The Maximum Upper Band Edge of the MS1 (NIR1) Imager is 901 nm.


The End of Mission Date of the CHAMP Satellite is September 19, 2010.


The Conference Presentation of the Solar Orbiter/METIS Coronagraph/Spectrometer is The optimization of the inverted occulter.


The Presentation of the POLO Satellite is http://smsc.cnes.fr/PLEIADES/Fr/PDF/presentation_pleiades.pdf.


The Spectral Range of the LWIR Cameras Camera is 7.5 - 13.5 µm.


The Sources of the Neutrons Radiation is Galactic Cosmic Radiation (GCR), Earth's radiation belt, Solar Particle Events (SPE).


The Time to Fly Beyond Oort Cloud of the Voyager 2 Space Probe is Possibly 30,000 years.


The Range of the Rate gyro Sensor is ±5º/s.


The Calibration Parameters of the SOFIE Instrument is Measurement background and noise, FOV, response linearity, relative spectral response, time response, absolute gain, difference signal gain.


The International Astronautical Congress Date of the VRSS-1 Satellite is Sept. 23-27, 2013.


The GMDSS Service Provider of the Iridium Satellite Communication Provider is Iridium.


The Ground Coverage of the Scanner Assembly Instrument is 96 km.


The Funding Agency of the Microage Experiment is UK Space Agency.


The Uplink Rate of the SGLS Link Communication System is 2 kbit/s.


The Hardware and Software Design of the PDH Payload Data Handling is Exactly the same as OBC.


The Image Capture Date of the CaSSIS Instrument is 22 December 2018.


The Technology of the MARIN Inertial Measuring Unit is Microelectromechanical systems (MEMS).


The Measurement Category of the Badr-B Satellite is Gravity, Magnetic and Geodynamic measurements.


The Mass of the DIWATA-1 Microsatellite is 50kg.


The DT Band of the DTS Data Transmission Subsystem is X-band.


The Hydrazine Quantity of the Hydrazine system Orbit control subsystem is 4.5 kg.


The Quantity of the 12-Port Ethernet switches Network Equipment is 2 units.


The Launch Readiness Capability of the JPSS Joint Polar Satellite System is FY 2015 and FY 2018.


The Energy Range for Ions of the MagEIS Magnetic Electron Ion Spectrometer is 20 keV to 1 MeV.


The SNR of the UV/VIS Spectrometer Spectrometer is >12.


The Preorder Count in India of the Starlink Satellite Internet Service is Over 5,000.


The Explosion Frequency of the Massive Star Star Type is About every fifty years.


The Per spacecraft mass of the  WorldView Legion Satellite System is 750kg.


The Purpose of the SMAP Satellite is Provide information on water availability and environmental stress for estimating plant productivity and potential yield.


The Frequency Stability of the Receiver Communication System is ±1 x10 -9 dB.


The Affiliated Organizations of the MANTIS Earth Observation Satellite is ESA, UK Space Agency, Open Cosmos, Satlantis, Terrabotics.


The Energy Comparison of the Lightning Natural Phenomenon is 1 bolt of ordinary lightning = enough energy to charge 20 electric cars.


The Science Control Location of the Chandra X-ray Center Center is Cambridge, Massachusetts.


The Objective of the Sentinel-1 Satellite is Assure C-band SAR data continuity for the user community currently provided by Envisat and ERS-2.


The NDVI Map Spatial Resolution of the Landsat-8 Satellite is Unknown.


The MTF of the Instrument Spectrometer is > 0.2 @ Nyquist frequency.


The Bandwidth of the A/D converter Data Converter is 500 MHz.


The Services of the Hellas Sat 3 Satellite is Direct-to-home (DTH) TV broadcast and telecommunications services, distribution of high-definition (HD) and ultra-high definition (UHD) video content.


The Communication Link Speed of the GEO LCT Laser Communication Terminal is 2.8 Gbit/s.


The Mission Type of the MetOp Second Generation Satellite is Weather forecast and climate monitoring.


The Imaging Improvement of the Nanosatellite System Satellite System is Better imagery at lower cost.


The Data Rate of the DORIS Instrument is 4 kbit/s.


The Face sheets thickness of the Bus structure Satellite Structure is t = 0.8 mm.


The Mission Objectives of the SAR-RCM Synthetic Aperture Radar is Monitoring of glacier cover, motion and topography, ice sheet and land surface topography, and sea-ice cover and type.


The Deployment Method of the SEDS Tether Experiment Demonstration Program is Deployer system.


The End of Operations of the SPOT-1 Satellite is November 2003.


The Orbital Plane of the Sentinel-1A and Sentinel-1B Satellites is Same.


The Expected Service Start of the Konnect Satellite is Fall.


The Altitude of the Resurs-P1 Satellite is 475 km.


The Duration of the NSSL Phase 2 Launch Program is 2022 until 2027.


The Image Size of the SIR-C Phased Array is 100 km (azimuth, flight direction) x 50 km (swath).


The Configuration Change of the NIRISS Near-Infrared Slitless Spectrometer is Summer of 2011.


The Center Frequency of the CSG-SAR Synthetic Aperture Radar is 9.6 GHz.


The Connection Check Date of the MetOp-C Satellite is 4 October 2018.


The Function of the RFGeo Product is Identifies and geolocates RF signals.


The Position of the Electric Field Antennas Sensor is Extends beyond the TPS.


The Observation Date of the ENVISAT satellite Satellite is 2006.


The Energy Range of the RHESSI Satellite is 3 keV - 17 MeV.


The Volume Comparison of the MiniCOR Coronagraph is ~10 smaller volume than LASCO C3.


The Target of the Hera Satellite is Didymos.


The Revisit Rate of the Planet SkySats Satellite is As high as 10 times per day.


The Software Load Location of the NigeriaSat-2 Satellite is On-Board Computer.


The Installation Time of the DESIS Instrument is One day.


The Number of Detectors of the SBUV Spectrometer is 3.


The Operation Period of the S-193 Radar System is Over 600 days.


The Applications of the SAR Satellites Satellite is Defense and intelligence, supply chain, insurance, maritime.


The Orbit Inclination of the GF-3 Satellite Satellite is 98.41º.


The Technique Developers of the Solar Flare Solar Event is Charles Lindsey and Douglas Braun.


The Application of the Compact off-axis telescope Telescope is Satellite-borne instrument for atmospheric research.


The Calibration of the HY-2A Satellite Satellite is Unknown.


The Additional Capability of the SMOS Satellite is Map the thickness of ice floating in the polar seas.


The Spectral Range of the HySI Hyperspectral Imager is 400-950 nm (VNIR).


The Number of Paths of the Payload Hosting Paths Satellite is Two.


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


The DC electric field measurement of the Geotail spacecraft Spacecraft is Unknown.


The URL of the SPOT 6 Satellite is http://www.astrium-geo.com/files/pmedia/edited/r18072_9_spot_6_technical_sheet.pdf.


The Mission Status of the OSIRISv3 System is Unknown.


The Design of the Antenna array Antenna is Adaptive nulling design, 4 elements, f c =5 GHz.


The Detection Capability of the OMI Satellite Instrument is Gas and Oil Facilities Emissions.


The Function of the Baseband Processor Processor is Demodulation, storage and remodulation of LBR (Low Burst Rate) data.


The Total Cost of the Satellogic Satellite Constellation is $20 million in total per year.


The Altitude Error Type of the OMPS Sensor is Rigid vertical shift.


The Presentation Date of the Data Volume Increase Solution Data Communication System is May 4-7, 2009.


The Operating Temperature of the Sensor Gas Sensor is Approximately 660°C.


The Data Collection of the ISS-RapidScat Satellite Instrument is Started on October 6, 2014.


The Memory Module Capacity of the IRIS Satellite is 8 Gbit.


The Planned Launch of the Resurs-P4 Satellite is 2023.


The Argument of Perigee of the Molniya Orbit Orbit is 270°.


The URL of the PROBA-V-CC Satellite is https://space.oscar.wmo.int/satellites/view/proba_v_cc.


The Diameter of the Tianhe Space Station Module is 4.2 meters.


The Rocket Height of the Chang'e-5 Lunar Mission is 57 meters.


The Mission Type of the ArgoMoon CubeSat is EO.


The Cross-track Swath of the Nadir total column spectrometer Spectrometer is 50 km x 2800 km.


The Launch Date of the Orbital ATK Mission Space Station Research is 21 May 2018.


The Mercury Orbit Arrival Date of the BepiColombo Satellite is End of 2025.


The Mass of the M2S Satellite is 848 kg.


The Launch Date of the ExoMars Mission is 2020.


The Mission Purpose of the CryoSat Satellite is Determine the Fluctuations in Earth's Land and Marine Ice Fields.


The Power Capacity of the Bus Satellite Component is 140 W.


The Bands of the GOES Imager Imager is 1 VIS band, 2 MWIR bands, 2 TIR bands.


The Number of Valves of the PROP unit Propulsion System is 6.


The Operational Cadence of the Instrument Satellite Instrument is Stare for ~30 seconds.


The Focal Length of the ART-XC Instrument Telescope is 2700 mm.


The Optical Downlink Rate of the Follow-on Optical Downlink Demonstrators Satellite is Approaching 1 Gbit/s.


The Age of the Ryugu asteroid Asteroid is 100 million years old.


The Formation Ranges of the CanX-4 Satellite is 1000 m, 500 m, 100 m.


The Purpose of the Remote Sensing Satellite Satellite is Remote sensing of terrestrial vegetation fluorescence.


The Launch Date of the Unknown Satellite is Dec. 17, 2015.


The Universal TC/TM system of the BEESAT-3 Satellite is Yes.


The Observation of the FAUST Instrument is Gas trail behind the cloud.


The Dry Mass of the Spacecraft Satellite is 1400 kg.


The Power Draw of the EPS Electrical Power Subsystem is < 50 mW.


The Cloud Brightness Trend of the AIM Satellite is Getting brighter.


The Development Locations of the CPE Communications Payload/Experiment is ITR of UniSA (University of South Australia), Adelaide, CSIRO (Commonwealth Scientific and Industrial Research Organization) Industrial Physics, Sydney, and at UTS (University of Technology), Sydney.


The | of the VIRGO Helioseismology and Solar Irradiance Monitoring Experiment is http://www.ias.u-psud.fr/virgo/.


The FPGA of the PCU Power Control Unit is Actel RTSX32SU-CQ84B.


The Measurement Method of the RISE Instrument is Estimation of the precession and nutation of the spin axis.


The Location of the PDGS Payload Data-processing Ground Segment is DLR in Oberpfaffenhofen.


The Mission Life of the YouthSat Satellite is 2 years.


The Daily Imaging Capacity of the SEOSat Satellite is 2,500,000 km2.


The Constellation Purpose of the Kleos Space S.A. Company is Monitoring global events and key locations of interest.


The Study Duration of the Blue Ring Nebula Nebula is 16 years.


The Delivery Location of the LunaH-Map Spacecraft is NASA's Kennedy Space Center.


The DOI of the NICER Satellite is 10.1117/12.2056811.


The Color of the Optical Elements Components is Light red.


The Reentry Plan of the NPP Satellite is Lower the orbit perigee to approximately 50 km and target any surviving debris for open ocean entry.


The Optical Axis Displacement of the Satellite Imaging Satellite is ±30º in steps of 2º.


The Launch Date of the NanoRacks-QB50 Satellite is April 5, 2017.


The Pixels per FWHM of the Spectrometer Instrument is 1220.


The Purpose of the CO2 Dry Air Mole Fraction Atmospheric Measurement is Integral constraint on the sum of these in the form of a net flux of CO2 to and from the atmosphere at the surface.


The Response to Gravity Wave Activity of the O2 Atmospheric Band airglow and NLC Atmospheric Emissions is Both feature horizontal and vertical structures that are a direct response to gravity wave activity.


The Meeting Date of the Swarm Satellite is April 21, 2017.


The Benefits of the Planet Orbit Partner Program is Access to Planet-certified partners with specific domain expertise.


The Mission Design of the RapidEye Satellite is Acta Astronautica Volume 56, Issues 1-2, January 2005, pp. 213-219.


The Yaw Maneuver Capability of the ADCS Attitude Determination and Control Subsystem is ±90º/180º.


The Observation Data of the CryoSat-2 Satellite is Changes in ice thickness for March/April 2011, 2012 and 2013.


The Launch Mass of the Spacecraft Satellite is 588 kg.


The URL of the VAMOS Verification System is http://elib.dlr.de/84313/1/IFAC2013_VAMOS_03.pdf.


The Orbit Altitude of the SpaceEye-T Satellite is 600 km.


The Zoom Capability of the Zoom-in Camera Camera is Yes.


The Launch Date of the OrbView-1 Satellite is April 1, 1995.


The Mission Date of the FedSat Microsatellite is 1998.


The Solar Array of the Orion Spacecraft is 1242 cells per panel.


The Function of the Herschel Telescope Telescope is Look deep into space by detecting light emitted in the far-infrared and sub-millimeter regions of the spectrum.


The Bus Size of the CubeSat Satellite is 6U.


The Movement of the Earth's Magnetic Field Natural Phenomenon is Up to tens of km every year.


The Measurement Type of the FTS Fourier Transform Spectrometer is Amount of direct sunlight absorbed by atmospheric gases.


The Drift Recovery Phase Duration of the CanX-4&5 Satellite is Several Days.


The Capabilities of the Procyon star tracker Attitude Determination Device is Excellent rate estimates, ‘lost in space' capability.


The Isolation Method of the KaRIn Radar is Offset feed reflectarray antennas.


The Maximum Battery Power Before 100% Depletion of the Satellite Spacecraft is 10 hrs.


The Flight Dynamics of the Retrieval of the Eureca Satellite is Unknown.


The Launch Date of the Satellite EO is Announced on 7 October 2021.


The Mission Duration of the PSAT Satellite is 18 months.


The Mass of the Trailblazer spacecraft Satellite is 83.5 kg.


The Detector Pixel Count of the Telescope Optical Instrument is 2 k x 1 k pixels.


The Communication Status of the UWE-1 Satellite is No communication signals can be received.


The Coordinates of the Tohoku-Kanto earthquake Earthquake is 38.32ºN, 142.37ºE.


The Developer Affiliation of the Kappa Scheme Flare Prediction Method is Institute for Space-Earth Environmental Research, Nagoya University.


The Diameter of the M1 Mirror is 415 mm.


The Platform Weight of the Satellite Vu Satellite is 100 kg.


The Center Frequency (GHz) of the Antenna Reflector is 19.35.


The Function of the APEX CubeSat CubeSat is Perform a multispectral mineral survey of its makeup.


The Additional Camera Resolution of the PROBA-1 Microsatellite is 5 m.


The Unknown of the CFOSat Ground Segment is Unknown.


The Last Update of the Spitzer Satellite is 16 December 2020.


The Mirror Coating of the PAN Camera Imaging Device is Enhanced AlO2coating.


The Altitude Range of the CO2 VMR Measurement Device is 50 - 100 km.


The Dimensions of the DECA Camera is about 9 cm x 9 cm x 9 cm.


The Member of the Andrew Dessler Individual is True.


The Radiometric Stability of the Instrument SAR is ≤ 0.5 dB.


The Illustration of the Drag Augmentation Device Satellite Component is Figure 16.


The Sensors of the iADCS-100 ADCS System is ST-200 star tracker.


The Datasheet Revision of the QubeAIS Software-Defined AIS Receiver is 1.4.


The Image Resolution of the EXI Camera is 12 megapixels.


The Multispectral Resolution of the SuperView 1A and 1B Satellite is 2 m.


The Default Measurement Mode of the SOVAP Instrument is Shuttered open/close sequence of the right channel.


The Mass of the SDS-4 Satellite is ~48 kg.


The Nadir Footprint of the Instrument Spectrometer is 60 x 0.3 arcmin2.


The End of Life Date of the SARAL Satellite is 31 Dec 2023.


The Launch Year of the NEMO-AM Satellite is 2023.


The Landing Site of the Beresheet Spacecraft is Moon.


The 2nd LO of the HRIT HiRID Data Receiver is 1558.


The Temperature of the Cold Focal Plane Imaging Device Component is 91 K.


The Launch Date of the Solar Orbiter Spacecraft is February 10, 2020.


The Commissioning Phase Start Date of the Electro-L Satellite is March 2011.


The URL of the Chandra X-Ray Observatory Satellite is https://arxiv.org/ftp/arxiv/papers/1110/1110.4020.pdf.


The Number of Monitored Stars of the Kepler Space Telescope Space Telescope is More than 150,000.


The Star Magnitude Registration of the Camera System Sensor is 4 and brighter.


The Field of View, vertical of the Instrument Spectrometer is -8 to -32 (20º).


The Spatial Resolution of the MWHS-II Microwave Humidity Sounder is ~15 km diameter at nadir, About 41 km x 27 km at outer edge of swath.


The Minimum Impulse Time of the PROP unit Propulsion System is 40 ms.


The Return to Flight Date of the Vega Launch Vehicle is 3 September 2020.


The In-orbit digital IP routing of the Heinrich Hertz Satellite Technology is Enabled.


The Orbit Shift Distance of the GomX-4B Satellite is Up to 2000 km.


The Launch Date of the OPS-SAT Satellite is 18 December 2019.


The Observation Start Date of the SAGE-II Satellite is 1984.


The Development Tool of the ACS Attitude Control System is Matlab/Simulink.


The Page Numbers of the Very-Wide-Filed Ultraviolet Sky Survey Instrument is 179-180.


The Pixel Resolution of the SPIM3 Spectrometer is 14 bit.


The Mission of the SWOT Satellite is Future Project.


The Article Author of the Magnetospheric Multiscale Mission Satellite is Mara Johnson-Groh.


The Manufacturer of the Satellite Spacecraft is Nanyang Technological University.


The Attitude Control of the ADCS unit Satellite Component is Nutation damping.


The Acceleration of the NigeriaSat-2 Satellite is 0.35°/s2.


The Observation Target of the EUVI Extreme Ultraviolet Imager is Chromosphere and innermost corona.


The URL of the Eutelsat Quantum Satellite is https://news.eutelsat.com/pressreleases/universal-eutelsat-quantum-satellite-to-revolutionise-telecoms-markets-1190652.


The Spectral Bands of the Focal Plane Array Detector is VNIR and SWIR.


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


The Stable Roll Frequency of the GP-B satellite Satellite is 0.081 rad/sec (13 mHz).


The Length of the Pas Moraine Moraine is 300 kilometers (185 miles).


The International Designation of the GFO Satellite is 1998-007A.


The Carbon Source of the Tropical Forests Ecosystem is True.


The Size of the ZACube-2 Satellite is 3U.


The Chirp Signal Bandwidth of the P Mode Observation Mode is 240 MHz.


The Image Processing Chain of the EO-ALERT Satellite System is Payload on-board the satellite, on-board data processing unit, flight-to-ground communications subsystem, ground units for decryption/decompression.


The Energy Range for Si of the LEICA Particle Detector is 0.33 - 5.5 9.6 - 177 21 - 330 54 - 195 MeV/n.


The Deployment Time of the STPSat-6 Satellite is About 6 hours, 30 minutes after launch.


The Centrals of the DRR Data Routing and Retrieval is NOAA/NESDIS (National Environmental Satellite, Data, and Information Service), NCEP (National Centers for Environmental Prediction), AFWA (Air Force Weather Agency), FNMOC (Fleet Numerical Meteorology and Oceanography Center), NavOceano (Naval Oceanograph.


The Leading Noise Terms of the Satellite Spacecraft is Thermal effects.


The Central Wavelength of the Current GOES imager Sensor is 6.19.


The Clues Date of the INTEGRAL Satellite is 14 Nov. 2008.


The Mission Status of the GeoSTAR Geostationary Synthetic Thinned Aperture Radiometer is Expected to be used during the NOAA and Aqua missions.


The Instruments of the NeuSAR Satellite is SAR.


The Maneuverable of the T6 thrusters Ion Thrusters is True.


The Candidate Landing Region of the Chang’e-4 Lunar Lander is 45°S-46°S and 176.4°E-178.8°E.


The Purpose of the STRATOS instrument Instrument is Makes use of GPS occultation measurements to determine temperature, pressure and humidity profiles of Earth's atmosphere for application in operational meteorology.


The Strategic Cooperation Sign Date of the Beijing Space View Company is 5 Dec. 2017.


The Objective of the Unseenlabs' Constellation Satellite Constellation is Create a constellation of 20 to 25 nanosatellites.


The Launch Date of the SARAL Satellite is 2012.


The Modes of the Myriad RF board RF Board is Full duplex.


The Nominal Thrust of the Chemical Propulsion Thrusters Orbit Maintenance is 10 N.


The Software Package of the PRISMA POD Facility is GHOST (GPS High precision Orbit determination Software Tools).


The Function of the Imaging System Camera System is Capture high resolution pictures.


The Deployment Length of the ROSA Solar Array is 8.6 meters.


The Altitude for Extended Mission of the SELENE/Kaguya Satellite is 50 km.


The Detector Type of the Instrument Spectrometer is 2D CCD of 1024 x1024 pixels in VIS; 2D InGaAs detector of 320 x 240 pixels in NIR.


The Imaging Frequency Band of the ALOS-2 Satellite is L.


The Concepts Investigated of the ALBus R&R Design is Piston design, Collet design.


The Sea Level Rise of the Copernicus Sentinel-6 Satellite is 4.8 mm per year.


The Discovery Date of the Chandra X-Ray Observatory Observatory is 31 March 2021.


The Signal Wavelength of the Clementine Satellite is 13.19 cm.


The Publication Date of the Active magnetic attitude control algorithms for a CubeSat for astrophysics research Document is 2014.


The Number of Pixels of the Band 5 Spectral Band is 800.


The Mass of the VENµS Satellite is 264 kg.


The Spotlight (SL) Spectral Resolution of the TSX-SAR Satellite is 2m.


The Data Transmission of the CSSS Canadian Space Surveillance System is JSpOC (Joint Space Operations Center).


The Affiliation of the SwissCube Satellite is EPFL (Ecole Polytechnique Federale de Lausanne).


The 2021 Fires of the U.S. Drought Monitor Report is 672.


The Mass of the CIVA Analyzer is 3.4 kg.


The Optical Downlink Rate of the NASA OCSD Satellite is Up to 200 Mbit/s.


The Ground Segment and Distributed Operations Concept of the BRITE-Austria Satellite is Unknown.


The Accomplished ?V Maneuver of the Satellite Spacecraft is 0.15 m/s.


The ESA: 12 eV-12 keV, ISA: 10 eV/ q-12 keV/q of the Energy Range Sensor is Energy range ESA: 12 eV-12 keV, ISA: 10 eV/ q-12 keV/q.


The Temperature Jump of the NIR_AB Antenna Antenna is Self-recovered in a few weeks.


The Solar Panel Orientation of the STRaND-1 nanosatellite Satellite is +Y body direction.


The Instrument Unit Volume of the Solar Orbiter Spacecraft is Tightly controlled.


The Electric Antennas Length of the ISEE-3 Satellite is 0.6 and 45 m.


The Data Quantization of the CSG-SAR Synthetic Aperture Radar is 10 bit.


The Outlived Design Lifetime of the ERBE Instrument is Factor of 5.


The Spectral Range of the UV-2 Spectrometer is 306 - 380 nm.


The Launch Date of the HTV-9 Cargo Transfer Spacecraft is 20 May 2020.


The Operation Strategy of the SLIM6 Satellite is Maximum imaging time in the sunlit phase of the orbit.


The Detection of the InSight Spacecraft is Thousands of passing whirlwinds.


The Strongest Winds of the Nor'easter Weather System is 78 miles per hour.


The Spectrum Comparison of the Vibration Testing Test Type is GSFC-7000 standard random vibration spectrum that is commonly used for CubeSats and the in-house SSTL Spectrum C random vibration spectrum.


The Description of the Orthorectified and Atmospheric Corrected Product (L1A) Data Product is The product is derived from the LevelC product, atmospherically corrected and the data converted to ground surface reflectance values.


The Drag Sails of the CanX-7 Satellite is 4.


The URL of the Space-based ADS-B Surveillance System is http://www.icao.int/Meetings/anconf12/WorkingPapers/ANConfWP141.1.1.ENonly.pdf.


The Earth Observation Precision of the ADCS Attitude Determination and Control Subsystem is Sub-degree.


The Symposium Date of the European Student Earth Orbiter Satellite is May 26-30, 2014.


The Expected Completion Date of the Europa Clipper Spacecraft is End of 2022.


The Remaining Propellant of the Advanced Composition Explorer Spacecraft is Approximately 46 kg.


The Sunlight Power Conversion Efficiency of the SBVR Power Supply is 98%.


The Aperture Area of the IBEX-Lo sensor Sensor is Fourth of the aperture area for IBEX-Lo.


The Spatial Co-registration of Spectral Bands of the Hyperion Imaging Spectrometer is < 20% of pixel.


The Maximum In-Storage Period of the MWI Instrument Instrument is 19 years.


The Measurements of the SAGE-III Satellite is Vertical distribution of aerosols and ozone, temperature in the stratosphere and mesosphere, profiles of trace gases such as water vapor and nitrogen dioxide.


The Scan Step Increment of the Visible Spectral Band Spectral Band is 140 µrad (N-S scanning).


The Form Factor of the MicroMAS Nanosatellite is 3U CubeSat.


The Material of the Propulsion System Satellite Component is Plastic.


The Presentation Date of the CHEOPS Satellite is April 20-24, 2015.


The Color of the Optomechanics Mechanical Component is Blue.


The Modulation of the Ranging Tones Signal is Onto the downlink.


The Operational Status of the OFEQ-3 Satellite is Operational as of 2002.


The Function of the EIS (Extreme Ultraviolet Imaging Spectrometer) Instrument is Scanned the active region, breaking the light into spectral lines used to identify specific elements.


The Glare Impact of the ISS-LIS Instrument is Will not impact ISS-LIS.


The Vertical Resolution (Troposphere) of the Aeolus Satellite is 1.0 km.


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


The Directional Impact Proportion of the Solar-cell cover glasses Component is About 30%.


The Orbit Altitude of the EAGLE Secondary Payload is 39,000 km.


The Launch Date of the CryoSat Satellite is 08 Oct 2005.


The Target Tracking Capability of the BILSAT-1 Satellite is Yes.


The Spectral Range of the SIM Solar Irradiation Monitor is 0.2~50 µm.


The Angle of Incidence of the Stripmap Imaging Mode is 20° - 50°.


The Microcontroller of the AIM Reconfigurable Computing Hardware Device is Intel 80C196 architecture.


The Field of View Directions of the CIRiS Infrared Imaging System is Four orthogonal directions.


The Average Power Consumption (Observation Mode) of the COMIS Satellite is 14 W.


The Map Date of the CryoSat-2 Satellite is Dec. 15, 2014.


The Required Power at EOL of the KOMPSAT-6 Satellite is 2,250 W.


The Operation Start Date of the Metcomp experiment Materials Science Experiment is 3 December.


The Last Operation Date of the Envisat Satellite is Nov. 2, 2010.


The Torque Provider of the Permanent Magnets Attitude Control is Small amount.


The Swath width of the Optical System Imaging System is 2000 km.


The Design and Implementation Date of the Argo Ocean Observing System is 1998.


The Symposium Date of the Geosat Follow-On Satellite is March 13-18, 2006.


The External Configurations of the GomX-4 Satellite is Antennas, sensors, solar panels, radiation shields and radiative surfaces.


The Data Rate of the AATSR Instrument is 625 kbit/s.


The In Orbit Commissioning (IOC) Start Date of the CHEOPS Satellite is 7th January.


The Instrument Type of the DMC-3 Satellite Constellation is High resolution optical imagers.


The Threshold of the Low LET Detector Detector is 0.2 MeV.


The Non-Polarized Channels of the VNIR Sensor is 11.


The Size of the STARLETTE and Stella Satellites is 24 cm in diameter.


The Mission Lead of the TEMPEST-D Satellite is Colorado State University.


The Design of the OMPS UV Hyperspectral Imaging Spectrometer is Limb- and nadir-viewing.


The Cross-Track Swath of the Nadir Sensor Wide-Field Telescope Sensor is 2800 km.


The Presentation Date of the PAZ and TerraSAR-X Satellite Constellation is Sept. 23-27, 2013.


The Storage Capacity of the GOES-R Access System Data Distribution System is Seven days.


The Function of the ISSAC SOC Space Operations Center is Uplink image acquisition and other ISSAC operational commands to the ISSAC payload software.


The Project Contributor of the MIMOSA Satellite is Ladislav Sehnal.


The Resolution of the Spotlight-2A Satellite is 0.8m.


The Temperature Resolution of the AMSU-A Instrument is 0.25 - 1.2 K.


The Satellite Mass of the Kleos S.A. Company is 8 kg.


The Size of the HyperScout Satellite Instrument is Milk-carton-sized.


The Subsystems of the Ground Station Ground Station is Monitor and Control, Atmospheric Monitoring Instruments, Laser Safety Systems.


The Travel Distance of the Envisat Satellite is 2.25 billion km.


The Battery Design of the TacSat-4 Satellite is Rapid, in the field replacement without spacecraft disassembly.


The Temperature Difference of the Hot and Cold Target Calibration Components is 50-60 K.


The Period of the Satellite Imaging Satellite is 98 min.


The Mission Type of the Etalon Satellite is Solid Earth Studies.


The RF Communications of the Spacecraft Satellite is 2 MByte (typical).


The Reflector Dimension of the Antenna System Communication System is 60 cm.


The Orbital Operations Duration of the CubeRRT Satellite is ~1 year.


The Maximum Azimuth Slewing Rate of the OCTL Telescope is 20º/s.


The Spectral Resolution of the CHIPS Spectrometer is Near 170 Å.


The Upgradable Speed of the Iridium Certus Satellite Communication Service is 704 kbit/s.


The Date of the Dnepr-1 Satellite Launch is April 18, 2007.


The Pixel Array Pitch of the MWIR Imager Imaging Device is 8 μm.


The Initial Scheduled Launch Date of the OFT-2 Uncrewed Test Flight is July 30.


The Tracking System of the DORIS Receiver is CNES.


The Spectral Range of the GOME-2 Spectrometer is 240-790 nm.


The Manufacturer of the SEVIRI Imager is EADS Astrium SAS, France.


The Solar Cells Quantity of the H3 and H4 Spacecraft is 140 cells.


The Size of the Comets Celestial Bodies is Roughly 5 km.


The Planned Launch Date of the SAOCOM-2A Satellite is 2025.


The Landing Date of the Starliner Spacecraft is December 22, 2019.


The Dimensions of the TUBSAT-N Satellite is 320 mm x 320 mm x 104 mm.


The Ground Resolution (Visible Channel) of the VIRR Instrument is 2.3 km.


The Orbit Determination Frequency of the ASNARO Ground Segment Ground Station is Twice per day.


The Altitude of the STPSat-3 Satellite is 500 km.


The Energy Range of the ART-XC Instrument Telescope is 5 to 30 keV.


The Testing Date of the BepiColombo Antenna Pointing Mechanism Antenna Pointing Mechanism is 23–25 September 2015.


The Launch Mass of the Satellite Spacecraft is 3100 kg.


The Quantity of the Impact Craters Surface Feature is 77.


The Funding of the Hiber BV Satellite and Communications Start-up is €26 million.


The Heat Source of the Laser Diode Optical Unit Component is Significant.


The Purpose of the Bragg-crystal telescope-spectrometer Mg1 and Mg2 Telescope-spectrometer is Imaging hot plasma (T ~ 10 MK) of the solar corona.


The Image Resolution of the RISING-2 Satellite is ~5m.


The Service Impact of the Lacuna Space Company is Monitor peatland restoration impact.


The MZ-Surface Function of the H3 and H4 Spacecraft is Faces to the sun.


The Components of the NLS-1 Launch System is CanX-1, AAUSat, DTUSat, XI, CUTE-I.


The Swath of the CAVIS Imager is Slightly wider than main instrument.


The Power of the Propulsion Satellite Subsystem is 0.53 W.


The SNR of the ALOS-3/PRISM-2 Satellite is >200.


The Image Resolution of the ExoMars TGO Trace Gas Orbiter is 460 km/pixel.


The Modulator Module of the Transmitter Communication Device is Xilinx Virtex-5 SX FPGA.


The Quantity of the CINEMA nanosatellite Satellite is 3.


The Measurement Range - Plasma Density of the ISL Instrument Langmuir Probe is 100 to 5 x 10^6 particles/cm3.


The Operation Mode of the LEDs Light Source is Pulse mode at higher currents.


The Sampling Frequency of the Precipitation Data Data is Every half hour.


The Observation Period of the Spitzer Space Telescope is 2015-2019.


The Expected Electrical Power Levels of the GSE Power Supplies Power Supply is Not provided.


The Launch Mass: 1670 kg of the Spacecraft Mass is Over half the launch mass of the entire spacecraft, about 1670 kg.


The User of the Canadarm2 Robotic Arm is NASA astronaut Megan McArthur.


The Symposium Date of the Universat-Tatyana-2 Small Spacecraft is Sept. 21-24, 2010.


The Locking Performance of the Rb Spectroscopy Unit Spectroscopy Unit is Stayed locked during vertical accelerations reaching 12.5 g.


The 1.4 kg/sensor head (including HVPS and preamplifier) of the Instrument Mass Sensor is Instrument mass 1.4 kg/sensor head (including HVPS and preamplifier).


The Number of TRMs of the CSG-SAR Synthetic Aperture Radar is 1280 @ H polarization and 1280 @ V polarization.


The Useful Data Bits of the MEV Electronics Module is 10.


The Non-Group Comet Sightings Frequency of the SOHO Satellite is A few times a year.


The Bandwidth of the Band 3 Spectral Band is 480-500 nm.


The Sensor of the TanDEM-X Satellite is SAR sensors.


The Impact on Mission Planning of the GOCE Satellite is Weekly replanning activity required.


The Downlink Data Rate of the RF Communication System Communication System is 1.2 kbit/s.


The Phase Difference Adjustment Method of the SJ-9A and SJ-9B Satellites is Adjusting the orbit semi-major axis and changing the phase relative drift ratio.


The Function of the GSD Ground Systems Division is Provide expertise in satellite ground systems design.


The Components of the Wolf-Rayet bubble Nebula is Blue, Yellow-Green, Red.


The Proton Energy Resolution of the REPT Instrument is 30%.


The Operator of the ICON Satellite is UCB/SSL (Space Sciences Laboratory).


The Launch Date of the XMM-Newton X-ray Satellite is End of 1999.


The Formation Mechanism of the Ozone Layer Atmospheric Layer is Photodissociation of stratospheric molecular oxygen by solar middle and far ultraviolet radiation.


The TRL Level of the RadSat Satellite is 9.


The Mission End Date of the CryoSat Satellite is Unknown.


The Range of the Angular Rate Sensor is ±200º/s(3-axis).


The Modes of the VLF Experiment Scientific Experiment is Slow, Fast.


The Developer of the CO2M Monitoring and Verification Support Capacity System is ECMWF (European Centre for Medium-Range Weather Forecasts).


The Landing Site Name of the Chang'e-4 Probe is Statio Tianhe.


The TRL Level of the Computer System Payload is 5.


The Business Focus of the Lacuna Space Satellite Company is IoT (Internet of Things).


The Modes of the Satellite Operation Modes is Open-loop, Interactive mode, Closed-loop, Automatic target pointing.


The Antenna Type of the ADS Antenna Deployment System is VHF/UHF.


The Checkpoint Rehearsal Duration of the OSIRIS-REx Spacecraft is Four hours.


The Docking Date of the Tianzhou-3 Spacecraft is 20 September 2021.


The Developer of the NewMag Magnetometer Experiment is University of Newcastle.


The Quantity of the LAXPCs X-ray Proportional Counters is 3.


The Formation Maintenance of the TanDEM-X and TerraSAR-X Satellites is 3 months.


The Image Quality of the CartoSat-2B Satellite is High.


The Establishment Date of the GMES Bureau is 2006.


The Project Scientist Affiliation of the Parker Solar Probe Spacecraft is Johns Hopkins University Applied Physics Laboratory.


The Struggle Duration of the New Horizons Spacecraft is 17 years.


The Apogee Alignment of the MMS Satellite is Opposing.


The Spatial Resolution of the Oceanography Short scale Satellite is 100 km.


The Mission Approval Year of the Aditya-L1 Satellite is 2015.


The Components of the TT Telescope Tube is Upper and lower tubes, VOD, OGB.


The Eclipse Observation Date of the PROBA-2 Satellite is Sept. 14, 2015.


The Maximum Optical Path Difference of the Michelson Interferometer Interferometer is ±0.8 cm.


The GPS L1 Complementary Signal Improvement of the QZS-1 Satellite is Approximately 1.7 to 2.5 times.


The Band 4 of the Landsat TM Satellite is Biomass surveys, water body delineation.


The Orbit Altitude of the SeaHawk-1 CubeSat is ~590 km.


The Launch Date of the AAUSAT3 Satellite is 25. February 2013.


The Configuration of the Lithium-ion batteries Battery is 3 parallel cells.


The Public Beta Test Plan of the Starlink Satellite Constellation is Before the end of the year.


The Dust Production of the McNaught Comet is High.


The Size of the Spacecraft Satellite is 100 mm x 100 mm x 243 mm.


The Sequence Steps of the AVGS Laser System is Image 1 is taken at 808 nm, Image 2 is taken at 850 nm, A threshold is taken of the differential image, A centroid is found for each spot in the image, Tracking windows are established, Position (azimuth/elevation and range); attitude (roll, pitch, yaw).


The Developer of the Aalto-1 Nanosatellite is Aalto University.


The Mission Type of the MTSAT Satellite is EO.


The Observation Time of the IRIS Observatory is Eight months per year.


The Interface of the ASIM Payload is CEPA.


The Uplink Data Rate of the RF Communications Communication System is 2 kbit/s.


The Image Type of the ICEYE-X2 Satellite is Radar.


The Targeted Regions of the XMM-Newton X-ray Space Observatory is LMC, Hickson Cluster Group 16 (HCG-16), HR 1099.


The Downlink Frequency of the Astrodev Lithium 2 Radio RF Communication Device is 401.3 MHz.


The Location of the EuTEF Payload Facility is Outside of the Columbus laboratory.


The | of the SFL Sun Sensor Sensor is SFL sun sensor.


The Orbit of the DMSP Follow-on program Satellite Program is Early morning (05:30 hours).


The Earth Explorer of the FORUM Mission is Ninth.


The Responsibilities of the ESA Organization is Payload Module, launcher, AIT facilities for spacecraft integration and testing.


The Processor of the OBC Onboard Computer is 80C186+16 MByte, 80C386+64 MByte.


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


The Purpose of the OCO-3 Satellite is Response to growing populations and varying patterns of fossil fuel consumption.


The TT&C Communication Frequency of the SCD-2 Satellite is S-band.


The HPGP Commissioning Date of the SkySat-3 Satellite is August 3, 2016.


The Electron Energy Range of the EPAM Particle Detector is Ee >30 keV.


The Stabilization of the Göktürk-1A Satellite is 3-axis.


The Data Rate Control of the MIU Interface is Based on commands from the FC.


The Amplitude of the daily variation of the horizontal magnetic intensity (ΔH) of the EEJ (Equatorial Electrojet) Phenomenon is 3–5 fold higher than the variation of data from other regions of Earth.


The Altitude of the Anand Satellite is Approximately 510 km.


The Emission Lines of the EUVI Extreme Ultraviolet Imager is Four EUV emission lines between 17.1 and 30.4 nm.


The Microcontroller Type of the Subsystems Satellite Subsystems is FPGA-based.


The Orbit Type of the EQUULEUS Satellite is 1:4 synodic resonant periodic orbit.


The Measurement of the GeoCARB Satellite is Total concentration of carbon dioxide, methane and carbon monoxide in the atmosphere.


The Height of the Instrument Instrument is 140 mm.


The Average Power Generation of the MicroMAS-1 Satellite is 14.5 W in sunlight (12.7 W orbit average) at a 400 km altitude orbit.


The Line-of-Sight Deformation Rate Maps Generation Period of the SAR Synthetic Aperture Radar is One year.


The FOV Motion of the MAHRSI Instrument is 0.01º x 1.13º.


The Conference Presentation of the DoD Space Test Program Satellite Program is Barbara Manganis Braun, Sam Myers Sims, James McLeroy, Ben Brining, "Breaking (Space) Barriers for 50 Years: Past, Present, and Future of the DoD Space Test Program," 31st Annual AIAA/USU Conference on Small Satellite, Logan UT, USA, Aug. 5-10, 2017.


The Effect of the Moonlight Lunar Telecommunications and Navigation Satellite Network is Reducing the design complexity and weight of individual missions.


The Rotation Modes of the AMSR2 Device is Lower (11 rpm), Regular observation mode (40 rpm).


The Instrument Package Power Consumption of the LCROSS Satellite is 27 W.


The Data Quantization of the TeLEOS-1 Imager Imaging Device is 10 bit.


The Mass Resolution of the ELENA Sensor is M/ΔM H and heavy species.


The Quantity of the Solar Cells Power Generation is 64.


The Enclosure Purpose of the CanX-7 Satellite is Converts the uncoiling motion of the tape springs into linear motion of the booms.


The (International) Harmonization of the CSK GS Ground Segment is Verify and harmonize the Service Request lists coming from the different Partners.


The Pointing Requirements of the AOCS Attitude and Orbit Control System is 2º about all axes.


The Launch Date of the Sentinel-3A Satellite is 2013.


The Color Filters of the LORRI Imaging Instrument is No.


The Launch Date of the ANGELS Satellite is 18 December 2019.


The Function of the BEESAT-4 CubeSat is Gather precise position and orbit determination information, as well as take series of photographs and individual images of Earth's surface with a special camera to confirm the position of the satellite.


The Mission Selection Criteria of the TacSat-3 Satellite is Specific capabilities to meet user needs.


The Detector Elements of the SEVIRI Spectral Imager is 3.


The Extended Mission Objective of the New Horizons Spacecraft is Study the Kuiper Belt environment, observe numerous Kuiper Belt Objects (KBOs) and Centaurs, make the first close flyby of the KBO 486958 2014 MU69.


The Launch Date of the OCO-3 Instrument is May 1, 2019.


The Image Credit of the Copernicus Sentinel-3 Satellite is ESA.


The Purpose of the MONTE Software is Deep space navigation.


The Published Online Date of the Hitomi Satellite is 13 November 2017.


The Detector Array of the SWIR Spectrometer Spectrometer is 160 x 250 channels.


The Potential Difference of the DSLP Data Acquisition System is A few tenths of Volts.


The Content of the Dataset Data is Location and crown diameter of trees in western Africa.


The Operating Phases of the NMS Neutral Mass Spectrometer is Perigee and near-perigee.


The Symposium Date of the Small Satellite Hyperspectral Mission Satellite is Sept. 20-24, 2004.


The Symposium Presentation Date of the Centralized Computation Service Architecture Computation Service Architecture is April 4-8, 2005.


The Objective of the SOSP Satellite is Study of solar physics and solar-terrestrial relationships in aeronomy and climatology.


The Brigthness Temperature (BT) Sensitivity of the Antenna Reflector is ±0.43 K.


The Modulation Type of the Low-rate Modulation Communication System is 9 kbit/s residual carrier PM.


The Launch Vehicle of the Deployment Systems Satellite is Dnepr-1.


The High-Energy Laser Transmitter Range of the OLA LIDAR Instrument is 1–7.5 km.


The Deceleration of the OMS-E engine Engine is 0.3 g.


The Coolant Supply Duration of the Herschel Space Observatory is More than three years.


The Number of Satellites of the Transport Layer Tranche 1 Satellite Network is 42.


The Cooling Temperature of the IRFPA Infrared Focal Plane Array is 70 K.


The Thruster Firing Duration of the Schiaparelli module Spacecraft is 3 sec.


The Resolution of the GOME-2 Spectrometer is 0.22-0.50 nm.


The Distance to Ingenuity Mars Helicopter of the InSight Mars Lander is Roughly 2,145 miles (3,452 km).


The Data Collection of the Copernicus Sentinel-5P Satellite is Nitrogen dioxide concentrations.


The Drive Signal of the Fast-Steering Mirror Device is Sinusoidal voltage signal.


The Manufacturer of the X-band transponder Transponder is Lockheed Martin.


The Sensor Quantity of the MAGIC Magnetometer is 2.


The Operating Modes of the iADCS100 Attitude Determination and Control System is Tracking mode.


The Specific Impulse of the CNAPS Propulsion System is 40 s.


The Primary Science Mission Duration of the Philae Lander is Nearly 57 hours.


The Number of Pixels of the MWHS-II Microwave Humidity Sounder is 98/scan.


The Collision Avoidance Maneuver Date of the PRISMA Satellites Satellite is July 7, 2010.


The Payload of the Irazú CubeSat Satellite is Secondary OBC which acts as an IMU.


The Material of the Reflection Diffuser Calibration Device is Spectralon.


The Concept Type of the PAZ-TerraSAR Constellation Satellite Constellation is Coordinated Constellation Concept (CCC).


The Energy Range of the Natalya-2M High energy radiation spectrometer is 0.3 to 2 GeV.


The CDR Date of the GCOM-W1 Satellite is December 2009.


The Off-nadir Angle of the Cartosat-2E Satellite is Up to 45°.


The Mass of the MuREM Radiation Monitor is < 1 kg.


The Energy Comparison of the Transient Luminous Event Natural Phenomenon is Energy produced by a transient luminous event would be enough to charge more than 800 vehicles.


The Launch Date of the STPSat-3 iMESA Technology is Nov. 2013.


The Function of the Pelican Satellites Satellite is Distinguish road markings on the ground.


The Launch Date of the ECOSTRESS ECOsystem Spaceborne Thermal Radiometer is June 2018.


The Quad-stack of the Satellite Bus Configuration is True.


The Event Name of the IceCube Neutrino Observatory Neutrino Detector is IceCube-170922A.


The Thermal Design of the Instrument Equipment Satellite Component is Classical thermal environment.


The Arrival Date of the ExoMars Mission is June 2023.


The Perihelion Distance of the Comet 67P/C-G Comet is 1.24 au.


The Precession Cycle of the Megha-Tropiques Satellite is Clearly seen.


The Death Year of the Max Valier Person is 1930.


The Function of the Micro-propulsion thrusters Attitude Control is Control the spin and precession motion of the spacecraft.


The Mission Extension of the WIND Satellite is 10 years.


The Processor Speed of the Spacecraft Satellite is 12 MHz.


The Laser Production Date of the GEDI Lidar is April 19-20, 2016.


The Arrival Date of the Docking Module Space Station Module is 26 November 2021.


The Flash Memory of the OBC On Board Computer is 256 MB.


The Energy Range for Fe of the LEICA Particle Detector is 0.21 - 3.1 11 - 90 27 - 450 70 - 270 MeV/n.


The Freezing Level Height of the GPM Satellite is Above 3 km.


The Ground Segment Elements of the SAMPEX Satellite is Ground stations, POCC, PACOR, UMSOC.


The Application of the SDR Software Defined Radio is Space applications.


The Altimetry of the Geosat Satellite is W. H. F. Smith, D. T. Sandwell.


The FOV of the Optics and detector assembly Assembly is ±0.25º.


The Mass of the Tianwen-1 Probe is 5 tons.


The Modulation Transfer Function of the MTF Spectrometer is ≥ 15% (@Nyquist frequency).


The Visibility of the Transient Luminous Events Atmospheric Phenomena is Rarely seen from the ground.


The Objective of the Landsat Next Satellite Constellation is Extend the ability to detect and quantitatively characterise changes on the global land surface.


The Viewing Geometry of the MRO Mars Reconnaissance Orbiter is West.


The Presentation Date of the TanDEM-X Satellite is July 23–28, 2017.


The Mission Status of the OSIRIS-REx Spacecraft is Ready for Touchdown on Asteroid Bennu.


The Orbital Inclination of the IceCube Satellite is 51.6°.


The Orbit (Revisit Time) of the Spacecraft Satellite is 14 days.


The Contact with Asteroid Surface of the MASCOT Lander is Approximately 20 minutes after separation.


The Launch Date of the RadSat Satellite is 2018.


The Impact Speed of the DART Space Probe is 6.6 km/s.


The Components of the Descent Subsystem Subsystem is Supersonic pilot, supersonic ribbon drogue, subsonic ribbon drogue, ringsail main parachute, mortar, strap-cutters.


The Frequency in Inertial Mode of the FEP Satellite Device is 1.7 x 10-4 Hz.


The Resonance Survey Requirement of the SERB Nanosatellite Satellite is First global mode > 250 Hz.


The Fluxgate Magnetometer Mass of the Microsatellite Satellite is 3.6 kg.


The Spatial resolution at nadir of the MWHS Microwave Humidity Sounder is 15 km.


The Operator of the SEOSat Satellite is Unknown.


The Service Area of the Bartolomeo External Payload Hosting Facility is Low Earth Orbit.


The Manufacturer of the DSP satellites Satellite is DFHSat (DFH Satellite Co. Ltd.).


The Operation Period of the IMA Mass Spectrometer is Limited to several hours/day.


The Field of View of the LWIR Camera Camera is 1º x 1º.


The Capacity of the OBR Onboard Recorder is 256 Gbit.


The owner of the Insight lander lander is NASA.


The Program URL of the DRACO System is [DRACO Program URL](https://www.darpa.mil/program/demonstration-rocket-for-agile-cislunar-operations).


The Potential Damage of the Geomagnetic Storm Space Weather Event is Collapse the whole telegraph system in North America and Europe.


The Relation to Sentinel-4A of the Sentinel-4B Satellite is Follow up satellite.


The Type of the PMDs Polarization Measurement Device is Identical.


The Cadence of the MEGS Spectrograph is 10 seconds.


The Image Resolution of the PMC Camera is 10 m.


The Thruster Temperature of the BepiColombo Spacecraft is Minus 150 C.


The Achievable of the Pointing Accuracies Attitude Control System is < 1arcsec.


The Purpose of the MANTIS Earth Observation Satellite is Monitor climate change, map the environment, forecast the weather, find new resources.


The Sample Rate of the Acceleration Sensor is 125 Hz.


The Lunar Eclipse Survival Plan of the Spacecraft Satellite is Developed baseline spacecraft configuration to use prior to and during the lunar eclipse.


The Components of the Bus Structure Satellite Structure is Metallic cube (aluminum panels), four motherboards.


The SAR Antenna Length of the StriX-α SAR Satellite is 5 m.


The Frequency of the RF communication subsystem Communication is 437 MHz (UHF), in uplink and downlink.


The Operating Frequency of the C&DH Subsystem Subsystem is 8 MHz.


The Operating Temperature of the OHIS Imaging System is 90 K.


The Integration Date of the SpIRIT Satellite is 2022.


The Geolocation and Ortho-rectification Methods of the Deimos-2 Satellite is Physical sensor model, RFM (Rational Function Model).


The Signal Modulation of the Signal Generator Subsystem Signal Generation System is Modulated with the relevant subcarriers according to the Galileo Navigation Signal in Space ICD.


The Drill Depth of the Rosalind Franklin Rover is Up to two meters.


The Orbit of the TOMS Instrument is Polar orbit.


The Alternate Name of the Prichal Module Docking Port is Prichal Node Module (UM) or Progress M-UM.


The Lunar Orbit Entry Date of the LRO Orbiter is June 23, 2009.


The Continental Crust Thickness of the Earth Planet is Averages from 35 to 40 kilometers.


The Focal Length of the Telescope Optical Instrument is 5.6 m.


The Launch Vehicle of the Göktürk-1 Satellite is Europe's new Vega small-satellite launch vehicle.


The States of the LCRD Payload Optical Space Terminal is S1 - LCRD Optical Space Terminal initialized but not illuminated by the beacon or uplink beam, S2 - LCRD Optical Space Terminal illuminated by the beacon, S3 - LCRD Optical Space Terminal illuminated by the uplink beam, S4 - LCRD Optical Space Terminal re.


The Effective Focal Length of the Telescope Optical Instrument is 1600 mm.


The Peak Detection Rate of the exact Earth Satellite AIS Receiver is TBD.


The Launch Mass of the CartoSat-2D Satellite is 1378 kg.


The Reflector Dish Diameter of the COMMx Payload is ~3.75 m.


The PSLR of the Instrument SAR is ≤-16 dB.


The Voltage source and the tether of the Negative Tether Charging Mode Test Procedure is The negative mode requires only a voltage source and the tether itself.


The Age of the Magma Ocean Planets Planets is Less than 100 million years old.


The Fly-over Date of the OSIRIS-REx Spacecraft is April 7.


The Mission Life of the TechEdSat-1 Satellite is 7-8 months.


The Field of View of the HXCP Hard X-ray Polarimeter is ±15º.


The Orbital Period of the SZ-7 Spaceship is 91 minutes.


The Band 6 Wavelength of the OCM Payload is From 670 nm to 620 nm.


The Material of the Thermal Isolation Components Satellite Component is Delrin.


The Total Mass of the SMILES Instrument is 475 kg.


The Extended Science Mission Duration of the LRO Satellite is 9/17/2012 - 9/16/2014.


The Interface of the RM Radiation Monitor is CAN bus.


The Propulsion System of the DFACS Attitude Control System is CGPS (Cold Gas Propulsion System).


The Measurement Objective of the ASCAT Instrument is Measure wind speed and direction over the oceans.


The Antenna Type of the UHF Transceiver Transceiver is Quadcanted monopole antenna array.


The Launch Date of the Bartolomeo Payload Platform is June 2, 2016.


The Power Consumption of the UVS Instrument is 1 W.


The Symposium Date of the SWOT Mission Satellite Mission is Sept. 24-29, 2012.


The Pressurized Module Interior Pressure of the JEM/Kibo Japanese Experiment Module is 1 atmosphere (1atm).


The Speed of the CME Coronal Mass Ejection is Between 1.5 and 1.8 million miles an hour (700 and 800 km/s).


The Mission Objective of the FASTRAC Satellite is Perform on-orbit real-time GPS relative navigation between satellites.


The Wavelength of the LIDAR Instrument is 1064 nm.


The Telescopes of the IPDA LIDAR Instrument is Two separate telescopes for the transmission (TX) and reception (RX) of the laser.


The Frequencies of the DORIS Receiver is 2.03625 GHz, 401.25 MHz.


The Function of the SGR-ReSI GNSS Reflectometry Instrument is Collect more data and allow processing on-board.


The Processor Speed of the Safe-mode Computer Computer is 400 MHz.


The Total Capacity of the EUTELSAT KONNECT Satellite is 75 Gbit/s.


The Signal of the FFRF Subsystem Relative Positioning System is GPS C/A navigation signal modulated on two S-band carrier frequencies (S1 and S2) with BPSK/QPSK modulation.


The Mass (kg) of the TecSAR Satellite is 300.


The FOV (Field of View) of the CIPS Instrument is 80º x 120º.


The Purpose of the PME Plasma Measurement Equipment is Studying characteristic macroscopic properties of ionospheric plasmas.


The Design Life of the Terra Satellite is 6 years.


The Zero Doppler Calibration of the Overall System System is Use of Tx leak signal.


The Product of the Climate Change Initiative Program is Maps that provide a global view of above-ground biomass.


The Orbit Altitude of the Tiangong Space Station is About 400 kilometers.


The Geometric Accuracy of the L1C Products Satellite Data is About 15 m (linear Root Mean Square).


The URL of the Galileo Satellite System is http://m.esa.int/spaceinimages/Images/2018/07/Galileo_satellites_viewed_in_smartphone_app.


The Landing Year of the Venera 9 Lander is 1975.


The Cross-Track Resolution of the MLS Spectrometer is 5 km.


The Telescope Type of the GOES Imager Imager is Cassegrain telescope.


The Funding of the IASI Instrument is EUMETSAT.


The IR Detector Cooling of the Instrument Spectrometer is Two-stage passive radiative cooler with retractable earth shield.


The 3-axis stabilization of the BEESAT-2 Satellite is Yes.


The Data Source of the IMERG Algorithm is GPM Core Observatory, GPM Constellation.


The Measurement Domain of the ISS-RapidScat Instrument is Ocean.


The Image of the SEOSAT/Ingenio Satellite is SEOSAT in the cleanroom.


The Purpose of the CRISTAL Satellite Mission is Monitor remote regions from space over long periods of time.


The Location of the IMGEOS Ground Segment Facility is NRSC (National Remote Sensing Center), Shadnagar, Hyderabad Complex.


The Frequency of the TT&R Telemetry, Telecommand & Ranging is Ku-band.


The Investment in OneWeb of the Hughes Company is $50 million.


The Altitude of the OneWeb Satellite Constellation is 1,200 kilometers.


The Power of the FSS Instrument is 0.1 W.


The Purpose of the NICER Mission is Observing X-ray MSPs for navigational purposes.


The Speed Relative to Jupiter of the Juno Spacecraft is Almost 130,000 mph (210,000 km/h).


The Altitude of Final Orbit of the OneWeb Satellites Satellite Manufacturer is 1,200 kilometers.


The Power of the ST (Star Tracker) Instrument is 6.5 W.


The Projected Annual Crewed Missions of the SpaceX Company is Five or six.


The Development Authors of the SpaceCube MINI Satellite is Michael Lin, Tom Flatley, Alessandro Geist, Dave Petrick.


The End Date of the Methane Leak Environmental Event is 26 September.


The Presentation Date of the PRISMA mission Mission is May 29-31, 2013.


The NRT Data Downlink Frequency of the Sentinel-6 Satellite is X-band contact.


The Sun sensors of the ADCS Attitude Determination and Control Subsystem is 6.


The Entrance Aperture Diameter of the Telescope Optical Instrument is 50 mm.


The Function of the DWP Control System is Data compaction and compression, event selection, particle/wave correlation, and control of WHISPER.


The Image Resolution of the PMC Camera is 2.5 m.


The Observation Period of the MOMS-2P Instrument is May 5, 1996 to August 1999.


The Current Orbit of the Galileo FOC satellites Satellite is Elliptical, with an eccentricity of 0.23, a semi major axis of 26,200 km and inclined at 49.8º.


The PI of the SOLSPC Radiometer is G. O. Thuillier.


The Ground Control Location of the SSOT Satellite is Chile.


The Solar Wind Speed of the Solar Wind Satellite Satellite is Speeding up.


The Designers of the Oculus-ASR Satellite is Undergraduate students of MTU (Michigan Technological University).


The URL of the GPM Satellite is http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20110011761_2011012112.pdf.


The Imaging Modes of the KazEOSat-2 Satellite is Agile.


The Proposed Mission of the Aditya-L1 Satellite is Conference on Coupling and Dynamics of the Solar Atmosphere", Pune, India, Nov. 10-14, 2014.


The Launch Date of the SGR-ReSI receiver Satellite Receiver is Q4 2016.


The Development Partners of the ZACube-2 Satellite is CPUT, French South African Institute of Technology, South African Council for Scientific and Industrial Research (CSIR).


The Launch Year of the AMSU Microwave Radiometer is 1998.


The Polarization of the High Resolution Spotlight Imaging Mode is Single or dual.


The Luminosity of the Eta Carinae Stellar System is One of the most luminous and massive stellar systems in our galaxy.


The On-Orbit Operations of the LS-7 Satellite is 11 years.


The Transmit-Mode Duty Cycle of the RainCube Satellite is 25%.


The Study Date of the EPIC Instrument is June 27.


The Operating Temperature of the Detector Imaging Device is < 60ºC.


The Measurement Range of the SWE Strahl sensor Sensor is 5 eV to 5 keV.


The 10 Year Anniversary Date of the TerraSAR-X Satellite is June 14, 2017.


The Launch Date of the CubeSat Satellite is 24 May 2022.


The On-Orbit Duration of the CanX-4 Satellite is More than one year.


The Spectral Range of the High-Resolution Hyperspectral Imager Imager is 0.4 to 2.5 µm.


The Slit Width of the Spectrometer Instrument is 84 µm.


The Target Application of the SGR-ReSI receiver Satellite Receiver is Take wind speed measurements within hurricanes.


The Noise of the NISP IR Detector Detector is CDS readout noise shows the same performances demonstrated during the NRE phase.


The Repeat Cycle of the IRS-1B Satellite is 22 days.


The Capacity of the MMU Mass Memory Unit is 16 Gbit.


The Dithering Maneuver Requirement of the Spectrometer (SPI) Spectrometer is Required.


The Presenters of the An Efficient Photoelectric X-ray Polarimeter Device is Enrico Costa, Paolo Soffitta, Ronaldo Bellazzini, Alessandro Brez, Nicholas Lumb & Gloria Spandre.


The Joint Type of the Structure General is Brazed joint.


The Silicon Thickness of the L0 Detector Detector is 12 µm.


The Orbit Raising Time of the Safran/Snecma PPS-5000 Electric Propulsion is Approximately four months.


The Launch Site of the EMIT Satellite is Kennedy Space Center in Florida.


The Optical System of the OCTS Sensor is Catoptric.


The Initial Altitude of the NRCSD Payload is 385-400 km.


The Altitude of the SWIM Real Aperture Radar is 519 km.


The Ability of the GHGSat Satellite Fleet is Pinpoint the source of even small leaks.


The Time Series of the ISS LIS Lightning Imaging Sensor is 16 years.


The Wavelength of the Laser Head Unit (LHU) Laser Unit is 1064 nm.


The Launch Date of the LAICE Satellite is > 2023.


The Computing Power of the SCP Spacecraft Process Controller is 1 MIPS.


The Launch Date of the Carbonite-1 Microsatellite is July 2015.


The Safety Measures of the ELSA-d Mission is Safety evacuations and passively safe trajectories, Collision Avoidance Maneuvers, Ground segment and operator oversight, Protected critical mission functions, Safety critical computing, Architectural redundancy, High-fidelity ground-based simulation.


The SAR Products Release Time of the TerraSAR-X Satellite is 5.5 months after launch.


The Function of the Lunar Ops E/PO Payload is Image the lunar surface.


The Measurement Accuracy of the D2P Radar Altimeter Altimeter is 1-3 cm average.


The Face Sheet Thickness of the Grating Optical Component is 1mm.


The Swath Width of the MESSR Radiometer is 200 km.


The Operational Position of the GOES-S Satellite is 137.2° West.


The Manufacturer of the VNREDSat-1A Satellite is Astrium.


The Propulsion of the NEA Scout CubeSat is Solar sail.


The Purpose of the CERN Radiation Testing Facility is Simulate conditions within Jupiter's massive magnetic field.


The Data Type of the Tropospheric Monitoring Instrument (TROPOMI) Instrument is High-resolution fluorescence data.


The Wavelength Detection Range of the Mapping Channel Spectrometer is 0.25 µm to 1 µm.


The Objective of the Gulfstream Supersite Experiment Location is Investigate oceanographic phenomena.


The Response of the Photodiode Detector is Linear.


The Dry Mass of the IMP-8 Spacecraft is 371 kg.


The Structure Material of the CeREs Satellite is Teflon.


The Orbit Inclination of the Aalto-1 Satellite is 97.44º.


The Payload Power of the Spacecraft Bus (Avionics Module=AM) Satellite is 350 W, 1.1 kW.


The AVGS Manufacturer of the ASTRO Satellite is NASA/MSFC.


The Lifetime of the Spacecraft Platform Satellite is 7 years.


The Orbit Type of the ELaNa-4 CubeSats Satellite is Near-circular orbit.


The Development Cooperation Agreement Date of the Alphabus Telecommunications Platform is March 2006.


The PAN Detector Array of the WV-3 Imager Imager is 35,000 pixel.


The Description of the SV-4 diagrams DoDAF 2 Viewpoint is Hierarchy of systems and system Functions.


The Sensor Complement of the OPAL CubeSat is Not provided.


The Pressurant of the ACE propulsion system Propulsion System is Gaseous nitrogen.


The Solar Wind Speed and Beta of the ACE Satellite is Typically observed from the mid-1970s through the mid-1990s.


The Pulse Repetition Frequency (PRF) of the Satellite Satellite is 1795.33 Hz (Ku-band), 448.83 Hz (S-band).


The Bus Type of the NorSat-1 Satellite is Nanosatellite and a small microsatellite.


The Manufacturer of the SeaWiFS Satellite is Raytheon SBRC.


The Launch Date of the Dnepr Rocket Launch Vehicle is Nov. 6, 2014.


The Purpose of the SIM Simulator is Testing and validation of operational procedures and databases, support the training of operators, and execution of simulation campaigns.


The Spatial Resolution of the L2SMP Soil Moisture Product is About 40 km.


The Power of the X-band Transmitter Transmitter is 3.4 W.


The URL of the The Charter Satellite Program is http://www.disasterscharter.org/c/document_library/get_file?folderId=33636&name=DLFE-2502.pdf.


The Period of the Landsat 9 Satellite is 99 minutes.


The Authors of the "Discrete and broadband electron acceleration in Jupiter's powerful aurora" Research Paper is B. H. Mauk, D. K. Haggerty, C. Paranicas, G. Clark, P. Kollmann, A. M. Rymer, S. J. Bolton, S. M. Levin, A. Adriani, F. Allegrini, F. Bagenal, B. Bonfond, J. E. P. Connerney, G. R. Gladstone, W. S. Kurth, D. J. McComas & P. Valek.


The Image Type of the TWINS Satellite is Stereo ENA.


The Launch Date of the Gokturk-2 Satellite is Dec. 18, 2012.


The Mission Duration of the UKube-1 Satellite is Over 14 months.


The Sensitivity of the Solar-B / Hinode Satellite is Unknown.


The Principal Investigator of the EFI Electric Fields Instrument is F. Mozer.


The | of the Coarse Pointing and Fine Pointing mechanism Pointing Mechanism is Coarse Pointing and Fine Pointing mechanism (CPA and FPA) for an optical communication link.


The Performance Requirement of the LISA Pathfinder Satellite is As close as possible to 10-12 ms-2 Hz-1/2 in the frequency band 10-3 to 10-1 Hz.


The FOV Overlap of the COR1 Coronagraph1 imager is Pointing stability required 1.5 arcsec over pB sequence (7 s).


The Mass of the TXS S-band Transmitter/Transceiver is 75 g.


The Launch Date of the Sentinel-3B Satellite is Spring 2018.


The Contact Establishment of the Aeolus Spacecraft is Through the Troll ground station in Antarctica.


The Altitude of the Satellite Satellite is 500-700 km.


The Architecture of the MERLIN Satellite Satellite is Based on the AS250 (AstroSat) avionics core and integrates all Myriade Evolutions common units.


The Solar Array Cells of the MarCO CubeSats Satellite is 42.


The Space Segment of the Galileo Satellite Navigation System is 30 MEO satellites in 3 planes inclined at 56º.


The Laser Observations Basis of the Starlette and Stella Satellites is Orbits and SLR stations' coordinates determination.


The Camera Function of the InSight Mars Lander is Guiding the placement of the SEIS and HP3 instruments, taking pictures of the surrounding landscape.


The Type of the FOG 120 HR Gyro is High precision Fiber Optic Gyro.


The Number of Wavelength Positions of the FG (Filtergraph) Instrument is One for the continuum.


The Redundancy Approach of the SSTL Company is High degree of cold parallel redundancy.


The Product of the Kleos Space Company is GEOINT DaaS.


The URL of the Dove Satellite is https://digitalcommons.usu.edu/cgi/viewcontent.cgi?article=3797&context=smallsat.


The Length of the LRS (Lunar Radar Sounder) antennas Instrument is 15 m.


The Optical Efficiency of the Overall System is 0.6.


The Swath Width of the MSU-100 Camera is 960 km.


The Decks of the Bus Satellite Structure is Bottom deck, top deck and payload deck.


The Mission Update of the Gravity Probe B Satellite is Sept. 26, 2008.


The Mass of the Spacecraft Satellite is 80 kg.


The Design Purpose of the First Arab mission to Mars Satellite is To inspire youth.


The LTAN of the KOMPSAT-6 Satellite is 6 hours.


The Size of the Jugnu Satellite is 10 cm x 10 cm x 32 cm.


The Characteristic of the Plasmapause Boundary of Plasmasphere is Sudden drop in plasma density by the order of one magnitude.


The Inclination of the Orbit Centaur AV-042 upper stage is ~120.5º.


The Operating Temperature of the GEDI Laser Laser System is 350 (±2)ºC.


The Arrival Date at Mars of the ExoMars 2020 mission Mission is March 2021.


The FOV of the Instrument Satellite Instrument is 19.3º.


The Spectrum Acquisition Time of the SOLSPC Radiometer is 11 minutes.


The Usage of the Testing Filters SWIR Instrument Component is During testing in ambient conditions.


The Stowed Configuration of the LF spacecraft Spacecraft is Illustrated in Figure 2(b).


The Testing Date of the Xona's Navigation System Navigation System is Earlier this year.


The Ground Resolution of the Pléiades Neo Satellite is Larger.


The Climatology Comparison of the ASCAT Satellite is RapidScat.


The RF Communications of the Spacecraft Satellite is Up to 4 kbit/s.


The Launch Mass of the GSAT-30 Satellite is 3357 kg.


The Software of the TIE Payload is AIS (Automated Identification System).


The Orbit Altitude of the MicroSat-2b Satellite is 514 km.


The Approval Date of the WFIRST Space Telescope is 02 March 2020.


The Leading Company of the EPS-MACCS Satellite Mission is GomSpace in Denmark.


The Wide Band Mode of the Receiver Communication System is ± 10.0 kHz (- 3 dB ).


The Receiver Operation of the ColAIS Experiment is Alternating, switching every three months.


The Sample Diameter of the Microcalorimeter Microcalorimeter is 2.5 cm.


The Orbit Type of the ExoMars Orbiter Satellite is Elliptical.


The Release Date of the Comet landscape Image is 01 October 2018.


The Establishment Year of the Cospas-Sarsat Satellite-based emergency detecting and locating system is 1982.


The Altitude of the OceanSat-1 Satellite is 720 km.


The Image Capture Date of the AlSat Nano CubeSat is January 9, 2017.


The Detector Types of the Spectrometer Instrument is Silicon and extended InGaAs photodiodes.


The Launch Center of the Chang'e-5 Spacecraft is Wenchang Space Center.


The Satellite Speed of the AIS System Communication System is ~7 km/s.


The Design and Verification Status of the EarthCARE/CPR Satellite is Unknown.


The Deliverable of the Product Level 1C (L1C) Data is Level 1b data orthorectified, re-sampled to a specified grid.


The Scheduled Launch Date of the Gaia Satellite is 20 December.


The Calibration of the Landsat-7 ETM+ Satellite is On-orbit.


The Secondary Diameter of the Telescope Optical Instrument is 34 mm.


The Measurement Domain of the Tatiana-2 Satellite is Atmosphere.


The Bandwidth of the SAW Filters Filters is 14 MHz.


The Approval Date of the EPS-SG Satellite is Nov. 16, 2012.


The ACT FOV Incidence Angles of the Sentinel-5 instrument Instrument is Up to 54°.


The Components of the Data Handling System (DHS) System is Baseband Data Handling (DH) and Solid State Recorder (SSR).


The Processor of the PROBA-2 Satellite is 32-bit LEON2-FT RISC processor with up to 100 MIPS.


The URL of the Airborne Lunar Spectral Irradiance (Air-LUSI) Instrument is https://airbornescience.nasa.gov/instrument/Air-LUSI.


The Minimum Concentration in 2015 of the Ozone Layer Atmospheric Layer is 101 Dobson Units.


The Clock Source of the X-band transmitter Transmitter is Local TXCO (Thermally Controlled Crystal Oscillator).


The Configuration of the UVIT Telescope Assembly is Two telescopes.


The Thrust of the CUS Cryogenic Upper Stage is 73.55 kN.


The Voltage of the S/C Power Satellite Power System is 28 V.


The Mission Status of the SVOM Satellite is Planned.


The Design Presentation Proceedings Date of the Microsatellites Satellite is Jan. 2005.


The Mission Duration of the Spacecraft Satellite is 2 years.


The Publication Date of the CONGO GPS/GIOVE Tracking Network is Sept. 1, 2009.


The FOV of the Particle Detector Instrument is ±21.8º.


The Energy: 0.4 keV (3.1 nm) of the N K-edge Atmospheric Cross Section Feature is N at 0.4 keV (3.1 nm).


The Development Status of the 20 N Thruster Propulsion System is Near-flight-ready.


The Functions of the Satellite Management Unit Management Unit is Onboard Data Handling, power and control distribution.


The Objective of the CRISTAL Satellite Mission is Simultaneously monitor snow depth and sea-ice thickness change over the Arctic.


The Orbit of the Telescope Optical Instrument is Lissajous orbit about L2.


The Objective of the Kent Ridge 1 Microsatellite is Integrate a VNIR/SWIR FTR (Fourier Transform Recovery) instrument into a microsatellite in support of disaster monitoring in Asia.


The Beacon Signal Frequency of the ALBus CubeSat Satellite is 400.4 MHz.


The Dimensions of the InP amplifier Amplifier is 900 x 560 µm2.


The Data Acquisition of the DAC Data Acquisition Card is Acquires temperature, current, and logic state values from sensors.


The NEΔT (K) of the ICI-9 Radiometer is 1.5.


The Flare Class of the Solar Dynamics Observatory Satellite is X1-class.


The Reflector Type of the Antenna Subsystem Communication is 1m parabolic dish.


The Objective of the SOTA/SOCRATES mission Mission is Fundamental experiment for laser communication between LEO and the ground.


The Data Rate of the Cadet-U UHF radio RF Communication Device is 3 Mbit/s.


The Azimuth Resolution of the SIR-C Phased Array is 7 m for the selected area.


The Number of Instrument Units of the Solar Orbiter Spacecraft is 33.


The Usage of the Radar Altimeter Altitude Measurement Device is Vertical descent phase.


The Publication Date of the Herschel Satellite is Aug. 20, 2013.


The Years on Orbit of the TerraSAR-X Satellite is 10.


The Environment Density of the GRB 130925A Gamma-Ray Burst is Low.


The Number of Identified Stars of the Delta Scuti stars Star Type is 60.


The Altitude of the Landsat 9 Satellite is 705 km.


The Number of Charge-to-Voltage Conversion Settings of the CTIA Charge Sensitive TransImpedance Amplifier is 4.


The Quantity of the Flock 4v SuperDoves Satellite is 26.


The Pulse Amplitude of the RainCube Radar is Variable.


The Launch Date of the EUTELSAT KONNECT Satellite is 17 January 2020.


The PROM of the STRV-2 DHS Data Handling System is 32 k PROM.


The Magnetization of the Rosetta Spacecraft is Not magnetized.


The Services of the EuTEF Payload Facility is Delivers EuTEF downlinked TM Data to EuTEF Ground Segment.


The Data Transmission Rate of the MSR Radiometer is 2000 MHz.


The Orbit Altitude of the Hinode Satellite is 680 km.


The Function of the Shaping Circuit Circuit is Reduce the length of the impulses and modify them to allow a numerical encoding.


The Components of the Focal Plane Cryostat Assembly Subsystem is Infra-red detectors, cold optics, cryocoolers, detection chain electronics.


The EOL Operations Date of the D-Sat Satellite is October 10, 2017.


The First TLE Payload Data Received of the Tatiana-2 Satellite is Oct. 21, 2009.


The Number of Contacts with the Comet of the Philae lander Lander is Four times.


The URL of the Tunneling Horizon Detector Detector is http://micromachine.stanford.edu/projects/tunneling_sensors/THD/THDSummary.html.


The Size, Weight, Power Reduction of the SPIDER Imaging Technology is 10 to 100 times.


The Release Date of the CubeSats Satellite is January 16, 2017.


The URL of the GaN Experiment Space Experiment is http://www.av.it.pt/medidas/space/Flayer/IT%20no%20Espa%C3%A7o%20EN_IT.pdf.


The Implementing control-user plane split of the Open5GCore Rel. 4 5G Core Network is PFCP [N4].


The Thermal Gradients of the PF1 Passband Filter is Unknown.


The Calibration of the UVNS Spectrometer is High absolute accuracy using sunlight and on-board illumination sources every orbit.


The Burrowing Depth of the HP3 Instrument is 3 to 5 meters.


The Closest Approach to the Sun of the ISON Comet is Unknown.


The Distance from Mars of the TGO Trace Gas Orbiter is About 41 million km.


The Risk Mitigation of the Autonomous Satellite Avoidance Program (ASAP) Satellite System is In Progress.


The Sun Model of the ADCS Attitude Determination and Control System is Computes sun vectors.


The Size of the SOAR Satellite is 3U CubeSat.


The Number of Thrusters of the Propulsion Subsystem Propulsion is 8 (2 x 4).


The Polar Regions of the Ryugu Asteroid is Very few craters.


The Calibration Targets of the TRUTHS Satellite is Deserts and the moon.


The Swath Width of the MSU-50 Camera is 940 km.


The Vehicle Height with 5 m short PLF of the CBAS and EAGLE Spacecraft is Approximately 60 m.


The Battery Type of the CubeSat power module Power Control is Lithium-polymer.


The Deployment Contract of the Diwata-1 Satellite is JAXA and Tohoku University.


The Mass of the IPS Pointing System is 1,180 kg.


The Mass of the MTQ Instrument is 225 g.


The Batteries Type of the Power Subsystem Satellite is Lithium-ion.


The Observation Dates of the MODIS Imaging Spectroradiometer is February 8-12, January 22-29, and January 14-17.


The Data Sampling Capacity of the NorAIS-2 Receiver AIS Receiver is Up to 512 MByte.


The Spectral Ranges of the 4-band CCD Imager Instrument is 0.42 - 0.50, 0.52 - 0.60, 0.61 - 0.69, 0.76 - 0.89 µm.


The Processing Capability of the Processor Satellite Component is 14 MIPS.


The Quantity of the Flock-4v Satellite is 14.


The Website of the GOCE Satellite is http://www.amptek.com/didm.html.


The Connector of the ENT EVR Nozzle Tool is Quick Disconnect Connector.


The Deorbiting Technology of the CanX-7 Satellite is Drag Sail.


The Voltage of the Solar Array Power Source is 20–40 V.


The Current Design of the DFACS Attitude Control System is CGPS (Cold Gas Propulsion System).


The Experimental Uplink of the QSat Satellite is Ku-band, 10 Mbit/s.


The Time to Stabilize of the Satellite Spacecraft is More than six hours.


The Backup for Rumpin of the Rancabungur Ground Station is True.


The Interference filter - Bandwidth of the Instrument Sensor is 1 nm.


The QE Variation of the Detector Arrays Sensor is Sub-pixel level.


The Life Expectancy of the SPOT-4 Satellite is Unchanged at the end of 2012.


The Focal Plane Cooling of the Spectrometers Instrument is Passively cooled.


The Quote Source of the Carruthers Geocorona Observatory Spacecraft is Dr. Mackenzie Lystrup.


The Reentry Date of the Skylab-1 Space Station is July 11, 1979.


The Processor of the MCM Memory System Module is TS68EN360 and XPC860.


The Operating Temperature of the Telescope Optical Instrument is 150 K.


The Wavelength Range of the Band No 4 Spectral Band is 3.50 ± 0.50 - 4.10 ± 0.50 µm.


The Mission Start Date of the Triana Satellite is October 2, 2000.


The Reflector Dimension of the Antenna System Communication System is 65 cm.


The Operating System of the UWE-1 Satellite is µCLinux.


The Orbital Period of the HAT-P-7 Exoplanet is 2.2 days.


The Size of Mount Doom of the OSIRIS-REx Spacecraft is The size of a small parking lot.


The Mission Type of the NigeriaSat-2 Satellite is Imaging.


The Orbit Altitude of the CANYVAL-X CubeSats CubeSats is 505 km.


The Data Rate of the TT&C Data Communication is 32 kbit/s.


The Data Analysis Plan of the THEMIS Probes Spacecraft is Look through archival THEMIS data for more events around Earth and determine how often the magnetopause may be booming like a drum.


The Resolution of the CCD Image Sensor is 512 x 2048 image pixels.


The Launch Date of the M3MSat Microsatellite is Unknown.


The Data Source of the GEOS Model Weather and Climate Model is Actual measurements of physical properties.


The Development Organizations of the SPIDER Imaging Sensor is Lockheed Martin Advanced Technology Center (LM ATC) and University of California at Davis (UC Davis).


The Observation Functions of the SGLI Satellite Instrument is NUV and polarization observations.


The End of Mission Date of the Kolibri-2000 Satellite is May 3, 2002.


The Mission Objective of the UWE-1 Satellite is Analyze and optimize different implementations of Internet protocols in space.


The Mass of the Carbon Dioxide Ice Patch Surface Feature is 57 kg.


The Energy Range for Charged Particles of the FREND Instrument is 0.5–10 MeV.


The Measurement Frequency of the Satellite RMIB TSI is Twice per day.


The Auroral Potentials of the Earth Planet is Several thousands of volts.


The Scan Rate of the VIRR Instrument is 48 rpm.


The Camera Quantity of the LED-arrays Lighting System is 2.


The Quantity of the Propulsion System Satellite Propulsion is 8.


The Downlink Beacon Data Rate of the RF Communications Communication System is 20 bit/s.


The Full-Aperture Reference Surface Temperature of the TIR Subsystem Imaging System is 340 K.


The Launch Date of the Space Technology 5 Satellite is Unknown.


The Launch Date of the TROPICS cubesats Satellite is 12 June 2022.


The Platform of the CASPR Experiment is Gimbal-actuated platform.


The Average Upper Atmosphere Temperature of the Jupiter Planet is About minus 100 º Fahrenheit or a chilly minus 73º Celsius.


The Vertical Resolution of the JPL Microwave Radiometer Radiometer is 240 m.


The Operation Lifetime of the TerraSAR-X Satellite is 10 years.


The Antenna Gain (dB) of the Antenna Reflector is >30.


The Cadence of the Composition of the Radiation Measurement is 30 minutes.


The Geolocation Accuracy Test Location of the Ikonos-2 Satellite is Big Spring, TX.


The Operation of the Payload Data Data is Continuous throughout the mission life.


The Total Impulse of the SkySat-6 Satellite is 269 Ns.


The Image Acquisition Date of the PROBA-V Satellite is Feb. 7, 2014.


The Ground Segment Components of the SARah system Satellite System is All necessary components for the ground segment.


The Planet of the AU Microscopii Star is Yes.


The Sensitivity of the Channel 4 Sensor is 0.3 K/pixel.


The Telescopes of the ROLO Robotic Lunar Observatory is 2.


The Operator of the Resurs-P1 Satellite is Roscosmos (Russian Federal Space Agency).


The Launch Date of the Iridium NEXT Satellite Constellation is June 2010.


The Attitude Control Mode of the Hayabusa-2 Spacecraft is One wheel control mode.


The Orbit Period of the BX-1 Microsatellite is 90.1 minutes.


The Development Start Date of the Satellites around the Moon Satellite Constellation is 20 May 2021.


The Orbital Angles of the PolyCam Camera is Northern hemisphere, equator, southern hemisphere.


The S/C Structure of the IRS-1C and IRS-1D Spacecraft is Main platform and the payload platform (aluminium honeycomb structure).


The Usage of the MDA Dock is Dock for the command and service modules.


The Downlink Data Rate of the RF Communications Communication System is 320 Mbit/s.


The Cadence of the MiniCOR Coronagraph is ~15 images/hour.


The Mass of the Microsatellites Satellite is < 100 kg.


The Service Spectrum of the NPOESS Program is Onboard acquisition and transmission (broadcast) of telemetry data in real-time to field terminals of the user community.


The Comparison of the CUMULOS Data is VIIRS, MODIS, DMSP, CIRC, and related on-orbit microbolometers.


The Mass of the OSIRISv3 Laser Communication Terminal is 1.65 kg.


The Force of the ESP Thrusters Maneuvering System is Provides force in the normal direction.


The Arrival Date of the Hera Spacecraft is November 2024.


The Data Transfer Rate of the LCRD Payload is Approximately 1.2 Gbit/s.


The Refractivity Profile Comparison Time of the GNOS Instrument Occultation Measurement Device is Within 1 hour.


The Ground Segment Locations of the Dove-2 Satellite is 5.


The Launch Date of the CartoSat-1 Satellite is May 5, 2005.


The URL of the TriG GNSS Receiver is http://authors.library.caltech.edu/21729/1/.


The On-board Data Analysis of the GimmeRF Radio Instrument is Up to 2 TFLOPs.


The Clocks of the QZS-1 Satellite is Two rubidium atomic clocks.


The Downlink Data Rate of the S-band system Communication System is 102 MB/day.


The Ecliptic Latitude Range of the NEOSSat Satellite is Tentatively ± 40º.


The Orbit of the DSCOVR Spacecraft is Lissajous orbit about L1.


The Launch Date of the SEOSAT-Ingenio Satellite is Later this year.


The Science Data Collection Modes of the DPU Data Processing Unit is Two.


The Number of Planets of the Kepler space telescope Telescope is Billions.


The Ground Support Provider of the TanSat Satellite Mission is NSMC (National Satellite Meteorological Center).


The Differential non-linearity of the PHA Detector is <1%.


The Size of the Spacecraft Satellite is 7.5 m (high), 4 m x 4 m overall cross section.


The Solar Array Normal Vector and Sun Vector Difference of the Spacecraft Satellite is Up to 30 degrees during eclipse seasons.


The Instrument of the DMC-3 Satellite Constellation is MSI (BJ-2).


The Date of the Next Flyby of Jupiter Event is July 21.


The Update Date of the Jason-3 Satellite is Feb. 12, 2016.


The Orbit Altitude of the ISS Space Station is ~400 km.


The Capture Time of the Images Image is Around 10:30 JST on 6 January 2018.


The Quantity of the CubeSats Satellite is 12.


The Attitude Control of the JL-1-GF03B Microsatellite is 3-axis, 4 flywheels.


The Radiation Tolerance of the Linear Encoder Sensor is <1 krad TID.


The Manufacturer of the Tianwen-1 Mars Lander is China.


The Design Life of the Yutu-2 Lunar Rover is Three months.


The Level 1 Products of the Sentinel-6 Satellite is Instrument measurements converted into recognized engineering units, calibration data (radiometric and spectral calibration as well as geometric registration to geodetic Earth coordinates) are appended (Level 1a) or applied (Level 1b), geolocation data ar.


The Antenna Size of the Altimetry Instrument Instrument is 1.2 m.


The Number of Satellites of the T1TL Prototype Constellation Satellite Constellation is 42.


The On-board Computer of the IOD-1 GEMS Satellite is CSL On-board Computer (OBC) with integrated GPS receiver.


The Control of the Shutter Optical System Component is Sun Sensor.


The Signal to Noise Ratio (SNR) of the Climate Observatory Satellite is ~300 in the vis-NIR.


The Launch Date of the GCOM-C Satellite is 23 December 2017.


The Warm Component Percentage of the Universe Cosmology is 15 percent.


The Average Data Rate Over Land of the KaRIN Instrument is ~271 Mbit/s.


The Observation Location of the ALOS satellite Satellite is Al Jawf oasis in southeastern Libya.


The Utilization Presentation Date of the ISERV Pathfinder EO Sensor is Oct. 1-5, 2012.


The Conference Presentation Date of the ROSA Radio-Occultation Receiver Receiver is Dec. 8-10, 2010.


The Solar Wind Behavior of the Comet 67P Comet is Beforehand, particles had been slower-moving, and the solar wind had been generally weaker.


The Primary Instrument of the CryoSat-2 Satellite is SIRAL (SAR (Synthetic Aperture Radar) Interferometer Radar Altimeter).


The Mass of the Optical Scanning Design Imaging Spectrometer is 150 kg.


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


The Mission Status of the Satellite EO is Operational (extended).


The Pressure of the PROP unit Propulsion System is 300 bar.


The Installation Location of the Metric Camera Camera is Inside the pressurized cabin of the Spacelab module.


The Launch Date of the NASA Orbiting Carbon Observatory-2 Satellite is Unknown.


The Sensor Type of the Satellite STRATOS is GNSS receiver.


The Boom Length of the Microsatellite Satellite is 2 m.


The Duration of the Spacewalk Activity is About five-and-a-half hours.


The Principal Investigator of the LROC Camera System is Mark Robinson.


The Downlink Band of the Spacecraft Satellite is S-band (variable to 2 Mbit/s).


The Measurement Range of the Particle Detector Instrument is Deuteron : 8 MeV/n ~ 26 MeV/n.


The Manufacturer of the SBSS-1 Pathfinder Satellite is Boeing.


The Mission Start Date of the IBEX Spacecraft is Unknown.


The Electronics Unit Weight of the PRARE ground transponder Ground Station Equipment is 35 kg.


The Activation Time of the NGC Lander Lander is Before the separation from orbiter.


The Relative Accuracy of the Instrument Sensor is Better than 1% for 45 s counting time on IP signal.


The Impact Date of the DART Spacecraft is October, 2022.


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


The Shape of the 67P/Churyumov-Gerasimenko Comet is Dual-lobed.


The Swath width of the ALOS/PRISM Satellite is 35 km / 70 km.


The Aperture Antenna Diameter of the COMMx Payload is 3.66 m.


The Measurement Swath of the ISS-RapidScat Scatterometer is Smaller by a factor of two compared to QuikSCAT.


The Percentage of Sky Observed in Three Exposures of the Euclid Reference Survey Survey is 47%.


The Mass of the DORIS Instrument is 15 kg.


The Payload Mass of the Spacecraft Satellite is 33.3 kg.


The Presentation Date of the MinXSS CubeSat is June 3-5, 2013.


The Resolution of the CMOS Camera Sensor is 3000 x 2000 pixels.


The Operation Time of the LEO-to-ground radio link Communication System is Twelve minutes.


The Headquarters of the EROS-B Satellite is Netherlands Antilles (Cayman Islands).


The Launch Date of the ASNARO Satellite is Nov. 6, 2014.


The Instrument Mass of the DUST sensor Cosmic Dust Sensor is 3.8 kg.


The Storage Capacity of the TUBSAT-N Satellite is Over 6000 messages at 134 bytes in length.


The Location of the ORBIMAGE Satellite Operations Center Satellite Operations Center is Dulles, VA.


The Size of the Irvine 02 CubeSat is 1U.


The URL of the ACE - Advanced Composition Explorer Satellite is http://www.nasa.gov/press-release/goddard/2016/ace-cosmic-ray.


The Launch Date of the NorSat-2 Satellite is July 2017.


The Flight of the PSLV-C16 Satellite is Successful.


The Image Posting Date of the Rosetta Satellite is March 4, 2015.


The Symbol Rate of the Channel Communication System is 76.8 Msps.


The Image Resolution of the RISING-2 Satellite is Unknown.


The Number of CCD Elements in Cross-track of the MSU-100 Camera is 8000.


The Commissioning Phase Duration of the CALIPSO Satellite is 38 days.


The | of the MicroASC Star Tracker is MicroASC A Miniature Star Tracker.


The Swath Width of the HORUS Sensor is 15 km.


The Ka-band Radar Frequency of the Tomorrow-R1 and -R2 Satellite is 35.75 GHz.


The Measurement Frequency of the TEMPO Instrument is Hourly.


The Bulletin Date of the GOCE Satellite is February 2008.


The RPO Capability of the GSSAP Satellite is Yes.


The Mission Status of the BeiDou-2 Satellite is Unknown.


The Power Requirement of the CubeSats Satellite is None.


The Cooling Temperature of the Baseplate of the Vessel Satellite Component is 15°C.


The Mass of the LEICA Particle Detector is 7.4 kg.


The Operational Status of the MTSAT-2 Satellite is Operational.


The Imaging Frequency Band of the TerraSAR-X Satellite is X.


The Detector Units Status of the IXPE observatory X-ray Observatory is Complete.


The Touchdown Requirement of the Lander Module Spacecraft Module is < 5 m/s in vertical and horizontal velocity.


The Launch Date of the Sentinel-1A Satellite is 2013+.


The Form Factor of the PACE nanosatellite Satellite is 2U CubeSat standard.


The Power of the QSat Satellite is 74 W.


The Manufacturer of the Antenna Device is TICRA.


The Electrical Noise Measurement of the ELS-A Sensor is 16.3 keV.


The Propellant of the OSAM-1 Satellite is Bi-propellant and mono-propellant.


The Main Bus Voltage of the MRU Main Regulator Unit is 28 V.


The Geometric Resolution of the TerraSAR-X Satellite is Up to 0.25 m.


The Predicted Quantity of the Fragments Debris is 85 k.


The Effect of the Dark Energy Hypothetical Energy is Shoving galaxies away from each other.


The Sensitivity of the Magnetic Field Sensor Sensor is Sub-picotesla.


The Swath Width of the TAC Camera is 52 km.


The Output Current of the Buck-Boost Converter Solar Array Regulator is 0 - 8 A.


The Leading Noise Terms of the Satellite Spacecraft is Magnetic disturbances.


The Anomaly Update of the Copernicus Sentinel-1B Satellite is 25 February 2022.


The Number of Thermal Emissive Bands of the VIIRS Satellite is 7.


The Dish Size of the Stanford Research International Ground Station is 18.3 m.


The Manufacturer of the NanoSatC-Br1 1U CubeSat is Southern Regional Space Research Center and of INPE.


The Observation Goal of the DELPHINUS Satellite is Detect over a hundred LIFs in a month.


The Value of the Spatial Resolution Satellite Instrument is 8.4 x 4.4 km.


The Length of the Tether Satellite Component is 4 km.


The Launch Site of the NPP Satellite is VAFB, CA.


The Attitude Determination of the Spacecraft Satellite is 10 arcsec.


The Launch Date of the MEV-1 Satellite is October 2019.


The Inclination of the SMART-1 Satellite is 90.188º.


The Apparent Cooling of the GeoSTAR Scattering Approach is Can exceed 100 K.


The Manufacturer of the SPOT-6 Satellite is Astrium Services Division of EADS.


The Impact Status of the LADEE Satellite is Planned.


The Mission Count of the X-37B space plane Space Plane is 4.


The LOS IAR Rotation Angle of the Integer Ambiguity Resolution Process is 50o.


The Thrust of the Electric Propulsion Test Subsystem Satellite Subsystem is 40 mN±4mN.


The Mass of the MSU-100 Camera is 2.9 kg.


The Attitude Control of the GNB Satellite is Passive magnetic attitude control.


The Field of View of the EPIC Cameras Imaging System is 30 arcmin.


The Stabilization of the Tsubame Microsatellite is 3-axis.


The Operation End Date of the BIRD Satellite is December 2005.


The Voltage of the Voltage 3 Digital is 5.5±2%.


The FOV of the Short Wavelength Band Spectrometer is 4º x 5'.


The Pointing Stability Requirement of the IRS Sounder Satellite is 300 m at SSP.


The Mass of the DIDM Instrument is 2.2 kg.


The Purpose of the Emirates Mars Mission Mission is Accelerate the development of the UAE’s space sector, education and science community.


The URL of the SMAP Satellite is http://smap.jpl.nasa.gov/mission/description.


The Workshop Date of the COSMO-SkyMed Satellite is June 12-13, 2007.


The Pixel Size of the Main Camera Camera is 300 m.


The Operational Life of the Spacecraft Satellite is ≥ 7.5 years from the end of IOT.


The Purpose of the CHRIS Imaging Spectrometer is Terrestrial and aquatic observation.


The Brigthness Temperature (BT) Sensitivity of the Antenna Reflector is ±0.29 K.


The Altitude of the Satellite Satellite is 904 km.


The Power Consumption of the DPU Digital Processing Unit is < 29 W.


The Thermal Operational Stability of the Instrument Satellite Instrument is ±1ºC.


The Risk of Collision of the AeroCube-OCSD-B and -C Satellites is Little risk.


The Full Commercial Service Launch of the OneWeb Satellite Constellation is 2022.


The Launch Vehicle of the Starliner Spacecraft is United Launch Alliance Atlas 5 rocket.


The Data Samples of the Experiment Data Telemetry is Roughly 1.3 million.


The High Spatial Resolution of the AMI Advanced Meteorological Imager is 0.5-1.0 km for VIS and 2 km for the infrared channels.


The CCD Array Elements of the LISS-3 Linear Imaging Self-Scanning Sensor is 6000.


The Frequency of the Millimeterwave receiver Receiver is 188.5 – 191.5 GHz.


The Benefits of the ASAP Autonomy System is Fast response to external events, reduces overall mission costs.


The Internal Magnetometer Calibration Method of the RAX-1 Satellite is Scalar based method that involved simple rotations of the satellite in a known magnetic field during ground calibration.


The NER of the Spectral Band A Spectrometer is 3.0 x 10^-5 W/(cm^2 sr µm).


The Arrival Date to Lunar Orbit of the CAPSTONE Satellite is November 13, 2022.


The Measurement Domain of the Biomass Satellite is Land.


The Exceeded Design Life of the Landsat-7 Satellite is Yes.


The Minimum BCRs for Normal Function of the DubaiSat-2 Satellite is Two BCRs.


The NiCd Batteries Capacity of the EURECA Spacecraft is 40 Ah.


The GSD (nadir) of the Payload Satellite Subsystem is Pan = ≤2.5 m, MS = ≤10 m.


The Ground Resolution (Infrared Channel) of the VIRR Instrument is 4.4 km.


The Monitoring Area of the PROBA-V Satellite is Europe and Africa.


The Sampling Interval of the sADC A/D Converter is 12 µs.


The Occurrence of the Solar Flare Natural Phenomenon is Second largest to have occurred from the past 11-year solar cycle.


The Functions of the Ground Segment System is Mission planning, sequence generation, station scheduling, spacecraft analysis, orbit determination, trajectory analysis and planning, maneuver design, instruments analysis, time correlation, data capture and distribution, science data gap reporting, gene.


The Launch Vehicle of the Yubileyniy-2/MiR Satellite is Rockot/Briz-KM.


The Newsletter Issue of the SHADOZ Ozonesondes is 11.


The Purpose of the MMS Satellite is Capture the show of charged particles in the magnetosphere.


The Operation Period of the ACLS Air and Oxygen System is Until the end of 2019.


The Power of the TRMM Satellite is 1100 W.


The Objectives of the PIXIE Satellite is Study of the morphology and spectra of energetic electron precipitation and its effect on the atmosphere. Derivation of the total electron energy deposition rate, the energy distribution of the precipitating electrons, and the altitude profile of ionizati.


The Resolution Δλ (0.10º slit) of the SPIM2 Spectrometer is 1.2 nm.


The Contact Separation of the PROBA Project Satellite Project is 14h for the nominal operations.


The Total Satellite Missions of the ICEYE Satellite Operator is 10.


The Mission End Date of the Spitzer Space Telescope Space Telescope is 30 January 2020.


The Mission Status of the RAVAN CubeSat is Still operating.


The Partial Service Launch Timeline of the OneWeb Satellite Constellation is Next 60-90 days.


The Separation Method of the ASTRO and NextSat Satellites is ASTRO's robotic arm.


The Period of the CBERS-2B Satellite is 100.26 minutes.


The Main Communication Bus of the CSI Data Communication is CAN (Controller Area Network).


The Resonance Survey Requirement of the SERB Nanosatellite Satellite is First resonant frequency > 90 Hz.


The Issue of the Attitude Control System Satellite System is Eclipse attitude control not achieved.


The Removability of the Optical Filters SWIR Instrument Component is Required.


The Spatial Resolution of the OLI-2 Sensor is 15 m.


The Mission Duration of the EURECA Satellite is 336 days.


The Radar Reflector Antenna Boom Length of the NISAR Satellite is 30 feet (9 meters).


The Mission Design Life of the DSP satellites Satellite is >18 months for the near-equatorial S/C, and >12 months for the polar S/C.


The Multitemporal Registration of the VSSC Satellite is Better than 3 m.


The Focus of the RECCAP-2 Satellite Mission is Reconcile and constrain the global GHGs budget with the aggregation of regional budgets.


The Altitude of the GPS Signal Environment Mapping is Up to geosynchronous orbit (35,900 km).


The Volume of the PHM Instrument is 28 liters.


The Potential Evaluation of the Indian Remote Sensing Satellite Satellite is "Potential of High-resolution Indian Remote Sensing Satellite Imagery for Large Scale Mapping".


The Measurement Category of the SARAL Satellite is Atmospheric Humidity Fields, Ocean topography/currents, Ocean surface winds, Ocean wave height and spectrum.


The Sensor Technology of the C3D Instrument CMOS Sensor is 0.18 µm CMOS technology.


The Bands of the CubeRRT Satellite is Tuned over 10 different bands commonly used for Earth observing microwave radiometers.


The Measurement Start Date of the SOVAP Instrument is 21/7/2010.


The Observation Modes of the OCO-2 Satellite is Nadir, Glint, Target.


The DOI of the Gravity Recovery and Interior Laboratory (GRAIL) Mission is 10.1126/science.1231507.


The Testing Temperature of the Faraday Cup Sensor is Exceeding 1650 ºC.


The Launch Date of the Polar Scout Satellite is 3 December 2018.


The Quantity of the Sun Sensor Suites Sensor is 4.


The Image Capture Date of the Sentinel-2 Satellite is 25 January 2022.


The Battery Type of the Spacecraft Satellite is Li-ion.


The Restructured Program Date of the NPOESS Satellite System is Nov. 2006.


The RF Output Power of the S-band transmitter Transmitter is Adjustable from 27 to 33 dBm.


The Purpose of the SMAP Satellite is Measuring the water content of soils.


The Power Consumption of the Nexus Electrical Power Subsystem is 1 watt.


The Purpose of the RISE Instrument is Deduce the size and density of the martian core.


The Size of the BRITE-Austria Satellite is 20 cm x 20 cm x 20 cm.


The Large Window Time Resolution of the CCD Image Sensor is 0.6 seconds.


The Greening of the Northern Forests Ecosystem is Rare benevolent effects of our warming climate.


The Launch Time of the CartoSat-2D Satellite is 3:58 UTC.


The Launch Date of the Nauka Module is July 21.


The Spatial Acquisition Duration of the Alphasat TDP1 GEO-relay is Achieved in no more than 80 s.


The Location of the PDCC Control Center is ESA/ESRIN, in Frascati, Italy.


The Manufacturer of the PolyITAN-1 CubeSat is KPI (Kiev Polytechnic Institute).


The Nominal SNR of the Band 6 Spectral Band is 870.


The Model Scale of the Juice Spacecraft is 1:18.


The Telecom, Landing Site Tilt Accommodation, Flight Hardware Thermal Safety of the Mission Requirements Satellite is Identified and Analyzed.


The FOV of the HIRES Instrument is 0.3º x 0.4º.


The Solar Spectral Irradiance Measurement Range of the SOLSPEC Spectrometer is 200 to 2400 nm.


The Location of the TAFF Software Package is OBC of the TDX spacecraft.