The Surface Features of the WISPR Imaging Instrument is Aphrodite Terra, Tellus Regio plateau, Aino Planitia plains.


The End of Mission Date of the SMART-1 Satellite is 3 September 2006.


The Cross-Track Separation of the ANDESITE Satellite is 5 km.


The Data Size of the Camera Imaging Device is 14 bit/pixel.


The Neutron Measurement of the SEDA-AP Instrument is Unknown.


The Payload Calibrations and Experiments Duration of the TeLEOS-1 Satellite is Five months.


The Swath width of the MWTS Microwave Temperature Sounder is .


The Development Status of the IASI-NG Instrument is Critical Design Reviews for Instrument and System aspects completed.


The NESZ of the Capella SAR System is Unknown.


The Dimensions of the SSTL-X50 Satellite Platform is 65 x 65 x 72 cm.


The Managed By of the GFO Satellite is METOC (Meteorological/Oceanographic) Program Office of SPAWAR.


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


The Temperature Stability of the HyperScout® Telescope Telescope is Within 2.5°C.


The Launch Date of the FormoSat-7 / COSMIC-2 Satellite Constellation is 25 June 2019.


The Sunlit Average Power of the UKube-1 Satellite is < 1200 mW.


The Location of the GRNS Team is Applied Physics Laboratory at Johns Hopkins University.


The Mission Count of the SSTL Company is 43.


The URL of the Resurs-P1 Satellite is http://eng.ntsomz.ru/news/news_center/resurs-p_images_gallery_201505.


The Size of the SeaHawk-1 CubeSat is 30 x 10 x 10 cm.


The Orbit of the IRS-1B Satellite is Polar sun-synchronous orbit.


The CubeSat Mounting of the Cygnus spacecraft Spacecraft is External.


The Orbits per Day of the TecSAR SAR is 15.22.


The Lifetime of the Satellite Satellite is 15 years design after IOT.


The Purpose of the Upper Barrel Assembly Satellite Component is Accurately locate and maintain the position of the optical subsystems throughout the life cycle of the instrument, whilst providing acceptable unit level dynamic environments during launch conditions.


The Orbit of the ECOSTRESS Instrument is Precessing orbit of the ISS.


The SST Temporal Sampling Period of the CIMR Radiometer Imager is Sub-daily.


The Last Command Date of the Ulysses Spacecraft is June 30, 2009.


The Repair Effectiveness of the Skylab Space Station is Exceeded expectations.


The Repeat Cycle of the ResourceSat-1 Satellite is 24 days.


The Design of the BBR Instrument Instrument is Physically separated into two units: OU (Optics Unit) and the ICU (Instrument Control Unit).


The Similarity to Earth of the Kepler-1649c Exoplanet is Earth in size and estimated temperature.


The Purpose of the Atomic Hydrogen-Maser Oscillator System Payload is Measure the effect of the gravitational potential on the frequency of a proper clock.


The Observation Parameters of the MWRI Microwave Radiometer Imager is Precipitation, cloud feature, vegetation, soil humidity, sea ice, etc.


The Image Date of the CaSSIS Imaging System is February 4, 2021.


The Number of Users of the FormoSat-3/COSMIC-1 Satellite Constellation is 3,000.


The Estimated End of the Oort Cloud Space Phenomenon is About 100,000 AU.


The Components of the ADCS Attitude Determination and Control System is Magnetometers, Solar array sensors, Magnetorquers, Gyroscope.


The Launch Time of the STPSat-3 Satellite is 01:15:00 UTC.


The FOV of the Band 1 Spectral Band is 400 km x 0.5 km.


The Gap of the Slits Optical Instrument is 30 µm.


The Objective of the OCO-2 Spectrometer is Measure sunlight reflected off the Earth's surface.


The Downlink Time of the Sentinel-1, -2 Satellites is Approximately 16-18 minutes per orbit.


The Planned Mission Duration of the Tiangong Space Lab Space Lab is 40 days.


The Goal for Number of Satellites by 2025 of the Satellogic Satellite Company is 200 or more.


The Primary Use of the Band 5 Spectral Band is SST, day/night clouds.


The Replacement of the MHS Instrument is AMSU-B.


The Experiment of the TU Graz University is Attempting to monitor signals emitted by devices in the 'Internet of Things' from space.


The Modification of the OCO-2 Instrument Verification Process is Seating Vibration followed by an alignment test.


The Mission Type of the Hinode Satellite is Solar Study.


The Instrument Types of the Sich-2 Satellite is Imaging multi-spectral radiometers (vis/IR), High resolution optical imagers.


The Platform of the Alphasat Satellite is Alphabus.


The Type of the LAICA Camera is Lyman Alpha Imaging Camera.


The Data Rate of the X-band transmitter Transmitter is 42.22 Mbit/s.


The Star Intensity Accuracy (3σ) of the STOs and STAEs Analog Electronic units is Random Bias -0.26 ~ +0.28 mag ((@ 6 mag) -0.4 ~ +0.65 mag (@ 6 mag).


The Critical Design Review End Date of the Lucy Discovery Program Mission is Oct. 18.


The Simultaneous Tracking of the SSTI GPS Receiver is Up to 12 GPS satellite signals.


The Number of Satellites of the NSPO Satellite Provider is 12.


The Manufacturer of the CEPA Adapter is Boeing.


The Pixel Count of the Kodak KAI-11002 CCD CCD is 11M pixel.


The Altitude of the Satellite Satellite is 764 - 824 km.


The Hypothesized Origin of the Psyche Asteroid is Nickel-iron heart or exposed core of an early planet.


The Agency of the MOMS Satellite is DLR.


The Beacon Frequency of the Life Raft Survival Equipment is 406 MHz.


The Data Relay Method of the GeneSat-1 Satellite is Encrypted communications through the public Internet.


The Sensitivity of the NIRSpec MIRI Optical Instrument is 5.2 x 10 -22  Wm -2  (2 µm, τ i =100,000 s, R=1000).


The Planned Launch Date of the CBERS-4 Satellite is 2013.


The Swath Width of the Satellite Imaging Satellite is 105 km.


The Number of Spacecraft of the Pléiades Satellite is 2.


The Co-Principal Investigator of the SIMPL Investigation is Walt Mirczak.


The Meeting Date of the Global Change Observation Mission (GCOM) Satellite is 24-26 April 2018.


The Provider of the GPM Core spacecraft Satellite is NASA.


The Flybys of the BepiColombo Spacecraft is One at Earth, two at Venus and six at Mercury.


The Backscatter Sensitivity of the Core Instrument Instrument is 8 x 10-7 m-1 sr-1.


The Total Cargo Delivery of the HTV-7 Cargo spacecraft is 6.2 metric tons.


The Altitude of the Satellite Orbit is 685 km.


The Application Topics of the Pol-InSAR Application is Forest, Agriculture, Snow and ice, Ship detection, Wind and waves, Geological mapping, Urban areas, Landslides/subsidence, Earthquakes/volcanoes, Development of new SAR techniques.


The LTAN Evolution of the Swarm-C (Charlie) Satellite is 9 hours of separation between lower pair and upper satellite at end of life.


The Regulated Voltage of the GHGSat-D Microsatellite is 5 and 3.3 V.


The Pixel size of the Channel 7 Sensor is 32 km x 32 km.


The Components of the Attitude Sensing System Satellite System is Sun sensors, a three-axis magnetometer, and a star-tracker.


The Bands of the Star One D2 Satellite is Ku-, Ka-, C- and X-band.


The Design of the MTVZA-GY Radiometer is Total-power.


The Frequency (GHz) of the ICI-9 Radiometer is 448±3.0.


The Orbit of the IRIS Observatory is Polar sun-synchronous orbit.


The Data Processing Levels of the SMC Center is N0, N1, N2.


The Online Date of the Chinese Earth observation satellites Satellites is Jan. 12, 2017.


The Accommodation Requirement of the ACC (Accelerometer) Instrument is Precise and stable in CoG (Center of Gravity).


The MEOP of the Main Tank Propulsion Subsystem is 31 bar.


The Proton Energy of the GALS-VE Particle Energy Measurement Device is > 1200 MeV.


The Orbit Extent of the Observatories Satellite is Close to Earth to just beyond the moon's orbit.


The Science Data Downlink Capacity of the Spacecraft Satellite is 105 Mbit/s.


The Spatial Resolution of the OLI-2 Sensor is 30 m.


The Distance from Sun of the Solar Orbiter Satellite is About twenty percent of the way from the Earth to the Sun.


The Signal-to-Noise Ratio for Bright Objects of the MSU-100 Camera is 200.


The Distance from the Sun of the Juno Spacecraft is Orbiting Jupiter 10 times closer to the Sun than New Horizons.


The Spectral Resolution Element Sampling of the Spectrometer Instrument is 2.5-3.0 detector pixels.


The Relative Performance Error of the Spacecraft Satellite is < 1.5 arcsec over 1.5 s (95%).


The Function of the MR LR Launch Restraint is Provide a stowed interface for the Main Reflector providing a load path through the composite structure to the spacecraft interface.


The Design Life of the DubaiSat-1 Satellite is 5 years.


The Landing Date of the MASCOT Lander is October 3, 2018.


The Function of the L1-SAIF+ Satellite Message is Augmentation of satellite-positioning signal and shortening the TTFF (Time To First Fix).


The Field of View of the Channels Spectrometer is 45'.


The Sail Deployment of the CanX-7 Satellite is Individual.


The Testing Start Date of the Parachute System Spacecraft Component is 2016.


The Mounting Location of the CREAM Cosmic-Ray Instrument is Externally to the ISS.


The Launch Date of the Vega Launch Vehicle is 29 April 2021.


The Purpose of the Universal Waste Management System (UWMS) Installation and Spare Hardware Hardware is Critical installation and spare items to support operations of the next generation toilet system during the 2021 timeframe.


The Resolution of the MSU-M Multispectral Scanner is 1.0 km x 1.7 km.


The Observation Period of the Wilkins Ice Shelf Ice Shelf is 2006–2009.


The Image Capture Date of the Kanopus-V1 Satellite is 21.01.2013 - 27.01.2013.


The Spectral Range of the TROPOMI Instrument is Ultraviolet to visible and selected bands in near-infrared.


The X-ray Source of the MAXI J1820+070 Black Hole is Point source.


The Field of View of the IRIS Observatory is 120 arcseconds.


The Operational Orientation of the AgCam/ISSAC Imaging System is Local-Vertical-Local-Horizontal (LVLH).


The Altitude of the 46 nanosatellites Satellite is 530 km.


The Agreement Date of the GMES-S Satellite is October 2014.


The Components of the FEU Faraday Cup Electronics Unit is Preamplifiers, FPGA, ADC, HMB.


The Composition of the Hamersley Group Rock Formation is Iron-rich rocks, banded iron formations, dolomites, shales, and volcanics.


The Payload Capacity of the ESPAStar Satellite Platform is Up to six hosted or 12 separable, free-flyer payloads.


The Launch Site of the CANYVAL-X CubeSats CubeSats is SDSC (Satish Dhawan Space Center) SHAR (Sriharikota) on the east coast of India.


The Orbital Period of the Kepler-442b Exoplanet is 112 days.


The Conference Date of the Cross-calibration for KOMPSAT-2 MSC images using EO-1 Hyperion Calibration is April 16-18, 2014.


The Field-of-View of the PanCam HRC Camera is 5° x 5°.


The Solar Array Capacity of the KOMPSAT-6 Satellite is 2.250 kW.


The Manufacturer of the SEPAC Instrument is SwRI (Southwest Research Institute), San Antonio, TX, USA.


The Number of Holes of the Spectrometer Wheel Spectrometer is 14.


The Global Coverage of the Antenna Subsystem Satellite Component is ±80º latitude.


The Launch Vehicle of the NPP Satellite is Delta-2-7920-10.


The Orbit Inclination of the Polar Scout 6U CubeSat Satellite is ~98º.


The Resolution of the Detector CMOS Sensor is 2048 x 2048 pixels.


The Date of the Alaska Ablaze Natural Event is 15 June 2022.


The Boom Length of the MAGIC Magnetometer is 1 m.


The Final Maneuver Date of the Rosetta Spacecraft is 29 September 2016.


The Measurement Accuracy of the LARES satellite Satellite is Accurately reflects Earth's tidal perturbations.


The Start of the Data Compression Imaging System Process is Autonomously as soon as the acquisition of data is stopped.


The Number of Deployment Orbits of the STP-2 Mission is Three.


The Number of AMR Sensors of the SOSMAG Magnetometer is 2.


The Flare List Events with Emission above 12 keV of the RHESSI Satellite is Over 14,000.


The Resolution of the spectral band band is 240 m.


The Development Team of the Space Cube 2 Onboard Computer is T. Takahashi, T. Takashima, S. Fukuda, S. Kuboyama, M. Nomachi, Y. Kasaba, T. Tohma, H. Hihara, S. Moriyama, T. Tamura.


The Launch Date of the SAOCOM-1A Satellite is 2014.


The Atmosphere Color of the Pluto Planet is Blue.


The Unknown of the CrIS Infrared Sounder is Unknown.


The Application of the Argos DCS Satellite System is Sustainable management of marine resources.


The Architecture of the MicroStar avionics Avionics is Largely unchanged.


The URL of the TOPCAT Satellite is https://web.archive.org/web/20120306134455/http://www.bis.gov.uk/assets/bispartners/ukspaceagency/docs/space%20science/cubesats/topcat%20text%20and%20picture.pdf.


The Manufacturer of the Orion spacecraft Spacecraft is Lockheed Martin.


The Evaluation of the GPM/DPR Satellite Instrument is Can be evaluated using ground validation observation network in Okinawa.


The Orbit Knowledge Accuracy of the Satellite Spacecraft is < 3 m rms in each axis.


The Battery Capacity of the EPS Electrical Power Subsystem is 1.8 Ah.


The Payload Volume of the TCS Thermal Control System is 279 x 406 x 254 mm.


The Minimum Looks in Range of the Radar Sensor is 40 looks for 10 km cells.


The Roll Phase Error of the GP-B satellite Satellite is 0.13 mrad RMS.


The Slit Height of the Long Wavelength Band Spectrometer is 2.75 cm; 1/33 for bright target.


The Launch Date of the Yubileyniy-2/MiR Satellite is July 28, 2012.


The Spectral Bands of the HyperScout Imaging System is 400-600 nm.


The Mean Height Values Rate of the GEOSAT Satellite is 1 Hz.


The Polarization of the ICI-8 Radiometer is V.


The Usage of the Vision Aiding or Terrain Sensor Obstacle Avoidance System is Landing phase.


The Mass of the Stars Celestial Bodies is As little as a tenth of our sun’s mass.


The Measurement Domain of the Meteor-1/Meteor-2/Meteor-Priroda Series Satellite Mission is Atmosphere, Snow & Ice.


The Laboratory and Flight Testing of the Chibis-M Microsatellite Satellite is Unknown.


The Antenna Size of the HDR Terminal Communication Equipment is 3.4 m.


The NEΔT (K) of the ICI-4 Radiometer is 0.6.


The Mass Balance Usage of the Integrated Firing Test Test is Not used.


The Mission Purpose of the ASTRO-H Satellite is Give us a new view of the non-thermal processes taking place in the universe.


The Measurement Domain of the QBITO CubeSat is Atmosphere.


The Aperture Diameter of the Telescope Optical Instrument is 5 cm.


The TT&C Downlink of the QSat Satellite is S-band with a data rate of 1 or 100 kbit/s.


The Bandwidth of the C-band Radar Altimeter Frequency Band is 160 MHz.


The Percentage of Global Warming of the CO2 and CH4 Greenhouse Gases is ~90%.


The Application of the Spaceborne GPS Instrument is Limb sounding and global monitoring.


The Inclination of the ELaNa-4 CubeSats Satellite is 40.5º.


The Aperture Shape of the IDM Ion Drift Meter is Square.


The Planetary Transits and Oscillations of stars of the PLATO Space Mission is Upcoming.


The Orbital Separation from SPOT-5 of the SPOT-4 Satellite is 138º.


The Inclination Accuracy of the Bloostar Launch Vehicle is ±0.05º.


The Structure Diameter of the Clementine Spacecraft is 1.14 m.


The Contains of the Ralph Satellite End-body is SEDS (Small Expendable Tether Deployer System) box.


The S-band Downlink Frequency of the MSX Satellite is 2282.5 MHz.


The Contents of the Level-2 Data is Granule scene and global (tile) data of geophysical parameters.


The Close Passes of the Messenger Spacecraft is 3.


The Frequency of the Sub-mm Band is 0.35 THz.


The Scientific Objectives of the EFILE Experiment is Development of the phase-change interfacial hydrodynamic theory by using microgravity environment, to obtain the novel knowledge on the coupling mechanism of evaporation and convection; Understand the gravity effects on the heat and mass transfers of evap.


The Calibration Procedure of the Radiometer System Instrument is Shutter of both channels closed, reference power source applied to one heater, and servo-system used to adjust the power applied to the other until heat flux balance is achieved.


The URL of the PSLV Satellite is https://www.isro.gov.in/2018press15.html.


The Measurement Domain of the ZACUBE-2 Satellite is Land.


The Hardware Cost of the Starlink Satellite Internet Service is $499.


The IAC Presentation Date of the SMOS Mission is Oct. 12-16, 2009.


The Bands of the Advanced Spaceborne Thermal Emission and Reflection Radiometer (ASTER) Radiometer is 4-2-1.


The Science Data Storage Capability of the Spacecraft Satellite is 48 Gbit.


The Ripple Amplification of the Solar Dynamics Observatory Satellite is Three times.


The Mission Duration of the Tandem-L Satellite is 10 years.


The Polarization, Right Swath of the KaRIn Instrument is VV.


The Communication Interface of the EC Digital Signal Processor is 16-bit parallel port.


The Number of Launch Tubes of the Picosa Launcher Satellite Component is 4.


The Mass Classes of the STAFF/DWP Instrument is 1, 4, 12-16, 28-56 amu.


The Number of Beams of the Eutelsat Quantum Satellite is 8.


The Thrust of the Chemical Propulsion Thrusters Orbit Maintenance is 6 to 12.5 N.


The Arrival Date at Guiana of the SEOSAT-Ingenio Satellite is September 25, 2020.


The Spacecraft Volume (After Inflatable and Sail Deployment) of the Spacecraft 3U CubeSat is 128 cm x 330 cm x 330 cm.


The Duration of the BLT Transfer System is Three to four months.


The X-band Resolution of the SAR-XL Payload SAR Instrument is 1m class.


The Data Usage of the ESA's CryoSat mission Satellite Mission is Monitoring mountain glaciers.


The Orbit of the Gaia Satellite is Second Lagrange point, L2, of the Sun-Earth system.


The Retraction Status of the AstroTubeTM Boom Boom is Retracted.


The Telescopes of the ASTRO-1 Satellite Mission is 4.


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


The Potential Adjustment of the Magnetic Field Models Geophysical Models is Send the pole back to Canada.


The Imaging Modes of the SAR-RCM Synthetic Aperture Radar is Single or dual polarisation, quad-polarisation.


The Chamber of the TVAC Testing is Thermal Vacuum.


The Impact of the Signal to Noise Ratio (SNR) Performance Metric is The higher the SNR, the smaller the bandwidth and the highest spatial resolution the better.


The Fast Imaging Time of the AMI Advanced Meteorological Imager is Within 10 minutes for FD (Full Disk) observations.


The Presentation of the Global Change Observation Mission Satellite is Unknown.


The Mass of the OTB-1 Satellite is 138 kg.


The Comparison of the Kuiper Belt Celestial Region is Big brother of the asteroid belt.


The Spectral Range (IR) of the VHRR Very High-Resolution Radiometer is 10.5 - 12.5 µm.


The Number of Experiments of the D-Sat Satellite is 3.


The Observation Start Date of the LIGO/Virgo sensors Sensors is Late 2018.


The Power of the HID Instrument is 2.0 W.


The Horizontal Resolution of the Mie co-polar channel Channel is 10 km.


The Purpose of the GEOTAIL Satellite is Study the processes that initiate magnetic field reconnection in the near-Earth tail and observe the microscopic nature of the energy conversion mechanism in the reconnection region.


The Image Credit of the CaSSIS Instrument is ESA/Roscosmos/CaSSIS.


The Swath Width of the WAOSS-B Sensor is 533 km.


The Battery Discharge of the Integral Satellite is Increased to more than six hours.


The Time Span of the GF-3 SAR Satellite is 29 days.


The Data Download Rate of the Second generation spacecraft UK-DMC-2 and Deimos-1 Satellite is Up to 80 Mbit/s.


The Operating Date of the ISS ship-tracker Satellite is Aug. 26, 2010.


The S/C Structure of the Payload Satellite Payload is Structure design.


The Manufacturer of the Himawari-8 Satellite is Mitsubishi Electric Corporation.


The Interstellar Dust Measurement Period of the Ulysses Spacecraft is 16 years.


The Effective FOV of the Channel 6 Sensor is 26 km x 60 km.


The URL of the MidSTAR-1 Satellite is http://www.usna.edu/Satellite/midstar/downloads/main/PDRfinal.ppt.


The Complex Amplitude Resolution of the Digital Mixer Signal Processing Device is 16-bit.


The Data Generation Interval of the IMERG Data Processing System is Half hourly.


The Sensitivity of the SCM Sensor is 100 nT.


The Launch Date of the SAOCOM-1A Satellite is 2019.


The | of the Canadian Electric Field Instrument (CEFI) Instrument is Overview of the Canadian Electric Field Instrument (CEFI) for Swarm.


The Spatial Sampling of the LI Instrument is < 10 km @ latitude 45º and subsatellite longitude.


The Maximum Power Point Tracking (MPPT) Mode of the NanoPower P60 Power Subsystem is Allows to gain around 20% of the input power.


The Coverage of the Permanently Shadowed Regions Lunar Surface Feature is About three percent of the moon's south pole.


The Pulsation Patterns of the Delta Scuti stars Star Type is Regular.


The Launch Dates of the GOES-N, -O, -P Satellite is May 2006, June 2009, March 2010.


The Image Types of the Optical System Instrument is Panchromatic, multispectral MWIR.


The Period of the FASat-Alfa Satellite is 98.7 minutes.


The Nadir Resolution of the OLS Imaging Sensor is 0.55 km in the VIS range.


The Purpose of the ASIM Observation Instrument is Shed more light on the lightning phenomena.


The End of Life Date of the Badr-B Satellite is 2 years.


The Launch of the Spacecraft Satellite is H-IIA launch vehicle from TNSC.


The Function of the Mirror Calibration Component is Reflects cold 2.7 K cosmic background radiation into the feedhorn.


The Thickness of the Carbon Dioxide Ice Patch Surface Feature is 9 cm.


The Satellite Integrator of the SORTIE CubeSat is COSMIAC.


The Quantity of the Magnetometer Sensor is 3 units.


The Purpose of the GEOTAIL Satellite is Study plasma entry, energization, and transport processes in interaction regions such as the inner edge of the plasma sheet, the magnetopause and the bow shock, and investigate associated boundary layer regions.


The Hardware Paths of the IRNSS Navigation Signal Signal is Main and redundant.


The Modes of the HRV Imager is Panchromatic (PAN) mode and Multispectral (MS) mode.


The Mass of the Total Satellite is 7.49 kg.


The Center Frequency of the Channel 3 Sensor is 23.8 GHz.


The Scintillation Module Size of the Natalya-2M High energy radiation spectrometer is 4.5 cm x 8 cm x 36 cm.


The Science Objectives of the THEMIS Satellite Constellation is Onset and evolution of the macroscale substorm instability, production of storm-time MeV electrons, control of the solar wind-magnetosphere coupling.


The Pixel Scale of the Detector E2V CCD-22 (Frame Store) is 4.13 arcsec/pixel.


The Total system cost of the WorldView-4 Satellite is $850 million.


The Spatial Resolution of the WFC CCD Camera is 125 m.


The Data Downlink Time from Larger Platforms of the HyperScout 1 Hyperspectral Imager is Several hours.


The Connectivity of the Ground Operations Networks Communication Networks is Spacecraft to the PCC (Payload Control Center) at a specific test site; to the Command Center at the Air Materiel Command's Detachment 2/Space and Missile Center, Onizuka AFB, CA; or to the MCC (Mission Control Center) at APL.


The Altitude Range of the Thermosphere Atmospheric Layer is 90 – 1000 km.


The Duration of the Computer System Payload is 10 hours.


The Total Stationkeeping Cost of the ISEE-3 Spacecraft is ~30 m/s.


The Closest Approach Distance of the GRACE Satellites Satellite is 406 meters.


The Signal Threshold of the GMOD Detector is 10 sigma.


The Nominal Input Level of the Antenna Communication System is Unknown.


The Telescope Size of the ASTERIA Satellite is 2.4-inch (6-centimeter).


The Calibration of the PIANO Airglow Camera Camera is Pre-Flight.


The Propulsion Subsystem of the AOCS Attitude and Orbit Control System is Cold gas propulsion subsystem and magnetic torquers.


The NEΔT (K) of the ICI-1 Radiometer is 0.6.


The URL of the Case studies of aerosol retrievals Study is http://glory.giss.nasa.gov/publications/2002_JAS_59_383.pdf.


The Pixel Size of the 4-band CCD Imager Instrument is 10 x 10 µm.


The Launch Date of the CANYVAL-X CubeSats CubeSats is 12 January 2018.


The Altitude at Touchdown of the Hayabusa-2 Spacecraft is 8.5 m.


The Ice Cover of the Landsat 8 Satellite is 82 percent.


The Range of the Unit Communication System is 75000 km.


The Altitude Range of the Nitric Oxide VMR Measurement Device is 80 - 120 km.


The Mass of the Miniaturized X-band transponders Communications System is < 0.300 kg.


The Conference Date of the MTG Satellites Satellite is June 22-24, 2010.


The Capacity of the UPM-1T card Mass Memory is 800 Gbit.


The Ground Stations of the HYPSO-1 Satellite is NTNU Trondheim.


The Revisit Time of the Sentinel-2 satellites Satellite is 5 days.


The Unknown of the Lunah-Map Spacecraft is Unknown.


The Orbit Synchronization Time of the Observatories Satellite is About 2 months after launch.


The Power Consumption of the Cospas-Sarsat search and rescue package Device is 3% of onboard power.


The Data Downlink of the AAUSat-1 CubeSat is Limited amount.


The Dimensions of the Iceberg B-22A Iceberg is 71 km by 45 km.


The Dust Measurement Particle Size of the UVS Instrument is 100 nm.


The Decommissioned Status of the Pirs ISS Module is True.


The Majority Pass Time of the GNOMES-1 Satellite is Over 400 seconds.


The Number of Research Facilities of the JEM Module is 2.


The Dark Matter Percentage of the Universe Cosmology is 25 percent.


The Range Direction Beam Steering of the SIR-C Radar System is 123º.


The MS of the Pushbroom imager GSD is 5.8 m.


The Launch Date of the ZY 1-02C Spacecraft is Dec. 22, 2011.


The Purpose of the Joint Polar Satellite System (JPSS) Satellite System is Collection of global multi-spectral radiometry and other specialized meteorological and oceanographic data.


The URL of the ESTCube-1 Satellite is http://icubesat.files.wordpress.com/2012/06/icubesat-org-2012-c-1-3-_presentation_noorma_201205301151.pdf.


The Number of Pixels of the Band 4 Spectral Band is 800.


The Orbit Type of the Alba Cluster 3 Satellite Cluster is SSO (Polar).


The Bandwidth of the RF communication subsystem Communication is 20 kHz.


The Minimum Optical Pulse Duration of the LI Instrument is 0.6 ms.


The Communication Protocol of the NEMO-AM Satellite is SFL's nanosatellite protocol.


The Developer of the SATTLA-2 PocketQube is Ariel University (Israel).


The Imaging Purpose of the Deployable Membrane Telescope Telescope is Narrow-band imaging of the sun's chromosphere.


The Launch Date of the Landsat-8 Satellite is 2013.


The Prototype Duration of the CIMON Astronaut Assistant is 2 July 2018 to 27 August 2019.


The Aperture Diameter of the Pushbroom imager Optics is 200 mm.


The Ka-band Frequency of the SARAL/AltiKa Satellite is 35.75 GHz.


The Total Energy of the Station Keeping Satellite Maneuver is Roughly half the amount needed for initial orbit raising.


The Launch Date of the Crew Dragon Spacecraft is 15 September 2021.


The Swath Width of the TeLEOS-1 Satellite is 12 km.


The URL of the Chinese satellite Satellite is http://www.nature.com/news/chinese-satellite-is-one-giant-step-for-the-quantum-internet-1.20329.


The Size of the Boulder Geological Feature is 10 m-wide.


The Constellation Size of the NewSat Satellite is 38 operating satellites.


The Operational Modes of the ACS Attitude Control System is Momentum biased stabilization, Nadir optimized pointing, Fixed scan angle.


The Average Power Consumption of the Satellite Satellite is 580 W.


The Orbital Slot of the GSAT-0101 Satellite is B05.


The Bus Design of the QZS-1 Satellite is ETS-8 (Engineering Test Satellite-8) heritage.


The Signal Frequencies of the QZS Satellite is L1-band, L2-band, L5-band, E6-band.


The Sampling Rate of the GPS/MET GPS Receiver is 50 times per second.


The Unknown of the Auroral Particle Instrument Instrument is Unknown.


The Filter Thickness of the NUV channel Spectrometer is 3.00 mm.


The Transit Duration of the KELT-11b Planet is Eight hours.


The Detector Array Size of the HySI Hyperspectral Imager is 512 x 512 pixels.


The Channel Spectral Widths of the IIR Imager is 0.9 µm, 0.6 µm, 1.0 µm.


The Trajectory Phases of the EQUULEUS Satellite is Science phase, forward transfer phase, backward transfer phase.


The Step 2 Operation of the TRUTHS Satellite is HIS (Earth Radiance view) calibrated against the TR at each LD wavelength.


The Altitude of the Computer System Payload is 90,000 feet.


The Design Presentation Proceedings Page Numbers of the Microsatellites Satellite is pp. 20-33.


The Topic of the SCISAT Satellite is Ozone depletion.


The URL of the NovaSAR-1 Satellite is http://www.eotechcluster.org.uk/eotechcluster/documents/novasar-overview-for-rspsoc-sep12.pdf.


The Calibration Function of the GMI Radiometer Radiometer is Transfer standard for the other radiometers of the GPM constellation.


The Mission Life of the Telescope Optical Instrument is 11 years for fuel.


The Max Frame Rate of the Telescope Optical Instrument is 232 Hz.


The Time to Refill the Plenum back to 95% of the Thruster Propulsion System is Approximately three seconds.


The Existence Period of the Ichthyosaurs Marine Reptiles is 250 and 90 million years ago.


The Instrument Mass of the MWHS-II Microwave Humidity Sounder is 60 kg.


The Spatial Resolution of the EXI Camera is Better than 8 km.


The Data Collection Duration of the LPR Radar is 2 days.


The Narrow Band Mode of the Receiver Communication System is ± 6.0 kHz (-1 dB).


The Mission of the MTG-I Satellite is Imaging.


The Front-End Filters Bandwidth of the TOTEM SDR SDR Platform is 10 MHz.


The Power Voltage of the PM Satellite Component is 120 V DC.


The Measurement Objective of the Potential Equipment Set is Measure neutral and charged particles in the ionosphere.


The Band 2 of the RBV Instrument Spectral Band is 0.58 - 0.68 µm.


The Temperature of the Nearside Hemisphere Moon's Hemisphere is Hotter than that of the farside.


The Rotation Period of the Pulsars Neutron Stars is Every few milliseconds to seconds.


The Cooling Temperature of the QWIP Detector Detector is 150 K.


The Position of the Inmarsat S – Europasat / Hellas-Sat 3 Satellite is 39° East.


The Orientation of the Solar Panels Satellite Component is Perpendicular to the sun direction.


The Definition of the Solar Phase of Apsides Angle Orbital Parameter is The angle between the line of apsides projected into the ecliptic plane and the Earth-Sun line.


The Tracking Station Passes of the Odin Satellite is 10 per day.


The Lander Touchdown Time of the MarCO-B Satellite is 11:54 am, November 26th, 2018.


The Battery Type of the SENSE Satellite is Li-Ion.


The Planning Window Length of the RASP Maneuver Planning System is 240 minutes.


The Purpose of the Land Information System Software is Integrate satellite and ground-based data using advanced mathematical techniques to improve performance of weather and climate computer models.


The Age of the FengYun-1C Satellite is Modern.


The Operational Concept of the PRISMA Satellite is Servicing a variety of experimental teams for the flight demonstration of formation flying technologies.


The Authors of the Rosetta Satellite is J.-B. Vincent, M. F. A'Hearn, Z.-Y. Lin, M. R. El-Maarry, M. Pajola, H. Sierks, C. Barbieri, P. L. Lamy, R. Rodrigo, D. Koschny, H. Rickman, H. U. Keller, J. Agarwa, M. A. Barucci, J.-L. Bertaux, I. Bertini, S. Besse, D. Bodewits, G. Cremonese, V. Da Depp.


The Development Start Date of the SMOS Satellite is 1992.


The Optical Path of the TEMPO Instrument is Yellow arrows through the block diagram.


The Usable Volume of the Galaxy Spacecraft is 16.7 m3.


The Size of the HawkEye Ocean Color Instrument is 10 x 10 x 10 cm.


The Repeat Cycle of the SEOSAT-Ingenio Satellite is 38 days.


The Realtime Storage of the Telemetry Data Transmission is Managed during the descent phase.


The Surface Area of the CSS Coarse Sun Sensor is 2 cm2.


The Quantity of the LightSail CubeSat CubeSat is 1 of 10.


The Power Source of the Psyche Spacecraft is Solar Arrays.


The Technical Specification of the Vegetation-2 Instrument is Identical to Vegetation flown on SPOT-4.


The Resolution of the MERSI-RM Radiometer is 500 m.


The Drought Percentage of the U.S. Drought Monitor Report is 99 percent.


The Telescope Focal Length of the ASTRO-H Mission is 5.6 m.


The Funding Period of the AIM spacecraft Satellite is Through September 2018.


The Power of the DC Power Communication System is 12.7 W conditioned power (transmit).


The Duration of Brightness Change of the X-ray Source Celestial Object is About five minutes.


The Energy Range of the ELENA Instrument is E ~20 eV up to E~5 keV.


The Mass of the MI Radiometer Radiometer is 139 kg.


The Battery Life of the Telemetry System System is Eight hours.


The Ground Resolution of the CCD Detector System Imaging System is 0.65 m.


The Sensitivity of the NIRSpec MIRI Optical Instrument is 560 nJy (10 μm, τ i =10,000 s, and λ/Δλ = 5).


The Data Source of the MODIS Imaging Spectroradiometer is NASA EOSDIS LANCE and GIBS/Worldview.


The Station keeping accuracy of the AOCS Attitude and Orbit Control System is Better than ±0.05º North-South/East-West.


The Detector of the DubaiSat-1 Satellite is CCD (Charged Coupled Device).


The Orbit Evolution of the POPACS Satellite is Data.


The Type of the Solar Panels Power Generation is Silicon solar cells.


The Affiliation of the K. Kondo, A. Kuze, T. Hamazaki Individuals is Unknown.


The Polarization of the Satellite Device Unknown is V.


The Dimensions of the WISA Woodsat Satellite is 10 x 10 x 10 cm.


The Number of Detector Pixels of the Short Wavelength Band Spectrometer is 512 x 512.


The Power of the S-band Transmitter Transmitter is 1 W.


The Spatial Resolution of the LWIR Cameras Camera is 348 m.


The Actual Launch Date of the Gaia Satellite is December 19, 2013.


The Technology of the ROSA Roll-Out Solar Array is Scalable solar power array.


The Power Consumption of the CMGs Attitude Control is 220 W.


The Boom Length of the L-band SAR instrument Instrument is 9-m.


The Speed of the ODHS Processor Module Onboard Data Handling System is Up to 200 MIPS.


The Launch Date of the CLARREO Pathfinder Satellite is Late CY2022.


The Number of NMGU of the GIOVE-A Satellite is 1.


The Provider of the DMSP Satellite is NOAA.


The Description of the Model Scientific Model is Describes the gamma-ray emission of pulsars detected by Fermi and combines this information with three parameters that determine the pulsar emission.


The SNR of the PMC-2 Imagers Imaging System is 23~43 db for PAN and 25~43db for MS data.


The Mass (kg) of the SARLupe Satellite is 770.


The Control Interface of the Payload 2 CMOS Camera is I2C bus.


The Subsystem of the C&DH Command and Data Handling is Dedicated processor.


The Launch Date of the ARIEL Satellite is 2029.


The Affiliation of the Frank Preud'homme Engineer is Unknown.


The Data Availability of the Copernicus Sentinel-6 Poseidon-4 Radar Altimeter is Now.


The Ground SAR Image Processor of the X-band SAR payload system Payload System is Included.


The Earth Scanning Time (LAC scenario) of the Instrument Satellite Instrument is 2.5 minutes.


The Detector Pitch of the FLIR Boson camera Thermal Imaging Camera is 12 µm.


The Operation Duration of the LIMS Instrument is About 9 months.


The Frequency (MHz) of the Galileo E5a Signal Carrier is 1176.45.


The Repeat Cycle of the TecSAR SAR is 36 days.


The Integration Status of the Electronics Module Subsystem is Ongoing.


The Understanding of the Galactic Cosmic Rays Cosmic Phenomenon is Remains poorly understood and controversial.


The Last Signal Date of the Philae lander Lander is 9 July 2015.


The Capture Date of the Image Data is 26 October 2019.


The Maximum Mass of the Lunar Flashlight 6U CubeSat Satellite is 14 kg.


The Velocity of the Zeta Puppis Star is About 60 km/s.


The MWIR Band Wavelength Range of the OHIS Imaging System is 3.0 - 5.0 μm.


The Proportional Function of the Extinction Atmospheric is exp(–τ(λ)).


The Average Power of the LWIR Camera Camera is 13 W.


The Resolution of the PAN Imaging System is 0.65 m.


The Operations Budget of the Small space mission Mission Type is May have long since been exhausted at end of mission.


The Quantity of the SpaceBEE Satellite is 12.


The Noise in NIR Channel of the R3 System Satellite is Noticeable.


The URL of the FalconSat-7 Satellite is http://www.usafa.edu/df/dfe/dfer/centers/lorc/docs/FalconSAT07.pdf.


The Pointing Angle of the FUV Instrument Spectrometer is 20º down towards nadir from the -Y axis.


The Launch Date of the Jason-3 Satellite is January 17, 2016.


The Survival of the Bdelloids Species of Rotifers is Can survive year-long droughts in the Sahara desert as well as in the frozen plains of Antarctica.


The Software of the OBC On-Board Computer is FOS (Flight Operations Segment).


The Formation of the B612 Foundation Organization is Unknown.


The Number of Profiles of the FormoSat-3/COSMIC-1 Satellite Constellation is 10 million.


The Coverage Repeat Period of the S/C Satellite is 5.5 days.


The Power Interface of the ESEO-TriTel EQM Satellite Instrument is TriTel PS (Power Supply) board.


The Effect of the SAA South Atlantic Anomaly is Causing technical disturbances in satellites.


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


The Orbit Type of the OrbView-2 Satellite is Sun-synchronous polar circular orbit.


The Search Coil Mass of the ULF Sensor Sensor is 2 kg.


The Interface Type of the FODB Data Interface is Fiber Optic.


The Earth Parking Orbit of the Chandrayaan-2 Spacecraft is 170 km x 45,475 km.


The Dry Mass of the HY-1C Satellite is 429 kg.


The Status Update Date of the SeaWiFS Satellite is Feb. 5, 2010.


The Total Number of Spectral Bands of the MSU-100 Camera is 6.


The f/number of the Imaging Subsystem Telescope is 4.


The Purpose of the ARI Infrared Spectrometer is Optimize measurement of the long-term changes of Earth’s atmosphere and surface.


The Downlink Rate of the CPUT STX S-band Transmitter is Up to 2 Mbit/s.


The Features of the Control Units Satellite Component is A/D (Analog-to-Digital) converters.


The Dynamic Range of the Instrument SAR is 35 dB.


The Impact on NGSO Terminals of the 5G Network Telecommunication Network is Fewer than 1%.


The Bus Voltage Regulation of the SBVR Power Supply is 100 V ± 1 V.


The Quake Duration of the SEIS Seismometer is Unknown.


The Development Team of the Microsized Microwave Atmospheric Satellite (MicroMAS) Satellite is K. Cahoy, R. Kingsbury, E. Peters, A. Marinan, M. Prinkey, E. Wise, P. Dave, S. Paek, C. Pong, D. Miller, D. Sklair, B. Coffee, L. Orrego, E. Main, K. Frey, R. Aniceto, P. Vaidyanathan.


The Mass of the SRMSat Satellite is 10.9 kg.


The Launch Date of the ELSA-d Mission is March 2021.


The Year of Launch of the Jason-1 Satellite is 2001.


The Designers of the NanoSail-D2 Satellite is NASA/MSFC, NASA/ARC, ManTech/NeXolve Corporation.


The Latency of the ATL15 Antarctica/Greenland Ice Sheet dh/dt Gridded Data is 45 days from receipt of last data in product.


The Halo Orbit Duration of the ISEE-3 Spacecraft is Nov. 1978 to June 1982.


The Monitoring Importance of the Ocean Acidification Environmental Phenomenon is Important for climate and environmental policy-making.


The Launch Date of the GRACE Satellite Satellite is March 17, 2002.


The Material of the JUICE Spacecraft is Non-magnetic material.


The Orbit Inclination of the SEOSat Satellite is 98°.


The Transceiver of the SCARAB 1U CubeSat bus is AstroDev Helium-100 UHF/VHF transceiver.


The Antenna Direction of the GPS/MET GPS Receiver is Anti-velocity direction.


The Mass of the HIT-Sat Satellite is 3 kg.


The Mass of the CCD Camera Imaging System is <55 kg.


The Facilities Launch Date of the UK space industry Industry is July 9, 2015.


The Observation Target of the Aditya-1 Satellite is Solar corona.


The Band Frequency of the SARAL/AltiKa Satellite is Ka-band.


The Data Acquisition Duration of the CERES on TRMM Instrument is 9 months.


The Power Supply of the GNB Satellite is 8 W peak and 5.6 W nominal.


The Components of the PCS separation system Satellite Separation System is Two spring loaded rings and a motorized release mechanism.


The Solar Array Power of the MarCO CubeSats Satellite is Approximately 35 W (at 1AU).


The Wind Mass of the Massive Stars Stars is Equivalent of Earth’s mass in a month.


The MS B3 of the Pushbroom imager Spectral Band is 0.62-0.69 µm.


The Typical Value of the BrO Satellite Instrument is 5 x 10 -2.


The Composition of the Normal Matter Cosmological Component is ~5%.


The Presenter of the CO2Image Demonstrator Presentation is Andre Butz.


The Exchange Time with Interplanetary Space of the Exosphere Atmospheric Layer is Monthly time scale.


The Ion Electric Propulsion of the Electric Propulsion Test Subsystem Satellite Subsystem is Isp = 3000 s ± 300 s.


The Mass of the Lemur-2 Nanosatellite is 4.5 kg.


The Design Standard of the Neutron-1 Satellite is 3U CubeSat standard.


The CCD Detector Assembly Cooling of the EUVI Extreme Ultraviolet Imager is Passively cooled by a radiator.


The Uplink Frequency of the CUTE-1.7+APD Satellite is L-band (1268.500 MHz).


The Mass of the TabletSat-Aurora Microsatellite is 25 kg.


The Power Off Period of the Spacecraft Satellite is Until Aug. 30.


The Falcon Rocket Landings of the SpaceX Company is 75.


The Components of the SHU Control and Data Handling Subsystem is Flash FPGA, CPU, telescope CCD sensors (HPC-R,G,B,M), sprite CMOS sensors (LSI-W,N), fish-eye CCD sensor (WFC), bolometer array sensor (BOL), VLF receiver (VLF-R).


The Smile of the System Optical System is Less than 0.5 µm.


The Signal to Noise Ratio of the APD Optical Radiation Detector is Good at room temperature.


The Volume of the OSDP Onboard Signal Data Processor is 0.024 m3.


The Basalt Flows Fill Time of the Von Kármán crater Lunar Crater is ~3.35 Ga.


The Battery Configuration of the Canopus Pipper Satellite is 1S4P.


The Schedule of the NPOESS Satellite Program is Further delays.


The Mission Type of the PSat-2 CubeSat is Non-EO.


The Energy Loss of the Neutron-Hydrogen Collisions Particle Interaction is About half its energy.


The Cadence of the LET-Spectra Measurement is In the range 0.1-430 keV/µm.


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


The Anomaly of the EAIM Subsystem is Occurred on the wheels command of satellite attitude control.


The Manufacturer of the Landsat 9 Satellite is NASA.


The Life Extension of the ESA's science missions Satellite is Extended.


The Standard Interface of the CEASE-2 Instrument is RS-422 or MIL-STD-1553B.


The Provider of the STM Sensor is MSSL (Mullard Space Science Laboratory) of Belgium.


The Radio Type of the SENSE Satellite is S-band.


The Mapping Completion Date of the ERS-1 Satellite is March 1995.


The Attachment of the CALET Telescope is JEM-EF (Japanese Experiment Module Exposed Facility), Port #9.


The Digital Subsystem of the SCATSat-1 Satellite is Redesigned leveraging some of the recent efforts that have resulted in a smaller form factor for the digital system.


The URL of the RADARSAT Constellation Mission Satellite is http://www.asc-csa.gc.ca.


The Design Lifetime of the RTAFSAT-1 Satellite is 3 years.


The On-board data storage of the First DMC generation Satellite is SSDRs (Solid State Data Recorders) capable of storing up to 1.5 GByte of imagery.


The Nozzle Material of the Propulsion System Satellite Component is Aluminum.


The Detection Threshold of the DICE body-mounted magnetometer Magnetometer is >100 nT.


The Visible/Reflected Channels of the AATSR Imaging Radiometer is 0.55, 0.66, 0.87 μm.


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


The Design and Pre-Flight Characterization of the TRUTHS Reference Sensor is Will be optimized to fully utilize the benefits.


The Orbit Determination Data Source of the WEOS Satellite is Onboard GPS receiver, TLE sets provided by NORAD.


The Attitude Stability of the AOCS Attitude Control System is <0.003º/s.


The Experiment Pointing System of the ATLAS-1 Satellite Mission is Orbiter.


The URL of the Eutelsat Quantum Satellite is https://www.esa.int/Applications/Telecommunications_Integrated_Applications/Reprogrammable_satellite_is_ready_for_launch.


The Image Shooting Date of the IKAROS Small Solar Power Sail Demonstrator is June 16, 2010.


The Mass Control Requirement of the Invar Material is Careful attention to mass control.


The Inclination of the OceanSat-1 Satellite is 98.28º.


The Network of the ATLAS Space Operations Ground Station is X- and S-band communications.


The Raw Data Size of the QuakeSat Satellite is 500 MB.


The Activation of the Gyroscopes Attitude Control is Active.


The Budget Lag Date of the ICESat Satellite is January 4, 2010.


The Mounting Method of the Propulsion Equipment Satellite Components is Mounted on a panel inside the launch adapter ring.


The X-band Synthetic Aperture Radar (SAR) of the CHORUS Satellite is ICEYE.


The Spectral Bands of the ROLO Robotic Lunar Observatory is 32.


The Altitude Measurement of the OMPS Sensor is Yes.


The Model of the Processor Satellite Component is TEMIC TSC695 32-bit RISC processor.


The Orbit Altitude of the Satellite Satellite is ~670 km.


The Cells in Series of the Solar Panels Power Source is 34.


The Data Range of the SERVIR Program is Not entirely available through non-commercial entities.


The Temperature of the MIRIS Telescope is Around 200 K.


The Battery Charging System Design of the SpriteSat Satellite is Mistake.


The Measurement Range - Satellite Potential of the ISL Instrument Langmuir Probe is ± 5 V.


The Design Basis of the Euclid Satellite is Experience gained with ESA’s Herschel and Planck missions.


The Battery Capacity of the Power Subsystem Subsystem is 7 Ah.


The Onboard AI Processing Unit of the PhiSat-1 Satellite is Intel® Movidius™ Myriad™ 2 Vision Processing Unit (VPU).


The Meteoroid Flux of the Lunar impact monitoring Monitoring System is Kilogram-sized.


The Energy Steps of the Electron Spectrometer Instrument is 24.


The Fault-tolerant satellite design of the BEESAT-1 Satellite is Yes.


The Location of the CSSS Canadian Space Surveillance System is 22 Wing in North Bay, Ontario.


The Data Transport of the SPA-U Interface is USB 1.1 limited to 12 Mbit/s.


The Li-ion Battery Capacity of the GNB Satellite is 5.3 Ah.


The Project Status Presentation of the James Webb Space Telescope Space Telescope is Phil Sabelhaus, "Project Status for the James Webb Space Telescope Partner's Workshop," JWST Partner's Workshop, Ottawa, Canada, May 19, 2009.


The Tracking Area of the BeaverCube Satellite is Northeastern section of the US coast.


The Observation Capabilities of the TWINS Satellite is 3D spatial, energy, and pitch angle distributions of the terrestrial ring current (RC).


The Thrusters of the Satellite Spacecraft is Micro-newton (µN) cold gas thrusters.


The Thickness of the Solar Panels Power Source is Less than one millimeter.


The Liquid Core Diameter of the Mars Planet is Half the diameter of the planet.


The Base Dimensions of the CMS Instrument is 380 mm x 315 mm x 186 mm.


The Function of the CASPER Autonomy Software Component is Replan activities, including downlink, based on science observations in the previous orbit cycles.


The Thermal Control of the UVNS Spectrometer is Passive cooling to ensure that temperature conditions are adapted to the different requirements of the instrument modules.


The Exploration Mission Duration of the LRO Satellite is 9/16/2009 - 9/16/2010.


The Manufacturer of the Landsat-9 Satellite is Northrop Grumman.


The Capacity of the Lithium-ion Polymer Batteries Energy Storage is 1.2 Ahr.


The Manufacturer of the Payload Satellite Component is EADS Astrium Ltd. and partners.


The Image Capture Date of the Landsat-8 Satellite is May 30, 2021.


The Presentation Date of the Xatcobeo CubeSat is May 12-14, 2010.


The Manufacturer of the Safran/Snecma PPS-5000 Electric Propulsion is Safran/Snecma.


The Effect of the Clusters Solar Phenomenon is Generates an enhanced particle acceleration compared to the isolated plasma cloud.


The URL of the OSIRIS-REx Spacecraft is https://earthobservatory.nasa.gov/IOTD/view.php?id=91494&src=iotdrss.


The Copyright of the eoPortal Website is © 2024.


The Passband Range of the SPIM5 Spectrometer is 589-902 nm.


The Solar Array of the KOMPSAT-6 Satellite is Fixed solar array with one deployable wing.


The Data Bus of the Payload Satellite Payload is LEON II FT MIL-STD-1553, CAN, SpaceWire.


The Sulfur Dioxide Content of the Dobson Unit Unit of Measurement is 0.0285 grams of sulfur dioxide/m2.


The Cone Structure Length of the COMMx Payload is ~1.85 m.


The Global Surface Temperature Data Recording Time of the Sentinel-3B Satellite is Less than 0.9 days at the equator and in less than 0.8 days in latitudes higher than 30º.


The Data Rate of the RAMIS Radiation Detector is 10 MB / day.


The URL of the Dellingr Satellite is https://www.nasa.gov/feature/goddard/2017/nasa.


The | of the Fluxgate magnetometer Instrument is Fluxgate magnetometer.


The Accuracy of the Ion & Electron Temperature Satellite System is < 20% (ρ >10 10  m -3 ).


The Relationship with Plasma Density of the Plasma Drifts Phenomenon is Requires components of drift parallel and perpendicular to the magnetic field to be considered, as well as season, and location with respect to the magnetic equator.


The Battery Type of the EPS Electric Power Subsystem is Lithium-ion.


The | of the Claire Pettersen Individual is Fred A. Best, Douglas P. Adler, Claire Pettersen, Henry E. Revercomb, P. Jonathan Gero, Joseph K. Taylor, Robert O. Knuteson, John H. Perepezko.


The Diameter of the IOL Antenna Reflectors Antenna is 2.85 m.


The Launch Date of the ASTROSAT Space Observatory is Sept. 28, 2015.


The Measurement Method of the OVM Overhauser scalar magnetometer is Proton Larmor precession in a weak magnetic field.


The Modes of the TerraSAR-X NG Satellite is Very high-resolution modes, heritage modes, wide swath modes.


The Spectral Signature of the Osprey Sample Collection Site is Carbon-rich material.


The Instrument Type of the SPOT-5 Satellite is Imaging multi-spectral radiometers (vis/IR), High resolution optical imagers, Precision orbit.


The Conference Location of the NovaSAR-1 Satellite is University of Greenwich, London, UK.


The Sensitivity of the Instrument Photometer is Detects an Earth-size transit of an mv=12 G2V star at 4 σ in 6.5 hours of integration.


The Observation of the New Horizons Spacecraft is Variations in particle fluxes over a wide range of energies and scales.


The Spectral Range of the HSC Spectrometer Spectrometer is 450-1000 nm.


The Latency of the ATL02 Science Unit Data is 2 days.


The Imaging Mission of the SSOT Satellite is High-resolution.


The Orbital Inclination of the Swarm-A (Alpha) Satellite is 87.4º.


The Year of Launch of the SORCE Satellite is 2003.


The Mapping Resolution of the EIS Imaging System is 330 feet (100 m) per pixel.


The Data Volume of the Ground Segment Communication System is 750 Mbit per orbit.


The Period of the ANUSat Satellite is ~90 minutes.


The Test Date of the HEPS Satellite Component is Beginning of the second calibration and validation phase.


The Mass of the Flock-4v Satellite is Not provided.


The Length of the Boom Assembly Assembly is 1.2 m.


The Integration Time of the PMC-2 Imagers Imaging System is 1~96 levels.


The Milestones of the PRISMA Satellites Satellite is Two new milestones achieved.


The Launch Date of the Sich-2 Satellite is April 17, 2007.


The Magnetic Impulse of the Ground-based sensors Sensor is Recorded.


The End of Life Date of the FITSat-1 Satellite is 4 July 2013.


The Mass (kg) of the TerraSAR-X Satellite is 1230.


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


The LEOP Duration of the TeLEOS-1 Satellite is Two weeks.


The Number of Spectrometers of the SOLSPEC-SOLAR Spectrometer is 3.


The Launch Vehicle Utilization of the PODSat Payload Delivery System is Excessive capacity on launch vehicles delivering a primary payload to geostationary orbit.


The Orbital Inclination of the Swarm-C (Charlie) Satellite is 88º.


The Spectral Range of the Instrument Spectral Imager is 8.80-15.39 µm.


The Manufacturer of the TIR detector Detector is TNO, SSTL.


The Beacon Frequency of the RF Communication System Communication System is 436.8475 MHz.


The Dynamic Range of the FIELDS suite Sensor Suite is 140 dB.


The Susceptibility of the CMOS Sensors Sensor is SEU and latchup effects.


The Dissolved Inorganic Carbon of the Marine Chemistry Study Parameter is Unknown.


The Average Efficiency of the Grating Grating is Greater than 60%.


The Observation of the Cluster Satellite Constellation is Magnetic Reconnection Events.


The Pulse period (ms) of the B0540-69 Pulsar is 50.499.


The Altitude in Orbit of the Electric Thruster Thruster is 410 km.


The Principle of the Sensor Gas Sensor is Amperometric three electrode principle.


The Shock Wave Speed of the Tycho Supernova Remnant is Millions of miles per hour.


The Swath Width of the OMI Spectrograph is 2600 km to 725 km.


The Regulated Pressure of the EPTA Electric Propulsion Thruster Assembly is 2.2 bar.


The Press Release Date of the AgNeo Precision Agriculture Solution is 6 March 2020.


The Period of the OrbView-2 Satellite is 98.2 minutes.


The Serial Number of the Rocket 3.3 Rocket is LV0007.


The Spectral Data Utilization of the Focal Plane Camera Component is Less than 20%.


The Use of the PREMOS Instrument is Entry point for GCM simulations.


The Communication Network of the Pléiades-Neo satellites Satellite is EDRS (European Data Relay System).


The Age of the Tropical Rainfall Measuring Mission Satellite is 15 years.


The Image Capture Date of the BepiColombo Spacecraft is 19 April.


The Magnetic Field Range of the iMTQ Magnetorquer is ±63 mT.


The Radar Altimeter System of the Envisat Satellite is RA-2.


The Number of Operational Satellites of the Starlink Satellite Constellation is About 1,350.


The Geological Process of the 67P/Churyumov-Gerasimenko Comet is Mechanical shear stress.


The Role of the Martin Popek Individual is His photographs are proving a very valuable to the team’s research.


The Operating Temperature of the WFS&C Wavefront Sensing and Control Subsystem is < 45 K.


The Accuracy Assured Rate of the STOs and STAEs Analog Electronic units is 0.0608 ± 0.0008º/s (H); 0.005º/s (V).


The Array Size of the NIR Detector is 80 x 640.


The Objective of the Micro-gravity experiment Experiment is Investigate the coupling between heat capillary convection and buoyancy convection, and other phenomena.


The Observation Duration of the TESS Satellite is 27 days.


The Number of Passes Over a Storm of the Weather Satellites Satellite is One or two in an entire day.


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


The Deployment Velocity of the Dispensers Satellite Component is 1 to 2 m/s.


The Number of Sets of the HETG Grating is 2.


The Swath of the IIR Imager is 64 km x 64 km.


The Measurement of the Planck Telescope is Direction of the polarized light emitted by the dust.


The Antenna Type of the Antenna Reflector is Offset Feed Paraboloidal Reflector Antenna.


The Visibility of the Event Celestial Event is About 2,000 years.


The Altitude of the CeREs CubeSat Satellite is 500 km.


The Power of the FGM Instrument is 2..5 W.


The Service Cost of the Starlink Satellite Internet Service is $99 per month.


The Optics Type of the LISS-3 Linear Imaging Self-Scanning Sensor is Refractive optics in four spectral bands.


The User Request of the DPE Data Processor Element is Via the Data Delivery subscription service.


The Spin Rate of the P2 Satellite is Unknown.


The Mass of the BRITE spacecraft Satellite is about 7 kg.


The Sensor Type of the HARP Imaging Polarimeter is Polarimeter.


The Quantity of the Tyvak 61C Satellite is 1.


The Article Date of the Clyde Space Rocket Rocket is Feb. 1, 2011.


The Signal Injection Window of the Time Delaying Transponder Calibration Device is Noise measurement slot.


The AM Mass of the DSX Spacecraft Payload Module Satellite is  180 kg.


The Spectral Bands of the Focal Plane Array Detector Array is Multiple.


The Function of the OBA Instrument Component is Contains all of the instrument optical subassemblies.


The Announcement Date of the Hickson Galaxy Group (HCG16) Satellite is Jan. 30, 2000.


The Presentation Date of the Michelson Interferometer Instrument is May 27-31, 1991.


The Design Life of the GEISAT Constellation Satellite is Five years.


The Door Latch of the CSD Satellite Component is Automatically resettable.


The Frequency Requirement of the SRMSat Satellite is > 90 Hz in longitudinal and > 45 Hz in lateral directions.


The Image Size of the File Transfer Test Communication is 150 MByte.


The Coverage of the Active Schedule Planning Product is Next fourteen 24-hour operational days.


The S/C Launch Mass of the Payload Satellite Payload is 1,900 – 2,100 kg.


The Data of the RADMON Radiation Monitor is Research Data.


The X-ray Emission of the Ophiuchus galaxy cluster Galaxy Cluster is Reveals the edge of a large cavity, carved in the hot gas by the black hole jets.


The Size of the SI-300 Satellite Bus is 1.5 m in diameter and 1.95 m in height.


The Function of the Green City Watch Application is Quantify the CO2 uptake of urban green spaces.


The Assembly of the SIMPL-Microsat Microsatellite is Manual crew member assembly in microgravity of eight subassemblies utilizing minimal tools and simple mechanical and electrical connections.


The Objective of the CRaTER Cosmic Ray Telescope is Characterize the global lunar radiation environment and its biological impacts.


The Presentation Date of the Megha-Tropiques Satellite Mission is November 7-11, 2011.


The Orbit of the SBSS Satellite System is Low Earth Orbit (LEO).


The LTDN of the CartoSat-2D Satellite is Local Time on Descending Node.


The Measurement Model of the ADCS Attitude Determination and Control System is Comprised of sensory inputs and computed attitudes.


The Ion Density of the PAP Plasma Analyzer is 5 x 10^2 ~ 1 x 10^7 cm^-3.


The Sun Angle Constraint of the CHEOPS Telescope is Larger than 120º.


The Altitude of the SCD-2 Satellite is 750 km.


The Altitude at Autonomous Landing of the Hayabusa-2 Spacecraft is About 500 m.


The Number of Private Launch Companies of the China Country is More than 10.


The Testing Period of the ExoMars Mission is Since April.


The UK's Record Maximum Temperature of the Meteosat-10 Satellite is 38.5°C.


The Spatial Acquisition Duration of the Alphasat TDP1 GEO-relay is Reliably achieved within 7 s.


The Function of the SSRU Data Processing Unit is Receive, process, store and transmit the image data.


The Model of the Parker Solar Probe Satellite is WSA model.


The Design Presentation Date of the Star Tracker CubeSat Component is March 3-10, 2012.


The Orbital Commissioning Finish Date of the Satellite Satellite is September 29, 2013.


The Average Number of Jointly Tracked Satellites of the T3000G2 receiver GPS Receiver is 2-3.


The Launch Date of the Indian rocket Rocket is April 15, 2017.


The Mission Status of the Satellite Spacecraft is Unspecified.


The Affiliation of the MAYA-1 1U CubeSat is PHL-Microsat Program of the University of the Philippines Diliman.


The Instrument Power Requirements of the FLP Satellite is Approximately 100 W.


The Thruster Quantity of the EPPS Electric Propulsion Subsystem is 8.


The Components of the Sensor Suite Payload is IMU, magnetometer.


The Transmitted Wavefront Error of the Photon Sieve Optic is λ/10.


The Number of Thermistors of the XMM-Newton Satellite is 8.


The Wind Profile Date of the ISS-RapidScat Scatterometer Instrument is Oct. 3, 2014.


The Type of the S/C Satellite is three-axis stabilized, zero-momentum satellite.


The INR Performance of the GOES N-P series Satellite is Improved.


The Orbit Transfer Method of the LUMIO Satellite is Stable Manifold Injection Maneuver.


The Uplink Data Rate of the TT&C Communications RF Communications is 2 kbit/s.


The Mass of the IOD-1 GEMS Satellite is Approximately 4 kg.


The Location of the ERSDAC Data Analysis Center is Japan.


The Developer of the MSG Satellite Fleet is Airbus Defence and Space.


The Output Power of the STX-01 S-band Transmitter/Transceiver is 30 dBm.


The Brighter than a trillion stars of the Flare Brightness Measurement is In less than 48 hours the system appears to quadruple in brightness.


The Formation Flying of the TanDEM-X Satellite is Yes.


The Tank Diameter of the Launcher Test Facility is 3 m.


The Mission Status of the FormoSat-2 Satellite is Currently operating.


The Deorbit Date of the ORBCOMM Satellite is Oct. 15, 2012.


The Principal Investigator of the SEOPS-PGTIDE (P&G Tide in Space) Research Project is Dr. Mark Sivik.


The Closest Exploration Distance of the New Horizons spacecraft Spacecraft is 4 billion miles from the Sun.


The Voltage of the 60V link Power Link is 60V.


The Source of the Solar Energetic Particle Events Space Phenomenon is Super active region 11944.


The Output Pulse Energy of the InnoSlab laser Laser is About 30 mJ.


The Components of the IRAS project Technology is Efficient type of solar cell by AzurSpace, a smart heater which self regulates the heat output and a multifunctional sandwich structure with built in radiometry sensors, inertial measurement units (IMUs) and strain gauges.


The Science Objectives of the TROPICS Constellation of CubeSats is Assimilate microwave radiances and/or retrievals in mesoscale and global numerical weather prediction models to assess impacts on storm track and intensity.


The Observation Frequency of the Megha-Tropiques Satellite is Up to 5 (3) observations per day.


The Diameter of the Great Blue Hole Underwater Sinkhole is Over 300 m.


The Rayleigh Impact of the Aeolus Satellite is Gradually declining as the instrument noise increases.


The Number of Visitors of the International Space Station Space Station is More than 230 people.


The Pointing Knowledge of the QuikTOMS spacecraft Satellite is < 0.25º.


The Imaging Modes of the ICEYE-X2 Satellite is High resolution and very wide swath.


The Solar Occulting Disk of the SOHO Satellite is LASCO C2 and C3 camera.


The Follow-up Targets of the CHEOPS Satellite is Targets from the planned TESS (Transiting Exoplanet Survey Satellite) mission of NASA.


The Function of the GOES Satellite is Relay data from remotely located in-situ sites to properly equipped receiving stations.


The Operation Duration of the GHGSat-D Satellite is Over three years.


The Purpose of the Unisat-7 smallsat Satellite is Tryout of technology for the precise orbit insertion of small satellites of CubeSat format.


The Sensor Complement of the MASCOT Sample Return Capsule Capsule is Unknown.


The Detector of the ELVIS Spectrometer is UV coated back-illuminated e2V CCD 30-11.


The Global Maps Resolution of the LEND Neutron Detector is 5-20 km.


The Resolution of the SMOS Satellite is 100 m.


The Research Center of the MEMS Space Telescope Telescope is Unknown.


The Usage of the AOPOD Data Products is Weather forecasting.


The Solar Sail Deployment Date of the IKAROS Small Solar Power Sail Demonstrator is June 11, 2010.


The Solar Panels of the IOD-1 GEMS Satellite is CSL Double Deploy Solar Panels.


The Full Science Mission Start of the ExoMars Trace Gas Orbiter Orbiter is 2018.


The Measurement Capability of the NICER X-ray Instrument is Intrinsic clock stabilities of MSPs.


The Observation Wavelength of the DCAM3 Camera is Visible.


The Measurement Rate of the FFRF Sensor Instrument is 1 Hz.


The Ground Network of the FormoSat-7 / COSMIC-2 mission Satellite Mission is U.S., European, Asian, and polar ground networks.


The Manufacturer of the SBSS Satellite System is Boeing Space and Intelligence Systems.


The Scintillator Thickness of the Gamma-ray Counter Detector is 5 mm.


The Measurement Domain of the DMC-3 Satellite Constellation is Land.


The Operation of the HTV Spacecraft is Berthing to the ISS.


The Delay Announcement Date of the Orbiting Carbon Observatory-2 Satellite is Feb. 10, 2012.


The Propulsion System Type of the Lunar Flashlight 6U CubeSat Satellite is “green” monopropellant.


The Dry Mass of the DMC Propulsion Subsystem Electric Propulsion is < 6 kg.


The Gain of the Ku-band Antenna Antenna is Greater than 42.5dB.


The Processing Power of the VPU Video Processing Unit is More than 1000 MIPS.


The Spectral Range of the LR Spectrometer Spectrometer is 500–758 nm.


The Small Lobe Dimensions of the Comet Celestial Body is 2.6 x 2.3 x 1.8 km.


The Voltage Ripple of the SBVR Power Supply is < 600 mVpp.


The Tasking Rate of the Pléiades Neo constellation Satellite Constellation is Five times higher than previous constellations.


The Flight Heritage of the CanX-2 S-band Transmitter/Transceiver is 1 mission.


The Pupil Diameter for LR of the Instrument Hyperspectral Imager is 36.1 mm.


The Scanner Portion Failure Date of the ERBE Instrument is Feb. 28, 1990.


The IFOV (beam width) of the Antenna Reflector is 0.94º.


The Experiment of the Tokyo Institute of Technology Organization is Evaluation of the robot arm's vibrations.


The Data Size of the Raw Science Data Packet Data Packet is 256 bytes.


The Antenna Polarization of the TUC Transponder Microwave Transponder is Circular.


The Spectral Region of the ERIP Earth Remote-Sensing Imaging Package is 252 - 340 nm.


The Number of Satellites of the Terra Bella Satellite Constellation is 13.


The Mass of the Antenna Communication is < 400 kg.


The Bandpass of the Long Wavelength Band Spectrometer is 1335-1750 Å.


The Broadcasting Service Channels of the GK2A satellite Satellite is LRIT, HRIT, UHRIT.


The Brightness of the Red Dwarfs Star Type is Much less than our Sun.


The Submission Date of the Copernicus Masters 2021 Competition is 2021.


The Orbit Type of the Anand Satellite is Sun-synchronous.


The Satellite Altitude of the MXT Instrument is 600 km.


The Type of the TT&C and Payload Data Communication System Satellite is Flexible.


The Ion Composition of the PAP Plasma Analyzer is H+, He+, O+.


The Reentry Time of the 3U CubeSat Satellite is 72 days.


The Monitoring Period of the Gaia Space Astrometric Mission is 5 years.


The Components of the ADCS Attitude Determination and Control Subsystem is Wheels, gyroscopes, magnetic control system, magnetorquers, magnetometer.


The Product Type of the Sentinel-1 Satellite is SLC (Slant-Range Single-Look Complex).


The Components of the Instrument Calibration is SEDF (Spatial Response), Alignment Parameters, ISRF Shape, SSI, SR, Smile, CU, Radiance Calibration Coefficients, Response Linearity, Noise, Detector PRNU, Detector DSNU.


The Unknown of the X-ray Pulsars Navigation Method is Unknown.


The Data Rate of the FGM Instrument is 0.80 kbit/s.


The Autonomous Operations of the Solar Orbiter Satellite is 15 days without ground contact.


The Inclination of the OrbView-2 Satellite is 98.2º.


The Good Solar Pointing Start Date of the SOVAP Instrument is 22/7/2010.


The Transmission Band of the Delft ground station Ground Station is S-band.


The Number of Bands of the SWIR Detector is 80.


The Channels of the MERSI-RM Radiometer is 8.


The Type of the TCS Thermal Control Subsystem is Semi-active.


The Launch Date of the Euclid Satellite is 2022.


The Energy Range of the MIPA Ion Mass Analyzer is Optimized to cover accelerated ionospheric ions.


The Orbit Repeat Cycle of the GOCE Satellite is 61 days.


The Redundancy of the OBC On-Board Computer is Yes.


The Propulsion Systems of the MTM Transfer Module is Chemical Propulsion System and Electrical Propulsion System.


The Managing Organization of the Jason-3 Satellite is NASA's Jet Propulsion Laboratory in Pasadena, California.


The Speed of the Flywheel Satellite Component is 4500 rpm.


The Acceleration of the Microgravity Regime Environment is <10-4 g for all directions.


The Bus Power Consumption of the EROS-A Satellite is 300 W.


The Launch Provider of the TEMPO Instrument is SpaceX Falcon-9.


The Number of Applications of the C&DH Subsystem Command and Data Handling is 17.


The PM Mass of the DSX Spacecraft Payload Module Satellite is 180 kg.


The Attitude Knowledge of the AOCS Attitude and Orbit Control Subsystem is 0.01º.


The Spectral Bands of the WV-3 Imager Imager is 29.


The Mission Status of the MASCOT Sample Return Capsule Capsule is Unknown.


The Manufacturer of the IVM Ion Velocity Meter is University of Texas, Dallas.


The CDR (Critical Design Review) of the SOURCE 3U CubeSat Satellite is Passed in July 2021.


The NOR Flash of the GomSpace NanoMind A3200 Onboard Computer is 128 MB.


The Antenna Diameter of the Satellite Satellite is 1.2 m, 1.84º (Ku-band), 6.2º (S-band).


The Project Status Presentation of the James Webb Space Telescope Space Telescope is Phil Sabelhaus, "James Webb Space Telescope (JWST) Project Status for the AAS Town Hall," January 5, 2010.


The Destination of the Dutch Radio Antenna Antenna is Moon.


The CubeSat Size of the SUNSTORM Satellite is 3U.


The Quantity of the GPS Antennas Antennas is 2.


The Frequency Band of the SWOT Satellite is 8.025-8.400 GHz.


The Agency of the CryoSat Satellite is ESA.


The Dark Current Source of the Photodiode Detector is Thermal and ionizing radiation effects.


The Host Galaxy of the Sw J1644+57 Supermassive Black Hole is Distant.


The Plasma Irregularities Model of the C/NOFS Satellite is Equatorial plasma bubbles age and irregularity spectra evolution.


The Pupil Diameter of the NAOMI Imager is Driven by the MTF (Modulation Transfer Function) requirement.


The Temperature of the Instrument Optical Subsystems is 130 K.


The Mission Date of the JEM-EUSO Satellite is June 5-12, 2011.


The Quantity of the Microcalorimeter Microcalorimeter is 14.


The Temperature Range of the DE probe Charged Particle Probe is 0.1 - 1.5 eV.


The Receiver Channels of the DIAL Instrument LIDAR is 2.


The Guide Stars Selection of the DPU Data Processing Unit is Up to 10 stars from the full OM image.


The Capability of the Torque Rods Attitude Control is 15 Am2.


The Azimuth Imaging Length of the P Mode Observation Mode is 10 km.


The Resolution Cell, Horizontal of the Instrument Spectrometer is 16 km.


The Antenna Location of the Voyager 2 Spacecraft is Canberra, Australia.


The Components of the SEXTANT System is 1) the NICER XTI, 2) the flight software and algorithms, 3) the ground testbed, and 4) the ground system.


The Number of Concepts of the ALBus R&R Design is Three.


The Mission Priority of the GOSAT Satellite is Short wave infrared observation.


The Number of Satellites of the Starlink Satellite Constellation is More than 500.


The Hydrogen Cell of the Instrument Sensor is Pyrex vessel (MgF 2  lens windows-distance 76 mm).


The Mission Type of the XMM-Newton Satellite is Follow-up of Gravitational Wave Detections.


The Science Instruments of the Solar Orbiter Satellite is 10.


The Spectral Bands of the Maps Data is 400-500 nm, 500-600 nm, 600-700 nm, 750-925 nm.


The Mass of the TUBSAT-N Satellite is 8.5 kg.


The Pixel Size of the LISS-3 Camera is 13 µm.


The Measurement Type of the Argo Ocean Buoys is Subsurface-salinity.


The Boom Length of the Spacecraft Satellite is 10.6 m.


The Duty Cycle of the Instrument General is 20%.


The Impact of the 5G Communications System is Drive a convergence of fixed and mobile services, introduce a new set of technologies and standards, create a network of networks and facilitate communications between everyone and everything.


The Manufacturer of the CPU Board Processor is BAE Systems.


The Orbit Altitude of the KSF1 satellites Satellite is 525 km.


The Merger Date of the Spire Company is Aug. 17.


The NASA Press Release of the Gravity Probe B Satellite is May 4, 2011.


The Orbital Altitude of the SZ-7 Spaceship is ~330 km.


The Module Assembly of the CanX-7 Satellite is Two decks.


The Magnetic Field Measurement Range of the Plasma Wave Instrument Instrument is 1 Hz to 10 kHz.


The Quantity of the Propellant Tanks Propellant is 2.


The Peak Data Rate of the EAN Connectivity System is 100 Mbit/s.


The Data Transfer Frequency of the SSRNI Data Acquisition and Registration System is X-band at 8.2 GHz.


The ULC Cargo of the HTV-7 Cargo spacecraft is 1.9 metric tons.


The New Factory Location of the Satellogic Satellite Company is Netherlands.


The Quantity of the CubeSats Satellite is 4.


The Presentation Date of the Nanosatellite Tracking Ships Nanosatellite is April 27–30, 2009.


The Swath width of the ALOS-3/PRISM-2 Satellite is 50 km.


The Data Rate (Downlink) of the S-band telemetry system Telemetry System is 1 Mbit/s.


The Location Knowledge of the GFO Satellite is Redundant GPS receivers.


The Cost (sensor + spacecraft) of the Framer Sensor is Very low.


The Software Code Reuse of the VMOC Mission Operations Center is About two-thirds between TacSat-4 and ORS-1 missions.


The Modulation and Coding of the Unit Communication System is BPSK, Rate 1/2, K=7.


The Impact of the Solar Energetic Particles Space Weather Phenomenon is Can fry sensitive spacecraft electronics and pose serious risks to human astronauts.


The Daily Global Composite Products of the PROBA-V Satellite is 728.


The Technologies of the IXV Communications Network Network is Serial leased lines, Ethernet lines, ISDN, IP Satellite Networks.


The Separation Date of the PRISMA Satellites Satellite is August 12, 2010.


The Model of the Diode Pumped Nd:YAG Laser Component is RLU.


The Angular Coverage of the STAFF/DWP Instrument is Polar(range/interval) = 180º/12 (IIMS), = 180º/9 (IES).


The Ground Resolution of the Mars Express Orbiter is Approximately 20 m/pixel.


The Light Emission of the Transient Luminous Events Atmospheric Phenomena is Weak.


The Location of the FOS Flight Operations Segment is ESOC in Darmstadt.


The Mission Duration of the NanoSail-D2 Solar Sail is 70 and 120 days.


The Manufacturer of the ELSA-d Satellite is Astroscale UK Ltd.


The Detector Type of the LISA Space Observatory is Gravitational Waves.


The PI of the IVM Ion Velocity Meter is Rod Heelis.


The Satellite Launches of the Space Flight Laboratory Organization is Five in Two Weeks.


The Design of the Radiometric Responsivity Tracking Method Method is For optical sensors without on-board calibration systems.


The Temperature of Spacecraft and Instruments at Closest Approach to the Sun of the Heat Shield Parker Solar Probe Component is About 85 degrees Fahrenheit (29ºC).


The Components of the AFSS Autonomous Flight Safety System is GPS, IMU, algorithms.


The Data Rate of the RF Communications TT&C is 2.5 or 15 kbit/s.


The Number of Arrays of the Detector Arrays Optical Component is 2.


The Mass of the Telesupport Payload is 27 kg.


The Affiliation of the Kazifumi Fukuda Author is Unknown.


The Angular Resolution of the RHESSI Satellite is Few arcseconds.


The Typical X-ray Flare Duration of the X-ray Source Celestial Object is Up to a few hours or even days.


The Operational Date of the ERS-1 Satellite is Unknown.


The Design Requirement 2 of the OCO-3 PMA Pointing Mirror Assembly is Movement not affect the measurements through angular dependent polarization or radiance changes.


The L-band Resolution of the SAR-XL Payload SAR Instrument is 5 m class.


The Mass of the NovAtel OEMV-2 L1/L2-F GPS unit GPS Unit is 56 g.


The Orbit Type of the JL-1-GF03D Microsatellite is SSO.


The Receive Frequency (MHz) of the HRIT HiRID Data Receiver is 2029.1.


The Observation Period of the Dynamics of the Radiative Environment Observation is 11/2000-11/2001.


The Orientation Requirement of the Radiator Thermal Control System is Oriented on cold, deep space.


The Imagery Capture Date of the WorldView-3 and GeoEye-1 Satellites is Northern California Wildfires.


The Mission Start Date of the THEMIS Satellite is Unknown.


The Spectrometer Type of the SPEXone Spectrometer is Compact and lightweight all-reflective imaging grating spectrometer.


The Antenna of the Lunar Pathfinder's Receiver Satellite Receiver is High-gain satnav antenna.


The Cadence of the Fast Cameras Camera is 2.5 seconds.


The Type of the MTG-I Satellite is Imager.


The Solar Panel Deployment of the LightSail Satellite is Possibly ajar or deployed.


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


The Aperture Diameter of the ALI Telescope is 12.5 cm.


The Function of the SMA Scan Mechanism Assembly is Steps the projected TEMPO instrument slit image, or FOV, aligned in the North-South direction, across the TEMPO field of regard and compensates for unwanted spacecraft motion.


The Managing Center of the Chandra X-ray Observatory is NASA's Marshall Space Flight Center.


The Data Rate of the MWHS-II Microwave Humidity Sounder is 15 kbit/s.


The Manufacturer of the STPSat-3 Satellite is Ball Aerospace.


The Power Consumption of the SEIS Instrument Seismometer is Around 1W.


The Body Dimensions of the Nanosatellite Satellite is 20 x 20 x 20 cm.


The Manned Moon Landing Deadline of the Artemis Program Space Exploration Program is 2024.


The J2000 right ascension (deg) of the B0540-69 Pulsar is 85.04668.


The Frequency of the Request for Information Process is Every 12 to 18 months.


The Conference Presentation Date of the SEXTANT X-ray Timing and Navigation Technology is 5-9 Jan. 2015.


The Data Sensitivity of the PAMELA Instrument is Exceeds current data by several orders of magnitude.


The Injection Velocity Shortfall of the ARTEMIS Spacecraft is About 500 m/s.


The Mission Objective of the Copernicus Sentinel-6 Satellite is Monitor sea-level change.


The Function of the IDE System is Controls instrument operations and collects instrument telemetry.


The Neon Temperature of the Sun's Lower Atmosphere Celestial Body is 630,000ºC.


The Data Collection Period of the Liulin-MO dosimeter Radiation Dosimeter is Six-month interplanetary cruise to Mars.


The Functions of the SMC Secure Management Center is TC authentication/ciphering and key management.


The Filter Type of the FUV channel Spectrometer is Calcium Fluoride.


The Missed Lightning in Northern Hemisphere of the ISS-LIS Lightning Detection Instrument is Nearly all of that lightning.


The Focal Plane CCD Lines of the Camera Imaging Device is 3.


The TGF Association of the RHESSI Satellite is Intracloud lightning.


The Resolving Power of the Spectrometers Spectrometers is 3 x 10^5 for the narrowband ones.


The L1 Detectors Purpose of the HIT Sensor is Sweep out a 4π, full-sky coverage.


The Onboard Recorder of the Satellite Satellite is No.


The Downlink Contacts per Day of the IXPE Satellite is Up to 9.


The Nominal Power of the IMP-8 Spacecraft is 150 W.


The Ground Stations of the PROBA Project Satellite Project is ESA station in Redu (Belgium), second ground station used in S-band during LEOP and the first part of the commissioning phase.


The Launch Configuration of the OSIRISv3 Laser Communication Terminal is Soft-stowed.


The Value of Information (VOI) of the COS Climate Observing System is Computed by IGW-SCC.


The Tuning of the AOCS Control System is Solar array natural mode damping, optimised wheel zero crossing management.


The Data Bus of the Suomi-NPP Satellite is MIL-STD-1553.


The Launch Date of the ESAIL Microsatellite is 3 September 2020.


The Publication Date of the SpooQy-1 CubeSat is 2017.


The Data Quantization of the Pushbroom imager Optics is 12 bit.


The Size of the Antenna Communication Device is 3.3 m x 2.7 m.


The Agency of the KySat-2 Satellite is MSU (Morehead State University), University of Kentucky (UKy), Kentucky Space LLC.


The URL of the James Webb Space Telescope Space Telescope is http://www.stsci.edu/jwst/operations.


The Software of the Modem Processor Signal-Processing Chain is Iris software.


The Access Capability of the JAXA Flight Controller Control System is Laptops in JEM.


The Launch Year of the RADARSAT-1 Satellite is 1995.


The Capture Date of the MODIS Imaging Spectroradiometer is June 16, 2022.


The Pointing Performance of the S/C Satellite is Better than 0.05º (3 σ).


The Pixel Size of the Eastman Kodak KLI14403 linear CCD sensor Sensor is 5.0 x 5.0 µm.


The URL of the Soil Moisture Active Passive (SMAP) Mission is http://secure.ntsg.umt.edu/publications/2010/ENOKCEEGJJKPKMMMMRSSTTV10/Entekhabi_IEEEProceedings_05_10.pdf.


The Azimuth Resolution of the Stripmap Imaging Mode is 3.3 m (single pol.), 6.6 m (dual pol.).


The Thrust of the CNAPS Propulsion System is 10 mN/thruster.


The Manufacturer of the XMM-Newton X-ray space observatory is ESA.


The Presentation Date of the Capella X-band SAR constellation Satellite Constellation is 28 July - 2 August 2019.


The Size of the CICERO-4 Satellite is 3U.


The Operation Pause Duration of the InSight Mars Lander is Several weeks.


The Redundancy of the Transmit chain Transmit Chain is Two chains.


The Manufacturer of the ERA Robotic Arm is Fokker Space.


The Data Production of the Sentinel-1, -2, and -3 Satellites is Approximately 4 TByte per day.


The Arrival Date of the E-THEMIS Thermal Emission Imaging Instrument is Unknown.


The Function of the SAR Antenna Assembly SAR Antenna Assembly is The SAA is an active phased array and it is able to operate different beam characteristics for transmission and reception.


The Role of the Thermohaline Circulation Oceanic Phenomenon is Supplying heat to the polar regions.


The Commissioning Phase of the RPW Radio and Plasma Waves Instrument is Before 15 June.


The Signal-to-Noise Ratio of the NISP Photometer Instrument is Magnitude 24.0.


The Operator of the Resurs-DK1 Earth Observation Satellite is Russia's Science Center for Remote Sensing of Earth, NTs OMZ.


The Spectral Band of the Band Cameras Camera is 762.4 nm.


The Output of the MCP Multi-Channel Plate is Proportional to the number of ions at its input.


The Secondary Objectives of the PROBA Satellite is Space environment investigation and Earth observation.


The Composition of the Fortescue Group Rock Formation is Volcanic and sedimentary rocks.


The Band-to-band co-registration of the Spectrometer Spectrometer is < 1.4%.


The TT&C Frequency of the Payload Communication System is S-band.


The Maximum Satellite Mass of the ALMASpace AD-SS Satellite Dispenser is 35 kg.


The Orientation Stabilization of the Solar Orbiter Spacecraft is After the first command was sent.


The Lens of the TV Camera Camera is Augeniux 50 mm f/0.95 lens.


The URL of the Aerosol Polarimetry Sensor Sensor is http://glory.giss.nasa.gov/aps/docs/SPIE_6786_67865L.pdf.


The Operation Support of the GeoXO Satellite System is Weather, ocean, and climate operations in the United States.


The Number of Products of the EnMAP Satellite is 3 + 1 internal product.


The Usage of the ASC (Advanced Stellar Compass) Star Tracker is Only at a low (<4.5 rpm) spin rate.


The Final Report Date of the Solar Mass Ejection Imager (SMEI) Satellite is Oct. 25, 2007.


The Catalog of the Star Tracker Attitude Determination Device is 3746 stars.


The Instrument Dimensions of the SEVIRI Imager is Diameter of about 1 m and a height of 2.1 m.


The Provider of the Keramis-2 Ceramic Microwave Circuits is IMST GmbH.


The Interface of the OBC On-Board Computer is 1553 RIU interface with the S-band transceiver.


The AD-SS Mass of the ALMASat-1 Satellite is 6.54 kg.


The Operation End Date of the PROBA-2 Satellite is December 31, 2016.


The Mirror Material of the Limb Imager Telescope is Aluminium.


The Regular Technology Demonstration Mode Start Date of the ICIR IceCube Cloud–Ice Radiometer is June 16, 2017.


The Agency of the DeMi Satellite is MIT.


The Launch Dates of the COSMO-SkyMed Satellite Constellation is 2007, 2008, 2010.


The Maximum Upper Band Edge of the MS8 (NIR2) Imager is 1043 nm.


The Calibration and Validation Team of the PALSAR Ground Data System is M. Shimada, H. Wakabayashi, T. Tadono, A. Rosenqvist, T. Igarashi.


The Mass of the TeleSat LEO Phase 1 Minisatellite is 168 kg.


The Distance from Earth of the M33 galaxy Galaxy is Three million light years.


The Spatial Resolution (Azimuth) of the Radar Radar is 50 m.


The Functionality of the DHU Data Handling Unit is Control & Monitoring, Generation of camera syncs, Interface to VNIR/SWIR, Sorting of incoming data, Storage of data, Compression, Generation of source packets, Interface for control & monitoring from S/C, RTC, Acquisition of HK data.


The Purpose of the COBE (COsmic Background Explorer) Satellite is Measure the leftover radiation from the big bang.


The Orbit Decay Rate of the GOCE Satellite is Less than 35 cm per day.


The Calibration and Mosaicking Chain Operational Date of the TanDEM-X Satellite is End of 2013.


The CCD Line Array of the MSU-E Multispectral Scanner is 1024 pixels.


The Launch Date of the MTSAT Satellite is 15 Nov 1999.


The Thrust Capability of the Propulsion System Satellite Component is Variable impulse.


The Primary Body Diameter of the Didymos Asteroid is Approximately 800 meters.


The Quantity of the Star sensor Sensor is 2 units.


The Location of the DLR ground station Ground Station is Neustrelitz.


The 100 pps (pulses per second) of the TT&C Communications Command Rate is Command rate - 100 pps (pulses per second).


The | of the IASI-New Generation Satellite is IASI-New Generation onboard EPS-SG: Expected impact on accuracy and vertical resolution for atmospheric variables.


The Constellation of the GPM Mission is Various satellites.


The Components of the SWEA Solar Wind Electron Analyzer is SWEA (Solar Wind Electron Analyzer) and STE (Suprathermal Electron Telescope).


The Image Location of the CaSSIS Instrument is 29.2ºS/66.8ºE.


The Orbit Inclination of the ISS International Space Station is 51°.


The Efficiency of the SFINKS Solar Cell Array is 32%.


The Number of Maneuvers of the SkySat-6 Satellite is 5.


The Purpose of the Airlock Stowage Platform Hardware is This deck configuration of the upgraded platform will increase the overall stowage capability on the International Space Station, allowing the crew to further reduce the impact of on-orbit cargo kept and maintained.


The Conference Presentation of the OSIRIS-REx Asteroid Sample Return Mission is SpaceOps 2014, 13th International Conference on Space Operations, Pasadena, CA, USA, May 5-9, 2014.


The Operator of the INSAT-3DR Satellite is ISRO (Indian Space Research Organisation).


The Energy Range of the RHESSI Imaging Instrument is Soft X-rays (about 3 keV) to gamma-rays (up to about 17 MeV).


The Sample Site Selection Board Chair of the OSIRIS-REx Spacecraft is Heather Enos.


The Unknown of the Extraterrestrial Material Unknown is Unknown.


The Operation of the EDR-2 European Drawer Rack is Run in parallel with the original European Drawer Rack.


The Launch Date of the Chinese satellite Satellite is Aug. 16, 2016.


The MS Camera of the Payload Satellite Subsystem is B1:0.45~0.52 µm, B2: 0.52~0.59 µm, B3: 0.63~0.69 µm, B4: 0.77 ~0.89 µm.


The Area Collection Rate of the Push Frame Framer with a fast steering mirror Sensor is Low.


The Voyage Article Date of the Argo Ocean Observing System is Feb. 28, 2002.


The Data Availability of the Carbon Mapper Satellite Project is Freely available.


The Magnetorquers of the NEMO-AM Satellite is Quantity: 3, Manufacturer: SFL, Current-Controlled up to 100 mA.


The Maximum Range of the TDC-GPX Time-to-digital converter is 7 µs.


The Test Phase Start Date of the IASI-NG Instrument is Early 2021.


The Conference Presentation Date of the Micro-Cathode Arc Thruster Thruster is 5-12 March 2016.


The Redundancy of the ADCS Attitude Determination and Control System is Full redundant backup with magnetorquers and reaction wheels.


The Member of the Richard Bevilacqua Individual is True.


The Study Subject of the Quasars Celestial Objects is Gravity in the very strong field of the supermassive black holes.


The Ion Propulsion System of the GOCE Satellite is Commissioned.


The Speed of the New Horizons Spacecraft is Over 30,000 miles per hour.


The Operation End Date of the ERBS satellite Satellite is Summer of 2005.


The Type of the Q/V-band transponder Technology Demonstration Payload is Unknown.


The Targeted Date of the Iridium-5 Satellite Launch is March 29, 2018.


The Presentation Date of the BEESAT-3 Satellite is Oct. 10-13, 2012.


The Attitude Control Stability of the BRITE spacecraft Satellite is 1 arcmin rms.


The Duration of the Performance Tests Process is Over long periods of time (many orbits).


The Development Location of the NEA Scout Spacecraft is NASA Marshall in Huntsville, Alabama, and JPL in Southern California.


The Testing Location of the Gaia SVM Satellite is EMC chamber at Intespace, Toulouse.


The Fairing Envelope Requirement of the TacSat-4 Satellite is Must fit within the fairing envelope of the Minotaur IV launch vehicle.


The Launch Date of the JPSS-2 Satellite is 2019.


The Daily system capacity of the WorldView-4 Satellite is 1x.


The FDC Algorithms of the ACS Attitude Control System is Included in ACS flight software (FSW).


The Number of Piezoelectric Sensors of the IS Diaphragm is 5.


The Process of the Personal Computer Computer is Plug-and-play.


The Wavelength FWHM of an unresolved line of the Spectrometer Instrument is 0.020 µm.


The Doppler Correction of the Communication System Satellite Subsystem is Pre-correcting Doppler.


The Number of Experiments of the SMART-1 Satellite is 7.


The Landing Date of the Chang'e-4 Mission is 3 January 2019.


The Ballistic Coefficient of the SpinSat Spacecraft is Well-determined and characterized.


The Altitude of the Meteor-M2 Satellite is ~ 825 km.


The Location of the NanoRacks LLC Company is Houston, TX.


The Data Access Level of the SAPHIR and SCARAB Instruments is 1A and 1A2.


The Components of the Central Propulsion Module Propulsion Module is Propellant tanks, LAE (Liquid Apogee Engine), East panel with the L-band antenna feed, West panel with the IOL (Inter Orbit Link) antenna.


The Operation of the Tether System Satellite Component is Voltage is on when the tether moves downwind with respect to the plasma ram flow and off when it moves upwind.


The Power Source of the Jason-3 Satellite is Two solar panels.


The Power Consumption of the Instrument Interface Module Interface Module is ~350 mW.


The Image Production of the GOCI Geostationary Ocean Color Imager is 3 times per day.


The Distance from Earth of the GRB 150101B Gamma Ray Burst is About 1.7 billion light years.


The Spectral Ranges of the Dichroics Optical Component is 4.


The Backup Location of the PAZ SAR Processor Ground Segment Processor is Maspalomas (Canary Islands).


The Exposure Time per Frame of the XMM-Newton X-ray Observatory is About three minutes.


The Uncertainty of the . Magnetometer Instrument is ±14 nT.


The System Mode of the KaRIn Radar is Non Ping Pong mode.


The Spectral Cube Size of the Observation Instrument Telescope/Spectrograph is 1900 (spectral) x 1150 (spatial).


The Tolerance of the SVOM Attitude Satellite Attitude is 5°.


The LYSO crystals of the Range Calorimeter Particle Detector is Height of 4 cm.


The Data Collection Period of the XMM-Newton Satellite is 2016 and 2018.


The Observation Type of the DICE CubeSats Satellite is Plasma.


The Mass of the M3S Satellite is 2800 kg.


The Delivery of the CAPSTONE 12U CubeSat is Rapid commercial delivery.


The Spatial Resolution of the Oceanography Basin scale Satellite is 200 km.


The Interaction with Magnetic Fields of the Cosmic Rays Charged Particles is Their path is bent by magnetic fields.


The Period of the WV-1 Satellite is 94.6 minutes.


The Product Specification Date of the RadidEye Imagery Satellite Imagery is January 2016.


The Spacecraft Size of the ArgoMoon CubeSat is 6U.


The Components of the Chang'e-5 Lunar Mission is Orbiter, lander, ascender and reentry module.


The Identification Time of the CSpOC Catalog Catalog is L+20.


The Sponsors of the CanX-7 Satellite is Defence R&D Canada – Ottawa, the Natural Sciences and Engineering Council of Canada, COM DEV, Royal Military College of Canada, and the Canadian Space Agency.


The Development Time of the IRIS Payload is One year.


The Accuracy of the UFF TLE Data Product is Less Accurate.


The Maximum Daily High-Speed Downlinks of the NEMO-AM Satellite is 2.


The Conference Presentation Date of the Near Earth Asteroid Scout Satellite is 2-9 March 2019.


The Li-ion Battery of the EPS Electric Power Subsystem is ABSL (UK), 35 kg, 126 Ah.


The Number of Satellites of the Satellite Constellation Non-Geostationary Satellites (NGS) is 4425.


The Public Engagement of the New Horizons Spacecraft is Broke NASA records, touched lives, and awed the world.


The Number of Elements of the ICEYE SAR Antenna Antenna is 5.


The Spacecraft Weight of the Tianwen-1 Mars Mission is Five-ton.


The Measurement Parameters of the CITRIS Receiver is Total electron content (TEC) and scintillation parameters.


The Technology Readiness Levels of the SWOT Instruments Instrument is 3 to 5.


The Presentation Date of the SWOT Mission Satellite Mission is 2012.


The Core Stage of the SLS Rocket Rocket is Assembled with four of the five parts.


The Orbit Altitude of the CBAS Primary Payload is 39,000 km.


The CubeSat of the Satellite KickSat is 3U.


The Freezing Level Height of the GPM Satellite is Higher than 4 km.


The Data Transfer of the Webb's Fine Guidance Sensor (FGS) Sensor is Limited communications bandwidth between L2 and Earth.


The Observation Date of the XMM-Newton X-ray Telescope is 2016.


The Launch Date of the RapidEye Satellite is Unknown.


The Location of the EARS Data Receiving Station is Multiple.


The Spectral Range of the VNIR Spectrometer Spectrometer is 420 nm to 1000 nm.


The Modulation of the TT&C Data Communication is MSK (Minimum Shift Keying).


The Manufacturer of the LF Receiver Receiver is Sierra Lobo Inc..


The Manufacturer of the SPIDER Imaging System is Lockheed Martin.


The Size of the iADCS100 Attitude Determination and Control System is Two standard CubeSat PCBs.


The URL of the Rosetta Satellite is http://sci.esa.int/rosetta/55295-getting-to-know-rosetta-s-comet/.


The RF Bandwidth (MHz) of the Antenna Reflector is 600.


The Spatial Resolution of the IRS Sounder Satellite is 800 m at SSP.


The Number of Voltage Probes of the FIELDS suite Sensor Suite is 5.


The Location of the Tyvak 61C Satellite is Irvine CA, USA.


The Polarization of the ICI-6 Radiometer is V.


The Height of the Spectral Block Focal Plane Component is 240 pixels.


The Propellant Mass of the XMM-Newton Satellite is 140 kg.


The Inclination of the Beijing-1 Satellite is 98.8º.


The Diameter of the Didymos Asteroid is 780 m.


The NESZ of the TerraSAR-X SAR System is Unknown.


The Ground System Review Date of the Roman Space Telescope Space Telescope is 24 July 2020.


The Power of the Capability Satellite is 24 W.


The Laser Diodes Wavelength of the SILEX Terminal is 0.8 to 0.86 µm.


The Altitude of the TSX and TDX Satellites is About 514 km.


The Geolocation accuracy of the ALOS-3/PRISM-2 Satellite is Better than PRISM.


The Rate Stability of the QuikTOMS spacecraft Satellite is < 0.01º/s.


The Swath Width of the ISS-RapidScat Scatterometer is Similar to the EUMETSAT ASCAT (Advanced Scatterometer).


The Sub-contractor of the Laser Transmitter Laser is TESAT.


The Measurement of the DFACS Attitude Control System is Accurately measures the spacecraft accelerations in 6-DoF (Six Degrees of Freedom).


The Data Compression Steps of the RFA Computer Signal Processing Device is 3.


The Launch Year of the ATHENA Advanced Telescope for High-ENergy Astrophysics is 2031.


The Global Average Detection Rate of the exact Earth Satellite AIS Receiver is 42 Messages/s.


The X-Ray Flares Count of the RHESSI Satellite is Forty Thousand.


The Electrical Power of the TXS S-band Transmitter/Transceiver is 4 W.


The Collaboration Members of the IceCube-Gen2 Satellite is M. G. Aartsen, R. Abbasi, M. Ackermann, .... M. Zöcklein.


The Operational Mode of the Aquarius Radiometer System is  Survival.


The Launch Date of the Light-1 Satellite is December 21, 2021.


The Subsystem Type of the AOCS Attitude and Orbit Control Subsystem is Attitude and Orbit Control.


The Attitude Prediction Accuracy of the ISS Satellite is Approx 0.2º for up to 4 days.


The Photodetector Sensing Area Size of the Optical Head Optical Device is 6.66 mm x 5.32 mm.


The Orbital Lifetime of the InflateSail Satellite is 72 days.


The Size of the MEPSI Satellite is 100 mm x 100 mm x 125 mm.


The Landing Camera (LCAM) of the Chang’e-4 Lander Lander is Payload.


The Measurement Date of the Chang'e-4 Lunar Probe is 15 August 2020.


The Frequency of the Downlink Signal is 880f0.


The Rainfall Accumulation Observation Period of the GPM Satellite Mission is May 27 to June 5, 2020.


The Conference Presentation of the Sensor Web Sensing System is 7th International Symposium Reducing the Costs of Spacecraft Ground Systems and Operations (RCSGSO 2007).


The Detector of the SEXTANT Technology is Required to provide source and background count rates.


The Precision of Post Event Processing of the GF-3 Satellite Satellite is Better than 20 cm (1σ).


The Service Commissioning Status of the Lacuna Space Company is Underway.


The Launch Date of the Argos-4 Satellite Instrument is November 26, 2022.


The Type of the Microprocessor Hardware is 32-bit ~200 MHz ARM.


The Mission Duration of the Electric Thruster Thruster is 2.5 years.


The End of Life Date of the COMS Satellite is 1 April 2021.


The Calibration Mode of the LISS-3 camera Camera is Pulsed.


The Outreach Program of the EduSat Satellite is Italian Space Agency.


The Interface Bracket Material of the ASM Satellite Component is CFRP (Carbon Fiber Reinforced Polymer).


The Position Determination Accuracy of the XNAV Navigation System is Expected to be on the order of hundreds of meters.


The NER of the Spectral Band D Spectrometer is 5.2 x 10^-7 W/(cm^2 sr µm).


The Data Storage of the Sentinel-1 Satellite is Large on-board science data storage.


The Data Downlink Frequency of the GFO Satellite is Real-time at sea, approximately every 12 hours at CONUS ground sites.


The FOV of the Hyperion Imaging Spectrometer is 0.624º.


The Goal of the Chang'e-5 Lunar Mission is Establish an international lunar research station.


The Temperature Range of the XRT X-Ray Telescope is 0.5 to 20 MK.


The Tape Recorder of the CBERS-1 Satellite is High Density Tape Recorder (HDTR).


The Operational Status of the PAZ Satellite is Unknown.


The Function of the VISTA Satellite is Complement AERO.


The Purpose of the Jamming and Spoofing Protection Mechanisms Security System is Safeguard Galileo signals.


The Solar Array Span of the Resurs-DK1 Spacecraft is about 14 m.