The Mission Start Date of the ARTEMIS Satellite is 2010.


The Wavelength of the X-band Band is 2.9 cm.


The Presentation Date of the ERG Satellite Satellite is June 5-12, 2011.


The Observation Location of the IBEX Satellite is About 30 degrees south of the interstellar upwind direction.


The Publisher of the Observation of the Earth and Its Environment Documentation is Springer Verlag.


The Objective of the Cluster Satellite Mission is Observation of key interaction processes between two cosmic plasmas.


The Accumulated Travel of the Yutu-2 Rover is 178.9 meters.


The Ultraviolet Spectrograph of the Juno Spacecraft is Instrument.


The Measurement Data of the Solar Orbiter Satellite is Solar wind, coronal mass ejection.


The Antenna Types of the Ground Station Ground Station is S-band, C-band.


The Observation Location of the RainCube Satellite is Sierra Madre Oriental, near Monterrey, Mexico.


The Main Beam 3 dB Footprint of the ICIR Radiometer is 10 – 20 km.


The Launch Date of the InSight Mars Lander Mars Lander is May 5, 2018.


The Heat Shield Diameter of the Orion Spacecraft is 5 m.


The Isolation Between Ports of the Array Radiator Antenna is Better than -22 dB.


The Purpose of the OSIRIS Device is Attitude control system and satellite performance testing.


The Functional Demonstration Date of the OHB Telecommunications Satellite Satellite is June 2, 2017.


The Pulse Repetition Frequency (PRF) of the PR Phased Array System is 2776 Hz.


The Instrument Type of the CHORUS Satellite Constellation is Imaging microwave radars.


The Power Consumption of the STL-11000M SBIG Camera CCD Camera is Low.


The Components of the Ka-band payload Communication System is Multi beam antenna, on-board switching transponder subsystem.


The Proximity to Sentinel-3B of the CDN2 Site Ground Station is 300 m west.


The Field of View of the Spectrometer Instrument is 3.5 x 3.5 to 7 arcsec x 7 arcsec.


The Solar Array Size of the EPS Electrical Power Subsystem is 5.661 m 2.


The Manufacturer of the UL 03041 pixel ULIS microbolometer array Microbolometer Array is ULIS.


The Data Downlink Speed of the Payload Satellite Payload is 128/256 kbit/s.


The Radiometric Stability of the Satellite Sensors Instrument is Crucial.


The Characterized Processes of the Models of the Oceans and Land Biosphere Earth Science is Photosynthesis, respiration, nutrient uptake and transport, fire, and chemical cycling, as well as fossil fuel inventories.


The Imaging Frequency Band of the RADARSAT-2 Satellite is C.


The Power of the LIMS Instrument is 27 W.


The Attitude Knowledge Error of the Spacecraft Satellite is 5 arcsec (95%).


The Cargo Storage of the HTV-8 Spacecraft is 3.5 metric tons in the PLC, 1.9 metric tons in the ULC.


The URL of the Observation of the Earth and Its Environment: Survey of Missions and Sensors Documentation is http://link.springer.com/article/10.1007/s12273-015-0241-8.


The Number of Supported Devices of the SSRNI Data Acquisition and Registration System is Up to 24.


The Battery Type of the Canopus Pipper Satellite is Molicel 18650 Li-ion batteries.


The Mass of the Nauka module Module is 20 tons.


The Radius of the Orbital Phase 1 Orbit is Ca. 29 km.


The Power of the RA-1 Antenna Antenna is ≤ 134.5 W.


The Swath of the MERSI-RM Radiometer is 2900 km.


The Cost per Satellite of the Satellogic Satellite Constellation is $2 million dollars per year.


The Temperature of the Optics Subsystem Camera Subsystem is 20 ±3ºC.


The Deorbit Date of the ICESat Satellite is Sept. 2, 2010.


The Pixel Size of the Telescope Optical Instrument is 24 x 24 µm.


The Objectives of the S 329 Satellite is Measurement of DC electric field grad |B|.


The Sensor Complement of the MMO Spacecraft is MERMAG, MPPE, PWI, MSASI, MDM.


The Cargo Capacity of the Tianzhou-2 Cargo Spacecraft is 4.69 tons.


The Pointing Precision of the FY-3 series spacecraft Satellite is 50 m on the ground.


The Purpose of the Hiber Satellite Constellation is Track and monitor machines and devices for a wide range of IoT solutions in some of the world's hardest-to-reach places.


The Image Data Storage of the ISERV Satellite is Compact Flash memory, WORF laptop hard disk.


The Velocity Resolution of the Spectrometer Instrument is ~100 km/s.


The Additional Downlink Subsystem of the Sentinel-1, -2 Satellites is Laser Communication Terminal (LCT).


The Frequency of the VNIR Band is 283 THz.


The Mean Anomaly at Epoch of the Swarm-C (Charlie) Satellite is N/A.


The Data Processing Challenge of the INCUS Satellite is Technical challenge that’s really fun.


The Arrival Date of the Parker Solar Probe Satellite is April 28, 2021.


The Science Levels of the MASCOT Science Landing Package is Context Science.


The Objectives of the WISPR Instrument is 1. Understand the morphology, velocity, acceleration, and density of evolving solar wind structures when they are close to the Sun. 2. Derive the 3D structure of the solar corona through which in-situ measurements are made to determine the sources of the .


The Components of the Optical Payload Payload is Wide-angle camera (primary) and a telescopic camera (secondary).


The Observation Date of the Solar-B/Hinode spacecraft Spacecraft is February 6, 2018.


The Calibration Method of the TRUTHS Satellite is Pre-flight calibration/characterization and during the commissioning phase.


The Minimum Required Functionality of the Development Approach Satellite Instrument Development is Kept strictly to the minimum required functionality to fulfill the science goal.


The Algorithm Improvement of the OMI Satellite is OMI O2–O2 operational cloud algorithm.


The Procurements Cost of the Galileo Second Generation (G2) Satellite Constellation is Up to approximately 950 million euros.


The Power Source of the Lander Spacecraft is Body mounted solar panels.


The URL of the SpaceX CRS-6 Mission is http://blogs.nasa.gov/spacex/wp-content/uploads/sites/227/2015/04/SpaceX_CRS-6_Mission_Overview.pdf.


The Unknown of the Metal mirror TMA Telescope is Unknown.


The Leading Noise Terms of the Satellite Spacecraft is Self gravitation to the satellite.


The Performance Range of the UV-2 Spectrometer is 310 - 365 nm.


The Constellation Number of the PlanetiQ satellites Weather Satellites is 20.


The Firing Duration of the CUS Cryogenic Upper Stage is Approximately 720 seconds.


The Mission Status of the OSIRIS-REx Spacecraft is One Step Closer to Touching Asteroid Bennu.


The Conference Date of the TacSat-4 Satellite is Aug. 11-14, 2008.


The Funding of the NIRSpec Near-Infrared multi-object Spectrograph is ESA.


The Attitude Orientation of the ICESat Satellite is -ZG axis is 0.3º from geodetic nadir.


The 205 kbit/s for each sensor (uncompressed case) of the Data Rate Sensor is Data rate 205 kbit/s for each sensor (uncompressed case).


The Manufacturer of the Maeva Hinges Deployment Mechanism is CNES.


The Size of the PolyITAN-2-SAU Satellite is 2U.


The Configuration of the VDES Antenna Antenna is Stowed and deployed.


The Approx. peak sensitivity altitude of the Channel 3 Sensor is Unknown.


The Image Capture Method of the WAC Camera is Moderate resolution images using filters.


The Manufacturer of the NIRSpec Instrument is Astrium GmbH.


The Data Rate of the Astrodev Lithium 2 Radio RF Communication Device is 9.6 kbit/s.


The Manufacturer of the Gaia Space Telescope is ESA.


The Azimuth Width of the Transmitting Beam of the UF Mode Observation Mode is Broadened 1.7 times.


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


The Deployment Date of the HawkEye 360 Satellite Constellation is Not Provided.


The Monitoring Period of the Envisat Satellite is 2008-2009.


The Ground Resolution of the HARP-2 Polarimeter is Narrow.


The Anomaly Date of the Sentinel-1B Satellite is 23 December 2021.


The Mission Lead of the THEMIS Satellite Constellation is Vassilis Angelopoulos.


The Mission Type of the GPM Satellite is Rainfall Measurement.


The SNR of the Band 1 Spectral Band is 260.


The Telescope Type of the R3 Sensor Imaging System is 1-inch refractive optical telescope.


The DOI of the Near Earth Asteroid Scout Satellite is https://doi.org/10.2514/6.2014-4435.


The Maneuver of the LISA Pathfinder Spacecraft is Keep test masses away from the housing walls.


The Trajectory Analysis and Design Presentation of the OMOTENASHI Satellite is 31st ISTS (International Symposium on Space Technology and Science).


The Communication Status of the MarCO CubeSat is Loud and Clear.


The Mass of the Battery Energy Storage is About 3.5 kg.


The Data Compression Rate of the Instrument Spectrometer is < 80%.


The Status of the SwissCube Satellite is Active.


The Channel Detectors of the SEVIRI Spectral Imager is 42.


The Input Voltage of the Transmitter Communication Device is +12 V DC.


The PSF (Point Spread Function) of the Telescope Optical Instrument is 1.5 - 2.5 arcmin (rms).


The Channels of the GOES Sounder Radiometer is 19.


The Optical System of the PS0 Optical Instrument is 2 element Maksutov Cassegrain.


The Launch Date of the EarthCARE Mission is Unknown.


The Drag Levels of the S/C Satellite is Several N.


The Swath Width of the OSCAT-3 Radar Scatterometer is 1440 km.


The Orbit of the Kounotori-5 Spacecraft is Near-circular orbit, altitude of ~400 km to ISS, inclination =51.6°.


The URL of the Kepler Satellite is http://www.nasa.gov/mission_pages/kepler/news/41-new-transiting-planets.html.


The Control Mode of the HM Heater System is Measurement and Calibration Modes and controlled through CCU-CMN (Correlator and Control Unit-Control and Monitoring Node) chain.


The Performance of the MW Instrument is 0-4 Nms.


The Function of the Drag Sail Satellite Component is Deorbit the satellite.


The Instrument Type of the TROPICS CubeSat Satellite is Microwave Spectrometer.


The Onboard Storage Capacity of the NigeriaSat-2 Satellite is 16 gigabytes.


The Mission Status of the FITSat-1 Satellite is Mission complete.


The Interior Volume of the BA 330 module Space Module is 330 m3.


The Power Distribution of the MERLIN Satellite is Unknown.


The Selection Date of the Lobster-Inspired Mirror Satellite Component is Oct. 27, 2015.


The Surface Area of the CSS Solar Cells is 2 cm2.


The Power of the RISAT-2 Satellite is 750 W.


The Mission Objectives of the ZACUBE-2 Satellite is Aligned with those of MDASat-1.


The Absolute Radiometric Calibration Accuracy of the PROBA-V Satellite is Unknown.


The Spectral Range of the SphinX X-ray Photometer is 1-12 Å.


The Period of the Satellite SuperView Constellation is 97 minutes.


The Voltage of the Antenna Power Supply Antenna Power Supply is 100 V.


The Apogee of the BUV Sensor is 1108 km.


The Configuration of the SGR-ReSI antenna Antenna is Nadir and zenith dual frequency antennas, two L1-only zenith antennas.


The Number of Student Images of the MoonKAM Education and Public Outreach Program is Over 70,000.


The Target Altitude of the CHEOPS Telescope is Equal or higher than 100 km.


The SAR Antenna Size of the CSG-SAR Synthetic Aperture Radar is ~7.5 m^2.


The Radiation Pattern of the Antenna Low-Gain Antenna is Broad-beam.


The Workshop Date of the Megha-Tropiques Satellite is 17-20 November 2014.


The Update Method of the Spectral Calibration Calibration is Vicarious techniques using the measurement of the atmospheric gas and/or the sun Fraunhofer lines.


The Ascender Weight of the Chang’e-5 Lunar Lander is 300 to 400 kg.


The ΔV of the NEA Scout CubeSat is Up to 2km/s.


The Observation Reach of the Roman Satellite is More than 13 billion years of cosmic history.


The Daily Coverage of the ZY-3A Satellite is 150,000 km2.


The Unknown of the IXV Spacecraft is Unknown.


The Imaging Technology of the IBEX Spacecraft is ENA (Energetic Neutral Atom) imaging.


The Components of the Camera Unit Calibration Assembly is Filters, spectral calibration sources (PTFE sun diffusers).


The Bands of the WFI Camera is Three visible bands and one NIR band.


The Beacon modulation of the RF communication subsystem Communication is OOK 15 WPM.


The Brigthness Temperature (BT) of the Antenna Reflector is 100~300 K.


The Energy Supply of the Payload Satellite Payload is Solar generator.


The URL of the SCD-2 Satellite is http://www.las.inpe.br/~veissid/eng18.html.


The Stages of the Vega Launcher Launch Vehicle is Three SRM stages, a liquid propulsion upper module.


The Communication Interface of the DCU Data Control Unit is Mil-STD-1553 bus.


The Year of Launch of the Terra Satellite is 1999.


The Beacon Period of the Spectrum Analyzer Device is 15 seconds.


The Single Point Acquisition Time of the Instrument Satellite Instrument is Less than 0.3 seconds.


The Locations of the LAPAN Ground Station Network is Rumpin and Rancabungur (Bogor), Bukittinggi (West Sumatra), Pontianak (West Borneo)and Biak (Papua).


The Mechanical Tests of the Biomass Satellite is Sine vibration, acoustic, shock and clamp-band release tests.


The Operating Voltage of the LVPS Board Power Supply is 28 V.


The Current Dependence of the Sensor Gas Sensor is Linear dependence on the oxygen partial pressure.


The Calibration Source of the LISS-3 camera Camera is LEDs (1.55 µm).


The Grating Type of the MEGS Spectrograph is Dual, holographic, spherical grating.


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


The Equator Crossing Time of the ResourceSat-2A Satellite is 10:30 AM.


The Command Execution Method of the Spacecraft Satellite is Immediate or Time-tag queue.


The Handle Distance from Center of the The Teacup Quasar is Around 30,000 light years.


The Field of View of the ART-XC Instrument Telescope is 36' diameter.


The Symmetry of the Earth's main magnetic field Magnetic Field is Not Geometrically Opposite.


The Launch Date of the CryoSat-2 Satellite is April 8, 2010.


The Brigthness Temperature (BT) Sensitivity of the Antenna Reflector is ±0.18 K.


The Pseudo-sounding Capability of the AMI Imager is Provides atmospheric instability information.


The Altitude of the MICROSCOPE Satellite is 710 km.


The Application of the Scanning Shack Hartmann Sensor Wavefront Measurement Device is Measurement of the human eye.


The Maximum Quantum Efficiency of the Kruiz CCD Detector is 0.33.


The Objective of the DRR Data Routing and Retrieval is Deliver global SMD (Stored Mission Data) to four US Operational Processing Centers.


The Technical Commissioning Completion Date of the SPOT 6 Satellite is January 2013.


The Performance Independence of the Instrument Unknown is Independent of variations of the receiver gain.


The Secondary Orbit Altitude Goal of the HAPS Hydrazine Auxiliary Propulsion System is 1200 km.


The Provider of the RTOS Real Time Operating System is VxWorks.


The Components of the TESIS Telescope-spectrometer is TESIS-BD, TESIS-BE, TESIS-OD.


The Maneuver Execution Time (240 minute window) of the RASP Maneuver Planning System is 143.36 minutes.


The Function of the TMTC Interface Software Layer is Telemetry and telecommand interface.


The Heater Lines of the STC Survival Thermal Control is 8.


The Objective Type of the Optics Subsystem Camera Subsystem is Ritchey-Chrétien type with auxiliary lenses.


The Deployment Status of the AstroTubeTM Boom Boom is Deployed to full length.


The GSD of the Spectral Band C Spectrometer is 5.


The Mission of the SOHO Satellite is Solar and Heliospheric Observatory.


The Authors of the Interstellar Boundary Explorer Satellite is D. J. McComas, F. Allegrini, P. Bochsler, M. Bzowski, E. R. Christian, Gjson B. Crew, R. DeMajistre, H. Fahr, H. Fichtner, P. C. Frisch, H. O. Funsten, S. A. Fuselier, G. Gloeckler, M. Gruntman, J. Heerikhuisen, V. Izmodenov, P. Janzen, P. Knappenberger, .


The Grating Angle of the UVS Instrument Spectrometer Telescope is 22.7º.


The Ground Segment Antennas of the IXPE Satellite is 10 m antennas at Malindi (primary) and Singapore (backup).


The Capacity of the Batteries Power subsystem is 7 Ah.


The Altitude of the SkySat-16 to -18 Satellite is 575 km.


The Orbit Type of the Satellite Constellation Satellite Constellation is Elliptical sun-synchronous dawn-dusk.


The Data Size of the Processed Science Data Packet Data Packet is 36 bytes.


The Distance from Earth of the Pulsar Neutron Star is Unknown.


The Launch Date of the HTV-7 Cargo Vessel is 22 September 2018.


The Autonomy of the F-DUGS Center is Operated by French personnel.


The Mission Design of the CICERO Satellite is Microsatellite to a 6U CubeSat Form Factor.


The Celestial Sphere Coverage of the Spacecraft Satellite is 50% during the extended mission phase.


The Edition of the Observation of the Earth and Its Environment: Survey of Missions and Sensors Documentation is 4th.


The RF Communications of the Spacecraft Satellite is 437.365 MHz.


The Power of the SCD-2 Satellite is 110 W.


The Spectral Band of the Camera Imaging Device is 744-826 nm.


The Status of the PAZ Satellite is In launch preparation.


The Mission Management Provider of the Lucy Satellite is Goddard.


The Launch Date of the TUBSAT Satellite is September 13-16, 1993.


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


The Observation Target of the NICER/SEXTANT Instrument is Neutron stars and pulsars.


The Telemetry Format of the Instrument Sensor is PCM (Pulse Code Modulation).


The Separation Distance of the Satellite Constellation Satellite Constellation is 100-1000 km.


The Radio and Reaction Wheels Current of the MarCO-B Satellite is Significantly more.


The Presentation Date of the SEDA-AP Instrument is August 3-6, 2010.


The Vector Components Random Error of the Ion Drift Velocity Satellite System is < 200 m/s.


The Launch Date of the SpaceX-CRS-4 Dragon capsule Cargo Capsule is Sept. 21, 2014.


The Flight Heritage of the MHX-2400 S-band Transmitter/Transceiver is 4 missions.


The Launch Date of the BeiDou-1A Satellite is Oct. 31, 2000.


The Manufacturer of the SARah-1 Earth Observation Satellite is Airbus.


The Sail Shape of the Drag Sail Modules Satellite Component is Trapezoidal.


The Data of the ICEYE Satellite is Used to monitor oil wells and measure global oil storage.


The Expansion Time of the BEAM Expandable Habitat is Seconds.


The In-situ Measurements of the ICON Space Mission is Provide the ability to explain how energy and momentum from the lower atmosphere propagate into the space environment.


The Global Ocean Color Data Recording Time of the Sentinel-3B Satellite is Less than 1.9 days at the equator, and in less than 1.4 days at latitudes higher than 30º.


The Energy Source of the Electric Power Subsystem Power System is Solar cells.


The Sensor Type of the CubeSense Attitude Determination and Control Subsystem is Integrated sun and nadir sensor.


The Quantity of the ICEYE US Satellites Satellite is 2.


The Spacecraft Type of the CHOMPTT Satellite is 3U.


The Discovery Date of the Integral Satellite is 20 Oct. 2003.


The Effect of the Galactic Cosmic Rays Cosmic Phenomenon is Penetrate Earth's magnetic fields and interact with the atmosphere.


The Discovery of the ASIM Instrument is Recently detected a unique gamma-ray burst from outer space.


The Operation Start of the Experiment Unknown is Launch.


The Spectral Range of the Spectrometer Instrument is 5-11 µm.


The Years on Orbit of the EO-1 Satellite is 13.


The Role of the INTEGRAL and XMM-Newton Satellite Missions is Follow-up of recent gravitational wave detections.


The Categories of the L1-SAIF+ Satellite Message is "SBAS-compatible" and "SBAS-incompatible".


The Observation Date of the ADONIS Instrument is 1996.


The Date of the Long-lasting Dust Storm from Chihuahua Image is 18 March 2021.


The Along-track FOV of the TIR Subsystem Imaging System is ±0.65º.


The Object Match of the CSpOC Catalog Catalog is Correct.


The Prime Instrument Contractor of the IASI Instrument is Alcatel Space.


The Number of Technologies of the CFESat Satellite is 8.


The Conference Date of the COSMO-SkyMed Satellite is Nov. 27-29, 2006.


The Energy Range for He of the LEICA Particle Detector is 0.45 - 6.1 4.3 - 38 7 - 20 18 - 350 MeV/n.


The Funding of the NIRCam Near-Infrared Camera is NASA.


The Spatial Resolution of the GHGSat-D Satellite System is 100 x better than the current state-of-the-art.


The Initial Acquisition Time of the CAPSTONE Spacecraft is Six days.


The Analysis of the Unresolved Imagery Data is Analyzing the spectral frequencies and temporal changes in the intensity.


The Sea-Level Rise Contribution of the Greenland and Antarctica Locations is About 11 mm.


The Detector Systems of the Spectrometer Instrument is 7.


The Launch Vehicle of the KANOPUS-V-IK Satellite is Soyuz-2.1a.


The Size of the StudSat Picosatellite is 10 cm x 10 cm x 13.5 cm.


The Test Period of the Sloshsat-FLEVO Satellite is About a week.


The Internal RAM of the OBC Onboard Data Handling is 4 kB.


The Launch Time (CEST) of the ESAIL Microsatellite is 03:51.


The Development Prize Date of the Global Change Observation Mission 1st – Water “SHIZUKU” Satellite is October 17, 2013.


The Sensitivity of the STROFIO Instrument is 0.14 counts/s when the density is 1 particle/cm3.


The URL of the Evaluation Process is https://spacenews.com/nasa-continues-csda-program/.


The Apogee of the Explorer 36 Satellite is 1570 km.


The Material of the Adsorbent Bed Component is Zeolite.


The Solar Array of the EPS Electric Power Subsystem is Articulated, 1 wing, 2-axis tracking.


The Antenna Weight of the PRARE ground transponder Ground Station Equipment is 42 kg including gearing unit.


The Attitude Determination and Control Subsystem Calibration of the Spacecraft Satellite is Ongoing.


The Segmentation of the LET Detector is Central bull’s-eye surrounded by a wide annular region.


The Data Processing Provider of the CloudSat Satellite is CIRA (Cooperative Institute for Research in the Atmosphere) of CSU (Colorado State University).


The Time Between Monitoring Campaigns of the OSIRIS Narrow Angle and Wide Angle Cameras Imaging System is Reduced to a few days.


The IFOV of the Earth Radiation Budget Experiment (ERBE) Instrument is 14 mrad.


The Instrument Type of the DMC-3 Satellite Constellation is Imaging multi-spectral radiometers (vis/IR).


The Bistatic Imaging of the TDX/TSX Satellite is Provides additional observables for the extraction of new scene and target parameters.


The Geometry Factor of the LEICA Particle Detector is 0.8 cm^2 sr.


The Planned Instruments of the FY-3RM Satellite is Ku/Ka band radar, microwave sounding and imaging instruments.


The Swath Width of the TopSAR narrow Imaging Mode is 100 - 150 km.


The Operation of the ULF Sensor Sensor is Continuous.


The Landing Accuracy of the Philae Lander Spacecraft is Less than 100 m from the planned Agilkia site.


The Kinematic properties of the β meteoroid Interplanetary Dust is > 77 km/s.


The Total Mass of the MERLIN Satellite is 430 kg.


The Mission of the Beowulf Cluster Computing Cluster is First in Space.


The Antenna Type of the Antenna Reflector is Dual Paraboloidal Reflector.


The Power Capacity of the Platform Satellite is 3 kW.


The Reproduction of the Bdelloids Species of Rotifers is Produce offspring from unfertilized eggs.


The Launch Date of the Aalto-1 Nanosatellite is Feb, 5, 2012.


The Function of the TEMPO Instrument is Provide near-real-time North American air quality information.


The Aviation Market Ranking of the India Country is Third largest.


The Tracking Duration of the TiPS Assembly Satellite is One year.


The Configuration of the STOs and STAEs Analog Electronic units is 3 on but 2 in operation.


The Test Number of the File Transfer Test Communication is 4.


The Influence on Storm Growth of the Drop Size Distribution Meteorological Phenomenon is Changes the rate of evaporation of rain, affects storm structure and behavior.


The NEΔT (K) of the ICI-8 Radiometer is 1.3.


The Launch Confirmation Date of the Telesat LEO Phase 1 Satellite is 12 Jan. 2018.


The Launch Mass of the FY-3 series spacecraft Satellite is 2450 kg.


The Characteristics of the Dark Matter Hypothetical Matter is Weird, unexpected.


The Comet Discoveries of the SOHO Satellite is 2000.


The J2000 right ascension (deg) of the GROJ1744-28 Pulsar is 266.138.


The Combined Weight of the Tiangong Space Station is Nearly 70 metric tons.


The Launch Date of the GCOM-W1 Satellite is May 17, 2012.


The Cross-Track Scanning Technique of the MERSI-RM Radiometer is 4096 samples.


The Development Date of the ETS-VIII Satellite Satellite is 2003.


The Microprocessor of the ADCS Attitude Determination and Control Subsystem is 32-bit ARM.


The Launch Window of the Gaia Satellite is 17 December to 5 January 2014.


The Lander/Rover Soft Landing Time of the Tianwen-1 Probe is 2–3 months after arrival of the spacecraft.


The Mass of the Spacecraft Repeater Communication Device is 24 kg.


The Power Source of the EPS Electrical Power Subsystem is Solar cells and lithium-ion battery.


The Inclination of the Spacecraft Orbit is 98°.


The Channel Wavelength of the SAM-II Instrument is 0.98-1.02 µm.


The Wavelength of the VIS (red) Band is 0.65 µm.


The Operational Cadence of the Instrument Satellite Instrument is Rotate 120º in < 2 minutes to blackbody view.


The Publication Date of the Solar Backscatter Ultraviolet/Total Ozone Mapping Spectrometer (SBUV/TOMS) Spectrometer is 1975.


The Responsible Agency of the DWSS Satellite is DoD.


The Drift Speed of the Great Red Spot Atmospheric Anticyclone on Jupiter is Circling the planet in about four-and-a-half years.


The Frequency of the ADS-B Air Traffic Surveillance System is 1090 MHz.


The URL of the Rosetta Satellite is http://www.esa.int/Our_Activities/Space_Science/Rosetta/Rosetta_factsheet.


The Under Voltage Cut Off of the DC-DC converter Power Converter is Yes.


The Sensor Types of the InSight Mars Lander is Wind, temperature, pressure, magnetometer.


The Accommodation Location of the ASIM Payload is Starboard deck of the CEPF.


The Launch Date of the Claire Satellite is February 2018.


The Collaboration of the TES Satellite Instrument is Close collaboration with the IASI scientists.


The AWiFS Data Access of the Resourcesat-1 Satellite is Unknown.


The Arrival Date of High-energy Neutrino of the IceCube Neutrino Observatory Neutrino Detector is 22 September 2017.


The Mass of the Genesis-2 Spacecraft is 1360 kg.


The Launch Date of the SPOT-2 Satellite is Jan. 22, 1990.


The Data Usage of the AVHRR/3 Visible and Infrared Spectral Bands Instrument is Provide image data in the visible and infrared spectral bands, information on cloud coverage within the footprints of the various sounding instruments.


The Antenna Type of the Knudsen Station Ground Station is Two phased 2MCP8A circularly polarized VHF yagis with polarizer switching capabilities.


The Capacity of the Power Storage Battery is 5 Ah.


The Launch Date of the NRCSD CubeSat Deployer is January 9, 2014.


The Operational Environment of the m-NLP system Langmuir Probe System is LEO up to 1000 km altitude.


The Support Plan of the KOMPSAT-2 Satellite is Support key technologies for application in the private sector and to promote the relevant industries.


The Launch Date of the Biomass Satellite is April 2024.


The Inclina. (º) of the Meteor-1-1 Satellite is 81.2.


The Data Record Start of the CERES FM6 Satellite is 1997.


The Data Archiving Site of the Deployment Systems Satellite is Las Vegas.


The Nominal Average of the Data Generation Rate Full Payload is 120 kbit/s.


The Data Storage of the SCP Spacecraft Process Controller is Half of programming space.


The Mass-Cage Contact of the Inertial Sensors Sensor is 5 µm diameter gold wire.


The Life-Test Status of the NIRISS Dual Wheel Cryogenic Mechanism Mechanism is Not Provided.


The Launch Time of the BRO-1 Satellite is 00:12 NZST.


The Fly on of the HIRS/4 Infrared Sounder is NOAA-N, NOAA-N', and MetOp 1 and 2.


The Reentry Capsule Recovery Date of the Hayabusa-2 Spacecraft is 6 December 2020.


The Launch Vehicle of the Galileo FOC satellites Satellite is Soyuz ST-B/Fregat-MT.


The Announcement Date of the Iridium Certus service providers Service Providers is February 28, 2018.


The Development Status of the Mission Control System Ground Segment Component is Currently being developed.


The Number of Collision Warnings Provided in 2014 of the JSpOC Joint Space Operations Center is 671,727.


The Enclosure Material of the VLF Antenna Antenna is Plastic.


The Function of the PTT Platform Transmitter Terminal is Collect and process relevant environmental data and transmit them to the NOAA-POES satellites.


The Number of Arrays of the FPA (Focal Plane Assembly) Detector Arrays is 4.


The Kinematic properties of the ISD Interstellar Dust is 25 km/s, ecliptic longitude of 252º & ecliptic latitude of 5º.


The Orbit Type of the Landsat 9 Satellite is Sun-synchronous near-circular orbit.


The Launch Date of the M6P and M12P Nanosatellite Buses is Early 2023.


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


The Conference Presentation Date of the GOMX-1 Satellite is April 23-25, 2014.


The Frequency of the MosaicGNSS receiver GPS Receiver is Single.


The Function of the Optical Telescopes Instrument is Determine the trajectory of an orbiting object, determine the object's attitude, physical profile, and features.


The Operation of the Automated Beacon Network Anomaly Detection System is Notifies on-call operators and initiates response actions.


The Number of Mirror Modules of the ART-XC Instrument Telescope is 7.


The Point of No Return of the Event Horizon Black Hole Feature is The point of no return.


The Total Mass of the PHM Instrument is 18 kg.


The Science Mission Duration of the LRO Satellite is 9/17/2010 - 9/16/2012.


The Mission Type of the AstroSat Astronomy Satellite is Non-EO.


The Birthday of the PROBA-V Satellite is May 7, 2014.


The On-Orbit Duration of the AIM spacecraft Satellite is 7 years.


The Data Rate (max) of the STX-01 S-band Transmitter/Transceiver is 2000 kbit/s.


The Signal Loss of the Schiaparelli module Spacecraft is After one housekeeping data packet.


The Launch Date of the Sentinel-1C Satellite is First half of 2023.


The Communication Network of the TTCS Telemetry & Telecommand Subsystem is CAN (Controller Area Network) bus.


The Mission Objectives Achievement of the Alexander PhoneSat is More than 100%.


The Sensor Type of the MAGIC Magnetometer is Dual, 3-axis AMR (Anisotropic MagnetoResistive) sensor.


The Mission Expectations of the Chang'e-5 Lunar Probe is Major Contributions.


The Workshop Date of the GIRO GSICS Implementation of the ROLO model is November 2017.


The Optical Efficiency of the Overall System is 0.4.


The Presentation Date of the STSat-1 Satellite is Dec. 13-17, 2004.


The Size of the Spacecraft Satellite is 10 cm x 10 cm x 10 cm.


The Mission Status of the NigeriaSat-2 Satellite is Operating nominally.


The Latency Requirement of the S-1 NRT Product is Within 3 hours.


The Conference Date of the NPOESS Preparatory Project (NPP) Satellite is May 26, 2005.


The Sensor of the WorldView-3 Satellite is SWIR.


The Environmental Testing of the Deimos-2 Satellite is Verified.


The Image of the SJ-5 Satellite is Fluid two-layer flow liquid-bath.


The Operator of the Gonets-M No.3 Communication Satellite is Gonets Satellite Company.


The Main Structure Material of the UVNS Spectrometer is CFRP (Carbon Fiber Reinforced Polymer).


The Instrument Mass of the Instrument Spectrometer is 177 kg.


The Coded Data Rate of the X-band transmitter Transmitter is 441.625 Mbit/s.


The Survey Date of the Hera Spacecraft is Unknown.


The Power Consumption of the LEID Instrument is 2.9 W.


The Attitude Sensors of the ANUSat Satellite is Tri-axial magnetometer and an optical TWSS (Twin Slit Sun Sensor).


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


The Software Standard of the OBC On-Board Computer is PUS (Packet Utilization Standard).


The Crew Capacity of the Shenzhou-11 Spacecraft is 2.


The Material of the Outer Panels Satellite is CFRP (EX-1515/M55J + Redux 312L).


The Purpose of the MSPR-2 Rack is Conduct a variety of experiments.


The Pulse Repeat Frequency of the X-band Radar is 100 Hz.


The Instrument Operation Time of the Philae Lander is First 60 hours following the touch-down.


The Provider of the IR-Camera Camera is DLR-OS.


The Telescope Focal Length of the XMM Spacecraft is 7.5 m.


The Inclination of the Tsubame Microsatellite is 97.4º.


The Objective of the BIRD Satellite is Observe thermal processes on the Earth’s surface.


The Optics Type of the Imager Suite Imaging System is All-reflective.


The Image Resolution of the MTG-S Spacecraft Satellite is 0.5 to 2 km.


The Period of the Tatiana-2 Satellite is 101.3 minutes.


The Data of the LPR Radar is Electromagnetic image of the far side subsurface structure.


The Telescope Type of the TIR Subsystem Imaging System is Newtonian catadioptric system with aspheric primary mirror and lenses for aberration correction.


The Lifted atop launcher Date of the Landsat-9 Satellite is 21 September 2021.


The Transition Point of the STP-H8 and H7 Missions is Unknown.


The Launch Mass of the Gokturk-2 Satellite is ~ 450 kg.


The Re-use of Electronic Equipment of the Sentinel-5P Satellite is From several suppliers.


The Survey Date of the Gaia Satellite is 23 March 2022.


The Publication Date of the Nimbus-7 SBUV radiometer Radiometer is 1988.


The Sample Stowage of the OSIRIS-REx Spacecraft is Expedited.


The Bands of the Spectral bands Spectrometer is 0.52 - 0.60 µm (green), 0.63 - 0.69 µm (red), 0.76 - 0.89 µm (NIR).


The Ground Station of the RF Communications Communication System is SPIV (San Pietro in Vincoli).


The Rotation Rate of the Satellite Spacecraft is Less than 1º/s.


The Simulation of the YES2 satellite Satellite is Space Tether Deployment on Earth.


The | of the SSO-A SmallSat Express Mission is Spaceflight SSO-A: SmallSat Express Mission.


The Launch Date of the KySat-2 Satellite is 20 November 2013.


The GPS/QZSS Differential Code Biases Stability of the QZS-1 Satellite is Better than 1 ns.


The Development Contractor of the SSOT Satellite is EADS Astrium SAS.


The PPTs of the EPS Electrical Power Subsystem is 4 independent PPTs.


The Placement of the Aditya-L1 Satellite is Lagrangian point L1.


The Bandwidth of the NewMag Magnetometer is 10Hz.


The Attitude Control of the PhoneSat-2.5 Satellite is Reaction wheels.


The Future Investigator of the Athena X-ray observatory X-ray Observatory is ESA’s future Athena X-ray observatory.


The Last Eclipse Avoidance Maneuver Date of the Gaia Satellite is 16 July 2019.


The Contribution of the HARP-2 Instrument is PACE mission.


The Launch Date of the Iridium NEXT Satellite is January 8, 2017.


The Monitoring Method of the Ocean Acidification Environmental Phenomenon is Measurements of seawater pH.


The Ka-band Repeater of the Repeater subsystem Communication System is 5/3 simultaneously operating transponders at saturation.


The Spectral range of the MWTS Microwave Temperature Sounder is 50-57 GHz.


The Ground Qualification Completion of the Aquajet Satellite Propulsion System is 2009.


The Altitude of the Primary Payload Unknown is 1450 km.


The Temperature of the IEC ISIM Electronics Compartment is Room temperature.


The Communication Link of the Bus Satellite Component is S-band radio frequency (RF) link.


The Spatial Resolution of the Sentinel-2 Satellite is 10, 20 or 60 m.


The Sensor of the ESAIL Microsatellite is VDES (VHF Data Exchange System).


The Altitude range of the UV/VIS Spectrometer Spectrometer is 20 - 100 km.


The Accuracy of the ARI Infrared Spectrometer is Better than 0.1 K 3σ.


The Orbit Altitude of the ProSEDS Tether Demonstration Experiment is 400 km.


The Orbit of the INTEGRAL Satellite is Highly eccentric 64-hour orbit, coming as close as 10,000 km and as distant as 140,000 km from Earth.


The FOV Angle of the Lenses Optical System is 2.7º.


The Design of the PHA HiLRS is Small, low power.


The RF Labs Equipment of the CesiumAstro Company is High performance test equipment, multiple RF chambers, antenna ranges, and environmental test stands.


The Reflector Illumination of the Biomass Satellite is 3 x 2 array of cavity-backed circular microstrip radiators.


The Launch Date of the Iris Satellite is 2nd September 2020.


The Revenue of the Satellogic Satellite Company is $4.2 million.


The Orbital Period of the Beijing-1 Satellite is About 97.7 minutes.


The Spectral Range of the Ma_MISS Spectrometer is 0.4–2.2 µm.


The Simulation Levels of the SEXTANT ground testbed architecture Testbed is Level 0, Level 1, Level 2.


The Max Bandwidth of the Spacecraft 406 MHz Processor Processor is 80 kHz.


The Water Points Connection Goal of the Astrocast Satellite Operator is 150 water points in 2022 in Senegal.


The Components of the NRD Electronics is Industrial, or in some cases automotive, grade commercial off-the-shelf components.


The OBC OS of the Spacecraft Satellite is VxWorks.


The Solar Power Generation of the EPS Electrical Power Subsystem is 48 W.


The Cal_solar data Collection of the OCO-2 Satellite is Absolute and Relative Instrument Response Calibration.


The Purpose of the Mars Terrain Simulator Simulator is Validate and simulate ExoMars Rover Operations and to support the ExoMars Surface Mission.


The Acceleration of the Getz Glaciers Glaciers is Almost 25% on average.


The Hypothesis of the Blue Ring Nebula Nebula is Composed of debris from two stars that collided and merged into a single star.


The Instrument Type of the MFI Magnetometer is Dual triaxial fluxgate magnetometers.


The Number of Cells of the Photo-Voltaic Array Power Generation is 25 strings, 18 cells per string.


The Manufacturer of the CubeStack Multi CubeSat Adapter is LoadPath LLC of Albuquerque, NM.


The Measurement Range of the EIS Sensor is ~45 keV to 500 keV.


The Geometric Accuracy of the Atmospheric Correction Processor Image Processing is ~10 m RMSE linear.


The Connection of the BCR Battery Charge Regulator is One half of the solar cell strings on two opposite sides of the spacecraft.


The Partner Levels of the Planet Orbit Partner Program is Gold and Platinum.


The Number of Detectors of the Scanner Assembly Instrument is 96.


The Lower Tray Height of the SUNSAT Satellite is 12 cm.


The Application Date of the Sentinel-5P Satellite is 17 September 2020.


The Orbit of the SeaHawk-1 CubeSat is Sun-synchronous.


The Funding Status of the Worldview Legion Satellite Constellation is Fully able to fund.


The Memory Storage of the CPU Board Processor is 128 MB of DRAM for data memory storage and cache memory storage.


The Altitude of the BEESAT-4 CubeSat is 515 km.


The Trajectory of the Periselene-1 Spacecraft is One loop around the Earth with perigee > 100,000 km altitude.


The IFOV diameter of the Spectrometer Spectrometer is 14 km.


The Instrument Support Capacity of the Bus Satellite Component is Up to 206 kg.


The Microwave Scatterometer of the HY-2A Satellite Satellite is Unknown.


The Data Volume of the Mini-RF Instrument is 200 GB.


The Design Life of the QZS-1 Satellite is > 10 years.


The GPS Receiver of the KOMPSAT-6 Satellite is Dual-frequency GPS receiver for POD generation.


The Sigma 0 Range of the Radar Radar is HH, VV: +15~-25 dB.


The Orbit Duration of the International Gamma-Ray Astrophysics Laboratory Satellite is 1 Year.


The Reentry Outcome of the Drag Sail Satellite Component is Disintegrate.


The TT&C Uplink of the QSat Satellite is S-band, 1 kbit/s.


The Mass of the Spacecraft Satellite is 47 kg.


The Speed of the Material from Exploded Star Unknown is Faster than 20 million miles per hour.


The Manufacturer of the Eutelsat Quantum Satellite is Airbus Defence and Space and Surrey Satellite Technology Limited.


The SNR at Maximum Radiance of the Satellite Imaging Satellite is 100.


The Launch Date of the ALL-STAR Satellite is 18 April 2014.


The IFOVs of the Detectors Photovoltaic Detectors is 14 km.


The Gyroscope of the Pico Dragon CubeSat is 3-axis.


The Total Channels of the Spectral Bands Spectrometer is 1305.


The CPU of the C&DH Subsystem Command & Data Handling is RAD750.


The NESZ of the Radar Instrument is -29 dB.


The Spatial Resolution of the Spectral Channels Satellite Instrument is 28 µrad (1 km x 1 km at nadir) (+0-10%).


The Inclination of the Tandem-L satellites Satellite is 98.4º.


The Number of RF Signals of the Antenna Subsystem Satellite Component is 6.


The AIS Receiver of the NorSat-3 Satellite is ASR x50.


The Number of Antennas of the KSAT Ground Station Network is Over 200.


The Design Approach of the Constellation Satellite System is Low cost and low risk, doesn't sacrifice performance.


The Budget of the Copernicus Programme Satellite Programme is EUR 4.3 billion.


The Active Starlink Terminals Target in India of the Starlink Satellite Internet Service is 200,000.


The Type of the Laser Device is Unknown.


The Number of Holes of the Deployment Specialists Personnel is 86.


The Bus Technologies of the KOMPSAT-5 Spacecraft is Enhanced based on previous programs.


The Manufacturer of the Gaia spacecraft Satellite is EADS Astrium.


The Status and Performance of the CALIOP Lidar is Unknown.


The Image Capture Date of the Earth Observation Satellite Satellite is 25 June 2021.


The Calibration Device Quantity of the OMPS Sensor is Two diffusers for each sensor.


The Projectile Diameter of the Launcher Test Facility is Up to 203 mm.


The Delivery Date of the FSS Fine Sun Sensor is June 2015.


The FPA Size of the Telescope Optical Instrument is 1056 (spatial) x 256 (spectral) pixel.


The Absorber Material of the Imaging Calorimeter Calorimeter is Tungsten.


The Mission Completion Date of the Kepler Satellite is Nov. 14, 2012.


The Acceleration of the Getz Glaciers Glaciers is Over 44% for three glaciers.


The F/D of the Antenna Communication is 0.8.


The Type of Array of the VNIR Detector is Si.


The Quasi-Periodic Eruptions (QPEs) Frequency of the GSN 069 Black Hole is Every nine hours.


The Coverage of the 5G Network Telecommunications Network is Global, always-on network.


The Mission Type of the Galileo Satellite Navigation System is Non-EO.


The Functionality of the HISat Satellite is Complete satellite functionality in a nanosat-scale package.


The Attitude Determination Accuracy of the AOCS Attitude and Orbit Control Subsystem is ≤ 0.2º (3σ).


The | of the NOAA Goes-12 Solar X-Ray Imager Instrument is The NOAA Goes-12 Solar X-Ray Imager (SXI).


The Number of Experiments of the TPMU Device is 3.


The Science Payload Developer of the Neutron-1 Satellite is Arizona State University (ASU).


The Maneuver Date of the P2 Satellite is Early May 2012.


The Observation Contribution of the MAHRSI Instrument is Help quantify the contribution of water vapor exhaust injected into the upper atmosphere from the space shuttle to PMCs.


The Purpose of the GRIDS Ion Sensor is Measure the distribution, motion, and velocity of ions.


The Mission Phases of the Solar Orbiter Satellite is Cruise phase and Science phase.


The Booster's Previous Flight Date of the Falcon 9 Rocket is Jan. 20.


The Electrical Power System of the IOD-1 GEMS Satellite is CSL FlexU Electrical Power System (EPS).


The Sample Collection Location of the Chang'e-5 Spacecraft is Siziwang Banner, Inner Mongolia.


The Optical Beacons Modulation of the CHOMPTT Satellite is 1 Hz.


The Cross-Calibration Partner of the QuikSCAT Satellite is Indian Space Research Organization (ISRO) Oceansat-2 scatterometer known as OSCAT.


The Output Power of the HiSPiCO S-band Transmitter/Transceiver is 27 dBm.


The Flights of the AEPI Instrument is Spacelab-1.


The Development Challenges of the Infrared Sounder (IRS) Sounder is Utilizing a corner cube mechanism design with successful IASI flight heritage for the Infrared Sounder (IRS) on MTG; recurrent mechanical design not correlated to recurrent development.


The Burned Area of the Calf Canyon-Hermits Peak Fire Fire is Exceeded 300,000 acres.


The Cross-Track of the WAOSS-B Sensor is 50°.


The Function of the DDA Delay-Doppler Altimeter is Measure the along-track position of the range measurement.


The Debut Speed of the Iridium Certus Satellite Communication Service is 352 kbit/s.


The Resolution of the Satellite GEO (Geostationary Earth Orbit) is Δx = 62 km for Δθ = 0.1º.


The Presentation Date of the Attitude Control Module Small Satellite Component is August 13-16, 2012.


The Data Release Dates of the Gaia Satellite is 2016, 2018.


The GPS Receiver of the AOCS Attitude and Orbit Control System is Dual frequency GPS receiver (GPSR).


The Spatial Resolution of the SLSTR Spectral Imaging Instrument is 500 m.


The Power of the Satellite Bus Spacecraft Component is Approximately 1.9 kW.


The Design Drivers of the ACE-FTS Instrument is Sensitivity (SNR), Spectral Resolution, Large Spectral Coverage.


The BW Film Type of the Metric Camera Camera is KODAK Double-X Aerographic Film 2405.


The Spatial Resolution of the Solid Earth Lithosphere and upper mantle density structure Satellite is 100 km.


The Latitude Observation Point of the SHIMMER Satellite is Around 55º.


The Purpose of the BEAT experiment Ballistocardiography for Extraterrestrial Applications and long-Term missions is Measure an astronaut’s ballistocardiographic data, including pulse and blood pressure.


The Inclination of the CICERO-4 Satellite is 85º.


The Test Date of the SpinSat Satellite is May 21, 2015.


The BER (Bit Error Rate) of the Payload Downlink Communication System is <10-9.


The Mission of the PanFTS Panchromatic Fourier Transform Spectrometer is GEO-CAPE.


The Manufacturer of the OLA LIDAR Instrument is MDA (MacDonald Dettwiler & Associates) and Optech Inc..


The Project Scientist of the Parker Solar Probe Spacecraft is Nicola Fox.


The Commissioning Completion Date of the DubaiSat-2 Satellite is April 14, 2014.


The ΔRAAN of the Swarm-C (Charlie) Satellite is ~0-135º difference wrt mean plane of A/B.


The Instrument Mass of the Pushbroom imager Optics is 18.5 kg.


The Dark Matter Content of the Leo I Galaxy is Not much.


The Band-to-Band Alignment of the IRIS Instrument Spectral Scanner is 0.1 pixels.


The Robotic Arms of the Satellite Platform is Deployable.


The Frequency (GHz) of the ICI-5 Radiometer is 325.15±9.5.


The Longitude of the Meteosat-7 Satellite is 57.5 °E.


The Function of the Juventas CubeSat CubeSat is Perform the first radar probe of an asteroid.


The Voltage Output of the PSU Power Supply Unit is 4.1 V for safe battery charging.


The Inclination of the S/C Spacecraft is 80.2º.


The Orbital Period of the OceanSat-1 Satellite is 99.31 min.


The AGC Time Constant of the Receiver Communication System is ≤ 40 x10 -9 ms.


The Power of the Payload Satellite Subsystem is 3.5 W.


The Quantity of Faraday Cup Ion Detectors of the SWE Instrument Sensor is 2.


The Inclination of the Satellite SuperView Constellation is 98º.


The Type of the ULEIS Spectrometer is Time-of-flight (TOF) mass spectrometer.


The Ordering follow-up of the CSK GS Ground Segment is Allow the FM to keep S-IM informed about the progression of the order.


The Deployment Timing of the CanX-7 Drag Sail Payload is End of a six-month phase of secondary payload operation.


The Orbit Altitude of the JAWSAT Satellite is 753 km x 805 km.


The RF Output Power of the X-band Transmitter Transmitter is 6 W.


The Maximum Battery Power Before 100% Depletion in Orbits of the Satellite Spacecraft is 2 orbits.


The Number of X-ray mirror module assemblies of the IXPE observatory X-ray Observatory is 3.


The URL of the AstroSat Satellite is http://www.tifr.res.in/~laxpcworkshop14/presentations/LAXPC_WORKSHOP%20%20_3-k%20s%20sharma.pdf.


The Launch Date of the Integral Satellite is 2002.


The Mission Observation Period of the TanDEM-X Satellite is 21 September 2017 until June 2020.


The Funding Requirement of the 90-satellite constellation Satellite Constellation is Another equity funding round, cash flow from operations and debt.


The Polarization of the ICI-2 Radiometer is V.


The Orbit Period of the Beijing-3B Satellite is 96.8 minutes.


The Field of View of the WAC Wide-Angle Camera is Large portions of Europa's landscape.


The Distance from Sun of the Solar Orbiter Satellite is Roughly 75 million km.


The Energy Range of the CXBN-2 X-ray Detector is 30-50 keV.


The Orbit Type of the SWFO-L1 Satellite is L1.


The URL of the Magnetospheric Multiscale Mission Satellite is https://www.nasa.gov/feature/goddard/2018/nasa-s-magnetospheric-multiscale-mission-locates-elusive-electron-act.


The Mission Status of the Resurs-P1 Satellite is Operational.


The Apogee of the IBEX Spacecraft is 319,000 km.


The Cu Foil Thickness of the RADFET Dosimeters Dosimeter is 50 µm.


The Detection of the Van Allen Probes Satellite is Increased number of even higher energy electrons.


The Prime Contractor of the SloshSat-FLEVO Satellite is NRL (National Aerospace Laboratory).


The Area in 2016 of the Ozone Hole Atmospheric Phenomenon is 23 million km2.


The Material of the Outer Shield Instrument Component is Aluminum.


The Total Number of Solar Cells of the TCS Thermal Control System is 190.


The LTDN of the Aalto-1 Satellite is 9:30 hours.


The Water Capacity of the Steam Propulsion Unit Propulsion is Up to 30 grams.


The Mass of the Instrument Satellite Instrument is 15 kg.


The Affiliation of the Yuji Sakamoto Author is Unknown.


The Calibration Activities of the GCOM-C Satellite is On-orbit.


The Inclination of the Satellite HY-1B is 98.8º.


The Reaction Wheels of the NEMO-AM Satellite is Quantity: 3, Manufacturer: SI, Momentum Storage: 60 Nms, Maximum Torque: 2 mNm, Maximum Torque Jitter: 5 x 10-5Nm.


The Measurement of the HGA High Gain Antenna is HGA gain.


The Booster of the Falcon 9 Rocket is B1060.


The Bandwidth (GHz) of the ICI-5 Radiometer is 6.


The Position of the VACCO MiPS cold gas thruster Thruster is Aft end (–y).


The Spectral Coverage of the Hyperion Imaging Spectrometer is 400 - 2500 nm.


The Apogee of the FASat-Alfa Satellite is 682 km.


The Cost of the Prometheus Block 2 CubeSats Satellite is Less than $100,000.


The Imaging System of the NewSat Satellite is Multispectral imager.


The Data Processing of the Satellite Satellite is Real-time.


The Bias Voltages of the EPE Energetic Particle Experiment is 1.25-1.5 times the values required for full depletion.


The Map Production Time of the SMOS Satellite is Within 24 hours.


The Operational Modes of the MIRAS Instrument is Dual-polarization or full-polarimetric.


The Orbit Life Without Balloon of the AeroCube-3 Satellite is 1-3 years.


The ROM/RAM of the SHU Science Handling Unit is EEPROM(128KB x 2), SRAM(8MB x 4), FROM(128MB).


The End of Life Date of the GEOSAT Satellite is January 1990.


The Effective Area of the Telescope Optical Instrument is ~ 15 cm2 for FUV channel, 15-40 cm2 for NUV & VIS channels.


The Inputs of the Active Schedule Planning Product is Mission Timeline, LMOC downtimes, OGS availability schedules, external interfaces availability, predictive avoidance constraints, experiment plans, user service requests.


The Battery of the IOD-1 GEMS Satellite is CSL 30 Whr Battery.


The Separation Distance of the Slits Optical Instrument is 4.5 mm.


The Power of the LISS-4 Camera is 216 W.


The Purpose of the MGF Instrument is Measure deviations of the magnetic fields during space storms.


The Status of the X-SAT Satellite is Functioning Satisfactorily.


The Field of View of the ELENA Instrument is Nadir pointing 1-D FOV.


The Effective Area of the EUV Simulation Simulation is 43 cm2.


The Data Used of the DInSAR Differential SAR Interferometry is TOPS (Terrain Observation with Progressive Scan).


The Drag Sails Deployment Date of the CanX-7 Satellite is May 3, 2017.


The Absolute Solar Shape Precision of the Instrument Optical Instrument is Better than 10 marcsec (milli-arcseconds).


The Hardware of the ACS Attitude Control System is Controlled by ACS flight software.


The Acquirer of the JPSS-1 Satellite is NOAA (National Oceanic and Atmospheric Administration).


The Mission Date of the Solar Probe Plus Satellite is Sept. 27-Oct. 1, 2010.


The Attitude Control of the ADCS Attitude Determination and Control Subsystem is Magnetorquers and reaction wheels.


The Re-entry Date of the Satellite Satellite is 8 December 2011.


The Complete Global DEM Availability Date of the TanDEM-X Satellite is September 2016.


The Applications of the Sich-2 Satellite is Monitoring of natural resources, rational nature management, Agriculture, land use, town building, environment pollution monitoring and evaluation, mapping, Diagnosis and forecast of technogenic and natural cataclysms, Monitoring of ionosphere parameters.


The Data Collection of the Rosetta Satellite is Comet's dust, gas and plasma environment, its surface characteristics and its interior structure.


The Partial Services Start Year of the OneWeb Low-Earth-Orbit Broadband Venture is 2021.


The Spatial Resolution of the IRIS Observatory is Between 0.33 and 0.44 arcseconds.


The Pupil Diameter of the NAOMI Imager is No longer sized to comply with SNR requirements.


The Protective Layer of the FPI Mirrors Component is 50 nm layer of silicon dioxide (SiO2).


The Technology Demonstration Phase Duration of the GomX-4B Satellite is 6 months.


The Anomaly Investigation Duration of the NextSat Satellite is Additional week.


The TAG Date of the OSIRIS-REx Spacecraft is Up to asteroid departure in March 2021.


The Mass of the Spacecraft Satellite is 2120 kg.


The Size of the PhiSat-1 Satellite is About the size of a cereal box.


The Responsibilities of the MC Mission Center is Mission planning and scheduling, X-band ground stations data reception scheduling, Payload telecommands management, Commands generation for detectors, PMS, and X-band subsystems, Command execution verification, TC plan (telecommands) sending to the CCC, S.


The Mass of the Geoton-L1 imager Instrument is 310 kg.


The Tandem Mission End Date of the Envisat / ERS-2 SAR Satellite is Late April 2009.


The Design of the Resurs-P Satellite is Modular.


The Collision Date of the A-74 iceberg Iceberg is 19 May 2021.


The Product Type of the Sentinel-1 Satellite is GRD (Ground Range Detected).


The Purpose of the Spectrometer Instrument is Separation of atmospheric extinction along the line-of-sight due to Rayleigh scattering, aerosols, ozone, nitrogen dioxide, water vapor concentration profiles, and aerosol detection.


The Function of the NuDose ASIC is Force a specified current through the RADFET.


The Location of the LIS Lightning Imaging Sensor is ISS.


The Total Mass of the HREP Instrument is 381 kg.


The Repeat Cycle of the OceanSat-1 Satellite is 2 days.


The Seismometer Deployment Date of the InSight Lander Lander is December 19, 2018.


The Measurement of the OCO-3 Instrument is CO2 Mole Fraction.


The Manufacturer of the ERNO-Box Computer is Astrium Space Transportation in Germany.


The Developing Entity of the MoonLIGHT Satellite is Italian National Institute of Nuclear Physics (INFN) in Frascati.


The Participating Countries of the Euclid Mission Consortium Consortium is Italy, France, Germany, Denmark, Portugal, Spain, The Netherlands, Norway, Romania, United Kingdom, Finland.


The Type of the First FPGA FPGA is GNSS receiver core functions.


The Total Firings of the LM thruster Thruster is More than 85.


The Measurement of the SKIM Satellite Mission is Ocean-surface currents.


The Function of the Battery Holder Electrical Power Subsystem is Battery control, battery overcharge protection and bus voltage regulation.


The Launch Date of the Kleos Scouting Mission (KSM1) Satellite is November.


The Ground Resolution (ScanSAR mode) of the XSAR SAR is Varying between 8 m and 20 m.


The | of the Juan Yin, Yuan Cao, Yu-Huai Li, Ji-Gang Ren, Sheng-Kai Liao, Liang Zhang, Wen-Qi Cai, Wei-Yue Liu, Bo Li, Hui Dai, Ming Li, Yong-Mei Huang, Lei Deng, Li Li, Qiang Zhang, Nai-Le Liu, Yu-Ao Chen, Chao-Yang Lu, Rong Shu, Cheng-Zhi Peng, Jian-Yu Wang, and Jia Authors is | False.


The Clock Frequency of the dsPIC33F microcontroller Microcontroller is Unknown.


The Storage Capacity of the Spacecraft 406 MHz Processor Processor is 324 kbit.


The Announcement Date of the SmallGEO Extension Satellite Extension is Sept. 30, 2011.


The Operator of the Canadarm2 Robotic Arm is Astronauts.


The Duration of the TTTC Imaging System is Longer than the data take itself.


The Anomaly Date of the Chandra X-ray Observatory X-ray Observatory is Aug. 24.


The Analog Outputs of the GOCI-II CMOS Imaging Sensor CMOS Imaging Sensor is 10.


The Orbit Altitude of the Odin Satellite is 600 km.


The Mass of the TriG GNSS-RO payload Instrument is 115 kg.


The Guard Angle of the MXT Instrument is 20°.


The Stability of the DSAC Clock is 100 times more stable than today's best navigation clocks.


The Number of Channels of the Interferometer Arrays Imaging Technology is Same as a digital camera.


The Launch Date of the OPAL Satellite is Jan. 27, 2000.


The Length of the Genesis-2 Spacecraft is 4.4 m.


The Instruments of the HJ-1 Satellite is S-Band SAR.


The Pointing Accuracy of the ADCS Attitude Determination and Control Subsystem is ≤ 0.1º (triaxial, 3σ).


The Quantity of the Magnetic Field Sensor Sensor is 5.


The Surface Accuracy Goal of the Reflector Assembly Satellite Component is 1.0 mm rms.


The Propellant Duration of the Butane Propulsion System Propulsion System is 3-4 years.


The Mass of the CINEMA-2 Nanosatellite is 4 kg.


The Mission Objective of the Juice Spacecraft is Study the potential habitability and the underground oceans of Ganymede, Callisto and Europa.


The Presentation Date of the RapidEye Earth Observation Constellation is Sept. 29 to Oct. 3, 2008.


The Management of the CTDA Component is Counts with a central management point for the tasking and cataloguing of information.


The Mission Lifetime of the EarthDaily Constellation Satellite Constellation is 10 years.


The Thrust Source of the LightSail-2 Spacecraft is Solar sails.


The Upper Stage Payloads of the Rocket Launch Vehicle is 114.


The URL of the Jaan Praks Person is https://web.archive.org/web/20160304222738/http://tstc2014.to.ee/download/m5429b9e5144f8.


The Filter Spectral Bands of the EXI instrument Imaging Instrument is UV1: 245-275 nm, UV2: 305-335 nm Blue: 427-447 nm, Green: 536-556 nm, Red: 625-645 nm.


The Power Consumption of the Myriad RF board RF Board is > 4 W.


The Sweep Duration of the FTS Interferometer Interferometer is 2, 1, 0.5, 0.1 s.


The Components of the Antenna/Drive/Calibration Subsystem Subsystem is Conical corrugated horn-fed shrouded reflector, multiplexer, closed-loop antenna scan drive assembly and closed path calibration assembly.


The Measurement of the ALACE Floats Oceanographic Instrument is Global subsurface circulation.


The Components of the OCO-2 MIP Project is Four different transport models with varying configurations, multiple different data assimilation frameworks, and diverse prior fluxes and uncertainties.


The Presentation Date of the COMS Satellite is July 12, 2005.


The Berthing Date of the Dragon spacecraft Spacecraft is 2 July 2018.


The Cion Size of the CICERO-6 6U CubeSat is 30 x 10 x 6 cm.


The Additional Calibration of the Mini-RF Instrument is Conducted on the flight instrument during thermal vacuum temperature ramp cycles.


The Measurement Capability of the NICER X-ray Instrument is Cooling histories of young neutron stars.


The Inclination of the Secondary Payloads Unknown is 69.5º.


The Purpose of the Wireless Compose-2 Wireless Network Infrastructure is Conduct and execute low-power, low-weight, and wireless experiments on the International Space Station (ISS).


The In-Orbit Calibration Plan Presentation of the Microscope Space Mission is Sept. 23-27, 2013.


The Function of the NAC Camera is Highlights variations in soil moisture content and vegetation density.


The Operational Ranges for non-main windows position of the NightPod Tracking Device is 1st:Yaw ±60º, 2nd:Roll +40º/-20º (constrained by NightPod geometry), 3rd:Pitch nodding ±20º.


The Data Usage of the Satellite Earth Observation Satellite is Critical role in the resiliency mindset.


The Location of the WIND Satellite is L1 halo upstream of Earth.


The Observation Modes of the StriX-α SAR Satellite is Stripmap and Sliding Spotlight mode.


The Purpose of the Remote Agent Software is Reduce the cost of future S/C operations.


The Image Release Date of the SMART-1 Satellite is Sept. 29, 2014.


The Detection Capability of the Satellite-based Radar Radar is Ripples and splashes caused by falling raindrops.


The Program Duration of the SOHLA-1 Satellite is 5 years.


The Docking Time of the Starliner Spacecraft is 26 hours after launch.


The Data Impact of the Aeolus Satellite is Positive impact of the data obtained in 2019 was roughly twice as big as it is now.


The Orbit Period of the SuperView-1 01 and Superview-1 02 Satellite is 97 minutes.


The Orbit Inclination of the Argos-4 Satellite Instrument is 98º.


The Primary Payload of the NROL-36 Satellite is NRO/MSD classified spacecraft.


The Spatial Resolution of the SLIM6 Satellite is 32 m GSD.


The Same Instrument as of the MAHRSI Instrument is STS-66 mission (CRISTA-SPAS-1).


The Quantity of the MnACQ-2000 Miniature Network Data Acquisition System Data Acquisition System is 9 units.


The Frequency of the Unit Communication System is 435 MHz.


The Field of View of the EXI instrument Imaging Instrument is 19.0º.


The Solar Conjunction Operation Period of the Hayabusa-2 Spacecraft is Late November 2018 until the end of December 2018.


The Passes in 1-year mission lifetime of the Satellite Satellite is ~1000.


The Wavelengths of the PACS Far-infrared camera is 70 µm (blue).


The Size of the RainCube Satellite is About the size of a cereal box to a toaster oven.


The Bus Integration and Testing Location of the Neutron-1 Satellite is Hawaii Space Flight Laboratory (HSFL).


The First Flight Date of the SLS Rocket is 2020.


The Processor of the MPM Main Processor Module is LEON2-E Sparc V8 processor.


The Software of the OBC On-Board Computer is FCS (Flight Control Software).


The Mission Status of the NanoSail-D2 Solar Sail is Active.


The Mission of the IBEX Satellite is Interstellar Boundary Explorer.


The Modules of the TTC Rx Receiver is LNA (Low Noise Amplifier), 208F Frequency Synthesiser, 10M7 Phase Detector, Power Supply.


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


The FOV of the CIRiS Instrument is 12.2º x 9.2º.


The Sensor complement / remarks of the Intercosmos- Bulgaria 1300 (Intercosmos-22) Satellite is Bulgarian sensors on Meteor-2 satellite technology (ionospheric plasma and high-energetic fluxes of charged particles, electric and magnetic fields, etc.).


The Communication Protocol of the Ground Software Architecture System is TCP/IP.


The Launch Provider of the TecSAR Satellite is Indian PSLV.


The RF Communications Band of the Kanopus-V 1 Satellite is X-band.


The Conference Location of the Trailblazer CubeSat is St. Louis, Missouri, USA.


The Number of Operational RAFS Clocks of the GIOVE-A Satellite is 1.


The Spin Frequency of the Myriade series spacecraft Satellite is Orbital Frequency.


The Default Propulsion Module of the Myriade Bus Satellite Bus is Hydrazine propulsion module provided by Airbus Defense and Space.


The Future Mission of the GEO-CAPE Geostationary Coastal and Air Pollution Events satellite is Yes.


The In-Flight Pointing Control Accuracy of the EFI (Electrical Field Instrument) Instrument is 5º.


The Processor of the Controller card C&DH Subsystem Component is PowerPC processor.


The Dry Mass of the EAGLE ESPAStar Satellite is 430 to 470 kg.


The Contract of the Thales Alenia Space Company is Won the first Spacebus Neo commercial satellite contract for a Broadband for Africa mission with Eutelsat (BB4A) to be launched in 2019.


The Data Transmission Mode of the Satellite Imaging Satellite is Direct transmission (DD).


The MWIR Band of the OHIS Imaging System is Cancelled in 2000.


The Release Date of the Figure 7 Image is Sept. 29, 2015.


The Accommodation Location of the Scientific Payload Satellite Payload is North Radiator Panel.


The Micro-Switch Location of the ISM Satellite Component is Adjacent to the ISM.


The 2022 Fires of the U.S. Drought Monitor Report is 211.


The Data Speed Options of the Iridium Certus Satellite Communication Service is Multiple.


The Support of the LRO Satellite is Future human missions to the moon.


The Orbit Altitude of the Hubble Satellite is 350 miles.


The Data Contribution of the Sentinel-6 Satellite is Sea state and wind speed measurements.


The Operations Center of the GIOVE-B Satellite is Telespazio's Fucino Space Center in Italy.


The URL of the RADARSAT Constellation Mission Satellite Constellation is http://www.asc-csa.gc.ca/eng/search/images/watch.asp?id=4247.


The Imaging Frequency Band of the KOMPSAT-5 Satellite is X.


The Size of the Spacecraft 406 MHz Processor Processor is 0.034 m3.


The Mission of the Spitzer Space Telescope Telescope is 2003 - 2020.


The Primary Diameter of the Telescope Optical Instrument is 120 mm.


The Design Life of the WorldView-1 Satellite is 7.25 years.


The Classification of the HAT-P-7 Exoplanet is Hot Jupiter.


The Launch Date of the Galileo FOC satellites Satellite is 22 August 2014.


The IAC Presentation Date of the GMES Sentinel-1 Satellite is Oct. 12-16, 2009.


The Age of the Hyades Star Cluster is 600–700 million years.


The Target Coverage of the OneWeb Satellite Constellation is All regions north of 50 degrees latitude.


The Manufacturer of the NewMag Magnetometer is UCLA (C. T. Russell).


The Operating System of the OBC On-Board Computer is CANOE (Canadian Advanced Nanospace Operating Environment).


The Diameter of the Aperture Function Image Processing is D.


The Payload Data Downlink of the PRISMA Satellite is X-band.


The Mass of the PACE nanosatellite Satellite is < 2 kg.


The Thermally Isolated of the HyperScout® Telescope Telescope is Yes.


The Instrument Concept of the IASI-NG Interferometer is Mertz Interferometer allowing to assess the Self Apodization issue by a Field Effect Compensation.


The Stability of the AOCS Attitude and Orbit Control Subsystem is 5 x 10-5 º/s.


The Propulsion System of the MERLIN Satellite is Newly adapted.


The Data Rate of the Satellite Satellite is 100 kbit/s.


The Wire Harness Length of the Integrated Sensor Sensor is 500 mm.


The Earth Observation Applications of the Aurora Satellite is Energy, mining and defence sectors, oil and gas pipeline monitoring, methane mapping, clean-energy resource exploration, sustainable mining practices and wildfire risk mitigation.


The Mass of the MIRAD Instrument is 0.5 kg.


The Measurement Error of the Particle Detectors Instrument is < 1%.


The Data Rate of the RF Communications Data Transmission is 280 Mbit/s.


The Detection Date of the REXIS Spectrometer is Last fall.


The Manufacturer of the MAC-200 Configuration is Bristol Aerospace.


The Measurement Date of the Solar Storm Natural Phenomenon is February 2014.


The Mission Status of the Sentinel-1 Satellite is Current.


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


The Initial Imaging and Observations Date of the Chandrayaan-2 Satellite is October 22, 2019.


The Earth Scanning Time (FDC) of the Instrument Satellite Instrument is Less than 10 minutes.


The Operator of the COMS Satellite is Korean Meteorological Association (KMA).


The Launch Vehicle of the GovSat-1 Satellite is SpaceX Falcon 9 Rocket.


The Signal Frequency of the Ground Station Antenna System Antenna System is 1.2 GHz or 720 MHz.


The BRDF Angle of the Telescope Optical Instrument is ±40º.


The Inclination of the ISS Space Station is 51.6º.


The Receive Chain Selection of the SAR Instrument SAR Instrument is Chain 1 or 2.


The LYSO crystals of the Range Calorimeter Particle Detector is 9.


The Size of the Eagle-2 ($50SAT) FemtoSat is 2.5U.


The Data Compression of the Instrument Spectrometer is DPCM (Differential Pulse Code Modulation) method.


The Dimensions of the EIRSAT-1 Satellite is 22 by 10 by 10 cm.


The Detector Cooling of the AVHRR/3 Instrument is <105 K.


The Regulatory Body for Satellite Light Pollution of the United States Country is None.


The Potential Mass of the White Dwarf Celestial Body is Similar to Jupiter.


The TT&C Uplink Rates of the MERLIN Satellite is 16, 32 and 64 kbit/s.


The Requirement of the Candidate Materials Satellite Components is Resistant to the effects of AO.


The Launch Date to ISS of the Flock 1d Nanosatellites is October 28, 2014.


The Rates of the Gimbal Satellite Component is 1 rad/s (max).


The Detector Cooling of the FTS Interferometer Interferometer is Passive cooling <100 K.


The Ground Monitoring Frequency of the EROS-A Satellite is S-band.


The Monitoring and Control Frequency of the RF Communications System is S-band.


The Tail Formation of the McNaught Comet is Two distinct tails: an ion tail carried by the solar wind and a dust tail.


The Application of the Satellite-based EO Satellite-based Service is Earth Observation.


The Distance from Comet Center of the NAVCAM Camera is 9.9 km.


The IFOV/line (pixels/scan line) of the IRAS Infrared Atmospheric Sounder is 56.


The Data Type of the GPM Satellite is Three-dimensional snapshots of drop size distribution.


The Connector Type of the Antennas Communication is SMA male.


The Antenna Chips Sales of the Astrocast Satellite Manufacturer is Sells the antenna chips to the clients.


The Instrument Payload of the Sentinel-4 Satellite is Passive UVN (Ultraviolet-Visible-Near-Infrared) hyperspectral imaging spectrometer.


The Manufacturer of the Restore-L Satellite is Maxar.


The Shielding Material Transparency of the CZTI Instrument is More transparent above 100 keV.


The Range of the Solar band Sensor is 0.32 µm to ≥ 100 µm.


The Calibration Period of the LISS-3 camera Camera is Eclipse period of the satellite pass.


The New Discovery of the Van Allen Probes Satellite is Temporary third radiation belt, acceleration energy within the belts themselves, and a nearly impenetrable barrier.


The Protocol of the High-speed link Radio Link is AX.25 packet protocol.


The Landing Date of the Zhurong Mars Rover Rover is Last week.


The Orbit of the Satellites Satellite is Geostationary.


The Importance of the Stepper Motor Motor is Mission critical part.


The Passband of the FUV channel Spectrometer is >125 nm.


The Development Status of the FormoSat-5 Satellite is In process of developing.


The Range of the Magnetometers Actuator is ±0.2 Am 2.


The Handling Safety of the Soft Stack Satellite Assembly is Can be handled safely for thermal cycling.


The Detector Elements of the SPIRIT-III Interferometer-Spectrometer is 6.


The Measurement Technique of the Sentinel-6 Michael Freilich Satellite is Synthetic aperture radar.


The Software Packages of the GeoSat-2 Satellite is User4EO, Plan4EO, Fly4EO, Control4EO, Track4EO, Archive4EO, Process4EO, Monitor4EO and CalVal4EO.


The Action of the UK Committee for Antarctic Place-Names Committee is Named 28 mountains, glaciers and bays after modern-day scientists.


The Chief Scientist of the QUESS Satellite is Jianwei Pan from the University of the Science and Technology of China.


The Swarm Size of the Desert Locusts Insect is 1 km2.


The Manufacturer of the RAD6000 Flight Processor is Unknown.


The Operation Status of the PREMOS Instrument is Continuously operating since the launch, except for mission interruption due to operational constraints.


The Design Life of the Satellite Spacecraft is 10 years.


The Velocity Resolution of the ELENA Sensor is Down to 10%.


The Calorimeter Diameter of the Microcalorimeter Microcalorimeter is 5.6 cm.


The Instrument Elements of the SHIMMER FTS Fourier Transform Spectrometer is Telescope, relay optics, interferometer, CCD camera.


The Function of the Space Solar Power System Power System is Collect solar energy, convert it to RF and beam it to a receiving station on the ground for conversion to clean, usable power.


The Footprint of the Submillimeterwave receiver Receiver is 5 m.


The HRV Channel Detectors of the SEVIRI Spectral Imager is 9.


The Radiometric Accuracy of the Spectral Band C Spectrometer is 3.


The Control Capability of the Attitude Control System Satellite Subsystem is Full three-axis control.


The Launch Date of the CHOMPTT Satellite is 16 Dec 2018.


The Components of the MIAS Magnetometer Package is Overhauser scalar magnetometer (OVM), two fluxgate vector magnetometers (FGM), and two-star imagers.


The URL of the Automatic Dependent Surveillance-Broadcast (ADS-B) Surveillance System is http://www.faa.gov/nextgen/implementation/programs/adsb/.


The Observation Time of the Band-1 and Band-64 Satellite Instruments is 37.68 seconds.


The Launch Time of the Kounotori Spacecraft is 11:50:49 UTC.


The Wavelength of the VIS Visible region of spectrum is 20 nm.


The Launch Date of the Electron rocket Launch Vehicle is November 11, 2018.


The Conference Location of the SEXTANT X-ray Timing and Navigation Technology is Kissimmee, FL, USA.


The URL of the OSIRIS-REx Asteroid Sample Return Mission is http://arc.aiaa.org/doi/pdf/10.2514/6.2014-1721.


The Orbit Altitude of the KSM-1 satellites Satellite is 500 km.


The Eclipse-Free Viewing of the IRIS Spacecraft is 7 months per year.


The Mission Type of the CAS500 Satellite is EO.


The Resolution of the ICEYE-X1 Satellite is 3 m.


The Diameter of the Primary Sensor Sensor is 1/8”.


The Channel Imbalance of the Instrument SAR is ≤-34 dB.


The Meeting Location of the LunaH-Map Satellite is Columbia, Maryland.


The Detector Quantity of the TIR Subsystem Imaging System is 50.


The Intensity of the Earth's main magnetic field Magnetic Field is Not the same in the north as in the south.


The Length of the Current Sheet Magnetic Field Structure is More than 40,000 kilometers.


The Pixel Size of the Image Sensor Imaging is 9.0 µm x 9.0 µm.


The DC Measurement Accuracy of the Magnetometer Instrument is 0.05% of the field in CuPID's orbit.


The Noise and Dark Current Performance of the STL-11000M SBIG Camera CCD Camera is Very good even at room temperature.


The Cargo Weight of the CREAM Cosmic-Ray Instrument is 1,258 kg.


The Launch Year of the Sentinel-5P Satellite is 2016.


The Ka-band System of the STPSat-6 Satellite is SpaceWire command, control, and telemetry to the spacecraft.


The Sea Ice Coverage of the Global Change Observation Mission 1st – Water “SHIZUKU” Satellite is 19.47 million km2.


The Function of the SES Instrument is Verify that the instrument high voltage performance as expected over temperature.


The Components of the Core-DHS Avionics Module is S-band Transmitter and Receiver, Global Positioning System, Attitude & Orbit Control System, Interface Module and Bridge and On Board Computer.


The Primary Pointing Reference of the CHOMPTT Satellite is Sun's orientation measured by the sun sensors.


The PRF of the SAR Radar is About 9 kHz.


The Launch Vehicle of the GFO Satellite is Taurus launcher.


The Operation Start Date of the RAVAN Satellite is Jan. 25.


The Apogee (km) of the Meteor-2-1 Satellite is 906.


The Orbit of the Beidou-3M/G/I satellites Satellite is MEO (Medium Earth Orbit) and GEO (Geosynchronous Orbit).


The Available DEM Geocells of the TanDEM-X Satellite is Over 15,000 geocells or nearly 80%.


The ICDS Redundancy of the ARTEMIS Satellite Subsystem is All units have a redundancy.


The Output Energy of the GEDI Laser Laser is 10 mJ.


The Diameter of the Entrance Pupil Optical Component is 320 mm.


The Milestone Date of the EGNOS V3 Satellite System is March 28, 2017.


The Footprint Shape of the CNSCAT Scatterometer is Rosette-shaped.


The Vertical Resolution of the Mie co-polar channel Channel is 100 m.


The Manufacturer of the DSAC Atomic Clock is SST-US.


The Swath of the LISS-IIM Instrument is 131 km.


The Size of the GomX-4B Satellite is Cereal-box-sized.


The Components of the IEPS Ion Electric Propulsion System is IT (Ion Thruster), PPU (Power Processing Unit), ECU (Electric-propulsion Control Unit), XT (Xenon Tank), PRU&FCU (Pressure Regulation Unit and Flow Control Unit), LCU (Line Connection Unit).


The Observation Period of the Megha-Tropiques Satellite is December 28, 2013 to January 4, 2014.


The Requirement of the Caging System Mechanism is Prevent damage to the sphere during launch and to release the sphere after arrival of the satellite on orbit.


The Burned Area of the Black Fire Fire is More than 130,000 acres.


The Detectors Type of the REM Radiation Environment Monitor is 300 Tm silicon diode detectors.


The Data Transmission of the Landsat-6 Satellite is X-band direct downlink.


The Measurement Types of the SAGE-III Spectrometer is UV and visible light.


The Speed of the CME (Coronal Mass Ejection) Solar Phenomenon is Tens of kilometres per second.


The Background Noise of the Lunar Meteoroid Impact Flash Detection Detection System is Earthshine (Earth reflected light on the Moon surface) in the visible spectrum, and by thermal emissions of the Moon surface in the infrared spectrum.


The Range Measurement Precision of the Satellite Satellite is Few decimeters.


The Photo of the SREM Instrument is Figure 19: Photo of the SREM instrument.


The Active Area of the X123-SDD X-ray Spectrometer is 25 mm2.


The Oscillation Modes Frequency Shift of the Gaia Satellite is 8.6 million times.


The Sample Size of the Vera C. Rubin Observatory Observatory is Very large.


The Measurement Resolution of the Cluster S/C Satellite is >= 6 pT.


The Technology of the MANTIS Earth Observation Satellite is Native multispectral Earth Observation.


The Sensor Complement of the AstroSat Astronomy Satellite is Five co-aligned telescopes.


The Image Rejection of the Receiver Communication System is 60 dB.


The Re-Entry Speed of the Chang’e-5 Lunar Lander is Approximately 40,000 km/hr.


The Chief Scientist of the Hubble Space Telescope Telescope is Ed Weiler.


The Requirement of the Data Processing System Computer System is Complex and robust.


The Measurements of the MAHRSI Instrument is Nitric oxide.


The Purpose of the NASA Instrument Instrument is Determines Hazards of Deep-Space Radiation.


The Mode of the Sentinel-1 Satellite is Complete coverage of Earth in six days.


The Cycle Length of the Satellite Imaging Satellite is 175 days.


The Power Bus of the Payload Instruments Satellite Components is 28 V unregulated, switched.


The Mission Start Date of the MANTIS Earth Observation Satellite is September 11, 2019.


The Transmission Spectra of the Altitude Range Atmospheric is 1 to 99%.


The Technology of the FPGAs Electronic Components is Six Sigma SolderQuik®.


The Article URL of the Herschel Satellite is http://sci.esa.int/herschel/54252-young-suns-violent-history-solves-meteorite-mystery/.


The Data Access of the GPM Satellite is Free and available to the public.


The End of Life Date of the OSCAR-QUBE Satellite is 29 August 2026.


The Orbit of the Lutetia Asteroid is Main asteroid belt between Mars and Jupiter.


The Detector Pixel Size of the Imager Satellite Instrument is Pan: 10µm x 10µm, MS: 40 µm×40 µm.


The Structure of the MTG-S Spacecraft Satellite is Two-winged satellite configuration.


The Conference Presentation Date of the Gravity Recovery and Interior Laboratory (GRAIL) Satellite is March 18-22, 2013.


The Data Collection of the OCO-3 Satellite is Denser data set than OCO-2.


The OBC of the Spacecraft Satellite is LEON3 FT.


The Earth's Entire Land Mass Mapping Completion Date of the TanDEM-X Satellite is By the end of 2014.


The First Light Observations Date of the MIRIS Satellite is Dec. 23, 2013.


The Global DEM Acquisition Start Date of the TanDEM-X Satellite is December 2010.


The Orbit Inclination of the STP-S26 mission Satellite Mission is 72º.


The Resolution of the True Color Composite Image Image is 250 m.


The Booster Segments Weight of the SLS Rocket is 180 tons.


The Roll Motion Range of the GF-2 spacecraft Satellite is ±35º.


The Noise Equivalent Radiance of the FTS Interferometer Interferometer is <0.5% of the radiance of a blackbody at 5800 K.


The Configuration of the Inertial Sensors Sensor is Concentric coaxial cylinders.


The LTDN of the CBERS-4 Satellite is 10:30 hours.


The Sampling Duration of the TAGSAM Sample Acquisition Mechanism is About five seconds.


The Rover Name of the ExoMars Mission is Rosalind Franklin.


The Ignition Capability of the Propulsion System Satellite Component is All CGGs individually upon request.


The Measurement Technique of the ICON Space Mission is Combines remote optical imaging and in situ measurements of the plasma.


The Measurement Range of the IMAP-Ultra Instrument is Extends the measurements through the range covered previously by Cassini/INCA.


The Conference Date of the Resurs-P1 Satellite is Feb. 28 - March 2, 2007.


The Wavelengths of the EPIC instrument Instrument is 10.


The Data Usage of the SAGE-III on ISS Satellite Instrument is Help the scientific community identify the cause and assess the threat of any new threats to the ozone layer.


The Body Height of the Spacecraft Satellite is 23.5 cm.


The Manufacturer of the Hugo Satellite is ABB.


The Workshop Date of the Skybox Imaging Company is March 26-28, 2014.


The Thrusters of the ALTIUS Satellite is Four 1N thrusters.


The Soil Moisture Accuracy of the SMOS Satellite is 4%.


The Cirrus Optical Depth of the Mie co-polar channel Channel is 0.05.


The Launch Mass of the Helios-2 satellites Satellite is Approximately 4200 kg.


The Net Loss of the Satellogic Satellite Company is $117.7 million.


The SNR @Lref [BOL] of the Spectral Channel Detector is 211-390.


The FPN Measurement Method of the Sensor Image Sensor is Capturing and averaging a series of 50 dark images, each containing 10 µs exposure time.


The Launch Date of the HORYU-4 Nanosatellite is Feb. 17, 2016.


The Data Rate of the MBEI Data Source is ~184 Mbit/s.


The Detector Type of the RAMIS Radiation Detector is Two silicon detectors.


The Diameter of the RRA Retroreflector Array is 57 cm.


The Plaque Designer of the LAGEOS Satellite is Carl Sagan.


The Ground Segment Components of the JUICE Mission Mission is Mission Operation Center (MOC) and the Science Operation Center (SOC).


The Availability of the European Aviation Network Inflight Broadband is 18 July 2019.


The Cadence of the Pulse Height Analysis Measurement is 1 minute.


The Sea Surface Salinity Accuracy Goal of the SMOS Satellite is 0.1 psu.


The Radiation Hardness of the Satellite Satellite is MEO compliant.


The Control Systems of the AVUM Upper Module is RACS (Roll and Attitude Control System) and the LPS (Liquid Propulsion System).


The Operation Management of the CAPSTONE Satellite is Advanced Space and Terran Orbital.


The Orbit Location Distance of the ACE Mission Satellite is About 1% of the way toward the sun on the sun-Earth line.


The Payload Power of the Inmarsat S – Europasat / Hellas-Sat 3 Satellite is About 12.3 kW.


The Bandwidth Impact of the Telemetry Data is Limited.


The Aggregation Time of the Satellite Measurements Data is Months or even years.


The IFOV of the PAN Detector is 0.45 - 0.52 µrad.


The Application of the Infrared Sensors Sensor is Astronomical observations.


The NWP Impact of the Aeolus Satellite is Positive.


The Orbit Inclination of the PRISMA Satellite is 98.19°.


The CubeSat Size of the RadCube Satellite is 3U.


The Fairing Reuse of the Falcon 9 Rocket is Half of which flew on two previous missions.


The Function of the Strain Relief Connector Saver Component is Alleviate issues and protect the access port.


The Meeting Date of the ECOSTRESS Instrument is 15 - 17 May 2017.


The URL of the BepiColombo Mission is http://www.lpi.usra.edu/meetings/lpsc2013/pdf/2172.pdf.


The Mission Flexibility Demonstration of the Soyuz Spacecraft is April 26, 2016.


The Mission Type of the Meteor-M-2 Satellite is EO.


The Crevice Length of the Philae Lander is 2.5 m.


The Size of the Didymos A Asteroid is About one-half mile.


The Data Volume Requirement of the HyperScout Imaging System is 1.5 MB.


The Orbit Altitude of the HY-2A Satellite is 971 km.


The Horizontal Onboard Accumulation Length of the Detector Instrument is 1.0 km and 3.5 km.


The Diameter of the Cas A Supernova Remnant is 10 light years.


The Unknown of the GOMOS Instrument is Unknown.


The Impact on Satellites of the Earth's Magnetic Field Natural Phenomenon is Can cause big headaches for satellites.


The Number of Instruments of the ISEE-1 Spacecraft is Unknown.


The Switches of the P-POD Poly-Picosatellite Orbital Deployer is 2.


The Shape of the DebriSat Satellite is Hexagonal Prism.


The Vertical Resolution of the VISION Instrument is 2 km.


The Modes of the Camera System Observation Modes is Automatic target pointing, Interactive operation.


The SNR of the Band 2 Spectral Band is 160.


The Expected Lifetime of the MetOp-SG Satellite is 7.5 years.


The Mass of the Jugnu Nanosatellite is 3 kg.


The Stable Electricity Supply Duration of the TSUBAME Satellite is At least 80 days.


The New Factory Production Capacity of the Satellogic Satellite Company is 25 satellites a quarter.


The Data Rates of the CC1101 UHF transceiver Transceiver is Up to 500 kbit/s.


The Retired Date of the Herschel and Planck Telescopes is Unknown.


The Mass of the HawaiiSat-1 Satellite is 40 kg.


The Mass of the D-Star One Nanosatellite is 3 kg.


The Inclination of the Meteor-M2 Satellite is 98.8º.


The Commissioning Date of the Small Satellite Constellation Satellite Constellation is Aug. 9-12, 2004.


The ISLR of the Instrument SAR is ≤-9 dB.


The Scintillation Module Layers of the Natalya-2M High energy radiation spectrometer is Two layers (4 crystals in each).


The Measurement Goal of the Lunar Flashlight Spacecraft is Identify locations where water ice is present at the surface of the Moon as a frost.


The Launch Date of the SLS Rocket is Four years from now.


The Development Cost of the BRITE Telescope is Minimized.


The Mission Status of the CHIPS Satellite is Unknown.


The Development Partnership of the MIRI Instrument is 50-50 partnership between NASA and ESA.


The Sensitivity of the Channel 6 Sensor is 0.4 K/pixel.


The Mass of the Satellite Communication Satellite is 2500 kg.


The Communication Interface of the EC Digital Signal Processor is Serial port.


The Material of the Reflector Film Satellite Component is 1/4 mil aluminized mylar.


The Sent to NASA Date of the Diwata-1 Satellite is January 18, 2016.


The Solar Cell Dimensions of the TUBSAT-N Satellite is 6 cm x 4 cm.


The Orbit Inclination of the JAWSAT Satellite is 100.2º.


The Launch of the Telescope Optical Instrument is 2019.


The Launch Date of the Rocket 3.3 Rocket is 20 November 2021.


The Conference Presentation Date of the GIOVE-A Satellite is Sept. 26-29, 2006.


The Year of Launch of the EO-1 Satellite is 2000.


The Downlink Frequency Band of the SAR/Galileo and SAR/GLONASS payloads Payloads is 1544 – 1545 MHz (L-band).


The Control Type of the Jerry 1U CubeSat is Passive.


The Spectral Sampling Distance of the SWIR Spectrometer Spectrometer is 10 nm on average.


The Development Center of the GeoXO Satellite System is NASA's Goddard Space Flight Center in Greenbelt, Maryland.


The Attitude Accuracy of the Attitude and Orbit Control Subsystem Subsystem is 0.5º in yaw.


The Evaluation Paper of the CartoSat-1 Satellite is "Evaluation of CartoSat-1 Multi-Scale Digital Surface Modelling Over France".


The Arrival Date at Launch Site of the OHB Communications Satellite Communications Satellite is Dec. 1, 2016.


The Size of the STAFF/DWP Instrument is 351 mm x 200 mm x 208 mm.


The EW FOV: max FPM of the AHI Scanner is 33,203 µrad.


The Orbit of the TET-1 Satellite is Low Earth Orbit.


The Nominal SNR of the Band 7 Spectral Band is 860.


The Impact on ILRS of the GOCE Satellite is Negative.


The Generation of the GOES 2nd generation spacecraft Satellite is 2nd.


The Orbit velocity of the KOMPSAT-3 Satellite is 7.51 km/second.


The Design Life of the COSMO-SkyMed spacecraft Satellite is 5 years.


The Orientation of the SERB Nanosatellite Satellite is +Z pointing to the Sun, +Y along the longitudinal nanosatellite axis, and +X along the deployed solar arrays.


The Launch Date of the Ikonos-2 Satellite is 24 Sep 1999.


The Position of the CASI-1500i Compact Airborne Spectrographic Imager is Left.


The Launch Location of the Italian mini-satellite Satellite is Russia.


The Mission Status of the ZACUBE-2 Satellite is Operational (nominal).


The Status of the MADRAS Instrument is Unknown.


The Wavelength Range of the Band 2 Spectral Band is 660-685 nm.


The Swath Width of the PanMUX Instrument is 60 km.


The Inertia Tensor of the AGS Attitude Determination System is Best available.


The Launch Date of the RHESSI Satellite is February 5, 2002.


The Repeat Cycle of the SPOT-1, -2 and -3 Satellites is 26 days.


The Length of Operation of the Internal Satellite Diffuser Calibration Device is 30 min, one or two wavelengths per orbit.


The Deployment Date of the CubeRRT, EQUiSat, HaloSat, MemSat, RadSat-g, RainCube, TEMPEST-D, EnduroSat One, Radix Satellites is July 15th.


The No of Stars Observed of the STOs and STAEs Analog Electronic units is 10 x 2 (acquisition), 5 x 2 (tracking).


The Radio Signals of the Hitomi Satellite is 3/29 00:33 (for about 6 sec) @ SNT.


The L0 and L1A Processing Time of the SAR Synthetic Aperture Radar is About 3 days.


The Exposure Time of the Channels Spectrometer is 0.01-600.


The Cross-Strapping of the KazEOSat-2 Satellite is Provides Redundancy.


The Energy Range for Electrons of the MagEIS Magnetic Electron Ion Spectrometer is 30 keV to 4 MeV.


The Current Status of the AeroCube-3 Satellite is Operating nominally as of summer 2009.


The Mass of the Sensor Unit Sensor is 4.815 kg.


The Movement of the REXJ Astrobot is Can theoretically move around the space station.


The Target Industry of the MANTIS Nanosatellite is Oil and gas sector.


The Observatory Presentation of the James Webb Space Telescope Space Telescope is Rob Garner, "The James Webb Space Telescope Observatory," NASA, July 28, 2013.


The Amplifier Efficiency of the Ka-band Signal is 13%.


The Percentage from Oil and Gas Sector of the Kayrros Studies Methane Leak Detection is Around 50%.


The Spectral Bandpass of the Instrument Photometer is 400 nm to 850 nm.


The Primary Cube Structure Side Length of the COMMx Payload is 0.93 m.


The Partner Agencies of the Odin Satellite is Canada, Finland and France.


The Effect of the Space Traffic Spacecraft Launches is Controls the year-to-year variability of mid-latitude noctilucent clouds.


The First Image Date of the SMOS Satellite is Feb. 23, 2010.


The RF Communications of the Spacecraft Satellite is S-band.


The Launch Date of the GEOS-3 Satellite is April 9, 1975.


The Release of the HPA Satellite is Not until a geostationary transfer orbit is attained.


The Roll Axis Control of the GNB Satellite is Not controlled.


The Launch Time of the Aeolus Spacecraft is 21:20 GMT.


The Manufacturer of the Microprocessor Component is PIC.


The Design of the Thermal Subsystem Satellite Subsystem is Largely passive solution using MLI (Multi-Layered Insulation) and surface coatings.


The Launch Date of the DSCOVR Spacecraft is February, 11, 2015.


The Orbit Inclination of the R3 CubeSat Satellite is 85°.


The Mass (kg) of the KOMPSAT-5 Satellite is 1400.


The Agency of the Meteor-M-2 Satellite is ROSKOSMOS, ROSHYDROMET.


The Solar Array Normal Vector and Sun Vector Difference of the Spacecraft Satellite is Up to 30 degrees during the extended mission phase.


The Launch Time of the Soyuz MS-17 Spacecraft is 1:45 a.m. Eastern Oct. 14.


The Apoherm of the MMO Spacecraft is 12,000 km.


The Number of Satellites of the MetOp-SG Satellite is 6.


The Repeat Coverage of the Landsat 9 Satellite is 16 days.


The Number of Secondary Payloads of the PSLV-C37 Launch Vehicle is 103.


The New Discovery of the Van Allen Probes Satellite is ULF (Ultra-Low Frequency) plasma waves transport the outer part of the belt radiation harmlessly into interplanetary space and create the previously unexplained feature of the third belt.


The Survival Temperature Range of the GEDI Laser Laser System is 50ºC to -10ºC.


The Mass of the Instrument mass Spectrometer is 12 kg (max).


The Signal Conditioning Modules of the MnACQ-2000 Miniature Network Data Acquisition System Data Acquisition System is Included.


The CCD Lines per Package of the Focal Plane Module Imaging Device is 3.


The Phase of the OLCI Instrument is PDR (Preliminary Design Review).


The Manufacturer of the Miniature High-Resolution Imaging Spectrometer Imaging Spectrometer is MPB Communications Inc..


The Array of the Detectors Photovoltaic Detectors is 3 x 3.


The Design Date of the CubeSat Guidance, Navigation, and Control Module CubeSat Component is August 2011.


The Proton Energy of the GALS-VE Particle Energy Measurement Device is > 800 MeV.


The Spectral Channel 1 of the Satellite Imaging Satellite is 0.50 - 0.59 µm.


The Principal Investigators of the Multiple Sclerosis and Parkinson’s Disease Cryovial Study Research Project is Dr. Andres Bratt-Leal and Dr. Valentina Fossati.


The Mission Control of the IBEX Satellite is Boston University.


The Quantity of the Laser Transmitter Device is 1.


The Article Date of the H1743-322 Black Hole Binary is July 2016.


The Interchangeable Barrels Sizes of the Launcher Test Facility is 84 mm, 102 mm, and 203 mm.


The Launch of the CLARREO Pathfinder Satellite is 11/2022.


The Primary Attitude Sensor of the ADCS Attitude Determination and Control System is Magnetometer.


The Polarization of the ICI-10 Radiometer is V.


The Battery Capacity of the EPS Electrical Power Subsystem is ~ 10 Whr.


The Latchup Event of the CMOS Sensors Sensor is Produces an increase in current consumption, and the device becomes un-responsive.


The Data Rate of the PEACE Instrument is 3.54 kbit/s.


The Methods of Communication of the MCS Communication System is Point-to-point client-server communication and communication on a message bus.


The Impact on Ganymede's Surface of the Juice Spacecraft is Late 2035.


The Mission Operator of the SPOT 1-5 Satellite is CNES.


The Function of the Satellite STRATOS is Performs radio occultation (RO).


The Document Date of the Paz ground segment Ground Segment is May 31, 2011.


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


The Operational Status of the MTSAT-1R Satellite is Standby.


The Registration Process of the Sentinel-1 Satellite is Online self-registration accessible via the Sentinel Data Hub.


The Development Date of the Multi-Needle Langmuir Probe System Probe System is May 25, 2009.


The Robustness of the Star Tracker Attitude Determination Device is Better robustness to Moon-blinding and to temperature constraints.


The Bandwidth of the Band Cameras Camera is 90 nm.


The Functions of the DAQLB Data Acquisition and Quicklook Browsing is Quicklook display, browse generation, calibration analysis and ADIF generation.


The Design Life of the S/C Spacecraft is 2 years.


The Maximum Distance of the Inter-satellite link Communication System is 2-5 km.


The Cost of the Radiation Effects Tests Testing Process is On the order of $400,000.


The Mass of the SaudiSat-4 Microsatellite is 112 kg.


The Sensitivity of the High-Altitude Water Cherenkov Observatory (HAWC) Observatory is Very high energy gamma-ray photons.


The Uplink Data Rate of the TT&C S-band Communications Communication System is 4 kbit/s.


The Data Provided of the CFOSAT Satellite is Co-located wind vector fields, directional spectra of ocean waves, normalized radar cross-section.


The Command Interface of the CCD (Charge-Coupled Device) Imaging Device is UART type.


The Total Mass of the Instrument Sensor is 13.25 kg.


The Field of View of the CERES Scanner is ±78°.


The Brightness of the Venus' Orbital Dust Ring Space Dust Feature is At least a hundred times brighter than the solar wind.


The Frequency Band of the TOTEM SDR SDR Platform is 400-440 MHz.


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


The Observation Capability of the SIR-C/X-SAR Radar System is Two-frequency.


The Light Travel Time to Earth of the OJ 287 galaxy Galaxy is 3.5 billion years.


The Keel Depth of the A-68A Iceberg is 141 metres below the ocean surface.


The Arbitration System of the CAN Bus Data Communication is Yes.


The Optical System of the SHS Interferometer is Similar to the Twyman-Green interferometer.


The Measurement Domain of the TEMPO Satellite is Atmosphere.


The Mission Status of the FORUM Satellite is Planned.


The End of Life Date of the GF-3 Satellite is 10 Aug 2024.


The Emissions Contribution in 2019 of the Sudd wetlands in South Sudan Wetlands is Over a quarter of the growth in global emissions.


The Nadir Pointing of the Dove-1 Nanosatellite is Twice per orbit.


The Test Date of the AltiKa Radar Altimeter is Nov. 17-18, 2009.


The Source of Carbon of the Northern Forests Ecosystem is Potential future outcome.


The URL of the Radio Aurora Explorer Satellite is http://rax.sri.com/index.html.


The Arrival at Jupiter of the Juice Spacecraft is July 2031.


The Function of the ICU Instrument Control Unit is FCI and IRS management and data-processing.


The Spectrum of the Sco X-1 X-ray Source is Soft X-ray.


The Control Algorithm of the SV-1 Satellite is Problematic.


The Role of the Copernicus Sentinel-6 Michael Freilich Satellite is Radar altimetry reference mission.


The Date of the Senior Review 2013 Review is June 13, 2013.


The Observation Time of the Satellite Orbit is Approximately 10 minutes per orbit.


The Function of the PACO Software is Perform atmospheric and topographic processing.


The Launch Vehicle of the KazSTSAT Microsatellite is SpaceX Falcon-9 Block 5.


The Transmission Frequency of the SAR Synthetic Aperture Radar is 1.275 GHz.


The Cloud Cover Impact of the CHOMPTT Satellite is Preventing lasing from the Mount Stromlo site.


The Orbit Control System of the Payload Satellite Payload is Propulsion.


The In-Orbit Nominal Lifetime of the MWI Instrument Instrument is 7.5 years.


The Antenna Diameter of the RA-1 Radar Altimeter is 1.2 m.


The Partners of the Hiber Satellite Network is Amazon Web Services, IBM Watson and Actility.


The Mission Type of the HJ-1 Satellite is EO.


The Alert Production of the Ground Software Data Processing is Produce and distribute alerts to the world-wide astronomical community.


The Mass of the CION Instrument is 1.5 kg.


The URL of the Swarm Mission is http://pcwww.liv.ac.uk/~holme/RAS/haagmans.pdf.