The Solar Panel Deployment Date of the ALBus CubeSat Satellite is December 16, 2018.


The Services of the Galileo Constellation Navigation Satellite is Positioning, navigation and timing services to our planet.


The Number of Satellites of the OneWeb Satellite Constellation is 648.


The Communication Bands of the BioSentinel Spacecraft is Higher frequency bands.


The Center Frequency of the Channel 9 Sensor is 53.30 GHz.


The Shape Knowledge of the ISRF Instrument Spectral Response Function is Within 1%.


The Location of the MBB Predecessor Organization of DASA is Ottobrunn, Germany.


The Payload Fairing Diameter of the CBAS and EAGLE Spacecraft is 5 m.


The Pointing Accuracy of the Spacecraft Satellite is 2.1 arcsec absolute pointing accuracy.


The Swath Width of the Instrument Spectral Imager is 2250 km.


The Freeze/Thaw State Resolution of the SMAP Satellite is 3 km.


The Voltage of the TriTel Electrical System Electrical System is 60 V.


The Number of RAFS Clocks of the GIOVE-A Satellite is 2.


The Launch Vehicle of the HORYU-2 Nanosatellite is H-IIA of Japan.


The Grating Angle of the Offner-type spectrometer Spectrometer is 5º at 325 nm.


The Frequency of the SIRAL Radar is 13.575 GHz.


The Altitude of the Orbit Centaur AV-042 upper stage is 467 km x 883 km.


The Energy Overlap of the IMAP-Ultra Instrument is Overlaps in energy with IMAP-Hi for heliospheric energetic H.


The Transmitter Power of the OPAL Satellite is 2.2 W.


The Total Ambiguity Ratio of the Instrument SAR is ≤ -18 dB.


The Orbit Type of the COMPASS-1 Satellite is Sun-synchronous circular polar orbit.


The CO2 Reactivity of the AIRS Satellite is Does not react with other gases in the atmosphere.


The Presentation Date of the SWIM Scatterometer is July 12-17, 2009.


The Mass of the NewMag Magnetometer is 3 kg.


The Orbit Repeat Cycle of the MSU-SK Radiometer is 21 days.


The Dataset of the SMOS Satellite is Vegetation optical depth dataset.


The Purpose of the Mouse Cells and Fruit Flies Biological Models is Obtain gene expression profiles and identify sensitive biological molecules as space radiation markers.


The Calibration Phase of the DEIMOS-2 Satellite is Coming days.


The Attitude Accuracy of the Sentinel-1 Satellite is Stringent requirements on attitude accuracy.


The Calibration Requirements of the MOPITT Instrument is Unknown.


The Scan Lines of the Visible Spectral Band Spectral Band is 2500 x 4.


The Deviation of Center Wavelength of the 4-band CCD Imager Instrument is < 5 nm.


The Test Flight Date of the Starliner Spacecraft is Late Summer.


The Detection Limit of the VIS Visual Instrument is AB 24.5 magnitude.


The Symposium Date of the ALOS PRISM Satellite is 14 – 16 May 2014.


The Design Life of the Odin Satellite is Two years.


The Stationkeeping Maneuvers of the ISEE-3 Spacecraft is 15.


The Consortium Leadership Date of the Planet Company is 27 January 2021.


The Presentation Date of the FormoSat-7 /COSMIC-2 Satellite is September 6-11, 2010.


The Focus of the Sustainability Tech Company is Tropical forest ecosystems in Southeast Asia.


The Dimensions of the FENIX micropropulsion device Micropropulsion Device is 10 cm long and 2 cm wide.


The URL of the NICER Neutron star Interior Composition Explorer is https://heasarc.gsfc.nasa.gov/docs/nicer/gallery/slides/NICER_Science_Overview.pdf.


The GIFOV of the TRUTHS Satellite is Unknown.


The Error of Amplitude Spectrum of the BRITE Satellite is 2 x 10-5 (20 ppm).


The Accuracy of the CERES Instrument is 0.8 Wm -2  sr -1.


The Developer of the Ground Segment Data Processing is Spacebel in Belgium with scientific support from the Belgian institute for Space Aeronomy (BISA) and the University of Saskatchewan (USASK) in Canada.


The Purpose of the PlasMag Fluxgate Magnetometer Magnetometer is Provide crucial continuity of observation of interplanetary solar wind parameter.


The Resolution (IR) of the VHRR Very High-Resolution Radiometer is 11 km.


The PRF of the KaRIn Instrument is 2 x 4420 Hz.


The No. of Bins of the SPIM4 Spectrometer is 68, 136, or 272.


The Arctic Sea Ice Volume of the CryoSat-2 Satellite is 10,200 km3.


The Operation Status of the China's Moon Rover Rover is Sleeps.


The Data Collection Method of the EARS-ASCAT Data Service is Collects ASCAT instrument data from MetOp satellite passes via a network of Direct Readout stations.


The Deployment Timing of the KE-2M satellite Satellite is After ISS reboost.


The Science Objectives of the SAGE-III Instrument is Investigate the spatial and temporal variability of the measured species.


The Data Rate of the SIOS Optical Link Demonstration Board Technology Demonstration Board is 100 Mbit/s.


The Declaration Date of the STRaND-1 Satellite is March 07, 2013.


The Energy Range of the HXCP Hard X-ray Polarimeter is 30-100 keV.


The Downlink Frequency of the NEMO-AM Satellite is S-band.


The Additional Data Sources of the TanDEM-X Satellite is ‘global urban footprint’, a global map of settlements created at the DLR Earth Observation Center (EOC), as well as the mapping of water bodies by ESA’s Climate Change Initiative.


The Reprogrammable of the MCU Microcontroller Unit is Reprogrammable.


The Manufacturer of the MOMA Mars Organics Molecule Analyzer is ESA.


The ADCS Equipments of the TDS-1 Satellite is Gyros and magnetometers.


The Launch Vehicle of the LightSail-2 Solar Sailing CubeSat is SpaceX Falcon Heavy rocket.


The Owner of the Beijing-3 Satellite Constellation is Twenty First Century Aerospace Technology Co., Ltd (21AT).


The Meeting Date of the ISSP International Space Station Program is January 2011.


The Date of the Solar Storms Natural Phenomenon is October and November of 2003.


The Mass of the COPS Ka-band Communication Payload is 316 kg.


The Mainframe Launch Size of the SRMSat Satellite is 286 mm x 286 x 294 mm.


The Width with Solar Paddles Extended of the Nimbus-7 S/C Satellite is 3.96 m.


The Sensor of the CartoSat-2B Satellite is PAN Camera.


The Type of the EFI Instrument is Electric Field Instrument.


The Solar Array Deployment Time of the James Webb Space Telescope Space Telescope is Approximately 30 minutes after launch.


The Attitude Control Strategy of the Microsatellite Satellite is Interactive spacecraft pointing for event monitoring support.


The Area of the SAA South Atlantic Anomaly is Stretching from Africa to South America.


The Manufacturer of the Satellite Vu Satellite is SSTL.


The Payload of the MPQ442 Satellite is SuperSprite.


The Launch Year of the S3C Satellite is 2024.


The Bands of the SCIAMACHY Spectrometer is 8.


The DOI of the Herschel Satellite is 10.1088/0004-637X/773/2/102.


The Number of Satellites of the SAR-Lupe Constellation Satellite Constellation is 5.


The Development Locations of the POPSAT-HIP1 Satellite is Italy, Japan, and Singapore.


The Carries of the Beijing-3B Satellite is Larger and higher resolution optical imager.


The Imaging Sensor of the ResourceSat-2 Satellite is LISS-3.


The TT&C Uplink of the Spacecraft bus Satellite is 2 kbit/s.


The Orbit Transfer Time of the Chang'e-1 Satellite is 8-9 days.


The Groundbreaking Date of the OneWebSatellites Spacecraft Integration Facility is March 16, 2017.


The Developer of the ADAM Data Acquisition and Messaging System is ITR (Institute for Telecommunications Research) at the University of South Australia.


The Spatial Resolution of the MSU-SK Radiometer is 170 m (in VIS) and 600 m (TIR).


The Hibernation Mode of the EDM Lander is Yes.


The Dynamic Range of the Instrument Sensor is >100.


The Planned Image Resolution Improvement of the Satellite Constellation Satellite Constellation is 70 centimeters.


The Objective 1 of the CITRIS Receiver is Reconstruct real-time phase screens for multiple frequency scintillation estimation.


The Communication Status During Upgrade of the Voyager 2 Spacecraft is Still be able to receive science data from Voyager 2.


The Frame Rate of the Hyperion Imaging Spectrometer is 225 Hz.


The Hosting of the HISats Satellite is In an unused recess on the host spacecraft.


The Filter Diameter of the LWIR Camera Camera is 15.5mm.


The Global Revisit Opportunities of the NigeriaSat-2 Satellite is At least every 2 days.


The Purpose of the PHA HiLRS is Monitor the effect of high energy particles on spacecraft electronics.


The URL of the IceCube Satellite is https://icecube.wisc.edu.


The Quantity of the AeroCube-5a and -5b CubeSats is 2.


The URL of the IceCube-Gen2 Satellite is https://arxiv.org/pdf/2008.04323.pdf.


The Length of the Ganges River River is Over 2400 km.


The Observation of the Satellite Observation Satellite is Wave-particle interactions in Earth’s magnetotail.


The Assets Ownership Transfer of the Copernicus Space Component Satellite Component is Defined in Agreement.


The Focal Length of the Lenses Optical System is 2.6 m.


The Logarithm Resolution Adjustment of the RFA Computer Signal Processing Device is 8 bits.


The Data Usage of the SAGE-III on ISS Satellite Instrument is Help to re-institute aerosol measurements crucial for more-accurate, long-term climate and O3 concentration and distribution models.


The URL of the TeleSupport-2-bis Onboard System is http://www.prismasatellites.se/filearchive/3/3615/2005%20tsuengelsk.pdf.


The Integration Date of the TROPOMI Space Air Quality Sensor is May 26-30, 2014.


The Gouge Dimensions of the SMART-1 Satellite is 4 m-wide and 20 m-long.


The Launch Date of the ExoMars 2020 Spacecraft is 2022.


The Response Date of the NASA Organization is July 10, 2015.


The Mission Purpose of the CHEOPS Satellite is Characterize exoplanets orbiting nearby stars.


The Cadence of the 3 He Spectrum Measurement is Up to roughly 20 MeV/nuc.


The Measurement Domain of the EXPORTS Satellite Mission is Ocean.


The Altitude of the Orbit Satellite is ~1075 km x 1089 km.


The Swath Width of the Instrument Spectrometer is 19.3 km.


The Maximum Efficiency of the Solar Cell Assemblies Power Source is 25%.


The Slew Rate of the Spacecraft Satellite is 15º / minute.


The Solid State Recorder Capacity of the C&DH Command & Data Handling is 4 TB @ BOL and 3.1 TB @ EOL.


The Data Rate of the Reception Station Ground Station is 16 Mbit/s.


The Data Usage of the TRUTHS Satellite is Global hyperspectral data.


The Mission Prediction of the Roman Space Telescope Space Telescope is Find 100,000 Transiting Planets.


The Image Capture Date of the Solar Dynamics Observatory Satellite is March 31, 2022.


The Height of the Langmuir Probe Assembly Probe is 10 mm.


The Orbit Type of the Aalto-1 Satellite is Sun-synchronous near-circular orbit.


The Mass of the 4-band CCD Imager Instrument is 15 kg.


The Affiliation of the Giacomo Peretto Engineer is Unknown.


The Tandem Mission Completion Date of the ERS-1 and ERS-2 Satellites is May/June 1996.


The Size of the LALT-E Electronics is 241 mm x 301 mm x 88 mm.


The Current Location of the Voyager 2 Spacecraft is Beyond the heliopause.


The Photodetector Resolution of the Optical Head Optical Device is 1280 x 1024 pixels.


The S-band Downlink of the UoSAT-12 Satellite is 2.


The Altitude Range of the Methane VMR Measurement Device is 40 - 95 km.


The Perigee of the Molniya Orbit Orbit is 1043 km.


The Memory of the AIM Reconfigurable Computing Hardware Device is 512 k x 16 SRAM for instructions and data for the microcontroller.


The Propulsion System of the AOCS Attitude and Orbit Control System is Bi-propellants.


The Solar Array Type of the EPS Electric Power Subsystem is Triple-junction solar cells.


The Observable of the COR1 Coronagraph1 imager is K-corona and CMEs.


The Dynamic Range of the EXI instrument Imaging Instrument is 12 bit, 13,500 e full well.


The Ground Control of the James Webb Space Telescope Space Telescope is Space Telescope Science Institute in Baltimore.


The Launch Date of the SOCRATES Microsatellite is May 24, 2014.


The Mission Lead of the SORTIE Satellite is ASTRA LLC.


The Bandwidth of the CSG-SAR Synthetic Aperture Radar is Programmable.


The Percentage of InSight EDL Data Sent of the MarCO-B Satellite is 97%.


The Dimensions of the Microsatellite Satellite is 315 mm x 315 mm x 260 mm.


The Collaboration URL of the Hinode Satellite is http://www.jaxa.jp/article/special/solar-b/1/index_e.html.


The Orbit Altitude of the SPOT 1-5 Satellite is 832 km.


The Mass of the Anand Satellite is Less than 15 kg.


The GSD of the SLIM6 Line Scan Imager Imager is 32 m.


The L-band region of the Inmarsat Satellite Communication is Fourth full-service.


The Science Phase Duration of the GP-B mission Mission is 50 weeks.


The Publication Date of the CYGNSS Satellite is 19 June 2018.


The Spectral Resolution of the HR Bands (677–686 nm, 740–759 nm and 769–780 nm) Spectral Bands is Principally driven from the aggregated pixel size (140 µm).


The Detectors Service Unit Status of the IXPE observatory X-ray Observatory is Complete.


The CIR Film Type of the Metric Camera Camera is KODAK Aerochrome Infrared Film 2443.


The Type of the Lutetia Asteroid is M-type (metallic).


The Interface of the Google Earth Application is Camera.


The Number of Satellites of the Spacety Company is 21.


The Dynamic Range of the Satellite Device Unknown is 3-340 K.


The Data Storage of the Spacecraft Satellite is 500 Mbit bus + 2 Gbit fpr payload data at EOL.


The URL of the MERTIS Thermal Infrared Spectrometer is https://www.researchgate.net/publication/224798007_Thermal_infrared_spectroscopy_to_investigate_the_composition_of_mercury_-_The_MERTIS_instrument_on_BepiColombo.


The Trace Gas Orbiter (TGO) of the ExoMars Mission is Launched in 2016.


The Launch Location of the RASAT Satellite is Orenburg Region, Russia.


The Stabilization of the S/C Satellite is Three-axis.


The Launch Date of the CubeSat Satellite is July 21, 2010.


The Nitrogen Dioxide Emission Reduction of the Copernicus Sentinel-5P Satellite is Decline of air pollution, specifically nitrogen dioxide emissions, over Italy.


The Ground Terminals of the ETS-VIII LRRA Satellite is Portable terminal, Handheld terminal.


The Solar Array Power of the Orion Spacecraft is 11.1 kW.


The Funding of the FGS Fine Guidance Sensor is CSA (Canadian Space Agency).


The Observation Date of the Chandra X-ray Telescope is Unknown.


The Centre of Pressure Position of the GOCE Satellite is Behind Centre of Mass.


The Presentation Date of the LIDAR Instrument is March 16-20, 2015.


The Description of the RO Proposals Payload is Polarimetric Global Navigation Satellite System (GNSS) Radio-Occultation (RO) payload.


The Ka-band Data Rate of the CASCADE Satellite Communication System is Up to 1.4 Gbit/s (QPSK modulation).


The Presentation Date of the Gravity Probe B Satellite is 23-24 July 1992.


The Orbit Transfer Thrusters of the EURECA Spacecraft is Redundant 4 x 21 N hydrazine thrusters.


The Location Accuracy of the SPOT-6 Satellite is 19.3 m CE90 @30º.


The Output Resolution of the Detector Sensor is 12 bits.


The URL of the GPM Satellite is http://www.esmats.eu/esmatspapers/pastpapers/pdfs/2011/sexton.pdf.


The Total payload mass of the Repeater subsystem Communication System is 400 kg.


The Date of the ESA Space19+ ministerial conference Conference is End of 2019.


The Energy Resolution of the RHESSI Satellite is One- to a few- keV.


The Power Generation Capability of the SBVR Power Supply is 20.3 kW max.


The URL of the GFO Satellite is http://gfo.wff.nasa.gov/.


The Frequency of the Calibration Phases Process is Periodically.


The Launch Date of the Dellingr Satellite is 2017.


The Area Covered of the Saltworks Salt Production Facility is 33,000 hectares (82,000 acres).


The Weight of the Electrons Particle is 2000 times lighter than other particles.


The Change DEM Availability of the TanDEM-X Satellite is Mid-2021.


The Conference Presentation Date of the TanDEM-X Satellite is July 22-27, 2012.


The Image Capture Dates of the XMM-Newton X-ray Space Observatory is 19-25 January.


The Functionalities of the DIS System is Scheduling X-band RF signal reception, X-band RF signal receiving and status monitoring, analog to digital conversion to extract CADU frames for retrieving SAR source packet data.


The Energy Range of the EPIC Cameras Imaging System is 0.15 to 15 keV.


The Performance Advantage of the FPGA based parallel computing Processing Technology is 100 x.


The Drift Start Date of the ERS-2 Satellite is After the completion of the tandem mission.


The Date of the Autonomous Sciencecraft Experiment Experiment is June 27-29, 2006.


The Orbit of the Queqiao Relay Satellite is Halo orbit around the second Lagrangian (L2) point of the Earth-moon system.


The Wavelength Range of the Grating Reflection Unit Spectrometer Component is 750nm to 775nm.


The Nominal Altitude of the DubaiSat-1 Satellite is 680 km.


The Number of Satellites of the UrtheCast Satellite Constellation is 16.


The Orbital Energy of the BepiColombo Spacecraft is Same as Earth's.


The Technology Demonstrator of the SIMBA Satellite RMIB SIMBA program is Intended.


The Mass of the Schiaparelli Module is 600 kg.


The Orbit Inclination of the Light-1 Satellite is 51.6°.


The MTF at Nyquist Frequency of the Spacecraft Satellite is > 20% for MS.


The Operator of the Göktürk-1 Satellite is Turkish Ministry of National Defense.


The Instrument of the GeoSTAR Geostationary Synthetic Thinned Aperture Radiometer is Utilizes the same established approach as is being used with the AMSU instrument.


The Attitude of the ISS Space Station is Torque Equilibrium Attitude (TEA).


The Power of the Voltage 5 Digital is 2.


The Location of the Ceres Dwarf Planet is Asteroid belt, between the orbits of Mars and Jupiter.


The Perigee Height of the INTEGRAL Satellite is 9,049.6 km.


The Protocol of the UoSAT-12 Satellite is AX.25 (Amateur radio X.25).


The Spectral Resolution of the Observation Instrument Telescope/Spectrograph is <0.6 nm (point source), <1.2 nm (extended source).


The Actuators of the Coarse ADCS ADCS System is Magnetotorquers.


The Data Quantization of the Visual Sensor Array Sensor Array is 6 bit.


The Planned Launch Date of the Nauka Laboratory Module is 15 July 2021.


The Cone Tilt of the SS 433 Cosmic Object is Periodically tilts slightly toward Earth.


The Width of the HXR Flare Ribbons Solar Phenomenon is ~1 arcsec.


The Pixel size of the Channel 5 Sensor is 32 km x 32 km.


The Operational Lifetime of the KazEOSat-2 Satellite is 7 years.


The Accuracy of the Climate Models Computer Models is Agree fairly well with observed data.


The Catcher Compartments of the Hayabusa-2 Sampler Mechanism is Three compartments.


The Frequency Range of the NewMag Magnetometer Experiment is 0.1 Hz to 1 kHz.


The Inclination Angle of the Suomi-NPP Satellite is 98.74°.


The Program Management Location of the SSETI Express Satellite is ESA Education Department at ESTEC.


The Number of Substorms Observed of the THEMIS Constellation Satellite Constellation is 57.


The Size of the VPU Video Processing Unit is 195 x 120 x 253 mm.


The Constellation Redundancy of the CYGNSS Satellite Constellation is Full.


The Planned Satellite Launches of the ICEYE Satellite Operator is At least eight more satellites in the coming year.


The Optics Type of the ALTIUS Instrument Satellite Instrument is Reflective optics.


The Manufacturer of the EC Digital Signal Processor is TI.


The Launch Date of the ICEYE Satellite is June 13, 2023.


The Orbit Inclination of the ERBS Satellite is 57º.


The Base Component of the GSCG Ground Station Control System is ESA SCOS2000 NIS.


The Orbit Inclination of the EURECA Satellite is 28.45º.


The Provided through a secure communication channel via VPN of the Real-time network communications Communication Services is Links the SCC of GISTDA to the RTS of NSPO and the SOCC of NSPO to the SBS of GISTDA.


The Image Telemetry Link of the SPOT-2 Satellite is 50 Mbit/s at 8 GHz.


The Regulators of the EPS Electrical Power Subsystem is 3.3 and 5 V.


The Platform of the SpooQySat Satellite is 3U GomX CubeSat.


The Launch Vehicle of the NigeriaSat-1 Satellite is Kosmos-3M.


The Launch Date of the GOMS-1 Satellite is October 31, 1994.


The Apogee Height of the INTEGRAL Satellite is 153,657.2 km.


The Ground Sample Distance of the GHOSt Constellation Satellite Constellation is 8 metres.


The Latency of the Satellite Constellation Constellation is Minimum.


The Booster Segments Trip Distance of the SLS Rocket is 2,800 miles.


The Maximum Latitude Coverage of the ISS Satellite is ±54.33º.


The Age of the Site Kingfisher Crater is Relatively young.


The Power Consumption of the TOTEM SDR SDR Platform is Low.


The Power of the PAP Plasma Analyzer is 7 W.


The Dynamic Range of Earth Background of the LI Instrument is 0 - 296.5 W/m 2 /µm/sr.


The Presentation of the TerraSAR-X, TanDEM-X, EnMAP Satellites is GSCB (Ground Segment Coordination Body) Workshop.


The Accuracy of the NIDEM Elevation Model is High.


The Orbit of the EO Satellite Satellite is LEO.


The MS Resolution at Nadir of the QuickBird-2 Satellite is 2.4 m - 1.8 m (8 bands).


The Spatial Resolution (Playback Mode) of the OCM Data Transmission System is 2.16 km.


The FOV (Field of View) of the Telescope Optical Instrument is 41.3 x 41.3 arcmin.


The Mission Extension of the SOHO Satellite is End of 2016.


The Daily Imaging Capacity of the PRISMA System Satellite Ground Segment is Up to 200,000 km2.


The Launch Date of the Space Weather Mission Satellite is Unknown.


The Launch Date of the NICER-SEXTANT Mission is 3 June.


The Location of the Hertz Chamber Test Chamber is ESA's ESTEC technical center in the Netherlands.


The Reentry Altitude of the First Stage Rocket Stage is 70 km.


The Components of the DarkCarb image sensor Photon Detector is Optical elements, detector, temperature sensors.


The International Participants of the ARTEMIS Satellite is The United Kingdom, Canada, and Australia.


The Along-Track Resolution of the MLS Spectrometer is 500 km.


The Weight of the mvBlueFOX-IGC (200w) Visual Sensor is 80 g.


The Design Class of the QSAT Satellite is 50 kg.


The Telecommand Uplink Data Rate of the GIOVE-B Satellite is 2 kbit/s.


The Pixel Type of the MWIR Imager Imaging Device is MWIR.


The Mission Status of the KOMPSAT-2 Satellite is Operational.


The Quantity of Proof Masses of the Electrode Housing Box Component is 1.


The Discovery Date of the NICER X-ray Pulsar Mission is 10 May 2018.


The Actuation Method of the SMA Scan Mechanism Assembly is Inductively using a network of voice coils and magnets.


The Voltage Levels of the Power Regulation System is 5V and 8V.


The Function of the Systematic and Radiometric Correction Processor Data Processor is Corrects the raw hyperspectral image (HSI) data for systematic effects and converts them to physical at-sensor radiance values.


The SAR Payload Swath Width of the RCM Satellite is 20 - 350 km.


The Hydrazine Exhaustion of the Envisat Satellite is End of 2010.


The Data Rate of the TT&C Downlink Communication System is 38.4 kbit/s.


The Area of the Solar Panels Power Generation is 2.44 m2.


The Measurement of the WISPR Instrument is SEP-Producing Shocks and CME Drivers.


The No of Passbands of the Channel 1 Sensor is 1.


The Launch Date of the IASI-NG Satellite is Unknown.


The Magnetic Field Profile of the Current Sheet Magnetic Field Structure is Matched the theoretical prediction.


The Program Purpose of the SBSS-1 Pathfinder Satellite is Develop and initiate operations.


The Material of the Baffle Telescope Component is CFRP laminate.


The Instrument Module Length of the Resurs-P1 Satellite is About 1 m.


The Spectral Band of the VIS Channel is 0.4 - 1.1 µm.


The Swath Width of the MWHS-II Microwave Humidity Sounder is 2600 km.


The Sampling of the Satellite GEO (Geostationary Earth Orbit) is Excellent sampling of one region of the globe.


The Wavelengths of the AVGS Laser System is 808 nm and 850 nm.


The Operations Concept of the Spacecraft Satellite is Unattended with distributed science operations.


The Data Transmission Rate of the RF Communications Transmitter is 1 kbit/s FSK modulated in S-band.


The Orbit Type of the Space Station Satellite is Low-Earth orbit.


The Emission Sources of the Nitrogen Dioxide (NO2) Gas is Burning of gasoline, coal, and diesel fuel by motor vehicles, power plants, and industrial facilities.


The Splashdown Date of the Orion Spacecraft is Dec. 5, 2014.


The Components of the Plasma Wave Instrument Instrument is Triaxial magnetic search coils, pair of electric dipole antennas, two sweep-frequency receivers, multichannel analyzer, low frequency waveform receiver, wideband waveform receiver.


The Expected Data Processing End Date of the MICROSCOPE Satellite is 2019.


The Data Availability of the CATS Lidar Instrument is Freely available.


The Attitude Control of the GCOM-W1 Satellite is 4 reaction wheels in response to the signal from IRU (Inertial Reference Unit) calibrated by Star Trackers and GPS receivers.


The Program Launch Date of the Polar Scout Satellite is 11 December 2018.


The Attitude Control of the AOCS Attitude Orbit Control Subsystem is 3-axis.


The Unknown of the DORIS Satellite System is Unknown.


The Manufacturer of the Fregat Upper Stage is RUAG Space in Sweden.


The Flight Control Team Location of the Gaia Satellite is ESA's ESOC mission control center in Darmstadt.


The Orbit Altitude of the HORYU-4 Nanosatellite is ~575 km.


The Strength of the Earth's Magnetic Field Natural Phenomenon is 0.5 gauss, 5 x 10-5 tesla.


The Architecture of the Microsatellite Satellite is Single string hardware architecture.


The Capital Raise of the Astrocast Satellite Manufacturer is Up to 50 million Francs.


The Total Number of Spectral Bands of the MSU-50 Camera is 6.


The Observation Angle of the VSSC Satellite is Constant for all data acquisition at a given site.


The DEM Extraction of the CartoSat-1 Satellite is Not Available.


The Operation Center of the EDR-2 European Drawer Rack is CADMOS, the French User Support Operations Centre located in Toulouse, France.


The Launch Contract Date of the 90-satellite constellation Satellite Constellation is January 15, 2019.


The Swath Width of the Scanner Assembly Instrument is 800 km.


The Level 0 Products of the Sentinel-6 Satellite is Raw data after restoration of the chronological sequence for each instrument and removal of data overlaps at dump boundaries and relevant quality flags related to the reception and decoding.


The Angular Rate Tolerance of the Procyon Star Tracker is 2°/s.


The F-Number of the Telescope Optical Instrument is 3.1.


The Purpose of the PREMOS Instrument is Measure UV solar radiance.


The Scanning Time per Image of the VHRR Very High-Resolution Radiometer is 30 minutes.


The Look Angle of the ICEYE-X1 Satellite is 11º.


The Large Window Imaging Area Pixels of the CCD Image Sensor is 300 x 300.


The Director of the Chandra X-ray Observatory Telescope is Harvey Tananbaum.


The Data Type of the SMAP Satellite is Soil moisture data.


The Location of the NewMag Magnetometer Experiment is New South Wales, Australia.


The Camera Data of the PSSCT-2 Satellite is Used for Understanding.


The Radar Frequency of the SeaWinds Scatterometer Scatterometer is 110 W pulse at 189 Hz pulse repetition frequency (PRF).


The Propulsion of the LightSail Satellite is Solar sailing.


The Energy Measurement Range for Particles of the Telescope 1 Solid-State Telescope is 1.6-12 MeV/n.


The Channel Data Rate of the Communication System Data Transmission is 310 Mbit/s.


The Data path diversity of the Open5GCore Rel. 4 5G Core Network is Supporting local offloading and backhaul control.


The Optical Path of the IASI-NG Interferometer is Two opposite prisms moving synchronously with the OPD change.


The Reentry Date of the TechEdSat-1 Satellite is May 5, 2013.


The Orbit Altitude of the Optsat-3000 Satellite is 720 km.


The Prism Material of the LAGEOS Satellite is 422 fused silica glass, 4 germanium.


The Resolution of the MWR Radiometer is 40 km.


The Data Rate of the DH Data Handling Component is 4.2 Msample/s.


The Type of the Detector Instrument is 2D microchannel plate.


The Mass of the X-band Transmitter Transmitter is 2.7 kg.


The Ocean Surface Resolution of the SWOT Satellite is 10 times current technologies.


The Image Capture Date of the DESIS Instrument is 13 January 2020.


The Attitude Control of the S/C Satellite is 3-axis stabilization with four reaction wheels and three torque rods as actuators.


The Transverse Propagation of Wave-like Drift Perturbations of the Plasma Drifts Phenomenon is Account for a phase difference between local maxima in the plasma drift and the plasma density.


The Collaboration Start Date of the NISAR Earth Observation Satellite is September 30, 2014.


The Operation Duration of the LRO Satellite is 9 years.


The Ground Station of the LightSail Satellite is Cal Poly San Luis Obispo.


The Data Resolution of the ICEYE-X1 Satellite is 10 x 10 meters.


The Small Size of the DC-DC converter Power Converter is 95 mm x 60 mm x 19 mm.


The Protocol of the RF Communications Communication Subsystem is CCSDS compatible.


The Sensor Subsystems of the SEEDS-2 Satellite is 3-axis geomagnetic sensors, 3-axis gyro sensors, temperature sensors, solar battery cell galvanometers, and voltage sensors.


The Subsystems of the Instrument Electronics Assembly Electronics is Instrument controller, Detector readout electronics, HVPS, LVPS.


The Altitude of the Satellite Constellation Satellite is About 500 km.


The Inclination of the KOMPSAT-3A Satellite is 97.513º.


The Development Timeline of the GHGSat-D Satellite System is Spring 2013 to Summer 2015.


The Dark-Adapted Experiment of the Apollo 9 mission Space Mission is Unknown.


The Time Synchronization of the Spacecraft Plug-n-Play Avionics (SPA) Standards is One pulse per second (1PPS) signal.


The Power Consumption of the XI-IV Picosatellite is Average consumption of 620 mW.


The CPU of the OBC On-Board Computer is ERC-32.


The Operational Life of the Kestrel Eye II Microsatellite is Greater than one year in low earth orbit.


The Development Status of the TRUTHS Mission is Preliminary design phase.


The Span of the Spacecraft Satellite is 14.67 m.


The Downlink Data Rate of the RF Communications Communication System is 4.8 kbit/s.


The Payload of the MPQ442 Satellite is OrbitView.


The Length of the Kurushima Kaikyo Bridge Bridge is 4,015 meters (13,173 feet).


The Launch Date of the GF-3 Satellite is 10 Aug 2016.


The Celestial Sphere Coverage of the Telescope Optical Instrument is 30% for > 197 days.


The Data Stream Treatment Capacity of the PLCDHS Data Handling System is 48 Mbit/s.


The Ocean Current Speed Accuracy of the Satellite System Earth Observation is 0.2 m/s.


The Xenon Pressure of the EPTA Electric Propulsion Thruster Assembly is 150 bar BOL.


The Launch Date of the CubeSat - Launch 4 Satellite is 17 April 2006.


The Reflector Aperture of the Biomass Satellite is 12 m circular projected aperture.


The Interplanetary Vector Magnetic Field Measurement Accuracy of the DSCOVR Satellite is ±1 nT.


The Launch Vehicle of the DubaiSat-2 Satellite is Dnepr.


The Unknown of the Direct Readout Data Users Organizations is Multiple.


The Technology of the Micro-gravity experiment Experiment is Important for improving the quality of crystals.


The Spectral range of the VIRR Visible and Infrared Radiometer is 0.43-12.5 µm.


The TT&C Station of the Ground Segment Satellite Ground Segment is Kiruna.


The Project Management Importance of the AzTechSat Nanosatellite is Main step for successfully completing any project.


The Image Capture Date of the Small Monitor Camera Camera is April 16, 2018.


The Mass and Volume of the Core-DHS Avionics Module is Reduced.


The Meeting Date of the EarthCARE Mission is April 19, 2017.


The Conference Presentation Date of the RISESAT Satellite is August 13-16, 2012.


The Power of the Voltage 4 Modulator is 1.38.


The Design of the Imaging Subsystem Telescope is Dall-Kirkham.


The Caption Author of the VIIRS Imaging Radiometer is Adam Voiland.


The URL of the Electron Tunneling Infrared Detector Detector is http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19910005078_1991005078.pdf.


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


The Manufacturer of the BILSAT-1 Satellite is BILTEN.


The New Fundraising Goal of the Inspiration4 Mission is $200 million.


The Microprocessor Core of the Chang'e-4 Mission is LEON2-FT.


The Polarization of the CSG-SAR Synthetic Aperture Radar is Single, Dual, Quad.


The Satellites of the MHS Instrument is NOAA-N (NOAA-18) and NOAA-N' (NOAA-19).


The Other Components of the DOSTEL Radiation Detector is Two PIN diodes fixed to the one print board and mounted towards the other two directions.


The Launch Type of the ORS-6 Satellite Mission is Commercial rideshare.


The Data Processing Method of the TanDEM-X Satellite is Special algorithms that first evaluate each image individually and then combines them to form a global map.


The Swath Width of the IRIS Instrument Spectral Scanner is 50 km.


The Field of View of the FOV Spectrometer is 4.2º.


The Departure Date from ISS of the Kounotori-6 Cargo Ship is Jan. 27.


The Function of the Imager Device is Regulate the temperature of the metering struts.


The Diameter of the Secondary Body Asteroid is 160 m.


The Time in Orbit of the Aeolus Satellite is 20 months.


The Mission Type of the CXBN-2 Satellite is Non-EO.


The Peak RF Power of the SAR antenna Antenna is 1.8 kW.


The Power of the TxU Transmitter Unit is 26 W.


The Safe Mode Data Rate of the LunaH-Map Satellite is 62.5 bit/s.


The Type of the Imager Satellite Instrument is Pushbroom with TDI capability.


The Technology Transfer Program of the SOHLA-1 Satellite is Ongoing.


The Provider of the RS2000 Spacecraft is NASA.


The Secure Commands of the DCU Data Control Unit is OTAR (Over-The-Air-Rekeying), key integrity checks and key disabling.


The Manufacturer of the TEMPO Instrument is Ball Aerospace.


The Acquisition Completion Date of the ICON Satellite is 6 June 2018.


The Satellite Launch Date of the Capella Space Company is December 2018.


The Multi-Look of the Non-Capella radar SAR System is 1.


The Operational Start Date of the GCOM-W1 Satellite is Mid-2013.


The Launch Date of the SPOT-4 Satellite is March 24, 1998.


The Receiver Telescope Type of the DIAL Instrument LIDAR is Cassegrain.


The Mass at Launch of the PARASOL microsatellite Satellite is 120 kg.


The Solar Array of the Orion Spacecraft is Four wings of three panels.


The Contact Email of the eoPortal Website is eoportal@symbios.space.


The Navigation Signal Provider of the GPS satellites Satellite is Broadcast navigation signals.


The Architecture of the UVNS Spectrometer is Modular.


The Power Consumption of the Instrument Optical Bench is 32 W.


The Pan of the Pushbroom imager Spectral Band is 0.45-0.9 µm.


The Mass of the Imager Satellite Instrument is 135 kg.


The Duration of the Crew-1 Mission is Six-month.


The Design Life of the ERBS Satellite is 2 years.


The Frequency of the W-band Band is 77 GHz.


The Bacteria Test Subject of the Biofilms Experiment is Staphylococcus capitis.


The Checkout Period of the FASTRAC satellites Satellite is About two weeks.


The Possible Extension of the SAMPEX Satellite is One year.


The Aperture of the Optics Device is 20 mm.


The Interstellar Space Survey Start Date of the Voyager 1 Satellite is 11 May 2021.


The Image Date of the VIIRS Imaging Radiometer Suite is 7 April 2022.


The Computer Memory Interfaces of the SMEX Satellite Program is Four EIA RS422 Direct Memory Access (DMA) interfaces.


The Development Steps Date of the RF-Ion Thrusters RIT Ion Thruster is 2001.


The Launch Date of the BEAM Module is 8 April 2016.


The Number of Thrusters of the PROP unit Propulsion System is 4.


The Antenna Beam Surface Incidence Angle of the SMAP Satellite is Approximately 40º.


The Shutter Operation Frequency of the ELENA Instrument is Above 20 kHz and up to 50 kHz.


The Mediating Percentage of the Photosynthesis Biological Process is 90% of carbon and water fluxes in the coupled biosphere-atmosphere system.


The Expected Profitability of the Astrocast Satellite Manufacturer is Loss-making for at least 2022 and 2023.


The Presentation Date of the CMC Windward TPS and Nose of the IXV Vehicle Thermal Protection System is Oct.12-16, 2015.


The Orbit Type of the OceanSat-1 Satellite is Sun-synchronous near-circular orbit.


The Data Throughput of the AIS Data Collection System Data Collection System is 30 MB per day.


The Diagnostic Port Function of the EDSN satellites Satellite is Data interface and battery charging during I&T activities.


The Satellite Production Cost of the Satellogic Satellite Imaging Company is One-tenth the cost.


The Ground Stations of the DEIMOS-2 Satellite is Puertollano, Kiruna, and Inuvik.


The Hardware of the FFRF Subsystem Relative Positioning System is One terminal and up to 4 sets of antennas on each satellite.


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


The Performance of the CSS Instrument is ±0.115º.


The Communication Status of the YES Satellite is Not Re-established.


The Scale of the Image Data is Indicated on the image.


The URL of the SwRI-led team Team is https://www.swri.org/press-release/high-fidelity-images-sun-atmosphere?.


The Array Pointing Requirement of the IXPE Mission Satellite Mission is Within ±25 degrees of sun normal.


The Relative Position Measurements Accuracy of the CanX-4&5 Satellite is Centimeter-levels.


The Function of the Single-function satlets Satellite Subsystem Type is Incorporate one individual satellite subsystem function per satlet.


The Shape of the Baffle Telescope Component is Closely follows the RX beam.


The Frame Format of the Iris Video Camera Camera is 4096 x 20 pixels (UHD); 1920 x 1080 pixels (HD).


The Location of the COR-2 Coronagraph is On board NASA’s STEREO-A (Solar and Terrestrial Relations Observatory-A).


The Thermal Design of the Antennas, Solar Array, Sun Sensors, MLI Satellite Components is Dedicated high temperature technologies.


The URL of the Chandra Satellite is http://chandra.harvard.edu/press/18_releases/press_101218.html.


The Speed of the Solar Particles Space Phenomenon is Fastest.


The Input Spectral Radiance Sources of the ICU Internal Calibration Unit is The Sun (ICU_S mode) or by Internal Sources (ICU_IS mode).


The Owner of the RapidEye Earth Observation Constellation is BlackBridge.


The Threshold of the High LET Detector Detector is 2 MeV.


The Investment of the IOD Program Program is œ1.5 million.


The Development Status of the CIMR Satellite Mission is Proposed.


The Data Rate of the OPAL Satellite is 9.6 kbit/s.


The Minimum Power of the Solar Arrays Power Source is 4kW.


The Number of IFOVs of the Spectrometer Spectrometer is 3 x 3 at 14 km diameter for each band.


The Functionality of the Ground Software Architecture System is Automatic query and validation of real-time telemetry, downloading stored spacecraft telemetry, and command and control of the platform and its experiments.


The ACS Development of the Chibis-M Microsatellite Satellite is Unknown.


The Applications of the Optical Payload Payload is Monitoring plankton blooms to changes in the polar ice caps.


The Calibration Conference Date of the GOMS Geostationary Operational Meteorological Satellite is March 15–19, 1999.


The Mission of the COWVR Radiometer is Space Test Program-Houston 8 (STP-H8).


The Total Mass of the TiPS Satellite is 54 kg.


The Duration of the Request for Proposal Process is 12– to 18–month period.


The Integration of the OCSE Satellite is Minotaur rocket.


The Measurement Category of the ISS-RapidScat Instrument is Ocean surface winds.


The Mission Timeframe of the RAVAN Satellite is Six months.


The Clock 1 Function of the QZS-1 Satellite is Generating positioning signals.


The Frequency Range of the Receiver Communication System is 7145 to 7235 MHz.


The Equipment Health of the Satellite Spacecraft is Nominal.


The Science Objective of the ELFIN Satellite is Identify the magnetospheric source location of ionospheric field aligned currents (FACs), in relation to tail boundaries.


The Function of the GYRO Inertial Sensor is Pick up the resulting angular rates of the system.


The Data Collection Duration of the OMI Ozone Monitoring Instrument is Over a decade.


The Star Scanner of the ERG Satellite is Spin-type.


The Publication Date of the System Concept for Wide-Field-Of View Observations of Ocean Phenomena from Space Publication is 1987.


The Altitude Range of the SOFIE Instrument is 40-95 km for T, 55-95 km for O3, 20-95 km for H2O, 20-75 km for CH4.


The Configuration of the NIRISS Near-Infrared Slitless Spectrometer is Grisms and filters optimized for first-light science and exo-planet observations.


The Pressure of the Airtight Vessel Satellite Component is 1200 mbar.


The Altitude of the Beijing-1 Satellite is 686 km.


The Integration Time of the Responsivity Measurement Instrument is Almost cancel the noise on the measurements.


The Receiver Type of the Satellite Spacecraft is Dual-frequency.


The Design Type of the TCS Thermal Control Subsystem is Passive and Active.


The Mission Goal of the Nanosatellite Satellite is Micro imaging system, GPS receiver, MEMS based IMU.


The Deployment Services of the NanoRacks LLC Company is Small satellites.


The Attitude Subsystem Knowledge of the Spacecraft Satellite is 0.1º (3σ).


The Unknown of the Space Environment Data Acquisition Equipment Data Acquisition Equipment is Unknown.


The Measurement Category of the Kolibri-2000 Satellite is Radiation budget, Gravity, Magnetic and Geodynamic measurements.


The Function of the OSCAT-3 Radar Scatterometer is Measure wind speeds and vectors at sea level.


The Test Date of the Narrow-Band IoT Technology is 17 October 2019.


The Software of the HISat Satellite is Enables HISats to be aggregated together informationally so that satlet resource exposure and sharing is transparent to the operation of the system.


The Science Payload Sensor Type of the Neutron-1 Satellite is Elpasolite sensor.


The Data Rate from FPGA to S-band transmitter of the Transmission Module FPGA Module is 1 Mbit/s.


The Operational Period of the ISS Space Station is Until 2030.


The Percentage of Components with No New Technology of the Instrument Assembly System is 80%.


The Type of the Spectrographs Optical Instrument is Aberration-corrected Offner-type.


The Resolution of the MGF Instrument is ~0.1 nT.


The Encryption of the Transceivers Communication Device is 128 AES.


The Polarisation of the CSG-SAR Satellite is Dual.


The Components of the SOT Telescope is OTA (Optical Telescope Assembly), FPP (Focal Plane Package).


The Deep-Space Calibration of the WindSat Radiometer is Not provided.


The Linearity of the PMC-2 Imagers Imaging System is Better than 3%.


The Desired Quake Magnitude of the InSight Seismic Experiment for Interior Structure (SEIS) is Bigger than 4.0.


The Cooperation Paradigms of the Multisensory feature Data Management is Federation and Expansion.


The Material Used for Signal Amplification of the ATMS Instrument is Indium Phosphide.


The Field of View, horizontal of the Instrument Spectrometer is 24º.


The Spectral Range of the HR Spectrometer Spectrometer is 740–780 nm.


The Launch Date of the FireBird Mission is April 8, 2013.


The Maximum Number of Optical Pulses in the FOV of the LI Instrument is 25 in 1 millisecond, 800 in 1 second.


The I&T Start Date of the IXPE observatory X-ray Observatory is March 2020.


The Data Processing Time of the C3S Command, Control and Communications Segment is Less than 30 minutes.


The Communication System of the CAPSTONE Satellite is S-band telecommunication system.


The Launch Date of the GOES-S Satellite is March 2018.


The Interfaces of the CIU Control and Interface Unit is CAN interface to the bus, PPS interface to the GPS.


The Mission Date of the Kolibri-2000 Microsatellite is April 4-8, 2005.


The Structure of the Lander Spacecraft is Truncated pyramid around a cylinder.


The Mass of the MI Radiometer Instrument is 139 kg.


The Wake Up Time of the Jade Rabbit-2 Rover is 10:51 a.m. last Thursday (28 February).


The Mounting Method of the Optomechanical System System is Epoxy bed of Stycast 2850FT.


The Photo Transmission Date of the Chang'e-3 Lunar Probe is Dec. 15, 2913.


The Presentation Date of the RapidEye Earth Observation Constellation is Oct. 4-8, 2004.


The Number of Orbits around Jupiter of the Juno Spacecraft is 35 times.


The URL of the Roman Space Telescope Space Telescope is https://www.nasa.gov/feature/goddard/2021/nasa-s-roman-mission-predicted-to-find-thousands-of-transiting-planets.


The Data Provider of the IDE System is Provides the stream of science data to the C&DHS.


The Data Quantization of the Instrument General is 10 bits.


The Primary Mirror Diameter of the Optics Assembly Telescope is 200 mm.


The Launch Date of the Resurs-P1 Satellite is May 2015.


The Launch Date of the FalconSAT-3 Satellite is Unknown.


The AIS Status of the AISSat-1 Satellite is Fully operational.


The Operational Experience of the Copernicus POD Service Service is Not provided.


The Mission Start Date of the Deep Space 1 Satellite is Unknown.


The Update Frequency of the Active Schedule Planning Product is Minimum of once per week.


The Purpose of the NICER XTI X-ray Timing Instrument is Observations of neutron stars with high time resolution.


The Power of the TRSR GPS Receiver is 7-15 W.


The Attitude Control Strategy Presentation Date of the LAPAN-A2 Satellite is April 8-12, 2013.


The Next Satellite Launch Date of the OneWeb Low-Earth-Orbit Broadband Venture is July 1.


The Uplink Modulation of the S-band transponder Communication Device is NRZ (Non-Return to Zero) bi-phase modulated synchronously on a 16 kHz subcarrier.


The Telemetry of the X-ray Satellite Navigation Navigation System is 40 kbit/s.


The Observation System of the SEOSAT/Ingenio Satellite is Combined radar and optical images.


The Location of the MOC Mission Operations Center is MBRSC.


The Vector Components Random Error of the Magnetic Field In-Situ Sensor is < 1 nT.


The Size of the Star Tracker Attitude Determination Device is 59 x 56 x 31.5 mm.


The Status and Instrument Performance of the SUOMI National Polar-orbiting Partnership Satellite is Unknown.


The MTF of the Instrument Spectrometer is ≥0.2, ≥0.3.


The Antenna Dish Size of the KSAT Ground Station is 3.7 meter.


The Power Consumption of the Imager Camera is 1 W.


The Operation of the DMC Constellation Satellite Constellation is Can act as a single coordinated instrument if required.


The Mass of the WNISAT-1R Satellite is 43 kg.


The Pin Count of the Virtex-4 FPGA Data Processing Unit is 1140.


The Energy Measurement Range for Protons of the Telescope 1 Solid-State Telescope is 0.05 and 25 MeV.


The BAA Framework Name of the NRO National Reconnaissance Office is Framework for Strategic Commercial Enhancements.


The Subsidiary Location of the Spacety Company is Luxembourg.


The Partner of the TanSat Satellite Mission is University of Leicester.


The Number of Stars of the Pleiades Open Cluster is Several hundred.


The Altitude of the ZY 1-02C Spacecraft is 781 km.


The Power of the RPU Receiver Processor Unit is 36 W.


The On-Ground Footprint Range of the MWI Instrument is 50 km down to 10 km.


The Payload of the VisionCube-1 CubeSat is Multi-anode photon multiplier tube(MaPMT), a camera, and a real-time image processing engine.


The Solar Panels of the NSat Satellite is 4.


The Sensor complement / remarks of the Cosmos-1066 (Astrofizika) Satellite is Exp. payload on Meteor-1 satellite technology,special geophysical experiment (look for artificial light sources on Earth).


The Launch Date of the James Webb Space Telescope Space Telescope is 25 December 2021.


The Solar Panel Power Output of the AprizeSat Satellite is 15 W.


The Components of the HISUI Instrument is A multispectral sensor (MSS) and a hyperspectral sensor (HSS).


The Range of the Magnetometer Sensor is ±60 µT.


The Altitude of the KOMPSAT-3 Satellite is 625 km.


The Operations Schedule of the Mission Plan Document is Weekly.


The Volume of the RCU Radiometer Calibration Unit is 300 x 240 x 80 mm.


The Location of the JPSS Ground System Satellite Ground System is Global.


The Type of the FUV Instrument Spectrometer is Off-axis Czerny-Turner.


The Inauguration Date of the Kleos Headquarters Facility is December 14, 2021.


The Stereo Imaging Capability of the WV60 Satellite is Yes.


The Final Stop of the Philae Lander is A few meters away from the bounce.


The Function of the Magnetorquer Attitude Actuation Device is Liberation damping in the event that the gravity gradient boom deployment erroneously causes the patch antennas to settle in zenith pointing attitude.


The Spatial Resolution of the SAR Sensor Subsystem SAR Sensor is 20 m x 20 m.


The Orbit Period of the S/C Spacecraft is 6.2 years.


The Deployment Repeatability of the RDA Deployment System is Not provided.


The URL of the Drag-Free and Attitude Control System Control System is http://sci.esa.int/science-e/www/object/index.cfm?fobjectid=39981.


The Mission Type of the SMART Satellite is Non-EO.


The Launch Date of the Galileo Satellite Navigation System is 22 August 2014.


The First Contact Date of the RASAT Satellite is August 17, 2011.


The Application of the FY-3 (FengYun-3) Satellite is Ocean.


The Mechanism of the HGA Antenna is Two-axis gimbal.


The Data Bus of the C&DH Command & Data Handling is MIL-STD-1553B.


The Spatial resolution at nadir of the SBUS Solar Backscattering UV Sounder is 70/10 km.


The Contracts Awarded Date of the Joint Polar Satellite System Satellite System is Unknown.


The Mission Status of the Tsubame microsatellite Satellite is Stopped receiving uplink commands.


The Propellant Mass of the Propulsion Subsystem Propulsion is 2.3 kg.


The Developer of the Unicorn-2A PocketQube is Alba Orbital UG (Germany).


The Measurement Type of the EIS Sensor is Ion Composition and Angular Distributions.


The Total FOV of the Eastman Kodak KLI14403 linear CCD sensor Sensor is 52º.


The Launch Vehicle of the COSMO-SkyMed-1 Satellite is Delta-2.


The Role of the COSMIAC Organization is Build the satellite and collect the data from it.


The Calibration Data Acquisition of the Mini-RF Instrument is During spacecraft integration and test.


The Spectral Resolution of the Instrument Spectrometer is 10 nm, 12.5 nm.


The Data Coverage of the AMSU Microwave Radiometer is Up to 50 km.


The Dynamic Range of the Electric Field Measurement System Instrument is 80 dB.


The Solar Array of the Spacecraft Satellite is 10.6 m2.


The Announcement Date of the Water mission Satellite Mission is Sept. 3, 2010.


The Interruption Period of the S-193 Radar System is 4-year and 30-day.


The Actuation Type of the Canopus Pipper Satellite is Magnetic torque coils.


The Power Source of the PhoneSat-2.5 Satellite is Solar cells.


The Function of the EPS board Power Management and Protection is Interface many solar arrays, integrate active solar array maximum power point tracking, protect the battery from under-voltage.


The Measuring Cadence of the CLARA Instrument Satellite Instrument is 30 s.


The Data Products of the DPE Data Processor Element is RDRs (Raw Data Records), Sensor Data Records, EDRs (Environmental Data Products), TDRs (Temperature Data Records).


The Purpose of the GHOSt Satellite Constellation is Provide enhanced hyperspectral imagery for use in industrial, government, agriculture, environmental and defence sectors.


The Test Phases of the IEPS Ion Electric Propulsion System is Dec. 10, 2012.


The IADP of the LI Instrument is 90% for latitude 45º, 70% as average over the FOV, 40% over EUMETSAT member states.


The Composition of the Galinstan Eutectic Liquid Metal Alloy is Gallium, Indium, Tin.


The Presentation of the GPM Satellite is 28th ISTS (International Symposium on Space Technology and Science).


The Width at 1000 km distance of the LWIR Camera Camera is About 17.5 km.


The Polarization Dependence of the Scanning Systems Optical System is Problematic.


The Orbit Period of the JAWSAT Satellite is 100.36 min.


The Energy Range of the EPI-Lo Electron Detector is ~25 keV to 1000 keV.


The Spectral Range (µm) of the Band 2 Spectral Band is 0.84 - 0.89.


The Optics Components of the MSASI Imager is Fabry-Perot etalon and a temperature-stable narrow band filter.


The Slit Dimensions of the Imaging Subsystem Telescope is 1/2 x 5 arcmin.


The Launch Date of the Satellite EO is 18 Dec 1999.


The Bandwidth of the Band Photometers Photometer is 90 nm.


The Function of the POIC Payload Operations and Integration Center is Coordinates allocation of onboard resources.


The Detector Elements of the VIS Channel Detector Satellite Instrument is 4.


The Mission Status of the ADM-Aeolus Satellite is Unknown.


The Mass of the Hodoyoshi-1 Microsatellite is 60 kg.


The Launch Date of the PW-Sat CubeSat is February 13, 2012.


The Manufacturer of the Bus Satellite Component is  Blue Canyon Technologies.


The Frequency of the OCXO Oscillator is 222 Hz.


The Calibration of the MIS Instrument Microwave Radiometer is 2-point.


The Qualification and Test Activity of the Taurus Frangible Joint System Satellite Component is Based on the results of an extensive failure analysis (for example, detailed fault tree or failure mode analysis) and with consideration for the environments in which the joint is operated.


The Dimensions of the ShadowCam Instrument is 118 cm long and 27 cm in diameter.


The Author of the Observation of the Earth and Its Environment: Survey of Missions and Sensors Documentation is Herbert J. Kramer.


The Collaboration of the JEM-EUSO Satellite is T. Ebisuzaki, H. Mase, Y. Takizawa, Y. Kawasaki, H. Miyamoto, K. Shinozaki, H. Ohmori, Hachisu, S. Wada, T. Ogawa, F. Kajino, N. Inoue, N. Sakaki, J. Adams, M. Christl, R. Young, M. Bonamente, A. Santangelo, M. Teshima, E. Parizot, P. Gorodetzky, O. Catal.


The Designing Institution of the ZACube-2 CubeSat is F'SATI (French South African Institute of Technology) at CPUT (Cape Peninsula University of Technology).


The Electrical Noise of the APS-A and APS-B Sensors is Smaller than a digit of the ADC.


The Preparatory Campaigns of the CryoSat-2 Satellite is Arctic Arc Expedition, Antarctic 2008/9 CroVEx campaign.


The Approx. peak sensitivity altitude of the Channel 5 Sensor is Unknown.


The Mass of the KOMPSAT-3 Satellite is 970 kg.


The Aperture Diameter of the Instrument Telescope is 35 cm.


The URL of the LRO Satellite is http://www.nasa.gov/mission_pages/LRO/news/lro-topo.html.


The Orbit of the ERBS satellite Satellite is 507 km x 559 km.


The Pulse period (ms) of the B1813-140 Pulsar is 3.300.


The Vertical Sampling of the Instrument Spectrometer is ≤1 km.


The Radar Wavelength of the Biomass satellite Satellite is Around 70 cm.


The Mission Type of the CO2M Satellite is Two-satellite mission, with the option of a third satellite.


The Formation Mechanism of the Sunspot Solar Phenomenon is Mystery of the formation mechanism of a stronger field outside an umbra than in the umbra.


The Arrival Date at Jupiter of the Juno Spacecraft is July 4, 2016.


The Observation Modes of the OCO Satellite is Nadir, Glint, Target.


The VIS Channel Detectors of the SEVIRI Spectral Imager is Photo-voltaic silicon diodes.


The Number of Galaxies to be Mapped of the Euclid Space Telescope is Up to two billion.


The On-Orbit Verification Date of the Space Inflatable Structures Technology is June 1-8, 2008.


The Wing Span of the Spacecraft bus Satellite is 13.7 m.


The Purpose of the RADARSAT-1 Satellite is Produced radar imagery for applications in agriculture, cartography, hydrology, forestry, oceanography, geology, ice and ocean monitoring, arctic surveillance, and detecting ocean oil slicks.


The Operation Duration of the e-POP RRI Radio Receiver Instrument is Three Years.


The Altitude of the Satellite Orbit is 572 km.


The Mass of the GOMX-1 Nanosatellite is Up to 2.66 kg.


The Photodetector Model of the Optical Head Optical Device is MT 9M001 by Micron Technology, Inc..


The Objective of the FlaPS Instrument Package is To provide a solution to the investigation of plasma distributions in space - to characterize the effects of charged particles on the formation, propagation and decay of ionospheric plasma bubbles.


The Shift Length of the On-call Operations Operations is 16 hours.


The Manufacturer of the MM Radiometer Sensor is NASA/JPL.


The BER of the Miniaturized X-band transponders Communications System is < 1 x 10-5 for downlink.


The Impact of the Aeolus Satellite is Comparable to the impact from other satellite-based observations which have been assimilated for many years and have much larger data volumes.


The Number of Independent Samples of the PR Phased Array System is 64.


The Formation of the TSX and TDX Satellites is Close Helix.


The Number of Satellites of the BRITE Constellation Satellite Constellation is 5.


The Design Life of the TRMM Satellite is 3 years.


The Array Power Average of the Spacecraft Bus (Avionics Module=AM) Satellite is 650 W.


The Side Panels of the CSTB1 Satellite is P0 through P5.


The Launch Date of the Meteor-1-2 Satellite is 06.10.1969.


The System AI&T Duration of the RRSW Integration Facility is Six months.


The Function of the Tether Spacecraft Component is Antenna.


The Direction of the Japan Current Ocean Current is South.


The Service Cost of the Starlink Premium Satellite Internet Service is $500 per month.


The Swath Width of the LIS Lightning Image Sensor is 550 km.


The Security of the QKD Quantum Key Distribution is Provable security against future hacks from advanced computers.


The Number of Sensors per Instrument of the PIMS Plasma Instrument is 2.


The URL of the OSCAR-QUBE Satellite is https://www.esa.int/Education/Orbit_Your_Thesis/.


The Orbit of the Tianzhou-2 Cargo Spacecraft is 343 by 371 kilometers.


The Quantity of the Solar Panels Power Source is 2 sets.


The Purpose of the Proof-of-Concept Prototype Prototype is Test future options for maritime autonomous vessel navigation.


The Ground Stations of the NigeriaSat-2 Satellite is Abuja and Guildford.


The | of the R. A. Schwartz Author is R. A. Schwartz.


The Ellipse Axis A of the Long Wavelength Band Spectrometer is 180 mm.


The Launch Status of the OrbView-4 Satellite is Failure.


The Landing Date of the Chang'e-3 Lunar Probe is Dec. 14, 2013.


The System Overview of the Sentinel-1 Satellite is Unknown.


The Launch Date of the Landsat Satellite is Unknown.


The Program Start Date of the OICETS Satellite is 1993.


The Launch Date of the OPS-SAT Satellite is 2012.


The Functions of the TDP Signal Processor is Gamma (spike) event circumvention, detector responsivity correction, background subtraction, time delay and integration (TDI), matched filtering, and thresholding.


The Publication Date of the Very-Wide-Filed Ultraviolet Sky Survey Instrument is July 13, 1984.


The CPU of the SCU Satellite Central Unit is HD64F7145FW50.


The First Image Release Date of the Webb Telescope Space Telescope is 12 July 2022.


The Separation Distance of the GRACE Satellite Satellite is Between 170 to 270 km.


The System Integration Review Date of the Europa Clipper Spacecraft is Late 2021.


The BDH Subsystem of the ResourceSat-2 Satellite is X-band data transmission system.


The Orbit Type of the BUV Sensor is Sun-synchronous near-circular polar orbit.


The Transmission Power of the SSRNI Data Acquisition and Registration System is 8 W.


The Location of the Wetlands Ecosystem is Iran's border with Afghanistan.


The File System of the Data Storage System is FAT32.


The Source Data of the µSCIA Monitoring Instrument is Planned to be posted onto the Internet.


The Flatness Requirement of the Photon Sieve Optic is Approximately 3λ.


The URL of the ICON Satellite is https://icon.ssl.berkeley.edu/science/.


The Orbit Altitude of the SuperView-1 01 and Superview-1 02 Satellite is 530 km.


The Detector Technology of the Optical Sensor Assembly (OSA) Instrument is Pushbroom detector technology.


The Integration Date of the Second Scientific Instrument Scientific Instrument is Unknown.


The Announcement Date of the OneWeb Satellite Constellation is June 25, 2015.


The Support Mode of the SLIM6 Imager is Window Pseudo Real-Time Imaging.


The Temperature Sensitivity of the Etalon Filter is 2.9 pm/K.


The URL of the James Webb Space Telescope Telescope is http://www.stfc.ac.uk/ukatc/resources/pdf/miri5487-28.pdf.


The Presentation Date of the RapidEye Earth Observation Constellation is Oct. 12-16, 2009.


The Accuracy of the CLARREO Pathfinder Satellite is 4 to 8 times more accurate than current best available sensors on orbit.


The Number of Eligible Rows of the QWIP Array Sensor Array is Not specified.


The Presentation Date of the Texas 2 STEP Satellite Mission is Aug. 11-14, 2008.


The Type of the AMSU-A Instrument is Cross-track, line-scanning instrument (whiskbroom type).


The Size of the MCubed/COVE-2 CubeSat is 1U.


The Ranging Accuracy of the Galileo Satellite Navigation System is Better than 1.07 m.


The Application of the CMT Imager is Local Mapping.


The Accelerating Rate of the Sea Level Climate Parameter is 3 mm/year.


The Satellite Constellation Goal of the Satellogic Satellite Company is 300 satellites by 2025.


The Mission of the Colloid Microthruster Thruster is Space Technology 7 and LISA.


The Function of the ShadowCam Instrument is Capture images in lunar orbit.


The Launch Date of the FalconSat-3 Satellite is 9 March 2007.


The Mass Resolution of the COSIMA Mass Spectrometer is 2000.


The Platform of the DoT-1 satellite Satellite is SSTL-Micro.


The Antenna Sizes of the Ground Station Ground Station is 9.1m, 4.6m.


The Crater Location of the CaSSIS camera Camera is 134°12'13.0"W/43°14'59.7"N.


The Calibration Methods of the SeaWiFS Satellite is Short-period solar calibration, long-term lunar calibration.


The Workshop Date of the China Earth Observation Satellite Program Satellite Program is Feb. 11-13, 2009.


The Downlink Channels of the CubeSat Satellite is 2.


The Depth of the Sognefjord Fjord is 1308 m.


The Mass memories of the Data Handling Unit Subsystem is MM0, MM1, MM2, MM4.


The Maximum Satellites Launched of the New Glenn rocket Rocket is Around 30.


The Symposium Date of the Flying Laptop Satellite is April 8-12, 2013.


The Attitude Control Subsystem of the TUBSAT-N Satellite is CCD star sensor, 3-D magnetic compass, two magnetic coils, reaction wheel.


The Capacity of the S/C Data Recorders Data Storage is 54 Gbit.


The Landing Date of the InSight Mars Lander is 29 November 2018.


The Heritage of the LET Low Energy Telescope is SOHO/ERNE.


The Design Life of the ACRIMSat Satellite is 5 years.


The Planned Operation of the ARTEMIS Probes Spacecraft is Routinely operate in the most eccentric lunar science orbits of any mission to date.


The Structure Material of the GNB Satellite Platform is Al 6061-T6.


The Sensitivity of the GOME-2 Spectrometer is Negligible.


The Mass of the Beta Pictoris b Planet is At least 50 times more massive than AU Mic b.


The Development of the PACE nanosatellite Satellite is Carried out by students of the PACELAB research laboratory at NCKU.


The Purpose of the GPM (Global Precipitation Measurement) Mission Satellite Constellation is Study global precipitation, evaporation and the water cycle.


The Purpose of the ICON Satellite is Explore the boundary between Earth and space – the ionosphere.


The Frequency of the TT&C Telemetry Tracking & Command is 437.385 MHz.


The Location of the Star Trackers Device is Zenith end assembly.


The User Data Rates of the Optical Downlink Communication System is 39 – 620 Mbit/s.


The URL of the FireBird Satellite is http://www.int-arch-photogramm-remote-sens-spatial-inf sci.net/XL-7-W3/461/2015/isprsarchives-XL-7-W3-461-2015.pdf.


The Transmitter Modulation Bandwidth of the S-band transponder Communication Device is 3 MHz.


The Along-Track Separation of the ATI Experiments Satellite Experiment is Optimal observation conditions.


The Satellite Class of the Cheollian 2B Satellite is 3.4-ton class.


The Polarization of the Antenna ADS-B Antenna is Right Hand Circular.


The Launch Date of the Jason 2 Satellite is June 20, 2008.


The Aperture Diameter of the COR1 Coronagraph1 imager is 36 mm.


The Field of View of the ALI Telescope is 15º x 1.26º.


The Mission Scientist of the CO2M Satellite is Yasjka Meijer.


The Solar Panels of the CartoSat-2B Satellite is Deployed.


The Moving Parts of the Spatial Heterodyne Spectroscopy (SHS) Interferometric Fourier transform technique is None.


The Design Approach of the Sentinel FOS Flight Operations Segment is Extensive re-use of elements developed in the context of previous Earth Observation ground segments.


The Wavelengths of the Herschel Space Telescope is 70 µm (blue), 160 µm (green) and 250 µm (red).


The Launch Date of the MEPSI Satellite is July 19, 2000.


The Acquisition Telescope Size of the OCTL Telescope is 20 cm.


The Amplifier Power of the Knudsen Station Ground Station is 500 W.


The Temperature at which it stopped working of the Home Switch Switch is Unknown.


The Launch Vehicle of the ICEYE-X2 Satellite is SpaceX Falcon 9 rocket.


The IAC Presentation Date of the D-Sat Satellite is 25-29 Sept. 2017.


The Launch Date of the AQT-D 3U CubeSat Satellite is 24 September 2019.


The TDP Command Release of the Inmarsat Automated Procedure Execution System System is Automatic.


The Conference Presentation Date of the Stuttgart Micro Satellite Satellite is May 5-9, 2014.


The Wavelength Range of the IR Channel Imaging Device is 1.3 – 4.5 µm.


The Imaging Modes of the SAR Instrument Synthetic Aperture Radar is Strip imaging, spot imaging.


The On-board Calibration System of the CLARREO Satellite is Uses the Sun as part of its on-board calibration system.


The Features of the ASAR Instrument is A digital chirp generator and an improved linear dynamic range, Flexible swath positioning, Dual polarization capability, Wide-swath coverage, Enhanced wave-mode, Extended duty cycle, Global SAR coverage.


The Visible and Infrared Spectrometer of the OSIRIS-REx Spacecraft is OVIRS.


The Experimental Mode Coverage of the TSX-SAR Satellite is 5 x 10.


The URL of the Swarm Satellite Mission is http://www.dsri.dk/~nio/papers/EPS_58040359.pdf.


The Data Transmission of the QARMAN CubeSat is Iridium telecom satellites.


The Atmospheric Measurements of the POPACS Satellite is Data.


The Measurement Range of the OVM Overhauser scalar magnetometer is 16,000 - 64,000 nT.


The Publication Journal of the Telerobotics Space Technology is Science Robotics.


The Field-of-View (FOV) Defining Apertures of the TR Integrating Sphere is 2.


The Tandem Mission Start Date of the Envisat / ERS-2 SAR Satellite is Nov. 23, 2008.


The Bit Depth of the MSS Instrument Radiometric Signal is 6 bit per pixel.


The Solar Elevation Angle of the Instrument Spectrometer is 30-90º.


The Weight of the Kowa LM16JC lens Lens is 55 g.


The Budget Allocation of the Galileo Global Navigation Satellite System is 8 billion euros.


The Instantaneous spectral coverage of the Spectrometer Instrument is 1.56 km/s.


The Design Life of the Gokturk-2 Satellite is 5 years.


The Bias Voltage of the Suppressor Grid Satellite Component is -12 V.


The LTAN of the Max Valier Satellite is 17:00 hours.


The Guide Stars Monitoring Interval of the DPU Data Processing Unit is 10-20 seconds.


The Formulation Date of the CLERREO Mission is 2009.


The Electrical Power of the MHX-2400 S-band Transmitter/Transceiver is 4.85 W.


The Propulsion System of the Clementine Spacecraft is Bipropellant nitrogen tetraoxide and monomethyl hydrazine system for the maneuvers in space.


The Flare Detection Date of the Spitzer Space Telescope Telescope is July 31, 2019.


The Design of the MMS Satellite is Four spacecraft flying in a tight tetrahedral formation.


The Orbital Period of the Main Payload Satellite is About 97.7 minutes.


The Beam Incidence Span of the SWIM Real Aperture Radar is Up to 10º.


The Purpose of the Webb's Fine Guidance Sensor (FGS) Sensor is Enable accurate science measurements and imaging with precision pointing.


The Verification Process of the ASAP Autonomy System is Closed loop manner, take over control of the satellite by manipulating SONATE’s active command list.


The Torque Input of the Attitude Control System Satellite System is Minute and continuous.


The Solar Absorptivity of the Cube Corner Reflectors (CCRs) Satellite Component is αs.


The Mode Name of the Poseidon 4 Radar Altimeter is InterLeaved Mode.


The Symposium Date of the GMES Sentinel-3 Satellite is July 25-30, 2010.


The Thermosphere Temperature of the Instrument Spectrometer is Typically > 600 K.


The Pointing Accuracy of the IPS Pointing System is Within 2 arcseconds.


The Development Schedule of the ANGELS Nanosatellite is Particularly short.


The Radio and Reaction Wheels Voltage of the MarCO-B Satellite is Greater than 8V.


The Mass of the Giant Molecular Clouds Interstellar Medium is Up to 10 million times the mass of the Sun.


The Backup Purpose of the CIRAS Instrument is Gap filler in the event of a failure of the CrIS.


The Purpose of the SAGE-III on ISS Satellite Instrument is Monitor the health of the ozone layer and track the recovery of stratospheric O3.


The Atomic Clocks of the Indian Regional Navigation Satellite System (IRNSS) Satellite System is Failed.


The Launch Date of the CBERS-1 Satellite is Oct. 14, 1999.


The Measurement Range of the Spectral Channels Satellite Instrument is 1.6 to100% albedo.


The Improvement of the DDA Delay-Doppler Altimeter is Capturing more reflected energy and requiring smaller transmitted power.


The Instrument Mass of the RA-1 Radar Altimeter is 96 kg.


The Battery Capacity of the EPS Electric Power Subsystem is < 7600 mAhr.


The Launch Target of the NISAR Earth Observation Satellite is 2022.


The Publication Date of the Small GEO Programme Satellite Programme is 2012.


The Impact on Astronomical Observations of the Satellite Constellations Satellite System is Not specified.


The Technology of the LOFTID Project is Hypersonic Inflatable Aerodynamic Decelerator (HIAD).


The Power Output of the PDC Power/Data Controller is Conditioned 28 VDC and 12 VDC.


The Orbit Type of the Tandem-L satellites Satellite is Sun-synchronous dawn/dusk orbit.


The Absolute Performance Error of the Spacecraft Satellite is < 20 arcsec (95%).


The Mass of the Earth Radiation Budget Experiment (ERBE) Instrument is 57 kg/scanner.


The Purpose of the SGLI Imager is Measure ocean color, SST (Sea Surface Temperature), land use and vegetation, snow and ice, clouds, aerosols and water vapor.


The Ability to Revisit of the ZY-3A Satellite is 4-5 days.


The Repetition Rate of the Drifting (Mobile) Platforms Ground Segment is 90 - 150 seconds.


The Solar Panel Power of the DubaiSat-2 Satellite is More than 450 W.


The TT&C Function of the COSMO-SkyMed-1 Satellite is S-band.


The Current Distance of the IC 4665 and Collinder 350 Star Clusters is More than twice as large as the diameters of the biggest molecular clouds.


The Downlink Speed of the Communication links Communication System is 9.6 - 38.4 kbit/s.


The Motion of the Solar Plumelets Solar Phenomenon is Move individually, oscillating on its own.


The Quasar Diminishment of the The Teacup Quasar is Only fading by a factor of 25 or less over the past 100,000 years.


The Contract Date of the AERO-VISTA mission Satellite Mission is May 7, 2020.


The Repeat Cycle of the CERES on TRMM Instrument is 46 days.


The Article Release Date of the Solar Orbiter Satellite is 17 May 2021.


The Number of Cells per String of the Solar Array Power Generation is 39.


The Last Spinup Maneuver Date of the Satellite Spacecraft is July 2, 2014.


The Type of the Orbit Satellite is Sun-synchronous near-circular.


The Function of the Antenna Payload is Easily removed from the spacecraft without removing any of the spacecraft panels.


The Swath Width of the SAM-II Instrument is 5 - 40 km vertical.


The Operation of the JEMRMS Robotic Arm is Catches EP and carries it to EFU.


The Data Collection Start Date of the TerraSAR-X Satellite is Early 2011.


The Payload Sizes of the Bartolomeo Platform Satellite Platform is Airlock-compatible size, FRAM-based standard size.


The Calibration Phase Start Date of the Hitomi X-ray Astronomy Satellite is Middle of April.


The Development of the MONTE Software is Precision one-way radiometric measurement modeling, high fidelity clock modeling, and appropriate filter methods.


The Orbit Altitude of the ALBus CubeSat Satellite is 500 km.


The Phase A/B1 Study Contracts of the OPS-SAT Satellite is Awarded to TU Graz and GOMSPACE.


The Overall Length of the GSLV-F05 Rocket is 49.1 m.


The Size of the OMS Radiometer Radiometer is 10 x 10 x 15cm.


The Focal Length of the Optical Head Optical Device is 3 mm.


The Reach of the InSight lander Robotic Arm is Nearly 2 meters.


The Band of the IASI Infrared Atmospheric Sounding Interferometer is 1.


The Control Center of the Colony I Satellite is SOC (Satellite Operations Center) at BPTF (Blossom Point Test Facility), located near LaPlata, MD.


The New Deadline for Completion of the SpaceIL Nonprofit Group is December 2017.


The Long Range Navigation of the ATV-5 Spacecraft is Relative GPS navigation.


The Type of the MWIR Sensor Sensor is Miniature high temperature Mid-Wave Infra-Red (MWIR).


The Power Consumption of the AMU Altimeter Microwave Unit is < 39 W.


The Minimum Duration of the PACE Satellite is Three years.


The Unknown of the BELA Instrument is Unknown.


The Electronic Noise Contribution to Energy Resolution of the Detector Instrument is 400 eV.


The Propellant Mass of the DMC Propulsion Subsystem Electric Propulsion is 2.35 kg.


The Formation Geometries of the TanDEM-X Satellite is Bistatic Close formation.


The S/N or NEDT of the Spectral Channels Satellite Instrument is 150:1.


The Redesign Purpose of the SMA Hinge Spring Component is Increase area to reduce stress on the part by more than 20%.


The URL of the Space Debris IADC Assessment Report for 2010 Report is http://www.iadc-online.org/Documents/IADC-2011-04,%20IADC%20Annual%20Report%20for%202010.pdf.


The AIS of the LAPAN-A2 Satellite is Automatic Identification System.


The Mass of the EPDP Technology Payload is 2.3 kg.


The Data Release 2 of the Gaia Satellite is April 25, 2018.


The Spectrometers of the DebriSat Satellite is 2.


The Solar Wing Deployment Test of the BepiColombo Satellite is March 6, 2017.


The Inflatable Mast Length of the 3U CubeSat Satellite is 1 m.


The Function of the Front-End Electronics Module (F2EM) Electronics Module is Provides the detectors with all the necessary biasing and clocking signals and performs preamplification and transmission of the video signal to the MEV.


The Mission Type of the Cheops Satellite is Study of exoplanets.


The Maneuvers Events of the ARTEMIS Satellite is 170.


The Anomalies of the Earth's Magnetic Field Natural Phenomenon is Deviations from the idealized field of a centered bar magnet.


The Ion energy of the Microdosimeter B Instrument is > 50 keV.


The Unique Feature of the Spire Satellite Constellation is Reaching remote areas like the open oceans.


The Developers of the CPR Cloud Profiling Radar is NASA/JPL and CSA.


The Adapter and Separation System Mass of the ALMASat-1 Satellite is 20.5 kg.


The Recommendation of the Commercial Smallsat Data Acquisition Program Program is Put into statute and robustly fund.


The Field of View of the Collecting Optics Lens Assembly is ± 7º.


The Mission Type of the Cluster Satellite is Magnetosphere Measurement.


The Mass of the CICERO-6 6U CubeSat is ~10 kg.


The Storage Media of the Data Storage System is CompactFlash® card.


The Flight Model Manufacturing Start Date of the CHEOPS Instrument is End of 2015.


The Resolution of the Pléiades Neo Satellite Constellation is 30cm.


The High Pressure Tank Size of the I-COUPS Satellite is 2.0 L.


The Mass of the Sloshsat-FLEVO Satellite is 50-150 kg.


The Development Date of the CHRIS Imaging Spectrometer is Unknown.


The Percentage of New Subscribers of the SecureWatch Service is 70%.


The Launch Date of the Minotaur I Rocket Rocket is Nov. 19, 2013.


The Slit 2 Material of the MEGS-A Spectrograph is Si.


The Capsule Drop Altitude of the Hayabusa-2 Spacecraft is About 120 miles (or 200 km) above Earth’s surface.


The Wavelength Bands of the B. subtilis Microorganism is 470, 525, and 615 nm.


The Number of Orbits of the Kolibri-2000 Satellite is 711.


The Purpose of the MVP Cell-03 Experiment is Examine whether microgravity increases the production of heart cells from human-induced pluripotent stem cells (hiPSCs).


The Launch Date of the Chang'e-5 Spacecraft is Nov. 23.


The Manufacturer of the DWP Control System is University of Sheffield.


The Ground Station of the HYPSO-1 Satellite is KSAT Svalbard, Norway.


The Bandwidth of the FODB Data Interface is Gbit/s.


The Uplink Frequency of the DRT Data Relay Transponder is 402.75 MHz.


The Mass of the Deimos-2 Satellite is ~310 kg.


The Dimensions of the DART spacecraft with ROSA Spacecraft is 12.5 meters by 2.4 meters.


The Observation Date of the DICE CubeSats Satellite is March 16-17, 2013.


The Launch Date of the ZACUBE-01 Satellite is Unknown.


The Access Method of the Argos Communication System is Pure (i.e. unslotted) ALOHA.


The Launch Vehicle of the Herschel Telescope Telescope is Ariane-5 ECA.


The Anomaly of the ALOS-3 Satellite is Ignition signals for the SRB-3s were not sent.


The Orbit of the Queqiao Lunar Relay Satellite is Halo orbit.


The Mission Outcome of the ESEO Satellite is Reduced success in achieving the science objectives.


The Pixel Classification of the JWST Fine Guidance Sensor Sensor is Not Provided.


The Distance from New Horizons of the Hydra Moon is About 231,000 km.


The Leader of the XMM-Newton Survey Science Center Consortium is Professor Mike Watson.


The Interface of the Formation Flying Computer Computer is Propulsion system and GPS receiver.


The Mass of the PROCYON Deep Space Probe is 50 kg.


The Remarks/Sensors of the OrbView-3 Satellite is commercial imaging PAN +MS.


The Observation Duration of the DELPHINUS Satellite is Long-time and continuous.


The Manufacturer of the ArgoMoon CubeSat is Argotec S.r.I..


The Band 7 of the MSS Instrument Spectral Band is 0.8 - 1.1 µm.


The Launch Date of the Chandrayaan-2 Spacecraft is 6 September.


The Data Interfaces of the EuTEF Payload Facility is MIL-STD-1553B data bus and a redundant Ethernet.


The Vertical Resolution (Stratosphere) of the Aeolus Satellite is 2.0 km.


The Ground Segment Operator of the Galileo Satellite System is European Global Navigation Satellite System Agency (GSA).


The Image Acquisition Time of the VIIRS Imaging Radiometer is 1:35 p.m. local time (19:35 Universal Time) on May 30, 2022.


The Version of the CCSDS Space Data Link Security Protocol Protocol is 355.0-R-2.


The Magnitude Stability of the Magnetic Field In-Situ Sensor is < 0.12 nT over 3 months.


The Critical Design Review Status of the MSASI Imager is Finished.


The Calibration of the DESIS Hyperspectral Instrument is Pre-launch and post-launch.


The GSD (Panchromatic) of the GF-2 Satellite is 0.81 m.


The Optics Unit Focal Length of the Imager Payload is 10.5 cm.


The Number of Phase Centers of the SAR antenna Antenna is 18.


The Azimuth Resolution of the ScanSAR Imaging Mode is 18.5 m.


The Orbit of the Dove-2 Satellite is 575 km x 575 km.


The Resolution of the ScanSAR-1 Mode is 4 x 20m.


The Period of the Satellite Constellation Satellite Constellation is 136 minutes.


The Journey Time towards the Sun of the ISON Comet is About 3 million years.


The Manufacturer of the SAOCOM-1A Satellite is ArSat.


The Image Registration Accuracy of the Attitude Determination & Control System Satellite System is 100 m.


The LRIT and HRIT Broadcasting Service Provider of the GK2A satellite Satellite is KMA (Korean Meteorological Administration).


The Planned Launch Year of the SMILE Satellite is 2022.


The End of Life Date of the TechEdSat Satellite is 5 May 2013.


The Tether Pull Force of the ENT EVR Nozzle Tool is Up to 40-50 N.


The Feasibility Analysis of the CSK GS Ground Segment is Check the possibility to perform sensing on the selected Area of Interest during the selected Time Window and according to the chosen mission/satellite acquisition parameters.


The Integration and Testing of the BRITE-PL Satellite Project is By the Polish team with mentoring and supervising support from UTIAS/SFL.


The TFSC Data of the AlSat Nano Satellite is Regularly returned.


The Power Requirement of the APL’s Frontier radio Radio is Less than other deep-space radios.


The Solar Array Deployment of the MicroSCOPE Satellite is 3 pyrolock mechanisms for release and 2 Carpenter blades for deployment.


The Calibration Frequency of the MAC Memory System Module is Periodic basis.


The Seismometer Distance from Lander of the InSight Lander Lander is 1.636 m.


The No of Passbands of the Channel 7 Sensor is 1.


The Design of the Orion spacecraft Spacecraft is Uniquely designed for long-duration deep space flight.


The Viewing Angle of the ISS-LIS Instrument is Nadir or 5º off-nadir.


The Flatness of the Grating Optical Component is 1 λ (634.8 nm).


The Test Date of the ISIM Compartment is Summer 2015.


The Power of the SAGE-III Instrument is 80 W average.


The Largest Crater Diameter of the Eureca Satellite is 6.4 mm on the solar arrays.


The Ordinary Matter Percentage of the Universe Cosmology is 5 percent.


The Media of the Sojourner 2020 Art Payload is Carved stone sculpture, liquid pigment experiments, sculptures made of transgender hormone replacement meds.


The Mission Status of the GOSAT Satellite is Operational (extended).


The Lifespan of the Dove Satellites Satellite is Five to six years.


The Energy Range of the Electrostatic Analysers Sensor is 0.2 to 20 keV.


The Agency of the FormoSat-1 Satellite is NSPO.


The GSD of the Spacecraft Satellite is 1 m (PAN), ~ 4 m (MS) @ 600 km altitude, nadir view.


The Geo-location Accuracy of the Satellite Satellite is <50 m without GCP, 20 m with GCP.


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


The Total Transfer Time of the Transfer Orbit Orbital Maneuver is 3 to 4 months.


The Field of View Resolution of the IBEX-Lo sensor Sensor is 7° x 7° FWHM.


The WDT Function of the Phoenix EPS Electrical Power System is Count up to 12 hours then power cycle the entire spacecraft for 10 seconds.


The Small Size, Low Mass, Low Power Consumption of the MTP Transponder is True.


The Launch Date of the PSLV-C32/IRNSS-1F Satellite is March 10, 2016.


The Worst-Case Depth-of-Discharge of the Power Subsystem Satellite System is Well below the limit allowed by FP (Fault Protection).


The Swath Width of the SMMR Microwave Radiometer is Approximately 600 km.


The Swath Width of the QuickBird-2 Satellite is 16.5 km.


The Type of the Telescope Optical Instrument is Off-axis three mirror anastigmat type (TMA).


The Data Rate of the S-band Frequency Band is 4 kbit/s.


The Mass of the Microsat of ISRO Microsatellite is 100 kg.


The IR Detector Temperature of the OCTS Sensor is 100 K.


The Sample Stowage of the OSIRIS-REx Spacecraft is Originally scheduled for Nov. 2.


The Frequency Band of the X-band downlink transmitters Downlink Transmitters is X-band.


The TT&C Uplink Data Rate of the RF Communications Communication Subsystem is 125 kbit/s.


The On-board Storage Capacity of the ALOS-3 Satellite is Greater than 200 Gbit.


The CEO of the Galileo 2nd Generation Satellites Satellite is Hervé Derrey.


The Manufacturer of the Magnetometer Sensor is Honeywell.


The Mission Status of the TET-1 Satellite is On-Orbit Verification.


The Component Manufacturing of the Structure General is Machining components from solid.


The Focusing Method of the Camera Camera is Adjusting the focal plane position resulting from the adjustment of the flat mirror assembly position.


The Image Capture Date of the MarCO CubeSat is 22 October 2018.


The Manufacturer of the DRF Radiation and Ultraviolet Detector is Nuclear Physics institute (NIIYaF) of the Moscow State University (MSU).


The Plane Spacing of the FormoSat-3/COSMIC-1 Satellite Constellation is 24º.


The Goal of the Ma_MISS Spectrometer is Study the martian subsurface environment.


The Provider of the Seismic Experiment for Interior Structure (SEIS) Seismometer is Centre National d'Études Spatiales (CNES).


The Across-track FOV of the Telescope Optical Instrument is ±1.31°.


The Source Data Rate of the Payload Satellite Component is 336 Mbit/s.


The Launch Date of the SEASAT Satellite is June 27, 1978.


The Function of the Hysteresis (Memory) Material Attitude Control is Memorizes the current magnetic field and resists changes in KySat-2's orientation.


The Servo Bandwidths of the Guider Instrument is 0 to a few Hz (platform), <50 Hz (prime mirror fine guiding).


The OBR of the Payload Satellite Payload is Special Operations, one unit only (emergency use).


The Scatterometer of the CYGNSS Satellite is OSCAT and ASCAT.


The Conference Date of the GCOM-W1 Satellite is 5-9 September 2011.


The Stability of the Satnav Signals Signal is Highly stable.


The Provider of the CAVIS Imager is BATC (Ball Aerospace and Technologies Corporation).


The Data Transfer Interfaces of the UVN-DEMs and SWIR modules FPGA-based modules is 140 Mbit/s Channel Link interfaces, 80 Mbit/s SpaceWire interface.


The Manufacturer of the InSight Spacecraft is Lockheed Martin Space, Denver.


The Jacobi Constants Range of the Quasi-Halo Orbits Orbit is Cj = 3.04 to Cj = 3.1613263.


The Propulsion System of the Clementine Spacecraft is Non-propellant hydrazine system for attitude control.


The Monitoring Capabilities of the Copernicus Sentinel-3 Satellite is Wildfires, land use, vegetation state, sea surface temperature, sea surface color, sea surface height.


The Repeat Cycle of the Satellite Satellite is 22 days.


The Radiation Hardened of the MCM (Multi-Tip-Module) Main On-board Computer is True.


The Current Detection Scale Sizes of the MGF Instrument is 100 m or larger.


The Average Power of the Payload Satellite Payload is 1 kW.


The Multi-function component assembly of the BEESAT-3 Satellite is Yes.


The Collection Mode of the QuakeSat Satellite is Unknown.


The Gradiometer Instrument Position of the GOCE Satellite is Near the Centre of Mass.


The Capacity of the HSDR Data Recorder is 16 GByte.


The Spacecraft Provider of the PTD series Satellite is Terran Orbital.


The Maintenance Schedule of the COSIMA Mass Spectrometer is Checkouts every 6 months.


The Relative Orbit of the TSX and TDX Satellites is TDX has a relative orbit to TSX.


The Thruster of the PLATiNO-2 Satellite is HT 100.


The FOV of the FSS Photodiode Detector is 128º x 128º.


The Orbit of the NanoRacks CubeSat Satellite is Near-circular orbit of the ISS, altitude of ~400 km, inclination of 51.6o.


The Purpose of the LPT Radiation Environment Characterization Instrument is Improve the radiation environment knowledge and characterize the local radiation environment.


The Publication Date of the IceCube-Gen2 Satellite is August 2020.


The Use of the ROBUSTA ground station Ground Station is Future GENSO (Global Educational Network for Satellite Operation) use.


The Development Oversight of the Galileo Second Generation Satellite System is ESA.


The Energy Range of the X-ray Imager Instrument is 0.1–2 keV.


The Docking System Compatibility of the MEV-1 Satellite is 80 percent of all geosynchronous satellites.


The Lighting Requirement of the OSIRIS-REx Spacecraft is At least a 5º elevation.


The Handover to Crew-4 of the Crew-3 Spacecraft is Timed to maintain a U.S. presence on board.


The Sampling Rate of the ULF Sensor Sensor is 10 Hz.


The Platform of the Göktürk-1A Satellite is Proteus.


The Duration of the Asteroid Day TV Online Program is Five hours.


The Sponsor of the DebriSat project Satellite is NASA and DoD.


The Spatial Resolution (PAN) of the PP Instrument is 2.5 m.


The Funding Raised of the Xona Company is About $10 million.


The Deliverables of the Laser Team Team is ETU laser, three flight units, and a flight spare.


The Data Interface of the NSat Satellite is UART and I2C.


The Control Ground Segment of the Ground Segment Communication is CNES station network.


The Variable Stars of the Gaia Satellite is 10 million.


The Detector Array of the X-ray Spectrometer Spectrometer is 36-pixel.


The Components of the DBCP Pseudo-depolarizer is Four wedges of birefringent material.


The Intersatellite Link Data Rate of the CNAPS Propulsion System is 10 kbit/s.


The Technology of the EARS System is DVB-S2.


The Sensor Complement of the BX-1 Microsatellite is WFOV (Wide Field of View) and a NFOV (Narrow Field of View) camera.


The Broadband Start of the OneWeb Satellite Constellation is Early 2022.


The Mass of the Cygnus capsule mass simulator Payload is ~3800 kg.


The Full Calibration Mode Frequency of the TRUTHS Satellite is Bi-monthly.


The Location of the Crater Surface Feature is 55º16'51.6"N/106º25'3.4"W.


The Data Quality Assessment of the Landsat-7 ETM+ Satellite is Not provided.


The Hydrazine Capacity of the Propulsion Subsystem Propulsion is Up to 28 kg.


The Mass of the Instrument Spectral Imager is 120 kg.


The Release Date of the HTV-6/Kounotori-6 Cargo Ship is January 23, 2017.


The Pixels per FWHM of the Spectrometer Instrument is 715.


The Next Deployment Test Location of the Copernicus Sentinel-1C Satellite is France.


The Mass of the SEAM Nanosatellite is 4.7 kg.


The Operation Start Date of the MAP-PACE Plasma Analyzer is 14 December 2007.


The Pressure of the Steam Propulsion Unit Propulsion is Atmospheric pressure.


The Agreement Date of the Spire Global Satellite Operator is August 14, 2019.


The Printed Circuit Board Thickness of the Sprite Tiny Spacecraft is A few millimeters.


The Total CO2 Equivalent Mitigated of the GHGSat Company is Over 10 million tons.


The Exposure Time of the Active Regions Imaging Device is < 100 ms.


The LTDN of the LitianicaSAT-2 Nanosatellite is 9:30 hours.


The Power of the Spacecraft bus Satellite is 3.8 kW.


The Pass Prediction Accuracy of the SpinSat Satellite is About three weeks.


The Apogee of the COMPASS-2 Satellite is 494 km.


The Mass of the Tyvak-0171 Minisatellite is 138 kg.


The Number of Nodes of the TacSat-4 SpaceWire Link Communication Link is 2.


The CO2 Relative Accuracy of the GOSAT Satellite is 1%.


The Mass of the SPACE HAUC CubeSat is 4 kg.


The Receiver Function of the SILEX Laser Communication System is Power detection device.


The Measurement Technique of the RISE Instrument is Doppler shift of radio signals.


The Mass of the Myriad RF board RF Board is 50 g.


The Every two days of the Radar Data Interval is At an interval of every two days.


The Uplink Frequency of the Cadet-U UHF radio RF Communication Device is 449.75 MHz.


The Number of the Columbus ESA ISS Science & System Operations Report is 78.


The Deployment Date on Mars of the Seismic Experiment for Interior Structure (SEIS) Seismometer is Late 2018.


The Scheduled Launch Date of the CBERS-3 Satellite is 2012.


The Mission Move Forward Date of the DSCOVR Satellite is 2015.


The Sampling Rates of the FGM Fluxgate Magnetometer is 32 Hz (both sensors active) or 64 Hz (one sensor active).


The Relay Hazard Avoidance Method of the Chang'e-3 lander Lander is Large-scale rough-hazard avoidance, three-dimensional imaging in hovering status, small-scale precise-hazard avoidance of the final landing site.


The Size of the Transmitter Communication Device is 230 mm x 136 mm x 30 mm.


The Spectral Resolution of the EO System Earth Observation System is <8 nm.


The Lightweighting of the PP Twin Telescopes Telescope is Up to 72%.


The Eclipse Period of the QuakeSat Satellite is Current.


The Array Size of the VNIR Detector is 40 x 640.


The Landing of the OMOTENASHI Satellite is On the moon.


The Components of the FDIR System Failure Detection, Isolation and Recovery System is On-ground system, Automation system, MOIS Event Monitor.


The Brightness of Star at High Noon of the Kepler-186f Exoplanet is As bright as our sun appears to us about an hour before sunset.


The End of Life Date of the LADEE Satellite is April 18, 2014.


The Workshop Date of the Peregrine Satellite is April 18-20, 2012.


The Orbit Inclination of the HY-2B Satellite is 99.3º.


The Detection Target of the SVOM Attitude Satellite Attitude is GRB on the night side.


The Dwell Time of the IRS Sounder Satellite is About 9 seconds.


The Global Wind Field Measurement of the Atmospheric Dynamics Mission Satellite Mission is True.


The Launch Date of the VRSS-1 Satellite is Sept. 29, 2012.


The Spectral Channels of the SEVIRI Spectral Imager is 12.


The Mass of the SEIS Instrument Seismometer is 29.5 kg.


The Spectral Channels of the Resurs-P1 Imaging Satellite is Seven.


The Activation Date of the LAXPCs X-ray Proportional Counters is October 2015.


The Noctilucent Cloud Observation Locations of the AIM Satellite is Arctic, Antarctica, Utah, Colorado.


The Function of the IBS LR Launch Restraint is Act as a load bypass mechanism for the bearings contained within the SMA and provide a direct load path for the supported mass into the spacecraft interface.


The Spectral Range of the ELVIS Spectrometer is 200-650 nm.


The Resolving Power of the Atmospheric Chemistry Suite Spectrometer is 10,000 or more.


The Cold Start Time of the DORIS Receiver is Less than 1 orbit.


The Process Management of the FreeRTOS Real-time Operating System is Separation of a program in several processes, managing the assignment of processor internal resources like processor time and memory to the various processes.


The Orbit Type of the Odin Satellite is Sun-synchronous polar orbit.


The Wavefront Error of the Sentinel-4 GRU Grating Reflection Unit is 6.0 nm (rms).


The Paraxial Focal Length (mm) of the FCI-TA Instrument is 1650.


The Components of the Spacecraft Plug-n-Play Avionics (SPA) Standards is Electronic datasheet.


The Yaw Maneuvers Frequency of the ERBE Instrument is Approximately every 36 days.


The Functionality of the HISats Nanosatellites is Independent and fully functional with their own propulsion, power, navigation, data processing, communications and payload accommodations.


The Altitude Range of the Air Density Measurement Device Instrument is ~200 km.


The Jupiter's Day of the Juno Spacecraft is About 10 hours.


The Location of the Ganges Delta River Delta is Bangladesh and the State of West Bengal in India.


The Sample Collection of the Chang'e-5 Lunar Mission is Younger than those brought back last century by the Apollo missions.


The Orbit Direction of the Space Station Satellite is From west to east.


The Number of Optical Elements of the Grating Wheel Assembly Optical Assembly is 8.


The Purpose of the Beesat-5,-6,-7,-8 smallsats Satellite is Unknown.


The Bandwidth (GHz) of the ICI-10 Radiometer is 2.4.


The Altitude of the Main Payload Satellite is ~661 km.


The Launch Mass of the ACTS/TOS Communication Technology Satellite is 2800 kg.


The Mission Status of the IRS-P6 Satellite is Mission Complete.


The Volume of the Lake Atatürk Dam Reservoir is 48.7 km3.


The Dynamic Range (Infrared Channel) of the VIRR Instrument is 180-330 K (scene temperature).


The Number of Antennas of the Heinrich Hertz Satellite is 8.


The Objective of the DCS Data Collection System is Collect and relay environmental data from unattended land- and ocean-based automatic data collection platforms.


The Emissions Contribution in 2020 of the Sudd wetlands in South Sudan Wetlands is Unknown.


The Connection of the TTC End-to-End Tests Test Type is Hardwired connections to the spacecraft TTC transmitters and the data umbilical will be connected.


The Provider of the Flexible thin-layer solar cells Solar Cells is Solarion GmbH.


The Optical Transmit Power of the Optical link Communication System is 2.2 W.


The Total Mass of the Spacecraft Satellite is 236 kg.


The Number of Bands of the R3 Sensor Sensor is 6.


The LI Optical Head Envelope of the LI Instrument is 718 mm x 1200 mm x 1456 mm.


The Water Loss Date of the Asteroid 162173 Ryugu Asteroid is Unknown.


The Imaging Modes of the TSX-SAR Satellite is Spotlight (SL), Spotlight High Resolution (HS), Experimental Mode.


The Failure Date of the NEOSSat Satellite is Late 2016.


The Mass of the Lens Assembly Lens Assembly is 266 g.


The Orbit Type of the ANUSat Satellite is Near-circular.


The Mass of the KaRIN Instrument is ~294 kg.


The Utilization of the ESP-MACCS Satellite is Quantify atmospheric processes in the upper troposphere and stratosphere.


The PSD Limit Frequency of the Payload Satellite Component is Until 6.5Hz.


The Darkening of the Satellite Communication is Surfaces on the satellite that scatter light or reflect light diffusely.


The Extended Mission End Date of the Van Allen Probes Satellite is June 2019.


The Measurement Depth of the SMAP Satellite is 5 cm.


The Operational Temperature of the Supercapacitor Energy Storage Device is -40°C to +70°C.


The Spectral Range (µm) of the Band 7 Spectral Band is 0.43 - 0.48.


The Calibration/Validation of the WindSat Spaceborne Polarimetric Radiometer is Special Issue (18 papers) on the WindSat Spaceborne Polarimetric Radiometer -Calibration/Validation and Wind Vector Retrieval.


The Launch Site of the CHAMP Satellite is Plesetsk Cosmodrome in Russia.


The Chassis Mass of the Supernova-Beta Satellite is 1.64 kg.


The Device Mass of the Gamma-ray Counter Detector is 260 g / unit.


The URL of the Dellingr Satellite is https://www.nasa.gov/sites/default/files/atoms/files/cuttingedge_-_vol._13_issue_1_-_fall_2016.pdf.


The Type of the Star Tracker Technology Demonstration Payload is Unknown.


The Deployment Camera Verification of the Spacecraft Satellite is Completed.


The Launch Date of the UKube-1 Satellite is July 2014.


The Orbital Period of the XMM-Newton Satellite is Exactly two times the Earth rotation period.


The Timer Interrupt Frequency of the AT91SAM9G20 Microprocessor is 1 millisecond.


The Design of the TEMBOTM EMC Material is Elastic Memory Composite.


The Computer of the ADCS Attitude Determination and Control System is ARM 7 MCU.


The Operation Period of the Rosetta Satellite is August 2014 to September 2016.


The Beacon Detection of the Ground System Communication System is At least one beacon per pass.


The First Stage Flights of the Falcon 9 Rocket is 7.