The Habitability of the Planet Candidate Exoplanet is Uninhabitable by life as we know it on Earth.


The Speed Range of the Coronal Mass Ejections Solar Phenomenon is 100 to 3500 km/s.


The End of Life Date of the SWFO-L1 Satellite is 31 December 2029.


The Number of Leaks of the Kayrros Studies Methane Leak Detection is Around 100.


The Measurement Accuracy - Time of the Instrument Sensor is Tag at frame rate.


The Type of the Energy Storage Power System is NiCd batteries.


The No of Passbands of the Channel 5 Sensor is 1.


The Mission Duration of the Van Allen Probes Satellite is 2 years.


The Earth Pointing Mode Function of the H3 and H4 Spacecraft is PZ-Surface faces into the nadir direction during observations.


The On-Orbit Duration of the ACE Mission Satellite is 18 years.


The Central Wavelength of the AVHRR/3 Sensor is 2.25.


The Mounting Angle of the AST Autonomous Star Tracker is 10º from the spin axis.


The Resolution of Accelerometer Measurements of the Three-axis diagonal gradiometer Gradiometer is < 2.0 x 10 -12  m s -2  Hz -1/2.


The Second-Generation Network Launch of the OneWeb Satellite Constellation is 2025.


The Launch Date of the Lunar Pathfinder Comsat Communication Satellite is End of 2023.


The Mission Concept of the TanDEM-X Satellite is Not provided.


The Power of the Spacecraft Satellite is 600 W.


The Deployment Type of the Helical Antenna Antenna is Self-Deploying.


The Orbit Type of the GCOM-W1 Satellite is Sun-synchronous orbit.


The Peaks of the Payload Power Power Generation is 180 W.


The Responsible Organization of the SWEM (SWEAP Electronics Module) Module is UCB/SSL (University of California, Berkeley /Space Sciences Laboratory).


The Launch Date of the Explorer 36 Satellite is Jan. 11, 1968.


The Mass of the RISAT-2 Satellite is 300 kg (including a payload mass of 100 kg).


The Phase B Payload Design Completion of the SMOS Satellite is Oct. 2003.


The Size of the Nightingale site Sample Collection Site is The size of a small parking lot.


The Quantity of the OBC On Board Computer is 3.


The Unregulated Bus Voltage of the Power Subsystem Subsystem is 14 V.


The Tip Mass of the Gravity-Gradient Boom Stabilization Device is 3 kg.


The Instrument Banks of the SLIM6 Satellite is 2.


The Orbit Frequency of the HyperScout® Satellite is 15 times a day.


The Telemetry Amplitude Digitization of the SXI Spacecraft is 12 bit.


The X-band, Downlink Data Rate of the Data Transmission Subsystem Satellite Subsystem is 190 Mbit/s.


The Manufacturer of the Lee Solenoid Valve Flow Control Valve is Lee.


The Launch Timeframe of the BA 330 module Space Module is 2012/14.


The Manufacturer of the DECA Camera is OIP (Optique et Instruments de Précision).


The Material of the Boom Assembly Assembly is CFRP (Carbon Fiber Reinforced Plastic).


The Function of the Y-axis aligned reaction wheel Reaction Wheel is Absorb the angular momentum of the spinning satellite.


The Output Signal of the Tunneling Infrared Sensor Sensor is 3.0 V signal + 1/400 of the tunneling high voltage + the tunneling signal disturbance.


The Data Downlink Volume of the EPICHyper Constellation Satellite Constellation is 20-100 times the downlink volume as a traditional cubesat.


The Size Discrepancy of the Impact Basins Lunar Surface Feature is Up to twice the diameter.


The Event Probability of the Safe Mode Satellite Mode is Sufficiently low and only possible under very special initial conditions.


The Design Lifetime of the Eutelsat Quantum Satellite is 15 years.


The Rotation Time of the M-CAM 1 Monitoring Camera is Less than two minutes.


The Period of the Satellite Orbit Orbit is 9.03 days.


The Manufacturer of the Prometheus Block 2 CubeSats Satellite is LANL (Los Alamos National Laboratory).


The Wait Time of the LT Device is 120 seconds.


The Orbital Period of the Shakuntala Satellite is 94.0 minutes.


The Detector Readouts of the ASTERIA Satellite is 20 Hz.


The Quantity of the Star Trackers AOCS Sensors is 2.


The Latitude and Longitude of the Gulfstream Supersite Experiment Location is 42º N, 75º W; 36º N, 65º W; 30º N, 73º W.


The Integration Time of the EyeSat Satellite is 15 seconds.


The Orbital Separation of the Sapphire and NEOSSat Satellites is Approximately 4700 km.


The IFOV of the 16 mm camera Camera is 9.2 x 10 -3  degrees.


The Co-aligned Telescopes of the ASTRO-1 Satellite Mission is 3.


The Band Reflection and Transmission of the Dichroic Filter Optical Filter is 400 to 1,000 nm reflected, 900 to 2,500 nm transmitted.


The Imagery Assessment of the TacSat-2 Minisatellite is Useful to the tactical operator.


The Calibration Performance of the VIIRS Instrument is Continuously Assessed.


The Apogee of the Deimos-1 Satellite is 680 km.


The X-band Downlink Transmission Data Rates of the CBERS-2B Satellite is 2 x 53 Mbit/s.


The Electron Energy Range of the SWEPAM Particle Detector is 1 - 1240 eV.


The Complementary Data Source of the VIIRS Instrument is AIS and VMS data.


The Location Knowledge Accuracy of the GFO Satellite is 10 cm (radial component).


The Composition of the Stardust Grain Particle is Carbon-rich graphite grain with an embedded speck of oxygen-rich material.


The Launch Date of the ExoMars 2020 Mission is July 2020.


The Number of Atmospheric Occultations of the GNOS-2 Satellite is Less than 1000 per day.


The Instrument System Testing Status of the IXPE observatory X-ray Observatory is Completed.


The Team Members of the Galileo 2nd Generation Satellites Satellite is Thales, Spaceopal, Leonardo and other partners.


The Aberrations of the SHS Interferometer is Introduce field of view limitations.


The Diameter of the Torus/Strut Structures Satellite Component is 61 cm and 46 cm.


The Mass of the FY-1C Satellite is Unknown.


The Data Downlink Time from Nanosatellite of the HyperScout 1 Hyperspectral Imager is Several weeks.


The Mission of the New Horizons Space Probe is Explore the Kuiper Belt.


The Number of CMOS Cameras of the CubeSense Attitude Determination and Control Subsystem is 2.


The Detector of the Spectral Band C Spectrometer is Si-PIN.


The Current of the Voltage 5 Digital is 525.


The Spin Axis Orientation of the IMP-8 Spacecraft is Normal to the ecliptic plane within 1º.


The Frequency Band of the Antenna Low-Gain Antenna is 8.025-8.400 GHz.


The Purpose of the Queqiao Relay Satellite is Bridge between Earth and the far side of the moon.


The First Earth Imagery Sent Date of the Kanopus-V Satellite is Sept. 3, 2012.


The Missions of the Solar Terrestrial Probes (STP) Program Program is STEREO, MMS, Hinode, TIMED.


The Observation Date of the Planck Telescope is Unknown.


The Development Lessons Learned of the EDSN Satellite is Unknown.


The Power Range of the Modular Power System Power System is 1W to 1kW.


The Hosting Service of the EUTELSAT 5 West B Satellite is EGNOS.


The Objective of the CVE Calibration and Verification Element is Calibration of the COSI payload and maintaining its long-term system performance.


The Off-Nadir Pointing Duration of the MicroSat-70 Satellite is Up to half an orbit.


The Detection Method of the Lunar Meteoroid Impact Flash Detection Detection System is Light flashes at the Moon are typically observed by detecting a local spike of the luminous energy in the visible spectrum when pointing a telescope at the lunar night side.


The Arrival Date of the Messenger Spacecraft is 18 March 2011.


The Launch Year of the Voyager 1 Spacecraft is 1977.


The Launch Date of the Herschel Telescope Telescope is May 14, 2009.


The Background Noise Reduction Method of the IXAE X-ray Astronomy Experiment is Mutual anti-coincidence fashion.


The Operation Start Date of the NICER X-ray telescope Telescope is June 2017.


The Ground Control Complex Location of the Kolibri-2000 Satellite is Kaluga (Russia).


The Start of Full-Scale Simulations of the BepiColombo Spacecraft is May 28, 2018.


The Polarimetry of the SAR-RCM Synthetic Aperture Radar is Hybrid.


The Mission of the JPSS-1 through JPSS-4 Satellites is Provide operational continuity of satellite-based observations and products from NOAA's POES and S-NPP satellites.


The Power of the Transponder Communication System is 5 W.


The | of the HISDESAT Satellite Operator is HISDESAT: PNOTS operator.


The Observation Objective of the Sentinel-4 Satellite is Observing the diurnal cycle of the tropospheric composition over Europe and North Africa.


The Image Quality of the Payload Satellite Payload is Maintained at consistent levels for more than 14 years.


The Energy Range of the XSM X-Ray Detector is 1-20 keV.


The Battery Capacity of the S/C Satellite is 920 mAh.


The Temperature of the Eureka Station Weather Station is 21.9°C.


The Linearity of the UV/VIS Spectrometer Spectrometer is 0.5%.


The Spatial Acquisition Duration of the Alphasat TDP1 GEO-relay is Reduced from 240 s at the very first tests to 34 s for default links.


The Deployment Location of the ECOSTRESS Instrument is JEM (Japanese Experiment Module) External Facility on the ISS.


The Accuracy of the GT Fine-Pointing Error Signal Provider is 0.4 arcsec, 3σ.


The Power Consumption Monitoring of the Propulsion System Satellite Component is Of the total propulsion system, of the CGG igniters and the main valve.


The Spectral Range of the TES Spectrometer is 3.2 μm to 15.4 μm.


The Conference Presentation Date of the STSat-2 Satellite is March 3-5, 2005.


The Radio-Frequency Test Completion Date of the Quantum Satellite is 27 July 2020.


The Function of the Sun-seeking precession controller Controller is Precess the solar panel normal vector to the sun vector.


The Design of the OTA Operational Transconductance Amplifier is Truly differential amplifier.


The Mass of the MWR Dicke Radiometer is 99 kg.


The Viewing Angle of the SCIAMACHY Spectrometer is 55º.


The SCI ports of the STRV-1d DHS Data Handling System is Eleven RS-422.


The Color of the Driver Electronics Electronic Component is Green.


The Activity of the Comet Celestial Body is Increased around the closest approach to the Sun.


The Mission Objectives of the GOCE Satellite is Obtain a portrait of Earth's most intimate features.


The Spin Frequency of the MicroSCOPE Satellite is Twice the Orbital Frequency.


The Filters of the Water Machines Water Filtration System is Ultrafiltration and reverse osmosis.


The Energy Measurement Range for Electrons of the Telescope 3 Telescope is 2-12 MeV.


The Launch Date of the MOMS Satellite is 18 June 1983.


The Camera Type of the CASPR Experiment is 8U binocular camera.


The Phase Change Sample Rate of the Satellite Communication Device is 10 Hz.


The Spectral Knowledge of the Individual Spectrometers Instrument is 1.5 pm.


The Location of the NASA's Jet Propulsion Laboratory Organization is Pasadena, California.


The Wavelength Range of the SUSIM Spectrometer Instrument is 110 to 410 nm.


The Quantity of the ICEYE SAR Satellites Satellite is 5.


The Size of the Instrument Sensor is 45 cm x 20 cm x 20 cm.


The Contribution of the SPEXone Instrument is PACE mission.


The Helix-Formation Distance of the TanDEM-X Satellite is Less than 1 km.


The Ground System of the ORS-6 Satellite is EGS (Enterprise Ground System).


The Purpose of the CAPSat CubeSat is Perform quantum annealing experiments.


The Vertical Resolution of the SAGE-III Spectrometer is 0.75 km (solar measurements), 1.5 km (lunar measurements).


The Power of the Particle Detectors Instrument is 20 - 50 V.


The Mission Goal of the Oculus-ASR Satellite is Exercise and validate techniques for determining an orbiting object's pose using unresolved ground imagery.


The Solar Panel Peak Power of the NSat Satellite is 28.8 W.


The Technology Management Contractor of the Heinrich Hertz satellite Communication Satellite is OHB.


The Solar Array Deployment Time of the Solar Orbiter Spacecraft is 06:24 CET.


The Manufacturer of the Pearl White-1 Satellite is United States Air Force Space Command.


The Local Time of Ascending Node of the COMPASS-1 Satellite is 9:15 AM.


The Survival Heaters Status of the RapidScat Satellite Instrument is On.


The Mission Status of the PhoneSat-1 and -2 Satellite is Mission complete.


The SP Performance of the SEIS Instrument Seismometer is < 5 x 10-8 m s-2 Hz-½ from 10-2 up to 100 Hz.


The Launch Site of the SMART-1 Satellite is Kourou, French Guiana.


The Power Source of the S/C Satellite is Surface-mounted triple-junction solar cells.


The Control Mode of the NEOSSat Satellite is Sun-Point.


The Cooling Temperature of the Filter Wheel Optics Subsystem is 213K.


The LYSO crystals of the Range Calorimeter Particle Detector is Side of 5 cm.


The PRN of the GSAT-0211 Satellite is 2.


The Number of Satellites to Launch in 2022 of the Satellogic Satellite Company is Up to 12.


The Internal Trays of the GNB Satellite Platform is 2.


The Lens System of the Instrument CCD Imaging Camera is f/4 telecentric lens system with a 5:1 fiber-optic taper.


The Antenna Length of the OPAL Satellite is About 17.5 cm.


The Orbit Inclination of the NRCSD Payload is 51.6º.


The Future Enhancements of the EDSN Data Network is Implementation of an ACK/NACK system, or via delay tolerant networks.


The Vibration Testing of the TEMPEST-D Radiometer Instrument is Passed.


The RF Transmit Power of the Transmitter Communication Device is 9.6 W.


The Quantity of the Zenith antennae Antenna is 2.


The Resolution of the RM-08 Passive Microwave Scanning Radiometer is 15 km x 20 km.


The Power Consumption of the Field Measurement Device Sensor is < 0.5 W.


The Plans of the ESA Organization is Develop a range of ‘in-orbit servicing’ technologies that will refuel, refurbish and de-orbit spacecraft.


The Conference Location of the High Spatio-Temporal Resolution Land Surface Temperature Mission Satellite is Valencia, Spain.


The Operation of the Satellite to Satellite Tracking Instrument (SSTI) Instrument is Provide Satellite-to-Satellite Tracking.


The Payload Space of the ITASat CubeSat Satellite is 2U.


The Attitude Angle Error of the Satellite Satellite is Occurs after 15-20 minutes.


The Tank Pressure Range of the Launcher Test Facility is 0.2 torr to 1.7 atmospheres.


The Time Reference of the CryoSat-2 Satellite is TAI (International Atomic Time).


The Capacity of the DDR2 SDRAM Memory is 1 GByte.


The LTDN of the WorldView-3 Satellite is 13:30 hours.


The Information Provider of the SwissCube Satellite is Muriel Richard of EPFL.


The Orbit Duration of the QARMAN CubeSat is Around four months.


The TDRSS Support of the Landsat-5 Satellite is No.


The Final Location Time of the Philae Lander is 17:32 GMT.


The Average power of the Spectrometer Spectrometer is 124 W.


The Telescope Focal Length of the SIS (Scanning Imaging Spectrograph) Spectrograph is 75 mm.


The Autonomy of the MPO-MAG instrument Instrument is Largely autonomous.


The Imagers of the BILSAT-1 Satellite is Medium resolution panchromatic and multispectral.


The Uplink Frequency of the RF Communications Communication System is S-band (2025-2110 MHz).


The Conference Presentation of the GPS Navigation Navigation System is 22nd International Technical Meeting of The Satellite Division of the Institute of Navigation (ION GNSS 2009).


The Total Imaging Swath of the Eastman Kodak KLI14403 linear CCD sensor Sensor is > 600 km.


The Agreement Date of the Nanosatellite And Plug-and-play Architecture (NAPA) Project Project is Sept. 17, 2010.


The Conference Date of the GOMS Geostationary Operational Meteorological Satellite is 1991.


The Mass of the APXS Spectrometer is 1.3 kg.


The Operation of the HTV Spacecraft is Reentry.


The Orbit Inclination of the SuperView-1 01 and Superview-1 02 Satellite is 98º.


The Number of Flights of the SEDS Tether Experiment Demonstration Program is Two.


The Data Update Frequency of the GPM Satellite is Every half-hour.


The Number of Satellites of the Satellite Constellation Constellation is 3-5.


The URL of the Cluster Satellite is http://www.esa.int/Our_Activities/Space_Science/Cluster/Origin_of_high-latitude_auroras_revealed.


The Purpose of the IRIS Satellite is Observe the transition region.


The Number of Lunar Days of the Chang'e-3 Moon Lander is 28.


The Mounting Configuration of the Honeywell QA2000-030 accelerometers Accelerometer is One measures spin rate and the other measures nutation.


The Frequency Band of the Ka-band transmitter Transmitter is Ka-band.


The Size of the  Submillimeterwave receiver receiver is 0.5 mm.


The Frequencies of the MSR Radiometer is 24 GHz and 31 GHz.


The Thermal Condition of the Satellite Spacecraft is Stable.


The Star Formation Rate Discrepancy of the Cluster XDCPJ0044.0-2033 Galaxy Cluster is Four times the rate found in its outer regions.


The Involvement of the HSI payload, the mass memory and coding unit (DSHA) and the AOCS (Attitude and Orbit Control Subsystem) Subsystems is Image acquisition and calibration.


The Constellation Status of the Astrocast Satellite Operator is Up and running in space.


The Payload Fairing Installation Date of the ICON Satellite is 17 October 2018.


The Producing Instruments of the AVTP and AVMP retrievals Data Products is Cross-track Infrared Sounder and the Advanced Technology Microwave Sounder suite (CrIMSS).


The Design of the SWiPS Sensor is Compact.


The Function of the Photo MOSFET Switch Component is Capacitor discharge.


The Global Observation Frequency of the TOMS Total Ozone Mapping Spectrometer is Daily.


The Certification Date of the SpaceX Crew Dragon Spacecraft is November 11, 2020.


The Design Lifetime of the SIMBA Satellite is 3 years.


The Components of the CDRA Orbital Replacement Unit is Two beds known as a Desiccant/Adsorbent Bed Orbital Replacement Unit.


The Intrinsic Range Resolution of the KaRIn Radar is 75 cm.


The Flight Heritage of the HiSPiCO S-band Transmitter/Transceiver is Sounding rocket.


The Polarized Channels of the VNIR Sensor is 2.


The Thesis URL of the AAUSAT3 Satellite is http://www.crn2.inpe.br/conasat1/projetos_cubesat/projetos/AAUSAT-3%20-%20Aalborg%20University%20-%20Denmark/AAUSAT-3%20-%20ADCS%20-%20Attitude%20Determination%20and%20Control%20System.pdf.


The Project Status Meeting Date of the Jason-1 Satellite is Oct. 18-20, 2010.


The Instantaneous spectral coverage of the Spectrometer Instrument is 3.58 km/s.


The Dimensions of the Iceberg B-22 Iceberg is 85 km long and 64 km wide.


The Operational Lifetime of the GOES-R Satellite is 10 years.


The Spectral Range (µm) of the Band 3 Spectral Band is 3.55 - 3.93.


The Components of the Command Communications System Communication System is VHF command receiver, pair of redundant UHF command and telemetry transceivers.


The Movement of the Telescope System Satellite Component is Along-track, across-track, or both.


The Data Management of the COSMOS Mission Operations System is Data transfer, data processing, data archiving.


The Signal Types of the QuakeSat Satellite is Approximately 25.


The ISPR of the PM Satellite Component is 12.


The Purpose of the LEO Low Earth Orbit is Weather and reconnaissance.


The Global Service Availability of the OneWeb Satellite Constellation is 2022.


The Resolution of the Radiometer Instrument is 40 km.


The Steering of the C-RADAR Phased Array Antenna System is 2-D electronic.


The Frequency of the L-band Transmitter Radio Transmitter is 1700 MHz.


The Altitude of the Swarm-A and Swarm-C Satellite Constellation is 468 km.


The Volume Occupation of the Sail Subsystem is Lower 2/3 of the spacecraft.


The Orbit Inclination of the GRIFEX 3U CubeSat is 99.12º.


The Processor MIPS of the MPM Main Processor Module is 42 MIPS.


The Wavebands of the R3 spacecraft CubeSat is Visible to near-IR.


The Nutation Rate of the O/OREOS nanosatellite Satellite is 4-5 rpm.


The Measurement of the WISPR Instrument is Solar Corona Structure.


The Height Error Requirement of the TanDEM-X Satellite is 10 m.


The Position Determination Accuracy of the SEXTANT Technology is Expected to be on the order of hundreds of meters.


The Desiccant Addition of the Valves Spacecraft Component is Done.


The Star Trackers of the ADCS Attitude Determination and Control System is 2.


The Mission of the IBEX Spacecraft is Outer heliosphere research.


The Longitude Range of the PRISMA Payload Satellite Payload is 180°W - 180°E.


The Rotation Rate of the MWI Instrument is 45 rpm.


The TDI Mode of the NAOMI Imager is Enabled in the Pan band.


The Purpose of the Sentinel-5P Satellite is Deliver a key set of atmospheric composition, cloud and aerosol data products for air quality and climate applications.


The Distance from Earth of the Chamaeleon I Star-forming Region is Around 550 light-years.


The Vertical Accuracy of the In-flight simulated radar interferometry experiment Experiment is 1 m.


The Operation al Concept Presentation Date of the PAZ Ground Segment Ground Segment is June 3-5, 2014.


The Latitude Coverage of the MLS Microwave Limb Sounder is Complete each orbit.


The Data Rate of the HDR Terminal Communication Equipment is Up to 622 Mbit/s.


The Image Type of the Multispectral Visible Imaging Camera (MVIC) Camera is Color.


The Material of the Primary Sensor Sensor is Niobium C-103.


The Upload Frequency of the IXPE Satellite is Once every three days.


The Header Size of the Processed Science Data Packet Data Packet is 23 bytes.


The Attitude Knowledge Accuracy of the MCS Magnetic Control System is Within 0.1º.


The Polarization of the TEC Antennas Antennas is Right, circular.


The Planned Imaging Area of the Pleiades Satellite is 150,000 km2.


The Total Geometrical Area of Solar Arrays of the CHEOPS Satellite is About 2.7 m2.


The Manufacturer of the SSP Altimeter Altimeter is SSTL/Astrium.


The Launch Date of the EROS-B Satellite is April 25, 2006.


The Plenum Pressure Threshold of the Thruster Propulsion System is 80% of the current main tank pressure.


The Radio Link Speed of the Ground Station Equipment Communication System is 9.6 kbaud.


The Ultimate Fate of the BepiColombo Spacecraft is To circle the Sun indefinitely in the vicinity of the planet.


The Configuration Bitstream Source of the V5QV FPGA FPGA is PROMs.


The Orbit Altitude of the Bion-M1 Spacecraft is 575 km.


The Launch Date of the KANOPUS-V-IK Satellite is July 14, 2017.


The Support Phase Time Period of the Mango Tango Satellite Formation is from 09.09 onwards.


The No. of Bins of the SPIM3 Spectrometer is 68, 136, or 272.


The Equator Crossing Time of the OrbView-2 Satellite is 12:00 hours on descending node.


The Expected Deployment Duration of the Spaceflight SSO-A: SmallSat Express Satellite is Over a period of six hours.


The Ground Stations Downlink Data Rate of the Payload Communication System is X-band at 800, 400, or 200 Mbit/s.


The Mounting Points of the Bus Structure Satellite Component is Star tracker, gyroscopes, High Gain Antenna, Low Gain Antennae, maneuvering thrusters.


The Signal Tracking of the TriG receiver GNSS Receiver is GPS, Galileo, CDMA GLONASS, Compass.


The Provider of the GCOM-W1 Satellite is JAXA.


The Power of the Total Satellite is 13.9 W.


The Establishment Year of the RADARSAT International Ltd. Company is 1989.


The Output Buffer Size of the Transmission Module FPGA Module is 1115 bytes.


The Deployment Time of the Secondary Mirror Support Structure Support Structure is Approximately 1 hour and 36 minutes.


The Absolute Accuracy of the FFRF sensor Metrology Instrument is 1 cm on distance.


The Annual Methane Release of the Kayrros Studies Methane Leak Detection is 20 megatons.


The SAR Interferometry Techniques of the TanDEM-X Satellite is Digital beamforming, single-pass polarimetric SAR interferometry, ATI with varying baseline, or super-resolution.


The Ku-band beams of the Repeater subsystem Communication System is 4 Ku-band beams using a receive-only direct radiating phased array antenna (DRA).


The Presentation Date of the FalconSAT-7 Satellite is Sept. 13-16, 2011.


The Sample Collection Amount of the Chang'e-5 Lander Lander is 0.5 kg from drilling and 1.5 kg scooped from the surface.


The Image Capture Frequency of the MSU-GS Imager is Every 15 minutes.


The Docking Date of the Tianzhou-2 Cargo Spacecraft is 29 May 2021.


The Power Output of the Solar Array Power Generation is Meets the satellite operation requirements.


The Location of the GPM Core spacecraft ground segment Ground Segment is JAXA.


The Data Production of the INCUS Satellite is About 15 times the data of CloudSat.


The Sensor Complement of the HJ-1A Satellite is Wide View CCD Cameras (WVC), Hyperspectral Imager(HSI).


The Power Consumption of the MSU-50 Camera is 6.8 W.


The Analog channel of the STRV-2 DHS Data Handling System is None.


The Signal Processing and Control Module Architecture of the IRIS Satellite is PowerPC.


The Software of the HISat Satellite is App-based, open-source approach to core resource-sharing cellular firmware.


The Calibration Standard of the ISS-RapidScat Scatterometer is Golden standard.


The Attitude Measurement Accuracy of the Spacecraft Satellite is 1-2º.


The SciC Mode Operation of the ADCS Attitude Determination and Control System is +X of the spacecraft towards the velocity direction with +Y of the spacecraft pointing as close as possible towards nadir direction.


The Water Ice Concentration Measurement Range of the Lunar Flashlight Spacecraft is 5 wt% or less to 0.5 wt%.


The Swath Width of the MIS Instrument Microwave Radiometer is ~1,700 km.


The Volume of the PROBA-1 Satellite is 1 m3.


The Variable Retardance with Applied Voltage of the LCVR Liquid Crystal Variable Retarder is Unknown.


The Components of the SIM Science Instrument Module is Focal-plane cameras, ACIS, HRC.


The URL of the IXV Spacecraft is http://www.esa.int/Our_Activities/Launchers/IXV/IXV_spacecraft.


The Start of Imagery Download of the TDRSS Satellite System is April 2010.


The Dynamic Range of the Magnetic Field Sensor Sensor is fT - mT.


The Power of the TCS Thermal Control Subsystem is 2 W.


The Launch Date of the PSLV-C41 Satellite is April 12, 2018.


The Publication Date of the Submerged Sources of Transient Acoustic Emission from Solar Flares Research Paper is 20 September 2020.


The Power of the CSS Instrument is 0.1 W.


The Bus Design of the TanDEM-X Satellite is Extended to allow the formation flight of both satellites.


The Data Usage of the ISS-RapidScat Satellite Instrument is Tropical Cyclone Forecasting.


The Prime Contractor of the OneWeb Satellite Constellation is OneWeb Satellites – a joint venture between OneWeb and Airbus Defence and Space.


The β Angle Variation of the NanoRacks-QB50 CubeSats Satellite is 0-75º.


The URL of the Space Cube 2 Onboard Computer is http://spacewire.computing.dundee.ac.uk/.../takahashi.pdf.


The Heritage of the NewMag Magnetometer is MFI (Magnetic Fields Instrument).


The Launch Date of the VRSS-1 Satellite is Sept. 28, 2012.


The Developer of the Small Analyzer for Neutrals Analyzer is Sweden.


The Swath Width of the Sensor Sensor is 72.4 km.


The Number of Tapes of the MOMS-2P Instrument is 19.


The Pointing Accuracy of the GP-B satellite Satellite is 0.97 µrad RMS (0.2 arcsec RMS).


The Count Rate of the Instrument Sensor is From 200/s (IP) to 104 /s (solar corona) per pixel.


The Range of the Experiment Unknown is 36 nT.


The Angular Resolution of the S-020 XUV Spectrograph is Modest.


The Structure Material of the Infrared Imager Sensor is CeSiC (Carbon-fiber reinforced Silicon Carbide).


The Primary Usage of the QuikSCAT Scatterometer is Measure winds inside distant hurricanes.


The Launch Date of the Polar Scout 6U CubeSat Satellite is December 3, 2018.


The | of the GOES-12 SXI Instrument Instrument is Coronal Imaging with the GOES-12 SXI Instrument.


The Size of the Miniature High-Resolution Imaging Spectrometer Imaging Spectrometer is 360 x 260 x 180 mm.


The Maximum Power Budget of the SERB Nanosatellite Satellite is 20 W.


The Spin Rate of the ELFIN Satellite is 20 rpm.


The Frequency Ranges of the TEC Antennas Antennas is 1250 MHz and 1600 MHz.


The Mass of the SS 433 Cosmic Object is Millions to billions of times the mass of the Sun.


The Number of Free Flyers of the ORS-3 Mission Satellite Mission is 26.


The Anomaly Start Date of the GOMOS instrument Instrument is August 2011.


The Image Span of the NGC 7538 Star Factory is About 50 x 50 arc minutes.


The Components of the ADCS Attitude Determination and Control Subsystem is 3 magnetorquers: two torque rods and one air coil torquer.


The Age of the Integral Spacecraft is 18 years.


The Data Collection to Estimate Extension of the C/NOFS Satellite is 24 hours.


The T1 - Ground Station or User Platform initialized but not illuminated by the downlink, T2 - Ground Station or User Platform illuminated by the (optionally dithered) downlink beam, T3 - Ground Station or User Platform synchronized clock to downlink beam str of the Ground Stations or User Platform States is The Ground Stations or User Platform states are: T1 - Ground Station or User Platform initialized but not illuminated by the downlink T2 - Ground Station or User Platform illuminated by the (optionally dithered) downlink beam T3 - Ground Station or User P.


The Visible Spectral Range / Bandwidth of the SOLSPEC-SOLAR Spectrometer is 285-910/1.6.


The Number of Data Takes of the TerraSAR-X Satellite is Over 12000.


The Cadence of the Electron Spectrum Measurement is 5 minutes.


The Number of Upper-Stage Engine Burns of the STP-2 Mission is Four.


The Imaging Type of the R3 spacecraft CubeSat is Multispectral.


The Collector Segments Arrangement of the IDM Ion Drift Meter is Along the satellite nadir and the orbit normal.


The Function of the ToF (Time-of-Flight) counter Instrument Component is Measure the velocity of particles.


The Full Implementation Approval Date of the SMOS Satellite is Nov. 2003.


The Cost of the NPOESS Satellite Program is Exceed $14 billion.


The Advancements of the Pelican Satellite Constellation is Higher revisit and higher spatial resolution, faster data access and delivery.


The Spatial Resolution of the Instrument Spectrometer is 13.5 km horizontal at nadir for IR bands.


The Mass of the SSRNI Data Acquisition and Registration System is 9 kg.


The Control Methods of the Attitude Control Satellite Subsystem is Magnetorquer-assisted gravity gradient, 3-axis reaction wheels and 3 magnetorquers.


The Thrust Level Increase of the IES Ion Engine System is 25%.


The GPS Occultations of the GNOS Instrument Occultation Measurement Device is More than 500 per day.


The Center Frequency of the Channel 5 Sensor is 36.5 GHz.


The Data Collection Focus of the CIP Instrument is Eclipse time and the transition time from sunlight to eclipse time.


The Instrument Type of the AIRS Atmospheric Infrared Sounder is Multi-aperture, non-Littrow echelle array grating spectrometer configuration.


The Downlink Time of the Sentinel-3 Satellite is Approximately 6 minutes per orbit.


The End of Life of the S3B Satellite is 2028.


The Launch Date of the PSLV-C35 / SCATSAT-1 Satellite is Sept. 26, 2016.


The Capacity of the Lithium-ion battery Power Source is 60 Ah.


The Coordination of the Commercial Partners Hisdesat and Airbus DS is Required.


The Orbit Period of the HORYU-4 Nanosatellite is 96.2 minutes.


The Image Resolution of the ASAP-Light Camera System is 4 Mpixels.


The CEO of the Iridium Satellite Operator is Matt Desch.


The Battery Charging Time of the NextSat Satellite is Within a single orbit.


The Sensitive Area of the IS Diaphragm is 100 cm2.


The Presentation Authors of the Lunar Reconnaissance Orbiter Satellite is Jan McGarry, Tom Zagwodzki, Ron Zellar, Carey Noll, Greg Neumann, Mark Torrence, Julie Horvath, Bart Clarke, Randy Ricklefs, Mike Pearlman.


The Function of the Ion Propulsion Assembly (IPA) Propulsion System is Compensated for the drag force experienced by the satellite’s orbit in real-time.


The Measurement Accuracy - Intensity of the Instrument Sensor is 10%.


The Swath Width of the MSC Camera is 51 km.


The Telemetry Data Rate of the AltiKa Altimeter+ Radiometer is 43 kbit/s.


The Small Window Imaging Area Pixels of the CCD Image Sensor is 100 x 100.


The Material of the Baffles Instrument Component is Same material as the heatshield first layer.


The Test Masses Relative Acceleration of the LISA Pathfinder Spacecraft is Lower than ten millionths of a billionth of Earth's gravity.


The Deployable Drag Sail Area of the 3U CubeSat Satellite is 10m2.


The Spatial Resolution of the MSU-MR Instrument is 1 km.


The Sun Sensors of the ADCS Attitude Determination and Control System is 4.


The Launch Provider of the NPP Satellite is ULA.


The Downlink Speed of the AprizeSat-3 and AprizeSat-4 Satellites is Up to 300 kbit/s.


The Accuracy of the Star Tracker Attitude Determination Device is < 7 arcsec RMS cross-boresight, < 70 arcsec RMS around boresight.


The Transmission Protocol of the UHRIT Data Dissemination System is DVB-S2 (Digital Video Broadcasting-Satellite-Second Generation).


The Total Weight of the ExoMars 2016 Trace Gas Orbiter and Schiaparelli Spacecraft is 4.300 kg.


The Modules of the TSCT Terminal is Data enquiry, data purchase, data acceptance, and the personal center.


The Flatness of the Grating Optical Component is 10 λ (6348 nm).


The Detector Type of the EPI-Lo Electron Detector is SSDs (Solid State Detectors).


The Structure Height of the Clementine Spacecraft is 1.88 m.


The Dynamical Disturbances of the Test Masses Satellite Component is < 3 x 10-14 m s-2 Hz1/2 @ 1 mHz.


The FOV of the Limb Imager Telescope is 5.67° x 0.91°.


The Effective Si Thickness of the X123-SDD X-ray Spectrometer is 0.5 mm.


The Mass of the Jupiter Planet is Over 300 times that of Earth.


The Number of Payloads of the FY-3E Satellite is 11.


The Redundancy of the OBC On-Board Computer is Cold dual-redundant.


The Program Motivation of the ISERV Satellite is Timely access to data.


The Function of the MMO Mission Management Office is Plan user requests for payload (SAR) tasking.


The Launch Date of the Arachne Satellite is Early 2025.


The Predicted Power Levels of the IXV Spacecraft is 700 W.


The Power of the Voltage 3 Digital is 1.93.


The Developer of the ROLO Robotic Lunar Observatory is USGS (United States Geological Survey).


The Ground Stations of the XMM-Newton Satellite is Perth, Kourou, Villafranca, Santiago.


The Development Start Date of the Airborne Lunar Spectral Irradiance (Air-LUSI) Instrument is 28 October 2020.


The Principal Investigator of the LOLA Lunar Orbiter Laser Altimeter is David E. Smith.


The Orbit Life With Balloon of the AeroCube-3 Satellite is 2-3 months.


The Perigee of the Deimos-1 Satellite is ~ 642 km.


The Key Unknown of the Kinetic Impactor Technique Asteroid Deflection Method is Beta.


The Launch Date of the REXJ Astrobot is July 21, 2012.


The Components of the ADCS Attitude Determination and Control Subsystem is Three magnetorquers, a single momentum wheel, a translation stage.


The Tracking Reliability of the CHOMPTT Satellite is Only reliable when the SLR facility is in darkness.


The Number of Channels of the HSB Humidity Sounder is 4.


The Orbit Type of the JL-1-GF03B Microsatellite is SSO.


The Water Ice Abundance of the Comet Celestial Body is 10-15%.


The Frequencies of the DOR Tones Signal is Typically at 1 MHz and 2f0.


The Revisit Period of the Constellation Satellite Constellation is 24 hours.


The Distance from Neutron Star of the Gaseous Atmosphere Atmospheric Feature is 1,500 miles.


The Data Rate of the Data downlink Data Transmission is 2 x 50 Mbit/s.


The Objective of the HJ-1 minisatellite constellation Satellite Constellation is Establish an operational Earth observing system for disaster monitoring and mitigation using remote sensing technology and to improve the efficiency of disaster mitigation and relief.


The Function of the EPC Layer Software Layer is Control task.


The Working Life of the Copernicus Sentinel-1 Satellite is Exceeded.


The Power of the Earth Radiation Budget Experiment (ERBE) Instrument is 50 W (average) per scanner.


The Mass (kg) of the COSMO-SkyMed Satellite is 1700.


The Function of the Ka-band payload Communication System is Receive, switch, amplify and transmit microwave signals.


The Components of the MEX Experiment Module is Memories, linear and optoelectronic devices, power MOSFETs.


The Fiber Optics Link Speed of the MIRAS Satellite Payload is 110 Mbit/s.


The Instrument of the DMC-3 Satellite Constellation is PAN (BJ-2).


The Junction Type of the Device Photo Diodes is P-type in an n-type substrate.


The Contract Date of the Ball Aerospace Company is Feb. 12, 2014.


The Data Distribution of the Satellite GFO is NOAA (and NASA) for distribution and use by the civilian community.


The Components of the Spacecraft Emulator Testing Equipment is Flight representative STRx Transceiver, OBC emulator development board, Antennas.


The Coverage of the TeLEOS-1 Satellite is Equatorial belt.


The Test Phase of the D-Sat Satellite is LEOP (Launch and Early Operations Phase).


The Modes of the RA-1 Instrument is Ocean mode and ice mode.


The Test Status of the Interferometer Subsystem is Completed.


The Telescope Primary Mirror Aperture Diameter of the WV-3 Imager Imager is 110 cm.


The Nominal Life of the Spacecraft Satellite is 1 year.


The Area of the Yaguas National Park National Park is 2 million acres (809,370 ha).


The CAVIS Ground Resolution of the WorldView-3 Satellite is 30 m.


The Gd Foil Thickness of the LND Particle Telescope is 20 µm.


The Launch Date of the CBERS 3 Satellite is November 2012.


The Mass of the Kolibri-2000 Satellite is 20.5 kg.


The Power Source of the Spacecraft Satellite is 28V battery.


The Wavelength of the UHF Band is 69 cm.


The Bandwidth of the Channel 1 Sensor is 100 MHz.


The Size of the Rosetta Stone Artifact is 114.4 cm x 72.3 cm x 27.93 cm.


The Thermal Reservoir of the Thermal Management Subsystem Thermal Management System is 1.


The Presentation Date of the NEMO Bus Nanosatellite is April 4-8, 2011.


The Purpose of the MAIA Multi-Angle Imager for Aerosols is Observations of small atmospheric aerosols will be combined with health information to determine the toxicity of different particulate matter types in airborne pollutants over the world's major cities.


The Data Storage Capacity of the SGR-ReSI GNSS Reflectometry Instrument is 1 GByte.


The Reaction Wheel Rotation of the Integral Satellite is Roughly one rotation every 21 minutes.


The Purpose of the MicroMAS Nanosatellite is Provide near-continuous views of severe weather.


The Number of Open Seats of the Crew-4 Spacecraft is 1.


The Leading Scientist of the IASI Satellite Instrument is Cathy Clerbaux.


The Effectiveness of the Hollow Cathode Plasma Contactor Technology is Most effective technology for mitigating charging effects.


The Orbit Insertion Burn Duration of the Juno spacecraft Spacecraft is 30 minutes.


The Modulator Grid of the FSU Faraday Cup Sensor Unit is High-voltage.


The Type of the OTB-1 Satellite is Minisatellite.


The Once per orbit of the Solar Array Rotation is The solar array rotates once per orbit to maintain a nominally normal orientation to the sun.


The Orbital Slot of the GSAT-0209 Satellite is C02.


The Scheduled Date of the Launch Mission Event is 14 March.


The Imaging Mission of the SEOSAT-Ingenio Satellite is High-resolution land imaging.


The Instruments of the Meteor-1/Meteor-2/Meteor-Priroda Series Satellite Mission is 174-K, MR-900B, RMK-2, Chaika, MR-2000, MR-900.


The Temperature Range of the Miniature High-Resolution Imaging Spectrometer Imaging Spectrometer is -40°C to +80°C.


The X-ray Instruments of the AstroSat Astronomy Satellite is 3 co-aligned X-ray instruments.


The Number of TMTC Interfaces of the Heinrich Hertz Satellite is 1150.


The Centers of Expertise Locations of the YES2 Satellite is Fachhochschule Rhein/Ahr Campus, Remagen/Krefeld, Germany; University of Modena & Reggio Emilia, Italy; University of Patras, Greece; and Volgaspace (Samara State Aerospace University SSAU), Samara, Russia.


The Data Usage of the GOSAT Satellite is CO2 levels in all layers of the atmosphere.


The Power of the Sensor Device is 2.24 W.


The Concept Interest of the Satellite Constellation Earth Observation is High.


The Communication Subsystem Radio of the Hope Probe Spacecraft is APL’s Frontier radio.


The Satellite Manufacturer of the Airbus Company is True.


The Mass of the Granada Payload is 5 kg.


The Deployment Date of the Jade Rabbit Rover is Dec. 14, 2013.


The Latency of the ATL14 Antarctica/Greenland Ice Sheet H(t) Gridded Data is 45 days from receipt of last data in product.


The Consortium Members of the Maritime AI-NAV Program is FGI, Aalto University’s Sensor Informatics and Medical Technology group, Fleetrange Ltd.


The Neutron Energy Range of the MGNS Neutron and Gamma-ray Spectrometer is Thermal to 10 MeV.


The Swath Width of the Pléiades Satellite is Larger.


The Imaging Spectrometer of the PROBA Satellite is CHRIS.


The Purpose of the SPDC Quantum Optical Effect is Trace the solar spectral irradiance to Planck’s constant and photon count number.


The NAND Flash of the Stamp9G20 Microcontroller is 128 MB.


The Handover Date of the PROBA-V Satellite is April 30, 2014.


The Lens System of the EXI instrument Imaging Instrument is 48 mm, f/3.6.


The Tuning Range of the FG (Filtergraph) Instrument is ±0.6 Å.


The Number of Countries with Researchers of the International Space Station Space Station is 106 countries.


The Wavelength of the Sub-mm Band is 860 µm.


The Orbit Localization Interval of the WEOS Satellite is 10 s.


The Data Input Rate of the Data Handling System System is 336 Mbit/s.


The Components of the MCCM Control Unit is Digital/analogue ASIC electronics.


The Size of the FREND Instrument is 465 x 380 x 370 mm.


The Launch Center of the RASAT Satellite is Jiuquan Satellite Launch Center in China.


The Latitude of the Noctilucent Clouds Atmospheric Phenomenon is Between 56 and 60 degrees north latitude.


The Feeder Links of the Iridium PRIME Satellite Platform is 2.


The Instruments of the Megha-Tropiques Satellite is ROSA, ScaRaB, SAPHIR, MADRAS.


The Date of the Medicane Ianos Weather Phenomenon is 18 September 2020.


The Age of the Comets Celestial Bodies is 4.6 billion years.


The Launch Date of the Deep Space 1 Satellite is Unknown.


The January 2016 Value of the CO2 Concentration Atmospheric Parameter is 401.1 ppm.


The Development of the SOLISS Satellite Optical Communication System is Collaboratively developed by Sony Computer Science Laboratories, Inc. and JAXA Space Exploration Innovation Hub Center.


The Dimensions of the MPA Structure is 71 cm x 71 cm x 76 cm.


The Cube Size of the LISA Pathfinder Spacecraft is 46 mm.


The Functions of the Ground System Ground System is MOC (Mission Operations Center) and DPDC (Data Processing and Distribution Center).


The Operating Temperature of the NIR Detector is 257 K.


The Orbital Period of the Kepler-186f Exoplanet is 130 days.


The Axis of the ISA Accelerometer is Three.


The Mission Status of the BeiDou-1 Satellite is Unknown.


The ΔV of the Deimos-1 Satellite is ~ 20 m/s.


The Inclination of the GCOM-W1 Satellite is 98.2º.


The Quantity of the Tri-TIP Instrument is 4.


The Revisit Time of the Cartosat-2E Satellite is Four-day.


The Type of the Solar Arrays Power System is Triple junction solar cells (GaAs).


The Affiliation of the Bruno N. Calvo Engineer is Unknown.


The Test Type of the CO2M Satellite is Shaker test.


The DRS Duration of the LISA Pathfinder Satellite is 90 days.


The Attitude Control Components of the STPSat-1 Satellite is Momentum wheel, two smaller reaction wheels.


The Spacewalk Elapsed Time of the Poisk ISS Module is 7 hours 19 minutes.


The M-CDR Date of the IXPE observatory X-ray Observatory is July 10, 2019.


The Inclination of the SARAL spacecraft Satellite is 98.538º.


The Mode of Operation of the Poseidon 4 Radar Altimeter is SAR and pulse-width limited modes.


The Formation of the Formation Flying Navigation Strategy is A-train (Aqua in the lead and Aura at the tail).


The Inputs of the TAFF Software Package is GPS data provided by the GPS receiver onboard TDX and, through the ISL, also from the GPS receiver data onboard the TSX.


The SNR of the 4-band CCD Imager Instrument is 641.


The Operation of the Automated Beacon Network Anomaly Detection System is Broadcasts a health message periodically.


The Scheduled Deployment Date of the Cygnus spacecraft Spacecraft is Sunday, July 15th.


The Instrument Delivery of the CLARREO Pathfinder Satellite is 6/2022.


The Separation Date of the ASTRO and NextSat Satellites is April 17, 2007.


The Telemetry Data Investigation Start Date of the Voyager 1 Satellite is 18 May 2022.


The Mission of the MERTIS Thermal Infrared Spectrometer is BepiColombo.


The Function of the GNSS-POD Precise Orbit Determination Instrument is Provide with high accuracy and precision a measurement of the orbital position as needed for the conversion of the measurement of altimeter range into a sea level.


The Mission Duration of the CryoSat-2 Satellite is October 2010 to April 2013.


The Main Mode Ground Resolution of the MRSE Instrument is 25 m.


The Data Transmission Rate of the RF Communications Transmitter is 1.2 kbit/s for the UHF band.


The Investment Minister of the OneWeb Satellite Communications Company is Gerry Grimstone.


The Thermal Control Type of the CASSIOPE spacecraft Satellite is Passive, supplemented with software-controlled operational heaters.


The Mission of the NEOSSat Microsatellite is Asteroid astronomy and Space Situational Awareness experimentation.


The Approval Date of the BRITE-PL Satellite Project is Early 2010.


The Bus Functions of the Restore-L Satellite is Structural support, propulsion, attitude control, data and communications interface and power.


The Attitude Data Acquisition Time of the Procyon Star Tracker is 8 seconds from power-on.


The Data Format of the Modem Processor Signal-Processing Chain is CCSDS AOS (Advanced Orbiting Systems) Transfer Frames.


The Demonstration Requirement of the DSAC Atomic Clock is In-orbit demonstration of the precision timing and navigation capabilities.


The Coarse Pointing Accuracy of the NEMO-AM Satellite is Better than 5°.


The Launch Date of the SVOM Satellite is No earlier than 2020.


The ADCS Malfunction Date of the Monitor-E Spacecraft is Feb. 2007.


The Off-nadir Capability of the Telescope Optical Instrument is ± 15º.


The Program Scientist of the New Horizons Spacecraft is Curt Niebur.


The Main Rocket Motor Usage of the Juno spacecraft Spacecraft is Twice.


The Formation Ranges of the CanX-4 Satellite is 50 m.


The Arrival Date at NASA Plum Brook of the Orion Spacecraft is November 22, 2019.


The developer of the UniSat-1 Satellite is GAUSS (Gruppo di Astrodinamica dell' Universita degli Studi “la Sapienza”).


The Flatness Target of the Euclid Spacecraft is Less than 50 microns.


The Launch Time of the CANYVAL-X CubeSats CubeSats is 03:59 UTC.


The Sensitivity of the CHIPS Spectrometer is High.


The Sampling of the Megha-Tropiques Satellite is At 13ºN,the various orbits come in one single packet following each other ~100 min apart.


The Dimensions of the ALOS-3 Satellite is 9.9 m x 16.6 m x 3.7 m.


The Material of the Desiccant Bed Component is Silica gel.


The Design Life Span of the Yutu Lunar Rover is Three months.


The Host Star Size of the Kepler-186 Star System is Half the size of the sun.


The Operation Status of the AISSat-1 Satellite is Nominal.


The F/No of the Telescope Optical Instrument is 2.8.


The Purpose of the Flight Dynamics Tool Ground Segment Component is Evaluate the navigation data and provides essential data for mission planning.


The Earth Mapping Cycle of the OCO Satellite is 32 days.


The Installation of the Antenna Communication is In a cavity equal to half of a 4U standard volume (211 x 211 x 43 mm).


The Climate Accuracy of the RAVAN Radiometer is Better than 0.3 W m-2 absolute.


The Battery Capacity (BOL) of the CubeSat power module Power Control is 7.2 Whr.


The Instantaneous Field of View of the IFOV Spectrometer is 14.60 µrad.


The Orbit Altitude of the Electron rocket Launch Vehicle is 500 km.


The Function of the ISSAC SOC Space Operations Center is Downlink resultant imagery data and transfer to UND for processing and quick delivery to image requestors.


The Instrument Mass of the DubaiSat-2 Satellite is 50 kg.


The Operational Period of the Trasser AOS Instrument is Until 1990.


The Role of the Martin Popek Individual is Scientific team member.


The Bus Design, Development and Integration of the KOMPSAT-5 Spacecraft is Led by KARI.


The Mission Status of the Odin Satellite is Operational (extended).


The Type of the Solar Cells Power Generation is Triple junction GaAs (Gallium Arsenide).


The Affiliation of the Yoshihiro Tomioka Author is Unknown.


The Electrical Power of the HiSPiCO S-band Transmitter/Transceiver is 5 W.


The Launch Mass of the IRNSS-1D Satellite is 1425.4 kg.


The Patented By of the iMESA Technology is USAFA.


The Frequency in Rotating Mode of the FEP Satellite Device is 1.0 x 10-3 Hz.


The Orbital Period of the ALL-STAR-1 Satellite is ~ 91 minutes.


The Observation Purpose of the SWFO-L1 Satellite is Continuous unobstructed observation of the corona.


The Unknown of the DDCM Dielectric Deep Charge Monitor is Dielectric Deep Charge Monitor (DDCM).


The Expected Data Transmission of the GRIFEX Satellite is Many months.


The Module Size of the Wireless Compose-2 Wireless Network Infrastructure is Roughly the size of a small smartphone.


The Mass of the ORA Offset Reflector Antenna is 16 kg.


The Backup Crew Member of the Crew-4 Spacecraft is Assigned to fill that seat.


The Instrument Lifetime of the Telescope Optical Instrument is 5 years.


The Positioning Errors Reduction with QZSS of the QZS-1 Satellite is More than 30%.


The Launch Date of the Arktika-M N1 Satellite is February 2021.


The Launch Date of the IBEX Spacecraft is 2008.


The FOV Resolution of the WAOSS-B Sensor is 1.11 arcmin.


The Resolution of the Visible Camera Camera is < 0.5 km.


The Spatial Resolution of the SRAL Radar Altimeter is 300 m.


The Data Interface of the ESEO-TriTel EQM Satellite Instrument is CAN (Controller Area Network) open protocol.


The Publication Date of the Atlas zur Interpretation von kosmischen Scanneraufnahmen Book is 1989.


The Geographic Coverage of the POPACS Satellite is Data.


The Storage Capacity of the Mission Operation System Data Processing System is More than 2.5 PB.


The Launch Mass of the Spacecraft Satellite is 730 kg.


The Sensors of the ADCS Attitude Determination and Control System is Redundant set of sun sensors and magnetometers.


The Scheduled Launch of the Patrol Mission Satellite Cluster is End of 2021.


The Data Access of the Vision-1 Satellite is Access to a full archive and new acquisition data.


The Solar Panels Power Generation of the EURECA Spacecraft is 1.5 kW at 28 VDC.


The Trailing Satellite of the GRACE-1 Satellite is December 10, 2005.


The Height of the Pas Moraine Moraine is About 30 meters (100 feet).


The Duration of the SJ-10 Satellite Satellite is About two weeks.


The Cost of the Full-size Earth-observing satellite Satellite is Hundreds of millions of dollars to build, launch, and operate.


The Scanning Beams of the OSCAT-3 Radar Scatterometer is 2 conical scanning beams.


The Calibration of the CERES Instrument is Highly calibrated.


The Altitude of the NanoRacks-QB50 CubeSats Satellite is ~ 400 km.


The Mass of the HawaiiSat-1 Satellite is 80 kg.


The Duty Cycle of the SAR antenna Antenna is 2-3 minutes per orbit.


The Symposium Date of the Flying Laptop Satellite is April 4-8, 2005.


The Data Delivery of the DPE Data Processor Element is HDF-5 formatted file.


The Contract Signing Date of the BepiColombo Mercury Probe is Dec. 5, 2012.


The TU Graz Team of the OPS-SAT Satellite is Composed of GMV and the Space Research Center Warsaw (Poland).


The 4º x 300º of the FOV Sensor is FOV (Field of View) 4º x 300º.


The Channels of the MWRI Microwave Radiometer Imager is 10 channels.


The Geometric Accuracy and Stability of the PROBA-V Satellite is Unknown.


The Mission Objective of the THEMIS Probes Spacecraft is Determine what physical process in near-Earth space initiates the auroras.


The RF Communications of the Spacecraft Satellite is 32 to 256 kbit/s.


The X-ray Spectrometer of the OSIRIS-REx Spacecraft is REXIS.


The Docking Date of the REXJ Astrobot is July 28, 2012.


The System of the Onboard Propulsion System Propulsion System is Dual-redundant.


The Mars Atmosphere Entry of the Schiaparelli Lander is 19 October, 14:42 GMT.


The Range of the spectral band band is 0.58 - 1.0 µm.


The Imaging Frequency of the PROBA-V Microsatellite is Every two days.


The Position Accuracy (RMS orbit) of the S-3 NRT Product is 10 cm threshold with a target of 8 cm (radial).


The Commercial Weather Data Program of the NOAA Agency is Operational.


The Inclination of the Satellite Satellite is 99.049º.


The Data Quantization of the MI Radiometer Instrument is 10 bit.


The Energy Threshold of the EPISEM Instrument is Specific energy threshold is different for electrons and protons.


The Adaptability of the COSMOS Software System is Easily adaptable for adding spacecraft, interfacing with external software, and porting to MOCs.


The Exposure Time of the M-CAM 1 Monitoring Camera is 20 ms.


The Presentation Date of the Hiroyuki Shindou Unknown is Oct. 6-7, 2008.


The Actuators of the ADCS Attitude Determination and Control System is Three in-house designed magnetorquer coils.


The Operation End Date of the Cluster Satellite Mission is December 2014.


The Weight per Unit Area of the Solar Panels Power Source is Half of the traditional solar arrays.


The Diameter of the KELT-11b Planet is 181,600 km.


The Frequency (MHz) of the GPS L1 C/A Signal Carrier is 1575.42.


The Debut Mission of the Grid Fins Control Surface is SpX-5.


The Mission Duration of the Kepler Space Telescope is Three-and-a-half years.


The Telemetry Transfer of the Interfaces Communication is Flawless.


The Ground Segment Ownership of the Helios-2 Satellite is Belgium, Spain, Italy, Greece, Germany.


The GCP Density of the GCP Extraction Approach Image Processing is About 450 GCP per 1000 km2.


The Preamp feedback capacitance of the PHA Detector is 5–75 pF.


The Number of Mirror Shells per Module of the ART-XC Instrument Telescope is 28.


The Launch Date of the Chang'e-5 Moon Surface Sampling Probe is Late November 2020.


The Repeated ground track of the KOMPSAT-3A Satellite is 28days/409revolutions.


The FMC Mode Rotation Speed of the Telescope Optical Instrument is 1.5º/s.


The Ability of the X-rays Communication Medium is Pierce the hot plasma sheath.


The Launch Year of the Tandem-L Satellite is 2022.


The Instrument Calibration Phase Duration of the GP-B mission Mission is 7 weeks.


The Technology Readiness Level of the OEM628 Receiver Receiver is TRL5.


The Mission Status of the NigeriaSat-X Satellite is Operational (extended).


The Problem of the NISP Near Infrared Spectrometer and Photometer is Stopped working in a cold vacuum state.


The Data Receiving Stations of the JERS-1 Satellite is NASDA/EOC (Hatoyama, Japan), Tokai University (Kumamoto, Japan), National Institute of Polar Research, Japan (Syowa, Antarctica), Alaska SAR Facility (ASF, Fairbanks, Alaska), Canada, CCRS (Gatineau, Prince Albert), ESA (Kiruna, Tromsoe), National Researc.


The Experiment Focus of the SJ-10 satellite Satellite is Study on the pre-ignition characteristics, soot emission, and smoke distributions of the overload wire insulation.


The Technology of the EMIT Imaging Spectrometer is Image spectrometer.


The Signal Travel Time of the OSIRIS-REx Spacecraft is Just over 18.5 minutes.


The Testing Start Date of the TET-1 Satellite is July 24, 2012.


The HPBW EL of the Antenna ADS-B Antenna is 73º.


The Launch Date of the James Webb Space Telescope Telescope is Later this year.


The Managing Organization of the SWEAP Science Operations Center (SOC) Center is SAO (Smithsonian Astrophysical Observatory).


The Spatial Resolution Calculation of the Radiometer Sensor is Geometric mean of the minor and major axes of the ellipse projected on the earth, also accounting for earth curvature.


The Operational Temperatures of the FPM Instrument is -40 °C and -10 °C.


The Tracking Station Location of the HTV-7 Cargo Vessel is Guam.


The Noise Measurement Window Length of the SCA Calibration System is 8.5 ms and 10.8 ms.


The Momentum wheel of the ADCS Attitude Determination and Control Subsystem is 0.002 Nms at 2000 rpm.


The Purpose of the Commercial Crew Vehicle Emergency Breathing Air Assembly (CEBAA) Flight Support Equipment (FSE) and Air Recharge Tank Assembly (RTA) Hardware is Critical hardware to support the build of the second set of emergency air supply for commercial crew vehicles, supporting as many as five crew members for up to 1 hour during an International Space Station emergency ammonia leak.


The URL of the Mass Change (MC) Satellite Mission is URL: https://science.nasa.gov/earth-science/decadal-mc.


The Launch Date of the CALIPSO Satellite is Unknown.


The Commissioning Duration of the Spacecraft Satellite is 30 days.


The Testing Status of the Euclid Satellite is Thermal qualification tests completed, mechanical vibration tests upcoming.


The Low-energy Response of the X-ray Satellite Navigation Navigation System is Down to 1 keV.


The Pixel size of the Channel 4 Sensor is 32 km x 32 km.


The Conference Date of the Joint Polar Satellite System Satellite System is June 11-15, 2012.


The Operation of the Space Comb Spectroscopy Setup is Under vacuum conditions.


The Parallelism of the Optical Window Component is ≤5 arcsec.


The Mission Duration of the Spacecraft Satellite is Minimum of 3 years.


The In-Orbit Design Life of the Aeolus Satellite is 36 months.


The Image Stack of the DInSAR Differential SAR Interferometry is 8 TOPS and 8 stripmap images.


The Usage of the CST Microwave Studio® Software is Electric field calculation.


The Plane Orientation of the Imaging Calorimeter Calorimeter is x-plane, y-plane.


The Downlink Data Rate of the Telemetry, Tracking, and Command (TT&C) Communication is 6 Mbit/s.


The Required Thesis Level of the Experiment Space Station Experiment is Master or PhD.


The Thermal Environment Before Separation of the MMO Spacecraft is Low temperature, not illuminated by sunlight.


The Purpose of the GPLTBs Navigation Payloads is Development models of the navigation payloads intended for the Galileo Second Generation (G2) satellites.


The Speed Estimation Accuracy of the In-flight simulated radar interferometry experiment Experiment is 0.05 m/s.


The Regions of the Data Nodes Data Center is Asia, Europe and Africa, North and South America, Australia and Oceania.


The Function of the ESPA Ring Interface is Multifunctional integrating element.


The Spatial Resolution of the MSU-100 Camera is 60 m.


The Attitude Control Computers of the GNB Satellite is 2 ARM7.


The Effective FOV of the Channel 7 Sensor is 24 km x 43 km.


The Manufacturer of the STACEM Satellite is SDL (Space Dynamics Laboratory) of USU (Utah State University).


The Spectral Signatures of the IRIS Satellite is Oxygen and heavier silicon ions.


The Pixel Resolution of the 4-band CCD Imager Instrument is 250 m.


The Revisit Frequency of the Satellite Constellation Constellation is Near the edge of the scan > Near nadir.


The Regions of Interest of the Lunar Flashlight Satellite is Permanently shadowed and occasionally sunlit regions poleward of 80º S latitude.


The Data Rate of the STAFF/DWP Instrument is 3.00 kbit/s.


The Functionality of the Ground Station Ground Station is Collect satellite telemetry data, send satellite tasking requests, retrieve relayed data, and extract ground sensor data.


The Inclination of the Molniya Orbit Orbit is 63.4°.


The Unknown of the Lightning Imaging Sensor (LIS) Sensor is Unknown.


The Data Gathering Start Date of the Space-Based Weather Instruments Weather Instruments is 8 February 2022.


The Ground Interference Frequency of the RAVAN CubeSat is 450 MHz.


The Observation Capabilities of the BILSAT-1 Satellite is Wide Field of Regard.


The Footprint Overlay of the CloudSat and CALIPSO Satellites is About 50%.


The Time to Reach Intelsat 10-02 of the MEV-2 Satellite is Nearly eight months.


The Material of the Chimney Structure is CFRP (Carbon Fiber Reinforced Polymer).


The Altitude of the KOMPSAT-6 Satellite is 505 km.


The Radiometric Bias of the Instrument SAR is ≤ 0.3 dB.


The Function of the DPU Data Processing Unit is Image processing and non-destructive compression.


The Pixel Response Time of the Detector Instrument Component is < 6 ms.


The IF Bandwidth (MHz) of the Antenna Reflector is 200.


The SMIM Location of the LUMIO Satellite is Periselene of the transition orbit.


The Orbit Altitude of the GOCE Satellite is ~260 km.


The Electric Charge of the Neutrinos Subatomic Particles is Neutral.


The Number of Lines of the Calibration Cycle Camera Calibration is 2048.


The Nominal SNR of the Band 3 Spectral Band is 1170.


The Energy Efficiency of the Optical Downlink Communication System is -4.6 dB detected photons/bit or 25-100 µJ/bit.


The Data Availability of the Landsat 1-5 Satellites is All MSS data January 2009.


The Goal of the EIAST Organization is Establish a complete Space Industry within the UAE.


The Angle of Incidence of the TopSAR wide Imaging Mode is 20° - 45°.


The Power Output of the Solar Panels Power Source is 20 KW.


The Measurement Coverage of the SMOS Satellite is Arctic.


The Frequency of the UHF Transceiver Transceiver is 437.365MHz.


The Projection of the CUTE Spectrograph Entrance Slit is 23 arcminutes (23').


The Lunar Orbit Altitude of the Chang'e-1 Satellite is 200 km.


The Required Precision of the AOD Satellite Instrument is 0.05.


The Quantity Launched of the SuperDoves Satellite is 12.


The Spacecraft pointing capability of the ALOS/PRISM Satellite is ±1.5º (in cross-track).


The Percentage of Sky Observed in Four Exposures of the Euclid Reference Survey Survey is 50%.


The Field of View of the 4-band CCD Imager Instrument is 36º, or 500 km swath width.


The Perturbation Forces of the Space Environment Satellite Environment is Solar pressure, drag.


The UHF/VHF omnidirectional antennas of the TT&C Tracking, Telemetry, and Command is 2.


The Spectral Resolution of the Spectrometer Spectrometer is <0.625 cm -1.


The Cross-Calibration Frequency of the CloudSat Satellite is Once in 3 days.


The Overall Length of the COR2 Coronagraph2 Imager is 1348 mm.


The Mass of the ITASat-1 Cubesat is ~8kg.


The Modulation of the X-band Transmitter Transmitter is QPSK.


The Optimal Radial Distance of the PIXIE Satellite is 6 RE.


The Purpose of the SAOCOM constellation Satellite Constellation is Imagery and observations in the fields of agriculture, forestry, weather, hydrology, oceanography, natural resources of land and sea, cartography, geology, mining, soil exploitation and archeology.


The Altitude Range of the Water Vapor VMR Measurement Device is 50 - 110 km.


The Lift-off Date of the Foton microgravity mission Mission is Sept. 14, 2007.


The Exposure of the Observation Data is 40 ks.


The PZ-Surface Function of the H3 and H4 Spacecraft is Location of major mission instruments.


The RAM of the protos Software is 8 kB of RAM.


The Use Case of the CubeSats Satellite is Atmospheric calibration objects.


The Developer of the PHI Instrument is Consortium with major contributions from institutes in Germany, Spain and France, and smaller contributions from Sweden, Norway and Switzerland.


The Required Rotation Rate Knowledge of the ANDERR-MAA spacecraft Satellite is Yes.


The Mission Consortium of the CHEOPS Satellite is University of Geneva and University of Bern.


The Number of Satellites of the Pléiades Neo constellation Satellite Constellation is 4.


The Maximum Battery Power Before 100% Depletion in Orbits of the Satellite Spacecraft is 6 orbits.


The Mission Objective of the Flying Laptop Satellite is Test ten different small-satellite technologies.


The Mission Status of the GF-3 Satellite is Operational (nominal).


The Measured Upper Atmosphere Temperature of the Jupiter Planet is Around 800º Fahrenheit (426º Celsius).


The Picture Interval of the M-CAM 1 Monitoring Camera is Six seconds.


The Functionality Duration of the SMDC-ONE Nanosatellite is Until reentry on 12 January 2011.


The Manufacturer of the MicrOmega Infrared Spectrometer is ESA.


The Data Storage Capacity of the ResourceSat-2 Satellite is 400 GB.


The Orbit Period of the Odin Satellite is 97.6 minutes.


The Measurement Rate of the SPAN Sensors Sensor is Constant.


The Industry Day Date of the GMES Sentinel-1 Satellite is Nov. 2007.


The Function of the Global Positioning System (GPS) Receiver Instrument is Receives tracking signals transmitted by GPS satellites.


The Citation of the SOLSPEC Spectrometer is E. Hilsenrath, in Optical Remote Sensing of the Atmosphere, 1990 Technical Digest Series of the Optical Society of America, Vol. 4, pp. 409-412.


The Number of Satellites of the OneWeb Satellite Constellation is 428.


The Development Date of the USNA MIDN Microdosimeter Instrument Microdosimeter is Unknown.


The Moving Part Mass of the SILEX Terminal is 70 kg.


The Debris Removal Capability of the ELSA-M Spacecraft Servicer is Multiple defunct satellites in a single mission.


The Launch Date of the TechEdSat Satellite is July 31, 2012.


The Project Management of the C&DH subsystem Satellite Subsystem is University of Tokyo, Hokkaido Institute of Technology, Tokyo Metropolitan College.


The Mounting Location of the RCS Pods Reaction Control System is Externally.


The Calibration Frequency of the TIR Instrument Telescope is Every 5 seconds.


The Orbit Stability of the EQUULEUS Satellite is Quasi-periodic.


The Quantum Efficiency (QE) of the NISP IR Detector Detector is Mean specified values.


The Deployment Location of the J-SSOD Satellite Deployer is ISS/JEM ( Japanese Experiment Module)/ Kibo.


The Payload of the Perseus-M1 and M2 6U CubeSats is AIS for ship tracking.


The Environment of the Linear Encoder Sensor is Vacuum-rated.


The Quantity in ADCS controller of the StrongARM SA1110 Processor is 1.


The Antenna Dish Size of the ATLAS Space Operations Ground Station is 3.4 m to 9.1 m.


The Development Responsibility of the µRTU Software Application is SRL.


The Max. Data Rate of the RA-1 Radar Altimeter is 15 kbit/s.


The Camera Supplier of the OPTSAT 3000 Satellite is Elop.


The Multi-mode Capability of the MTP Transponder is True.


The Testing Date of the EO-1 Satellite is Oct. 18, 2004.


The Measurement Domain of the FORUM Satellite is Atmosphere, Gravity and Magnetic Fields.


The Permanent Failure Date of the B1 Segment Antenna Segment is January 2011.


The Momentum Envelope of the CMG Control Moment Gyroscope is 0.8 mNms.


The Size of the Receive Antenna Antenna is 2.2 m dish.


The Locations of the Shocks Phenomenon is Universe around stars, supernova remnants, comets, and planets.


The Digital Resolution of the Cluster S/C Satellite is 7.813 x 10 -3 nT, 3.125 x 10 -2 nT, 0.125 nT, 0.5 nT, 8 nT.


The Latency of the ATL11 Antarctica/Greenland Ice Sheet H(t) Series Data is 45 days from receipt of last data in product.


The Slit Length of the Instrument Spectrometer is 150 arcmin.


The Altitude of the Secondary Payloads Satellites is ~325 km.


The Purpose of the IBEX Satellite is Provide images of the solar system's boundaries.


The Crevice Width of the Philae Lander is 1–1.5 m.


The URL of the SCD-2 Satellite is https://www.wmo-sat.info/oscar/satellites/view/392.


The Bulk Velocity of the Proton Component Measurement Accuracy of the DSCOVR Satellite is 20%.


The Orbital Distances of the TRAPPIST-1 Star System is Within the orbital distance of Mercury.


The Monoscopic Collection Capacity of the GIS Instrument Satellite Instrument is Up to 700,000 km2 of panchromatic imagery, Up to 350,000 km2 of pan-sharpened multispectral imagery.


The L1 Detectors Thickness of the HIT Sensor is 24 µm.


The End of Life Date of the IDEA OSG 1 Satellite is 28 November 2017.


The Collaboration of the Mars Express and ExoMars TGO Mars Missions is At the forefront of the international fleet investigating the Red Planet.


The Far-UV Channel Range of the IRIS Observatory is 133.0–141.0 nm.


The Pixel Resolution of the SPIM4 Spectrometer is 14 bit.


The Pointing Accuracy of the DSP satellites Satellite is <5º.


The Date of the West Lothian Shale Bings Image is 21 March 2022.


The Functions of the OBC On-Board Computer is Processing, reconfiguration and timing.


The Development Date of the Strategic Sites Monitoring Solution Monitoring Solution is 8 October 2020.


The Number of Soundings of the GNOS-2 Satellite is 1000 per day.


The Launch Date of the STPSat-3 Satellite is 20 Nov 2013.


The Location of the SCM Device is In the shade of the spacecraft, at the end of the magnetometer boom.


The Data Collection Time of the TerraSAR-X Satellite is 60 years.


The Hot Gas in Galaxy Clusters Percentage of the Universe Cosmology is 4 percent.


The Spatial Resolution of the WFI Camera is 16 m.


The TT&C of the Bus Satellite Bus is Nominal operations.


The Canting Angle of the SAWs Satellite Component is +55º / 0º.


The Apogee (km) of the Meteor-1-2 Satellite is 690.


The CMG Assembly of the ACS Attitude Control Subsystem is IMPACT 1.1.


The Data Compression of the NMS Neutral Mass Spectrometer is Yes.


The Instantaneous spectral coverage of the Spectrometer Instrument is 1.38 km/s.


The Crystal Axes Orientation of the DBCP Pseudo-depolarizer is Crossed and rotated by 45°.


The S-band of the RF Communications Communication Subsystem is TT&C + ePOP.


The Wavelength Range of the Telescope Optical Instrument is 600 -1000 nm.


The Function of the Bus Satellite Component is Provides the structural, power, and communications interfaces to the payload.


The TAG Site Flexibility of the Spacecraft Satellite is Maximum.


The Distance from the Sun within the orbit of Mercury of the Solar Orbiter Satellite is Around 42 million kilometers.


The Data Rate of the L-band HRPT High Resolution Picture Transmission is 665,400 bit/s.


The Collaboration Invitation Date of the SWOT Satellite is 2 January 2019.


The Main Beam Efficiency (%) of the Antenna Reflector is 85.


The Duration of the TAKE5 mission Satellite Mission is Jan. 31, 2013 - June 19, 2013.


The Visible Energy Transmission of the Optics Assembly Dichroic Mirror is 75%.


The Size of the Comet Leonard Comet is About a kilometer across.


The Capacity of the Battery Assembly Energy Storage is 15 Ahr.


The Role of the Hinode Spacecraft is Sun-watching.


The Launch Date of the ANGELS Nanosatellite is 2019.


The Solar Wind Source Prediction of the Parker Solar Probe Satellite is Daily.


The Downlink Frequency of the RF Communications Communication System is X-band (8345.968-8346.032 MHz).


The Deployment Time of the NanoSail-D2 Solar Sail is 30-45 seconds.


The Affiliation of the MAHRSI Instrument is NRL (Naval Research Laboratory).


The Time Extension Date of the BEAM Space Station Module is 4 Dec. 2017.


The Size of the Earth Radiation Budget Experiment (ERBE) Instrument is 60 cm x 60 cm x 57.6 cm/unit.


The Orbital Average Power of the KaRIN Instrument is ~810 W.


The Missed Lightning in Northern Hemisphere of the TRMM LIS Lightning Detection Instrument is Up to 30% in the warm season months.


The Type of the NorAIS Sensor is Norwegian Automatic Identification System.


The Number of Instruments of the JWST Satellite is 4.


The Quantity of the Dove satellites Satellite is 88.


The Number of Probe Conjunctions of the THEMIS Constellation Satellite Constellation is 154 hours.


The Altimeter Observations of the Geosat Satellite is L. Miller, R. E. Cheney, B. C. Douglas.


The Data Source of the IMERG Rainfall Estimation System is Integrated Multi-Satellite Retrievals for GPM (IMERG).


The Mass of the SRMSat Nanosatellite is 10.9 kg.


The Quantity Needed of the Amazonia-1 Satellite is At least 30.


The Incidence Angle Range of the Scatterometer Sensor is 0 to 48º.


The Inclination of the KOMPSAT-3 Satellite is 98.13º.


The Establishment Date of the Yaguas National Park National Park is January 2018.


The End of Life Date of the Tatiana-2 Satellite is 16 January 2010.


The Unknown of the EROS-B Satellite is Unknown.


The Announcement Date of the OneWeb Satellite Constellation is January 15, 2015.


The Image Quality of the Pleiades 1B Satellite is Unknown.


The RF Communications of the Spacecraft Satellite is 2234.4 MHz.


The Accuracy of the Horizon sensor Sensor is 0.06º (3σ).


The Observation Date of the ISEE-1 and ISEE-2 Satellites is 29 September 1978.


The Response of the APD Avalanche Photodiode is High-speed.


The Observation of the SAGE-II Satellite is Stratospheric ozone decline over the Antarctic.


The Spare Satellite of the NSPO Satellite Provider is Provided in space depending on the launch vehicle capability.


The Entanglement Distance of the Satellite Satellite is Approximately 500 to 1,400 km.


The Launch Date of the PSLV-C31/IRNSS-1E Satellite is January 20, 2016.


The Functionality of the XB1 Bus is GN&C, EPS, Thermal, C&DH, RF Comm, and SSR.


The Spectrum of the Starlink and OneWeb Satellite Constellations is Ka-band.


The Manufacturer of the JUICE Satellite is Airbus.


The Electrical/Functional Allocation of the Sentinel-5P Satellite is Classical architecture.


The Launch Date of the Chang'e-1 Satellite is Oct. 24, 2007.


The Channels of the GPS Receiver Payload Module is 12.


The Polarization Sensitivity of the Grating Optical Component is Less than 20%.


The Type of the TEMPO Instrument is Spaceborne ultraviolet/visible light air quality spectrometer.


The Formation Geometry of the TDX and TSX Satellites Satellites is Pursuit Monostatic Far formation.


The Number of Pixels of the Image Sensor Imaging is 4008 x 2672.


The Spatial Resolution at Nadir of the WV60 imager Imaging System is 0.50 m.


The Point Spread Function Assessment of the OVIRS Spectrometer is Using collimated point and extended sources.


The Structure Shape of the Baumanets-2 Microsatellite is Regular hexagon.


The Launch Time of the Falcon 9 rocket Rocket is 06:17 Pacific Time (14:17 UTC) on 22 February 2018.


The Detector Pixel Size of the Instrument Satellite Instrument is 7 µm x 7 µm.


The Function of the ADCC Attitude Determination and Control Computer is Interfaces with the attitude sensors and actuators and runs the attitude control algorithms.


The Moving Mirror Unit Location of the MSASI Imager is Russia.


The Reflecting Performances Evaluation of the Cube Corner Reflectors (CCRs) Satellite Component is Through the analysis of the FFDP (Far Field Diffraction Pattern).


The Launch Date of the PSLV-C38 / Cartosat-2 Series Satellite Mission Satellite Mission is June 23, 2017.


The Encounter Date of the Solar Orbiter Satellite is 4 June.


The Mass of the Spacecraft Satellite is 447 kg.


The Tracking Method of the Aluminum Spheres Satellite is Radar tracked by the U.S. Space Command and optically tracked by a world-wide network of university students and amateur observers with "Go To" telescopes.


The SAR Bands of the SAR Satellite Satellite is X-band and L-band.


The Attitude Control of the QuickBird-2 Satellite is Low-vibration reaction wheels, three torque rods, and four hydrazine thrusters.


The Starlink Satellites Launch Date of the SpaceX Company is 4 March 2021.


The On-Orbit Performance of the ATMS Instrument is Superior to AMSU.


The Size of the ROBUSTA picosatellite Satellite is 10 cm sidelength.


The Purpose of the Computer Ground Station Equipment is Provide the interface between COSMOS and the ground station for data management, monitor and possibly control the operations of the ground station.


The Project of the Microwave Remote Sensing Small Satellite Satellite is Unknown.


The Population of the Dhaka City is Unknown.


The Number of Bands of the Optical Scanning Design Imaging Spectrometer is 45 bands (spectral campaigns).


The Orbiting Black Hole Mass of the OJ 287 galaxy Galaxy is About 150 million times the Sun's mass.


The Power Source of the Spacecraft Module Satellite Module is Solar arrays and three nickel-hydrogen batteries.


The Rendezvous Sensor Test Date of the ATV-5 Spacecraft is March 18, 2014.


The Composition of the Universe Cosmological Model is ~68% dark energy, ~27% dark matter, ~5% normal matter.


The Position Accuracy (RMS orbit) of the S-1 NTC Product is 5 cm (3D).


The Information Kit Date of the Columbus Space Module is January 2008.


The Test Mass Relative Displacement Measurement of the Laser Interferometer Measurement Device is High resolution.


The Resonant Frequency of the 3D Printed Polymers Material is Unknown.


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


The Required Accuracy of the Mie co-polar channel Channel is 50%.


The Swath Width of the Instrument Satellite Instrument is 35 km (nominal mode).


The Resolution of the Pleiades-1A Satellite is 70 cm.


The Departure Date from Bennu of the OSIRIS-REx Spacecraft is 2021.


The URL of the Chandra X-Ray Observatory Satellite is https://www.nasa.gov/mission_pages/chandra/.


The Bias Estimation of the Overall System System is Use of surface return.


The Sensor Complement of the ERS-2 Satellite is Unknown.


The End of Life Date of the JERS-1 Satellite is 12 Oct 1998.


The Access to Satellites of the Satellogic Satellite Constellation is 10 satellites.


The Launch Year of the KOMPSAT-5 Satellite is 2013.


The Ice Volume of the CryoSat Satellite is 1Gt corresponds to a volume of 1 km3.


The | of the IASI-NG Satellite is IASI-NG (Next Generation),” CNES, URL: http://smsc.cnes.fr/IASI-NG/index.htm.


The Meeting Date of the Swarm Satellite Mission is May 3-5, 2006.


The Type of the DBCP Dual Babinet Compensator Pseudo-depolarizer is Pseudo-depolarizer.


The Stabilization Accuracy of the Attitude Control System Control System is ±10º.


The Conference Date of the MTG Satellites Satellite is June 10 - 14, 2013.


The Truss Structure Material of the ALI Telescope is Invar.


The System Development Date of the PRARE Satellite Observation System is April-Mei 1991.


The Project Philosophy of the ESEO Satellite is Maximize student participation in AIV activities and spacecraft operations.


The Unknown of the SPIRALE Space-based Early Warning Demonstrator is Unknown.


The Review Date of the RHESSI Satellite is August 3, 2003.


The Campaign of the Sentinel-1 Satellite is AgriSAR 2009.


The Manoeuvre Frequency of the PARASOL Satellite is Nearly every month.


The Bus Assembly Type of the LunIR Satellite is 6U CubeSat.


The Orbit of the CM1 Satellite is Low Earth Orbit (LEO).


The Bandwidth Savings of the PhiSat-1 Satellite is About 30%.


The Satellite Navigation Company of the GMV-NSL Company is British.


The Development Schedule of the SWOT Satellite is Optimised.


The Authors of the Cosmic Ray Isotope Spectrometer Spectrometer is E. C. Stone, C. M. S. Cohen,W. R. Cook, A. C. Cummings, B. Gauld, B. Kecman, R. A. Leske, R. A. Mewaldt, M. R. Thayer, B. L. Dougherty, R. L. Grumm, B. D. Milliken, R. G. Radocinski , M. E. Wiedenbeck, E. R. Christian, S. Shuman, H. Trexel, T. T. von Rose.


The Continuous Operation of the Fission Surface Power System Power System is At least 10 years.


The Mean LTAN of the KOMPSAT-3A Satellite is 13:30 hours.


The Gas Purification of the LAXPCs X-ray Proportional Counters is Onboard purifier.


The Resolution of the T2 Zoom-in Camera is 5 km x 5 km.


The Attitude Control of the CeREs Satellite is Precision star tracker and two Sun pointers.


The Components of the Sundancer Spacecraft is Life support systems, attitude control, three windows, on-orbit maneuverability, reboost, and de-orbit capability.


The Download Speed of the Starlink Premium Satellite Internet Service is 150-500 Mbit/s.


The Measurement of the Copernicus Sentinel-5P Satellite is Nitrogen dioxide and other trace gases.


The Primary Instrument of the GEOSAT Satellite is GEOSAT Radar Altimeter (GRAS).


The Function of the On-board Processor Data Processing Device is Real-time radiometric/geometric calibration and image compression for all imaging data.


The Enhancement of the Onboard Atomic Clocks Clocks is More precise.


The Function of the Docking Plate Rendezvous Suite Component is Provides a point of contact on the target for a magnetic capture system, and also provides an optically controlled surface for GNC.


The End of Life Date of the ITUpSat-1 Satellite is 2030.


The System Latency of the DSCOVR Satellite is No more than 5 minutes.


The Orbit Entry Time of the Chang'e-5 Spacecraft is Around 21:45 UTC.


The Length of the Primary Sensor Sensor is 2 m.


The Nominal Attitude of the AOCS Attitude and Orbit Control System is Nadir orientation.


The Function of the OMS Radiometer Radiometer is Deliver highly-accurate temperature, humidity, and precipitation data.


The Launch Date of the Meteor-1-1 Satellite is 26.03.1969.


The Test Date of the Aireon Air Traffic Surveillance System is May 3, 2017.


The Center Frequency (GHz) of the Antenna Reflector is 37.


The Image Scene Length of the Image scene length Spectrometer is 500 km.


The Initial Orbit Type of the Observatories Satellite is Highly elliptical orbits.


The Detection Range of the VIIRS Sensor is Green to near-infrared.


The Emissive Band Wavelengths of the VIIRS Satellite is 3.74, 11.45, 3.75, 4.05, 8.55, 10.76, and 12.01 µm.


The Launch Date of the Kolibri-2000 Satellite is 20 March 2002.


The Geophysical Products of the Tandem-L Satellite is 26.


The Type of the GOES Sounder Instrument is Sounder.


The Investigation Date of the ASGA Solar Cell Experiment Solar Cell Experiment is Dec. 05 - 09, 1994.


The Performance of the MTQ Instrument is 0-4 Nms.


The Workshop Date of the COSMIC-II Satellite is October 21-22, 2010.


The Personnel Needs of the Specialized Asset Trackers Tracking Device is Full time employees for monitoring.


The Lifetime of the SmallGEO Satellite Platform is Up to 15 years.


The Design of the Antenna Communication is Square array of tunable inverted F UHF antennas, and of one stacked circularly polarized L-band patch.


The Objectives of the NISAR Satellite is Study solid Earth, ice masses, and ecosystems.


The Field of View of the Camera System Sensor is 15° x 20.2°.


The | of the G. J. Hurford Author is G. J. Hurford.


The | of the SI Star Tracker Star Tracker is SI star tracker.


The Public Listing Date of the Astrocast Satellite Operator is August 2021.


The Maneuver Time ahead of CALIPSO of the CloudSat Satellite is 15 s.


The Operation Status of the Genesis-2 Satellite is Nominal in 2011.


The Geographical Coverage of the Satellite Satellite is World coverage, with latitudes from 83ºN to 56ºS.


The Unbalance of the Land and Sea Contamination Signal Anomaly is 2%.


The Launch Date of the CeREs CubeSat Satellite is 16 December 2018.


The Type of the Dione Spacecraft is Prototype.


The 3-axis stabilization of the BEESAT-1 Satellite is Yes.


The Total Observation Time of the MOMS-2P Instrument is 25 hours.


The Spectral Bands of the Hyperion Imaging Spectrometer is 220.


The LISS-I Data Downlink Transfer Rate of the Satellite Satellite is 5.4 Mbit/s.


The Orbit Altitude of the KySat-1 Satellite is 705 km.


The Focal Length of the spaceCam c4000 Video Camera is 600 mm.


The Operating Frequency of the Passive Microwave Spectrometer Spectrometer is Near the 118.75 GHz oxygen absorption line.


The Status of the CanX-6/NTS Satellite is Retired, R&D.


The Function of the Attitude Control System Satellite Subsystem is Pointing of the satellite.


The Bandwidth (GHz) of the ICI-11 Radiometer is 10.


The Launch Date of the RAVAN Satellite is Nov. 11, 2016.


The Xenon Pressure of the XTA Xenon Tank Assembly is 186 bar.


The Power Source of the Lander Spacecraft is Lithium ion battery.


The URL of the VRSS-1 Satellite is http://cn.cgwic.com/VRSS-1/english/focus.html#.


The Purpose of the Transport Layer Tranche 1 Satellite Network is Support military communications, surveillance and tracking of enemy targets.


The Battery Recharge of the Safe-mode System System is Possible while it is in operation.


The Current Location of the Voyager 2 Spacecraft is Interstellar space.


The Voltage of the Voltage 5 Digital is 3.8±2%.


The Attitude Stabilization Margin of the HIT-Sat Satellite is About 10º.


The Imaging Capability of the Chandra X-ray Telescope is Capturing intricate details in X-rays.


The Orbit (Altitude) of the Spacecraft Satellite is 628km.


The Lifespan of the Satellite Satellite is 11/12 years.


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


The Publication Date of the Shuttle Radar Topography Mission Satellite Mission is 2003.


The Bathymetry Measurement Depth of the ICESat-2 Satellite is 10 meters or more.


The Swath of the LISS-3 Camera is 140 km.


The Solar Array of the Helios-2A and -2B Satellite is Two Gallium Arsenide panels and three silicon panels.


The Operation Status of the ICIR IceCube Cloud–Ice Radiometer is Normal.


The Period of the Satellite Orbit is 103 minutes.


The Roll/Pitch Pointing Accuracy of the Attitude Control Satellite Subsystem is ±0.3º.


The Quantity of the Reaction Wheels AOCS Actuators is 4.


The End of Operations Date of the GEOS-2 Satellite is January 1970.


The Imaging Date of the MRO Mars Reconnaissance Orbiter is Nov. 1, 2016.


The Observation Modes of the Trace Gas Orbiter Satellite is Solar occultation, Nadir, Nightside.


The Managing Institution of the Carruthers Geocorona Observatory Spacecraft is University of California, Berkeley (UC Berkeley).


The GEO-to-ground Communication Link Speed of the Optical Ground Station Ground Station is 2.8 Gbit/s.


The CCSDS ID of the GSAT-0205 Satellite is 265.


The Size of the EXOpod CubeSat deployers Deployer is 12U and 16U.


The Rotation Period of the Zeta Puppis Star is 1.78 d.


The Field of View of the NAC Narrow-Angle Camera is Smaller portions of the landscape.


The Operational Modes of the MOMA Instrument is 1) Heating of the sample to induce evaporation and/or thermochemical decomposition (pyrolysis) and liberate species into the gas phase, possibly also being preceded by a chemical derivatization step to aid in this gas-phase transition, and 2) Direct inter.


The Launch Date of the Resurs-P1 Satellite is June 2013.


The Radio Frequency of the PhoneSat-2.5 Satellite is S-band.


The Torque Margin of the RDA Deployment System is Not provided.


The Battery Capacity of the NSat Satellite is 5.2 Ah.


The Number of CubeSats of the PSLV-C37 Launch Vehicle is 88.


The Quantity of the Temperature Sensors Sensors is 2.


The Surrounding Gas Temperature of the Black Holes Astronomical Object is More than a million degrees.


The Seeing Diameter of the Acquisition and Tracking Camera (ATC) Camera is 1 arcsec = 65 µm.


The Power Dissipation of the Focal Plane Detector is Less than 1 watt.


The Mission Duration of the Euclid Space Telescope is 6 years.


The Equipment Temperatures of the Satellite Spacecraft is Stable.


The End of Life Date of the ZACUBE-2 Satellite is 27 Dec 2022.


The Mission of the CuSP Satellite is Measure particles and magnetic fields in space, testing the practicality for a network of stations to monitor space weather.


The End of Life Date of the ISS:LIS Lightning Imaging Sensor is 30 Sep 2023.


The Release Date of the SCI Spacecraft is April 5.


The Accommodation Location of the Hosted Military Payload Satellite Payload is South Panel.


The Pointing Precision of the HY-2A Satellite is < 0.1º in pitch, roll and yaw.


The Output Power of the CanX-2 S-band Transmitter/Transceiver is 27 dBm.


The Mass of Payloads of the FAST Program Technology Demonstration Program is Starting at just 1 kg.


The Observation Frequency of the Megha-Tropiques Satellite is Up to 6 overpasses per day.


The Sensor Types of the Pico Dragon CubeSat is Gather data of the temperature, voltage and current of the satellite systems.


The Utilization Plan of the KIBO Payload is Unknown.


The Closest Distance to Stone of the Yutu-2 Rover is 1.2 meters.


The NN Frameworks of the Ubotica CogniSAT-XE1TM CubeSat Board Satellite Device is TensorFlow, PyTorch, Caffe.


The Operation Completion Date of the KIKU No. 8 Satellite is January 11, 2017.


The Magnetometer Installation Date of the Iridium Constellation Satellites Satellite is February 1999.


The Yearly Trajectory Deflection of the Solar System Celestial System is Around 115 km.


The Dimensions of the Microsatellite Satellite is 52 cm x 52 cm x 45 cm.


The Mass of the SESAME Experiments is 1.8 kg.


The Area of the Effective Collecting Area Telescope is 767.93 cm2.


The Components of the Merlin Satellite Device is Two `card-frame' modules, printed circuit boards, lid, base, EMC screen.


The Modes of the OCM Data Transmission System is Real-time and playback.


The Proximity to Sentinel-3A of the CDN2 Site Ground Station is 100 m east.


The Mission Type of the FormoSat-1 Satellite is EO.


The Launch Date of the MANTIS Earth Observation Satellite is 11 November 2023.


The Altitude of the SAOCOM-1A and -1B Satellites is 619.6 km.


The Bus Mass of the Spacecraft Bus (Avionics Module=AM) Satellite is 180 kg.


The Unknown of the Pleiades Satellite is Unknown.


The Function of the Power Distributor Unit (PDU) Subsystem is Distributes the platform power bus to all units of the SAR electronics subsystem, as well as AIU and TGCUs of the antenna subsystem, and powers up these units.


The Downlink Function of the Argos System Satellite Communication System is Acknowledge uplink messages, increase system capacity, transmit broadcasting messages, modulate message length or repetition period.


The Absolute / Relative Scale Factors of the Three-axis diagonal gradiometer Gradiometer is 10 -3  / 10 -5.


The Swath Width of the MESSR Radiometer is 100 km.


The Polarization of the ICI-9 Radiometer is V.


The Authors of the The Global Dynamical Atlas of the Milky Way Mergers Research Paper is Khyati Malhan, Rodrigo A. Ibata, Sanjib Sharma, Benoit Famaey, Michele Bellazzini, Raymond G. Carlberg, Richard D'Souza, Zhen Yuan, Nicolas F. Martin, and Guillaume F. Thomas.


The Trays Material of the QSP-1 Satellite is Aluminum.


The Detectors Quantity of the REM Radiation Environment Monitor is 2.


The Redundant Chain of the TMCU Subsystem is QPSK-B / ATOP-B.


The Type of the Artemis-I Mission is Non-EO.


The Launch Date of the TerraSAR-X Satellite is June 15, 2007.


The Final Impact Velocity of the Schiaparelli Lander is Just under 11 km/h.


The Number of CubeSats of the EM-1 Mission is 13.


The Insight of the Comets Celestial Bodies is Planetary construction yard at these early times.


The Camera Mass of the Pushbroom imager Optics is 13 kg.


The Launch Vehicle of the Jugnu Nanosatellite is ISRO PSLV launcher.


The Dimensions of the INTEGRAL Satellite is (5 x 2.8 x 3.2) m.


The Power of the PEACE Instrument is 5.0 W.


The IFOV/line (pixels/scan line) of the VIRR Visible and Infrared Radiometer is 2048.


The Orbit Shift Distance of the GomX-4B Satellite is 300 km.


The Power Delivery of the Spacecraft Plug-n-Play Avionics (SPA) Standards is Separate 28V power delivery.


The Orbit Inclination of the Genesis-2 Satellite is 64.5º.


The Spatial Resolution of the MWRI Microwave Radiometer Imager is 15-85 km.


The J2000 right ascension (deg) of the B1813-140 Pulsar is 274.006.


The Manufacturer of the MSS Multispectral Scanner is SBRC (Santa Barbara Research Center) of Hughes.


The Manufacturer of the Drag Augmentation Device Satellite Component is Ryokeiso CO., Ltd..


The Landing Site of the Capsule Sample Container is Southern Australian desert.


The Orbit (number of cycles/day) of the Spacecraft Satellite is 15 3/14.


The Mission of the Mars Hope probe Spacecraft is Orbit Mars.


The Operation Mode of the Radiometer Sensor is Integrate-while-scanning.


The Accuracy of the SubWave+ Underground Geolocation System is Few meters.


The Scheduled Flight Date of the HTV-7 Cargo Vessel is Sept. 10.


The Bands of the High Gain Antenna Communication System is Ka-band and S-band.


The Launch Date of the Falcon 9 Rocket is 21 April 2022.


The Sensor Complement of the Satellite Spacecraft is Unknown.


The Post-flight Inspection Date of the IXV Spacecraft is Autumn 2015.


The Opening Date of the ESA Facility Facility is 9 November 2018.


The Launch Year of the Carbonite-2 Satellite is 2018.


The Moon Orbit of the Chandrayaan-2 Spacecraft is 100 km circular polar orbit.


The Data Packet Length of the Science Data Interface Interface is 1024 bytes.


The Resolution Δλ (0.05º slit) of the SPIM4 Spectrometer is 2.1 nm.


The Transaction Time of the CPT Data Processing System is Allocated time.


The Current-Limiting Resistor of the PPPT Circuit is Unknown.


The Descent Duration of the Schiaparelli Lander is Just under six minutes.


The Potential Applications of the STP-H6-XCOM X-ray communications system is Deep space probes, communicating with hypersonic vehicles.


The Orbital Plane Tilt of the Orbital Phase 1 Orbit is 60º away from the Sun direction.


The Redundancy of the CFI Signal Generator Chains Signal Generator is Two chains.


The Launch Date of the Crew-1 Mission is Oct. 31.


The Battery Capacity of the MTM Transfer Module is 12 Ah.


The Launch Date of the GHGSat's Second Satellite Satellite is August.


The Nominal Looking Direction of the SAR Synthetic Aperture Radar is Right.


The Data Rate of the Camera Imaging Device is 336 Mbit/s.


The Date of the Bristol Abloom Natural Event is 4 June 2022.


The Effective FOV of the Channel 2 Sensor is 52 km x 16 km.


The Presentation Date of the TeLEOS-1 Satellite is Feb. 11-13, 2015.


The Imaging Wavelength of the Solar Orbiter Satellite is 17 nm.


The Operator of the CSSS Canadian Space Surveillance System is DND.


The Weight of the CHRIS Imaging Spectrometer is 14 kg.


The Support Level of the Test Station Testing Equipment is Subsystem to SV (Space Vehicle) I&T (Integration and Test) level.


The Housing Dimensions of the MuREM Radiation Monitor is 10 cm x 10 cm x 4.5 cm.


The Side Length of the ESTCube-1 & -2 CubeSat is 10 cm.


The Timers of the MCU Microcontroller Unit is Three 16-bit timers.


The Instrument Mass of the Hyperion Imaging Spectrometer is 49 kg.


The Mass of the Carbonite-2 Microsatellite is ~100 kg.


The Attitude Control Thrusters of the INSAT-2A/2B Satellite is 16.


The Payload Interaction Window of the SOC Satellite Operations Center is Up to 20 minutes before each contact.


The Field of View of the LI Instrument is 16º Ø shifted northward or 84% of visible Earth disk.


The Measurement Domain of the LAICE Satellite is Atmosphere.


The Operation of the OCO-2 Spectrometer is Employ a diffraction grating to separate the inbound light energy into a spectrum of multiple component colors.


The Mass of the CEASE-2 Instrument is 1.3 kg.


The Publication Year of the Observation of the Earth and Its Environment Documentation is 2002.


The Launch of the OSIRISv3 System is Unknown.


The PDR Date of the GCOM-W1 Satellite is March 2008.


The Mass of the NorSat-2 Satellite is 16 kg.


The Size of the ASAP Nanosatellite is 175 x 245 x 100 mm3.


The Housing Location of the SMA Scan Mechanism Assembly is First optic within the telescope optical assembly.


The Constellation Type of the OptiSAR™ Constellation Satellite Constellation is Paired, tandem configuration.


The Image Capture Date of the BepiColombo Spacecraft is 10 April.


The Characteristic Wavelength of the Tandem-L Satellite is 236 mm.


The Full Deployment Time of the NanoSail-D2 Solar Sail is Within just five seconds.


The Bistatic Phase of the TanDEM-X Satellite is March 2015 to September 2015.


The Dust Measurement Concentration of the UVS Instrument is As low as 10-4 per cc.


The Team Members of the HORYU-4 Satellite is More than 30.


The Duration of the Drift Ice Season Natural Phenomenon is January to March.


The Data Collection Start of the ERBE Experiment is 1984.


The Delta-V Capacity of the Bus Satellite Component is More than 154 m/s.


The Ion Energy Channels of the EPE Energetic Particle Experiment is 0.05 - 0.20 MeV, 2.1 - 4.5 MeV.


The Imaging Capacity of the KazEOSat-2 Satellite is Up to 1,000,000 km2 per day.


The Orbit Inclination of the ResourceSat-2 Satellite is 98º.


The Sensitivity of the THD Horizon Detector is 1,500 V/W.


The Data collection rate of the Millimeterwave receiver Receiver is 0.23 – 2.53 kbit/s.


The Downlink Method of the Sentinel-1 Satellite is Laser Communication Terminal unit allowing downlink of recorded data via the EDRS.


The Image Captures of the C3D2 Payload is >100.


The Objectives of the S 321 Satellite is Measurement of the pitch-angle distribution for electrons (20-300 keV) and protons (20 keV - 3 MeV).


The Design Life of the EO-1 Satellite is 2 years.


The Structure Type of the Microsatellite Satellite is Hexagonal prism.


The PPM Slot Rates of the Optical Downlink Communication System is 0.311 – 5 GHz.


The Bandwidth of the Band 6 Spectral Band is 675-685 nm.


The Uplink Data Rate of the Telemetry, Tracking, and Command (TT&C) Communication is 4 kbits/s.


The Imaged Region of the HyperScout Imaging System is Scotland.


The Type of the Orphan Cloud Phenomenon is Isolated cloud in a galaxy cluster.


The Instrument of the RHESSI Satellite is X-ray and γ-ray imaging spectroscopy.


The Operating Wavelength of the IRS Interferometric Radar System is Millimeter.


The Spectral Range of the Instrument Spectral Imager is 5.71-8.26 µm.


The Polarization of the Stripmap Imaging Mode is Single or dual.


The Volume of the Spacecraft Satellite is 20 cm x 20 cm x 20 cm.


The Common Ground System of the JPSS and DWSS Satellites is Yes.


The Required Processing System of the UHRIT Data Dissemination System is Processing system including DVB-S2 equipment.


The Agency of the Sich-2 Satellite is NSAU.


The Capabilities of the X-ray Navigation Navigation System is Position, attitude, and timekeeping.


The Number of Near-Perigee and Apogee Maneuvers of the ARTEMIS Spacecraft is 5 near-perigee and 3 apogee maneuvers.


The Operation Timeframe of the AaSI Instrument is June-August growing season.


The Image Capture Date of the Copernicus Sentinel-3 Satellite is 3 January.


The Data Streams of the Baseband Processor Processor is Two 110 Mbit/s TDMA/DAMA data streams assignable in increments of 64 kbit/s.


The Internet Access Speed of the EUTELSAT KONNECT Satellite is Up to 100 Mbit/s.


The Field of Regard of the Resurs-P1 Imaging Satellite is 950 km.


The Channel Frequency of the MHS Instrument is 183.311 GHz.