] SR added new platform. insert AltLabel (id: null text: Defense Meteorological Satellite Program-F19 language code: en); 2014-05-28 14:37:39.0 [128.183.164.42] SR Added new Satellite insert Definition (id: null text: A United Launch Alliance Atlas 5-401 rocket (AV-044) will be used to launch the Defense Meteorological Satellite Program Flight 19 military weather satellite for the U.S. Air Force. The polar orbiting satellite will collect global data on cloud movements, atmospheric profiles and the other ingredients needed by meteorologists to generate strike quality weather forecasts across the globe for the warfighter. The rocket stands 189 feet tall, weighs 737,000 pounds at launch and produces 860,000 pounds of sea-level thrust. The spacecraft is encapsulated in a 14-foot, diameter, 39-foot-tall aluminum payload fairing. language code: en); 2014-05-28 14:35:18.0 [128.183.164.42] Insert Concept add broader relation (DMSP 5D-3/F19 [d1ad8ea7-b460-44b2-a96a-1040d156eeb4,106417] - DMSP (Defense Meteorological Satellite Program) [1cf8cbcd-c1be-4c78-9272-b62adad59aa1,73429]); AD (Atmospheric Dynamics) GOES-11 Update 2011-12-12: GOES-15 replaced GOES-11 as the GOES-West operational spacecraft on 2011-12-06, Source: http://noaasis.noaa.gov/NOAASIS/ml/status.html ] [Text For Archival Purposes only] GOES-11 (GOES-L) was launched May 3, 2000 from Cape Canaveral Air Station. The spacecraft will continue the long term geostationary monitoring of U.S. weather. The spacecraft will monitor hurricanes, severe thunderstorms, flash floods, and other severe weather as well as provide short-term weather forecasting or nowcasting. Combined with Doppler radar and automated surface weather stations, real-time GOES data will greatly aid weather foecasters in providing better warnings of severe weather. NOAA's National Environmmental Satellite, Data, and Information Service will operate GOES. The instrument package includes a GOES I-M Imager and GOES I-M Sounder. For more information see: https://www.ospo.noaa.gov/Operations/GOES/index.html 2017-09-01 16:52:22.0 [sritz] insert Definition (id: null text: Update 2011-12-12: GOES-15 replaced GOES-11 as the GOES-West operational spacecraft on 2011-12-06, Source: http://noaasis.noaa.gov/NOAASIS/ml/status.html ] [Text For Archival Purposes only] GOES-11 (GOES-L) was launched May 3, 2000 from Cape Canaveral Air Station. The spacecraft will continue the long term geostationary monitoring of U.S. weather. The spacecraft will monitor hurricanes, severe thunderstorms, flash floods, and other severe weather as well as provide short-term weather forecasting or nowcasting. Combined with Doppler radar and automated surface weather stations, real-time GOES data will greatly aid weather foecasters in providing better warnings of severe weather. NOAA's National Environmmental Satellite, Data, and Information Service will operate GOES. The instrument package includes a GOES I-M Imager and GOES I-M Sounder. For more information see: https://www.ospo.noaa.gov/Operations/GOES/index.html language code: en); 2017-09-01 16:46:41.0 [sritz] Insert Concept add broader relation (GOES-11 [d1c98f16-ae13-45a0-b1bf-de4fd2a5b1c7,310115] - GOES [6e332c25-caeb-4917-afb6-af757bcecd72,310071]); GCM General Circulation Models (GCM) are mathematical representations of atmospheric and oceanic properties and processes that attempt to describe Earth's climate system. [Source: Center for the study of Carbon Dioxide and Global Change] Group: Platform_Details Entry_ID: GCM Group: Platform_Identification Platform_Category: Models Short_Name: GCM Long_Name: General Circulation Model End_Group Group: Synonymous_Platform_Names Short_Name: GCM End_Group Creation_Date: 2007-12-13 Online_Resource: http://www.aip.org/history/climate/GCM.htm Sample_Image: http://www.noc.soton.ac.uk/JRD/PROC/Q-GCM/schematic.jpg End_Group SN-2 2013-11-11 19:18:52.0 [aaleman] created new keyword insert AltLabel (id: null text: Submarine Network 2 language code: en); 2013-11-11 19:18:22.0 [aaleman] Insert Concept add broader relation (SN-2 [d227bc01-e09a-4356-89d3-84cae164eeec,105917] - OCEAN PLATFORM/OCEAN STATIONS [6ee1cf85-aa14-4fe9-a915-a8022830d8a7,73557]); OCEAN WEATHER STATIONS Ocean Weather Stations are ocean based facilities or locations where meteorological data are gathered, recorded, and released. Such stations are of the first order when they make observations of all the important elements either hourly or by self-registering instruments; of the second order when only important observations are taken; of the third order when simpler work is done, as to record rainfall and maximum and minimum temperatures. [Source : Webster's Revised Unabridged Dictionary. 1996] Group: Platform_Details Entry_ID: OCEAN WEATHER STATIONS Group: Platform_Identification Platform_Category: In Situ Ocean-based Platforms Platform_Series_or_Entity: OCEAN PLATFORM/OCEAN STATIONS Short_Name: OCEAN WEATHER STATIONS End_Group Group: Synonymous_Platform_Names Short_Name: Ocean Weather Stations End_Group Creation_Date: 2007-12-12 End_Group FY-2E HAGGLUND The Hagglund Oversnow vehicle can travel over large distances and on different terrain surfaces. See "http://www.terratrak.co.uk/" for more information. Group: Platform_Details Entry_ID: HAGGLUND Group: Platform_Identification Platform_Category: In Situ Land-based Platforms Platform_Series_or_Entity: MOBILE STATIONS/VEHICLES Short_Name: HAGGLUND Long_Name: NZAP Hagglund Oversnow Vehicle End_Group Group: Synonymous_Platform_Names Short_Name: HAGGLUND End_Group Creation_Date: 2007-12-07 Online_Resource: http://www.terratrak.co.uk/ Sample_Image: http://www.andrill.org/iceberg/blogs/betty/images/vehicles-hagglund.jpg End_Group SPOT-3 The SPOT-3 (Satellite Pour l'Observation de la Terre) spacecraft was launched in September 26,1993. SPOT-3 is a earth observation satellite with a ground resolution better than that of the Landsat series satellites. The main applications for the images returned by the third SPOT mission are land-use studies, agriculture and forestry resources, mineral and oil resources, and cartography. The three-axis stabilized satellite operates in a circular sun-synchronous near-polar orbit for a design lifetime of 2 years. Orbital Characteristics- Orbital Period: 101.20 m Inclination: 98.60 degrees Periapsis: 819.00 km Apoapsis: 846.00 km The spacecraft dimensions are 2 x 2 x 3.5 m and 15.60 m for the overall length of the deployed solar panel. SPOT-3 consists of two parts: (1) the bus, a standard multipurpose platform, and (2) the payload. The bus provides housekeeping information and an onboard computer. The payload is mounted on one of the side panels of the bus. It consists of two identical high-resolution visible (HRV) imaging instruments and a package comprising two magnetic-tape data recorders and a telemetry transmitter. The HRV imaging instrument observes in three spectral bands (in the visible and near infrared regions) with a ground resolution of 20 m, and/or in a broader spectral band (panchromatic black and white) with a ground resolution of 10 m. The pattern of successive ground tracks is repeated exactly at 26-day intervals. The SPOT-3 instrument package has the provision for off-nadir viewing which should be particularly useful for monitoring localized phenomena evolving on a relatively short timescale. Also, the satellite provides the capability for recording stereoscopic pairs of images of a given area during successive satellite passes. Group: Platform_Details Entry_ID: SPOT-3 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: SPOT Short_Name: SPOT-3 Long_Name: Systeme Probatoire Pour l'Observation de la Terre-3 End_Group Group: Synonymous_Platform_Names Short_Name: SPOT-3 Short_Name: 22823 End_Group Group: Platform_Associated_Instruments Short_Name: DORIS Short_Name: POAM II Short_Name: HRV End_Group Group: Orbit Orbit_Inclination: 98.6° Period: 101.20 minutes Perigee: 819.0 km Apogee: 846.0 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-11-13 Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1993-061A Online_Resource: http://www.cnes.fr/web/1417-spot-1-to-5.php Online_Resource: http://www.spot.com/ Group: Platform_Logistics Launch_Date: 1993-09-26 Launch_Site: Kourou, French Guiana Design_Life: 2 YEARS Primary_Sponsor: France/CNES End_Group End_Group ARGON ARGON was a photo-reconnaissance satellite that was operation between 1960-1972. The images were used to produce maps and charts for the Department of Defense and other Federal Government mapping programs. President Clinton signed an Executive Order on 24 February 1995, directing the declassification of intelligence imagery acquired by the first generation of United States photo-reconnaissance satellites, including the systems code-named CORONA, ARGON and LANYARD. Additional information available at "http://edc.usgs.gov/guides/disp1.html" [Summary provided by USGS] Group: Platform_Details Entry_ID: ARGON Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: ARGON End_Group Group: Platform_Associated_Instruments Short_Name: CAMERAS End_Group Group: Orbit Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Online_Resource: http://edc.usgs.gov/guides/disp1.html Group: Platform_Logistics Launch_Date: 1961-02-17 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: United States End_Group End_Group TIROS-7 TIROS-7 Objectives: Continue research and development of the meteorological satellite information system; obtain improved data for use in weather forecasting, especially during hurricane season. Description: The spacecraft was 42 inches in diameter, 19 inches high and weighed 270 pounds. The craft was made of aluminum alloy and stainless steel then covered by 9200 solar cells. The solar cells served to charge the nickel-cadmium (nicad) batteries. Three pairs of solid-propellant spin rockets were mounted on the base plate. TIROS-7 was also designed to make infrared measurements of reflected solar and terrestrial radiation over selected spectrum ranges and gather data on electron density and temperature in space. To accomplish this new expanded mission, TIROS-7 carried two wide-angle camera systems, a magnetic tape recorder, and infrared experimentation equipment. The electron density and temperature probes were the same as the ones flown on board Explorer 17. The spacecraft operating system still included the infrared horizon scanner, the north direction indicator, despin weights and spinup rockets, and the magnetic attitude control system. TIROS-7 was deactivated after furnishing over 30,000 cloud photographs; it lasted the longest of the TIROS series thus far, 1809 days. Experiments on Tiros-7: Low-Resolution Omnidirectional Radiometer Scanning Radiometer Langmuir Probe Television Camera System Additional information available at http://nasascience.nasa.gov/missions/tiros [Summary provided by NASA] Group: Platform_Details Entry_ID: TIROS-7 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: TIROS Short_Name: TIROS-7 Long_Name: Television Infrared Operational End_Group Group: Synonymous_Platform_Names Short_Name: TIROS G Short_Name: 00604 End_Group Group: Platform_Associated_Instruments Short_Name: SR End_Group Group: Orbit Orbit_Inclination: 58.2 deg Period: 88.3 min Perigee: 188 km Apogee: 194 km End_Group Creation_Date: 2007-11-14 Online_Resource: http://nasascience.nasa.gov/missions/tiros Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1963-024A Sample_Image: http://www.cira.colostate.edu/cira/RAMM//hillger/TIROS-7_cover.jpg Group: Platform_Logistics Launch_Date: 1963-06-19 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: USA/NASA End_Group End_Group T-39 The T-39 is the Air Force version of Rockwell's popular Sabreliner executive aircraft. This handy twin-jet utility plane has been used for many purposes: a four-passenger executive transport, light priority cargo and for radar and navigational training. The T-39 Sabreliner is a low wing, twin jet aircraft. The cockpit and cabin compartments are pressurized and soundproofed for high altitude flight. Power is supplied by two Pratt and Whitney, J60 gas turbine engines located on each side of the aft fuselage. The rated sea level static thrust of each engine is 3,000 pounds at military power. The T-39 was developed by North American Aviation Inc. as a private venture to meet a USAF requirement for a twin jet utility trainer. The prototype T-39 made its first flight on September 16, 1958. In January 1959, the USAF placed a production order and on June 30, 1960, the first production T-39A made its initial flight. In all, 143 T-39As and 6 T-39Bs were built for the USAF. Another 62 T-39 variants were produced for the Navy. In July 1961, the Navy ordered ten of North American’s Model NA-277 to train radar operators. In that order the aircraft was designated T3J-1, but by the time the first one was delivered in 1962, the designation had been changed to T-39D. A total of 52 additional aircraft were accepted. After the bulk of military contracts had been met, the Sabreliner entered the commercial market where it became a highly successful executive jet transport. [Text provided by: http://www.globalsecurity.org/military/systems/aircraft/ct-39.htm ] [Photo provided by: http://wikipedia.org ] Group: Platform_Details Entry_ID: T-39 Group: Platform_Identification Platform_Category: Aircraft Short_Name: T-39 Long_Name: Rockwell Sabreliner T-39 End_Group Creation_Date: 2008-07-14 Online_Resource: http://en.wikipedia.org/wiki/North_American_Sabreliner Sample_Image: http://upload.wikimedia.org/wikipedia/commons/d/d5/T39_mainlarge_cnatra_navy.jpg End_Group GEOS-2 Spacecraft Brief Description The GEOS 2 (Geodetic Earth Orbiting Satellite) was a gravity-gradient-stabilized, solar-cell-powered spacecraft that carried electronic and geodetic instrumentation. The geodetic instrumentation systems included (1) four optical beacons, (2) two C-band radar transponders, (3) a passive radar reflector, (4) a sequential collation of range radio range transponder, (5) a Goddard range and range rate transponder, (6) laser reflectors, and (7) Doppler beacons. Non-geodetic systems included a laser detector and a Minitrack interferometer beacon. The objectives of the spacecraft were to optimize optical station visibility periods and to provide complementary data for inclination-dependent terms established by the Explorer 29 (GEOS 1) gravimetric studies. The spacecraft was placed into a retrograde orbit to accomplish these objectives. Operational problems occurred in the main power system, optical beacon flash system, and the spacecraft clock, and adjustments in scheduling resulted in nominal operations. Auxiliary Information Launch Date and Time : 1968-01-11 16:19:00 Epoch Date and Time : 1977-02-28 Orbit Type : Geocentric Apogee(km) : 1570. Perigee(km) : 1082. Inclination : 105.8 Date of last update : 1992-03-09 Group: Platform_Details Entry_ID: GEOS-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: GEOS (Geodetic Earth Orbiting Satellite) Short_Name: GEOS-2 Long_Name: Geodetic Earth Orbiting Satellite-2 End_Group Group: Synonymous_Platform_Names Short_Name: GEOS-2 End_Group Group: Platform_Associated_Instruments Short_Name: RADIO TRANSPONDERS Short_Name: OPTICAL BEACON End_Group Group: Orbit Orbit_Inclination: 105.8 Perigee: 1082 km Apogee: 1570 km End_Group Creation_Date: 2007-09-26 Online_Resource: http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1978-071A Group: Platform_Logistics Launch_Date: 1968-01-11 Primary_Sponsor: NASA End_Group End_Group LANDSAT-1 Landsat 1, originally named Earth Resources Technology Satellite 1, was a modified version of the Nimbus 4 meteorological satellite. It was launched on July 23, 1972, the first satellite of the United States&#039; Landsat program. The near-polar orbiting spacecraft served as a stabilized, Earth-oriented platform for obtaining information on agricultural and forestry resources, geology and mineral resources, hydrology and water resources, geography, cartography, environmental pollution, oceanography and marine resources, and meteorological phenomena. To accomplish these objectives, the spacecraft was equipped with (1) a three-camera return beam vidicon (RBV) to obtain visible light and near infrared photographic images of Earth, (2) a four-channel multispectral scanner (MSS) to obtain radiometric images of Earth, and (3) a data collection system (DCS) to collect information from remote, individually equipped ground stations and to relay the data to central acquisition stations. Landsat 1 carried two wide-band video tape recorders (WBVTR) capable of storing up to 30 min of scanner or camera data to give the spacecraft&#039;s sensors a near-global coverage capability. An advanced attitude control system consisting of horizon scanners, sun sensors, and a command antenna combined with a freon gas propulsion system permitted the spacecraft&#039;s orientation to be maintained within plus or minus 0.7 degrees in all three axes. Spacecraft communications included a command subsystem operating at 154.2 and 2106.4 MHz and a PCM narrow-band telemetry subsystem, operating at 2287.5 and 137.86 MHz, for spacecraft housekeeping, attitude, and sensor performance data. Video data from the three-camera RBV system was transmitted in both real-time and tape recorder modes at 2265.5 MHz, while information from the MSS was constrained to a 20 MHz rf bandwidth at 2229.5 MHz. In 1976, Landsat 1 discovered a tiny uninhabited island 20 km off the eastern coast of Canada. This island was thereafter designated Landsat Island after the satellite. As of 2006, it is the only island to be discovered via satellite imagery. The spacecraft was turned off on January 6, 1978, when cumulative precession of the orbital plane caused the spacecraft to see almost constant sunlight which led to overheating. [Summary provided by NASA.] Group: Platform_Details Entry_ID: LANDSAT-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: LANDSAT Short_Name: LANDSAT-1 End_Group Group: Platform_Associated_Instruments Short_Name: MSS Short_Name: RBV End_Group Group: Orbit Orbit_Altitude: 917 km (570 mi) Orbit_Inclination: 99.2 degree Equator_Crossing: 9:30 AM +/- 15 minutes Period: 103 minutes Repeat_Cycle: 18 days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-02-01 Online_Resource: https://landsat.gsfc.nasa.gov/landsat-1/ Online_Resource: https://www.usgs.gov/land-resources/nli/landsat/landsat-1 Group: Platform_Logistics Launch_Date: 1972-07-23 Launch_Site: Vandenberg AFB Primary_Sponsor: NASA Primary_Sponsor: USGS End_Group End_Group 2019-12-31 21:29:24.0 [sritz] update Definition (Landsat 1, originally named Earth Resources Technology Satellite 1, was a modified version of the Nimbus 4 meteorological satellite. It was launched on July 23, 1972, the first satellite of the United States&#039; Landsat program. The near-polar orbiting spacecraft served as a stabilized, Earth-oriented platform for obtaining information on agricultural and forestry resources, geology and mineral resources, hydrology and water resources, geography, cartography, environmental pollution, oceanography and marine resources, and meteorological phenomena. To accomplish these objectives, the spacecraft was equipped with (1) a three-camera return beam vidicon (RBV) to obtain visible light and near infrared photographic images of Earth, (2) a four-channel multispectral scanner (MSS) to obtain radiometric images of Earth, and (3) a data collection system (DCS) to collect information from remote, individually equipped ground stations and to relay the data to central acquisition stations. Landsat 1 carried two wide-band video tape recorders (WBVTR) capable of storing up to 30 min of scanner or camera data to give the spacecraft&#039;s sensors a near-global coverage capability. An advanced attitude control system consisting of horizon scanners, sun sensors, and a command antenna combined with a freon gas propulsion system permitted the spacecraft&#039;s orientation to be maintained within plus or minus 0.7 degrees in all three axes. Spacecraft communications included a command subsystem operating at 154.2 and 2106.4 MHz and a PCM narrow-band telemetry subsystem, operating at 2287.5 and 137.86 MHz, for spacecraft housekeeping, attitude, and sensor performance data. Video data from the three-camera RBV system was transmitted in both real-time and tape recorder modes at 2265.5 MHz, while information from the MSS was constrained to a 20 MHz rf bandwidth at 2229.5 MHz. In 1976, Landsat 1 discovered a tiny uninhabited island 20 km off the eastern coast of Canada. This island was thereafter designated Landsat Island after the satellite. As of 2006, it is the only island to be discovered via satellite imagery. The spacecraft was turned off on January 6, 1978, when cumulative precession of the orbital plane caused the spacecraft to see almost constant sunlight which led to overheating. [Summary provided by NASA.] Group: Platform_Details Entry_ID: LANDSAT-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: LANDSAT Short_Name: LANDSAT-1 End_Group Group: Platform_Associated_Instruments Short_Name: MSS Short_Name: RBV End_Group Group: Orbit Orbit_Altitude: 917 km (570 mi) Orbit_Inclination: 99.2 degree Equator_Crossing: 9:30 AM +/- 15 minutes Period: 103 minutes Repeat_Cycle: 18 days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-02-01 Online_Resource: https://landsat.gsfc.nasa.gov/landsat-1/ Online_Resource: https://www.usgs.gov/land-resources/nli/landsat/landsat-1 Group: Platform_Logistics Launch_Date: 1972-07-23 Launch_Site: Vandenberg AFB Primary_Sponsor: NASA Primary_Sponsor: USGS End_Group End_Group); update Definition (https://landsat.gsfc.nasa.gov/landsat-1/); delete Resource (null); FY-2 China began its geostationary meteorological satellite FY-2 program in 1980. Through hard work for more than ten years, the first FY-2 satellite was launched on June 10, 1997 and located in the geostationary orbit at an altitude of 35800 kilometers over 105 degrees E. The satellite is a cylinder of 2.1 m by 1.6 m. The attitude of the satellite is spin stabilized with a speed of 100 rotation/min. FY-2A is the first geostationary meteorological satellite in China. It is a spin-stabilized satellite. The main function of FY-2A is observation. It takes visible, infrared and water vapor disk images of the Earth hourly. The main payload of FY-2A is a Visible and Infrared Spin Scan Radiometer (VISSR). The VISSR takes the Earth and cloud images from the space. A complete 20° x20° scan covering the full Earth disk can be accomplished every 30 minutes by means of combination of satellite spin motion (100 rpm from the west to east) and step action of the scan mirror (2500 steps from north to south). The S-VISSR data are retransmitted to user stations via FY-2A during the VISSR observation. The stretched VISSR (S-VISSR) data are the digital image data originated by VISSR on board and stretched on the Command and Data Acquisition Station (CDAS) in time. After stretching, the transmission rate of S-VISSR data is reduced and can be easily received by the users. Additional information available at http://nsmc.cma.gov.cn/fy2e.html [Summary provided by China's National Satellite Meteorological Center] Group: Platform_Details Entry_ID: FY-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: FY (Feng-Yun) Short_Name: FY-2 Long_Name: China's Meteorological Satellite-2 End_Group Group: Synonymous_Platform_Names Short_Name: Feng Yun 2 End_Group Group: Platform_Associated_Instruments Short_Name: VISSR End_Group Group: Orbit Orbit_Altitude: 35,800 km Orbit_Type: GEO > Geosynchronous > Geostationary End_Group Creation_Date: 2007-09-26 Online_Resource: http://www.fas.org/spp/guide/china/earth/fy-2.htm Sample_Image: http://www.fas.org/spp/guide/china/earth/fy2-s.jpg Group: Platform_Logistics Launch_Date: 1997-06-10 Launch_Site: Xichang Space Launch Center, China Primary_Sponsor: CHINA/CMA End_Group End_Group NOAA-14 NOAA-14 (NATIONAL OCEANIC & ATMOSPHERIC ADMINISTRATION-14) NOAA 14 (National Oceanic & Atmospheric Administration) Weather Satellite: Objectives: To continue the Advanced TIROS-N program by working as a companion with NOAA-10, 11 and 12 in order to provide continuous coverage of the Earth and to provide high-resolution global meteorological data. NOAA-14 is the sixth operational satellite in the Advanced TIROS-N series (NOAA 13 never officially became operational as it failed during its 21 day checkout period). The satellite carried the AVHRR, TOVS, and the solar proton monitor. All of which were present on previous NOAA satellites. The ERBE instruments, the SBUV radiometer and the SARSAT systems were also flown on this satellite. NOAA-14 was placed in a near circular, (470nm) polar orbit. NOAA 14 replaced NOAA 11 whose cloud cover imaging instrument had failed a few months before this launch. Besides an imaging radiometer, it carries optical sounders to monitor temperature and moisture content in the atmosphere, and counters to measure energetic electrons and protons. A gas leak caused some difficulties in attitude control shortly after launch, but this has been resolved. The motor for the Microwave Sounding Unit on the NOAA 14 spacecraft has stopped working. Records show the unit is from a delivery made to Martin Marietta dating back to 1984! The microwave sounder returned to normal operation in May 1995 after a software patch was installed to cope with any repeat failure. Its life expectancy remains uncertain. In Feb 1995, the SARP failed, the SBUV/2 Cloud Cover Radiometer (CCR) failed, and DTR 4A/B was deemed inoperable. Specifications: Designation: 23455 / 94089A Launch date: 30 Dec 1994 at 10:02 UT Country of origin: United States Perigee/Apogee: 847/861 km Inclination: 98.9° Period: 02 min Launch vehicle: Atlas E Launch site: Vandenberg SLC3 Prime contractor: GE Astro Platform: evolved from NOAA 2nd generation Mass at launch: 1420 kg Mass in orbit: ~1050 kg Dimension: 4.18 m long x 1.88 m diameter Stabilization: 3-axis Design lifetime: 3 years APT downlink freq: 137.620 MHz (standby) HRPT downlink freq: 1698.0 MHz Beacon: 136.770 MHz Payload: AVHRR (Advanced Very High Resolution Radiometer): Wavebands: 0.58-0.68 µm (visible): cloud, snow and ice monitoring 0.725-1.10 µm (near IR): water, vegetation and agriculture surveys 3.55-3.93 µm (near IR): sea surface temperature, volcano, forest fire activity 10.3-11.3 µm (thermal IR): sea surface temperature, soil moisture 11.3-12.5 µm (thermal IR): sea surface temperature, soil moisture Resolution: 1.1 km Swath width: 3000 km TOVS (Tiros Operational Vertical Sounder): HIRS/2 (High Resolution IR Sounder): 20 channels in the 0.69 - 14 - 95 µm band; 17.4 km resolution SSU (Stratospheric Sounding Unit): step-scanned far IR spectrometer with 3 channels in the CO² absorption band (15 µm);147.3 km resolution MSU (Microwave Sounding Unit): passive 4-channel radiometer operating around 55 GHz; 109 km resolution [Summary provided by NOAA and The Satellite Encyclopedia] Group: Platform_Details Entry_ID: NOAA-14 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NOAA POES (Polar Orbiting Environmental Satellites) Short_Name: NOAA-14 Long_Name: National Oceanic & Atmospheric Administration-14 End_Group Group: Synonymous_Platform_Names Short_Name: NOAA-14 End_Group Group: Platform_Associated_Instruments Short_Name: TOVS Short_Name: HIRS/2 Short_Name: MSU Short_Name: SSU End_Group Group: Orbit Orbit_Inclination: 98.9 DEG Period: 02 min Perigee: 847 km Apogee: 861 km End_Group Creation_Date: 2007-11-05 Online_Resource: http://www2.ncdc.noaa.gov/docs/podug/html/c1/sec1-410.htm Sample_Image: http://www2.ncdc.noaa.gov/docs/podug/images/guide/f1410-1.gif Group: Platform_Logistics Launch_Date: 1994-12-30 Primary_Sponsor: NASA End_Group End_Group 2016-06-09 17:15:08.0 [epneff] added altLabel insert AltLabel (id: null text: NOAA-14 (NATIONAL OCEANIC & ATMOSPHERIC ADMINISTRATION-14) language code: en); ATLAS MOORINGS The Autonomous Temperature Line Acquisition System was initiated by PMEL's Engineering Development Division (EDD) in 1984. The standard ATLAS mooring had a design lifetime of one year, and the system proved to be robust and reliable. Over 500 Standard ATLAS moorings were deployed between 1984 and 2001. The final standard ATLAS was recovered in November 2001 and NextGeneration ATLAS moorings are now used exclusively in the TAO array. Standard ATLAS moorings measured surface winds, air temperature, relative humidity, sea surface temperature, and ten subsurface temperatures from a 500 m long thermistor cable. Daily-mean data were telemetered to shore in near real-time via NOAA's polar-oribiting satellites and Service Argos. A small subset of hourly values (2-3 per day) coinciding with satellite passes were also transmitted in real time. Hourly values of surface data were internally recorded and available after mooring recovery. More info at "http://www.pmel.noaa.gov/tao/proj_over/mooring.shtml" [Source: NOAA] Group: Platform_Details Entry_ID: ATLAS MOORINGS Group: Platform_Identification Platform_Category: In Situ Ocean-based Platforms Platform_Series_or_Entity: MOORINGS Short_Name: ATLAS MOORINGS Long_Name: Autonomous Temperature Line Acquisition System End_Group Group: Synonymous_Platform_Names Short_Name: Atlas Moorings End_Group Creation_Date: 2007-12-12 Online_Resource: http://www.pmel.noaa.gov/tao/proj_over/mooring.shtml Sample_Image: http://www.whoi.edu/cms/images/lstokey/2005/1/v39n2-rothstein3en_4592.jpg End_Group SURFRAD To understand the global surface energy budget is to understand climate. Because it is impractical to cover the earth with monitoring stations, the answer to global coverage lies in reliable satellite-based estimates. Efforts are underway at NASA and universities to develop algorithms to do this, but such projects are in their infancy. In concert with these ambitious efforts, accurate and precise ground-based measurements in differing climatic regions are essential to refine and verify the satellite-based estimates, as well as to support specialized research. To fill this niche, the Surface Radiation Budget Network (SURFRAD) was established in 1993 through the support of NOAA's Office of Global Programs. The SURFRAD mission is clear; its primary objective is to support climate research with accurate, continuous, long-term measurements of the surface radiation budget over the United States. This differs from DOE's ARM/SGP site, where surface radiation budget measurements are also being made, in that ARM uses clustered measurements over a limited area for process-oriented studies. 2019-08-26 18:31:06.0 [sritz] insert Definition (id: null text: To understand the global surface energy budget is to understand climate. Because it is impractical to cover the earth with monitoring stations, the answer to global coverage lies in reliable satellite-based estimates. Efforts are underway at NASA and universities to develop algorithms to do this, but such projects are in their infancy. In concert with these ambitious efforts, accurate and precise ground-based measurements in differing climatic regions are essential to refine and verify the satellite-based estimates, as well as to support specialized research. To fill this niche, the Surface Radiation Budget Network (SURFRAD) was established in 1993 through the support of NOAA's Office of Global Programs. The SURFRAD mission is clear; its primary objective is to support climate research with accurate, continuous, long-term measurements of the surface radiation budget over the United States. This differs from DOE's ARM/SGP site, where surface radiation budget measurements are also being made, in that ARM uses clustered measurements over a limited area for process-oriented studies. language code: en); 2019-08-26 18:29:51.0 [sritz] insert AltLabel (id: null category: primary text: Surface Radiation Budget Network language code: en); 2019-08-26 18:28:47.0 [sritz] Insert Concept add broader relation (SURFRAD [d5456efc-ae6c-4c68-8b5e-66e40226d897,369065] - SOLAR/SPACE MONITORING STATIONS [a143e5f5-4e4c-45cb-8053-5c9f6a099784,345507]); RADARSAT-1 Radarsat, a Canadian-led international program and a major part of the overall Canadian Space Agency (CSA) program, is Canada's first remote-sensing satellite. Radarsat delivers C-Band SAR imagery to the CSA and numerous commercial customers worldwide. The images are used for locating and identifying ice in the Arctic Ocean to aid in navigation; monitoring offshore oil and gas explosions and oil slicks; and acquiring remote sensing data for the management of agriculture and updating the Canadian geological map. General Information: Designation: 23710 / 95059A Launch date: 4 Nov 1995 Country of origin: Canada Operator: Canadian Space Agency Mission: Remote sensing Perigee/Apogee: 783/787 km (polar orbit) Inclination: 98.6° Period: 100 min Launch vehicle: Delta 2 #229 Mass at launch: 2750 kg Specifications: Prime contractor: Spar Aerospace (Canada) Mass at launch: 3150 kg? Payload mass: 1500 kg Solar array: 18 m span Stabilization: 3-axis DC power: 2200 W Design lifetime: 5 years Dimensions: 15 m long x 1.5 m wide Synthetic Aperture C-band Radar Other information: Resolution: between 30 m and 90 m On-board storage: 96 MB Uplink: S-band (2 kbps) Downlink: S-band (2.5, 2, 4, 32 or 128 kbps) Another downlink for science data is at: 2230.000 MHz Additional information available at https://www.asc-csa.gc.ca/eng/satellites/radarsat1/Default.as https://science.nasa.gov/missions/radarsat Contact Information: Canadian Space Agency Tel: +1-514-926-4436 Fax: +1-514-926-4973 [Summary provided by The Satellite Encyclopedia] Group: Platform_Details Entry_ID: RADARSAT-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: RADARSAT Short_Name: RADARSAT-1 End_Group Group: Synonymous_Platform_Names Short_Name: RADARSAT-1 End_Group Group: Platform_Associated_Instruments Short_Name: SAR End_Group Group: Orbit Orbit_Inclination: 98.6 deg Period: 100 min Perigee: 783 km Apogee: 787 km End_Group Creation_Date: 2007-11-09 Online_Resource: https://www.asc-csa.gc.ca/eng/satellites/radarsat1/Default.asp Online_Resource: https://science.nasa.gov/missions/radarsat Group: Platform_Logistics Launch_Date: 1995-11-04 Primary_Sponsor: Canada/CSA Primary_Sponsor: Canada/MDA End_Group End_Group 2019-12-31 20:58:45.0 [sritz] update Definition (Radarsat, a Canadian-led international program and a major part of the overall Canadian Space Agency (CSA) program, is Canada's first remote-sensing satellite. Radarsat delivers C-Band SAR imagery to the CSA and numerous commercial customers worldwide. The images are used for locating and identifying ice in the Arctic Ocean to aid in navigation; monitoring offshore oil and gas explosions and oil slicks; and acquiring remote sensing data for the management of agriculture and updating the Canadian geological map. General Information: Designation: 23710 / 95059A Launch date: 4 Nov 1995 Country of origin: Canada Operator: Canadian Space Agency Mission: Remote sensing Perigee/Apogee: 783/787 km (polar orbit) Inclination: 98.6° Period: 100 min Launch vehicle: Delta 2 #229 Mass at launch: 2750 kg Specifications: Prime contractor: Spar Aerospace (Canada) Mass at launch: 3150 kg? Payload mass: 1500 kg Solar array: 18 m span Stabilization: 3-axis DC power: 2200 W Design lifetime: 5 years Dimensions: 15 m long x 1.5 m wide Synthetic Aperture C-band Radar Other information: Resolution: between 30 m and 90 m On-board storage: 96 MB Uplink: S-band (2 kbps) Downlink: S-band (2.5, 2, 4, 32 or 128 kbps) Another downlink for science data is at: 2230.000 MHz Additional information available at https://www.asc-csa.gc.ca/eng/satellites/radarsat1/Default.as https://science.nasa.gov/missions/radarsat Contact Information: Canadian Space Agency Tel: +1-514-926-4436 Fax: +1-514-926-4973 [Summary provided by The Satellite Encyclopedia] Group: Platform_Details Entry_ID: RADARSAT-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: RADARSAT Short_Name: RADARSAT-1 End_Group Group: Synonymous_Platform_Names Short_Name: RADARSAT-1 End_Group Group: Platform_Associated_Instruments Short_Name: SAR End_Group Group: Orbit Orbit_Inclination: 98.6 deg Period: 100 min Perigee: 783 km Apogee: 787 km End_Group Creation_Date: 2007-11-09 Online_Resource: https://www.asc-csa.gc.ca/eng/satellites/radarsat1/Default.asp Online_Resource: https://science.nasa.gov/missions/radarsat Group: Platform_Logistics Launch_Date: 1995-11-04 Primary_Sponsor: Canada/CSA Primary_Sponsor: Canada/MDA End_Group End_Group); delete Resource (null); HJ1A Disaster and Environment Monitoring and Forecast Small Satellite Constellation A Launch Date: 06 Sep 2008 EOL Date: 01 Sep 2011 Type: Sun-synchronous Altitude: 649 km Period: Inclination: 97.9 deg Repeat cycle: 31 days LST: 10:30 Asc/desc: Descending URL: http://www.cresda.com/ Group: Platform_Details Entry_ID: HJ1A Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: HJ1A Long_Name: HuanJing 1A Satellite End_Group Group: Synonymous_Platform_Names Short_Name: HJ-1A End_Group Group: Platform_Associated_Instruments Short_Name: CCD2 (HuanJing 1A) Short_Name: CCD1 (HuanJing 1A) End_Group Group: Orbit Orbit_Altitude: 649 km Orbit_Inclination: 97.9 deg Equator_Crossing: 10:30 Local time: e.g. Repeat_Cycle: 31 days Orbit_Type: LEO > LOW EARTH ORBIT > POLAR SUN-SYNCHRONOUS End_Group Creation_Date: 2012-07-25 Online_Resource: http://www.cresda.com/n16/n92006/n92066/n98627/index.html Group: Platform_Logistics Launch_Date: 2008-09-06 Launch_Site: TAIYUAN SPACE LAUNCH CENTER, CHINA Primary_Sponsor: CRESDA Primary_Sponsor: CAST Primary_Sponsor: NRSCC End_Group End_Group 2012-07-25 12:28:41.0 [mpmorahan] Insert Concept add broader relation (HJ1A [d65fc363-e9b4-410a-b5e3-8dbd87b510b4,40355] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,31221]); ERBS ERBS was part of the NASA's 3 satellite Earth Radiation Budget Experiment (ERBE), designed to investigate how energy from the Sun is absorbed and re-emitted by the earth. This process of absorption and re-radiation is one of the principal drivers of the Earth's weather patterns. Observations from ERBS are also used to determine the effects of human activities (such as burning fossil fuels and the use CFCs) and natural occurrences (such as volcanic eruptions) on the Earth's radiation balance. In addition to the ERBE scanning and nonscanning instruments, the satellite also carried the Stratospheric Aerosol Gas Experiment (SAGE II). The ERBS was the first of three ERBE platforms which would eventually carry the ERBE Instruments. Goddard Space Flight Center built the satellite and it was launched by the Space Shuttle Challenger in 1984. The second ERBE Instrument was aboard the NOAA-9 satellite when it was launched in January of 1985, and the third was aboard the NOAA-10 satellite when it was launched in October of 1986. Although the scanning instruments on board all three ERBE satellites are no longer operational, the nonscanning instruments are all presently functioning. Launch: Launched: October 5, 1984 Launch Site: Kennedy Space Center Orbit: Altitude: 610 km Inclination: 57 degrees Period: 96.4 Non-Sun-Synchronous Sun-Synchronous Vital Statistics: Power: 622 watts quiescent watts watts Design Life: 2 years Instruments: ERBE (Earth Radiation Budget Experiment) SAGE II (Stratospheric Aerosol Gas Experiment) Website: "http://nasascience.nasa.gov/missions/erbs" [Summary provided by NASA.] Group: Platform_Details Entry_ID: ERBS Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: ERBS Long_Name: Earth Radiation Budget Satellite End_Group Group: Synonymous_Platform_Names Short_Name: ERBS End_Group Group: Platform_Associated_Instruments Short_Name: ERB-SCANNER Short_Name: ERB-NONSCANNER End_Group Group: Orbit Orbit_Altitude: 610 km Orbit_Inclination: 57 deg Period: 96.4 Orbit_Type: LEO > Low Earth Orbit > Polar Non-Sun-Synchronous End_Group Creation_Date: 2007-11-19 Online_Resource: http://asd-www.larc.nasa.gov/erbe/erbs.html Online_Resource: http://nasascience.nasa.gov/missions/erbs Sample_Image: http://asd-www.larc.nasa.gov/erbe/erbssat.gif Group: Platform_Logistics Launch_Date: 1984-10-05 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: USA/NASA End_Group End_Group DMSP 5D-2/F8 DMSP-F08 [Source: National Space Science Data Center, http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1987-053A ] DMSP 5D-2/F8 is one of a series of meteorological satellites developed and operated by the Air Force under the Defense Meteorological Satellite Program (DMSP). Its pre-launch designation was DMSP 5D-2/S9. This program, previously known as DAPP (Data Acquisition and Processing Program), was classified until March 1973. The objective of this program is to provide global visual and infrared cloudcover data and specialized environmental data to support Department of Defense operational weather analysis and forecasting requirements. Operationally, the program consists of two satellites in sun-synchronous polar orbits, with the ascending node of one satellite in early morning and the other at local noon. The 6.4-m-long spacecraft is separated into four sections: (1) a precision mounting platform for sensors and equipment requiring precise alignment; (2) an equipment support module containing the electronics, reaction wheels, and some meteorological sensors; (3) a reaction control equipment support structure containing the third-stage rocket motor and supporting the ascent phase reaction control equipment; and (4) a 9.29-sq-m solar cell panel. The spacecraft stabilization is controlled by a combination flywheel and magnetic control coil system so sensors are maintained in the desired earth-looking mode. One feature is the precision-pointing accuracy of the primary imager to 0.01 deg provided by a star sensor and an updated ephemeris navigation system. This allows automatic geographical mapping of the digital imagery to the nearest picture element. The operational linescan system is the primary data acquisition system that provides real-time or stored, multi-orbit, day-and-night, visual and infrared imagery of clouds. A supplementary sensor package contains five special sensors: (1) a microwave temperature sounder, (2) an advanced X-ray detector, (3) an ionospheric/scintillation monitor, (4) a precipitating electron/ion spectrometer, and (5) a microwave imager. An infrared temperature and moisture sounder and a magnetometer may also be included on this spacecraft. Either recorded or real-time data are transmitted to ground-receiving sites by two redundant S-band transmitters. Recorded data are read out to tracking sites located at Fairchild AFB, Wash., and at Loring AFB, Maine, and relayed by SATCOM to Air Force Global Weather Central, Offutt AFB, Nebraska. Real-time data are read out at mobile tactical sites located around the world. Additional information concerning this satellite program can be found in the report by D. A. Nichols, "The Defense Meteorological Satellite Program," Optical Engineering, v. 14, n. 4, p. 273, July-August, 1975. Group: Platform_Details Entry_ID: DMSP 5D-2/F8 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: DMSP (Defense Meteorological Satellite Program) Short_Name: DMSP 5D-2/F8 Long_Name: Defense Meteorological Satellite Program-F8 End_Group Group: Synonymous_Platform_Names Short_Name: DMSP-F8 Short_Name: USA 26 Short_Name: WX9543 Short_Name: 18123 End_Group Group: Platform_Associated_Instruments Short_Name: SSJ/4 Short_Name: SSM/T Short_Name: SSB/X Short_Name: OLS Short_Name: SSM/I Short_Name: SSI/ES End_Group Group: Orbit Orbit_Inclination: 97.6° Period: 96.89 minutes Perigee: 564.0 km Apogee: 653.0 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1987-053A Online_Resource: http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/dmsp.html Online_Resource: http://www.ngdc.noaa.gov/dmsp/index.html End_Group 2016-06-09 14:36:43.0 [epneff] added altLabel insert AltLabel (id: null text: DMSP-F08 language code: en); B-200 The Beechcraft Super King Air family is part of a line of twin-turboprop aircraft produced by the Beech Aircraft Corporation (now the Beechcraft Division of Hawker Beechcraft). The King Air line comprises a number of model series that fall into two families: the Model 90 series, Model 100 series (these models comprising the King Air family), Model 200 series and Model 300 series. The latter two models were originally marketed as the "Super King Air" family, but the "Super" was dropped in 1996. [Text provided by Wikipedia, http://en.wikipedia.org/wiki/Beechcraft_Super_King_Air ] [Photo provided Iowa State University Flight Service, http://www.fpm.iastate.edu/FlightService/kingair/ ] Group: Platform_Details Entry_ID: B-200 Group: Platform_Identification Platform_Category: Aircraft Short_Name: B-200 Long_Name: Beechcraft King Air B-200 End_Group Creation_Date: 2008-07-14 Online_Resource: http://www.fpm.iastate.edu/FlightService/kingair/ Online_Resource: http://www.hawkerbeechcraft.com/ Online_Resource: http://en.wikipedia.org/wiki/Beechcraft_Super_King_Air Sample_Image: http://www.fpm.iastate.edu/FlightService/kingair/kingair03.jpg End_Group HU-25A 2017-02-08 18:32:22.0 [aaleman] added new platform at request of NSIDC insert AltLabel (id: null text: Dassault HU-25A Guardian language code: en); 2017-02-08 18:31:23.0 [aaleman] Insert Concept add broader relation (HU-25A [d77685bd-aa94-4717-bd97-632699d999b5,278645] - Aircraft [227d9c3d-f631-402d-84ed-b8c5a562fc27,256457]); GEMS [Source: NASA Goddard Space Flight Center News, http://www.nasa.gov/centers/goddard/news/topstory/2009/gems_explore.html ] An exciting new astrophysics mission led by NASA’s Goddard Space Flight Center in Greenbelt, Md., will provide a revolutionary window into the universe. Named the Gravity and Extreme Magnetism Small Explorer (GEMS), the satellite will be the first to systematically measure the polarization of cosmic X-ray sources. "To date, astronomers have measured X-ray polarization from only a single object outside the solar system -- the famous Crab Nebula, the luminous cloud that marks the site of an exploded star," said Jean Swank, a Goddard astrophysicist and the GEMS principal investigator. “We expect that GEMS will detect dozens of sources and really open up this new frontier." Goddard will provide the X-ray mirrors and polarimeter instrument for GEMS and oversee the mission's science operations center, science data processing and systems engineering. Electromagnetic radiation -- light, radio waves, X-rays -- contains a varying electric field. Polarization refers to this field's direction. An everyday example of putting polarization to use is as close as a pair of sunglasses. Reflected light contains an electric field with a specific orientation. Because polarized sunglasses block light vibrating in this direction, they can reduce the glare of reflected sunlight. The extreme gravitational field near a spinning black hole not only bends the paths of X-rays, it also alters the directions of their electric fields. Polarization measurements can reveal the presence of a black hole and provide astronomers with information on its spin. Fast-moving electrons emit polarized X-rays as they spiral through intense magnetic fields, providing GEMS with the means to explore another aspect of extreme environments. "Thanks to these effects, GEMS can probe spatial scales far smaller than any telescope can possibly image," Swank said. Polarized X-rays carry information about the structure of cosmic sources that isn't available in any other way. Group: Platform_Details Entry_ID: GEMS Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Platform_Series_or_Entity: NASA Small Explorer (SMEX) Short_Name: GEMS Long_Name: Gravity and Extreme Magnetism Small Explorer End_Group Creation_Date: 2009-08-11 Online_Resource: http://www.nasa.gov/centers/goddard/news/topstory/2009/gems_explore.html Online_Resource: http://heasarc.gsfc.nasa.gov/docs/gems/ Online_Resource: http://explorers.gsfc.nasa.gov/ Sample_Image: http://www.nasa.gov/centers/goddard/images/content/376204main_GEMS_labeled_226.jpg Group: Platform_Logistics Launch_Date: 2014-07-01 Design_Life: 2 years Primary_Sponsor: USA/NASA End_Group End_Group CESSNA SINGLE-ENGINE AIRCRAFT Himawari The Japanese Geostationary Meteorological Satellite (GMS) series, also known as its nickname, "Himawari" (meaning a "sunflower"), is on the geostationary orbit at 140 degrees of east longitude to carry out weather observation from space being part of the World Weather Watch (WWW) project of the World Meteorological Organization. The images of the earth and clouds sent from this satellite series have been used in many areas such as weather forecasts in TV or newspaper; therefore, it is strongly connected to our daily life. After the "Himawari-6", the GMS series was replaced by a Multifunctional Transport Satellite series to broaden its scope of operation. It is operated by the Japan Meteorological Agency for climatic observation. 2018-07-27 20:20:38.0 [sritz] Move Concepts add narrower relation (Himawari [d8b7fc7d-9cf3-4020-947d-f33d712b64ab,345895] - Himawari-9 [e43cfa6a-fb75-4eeb-8674-25917275ea7e,368003]); 2017-09-27 20:40:31.0 [sritz] insert Definition (id: null text: The Japanese Geostationary Meteorological Satellite (GMS) series, also known as its nickname, "Himawari" (meaning a "sunflower"), is on the geostationary orbit at 140 degrees of east longitude to carry out weather observation from space being part of the World Weather Watch (WWW) project of the World Meteorological Organization. The images of the earth and clouds sent from this satellite series have been used in many areas such as weather forecasts in TV or newspaper; therefore, it is strongly connected to our daily life. After the "Himawari-6", the GMS series was replaced by a Multifunctional Transport Satellite series to broaden its scope of operation. It is operated by the Japan Meteorological Agency for climatic observation. language code: en); 2017-09-27 20:38:46.0 [sritz] Insert Concept add narrower relation (Himawari [d8b7fc7d-9cf3-4020-947d-f33d712b64ab,310213] - Himawari-8 [dd2591d9-35a1-4037-9664-bbfcf4c80b71,310217]); 2017-09-27 20:38:22.0 [sritz] Insert Concept add broader relation (Himawari [d8b7fc7d-9cf3-4020-947d-f33d712b64ab,310213] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,287601]); IMPROVE Initiated by the Environmental Protection Agency (EPA), Interagency Monitoring of Protected Visual Environments(IMPROVE) ambient monitoring network was formed to monitor Federal Class I Areas visibility at 20 locations. Now, the network has expanded to almost 110 sites. IMPROVE's goals are as follow: - Establish current visibility and aerosol conditions in FCIA - Identify chemical species and emission sources responsible for existing man-made visibility impairment in FCIA - Document long-term trends for assessing progress towards the national visibility goal for FCIA (& as required by the Regional Haze Rule) Group: Platform_Details Entry_ID: IMPROVE Group: Platform_Identification Platform_Category: In Situ Land-based Platforms Short_Name: IMPROVE Long_Name: IMPROVE ambient monitoring network End_Group Creation_Date: 2012-07-18 Online_Resource: http://www.epa.gov/ttnamti1/visdata.html End_Group CLM-LSM 2014-05-30 09:15:30.0 [128.183.164.42] SR Added new model. insert AltLabel (id: null text: Common Land Model (CLM) Land Surface Model language code: en); 2014-05-30 09:14:58.0 [128.183.164.42] Insert Concept add broader relation (CLM-LSM [d8e67ddc-abaf-469b-8e84-f1549c1ca70d,106429] - Models [113ecbc2-ab36-4d58-a96c-a6ce0106e749,73395]); Noah-LSM Noah-MP is a land surface model (LSM) using multiple options for key land-atmosphere interaction processes (Niu et al., 2011). Noah-MP contains a separate vegetation canopy defined by a canopy top and bottom, crown radius, and leaves with prescribed dimensions, orientation, density, and radiometric properties. The canopy employs a two-stream radiation transfer approach along with shading effects necessary to achieve proper surface energy and water transfer processes including under-canopy snow processes (Dickinson, 1983; Niu and Yang, 2004). Noah-MP contains a multi-layer snow pack with liquid water storage and melt/refreeze capability and a snow-interception model describing loading/unloading, melt/refreeze capability, and sublimation of canopy-intercepted snow (Yang and Niu 2003; Niu and Yang 2004). Multiple options are available for surface water infiltration and runoff and groundwater transfer and storage including water table depth to an unconfined aquifer 2018-12-20 18:03:48.0 [tstevens] insert Definition (id: null text: Noah-MP is a land surface model (LSM) using multiple options for key land-atmosphere interaction processes (Niu et al., 2011). Noah-MP contains a separate vegetation canopy defined by a canopy top and bottom, crown radius, and leaves with prescribed dimensions, orientation, density, and radiometric properties. The canopy employs a two-stream radiation transfer approach along with shading effects necessary to achieve proper surface energy and water transfer processes including under-canopy snow processes (Dickinson, 1983; Niu and Yang, 2004). Noah-MP contains a multi-layer snow pack with liquid water storage and melt/refreeze capability and a snow-interception model describing loading/unloading, melt/refreeze capability, and sublimation of canopy-intercepted snow (Yang and Niu 2003; Niu and Yang 2004). Multiple options are available for surface water infiltration and runoff and groundwater transfer and storage including water table depth to an unconfined aquifer language code: en); 2018-12-20 18:00:37.0 [tstevens] update AltLabel (Noah Land Surface Model); 2014-05-30 09:17:48.0 [128.183.164.42] SR Added new model insert AltLabel (id: null text: Noah Land Surface Model language code: en); 2014-05-30 09:16:49.0 [128.183.164.42] Insert Concept add broader relation (Noah-LSM [d92e3dca-7aeb-4cc1-9dc0-571844337222,106437] - Models [113ecbc2-ab36-4d58-a96c-a6ce0106e749,73395]); SEASOAR SeaSoar is a a towed, undulating measurement package. The moveable wings are contolled by a topside computer which sends up-down signals via the conducting tow cable. The wings are moved by a hydraulic unit which is powered by an impeller on the tail of SeaSoar. Data is returned to a topside computer network via the conducting cable. Additional info and pictures at "http://www.oce.orst.edu/po/research/barth/" [Source: Oregon State University] DSCOVR [Text Source: NOAA NESDIS] The Deep Space Climate Observatory, or DSCOVR, will maintain the nation's real-time solar wind monitoring capabilities which are critical to the accuracy and lead time of NOAA's space weather alerts and forecasts. Without timely and accurate warnings, space weather events like the geomagnetic storms caused by changes in solar wind have the potential to disrupt nearly every major public infrastructure system, including power grids, telecommunications, aviation and GPS. DSCOVR will succeed NASA's Advanced Composition Explore's (ACE) role in supporting solar wind alerts and warnings from the L1 orbit, the neutral gravity point between the Earth and sun approximately one million miles from Earth. L1 is a good position from which to monitor the sun, because the constant stream of particles from the sun (the solar wind) reaches L1 about an hour before reaching Earth. More Information: https://www.nesdis.noaa.gov/content/dscovr-deep-space-climate-observatory Group: Platform_Details Entry_ID: DSCOVR Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Short_Name: DSCOVR Long_Name: Deep Space Climate Observatory End_Group Creation_Date: 2014-05-07 Online_Resource: https://www.nesdis.noaa.gov/content/dscovr-deep-space-climate-observ Online_Resource: https://epic.gsfc.nasa.gov Online_Resource: https://eosweb.larc.nasa.gov/project/dscovr/dscovr_table Group: Platform_Logistics Primary_Sponsor: NOAA End_Group End_Group 2019-10-01 16:34:57.0 [sritz] update Definition ([Text Source: NOAA NESDIS] The Deep Space Climate Observatory, or DSCOVR, will maintain the nation's real-time solar wind monitoring capabilities which are critical to the accuracy and lead time of NOAA's space weather alerts and forecasts. Without timely and accurate warnings, space weather events like the geomagnetic storms caused by changes in solar wind have the potential to disrupt nearly every major public infrastructure system, including power grids, telecommunications, aviation and GPS. DSCOVR will succeed NASA's Advanced Composition Explore's (ACE) role in supporting solar wind alerts and warnings from the L1 orbit, the neutral gravity point between the Earth and sun approximately one million miles from Earth. L1 is a good position from which to monitor the sun, because the constant stream of particles from the sun (the solar wind) reaches L1 about an hour before reaching Earth. More Information: https://www.nesdis.noaa.gov/content/dscovr-deep-space-climate-observatory Group: Platform_Details Entry_ID: DSCOVR Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Short_Name: DSCOVR Long_Name: Deep Space Climate Observatory End_Group Creation_Date: 2014-05-07 Online_Resource: https://www.nesdis.noaa.gov/content/dscovr-deep-space-climate-observ Online_Resource: https://epic.gsfc.nasa.gov Online_Resource: https://eosweb.larc.nasa.gov/project/dscovr/dscovr_table Group: Platform_Logistics Primary_Sponsor: NOAA End_Group End_Group); delete Resource (null); 2014-05-07 12:52:00.0 [128.183.164.42] added platform update AltLabel (Deep Space Climate Observatory); 2014-05-07 12:43:34.0 [128.183.164.42] added platform insert AltLabel (id: null text: DEEP SPACE CLIMATE OBSERVATORY language code: en); insert Definition (id: null text: The primary operations objective of the DSCOVR mission is to provide solar wind thermal plasma and magnetic field measurements to enable space weather forecasting by NOAA. Secondary science objectives are to image the Sun lit disk of Earth in 10 spectral bands with a spatial resolution of 12 km or better, to determine ozone, aerosol, cloud cover, cloud height, vegetation, and leaf area indices and to measure the Earth reflected irradiance in the wavelength range of 0.2 - 100 microns. language code: en); 2014-05-07 12:41:20.0 [128.183.164.42] Insert Concept add broader relation (DSCOVR [d9cc74c9-34f5-48a4-a982-e4c6f8a5171c,106359] - Solar/Space Observation Satellites [8e8b7689-0a8e-47a4-9c68-5f6a207104d5,73505]); STS-51B The first dedicated mission with acquisition of science data as its primary objective, Spacelab 3 was a multidisciplinary mission emphasizing investigations requiring the low-gravity environment of Earth orbit. The experiments covered several disciplines. For the materials processing discipline, higher-quality crystals were grown by two methods; namely, seed crystal growth in a saturated solution and condensation from the vapor phase. The two fluid physics experiments studied the dynamic behavior of rotating and oscillating liquid drops, and the convection processes found in planetary atmospheres and in stellar interiors. The performance of equipment and facilities specially designed for investigations on the Spacelab Life Sciences mission series was evaluated. The investigations selected for the Spacelab 3 mission originated in the United States, France, and India, and represented a total of five different disciplines, including material science, life sciences, fluid mechanics, atmospheric science, and astronomy. Two of the investigations, one in material science and one in astronomy, had already flown aboard Spacelab 1. Many of the Spacelab 3 investigations were scheduled to be modified and reflown on later missions to further explore the discoveries of this mission. Some of the experiments were located in the module, some on the pallet in the payload bay, and one at middeck. Spacelab 3 consisted of a Spacelab long module and a pallet. The mission successfully demonstrated the capability of Spacelab for multidiscipline research in microgravity. [Summary provided by NASA.] Group: Platform_Details Entry_ID: STS-51B Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Platform_Series_or_Entity: SPACE SHUTTLE Short_Name: STS-51B Long_Name: Space Transport System STS-51B End_Group Group: Synonymous_Platform_Names Short_Name: Challenger End_Group Group: Orbit Orbit_Inclination: 28.45 degrees Perigee: 370 km Apogee: 370 km End_Group Creation_Date: 2008-01-29 Online_Resource: http://science.ksc.nasa.gov/shuttle/missions/sts-51/mission-sts-51.html Sample_Image: http://www.nasa.gov/images/content/134455main_sts-51b-crew-sm.jpg Group: Platform_Logistics Launch_Date: 1985-04-29 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: NASA End_Group End_Group Spire ire's constellation of 60+ nanosatellites is designed, built, and operated by Spire out of Glasgow, UK and its European headquarters in Luxembourg. With a diversified launch manifest and the capacity to build up to two satellites per week, Spire's constellation continues to grow. The 28-strong ground station network provides timely data that is processed by Spire and made available through their customer API. Spire is a data and analytics company that collects data from space to solve problems on Earth. They identify, track, and predict the movement of the world's resources and weather systems by "listening" to the planet in real-time and applying machine learning to understand what will happen in the future. They continue to launch additional satellites and add new payloads to the constellation. 2019-05-06 12:42:47.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: 9a8265a0-1ff1-47ac-9204-f839ab508471 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 75a145eb-0fed-4011-90db-286010e10fb0 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 4e7f5d0e-4d2a-4a03-bd89-6361cc46f207 relationship type: null relationship value: null generated by: null); 2019-05-02 19:40:21.0 [mmorahan] insert Definition (id: null text: ire's constellation of 60+ nanosatellites is designed, built, and operated by Spire out of Glasgow, UK and its European headquarters in Luxembourg. With a diversified launch manifest and the capacity to build up to two satellites per week, Spire's constellation continues to grow. The 28-strong ground station network provides timely data that is processed by Spire and made available through their customer API. Spire is a data and analytics company that collects data from space to solve problems on Earth. They identify, track, and predict the movement of the world's resources and weather systems by "listening" to the planet in real-time and applying machine learning to understand what will happen in the future. They continue to launch additional satellites and add new payloads to the constellation. language code: en); insert Resource (id: null type: image url: https://earth.esa.int/documents/10174/3652683/Spire-120.jpg); 2019-05-02 19:36:37.0 [mmorahan] Insert Concept add broader relation (Spire [da278af5-097b-47e7-903d-4deac395c4de,368757] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761]); HYSPIRI [Source: NASA Hyperspectral Infrared Imager, https://hyspiri.jpl.nasa.gov/ ] The Hyperspectral Infrared Imager or HyspIRI mission will study the world’s ecosystems and provide critical information on natural disasters such as volcanoes, wildfires and drought. HyspIRI will be able to identify the type of vegetation that is present and whether the vegetation is healthy. The mission will provide a benchmark on the state of the worlds ecosystems against which future changes can be assessed. The mission will also assess the pre-eruptive behavior of volcanoes and the likelihood of future eruptions as well as the carbon and other gases released from wildfires. Orbit: LEO, SSO Instruments: Hyperspectral spectrometer Group: Platform_Details Entry_ID: HYSPIRI Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NASA Decadal Survey Short_Name: HYSPIRI Long_Name: Hyperspectral Infrared Imager End_Group Group: Orbit Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2009-12-18 Online_Resource: https://hyspiri.jpl.nasa.gov/ Group: Platform_Logistics Primary_Sponsor: USA/NASA End_Group End_Group 2020-01-03 23:44:40.0 [sritz] update Definition ([Source: NASA Hyperspectral Infrared Imager, https://hyspiri.jpl.nasa.gov/ ] The Hyperspectral Infrared Imager or HyspIRI mission will study the world’s ecosystems and provide critical information on natural disasters such as volcanoes, wildfires and drought. HyspIRI will be able to identify the type of vegetation that is present and whether the vegetation is healthy. The mission will provide a benchmark on the state of the worlds ecosystems against which future changes can be assessed. The mission will also assess the pre-eruptive behavior of volcanoes and the likelihood of future eruptions as well as the carbon and other gases released from wildfires. Orbit: LEO, SSO Instruments: Hyperspectral spectrometer Group: Platform_Details Entry_ID: HYSPIRI Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NASA Decadal Survey Short_Name: HYSPIRI Long_Name: Hyperspectral Infrared Imager End_Group Group: Orbit Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2009-12-18 Online_Resource: https://hyspiri.jpl.nasa.gov/ Group: Platform_Logistics Primary_Sponsor: USA/NASA End_Group End_Group); update Definition (NASA Hyperspectral Infrared Imager, https://hyspiri.jpl.nasa.gov/); delete Resource (null); ROV Remotely operated underwater vehicles (ROVs) are unoccupied, highly maneuverable underwater robots operated by a person aboard a surface vessel. They are linked to the ship by a group of cables that carry electrical signals back and forth between the operator and the vehicle. Most are equipped with at least a video camera and lights. Additional equipment is commonly added to expand the vehicle's capabilities. These may include a still camera, a manipulator or cutting arm, water samplers, and instruments that measure water clarity, light penetration, and temperature. First developed for industrial purposes, such as internal and external inspections of pipelines and the structural testing of offshore platforms, ROVs are now used for many applications, many of them scientific. They have proven extremely valuable in ocean exploration, and are also used for educational programs at aquaria and to link to scientific expeditions live via the internet. [Information obtained from http://www.oceanexplorer.noaa.gov/technology/subs/rov/rov.html ] Group: Platform_Details Entry_ID: ROV Group: Platform_Identification Platform_Category: In Situ Ocean-based Platforms Short_Name: ROV Long_Name: Remotely Operated Vehicles End_Group Group: Synonymous_Platform_Names Short_Name: ROV End_Group Creation_Date: 2007-12-13 Online_Resource: http://www.oceanexplorer.noaa.gov/technology/subs/rov/rov.html Sample_Image: http://upload.wikimedia.org/wikipedia/en/thumb/9/99/ROV_working_on_a_subsea_structure.jpg/400px-ROV_working_on_a_subsea_structure.jpg End_Group 2020-01-21 17:27:29.0 [tstevens] Insert Concept add narrower relation (ROV [da6420b6-48ec-4ae2-98c7-0ef0538815a0,542741] - Argus [ddc7ed71-2626-4b81-8079-82c04d0bdc91,559755]); 2020-01-21 17:27:17.0 [tstevens] Insert Concept add narrower relation (ROV [da6420b6-48ec-4ae2-98c7-0ef0538815a0,542741] - Seirios [f21d8715-f805-427d-b006-57a5d1240d1c,559751]); 2020-01-21 17:26:55.0 [tstevens] Insert Concept add narrower relation (ROV [da6420b6-48ec-4ae2-98c7-0ef0538815a0,542741] - RCV-150 [7ec61a93-3c42-4af1-adca-8f26d22d3d27,559747]); 2020-01-21 17:26:43.0 [tstevens] Insert Concept add narrower relation (ROV [da6420b6-48ec-4ae2-98c7-0ef0538815a0,542741] - Little Hercules [b3ef5a11-5c6d-4f14-a0bb-a90e8614a908,559743]); 2020-01-21 17:26:19.0 [tstevens] Insert Concept add narrower relation (ROV [da6420b6-48ec-4ae2-98c7-0ef0538815a0,542741] - Hercules [654fb060-af2f-4d5d-af89-2216ef7939ca,559739]); 2020-01-21 17:25:56.0 [tstevens] Insert Concept add narrower relation (ROV [da6420b6-48ec-4ae2-98c7-0ef0538815a0,542741] - Sonsub Innovator [2adc78b1-be95-4cec-82a9-603f6a493d5b,559735]); 2020-01-21 17:25:27.0 [tstevens] Insert Concept add narrower relation (ROV [da6420b6-48ec-4ae2-98c7-0ef0538815a0,542741] - ROPOS [127be6b4-50ad-496d-939b-5c1dc47ac4ff,559731]); 2020-01-21 17:25:15.0 [tstevens] Insert Concept add narrower relation (ROV [da6420b6-48ec-4ae2-98c7-0ef0538815a0,542741] - Phantom DHD2+2 [897c4eed-6f5a-4b60-9780-a73362ec84f2,559727]); 2020-01-21 17:24:41.0 [tstevens] Insert Concept add narrower relation (ROV [da6420b6-48ec-4ae2-98c7-0ef0538815a0,542741] - Jason II [b7831fc5-0da7-4c2a-b4d6-dae934648d95,559723]); 2020-01-21 17:24:23.0 [tstevens] Insert Concept add narrower relation (ROV [da6420b6-48ec-4ae2-98c7-0ef0538815a0,542741] - Jason [74995db1-1047-4e0b-b0c9-b4b9f7bdd6b6,559719]); 2020-01-21 17:23:04.0 [tstevens] Insert Concept add narrower relation (ROV [da6420b6-48ec-4ae2-98c7-0ef0538815a0,542741] - Global Explorer [464643c0-4600-4d38-9927-9587fa8904bb,559715]); 2020-01-21 17:21:50.0 [tstevens] Insert Concept add narrower relation (ROV [da6420b6-48ec-4ae2-98c7-0ef0538815a0,542741] - Deep Discoverer [023cf280-8fd9-4a4d-8e18-54fac3f6dbbb,559711]); OCO-3 Orbiting Carbon Observatory-3 (OCO-3) will be flying on the International Space Station (ISS) and will continue the important measurement begun by OCO-2 in 2014. Some quick facts about OCO-3 are: - OCO-3 is a critical element in the continuation of global carbon dioxide (CO2) measurements focused on understanding the regional sources and sinks of CO2 from the unique vantage point of the International Space Station (ISS). - OCO-3 can also contribute to focused studies of how space based measurements can constrain rapidly changing anthropogenic (man-made) emissions. Anthropogenic emissions could be the largest source of uncertainty in the global carbon budget as OCO-3 measurements reduce uncertainty of natural fluxes. OCO-3 has the ability to makes measurements at different times of the day. - OCO-3 measurements can be combined with evapotranspiration and biomass measurements, such as those from other ISS instruments ECOSTRESS and GEDI, to study process details of the terrestrial ecosystem. - OCO-2 has demonstrated that atmospheric XCO2 can be measured from space with precision of better than 1 ppm. OCO-3 is expected to have similar performance. More Information: https://ocov3.jpl.nasa.gov/ 2020-01-04 00:19:19.0 [sritz] Move Concepts delete broader relation (null); add broader relation (OCO-3 [da687fb4-016d-4b4d-92c2-380640ca5640,542743] - NASA Earth System Science Pathfinder [de1e0fd4-d865-4726-9bde-96804cf455b7,542765]); 2019-05-03 17:56:18.0 [sritz] update Definition (Orbiting Carbon Observatory-3 (OCO-3) will be flying on the International Space Station (ISS) and will continue the important measurement begun by OCO-2 in 2014. Some quick facts about OCO-3 are: - OCO-3 is a critical element in the continuation of global carbon dioxide (CO2) measurements focused on understanding the regional sources and sinks of CO2 from the unique vantage point of the International Space Station (ISS). - OCO-3 can also contribute to focused studies of how space based measurements can constrain rapidly changing anthropogenic (man-made) emissions. Anthropogenic emissions could be the largest source of uncertainty in the global carbon budget as OCO-3 measurements reduce uncertainty of natural fluxes. OCO-3 has the ability to makes measurements at different times of the day. - OCO-3 measurements can be combined with evapotranspiration and biomass measurements, such as those from other ISS instruments ECOSTRESS and GEDI, to study process details of the terrestrial ecosystem. - OCO-2 has demonstrated that atmospheric XCO2 can be measured from space with precision of better than 1 ppm. OCO-3 is expected to have similar performance. More Information: https://ocov3.jpl.nasa.gov/); update Definition (https://ocov3.jpl.nasa.gov/); 2018-04-24 20:51:33.0 [sritz] insert WeightedRelation (id: null related concept uuid: 3e77610e-bb50-4c45-a62a-c50194ec16c2 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 6d5f222a-7750-4fd3-aa14-3c0d0059bc85 relationship type: null relationship value: null generated by: null); 2018-04-24 20:49:01.0 [sritz] insert Definition (id: null text: Orbiting Carbon Observatory – 3 (OCO-3) is a complete stand-alone payload built using the spare OCO-2 flight instrument, with additional elements added to accommodate installation and operation on the International Space Station (ISS). More Information: https://science.nasa.gov/missions/oco-3 language code: en); 2018-04-24 20:47:39.0 [sritz] Insert Concept add broader relation (OCO-3 [da687fb4-016d-4b4d-92c2-380640ca5640,367551] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761]); INSAT INSAT-3D is an advanced weather satellite of India configured with improved Imaging System and Atmospheric Sounder. INSAT-3D is designed for enhanced meteorological observations, monitoring of land and ocean surfaces, generating vertical profile of the atmosphere in terms of temperature and humidity for weather forecasting and disaster warning. It carries four payloads - a) 6 channel multi-spectral Imager b) 19 channel Sounder c) Data Relay Transponder (DRT) d) Search and Rescue Transponder The payloads of INSAT-3D provides continuity and further augment the capability to provide various meteorological as well as search and rescue services. Group: Platform_Details Entry_ID: INSAT-3D Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: INSAT (Indian National Satellite) Short_Name: INSAT Long_Name: Indian National Satellite End_Group Group: Synonymous_Platform_Names Short_Name: INSAT-3D End_Group Group: Orbit Orbit_Altitude: 36000 Orbit_Inclination: 0.23 Period: 1428 Perigee: 35469 Apogee: 35799 Orbit_Type: GEO > GEOSYNCHRONOUS > GEOSTATIONARY End_Group Creation_Date: 2014-06-11 Online_Resource: http://www.isro.gov.in/satellites/insat-3d.aspx Sample_Image: http://www.isro.gov.in/satellites/images/insat-3d_img.jpg Group: Platform_Logistics Launch_Date: 2013-07-26 Launch_Site: KOUROU, FRENCH GUIANA Design_Life: 07 years Primary_Sponsor: ISRO End_Group End_Group LPATS Global Atmospherics, Inc's large-area Lightning Position and Tracking System (LPATS) is a highly-accurate and sophisticated computer-based system using a time-of-arrival (TOA) technique for locating cloud-to-ground lightning strokes. This system has been installed throughout the U.S. to form the LPATS National Network (LN2). The precise time that lightning touches the ground is monitored to sub microsecond accuracy at several receiver sites simultaneously. Available data include stroke position, energy, rise time, probability, counting, and ranging, along with color tracking, time of incidence, and storm historic events on a national or regional scale. LPATS networks also currently exist in Europe, South America, and Asia. Group: Platform_Details Entry_ID: LPATS Group: Platform_Identification Platform_Category: In Situ Land-based Platforms Platform_Series_or_Entity: WEATHER STATIONS/NETWORKS Short_Name: LPATS Long_Name: Lightning Positioning and Tracking System Network End_Group Group: Synonymous_Platform_Names Short_Name: LPATS End_Group Creation_Date: 2007-12-10 Online_Resource: http://www.pa.op.dlr.de/cleocd/lpats/s.htm End_Group Kingfisher Kingfisher Unmanned Surface Vessel (USV) is an agile, battery operated boat designed for research and rapid prototyping. Fully equipped with a sensor station, an onboard Atom PC for running hardware drivers and intelligence, electric thrusters, GPS, wifi radio, and semi-planing hulls, Kingfisher serves as a marine research platform as well as a remote survey system for bathymetric and hyrometric data collection. This USV includes advanced payload capabilities, easy stow and portability, and can be easily customized to meet research requirements. 2020-03-17 12:21:23.0 [tstevens] insert Definition (id: null text: Kingfisher Unmanned Surface Vessel (USV) is an agile, battery operated boat designed for research and rapid prototyping. Fully equipped with a sensor station, an onboard Atom PC for running hardware drivers and intelligence, electric thrusters, GPS, wifi radio, and semi-planing hulls, Kingfisher serves as a marine research platform as well as a remote survey system for bathymetric and hyrometric data collection. This USV includes advanced payload capabilities, easy stow and portability, and can be easily customized to meet research requirements. language code: en); 2020-03-17 12:19:43.0 [tstevens] Insert Concept add broader relation (Kingfisher [dba6c8ed-8444-4e18-965c-9c0e30186ac3,559867] - USV [bf17bbac-0fc9-48b3-9b03-bd780ffe1eb0,542539]); LANDSAT-2 LANDSAT-2 (LAND REMOTE-SENSING SATELLITE-2) Landsat 2 is the second satellite of the Landsat program. The spacecraft originally carried a designation of ERTS-B (Earth Resource Technology Satellite B) but was renamed &Landsat 2& prior to its launch on January 22, 1975. Despite having a design life of one year, Landsat 2 operated for over seven years, finally ceasing operations on February 25, 1982. As in the case of its predecessor Landsat 1, the satellite&#039;s payload included two remote sensing instruments, the Return Beam Vidicon (RBV) and the Multi-Spectral Scanner (MSS). The specifications for these instruments were identical to those of the instruments carried on Landsat 1. (This was not the case for Landsat 3, which added a short-lived thermal band to the MSS instrument.) The data acquired by the MSS was considered more scientifically useful than the data returned from the RBV, which was rarely used and considered only for engineering evaluation purposes. [Summary provided by NASA.] Group: Platform_Details Entry_ID: LANDSAT-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: LANDSAT Short_Name: LANDSAT-2 End_Group Group: Platform_Associated_Instruments Short_Name: MSS Short_Name: RBV End_Group Group: Orbit Orbit_Altitude: 900 km Orbit_Inclination: 99.2 degree Equator_Crossing: 9:42 AM mean local time Period: 103 minutes Repeat_Cycle: 18 days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-02-01 Online_Resource: https://landsat.gsfc.nasa.gov/landsat-2-2/ Online_Resource: https://www.usgs.gov/land-resources/nli/landsat/landsat-2 Group: Platform_Logistics Launch_Date: 1975-01-22 Launch_Site: Vandenberg AFB Design_Life: 1 Year Primary_Sponsor: NASA Primary_Sponsor: USGS End_Group End_Group 2020-01-02 18:49:02.0 [sritz] update Definition (Landsat 2 is the second satellite of the Landsat program. The spacecraft originally carried a designation of ERTS-B (Earth Resource Technology Satellite B) but was renamed &Landsat 2& prior to its launch on January 22, 1975. Despite having a design life of one year, Landsat 2 operated for over seven years, finally ceasing operations on February 25, 1982. As in the case of its predecessor Landsat 1, the satellite&#039;s payload included two remote sensing instruments, the Return Beam Vidicon (RBV) and the Multi-Spectral Scanner (MSS). The specifications for these instruments were identical to those of the instruments carried on Landsat 1. (This was not the case for Landsat 3, which added a short-lived thermal band to the MSS instrument.) The data acquired by the MSS was considered more scientifically useful than the data returned from the RBV, which was rarely used and considered only for engineering evaluation purposes. [Summary provided by NASA.] Group: Platform_Details Entry_ID: LANDSAT-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: LANDSAT Short_Name: LANDSAT-2 End_Group Group: Platform_Associated_Instruments Short_Name: MSS Short_Name: RBV End_Group Group: Orbit Orbit_Altitude: 900 km Orbit_Inclination: 99.2 degree Equator_Crossing: 9:42 AM mean local time Period: 103 minutes Repeat_Cycle: 18 days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-02-01 Online_Resource: https://landsat.gsfc.nasa.gov/landsat-2-2/ Online_Resource: https://www.usgs.gov/land-resources/nli/landsat/landsat-2 Group: Platform_Logistics Launch_Date: 1975-01-22 Launch_Site: Vandenberg AFB Design_Life: 1 Year Primary_Sponsor: NASA Primary_Sponsor: USGS End_Group End_Group); 2019-12-31 21:26:49.0 [sritz] update Definition (https://landsat.gsfc.nasa.gov/landsat-2/); 2019-12-31 21:16:19.0 [sritz] update Definition (Landsat 2 is the second satellite of the Landsat program. The spacecraft originally carried a designation of ERTS-B (Earth Resource Technology Satellite B) but was renamed &Landsat 2& prior to its launch on January 22, 1975. Despite having a design life of one year, Landsat 2 operated for over seven years, finally ceasing operations on February 25, 1982. As in the case of its predecessor Landsat 1, the satellite&#039;s payload included two remote sensing instruments, the Return Beam Vidicon (RBV) and the Multi-Spectral Scanner (MSS). The specifications for these instruments were identical to those of the instruments carried on Landsat 1. (This was not the case for Landsat 3, which added a short-lived thermal band to the MSS instrument.) The data acquired by the MSS was considered more scientifically useful than the data returned from the RBV, which was rarely used and considered only for engineering evaluation purposes. [Summary provided by NASA.] Group: Platform_Details Entry_ID: LANDSAT-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: LANDSAT Short_Name: LANDSAT-2 End_Group Group: Platform_Associated_Instruments Short_Name: MSS Short_Name: RBV End_Group Group: Orbit Orbit_Altitude: 900 km Orbit_Inclination: 99.2 degree Equator_Crossing: 9:42 AM mean local time Period: 103 minutes Repeat_Cycle: 18 days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-02-01 Online_Resource: https://landsat.gsfc.nasa.gov/landsat-2-2/ Online_Resource: https://www.usgs.gov/land-resources/nli/landsat/landsat-2 Group: Platform_Logistics Launch_Date: 1975-01-22 Launch_Site: Vandenberg AFB Design_Life: 1 Year Primary_Sponsor: NASA Primary_Sponsor: USGS End_Group End_Group); delete Resource (null); 2016-06-09 15:31:39.0 [epneff] added altLabel insert AltLabel (id: null text: LANDSAT-2 (LAND REMOTE-SENSING SATELLITE-2) language code: en); PIBAL A small balloon whose ascent is followed by a theodolite in order to obtain data for the computation of the speed and direction of winds in the upper air. [Source: DSS] Group: Platform_Details Entry_ID: PIBAL Group: Platform_Identification Platform_Category: Balloons/Rockets Short_Name: PIBAL Long_Name: Pilot Balloons End_Group Creation_Date: 2007-08-21 Online_Resource: http://www.tpub.com/content/aerographer/14270/css/14270_29.htm End_Group IRS-P3 The IRS-P3 satellite was launched from Sriharikota, India, using Polar Satellite Launch Vehicle – PLSV-D3. IRS-P3 was put in a polar, sun-synchronous orbit at an altitude of 817km with equatorial crossing time of 10:30 A.M in the descending node. IRS - P3 has an X-ray astronomy and two remote sensing payloads, namely Wide Field Sensor (WiFS) and Modular Optoelectronics Scanner (MOS). The mission caters to oceanography applications. IRS - P3 WiFS is similar to IRS - 1C WiFS but for the inclusion of an additional band in the Middle Infra-red (MIR) region. This sensor is primarily meant for vegetation dynamic studies while MOS is meant for ocean related studies. MOS has helped the ocean application scientists in developing necessary algorithms for extracting ocean parameters such as phytoplankton, yellow substance and suspended sediments in ocean waters. [Summary provided by the Indian Remote Sensing Agency.] Group: Platform_Details Entry_ID: IRS-P3 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: IRS (Indian Remote Sensing Satellite) Short_Name: IRS-P3 Long_Name: Indian Remote Sensing Satellite P3 End_Group Group: Synonymous_Platform_Names Short_Name: IRS-P3 End_Group Group: Platform_Associated_Instruments Short_Name: WIFS Short_Name: MOS End_Group Group: Orbit Orbit_Altitude: 817 km Orbit_Inclination: 98.69 deg Equator_Crossing: 10.30 A.M Period: 101.35 min Repeat_Cycle: 24 days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-10-05 Online_Resource: http://www.isro.gov.in/satellites/irs-p3.aspx Sample_Image: http://www.isro.gov.in/satellites/images/irsp3_img.gif Group: Platform_Logistics Launch_Date: 1996-03-21 Launch_Site: Sriharikota Island, India Primary_Sponsor: India End_Group End_Group GROUND-BASED OBSERVATIONS GROUND-BASED OBSERVATION Ground-based Observations: Observations that are located along the ground or land surface. [Source: The American Heritage Dictionary of the English Language, Fourth Edition Copyright 2000 by Houghton Mifflin Company] Group: Platform_Details Entry_ID: GROUND-BASED OBSERVATIONS Group: Platform_Identification Platform_Category: In Situ Land-based Platforms Short_Name: GROUND-BASED OBSERVATIONS End_Group End_Group 2016-06-09 18:42:47.0 [epneff] added altLabel insert AltLabel (id: null text: GROUND-BASED OBSERVATION language code: en); METEOSAT [Text Source: EUMETSAT, http://www.eumetsat.int/Home/Main/Satellites/index.htm?l=en ] Meteosat First Generation refers to a series of geostationary satellites that have provided images of the full Earth disc and data for weather forecasts in a continuous and reliable stream for a quarter of a century. The first Meteosat, Meteosat-1, was launched in 1977, and the last of the first generation, Meteosat-7, was launched 20 years later, in 1997. More Information: http://www.eumetsat.int/Home/Main/Satellites/MeteosatFirstGeneration/index.htm?l=en Meteosat Second Generation (MSG) consists of a series of four geostationary meteorological satellites, along with ground-based infrastructure, that will operate consecutively until 2020. The MSG satellites carry an impressive pair of instruments, the Spinning Enhanced Visible and InfraRed Imager (SEVIRI), which has the capacity to observe the Earth in 12 spectral channels and provide image data which is core to operational forecasting needs, and the Geostationary Earth Radiation Budget (GERB) instrument supporting climate studies. More Information: http://www.eumetsat.int/Home/Main/Satellites/MeteosatSecondGeneration/MissionOverview/index.htm?l=en The Meteosat Third Generation (MTG) system is being established through cooperation between EUMETSAT and the European Space Agency (ESA). ESA has already contributed to the initial research and development of the new satellites. The first MTG-I and MTG-S prototypes are being developed by ESA as part of its MTG programme. The EUMETSAT MTG programme includes the procurement of the four recurrent satellites - three MTG-Is and one additional MTG-S - as well as six launches, the development of the ground segment and the operations of all satellites. The Euronews video (right) provides a useful introduction to past and future developments in European satellite meteorology, with particular reference to the MTG programme. The MTG series will comprise six satellites, with the first spacecraft likely to be ready for launch from 2017. The in orbit configuration will consist of two parallel positioned satellites, the MTG-I (imager) and the MTG-S (sounder) platforms. Unlike the first and second generation Meteosat series, MTG will be based on three axes stabilised platforms having the advantage that the instruments are 100% of their in orbit time pointed to the Earth. Such improvements are necessary to achieve compliance with more demanding user requirements on spatial resolution, repeat cycle and signal to noise ratio, and are a prerequisite to conduct soundings from geostationary orbit. MTG-I satellites will fly the Flexible Combined Imager (FCI) and an imaging lightning detection instrument the Lightning Imager (LI). The MTG-S will include an interferometer the InfraRed Sounder (IRS) with hyper-spectral resolution in the thermal spectral domain, and the Sentinel-4 instrument, the high resolution Ultraviolet Visible Near-infrared (UVN) spectrometer. The programme should guarantee access to space-acquired meteorological data until at least the late 2030s. http://www.eumetsat.int/Home/Main/Satellites/MeteosatThirdGeneration/index.htm?l=en Group: Platform_Details Entry_ID: METEOSAT Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: METEOSAT Short_Name: METEOSAT End_Group Online_Resource: http://www.eumetsat.int/Home/Main/Satellites/MeteosatFirstGeneration/index.htm?l=en Online_Resource: http://www.eumetsat.int/Home/Main/Satellites/MeteosatSecondGeneration/MissionOverview/index.htm?l=en Online_Resource: http://www.eumetsat.int/Home/Main/Satellites/MeteosatThirdGeneration/index.htm?l=en Group: Platform_Logistics Launch_Date: 1977-12-09 Primary_Sponsor: ESA Primary_Sponsor: EUMETSAT End_Group End_Group Himawari-8 Himawari 8 (ひまわり8号) is a Japanese weather satellite, the 8th of the Himawari geostationary weather satellites operated by the Japan Meteorological Agency. The spacecraft was constructed by Mitsubishi Electric with assistance from Boeing, and is the first of two similar satellites to be based on the DS-2000 satellite bus.[3] Himawari 8 entered operational service on 7 July 2015 and is the successor to MTSAT-2 (Himawari 7) which was launched in 2006. 2018-07-27 20:20:38.0 [sritz] Move Concepts delete narrower relation (null); 2018-07-27 20:20:17.0 [sritz] Insert Concept add narrower relation (Himawari-8 [dd2591d9-35a1-4037-9664-bbfcf4c80b71,345927] - Himawari-9 [e43cfa6a-fb75-4eeb-8674-25917275ea7e,368003]); 2017-09-27 20:58:38.0 [sritz] update WeightedRelation (Platform-Instrument); update WeightedRelation (1); 2017-09-27 20:58:11.0 [sritz] insert WeightedRelation (id: null related concept uuid: 228edef6-d682-40eb-8b41-e37c78b9e7c5 relationship type: null relationship value: null generated by: null); 2017-09-27 20:43:41.0 [sritz] insert Definition (id: null text: Himawari 8 (ひまわり8号) is a Japanese weather satellite, the 8th of the Himawari geostationary weather satellites operated by the Japan Meteorological Agency. The spacecraft was constructed by Mitsubishi Electric with assistance from Boeing, and is the first of two similar satellites to be based on the DS-2000 satellite bus.[3] Himawari 8 entered operational service on 7 July 2015 and is the successor to MTSAT-2 (Himawari 7) which was launched in 2006. language code: en); 2017-09-27 20:38:46.0 [sritz] Insert Concept add broader relation (Himawari-8 [dd2591d9-35a1-4037-9664-bbfcf4c80b71,310217] - Himawari [d8b7fc7d-9cf3-4020-947d-f33d712b64ab,310213]); Ice Shelf Ice Shelf 2018-11-07 21:51:20.0 [sritz] insert AltLabel (id: null category: null text: Ice Shelf language code: en); 2018-11-07 21:50:54.0 [sritz] Insert Concept add broader relation (Ice Shelf [dd445d5a-14d5-4813-b1cb-243799a044f7,368249] - In Situ Land-based Platforms [4f396ff6-7bea-4ba4-afa3-198ebd914a4a,344951]); AIM NASA's AIM spacecraft began its two-year mission April 25, 2007 after a flawless ride to Earth orbit aboard an Orbital Sciences Pegasus XL rocket. Launch took place at 1:26 PDT. Launch operations at Vandenberg Air Force Base in California ran smoothly, with no technical or weather issues causing concern. The AIM mission is the first dedicated to exploring mysterious ice clouds that dot the edge of space in Earth's polar regions. These clouds have grown brighter and more prevalent in recent years and some scientists suggest that changes in these clouds may be the result of climate change. [Source: NASA AIM Mission Home Page http://www.nasa.gov/mission_pages/aim/index.html ] Group: Platform_Details Entry_ID: AIM Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NASA Small Explorers (SMEX) Short_Name: AIM Long_Name: Aeronomy of Ice in the Mesosphere End_Group Group: Platform_Associated_Instruments Short_Name: SOFIE Short_Name: CIPS-AIM Short_Name: CDE End_Group Group: Orbit Orbit_Altitude: 600km Orbit_Inclination: 97.4° inclination Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-05-01 Online_Resource: http://www.nasa.gov/mission_pages/aim/index.html Online_Resource: http://aim.hamptonu.edu/ Online_Resource: http://explorers.gsfc.nasa.gov/ Sample_Image: http://www.nasa.gov/images/content/148220main_aim_banner.jpg Group: Platform_Logistics Launch_Date: 2007-04-25 Launch_Site: Vandenberg Air Force Base, USA Design_Life: 26 months Primary_Sponsor: NASA End_Group End_Group Argus Referred to as a “tow sled,” remotely operated vehicle (ROV) Argus typically operates in tandem with ROV Hercules, although it can also operate alone. Both vehicles are deployed from the Ocean Exploration Trust ’s Exploration Vessel (E/V) Nautilus . Argus “dangles” at the end of a steel-armored fiber-optic cable that is tethered to E/V Nautilus at the sea surface. Because Argus lacks a buoyancy module and is built of heavy stainless steel, its movements are controlled by moving the ship or raising and lowering the cable. A short 100-foot (30-meter) tether connects Hercules to Argus. By keeping the tether between Argus and Hercules slack, Argus can absorb the brunt of any ship movements, so that Hercules, the workhorse of the duo, can remain stable and collect high-definition video from the seafloor. Argus carries a high-definition video camera similar to the one on Hercules, as well as large lights that illuminate the area around Hercules. The overhead view from Argus allows the pilots and scientists to get a better of view Hercules' surroundings. Thrusters on Argus control its heading, so pilots “flying” the ROV while sitting in the control room on E/V Nautilus can aim the video cameras and lights toward Hercules and sites of interest. Although Hercules is depth rated to 2.5 miles (4,000 meters), when operating alone, Argus can dive deeper – down to 3.7 miles (6,000 meters). 2020-01-21 18:19:48.0 [tstevens] insert Definition (id: null text: Referred to as a “tow sled,” remotely operated vehicle (ROV) Argus typically operates in tandem with ROV Hercules, although it can also operate alone. Both vehicles are deployed from the Ocean Exploration Trust ’s Exploration Vessel (E/V) Nautilus . Argus “dangles” at the end of a steel-armored fiber-optic cable that is tethered to E/V Nautilus at the sea surface. Because Argus lacks a buoyancy module and is built of heavy stainless steel, its movements are controlled by moving the ship or raising and lowering the cable. A short 100-foot (30-meter) tether connects Hercules to Argus. By keeping the tether between Argus and Hercules slack, Argus can absorb the brunt of any ship movements, so that Hercules, the workhorse of the duo, can remain stable and collect high-definition video from the seafloor. Argus carries a high-definition video camera similar to the one on Hercules, as well as large lights that illuminate the area around Hercules. The overhead view from Argus allows the pilots and scientists to get a better of view Hercules' surroundings. Thrusters on Argus control its heading, so pilots “flying” the ROV while sitting in the control room on E/V Nautilus can aim the video cameras and lights toward Hercules and sites of interest. Although Hercules is depth rated to 2.5 miles (4,000 meters), when operating alone, Argus can dive deeper – down to 3.7 miles (6,000 meters). language code: en); 2020-01-21 17:27:29.0 [tstevens] Insert Concept add broader relation (Argus [ddc7ed71-2626-4b81-8079-82c04d0bdc91,559755] - ROV [da6420b6-48ec-4ae2-98c7-0ef0538815a0,542741]); NASA Earth System Science Pathfinder 2020-01-04 00:19:19.0 [sritz] Move Concepts add narrower relation (NASA Earth System Science Pathfinder [de1e0fd4-d865-4726-9bde-96804cf455b7,542765] - OCO-3 [da687fb4-016d-4b4d-92c2-380640ca5640,542743]); 2018-03-12 15:10:56.0 [sritz] Remove Concepts delete narrower relation (null); GMS (Japan Geostationary Meteorological Satellite) AEROS-2 The AEROS 2 satellite had a cylindrical shape, a diameter of 0.914 m, and a height of 0.710 m. It was launched into an elliptical, polar, nearly sun-synchronous earth orbit. The spacecraft was spin-stabilized at 10 rpm and oriented with the spin axis toward the sun. The purpose of the mission was to study the state and behavior of the upper atmosphere and ionospheric F region, especially with regard to the influence of the solar ultraviolet radiation. Five experiments provided data which included the temperature and density of electrons, ions, and neutral particles, the composition of ions and neutral particles, and solar ultraviolet flux. Group: Platform_Details Entry_ID: AEROS-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: AEROS Short_Name: AEROS-2 End_Group Group: Synonymous_Platform_Names Short_Name: AEROS-B Short_Name: 07371 End_Group Group: Platform_Associated_Instruments Short_Name: SPECTROMETERS End_Group Group: Orbit Orbit_Inclination: 97.4 degrees Period: 95.7 minutes Perigee: 217.0 km Apogee: 879.0 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-08-22 Online_Resource: http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1974-055A Sample_Image: http://library01.gsfc.nasa.gov/gdprojs/images/aeros-b.jpg Group: Platform_Logistics Launch_Date: 1974-07-16 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: NASA Primary_Sponsor: Germany End_Group End_Group Nimbus The Nimbus Technology satellite program was initiated by NASA in the early 1960's to develop an observational system capable of meeting the research and development needs of Earth scientists. The objectives of the program were to: develop advanced passive radiometric and spectrometric sensors for surveillance of the atmosphere and oceans; develop and evaluate new active and passive sensors for sounding the atmosphere and for mapping surface characteristics; develop advaced space technology and ground data processing techniques for meteorological and scientific research; and participate in global observation programs such as the World Weather Watch (WWW). Eight spacecraft were built, of which 7 were launched, with one failure, between 1964 and 1978. The Nimbus satellites were placed in polar orbits and acquired global data twice every 24 hours. ----------------- Entry taken from: Rao, P.K., S.J. Holmes, R.K. Anderson, J.S. Winston, and P.E. Lehr, Weather Satellites: Systems, Data, and Environmental Applications, American Meteorological Society, Boston, 1990. ISBN 0-933876-66-1 Group: Platform_Details Entry_ID: NIMBUS Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NIMBUS Short_Name: NIMBUS End_Group Group: Synonymous_Platform_Names Short_Name: NIMBUS End_Group Creation_Date: 2007-10-11 Online_Resource: http://nssdc.gsfc.nasa.gov/earth/nimbus.html Online_Resource: http://nasascience.nasa.gov/missions/nimbus Group: Platform_Logistics Primary_Sponsor: USA/NASA End_Group End_Group 2015-05-12 16:55:35.0 [saritz] update PrefLabel (Nimbus); IRS-O2 Indian Remote Sensing Satellite Oceansat-2 was launched by PSLV-C14 from Satish Dhawan Space Centre, Sriharikota on Sept. 23, 2009. It carries three payloads: 1) Ocean Colour Monitor (OCM) 2) Ku-band Pencil Beam scatterometer (OSCAT) 3) Radio Occultation Sounder for Atmosphere (ROSA) developed by the Italian Space Agency. Oceansat-2 is envisaged to provide continuity of operational services of Oceansat-1(IRS-P4) with enhanced application potential. Group: Platform_Details Entry_ID: IRS-O2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: IRS (Indian Remote Sensing Satellite) Short_Name: IRS-O2 Long_Name: Oceansat-2 End_Group Group: Synonymous_Platform_Names Short_Name: IRS-O2 End_Group Group: Platform_Associated_Instruments Short_Name: OCM-2 Short_Name: OSCAT Short_Name: ROSA End_Group Group: Orbit Orbit_Altitude: 720 km Orbit_Inclination: 98.28 deg Equator_Crossing: 12:00 Local time: e.g. Period: 99.31minutes Repeat_Cycle: 2 days Perigee: 720 km Apogee: 720 km Orbit_Type: LEO > LOW EARTH ORBIT > POLAR SUN-SYNCHRONOUS End_Group Creation_Date: 2007-10-05 Online_Resource: http://www.isro.gov.in/satellites/oceansat-2.aspx Sample_Image: http://www.isro.gov.in/satellites/images/irs1a_img.gif Group: Platform_Logistics Launch_Date: 2009-09-23 Launch_Site: SRIHARIKOTA ISLAND, INDIA Primary_Sponsor: India End_Group End_Group 2019-12-19 14:16:33.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: 6e24a235-4813-44dd-8be0-0c74e6898e15 relationship type: null relationship value: null generated by: null); 2019-02-22 13:27:04.0 [mmorahan] update Resource (image); insert WeightedRelation (id: null related concept uuid: 715bd84e-47a5-4da8-baf4-a283c46ccadf relationship type: null relationship value: null generated by: null); 2012-10-25 13:03:29.0 [mpmorahan] Insert Concept add broader relation (IRS-O2 [df967339-0096-4445-8732-0071f1de9e27,81983] - IRS (Indian Remote Sensing Satellite) [3e8bc0c6-f599-4e23-9535-449af00edd61,74275]); WORLDVIEW-3 2019-02-22 22:06:13.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: 001d8e8c-e9b1-4418-9941-f41321c2c500 relationship type: null relationship value: null generated by: null); 2017-03-02 21:12:21.0 [aaleman] Insert Concept add broader relation (WORLDVIEW-3 [dfb49f10-0755-464f-96b1-fc037802c86d,278669] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,256549]); ISIS (International Satellite for Ionospheric S SOLRAD-1 Orbiting Solar Observatory - 1 (OSO-1) Engineering Prototype The Orbiting Solar Observatory (OSO) series was the earliest of the spin stabilized scientific satellites. OSO-1 was launched on March 7, 1962 to study the sun in the ultraviolet, x-ray and gamma-ray regions of the spectrum. Sun sensors connected to servo-feedback systems on the upper "sail" portion were designed to keep the pointed instruments (75 pound payload) to within +/- 1 minute of arc on the center of the sun. The lower spinning portion carried some 100 pounds of instruments and rotated once every two seconds, allowing those instruments to scan the solar disk and atmosphere. The OSO had three protruding arms that extended after deployment which gave the system greater axial stability. Among many observations by the battery of instruments on OSO was that the sun's corona had openings, now called coronal holes, which were interpreted as huge fast-moving bubbles rising through the corona. Ball Aerospace Systems Division restored the OSO-I engineering prototype in 1982 af ter it was transferred from NASA in 1981. For additional information, link to "http://www.nasm.si.edu/nasm/dsh/artifacts/SS-OSO1.htm" [Summary provided by the Smithsonian, National Air and Space Museum] Group: Platform_Details Entry_ID: SOLRAD-1 Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Platform_Series_or_Entity: SOLRAD Short_Name: SOLRAD-1 Long_Name: Solar Radiation-1 End_Group Group: Synonymous_Platform_Names Short_Name: solrad-1 End_Group Creation_Date: 2007-01-14 Online_Resource: http://www.nasm.si.edu/nasm/dsh/artifacts/SS-OSO1.htm Sample_Image: http://www.weltraumforschung.de/Images/solrad1.jpg Group: Platform_Logistics Launch_Date: 1962-03-07 Primary_Sponsor: United States Department of Defense End_Group End_Group CESSNA 320 The Cessna 310/320 The sleek Cessna 310 was the first twin engine design from Cessna to enter production after WW2. The 310 first flew on January 3 1953. The modern rakish lines of the new twin were backed up by innovative features such as engine exhaust thrust augmentor tubes and the storage of all fuel in tip tanks. Deliveries commenced in late 1954. The first significant upgrade to the 310 line came with the 310C of 1959, which introduced more powerful 195kW (260hp) IO-470-D engines. The 310D of 1960 featured swept back vertical tail surfaces. An extra cabin window was added with the 310F. A development of the 310F was the turbocharged 320 Skyknight, with TSIO-470-B engines and a fourth cabin side-window. The Skyknight was in production between 1961 and 1969 (the 320D, E and F were named Executive Skyknight), when it was replaced by the similar Turbo 310. The 310G introduced the 'stabila-tip' tip tanks, while the 310K replaced the rear two windows on each side with a single unit. Subsequent significant developments include the 310Q and turbocharged T310Q with redesigned rear cabin with a skylight window, and the final 310R and T310R, identifiable for their lengthened noses. Production ended in 1980. USAF military versions were the L-27A (310A) and L-27B (310M) Blue Canoe, later redesignated U-3A and U-3B. [Text provided by: http://www.airliners.net/aircraft-data/stats.main?id=149 ] [Photo provided by: http://www.edcoatescollection.com ] Group: Platform_Details Entry_ID: CESSNA 320 Group: Platform_Identification Platform_Category: Aircraft Short_Name: CESSNA 320 End_Group Creation_Date: 2008-07-14 Online_Resource: http://en.wikipedia.org/wiki/Cessna_310 Online_Resource: http://www.cessna.com/ Sample_Image: http://www.edcoatescollection.com/ac3/Civil%20Planes/Cessna%20320%20Skynight.jpg End_Group Aquarius_SAC-D [Aquarius completed its primary three-year mission in November 2014] Mission Overview The Aquarius/SAC-D mission was developed collaboratively between NASA and Argentina's space agency, Comisión Nacional de Actividades Espaciales (CONAE) to best meet the goals of each agency while giving priority to salinity measurements. CONAE built complementary sensors to detect rain, sea ice, and wind speed, plus sea surface temperature sampling. CONAE-sponsored instruments — including sensors from the French Space Agency (Centre National d'Etudes Spatiales, CNES) and another from the Italian Space Agency (Agenzia Spaziale Italiana, ASI) — provide environmental data for a wide range of applications, including natural hazards, land processes, epidemiological studies, and air quality issues. Group: Platform_Details Entry_ID: AQUARIUS_SAC-D Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: AQUARIUS_SAC-D Long_Name: Aquarius SAC-D End_Group Group: Platform_Associated_Instruments Short_Name: AQUARIUS_RADIOMETER Short_Name: AQUARIUS_SCATTEROMETER End_Group Group: Orbit Orbit_Altitude: 657 Orbit_Inclination: 98 Equator_Crossing: 18:00 Local time: e.g. Period: 98 Repeat_Cycle: 7 Orbit_Type: LEO > LOW EARTH ORBIT > POLAR SUN-SYNCHRONOUS End_Group Creation_Date: 2013-04-01 Online_Resource: https://aquarius.nasa.gov/ Group: Platform_Logistics Launch_Date: 2011-06-10 Launch_Site: VANDENBERG AIR FORCE BASE, USA Design_Life: 3 years Primary_Sponsor: NASA Primary_Sponsor: CONAE End_Group End_Group 2020-01-29 21:35:34.0 [sritz] update Definition ([Aquarius completed its primary three-year mission in November 2014] Mission Overview The Aquarius/SAC-D mission was developed collaboratively between NASA and Argentina's space agency, Comisión Nacional de Actividades Espaciales (CONAE) to best meet the goals of each agency while giving priority to salinity measurements. CONAE built complementary sensors to detect rain, sea ice, and wind speed, plus sea surface temperature sampling. CONAE-sponsored instruments — including sensors from the French Space Agency (Centre National d'Etudes Spatiales, CNES) and another from the Italian Space Agency (Agenzia Spaziale Italiana, ASI) — provide environmental data for a wide range of applications, including natural hazards, land processes, epidemiological studies, and air quality issues. Group: Platform_Details Entry_ID: AQUARIUS_SAC-D Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: AQUARIUS_SAC-D Long_Name: Aquarius SAC-D End_Group Group: Platform_Associated_Instruments Short_Name: AQUARIUS_RADIOMETER Short_Name: AQUARIUS_SCATTEROMETER End_Group Group: Orbit Orbit_Altitude: 657 Orbit_Inclination: 98 Equator_Crossing: 18:00 Local time: e.g. Period: 98 Repeat_Cycle: 7 Orbit_Type: LEO > LOW EARTH ORBIT > POLAR SUN-SYNCHRONOUS End_Group Creation_Date: 2013-04-01 Online_Resource: https://aquarius.nasa.gov/ Group: Platform_Logistics Launch_Date: 2011-06-10 Launch_Site: VANDENBERG AIR FORCE BASE, USA Design_Life: 3 years Primary_Sponsor: NASA Primary_Sponsor: CONAE End_Group End_Group); 2018-04-24 20:20:01.0 [sritz] update PrefLabel (Aquarius_SAC-D); 2018-03-09 17:08:23.0 [sritz] update Definition (Mission Overview The Aquarius/SAC-D mission was developed collaboratively between NASA and Argentina's space agency, Comisión Nacional de Actividades Espaciales (CONAE) to best meet the goals of each agency while giving priority to salinity measurements. CONAE built complementary sensors to detect rain, sea ice, and wind speed, plus sea surface temperature sampling. CONAE-sponsored instruments — including sensors from the French Space Agency (Centre National d'Etudes Spatiales, CNES) and another from the Italian Space Agency (Agenzia Spaziale Italiana, ASI) — provide environmental data for a wide range of applications, including natural hazards, land processes, epidemiological studies, and air quality issues. Group: Platform_Details Entry_ID: AQUARIUS_SAC-D Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: AQUARIUS_SAC-D Long_Name: Aquarius SAC-D End_Group Group: Platform_Associated_Instruments Short_Name: AQUARIUS_RADIOMETER Short_Name: AQUARIUS_SCATTEROMETER End_Group Group: Orbit Orbit_Altitude: 657 Orbit_Inclination: 98 Equator_Crossing: 18:00 Local time: e.g. Period: 98 Repeat_Cycle: 7 Orbit_Type: LEO > LOW EARTH ORBIT > POLAR SUN-SYNCHRONOUS End_Group Creation_Date: 2013-04-01 Online_Resource: https://aquarius.nasa.gov/ Group: Platform_Logistics Launch_Date: 2011-06-10 Launch_Site: VANDENBERG AIR FORCE BASE, USA Design_Life: 3 years Primary_Sponsor: NASA Primary_Sponsor: CONAE End_Group End_Group); 2018-03-09 17:05:54.0 [sritz] update Definition (Mission Overview The joint U.S./Argentinian Aquarius/Satélite de Aplicaciones Científicas (SAC)-D mission will map the salinity—the concentration of dissolved salt—at the ocean surface, information critical to improving our understanding of two major components of Earth's climate system: the water cycle and ocean circulation. By measuring ocean salinity from space, Aquarius will provide new insights into how the massive natural exchange of freshwater between the ocean, atmosphere and sea ice influences ocean circulation, weather and climate. Because ocean surface salinity varies from place to place and over time, scientists can use it to trace the ocean's role in Earth's water cycle. For example, more than 85 percent of global evaporation and more than 75 percent of global precipitation occur over the ocean. By measuring changes in ocean surface salinity caused by these processes, as well as by ice melting and river runoff, Aquarius/SAC-D will provide important new information about how Earth's freshwater moves between the ocean and atmosphere and around the globe. Knowing ocean surface salinity can also help scientists track ocean currents and better understand ocean circulation. Salinity, together with temperature, determines how dense and buoyant seawater is. This, in turn, drives how ocean waters are layered and mixed and the formation of water masses. Salinity also has a major effect on ocean circulation, including the flow of currents that move heat from the tropics to the poles. Aquarius/SAC-D will provide essential ocean surface salinity data needed to link the water cycle and ocean circulation—two major components of the climate system. This information, in turn, will help scientists improve the accuracy of computer climate models. Global ocean salinity has been an area of much scientific uncertainty. Past measurements of salinity have been limited mostly to summertime observations in shipping lanes. Recently, a European mission has begun making ocean surface salinity measurements. With the launch of Aquarius/SAC-D, scientists will collect more data in the mission's first few months than had been amassed by ships and in-water sensors during the previous 125 years. Scheduled for launch no earlier than June 2011, Aquarius/SAC-D is designed to measure ocean surface salinity for at least three years, repeating its global pattern every seven days. During its lifetime, the mission will provide monthly maps of global changes in ocean surface salinity with a resolution of 150 kilometers (93 miles), showing how salinity changes from month-to-month, season-to-season and year-to-year. The spacecraft will fly in a sun-synchronous orbit 657 kilometers (408 miles) above Earth's surface. NASA's Aquarius is the primary instrument on the SAC-D spacecraft. It consists of three passive microwave radiometers to detect the surface emission that is used to obtain salinity and an active scatterometer to measure the ocean waves that affect the precision of the salinity measurement. While salinity levels in the open ocean generally range from 32 to 37 practical salinity units, or psu (roughly equivalent to parts per thousand), the Aquarius sensor will be able to detect changes in salinity as small as 0.2 psu. This is equivalent to about a "pinch" (i.e., 1/8 of a teaspoon) of salt in one gallon of water. Aquarius/SAC-D is a collaboration between NASA and Argentina's space agency, Comision Nacional de Actividades Espaciales (CONAE), with participation from Brazil, Canada, France and Italy. The Aquarius instrument was jointly built by NASA's Jet Propulsion Laboratory, Pasadena, Calif., and NASA's Goddard Space Flight Center, Greenbelt, Md. JPL will manage Aquarius through the mission's commissioning phase and will archive mission data. Goddard will manage the mission's operations phase and process Aquarius science data. NASA's Launch Services Program at the Kennedy Space Center in Florida is managing the launch. CONAE is providing the SAC-D spacecraft, an optical camera, a thermal camera in collaboration with Canada, a microwave radiometer, sensors developed by various Argentine institutions, and the mission operations center in Argentina. France and Italy are also contributing instruments. Group: Platform_Details Entry_ID: AQUARIUS_SAC-D Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: AQUARIUS_SAC-D Long_Name: Aquarius SAC-D End_Group Group: Platform_Associated_Instruments Short_Name: AQUARIUS_RADIOMETER Short_Name: AQUARIUS_SCATTEROMETER End_Group Group: Orbit Orbit_Altitude: 657 Orbit_Inclination: 98 Equator_Crossing: 18:00 Local time: e.g. Period: 98 Repeat_Cycle: 7 Orbit_Type: LEO > LOW EARTH ORBIT > POLAR SUN-SYNCHRONOUS End_Group Creation_Date: 2013-04-01 Online_Resource: https://aquarius.nasa.gov/ Group: Platform_Logistics Launch_Date: 2011-06-10 Launch_Site: VANDENBERG AIR FORCE BASE, USA Design_Life: 3 years Primary_Sponsor: NASA Primary_Sponsor: CONAE End_Group End_Group); delete Resource (null); 2013-03-28 19:31:33.0 [mpmorahan] Insert Concept add broader relation (AQUARIUS_SAC-D [e13d801e-19a3-4516-a64c-27f003b3d963,83227] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,73425]); R/V LOUIS S. ST. LAURENT 2012-06-29 20:40:35.0 [aaleman] Insert Concept add broader relation (R/V LOUIS S. ST. LAURENT [0d34806c-5288-4939-96e7-afdda39342fb,40293] - SHIPS [82a67b12-e99d-4c90-8a6a-a6f79d4c3c7b,31201]); LAGEOS-2 The LAGEOS satellites are passive vehicles covered with retroreflectors designed to reflect laser beams transmitted from ground stations. By measuring the time between transmission of the beam and reception of the reflected signal from the satellite, stations can precisely measure the distance between themselves and the satellite. These distances can be used to calculate station positions to within 1-3 cm. Long term data sets can be used to monitor the motion of the Earth's tectonic plates, measure the Earth's gravitational field, measure the "wobble" in the Earth's axis of rotation, and better determine the length of an Earth day. LAGEOS 2 was a joint program between NASA and the Italian space agency (ASI), which built the satellite using LAGEOS 1 drawings and specifications, handling fixtures, and other materials provided by NASA. LAGEOS 2's orbit was selected to provide more coverage of seismically active areas, such as the Mediterranean Basin and California, and may help scientists understand irregularities noted in the motion of LAGEOS 1. Ground tracking stations are located in many countries (including the US, Mexico, France, Germany, Poland, Australia, Egypt, China, Peru, Italy, and Japan) and data from these stations is available world-wide to investigators studying crustal dynamics. LAGEOS 1 also contains a message plaque addressed to human and other beings of the far distant future with maps of the Earth from 3 different eras - 268 million years in the past, present day, and 8 million years in the future (the satellite's estimated decay date). Spacecraft: Both satellites are spherical bodies with an aluminum shell wrapped around a brass core. The design was a compromise between numerous factors including the need to be as heavy as possible to minimise the effects of non-gravitational forces vs. being light enough to be placed in a high orbit and the need to accommodate as many retroreflectors as possible vs. the need to minimise surface area to minimise the effects of solar pressure. The materials were chosen to reduce the effects of the Earth's magnetic field on the satellite's orbit.426 cube-corner retroreflectors are imbedded in the satellites' surface.422 of these are made of fused silica glass while the other 4 are made of germanium. The vehicles have no onboard sensors or electronics, and are not attitude controlled. Payload: Science is performed by reflecting laser light from the vehicle's 426 retroreflectors. Additional characteristics: -50 years design life -0.6m total length -0.6m maximum diameter -405 kg total mass Additional information available at "http://www.astronautix.com/craft/lageos.htm" [Summary provided by SpaceBank.com] Group: Platform_Details Entry_ID: LAGEOS-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: LAGEOS (Laser Geodetic Satellite) Short_Name: LAGEOS-2 Long_Name: Laser Geodetic Satellite-2 End_Group Group: Synonymous_Platform_Names Short_Name: LAGEOS-2 End_Group Group: Platform_Associated_Instruments Short_Name: LASER TRACKING REFLECTOR End_Group Group: Orbit Orbit_Inclination: 52.70 deg Period: 222.50 min Perigee: 5,616 km Apogee: 5,952 km End_Group Creation_Date: 2007-10-10 Online_Resource: http://www.astronautix.com/craft/lageos.htm Online_Resource: http://ilrs.gsfc.nasa.gov/satellite_missions/list_of_satellites/lag1_general.html Online_Resource: http://nasascience.nasa.gov/missions/lageos-1-2 Sample_Image: http://msl.jpl.nasa.gov/QuickLooks/pictures/lageos.gif Group: Platform_Logistics Launch_Date: 1992-10-22 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Design_Life: 50 year Primary_Sponsor: USA/NASA End_Group End_Group R/V ITALIA 2012-07-30 19:46:27.0 [aaleman] Insert Concept add broader relation (R/V ITALIA [e2e59fcb-be11-4ff2-bd7f-eee34a76aa45,40429] - SHIPS [82a67b12-e99d-4c90-8a6a-a6f79d4c3c7b,31201]); Aeolus ADM-Aeolus The Earth Explorer Atmospheric Dynamics Mission Aeolus will provide global observations of wind profiles from space to improve the quality of weather forecasts, and to advance our understanding of atmospheric dynamics and climate processes. Although there are several ways of measuring wind from a satellite, Aeolus will utilise the active Doppler Wind Lidars (DWL) method. This is the only method that has the potential to provide the required data globally, from direct wind observations. In addition, a DWL will provide information on cloud top heights, vertical distribution of cloud, aerosol properties, and wind variability. This information is a useful by-product of the DWL method. An improved model of the Earth's climate and atmosphere will lead to progress in numerical weather prediction (NWP), especially concerning long-term forecasting. It is widely recognised that a new global atmospheric observing system, such as Aeolus, will have a great effect upon operational weather forecasting. The provision of detailed wind profiles will also benefit scientists involved with climate research, allowing for greater accuracy in the numerical modelling of tropical regions in particular. The Aeolus mission was launched on 22 August 2018. 2019-02-11 19:10:35.0 [mmorahan] update Definition (The Earth Explorer Atmospheric Dynamics Mission Aeolus will provide global observations of wind profiles from space to improve the quality of weather forecasts, and to advance our understanding of atmospheric dynamics and climate processes. Although there are several ways of measuring wind from a satellite, Aeolus will utilise the active Doppler Wind Lidars (DWL) method. This is the only method that has the potential to provide the required data globally, from direct wind observations. In addition, a DWL will provide information on cloud top heights, vertical distribution of cloud, aerosol properties, and wind variability. This information is a useful by-product of the DWL method. An improved model of the Earth's climate and atmosphere will lead to progress in numerical weather prediction (NWP), especially concerning long-term forecasting. It is widely recognised that a new global atmospheric observing system, such as Aeolus, will have a great effect upon operational weather forecasting. The provision of detailed wind profiles will also benefit scientists involved with climate research, allowing for greater accuracy in the numerical modelling of tropical regions in particular. The Aeolus mission was launched on 22 August 2018.); update Definition (https://earth.esa.int/web/guest/missions/esa-operational-eo-missions/aeolus); insert WeightedRelation (id: null related concept uuid: f94386e2-8e9b-4a95-9071-fb617a50cabb relationship type: null relationship value: null generated by: null); 2018-06-12 08:58:14.0 [mmorahan] insert AltLabel (id: null category: null text: ADM-Aeolus language code: en); insert Definition (id: null text: Set for launch in 2018, ADM-Aeolus (or just 'Aeolus'), is the fourth Earth Explorer mission to be developed within ESA's Living Planet Programme. Aeolus will be the first-ever satellite to directly observe wind profiles from space. Named after Aeolus, who in Greek mythology was appointed 'keeper of the winds' by the Gods, this mission will provide much-needed data to improve the quality of weather forecasts as well as contribute to long-term climate research. language code: en); 2018-06-12 08:47:45.0 [mmorahan] Insert Concept add broader relation (Aeolus [e31c4750-9903-4de7-95ef-faa9610f3a63,367659] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761]); GOES (Geostationary Operational Environmental Satellite) 2018-03-02 15:41:19.0 [tstevens] Insert Concept add narrower relation (GOES (Geostationary Operational Environmental Satellite) [e31e924e-9e50-4856-b85d-862ee3d084a4,288727] - GOES-17 [bec0b215-7fe0-46e8-855a-d1807779f004,310619]); FengYun-2 BUOYS MTSAT MTS-1 2016-06-09 15:35:20.0 [epneff] added altLabel insert AltLabel (id: null text: MTS-1 language code: en); 2016-03-21 20:44:04.0 [saritz] insert AltLabel (id: null text: Multi-functional Transport Satellite language code: en); 2016-03-21 20:43:23.0 [saritz] Insert Concept add broader relation (MTSAT [e3679e9e-5a95-46f4-a856-e51d459469fd,158711] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,143415]); CRYOSAT Europe's first ice mission is an advanced radar altimeter specifically designed to monitor the most dynamic sections of Earth's cryosphere. It borrows synthetic aperture radar and interferometry techniques from standard imaging radar missions to sharpen its accuracy over rugged ice sheet margins and sea ice in polar waters. CryoSat-2 measures 'freeboard' - the difference in height between sea ice and adjacent water - as well as ice sheet altitude, tracking changes in ice thickness. 2019-02-12 19:35:17.0 [mmorahan] update Definition (Europe's first ice mission is an advanced radar altimeter specifically designed to monitor the most dynamic sections of Earth's cryosphere. It borrows synthetic aperture radar and interferometry techniques from standard imaging radar missions to sharpen its accuracy over rugged ice sheet margins and sea ice in polar waters. CryoSat-2 measures 'freeboard' - the difference in height between sea ice and adjacent water - as well as ice sheet altitude, tracking changes in ice thickness.); update Definition (https://earth.esa.int/web/guest/missions/esa-operational-eo-missions/cryosat); insert Resource (id: null type: image url: https://earth.esa.int/image/image_gallery?img_id=17270); insert WeightedRelation (id: null related concept uuid: 30787b9f-a407-47a5-b69b-5b9e1d1b1144 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 9bfd9ff7-b838-4834-bd47-0127384c79f7 relationship type: null relationship value: null generated by: null); RRS DISCOVERY ALOS-2 The Advanced Land Observing Satellite-2 (ALOS-2) is follow-on mission from the "DAICHI", which contributed to cartography, regional observation, disaster monitoring, and resource surveys. ALOS-2 will succeed this mission with enhanced capabilities. Specifically, JAXA is conducting research and development activities to improve wide and high-resolution observation technologies developed for DAICHI in order to further fulfill social needs. These social needs include: 1) Disaster monitoring of damage areas, both in cosiderable detail, and when these areas may be large 2) Continuous updating of data archives related to national land and infrastructure information 3) Effective monitoring of cultivated areas 4) Global monitoring of tropical rain forests to identify carbon sinks. The state-of-the-art L-band Synthetic Aperture Radar (SAR) aboard ALOS-2, which is an active microwave radar using the 1.2GHz frequency range, will, in responding to society's needs, have enhanced performance compared to DAICHI/PALSAR. The SAR is capable of observing day and night, and in all weather conditions. The Advanced Land Observing Satellite-2 (ALOS-2) is follow-on mission from the "DAICHI", which contributed to cartography, regional observation, disaster monitoring, and resource surveys. ALOS-2 will succeed this mission with enhanced capabilities. Specifically, JAXA is conducting research and development activities to improve wide and high-resolution observation technologies developed for DAICHI in order to further fulfill social needs. These social needs include: 1) Disaster monitoring of damage areas, both in cosiderable detail, and when these areas may be large 2) Continuous updating of data archives related to national land and infrastructure information 3) Effective monitoring of cultivated areas 4) Global monitoring of tropical rain forests to identify carbon sinks. The state-of-the-art L-band Synthetic Aperture Radar (SAR) aboard ALOS-2, which is an active microwave radar using the 1.2GHz frequency range, will, in responding to society's needs, have enhanced performance compared to DAICHI/PALSAR. The SAR is capable of observing day and night, and in all weather conditions. Group: Platform_Details Entry_ID: ALOS-2 Group: Platform_Identification Platform_Category: EARTH OBSERVATION SATELLITES Short_Name: ALOS-2 Long_Name: ADVANCED LAND OBSERVING SATELLITE-2 End_Group Group: Platform_Associated_Instruments Short_Name: SAR End_Group Group: Orbit Orbit_Altitude: 628 Orbit_Inclination: 97.9 Period: 100 Repeat_Cycle: 14 Orbit_Type: LEO > LOW EARTH ORBIT > POLAR SUN-SYNCHRONOUS End_Group Creation_Date: 2011-10-14 Online_Resource: http://www.jaxa.jp/projects/sat/alos2/index_e.html Sample_Image: http://www.jaxa.jp/projects/sat/alos2/index_e.html Group: Platform_Logistics Launch_Date: 2013-01-24 Launch_Site: Tanegashima Island, Japan Design_Life: Jan. 2017 Primary_Sponsor: JAXA End_Group End_Group Himawari-9 41836 Himawari 9 is the second of two third-generation satellites in Japan’s Himawari weather-monitoring series. Alongside Himawari 8, which was launched in October 2014, it is expected to provide the Japan Meteorological Agency (JMA) and the Ministry of Transport with observational data into the late 2020s Facts in Brief Launch Date: 2016-11-02 Launch Vehicle: H-2A Launch Site: Tanegashima, Japan Mass: 1300.0 kg 2018-07-27 20:28:14.0 [sritz] update Definition (Himawari 9 is the second of two third-generation satellites in Japan’s Himawari weather-monitoring series. Alongside Himawari 8, which was launched in October 2014, it is expected to provide the Japan Meteorological Agency (JMA) and the Ministry of Transport with observational data into the late 2020s Facts in Brief Launch Date: 2016-11-02 Launch Vehicle: H-2A Launch Site: Tanegashima, Japan Mass: 1300.0 kg); 2018-07-27 20:27:30.0 [sritz] insert AltLabel (id: null category: null text: 41836 language code: en); 2018-07-27 20:26:46.0 [sritz] insert Definition (id: null text: Himawari 9 is the second of two third-generation satellites in Japan’s Himawari weather-monitoring series. Alongside Himawari 8, which was launched in October 2014, it is expected to provide the Japan Meteorological Agency (JMA) and the Ministry of Transport with observational data into the late 2020s language code: en); 2018-07-27 20:20:38.0 [sritz] Move Concepts delete broader relation (null); add broader relation (Himawari-9 [e43cfa6a-fb75-4eeb-8674-25917275ea7e,368003] - Himawari [d8b7fc7d-9cf3-4020-947d-f33d712b64ab,345895]); 2018-07-27 20:20:17.0 [sritz] Insert Concept add broader relation (Himawari-9 [e43cfa6a-fb75-4eeb-8674-25917275ea7e,368003] - Himawari-8 [dd2591d9-35a1-4037-9664-bbfcf4c80b71,345927]); In Situ Ocean-based Platforms Fixed and mobile ocean-based platforms. Group: Platform_Details Entry_ID: In Situ Ocean-based Platforms Group: Platform_Identification Platform_Category: In Situ Ocean-based Platforms Short_Name: In Situ Ocean-based Platforms End_Group End_Group 2020-01-21 17:30:18.0 [tstevens] Insert Concept add narrower relation (In Situ Ocean-based Platforms [e50b2a1a-7d9d-4c09-ac7e-dc29f0c08fc7,542811] - HOV [63c8aa1d-6efc-4943-8891-3a1cd520dde0,559759]); 2019-01-18 20:44:27.0 [sritz] Insert Concept add narrower relation (In Situ Ocean-based Platforms [e50b2a1a-7d9d-4c09-ac7e-dc29f0c08fc7,345973] - USV [bf17bbac-0fc9-48b3-9b03-bd780ffe1eb0,368431]); 2018-06-20 15:57:20.0 [tstevens] Insert Concept add narrower relation (In Situ Ocean-based Platforms [e50b2a1a-7d9d-4c09-ac7e-dc29f0c08fc7,345973] - MOUSS [e8299623-dad3-4773-b14a-39482873322f,367723]); 2015-08-20 16:52:25.0 [mpmorahan] Remove Concepts delete narrower relation (null); 2012-10-17 21:23:50.0 [aaleman] Remove Concepts delete narrower relation (null); 2012-08-07 19:42:14.0 [mpmorahan] Insert Concept add narrower relation (In Situ Ocean-based Platforms [e50b2a1a-7d9d-4c09-ac7e-dc29f0c08fc7,31421] - NDBC MOORED BUOY [92d903c9-147b-462e-8c21-68604bf19251,40475]); 2012-08-07 19:42:12.0 [mpmorahan] Insert Concept add narrower relation (In Situ Ocean-based Platforms [e50b2a1a-7d9d-4c09-ac7e-dc29f0c08fc7,31421] - NDBC MOORED BUOY [3d83b3e3-1be0-4ab8-9cf5-3b7ade27586e,40471]); DMC-2G (Disaster Monitoring Constellation- 2nd Generation) 2019-07-24 16:28:01.0 [mmorahan] Insert Concept add narrower relation (DMC-2G (Disaster Monitoring Constellation- 2nd Generation) [e5184d15-eec8-4703-8318-243748ddbd0e,368737] - UK-DMC-2 [03afbb23-76cc-4241-b5a3-853367f8461f,368969]); 2019-07-24 16:25:05.0 [mmorahan] Move Concepts add narrower relation (DMC-2G (Disaster Monitoring Constellation- 2nd Generation) [e5184d15-eec8-4703-8318-243748ddbd0e,368737] - Deimos-1 [8b35d386-0999-4b6e-ad12-f8501427b0ca,345361]); 2019-05-02 15:57:44.0 [mmorahan] Insert Concept add narrower relation (DMC-2G (Disaster Monitoring Constellation- 2nd Generation) [e5184d15-eec8-4703-8318-243748ddbd0e,368737] - NigeriaSat-X [35cafb99-393d-4727-a89d-5472512b2fdf,368745]); 2019-05-02 15:45:03.0 [mmorahan] Insert Concept add narrower relation (DMC-2G (Disaster Monitoring Constellation- 2nd Generation) [e5184d15-eec8-4703-8318-243748ddbd0e,368737] - NigeriaSat-2 [1dda5116-4079-445e-ae1c-614e49879cf3,368741]); 2019-05-02 15:43:20.0 [mmorahan] Rename Concept update PrefLabel (DMC-2G (Disaster Monitoring Constellation- 2nd Generation)); 2019-05-02 15:41:59.0 [mmorahan] Insert Concept add broader relation (DMC-2G [e5184d15-eec8-4703-8318-243748ddbd0e,368737] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761]); EXPLORER-33 AIMP-1 (also known as AIMP-D or IMP-D or Explorer 33, NSSDC ID: 66-058A) was launched into a lunar orbit in order to 'anchor' it to the lunar distance from the earth. AIMP-1 was a spin-stabilized spacecraft with spin axis parallel to the ecliptic plane, and spin period varying between 2.2 sec and 3.6 sec. The spacecraft was instrumented for studies of interplanetary plasma, energetic charged particles [electrons, protons and helium ions (alpha particles)], magnetic fields, and solar X-rays at lunar distances. Unfortunately, the spacecraft failed to achieve lunar orbit but did achieve major mission objectives. The initial AIMP-1 apogee occurred at about 16:00 hour local time. Over the first 3-year period, perigee varied between 6 earth radii and 44 earth radii and apogee varied between 70 earth radii and 135 earth radii. The inclination with respect to the equatorial plane of the earth varied between 7 degrees and 60 degrees. Group: Platform_Details Entry_ID: EXPLORER-33 Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Platform_Series_or_Entity: EXPLORER Short_Name: EXPLORER-33 Long_Name: Interplanetary Monitoring Platform D (IMP-D) End_Group Group: Synonymous_Platform_Names Short_Name: Explorer 33 Short_Name: AIMP-D Short_Name: IMP-D End_Group Group: Orbit Orbit_Inclination: 24.4 degrees Period: 3879 min Perigee: 2657 km Apogee: 4808 km End_Group Creation_Date: 2007-12-14 Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/masterCatalog.do?sc=1966-058A Sample_Image: http://nssdc.gsfc.nasa.gov/image/spacecraft/explorer33.jpg Group: Platform_Logistics Launch_Date: 1966-07-01 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: NASA End_Group End_Group OSTA-1 The STS-2 mission was planned as a five day mission, but was cut nearly three days due to the failure of one of three fuel cells that produce electricity and drinking water. However, 90 percent of the mission objectives were still achieved. The flight marked the first time a manned space vehicle had been reflown with a second crew: Commander Joseph Engle and Pilot Richard Truly. It again carried the Development Flight Instrumentation (DFI) package , which contained sensors and measuring devices to record orbiter performance and the stresses that occurred during launch, ascent, orbital flight, descent and landing. Also, onboard were the Office of Space and Terrestrial Applications-1 (OSTA-1) Earth observation experiments mounted on Spacelab pallet in payload bay. These instruments, including the Shuttle Imaging Radar-A (SIR-1), successfully carried out remote sensing of Earth resources, environmental quality, ocean and weather conditions. In addition, the Canadian-built Remote Manipulator System (RMS), a mechanical robot arm located in the payload bay of the Shuttle, was successfully operated for the first time. Additional information available at "http://history.nasa.gov/NP-119/ch1.htm" [Summary provided by NASA] OGO (Orbiting Geophysical Observatory) OSO-8 The objectives of the OSO satellite series were to perform solar physics experiments above the atmosphere during a complete solar cycle and to map the celestial sphere for direction and intensity of UV light, X-rays, and gamma radiation. General Information: Designation: 07970 / 75057A Launch date: 21 Jun 1975 Country of origin: United States Mission: Scientific (Sun observation) Perigee/Apogee: 539/553 km Inclination: 32.9° Period: 95.6 min Launch vehicle: Thor Delta #112 Mass at launch: 1064 kg Out of service: Sep 1978 Decay: 9 Jul 1986 Additional information available at "http://heasarc.gsfc.nasa.gov/docs/oso8/oso8.html" [Summary provided by The Satellite Encyclopedia] Group: Platform_Details Entry_ID: OSO-8 Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Platform_Series_or_Entity: OSO (Orbiting Solar Observatory) Short_Name: OSO-8 Long_Name: Orbiting Solar Observatory-8 End_Group Group: Synonymous_Platform_Names Short_Name: OSO-8 End_Group Group: Platform_Associated_Instruments Short_Name: GAMMA RADIATION DETECTOR End_Group Group: Orbit Orbit_Inclination: 32.9 degrees Period: 95.6 min Perigee: 539 km Apogee: 553 km End_Group Creation_Date: 2007-12-14 Online_Resource: http://heasarc.gsfc.nasa.gov/docs/oso8/oso8.html Sample_Image: http://heasarc.gsfc.nasa.gov/Images/oso/oso8_2.gif Group: Platform_Logistics Launch_Date: 1975-06-21 Primary_Sponsor: NASA End_Group End_Group RQ-4 2015-12-24 17:55:28.0 [aaleman] added new platform for NSIDC insert AltLabel (id: null text: Northrop Grumman RQ-4 Global Hawk language code: en); 2015-12-24 17:54:53.0 [aaleman] Insert Concept add broader relation (RQ-4 [e5aedd55-cce6-417c-97c0-595448406ad5,158567] - Aircraft [227d9c3d-f631-402d-84ed-b8c5a562fc27,143335]); TOPEX/POSEIDON TOPEX/Poseidon was an oceanography mission to monitor global ocean circulation, improve global climate predictions, and monitor events such as El Niño and ocean eddies. These data have greatly enhanced our understanding of the role of the ocean in the formation of Earth?s weather and climate. Key TOPEX/Poseidon Facts Joint with France Mass: 2388 kg Power: 3,385 W Operating Life: Over 13 years, until October 9, 2005 Group: Platform_Details Entry_ID: TOPEX/POSEIDON Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: TOPEX/POSEIDON Long_Name: Topography Experiment/Poseidon End_Group Group: Platform_Associated_Instruments Short_Name: SSALT Short_Name: TMR Short_Name: LRA Short_Name: DORIS Short_Name: NRA Short_Name: TRSR End_Group Group: Orbit Orbit_Altitude: 1336 km Orbit_Inclination: 66 degrees Period: 112.4 minutes Repeat_Cycle: 10 days Perigee: 1,331 km (827 mi) Apogee: 1,344 km (835 mi) Orbit_Type: LEO > Low Earth Orbit > Polar Non-Sun-Synchronous End_Group Creation_Date: 2007-04-16 Online_Resource: http://sealevel.jpl.nasa.gov/mission/topex.html Online_Resource: http://science.hq.nasa.gov/missions/satellite_14.htm Online_Resource: http://topex-www.jpl.nasa.gov/ Sample_Image: http://sealevel.jpl.nasa.gov/gallery/spacecraft/gifs/BHT.jpg Group: Platform_Logistics Launch_Date: 1992-08-10 Launch_Site: KOUROU, FRENCH GUIANA Design_Life: 5 years Primary_Sponsor: NASA Primary_Sponsor: CNES End_Group End_Group GPS The Global Positioning System (GPS) Satellite is a system of satellites developed by the US Department of Defense to provide all-weather round-the-clock navigation capabilities for military ground, sea, and air forces. Since its implementation, GPS has also become an integral asset in numerous civilian applications and industries around the globe, including recreational uses (e.g. boating, aircraft, hiking), corporate vehicle fleet tracking, and surveying. GPS employs 24 spacecraft in 20,200 km circular orbits inclined at 55 degrees. These spacecraft are placed in 6 orbit planes with four operational satellites in each plane. All launches have been successful except for one launch failure in 1981. The full 24-satellite constellation was completed on March 9, 1994. GPS receivers use triangulation of the GPS satellites' navigational signals to determine their location. The satellites provide two different signals that provide different accuracies. Coarse-acquisition (C/A) code is intended for civilian use, and is deliberately degraded. The accuracy using a typical civilian GPS receiver with C/A code is typically about 100 meters. The military's Precision (P) code is not corrupted, and provides positional accuracy to within approximately 20 meters. Group: Platform_Details Entry_ID: GPS Group: Platform_Identification Platform_Category: Navigation Platforms Platform_Series_or_Entity: GPS (Global Positioning System) Short_Name: GPS Long_Name: Global Positioning System Satellites End_Group Group: Synonymous_Platform_Names Short_Name: Navstar Short_Name: USA End_Group Group: Platform_Associated_Instruments Short_Name: GPS Short_Name: GPS RECEIVERS End_Group Group: Orbit Orbit_Altitude: 20,200 km Orbit_Type: MEO > Semi-Synchronous > Navigation End_Group Creation_Date: 2007-02-12 Group: Platform_Logistics Primary_Sponsor: U.S. Department of Defense End_Group End_Group 2017-08-15 14:02:05.0 [tstevens] update Definition (The Global Positioning System (GPS) Satellite is a system of satellites developed by the US Department of Defense to provide all-weather round-the-clock navigation capabilities for military ground, sea, and air forces. Since its implementation, GPS has also become an integral asset in numerous civilian applications and industries around the globe, including recreational uses (e.g. boating, aircraft, hiking), corporate vehicle fleet tracking, and surveying. GPS employs 24 spacecraft in 20,200 km circular orbits inclined at 55 degrees. These spacecraft are placed in 6 orbit planes with four operational satellites in each plane. All launches have been successful except for one launch failure in 1981. The full 24-satellite constellation was completed on March 9, 1994. GPS receivers use triangulation of the GPS satellites' navigational signals to determine their location. The satellites provide two different signals that provide different accuracies. Coarse-acquisition (C/A) code is intended for civilian use, and is deliberately degraded. The accuracy using a typical civilian GPS receiver with C/A code is typically about 100 meters. The military's Precision (P) code is not corrupted, and provides positional accuracy to within approximately 20 meters. Group: Platform_Details Entry_ID: GPS Group: Platform_Identification Platform_Category: Navigation Platforms Platform_Series_or_Entity: GPS (Global Positioning System) Short_Name: GPS Long_Name: Global Positioning System Satellites End_Group Group: Synonymous_Platform_Names Short_Name: Navstar Short_Name: USA End_Group Group: Platform_Associated_Instruments Short_Name: GPS Short_Name: GPS RECEIVERS End_Group Group: Orbit Orbit_Altitude: 20,200 km Orbit_Type: MEO > Semi-Synchronous > Navigation End_Group Creation_Date: 2007-02-12 Group: Platform_Logistics Primary_Sponsor: U.S. Department of Defense End_Group End_Group); update Definition (https://www.nasa.gov/directorates/heo/scan/communications/policy/GPS.html); update Resource (image); R/V ARAON 2012-06-29 20:26:43.0 [aaleman] Insert Concept add broader relation (R/V ARAON [b86ba8f3-1d11-4603-8d5a-5633be4529c8,40285] - SHIPS [82a67b12-e99d-4c90-8a6a-a6f79d4c3c7b,31201]); RADIO TRANSMITTERS Radio transmitters: The wireless transmission through space of electromagnetic waves in the approximate frequency range from 10 kilohertz to 300,000 megahertz which results in meaningful signal derived from speech or other sources. [Source: The American Heritage? Dictionary of the English Language, Fourth Edition Copyright ? 2000 by Houghton Mifflin Company.] STS-43 Atlantis will put NASA's fourth Tracking and Data Relay Satellite (TDRS-E) into orbit on Space Shuttle mission STS-43 to update the satellite tracking network, resulting in two operating satellites plus a complement of two spares in the space network. TDRS-E, to be deployed from Atlantis about 6 hours after launch, will be boosted to a geosynchronous orbit by an attached upper stage where TDRS-E will be positioned to remain stationary 22,400 miles above the Pacific Ocean southwest of Hawaii. The Tracking and Data Relay Satellite System, in operation since the eighth Space Shuttle flight, provides almost uninterrupted communications with Earth-orbiting shuttles and satellites and has replaced the intermittent coverage provided by globe-encircling ground tracking stations used during the early space program. A reduced string of ground stations remains in operation, however, for radar tracking and backup communications. [Summary provided by NASA] Group: Platform_Details Entry_ID: STS-43 Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Platform_Series_or_Entity: SPACE SHUTTLE Short_Name: STS-43 Long_Name: Space Transport System STS-43 End_Group Group: Synonymous_Platform_Names Short_Name: Atlantis (9) End_Group Group: Orbit Orbit_Altitude: 174nm Orbit_Inclination: 28.45 degrees End_Group Creation_Date: 2008-01-29 Online_Resource: http://science.ksc.nasa.gov/shuttle/missions/sts-43/mission-sts-43.html Sample_Image: http://www.nasa.gov/images/content/134436main_sts-43-crew-sm.jpg Group: Platform_Logistics Launch_Date: 1991-08-02 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: NASA End_Group End_Group REANALYSIS MODELS 2015-08-10 14:41:43.0 [gee-cee] Insert Concept add broader relation (REANALYSIS MODELS [e804fb28-786b-460f-969c-7005b0803cde,158201] - Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215]); MOUSS A drop platform that holds cameras. 2018-06-20 15:58:24.0 [tstevens] insert AltLabel (id: null category: primary text: MOdular Underwater Sampling System language code: en); insert Definition (id: null text: A drop platform that holds cameras. language code: en); 2018-06-20 15:57:20.0 [tstevens] Insert Concept add broader relation (MOUSS [e8299623-dad3-4773-b14a-39482873322f,367723] - In Situ Ocean-based Platforms [e50b2a1a-7d9d-4c09-ac7e-dc29f0c08fc7,345973]); NOAA POES (Polar Orbiting Environmental Satellites) 2017-11-27 17:19:09.0 [sritz] Move Concepts delete narrower relation (null); 2017-11-27 16:46:53.0 [sritz] Move Concepts add narrower relation (NOAA POES (Polar Orbiting Environmental Satellites) [e8baa3a4-ef5a-455a-bf25-d61e59fc9bb3,288767] - JPSS-1 [586db0b3-5f94-466e-b7c1-a2dbedc0c1fc,287835]); GOES-7 GOES 7 was launched in February 1987 and was a NASA-developed, NOAA-operated, geosynchronous, and operational spacecraft. The cylindrically shaped spacecraft measured 190.5 cm in diameter and 230 cm in length, exclusive of a magnetometer that extended an additional 83 cm beyond the cylinder shell. The primary structural members were a honeycombed equipment shelf and thrust tube. The VISSR telescope was mounted on the equipment shelf and viewed the Earth through a special aperture in the side of the spacecraft. A support structure extended radially out from the thrust tube and was affixed to the solar panels, which formed the outer walls of the spacecraft and provided the primary source of electrical power. Located in the annulus-shaped space between the thrust tube and the solar panels were stationkeeping and dynamics control equipment, batteries, and most of the SEM equipment. Proper spacecraft attitude and spin rate (approximately 100 rpm) were maintained by two separate sets of jet thrusters mounted around the spacecraft equator and activated by ground command. The spacecraft used both UHF-band and S-band frequencies in its telemetry and command subsystem. A low-power VHF transponder provided telemetry and command during launch and then served as a backup for the primary subsystem once the spacecraft attained orbit. The spin-stabilized spacecraft carried a visible infrared spin-scan radiometer atmospheric sounder, meteorological data collection and transmission system, space environment monitor, energetic particle monitor, and a magnetic field monitor. GOES 7 was positioned at 98 degrees West in the summer (Atlantic hurricane season) and 108 degrees West in the winter (Pacific storm season). For more information on GOES satellites: http://www.ospo.noaa.gov/Operations/GOES/index.html 2017-09-01 17:07:34.0 [sritz] insert Definition (id: null text: GOES 7 was launched in February 1987 and was a NASA-developed, NOAA-operated, geosynchronous, and operational spacecraft. The cylindrically shaped spacecraft measured 190.5 cm in diameter and 230 cm in length, exclusive of a magnetometer that extended an additional 83 cm beyond the cylinder shell. The primary structural members were a honeycombed equipment shelf and thrust tube. The VISSR telescope was mounted on the equipment shelf and viewed the Earth through a special aperture in the side of the spacecraft. A support structure extended radially out from the thrust tube and was affixed to the solar panels, which formed the outer walls of the spacecraft and provided the primary source of electrical power. Located in the annulus-shaped space between the thrust tube and the solar panels were stationkeeping and dynamics control equipment, batteries, and most of the SEM equipment. Proper spacecraft attitude and spin rate (approximately 100 rpm) were maintained by two separate sets of jet thrusters mounted around the spacecraft equator and activated by ground command. The spacecraft used both UHF-band and S-band frequencies in its telemetry and command subsystem. A low-power VHF transponder provided telemetry and command during launch and then served as a backup for the primary subsystem once the spacecraft attained orbit. The spin-stabilized spacecraft carried a visible infrared spin-scan radiometer atmospheric sounder, meteorological data collection and transmission system, space environment monitor, energetic particle monitor, and a magnetic field monitor. GOES 7 was positioned at 98 degrees West in the summer (Atlantic hurricane season) and 108 degrees West in the winter (Pacific storm season). For more information on GOES satellites: http://www.ospo.noaa.gov/Operations/GOES/index.html language code: en); 2017-09-01 16:45:49.0 [sritz] Insert Concept add broader relation (GOES-7 [e8fbbfce-0ba2-431c-8533-a1ec9347efd1,310099] - GOES [6e332c25-caeb-4917-afb6-af757bcecd72,310071]); TMRS2 The Tower Mounted Radiometer System (TMRS2) was a ground-based SSM/I simulator and surface energy balance monitoring system. The primary application of TMRS2 were to collect long-term (months) time-series data sets at sites representative of various biomes in support of land surface process modeling and remote sensing research. The system was also used in support of studies in the passive remote sensing of soil moisture, frozen/thawed soil state determination, permafrost, and snow. List of TMRS2 Instruments: TMRS2 was composed of a Radiometer Subsystem, a Micro-Meteorological Subsystem (MMS), and a Control and Data Management Subsystem (CDMS). Micro-Meteorological Instruments: 10 meter anemometer 2 meter anemometer and wind vane 2 m Air temperature and relative humidity Bowen Ratio Downwelling shortwave hemispherical flux Upwelling shortwave hemispherical flux Net radiometer w/aspirator Rain gage Rain gage wind screen TDR Soil moisture (10 probes Subsurface temperature (12 probes) Snowpack temperature (12 probes) Snowpack depth Subsurface heat flux (3 disks) CDMS Componets: Data logger and controller (hardware) Data logger and controller (hardware) Microwave/IR Radiometers: 19.35 GHz V & H polarizations 37.0 GHz V & H polarizations 85.5 GHz V or H polarization thermal IR radiometer Other Instruments: Video camera More information available at "http://www.eecs.umich.edu/grs/projects/tmrs2/" [Source: University of Michigan, College of Engineering] Group: Platform_Details Entry_ID: TMRS2 Group: Platform_Identification Platform_Category: In Situ Land-based Platforms Platform_Series_or_Entity: WEATHER STATIONS/NETWORKS Short_Name: TMRS2 Long_Name: Tower Mounted Radiometer System 2 End_Group Group: Synonymous_Platform_Names Short_Name: TMRS2 End_Group Group: Platform_Associated_Instruments Short_Name: RAIN GAUGES Short_Name: SNOWPACK TEMPERATURE PROBE Short_Name: ANEMOMETERS End_Group Creation_Date: 2007-12-12 Online_Resource: http://www.eecs.umich.edu/grs/tmrs.htm Sample_Image: http://www.eecs.umich.edu/grs/images/tmrs_one.jpg End_Group GOES-15 [Update 2011-12-13: GOES-15 replaced GOES-11 as the GOES-West operational spacecraft on 2011-12-06, Source: http://noaasis.noaa.gov/NOAASIS/ml/status.html ] [Source: NASA GOES Mission Overview, http://www.nasa.gov/mission_pages/GOES-P/overview/index.html ] The Geostationary Operational Environmental Satellite (GOES)-P represents a continuation of the newest generation of environmental satellites built by Boeing for the National Oceanic and Atmospheric Administration (NOAA) under the technical guidance and project management of NASA's Goddard Space Flight Center, Greenbelt, Md. GOES satellites provide the familiar weather pictures seen on United States television newscasts every day. The GOES imaging and sounding instruments (built by ITT) feature flexible scans for small-scale area viewing in regions of the visible and infrared spectrum allowing meteorologists to improve short-term forecasts. GOES provides nearly continuous imaging and sounding, which allow forecasters to better measure changes in atmospheric temperature and moisture distributions and hence increase the accuracy of their forecasts. GOES environmental information is used for a host of applications, including weather monitoring and prediction models, ocean temperatures and moisture locations, climate studies, cryosphere (ice, snow, glaciers) detection and extent, land temperatures and crop conditions, and hazards detection. The GOES-O&P Imagers have improved resolution in the 13 micrometer channel from 8 km to 4 km. The finer spatial resolution allows an improved cloud-top product, height of atmospheric motion vectors and volcanic ash detection. GOES-P continues the improved image navigation and registration, additional power and fuel lifetime capability, space weather, solar x-ray imaging, search and rescue, and communication services as provided on GOES-13. GOES-P Launches! The GOES-P satellite launched at 6:57 p.m. EST March 4 aboard a United Launch Alliance Delta IV rocket from Launch Complex 37B at Cape Canaveral Air Force Station in Florida. GOES-P is the third and final spacecraft to be launched in the GOES-N series of geostationary environmental weather satellites. Group: Platform_Details Entry_ID: GOES-15 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: GOES (Geostationary Operational Environmental Satellite) Short_Name: GOES-15 Long_Name: Geostationary Operational Environmental Satellite 15 End_Group Group: Synonymous_Platform_Names Short_Name: GOES-P Short_Name: 36411 End_Group Group: Platform_Associated_Instruments Short_Name: GOES N-P SOUNDER Short_Name: GOES N-P IMAGER End_Group Group: Orbit Period: 24 hours Orbit_Type: GEO > GEOSYNCHRONOUS > GEOSTATIONARY End_Group Creation_Date: 2010-02-24 Online_Resource: http://goespoes.gsfc.nasa.gov/goes/spacecraft/n_p_spacecraft.html Online_Resource: http://goes.gsfc.nasa.gov/text/goespstatus.html Online_Resource: http://www.nasa.gov/mission_pages/GOES-P/news/goes-15-active.html Online_Resource: http://www.nasa.gov/mission_pages/GOES-P/main/ Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=2010-008A Sample_Image: http://www.nasa.gov/centers/kennedy/images/content/417581main_2010-1220_1600_946-710.jpg Group: Platform_Logistics Launch_Date: 2010-03-04 Launch_Site: CAPE CANAVERAL/KENNEDY SPACE CENTER, USA Primary_Sponsor: USA/NASA Primary_Sponsor: USA/NOAA End_Group End_Group LANDMET 2016-12-07 18:56:19.0 [sritz] insert AltLabel (id: null text: CCNY NOAA-CREST Land Surface Atmospheric Boundary Processing Method language code: en); 2016-12-07 14:47:29.0 [sritz] Insert Concept add broader relation (LANDMET [e951dc1d-eeb5-4d67-ad77-e60ee469486c,278537] - Merged Analysis [6acce314-322f-4d58-9dcb-1f93457a9d86,278533]); SkySat The SkySat constellation is the Very High Resolution component of Planet's satellite image portfolio. Skysat-A and B generation satellites were launched in 2013/14. The SkySat-C generation satellite is a high-resolution Earth imaging satellite, first launched in 2016. Eleven are currently in orbit, all collecting thousands of square kilometres of imagery. Each satellite is 3-axis stabilised and agile enough to slew between different targets of interest. Each satellite has four thrusters for orbital control, along with four reaction wheels and three magnetic torquers for attitude control. 2019-05-06 11:54:08.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: bd5a9e8c-72db-4244-9455-53b0f19950b4 relationship type: null relationship value: null generated by: null); 2019-05-02 19:30:50.0 [mmorahan] insert Definition (id: null text: The SkySat constellation is the Very High Resolution component of Planet's satellite image portfolio. Skysat-A and B generation satellites were launched in 2013/14. The SkySat-C generation satellite is a high-resolution Earth imaging satellite, first launched in 2016. Eleven are currently in orbit, all collecting thousands of square kilometres of imagery. Each satellite is 3-axis stabilised and agile enough to slew between different targets of interest. Each satellite has four thrusters for orbital control, along with four reaction wheels and three magnetic torquers for attitude control. language code: en); 2019-05-02 19:26:59.0 [mmorahan] Insert Concept add broader relation (SkySat [e9611632-822d-468b-9748-a392991a0718,368753] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761]); G-II The Rolls-Royce Dart turboprop powered Grumman Gulfstream I proved to be quite successful as a large long range corporate transport, while the availability of an faster and more powerful turbojet powered model, the Rolls-Royce Spey meant that a jet powered successor was a logical development. Grumman launched such an aircraft, named the Gulfstream II or G-II, in May 1965. [Text and Photo provided by Airliner.net: http://www.airliners.net/aircraft-data/stats.main?id=237 ] Group: Platform_Details Entry_ID: GULFSTREAM II Group: Platform_Identification Platform_Category: Aircraft Short_Name: GULFSTREAM II End_Group Creation_Date: 2008-07-14 Online_Resource: http://en.wikipedia.org/wiki/Grumman_Gulfstream_II Online_Resource: http://www.gulfstream.com/ Sample_Image: http://cdn-www.airliners.net/aviation-photos/middle/9/8/2/0254289.jpg End_Group 2014-07-02 15:10:13.0 [aaleman] fixed typo update PrefLabel (G-II); 2014-07-02 15:08:50.0 [aaleman] edited keyword at NSIDC request insert AltLabel (id: null text: GULFSTREAM II language code: en); update PrefLabel (G-2); TRAVERSE SAC 2013-08-14 18:13:24.0 [aaleman] Insert Concept add narrower relation (SAC [ea7e0cb4-5764-4ca4-89f6-913b22a47eff,74071] - SAC-D [fb9164bb-4dba-4598-ba56-cb24d8db5527,105723]); Aqua AQUA (AFTERNOON EQUATORIAL CROSSING TIME SATELLITE) Aqua is a major international Earth Science satellite mission centered at NASA. Launched on May 4, 2002, the satellite has six different Earth-observing instruments on board and is named for the large amount of information being obtained about water in the Earth system from its stream of approximately 89 Gigabytes of data a day. The water variables being measured include almost all elements of the water cycle and involve water in its liquid, solid, and vapor forms. Additional variables being measured include radiative energy fluxes, aerosols, vegetation cover on the land, phytoplankton and dissolved organic matter in the oceans, and air, land, and water temperatures. Key Aqua Facts Joint with Brazil and Japan Dimensions: 2.7 m x 2.5 m x 6.5 m stowed; 4.8 m x 16.7 m x 8.0 m deployed Mass: 2,934 kg (1,750 kg spacecraft, 1,082 kg instruments, 102 kg propellants) Power: 4,600 W silicon cell array and a NiH2 battery Average Data Rate: 89 Gbytes/day Data Storage: 136-Gbit solid state recorder (SSR) for storage of up to two orbits of data Data Relay Methods: Direct downlink from the SSR to polar ground stations; direct broadcast Data Links: X-band Telemetry: S-band Group: Platform_Details Entry_ID: AQUA Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: EOS (Earth Observing System) Short_Name: AQUA Long_Name: Earth Observing System, AQUA End_Group Group: Platform_Associated_Instruments Short_Name: CERES-FM4 Short_Name: CERES-FM3 Short_Name: AIRS Short_Name: AMSR-E Short_Name: AMSU-A Short_Name: HSB Short_Name: MODIS End_Group Group: Orbit Orbit_Altitude: 705 km Orbit_Inclination: 98.2 degrees Equator_Crossing: 1:30 p.m. (south to north) and 1:30 a.m. (north to south) Period: 98.8 minutes Repeat_Cycle: 16 days (233 revolutions) Perigee: 699 km (434 mi) Apogee: 706 km (438 mi) Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-04-16 Online_Resource: https://aqua.nasa.gov/ Online_Resource: https://www.nasa.gov/mission_pages/aqua/ Sample_Image: https://gcmd.gsfc.nasa.gov/KeywordSearch/default/images/aqua.gif Group: Platform_Logistics Launch_Date: 2002-05-04 Launch_Site: Vandenberg Air Force Base, USA Design_Life: 6 years Primary_Sponsor: USA/NASA Primary_Sponsor: BRAZIL/INPE Primary_Sponsor: JAPAN/JAXA End_Group End_Group 2018-04-26 01:22:27.0 [sritz] update AltLabel (Earth Observing System, Aqua); 2018-04-05 19:29:33.0 [sritz] insert AltLabel (id: null category: outdated text: AQUA language code: en); update PrefLabel (Aqua); 2018-03-09 17:01:42.0 [sritz] insert Resource (id: null type: provider url: https://aqua.nasa.gov/); 2018-03-09 17:00:57.0 [sritz] update Definition (Aqua is a major international Earth Science satellite mission centered at NASA. Launched on May 4, 2002, the satellite has six different Earth-observing instruments on board and is named for the large amount of information being obtained about water in the Earth system from its stream of approximately 89 Gigabytes of data a day. The water variables being measured include almost all elements of the water cycle and involve water in its liquid, solid, and vapor forms. Additional variables being measured include radiative energy fluxes, aerosols, vegetation cover on the land, phytoplankton and dissolved organic matter in the oceans, and air, land, and water temperatures. Key Aqua Facts Joint with Brazil and Japan Dimensions: 2.7 m x 2.5 m x 6.5 m stowed; 4.8 m x 16.7 m x 8.0 m deployed Mass: 2,934 kg (1,750 kg spacecraft, 1,082 kg instruments, 102 kg propellants) Power: 4,600 W silicon cell array and a NiH2 battery Average Data Rate: 89 Gbytes/day Data Storage: 136-Gbit solid state recorder (SSR) for storage of up to two orbits of data Data Relay Methods: Direct downlink from the SSR to polar ground stations; direct broadcast Data Links: X-band Telemetry: S-band Group: Platform_Details Entry_ID: AQUA Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: EOS (Earth Observing System) Short_Name: AQUA Long_Name: Earth Observing System, AQUA End_Group Group: Platform_Associated_Instruments Short_Name: CERES-FM4 Short_Name: CERES-FM3 Short_Name: AIRS Short_Name: AMSR-E Short_Name: AMSU-A Short_Name: HSB Short_Name: MODIS End_Group Group: Orbit Orbit_Altitude: 705 km Orbit_Inclination: 98.2 degrees Equator_Crossing: 1:30 p.m. (south to north) and 1:30 a.m. (north to south) Period: 98.8 minutes Repeat_Cycle: 16 days (233 revolutions) Perigee: 699 km (434 mi) Apogee: 706 km (438 mi) Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-04-16 Online_Resource: https://aqua.nasa.gov/ Online_Resource: https://www.nasa.gov/mission_pages/aqua/ Sample_Image: https://gcmd.gsfc.nasa.gov/KeywordSearch/default/images/aqua.gif Group: Platform_Logistics Launch_Date: 2002-05-04 Launch_Site: Vandenberg Air Force Base, USA Design_Life: 6 years Primary_Sponsor: USA/NASA Primary_Sponsor: BRAZIL/INPE Primary_Sponsor: JAPAN/JAXA End_Group End_Group); update Resource (image); 2016-10-13 20:33:23.0 [saritz] update AltLabel (Aqua); update PrefLabel (AQUA); 2016-09-13 21:44:26.0 [saritz] update AltLabel (AQUA); update PrefLabel (Aqua); 2016-06-09 19:12:32.0 [epneff] added altLabel insert AltLabel (id: null text: Aqua language code: en); 2016-06-09 14:29:31.0 [epneff] added altLabel insert AltLabel (id: null text: AQUA (AFTERNOON EQUATORIAL CROSSING TIME SATELLITE) language code: en); GOES-4 [Source: NASA NSSDC, http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1980-074A ] GOES 4 was launched in September 1980 and was a NASA-developed, NOAA-operated, geosynchronous, and operational spacecraft. The cylindrically shaped spacecraft measured 190.5 cm in diameter and 230 cm in length, exclusive of a magnetometer that extended an additional 83 cm beyond the cylinder shell. The primary structural members were a honeycombed equipment shelf and thrust tube. The VISSR telescope was mounted on the equipment shelf and viewed the Earth through a special aperture in the side of the spacecraft. A support structure extended radially out from the thrust tube and was affixed to the solar panels, which formed the outer walls of the spacecraft and provided the primary source of electrical power. Located in the annulus-shaped space between the thrust tube and the solar panels were stationkeeping and dynamics control equipment, batteries, and most of the SEM equipment. Proper spacecraft attitude and spin rate (approximately 100 rpm) were maintained by two separate sets of jet thrusters mounted around the spacecraft equator and activated by ground command. The spacecraft used both UHF-band and S-band frequencies in its telemetry and command subsystem. A low-power VHF transponder provided telemetry and command during launch and then served as a backup for the primary subsystem once the spacecraft attained orbit. The spin-stabilized spacecraft carried a visible infrared spin-scan radiometer atmospheric sounder, meteorological data collection and transmission system, space environment monitor, and a biaxial fluxgate magnetometer. It operated at 100 degrees West initially, but replaced GOES 3 at 135 degrees West in March 1981. When GOES 5 VAS experienced a failure on July 30, 1984, GOES 4 was reactivated by NOAA to provide GOES 1 VISSR data relay services to western users. More information about GOES Satellites: http://www.oso.noaa.gov/goes/ Group: Platform_Details Entry_ID: GOES-4 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: GOES (Geostationary Operational Environmental Satellite) Short_Name: GOES-4 Long_Name: Geostationary Operational Environmental Satellite 4 End_Group Group: Synonymous_Platform_Names Short_Name: GOES D Short_Name: 11964 End_Group Group: Platform_Associated_Instruments Short_Name: SXM Short_Name: VAS End_Group Group: Orbit Orbit_Type: GEO > Geosynchronous > Geostationary End_Group Creation_Date: 2007-10-04 Online_Resource: http://www.oso.noaa.gov/goes/ Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1980-074A Group: Platform_Logistics Launch_Date: 1980-09-09 Launch_Site: CAPE CANAVERAL/KENNEDY SPACE CENTER, USA Primary_Sponsor: USA/NASA Primary_Sponsor: USA/NOAA End_Group End_Group SV A snow vehicle is a vehicle that is specifically designed to to be driven primarily on snow. Group: Platform_Details Entry_ID: SV Group: Platform_Identification Platform_Category: In Situ Land-based Platforms Platform_Series_or_Entity: MOBILE STATIONS/VEHICLES Short_Name: SV Long_Name: Snow Vehicle End_Group Group: Synonymous_Platform_Names Short_Name: SV End_Group Creation_Date: 2007-12-10 Online_Resource: http://en.wikipedia.org/wiki/Winter_service_vehicle Sample_Image: http://www.cwru.edu/affil/ansmet/snowcat.jpg End_Group PACE PACE is NASA's Plankton, Aerosol, Cloud, ocean Ecosystem mission, currently in the design phase of mission development. It is scheduled to launch in 2022, extending and improving NASA's over 20-year record of satellite observations of global ocean biology, aerosols (tiny particles suspended in the atmosphere), and clouds. PACE will advance the assessment of ocean health by measuring the distribution of phytoplankton, tiny plants and algae that sustain the marine food web. It will also continue systematic records of key atmospheric variables associated with air quality and Earth's climate. More information: https://pace.gsfc.nasa.gov/ 2019-04-30 16:21:25.0 [sritz] insert Definition (id: null text: PACE is NASA's Plankton, Aerosol, Cloud, ocean Ecosystem mission, currently in the design phase of mission development. It is scheduled to launch in 2022, extending and improving NASA's over 20-year record of satellite observations of global ocean biology, aerosols (tiny particles suspended in the atmosphere), and clouds. PACE will advance the assessment of ocean health by measuring the distribution of phytoplankton, tiny plants and algae that sustain the marine food web. It will also continue systematic records of key atmospheric variables associated with air quality and Earth's climate. More information: https://pace.gsfc.nasa.gov/ language code: en); 2019-04-30 16:20:10.0 [sritz] insert AltLabel (id: null category: primary text: Plankton, Aerosol, Cloud, ocean Ecosystem mission language code: en); 2019-04-30 16:17:43.0 [sritz] Insert Concept add broader relation (PACE [eb4175de-3ee7-4897-bbbe-590ad7e09b4f,368729] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761]); P-3B In April 1958 Lockheed corporation won a US Navy competition to find a replacement for the Navy's aging P2V Neptune series of long range antisubmarine warfare and maritime patrol aircraft. Lockheed's winning proposal was designated "P3V Orion". Named for the winter constellation of the mighty hunter, the Orion was actually derived from the famous Lockheed Electra civil airliner. [Text provided by: http://www.geocities.com/lucktam/awacs/orion/orion.htm ] [Photo provided by: http://www.farfromglory.com/images/p3b.jpg ] Group: Platform_Details Entry_ID: P-3B ORION Group: Platform_Identification Platform_Category: Aircraft Short_Name: P-3B ORION Long_Name: Lockheed P-3B Orion End_Group Creation_Date: 2008-07-14 Online_Resource: http://aeroweb.brooklyn.cuny.edu/specs/lockheed/p-3b.htm Online_Resource: http://www.aeroflight.co.uk/types/usa/lockheed_martin/p-3/P-3_Orion.htm Sample_Image: http://www.farfromglory.com/images/p3b.jpg End_Group 2015-06-18 16:12:43.0 [aaleman] revised short name per NSIDC request update PrefLabel (P-3B); R/V DOLPHIN CESSNA 206 The Cessna 205, 206, and 207, known variously as the Super Skywagon, Stationair, and Super Skylane are a family of single engine, general aviation aircraft with fixed landing gear used in commercial air service and also for personal use. The family was originally developed from the popular retractable-gear Cessna 210. The line's combination of a powerful engine, rugged construction and a large cabin has made these aircraft popular bush planes. Cessna describes the 206 as "the sport-utility vehicle of the air." These airplanes are also used for aerial photography, skydiving and other utility purposes. They can also be equipped with floats, amphibious floats and skis. Alternatively, they can be fitted with luxury appointments for use as a personal air transport. Between the start of production in 1962 and 2006 the total Cessna 205, 206 and 207 production has been 8509 aircraft so far. [Text and Photo provided by: http://en.wikipedia.org/wiki/Cessna_206 ] Group: Platform_Details Entry_ID: CESSNA 206 Group: Platform_Identification Platform_Category: Aircraft Short_Name: CESSNA 206 End_Group Creation_Date: 2008-07-14 Online_Resource: http://en.wikipedia.org/wiki/Cessna_206 Online_Resource: http://www.cessna.com/ Sample_Image: http://upload.wikimedia.org/wikipedia/commons/thumb/9/91/Cessna.206h.stationair2.arp.jpg/800px-Cessna.206h.stationair2.arp.jpg End_Group NASA Small Explorer (SMEX) PHOTOSYNTHESIS CHAMBER A photosynthesis chamber is a transparent airtight enclosure that is used along with a gas exchange system and sensing devices to measure plant functions, such as photosynthetic respiration, stomatal conductance, canopy resistance, and leaf photosynthetic rate, especially in response to changes in light and carbon dioxide concentrations. Photosynthesis chambers can be equipped with environmental control equipment (which allow researchers to vary such things as light, temperature, relative humidity, and gas concentrations). Photosynthesis chambers provide a controlled environment that supports the study of leaf and plant functions. The specific objectives of a photosynthesis chamber vary according to the needs of the particular study. Group: Platform_Details Entry_ID: PHOTOSYNTHESIS CHAMBER Group: Platform_Identification Platform_Category: In Situ Land-based Platforms Short_Name: PHOTOSYNTHESIS CHAMBER End_Group Creation_Date: 2012-07-18 Online_Resource: http://daac.ornl.gov/source_documents/photosynthesis_chamber.html End_Group COMS Cheollian-1 GEO-KOMPSAT-1 In 1996, Korea established its long-term plan of the National Space Program which was revised in 2000 to accommodate the public and civilian demand for satellite utilization and to maintain the continuity of satellite services. The plan prospects the details of the future space activities of Korea until 2015 and serves as a basis for space development in Korea. In response to this space plan, the Korea Meteorological Administration (KMA) started to define and formulate the basic requirements for COMS, the first geostationary meteorological satellite mission of Korea. - Note: The nickname Cheollian means long distance view (literally "Thousand Li View") in Korean. COMS is a geostationary meteorological satellite program of Korea with multifunctional applications in the fields of: 1) Experimental communications: a) in-orbit verification of developed communication technology, b) experiment of wide-band multimedia communication service 2) Ocean color monitoring: a) monitoring of marine environment and ecosystem, b) production of fishery information. The scope of the ocean color mission includes detecting, monitoring and predicting short-term biological phenomena such as HAB (Harmful Algal Bloom), studies on biogeochemical variables, monitoring health of the marine ecosystem, coastal zone and resource management and providing information for fishing communities. 3) Meteorological observations: a) continuous monitoring of the ground segment from GEO and extraction of meteorological products, b) early detection of severe weather phenomena, c) monitoring of long-term change of SST and clouds. The meteorological mission will complement the existing network of geostationary satellites, providing improved input data for numerical weather prediction models, and monitoring climate changes; the data, imagery and derived products will be freely available to both domestic and international community in real-time or near real-time basis through direct broadcasting or land lines. 2018-02-26 21:13:48.0 [sritz] update WeightedRelation (Platform-Instrument); update WeightedRelation (1.0); 2018-02-26 21:13:08.0 [sritz] insert WeightedRelation (id: null related concept uuid: 7a5528bc-32da-43e1-9790-23c91b4484ed relationship type: null relationship value: null generated by: null); 2018-02-26 20:57:08.0 [sritz] insert Definition (id: null text: In 1996, Korea established its long-term plan of the National Space Program which was revised in 2000 to accommodate the public and civilian demand for satellite utilization and to maintain the continuity of satellite services. The plan prospects the details of the future space activities of Korea until 2015 and serves as a basis for space development in Korea. In response to this space plan, the Korea Meteorological Administration (KMA) started to define and formulate the basic requirements for COMS, the first geostationary meteorological satellite mission of Korea. - Note: The nickname Cheollian means long distance view (literally "Thousand Li View") in Korean. COMS is a geostationary meteorological satellite program of Korea with multifunctional applications in the fields of: 1) Experimental communications: a) in-orbit verification of developed communication technology, b) experiment of wide-band multimedia communication service 2) Ocean color monitoring: a) monitoring of marine environment and ecosystem, b) production of fishery information. The scope of the ocean color mission includes detecting, monitoring and predicting short-term biological phenomena such as HAB (Harmful Algal Bloom), studies on biogeochemical variables, monitoring health of the marine ecosystem, coastal zone and resource management and providing information for fishing communities. 3) Meteorological observations: a) continuous monitoring of the ground segment from GEO and extraction of meteorological products, b) early detection of severe weather phenomena, c) monitoring of long-term change of SST and clouds. The meteorological mission will complement the existing network of geostationary satellites, providing improved input data for numerical weather prediction models, and monitoring climate changes; the data, imagery and derived products will be freely available to both domestic and international community in real-time or near real-time basis through direct broadcasting or land lines. language code: en); 2018-02-26 20:53:48.0 [sritz] update AltLabel (null); 2018-02-26 20:53:28.0 [sritz] insert AltLabel (id: null category: primary text: Communication, Ocean and Meteorological Satellite language code: en); insert AltLabel (id: null category: null text: GEO-KOMPSAT-1 language code: en); insert AltLabel (id: null category: null text: Cheollian-1 language code: en); 2018-02-26 20:52:22.0 [sritz] Insert Concept add broader relation (COMS [ec484699-009f-4f39-93aa-d11379b4288a,310595] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,287601]); FY (Feng-Yun) CORSAIR 131A he S-3B Viking was built to take off and land on carrier ships, fly into enemy territory and take out threatening submarines. It's rugged, fast and powerful, but its fighting days are numbered. Though the United States Navy is slowly decommissioning the fleet, one S-3B is still flying in hostile conditions. Its next mission? Venture into hazardous weather to study a phenomenon that has caused more than 100 commercial aircraft engines to fail, stall or temporarily lose power. Engineers from NASA's Glenn Research Center, Boeing and the Navy have combined forces to transform the S-3B into a state-of-the-art NASA research aircraft. Last month, NASA Glenn unveiled the modified plane in Cleveland. "We were able to capitalize on the decommissioning by acquiring the aircraft directly from the Navy," explained Dr. Rickey Shyne, director of Glenn's Facilities and Test Directorate. "This saved taxpayers millions of dollars compared to the cost of a new aircraft." Workers at the Navy's Fleet Readiness Center - Southeast and a Boeing facility in Fla. enhanced the plane by adding commercial satellite communications, global positioning navigation and weather radar systems. They installed research equipment racks in what was once the plane's bomb bay. And they gave it a shiny blue-and-white NASA paint job. With these new features, NASA's S-3B Viking is equipped to conduct science and aeronautics missions, such as environmental monitoring, satellite communications testing and aviation safety research. It can fly up to 40,000 feet high and reach speeds faster than 500 miles per hour, which makes it perfect for studying commercial airline safety issues. [Text provided by: http://www.nasa.gov/topics/aeronautics/features/s3_viking.html ] [Photo provided by: http://farm3.static.flickr.com/2368/2327814717_4ce60b336d.jpg?v=1205338421 ] Group: Platform_Details Entry_ID: CORSAIR 131A Group: Platform_Identification Platform_Category: Aircraft Short_Name: CORSAIR 131A End_Group Creation_Date: 2008-07-14 Online_Resource: http://www.nasa.gov/topics/aeronautics/features/s3_viking.html Sample_Image: http://farm3.static.flickr.com/2368/2327814717_4ce60b336d.jpg?v=1205338421 End_Group CESSNA 172 SKYHAWK The Cessna 172 Skyhawk is a four-seat, single-engine, high-wing airplane. More Cessna 172s have been built than any other aircraft. It is probably the most popular flight training aircraft in the world. Measured by its longevity and popularity, the Cessna 172 is the most successful mass produced light aircraft in history. The first production models were delivered in 1956 and they are still in production as of 2008; more than 43,000 have been built.[1] The Skyhawk's main competitors have been the Beechcraft Musketeer and Grumman AA-5 series (neither in production), the Piper Cherokee and, more recently, the Diamond DA40. The Cessna 172 started life as a tricycle landing gear upgrade from the taildragger Cessna 170, with a basic level of standard equipment. The first flight of the prototype was in November 1955. The 172 became an overnight sales success and over 1400 were built in 1956, its first full year of production. Early 172s were similar in appearance to the 170, with the same straight aft fuselage and tall gear legs, although the 172 had a straight vertical tail while the 170 had a rounded fin and rudder. Later 172 versions incorporated revised landing gear and the sweptback tail which is still in use today.The final aesthetic development in the mid-1960s, was a lowered rear deck that allowed an aft window. Cessna advertised this added rear visibility as "Omni-Vision" . This airframe configuration has remained almost unchanged since then, except for updates in avionics and engines, including the Garmin G1000 glass cockpit in 2005. Production had been halted in the mid-1980s, but was resumed in 1996 with the 160 hp (120 kW) Cessna 172R Skyhawk and was supplemented in 1998 by the 180 hp (135 kW) Cessna 172S Skyhawk SP. [Text and Photo provided by: http://en.wikipedia.org/wiki/Cessna_172 ] Group: Platform_Details Entry_ID: CESSNA 172 SKYHAWK Group: Platform_Identification Platform_Category: Aircraft Short_Name: CESSNA 172 SKYHAWK End_Group Creation_Date: 2008-07-14 Online_Resource: http://en.wikipedia.org/wiki/Cessna_172 Online_Resource: http://www.cessna.com/ Sample_Image: http://upload.wikimedia.org/wikipedia/commons/thumb/c/c8/Cessna172-CatalinaTakeOff.JPG/800px-Cessna172-CatalinaTakeOff.JPG End_Group R/V OREGON The NOAA Ship Oregon II conducts fishery and living marine resource studies in support of the research of the National Marine Fisheries Service (NMFS), Pascagoula Laboratory in Pascagoula, Mississippi. The ship collects fish and crustacean specimens using trawls and benthic longlines and fish larvae and eggs, and plankton using plankton nets and surface and midwater larval nets. The Oregon II normally operates in the Gulf of Mexico, the Atlantic Ocean, and the Caribbean Sea. The vessel is operated by NOAA's Office of Marine and Aviation Operations. Group: Platform_Details Entry_ID: R/V OREGON Group: Platform_Identification Platform_Category: In Situ Ocean-based Platforms Platform_Series_or_Entity: SHIPS Short_Name: R/V OREGON End_Group Creation_Date: 2012-07-19 Online_Resource: http://www.moc.noaa.gov/ot/ Sample_Image: http://www.moc.noaa.gov/ot/oregon2%202007a.jpg End_Group LARES LARES is a small space mission that will achieve important measurements in gravitational physics, General Relativity, space geodesy and geodynamics In particular, together with the LAGEOS and LAGEOS 2 satellites and with the GRACE models, it will provide a very accurate determination of the Earth gravitomagnetic field and of the Lense-Thirring effect. The orbital data are acquired by the International Laser Ranging Service (ILRS), a worldwide network of a number of laser-ranging stations. The Data analysis is carried on by a research centre at Sapienza, Univeristy of Rome in collaboration with Italian Space Agency (ASI), University of Salento, Istituto Nazionale Fisica Nucleare (INFN), University of Maryland Baltimore County, NASA Goddard, University of Texas at Austin and the German Research Centre for Geoscience (GFZ) of Potsdam. 2018-07-19 16:48:06.0 [sritz] insert Definition (id: null text: LARES is a small space mission that will achieve important measurements in gravitational physics, General Relativity, space geodesy and geodynamics In particular, together with the LAGEOS and LAGEOS 2 satellites and with the GRACE models, it will provide a very accurate determination of the Earth gravitomagnetic field and of the Lense-Thirring effect. The orbital data are acquired by the International Laser Ranging Service (ILRS), a worldwide network of a number of laser-ranging stations. The Data analysis is carried on by a research centre at Sapienza, Univeristy of Rome in collaboration with Italian Space Agency (ASI), University of Salento, Istituto Nazionale Fisica Nucleare (INFN), University of Maryland Baltimore County, NASA Goddard, University of Texas at Austin and the German Research Centre for Geoscience (GFZ) of Potsdam. language code: en); 2018-07-19 16:47:32.0 [sritz] insert AltLabel (id: null category: primary text: LAser Relativity Satellite language code: en); 2018-07-19 16:45:56.0 [sritz] Insert Concept add broader relation (LARES [ef053df7-ff76-47f3-a335-5d4e87e51b92,367855] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761]); Beidou (China's Satellite Navigation System) The BeiDou Navigation Satellite System will provide global coverage with positioning, navigation and timing services, including two kinds of service modes: an open service and an authorized service. The open service is provided free of charge location, velocity and timing, with positioning accuracy of 10 meters, velocity accuracy of 0.2 meters / second and timing accuracy of 10 nanoseconds. The authorized service provides a more secure position, velocity, timing, and communications services as well as a higher level of integrity. In order to make BeiDou Navigation Satellite System work better for global service, strengthen compatibility and interoperability between BeiDou and other countries’satellite navigation systems,and promote satellite positioning, navigation and timing service application, China is willing to cooperate with other countries in developing satellite navigation industry. 2017-08-15 13:27:58.0 [tstevens] insert Definition (id: null text: The BeiDou Navigation Satellite System will provide global coverage with positioning, navigation and timing services, including two kinds of service modes: an open service and an authorized service. The open service is provided free of charge location, velocity and timing, with positioning accuracy of 10 meters, velocity accuracy of 0.2 meters / second and timing accuracy of 10 nanoseconds. The authorized service provides a more secure position, velocity, timing, and communications services as well as a higher level of integrity. In order to make BeiDou Navigation Satellite System work better for global service, strengthen compatibility and interoperability between BeiDou and other countries’satellite navigation systems,and promote satellite positioning, navigation and timing service application, China is willing to cooperate with other countries in developing satellite navigation industry. language code: en); 2017-08-15 11:33:05.0 [tstevens] update PrefLabel (Beidou (China's Satellite Navigation System)); 2017-08-14 19:22:02.0 [tstevens] Insert Concept add narrower relation (Beidou (China’s Satellite Navigation System) [ef679d6a-a05b-4976-a236-ce2158b758ea,309903] - Beidou [b4306421-a1b1-4d56-ad84-6f0c57806369,309907]); 2017-08-14 19:21:42.0 [tstevens] Insert Concept add broader relation (Beidou (China’s Satellite Navigation System) [ef679d6a-a05b-4976-a236-ce2158b758ea,309903] - Navigation Platforms [1506fb17-7ac4-44ce-bde5-074885bdb2d2,287403]); NCEP GTS The Global Telecommunication System (GTS) consists of an integrated network of point-to-point circuits, and multi-point circuits which interconnect meteorological telecommunication centres. The circuits of the GTS are composed of a combination of terrestrial and satellite telecommunication links of: - point-to-point circuits, - point-to-multi-point circuits for data distribution, - multi-point-to-point circuits for data collection, - as well as data-communication network services. [Text and Photo Source, World Meteorological Organization: http://www.wmo.ch/pages/prog/www/TEM/GTS/gts.html ] Group: Platform_Details Entry_ID: NCEP GTS Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: NCEP GTS Long_Name: National Centers for Environmental Prediction Global Telecommunications Systems End_Group Creation_Date: 2008-08-07 Online_Resource: http://www.wmo.ch/pages/prog/www/TEM/GTS/gts.html Sample_Image: http://www.wmo.ch/pages/prog/www/TEM/GTS/images/StructureGTS.gif Group: Platform_Logistics Primary_Sponsor: NOAA NCEP End_Group End_Group TMPA TRMM Multi-Satellite Precipitation Analysis The Tropical Rainfall Measuring Mission (TRMM) Multisatellite Precipitation Analysis (TMPA) provides a calibration-based sequential scheme for combining precipitation estimates from multiple satellites, as well as gauge analyses where feasible, at fine scales (0.25 x 0.25 deg and 3 hourly). TMPA is available both after and in real time, based on calibration by the TRMM Combined Instrument and TRMM Microwave Imager precipitation products, respectively… Most of the coverage in the TMPA depends on input from two different sets of sensors. First, precipitation-related passive microwave data are collected by a variety of low earth orbit (LEO) satellites, including the Microwave Imager (TMI) on TRMM, Special Sensor Microwave Imager (SSM/I) on Defense Meteorological Satellite Program (DMSP) satellites, Advanced Microwave Scanning Radiometer-Earth Observing System (AMSR-E) on Aqua, and the Advanced Microwave Sounding Unit-B (AMSU-B) on the National Oceanic and Atmospheric Administration (NOAA) satellite series… The second major data source for the TMPA is the window-channel infrared data that are being collected by the international constellation of geosynchronous earth orbit (GEO) satellites. 2019-06-25 14:13:14.0 [tstevens] insert AltLabel (id: null category: null text: TRMM Multi-Satellite Precipitation Analysis language code: en); insert Definition (id: null text: The Tropical Rainfall Measuring Mission (TRMM) Multisatellite Precipitation Analysis (TMPA) provides a calibration-based sequential scheme for combining precipitation estimates from multiple satellites, as well as gauge analyses where feasible, at fine scales (0.25 x 0.25 deg and 3 hourly). TMPA is available both after and in real time, based on calibration by the TRMM Combined Instrument and TRMM Microwave Imager precipitation products, respectively… Most of the coverage in the TMPA depends on input from two different sets of sensors. First, precipitation-related passive microwave data are collected by a variety of low earth orbit (LEO) satellites, including the Microwave Imager (TMI) on TRMM, Special Sensor Microwave Imager (SSM/I) on Defense Meteorological Satellite Program (DMSP) satellites, Advanced Microwave Scanning Radiometer-Earth Observing System (AMSR-E) on Aqua, and the Advanced Microwave Sounding Unit-B (AMSU-B) on the National Oceanic and Atmospheric Administration (NOAA) satellite series… The second major data source for the TMPA is the window-channel infrared data that are being collected by the international constellation of geosynchronous earth orbit (GEO) satellites. language code: en); 2019-06-25 14:11:29.0 [tstevens] Insert Concept add broader relation (TMPA [eff6fbfa-3ccf-4848-89a2-b0b0e65e3524,368909] - Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,344529]); FY-3B Storm III (FY-3) satellite is China's second-generation polar orbit meteorological satellite, which is the basis of FY-1 meteorological satellite technology on the development and improvement in function and technology a big step forward with qualitative change, specific requirements to solve the three-dimensional atmospheric detection, ability to obtain substantial increase in global data to further enhance the cloud and surface characteristics of remote sensing capabilities, enabling access to global, all-weather, three-dimensional, quantitative, multi-spectral atmosphere, surface and sea surface parameters. FY-3 meteorological satellite applications for purposes such as four aspects: ● the provision of global numerical weather prediction for the medium-term resolution of the meteorological parameters uniform. ● study of global change, including climate variation, climate prediction for the variety of meteorological and geophysical parameters. ● monitoring of large-scale natural disasters and the surface environment. ● for a variety of professional activities (aviation, maritime, etc.) of any region to provide global weather information, meteorological support services for the military. FY-3 research and production is divided into two batches, 01 batches of two satellites, FY-3B has been on 05 November 2010 successfully launched. 02 star award in 2010 after the launch, and some remote sensing instruments for the addition, replacement and performance improvements, FY-3 satellites will apply 15 years. Group: Platform_Details Entry_ID: FY-3B Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: FY-3B Long_Name: FengYun-3B End_Group Group: Platform_Associated_Instruments Short_Name: VIRR Short_Name: TOU Short_Name: SIM Short_Name: SBUS Short_Name: MWTS Short_Name: MWRI Short_Name: MWHS Short_Name: MERSI Short_Name: IRAS Short_Name: ERM End_Group Group: Orbit Orbit_Altitude: 836 km Orbit_Inclination: 98.75 Equator_Crossing: descending node local time 10:00 AM ~ 10:20 AM Local time: e.g. Local time: e.g. Period: 101 Orbit_Type: LEO > LOW EARTH ORBIT > POLAR NON-SUN-SYNCHRONOUS End_Group Creation_Date: 2011-02-24 Online_Resource: http://www.nsmc.cma.gov.cn/NewSite/NSMC_EN/Channels/100222.html Online_Resource: http://satellite.cma.gov.cn/ArssEn/Ord/Satellite.aspx Group: Platform_Logistics Launch_Date: 2010-11-05 Launch_Site: TAIYUAN SPACE LAUNCH CENTER, CHINA Primary_Sponsor: China/NSMC End_Group End_Group OV-103 The Space Shuttle Discover was the the third orbiter to become operational at Kennedy Space Center, was named after one of two ships that were used by the British explorer James Cook in the 1770s during voyages in the South Pacific that led to the discovery of the Hawaiian Islands. Another of his ships was the Endeavour, the namesake of NASA's newest orbiter. Discovery benefited from lessons learned in the construction and testing of Enterprise, Columbia and Challenger. At rollout, its weight was some 6,870 pounds less than Columbia. Two orbiters, Challenger and Discovery, were modified at KSC to enable them to carry the Centaur upper stage in the payload bay. These modifications included extra plumbing to load and vent Centaur's cryogenic (L02/LH2) propellants (other IUS/PAM upper stages use solid propellants), and controls on the aft flight deck for loading and monitoring the Centaur stage. No Centaur flight was ever flown and after the loss of Challenger it was decided that the risk was too great to launch a shuttle with a fueled Centaur upper stage in the payload bay. [Summary provided by NASA] Group: Platform_Details Entry_ID: OV-103 Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Platform_Series_or_Entity: SPACE SHUTTLE Short_Name: OV-103 Long_Name: Discovery Space Shuttle End_Group Group: Synonymous_Platform_Names Short_Name: Discovery End_Group Creation_Date: 2008-01-25 Online_Resource: http://science.ksc.nasa.gov/shuttle/resources/orbiters/discovery.html Sample_Image: http://science.ksc.nasa.gov/shuttle/resources/orbiters/discovery-logo.gif Group: Platform_Logistics Launch_Date: 1984-08-30 Primary_Sponsor: NASA End_Group End_Group FSL-MAPS 2015-08-10 18:47:39.0 [epneff] added long name insert AltLabel (id: null text: FSL Mesoscale Analysis and Prediction System language code: en); 2015-08-10 18:47:07.0 [epneff] Insert Concept add broader relation (FSL-MAPS [f065f97b-a10e-4204-8807-dc904c409b51,158231] - Models/Analyses [113ecbc2-ab36-4d58-a96c-a6ce0106e749,143215]); Deimos Deimos missions The Deimos-1 and Deimos-2 mission archive and new acquisitions are now available for research and application development. 2019-07-24 16:25:05.0 [mmorahan] Move Concepts delete narrower relation (null); 2018-06-12 09:18:45.0 [mmorahan] Insert Concept add narrower relation (Deimos [f122ab59-266b-4be9-99ad-4c2172bcf97c,367663] - Deimos-2 [48e0f5f2-08fb-4739-8c5f-f53e24003f8c,367667]); 2018-06-12 09:14:20.0 [mmorahan] Move Concepts add narrower relation (Deimos [f122ab59-266b-4be9-99ad-4c2172bcf97c,367663] - DEIMOS-1 [8b35d386-0999-4b6e-ad12-f8501427b0ca,345361]); 2018-06-12 09:13:35.0 [mmorahan] insert AltLabel (id: null category: null text: Deimos missions language code: en); insert Definition (id: null text: The Deimos-1 and Deimos-2 mission archive and new acquisitions are now available for research and application development. language code: en); 2018-06-12 09:10:05.0 [mmorahan] Insert Concept add broader relation (Deimos [f122ab59-266b-4be9-99ad-4c2172bcf97c,367663] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761]); TIUNGSAT-1 TiungSat-1 is Malaysia's first national microsatellite. It was designed and developed in a collaborative effort between the Malaysian government, under the government appointed company ATSB \[Astronautic Technology (Malaysia) Sdn. Bdh.\] of Kuala Lumpur, and SSTL (Surrey Satellite Technology Ltd.) of Surrey, UK. In the view of the Malaysian government, the satellite development program was seen as an impetus for expanding Malaysia's capability in the area of high-technology industry. The first satellite was named "Tiung" after a beautiful small singing bird in Malaysia. Astronautic Technology Sdn. Bhd. (ATSB) is a research and development organization, which was formed in 1995 by the government of Malaysia. The TiungSat-1 specific applications are in the following fields: * Collection of imagery for environmental and meteorological use * Digital S&F (Store & Forward) communications * Technology demonstration * Space science * Amateur radio access Spacecraft: The TiungSat-1 S/C structure comprises eleven module trays used to house the electronics for the bus and payload systems. The box-like spacecraft has a size of 690 mm x 360 mm x 360 mm; it is three-axis stabilized using a gravity-gradient boom (6 m boom with tip mass), two 3-axis magnetorquers, and a momentum wheel. Attitude is sensed by two 3-axis magnetometers and by two-axis analog sun sensors. In addition, there are UED (Underneath Earth Detector) and SOD (Sun Overhead Detector). The pointing knowledge is in roll and pitch and in yaw (3 sigma values). The S/C power is 35 W per panel, provided by four surface-mounted GaAs solar panels and by a 10-cell NiCd battery (7 Ah). The power subsystem provides regulated voltage supplies at +5V and 10V along with an unregulated supply which fluctuates between 12-14 V. Autonomous functions, safe modes and data are handled by two OBCs (On-Board Computer), OBC-186 and OBC-386. Onboard data handling via a CAN (Controller Area Network) between platform and payloads. The onboard data storage capacity is 1 Gbit. The S/C mass is 50 kg (platform = 35 kg, payload = 15 kg). The nominal design life is three years. RF communications: TiungSat uses conventional AMSAT frequencies (Malaysian Oscar-46), thereby giving amateur radio operators access to its data (imagery and communication capabilities). The microsatellite features an AX.25 protocol store-and-forward PACSAT protocol suite communications system. The uplink is in VHF-band with a data rate of 9.6 kbit/s; three receivers are used: Rx1 operates at 144.46 MHz, Rx2 and Rx3 operate at 145.86 145.925 MHz, selectable. The downlink is dual-redundant in UHF-band (435 to 438 MHz range with 437.300, 437.325, 437.350, 437.375 MHz, selectable) with data rates of 9.6, and 38.4 kbit/s (experimentally at 76.8 kit/s). An error-protected digital packet communications protocol is used. All spacecraft operations are performed at ATSB in Kuala Lumpur. TiungSat-1 was launched Sept. 26, 2000 on a Dnepr-1 vehicle along with other satellites (the other payloads were: SaudiSat-1A/-1B of SISR (Saudi Institute for Space Research), UniSat of the University of Rome, and MegSat-1 of the MegSat Space Division of "Gruppo Meggiorin," Bresia, Italy) from the Baikonur Cosmodrome, Kazakhstan. Orbit: Circular orbit, altitude = 650 km, inclination = 64, period = 97 minutes. Spacecraft operations are carried out at ATSB's Mission Control Station located at the Universiti Kebangsaan Malaysia, Bangi, Selangor. The satellite has also been used in a number of educational activities ranging from the physical sciences to the humanities. Operational status of TiungSat-1 as of 2004: The payload was fully operational well beyond its design life of three years. However, since Jan. 2004, the payload is only being operated intermittently to reduce the power consumption of the battery. Sensor/experiment complement (MSEIS, MEIS, S&F, CEDEX): MSEIS (Multi-Spectral Earth Imaging System). MSEIS is a NAC (Narrow Angle Camera), a multispectral system of three cameras (green, red and near-infrared) in parallel, each with a 75 mm focal length optic and 100 mm aperture diameter. The NAC system provides a 78 m ground spatial resolution in three spectral bands: 510-590 nm, 610-690 nm and 810-890 nm (green, red, and near infrared). A two-dimensional CCD staring array detector with 1024 x 1024 pixels is used providing snapshot imagery of scene size 78 km x 78 km. Up to four contiguous images can be collected along the flight path. The data are digitized to 8 bits radiometric resolution (256 levels). MEIS (Metrological Earth Imaging System). MEIS is a single-band WAC (Wide Angle Camera) system with 6.5 mm focal length optics. It provides NIR imagery (810-890 nm) with a 900 m spatial resolution. The CCD area array detector has a size of 1024 x 1024 elements (pixels) for snapshot observations. Data are quantized to 8 bits radiometric resolution. An image has the size of 900 km x 900 km. The data is being used for meteorological applications. S&F (Digital Store & Forward Communications). The subsystem provides global, frequency-agile, communications for any form of digitized data: e-mail, voice-mail, scientific data exchange, fax, imagery, or even Internet mail for remote regions. The low cost and direct access offered by the TiungSat-1 microsatellite in orbit also makes it ideal for use by scientists, engineers and students based in institutes, universities and even schools throughout the world. - DSPE (Digital Signal Processing Experiment). The DSPE consists of a TM320C31 low power DSP suitable for special or general purpose signal processing tasks on LEO satellites. The VHF scanner operates in the 140-150 MHz range. A built-in FSK decoder is used. The system is capable to detect signals from a pre-set signal strength threshold within selected bar. DSP can be used for processing audio transmission for rebroadcast. CEDEX (Cosmic Ray Energy Deposition Experiment). The objective of CEDEX is to characterize the TiungSat-1 orbit radiation environment in terms of the observed particle LET (Linear Energy Transfer) spectrum at the spacecraft. The primary sensor consists of a 30mm x 30mm PIN diode detector 300 microns in depth, housed in a separate screened aluminium unit mounted on the CEDEX module box (three area PIN-diode detectors are mounted in a "telescopic" arrangement; hence, information pertaining to directions of the energy particles detected can be derived.). This is connected to a charge amplifier and a pulse-shaping circuit which, in turn, are connected to an event-driven, hardware-logic controlled pulse-height multi-channel analyzer. CEDEX is controlled autonomously by a CAN-microcontroller with its own data-storage RAM and built-in data-compression software. This sends data to an internal CAN-controller which formats and sends them on to the primary OBC via the spacecraft's CAN (Controlled Area Network) bus. CEDEX is a multichannel analyzer with 512 channels and a 0.5 pC (picocoulomb) charge resolution. The instrument charge range is between 0.2 -24 pC, equivalent to a normal incidence particle LET range of about 60 - 7500 MeV cm2 g-1 (200,000 particles/s). The CEDEX data obtained are comparable directly with such instruments as CREDO-II flown on STRV-1c (launch Nov. 16, 2000) and CRE (Cosmic Ray Experiment) flown on KitSat-1 (launch Aug. 10, 1992) and PoSat-1 (launch Sept. 26, 1993). Experimental Microsatellite GPS, an SSTL/ESA collaboration. An advanced 12-channel GPS receiver with two GPS patch antennas is installed for several objectives: 1) onboard generation of Keplerian orbital elements (NORAD experiment, this was first performed on PoSat), 2) onboard navigation, attitude, and timing services, and 3) refractive sounding of the ionosphere. The instrument is primarily used for orbit and position determination and for precise onboard timing services. In parallel, the instrument is also employed for refractive ionospheric monitoring. The TEC (Total Electron Content) occultation observations of the instrument provide slant range measurements which can be converted into vertical profiles. Information provided by: http://www.eoPortal.org Group: Platform_Details Entry_ID: TIUNGSAT-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: TIUNGSAT-1 End_Group Group: Synonymous_Platform_Names Short_Name: MySat-1 Short_Name: Oscar-46 Short_Name: MO-46 End_Group Group: Platform_Associated_Instruments Short_Name: CCD IMAGER Short_Name: CAMERAS End_Group Group: Orbit Orbit_Altitude: 650 Orbit_Inclination: 64.6 Period: 97.1 Perigee: 605.3 Apogee: 647 Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2008-06-19 Online_Resource: http://directory.eoportal.org/get_announce.php?an_id=7470 Online_Resource: http://www.sstl.co.uk/ Group: Platform_Logistics Launch_Date: 2000-09-26 Launch_Site: Baikonur Cosmodrome, Tyuratam, Russia Primary_Sponsor: Malaysia Primary_Sponsor: Surrey Satellite Technology Ltd. (SSTL) End_Group End_Group BE-B BE-B (Explorer 22) was a small ionospheric research satellite instrumented with an electrostatic probe, a 20-, 40-, and 41-Hz radio beacon, a passive laser tracking reflector, and a Doppler navigation experiment. Its objective was to obtain worldwide observations of total electron content between the spacecraft and the earth. The satellite was initially spin-stabilized, but it was despun after solar paddle erection. Subsequent stabilization oriented the satellite axis of symmetry with the local magnetic field by means of a strong bar magnet and damping rods. A three-axis magnetometer and sun sensors provided information on the satellite attitude and spin rate. There was no tape recorder aboard so that satellite performance data and electrostatic probe data could be observed only when the satellite was within range of a ground telemetry station. Continuous transmitters also operated at 162 and 324 MHz to permit precise tracking by 'Transit' tracking stations for navigation and geodetic studies. In August 1968, data acquisition from the satellite telemetry channels was discontinued. In July 1969, tracking and world map production were discontinued by GSFC, and world map production based on NORAD orbit elements was subsequently assumed by ESRO. The satellite failed in February 1970 and BE-C was turned on in order to partially replace use made of this satellite beacon experiment. Group: Platform_Details Entry_ID: BE-B Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: BE (Beacon Explorer) Short_Name: BE-B Long_Name: Beacon Explorer-B End_Group Group: Synonymous_Platform_Names Short_Name: Explorer 22 Short_Name: 00899 End_Group Group: Platform_Associated_Instruments Short_Name: DOPPLER RADAR End_Group Group: Orbit Orbit_Inclination: 79.7 degrees Perigee: 889 km Apogee: 1081 km End_Group Creation_Date: 2007-08-29 Online_Resource: http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1964-064A Group: Platform_Logistics Launch_Date: 1964-10-10 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: NASA End_Group End_Group Seirios Seirios is one of two of the remotely operated vehicles (ROVs) aboard NOAA Ship Okeanos Explorer. Much like its namesake, Seirios acts as a brilliant source of light in the “night sky” of the ocean, providing illumination and a wide-angle view from above for its counterpart ROV, the Deep Discoverer (D2). Referred to in the industry as a ‘camera sled,’ Seirios is directly tethered via a cable to the Okeanos Explorer and then is further tethered to D2. This cable provides power to the ROVs as well as a pathway for data transfer between the vehicles and the ship. This configuration allows Seirios to absorb the heave from the ship while keeping D2 stable as it explores the ocean floor and gives ROV pilots from the Global Foundation for Ocean Exploration on board the Okeanos an expanded view of D2 and surrounding areas. This tandem robot configuration allows stunning imagery to be captured for an undisturbed look at the seafloor, literally shedding light on a location’s features and inhabitants. Seirios is equipped with a scanning 360-degree sonar as well as a series of cameras, including one high-definition camera and several standard-definition cameras. Three rear-mounted LED light banks aimed forward and below the vehicle illuminate D2 from above. Seirios is also outfitted with a complement of sensors similar to those found on D2 that measure conductivity, temperature, dissolved oxygen, depth, and other information from the ocean and help to better characterize each of the areas that are explored. While Seirios usually isn’t the star of the show, it plays an invaluable role in allowing the dynamic duo of robots to explore the ocean together. 2020-01-21 18:18:37.0 [tstevens] insert Definition (id: null text: Seirios is one of two of the remotely operated vehicles (ROVs) aboard NOAA Ship Okeanos Explorer. Much like its namesake, Seirios acts as a brilliant source of light in the “night sky” of the ocean, providing illumination and a wide-angle view from above for its counterpart ROV, the Deep Discoverer (D2). Referred to in the industry as a ‘camera sled,’ Seirios is directly tethered via a cable to the Okeanos Explorer and then is further tethered to D2. This cable provides power to the ROVs as well as a pathway for data transfer between the vehicles and the ship. This configuration allows Seirios to absorb the heave from the ship while keeping D2 stable as it explores the ocean floor and gives ROV pilots from the Global Foundation for Ocean Exploration on board the Okeanos an expanded view of D2 and surrounding areas. This tandem robot configuration allows stunning imagery to be captured for an undisturbed look at the seafloor, literally shedding light on a location’s features and inhabitants. Seirios is equipped with a scanning 360-degree sonar as well as a series of cameras, including one high-definition camera and several standard-definition cameras. Three rear-mounted LED light banks aimed forward and below the vehicle illuminate D2 from above. Seirios is also outfitted with a complement of sensors similar to those found on D2 that measure conductivity, temperature, dissolved oxygen, depth, and other information from the ocean and help to better characterize each of the areas that are explored. While Seirios usually isn’t the star of the show, it plays an invaluable role in allowing the dynamic duo of robots to explore the ocean together. language code: en); 2020-01-21 17:27:17.0 [tstevens] Insert Concept add broader relation (Seirios [f21d8715-f805-427d-b006-57a5d1240d1c,559751] - ROV [da6420b6-48ec-4ae2-98c7-0ef0538815a0,542741]); SENTINEL-2B The Sentinel-2 mission is a land monitoring constellation of two satellites that provide high resolution optical imagery and provide continuity for the current SPOT and Landsat missions. The orbit is an average height of 785 km and the presence of two satellites in the mission allow repeated surveys every 5 days at the equator and every 2-3 days at middle latitudes. The satellites are equipped with the state-of-the-art MSI (Multispectral Imager) instrument for surveying with a resolution of 10 to 60 m in the visible, near infrared (VNIR), and short-wave infrared (SWIR) spectral zones, including 13 spectral channels, which ensures the capture of differences in vegetation state, including temporal changes, and also minimizes impact on the quality of atmospheric photography. Sentinel-2B was launched March 7, 2017. 2020-02-12 16:40:48.0 [sritz] Move Concepts delete broader relation (null); add broader relation (SENTINEL-2B [f2445400-1981-4ef3-bf7c-f4aa35923ae9,559803] - SENTINEL-2 [2ce20983-98b2-40b9-bb0e-a08074fb93b3,541455]); 2020-01-30 16:00:22.0 [tstevens] Move Concepts delete broader relation (null); add broader relation (SENTINEL-2B [f2445400-1981-4ef3-bf7c-f4aa35923ae9,559803] - SENTINEL-2 [6f1c359b-b1a6-47c1-979e-0689e637fbdc,559807]); 2020-01-29 12:35:57.0 [tstevens] insert Definition (id: null text: The Sentinel-2 mission is a land monitoring constellation of two satellites that provide high resolution optical imagery and provide continuity for the current SPOT and Landsat missions. The orbit is an average height of 785 km and the presence of two satellites in the mission allow repeated surveys every 5 days at the equator and every 2-3 days at middle latitudes. The satellites are equipped with the state-of-the-art MSI (Multispectral Imager) instrument for surveying with a resolution of 10 to 60 m in the visible, near infrared (VNIR), and short-wave infrared (SWIR) spectral zones, including 13 spectral channels, which ensures the capture of differences in vegetation state, including temporal changes, and also minimizes impact on the quality of atmospheric photography. Sentinel-2B was launched March 7, 2017. language code: en); 2020-01-29 12:34:29.0 [tstevens] Insert Concept add broader relation (SENTINEL-2B [f2445400-1981-4ef3-bf7c-f4aa35923ae9,559803] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,541501]); DMSP 5D-1/F1 [Source: National Space Science Data Center, http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1976-091A ] DMSP-5D-1/F1 was one of a series of meteorological satellites developed and operated by the Air Force under the Defense Meteorological Satellite Program (DMSP). This program, previously known as DAAP (Data Acquisition and Processing Program), was classified until March 1973. The objectives of this program were to provide global visual and infrared cloud cover data and specialized environmental data to support Department of Defense requirements. Operationally, the program consisted of two satellites in planned 83-km sun-synchronous polar orbits, with the ascending node of one satellite in early morning and the other at local noon. The 5.4-m-long spacecraft was separated into four sections: (1) a precision mounting platform (PMP) for sensors and equipment requiring precise alignment, (2) an equipment support module (ESM) containing the electronics, reaction wheels, and some meteorological sensors, (3) a reaction control equipment (RCE) support structure (that has the third-stage motor, hydrazine reaction control system) which supports (4) a 9.29 sq m solar cell panel. The Block 5D spacecraft stabilization was controlled by a conbination flywheel and magnetic control coil system so sensors could be maintained in the desired 'earth-looking' mode. One feature of Block 5D was the precision-pointing accuracy of the primary imager to 0.01 deg provided by a star sensor and an updated ephemeris navigation system. This allowed automatic geographical mapping of the digital imagery to the nearest picture element. The operational line scan system (OLS) built by Westinghouse, was the primary acquisition system that provided real-time or stored, multi-orbit, day-and-night visual and infrared imagery at 1/3 nautical mile resolution for all major land masses, 1-1/2 nautical mile resolution for complete global coverage, and provided with this data calibration, timing, and other auxiliary signals to the spacecraft for digital transmission to the ground. A supplementary sensor package, the special sensor H (SSH), a step-scanning radiometer, was the infrared temperature-humidity-ozone sounder. The data processing system, which included three high-density tape recorders, could store a total of 400 min of data, each allowing full global coverage twice daily. Either recorded or real-time data were transmitted to ground-receiving sites via two redundant s-band transmitters. Recorded data were read out to tracking sites located at Fairchild AFB, WA, and Loring AFB, ME, and relayed via SATCOM to Air Force Global Weather Central, Offutt AFB, NE. Real-time data were read out at mobile tactical sites located around the world. A more complete description of the Block 5D satellite can be found in the report, 'The Defense Meteorological Satellite Program,' D. A. Nichols, Optical Engineering, 14, 4, July - August 1975. Group: Platform_Details Entry_ID: DMSP 5D-1/F1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: DMSP (Defense Meteorological Satellite Program) Short_Name: DMSP 5D-1/F1 Long_Name: Defense Meteorological Satellite Program-F1 End_Group Group: Synonymous_Platform_Names Short_Name: DMSP 12535 Short_Name: DMSP-F1 Short_Name: 09415 End_Group Group: Platform_Associated_Instruments Short_Name: MFR/SSH Short_Name: OLS Short_Name: GAMMA RAY DETECTOR (SSB) Short_Name: GFE-3R DOSIMETER End_Group Group: Orbit Orbit_Altitude: 830 km Orbit_Inclination: 98.6 degrees Period: 101.3 min Perigee: 806 km Apogee: 832 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-09-14 Online_Resource: http://www.ngdc.noaa.gov/dmsp/ Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1976-091A Online_Resource: http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/dmsp.html Group: Platform_Logistics Launch_Date: 1976-09-11 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: Department of Defense-Department of the Air Force (United States) End_Group End_Group GOES-2 GOES 2 was a NASA-developed, NOAA-operated, geosynchronous, and operational spacecraft. The spin-stabilized spacecraft carried (1) a visible infrared spin-scan radiometer (VISSR) to provide high-quality day/night cloudcover data and to take radiance-derived temperatures of the earth/atmosphere system, (2) a meteorological data collection and transmission system to relay processed data from central weather facilities to APT-equipped regional stations and to collect and retransmit data from remotely located earth-based platforms, and (3) a space environment monitor (SEM) system to measure proton, electron, and solar X-ray fluxes and magnetic fields. The cylindrically shaped spacecraft measured 190.5 cm in diameter and 230 cm in length, exclusive of a magnetometer that extended an additional 83 cm beyond the cylinder shell. The primary structural members were a honeycombed equipment shelf and thrust tube. The VISSR telescope was mounted on the equipment shelf and viewed the earth through a special aperture in the side of the spacecraft. A support structure extended radially out from the thrust tube and was affixed to the solar panels, which formed the outer walls of the spacecraft and provided the primary source of electrical power. Located in the annulus-shaped space between the thrust tube and the solar panels were stationkeeping and dynamics control equipment, batteries, and most of the SEM equipment. Proper spacecraft attitude and spin rate (approximately 100 rpm) were maintained by two separate sets of jet thrusters mounted around the spacecraft equator and activated by ground command. The spacecraft used both UHF-band and S-band frequencies in its telemetry and command subsystem. A low-power VHF transponder provided telemetry and command during launch and then served as a backup for the primary subsystem once the spacecraft attained synchronous orbit. For more detailed information, see "The GOES/SMS User's Guide" (TRF B28599), available from NSSDC. 2017-09-01 17:01:54.0 [sritz] insert Definition (id: null text: GOES 2 was a NASA-developed, NOAA-operated, geosynchronous, and operational spacecraft. The spin-stabilized spacecraft carried (1) a visible infrared spin-scan radiometer (VISSR) to provide high-quality day/night cloudcover data and to take radiance-derived temperatures of the earth/atmosphere system, (2) a meteorological data collection and transmission system to relay processed data from central weather facilities to APT-equipped regional stations and to collect and retransmit data from remotely located earth-based platforms, and (3) a space environment monitor (SEM) system to measure proton, electron, and solar X-ray fluxes and magnetic fields. The cylindrically shaped spacecraft measured 190.5 cm in diameter and 230 cm in length, exclusive of a magnetometer that extended an additional 83 cm beyond the cylinder shell. The primary structural members were a honeycombed equipment shelf and thrust tube. The VISSR telescope was mounted on the equipment shelf and viewed the earth through a special aperture in the side of the spacecraft. A support structure extended radially out from the thrust tube and was affixed to the solar panels, which formed the outer walls of the spacecraft and provided the primary source of electrical power. Located in the annulus-shaped space between the thrust tube and the solar panels were stationkeeping and dynamics control equipment, batteries, and most of the SEM equipment. Proper spacecraft attitude and spin rate (approximately 100 rpm) were maintained by two separate sets of jet thrusters mounted around the spacecraft equator and activated by ground command. The spacecraft used both UHF-band and S-band frequencies in its telemetry and command subsystem. A low-power VHF transponder provided telemetry and command during launch and then served as a backup for the primary subsystem once the spacecraft attained synchronous orbit. For more detailed information, see "The GOES/SMS User's Guide" (TRF B28599), available from NSSDC. language code: en); 2017-09-01 16:36:21.0 [sritz] Insert Concept add broader relation (GOES-2 [f2b36444-124d-4f32-97c7-dc8a09b2d0f0,310079] - GOES [6e332c25-caeb-4917-afb6-af757bcecd72,310071]); JERS-1 JERS-1 (JAPANESE EARTH RESOURCES SATELLITE-1) [Source: JAXA, http://www.eorc.jaxa.jp/JERS-1/en/index.html ] JERS-1 is an Earth Observation Satellite to cover the global land area for national land survey, agriculture, forestry, and fishery, environmental protection, disaster protection, and coastal monitoring, etc. focusing on observation around the world and resource exploitation. It was launched into a solar-synchronous sub-recurrent orbit at an altitude of 568 km with a recurrent period of 44 days by the H-I launch vehicle on February 11, 1992 from National Space Development Agency of Japan (NASDA) Tanegashima Space Center, and has been continuing to observe and collect data with a mission data recorder by the high performance Synthetic Aperture Radar (SAR) and Optical Sensor (OPS). SAR is an active sensor which transmits microwave and observes characteristics, inequality, slope in the surface of the earth, etc. without being influenced by the weather day and night due to scattered waves from the Earth. OPS can observe in seven bands from the visible region to short wave infrared band and is capable of stereoscopic observation by forward look of 15.3 (J from nadir in near infrared band and highly is usable for identifying stones, rocks, and minerals. Group: Platform_Details Entry_ID: JERS-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: JERS Short_Name: JERS-1 Long_Name: Japanese Earth Resources Satellite-1 End_Group Group: Synonymous_Platform_Names Short_Name: FUYO-1 End_Group Group: Platform_Associated_Instruments Short_Name: OPS Short_Name: SAR End_Group Group: Orbit Orbit_Altitude: 580 km Orbit_Inclination: 98 deg Period: 96 min Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-10-10 Online_Resource: http://www.eorc.jaxa.jp/JERS-1/en/index.html Sample_Image: http://www.jaxa.jp/projects/sat/jers1/img/photo_jers1.jpg Group: Platform_Logistics Launch_Date: 1992-02-11 Launch_Site: Tanegashima Island, Japan Design_Life: 2 Years Primary_Sponsor: JAPAN/JAXA End_Group End_Group 2016-06-09 14:50:40.0 [epneff] added altLabel insert AltLabel (id: null text: JERS-1 (JAPANESE EARTH RESOURCES SATELLITE-1) language code: en); Platforms A schematic description of a system, theory, or phenomenon that accounts for its known or inferred properties and may be used for further study of its characteristics [Source: The Free Dictionary] Group: Platform_Details Entry_ID: MODELS/ANALYSES Group: Platform_Identification Platform_Category: MODELS/ANALYSES End_Group End_Group 2017-06-27 16:22:26.0 [tstevens] Remove Concepts delete narrower relation (null); 2017-06-27 15:11:32.0 [tstevens] Insert Concept add narrower relation (Platforms [f3261de5-34c1-4980-af22-f9d7e7206d12,288823] - TEST [a861a0cb-a973-4c20-939b-1d8019e32cb7,309681]); 2015-08-19 13:45:13.0 [tbs1979] Insert Concept add narrower relation (Platforms [f3261de5-34c1-4980-af22-f9d7e7206d12,144559] - NOT APPLICABLE [41d72eb0-9554-48a7-8821-dec569503da3,158307]); 2012-10-18 14:39:22.0 [gee-cee] Remove Concepts delete narrower relation (null); 2012-10-17 01:30:33.0 [saritz] Move Concepts delete narrower relation (null); 2012-10-17 01:29:33.0 [saritz] Insert Concept add narrower relation (Platforms [f3261de5-34c1-4980-af22-f9d7e7206d12,31173] - UND CITATION II [7f2883c4-bbaf-4150-93d8-dc48716476ca,61305]); GLOBAL HAWK UAV [Source: Wikipedia, http://en.wikipedia.org/wiki/Northrop_Grumman_RQ-4_Global_Hawk ] The Northrop Grumman (formerly Ryan Aeronautical) RQ-4 Global Hawk (known as Tier II+ during development) is an unmanned aerial vehicle (UAV) used by the United States Air Force and Navy as a surveillance aircraft. In role and operational design, the Global Hawk is similar to the Lockheed U-2, the venerable 1950s spy plane. It is a theater commander's asset to provide a broad overview and systematic target surveillance. For this purpose, the Global Hawk is able to provide high resolution Synthetic Aperture Radar (SAR)—that can penetrate cloud-cover and sandstorms— and Electro-Optical/Infrared (EO/IR) imagery at long range with long loiter times over target areas. It can survey as much as 40,000 square miles (103,600 square kilometers) of terrain a day. Group: Platform_Details Entry_ID: GLOBAL HAWK UAV Group: Platform_Identification Platform_Category: Aircraft Short_Name: GLOBAL HAWK UAV End_Group Group: Synonymous_Platform_Names Short_Name: RQ-4 Block 20 Global Hawk End_Group Group: Platform_Associated_Instruments Short_Name: HIWRAP Short_Name: HAMSR Short_Name: GHIS End_Group Creation_Date: 2011-05-26 Online_Resource: http://www.nasa.gov/topics/earth/features/global-hawk.html Online_Resource: http://www.as.northropgrumman.com/products/ghrq4b/index.html Group: Platform_Logistics Primary_Sponsor: USA/DOD Primary_Sponsor: USA/NASA End_Group End_Group CloudSat CLOUDSAT [Source: NASA Science Missions Home Page] CloudSat uses advanced radar to "slice" through clouds to see their vertical structure, providing a completely new observational capability from space. Earlier satellites could only image the uppermost layers of clouds. CloudSat is among the first satellites to study clouds on a global basis. It will look at their structure, composition and effects. This is a cooperative mission with Canada. CloudSat measurements have applications in air quality, weather models, water management, aviation safety, and disaster management. The key observations are the vertical profiles of cloud liquid water and ice water contents and related cloud physical and radiative properties. The spacecraft payload consists of a millimeter-wave radar. CloudSat will fly in tight formation with the CALIPSO satellite carrying a backscattering lidar, and these two satellites will follow behind the Aqua satellite in a somewhat looser formation. The combination of data from the CloudSat radar with coincident measurements from CALIPSO and Aqua provides a rich source of information that can be used to assess the role of clouds in both weather and climate. CloudSat was launched on 2006-04-28 from Vandenberg AFB, California More Information: http://cloudsat.atmos.colostate.edu/ Group: Platform_Details Entry_ID: CloudSat Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: EOS (Earth Observing System) Short_Name: CloudSat End_Group Group: Synonymous_Platform_Names Short_Name: CloudSat End_Group Group: Platform_Associated_Instruments Short_Name: CloudSat-CPR End_Group Group: Orbit Orbit_Altitude: 705 km Orbit_Inclination: 98.2 Degrees Period: 99 Minutes Repeat_Cycle: 16 Days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-04-17 Online_Resource: https://cloudsat.atmos.colostate.edu/ Online_Resource: https://www.nasa.gov/mission_pages/cloudsat/ Online_Resource: https://www.jpl.nasa.gov/missions/cloudsat/ Group: Platform_Logistics Launch_Date: 2006-04-28 Launch_Site: VANDENBERG AIR FORCE BASE, USA Design_Life: 22 months Primary_Sponsor: USA/NASA Primary_Sponsor: CANADA/CSA Primary_Sponsor: USA/DOD/USAF Primary_Sponsor: USA/DOE End_Group End_Group 2020-01-02 22:48:59.0 [sritz] update Definition ([Source: NASA Science Missions Home Page] CloudSat uses advanced radar to "slice" through clouds to see their vertical structure, providing a completely new observational capability from space. Earlier satellites could only image the uppermost layers of clouds. CloudSat is among the first satellites to study clouds on a global basis. It will look at their structure, composition and effects. This is a cooperative mission with Canada. CloudSat measurements have applications in air quality, weather models, water management, aviation safety, and disaster management. The key observations are the vertical profiles of cloud liquid water and ice water contents and related cloud physical and radiative properties. The spacecraft payload consists of a millimeter-wave radar. CloudSat will fly in tight formation with the CALIPSO satellite carrying a backscattering lidar, and these two satellites will follow behind the Aqua satellite in a somewhat looser formation. The combination of data from the CloudSat radar with coincident measurements from CALIPSO and Aqua provides a rich source of information that can be used to assess the role of clouds in both weather and climate. CloudSat was launched on 2006-04-28 from Vandenberg AFB, California More Information: http://cloudsat.atmos.colostate.edu/ Group: Platform_Details Entry_ID: CloudSat Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: EOS (Earth Observing System) Short_Name: CloudSat End_Group Group: Synonymous_Platform_Names Short_Name: CloudSat End_Group Group: Platform_Associated_Instruments Short_Name: CloudSat-CPR End_Group Group: Orbit Orbit_Altitude: 705 km Orbit_Inclination: 98.2 Degrees Period: 99 Minutes Repeat_Cycle: 16 Days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-04-17 Online_Resource: https://cloudsat.atmos.colostate.edu/ Online_Resource: https://www.nasa.gov/mission_pages/cloudsat/ Online_Resource: https://www.jpl.nasa.gov/missions/cloudsat/ Group: Platform_Logistics Launch_Date: 2006-04-28 Launch_Site: VANDENBERG AIR FORCE BASE, USA Design_Life: 22 months Primary_Sponsor: USA/NASA Primary_Sponsor: CANADA/CSA Primary_Sponsor: USA/DOD/USAF Primary_Sponsor: USA/DOE End_Group End_Group); 2020-01-02 22:42:45.0 [sritz] delete Resource (null); 2018-04-17 16:18:02.0 [sritz] update Definition ([Source: NASA Science Missions Home Page] CloudSat uses advanced radar to "slice" through clouds to see their vertical structure, providing a completely new observational capability from space. Earlier satellites could only image the uppermost layers of clouds. CloudSat is among the first satellites to study clouds on a global basis. It will look at their structure, composition and effects. This is a cooperative mission with Canada. CloudSat measurements have applications in air quality, weather models, water management, aviation safety, and disaster management. The key observations are the vertical profiles of cloud liquid water and ice water contents and related cloud physical and radiative properties. The spacecraft payload consists of a millimeter-wave radar. CloudSat will fly in tight formation with the CALIPSO satellite carrying a backscattering lidar, and these two satellites will follow behind the Aqua satellite in a somewhat looser formation. The combination of data from the CloudSat radar with coincident measurements from CALIPSO and Aqua provides a rich source of information that can be used to assess the role of clouds in both weather and climate. CloudSat was launched on 2006-04-28 from Vandenberg AFB, California More Information: http://cloudsat.atmos.colostate.edu/ Group: Platform_Details Entry_ID: CloudSat Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: EOS (Earth Observing System) Short_Name: CloudSat End_Group Group: Synonymous_Platform_Names Short_Name: CloudSat End_Group Group: Platform_Associated_Instruments Short_Name: CloudSat-CPR End_Group Group: Orbit Orbit_Altitude: 705 km Orbit_Inclination: 98.2 Degrees Period: 99 Minutes Repeat_Cycle: 16 Days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-04-17 Online_Resource: https://cloudsat.atmos.colostate.edu/ Online_Resource: https://www.nasa.gov/mission_pages/cloudsat/main/index.html Sample_Image: https://www.nasa.gov/images/content/126766main_cloudsat-clouds-330.jpg Group: Platform_Logistics Launch_Date: 2006-04-28 Launch_Site: VANDENBERG AIR FORCE BASE, USA Design_Life: 22 months Primary_Sponsor: USA/NASA Primary_Sponsor: CANADA/CSA Primary_Sponsor: USA/DOD/USAF Primary_Sponsor: USA/DOE End_Group End_Group); 2018-03-13 18:16:56.0 [sritz] update Definition ([Source: NASA Science Missions Home Page] CloudSat uses advanced radar to "slice" through clouds to see their vertical structure, providing a completely new observational capability from space. Earlier satellites could only image the uppermost layers of clouds. CloudSat is among the first satellites to study clouds on a global basis. It will look at their structure, composition and effects. This is a cooperative mission with Canada. CloudSat measurements have applications in air quality, weather models, water management, aviation safety, and disaster management. The key observations are the vertical profiles of cloud liquid water and ice water contents and related cloud physical and radiative properties. The spacecraft payload consists of a millimeter-wave radar. CloudSat will fly in tight formation with the CALIPSO satellite carrying a backscattering lidar, and these two satellites will follow behind the Aqua satellite in a somewhat looser formation. The combination of data from the CloudSat radar with coincident measurements from CALIPSO and Aqua provides a rich source of information that can be used to assess the role of clouds in both weather and climate. CloudSat was launched on 2006-04-28 from Vandenberg AFB, California More Information: http://cloudsat.atmos.colostate.edu/ Group: Platform_Details Entry_ID: CLOUDSAT Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: EOS (Earth Observing System) Short_Name: CLOUDSAT End_Group Group: Synonymous_Platform_Names Short_Name: CLOUDSAT End_Group Group: Platform_Associated_Instruments Short_Name: CLOUDSAT-CPR End_Group Group: Orbit Orbit_Altitude: 705 km Orbit_Inclination: 98.2 Degrees Period: 99 Minutes Repeat_Cycle: 16 Days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-04-17 Online_Resource: https://cloudsat.atmos.colostate.edu/ Online_Resource: https://www.nasa.gov/mission_pages/cloudsat/main/index.html Sample_Image: https://www.nasa.gov/images/content/126766main_cloudsat-clouds-330.jpg Group: Platform_Logistics Launch_Date: 2006-04-28 Launch_Site: VANDENBERG AIR FORCE BASE, USA Design_Life: 22 months Primary_Sponsor: USA/NASA Primary_Sponsor: CANADA/CSA Primary_Sponsor: USA/DOD/USAF Primary_Sponsor: USA/DOE End_Group End_Group); 2018-03-13 18:15:08.0 [sritz] insert AltLabel (id: null category: null text: CLOUDSAT language code: en); update PrefLabel (CloudSat); update Definition ([Source: NASA Science Missions Home Page] CloudSat uses advanced radar to "slice" through clouds to see their vertical structure, providing a completely new observational capability from space. Earlier satellites could only image the uppermost layers of clouds. CloudSat is among the first satellites to study clouds on a global basis. It will look at their structure, composition and effects. This is a cooperative mission with Canada. CloudSat measurements have applications in air quality, weather models, water management, aviation safety, and disaster management. The key observations are the vertical profiles of cloud liquid water and ice water contents and related cloud physical and radiative properties. The spacecraft payload consists of a millimeter-wave radar. CloudSat will fly in tight formation with the CALIPSO satellite carrying a backscattering lidar, and these two satellites will follow behind the Aqua satellite in a somewhat looser formation. The combination of data from the CloudSat radar with coincident measurements from CALIPSO and Aqua provides a rich source of information that can be used to assess the role of clouds in both weather and climate. CloudSat was launched on 2006-04-28 from Vandenberg AFB, California Group: Platform_Details Entry_ID: CLOUDSAT Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: EOS (Earth Observing System) Short_Name: CLOUDSAT End_Group Group: Synonymous_Platform_Names Short_Name: CLOUDSAT End_Group Group: Platform_Associated_Instruments Short_Name: CLOUDSAT-CPR End_Group Group: Orbit Orbit_Altitude: 705 km Orbit_Inclination: 98.2 Degrees Period: 99 Minutes Repeat_Cycle: 16 Days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-04-17 Online_Resource: https://cloudsat.atmos.colostate.edu/ Online_Resource: https://www.nasa.gov/mission_pages/cloudsat/main/index.html Sample_Image: https://www.nasa.gov/images/content/126766main_cloudsat-clouds-330.jpg Group: Platform_Logistics Launch_Date: 2006-04-28 Launch_Site: VANDENBERG AIR FORCE BASE, USA Design_Life: 22 months Primary_Sponsor: USA/NASA Primary_Sponsor: CANADA/CSA Primary_Sponsor: USA/DOD/USAF Primary_Sponsor: USA/DOE End_Group End_Group); 2018-03-12 18:50:17.0 [sritz] update Definition ([Source: NASA Science Missions Home Page, http://nasascience.nasa.gov/missions/cloudsat ] CloudSat uses advanced radar to "slice" through clouds to see their vertical structure, providing a completely new observational capability from space. Earlier satellites could only image the uppermost layers of clouds. CloudSat is among the first satellites to study clouds on a global basis. It will look at their structure, composition and effects. This is a cooperative mission with Canada. CloudSat measurements have applications in air quality, weather models, water management, aviation safety, and disaster management. The key observations are the vertical profiles of cloud liquid water and ice water contents and related cloud physical and radiative properties. The spacecraft payload consists of a millimeter-wave radar. CloudSat will fly in tight formation with the CALIPSO satellite carrying a backscattering lidar, and these two satellites will follow behind the Aqua satellite in a somewhat looser formation. The combination of data from the CloudSat radar with coincident measurements from CALIPSO and Aqua provides a rich source of information that can be used to assess the role of clouds in both weather and climate. CloudSat was launched on 2006-04-28 from Vandenberg AFB, California Group: Platform_Details Entry_ID: CLOUDSAT Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: EOS (Earth Observing System) Short_Name: CLOUDSAT End_Group Group: Synonymous_Platform_Names Short_Name: CLOUDSAT End_Group Group: Platform_Associated_Instruments Short_Name: CLOUDSAT-CPR End_Group Group: Orbit Orbit_Altitude: 705 km Orbit_Inclination: 98.2 Degrees Period: 99 Minutes Repeat_Cycle: 16 Days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-04-17 Online_Resource: https://cloudsat.atmos.colostate.edu/ Online_Resource: https://www.nasa.gov/mission_pages/cloudsat/main/index.html Sample_Image: https://www.nasa.gov/images/content/126766main_cloudsat-clouds-330.jpg Group: Platform_Logistics Launch_Date: 2006-04-28 Launch_Site: VANDENBERG AIR FORCE BASE, USA Design_Life: 22 months Primary_Sponsor: USA/NASA Primary_Sponsor: CANADA/CSA Primary_Sponsor: USA/DOD/USAF Primary_Sponsor: USA/DOE End_Group End_Group); update Resource (image); update Resource (https://www.nasa.gov/images/content/126766main_cloudsat-clouds-330.jpg); SAC-A [Source: NASA National Space Science Data Center, http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1998-069B ] Satellite de Aplicaciones Cientifico-A (SAC-A) was a small non-recoverable satellite built by the Argentinean National Commission of Space Activities (CoNAE). The satellite will test and characterize the performance of new equipment and technologies which may be used in future operational or scientific missions. The satellite payload included a Differential Global Positioning Systems (DGPS) to provide real-time autonomous attitude measurements for the satellite, a CCD camera to perform digital space photography, Argentinean built silicon solar cells, a magnetometer to take scalar measurements of the Earth's magnetic field, and an Argentinean experiment to track endangered whale population migrations in the southern hemisphere. Group: Platform_Details Entry_ID: SAC-A Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: SAC Short_Name: SAC-A Long_Name: Satelite de Aplicaciones Cientifico - A End_Group Group: Synonymous_Platform_Names Short_Name: SAC-A End_Group Group: Platform_Associated_Instruments Short_Name: CCD IMAGER End_Group Group: Orbit Orbit_Inclination: 51.6 deg Period: 92.3 min Perigee: 378 km Apogee: 395 km End_Group Creation_Date: 2007-11-13 Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1998-069B Sample_Image: http://space.skyrocket.de/img_sat/sac-a__1.jpg Group: Platform_Logistics Launch_Date: 1998-12-14 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: Argentina./CoNAE End_Group End_Group RAE-A The RAE-1 spacecraft measured the intensity of celestial radio sources, particularly the sun, as a function of time, direction, and frequency (0.2 to 20 MHz). The spacecraft was gravity gradient oriented. The spacecraft weight was 193 kg, and average power consumption was 25 W. It carried two 750-ft-long V-antennas, one facing toward the earth and one facing away from the earth. A 120-ft-long dipole antenna was oriented tangentially with respect to the earth's surface. The spacecraft was also equipped with one 136-MHz telemetry turnstile. The onboard experiments consisted of four step-frequency Ryle-Vonberg radiometers operating from 0.45 to 9.18 MHz, two multichannel total power radiometers operating from 0.2 to 5.4 MHz, one step frequency V-antenna impedance probe operating from 0.24 to 7.86 MHz, and one dipole antenna capacitance probe operating from 0.25 to 2.2 MHz. RAE-1 was designed for a 1-year minimum operating lifetime. The spaecraft tape recorder performance began to deteriorate after 2 months in orbit. In spite of several cases of instrument malfunction, good data were obtained on all three antenna systems. For more details, see R. R. Weber, J. K. Alexander, and R. G. Stone, Radio Sci., v. 6, p. 1085, 1971. - Auxiliary Information - Launch Date and Time : 1968-07-04 17:31:00 Epoch Date and Time : 1968-07-07 Apogee (km or AU): 5861. Perigee (km or AU): 5851. Inclination (degree) : 120.6 Orbit Type : Geocentric Information last updated on 1992-03-09 Group: Platform_Details Entry_ID: RAE-A Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Platform_Series_or_Entity: RAE (Radio Astronomy Explorer) Short_Name: RAE-A Long_Name: Radio Astronomy Explorer-A End_Group Group: Synonymous_Platform_Names Short_Name: Explorer 38 End_Group Group: Orbit Orbit_Inclination: 120.6 Perigee: 5851 Apogee: 5861 End_Group Creation_Date: 2008-01-02 Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/masterCatalog.do?sc=1968-055A Sample_Image: http://www.astronautix.com/graphics/r/rae.jpg Group: Platform_Logistics Launch_Date: 1968-07-04 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: NASA End_Group End_Group G-LiHT Goddard’s Lidar, Hyperspectral and Thermal (G-LiHT) airborne imaging system simultaneously maps the composition, structure, and function of terrestrial ecosystems. The G-LiHT platform is comprised of Light Ranging and Detection (LiDAR), visible and near-infrared (VNIR) imaging spectroscopy, and broad band thermal instruments. Additional Information: https://gliht.gsfc.nasa.gov 2019-10-07 16:51:31.0 [sritz] insert Definition (id: null text: Goddard’s Lidar, Hyperspectral and Thermal (G-LiHT) airborne imaging system simultaneously maps the composition, structure, and function of terrestrial ecosystems. The G-LiHT platform is comprised of Light Ranging and Detection (LiDAR), visible and near-infrared (VNIR) imaging spectroscopy, and broad band thermal instruments. Additional Information: https://gliht.gsfc.nasa.gov language code: en); 2019-10-07 16:50:24.0 [sritz] insert AltLabel (id: null category: primary text: Goddard’s LiDAR, Hyperspectral and Thermal (G-LiHT) airborne imaging system language code: en); 2019-10-07 16:49:50.0 [sritz] Insert Concept add broader relation (G-LiHT [f4dbe34b-a93e-439f-bdbb-4167c833aba6,369229] - Aircraft [227d9c3d-f631-402d-84ed-b8c5a562fc27,344663]); PIONEER 6 Pioneer 6 was the first of four NASA spacecraft designed to study interplanetary phenomena in space. The spacecraft successfully provided simultaneous scientific measurements at widely dispersed locations in heliocentric orbit. It returned the first data on the tenuous solar atmosphere and later recorded the passage of Comet Kohoutek's tail in 1974. Along with Pioneers 7, 8, and 9, the spacecraft formed a ring of solar weather stations spaced along Earth's orbit. Measurements by the four Pioneers were used to predict solar storms for approximately 1,000 primary users, including the Federal Aviation Administration; commercial airlines; power companies; communication companies; military organizations; and entities involved in surveying, navigation, and electronic prospecting. By December 1990, Pioneer 6 had circled the Sun twentynine times (traveling 24.8 billion kilometers) and had been operational for twenty years -- a record for a deep space probe. Its original slated lifetime had been only six months. On 15 December 1996, the spacecraft's primary transmitter failed, but during a track on 11 July 1996, ground controllers switched on the backup transmitter. Of the spacecraft's six scientific instruments, two (the plasma analyzer and the cosmic-ray detector) still continue to function. NASA maintains contact with the spacecraft once or twice each year. For example, 1 hour's worth of scientific data was collected on 29 July and 15 December 1995 (although the primary transmitter failed soon after that), and again on 6 October 1997, more than thirty years after launch. The probe's solar arrays continue to deteriorate, although the transmitters can be turned on at perihelion when the solar flux is strong enough to provide sufficient power. On 8 December 2000, to commemorate its thirty-fifth anniversary of operation, ground controllers established successful contact with the spacecraft for about 2 hours. Information provided by http://solarsystem.nasa.gov/missions/profile.cfm?Sort=Alpha&Alias=Pioneer%206&Letter=P&Display=ReadMore Group: Platform_Details Entry_ID: PIONEER 6 Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Short_Name: PIONEER 6 End_Group Group: Platform_Associated_Instruments Short_Name: WAVES Short_Name: MUON COSMIC RAY DETECTORS Short_Name: PROBES Short_Name: FLUXGATE MAGNETOMETERS End_Group Creation_Date: 2007-08-20 Online_Resource: http://solarsystem.nasa.gov/missions/profile.cfm?Sort=Alpha&Alias=Pioneer%206&Letter=P&Display=ReadMore Sample_Image: http://solarsystem.nasa.gov/missions/images/miss-pioneer_06.gif Group: Platform_Logistics Launch_Date: 1965-12-16 Design_Life: 6 months Primary_Sponsor: NASA End_Group End_Group CHAMP CHAMP will generate for the first time simultaneously highly precise gravity and magnetic field measurements over a 5 years period. This will allow us to detect besides the spatial variations of both fields also their variability with time. The CHAMP mission will open a new era in geopotential research and will become a significant contributor to the Decade of Geopotentials. It will perform the following three tasks: 1) Mapping of the Earth's global long to medium wavelength gravity field and temporal variations with applications in the geophysics, geodesy and oceanography; 2) Mapping of the Earth's global magnetic field and temporal variations with applications in geophysics and solar terrestrial physics; 3) Atmosphere/ionosphere sounding with applications in global climate studies, weather forecasting, disaster research and navigation. CHAMP-derived data will serve as an ideal basis for a further refinement of modern satellite surveying methods and constructing digital terrain models covering large land and ice areas for remote sensing applications and for cartography. The evaluation of all three kinds of signals CHAMP will be observing will allow a complete and integrated modeling of the structure and dynamics of the Earth core and mantle. Such an improvement will strongly enhance studies concerning the structure and composition of the Earth's interior and will open new insights and application areas in geodesy, solid Earth physics and oceanography. Launch: Launched: July 15, 2000 Launch Site: Plesetzk, Russia Orbit: Altitude: 450 km and circular Inclination: 87.27 Period: 94 minutes Non-Sun-Synchronous Vital Statistics: Weight: 500 kg Power: 167 watts Design Life: 5 years Instruments: LRR (Laser Retro Reflector) OVM (Overhauser Magnetometer) and the FGM (Fluxgate Magnetometer) DIDM (Digital Ion Drift Meter) ACC (Accelerometer) GPS (Global Positioning System) Receiver CHAMP home Page: http://op.gfz-potsdam.de/champ/ [Summary provided by NASA.] Group: Platform_Details Entry_ID: CHAMP Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: CHAMP Long_Name: Challenging Minisatellite Payload End_Group Group: Synonymous_Platform_Names Short_Name: CHAMP End_Group Group: Platform_Associated_Instruments Short_Name: CHAMP-BLACKJACK Short_Name: MAGNETOMETERS Short_Name: FLUXGATE MAGNETOMETERS Short_Name: DIDM Short_Name: ACCELEROMETERS Short_Name: GPS End_Group Group: Orbit Orbit_Altitude: 450 km Orbit_Inclination: 87.27 Period: 94 min Orbit_Type: LEO > Low Earth Orbit > Polar Non-Sun-Synchronous End_Group Creation_Date: 2007-09-24 Online_Resource: http://op.gfz-potsdam.de/champ/ Online_Resource: http://science.nasa.gov/missions/champ/ Online_Resource: http://eospso.gsfc.nasa.gov/eos_homepage/mission_profiles/show_mission.php?id=66 Sample_Image: http://www.gfz-potsdam.de/pb1/op/champ/media_CHAMP/champ_startconf.jpg Group: Platform_Logistics Launch_Date: 2000-07-15 Launch_Site: Plesetsk Cosmodrome, Russia Primary_Sponsor: Germany/GFZ Primary_Sponsor: USA/NASA End_Group End_Group RSTN The Radio Solar Telescope Network (RSTN) is a network of solar observatories maintained and operated by the U.S. Air Force Weather Agency. The RSTN consists of ground-based observatories in Australia, Italy, Massachusetts, New Mexico and Hawaii. [Source: Wikipedia, http://en.wikipedia.org/wiki/Radio_Solar_Telescope_Network ] Group: Platform_Details Entry_ID: RSTN Group: Platform_Identification Platform_Category: In Situ Land-based Platforms Platform_Series_or_Entity: SOLAR/SPACE MONITORING STATIONS Short_Name: RSTN Long_Name: Radio Solar Telescope Network End_Group Creation_Date: 2012-04-20 Online_Resource: http://en.wikipedia.org/wiki/Radio_Solar_Telescope_Network End_Group AE-C 06977 Atmosphere Explorer-C Explorer 51 PL-721C S 6C The Atmospheric Explorer-C (AE-C) spacecraft (designation: 06977 / 73101A ) was designed as a multi- sided polyhedron shaped frame with a mean diameter of 1.4 meter. AE-C weighed about 660 kg which included 85 kg of scientific instrumentation. AE-C was launched on 1973-12-16 and decayed on 1978-12-12. The purpose of the AE-C mission was to investigate the uppermost layer of the earth's atmosphere, the thermosphere, with emphasis on energy transfer and other controlling processes. Photochemical processes related to the absorption of solar UV radiation were studied by making coordinated measurements of reacting constituents and the solar input. The payload included instrumentation to measure: Solar UV Fluxes, the Composition of Positive Ions and Neutral Particles, the Density and Temperature of neutral particles, positive ions and electrons, Atmospheric airglow emissions, Photoelectron Energy Spectra, and Proton and Electron Fluxes with particle energy up to 25 keV. The initial elliptical orbit of AE-C was altered many times in the first year of operations by means of an onboard propulsion system employing a 3.5-lb thruster. PERIGEE CHANGES: The purpose of these changes was first to alter the perigee height to 129 km. Later the AE-C orbit was circularized and the perigee height was raised periodically, eventually to about 390 km height. By the natural drag action of the exosphere the orbit was then let to decay to 250 km perigee altitude. LATITUDE COVERAGE: During the first year, the latitude of perigee moved from about 10 degrees north up to 68 degrees north and then down to about 60 degrees south. LOCAL TIME COVERAGE: During this period of orbit modification about two cycles through all local times were completed. OPERATIONAL MODES: The spacecraft could be operated in either of two modes: spinning at a nominal 4 rpm or despun to 1 revolution per orbit. The spin axis was perpendicular to the orbit plane. Power was supplied by a solar cell array. The spacecraft used a PCM telemetry data system that operated in real time or using an onboard tape recorder. More Information: https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1973-101A [Summary provided by NASA.] Group: Platform_Details Entry_ID: AE-C Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: AE (Atmosphere Explorer) Short_Name: AE-C Long_Name: Atmosphere Explorer C (Explorer 51) End_Group Group: Synonymous_Platform_Names Short_Name: Explorer 51 Short_Name: 06977 End_Group Group: Platform_Associated_Instruments Short_Name: SPECTROMETERS End_Group Group: Orbit Orbit_Inclination: 68.1 degrees Period: 132.3 minutes Perigee: 390 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-08-22 Online_Resource: https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1973-101A Sample_Image: https://library01.gsfc.nasa.gov/gdprojs/images/explorer_51.jpg Group: Platform_Logistics Launch_Date: 1973-12-16 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: NASA End_Group End_Group 2019-09-17 21:37:34.0 [sritz] insert AltLabel (id: null category: null text: PL-721C language code: en); insert AltLabel (id: null category: null text: Atmosphere Explorer-C language code: en); insert AltLabel (id: null category: null text: Explorer 51 language code: en); insert AltLabel (id: null category: null text: S 6C language code: en); insert AltLabel (id: null category: null text: 06977 language code: en); 2019-09-17 21:35:57.0 [sritz] update Definition (The Atmospheric Explorer-C (AE-C) spacecraft (designation: 06977 / 73101A ) was designed as a multi- sided polyhedron shaped frame with a mean diameter of 1.4 meter. AE-C weighed about 660 kg which included 85 kg of scientific instrumentation. AE-C was launched on 1973-12-16 and decayed on 1978-12-12. The purpose of the AE-C mission was to investigate the uppermost layer of the earth's atmosphere, the thermosphere, with emphasis on energy transfer and other controlling processes. Photochemical processes related to the absorption of solar UV radiation were studied by making coordinated measurements of reacting constituents and the solar input. The payload included instrumentation to measure: Solar UV Fluxes, the Composition of Positive Ions and Neutral Particles, the Density and Temperature of neutral particles, positive ions and electrons, Atmospheric airglow emissions, Photoelectron Energy Spectra, and Proton and Electron Fluxes with particle energy up to 25 keV. The initial elliptical orbit of AE-C was altered many times in the first year of operations by means of an onboard propulsion system employing a 3.5-lb thruster. PERIGEE CHANGES: The purpose of these changes was first to alter the perigee height to 129 km. Later the AE-C orbit was circularized and the perigee height was raised periodically, eventually to about 390 km height. By the natural drag action of the exosphere the orbit was then let to decay to 250 km perigee altitude. LATITUDE COVERAGE: During the first year, the latitude of perigee moved from about 10 degrees north up to 68 degrees north and then down to about 60 degrees south. LOCAL TIME COVERAGE: During this period of orbit modification about two cycles through all local times were completed. OPERATIONAL MODES: The spacecraft could be operated in either of two modes: spinning at a nominal 4 rpm or despun to 1 revolution per orbit. The spin axis was perpendicular to the orbit plane. Power was supplied by a solar cell array. The spacecraft used a PCM telemetry data system that operated in real time or using an onboard tape recorder. More Information: https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1973-101A [Summary provided by NASA.] Group: Platform_Details Entry_ID: AE-C Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: AE (Atmosphere Explorer) Short_Name: AE-C Long_Name: Atmosphere Explorer C (Explorer 51) End_Group Group: Synonymous_Platform_Names Short_Name: Explorer 51 Short_Name: 06977 End_Group Group: Platform_Associated_Instruments Short_Name: SPECTROMETERS End_Group Group: Orbit Orbit_Inclination: 68.1 degrees Period: 132.3 minutes Perigee: 390 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-08-22 Online_Resource: https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1973-101A Sample_Image: https://library01.gsfc.nasa.gov/gdprojs/images/explorer_51.jpg Group: Platform_Logistics Launch_Date: 1973-12-16 Launch_Site: Cape Canaveral/Kennedy Space Center, USA Primary_Sponsor: NASA End_Group End_Group); 2019-09-17 21:34:20.0 [sritz] update Resource (image); update Resource (https://library01.gsfc.nasa.gov/gdprojs/images/explorer_51.jpg); GRACE-FO [Source: GRACE-FO Home Page, https://gracefo.jpl.nasa.gov/ ] The Gravity Recovery and Climate Experiment Follow-on (GRACE-FO) mission is a partnership between NASA and the German Research Centre for Geosciences (GFZ). GRACE-FO is a successor to the original GRACE mission, which began orbiting Earth on March 17, 2002. GRACE-FO will carry on the extremely successful work of its predecessor while testing a new technology designed to dramatically improve the already remarkable precision of its measurement system. GRACE-FO, launched in May 2018, will continue the work of tracking Earth's water movement to monitor changes in underground water storage, the amount of water in large lakes and rivers, soil moisture, ice sheets and glaciers, and sea level caused by the addition of water to the ocean. These discoveries provide a unique view of Earth's climate and have far-reaching benefits to society and the world's population. More Information: https://gracefo.jpl.nasa.gov/ Group: Platform_Details Entry_ID: GRACE II Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NASA Decadal Survey Short_Name: GRACE-FO Long_Name: Gravity Recovery and Climate Experiment Follow On End_Group Group: Orbit Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2010-05-07 Online_Resource: https://gracefo.jpl.nasa.gov/ Sample_Image: Group: Platform_Logistics Primary_Sponsor: USA/NASA End_Group End_Group 2019-09-12 20:02:34.0 [sritz] update AltLabel (outdated); insert AltLabel (id: null category: primary text: Gravity Recovery and Climate Experiment Follow-On language code: en); 2019-09-11 15:59:25.0 [sritz] update WeightedRelation (Platform-Instrument); update WeightedRelation (1.0); update WeightedRelation (Platform-Instrument); update WeightedRelation (1.0); update WeightedRelation (Platform-Instrument); update WeightedRelation (1.0); 2019-09-11 15:57:34.0 [sritz] insert WeightedRelation (id: null related concept uuid: 9cf060b8-d8ea-46c4-a8de-f2073df5d0ae relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: f6ae33f3-f492-4f32-9526-a7e289d542e7 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: cf6b8783-02c7-4aae-9c46-08468a6c61c8 relationship type: null relationship value: null generated by: null); 2018-06-04 16:59:27.0 [sritz] update Definition ([Source: GRACE-FO Home Page, https://gracefo.jpl.nasa.gov/ ] The Gravity Recovery and Climate Experiment Follow-on (GRACE-FO) mission is a partnership between NASA and the German Research Centre for Geosciences (GFZ). GRACE-FO is a successor to the original GRACE mission, which began orbiting Earth on March 17, 2002. GRACE-FO will carry on the extremely successful work of its predecessor while testing a new technology designed to dramatically improve the already remarkable precision of its measurement system. GRACE-FO, launched in May 2018, will continue the work of tracking Earth's water movement to monitor changes in underground water storage, the amount of water in large lakes and rivers, soil moisture, ice sheets and glaciers, and sea level caused by the addition of water to the ocean. These discoveries provide a unique view of Earth's climate and have far-reaching benefits to society and the world's population. More Information: https://gracefo.jpl.nasa.gov/ Group: Platform_Details Entry_ID: GRACE II Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NASA Decadal Survey Short_Name: GRACE-FO Long_Name: Gravity Recovery and Climate Experiment Follow On End_Group Group: Orbit Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2010-05-07 Online_Resource: https://gracefo.jpl.nasa.gov/ Sample_Image: Group: Platform_Logistics Primary_Sponsor: USA/NASA End_Group End_Group); 2018-06-04 16:58:57.0 [sritz] update Definition ([Source: GRACE-FO Home Page, https://gracefo.jpl.nasa.gov/ ] The Gravity Recovery and Climate Experiment Follow-on (GRACE-FO) mission is a partnership between NASA and the German Research Centre for Geosciences (GFZ). GRACE-FO is a successor to the original GRACE mission, which began orbiting Earth on March 17, 2002. GRACE-FO will carry on the extremely successful work of its predecessor while testing a new technology designed to dramatically improve the already remarkable precision of its measurement system. GRACE-FO, launch in May 2018, will continue the work of tracking Earth's water movement to monitor changes in underground water storage, the amount of water in large lakes and rivers, soil moisture, ice sheets and glaciers, and sea level caused by the addition of water to the ocean. These discoveries provide a unique view of Earth's climate and have far-reaching benefits to society and the world's population. More Information: https://gracefo.jpl.nasa.gov/ Group: Platform_Details Entry_ID: GRACE II Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NASA Decadal Survey Short_Name: GRACE-FO Long_Name: Gravity Recovery and Climate Experiment Follow On End_Group Group: Orbit Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2010-05-07 Online_Resource: https://gracefo.jpl.nasa.gov/ Sample_Image: Group: Platform_Logistics Primary_Sponsor: USA/NASA End_Group End_Group); 2018-03-14 18:48:35.0 [sritz] update Definition ([Source: GRACE-FO Home Page, https://gracefo.jpl.nasa.gov/ ] The Gravity Recovery and Climate Experiment Follow-on (GRACE-FO) mission is a partnership between NASA and the German Research Centre for Geosciences (GFZ). GRACE-FO is a successor to the original GRACE mission, which began orbiting Earth on March 17, 2002. GRACE-FO will carry on the extremely successful work of its predecessor while testing a new technology designed to dramatically improve the already remarkable precision of its measurement system. GRACE-FO, scheduled for launch in early 2018, will continue the work of tracking Earth's water movement to monitor changes in underground water storage, the amount of water in large lakes and rivers, soil moisture, ice sheets and glaciers, and sea level caused by the addition of water to the ocean. These discoveries provide a unique view of Earth's climate and have far-reaching benefits to society and the world's population. More Information: https://gracefo.jpl.nasa.gov/ Group: Platform_Details Entry_ID: GRACE II Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NASA Decadal Survey Short_Name: GRACE II Long_Name: Gravity Recovery and Climate Experiment II End_Group Group: Orbit Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2010-05-07 Online_Resource: https://gracefo.jpl.nasa.gov/ Sample_Image: Group: Platform_Logistics Primary_Sponsor: USA/NASA End_Group End_Group); 2018-03-14 18:35:46.0 [sritz] update Definition ([Source: NASA Earth Science Decadal Survey Studies, http://decadal.gsfc.nasa.gov/grace2.html ] The Gravity Recovery and Climate Experiment Follow-on (GRACE-FO) mission is a partnership between NASA and the German Research Centre for Geosciences (GFZ). GRACE-FO is a successor to the original GRACE mission, which began orbiting Earth on March 17, 2002. GRACE-FO will carry on the extremely successful work of its predecessor while testing a new technology designed to dramatically improve the already remarkable precision of its measurement system. GRACE-FO, scheduled for launch in early 2018, will continue the work of tracking Earth's water movement to monitor changes in underground water storage, the amount of water in large lakes and rivers, soil moisture, ice sheets and glaciers, and sea level caused by the addition of water to the ocean. These discoveries provide a unique view of Earth's climate and have far-reaching benefits to society and the world's population. More Information: https://gracefo.jpl.nasa.gov/ Group: Platform_Details Entry_ID: GRACE II Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NASA Decadal Survey Short_Name: GRACE II Long_Name: Gravity Recovery and Climate Experiment II End_Group Group: Orbit Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2010-05-07 Online_Resource: https://gracefo.jpl.nasa.gov/ Sample_Image: Group: Platform_Logistics Primary_Sponsor: USA/NASA End_Group End_Group); delete Resource (null); 2018-03-14 18:33:13.0 [sritz] update AltLabel (outdated); insert AltLabel (id: null category: primary text: The Gravity Recovery and Climate Experiment Follow-on language code: en); 2018-03-14 18:24:53.0 [sritz] insert AltLabel (id: null category: outdated text: GRACE-II language code: en); update PrefLabel (GRACE-FO); update Resource (image); JERS R/V AMA NOAA-1 NOAA-1 (ITOS-1) was launched in December 1970 and the primary objective of the sun-synchronous meteorological satellite was to provide improved operational infrared and visual observations of earth cloud cover for use in weather analysis and forecasting. Secondary objectives included providing solar proton and global heat balance data on a regular daily basis. The nearly cubical spacecraft measured 1 by 1 by 1.2 m. The TV cameras and infrared sensors were mounted on the satellite baseplate with their optical axes directed vertically earthward. The spacecraft was equipped with three curved solar panels that were folded during launch and deployed after orbit was achieved. Each panel measured over 4.2 m in length when unfolded and was covered with 3420 solar cells, each measuring 2 by 2 cm. The attitude control system maintained desired spacecraft orientation through gyroscopic principles incorporated into the satellite design. Earth orientation of the satellite body was maintained by taking advantage of the precession induced from a momentum flywheel so that the satellite body precession rate of one revolution per orbit provided the desired 'earth looking' attitude. Minor adjustments in attitude and orientation were made by means of magnetic coils and by varying the speed of the momentum flywheel. This spacecraft carried four cameras; two television cameras for Automatic Picture Transmission (APT), and two Advanced Vidicon Camera System (AVCS) cameras. The satellite also carried a low-resolution flat plate radiometer, a solar proton monitor, and two scanning radiometers that not only measured emitted IR radiation but also served as a backup system for the onboard cameras. Launched into a near-polar orbit, the spacecraft and its subsystems performed normally until May 29, 1971 when the incremental tape recorder failed, resulting in partial loss of solar proton data and total loss of flat plate radiometer data. The APT and Direct Readout Infrared (DRIR) subsystems were turned off on June 20, 1971 in an attempt to reduce the above normal temperature due to overheating in the attitude control system. The AVCS was turned off shortly thereafter, and the scanning radiometer continued partial operations until the spacecraft was deactivated on August 19, 1971. For more information about NOAA-1: https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1970-106A __________ Taken from the NSSDC System for Information Retrieval and Storage (SIRS). For more information contact the NSSDC Coordinated Request and User Support Office, 301-286-6695 (NASA Goddard Space Flight Center, Code 933.4, Greenbelt, Maryland 20771, USA, https://nssdca.gsfc.nasa.gov/). Group: Platform_Details Entry_ID: NOAA-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NOAA POES (Polar Orbiting Environmental Satellites) Short_Name: NOAA-1 Long_Name: National Oceanic & Atmospheric Administration-1 End_Group Group: Synonymous_Platform_Names Short_Name: ITOS-A End_Group Creation_Date: 2007-10-17 Online_Resource: https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1970-106A Group: Platform_Logistics Launch_Date: 1970-12-11 Primary_Sponsor: NASA End_Group End_Group 2019-11-22 22:46:07.0 [sritz] update Definition (NOAA-1 (ITOS-1) was launched in December 1970 and the primary objective of the sun-synchronous meteorological satellite was to provide improved operational infrared and visual observations of earth cloud cover for use in weather analysis and forecasting. Secondary objectives included providing solar proton and global heat balance data on a regular daily basis. The nearly cubical spacecraft measured 1 by 1 by 1.2 m. The TV cameras and infrared sensors were mounted on the satellite baseplate with their optical axes directed vertically earthward. The spacecraft was equipped with three curved solar panels that were folded during launch and deployed after orbit was achieved. Each panel measured over 4.2 m in length when unfolded and was covered with 3420 solar cells, each measuring 2 by 2 cm. The attitude control system maintained desired spacecraft orientation through gyroscopic principles incorporated into the satellite design. Earth orientation of the satellite body was maintained by taking advantage of the precession induced from a momentum flywheel so that the satellite body precession rate of one revolution per orbit provided the desired 'earth looking' attitude. Minor adjustments in attitude and orientation were made by means of magnetic coils and by varying the speed of the momentum flywheel. This spacecraft carried four cameras; two television cameras for Automatic Picture Transmission (APT), and two Advanced Vidicon Camera System (AVCS) cameras. The satellite also carried a low-resolution flat plate radiometer, a solar proton monitor, and two scanning radiometers that not only measured emitted IR radiation but also served as a backup system for the onboard cameras. Launched into a near-polar orbit, the spacecraft and its subsystems performed normally until May 29, 1971 when the incremental tape recorder failed, resulting in partial loss of solar proton data and total loss of flat plate radiometer data. The APT and Direct Readout Infrared (DRIR) subsystems were turned off on June 20, 1971 in an attempt to reduce the above normal temperature due to overheating in the attitude control system. The AVCS was turned off shortly thereafter, and the scanning radiometer continued partial operations until the spacecraft was deactivated on August 19, 1971. For more information about NOAA-1: https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1970-106A __________ Taken from the NSSDC System for Information Retrieval and Storage (SIRS). For more information contact the NSSDC Coordinated Request and User Support Office, 301-286-6695 (NASA Goddard Space Flight Center, Code 933.4, Greenbelt, Maryland 20771, USA, https://nssdca.gsfc.nasa.gov/). Group: Platform_Details Entry_ID: NOAA-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NOAA POES (Polar Orbiting Environmental Satellites) Short_Name: NOAA-1 Long_Name: National Oceanic & Atmospheric Administration-1 End_Group Group: Synonymous_Platform_Names Short_Name: ITOS-A End_Group Creation_Date: 2007-10-17 Online_Resource: https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1970-106A Group: Platform_Logistics Launch_Date: 1970-12-11 Primary_Sponsor: NASA End_Group End_Group); 2019-11-22 22:23:58.0 [sritz] update Definition (NOAA-1 (ITOS-1) was launched in December 1970 and the primary objective of the sun-synchronous meteorological satellite was to provide improved operational infrared and visual observations of earth cloud cover for use in weather analysis and forecasting. Secondary objectives included providing solar proton and global heat balance data on a regular daily basis. The nearly cubical spacecraft measured 1 by 1 by 1.2 m. The TV cameras and infrared sensors were mounted on the satellite baseplate with their optical axes directed vertically earthward. The spacecraft was equipped with three curved solar panels that were folded during launch and deployed after orbit was achieved. Each panel measured over 4.2 m in length when unfolded and was covered with 3420 solar cells, each measuring 2 by 2 cm. The attitude control system maintained desired spacecraft orientation through gyroscopic principles incorporated into the satellite design. Earth orientation of the satellite body was maintained by taking advantage of the precession induced from a momentum flywheel so that the satellite body precession rate of one revolution per orbit provided the desired 'earth looking' attitude. Minor adjustments in attitude and orientation were made by means of magnetic coils and by varying the speed of the momentum flywheel. This spacecraft carried four cameras; two television cameras for Automatic Picture Transmission (APT), and two Advanced Vidicon Camera System (AVCS) cameras. The satellite also carried a low-resolution flat plate radiometer, a solar proton monitor, and two scanning radiometers that not only measured emitted IR radiation but also served as a backup system for the onboard cameras. Launched into a near-polar orbit, the spacecraft and its subsystems performed normally until May 29, 1971 when the incremental tape recorder failed, resulting in partial loss of solar proton data and total loss of flat plate radiometer data. The APT and Direct Readout Infrared (DRIR) subsystems were turned off on June 20, 1971 in an attempt to reduce the above normal temperature due to overheating in the attitude control system. The AVCS was turned off shortly thereafter, and the scanning radiometer continued partial operations until the spacecraft was deactivated on August 19, 1971. For more information about the NOAA satellite series link to the URL: https://www.noaa.gov/satellites __________ Taken from the NSSDC System for Information Retrieval and Storage (SIRS). For more information contact the NSSDC Coordinated Request and User Support Office, 301-286-6695 (NASA Goddard Space Flight Center, Code 933.4, Greenbelt, Maryland 20771, USA, https://nssdca.gsfc.nasa.gov/). Group: Platform_Details Entry_ID: NOAA-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NOAA POES (Polar Orbiting Environmental Satellites) Short_Name: NOAA-1 Long_Name: National Oceanic & Atmospheric Administration-1 End_Group Group: Synonymous_Platform_Names Short_Name: ITOS-A End_Group Creation_Date: 2007-10-17 Online_Resource: https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1970-106A Group: Platform_Logistics Launch_Date: 1970-12-11 Primary_Sponsor: NASA End_Group End_Group); delete Resource (null); MOS (Japan Marine Observation Satellite) GOES-1 GOES-1 (SMS-C) was launched in October 1975 and was a NASA-developed, NOAA-operated, geosynchronous, and operational spacecraft. The cylindrically shaped spacecraft measured 190.5 cm in diameter and 230 cm in length, exclusive of a magnetometer that extended an additional 83 cm beyond the cylinder shell. The primary structural members were a honeycombed equipment shelf and thrust tube. The VISSR telescope was mounted on the equipment shelf and viewed the Earth through a special aperture in the side of the spacecraft. A support structure extended radially from the thrust tube and was affixed to the solar panels, which formed the outer walls of the spacecraft and provided the primary source of electrical power. Located in the annulus-shaped space between the thrust tube and the solar panels were stationkeeping and dynamics control equipment, batteries, and most of the SEM equipment. Proper spacecraft attitude and spin rate (approximately 100 rpm) were maintained by two separate sets of jet thrusters mounted around the spacecraft equator and activated by ground command. The spacecraft used both UHF-band and S-band frequencies in its telemetry and command subsystem. A low-power VHF transponder provided telemetry and command during launch and then served as a backup for the primary subsystem once the spacecraft attained orbit. This spin-stabilized spacecraft carried a visible infrared spin-scan radiometer, meteorological data collection and relay system, space environment monitor, and a biaxial fluxgate magnetometer. On December 1, 1978, responsibility for GOES 1 was turned over to ESA to be used as part of FGGE/GARP. It was stationed over the Indian Ocean and controlled by ESOC in Darmstadt, F.R.G. In December 1979, it was returned to the control of NOAA and positioned at 135 degrees West. When GOES 5 VAS experienced a failure on July 30, 1984, GOES 6 was moved east and GOES 1 was reactivated by NOAA to provide visible imaging capability over the western U.S. GOES 1 failed on February 3, 1985. Additional Information on GOES Satellites: http://www.ospo.noaa.gov/Operations/GOES/index.html 2017-09-01 16:51:22.0 [sritz] update Definition (GOES-1 (SMS-C) was launched in October 1975 and was a NASA-developed, NOAA-operated, geosynchronous, and operational spacecraft. The cylindrically shaped spacecraft measured 190.5 cm in diameter and 230 cm in length, exclusive of a magnetometer that extended an additional 83 cm beyond the cylinder shell. The primary structural members were a honeycombed equipment shelf and thrust tube. The VISSR telescope was mounted on the equipment shelf and viewed the Earth through a special aperture in the side of the spacecraft. A support structure extended radially from the thrust tube and was affixed to the solar panels, which formed the outer walls of the spacecraft and provided the primary source of electrical power. Located in the annulus-shaped space between the thrust tube and the solar panels were stationkeeping and dynamics control equipment, batteries, and most of the SEM equipment. Proper spacecraft attitude and spin rate (approximately 100 rpm) were maintained by two separate sets of jet thrusters mounted around the spacecraft equator and activated by ground command. The spacecraft used both UHF-band and S-band frequencies in its telemetry and command subsystem. A low-power VHF transponder provided telemetry and command during launch and then served as a backup for the primary subsystem once the spacecraft attained orbit. This spin-stabilized spacecraft carried a visible infrared spin-scan radiometer, meteorological data collection and relay system, space environment monitor, and a biaxial fluxgate magnetometer. On December 1, 1978, responsibility for GOES 1 was turned over to ESA to be used as part of FGGE/GARP. It was stationed over the Indian Ocean and controlled by ESOC in Darmstadt, F.R.G. In December 1979, it was returned to the control of NOAA and positioned at 135 degrees West. When GOES 5 VAS experienced a failure on July 30, 1984, GOES 6 was moved east and GOES 1 was reactivated by NOAA to provide visible imaging capability over the western U.S. GOES 1 failed on February 3, 1985. Additional Information on GOES Satellites: http://www.ospo.noaa.gov/Operations/GOES/index.html); update Definition (https://nssdc.gsfc.nasa.gov/); 2017-09-01 16:49:46.0 [sritz] insert Definition (id: null text: Source: NASA NSSDC, https://nssdc.gsfc.nasa.gov/ ] GOES-1 (SMS-C) was launched in October 1975 and was a NASA-developed, NOAA-operated, geosynchronous, and operational spacecraft. The cylindrically shaped spacecraft measured 190.5 cm in diameter and 230 cm in length, exclusive of a magnetometer that extended an additional 83 cm beyond the cylinder shell. The primary structural members were a honeycombed equipment shelf and thrust tube. The VISSR telescope was mounted on the equipment shelf and viewed the Earth through a special aperture in the side of the spacecraft. A support structure extended radially from the thrust tube and was affixed to the solar panels, which formed the outer walls of the spacecraft and provided the primary source of electrical power. Located in the annulus-shaped space between the thrust tube and the solar panels were stationkeeping and dynamics control equipment, batteries, and most of the SEM equipment. Proper spacecraft attitude and spin rate (approximately 100 rpm) were maintained by two separate sets of jet thrusters mounted around the spacecraft equator and activated by ground command. The spacecraft used both UHF-band and S-band frequencies in its telemetry and command subsystem. A low-power VHF transponder provided telemetry and command during launch and then served as a backup for the primary subsystem once the spacecraft attained orbit. This spin-stabilized spacecraft carried a visible infrared spin-scan radiometer, meteorological data collection and relay system, space environment monitor, and a biaxial fluxgate magnetometer. On December 1, 1978, responsibility for GOES 1 was turned over to ESA to be used as part of FGGE/GARP. It was stationed over the Indian Ocean and controlled by ESOC in Darmstadt, F.R.G. In December 1979, it was returned to the control of NOAA and positioned at 135 degrees West. When GOES 5 VAS experienced a failure on July 30, 1984, GOES 6 was moved east and GOES 1 was reactivated by NOAA to provide visible imaging capability over the western U.S. GOES 1 failed on February 3, 1985. Additional Information on GOES Satellites: http://www.ospo.noaa.gov/Operations/GOES/index.html language code: en); 2017-09-01 16:36:06.0 [sritz] Insert Concept add broader relation (GOES-1 [f86fcbce-178c-410a-8e6e-380c0bc392ad,310075] - GOES [6e332c25-caeb-4917-afb6-af757bcecd72,310071]); ATLAS A series of Space Shuttle-Spacelab missions, designated the Atmospheric Laboratory for Applications and Science (ATLAS), is part of NASA's Mission to Planet Earth. The series, originally planned to acquire data throughout the Sun's 11-year active cycle, investigated how Earth's atmosphere and climate are affected by the Sun, and by the products of industrial complexes and agricultural activities. ATLAS 1, the first spacecraft in this series conducted 14 investigations in atmospheric science, solar physics, space plasma physics, and astrophysics. The 14 ATLAS 1 experiments included: (1) Atmospheric Lyman-Alpha Emissions (ALAE) (2) Atmospheric Trace Molecule Spectroscopy (ATMOS) (3) Grille Spectrometer (GRILLE) (4) Imaging Spectrometric Observatory (ISO) (5) Millimeter-wave Atmospheric Sounder (MAS) (6) Shuttle Solar Backscatter Ultraviolet Spectrometer (SSBUV-4) - technically, this instrument was seperate from the ATLAS payload and was a co-manifested payload (7) Active Cavity Radiometer Irradiance Monitor (ACRIM) (8) Solar Spectrum Measurement (SOLSPEC) (9) Solar Ultraviolet Spectral Irradiance Monitor (SUSIM) (10) Measurement of the Solar Constant (SOLCON) (11) Atmospheric Emissions Photometric Imaging (AEPI) (12) Space Experiments with Particle Accelerators (SEPAC) (13) Energetic Neutral Atom Precipitation (ENAP). ENAP was not a seperate instrument but used the ISO instrument measurements (14) Far Ultraviolet Space Telescope (FAUST) ATLAS 2 was flown on the STS-56 in April 1993 and consisted of seven of the ATLAS 1 instruments: ATMOS, MAS, SSBUV-5, ACRIM, SOLSPEC, SUSIM, AND SOLCON. ATLAS 3 was flown on the STS-66 in November 1993 and consisted of the same instruments as ATLAS 2. These investigations studied the chemical makeup of the atmosphere between approximately 15 and 600 kilometers (8.3 to 330 miles) above the Earth's surface, measured the total energy contained in sunlight and energy variations, investigated how Earth's electric and magnetic fields and atmosphere influence each other, and examined sources of ultraviolet light in the Universe. The instruments were mounted on two Spacelab pallets in the Shuttle payload bay. The Shuttle's changing orientation to Earth placed the experiments in advantageous orbiting locations, to observe the atmosphere, the Sun, and astronomical targets. Specifically, the orbiter orientation was either inertially fixed so that selected instruments were pointed at the sun, or nadir pointed for observations of the Earth's atmosphere. Crew members were in consultation with the investigators while controlling and monitoring the experiments. The atmospheric and solar instruments provided correlative measurements with the Upper Atmosphere Research Satellite (UARS). Group: Platform_Details Entry_ID: ATLAS Group: Platform_Identification Platform_Category: Space Stations/Manned Spacecraft Platform_Series_or_Entity: SPACE SHUTTLE Short_Name: ATLAS Long_Name: Atmospheric Laboratory for Applications and Science End_Group Group: Synonymous_Platform_Names Short_Name: ATLAS End_Group Creation_Date: 2008-01-24 Online_Resource: http://www.nasa.gov/audience/formedia/factsheet/Atlas-1_factsheet_prt.htm Sample_Image: http://www.ghcc.msfc.nasa.gov/images/atlas/atlaslogo.gif Group: Platform_Logistics Primary_Sponsor: USA/NASA End_Group End_Group NIMBUS King Air The Beechcraft King Air family is part of a line of twin-turboprop aircraft produced by the Beech Aircraft Corporation (now Beechcraft Division of Hawker Beechcraft). The King Air line comprises a number of models that have been divided into two families; the Model 90 and 100 series are known as King Airs, while the Model 200 and 300 series were originally marketed as Super King Airs, with "Super" being dropped by Beechcraft in 1996 (although it is still often used to differentiate the 200 and 300 series King Airs from their smaller stablemates). As of October 2007, the only small King Air in production is the conventional-tail C90GT. The King Air was the first aircraft in its class and has been in continuous production since 1964. It has outsold all of its turboprop competitors combined and is the only small twin-turboprop business aircraft in production. It now faces competition from jet aircraft such as the Beechcraft Premier I and Cessna Citation Mustang. [Photo and text provided by Wikipedia, http://en.wikipedia.org/wiki/Beechcraft_King_Air ] Group: Platform_Details Entry_ID: BEECHCRAFT KING AIR Group: Platform_Identification Platform_Category: Aircraft Short_Name: BEECHCRAFT KING AIR End_Group Creation_Date: 2008-07-14 Sample_Image: http://upload.wikimedia.org/wikipedia/commons/thumb/5/5d/C-GSYN_Adlair_Aviation_Ltd_Beechcraft_King_Air_100_%28BE10%29_03.JPG/794px-C-GSYN_Adlair_Aviation_Ltd_Beechcraft_King_Air_100_%28BE10%29_03.JPG End_Group 2017-02-10 21:55:35.0 [aaleman] updated case update AltLabel (Beechcraft King Air); update PrefLabel (King Air); 2017-01-20 20:29:19.0 [sritz] insert AltLabel (id: null text: BEECHCRAFT KING AIR language code: en); update PrefLabel (KING AIR); GOES-15 [Update 2011-12-13: GOES-15 replaced GOES-11 as the GOES-West operational spacecraft on 2011-12-06] The Geostationary Operational Environmental Satellite (GOES)-P represents a continuation of the newest generation of environmental satellites built by Boeing for the National Oceanic and Atmospheric Administration (NOAA) under the technical guidance and project management of NASA's Goddard Space Flight Center, Greenbelt, Md. GOES satellites provide the familiar weather pictures seen on United States television newscasts every day. The GOES imaging and sounding instruments (built by ITT) feature flexible scans for small-scale area viewing in regions of the visible and infrared spectrum allowing meteorologists to improve short-term forecasts. GOES provides nearly continuous imaging and sounding, which allow forecasters to better measure changes in atmospheric temperature and moisture distributions and hence increase the accuracy of their forecasts. GOES environmental information is used for a host of applications, including weather monitoring and prediction models, ocean temperatures and moisture locations, climate studies, cryosphere (ice, snow, glaciers) detection and extent, land temperatures and crop conditions, and hazards detection. The GOES-O&P Imagers have improved resolution in the 13 micrometer channel from 8 km to 4 km. The finer spatial resolution allows an improved cloud-top product, height of atmospheric motion vectors and volcanic ash detection. GOES-P continues the improved image navigation and registration, additional power and fuel lifetime capability, space weather, solar x-ray imaging, search and rescue, and communication services as provided on GOES-13. GOES-P Launches! The GOES-P satellite launched at 6:57 p.m. EST March 4 aboard a United Launch Alliance Delta IV rocket from Launch Complex 37B at Cape Canaveral Air Force Station in Florida. GOES-P is the third and final spacecraft to be launched in the GOES-N series of geostationary environmental weather satellites. 2017-09-01 17:00:38.0 [sritz] insert Definition (id: null text: [Update 2011-12-13: GOES-15 replaced GOES-11 as the GOES-West operational spacecraft on 2011-12-06] The Geostationary Operational Environmental Satellite (GOES)-P represents a continuation of the newest generation of environmental satellites built by Boeing for the National Oceanic and Atmospheric Administration (NOAA) under the technical guidance and project management of NASA's Goddard Space Flight Center, Greenbelt, Md. GOES satellites provide the familiar weather pictures seen on United States television newscasts every day. The GOES imaging and sounding instruments (built by ITT) feature flexible scans for small-scale area viewing in regions of the visible and infrared spectrum allowing meteorologists to improve short-term forecasts. GOES provides nearly continuous imaging and sounding, which allow forecasters to better measure changes in atmospheric temperature and moisture distributions and hence increase the accuracy of their forecasts. GOES environmental information is used for a host of applications, including weather monitoring and prediction models, ocean temperatures and moisture locations, climate studies, cryosphere (ice, snow, glaciers) detection and extent, land temperatures and crop conditions, and hazards detection. The GOES-O&P Imagers have improved resolution in the 13 micrometer channel from 8 km to 4 km. The finer spatial resolution allows an improved cloud-top product, height of atmospheric motion vectors and volcanic ash detection. GOES-P continues the improved image navigation and registration, additional power and fuel lifetime capability, space weather, solar x-ray imaging, search and rescue, and communication services as provided on GOES-13. GOES-P Launches! The GOES-P satellite launched at 6:57 p.m. EST March 4 aboard a United Launch Alliance Delta IV rocket from Launch Complex 37B at Cape Canaveral Air Force Station in Florida. GOES-P is the third and final spacecraft to be launched in the GOES-N series of geostationary environmental weather satellites. language code: en); 2017-09-01 16:47:27.0 [sritz] Insert Concept add broader relation (GOES-15 [f9649a77-f89c-4b3a-a5e5-624ccfccf97d,310131] - GOES [6e332c25-caeb-4917-afb6-af757bcecd72,310071]); MISSION REPORTS MISSION REPORT A document describing an observation flight, which is completed after the termination of the observation flight by the observing Party and which is signed by both the observing and observed Parties. [Source: Federation of American Scientists, Glossary of Open Skies Treaty Terms, http://www.fas.org/nuke/control/os/os_glsry.html ] Group: Platform_Details Entry_ID: MISSION REPORTS Group: Platform_Identification Platform_Category: Maps/Charts/Photographs Short_Name: MISSION REPORTS End_Group Creation_Date: 2012-10-24 End_Group 2016-06-09 18:49:32.0 [epneff] added altLabel insert AltLabel (id: null text: MISSION REPORT language code: en); 2012-10-24 18:22:41.0 [saritz] Insert Concept add broader relation (MISSION REPORTS [f9846838-fdbc-4aa0-86e9-b0e70e97d0e2,81979] - Maps/Charts/Photographs [af11dd2a-e514-4329-bbc5-0f36f2776a26,73527]); TSINGHUA-1 Tsinghua-1 is a microsatellite of Tsinghua University, developed and built in a joint venture between SSTL of Guildford, Surrey, UK, and Tsinghua University in Beijing, China. The TSRC (Tsinghua Space Research Center) was set up in Oct. 1998 with the goal to integrate all space research activities at Tsinghua University and to provide a means and facilities for S/C building. The joint-venture company in Beijing is referred to as T-SSSC (Tsinghua-Surrey Small Satellite Company). The cooperative program is to develop and build microsatellites (Tsinghua-1) and nanosatellites (THNS-1) and to provide integrated training in small satellite design. Tsinghua-1 (also referred to as "Hangtian" in Chinese) is a demonstrator microsatellite in the 50 kg class of size: 35 cm x 35 cm x 64 cm. The overall objective is to provide daily high-resolution imaging for disaster monitoring and mitigation on a worldwide scale. A further goal of Tsinghua-1 is to conduct communications research in LEO. The design uses the new MicroSat-70 platform modules or trays to carry the subsystems and payload. The power subsystem design includes the regulation, protection and distribution of a 35 W solar array and 7 Ah NiCd batteries. This subsystem essentially offers two buses: an unregulated 14 V bus and a regulated 5 V bus. The three payload modules include the GPS receiver (SGR-10 with 12 channels), transputer, and DSP/DTE (Digital Signal Processing/Data Transfer Experiment) unit. The three cameras and 3 reaction wheels are accommodated in the Earth Observation Compartment. Two GPS antennas are accommodated on the space facing side of the S/C. The spacecraft is three-axis stabilized using a combination of passive (gravity-gradient boom) and active (magnetorquers, reaction wheels) actuator elements. The platform is nadir pointing. Attitude is sensed by sun sensors and a magnetometer. The body-pointing platform has the capability to perform fast slew maneuvers within 15 about the roll axis (or 180 about the yaw axis). An off-nadir pointing configuration can be sustained for up to half an orbit. Onboard data handling is provided with a dual CAN (Controller Area Network) bus (ISO 11898 & ISO 11519-1) 20 Mbit/s, and INMOS serial point-to-point link 9.6 kbit/s asynchronous duplex UART (Universal Asynchronous Receiver/Transmitter). A launch of Tsinghua-1, along with SNAP-1 of SSTL as secondary payloads to Nadezhda-6, the prime Russian S&RSAT (Search & Rescue Satellite) of COSPAS, took place on June 28, 2000 on a Russian Cosmos-3M launcher from the Plesetsk Cosmodrome, Russia. Orbit: Sun-synchronous circular orbit, altitude = 700 km, inclination = 98, period of 100 minutes. Status of Tsinghua-1 mission: The spacecraft is operational as of 2004. Sensor complement: MEIS (Multispectral Earth Imaging System).MEIS is a demonstrator instrument intended for the upcoming DMC (Disaster Monitoring Constellation) mission. The objective is to acquire multispectral Earth surface imagery with a spatial resolution of 40 m (snapshot imagery). The MEIS camera assembly consists of three cameras (one for each spectral band) mounted at an angle of 15 from nadir so that the yaw angle can be selected to offer the required off-pointing angle of 15 from nadir. The image swath width is 80 km and each camera can collect four images contiguously along the flight path. The instrument performs autonomous onboard histogram analysis to ensure optimum image quality involving image processing, compression and onboard storage. The OBCs may also be used to carry out autonomous onboard cloud editing and high-compression thumb-nail image previews. SGR-10 (Space GPS Receiver-10). The objective is real-time positioning for tracking the satellite and providing orbital elements for the spacecraft mission and ground station. SGR is a customized COTS-developed receiver. The instrument is based on the second generation GPS chip set of MITEL Semiconductors. The SGR consists of the following elements: GPS antennas, LNAs, the RF section, the digital section and the TLM/TC node. RF section: The SGR has two separate RF front-ends in the RF section which are responsible for down-converting the GPS signals and digitizing the IF signals. The RF sections use the same local oscillator so that the measurements are referenced to the same fundamental TCXO clock. Digital section: This part consists of hardware correlator channels, memory, a 32 bit RISC microprocessor with supporting peripherals and the interface circuitry. There are 24 C/A code correlation channels available, although only 12 channels are available if only 2 antennas are used. TLM/TC node: A separate 8 bit microcontroller is used to provide telemetry and telecommands. The telemetry includes status monitoring of SGR, while telecommand include reset, power down parts of the receiver, some redundancy switching etc. The SGR-10 receives the L1 signal from the GPS constellation. The total SGR mass is 1.355 kg, including antenna/LNA. The accuracy of positioning, velocity and time synchronization (under Selective Availability on GPS) are: 150 m, 1 m/s, 3-D, 2 sigma approximately, and + 1 s, respectively. Information from http://www.eoPortal.org Group: Platform_Details Entry_ID: TSINGHUA-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: TSINGHUA-1 End_Group Group: Platform_Associated_Instruments Short_Name: CAMERAS End_Group Group: Orbit Orbit_Altitude: 700 Orbit_Inclination: 98.14 Period: 98.68 Perigee: 687 Apogee: 713 Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2008-06-19 Online_Resource: http://directory.eoportal.org/get_announce.php?an_id=9264 Online_Resource: http://www.sstl.co.uk/ Group: Platform_Logistics Launch_Date: 2000-06-28 Launch_Site: Plesetsk Cosmodrome, Russia Primary_Sponsor: Tsinghua University (China) Primary_Sponsor: Surrey Satellite Technology Ltd. (SSTL) End_Group End_Group DROPWINDSONDES Dropwindsondes are weather instruments that collect atmospheric data as they descend after being dropped from research aircraft. These dropwindsondes obtain vertical profiles of wind, temperature, and humidity from 400mb to the surface. This data is then ingested by numerical numerical models to come up with hurricane track and intensity forecasts. These observations provide grid points of observations over the tropical oceans which are generally devoid of weather observations. Aberson and Franklin (1999) state that "accurate modeling of tropical cyclone motion and intensity requires both realistic numerical models and accurate representation of meteorological fields through the depth of the troposphere on a variety of scales." While models have greatly improved over the past 20 years, significant forecast improvements are still possible by decreasing the analysis error. This has been the primary goal of the Hurricane Research Division (HRD) branch of NOAA. This is wh! y NOAA has procured a new generation of dropwindsondes based on the Global Positioning System (GPS) as well a Gulfstream-IV jet aircraft (G-IV). A study of the impact of the new dropwindsondes' observations on hurricane forecast models was conducted by Aberson and Frankilin in 1997. In the 1997 study about 30 dropwindsondes were used during each mission. These observations were then put into the Geophysical Fluid Dynamics Laboratory (GFDL) and VICBAR hurricane models and the Global Spectral Model (GSM) using the National Center for Environmental Prediction (NCEP) Global Data Assimilation (GDAS). GDAS uses a quality control algorithm, synthetic data and analysis procedures, and the Global Spectral Model in its data assimilation. Further information about the data assimilation can be found in Aberson and Franklin (1999). For the study NCEP's GSM is run and is used as the boundary conditions for the HRD's barotropic model (VICBAR) and the GFDL model. The track forecasts of the GSM, VICBAR, and GFDL models were compared to the CLIPER model to calculate track errors and the SHIFOR model to calculate intensity errors. The CLIPER and SHIFOR models are statistical regression models which use only climatology and persistence in their forecasts. More info at: "http://marine.rutgers.edu/mrs/education/spring2000/louisb/Results.html" [Source: Reuters] OGO-6 The Orbiting Geophysical Observatory 6 (OGO 6) was a large observatory instrumented with 26 experiments designed to study the various interrelationships between, and latitudinal distributions of, high-altitude atmospheric parameters during a period of increased solar activity. The main body of the spacecraft was attitude controlled by means of horizon scanners and gas jets so that its orientation was maintained constant with respect to the earth and the sun. The solar panels rotated on a horizontal axis extending transversely through the main body of the spacecraft. The rotation of the panels was activated by sun sensors so that the panels received maximum sunlight. Seven experiments were mounted on the solar panels (the SOEP package). An additional axis, oriented vertically across the front of the main body, carried seven experiments (the OPEP package). Nominally, these sensors observed in a forward direction in the orbital plane of the satellite. The sensors could be rotated more than 90 deg relative to the nominal observing position and more than 90 deg between the upper and lower OPEP groups mounted on either end of this axis. On June 22, 1969, the spacecraft potential dropped significantly during sunlight operation and remained so during subsequent sunlight operation. This unexplained shift affected seven experiments which made measurements dependent upon knowledge of the spacecraft plasma sheath. During October 1969, a string of solar cells failed, but the only effect of the decreased power was to cause two experiments to change their mode of operation. Also during October 1969, a combination of manual and automatic attitude control was initiated, which extended the control gas lifetime of the attitude control system. In August 1970, tape recorder (TR) no. 1 operation degraded, so all recorded data were subsequently taken with TR no. 2. By September 1970, power and equipment degradation left 14 experiments operating normally, 3 partially, and 9 off. From October 14, 1970, TR no. 2 was used only on Wednesdays (world days) to conserve power and extend TR operation. In June 1971, the number of 'on' experiments decreased from 13 to 7, and on June 28, 1971, the spacecraft was placed in a spin-stabilized mode about the yaw (Z) axis and turned off due to difficulties with spacecraft power. OGO 6 was turned on again from October 10, 1971, through March 1972, for operation of experiment 25 by The Radio Research Laboratory, Japan. [Summary provided by NASA.] Group: Platform_Details Entry_ID: OGO-6 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: OGO (Orbiting Geophysical Observatory) Short_Name: OGO-6 Long_Name: Orbiting Geophysical Observatory-6 End_Group Group: Synonymous_Platform_Names Short_Name: OGO-F Short_Name: PL-691D Short_Name: POGO 3 Short_Name: S 60 Short_Name: 03986 End_Group Group: Platform_Associated_Instruments Short_Name: MAGNETOMETERS Short_Name: PHOTOMETERS Short_Name: SPECTROMETERS End_Group Group: Orbit Orbit_Inclination: 82 degrees Period: 99.7 minutes Perigee: 413 km Apogee: 1077 km Orbit_Type: HEO > Highly Elliptical Orbit End_Group Creation_Date: 2007-02-13 Online_Resource: http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1969-051A Sample_Image: http://heasarc.gsfc.nasa.gov/Images/ogo/ogo.gif Group: Platform_Logistics Launch_Date: 1969-06-05 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: NASA End_Group End_Group OSO-3 The objectives of the OSO satellite series were to perform solar physics experiments above the atmosphere during a complete solar cycle and to map the celestial sphere for direction and intensity of UV light, X-rays, and gamma radiation. General Information: Designation: 02703 / 67020A Launch date: 8 Mar 1967 Country of origin: United States Mission: Scientific (Sun observation) Perigee/Apogee: 546/570 km Inclination: 32.8° Period: 95.8 min Launch vehicle: Thor Delta #46 Out of service: Nov 1969 Decay: 4 Apr 1982 Additional information available at "http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/oso3.html" [Summary provided by of The Satellite Encyclopedia] Group: Platform_Details Entry_ID: OSO-3 Group: Platform_Identification Platform_Category: Solar/Space Observation Satellites Platform_Series_or_Entity: OSO (Orbiting Solar Observatory) Short_Name: OSO-3 Long_Name: Orbiting Solar Observatory-3 End_Group Group: Synonymous_Platform_Names Short_Name: OSO-3 End_Group Group: Platform_Associated_Instruments Short_Name: GAMMA RADIATION DETECTOR End_Group Group: Orbit Orbit_Inclination: 32.8 degrees Period: 95.8 min Perigee: 546 km Apogee: 570 km End_Group Creation_Date: 2007-12-14 Online_Resource: http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/oso3.html Sample_Image: http://heasarc.gsfc.nasa.gov/Images/oso/oso3.gif Group: Platform_Logistics Launch_Date: 1967-03-08 Primary_Sponsor: NASA End_Group End_Group SAC-D 2013-08-14 18:14:26.0 [aaleman] added new valid insert AltLabel (id: null text: Satélite de Aplicaciones Científico - D language code: en); 2013-08-14 18:13:24.0 [aaleman] Insert Concept add broader relation (SAC-D [fb9164bb-4dba-4598-ba56-cb24d8db5527,105723] - SAC [ea7e0cb4-5764-4ca4-89f6-913b22a47eff,74071]); NP-3C Orion 2017-08-29 21:03:10.0 [aaleman] added new platform at NSIDC request insert AltLabel (id: null category: primary text: Naval Research Lab P-3C Orion language code: en); 2017-08-29 21:02:04.0 [aaleman] Insert Concept add broader relation (NP-3C Orion [fb9f4171-b9b6-4627-9c79-1d3b5890dfc4,310067] - Aircraft [227d9c3d-f631-402d-84ed-b8c5a562fc27,287509]); MOORINGS Moorings: Equipment, such as anchors or chains, for holding fast a vessel or an aircraft. [Source: The American Heritage Dictionary of the English Language, Fourth Edition Copyright 2000 by Houghton Mifflin Company.] CONVAIR-990 he Convair 990 Coronado was an enhanced version of the Convair 880. Specifically, it was 10 feet longer, could hold as many as 39 more passengers, and has anti-shock bodies extending back from the trailing edge of the wing (see picture below). General Dynamics, the parent company of Convair, was the third American aerospace company to enter the jet race behind Boeing with its 707 and Douglas with its DC-9. Being third was a distinct disadvantage as most airlines had already purchased jets before the first Convair ever flew. However, Convair believed it could win with a jet that would be the fastest civilian aircraft in the skies. [Text and Photo provided by: http://www.super70s.com/Super70s/Tech/Aviation/Aircraft/Convair-990.asp ] Group: Platform_Details Entry_ID: CONVAIR-990 Group: Platform_Identification Platform_Category: Aircraft Short_Name: CONVAIR-990 CORONADO End_Group Creation_Date: 2008-07-14 Online_Resource: http://www.super70s.com/Super70s/Tech/Aviation/Aircraft/Convair-990.asp Online_Resource: http://en.wikipedia.org/wiki/Convair_990 Sample_Image: http://www.super70s.com/Super70s/Tech/Aviation/Aircraft/images/CV990-EC92-05275-30(320).jpg End_Group Nimbus-1 Nimbus-1 was launched in August 1964 and was the first in a series of second-generation meteorological research-and-development satellites that was designed to serve as a stabilized, earth-oriented platform for the testing of advanced meteorological sensor systems and for collecting meteorological data. The polar-orbiting spacecraft consisted of three major elements: (1) a sensory ring, (2) solar paddles, and (3) the control system housing. The solar paddles and the control system housing were connected to the sensory ring by a truss structure, giving the satellite the appearance of an ocean buoy. Nimbus-1 was nearly 3.7 m tall, 1.5 m in diameter at the base, and about 3 m across with solar paddles extended. The sensory ring, which formed the satellite base, housed the electronics equipment and battery modules. The lower surface of the torus-shaped sensory ring provided mounting space for sensors and telemetry antennas. An H-frame structure mounted within the center of the torus provided support for the larger experiments and tape recorders. Mounted on the control system housing, which was located on top of the spacecraft, were sun sensors, horizon scanners, gas nozzles for attitude control, and a command antenna. Use of a stabilization and control system allowed the spacecraft's orientation to be controlled to within plus or minus 1 degree for all three axes (pitch, roll, and yaw). The spacecraft carried an advanced vidicon camera system for recording and storing remote cloudcover pictures, an automatic picture transmission camera for providing real-time cloudcover pictures, and a high-resolution infrared radiometer to complement the daytime TV coverage and to measure nighttime radiative temperatures of cloud tops and surface terrain. A short second-stage burn resulted in an unplanned eccentric orbit. Otherwise, the spacecraft and its experiments operated successfully until September 22, 1964. The solar paddles became locked in position, resulting in inadequate electrical power to continue operations. __________ Taken from the NSSDC System for Information Retrieval and Storage (SIRS). For more information contact the NSSDC Coordinated Request and User Support Office, 301-286-6695 (NASA Goddard Space Flight Center, Code 933.4, Greenbelt, Maryland 20771, USA). Group: Platform_Details Entry_ID: NIMBUS-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NIMBUS Short_Name: NIMBUS-1 End_Group Group: Synonymous_Platform_Names Short_Name: NIMBUS-A Short_Name: 00872 End_Group Group: Platform_Associated_Instruments Short_Name: APT NIMBUS-1 Short_Name: HRIR NIMBUS-1 Short_Name: AVCS NIMBUS-1 End_Group Group: Orbit Orbit_Inclination: 98 degrees Period: 98.41999816894531 minutes Perigee: 429.0 km Apogee: 937.0 km Orbit_Type: GEO > Geosynchronous > Geostationary End_Group Creation_Date: 2007-10-11 Online_Resource: http://nssdc.gsfc.nasa.gov/nmc/masterCatalog.do?sc=1964-052A Online_Resource: http://nasascience.nasa.gov/missions/nimbus Online_Resource: http://atmospheres.gsfc.nasa.gov/nimbus/ Group: Platform_Logistics Launch_Date: 1964-08-28 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: USA/NASA End_Group End_Group 2015-05-12 16:53:02.0 [saritz] update PrefLabel (Nimbus-1); MTSAT-1R MTSAT1R The MTSAT-1R is a geostationary satellite from Japan. It has an onboard sensor, which is called the Japanese Advanced Meteorological Imager (JAMI). JAMI obtains round earth imagery, called "full-disk image", and observes earth surface conditions and cloud distributions as well as meteorological phenomena such as typhoons, depressions, front and so on. In addition, the various meteorological parameters, such as sea surface temperature and cloud motion winds are extracted from image data. Group: Platform_Details Entry_ID: MTSAT-1R Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: GMS (Japan Geostationary Meteorological Satellite) Short_Name: MTSAT-1R Long_Name: Multi-functional Transport Satellite 1 Replacement End_Group Group: Platform_Associated_Instruments Short_Name: JAMI End_Group Creation_Date: 2007-12-06 Online_Resource: http://mscweb.kishou.go.jp/index.htm Group: Platform_Logistics Launch_Date: 2005-02-26 Launch_Site: Tanegashima Island, Japan Primary_Sponsor: Japan Meteorological Agency End_Group End_Group 2016-06-09 15:35:43.0 [epneff] added altLabel insert AltLabel (id: null text: MTSAT1R language code: en); AD-B Explorer 24 was placed in orbit together with Explorer 25 from a single launch vehicle. Explorer 24 was identical in configuration to the previously launched balloon satellites Explorer 9 and 19. The spacecraft was 3.6 m in diameter, was built of alternating layers of aluminum foil and plastic film, and was covered uniformly with 5.1-cm white dots for thermal control. It was designed to yield atmospheric density near perigee as a function of space and time from sequential observations of the sphere's position in orbit. To facilitate ground tracking, the satellite carried a 136-MHz tracking beacon. The satellite reentered the earth's atmosphere on October 18, 1968. http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1964-076A Group: Platform_Details Entry_ID: AD-B Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: AD (Atmospheric Dynamics) Short_Name: AD-B Long_Name: Atmosphere Dynamics B (Explorer 24) End_Group Group: Synonymous_Platform_Names Short_Name: EXPLORER 24 Short_Name: 00931 End_Group Group: Platform_Associated_Instruments Short_Name: OPTICAL BEACON End_Group Group: Orbit Orbit_Inclination: 81.4 degrees Period: 116.3 minutes Perigee: 525 km Apogee: 2498 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-08-22 Online_Resource: http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1964-076A Group: Platform_Logistics Launch_Date: 1964-11-21 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: NASA End_Group End_Group NOAA-7 NOAA-7 was launched in June 1981 and was a third generation operational meteorological satellite for use in the National Operational Environmental Satellite System (NOESS) and for the support of the Global Atmospheric Research Program (GARP) during 1978-84. The satellite design provided an economical and stable sun-synchronous platform for advanced operational instruments to measure the earth's atmosphere, its surface and cloud cover, and the near-space environment. The satellite was based upon the Block 5D spacecraft bus developed for the U.S. Air Force, and it was capable of maintaining an earth-pointing accuracy of better than plus or minus 0.1 degree with a motion rate of less than 0.035 degree/second. Primary sensors included an Advanced Very High Resolution Radiometer (AVHRR) and a TIROS Operational Vertical Sounder (TOVS). Secondary experiments consisted of a Space Environment Monitor (SEM) and a Data Collection and Platform Location System (DCPLS). A contamination monitor was provided by the U.S. Air Force to assess contamination sources, levels, and effects for consideration on future spacecraft. __________ Taken from the NSSDC System for Information Retrieval and Storage (SIRS). For more information contact the NSSDC Coordinated Request and User Support Office, 301-286-6695 (NASA Goddard Space Flight Center, Code 933.4, Greenbelt, Maryland 20771, USA, "http://nssdc.gsfc.nasa.gov/"). Group: Platform_Details Entry_ID: NOAA-7 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: NOAA POES (Polar Orbiting Environmental Satellites) Short_Name: NOAA-7 Long_Name: National Oceanic & Atmospheric Administration-7 End_Group Group: Synonymous_Platform_Names Short_Name: NOAA-C End_Group Group: Platform_Associated_Instruments Short_Name: TOVS Short_Name: AVHRR End_Group Creation_Date: 2007-11-09 Online_Resource: http://nssdc.gsfc.nasa.gov/ Sample_Image: http://www.siloworld.com/MISSILE%20%20LAUNCHES/VAFB/SLC-3/19810623_087F_1229.JPG Group: Platform_Logistics Launch_Date: 1981-06-23 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: NASA End_Group End_Group IRS-RS2 2019-02-22 17:36:33.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: 86402184-15ee-435c-933f-d70eb986c715 relationship type: null relationship value: null generated by: null); 2019-02-20 21:41:03.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: 3a3c2498-8e0e-4138-b5a2-7c2a80e1b598 relationship type: null relationship value: null generated by: null); insert WeightedRelation (id: null related concept uuid: 7903c432-f65f-4b92-bb9e-96cd3036fd1d relationship type: null relationship value: null generated by: null); 2016-04-05 14:42:49.0 [mpmorahan] insert AltLabel (id: null text: Indian Remote Sensing Satellite-RS2 language code: en); 2016-04-05 14:41:06.0 [mpmorahan] Insert Concept add broader relation (IRS-RS2 [fd710ee8-797c-490a-9f90-064a38141f99,158885] - IRS (Indian Remote Sensing Satellite) [3e8bc0c6-f599-4e23-9535-449af00edd61,143483]); NCAR ELECTRA HY2-A Ocean-2A HY-2 is a second generation ocean observation/monitoring satellite series approved by CNSA (China National Space Administration) Beijing in Feb. 2007. The HY-2A mission represents a follow-up of the HY-1A and HY-1B missions. The overall objective of HY-2 is the measurement of ocean dynamic and environmental parameters in the microwave region (i.e., all weather observations). The requirements call also for the collection of data on marine wind setup (wind vector), marine surface height, and SST (Sea Surface Temperature), along with aero-marine forecasts for the prevention and relief of disaster. 2018-08-10 18:50:40.0 [sritz] insert AltLabel (id: null category: null text: Ocean-2A language code: en); 2018-08-10 18:48:57.0 [sritz] insert AltLabel (id: null category: primary text: Haiyang-2A language code: en); insert Definition (id: null text: HY-2 is a second generation ocean observation/monitoring satellite series approved by CNSA (China National Space Administration) Beijing in Feb. 2007. The HY-2A mission represents a follow-up of the HY-1A and HY-1B missions. The overall objective of HY-2 is the measurement of ocean dynamic and environmental parameters in the microwave region (i.e., all weather observations). The requirements call also for the collection of data on marine wind setup (wind vector), marine surface height, and SST (Sea Surface Temperature), along with aero-marine forecasts for the prevention and relief of disaster. language code: en); 2018-08-10 18:47:59.0 [sritz] Insert Concept add broader relation (HY2-A [fe07a2e4-a6cd-401c-af3e-433bbc8c2c98,368063] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,344761]); PROBA-1 [Text Source: ESA Proba web site, http://www.esa.int/SPECIALS/Proba_web_site/index.html ] The Project for On-Board Autonomy (Proba) is a technology demonstration mission of the European Space Agency, funded within the frame of ESA's General Support Technology Programme. It is managed by ESA??s Control and Data Systems Division within the Department of Electrical Engineering, part of the Directorate for Technical and Operational Support at ESA/ESTEC. Work on the project began in mid-1998 and Proba was successfully launched on 22 October, 2001, initially for a one-year mission. Proba objectives The objectives of Proba are: -in-orbit demonstration and evaluation of new hardware and software spacecraft technologies - in-orbit demonstration and evaluation of onboard operational autonomy - in-orbit trial and demonstration of Earth observation and space environment instruments More Information: http://www.esa.int/SPECIALS/Proba_web_site/index.html Group: Platform_Details Entry_ID: PROBA-1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: PROBA-1 Long_Name: Project for On-Board Autonomy, PROBA-1 End_Group Group: Synonymous_Platform_Names Short_Name: PROBA End_Group Group: Platform_Associated_Instruments Short_Name: PROBA.CHRIS.1A Short_Name: HRC Short_Name: WAC Short_Name: SREM Short_Name: DEBIE Short_Name: SIPS Short_Name: MRM Short_Name: PASS End_Group Group: Orbit Orbit_Altitude: 615 km Orbit_Inclination: 98.75 deg Period: 101.3 min Repeat_Cycle: 16 days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-11-21 Online_Resource: http://www.esa.int/esaMI/Proba_web_site/ Group: Platform_Logistics Launch_Date: 2001-10-22 Launch_Site: Sriharikota Island, India Primary_Sponsor: ESA End_Group End_Group LANDSAT-5 LANDSAT-5 (LAND REMOTE-SENSING SATELLITE-5) Landsat 5 is the fifth satellite of the Landsat program. It was launched on March 1st, 1984, with the primary goal of providing a global archive of satellite photos. The Landsat Program is managed by USGS, and data from Landsat 5 is collected and distributed from the USGS's Center for Earth Resources Observation and Science (EROS). Landsat 5 has significantly exceeded its designed life expectancy, and has a maximum transmission bandwidth of 85 Mbit/s. It was deployed at an altitude of 705.3 km, a lower orbit than Landsat 4. It takes some 16 days to scan the entire Earth. The satellite is an identical copy of Landsat 4 and was originally intended as a backup - it therefore carries the same instruments, including the Thematic Mapper and Multi-Spectral Scanner. The Multi-Spectral Scanner was powered down in 1995. [Summary provided by NASA.] Group: Platform_Details Entry_ID: LANDSAT-5 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: LANDSAT-5 End_Group Group: Platform_Associated_Instruments Short_Name: MSS Short_Name: TM End_Group Group: Orbit Orbit_Altitude: 705 km Orbit_Inclination: 98.2 degree Equator_Crossing: 9:45 AM (&#177; 15 min.) local time (descending node) Period: 99 minutes Repeat_Cycle: 16 days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-02-01 Online_Resource: https://landsat.gsfc.nasa.gov/landsat-5/ Online_Resource: https://www.usgs.gov/land-resources/nli/landsat/landsat-5 Group: Platform_Logistics Launch_Date: 1984-03-01 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: NASA Primary_Sponsor: USGS End_Group End_Group 2019-12-31 21:37:11.0 [sritz] update Definition (Landsat 5 is the fifth satellite of the Landsat program. It was launched on March 1st, 1984, with the primary goal of providing a global archive of satellite photos. The Landsat Program is managed by USGS, and data from Landsat 5 is collected and distributed from the USGS's Center for Earth Resources Observation and Science (EROS). Landsat 5 has significantly exceeded its designed life expectancy, and has a maximum transmission bandwidth of 85 Mbit/s. It was deployed at an altitude of 705.3 km, a lower orbit than Landsat 4. It takes some 16 days to scan the entire Earth. The satellite is an identical copy of Landsat 4 and was originally intended as a backup - it therefore carries the same instruments, including the Thematic Mapper and Multi-Spectral Scanner. The Multi-Spectral Scanner was powered down in 1995. [Summary provided by NASA.] Group: Platform_Details Entry_ID: LANDSAT-5 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: LANDSAT-5 End_Group Group: Platform_Associated_Instruments Short_Name: MSS Short_Name: TM End_Group Group: Orbit Orbit_Altitude: 705 km Orbit_Inclination: 98.2 degree Equator_Crossing: 9:45 AM (&#177; 15 min.) local time (descending node) Period: 99 minutes Repeat_Cycle: 16 days Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-02-01 Online_Resource: https://landsat.gsfc.nasa.gov/landsat-5/ Online_Resource: https://www.usgs.gov/land-resources/nli/landsat/landsat-5 Group: Platform_Logistics Launch_Date: 1984-03-01 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: NASA Primary_Sponsor: USGS End_Group End_Group); update Definition (https://landsat.gsfc.nasa.gov/landsat-5/); delete Resource (null); 2016-06-09 15:32:33.0 [epneff] added altLabel insert AltLabel (id: null text: LANDSAT-5 (LAND REMOTE-SENSING SATELLITE-5) language code: en); Earth Explorers 2019-04-25 06:26:18.0 [mmorahan] Insert Concept add narrower relation (Earth Explorers [fe9b35e7-6243-44bb-ac42-ce8350e7a86f,346137] - Biomass [a9b21edd-49b7-43be-8e35-8652bbc5559a,368657]); SGO The most important signal to be recorded at the Superconducting Gravimeter Observatory is gravity. For most Global Geodynamics Project (GGP) purposes the atmospheric correction to gravity is required and so the local measurement of pressure is also necessary. At most sites the effect of groundwater, often associated with rainfall, is an important contributor to gravity variations over periods of days to years. Superconducting Gravimeter groups are therefore urged to record rainfall and groundwater level at their sites as auxiliary data. Finally each station is asked to supply a log file of important events that might affect the data for each month. Group: Platform_Details Entry_ID: SGO Group: Platform_Identification Platform_Category: In Situ Land-based Platforms Platform_Series_or_Entity: GEOPHYSICAL STATIONS/NETWORKS Short_Name: SGO Long_Name: Superconducting Gravimeter Observatory End_Group Creation_Date: 2007-06-28 Online_Resource: http://www.gfz-potsdam.de/pb1/pg3/ggp/ggp.html Sample_Image: http://www.gfz-potsdam.de/pb1/pg3/ggp/pic/sggrav.gif End_Group IMS 2017-12-27 10:08:51.0 [mmorahan] Insert Concept add narrower relation (IMS [fecf6a37-ffa9-4e11-90cf-1abfeb95cb95,288895] - IMS-2 [aa137482-53a7-455d-b8d8-52d487380c2a,310491]); WORLDVIEW-2 WorldView-2, launched October 2009, is the first high-resolution 8-band multispectral commercial satellite. Operating at an altitude of 770 kilometers, WorldView-2 provides 46 cm panchromatic resolution and 1.85 meter* multispectral resolution. WorldView-2 has an average revisit time of 1.1 days and is capable of collecting up to 1 million square kilometers of 8-band imagery per day, greatly enhancing the DigitalGlobe multispectral collection capacity for more rapid and reliable collection. The WorldView-2 system, offering incredible accuracy, agility, capacity and spectral diversity, allows DigitalGlobe to substantially expand its imagery product offerings to both commercial and government customers. Group: Platform_Details Entry_ID: WORLDVIEW-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: WORLDVIEW-2 End_Group Group: Orbit Orbit_Altitude: 770 km Equator_Crossing: 10:30 am Local time: e.g. Period: 100 min Repeat_Cycle: 101 days at 1 meter GSD or less; 3.7 days at 20deg off-nadir or less (0.52 meter GSD) Orbit_Type: LEO > LOW EARTH ORBIT > POLAR SUN-SYNCHRONOUS End_Group Creation_Date: 2013-05-08 Online_Resource: http://www.digitalglobe.com/about-us/content-collection#satellites&worldview-2 Group: Platform_Logistics Launch_Date: 2009-10-08 Launch_Site: VANDENBERG AIR FORCE BASE, USA Design_Life: 10-12 years Primary_Sponsor: DigitalGlobe End_Group End_Group 2019-02-22 22:05:06.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: 001d8e8c-e9b1-4418-9941-f41321c2c500 relationship type: null relationship value: null generated by: null); 2013-05-07 19:05:56.0 [aaleman] added new platform insert Definition (id: null text: WorldView-2, launched October 2009, is the first high-resolution 8-band multispectral commercial satellite. Operating at an altitude of 770 kilometers, WorldView-2 provides 46 cm panchromatic resolution and 1.85 meter* multispectral resolution. WorldView-2 has an average revisit time of 1.1 days and is capable of collecting up to 1 million square kilometers of 8-band imagery per day, greatly enhancing the DigitalGlobe multispectral collection capacity for more rapid and reliable collection. The WorldView-2 system, offering incredible accuracy, agility, capacity and spectral diversity, allows DigitalGlobe to substantially expand its imagery product offerings to both commercial and government customers. language code: en); 2013-05-07 19:00:54.0 [aaleman] Insert Concept add broader relation (WORLDVIEW-2 [ff0ed18d-c476-4dc4-a248-d42ad74bb4a1,105099] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,73425]); Resurs DK 1 Environmental Satellite Resurs-DK N1 Group: Platform_Details Entry_ID: Resurs DK 1 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: Resurs DK 1 Long_Name: Environmental Satellite Resurs-DK N1 End_Group Group: Platform_Associated_Instruments Short_Name: Geoton-L1 (1) Short_Name: Arina Short_Name: Pamela End_Group Group: Orbit Orbit_Altitude: 361x604 km Orbit_Inclination: 70 degrees Period: 94 minutes Repeat_Cycle: 6 days Orbit_Type: LEO > LOW EARTH ORBIT > INCLINED NON-POLAR End_Group Creation_Date: 2015-01-26 Online_Resource: http://samspace.ru/products/earth_remote_sensing_satellites/ka_resurs_dk_1/ Online_Resource: http://en.samspace.ru/products/earth_remote_sensing_satellites/ka_resurs_dk_1/ Sample_Image: http://ruscosmos.narod.ru/KA/RSR-DK/karsr/DK.jpg Sample_Image: http://wizard.roma2.infn.it/pamela/images/resurs-DK1_Spacecraft.jpg Group: Platform_Logistics Launch_Date: 2006-06-15 Design_Life: 9 years End_Group End_Group 2015-08-03 12:54:27.0 [mpmorahan] insert AltLabel (id: null text: Environmental Satellite Resurs-DK N1 language code: en); 2015-08-03 12:47:01.0 [mpmorahan] Insert Concept add broader relation (Resurs DK 1 [ff2141a6-5682-44da-88fc-9a4e78de35ad,158127] - Earth Observation Satellites [3466eed1-2fbb-49bf-ab0b-dc08731d502b,143415]); OGO-4 The Orbiting Geophysical Observatory 4 (OGO 4) was a large observatory instrumented with experiments designed to study the interrelationships between the aurora and airglow emissions, energetic particle activity, geomagnetic field variation, ionospheric ionization and recombination, and atmospheric heating which take place during a period of increased solar activity. After the spacecraft achieved orbit and the experiments were deployed into an operating mode, an attitude control problem occurred. This condition was corrected by ground control procedures until complete failure of the tape recording systems in mid-January 1969. At that time, due to the difficulty of maintaining attitude control without the tape recorders, the attitude control system was commanded off, and the spacecraft was placed into a spin-stabilized mode about the axis which was previously maintained vertically. In this mode, seven of the remaining experiments were turned off since no meaningful data could be observed by them. On October 23, 1969, the satellite was turned off. It was reactivated again in January 1970 for 2 months to obtain VLF observations. [Summary provided by NASA.] Group: Platform_Details Entry_ID: OGO-4 Group: Platform_Identification Platform_Category: Earth Observation Satellites Platform_Series_or_Entity: OGO (Orbiting Geophysical Observatory) Short_Name: OGO-4 Long_Name: Orbiting Geophysical Observatory-4 End_Group Group: Synonymous_Platform_Names Short_Name: OGO-D Short_Name: POGO 2 Short_Name: 02895 End_Group Group: Platform_Associated_Instruments Short_Name: SPECTROMETERS Short_Name: PHOTOMETERS Short_Name: PARTICLE DETECTORS End_Group Group: Orbit Orbit_Inclination: 86 degrees Period: 98 minutes Perigee: 412 km Apogee: 908 km Orbit_Type: LEO > Low Earth Orbit > Polar Sun-Synchronous End_Group Creation_Date: 2007-02-13 Online_Resource: http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1967-073A Sample_Image: http://heasarc.gsfc.nasa.gov/Images/ogo/ogo.gif Group: Platform_Logistics Launch_Date: 1967-07-28 Launch_Site: Vandenberg Air Force Base, USA Primary_Sponsor: NASA End_Group End_Group