The Data Application of the CYGNSS Satellite is Flood Inundation Mapping.


The Pixels per FWHM of the Spectrometer Instrument is 1400.


The Ground Sample Distance of the GSD Spectrometer is 12 m at nadir.


The Low Frequency Spectrometer (LFS) of the Chang’e-4 Lander Lander is Payload.


The Senior Director of Human Spaceflight Programs of the SpaceX Company is Benji Reed.


The Primary Applications of the AATSR Instrument is Chlorophyll, Vegetation index, Cloud clearing, SST.


The Position of the SPC (Solar Probe Cup) Sensor is Extends beyond the TPS.


The Operating Frequencies of the MWR Noise Injection Radiometer is 23.8 and 36.5 GHz.


The CCD Packages of the Focal Plane Module Imaging Device is 2.


The Power of the BRITE spacecraft Satellite is 5.4 W to 10 W.


The Imaging System of the NewSat Satellite is Panchromatic imager.


The Hosted Payload Mission Objectives of the Alphasat Satellite is Fulfillment of each TDP experimentation plan.


The Components of the CrIMSS OPS-EDR Product Data Product is (a) CrIMSS second stage ‘IR+MW’ retrieval; (b) ATMS-only retrieval; (c) Corresponding ECMWF analysis; (d) Aqua-AIRS retrieval; (e) Aqua-AMSU retrieval; (f) corresponding ECMWF analysis.


The Calibration Method of the TerraSAR-X SAR Satellite is Antenna model approach.


The Purpose of the SEXTANT Engineering Demonstration is Realizable in a single package with NICER.


The Impact Time of the Geomagnetic Storm Space Weather Event is Less than a day.


The Field of the Micro-gravity experiment Experiment is Fluid mechanics.


The Orbit Altitude of the ResourceSat-2A Satellite is 817 km.


The Total system cost of the WorldView Legion Satellite System is $600 million.


The Falcon 1e Launch Date of the FormoSat-5 Satellite is June 15, 2010.


The Publication Date of the New Horizons Spacecraft is 15 November 2021.


The Mass of the Satellite Bus Spacecraft Component is Approximately 3850 kg.


The Material of the Spacecraft Structure Satellite Component is Aluminum 7075-T6.


The Additional Velocity of the Objects Orbiting at LEO Satellite Components is ~7700 m s-1.


The Data Format of the Optical link Communication System is 1064 nm, BPSK (Bi-Phase Shift Keying) modulated, homodyne.


The Application Areas of the ResourceSat-2 Satellite is Agricultural crop discrimination and monitoring, crop acreage/yield estimation, precision farming, water resources, forest mapping, rural infrastructure development, disaster management.


The Nozzle Throat Diameter of the Propulsion System Satellite Component is 700 µm.


The Secondary Objective of the BIRD Satellite is Demonstrate new microsatellite technologies.


The Measurement Distance of the Autonomous Wireless Payload Payload is 635 km.


The Goal of the RASAT Satellite Mission is to test the equipments.


The Monoscopic Area Coverage of the QuickBird-2 Satellite is 1 x > 4 x.


The Overview Date of the Terrestrial Imaging Spectroscopy Missions Missions is 21–26 July 2013.


The Observation Cycle of the Landsat-8 Satellite is Every eight days.


The Goal Life of the Gokturk-2 Satellite is 7 years.


The Development Start Date of the Galileo Second Generation Satellites Satellite is Unknown.


The Correction Types of the Atmospheric Correction Image Processing is Flat and rugged terrain, haze/cirrus detection.


The Launch Date of the Göktürk-1 Satellite is December 5, 2016.


The Swath Width of the DMC-3 Satellite Constellation is 23 km.


The Workshop Presentation Date of the EnMAP Satellite is March 16-18, 2009.


The Operational Date of the PAZ-TerraSAR Constellation Satellite Constellation is Late 2017.


The Anticoincidence Efficiency of the GRS Gamma-Ray Spectrometer is ≥90%.


The Type of the ADCS Attitude Determination and Control Subsystem is Passive magnetic attitude stabilization system.


The Position Calculation Method of the DIOGENE Navigator is Least squares method.


The Disciplines of the EuTEF Payload Facility is Material science, physics, astrobiology and astronomy.


The Operations Support of the TGO Satellite is Yes.


The Study Phenomena of the RUBI Fluid Science Experiment is Phase transition and heat transfer during the evaporation of fluids.


The Clear Aperture of the Etalon Filter is 50 mm.


The Coverage of the Coverage Satellite is 2-day global coverage at 1 km resolution.


The Nominal FOV of the SPARCS Satellite is 2°.


The Forecast Duration of the HWRF Model is 24 hours.


The Data Source of the Green City Watch Application is Copernicus Sentinel satellite data.


The DVB-RCS/DVB-S2 On-Board Processors (OBPs) of the Repeater subsystem Communication System is 4 channels in Ku-band.


The Geolocation and Pointing Accuracy of the WindSat Sensor is Not provided.


The Orbit Inclination of the PAZ Satellite is 98º.


The Antenna Aperture in the Azimuth of the UF Mode Observation Mode is 7.5 m.


The Expected Stabilization Effect of the CanX-7 Satellite is Aerodynamically stabilize due to the so-called "shuttlecock" effect.


The Various Times of the Notional Pass Time Task Schedule is 12:00 pm, 1:30 pm, 12:00 am, 1:30 am, 8:00 am, 2:00 pm, 11:30 am.


The Launch Date of the SpaceX Falcon 9 Rocket is Nov. 14.


The Altitude of the JL-1-GF03D Microsatellite is 535 km.


The Launch Date of the Emirates Mars Mission (Hope) Satellite is 17 April 2020.


The Orbit Period of the ResourceSat-1 Satellite is 101.35 minutes.


The Lunar Lander Neutrons and Dosimetry(LND) of the Chang’e-4 Lander Lander is International Joint Collaboration Payload.


The Spectral Ranges of the Spectrometer Modules Spectrometer is 190-735 nm (UV-VIS) and 350-1100 nm (VNIR).


The Random Acceleration of the PP Twin Telescopes Telescope is Up to 88.1g.


The Fairing Extension Length of the TerraSAR-X Satellite is 1.5 m.


The Launch Date of the SMART-1 Satellite is 2003.


The Transmit Power of the LCT Laser Communication Terminal is 2.2 W.


The Estimated Start of the Oort Cloud Space Phenomenon is About 1,000 astronomical units (AU) from the Sun.


The Re-entry Date of the HITSAT Satellite is June 18, 2008.


The Function of the ISSAC SOC Space Operations Center is Coordinate with NASA for ISS and WORF rack operations.


The Presentation Date of the GRAIL Mission is March 18-21, 2013.


The Size of the Detector Imaging Device is 2048 x 2048 pixels.


The Navigation of the Lander Spacecraft is Absolute sensors determine the position and velocity with respect to the landing site.


The Inner Diameter of the PM Satellite Component is 4.2 m.


The Testing Duration of the Galileo Satellites 13 and 14 Satellites is Lengthy.


The Swath Width of the Instrument Spectrometer is 1650 km for IR bands.


The Application of the GeoSTAR Scattering Approach is Detect and track hurricanes and other severe storms.


The Mission Goals of the Psyche Asteroid is Understand the building blocks of planet formation, determine Psyche's age and formation process, and study its surface.


The Repeat Cycle of the Satellite Orbit Orbit is 17 days.


The Vector Components Random Error of the Electrical Field Satellite System is < 10 mV/m.


The URL of the China High-resolution Earth Observation System (CHEOS) Satellite System is http://spacenews.com/article/civil-space/39665china-pushing-ahead-on-hi-res-satellite-system.


The Proximity Operations Plan of the AeroCube-OCSD-B and -C Satellites is Co-orbital corkscrew orbit.


The Purpose of the STIS Ion Sensor is Measures solar energetic particles and provide advance warning if a shock wave produced by those particles is headed for Earth.


The Image Processing of the NASA's Solar Dynamics Observatory Satellite is Enhance small features.


The Modulation Scheme of the S-band transmitter Transmitter is BPSK.


The Placement of the Langmuir Probe Plasma Measurement Device is On long protruding booms.


The Uplink/Downlink Frequency of the OPAL Satellite is 420-450 MHz.


The Antenna Subsystem Rotation Speed of the GMI Instrument is 32 rpm.


The Arrival Date of the NICER Payload is June 8, 2016.


The Data Transmission Rate of the S-band Communication Band is 16 kbit/s.


The Mission Objective of the IMAP Satellite is Understand the boundary of the heliosphere.


The Maneuver Scheme of the P2 Satellite is Spin control maneuver scheme.


The Downlink Frequency of the Communication System Satellite System is 437.325 MHz.


The Swath Width of the MSU-M Multispectral Scanner is 1900 km.


The Image Transfer Modes of the Payload 2 CMOS Camera is 8/16 bit.


The Mission of the LunaH-Map Satellite is Map hydrogen within craters and other permanently shadowed regions throughout the moon’s south pole.


The Type of the ExoCube Payload is Space weather nanosatellite.


The Bus Type of the Jason-2 Satellite is Proteus.


The Date of the Divine Providencia Image is 27 March 2022.


The Attitude Variation During Maneuvers of the ISS Satellite is ~2-3º.


The Number of Temperature-Controlled Zones of the HTSSE-II payload Satellite Payload is 5.


The Packet Storage of the LT Device is Queue.


The Data Volume of the Hubble Space Telescope is 172 terabytes of data since its launch in 1990.


The Attitude Control of the ADCS unit Satellite Component is Y-momentum 3-axis stabilization.


The Measurement Range of the Faraday Cup Ion Detectors Sensor is Up to 8 keV.


The Journal Publication Date of the GPS/MET Satellite is 1997.


The OAP Increase of the UK-DMC-2 Satellite is 60%.


The Measurement Domain of the JERS-1 Satellite is Land, Snow & Ice.


The Mission Type of the Myriade/AstroSat-100 Satellite is EO.


The Instrument Power of the Instrument Spectrometer is 220 W.


The Configuration of the PSLV-C38 Launch Vehicle is XL.


The Launch Date of the OPTSAT-3000 Satellite is Aug. 2, 2017.


The Hardening Process of the Bricks Building Material is Water evaporation.


The Temperature of the OBCT Calibration Target is Approx. 273 K.


The Instrument Type of the HJ-1 Satellite is Imaging multi-spectral radiometers (vis/IR).


The Movement of the SAA South Atlantic Anomaly is Slow-moving.


The Mass at Launch of the Spacecraft Satellite is 2093 kg.


The Mission Type of the FITSat-1 Satellite is Non-EO.


The S/C Design Life of the Payload Satellite Payload is Up to 12 years.


The Crash Date of the SMART-1 Satellite is 3 September 2018.


The CCDs Read-Out Chain of the MATS Satellite is Characterized.


The Launch Date of the Falcon 9 Rocket is Early 2018.


The Tracking Data Source of the A-68A Iceberg is Copernicus Sentinel-3 mission, MODIS instrument on the US Terra mission, Copernicus Sentinel-1 mission.


The Development and Lessons Learnt Presentation Date of the SMART-1 Satellite is Oct. 4-8, 2004.


The Baud Rate of the Command and Telemetry Interface Interface is 19.2 kbit/s.


The Cryogen Volume of the Instrument Dewar/Heat Exchanger is 944 liter.


The Dark Current of the Sensor Image Sensor is Negligible.


The Orbital Period of the MMO Spacecraft is 9.2 hours.


The Period of the Satellite Communication is 105.33 min.


The Bands of the SRAL SAR Radar Altimeter is C+Ku.


The Orbit Inclination of the CBAS Primary Payload is 0º.


The Publisher of the Observation of the Earth and Its Environment Documentation is Herbert J. Kramer.


The Grating Type of the OCO-3 Spectrometer is Reflection gratings.


The NRL Review Date of the TacSat-4 Satellite is 2009.


The New spectral channels of the OLCI Camera Assembly is Implemented in OLCI.


The Field of View of the MiniCOR Coronagraph is 60% of the C3 FOV.


The Critical Design Review Start Date of the Lucy Discovery Program Mission is Oct. 15.


The Grating Type of the Grating Reflection Unit Spectrometer Component is Dielectric reflection grating.


The Launch Date of the LitianicaSAT-2 Nanosatellite is June 23, 2017.


The Purpose of the DSLP Instrument is Studying characteristic macroscopic properties of ionospheric plasmas and identifying observed irregularities with possible solar-terrestrial connection related to sudden space weather events.


The Components of the ESEX Satellite is PFS (Propellant Feed System), power subsystem, command and telemetry modules, onboard diagnostics, arcjet assembly.


The Stress Level of the Reflector Film Satellite Component is 82.5 bar (1200 psi).


The Total Value of the Joint Polar Satellite System Common Ground System contract Contract is Approximately $1,919,705,269.


The Effect of Traffic Levels of the Model Atmospheric Model is Increased coverage from contrail cirrus clouds, with an increased optical thickness of the ice clouds.


The Operator of the OrbView-1 Satellite is Orbital Imaging Corporation (ORBIMAGE).


The Closest Approach Date of the Rosetta Spacecraft is 13 November 2007.


The Size of the Hofsjökull Glacier is Third largest in Iceland.


The Impact on Numerical Weather Prediction Models of the MiniRad Microwave Radiometer is Largest positive impact of any assimilated observation.


The Spectral Coverage of the TANSO-FTS Sensor is Unknown.


The Mass of the Chang'e-4 lunar probe Lunar Probe is 400 kg.


The Spectrometer Type of the The Rossi Explorer Satellite is Timing.


The Antenna Type of the XSAR SAR Sensor Subsystem is Active phased array antenna.


The Volume of the ORA Offset Reflector Antenna is 1230 x 1010 x 905 mm.


The Mass of the HEPD Instrument is 2.2 kg.


The Observation Date of the ACE - Advanced Composition Explorer Satellite is April 21, 2016.


The Planned Satellite Name of the Capella Space Company is Sequoia.


The Contract Signing Date of the Arctic Weather Satellite Satellite is 09 March 2021.


The Number of Stars' Rotation Rates Measured of the Kepler Telescope is More than 750.


The X-band Transmission Speed of the NigeriaSat-2 Satellite is Up to 210 Mbit/s.


The Energy Measurement Range of the HEPD High Energy Proton Detector is 1 - 1000 MeV.


The Final Parking Time of the Philae Lander is 17:31:17 GMT.


The Imagery of the ResourceSat-2 LISS-3 Satellite is Data.


The Viewing Angle of the ELENA Sensor is 4.5º x 76º.


The Mass of the Companion Star Star is About half the mass of the Sun.


The Start Time of the Asteroid Day TV Online Program is 30 June at 12:00 CEST.


The Manufacturer of the Electrical Power Subsystem (EPS) Power Regulation System is Clyde Space.


The Real-time Navigation Data Frequency of the DIOGENE Navigator is Every 30 s.


The Pursuit Monostatic Phase of the TanDEM-X Satellite is Sept. 20, 2014, to the end of March 2015.


The Orbital Period of the ISS Space Station is 90 minutes.


The URL of the Submerged Sources of Transient Acoustic Emission from Solar Flares Research Paper is https://iopscience.iop.org/article/10.3847/2041-8213/abad2a/pdf.


The Survive Without Damage of the DC-DC converter Power Converter is ±50 V on input terminals.


The Local Equatorial Crossing Time of the Tatiana-2 Satellite is 12:00 hours.


The Pixel Count of the Kruiz CCD Detector is 1024 x 128.


The Level-0 Products of the Sentinel-1 Satellite is Compressed, unprocessed instrument source packets, with additional annotations and auxiliary information to support the processing.


The Pixel size of the 16 mm camera Camera is 8 μm x 8 μm.


The Embankment Length of the Ataturk Dam Dam is 1,820 m.


The Prime Contractor of the IASI Instrument is CNES.


The Maps of the Free-air and Bouguer Gravity Anomaly Data is Free-air (left), Bouguer (right).


The Instrument Types of the Megha-Tropiques Satellite is Earth radiation budget radiometers, Imaging multi-spectral radiometers (passive microwave), Atmospheric temperature and humidity sounders.


The Number of Satellites of the Falcon 9 Rocket is 60.


The Input Current of the Buck-Boost Converter Solar Array Regulator is 0 - 16 A.


The Conference Presentation Date of the CubeSat TestBed 1 Satellite is Aug. 10-13, 2009.


The Mission Type of the NeuSAR Satellite is EO.


The Area Coverage of the CHORUS Satellite is 63% of the area around the ice limit border.


The Launch Date of the IDEA OSG 1 Microsatellite is 2018.


The Discharge of the Yellowstone River River is 51,400 cubic feet per second.


The Orbit Position of the BeiDou-1D Satellite is GEO, 58.75º E.


The Orbit Type of the Satellite PAZ is Sun-synchronous dawn-dust orbit.


The Coverage of the Konnect Satellite is Sub-Saharan Africa.


The Global Coverage Date of the BeiDou-2 Navigation Satellite System Satellite System is 2020.


The Presentation Date of the Navy GEOSAT follow-on altimeter Altimeter is Feb. 1-8, 1997.


The Mission Start Date of the Solar Dynamics Observatory Satellite is Feb. 5, 2010.


The Cube Volume of the E1P-2 CubeSat Satellite is 10 cm.


The Dry Mass of the Göktürk-1A Satellite is 1,060 kg.


The Funding Date of the BRITE Satellites Satellite is 2010.


The Manufacturer of the Safe-mode Computer Computer is ÅAC Microtec.


The Transfer Phase End of the LUMIO Satellite is Halo Injection Maneuver.


The Event of the Stockholm Glacier Memorial Glacier is IPCC fifth assessment report approval session in 2014.


The Measurement of the GeoCARB Satellite is Solar-induced fluorescence.


The Electron Energy Resolution of the REPT Instrument is 25%.


The Members of the Providers Forum Committee is China (CNSS), EU (Galileo, EGNOS), India (IRNSS, GAGAN), Japan (QZSS, MSAS), Russia (GLONASS), and USA (GPS, WAAS).


The Purpose 3 of the PW-Sat CubeSat is Testing of the satellite communication system.


The Sustained Winds of the RapidScat Scatterometer is 45 m/s (162 km/hr).


The Functionalities of the ICPS System is Generation of image collection plan, management of image collection planning status, managing resources related to the SAR payload operation.


The Dynamic Range of the Magnetic Field Measurement System Instrument is 60 dB.


The Mass of the MW Instrument is 1.625 kg.


The Anomalous Jet Firing ?V of the ICE (International Cometary Explorer) Spacecraft is 32 m/s.


The Operation Principle of the STROFIO Instrument is The start time is imprinted on the trajectory of the particle by a radio frequency electric field, that bends the trajectory in a given plane, and the stop time is the time when the particle reaches the detector.


The Landing Date of the Chang'e-4 Lunar Spacecraft is January of this year.


The Function of the VMC Camera is Visual Monitoring.


The Input Voltage of the Buck-Boost Converter Solar Array Regulator is 60 - 150 V.


The Solar Panels of the DebriSat Satellite is 3 deployable.


The Frequency of the Space Micro µSTDN S-band Transponder is S-band.


The Number of Pixels of the Band 1 Spectral Band is 1600.


The Potential Repeat Cycle of the MSU-SK Radiometer is 3-5 days.


The Average Power Supply of the EPS Electrical Power Subsystem is 50 W.


The Data Transport Standards of the SPA Interface Standard is USB 1.1 limited to 12 Mbit/s, SpaceWire 400~600 Mbit/s.


The Attitude Measurement Devices of the Spacecraft Satellite is Miniature Spinning Sun Sensor (MSSS), two single-axis Inertial Reference Units (IRU), and a Flux Gate Magnetometer (FGM).


The Components of the Communications Payloads Payloads is Common, monolithic LNAs (Low Noise Amplifiers) and T/R (Transmit / Receive) switching protection circuits.


The Modulation Scheme of the VHF and UHF Links Communication Links is GMSK (Gaussian Minimum Shift Keying).


The Coverage Regions of the MOMS-02 Instrument is General.


The Velocity of the QUESS Satellite is 8 km/s.


The Energy Threshold of the CRaTER Cosmic Ray Telescope is >10 MeV.


The Agreement Date of the FormoSat-7/COSMIC-2 Satellite Satellite is October 2017.


The Communication Status of the MarCO CubeSat is Silent.


The Cross-Calibration Target of the CloudSat Satellite is Ocean surface.


The On-Orbit Operations of the SENSE Satellites Satellite is August 8-13, 2015.


The Volume of the Xenon Gas Tank Propellant Storage is 49 liter.


The Testing Start Date of the Prichal Module is Early October 2021.


The Mass of the SAGE-III Instrument is 76 kg.


The Risk of the Van Allen Probes Satellite is Earth could be at risk for up to trillions of dollars of damage.


The Time Resolution of the MTEL Space Telescope Telescope is 1,000 times better than CCD cameras.


The Instrument Concept of the GeoSTAR-III Satellite System is Unknown.


The Orbit Type of the QuakeSat Satellite is Near-circular sun-synchronous dawn-dusk orbit.


The Operation Principle of the EMP (Electromagnetic Pump) Pump is Utilizes the Lorentz body force to propel the electrically conductive fluid inside the toroidal channel.


The Entrance Slit Dimensions of the Spectrometer Instrument is 0.3 mm x 7 mm.


The Purpose of the Vizcaíno Biosphere Reserve Biosphere Reserve is Important whale sanctuary for the North Pacific grey whale.


The Imager Start Date of the IBEX Satellite is Late 2016.


The Bore Site Shift of the OCO Instrument CO2 Channel is ~70 arcsec.


The Device Operating Temperature of the Gaia Satellite is 130 K.


The Thermal Conductivity of the Carbon-Carbon Radiator panel Radiator Panel is 230 W/m K.


The CCD Detector of the PS0 Optical Instrument is 11MP.


The Wavelength Range of the S-020 XUV Spectrograph is 1-20 nm (or 10 - 200 Å).


The Spectral Sampling Interval of the HR Spectrometer Spectrometer is 0.0933 nm/pixel.


The Challenge of the Attitude Control System Satellite System is Inability to achieve sustained nadir pointing.


The Detector Type of the TIR Subsystem Imaging System is Mercury cadmium telluride (HgCdTe).


The Primary Images of the PROBA-V Satellite is 14.021.


The Pointing Accuracy of the MWI Instrument Scan Mechanism Assembly is Unknown.


The Number of Channels of the SMMR Scanning Multispectral Microwave Radiometer is 10.


The Power of the L-band Transmitter Radio Transmitter is 10 W.


The Operational Mode of the Aquarius Radiometer System is Standby.


The Vertical Resolution of the OMPS UV Hyperspectral Imaging Spectrometer is 1 km.


The Staffing of the Ground Segment Ground Segment is 24 hour period during the mission.


The Primary Semi-Major Axis of the Didymos Binary System is 1.1 km.


The Components of the Drum Mounting Assembly is Digital data subsystem, power and the signal transfer assembly.


The No. of Bins of the SPIM1 Spectrometer is 68, 136, or 272.


The Role of the Space Development Agency Agency is Accelerate delivery of needed space-based capabilities to the joint warfighter.


The Contents of the Level-3 Data is Spatially and temporally averaged data of geophysical parameters.


The Measurement Domain of the ISS:LIS Lightning Imaging Sensor is Atmosphere.


The Swath Width of the MWR Dicke Radiometer is 380 km.


The Mass of the MKA-N 2 Satellite is 10 kg.


The Initial Size of the OneWeb Satellite Constellation is 650.


The Transiting Exoplanet Survey Satellite of the TESS Space Mission is Upcoming.


The Spectral Bandwidth of the SWIR Spectrometer Spectrometer is 10 nm.


The Swath Width of the PamCam Panoramic Camera is Approximately 250 km.


The Orbital Period of the Planet Candidate Exoplanet is Roughly every 70 years.


The Upload Data Rate of the IXPE Satellite is 2 kbit/s.


The Function of the POAM-II Payload System is Provide a measurement of the vertical distribution of atmospheric ozone, nitrogen dioxide, aerosol extinction, water vapour and temperature.


The Fine-Pointing Capability of the ATLAS-1 Satellite Mission is Limited.


The Contents of the Level-1A Data is Granule scene sensor output data with geolocation and radiometric correction information.


The Number of Detectors of the SIS (Scanning Imaging Spectrograph) Spectrograph is 2.


The Diameter Range of the Kuiper Belt Object Celestial Object is 50 to 2,000 kilometers.


The Resolution of the HIT High-energy Ion Telescope is 1 min.


The Power of the Instrument Sensor is 35 W average.


The Primary Use of the Band 2 Spectral Band is Daytime clouds, vegetation, water.


The Mass of the SARAL spacecraft Satellite is 407 kg.


The Sun Size Comparison of the TRAPPIST-1 Star System is Not much bigger than Jupiter.


The Material of the Cold Plates Thermal Management Component is Stainless steel channelling enclosed in an aluminum casting.


The Forecast Date of the Hurricane Michael Tropical Cyclone is 8 Oct 2018.


The Mask Material of the Optical Head Optical Device is Steel.


The Magnetic Cleanliness Requirement of the Magnetometers Instrument is Sub nT-range for VFM and ASM.


The Communication Reestablishment Date of the STEREO-B Satellite is Aug. 21, 2016.


The Latency of the ATL16 ATLAS Atmosphere Weekly Data is 45 days from receipt of last data in product.


The Isp of the Hydrazine system Orbit control subsystem is 210 s.


The Model of the OBC On-Board Computer is GomSpace NanoMind A712D.


The Bands of the Optical Sensor Assembly (OSA) Instrument is Four multispectral bands and one panchromatic band.


The Announcement Date of the XMM-Newton Satellite is Dec. 21 2007.


The End of life date of the Meteor-M-2 Satellite is 31 Dec 2030.


The LTAN of the Main Payload Satellite is 10:39 hours.


The Distance from the Sun at Expected Perihelion of the Comet ATLAS Comet is Around 37 million kilometers.


The Number of Satellites of the Lightspeed Satellites Satellite is Nearly 300.


The Launch Start Date of the Transport Layer Satellite Network is Late 2024.


The Spectral Resolution of the HR Bands (677–686 nm, 740–759 nm and 769–780 nm) Spectral Bands is Principally driven by the slit width (Figure 23a).


The Ground Segment of the CO2Image Satellite is DLR’s Space Operations facility.


The Manifested Date of the ELaNa-4 CubeSats Satellite is March 1, 2013.


The GPS Receiver of the RAX-1 Satellite is Operated as predicted and maintained lock in the experimental zones.


The Broadcast Bands of the First Batch of Satellites Satellite is "Ku" band.


The FOV for VNIR-P pushbroom scanning of the VNIR-NP Imager is 55º.


The Conference Date of the High Data Rate Optical Inter-Satellite Links Communication System is Sept. 20-24, 2009.


The Outflow Channels of the Milky Way Galaxy is Above and below the plane of the Milky Way.


The Period of the Lateral Shearing Angular Period Device is 200 µrad.


The Instrument Power of the AATSR Instrument is 100 W.


The Measurement Accuracy - Location of the Instrument Sensor is 1 pixel.


The Size of the Sundancer Spacecraft is ~180 m3.


The Sample Rate of the MGF Instrument is 160 per second.


The Average Power Consumption of the Instrument Instrument is 5.6 W.


The Impact of the CATS Lidar Instrument is Enabled more accurate aerosol modeling and forecasting.


The Spatial Resolution of the TAC Camera is 2.1 m.


The Launch Date of the FASat-Alfa Satellite is August 31, 1995.


The 3σ Low Result of the Close Approach Distance Parameter is 1.45 km.


The Mass Data Storage of the DubaiSat-2 Satellite is 256 GBit.


The Launch Date of the SkySat-4-7 Satellite is September 16, 2016.


The Alias of the AstroBus-L platform Satellite Platform is AstroSat-250 (AS250).


The Number of Satellites Launched of the Starlink Communication Satellite is 60.


The Scanning Pattern Loss of the OGS Ground Station is Applies during initial acquisition.


The Launch Date of the OFEQ-1 Satellite is September 1988.


The Checksum Size of the Raw Science Data Packet Data Packet is 1 byte.


The Mass of the ZASat-002 Microsatellite is 82 kg.


The Retirement Date of the Kepler space telescope Telescope is 2018.


The Energy Resolution Improvement of the NICER X-ray Timing Instrument is A factor of 8 improvement.


The Function of the SAR Controller Electronics SAR Controller Electronics is In charge of the command and control of the SSS to achieve the SAR mission.


The On-Orbit Duration of the CanX-5 Satellite is More than one year.


The Ion energy of the Microdosimeter A Instrument is > 1 MeV.


The Capacity of the NiH2 batteries Power Source is 12 Ah.


The Inclination of the Secondary Payloads Nanosatellites and CubeSat is ~51.6o.


The Closest Edge Distance from Earth of the Heliosphere Space Phenomenon is More than ten billion miles.


The Mirror Alignment Continues Date of the Webb Satellite is 25 February 2022.


The Minimum Value of the Spectral Angle Measurement is Achieved when the yellow-gold reflection of the satellite bus is prominent.


The Band of the SWIR Camera Imaging System is 0.9 to 1.7 µm.


The Launch Year of the Capella X-SAR Constellation Satellite Constellation is 2018.


The Bandpass of the COR1 Coronagraph1 imager is 648-750 nm.


The Pointing Accuracy of the S/C Satellite is Within 5-10º.


The Volume of the GHGSat-D Microsatellite is 20 x 30 x 42 cm.


The Cross-Calibration Latitude of the CloudSat Satellite is 12 degrees.


The Area Collection Rate of the Pushbroom Sensor is Very high.


The Signal Data Provider of the AMBER IOD-3 CubeSat is National Maritime Information Centre (NMIC).


The Size of the Hayabusa-2 Space Probe is Fridge-sized.


The Signal to Noise of the Polar Scout Satellite is Best at high elevation angles.


The Mass of the Satellite Observation Instrument is 19.6 kg.


The Up to 15 W of the CLAVIS Power Generation is True.


The Operational Duration of the OPAL Satellite is 29 months.


The SRAMs Memory of the RADMON Radiation Monitor is 4-kbit each.


The Distance from Earth of the Carina Nebula Nebula is 7500 light-years.


The Presentation Date of the MICROSCOPE Satellite is Sept. 27-Oct. 1, 2010.


The Re-Entry Survival of the QARMAN CubeSat is Yes.


The Decade-Daily Global Composite Products of the PROBA-V Satellite is 36.


The Design and Performance of the Dual-channel Radiometers for Earth and Atmosphere Monitoring (DREAM) Radiometer is Protoflight Model.


The Orbit of the AVUM Spacecraft is Final Orbit (1450 km x 1450 km, i=69.5º).


The Size of the Reaction Wheels Attitude Control System is Large (0.2 Nm, 12 Nms).


The Flight Results Presentation Date of the BIRD Onboard Navigation System Navigation System is Oct. 22-25, 2002.


The Threshold programmability of the PHA Detector is Up to 6% of full scale.


The Manufacturer of the PP Twin Telescopes Telescope is SAGEM-REOSC.


The Data Usage of the Copernicus Sentinel-5P Satellite is Track and attribute methane emissions.


The Power of the ADCS Attitude Determination and Control System is 0.66 W.


The Power Protection Design of the FormoSat-5 Satellite is Unknown.


The Minimum Separation for Distinguishing Spacecraft of the TIRA Radar Tracking Station is 5 km.


The Spatial Resolution of the IRIS Instrument Spectral Scanner is 10 m GSD.


The Launch Date of the MSG-3 Satellite is July 5, 2012.


The Wavelength Range of the SWIR Detector is 1.58 - 2.49 μm.


The Conference Date of the EarthCARE/CPR Satellite is Sept. 24-27, 2012.


The Focal Length of the TIR Subsystem Imaging System is 31.14 mm.


The Imaging Mode of the CHORUS Satellite is WideFine mode with 8m resolution.


The Freeze/Thaw State Refresh Rate of the SMAP Satellite is 2 days.


The Electric Field Property of the IVM Ion Velocity Meter is Direction parallel to the Earth's magnetic field is an electric equipotential for horizontal scales greater than 25 km.


The Purpose of the SES Instrument is Calibrate and control the photon flux.


The Satellite Bus of the Tomorrow-R1 and -R2 Satellite is Corvus-XL satellite platform.


The Components of the KSEM Instrument is Particle Detector (PD), Magnetometer (MAG), and a Satellite Charging Monitor (SCM).


The Conference Presentation Date of the TacSat-4 Satellite is Feb. 24-26, 2009.


The Units of the MWHS-II Microwave Humidity Sounder is Antenna and receiver unit, power supply unit and electronic unit.


The Swath Width of the MWNIR Imaging System is 1600 km.


The Platform Reference of the BRITE Satellites Satellite is CanX-3.


The Calibration Resolution of the Satellite Device Unknown is 1.3 k.


The Objective of the AIS Automatic Identification System is Provide a SAR data fusion capability for maritime surveillance from space with AIS data services.


The Array of the Eastman Kodak KLI14403 linear CCD sensor Sensor is 14,400.


The Image Resolution of the RapidEye Satellite Constellation is 30 cm.


The Software of the TIE Payload is BASH.


The Communication Frequency of the Spacecraft Satellite is S-band RF (radio frequency).


The Mini-commissioning Phase of the Envisat Satellite is November and December 2010.


The Orbit Offset of the ERS-2 Satellite is 2 km versus nominal ground track.


The Deployment Date of the MicroMAS-1 Satellite is March 4, 2015.


The Orbit Altitude of the Secondary Payloads Satellite is ~820 km.


The Deployment Mechanism of the CanX-7 Satellite is Stored mechanical energy.


The Image Release Date of the MERIS Satellite is Nov. 15, 2013.


The Ground Pixel Size of the HORUS Sensor is 14.6 m.


The Expected Number of AIS Signals of the ZACUBE-2 Satellite is 6000.


The CCD Array Size of the Instrument Sensor is 128 x 128 pixels.


The Size of the Tyvak 61C Satellite is 3U.


The Contribution to Environmental Monitoring of the LARES Satellite is Unknown.


The Development Status of the DRACO System is Ongoing.


The Type of the Camera Sensor Imaging System is EEV CCD04-06 image sensor + chip set.


The On-Orbit Calibration Method of the RAX-1 Satellite is Used the IGRF magnetic field model and current satellite measurements.


The Rover Operation Duration of the Tianwen-1 Probe is About 90 Martian days.


The Storage and Reuse Capability of the OWS Space Station is Yes.


The Goal of the RAIDS Experiment is Obtain a set of simultaneous airglow profiles at a number of wavelengths.


The Wavelength Range of the NIR Detector is 0.83 - 1.74 μm.


The Ka-band System of the STPSat-6 Satellite is Transmit up to 622 Mbit/s.


The Cross-Track Separation of the TDX and TSX Satellites Satellites is 3600 m over the equator.


The Operation Attitude of the Satellite Communication is Maximum power generation attitude with the –Z satellite face sun pointing.


The URL of the BepiColombo Mission is http://sait.oat.ts.astro.it/MSAIS/20/PDF/127.pdf.


The Whistler Waves Amplitudes of the Van Allen Probes Satellite is Unusually large.


The Position Accuracy (RMS orbit) of the S-3 NTC Product is 3 cm threshold with a target of 2 cm (radial).


The Purpose of the Gasket Satellite Component is Create a light-tight seal.


The Objective of the APD detector Experiment is Observe the low energy charged particle density distribution in LEO (Low Earth Orbit).


The Groundtrack Mission Requirement of the EO-1 Satellite is Fly over the current groundtrack of Landsat-7 within ±3 km.


The Stabilization of the AOCS Attitude and Orbit Control Subsystem is Three-axis.


The NASA URL of the BioSentinel Satellite is https://www.nasa.gov/centers/ames/engineering/projects/biosentinel.html.


The Data Delivery of the Science Data Interface Interface is 1/8/64 science data packet(s) every 3 seconds.


The Mission of the Roman Satellite is Provide 3D images of the universe.


The Operational Date of the QUESS satellite Satellite is January 19, 2017.


The Mass of the Propulsion Satellite Subsystem is 1.1 kg.


The Launch Date of the OneWeb Satellite Constellation is 7 February, 2020.


The Performance Check Modes of the ARC Active Radar Calibrator is Receiver mode, Transmitter mode, Transponder mode with delay.


The Mission Concept & Status of the TanDEM-X Satellite is Not Provided.


The GMU Modification of the I-COUPS Satellite is Addition of CTU and modification of GMU.


The Simulation Study of the Solar Wind Electric Sail Propulsion System is P. Janhunen, A. Sandroos.


The Solar Panels of the Lander Spacecraft is Vertical panels.


The Attitude Error of the AOCS Attitude Control System is <0.3º.


The Thrust of the Steam Propulsion Unit Propulsion is 4 mN.


The Additional Contract Award Date of the SARah project Satellite Project is 7 August 2019.


The Approx. peak sensitivity altitude of the Channel 8 Sensor is Unknown.


The Microcontroller of the On-board Computer Computer is Motorola 68332.


The SCI ports of the STRV-2 DHS Data Handling System is Six RS-422, MIL-STD-1553 S/C bus.


The Date of the Phytoplankton Productivity Down in Gulf of Maine Natural Event is 8 June 2022.


The Application of the Geostationary Communication Relays Satellite-based Service is Communication.


The Low Cost of the MTP Transponder is True.


The Number of Satellites of the PanGeo Fleet Satellite Fleet is 9.


The URL of the Miniature Integrated Camera and Imaging Spectrometer Imaging Spectrometer is http://nmp.nasa.gov/ds1/tech/micas.html.


The Purpose of the BPP Bi-axial Pointing Platform is Enable the High-Resolution Camera to point in the direction of its targets and keep its field of view stable.


The Inclination of the SAOCOM-1A and -1B Satellites is 97.86°.


The Total O3 of the O3 Profile Satellite Instrument is 9 x 10 3.


The Firing Duty Cycle of the Y-axis Bang-Bang Maneuver Satellite Maneuver is 90%.


The Application of the SAR Mode Synthetic Aperture Radar Mode is Fully polarimetric 3-D structure mode and the ultra-wide swath deformation mode.


The Data Center of the Euclid Satellite is CosmoHub hosted by PIC.


The Band 2 of the CIRiS Instrument is 9.85 µm to 11.35 µm.


The Payload of the MPQ442 Satellite is OpenSpace365.


The Mission Quantity of the CubeStack Multi CubeSat Adapter is 2.


The Conference Date of the CHIPS Satellite is Aug. 11-14, 2003.


The Importance of the SMAP Satellite is Understanding of Earth's cycles.


The Operator of the Resurs-P1 Satellite is Roskosmos.


The Onboard Data Storage Capacity of the XMM-Newton Satellite is None.


The Axis Orientation Accuracy of the Resurs-DK1 Spacecraft is 0.2 arcmin.


The URL of the SpaceX CRS-24 Mission is https://www.issnationallab.org/iss360/spacex-crs-24-mission-overview/.


The Geolocation Accuracy of the Imager Imaging System is ≤ 3 m.


The URL of the THERME experiment Experiment is http://esmat.esa.int/Materials_News/ISME09/pdf/10-In-flight/Remaury%20Paper.pdf.


The Extreme to Exceptional Dryness Percentage of the U.S. Drought Monitor Report is 83 percent.


The Long-Term Acquisition Plan Publication Date of the Landsat-7 Satellite is Oct. 2006.


The Detector Operation of the SIS (Scanning Imaging Spectrograph) Spectrograph is Selected by a “pop-up” mirror.


The Wavelength Range of the SiPD Detector is 0.50 - 0.90 µm.


The Manufacturer of the Ozone Mapping and Profiler Suite-Nadir (OMPS-N) Instrument is Ball Aerospace.


The Manufacturing Process Controls of the Frangible Joint System Satellite Component is Sufficient to assure that variability in materials properties and hardware component dimensions, within both maximum and minimum tolerances, will not invalidate design performance requirements.


The Number of Bands of the OHIS Imaging System is 80.


The Mass of the FLP Satellite is 120 kg.


The Ku-band Link Availability of the Bartolomeo Payload Communication System is 70 - 90%.


The Contact Operations of the COSMOS Mission Operations System is Pre-contact operations, real-time contact operations, and post-contact operations.


The Number of Satellites of the Starlink Communication Satellite is 422.


The Exceeded Design Life of the Jason-1 Satellite is Yes.


The Connector Type of the Antennas Communication is MMCX.


The Payload of the ZACUBE-2 Satellite is SDR-based payload that will provide AIS and VDES services.


The RF Link Speed of the BILSAT-1 Satellite is 2 Mbit/s.


The Mission of the Satellogic Company is Build an accurate and up-to-date picture of our planet.


The Weather Data of the Spire Global Satellite is Improve Maritime Vessel Performance and Reduce Carbon Emissions.


The Activation and Calibration Time of the SAGE-III Instrument is Approximately 90 days.


The Docking Date of the Intelsat 901 Satellite Communication Satellite is 27 February 2020.


The Maximum Satellite Mass of the AD-SS 200 Satellite Dispenser is 200 kg.


The Minimum Looks in Range of the Radar Sensor is 12 looks for 3 km cells.


The Telemetry S-band of the RF communications Communication Subsystem is 0.1 W, 9.6 kbit/s.


The Mission Date of the NovaSAR-1 Satellite is Sept. 13-14, 2012.


The Mission Start Date of the HEOSS High Earth Orbit Space Surveillance is Late 2015.


The Components of the DDS Deployment Detection Subsystem is COTS camera.


The Instrument Behavior of the OCO-2 Satellite is Change in flight.


The High Energy Telescope Energy of the CRS Cosmic Ray Subsystem is 70MeV.


The Faraday Rotation of the AIS System Communication System is Inversely proportional to the square of the frequency.


The Network Type of the Iridium NEXT Satellite Constellation is IP-based, broadband.


The Distance from Earth of the Kepler-1649c Exoplanet is 300 light-years.


The Bus Design of the ERG Satellite is Small science satellite bus design.


The Number of Cameras of the MoonKAM Camera System is 4 on each vehicle.


The Range of the Incident Particle Energy Range Parameter is > 20 MeV (H), > 87 MeV/nucleon (Fe).


The Band 5 of the R3 Sensor Sensor is Red.


The Spectral Range of the TIR Thermal Infrared region is 2.15-2.25 µm.


The Mechanisms of the Aerosol Indirect Effect Atmospheric Phenomenon is Clouds with smaller droplets appear to be thicker to visible-light wavelengths and clouds that are more polluted are believed to be less likely to produce rain or snow.


The Actual Launch Date of the Spacelab-1 Satellite is End of November 1983.


The Function of the Antenna System Communication System is Receive GRB and legacy GVAR downlinks.


The Release Date of the DCAM3 Deployable Camera is 5 April 5 at 2:14 UT.


The Aperture Size of the Reflector Assembly Satellite Component is 14 m.


The Data Compression of the Onboard Data Handling Subsystem (OBDH) Data Handling System is Achieving compression ratios of 2.28 - 2.8.


The Detection Limit for Water Ice of the LEND Neutron Detector is ~0.1 wt%.


The Orbit Position of the Vigil Spacecraft is L5 (Langrage Point 5).


The Manufacturer of the European Robotic Arm Robotic Arm is Unknown.


The Actual Orbit Duration of the Skylab-1 Space Station is Prematurely decayed.


The Launch Date of the Dnepr Rocket Rocket is June 19, 2014.


The L0 Product Destination of the EnMAP Satellite is DIMS Product Library.


The Integration Date with GEOSS of the GMES Program is 2016.


The Mechanical Coupling of the Readout Electronics Electronics is No.


The Relative Position of the AC4-B Satellite is Below AC4-A.


The Method of the Data Transmission Process is Placing it into an ftp-site with password protection.


The Track Spacing of the ERS-1 Satellite is ~8 km at the equator.


The Function of the V5 Sensor Sensor is Makes a simple voltage measurement near the magnetometer boom and may be used to infer the sunward electric field for plasma waves.


The Checkpoint Maneuver Altitude of the OSIRIS-REx Spacecraft is 410 feet (125 meters).


The Purchase of the THEMIS Satellite Constellation is Alliant Techsystems Inc. (ATK).


The Power of the Solar panels Power subsystem is about 35 W/panel (BOL).


The Design Review Date of the IRIS instrument Instrument is December 2010.


The Launch Pad Explosion Date of the SpaceX Falcon-9 Rocket is Sept. 1, 2016.


The Spatial Resolution of the SLSTR Spectral Imaging Instrument is 1 km.


The Data Rate of the LISS-4 Camera is 105 Mbit/s.


The Launch Date of the GeoEye-1 Satellite is September 2008.


The Previous Record Discharge of the Yellowstone River River is 32,200 cubic feet per second.


The Validation Tests of the OCK (Orbit Control Kit) Orbit Control System is Three short tests lasting up to several days, followed by a 4th extended test that lasted two weeks.


The Operation of the SEXTANT XFSW Navigation System is Observes MSPs, processes photon events, updates spacecraft state.


The Grid of the Phantoms Mannequin Torsos is Three-centimeter grid embedded throughout the torsos.


The Photon Counting Rate of the PSR B0531+21 Pulsar is Poisson Distribution.


The Type of the DERA-patented carbon-composite joint Spacecraft Structure is Novel.


The Diameter of the Central Obstruction Optical Component is 68 mm.


The Thrusters of the Hydrazine system Orbit control subsystem is Four 1 N thrusters.


The Measures of the EMUS Spectrometer is Oxygen and carbon monoxide in the thermosphere and the variability of hydrogen and oxygen in the exosphere.


The Maximum Number of Transmission Attempts of the Drifting (Mobile) Platforms Ground Segment is 5 - 6.


The Along-Track Resolution of the Copernicus Sentinel-6 Poseidon-4 Radar Altimeter is About 300 m.


The Beam width of the X-band Band is 0.15 rad.


The Time to First Stage Landing of the Falcon 9 Rocket is Eight and a half minutes.


The IMU of the PSSCT-2 Satellite is COTS MEMS IMU (Inertial Measurement Unit) from Analog Devices.


The Average of the Power Consumption System is 2.4 W.


The Spectrometer Type of the INMS Ion Neutral Mass Spectrometer is Gated time-of-flight.


The Research Contract Date of the Capella Space Company is 17 June 2021.


The Image Delivery Time of the 24/7 Emergency Image Delivery Service Service is Averaging two hours after acquisition.


The Lifetime of the OFEQ-2 Satellite is 6 months.


The Antenna Aperture in the Azimuth of the P Mode Observation Mode is 7.5 m.


The Budgets of the Spacecraft Spacecraft is Mass, Power, Data.


The Function of the Microprocessor Component is Grouping the measurements into a packet and sending them over the I2C bus to the OBC for downlink transmission.


The Magnification of the HSC Spectrometer Spectrometer is 1:1.


The Material of the RX-M2 Tower Structure is CFRP skins.


The Perigee of the COMPASS-2 Satellite is 402 km.


The Calibration Status of the Satellite Spacecraft is Calibrated.


The Development Start Date of the SARah project Satellite Project is 19 September 2013.


The Number of Participating Students of the YES2 Satellite is About 400.


The Performance Improvement of the IASI-NG Instrument Spectral Resolution is 2 times.


The Operation Status of the Genesis-2 Satellite is Nominal in 2013.


The Affiliation of the Carlos Flores Engineer is Unknown.


The Constellation Size for Weekly Remapping of the Satellite Constellation Satellite Constellation is About 90 satellites.


The Communication of the CICERO satellites Satellite is X-band downlink of payload data.


The Launch Date of the POPSAT-HIP1 Satellite is June 3, 2014.


The Orbit Period of the Sentinel-2 satellites Satellite is 101 minutes.


The Center Frequency of the Radar Instrument is 1.26 GHz.


The Launch Site of the Crew Dragon Spacecraft is Kennedy Space Center.


The Communication Experiment Date of the ARTEMIS satellite Satellite is Sept. 23-27, 2013.


The Payloads of the Carbonite Series Small Satellite Platforms is Visible, MWIR, and X-band radar wavelengths.


The Purpose of the GeoXO Satellite System is Advance Earth observations from geostationary orbit.


The Antenna Scan of the MSR Radiometer is Oscillating 10° either side of nadir.


The Mass of the KGI-4C Instrument is 12 kg.


The SCI of the OBC Onboard Data Handling is 38.4 kbit/s.


The Number of Alerts Per Day of the SKA Square Kilometre Array is Unknown.


The Thruster Type of the GPIM Propulsion System is Aerojet Rocketdyne GR-1 1-N class.


The Detector Technology of the SIS (Scanning Imaging Spectrograph) Spectrograph is Position-sensitive anode.


The Mission Tasks of the Chang'e-4 Probe is Low-frequency radio astronomical observation, surveying the terrain and landforms, detecting the mineral composition and shallow lunar surface structure, and measuring neutron radiation and neutral atoms.


The Center Wavelength of the MS1 (NIR1) Imager is 831 nm.


The Apogee of the Chang'e-1 Satellite is 51000 km.


The Spatial Resolution of the SPOT 1-5 Satellite is From 20 m to 1.5 m.


The Magnetometer Collections of the QuakeSat Satellite is Nearly 2000.


The Pixel Size of the Detector Imaging Device is 15 µm.


The Ground Location Accuracy of the AOCS Attitude and Orbit Control Subsystem is < 220 m.


The Type of the LCT Technology Demonstration Payload is Unknown.


The Center Wavelength of the Band No. 30 Spectral Band is 891.11 nm.


The On-Board Processing Time of the HyperScout 1 Hyperspectral Imager is About one minute.


The URL of the Next Generation Gravity Mission Elements of the Mass Change and Geoscience International Constellation Satellite Mission is URL: https://www.mdpi.com/2072-4292/13/19/3935.


The Function of the Ground Software Data Processing is Search the optical counterparts of the GRB.


The Pupil Diameter for HR of the Instrument Hyperspectral Imager is 75.6 mm.


The Project Name of the XI-IV Picosatellite is XI-IV.


The Charge Range for Elements of the LEICA Particle Detector is 1 - 26.


The Altitude of the First Batch of Satellites Satellite is 550 km.


The Launch Year of the RADARSAT-2 Satellite is 2007.


The Attitude Control of the CanX-4&5 Satellite is 1.0º.


The Spacecraft of the SpaceX Launch Provider is Dragon.


The Mission Start Date of the CryoSat Satellite is Unknown.


The Conference Presentation Date of the Plug-and-play System Spacecraft Components System is Aug. 13-16, 2007.


The Operational Status of the Jason-3 Satellite is Operational as of August 2022.


The Test Completion Date of the Konnect satellite Satellite is 6 September 2019.


The Required Precision of the O3 Profile Satellite Instrument is 3%.


The Sensor complement / remarks of the Meteor-2-1 Satellite is TV, IR, SM, RMK-2 (experimental).


The Focal Length of the UVS Instrument Spectrometer Telescope is 250 mm.


The Energy Range of the Satellite Imaging Instrument is Above 10 keV.


The Support Component Material of the TX Telescope Telescope is Invar.


The FOV of the VIS Visible region of spectrum is ±44º (700 km swath).


The Full Well Charge of the Image Sensor Imaging is 60,000 e-.


The URL of the Copernicus Imaging Microwave Radiometer (CIMR) Radiometer is https://agupubs.onlinelibrary.wiley.com/doi/epdf/10.1029/2021JC017610.


The Bus of the NorSat-3 Satellite is NEMO bus from UTIAS/SFL.


The Resolution Δλ (0.05º slit) of the SPIM1 Spectrometer is 0.5 nm.


The Center Wavelength of the Pan (WorldView-1) Imager is 650 nm.


The Transverse Dimensions of the HXT-C X-ray Optics is 417 mm x 376 mm.


The | of the SFL Magnetorquer Magnetorquer is SFL magnetorquer.


The LI Mass of the LI Instrument is 93 kg.


The Total Range of the CERES Instrument is 0.3 - 100 µm.


The Payload of the PROBA-II Satellite is PROBA-II Payload: A Belgian Mini Space Weather Observatory.


The Mass of the Telescope Optical Instrument is 1.7 kg.


The Post-facto baseline reconstruction accuracy of the TDX/TSX Satellite is 1 mm.


The Antenna Size of the Reception Station Ground Station is 2.4 m.


The Energy Range for Electrons of the LEICA Particle Detector is 0.4-30 MeV.


The Activation Time of the LIRIS Laser Infrared Imaging Sensors is Two and a half hours before docking.


The Gain of the C-band Antenna Antenna is More than 32.5dB.


The Mapping of the Magellan Spacecraft is 1990s.


The Potential Return of the Magnetic Pole Geomagnetic Feature is Canada.


The Pointing Method of the ASTRO-1 UV payload UV Telescopes is Shuttle maneuvers and slews of the IPS.


The Number of channels of the Millimeterwave receiver Receiver is 4096.


The Unknown of the Kompsat-2 Satellite is Unknown.


The Sensitivity of the Channel 3 Sensor is 0.3 K/pixel.


The Industry Day Date of the SEOSat/Ingenio Satellite is Nov. 17, 2008.


The Components of the ORA Instrument Atmospheric Measurement Instrument is UV-visible module, infrared unit, electronics unit.


The Image Credit of the AIP (Advanced Ionospheric Probe) Probe is NCU.


The Manufacturer of the OAPs Optical System is Thorlabs Inc.


The PLSO Location of the FOS Satellite is ESTEC.


The Resolution of the Comedia C328 Camera is VGA.


The Performance of the FACT Data Distribution System is Fine.


The Temporal Resolution of the GK-2A Satellite is Improved.


The Energy Range for Neutrons of the FREND Instrument is 0.4–500 keV.


The URL of the New Horizons Spacecraft is https://www.nasa.gov/feature/nasa-s-new-horizons-reaches-a-rare-space-milestone.


The Entrance Slit of the UVS Instrument Spectrometer Telescope is 0.31 x 3.2 mm.


The Image Span of the Herschel Space Observatory is 2 x 2 degrees.


The Catalogue Release Date of the XMM-Newton Satellite is May 15, 2017.


The Orbit Altitude of the Light-1 Satellite is Approximately 400 km.


The Period of the Yubileyniy-2/MiR Satellite is 115.8 minutes.


The Purpose of the MOIS Event Monitor Event Monitor is React to different types of events, Check the consistency of the anomaly, Request the start of the contingency recovery procedure.


The Iron Particle Speeds of the WISPR Optics Optical System is 0.5 - 8 km/s.


The Manufacturer of the CesiumAstro Company is Full-scale manufacturer advancing airborne and next-generation aerospace platforms.


The Ownership of the Deimos-2 Earth Observation Satellite is Elecnor.


The Beacon Transmission Frequency of the ELFIN-B Satellite is 437.475 MHz.


The Ground Range x Product Length of the Stripmap Imaging Mode is 30 x 50 km (single pol.); 15 x 50 km (dual pol.).


The Launch Site of the GFO Satellite is VAFB (Vandenberg Air Force Base), CA.


The Nominal Operating Speed of the DCU-S(TC) module Communication Module is 64 kbit/s.


The Start Date of the Cerro Pelado fire Wildfire is April 22.


The Spectral resolution of the Millimeterwave receiver Receiver is 44 kHz.


The Processor of the C&DH Command and Data Handling is 2 x C8051F120 microcontroller.


The Assembly Date of the MARFEQ Equipment is 10-19 Oct. 10-19, 2002.


The Observation of the OCO-3 Satellite is First dawn-to-dusk observations of how SIF varies over the course of a day.


The Wavelength FWHM of an unresolved line of the Spectrometer Instrument is 0.036 µm.


The VNIR Resolution of the PROBA-V Satellite is 5200 pixel.


The Roughness of the Ir Layer Optical Instrument Component is 1.3 nm rms.


The Development Partners of the SOHLA-1 Satellite is JAXA, Tokyo University, Osaka University, Osaka Prefecture University.


The Discovery Date of the Herschel Space Observatory is November 27, 2017.


The Mission Objective of the LLITED CubeSat Satellite is Provide ionosphere and thermosphere measurements.


The Batteries Capacity of the EROS-A Satellite is 14 Ah.


The Comet Distance from Earth of the TESS Satellite is About 29 million miles (48 million km).


The News Release Date of the Spitzer Space Telescope Space Telescope is 19 December 2019.


The URL of the Gravity Recovery and Interior Laboratory (GRAIL) Satellite is http://www.lpi.usra.edu/meetings/lpsc2013/pdf/1777.pdf.


The Manufacturer of the Iris camera Camera is UrtheCast Corp..


The Manufacturer of the Composite Dispenser Dispenser is RUAG Space in Sweden.


The Rainfall Amount of the IMERG Rainfall Estimation System is Up to 10 cm (4 inches).


The Latitude Range of the PRISMA Payload Satellite Payload is 70°S - 70°N.


The Design Completion Date of the Development Status Satellite is June 16, 2016.


The Global Coverage of the ILRS Tracking Service is Yes.


The System Racks of the PM Satellite Component is 11.


The Protocol of the RF Communications Subsystem Communications Subsystem is Strandatoga.


The Frequency Response of the SCM Sensor is LF/MF range.


The Spectral Regions of the IRIS Satellite is FUV (Far Ultraviolet) and NUV (Near Ultraviolet).


The Risk Mitigation of the On-Board Computer (OBC) Computer System is In Progress.


The Attitude Range of the CHEOPS Satellite is Not provided.


The Pointing Accuracy of the IPS Pointing System is Within 1.2 arcseconds.


The Gain temperature coefficient of the PHA Detector is <50 ppm/ºC.


The Wavelength FWHM of an unresolved line of the Spectrometer Instrument is 0.098 µm.


The Gamma-Ray Measurement of the GRB 031203 Gamma-Ray Burst is About one thousand times less than expected.


The Program Timeframe of the Jason-CS Satellite Mission is 2015-2020.


The Backup Astronaut of the SpaceX CRS-17 Mission is Nick Hague.


The Productivity Decline of the Cropland Land is 15 percent in 2019 from 2018 levels.


The Frequency Band of the ICEYE Constellation Satellite Constellation is X-band.


The Magnetic Field Measurement Frequency Range of the IOF Plasma Wave Instrumentation is 40 Hz to 1.78 kHz.


The Spectral Bands of the ECOSTRESS Instrument is Five.


The Length of Observational Data Set of the Aeolus Satellite is 3 years.


The Imager Type of the Satellite Vu Satellite is MWIR.


The Cloud Area Coverage of the HARP Imaging Polarimeter is < 4 km x 4 km.


The Principal Investigator of the Juno Space Probe is Scott Bolton.


The Data Rate of the S-band transmitter Transmitter is Up to 144 kbit/s.


The Objective of the SOVA Radiometer is Measurement of the solar constant, its variability and its spectral distribution.


The Orbit Inclination of the HORYU-4 Nanosatellite is 31º.


The Orbital Altitude of the International Space Station Space Station is Relatively low over our planet.


The Project Funding of the SCIAMACHY Spectrometer is DLR/NIVR.


The Launch Date of the OPAL Satellite is Late 2016.


The High-speed raw image data processing of the Frame Grabber Computational Capacity is Sufficient computational capacity to receive and store the high-speed raw image data.


The Image Capture Date of the Payload Camera Instrument is July 29, 2018.


The Ground Station of the KySat-1 Satellite is Space Science Center at Morehead State University (MSU).


The Mission Goals of the Tandem-L Satellite is Global measurement of forest biomass, recording of earth’s surface deformations for earthquake research and risk analysis, large scale observation of ocean currents and sea ice drift, and quantification of glacier movements and melting processes.


The End Date of the ISS-RapidScat Earth Science Mission is Nov. 28, 2016.


The Operation of the Command and Data Handling Subsystem Subsystem is Autonomously schedules GPS acquisitions and uplink/downlink operations.


The Principal Investigators of the Rhodium Synthetic Cryptobiology Research Project is Drs. Heath Mills and Aindrila Mukhopadhay.


The Ka-band System of the STPSat-6 Satellite is Ability to be reconfigured on orbit.


The Bandwidth of the Capella X-SAR Constellation Satellite Constellation is 500 - 700 MHz.


The Frame Coverage of the Iris Video Camera Camera is Approximately 3.8 km x 2.2 km (UHD); Approximately 1.9 km x 1.1 km (HD).


The Minimum Success Criteria of the SMDC-One Satellite is 6 months.


The Fiber Optic Cable Diameter of the Detector Box Instrument is 3 mm.


The Sampling Latitude Range of the OSIRIS-REx Spacecraft is 85º North to 85º South.


The Swath of the LISS-4 Camera is 70 km.


The Attitude Stabilization Time of the GF-2 spacecraft Satellite is Within 150 s.


The Position of the Magnetic Pole Geomagnetic Feature is Shifting towards Siberia.


The Launch Vehicle of the SEOSAT-Ingenio Satellite is Vega.


The Optics URL of the Imaging X-ray Polarimetry Explorer Satellite is https://doi.org/10.1117/12.2275502.


The Strongest X-class flare date of the SOHO Satellite is October-November 2003.


The Function of the Reaction Wheels Satellite Component is Desaturate.


The Altitude of the EFT-1 Spacecraft is Approximately 5800 km.


The Communication Rate of the TSUBAME Satellite is More than 10 kbit/s.


The Objective of the Tatiana-2 Satellite is Measurement of TLEs (Transient Luminous Events) in Earth's atmosphere.


The Communication Bandwidth of the Pléiades Neo Satellite Constellation is Up to 1.8 Gbit/s.


The Light Intensity of the Faraday Cup Sensor is Roughly 10 kilowatts.


The Dimensions of the SAR Antenna Antenna is 3.3 m x 2.7 m.


The Quantity of the GARI-1 Instrument is Two identical GAGG instruments.


The Other Missions of the NewMag Magnetometer is ISEE-1/2 (launch Oct. 2, 1977), AMPTE-UKS (launch Aug. 16, 1984), POLAR (launch Feb. 24, 1996), and Galileo (launch 1989).


The Function of the Rowland circle Spectrograph Component is Determines the locations of slit, grating, and detector in a concave grating spectrograph.


The Field of View of the ISIS Instrument is Within 10º of the Sun-Probe line.


The Spectral Range of the Limb Sensor Sensor is 290 to 1000 nm.


The Timing of the Satnav Signals Signal is Precisely timed to a few billionths of a second.


The Age of the Cosmos 2251 Satellite is Older.


The Data Collection Status of the STP-H7 and H8 Scientific Payloads is Ongoing.


The Best Measurement Position of the IMAP Satellite is He 58.4 glow from the crosswind position.


The Gases Measured of the TEMPO Instrument is Ozone, nitrogen dioxide and formaldehyde.


The Conference Presentation Date of the Eu:CROPIS Satellite is May 16-20, 2016.


The Type of the AEEF Technology Demonstration Payload is Unknown.


The Resumption of Science Observations Date of the Chandra X-ray Observatory X-ray Observatory is Sept. 12.


The Size of the PROBA-V Microsatellite is 1 cubic meter.


The Ground Range x Product Length of the ScanSAR Imaging Mode is 100 x 150 km.


The Type of the APL’s Frontier radio Radio is Software-defined.


The Build Date of the Maspalomas MEOLUT Ground Station is Oct. 8, 2013.


The 14-Day Lunar Night of the Yutu Lunar Rover is Feb. 13, 2014.


The Data Rate for Spectra of the IRIS Observatory is Every 1–2 s.


The Primary Structure Material of the KOMPSAT-6 Satellite is CFRP (Carbon Fiber Reinforced Polymer).


The Function of the TEMBOTM EMC Material is Allows for strain energy to be "frozen" into an EMC structure by cooling the deformed laminate below the critical temperature.


The Launch Date of the PhoneSat-1 and -2 Satellite is 21 April 2013.


The Swath Width of the SIR-C Phased Array is 40 to 90 km for mapping mode (ScanSAR) images.


The Mission Type of the Gaia Satellite is Astrometric Survey.


The Eclipse Capability of the Satellite Satellite is 100 % payload operation; battery max. 75% EOL.


The Operation Period of the Skylab-1 Space Station is Up to 84 days.


The Control Room of the Aeolus Satellite is Earth Explorer control room at ESOC.


The Utilization of the ICI-5 Radiometer is Cloud ice effective radius.


The Purpose of the ASIM Instrument is Measures electric events in Earth’s upper atmosphere with cameras, photometers and X- and gamma-ray detectors.


The Components of the Robotic Servicing Platform Satellite Servicing Technology is Camera, robotic arm, fuel reserve, GN&C rendezvous and proximity operations capabilities.


The End of Life Date of the ALL-STAR Satellite is 26 May 2014.


The Spectral Range (µm) of the Band 9 Spectral Band is 0.53 - 0.58.


The Features of the Poseidon-4 Altimeter is Higher performance than the previous generation, new "interleaved" SAR operating mode, new architecture improving the role of the digital functions.


The Arrival in Mercury orbit of the BepiColombo Spacecraft is 2025.


The L1 Detectors Thickness of the HIT Sensor is 1000 µm.


The Frequency of the Receiver Communication Device is 435 MHz.


The Unknown of the Thermal Plasma Measurement Unit Measurement Unit is Unknown.


The Tracking of the Topstar GPS receiver GPS Receiver is Dual-frequency.


The PRF of the HPA High Power Amplifier is 3050 Hz.


The Number of Physical Modules of the MIRO Instrument is 4.


The Meteoritic Origin of NLCs of the AIM spacecraft Satellite is About 3% of each ice crystal.


The Steering Capability of the LISS-4 Camera is ±26º in the cross-track direction.


The Service Provision of the MetOp program Satellite Program is Continuous broadcast of its meteorological data to the worldwide user community.


The Orbit Determination Accuracy of the AutoNav Autonomous Navigation System is Later refinements improved these values substantially.


The Data of the Aeolus Satellite is Most of the dust was 3—6 km above the ground.


The Payload Spin of the Bloostar Launch Vehicle is Up to 10 rpm.


The Wavelengths of the Telescope Optical Instrument is Fe XIV 530.3 nm; He I 587.6 nm.


The Affiliation of the OSIRIS CubeSat is PSU (Penn State University), University Park, PA, USA.


The Launch Vehicle of the Aeolus Spacecraft is Vega vehicle.


The Calibration Time of the LD Output Laser Diode is Unknown.


The Manufacturer of the MCU Microcontroller Unit is Texas Instruments.


The Orbit Type of the ICEYE-X14 and ICEYE-X16 Satellites is Sun-synchronous.


The Configuration of the MTG Satellite System is Twin configuration of 3-axis stabilized satellites.


The Target of the External Calibration Calibration is Deep space, the moon, the sun, or known ground targets.


The Self-identification of the SPA Components Components is Provide information about their functions and use to the system.


The Estimated SNR of the Band 5 Spectral Band is 416.39 ± 129.03.


The Orbit Information of the SWOT Satellite is http://www.aviso.altimetry.fr/es/misiones/future-missions/swot/orbit.html.


The Manufacturer of the AMSU-A Instrument is Aerojet, a subsidiary of GenCorp.


The Number of Images of the POLO data set Image Dataset is Over 1000.


The Memorandum of Understanding Date of the Global Precipitation Measurement (GPM) Satellite is Aug. 3, 2009.


The Mass Determination Method of the EIS Sensor is Measuring velocity and total energy.


The Location of the DMMC Downlink Messages Management Center is Toulouse.


The Cloud Deck Resolution of the CIPS Instrument is 2 km.


The Ion Analysis of the Time-of-flight/position sensing section Component is Mass, energy, and angle.


The Eclipse Depth-of-Discharge of the Power Subsystem Satellite System is Only slightly higher than the LOI (Lunar Orbit Insertion) depth-of-discharge.


The Control System of the CUTE-1.7 Picosatellite is PDA-Controlled.


The Height of the Large Space Simulator (LSS) Vacuum Chamber is 15 m.


The Closest Approach Distance of the Rosetta Satellite is 3162 km.


The Final Results of the SPADUS Instrument is Planetary Space Science, Vol. 53, 2005, pp. 903-923.


The Star Sensors of the R3 Spacecraft Satellite is Two 90° offset star sensors.


The Resolution of the EIC Camera is 250 m x 250 m.


The Nominal SNR of the Band 2 Spectral Band is 1090.


The Distance from the Sun at First Perihelion of the Solar Orbiter Satellite is Around 77 million kilometers.


The Mission of the TANGO satellite Satellite is Monitoring greenhouse gas emissions.


The Affiliation of the Junichi Kurihara Author is Hokkaido University.


The Length of the Hyades Tidal Tails Tidal Tails is Thousands of light years.


The Orbital Period of the Kepler-438b Exoplanet is 35.2 days.


The Funding Source of the MOMS Optical Camera is German Ministry for Research and Technology.


The Operation of the DMC Constellation Satellite Constellation is Independently owned and operated by one nation or organization.


The Launch Date of the Meteor-1/Meteor-2/Meteor-Priroda Series Satellite Mission is 01 Jan 1993.


The Roles of the Hayley Arceneaux, Sian Proctor and Chris Sembroski Crew Members is Not specified.


The Size of the Detector Array Assembly Detector Array is 5 x 6000 (30,000 pixels or samples in cross-track).


The Sensor Volume of the R3 spacecraft CubeSat is Less than 1.5U.


The Operator of the Bartolomeo External Payload Hosting Facility is Airbus DS.


The Focal Ratio of the Lens Optical Instrument is f/1.4.


The Launch Date of the COSMO-SkyMed-4 Satellite is Nov. 6, 2010 (UTC).


The Decommission Date of the GIOVE-A Satellite is 24 November 2021.


The Conference Date of the Oculus-ASR Satellite is Sept. 11-14, 2012.


The Relative Acceleration of the LISA Pathfinder Spacecraft is Lower than ten millionths of a billionth of Earth's gravitational acceleration.


The Standard of the TM Synchronization and Channel Coding Data System is CCSDS 131.0-B-2.


The Delivery Date to ISS of the OPALS Optical PAyload for Lasercomm Science is April 20, 2014.


The Forward of the S-193 Ground Coverage is 48º.


The Dimensions of the SAR Antenna Antenna is 2.2 m x 1.5 m panels, measuring 2.2 m x 11.9 m in total.


The Arrival Date of the Cygnus Cargo Spacecraft is 14 Nov. 2017.


The Objectives of the UWE-2 Satellite is Continue the communication protocol experiments and to include technology tests related to attitude determination.


The Efficiency of the Solar Panels Power Source is 28%.


The Bus of the Payload Instruments Satellite Components is Redundant CAN (Control Area Network) bus.


The Cargo Mass of the HTV-3 H-II Transfer Vehicle is About 4600 kg.


The Launch Date of the Gaia Satellite is 2013.


The Image Quantity of the LROC Camera is Over 3,000.


The Maximum Operating Pressure of the Xenon Gas Tank Propellant Storage is 150 bar.


The Launch Date of the Apollo 15, 16, 17 Missions is 1960s.


The Event Date of the LROC Camera System is October 13, 2014.


The Purpose of the CLARREO Satellite is Accurately measuring and attributing climate change.


The Repeat Cycle of the ALOS-3 Satellite is 35 days.


The Target Size of the PRISMA Payload Satellite Payload is 30 km x 30 km.


The Frequency Bands of the GovSat-1 Communication Satellite is X-band and Military Ka-band.


The Protocol of the RF Communications Communication System is AX.25.


The Data Transmission Rate of the RF Communications Transmitter is 9.6 to 500 kbit/s in Ku-band.


The Branch of the Level-1 Processor v700 Data Processor is ALL-LICEF.


The Tether Break of the AeroCube-3 Satellite is The tether to the upper stage broke within hours.


The Payload Sites of the Bartolomeo research platform Research Platform is 13 (12 active, 1 passive).


The Golf Course Temperature of the ECOSTRESS Instrument is 23 F (13 C) cooler.


The Development Timeline of the Dellingr Nanosatellite is February 2014 to February 2015.


The Spectral Resolution of the UV-1 Spectrometer is 0.42 nm.


The Capacity Reservation of the Eutelsat Quantum Satellite is Majority.


The Mission Objectives of the BeaverCube CubeSat is Demonstrate the use of a CubeSat platform to gather important ocean and atmospheric measurements, support teaching and outreach.


The Solar Wind Speed and Beta of the ACE Satellite is ~31% lower on average from 2009 through the day 79 of 2013.


The Channel Bandwidth of the Channel Communication System is 100 MHz.


The Time to Point to the Sun and Balance Electrical Power of the TSUBAME Satellite is Within 33873 seconds after rocket separation.


The Imaging Date of the ALOS satellite Satellite is September 2013.


The Bias Error of the Aeolus Satellite is 0.4 m/s.


The Size of the CEASE-1 Instrument is 10 cm x 10 cm x 8.2 cm.


The Amplifier Gain of the Ka-band Signal is 36 dB.


The Impact Punctures of the Eureca Satellite is 71 in the outer layer of the thermal blankets.


The Applications of the MiniRad Microwave Radiometer is Improved weather forecasting, better crop yields, safer and more efficient route planning for aviation and shipping.


The Gain Setting Ability of the Intermediate Frequency Amplifier Signal Processing Component is Yes.


The Components of the FWS Band and Polarization State Selector is OPC (Optical Path Compensator), BP (Band Pass) filter, POL (Linear Polarizer) or optical path compensator, ND (Neutral Density) filter.


The Conference Date of the EarthCARE Satellite is Oct. 4-8, 2010.


The Start of Science Mission of the LISA Pathfinder Satellite is 1 March 2016.


The Enrichment of the Moon Celestial Body is Heat-producing elements.


The Coverage of the EUTELSAT KONNECT Satellite is Up to 40 countries across Africa and 15 over Europe.


The Target Availability of the SPARCS Satellite is ~3 months for targets in the ecliptic plane.


The Launch Date of the AstroSat Astronomy Satellite is 28 September 2015.


The Data Enhancement Technique of the Spire Satellite Constellation is Cutting-edge machine learning techniques.


The Science Objectives of the IMAP Satellite is LISM (Local Inter-Stellar Medium) Properties and Composition.


The Spatial Resolution of the COR1 Coronagraph1 imager is ≤ 16.0 arcsec.


The Agency of the IMAGE Satellite is NASA.


The Antenna Design of the Radio Communication Device is Omnidirectional/medium gain.


The Operation of the THEIA Satellite is Data Processing.


The Coast Phase Dates of the THEMIS Constellation Satellite Constellation is July 1 to Aug. 31, 2007.


The Slew Rate of the Spacecraft Satellite is 0.25 to 1.0º/s.


The Period of the SPOT-1, -2 and -3 Satellites is 101 minutes.


The Mass of the CEASE-1 Instrument is 1 kg.


The Data Retrieval Time of the SafetyNet Ground Data Receptor Network is Less than 28 minutes.


The length of the toroidal holographic diffraction grating grating is 50 mm.


The X-ray Nova Detection Date of the ISS, Swift Instruments is Oct. 25, 2010.


The Operational Duration of the Meteosat-7 Satellite is 17 years.


The Design Life of the Göktürk-1A Satellite is Seven years.


The Frequency Range of the MTVZA-GY Radiometer is 52-57, 91 and 183 GHz.


The Bankruptcy Filing Date of the UrtheCast Company is October 24, 2020.


The Number of Satellites of the SARah Satellite Constellation is 3.


The Pan Camera of the Payload Satellite Subsystem is 0.45~0.89 µm.


The Operation Location of the Ground Segment Satellite System is CONAE Control Center at Cordoba, Argentina.


The Orbit Altitude of the TecSAR SAR is 450 km x 580 km.


The Conference Date of the STRaND-1 Satellite is Oct. 3-7, 2011.


The Observation Coverage of the GEO Satellite Satellite is About 40% of the Earth's surface.


The Wind Speeds of the Hurricane Models Weather Model is Up to category 5 strength.


The Field of View of the VIS Camera Camera is 30º x 19º.


The Pixel Size of the SXI Spacecraft is 5 arcsec x 5 arcsec.


The Payload Systems of the SPOT-4 Spacecraft is PASTEC, POAM-II.


The Frequency (GHz) of the ICI-11 Radiometer is 664±4.2.


The Conference Presentation Date of the Earth Observation System of the Republic of Kazakhstan Satellite System is Sept. 23-27, 2013.


The Orbit Position Accuracy of the GPS Receiver Navigation System is 50 m (1σ).


The URL of the Shuttle Radar Topography Mission Satellite Mission is http://www2.jpl.nasa.gov/srtm/srtmBibliography.html.


The Orbit Type of the ICEYE-X10 Satellite is Sun-synchronous.


The Nominal Vertical Resolution of the Detector Instrument is 1 km.


The Board Quantity of the MuREM Radiation Monitor is 3.


The Pressure of the Gas Tank Propulsion System is 1.78 bar.


The Landing Site of the Chang'e-4 Lunar Spacecraft is Von Karman crater in the South-Pole-Aitken (SPA) basin.


The Geolocation Method of the NigeriaSat-2 Satellite is Precise measurement of the position and attitude of the payload.


The Processing Levels of the OSIRIS Data Processing is 1 and 2.


The Mass of the TRSR GPS Receiver is 4 kg.


The Network Redundancy of the MTG satellites Satellite is Full cross-strapping redundancy with SpW-10X routers.


The Last Data Received of the MaSat-1 CubeSat is January 9, 2015.


The Sensing Ability of the TEMPEST Sensor is Atmospheric moisture and its vertical distribution.


The Swath Width of the Scanning geometry Instrument is 2800 km.


The Tuned Wavelengths of the FUV Instrument Spectrometer is 135.6 and 155.0 nm.


The Payload Power of the SmallGEO Satellite Platform is Up to 3 kW.


The Data Quantization of the Eastman Kodak KLI14403 linear CCD sensor Sensor is 8 bit or 10 bit.


The Launch Date of the Tianwen-1 Spacecraft is July 23, 2020.


The BAQ Data Compression of the CSG-SAR Synthetic Aperture Radar is 10:6, 10:5, 10:4, 10:3, 10:2, 10:1, 10:10.


The Fabrication Project Date of the MIMOSA Satellite is April 2-6, 2001.


The Wavelength Range of the Band 5 Spectral Band is 1628-1654 nm.


The Orbit Inclination of the Starlink Group 4-14 Satellite Group is 53.2º.


The Function of the PC5 Power Supply is Supplies power to the detector, including low voltages for the preamps, high voltage to bias the detector, and a supply for the thermoelectric cooler which provides closed loop control with a maximum temperature differential of 85 °C.


The Memory Type of the Second FPGA FPGA is SRAM.


The Mass of the Flock-4v Satellite is Undisclosed.


The Interaction of the Mission Planning System is Uptakes CTDA requests into its planning cycle.


The Collaborating Institution of the MAST Satellite is Stanford University's SSDL.


The CCD Detector Assembly of the EUVI Extreme Ultraviolet Imager is Backside-illuminated, backside-thinned and pacified array of size 2k x 2k with an EUV quantum efficiency >70%.


The Observation Frequency of the Megha-Tropiques Satellite is A minimum of 4 per day over the 22°S-22°N band.


The Mission Status of the Beijing-1 Satellite is Operating nominally in 2012.


The Partner of the Weather Observation Satellite Satellite is NanoAvionics.


The Event of the Glasgow Glacier Memorial Glacier is COP26 being held in Glasgow, Scotland, UK in October 2021.


The Launch Date of the SpaceX Dragon Spacecraft is October 8, 2012.


The Firefighters of the Calf Canyon-Hermits Peak fire Fire is 1,800.


The Instrument Type of the ST5 Satellite is Magnetic field, Atmospheric chemistry, Data collection.


The Structure Designer of the Biomass Satellite is OHB in Italy.


The Affiliation of the Yukihoro Takahashi Author is Unknown.


The Senegal Population Coverage of the Astrocast Satellite Operator is Almost 5%.


The CDH Boot Sector Voltage of the MarCO-B Satellite is Approximately 3.3 V.


The Multi-channel Observation Capability of the AMI Advanced Meteorological Imager is 16 channels (4 VIS and 12 infrared).


The Components of the Microstrain 3DM-GX2 Inertial Measurement Unit is 3-axis magnetometer, three accelerometers, and a rate gyroscope.


The Number of Detector Pixels of the Long Wavelength Band Spectrometer is 512 x 512.


The URL of the Intermediate Experimental Vehicle Spacecraft is http://www.spaceflight101.com/ixv.html.


The Attitude Sensing of the AOCS Attitude and Orbit Control System is Star tracker assembly (3 star tracker heads), 3 magnetometers, and a CESS (Coarse Earth and Sun Sensor) assembly.


The Science Investigations of the ARTEMIS Probes Spacecraft is 3-D mapping of the lunar wake induced by the solar wind, Measurements of selected lunar crustal magnetic anomalies, Measurements of the lunar exosphere and surface charging, Coordinated measurements with NASA’s forthcoming LADEE mission.


The Instrument Size of the Aquajet Satellite Propulsion System is 100 mm x 100 mm x 30 mm.


The Member of the Mark Bourassa Individual is True.


The Purpose of the In-Space Relay Network Communication System is Allow continuous communications from space to ground.


The Clock Rate of the DPSK Transmitter Transmitter is 2.88 GHz.


The Launch Schedule of the Shenzhou XIV Manned Spacecraft is This year.


The Intrinsic Noise Level of the ISA Accelerometer is About 10-10g/√Hz.


The Power Consumption of the Power Electrical System is 43.5 W.


The CCD Detector Type of the MEGS Spectrograph is Back-thinned, back-illuminated.


The S/C Power of the QuikTOMS spacecraft Satellite is 228 W EOL.


The Size of the GRACE-FO satellites Satellite is 3 m x 3 m x 0.8 m.


The Depth Resolution of the FREND Instrument is ~1 m.


The Noctilucent Cloud Observation Frequency of the AIM Satellite is Late spring and early summer.


The ADCS of the MiRaTA Satellite is 3-axis stabilized.


The IR Bands of the CrIS Instrument is 3.


The Approx. peak sensitivity altitude of the Channel 6 Sensor is Unknown.


The URL of the Space Based Space Surveillance (SBSS) Satellite is http://www.afspc.af.mil/library/factsheets/factsheet.asp?id=20523.


The SAR Constellation Data Distribution of the Spacety Company is Worldwide.


The Next Close Pass of the Sun of the Solar Orbiter Satellite is March 2022.


The Control Date of the QZS-1 Satellite is Feb. 22, 2017.


The Mission Date of the KazSTSAT Satellite is Unknown.


The URL of the Electric Solar Wind Sail (E-sail) Solar Sail is http://www.electric-sailing.com/.


The Fabrication Defect of the Robusta Satellite is Prevents the CubeSat’s batteries from being charged.


The Type of the TROPOMI Instrument is Pushbroom type imaging spectrometer.


The Function of the Gyroscopes Gyroscopes is Derive the satellite rates.


The Ground Swath of the AEISS-A Instrument is Around 12 km.


The Orbital Position of the ACTS/TOS Communication Technology Satellite is GEO (Geosynchronous Earth Orbit) at longitude 100º West.


The Function of the OSCAR-QUBE Experiment is Perform extremely rapid and precise magnetic field measurements.


The Electron Production Time of the Solar storm Natural Phenomenon is 60 seconds.


The Number of Images of the DECA Descent Camera is 15.


The Upper Plate Shape of the Baumanets-2 Microsatellite is Hexagonal.


The Function of the PPS Precipitation Processing System is Create higher-level science data products, deliver science data products to the user community, provide interface to the instrument science teams, and deliver instrument commands and instrument team command requests to the MOC.


The Tandem Passes Separation of the Envisat / ERS-2 SAR Satellite is 28 minutes.


The QKD Channel Collaborator of the QUESS Satellite is Anton Zeilinger and colleagues at the University of Vienna.


The Prime Contractor of the NIRCam Near-Infrared Camera is University of Arizona.


The Orbit of the ProSEDS Tether Demonstration Experiment is Circular.


The Frequency of the Ka-band Channels Communication System is 30 GHz uplink, 20 GHz downlink.


The Rotation Rate of the Antenna Conically-scanning reflector is 14.6 rpm.


The Pixels per FWHM of the Spectrometer Instrument is 1650.


The Temperature of the Solar Panel Satellite Component is Variable.


The Mission of the BioSentinel Satellite is Detect, measure and compare the impact of deep space radiation on living organisms over long durations in deep space.


The Inclination of the ExoMars Orbiter Satellite is 74º.


The Meeting Date of the BioSentinel Satellite is 2-3 September 2-3 2015.


The Methane Detection Threshold of the iSIM-90 Imager is 150 kg/h.


The Data Receiving and Processing Stations Locations of the Kolibri-2000 Satellite is Tarusa, Obninsk (Russia), and Sydney (Australia).


The Unknown of the RapidEye Satellite Constellation is Unknown.


The | of the Douglas P. Adler Individual is Fred A. Best, Douglas P. Adler, Claire Pettersen, Henry E. Revercomb, P. Jonathan Gero, Joseph K. Taylor, Robert O. Knuteson, John H. Perepezko.


The Launch Date of the GRIFEX 3U CubeSat is January 31, 2015.


The Weight of the Windsat Instrument is 450 kg.


The Contract Value of the GeoOptics Satellite Manufacturer is $1 million.


The Announcement Date of the 2Operate and GomSpace Companies is 5 March 2019.


The Data Processing of the Sentinel-4 Satellite is Level-0 data into Level-1B data.


The Components of the Communications PCPMU Communication System is PU (Processing Unit), DSU (Data Storage Unit), MDMs (Modulator/Demodulator) assemblies, FGMs (Frequency Generator Modules), EPCs (Electric Power Control) cards.


The Frequency of the HSB Humidity Sounder is 183.3 GHz.


The Width of the Pluto's Glacier Nitrogen Glacier is 1,000 kilometers.


The Uplink Data Rate of the RF Communications Communication System is 4.8 kbit/s.


The Antenna Length of the Cluster spacecraft Satellite is 88 m.


The Controls the state of charge of a 40 Wh battery pack and distributes power to all satellite subsystems of the PCDU Function is True.


The Interrupts of the dsPIC33F microcontroller Microcontroller is Unknown.


The Payload Mass (max) of the  DSX Spacecraft Payload Module Satellite is 170 kg.


The Swath Width of the Instrument Satellite Instrument is 40 km (full mode).


The Solar Panel Efficiency of the AprizeSat Satellite is 28.3%.


The End of Life Date of the Megha-Tropiques Satellite is 15 Dec 2021.


The Number of Crews of the Skylab-1 Space Station is Three.


The Arrival Date at Space Station of the Cargo Dragon Spacecraft is December 7.


The Previous Lunar Landings of the Chang'e-5 Spacecraft is Chang’e-3 and Chang’e-4 missions.


The Launch Cost Savings of the ORS-6 Satellite Mission is 25-50%.


The Sensors of the SPOT-4 Satellite is Unknown.


The Sensitivity of the INTEGRAL Satellite is High sensitivity to gamma rays.


The Period of the ZY 1-02C Spacecraft is 100.3 minutes.


The Symbol Rate of the Transmitter Communication Device is 200 Msample/s.


The Number of Satellite Pairs of the MetOp-SG Satellite Program is 3.


The Size of the Receiver Communication Device is 70 mm x 60 mm x 30 mm.


The Power of the Spacecraft Satellite is 1260 W.


The Period of the CSG and CSK satellites Satellite is 97 minutes.


The Magnetic Field Alignment of the Dove-1 Nanosatellite is About 1º.


The Battery Type of the TacSat-4 Satellite is Lithium ion.


The Latency of the ATL00 Telemetry Data Data is Downlinked 8 times/day.


The Collection Location of the Yuanwang-21 and -22 Cargo Ships is Tianjin.


The Launch Site of the IDEA-OSG 1 Microsatellite is Vostochny launch site.


The Main Tank Replenishing Procedure of the XMM-Newton Satellite is Under development.


The Planned Number of Satellites of the OneWeb Satellite Constellation is 648.


The Bottom Plate Shape of the Baumanets-2 Microsatellite is Hexagonal.


The Impact Experiment Initiation Year of the DebriSat Satellite is 2011.


The Mission Design Life of the Spacecraft Satellite is 1.5 years.


The Ground Truth of the LPR Radar is Stratigraphic architecture of an ejecta deposit.


The Payloads of the TDS-1 Satellite is 8.


The Uplink Band of the Spacecraft Satellite is S-band (2 kbit/s).


The Spatial Resolution of the Pixxel’s planned satellites Satellite is 5 m.


The Purpose of the Webb Space Observatory is To see farther into our origins: from the formation of stars and planets to the birth of the first galaxies in the early Universe.


The Router Internal Connections of the SpaceWire ASIC Application-Specific Integrated Circuit is 2.


The Provider of the LRR Instrument is GFZ Potsdam.


The Minimum Concentration in 2016 of the Ozone Layer Atmospheric Layer is 114 Dobson Units.


The Launch Year of the ESA’s Space Situational Awareness (SSA) program Program is 2009.


The Wavelength Bands of the SBUV Spectrometer is 0.250 - 0.340 µm.


The Mission of the GOSAT Satellite is Greenhouse Gases Observing.


The Bus Voltage of the Spacecraft Satellite is 4.0 V.


The External Surface Coating of the Receiver Housing Housing is Gold.


The Affiliated Countries of the PUTC Program is France, Belgium, Spain, Sweden and Austria.


The Type of the 55 Cancri e Exoplanet is Rocky.


The Actuators of the iADCS-100 ADCS System is Miniature reaction wheels.


The Imaging of the Parker Solar Probe Satellite is Visible Light.


The Observation Duration of the Kepler space telescope Telescope is Nine years.


The Imaging Resolution of the PAIS Imaging System is Higher than an equivalent direct imaging system.


The Instruments of the MTSAT Satellite is Imager, JAMI, MTSAT DCS, MTSAT Comms, GPS receiver.


The Orbit Altitude of the Tianhe Space Station Module is 370 kilometers.


The Frequency Selectivity of the LICEF Receiver is High.


The Signal Strength Level of the RRA RetroReflector Array is Between LAGEOS and ETALON.


The URL of the James Webb Space Telescope Space Telescope is http://www.stsci.edu/jwst/.


The Years on Orbit of the Megha-Tropiques Satellite is 3.


The Deployment Position Reporting of the AstroTubeTM Boom Boom is Yes.


The Purpose of the MEO Medium Earth Orbit is Cellular telephone communication and navigation.


The Pass-Prediction Frequency of the SpinSat Satellite is Once every two weeks.


The Mission Status Presentation of the GCOM-W Satellite is August 13, 2005.


The Mechanism of the IASI-NG Interferometer is Patented mechanism allows performing simultaneously the OPD scan and the compensation using a single actuator.


The Mass of the Spacecraft Satellite is 1.22 kg.


The Total Power of the Spacecraft Satellite is 5.4-11 W (6 W average).


The Discovery Date of the NASA Satellite Satellite is June 1, 2016.


The Number of Satellites of the Galileo Satellite Constellation is 2.


The Launch Vehicle of the ALOS-2 Satellite is Mitsubishi vehicle - an H-IIA F24 bus.


The Hubble Space Telescope Images Containing Satellite Streaks of the Starlink Satellite Constellation is Currently 8% of all images.


The Launch Date of the SAMPEX Satellite is July 3, 1992.


The Radar of the Sentinel-1A Satellite is C-band.


The Designing University of the VisionCube-1 CubeSat is Korea Aerospace University (KAU).


The Wavelength Separation Direction of the HyperScout® Imaging System is Along track.


The Dynamic Range of the Kruiz CCD Detector is 2500.


The Satellite Configuration of the RADARSAT Constellation Satellite Constellation is Orbiting in formation, each dephased by 120°.


The Mission Duration of the Falcon Heavy Launch Vehicle is Over six hours.


The Renamed By of the KhalifaSat Satellite is His Highness Sheikh Mohammed Bin Rashid Al Maktoum.


The Spectral Bands of the EarthDaily Optical Imager Optical Imager is 22.


The Year Founded of the Saltworks Salt Production Facility is 1954.


The Record Load of the Minotaur I Rocket Rocket is 28 CubeSats.


The Spatial Resolution of the MSASI Imager is 1.25 km.


The Launch Date of the Resurs-P2 Satellite is December 2014.


The Location of the Aerosol Images Image is Ganges river.


The Imaging Capability of the SEOSAT–Ingenio Satellite is Sideways with access to any point on Earth within three days.


The Energy Optimization of the MEG Grating is Medium.


The DEM/DSM Accuracy of the HRS Instrument is 5 m (relative) and 10/15 m (absolute).


The Number of Satellites of the Transport Layer Satellite Network is Up to 150.


The Geometric Factor of the Instrument Instrument is 0.52 sr cm2.


The Attitude Actuators of the SUNSAT Satellite is 3-axis reaction wheels, 3-axis magnetic torquer coils.


The Number of Subapertures of the Direct Imaging System Imaging System is 8.


The Inclination of the CBERS-2B Satellite is 98.5º.


The Optics Unit Architecture of the Imager Payload is Extendable.


The Measurement of the PHA HiLRS is Spectrum of ionizing particle energy, charge, and mass.


The Imaging System of the Rosetta Satellite is OSIRIS camera.


The Mass of the TechDemoSat-1 Satellite is 150 kg.


The Slit Width of the Long Wavelength Band Spectrometer is 150 µm.


The Semi-Major Axis Adjustment of the CanX-5 Satellite is Within Meters of What Was Planned.


The Orbit Altitude of the GOCE Satellite is Varies.


The Responsivity Measurement of the Responsivity Measurement Instrument is 106 A/W.


The Manufacturer of the GMAG Magnetometer is NASA’s Goddard Space Flight Center.


The Toolkit of the Ubotica CogniSAT-XE1TM CubeSat Board Satellite Device is Intel®’s OpenVINO™.


The Material of the TOGS Telescope is Aluminum.


The Beamwidth of the AMSU Microwave Radiometer is 3.3º.


The Energy Range of the LET Low Energy Telescope is ~1.5 to ~60 MeV/nucleon.


The Attitude Subsystem Agile Platform of the Spacecraft Satellite is ±45º pointing in cross-track (max), ±30º pointing in cross-track (nominal).


The Osculating Orbital Period of the SMART-1 Satellite is 4.978457 hours.


The Receiver Type of the Jason-1 Satellite is Miniaturized 2nd generation receiver (5.6 kg), a bi-frequency system in 2 channels.


The Operator of the Deimos-2 Earth Observation Satellite is Elecnor Deimos.


The Number of Teams of the PRISMA Satellite Network is 3.


The Data Usage of the Iridium Constellation Satellites Satellite is Characterize the variation of the Birkeland currents with interplanetary conditions, particularly during magnetic storms.


The Purpose of the Google Earth Application is Earth surface image generator.


The Launch Date of the GEOS-1 Satellite is 6 November 1965.


The Type of the SGR-07 GPS Receiver is Space.


The X-ray Nova Detection Date of the ISS Instrument Instrument is Oct. 4, 2010.


The Materials of the FSU Solar Wind Faraday Cup is Molybdenum TZM.


The Control Accuracy of the CALIPSO Satellite is ± 10 km at equator crossing.


The Platform of the IOD-1 GEMS Satellite is CSL 3U structure.


The Mission Overview Date of the WindSat Satellite is Polar Max 2006.


The Sensor Type of the LINAS Ionization Gauge is Hot-filament ionization gauge.


The Funding Source of the Small Monitor Camera (CAM-H) Camera is Contributions from the public.


The Maximum Satellite Mass of the AD-SS 150 Satellite Dispenser is 150 kg.


The Number of Stars of the Lower Centaurus Crux Star Cluster is 97.


The Radio Frequency Output Power of the X-band transmitter Transmitter is Programmable.


The Mission Lifetime of the Satellite Communication Satellite is ~17 years.


The IFOV of the Telescope Optical Instrument is 0.004º.


The Measurement Importance of the FORUM Satellite Mission is Important for understanding atmospheric processes linked to climate change.


The No of revolutions of the KOMPSAT-3A Satellite is 15.1 revolutions/day.


The Number of Stars of the Gaia EDR3 Satellite Data is More than 1.8 billion.


The Type of the GPS receiver Receiver is SGR-20 model.


The News Archive Date of the INTEGRAL Satellite is 5 Aug. 2011.


The Presentation Date of the COSMIC-2 Satellite Constellation is April 3, 2015.


The Range Measurement Accuracy of the RA-1 Instrument is Better than 10 cm.


The Fast Plasma Investigation Event Duration of the MMS Satellite is 45 milliseconds.


The Heritage of the SUSIM Spectrometer Instrument is Spacelab-2 (STS-19, July 29-August 6, 1985) and on UARS.


The Input Matching of the Array Radiator Antenna is Better than -18 dB in the full 300 MHz bandwidth.


The Instrument Data Rate of the GNSS-RO Receiver Receiver is About 53 kbit/s.


The Design of the Optic with SDD Optic and Detector is Low-cost, low-mass.


The Transmission Type of the AISat Satellite is From space.


The Software of the Control Room Facility is SCOS-2000.


The Deployment Goal of the ADS-B Air Traffic Surveillance System is End of 2019.


The Purpose of the S&RSAT Search&Rescue Satellite Aided Tracking System is Support search and rescue operations for aviators, mariners, and land travellers in distress.


The Protocol of the FODB Data Interface is Asynchronous Transfer Mode (ATM) based.


The Mission Plan of the TanDEM-X Satellite is Not provided.


The Publication Date of the Onboard Processing Satellite System is 27 February 2018.


The Orbit Altitude of the R3 CubeSat Satellite is 500 km.


The FOV of the Microdosimeter A Instrument is 38º.


The First-Light Measurement Date of the ICIR IceCube Cloud–Ice Radiometer is June 6, 2017.


The Effect on Climate of the El Niño Weather Phenomenon is Above-average winter rainfall in California, drier-than-normal winters in Oregon and Washington.


The Operation of the UV/VIS Spectrometer Spectrometer is Continuously over full orbit.


The Attitude Knowledge of the GFO Satellite is Derived from horizon scanners.


The Complexity of the EIRSAT-1 Satellite is Equivalent to a standard space mission.


The Survey Date of the CubeSat Communication Systems Satellite System is April 18, 2008.


The URL of the GFO Satellite is http://ibis.grdl.noaa.gov/SAT/gfo/.


The Size of the Solar Cells Power Generation is 40 x 80 cm.


The Size of the Langjökull Glacier is Iceland’s second largest ice cap.


The Period (min) of the Meteor-2-1 Satellite is 102.5.


The Tether Composition of the ProSEDS Tether Demonstration Experiment is 10 km of nonconducting Spectra tether for ballast and to begin the deployment, and of a 5 km of aluminum wire (1.2 mm diameter).


The Imaging Spectrometers of the CASA-212-200 aircraft Aircraft is Three.


The Date of the Hunting Milky Seas by Satellite Image is 2 November 2021.


The Swath of the OSCAT Scatterometer is 1400 km.


The Cost of the Low Cost Solar Panel Solar Panel is Low.


The Contract Award Date of the M3MSat Microsatellite is June 23, 2008.


The Ground Stations of the Sentinel-1 Satellite is Svalbard, Maspalomas, Matera.


The Residual Phase Error of the Instrument SAR is ≤10º.


The Image Capture Time of the Long Range Reconnaissance Imager (LORRI) Imager is 11:04 Universal Time on February 28, 2007.


The Orbit Type of the Satellite SuperView Constellation is Sun-synchronous orbit.


The Purpose of the TROPICS Constellation of CubeSats is Study the development of tropical cyclones through rapid-revisit sampling.


The Transmission Profile of the Etalon Etalon is Unknown.


The Properties Below Critical Temperature of the TEMBOTM EMC Material is Comparable to the conventional "rigid" composite structures.


The Geo-Referencing Precision of the Claire Satellite is With sufficient precision to identify facilities of interest.


The | of the iADCS Flight Model is Preparing the First Flight Model of iADCS - Results of Air Bearing Tests.


The Leading Organization of the TacSat-3 Satellite is AFRL.


The Actual Battery DoD of the IXV Spacecraft is 10%.


The Development Status of the Space Weather Mission Satellite is Not Launched.


The Constellation Operations of the FormoSat-7 / COSMIC-2 mission Satellite Mission is 6 satellite constellation operations.


The Maximum Relative Distance of the CNAPS Propulsion System is 1000 m.


The Product Definition of the TanDEM-X Satellite is Not provided.


The Test Transmission Location of the Herschel Spacecraft is ESA's ESTRACK (ESA Tracking stations network) station at New Norcia, Australia.


The Beacon Ku-band of the RF communications Communication Subsystem is 1 mW.


The Data Density of the DMC-2G imager Imager is Doubled.


The Sensor Suites of the ADCS Attitude Determination and Control Subsystem is Four sun sensor suites and five two-axis magnetic sensors.


The Previous Planned Launch Year of the NEMO-AM Satellite is 2017.


The Images Collected per Day of the Landsat-8 Satellite is Approximately 1,500.


The Mass of the PSU Power Supply Unit is 8 kg.


The Ground Sample Distance of the PamCam Panoramic Camera is Around 200 m.


The Presentation Date of the JC2Sat-FF Satellite is April 23-25, 2008.


The Satellite Mission Types of the Spacety Company is Science experiments or observation, in-orbit demonstrations and/or validations of space technologies and products, or space systems.


The Publication Date of the Solar Mass Ejection Imager Imager is 1997.


The Data Downlink of the GHOSt satellites Satellite is Ka-band, S-band for high speed data (HSD) transmissions.


The Received Eb/No of the Unit Communication System is 7.52 dB.


The Altitude of the Satellite GEO (Geostationary Earth Orbit) is 35,786 km.


The Responsivity Requirement of the Responsivity Measurement Instrument is >1.04 A/W.


The Data Rate of the WFC CCD Camera is 26 kbit/s.


The Temperature Sensors of the SEEDS-2 Satellite is Installed in 14 locations within the spacecraft.


The Collector Head Depth of the OSIRIS-REx Spacecraft is 1.6 feet (48.8 cm).


The Launch Site of the HORYU-2 Nanosatellite is TNSC (Tanegashima Space Center), Japan.


The Size of the CEASE-2 Instrument is 10 cm x 10 cm x 8.2 cm.


The Image Content of the ExoMars Trace Gas Orbiter Orbiter is The region where the ancient Uzboi Vallis enters the Holden crater.


The Orbit of the MOST Payload is Sun-synchronous orbit of 820 km near-circular altitude.


The Brightness Change of the X-ray Source Celestial Object is Up to 50 times its normal level.


The Temperature of the PICNIC IR detector Detector is Around 90 K.


The Optical Gains of the Limb Sensor Sensor is Two.


The URL of the "Discrete and broadband electron acceleration in Jupiter's powerful aurora" Research Paper is https://doi.org/10.1038/nature23648.


The Solar Array of the Orion Spacecraft is Weight 260 kg.


The Antenna Quantity of the Ground Segment Ground Control Infrastructure is 2.