The Function of the CIRAS Satellite is Measuring temperature and water vapor profiles.


The NASA Instruments of the Rosetta spacecraft Spacecraft is Three.


The Mission Status of the ALL-STAR Satellite is Unknown.


The Range of the Pitch momentum wheel Actuator is ±1.7 mNms.


The Power Consumption of the MI Radiometer Instrument is < 195 W.


The Pixel Resolution of the SPIM2 Spectrometer is 14 bit.


The Low Energy Telescope Energy of the CRS Cosmic Ray Subsystem is 5MeV.


The Clone Date of the Satellite Vu’s original satellite Satellite is July 21, 2022.


The Capability of the Carbonite Smallsat Satellite is Multi payload.


The Swath Width of the Satellite Imaging Satellite is 48 km.


The Lower Module Components of the Merlin Satellite Device is `generic processor board', power conditioning, microprocessor, analog-to-digital converter, memory, I/O ports, data interfaces.


The Power Output of the Fission Surface Power System Power System is Up to 10 kilowatts.


The Band of the Nighttime SST Product Dataset is Band 7 (3.9 µm wavelength).


The Attitude Control System of the NorSat-3 Satellite is Star tracker, attitude sensors and reaction wheels.


The Type of the Solar Arrays Satellite is Articulating.


The Typical Number of Stars of the Young Moving Groups Stellar Groups is Only a few tens of stars.


The Method of the Cluster spacecraft Satellite is Triangulation.


The Spectral stability of the UV/VIS Spectrometer Spectrometer is 0.04 nm.


The Experimental Payloads of the DoT-1 satellite Satellite is Flying further experimental payloads as part of SSTL’s ongoing R&D program.


The Launch Date of the GeoEye-1 Satellite is Sept. 2008.


The Center Frequency of the Channel 4 Sensor is 31.5 GHz.


The Status of the P-PODs Device is Needed to be de-manifested.


The Data Availability of the Sentinel-3 Satellite Constellation is Full, free and open basis.


The Operation Period of the TOMS Instrument is October 1978 to May 1993.


The Spectrometer Components of the Natalya-2M High energy radiation spectrometer is Two spectrometers, eight scintillation modules with CsI(Tl) crystals each, anti-coincident protection detectors from polystyrene.


The Propulsion Systems of the MEV-1 Satellite is Hybrid chemical and electric.


The VNIR Channels of the PROBA-V Satellite is 3.


The Diameter of the Potentially Hazardous Asteroid (PHA) Asteroid Type is ~140 m or larger.


The Peak Power of the EPS Electric Power Subsystem is 230 W.


The Band 3 of the Landsat TM Satellite is Chlorophyll absorption, plant type discrimination.


The Surface Temperature of the Zeta Puppis Star is Seven times hotter than our sun.


The Photodiodes per Suite of the Sun Sensor Suites Sensor is 4.


The Presentation Date of the CEBRAS SAR System is July 26-31, 2015.


The Number of Satellites of the DMSP (Defense Meteorological Satellite Program) Satellite Program is 19.


The Power Generation of the Spacecraft Satellite is 450 W @ EOL.


The Number of Planets of the TOI-178 Exoplanet System is 6.


The Type of the ALL-STAR Satellite is 3U CubeSat.


The Diameter of the Von Kármán crater Lunar Crater is 180 km.


The Discovery Year of the Lutetia Asteroid is 1852.


The Cover Glass Thickness of the TFSC Thin Film Solar Cell is 0.1 mm.


The Orbit of the CSSWE Satellite is Low Earth Orbit.


The Typical high cadence of the HRI Lyman-α 1216 Å Passband center is Sub-second.


The Purpose of the EMIT Imaging Spectrometer is Map the surface composition of minerals in Earth’s dust-producing regions.


The Duration of the Orbital Express Satellite Mission is 3 months.


The Period of the Anand Satellite is 94.6 minutes.


The Data Volume of the Nancy Grace Roman Space Telescope is 20,000 terabytes (20 petabytes) over the course of its five-year primary mission.


The Status of the CartoSat-2B Satellite is Operational.


The Number of Stations of the Satellite Laser Ranging Stations Tracking Stations is 3 in Russia, 10 outside Russia.


The Operational of the BDS-3 Satellite System is Yes.


The Number of Professionals of the SAOCOM-1A Satellite is As many as 600.


The Monitoring Purpose of the SMOS Satellite is Antarctic ice sheet.


The Ground Stations of the HYPSO-1 Satellite is KSAT Puertollano, Spain.


The Number of Planned Propulsive Maneuvers of the ICE (International Cometary Explorer) Spacecraft is 4.


The Band Spacing of the NIR Detector is 11.4 nm.


The Direct Transmission Delivery Time of the Polar Satellite Data Data is Virtually at the time of measurement.


The Operating Frequencies of the SMMR Microwave Radiometer is 21.0 GHz.


The Data Rate of the IREI Data Source is 1.92 Mbit/s.


The Power of the Power Satellite is 275 W.


The Functions of the ARF Acquisition & Routing Facility is Second level of synchronization, generation of ISP files and routing to the Nominal PDGS or the Defence one.


The Symposium Date of the NISAR Spaceborne SAR Mission is 21-26 July 2013.


The Ground Sites of the ARTEMIS Satellite is MOD (Ministry of Defense) ground sites.


The Launch Date of the GomX-4B Nanosatellite is 2 February 2018.


The Operation Declaration Date of the QZS-1/Michibiki Satellite is July 2011.


The Geometric Factor of the ELENA Sensor is 2 x 10 -5 cm 2 sr.


The Purpose of the Thermal Shrouds Thermal Isolation is Isolate the cold detector plate from the warm ROEs.


The Mounting of the LAD Instrument is Rotating actuator platform.


The Frequency of the RF Output Frequency Communication System is 2214.97 MHz.


The Affiliation of the Nobuo Sugimura Author is Unknown.


The Launch Date of the Envisat Satellite is March 01, 2002.


The Data Monitor of the Seismic Experiment for Interior Structure (SEIS) Seismometer is Marsquake Service.


The Altitude of the GEO Satellite Satellite is About 35,800 km.


The Number of Mirrors of the Shafer Telescope Optical System is 5.


The Function of the V1-V4 Voltage Probes Sensor is Current-biased double probe electric fields sensors and capacitively-coupled radio and plasma wave sensors.


The Launch Date of the ProSEDS Tether Demonstration Experiment is 2003.


The Uptime of the AlSat Nano Satellite is 27.4 days.


The Magnetic Field Strength of the Rho Ophiuchi A Star is 500 times stronger than that of the Sun.


The Power of the DubaiSat-1 Satellite is 53.2 W.


The Spacecraft Mass of the TCS Thermal Control System is 55 kg.


The Launch Date of the CubeSat ELaNa III Satellite is October 2011.


The Structure Tolerances of the CXBN-2 Spacecraft is Better than ±0.1 mm.


The Data Access of the Landsat-7 Satellite is Free access to the entire user community.


The Weight of the PeruSat-1 Satellite is Up to 500 kg.


The Measurement Range of the ACE Mission Satellite is Low energies of the solar wind up to the high energies of the galactic cosmic rays.


The Uplink Frequency of the Communication System Satellite System is 145.95 MHz.


The Baseline Length of the Three-axis diagonal gradiometer Gradiometer is 0.5 m.


The Conference Date of the AlphaSat TDP Operations Support is May 15-17, 2013.


The Weight of the NorSat-3 Satellite is 16 kg.


The Compatibility of the NovAtel OEM-615 GPS Module is GOMSpace Nanodock DMC-3 Motherboard.


The Author of the IceCube Satellite is Madeleine O'Keefe.


The Mounting Location of the SAWs Solar Array Wings is Externally.


The Loss of Contact Date of the TSUBAME Satellite is January 27, 2015.


The Mass of the Harness Harness is 3 kg.


The Responsibilities of the CAS Organization is Propulsion Module, Service Module, Spacecraft Prime, Mission Operations (with ESA contribution), Chinese instruments.


The Rate of Movement Away from Earth of the Moon Celestial Body is 3.8 cm/year.


The Initial Operations Start Date of the Galileo Satellite Navigation System is December 2016.


The Resolution of the EarthDaily Constellation Satellite Constellation is 5-metre.


The Substrate Material of the Primary Mirror Optical Component is Fused silica.


The Mission Duration of the AIST-2 Microsatellite is 3 years.


The Accuracy of the Star sensor Sensor is +1.0-6.0 m v 0.02º (3σ).


The Antenna Length of the Instrument DC Electric Fields Investigation is 60 m.


The URL of the MICROSCOPE Spacecraft is http://missions-scientifiques.cnes.fr/MICROSCOPE/GP_segment_sol.htm.


The Mission of the THEMIS Satellite is Uncover the mysteries behind the formation of auroral beads.


The Effective Area of the Detector E2V CCD-22 (Frame Store) is 200 cm 2 @ 1.5 keV.


The Type of the Linear Encoder Sensor is Non-contacting.


The Mass of the MiniCOR Coronagraph is <3.6 kg.


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


The Size of the APSS-1 Satellite is 1U CubeSat.


The Operating Mode of the T3000G2 receiver GPS Receiver is Dual-frequency mode.


The Sensor Type of the SeaWiFS Satellite is Scanning telescope.


The Flexibility of Satellite Operations of the MTP Transponder is True.


The Number of Spectral Bands of the ERIP Earth Remote-Sensing Imaging Package is 7.


The Landing Date of the Chang'e-5 Lunar Probe is 1 December 2020.


The Onboard Innovations of the PROBA-1 Microsatellite is Gallium-arsenide solar cells, star trackers for gyroless attitude control, lithium-ion batteries, ESA’s first ERC32 microprocessors.


The Science Mission Orbit of the LRO Satellite is Quasi-circular orbit (50 ± 15km).


The Sensitivity of the Channel 5 Sensor is 0.3 K/pixel.


The Data Encoding of the MIU Interface is CCSDS.


The Operating Frequency Range (TC) of the EWC31 S-band transceiver module Communication Module is 2025-2110 MHz.


The Availability of the Avionics Components Components is Flight model version.


The Mirror Rotation Capability of the TIR Subsystem Imaging System is 180º from the nadir position.


The Mission of the CEDEX Payload Payload is GIOVE-A.


The Constellation Partners of the GPM Constellation Satellite Constellation is DMSPs from the U.S. Department of Defense, GCOM-W from JAXA, Megha-Tropiques from CNES and ISRO (Indian Space Research Organization), the NOAA series Suomi-NPP from NOAA-NASA, and MetOps from EUMETSAT.


The Pulse Repetition Interval of the RainCube Radar is 1660 µs.


The Test Completion Date of the Integrated Circuit Boards Hardware is June 2019.


The Data Display of the TechDemoSat-1's radiation monitor Radiation Monitor is Google Earth.


The URL of the FORUM Mission is https://www.esa.int/Our_Activities/Observing_the_Earth/Two_new_Earth_Explorer_concepts_to_understand_our_rapidly_changing_world.


The Contacted Satellites of the CYGNSS Satellite Constellation is Eight.


The Purpose of the Ultra Stable Oscillator (USO) Oscillator is Precise time tagging.


The Data Processing of the TanDEM-X Satellite is More than 400,000 datasets.


The Data-handling infrastructure of the LIS Lightning Imaging Sensor is TRMM.


The Presentation Date of the Membrane Photon Sieve Space Telescope Telescope is May 21, 2013.


The Announcement Year of the European Sentinel Satellites Satellite is 2020.


The Delivery of the CSG GS Ground Segment is Responsible for the delivery to the final user.


The Orbit Altitude of the PhiSat-1 Satellite is About 329 miles (530 km).


The Data Availability of the Landsat 5 TM Satellite is All TM data December 2008.


The Date of the West coast wildfires Natural Disaster is 11 September 2020.


The In-Flight Calibration Strategy of the TRUTHS Reference Sensor is Radiometric gain/bias, linearity, spectral performance.


The Modulation of the Transmitter Communication Device is 1200 bit/s FSK / 1 bit/s CW.


The Conversion Type of the ADC Analog-to-Digital Converter is Linear analog to digital conversion of dV in 256 channels.


The Maximum Battery Power in Uncontrolled Tumble of the Satellite Spacecraft is 3 hrs.


The Operating Temperature of the CCD Charge Coupled Device is 155 K.


The Developer of the Magnetometer Sensor is GAUSS team.


The Presentation Date of the Remote Sensing Activities Activity is Feb. 6-17, 2012.


The Local Time of Ascending Node of the Satellite Communication is 9:15 AM.


The Spatial Resolution of the JL-1-GF03D Microsatellite is 0.75 m.


The Data Transmission Rate of the RF Communications Transmitter is 9.6 to 100 kbit/s in S-band.


The Moving Mirror Scan Time of the MSASI Imager is 80 seconds.


The Number of Stations of the SVOM VHF Network Ground Station Network is 45.


The Mission Start Date of the SMAP Satellite is March 3, 2012.


The Nominal power generation of the EPS Electric Power Subsystem is 2 W.


The Error (RMS) of the Rate sensor Sensor is <0.05/s.


The Bandwidth of the Band 1 Spectral Band is 402-422 nm.


The Instruments of the Solar Orbiter Satellite is In-situ instruments and Remote sensing equipment.


The NEΔT @ specified scene temperature of the Instrument Spectral Imager is 0.3-1.2 K @ 250 K.


The Number of Satellites of the FFRF Subsystem Relative Positioning System is 2 to 4.


The Launch Date of the Landsat-9 Satellite is December of 2020.


The Presentation Date of the BepiColombo Mission is 2012.


The Active Area of the ICON FUV Instrument Detector is 25 mm (circular).


The Science Mission Duration of the RapidScat Instrument is Two years.


The Constellation Architecture of the CIRCE Mission is Dual satellite bus.


The Description of the Orthorectified Product (L1C) Data Product is The product is derived from the L1 product and geometrically corrected (correction of sensor, satellite motion and terrain related distortions) and re-sampled to a specified grid (orthorectified).


The Former Name of the Copernicus Program is GMES.


The 18.7 GHz Channel Function of the JMR Microwave Radiometer is Correction for effects of wind-induced enhancements in the sea surface background emission.


The Orbit Localization Accuracy of the WEOS Satellite is About 30 m.


The Signal-to-Noise Ratio of the SNR Spectrometer is ≥ 100.


The Thrusting Modes of the T3µPS Micropropulsion System is Continuous thrust mode, Burst thrust mode.


The Reentry Date of the Long March 5B Rocket Stage is 9 March 2021.


The Distortion of the SHS Interferograms Interferometer Output is Figure errors distort the individual (carrier) fringes to a greater extent than the envelope (visibility) of the fringes.


The Frequency of the Solar Measurements Instrument is Every orbit.


The Monitoring of the AIS Automatic Identification System is Ships.


The Deputy CEO of the Galileo 2nd Generation Satellites Satellite is Massimo Claudio Comparini.


The Working Principle of the Instrument Unknown is Balance between the total amount of power received in the first and second half of the Dicke cycle.


The Manufacturer of the OPTSAT 3000 Satellite is IAI.


The Observations per Day of the Sapphire Satellite is More than 3000.


The Length of Operation of the Full Calibration of HIS Calibration Process is 1 day accumulated.


The Altitudes of Operation of the Starlink Satellite Constellation is Around 550 kilometers.


The Communication Interfaces of the MCU Microcontroller Unit is Up to 8 communication interfaces.


The Arc Duration of the BepiColombo Spacecraft is Two months.


The Function of the Instrument Control Unit (NI-ICU) Control Unit is Housekeeping management.


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


The Altitude after Five Years of the GRACE Satellite Satellite is About 300 km.


The Life Expectancy of the RapidEye Satellite Constellation is 6 years of operations, with full image performance for another 5 or more operational years.


The Number of Firings of the IEPS Ion Electric Propulsion System is 22.


The Grating Type of the OCO-2 Spectrometer is Regularly-spaced series of grooves on a very flat surface.


The Final Preparations Date of the ESAIL Satellite is 8 July 2019.


The Pixels per FWHM of the Spectrometer Instrument is 3030.


The Storage of the SDR Host Computer Computer is 250 GB SSD.


The Orbit Parameters of the GEOS-2 Satellite is 1,079 km x 1,572 km x 105.8º.


The Field of Regard of the AOCS Attitude and Orbit Control Subsystem is ±26º.


The Electronic Outputs Resolution of the SEVIRI Spectral Imager is 10 bit.


The Orbit Duration of the NanoSail-D2 Satellite is 95 days.


The Spacecraft Builder of the Lucy Satellite is Lockheed Martin Space Systems.


The Launch Date of the Solar-A / Yohkoh Satellite is 30 August 1991.


The SO2 Emissions of the San Nicolas refinery Refinery is Roughly 350 kilotons per year.


The Temperature of the Tank B1 Fuel Tank is Daily average.


The Size of the Didymos B Asteroid is About 530 feet (~160 m) across.


The Impact Features of the Eureca Satellite is More than 1000 on the front sides of the solar arrays.


The Orbit velocity of the KOMPSAT-3A Satellite is 7.60 km/second.


The Ku-band antennas of the Spire Global Satellite is High-capacity.


The Spectral Range of the Instrument Spectrometer is 420 nm to 2450 nm.


The Total Mass of the Aquajet Satellite Propulsion System is ~0.5 kg.


The Impact on Xenon Consumption of the Solar Activity Natural Phenomenon is Lower than what was expected in the mission design phase.


The Capability of the Visible and SWIR Cameras Imaging System is Imaging the Earth's surface and clouds when illuminated by moonlight and the airglow.


The Launch Date of the PSLV-C26 Satellite is Unknown.


The Developer of the Transponder Device is Italian company IDS.


The Sensor Complement of the FormoSat-7 / COSMIC-2 Satellite Constellation is Unknown.


The Bands of the CCD Camera Optical Device is 430-520 nm, 520-600 nm, 630-690 nm, 760-900 nm.


The Manager of the Space Weather Network Network is ESOC.


The Distance from the Sun of the Comet 67P/C-G Comet is About 1.7 au.


The Apolune Altitude of the Rstar Data Relay Microsatellite is ~2400 km.


The Altitude of the NEMO-AM Satellite is 650 km.


The Effective Area of the Observation Instrument Telescope/Spectrograph is 0.6 cm 2 @ 125 nm.


The Capacity of the Solid State Recorders Data Recorders is 24 GB.


The Maximum Range of the ARTEMIS Spacecraft is 1.2 million km.


The Effective Pixel Dimensions of the Kodak KAI-11002 CCD CCD is 4008 x 2672.


The Model of the NovAtel OEM-615 GPS Module is NovAtel OEM-615.


The Observation Purpose of the Integral Satellite is Measure the cosmic X-ray background.


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


The Instrument Type of the QBITO CubeSat is Imaging multi-spectral radiometers (vis/IR).


The TDI Levels of the Pan band Detector Array is 5 selectable levels from 7 to 20.


The Swath Width of the SMAP Satellite is Approximately 1000 km.


The Image Sequence Specification of the COR1 Coronagraph1 imager is 3 white light images at 3 different polarization angles.


The Calibration Mode Components of the LIBRA Satellite is Rotating mirror, middle optics, two monochromators, avalanche photodiodes.


The Memory of the protos Software is 128 kB of flash memory.


The Spectra Captured of the Limb Sensor Sensor is Six.


The Role of the Kimiya Yui Astronaut is Manipulate the SSRMS (Space Station Remote Manipulator System) for the operation of capturing Kounotori-5.


The Team Size of the New Horizons Spacecraft is About 200.


The Vector Components Random Error of the Air Drag Satellite System is < 5 x 10 -8  ms -2.


The Latency of the ATL12 Ocean Elevation Data is 45 days from receipt of last data in product.


The Ion Drift Velocity of the PAP Plasma Analyzer is -3 ~ +3 km/s.


The Color Composition of the False-color image Image is Shortwave infrared, near-infrared, and green light in the red, green, and blue channels of an RGB picture.


The Dimensions of the Research Facility Facility is 26 inches high, 35 inches wide, 24 inches deep.


The Technique of the Level-2 Data Processor is Empirical.


The Integration Levels of the Cooperation by Expansion Data Exchange is Within CSK boundaries and with other EO systems.


The Pointing Accuracy of the Attitude Control Subsystem (ACS) Attitude Control System is 0.05°.


The Launch Date of the GeneSat-1 Satellite is December 16, 2006.


The Technology Readiness Level of the CubeSats Satellite is Higher.


The Data Collection Period of the Liulin-MO dosimeter Radiation Dosimeter is Since the spacecraft reached orbit around the planet.


The On-Orbit Spectral Characterization Duration of the Terra MODIS Satellite Instrument is Five Years.


The Distance from Earth of the GW170817 Gravitational Wave Event is About 130 million light years.


The Antenna Aperture Size of the GMI Instrument is 1.2 m.


The Testing Focus of the RAMIS Payload is Reduced gravitational force.


The Co-Alignment of the OSIRIS Optical Sensor is With a reference spot in the measurement devices.


The Heat Shield Material of the Schiaparelli Module is Norcoat Liege.


The Impact Location of the SMART-1 Satellite is 34.262° south, 46.193° west.


The Diagram of the TEC Antennas Antennas is Circular with 3 db.


The Development Date of the China High-resolution Earth Observation System (CHEOS) Satellite System is 2014.


The Spatial Resolution of the Visible Spectral Band Spectral Band is 1.25 km x 1.25 km.


The Download Time of the QuakeSat Satellite is Premium.


The Constellation Full Operational Date of the Arktika-M N1 Satellite is 2025.


The Location of the Translation Stage Actuator is Between the electronics bus and the sail storage area.


The Reentry Date of the Kounotori-6 Cargo Ship is February 5, 2017.


The Frequency Bands of the CITRIS Receiver is 401.25 and 2036.25 MHz, 150, 400 and 1067 MHz.


The Scan Modes of the CERES on TRMM Instrument is Cross-track, along-track, and rotating azimuth plane (RAP) mode.


The Hydrazine Consumption of the Envisat Satellite is 25.8 kg on average per year.


The Data Channels of the SAGE-III Spectrometer is 8 spectral channels + 1 zero-order light channel.


The Sensitivity of the Channel 7 Sensor is 0.4 K/pixel.


The Horizontal Spatial Resolution of the Tomorrow-R1 and -R2 Satellite is 5 km.


The Altitude of the QuakeSat Satellite is 820 km.


The Content of the L2A Products Data is Ground reflectance cube, maps for estimated WV, AOT and image masks for land, water, haze, clouds, cloud-shadows and snow.


The Infrared Emissivity of the Cube Corner Reflectors (CCRs) Satellite Component is ε.


The Information Source of the Remote Sensing Observation Method is Reflected light in the solar domain.


The Science Instruments of the Dellingr Satellite is Boom-mounted fluxgate magnetometer, gated time-of-flight ion-neutral mass spectrometer (INMS).


The Launch Date of the PROBA-1 Microsatellite is 22 October 2001.


The Environment Requirement of the CITRIS Receiver is Electromagnetically pristine.


The Signal Spectrum of the AIS Automatic Identification System is Entire signal spectrum is downloaded for de-collision of the AIS messages.


The Type of the Twin 6U CubeSats Satellite is CubeSat.


The Quantity of the Rx Channels Receiver is 2.


The TRL of the Myriad RF board RF Board is 3.


The Data Rates of the Downlink Communication System is 1.024 to 1048.576 kbit/s.


The Launch Date of the Badr-B Satellite is 10 December 2001.


The Equipment of the GPS Spoofing Activity is GSE (Ground Support Equipment).


The HPA of the ASCAT Scatterometer is High Power Amplifier.


The Distance Between Satellites of the DICE nanosatellites Satellite is ~300 km.


The Radial Baselines of the Tandem-L Satellite is 0 m to 600 m.


The Type of the Photodetector Sensor is 3 mm FCI InGaAs quadrant photodiode with amplifier board.


The Image Capture Date of the CaSSIS Camera is 23 April 2020.


The Solar Panels Span of the INTEGRAL Satellite is 16 m.


The Ground Station Locations of the KazSTSAT Satellite is Svalbard, Astana and Guildford.


The Authors of the ACES Space Clock Experiment is L. Cacciapuoti, Ch. Salomon.


The Operation Start Date of the Cluster Satellite Mission is 2009.


The Year of Launch of the QuikSCAT Satellite is 1999.


The Publication Year of the Observation of the Earth and Its Environment: Survey of Missions and Sensors Documentation is 2002.


The Propellant Capacity of the Spacecraft Satellite is 23 kg.


The Efficiency of the SABR DC/DC Converter is Above 95%.


The LEO-to-ground Communication Link Speed of the Optical Ground Station Ground Station is 5.625 Gbit/s.


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


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


The Frequency of the MWR Radiometer is 36.5 GHz.


The Altitude of the OrbView-2 Satellite is 705 km.


The Technology of the Radiating Board Antenna Component is Based on the same technology developed in the frame of CSK.


The IFOV of the SAGE-III Instrument is 1-2 km.


The Acquisition Date of the MODIS Imaging Spectroradiometer is July 30, 2019.


The Type of the NIU VShE — DZZ Satellite is Earth Observation spacecraft.


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


The Optical Path of the IASI-NG Interferometer is Refractive material which thickness changes with the OPD.


The Location of the CryoVEx Campaign is Arctic.


The Digital sun sensors of the ADCS Attitude Determination and Control Subsystem is 1º (accuracy), ±60º (range).


The Power Bus Voltage of the MuREM Radiation Monitor is +5V.


The Launch Dates of the Orbiting Astronomical Observatories Satellite is 1966-1972.


The Mass of the HawaiiSat-1 Satellite is 55 kg.


The Mass (kg) of the HJ-1C Satellite is 890.


The Size of the Dove-1 Nanosatellite is 10 cm x 10 cm x 30 cm.


The Liftoff of the Antares Rocket is Ten minutes.


The Spectral Stability of the FTS Interferometer Interferometer is 3 x 10 -7  rms for 180 s.


The Band 4 of the MSS Instrument Spectral Band is 0.8 - 1.1 µm.


The Wavelengths of the Lunar Flashlight Spacecraft is ~1.495 µm, ~1.990 µm, ~1.064 µm, ~1.850 µm.


The Instrument Type of the BUV Sensor is Backscatter Ultraviolet (BUV) sensor.


The RF Communications of the IRIS Satellite is X-band for payload downlink at 15 Mbit/s.


The Vision Date of the Spitzer Space Telescope is 1946.


The Total Satellites of the ICEYE Satellite Constellation Satellite Constellation is 21.


The Imaging Modes of the Capella X-SAR Constellation Satellite Constellation is Stripmap, spotlight, and sliding spotlight.


The Signal Amplification Approach of the ATMS Instrument is Amplify first and then split into the various channels.


The Date of the Pacific Tic-Tac-Toe Image is 29 December 2021.


The Celestial Sphere Coverage of the Telescope Optical Instrument is 100% annually.


The Mass of the Total with contingency Satellite is 8.83 kg.


The Manufacturer of the ALTIUS Satellite is QinetiQ Space.


The Magnitude of the Trajectory Correction Maneuver Maneuver is 22 cm/s.


The Attitude Measurements of the Star Sensor Sensor is Roll, pitch, and yaw.


The Length of the Booms Deployment System is 30 cm.


The Launch Date of the CRISTAL Satellite is 2028.


The Planned Number of Satellites of the OneWeb Satellite Constellation is Up to 672.


The Altitude in Orbit of the Electric Thruster Thruster is 720 km.


The Mission Duration of the XMM-Newton X-ray Space Observatory is 20 years.


The Swath width at nadir of the Imager Satellite Instrument is ~57 km.


The Speed Requirement of the MOBC Main On-board Computer is Modest.


The Data Collection Area of the FORMOSAT-7/COSMIC-2 Satellite Constellation is Low- and mid-latitudes.


The Data Service of the Spire Satellite Constellation is Provides reliable and accurate global weather forecast.


The Purpose of the Cold Atom Laboratory (CAL) Facility is Produces clouds of atoms chilled to temperatures much colder than deep space.


The Measured Position Accuracy of the DIOGENE Navigator is ~ 5 m (3D, 1σ).


The Total Cost of the GHGSat-D Satellite System is 1% of other greenhouse gas measurement missions.


The Fully Charged Bus Voltage of the EPS Electric Power Subsystem is 33.6 V.


The Development Phase of the Spacebus Neo Satellite is Passed the Preliminary Design Review in early 2015.


The Compensates for of the LISA Pathfinder Spacecraft is Other forces acting upon it.


The URL of the STEREO Satellite is http://www.nasa.gov/mission_pages/stereo/news/five-years.html.


The Number of CubeSats of the Spire Satellite Operator is More than 70.


The | of the J.-H. Yeh Author is J.-H. Yeh.


The Reflector Size of the Harris Corporation Manufacturer is 12-meter.


The Unknown of the RadMon Radiation Measurement Device is Unknown.


The Precision of the Sentinel-6 Michael Freilich Satellite is Millimeter-scale.


The Deployment Sequence of the SkySat-16 to -18 Satellite is SkySat satellites first, about 13 minutes after liftoff, followed by the Starlink satellites about 39 minutes after liftoff.


The Material of the Structural Frame Trusses Satellite Component is Flat stock graphite/epoxy (Gr/E).


The Data Rate of the HEPD Instrument is 0.19 kbit/s.


The Purpose of the Automated Beacon Network Anomaly Detection System is Provide cost-effective anomaly detection and notification capabilities.


The Attitude Measurement Periodicity of the ISS Satellite is ~±0.5º in each axis over one orbit.


The No of Passbands of the Channel 4 Sensor is 1.


The Mission Number of the Swarm Satellite Constellation is 4th.


The Structure of the Solar Plumes Solar Phenomenon is Bundle of denser, flowing plumelets.


The Sea Level Rise Contribution of the CryoSat Satellite is 0.21 mm per year for Gulf of Alaska, 0.05 mm per year for High Mountain Asia.


The Detector Elements of the AHI Scanner is 77,400.


The Announcement Date of the PROBA-V Satellite is 20 April 2020.


The Pointing of the MicroSat-70 Satellite is Nadir pointing.


The Conference Presentation Date of the EnMAP Satellite is March 6-13, 2010.


The Power of the ISEE-1 Spacecraft is 175 W.


The Developer of the CIMON Astronaut Assistant is Airbus.


The Launch Date of the DMC-3 Satellite Constellation is 10 Jul 2015.


The Spectral Range of the Detector Instrument Component is 0.25-50 µm.


The Operator of the GeoEye-1 Satellite is Maxar Technologies.


The Launch Vehicle of the SkySat-16 to -18 Satellite is Falcon 9 rocket.


The Power Consumption of the Core-DHS Avionics Module is Reduced.


The Repeat Cycle of the HY-2B Satellite is 14 days.


The Conference Date of the NPOESS Satellite System is Sept. 9-11, 2008.


The Components of the Interactive Operation Mode Observation Mode is Video camera mode.


The Effect of Diffraction of the Geostationary Infrared Sounder Satellite Instrument is Increased compared to sounding from LEO.


The Ground Segment of the ERS-2 Satellite is Unknown.


The Interface of the Phoenix GPS Receivers GPS Receiver is AOCS interface box.


The Focus of the RAIDS Instrumentation is Remote sensing of the ionosphere.


The DEM Resolution of the TanDEM-X Satellite is 12 m.


The Accuracy of the Laser Rangefinder Device is Within 1 m.


The Microprocessor of the Beresheet lander Lander is GR712RC.


The Commissioning Phase Duration of the TerraSAR-X Satellite is Until the end of 2007.


The Mode of the RADARSAT-2 Satellite is ScanSAR Wide mode.


The Design Influence of the SWEM Satellite is THEMIS, HESSI, STEREO, and MAVEN.


The Model of the EC Digital Signal Processor is SMJ3320C30.


The Number of Satellites of the Iridium Satellite LLC Satellite Operator is 66.


The Pixel Size of the OCO-3 Instrument is About 1.3 miles (2.2 km).


The Electromagnetic Waves of the Tether Spacecraft Component is ULF, ELF, VLF.


The Launch Date of the ECSAT Space Center is 14 June 2017.


The Manufacturer of the GOES Sounder Instrument is NASA.


The IFOV (beam width) of the Antenna Reflector is 1.57º.


The Refurbishment Locations of the OMS-E Orbital Maneuvering System-Engine is NASA’s White Sands Test Facility in New Mexico, Johnson Space Center in Houston.


The Filter Type of the FUV channel Spectrometer is Block with Aluminum.


The Mechanism Failure Rate of the CubeSats Satellite is Less than 10%.


The Cyclone Yasi Rainfall Date of the TRMM Satellite is Feb. 7, 2011.


The No of Passbands of the Channel 2 Sensor is 1.


The Launch Date of the Galileo Satellites 13 and 14 Satellites is 24 May.


The Operating Temperature Range of the FEEU Payload Assembly Subsystem is 10:45ºC.


The Designation of the DFACS Attitude Control System is DFACS (aka AACS).


The X-ray Spectrum of the SXT Soft X-ray Telescope is Provides both the continuum spectrum which is indicative of the temperature of the plasma and the lines of the elements which are expected to be formed during the final evolution before the supernova explosion.


The Thickness of the High LET Detector Detector is 140 µm.


The Instrument Size of the RAMIS Radiation Detector is 140 x 140 x 35 mm3.


The Downlink Rates of the LLCD PAT Systems Communication System is Up to 311 Mbit/s.


The Input Voltage of the Receiver Communication Device is 5 V.


The Function of the TROPOMI Sensing Instrument is Bring a significant improvement in the precision as well as temporal and spatial resolution of derived atmospheric constituents.


The Operating Range of the FFRF Sensor Instrument is 3 m-30 km.


The Data Stream Availability of the Sentinel-6 Satellite is Within hours of collection.


The Area of the High LET Detector Detector is 9.6 cm^2.


The Thrust of the PROP unit Propulsion System is 130 mN.


The Max Recorded Pressure of the T3µPS Pressure Sensor is 3000 mbar.


The Number of Bands of the CIRiS Infrared Imaging System is 3.


The Propulsion System Control of the BepiColombo Spacecraft is Mercury Planetary Orbiter’s onboard computer.


The Unknown of the DLTU Data-Link Transmission Unit is Unknown.


The Mean Revisit Time of the TeLEOS-1 Satellite is 12-16 hours.


The Observation Type of the OCO-3 PMA Pointing Mirror Assembly is Non-nadir.


The Products of the AMSR3 Satellite is Brightness Temperature, Total Precipitable Water, Sea Surface Temperature, Sea Ice Motion Vector, Precipitation, Land Surface Temperature, Sea Surface Wind Speed, Soil Moisture Content, Vegetation Water Content, Sea Ice Concentration, Snow Depth.


The Ground Resolution of the StriX-α SAR Satellite is 1-3 m.


The Memory of the Satellite Memory Satellite is Limited.


The Bus Provider of the Jason-2 Satellite is CNES.


The Image Footprint of the HyperScout Earth-observing Instrument is Approximately 200 x 150 km2.


The Perigee (km) of the Meteor-1-2 Satellite is 630.


The Planned Satellite Launch of the OneWeb Company is December.


The Partnership Date of the Skybox Imaging Company is May 14, 2013.


The Instruments of the SPOT-5 Satellite is Vegetation, HRS, DORIS-NG (SPOT), HRG.


The Function of the Magnetic Spectrometer Instrument Component is Track charged particles and determine the sign of their charge and their rigidity.


The Spectral Range of the Current GOES imager Sensor is 5.77-6.6.


The Mission Objectives of the ITUpSat-1 Satellite is Capture imagery of the CMOS payload and to study the behavior of the passive stabilization system of the CubeSat.


The S/C Pointing of the DSX Spacecraft Payload Module Satellite is 1.0º, 1.0º.


The Mass of the DeOrbitSail Nanosatellite is 7 kg.


The Spectral Bands of the HyperScout Earth-observing Instrument is 45 visible and near-infrared spectral bands.


The URL of the GRAIL Mission is http://moon.mit.edu/index.html.


The Location of the SOC Science Operations Center is Villafranca near Madrid.


The Number of Satellites of the COSMO-SkyMed Satellite Constellation is 4.


The Servicer Mass of the ELSA-d Mission is ~175 kg.


The Mission Status of the CryoSat Satellite is Mission complete.


The URL of the Alphabus Satellite Platform is http://www.esa.int/esaTE/SEMSIGKTYRF_index_0.html.


The Onboard Storage of the Kanopus-V 1 Satellite is 24 GB.


The First Precipitation Observation Date of the RainCube Satellite is August 27, 2018.


The Detector Type of the Imager Satellite Instrument is CCD.


The Output Power of the XBT X-band Transmitter is 10.5 W.


The Position Date of the Storm Hunter Satellite is 13 April, 2018.


The Operational Duration of the MADRAS Instrument is Up to the end of January 2013.


The Lens Aperture of the MSI-0 and MSI-1 MSI Instruments is 180 mm.


The Power of the MuREM Radiation Monitor is Low.


The Exposure time of the Star Tracker Attitude Determination Device is 100 ms.


The Spatial Resolution - MS of the Spacecraft Satellite is 4 m GSD.


The Deployment of the Antenna Dish Satellite Component is Outer portion of the rib must be folded before the inner portion of the rib.


The Overview of the Air Force ESEX Flight Experiment Flight Experiment is Not provided.


The Deep-Space Observations of the SBSS-1 Satellite System is 3.8 million in first year.


The Beamwidth of the Antenna Conically-scanning reflector is 2.7º.


The One Year on Orbit Date of the MaSat-1 CubeSat is Feb. 13, 2013.


The Electromagnetic Interference Chamber Testing Location of the Crew Dragon Spacecraft is SpaceX factory in Hawthorne, California.


The Mass of the Venta-1 Nanosatellite is ~5 kg.


The Bistatic Phase of the TanDEM-X Satellite is October 2015 to End of the Year.


The Observation of the ERG (Arase) spacecraft Satellite is Chorus waves and scattered electrons in the magnetosphere.


The Functions of the PCU Power Control Unit is Battery charge / discharge control, peak power tracking (PPT) control for power generation of the solar cells.


The Structure Shape of the Clementine Spacecraft is Octagonal prism.


The Spectral Range of the VIS Visible region of spectrum is 403-803 nm.


The Inclina. (º) of the Intercosmos- Bulgaria 1300 (Intercosmos-22) Satellite is 81.2.


The Launch Date of the EarthCARE Satellite is 2015.


The Accuracy of the Ozone Measurement Instrument Atmospheric Measurement Device is Greater of (20%, 0.1 ppmv) below 15 km.


The Date of the New NASA Model Finds Landslide Threats Event is 22 March 2018.


The Design of the E-THEMIS Thermal Emission Imaging Instrument is Infrared camera.


The Launch Date of the Argos-3 Instrument is November 6th – November 7th.


The Height of the Falcon 9 first stage Rocket is 42 m.


The Inclination of the Satellite Imaging Satellite is 98.1º.


The Date of the Plugging-in Sub-Saharan Africa Image is 22 March 2021.


The Hosted Instrument of the PLATiNO 2 Satellite is MAIA instrument.


The Ready for Flight Date of the CubeSats Satellite is Dec. 16, 2011.


The Instrument of the EMIT Satellite is Imaging Spectrometer.


The Separation Time of the OG2-1 Satellite is Approximately 9:00 pm EST.


The Swath Width of the Spotlight-2A Satellite is 10km.


The Image Acquisition Files of the PROBA-V Satellite is 1.392.


The Operations Location of the Ground Segment Satellite Ground Segment is ESOC (Darmstadt, Germany).


The Resolution of the Deimos-2 Earth Observation Satellite is 75 cm per pixel.


The Structural Qualification Time of the SSTL-300 S1 Satellite is 24 months.


The Mass of the Rising-2 Microsatellite is 43 kg.


The ACS Testing Device of the AeroCube-4 Satellite is Simple single degree-of-freedom hanging string.


The Frequency Bands of the JMR Microwave Radiometer is 18.7, 23.8, and 34 GHz.


The Launch Vehicle of the AeroCube-4 Satellite is Atlas-5-411.


The Number of Arrays of the Solar Panel Power Generator is 6.


The Launch Plans of the Sentinel-1C Satellite is In force to launch as soon as possible.


The Survey Date of the Gaia Satellite is 13 May 2022.


The Orbit Reach Time of the Kick Stage Rocket Stage is About 10 minutes later.


The Observation Capabilities of the Aditya-L1 Satellite is Sun's Photosphere (soft and hard X-ray), Chromosphere (UV) and corona (Visible and NIR).


The Data Delivery Time of the HRFI Imagery Satellite is 150 seconds.


The Within about one to three weeks of the Flare Prediction Accuracy Model Performance is They demonstrated that their model was correct by predicting the appearance of a flare in December 2015 to within three weeks.


The Center Frequency of the Instrument SAR is 435 MHz.


The Telescope Type of the ISAMS Instrument is Movable off-axis reflecting telescope.


The Purpose of the Space Cameras Imaging Device is Monitor forests.


The Operation Duration of the Landsat 5 Satellite is Unknown.


The Number of Tiles of the TanDEM-X Satellite is More than 19,000.


The Orbit Type of the FY-3E Satellite is Sun-synchronous near-circular orbit.


The Spacecraft Housekeeping Data Bus of the SAMPEX Satellite is Mil-Std-1773B fiber optic data bus.


The Number of Bands of the VNIR Detector is 40.


The Downlink of the Miniaturized X-band transponders Communications System is 100 kbit/s.


The J2000 right ascension (deg) of the B1617-155 (Sco X-1) Pulsar is 244.979.


The Manufacturer of the DESIS Instrument is German Aerospace Center (DLR).


The Role of the Electrical GSE Ground Support Equipment is Simulating the LEU and taking all of the required data needed to record laser performance.


The Measurement Synergy of the GMI Radiometer Radiometer is Mutual overlap of actively sensed, vertically-profiled, radar data at two frequencies in combination with the multi-channel passive data of GMI.


The URL of the Glory Satellite is http://glory.gsfc.nasa.gov/launch.html.


The Local Solar Time on Descending Node of the CBERS-2B Satellite is 10:30 hours.


The Pixel size of the Channel 2 Sensor is 32 km x 32 km.


The Operation of the Pleiades System Satellite System is Coordinated operation of the Pleiades satellites, spaced 180º apart in orbit.


The Workshop Date of the PROBA-1 Satellite is April 28, 2004.


The Total Allowable Mass of the Supernova-Beta Satellite is 12 kg.


The Radar Signature Change of the ENVISAT satellite Satellite is Increased with rainfall, then shrank at a rate of 2.4 cm/hr.


The Planned Number of Satellites for 2020 of the Satellite Constellation Satellite Constellation is 16.


The Status of the STEREO-A Satellite is Operating fully.


The Mission Focus of the ACE Satellite is Solar wind and ICME (Interplanetary Coronal Mass Ejections), solar and interplanetary energetic particles, cosmic rays and heliosphere/interstellar interactions, and space weather.


The Ground Resolution of the Pléiades-Neo satellites Satellite is 30 cm.


The Engines of the Propulsion Qualification Model Model is 21.


The Efficiency of the Transponders Device is 40%.


The Reentry Burn Duration of the First Stage Rocket Stage is 19 seconds.


The Total Mass of the Minisatellite Satellite is 150 kg.


The Launch Date of the Sentinel-6 Satellite is 30 September 2020.


The Detection Threshold of the Instrument Sensor is 4.7 µJ m -2  sr -1.


The Altitude of the JL-1-GF03B Microsatellite is 535 km.


The Rainfall Accumulation of the GPM Satellite Mission is Particularly intense in the Mexican states of Yucatán, Campeche, and Quintana Roo.


The Polarization of the MWR Radiometer is V.


The Anniversary Date of the Landsat Satellite is July 23, 2012.


The Losses of the Harness Component is 1%.


The Greg Wyler Testimony Date of the OneWeb Satellite Constellation is October 25, 2017.


The Drag Profile of the AC4-B Satellite is Larger.


The USC Operation End Date of the Hitomi X-ray Astronomy Satellite is March 26.


The Maximum Firing Rate of the CU Control Unit is 55 Hz.


The Terminal Type of the Pléiades Neo Satellite Constellation is Reactive Ka-band.


The Design Bandwidth of the Three-axis diagonal gradiometer Gradiometer is 5 x 10 -3 to 10 -1 Hz.


The Use of the Quasars Celestial Objects is Probes of the expansion history of the Universe.


The Total Impulse of the SkySat-5 Satellite is 150 Ns.


The Number of Substorms Caught of the THEMIS Constellation Satellite Constellation is More than five dozen.


The Data Rate of the X-band Data Acquisition is 18.4 Mbit/s.


The Repeat Cycle of the Orbit Satellite Orbit is 24 days.


The Delivery Date of the FORMOSAT-7 Satellite Constellation is May 1, 2015.


The Bandwidth of the Ranging Channel Communication System is Approximately 800 kHz.


The Measurement Method of the Electrodes Displacement Detection is Differential capacitive measurement.


The Abbreviation of the MTSAT Satellite is Multifunction Transport Satellite.


The Dust Velocity Distribution Analysis of the GIADA Contamination Monitor is Dust ejection velocity depends both on the grain size and on time.


The Spectral Range of the CCD Detector System Imaging System is 450 nm to 900 nm.


The Spectral Range of the WV60 imager Imaging System is 0.45 µm- 0.90 µm.


The Technology of the EXI instrument Imaging Instrument is CMOS.


The Minimum Variance Wind Speed Estimator of the Spaceborne GNSS-R Device is Spaceborne GNSS-R Minimum Variance Wind Speed Estimator.


The Lifetime of the Satellite Satellite is 7 years.


The Field of View of the Electron Spectrometer Spectrometer is Nearly 4π.


The Operation Status of the Kepler Spacecraft is Nominal.


The Sector Ice Discharge Increase of the Austfonna Ice Cap is 45-fold.


The Firing Duration of the X-axis Bang-Bang Maneuver Satellite Maneuver is 10 s.


The Publication Date of the "Discrete and broadband electron acceleration in Jupiter's powerful aurora" Research Paper is 7 September 2017.


The Attitude Control System Design Life of the ANUSat Satellite is 6 months.


The Experiment of the STAR-Dundee Company is Testing a next-gen high-speed communication protocol called SpaceFibre.


The Modes of the RADARSAT-2 Satellite is Spotlight mode, Five wider coverage stripmap modes, Two higher resolution ScanSAR modes for maritime surveillance, Extra wide swath 5 m resolution mode (Extra Fine).


The Constellation Deployment Timeframe of the Satellite Constellation Satellite Constellation is Over the course of 24 months.


The Number of AIS Transmissions Captured of the AprizeSat-3 and AprizeSat-4 Satellites is Over 200,000.


The Purpose of the Parker Solar Probe Spacecraft is Answer questions about solar physics.


The Field Range of the Magnetic Field Sensor Magnetoresistive Sensor is 64 µT.


The Implementation of the PGS Ground Segment is Heterogeneous Mission Access (HMA).


The Performance of the GPS Navigation System is Degraded.


The Power Consumption of the DPU Digital Processing Unit is 130 W.


The Data Processing Location of the Ground Segment Satellite System is MOC (Mission Operations Center) facility at Cordoba.


The Deliverable of the Product Level 2A (L2A) Data is Earth located pixel values converted to ground surface reflectance.


The Solar Panels Power of the EROS-A Satellite is 450 W.


The Size of the MSU-100 Camera is 210 x 200 x 200 mm.


The SPAC Valuation of the Satellogic Satellite Company is $1.1 billion.


The Failure Detection System of the SMART-1 Satellite is FDIR system.


The Braking Method of the Tether Spacecraft Component is Mechanical friction.


The Size of the SPORT 6U CubeSat Satellite is 6U.


The Data Products Archive of the IXPE Observatory Satellite is NASA's HEASARC.


The Calibration Stability of the CERES on TRMM Instrument is 0.25%.


The Satellite Build Time of the ÅAC Microtec group Manufacturer is 4 months.


The Battery Capacity of the XI-IV Picosatellite is 780 mAh.


The Spatial resolution at nadir of the TOU Total Ozone Unit is 50 km.


The LTDN of the JL-1-GF03D Microsatellite is 10:00.


The Accuracy of the Atomic Clock Timekeeping Device is One second in three million years.


The Number of Satellites in Orbit of the Satellogic Satellite Company is 68.


The Wavelength of the W-band Band is 3.9 mm.


The Operations Phase Duration of the LISA Pathfinder Satellite is 6 months.


The Conference Date of the MicroMAS Project Satellite is August 13-16, 2012.


The Purpose of the Ground Station Ground Station is Send commands or receive data.


The Size of the KELT-11b Planet is About 30% larger in size than Jupiter.


The Level-1 SLC Products of the Sentinel-1 Satellite is Focused data in slant-range geometry, single look, containing phase and amplitude information.


The Calibration of the Advanced Land Imager Imaging Device is Spectral and Radiometric.


The Gases Measured of the FTS Fourier Transform Spectrometer is CO2, CH4, carbon monoxide (CO), and other gases.


The Ground Segment Components of the TEMPO Satellite is IOC (Instrument Operations Centre) and the interface to the host SOC (Spacecraft Operations Centre).


The Mission Status of the YES Satellite is Failure.


The Composition of the CAM Core Team Team is 2 MSc students, 3 PhD students, 3 MSc graduates.


The Attitude Control System of the Bus Satellite Component is Reaction Control Subsystem (RCS) - a hydrazine blowdown system pressurised with helium.


The Real Time Clock and Calendar (RTCC) of the dsPIC33F microcontroller Microcontroller is Unknown.


The Image Resolution of the VSSC Satellite is 10 m.


The Instrument Suite of the EUI Extreme UV Imager is Two HRI (High Resolution Imagers), one at Lyman α and one dual-band in the extreme UV, and one dual-band FSI (Full Sun Imager) working alternatively at the two 174 Ä and 304 Ä EUV passbands.


The Detector Temperature of the ATSR-1 Instrument is < 95 K.


The Alignment of the FG Filtergraph is Unknown.


The Spatial Resolution & Stability of the Telescope Optical Instrument is PSF stability better than 1%.


The Operator of the Argos/DCS Satellite System is NOAA.


The Manufacturer of the SeaHawk-1 CubeSat is AAC Clyde Space.


The De-orbit Date of the Tiangong-2 Space Lab is July 2019.


The Processing Functions of the DCU-S(TC) module Communication Module is CLTU delimitation, BCH decoding, de-randomization, Security Header extraction, TC Transfer Frame (TF) authenticated decryption and anti-replay control, pseudorandomization and BCH encoding.


The Measurement Category of the EXPORTS Satellite Mission is Ocean colour/biology, Multi-purpose imagery (ocean).


The Environmental Qualification of the Prometheus Satellite is GEVS (General Environmental Verification Specification).


The Rocket Type of the Chang'e-5 Lunar Mission is Long March 5.


The Freezing Temperature of the Carbon Dioxide Ice Substance is -193°C.


The Orbit Location of the ACE Mission Satellite is First Lagrangian orbit point (L1).


The Objective of the PhoneSat-1 and -2 Satellite is Use a commercial mobile telephone (smartphone) as an avionics system in a nanosatellite.


The LEOP Completion Date of the TerraSAR-X Satellite is June 21, 2007.


The Battery Quantity of the HTV Spacecraft is 6.


The Orbital Slot of the GSAT-0210 Satellite is A02.


The Spatial Resolution of the TopSAR narrow Imaging Mode is 30 - 50 m.


The Temperature Increase of the Surrounding Ocean Ocean is Yes.


The Spatial Resolution of the Solid Earth Continental lithosphere Satellite is 50-100 km.


The Swath of the Megha-Tropiques Satellite is ~2200 km.


The Error (RMS) of the Magnetometer Sensor is <40 nT.


The Apocenter Distance of the SMART-1 Satellite is 4644.004 km.


The Formation of the Shocks Phenomenon is When a supersonic – faster-than-sound – flow encounters an obstacle.


The Mass of the CBNT-1 (Carbonite-1) Earth Observation Microsatellite is 91 kg.


The Detector Types of the Instrument CCD Imaging Camera is NIR and narrow-band VIS (630 nm).


The Planned Crew Capacity of the Tiangong Space Lab Space Lab is 3.


The Image Acquisition Date of the Landsat 8 Satellite is February 5.


The Date of the Vega flight VV16 Launch is Unknown.


The Control Station Location of the JERS-1 Satellite is Tracking and Control Center (TACC), located at the Tsukuba Space Center.


The Propulsion of the TEPCE Satellite is Earth's magnetic field.


The Design of the Hyperion HSI (Hyperspectral Imager) is Telescope, two grating spectrometers with supporting focal plane electronics, and a cooling system.


The Cooperation Agreement Date of the Astroscale UK Company is December 2018.


The | of the GOSAT-2 Satellite is Space.based Carbon Monitoring by GOSAT and GOSAT-2.


The Orbit Altitude of the TEMPO Satellite is 35,786 km.


The Launch Site of the STPSat-3 Satellite is MARS (Mid-Atlantic Regional Spaceport) on Wallops Island, VA.


The Operational Power Consumption of the MIS Instrument Microwave Radiometer is 357 W.


The Number of Launches of the Arianespace Company is Fourth launch of the year.


The Equatorial Nodal Crossing Time of the NigeriaSat-2 Satellite is 10:15 LTAN.


The Launch Date of the ORBCOMM Satellite is Oct. 8, 2012.


The Connection to Electronics Boards of the MAG Sensor Sensor is Accomplished by a tuned circuit, including the harness.


The Conference Date of the EarthCARE Satellite is Dec. 8, 2011.


The Magnetic Field Measurement Rate of the ULF Sensor Sensor is 0.03 to 3 Hz.


The Typical Value of the C2H2O2 Satellite Instrument is 0.2.


The Ground Sampling Distance of the TrueColour Imager Optical Imager is 5 m.


The Launch Date of the Cesium Satellite 1 Satellite is 27 September 2021.


The Services of the Ground Station Ground Segment is Monitoring and control.


The Operational of the Resurs-P3 Satellite is True.


The Data Rate of the S-band Communication Band is 665.4 kbit/s.


The URL of the Jupiter's Auroras Natural Phenomenon is https://www.nasa.gov/feature/jpl/jupiter-s-aurora-presents-a-powerful-mystery.


The Altitude of the ExoMars Orbiter Satellite is Approximately 400 km.


The Tracking of the Ground System Communication System is Imprecise.


The Unknown of the TROPOMI satellite instrument Satellite Instrument is Unknown.


The Mass of the CNUSail-1 CubeSat is 4 kg.


The Wavefront Sensing of the DeMi Satellite is Image plane and pupil plane (Shack-Hartmann).


The Leak of the MarCO-B CubeSat is Thruster Valve.


The Nr. of spectral or frequency bands of the Optical System Imaging System is 4 in VIS and 1 in SWIR.


The Replacement Date for Meteosat-7 of the Meteosat-8 Satellite is First quarter of 2017.


The Mission Type of the HTV-9 Cargo Transfer Spacecraft is Non-EO.


The Affiliated Institutions of the Bluecrab supercomputer cluster Supercomputer Cluster is Johns Hopkins University and University of Maryland.


The Interface Type of the GOES-R Access System Data Distribution System is Subscription-based and ad hoc data requests.


The Flight Time for Ions of the COSIMA Mass Spectrometer is 16 µs.


The J2000 right ascension (deg) of the B1509-58 Pulsar is 228.48175.


The Launch Site of the Falcon 9 Launch Vehicle is Launch Complex 39A (LC-39A) at NASA’s Kennedy Space Center in Florida.


The Service Module Assembly Start Date of the Orion Spacecraft is May 19, 2016.


The Detection Capability of the Copernicus Sentinel-5P Satellite is Methane cloud, nitrogen dioxide plumes from individual ships.


The Effect of the South Atlantic Anomaly Magnetic Anomaly is Affects the amount of cosmic radiation reaching the passengers and crew of any plane and spacecraft led to cross it.


The Data Production Period of the IMERG Data Processing System is Seven day period from 23-30 November 2018.


The Mission Type of the TUBSAT Satellite is EO.


The Floating Distance of the Orihime Satellite is About 200 mm.


The Number of Planets of the TRAPPIST-1 Star System is 7.


The Angular Resolution of the ELENA Sensor is 4.5º x 4.5º.


The Type of the PRARE space segment oscillator Quartz-Crystal Oscillator is Voltage-controlled.


The Age Difference of the IC 4665 and Collinder 350 Star Clusters is More than 500 million years.


The Launch Date of the Earth Science Sensor Sensor is 2021.


The Technology of the Procyon star tracker Attitude Determination Device is Active Pixel Sensor (APS).


The Charge Range of the ULEIS Spectrometer is He through Ni.


The Pulse Length of the RA-1 Radar Altimeter is 20 μs.


The Panchromatic Band Off-nadir Resolution of the WorldView-3 Satellite is 0.34 m.


The Uncertainty of the Responsivity Measurement Instrument is <0.1%.


The Precision of the OCO-2 Satellite is <0.3% (1 ppm).


The Processor of the ODHS Processor Module Onboard Data Handling System is Atmel 32 bit processor of ARM9 architecture.


The Impact Test Date of the DebriSat Satellite is 15 April, 2014.


The Date of the High-Latitude Cold-Season Snowfall Campaign Field Campaign is January 15, 2012 until March 3, 2012.


The Development Start Date of the MMO Spacecraft is March 19, 2015.


The Bus Concept of the MS-2 Minisatellite is Modular platform capable to accommodate various types of payloads within the minisatellite class and to permit various versions and modifications of the onboard supporting subsystems.


The Number of Satellites in Orbit of the Satellogic Satellite Manufacturer is 8.


The Subsystem Microprocessor of the CubeSat Satellite is Each subsystem has its own microprocessor.


The Data Revealed of the Hinode Spacecraft is The source of the SEP events.


The Conference Date of the Dove Satellite is Aug. 5-10, 2017.


The Density of the Comet Celestial Body is 470 kg/m3.


The Navigation System of the Resurs-P Satellite is Star and sun sensors for attitude data, GLONASS/GPS system for orbital position determination.


The Image Content of the INTEGRAL Satellite is Shows the auroras forming a rough semi-circle at Earth’s northern latitudes.


The Presentation Date of the CartoSat-2 Satellite is Sept. 29 to Oct. 3, 2008.


The Overview of the TECSAR Satellite Hardware and Mosaic Mode of the TecSAR Satellite is Ury Naftaly, Ronit Levy-Nathansohn, “Overview of the TECSAR Satellite Hardware and Mosaic Mode,” Geoscience and Remote Sensing Letters, IEEE Geoscience and Remote Sensing Letters, IEEE Vol. 5, Issue 3, July 2008, pp.:423 - 426.


The | of the Plasma Experiment for Planetary Exploration (PEPE) Plasma Experiment is Plasma Experiment for Planetary Exploration (PEPE).


The Objective of the PLEGPAY Experiment is Study of spacecraft/space environment interactions in LEO with reference to electrostatic charging/discharging phenomena.


The Spatial Resolution of the spaceCam c4000 Video Camera is 6 m.


The Observation Area of the IBEX Spacecraft is Outside the heliosphere.


The Application of the RISAT-2 Satellite is Radar satellite imagery for assessing cyclone damages.


The Number of PCBs of the EPS Electric Power Subsystem is 5.


The Primary Role of the Dextre Robotic System is ISS Handyman, replacing failed components, unloading cargo, supporting technology demonstrations.


The Satellite Size of the Sounder Instrument Instrument is 6U.


The Image Frequency of the TESS Satellite is Every 30 minutes.


The Voltage of the Voltage 7 Power Amplifier is 3.5±2%.


The Mission Start Date of the DSCOVR Satellite is March 3, 2012.


The Wavelength of the Telescope Optical Instrument is 0.6 - 29 µm.


The Conference Date of the TanDEM-X Satellite is April 25-30, 2010.


The Redundancy of the Reaction Wheels Attitude Control Device is 1 RW loss allowed.


The Array Size of the CCD Detector Matrix Detector is 576 lines x 780 columns.


The Mask at Intermediate Image Plane FOV of the TIR Subsystem Imaging System is ±11.3º.


The Rotation Capability of the JUICE Spacecraft is True.


The Operation Principle of the Imaging Pushbroom Spectrometer Spectrometer is A strip (swath) of the Earth's surface is imaged through the entrance optics on the field stop. The collimator optics realizes parallel light rays falling onto the grating. The grating disperses the different “colors” that are focussed by the imager into .


The Orbital Slot of the GSAT-0211 Satellite is A06.


The Measurement Modes of the Sensor Particle Detector is Count Mode, List Mode.


The Orbit Inclination of the Secondary Payloads Satellite is 102º.


The Components of the Chang'e-5 Lunar Probe is Lander, orbiter, ascender, returner.


The Processed Imagery of the Image Location Knowledge Satellite Component is < 100 m.


The Launch Site of the ALL-STAR-1 Satellite is Cape Canaveral, FL.


The Conference Presentation of the EDSN Intersatellite Communications Architecture Communications Architecture is AIAA/USU Pre-Conference: CubeSat Developers' Workshop, Logan, Utah, USA, August 2-3, 2014.


The Period of the Molniya Orbit Orbit is 11 hours and 58 minutes.


The Orientation of the ESP Thrusters Maneuvering System is For the spin-up maneuver, pairs of thrusters will be co-aligned 180º apart; for de-spin, a 2nd pair of thrusters will provide the opposite force; for the normal thrust maneuver, the thrusters will be oriented perpendicular to the exterior of the satellite.


The End of Life Date of the ALOS-3 Satellite is 7 March 2023.


The About Author of the Optical Inter-orbit Communications Engineering Test Satellite (OICETS) Satellite is Yasuhiro Morita.


The Antennas of the Antenna System Communication System is Four broadband feed-horn antennas.


The Number of Asteroids of the Gaia Satellite is 154,741.


The Data Release of the NISTAR National Institute of Standards and Technology Advanced Radiometer is Expected shortly after EPIC data.


The Daughter card of the C&DH subsystem Onboard Computer System is Cortex A8 processor.


The Panchromatic Mode Band of the SPOT satellite constellation Satellite Constellation is Single wide band in the visible part of the spectrum.


The Type of the Microwheel 10SP-M Reaction Wheel is Small Satellite.


The Area of the Low LET Detector Detector is 9.6 cm^2.


The Spectral Region (Infrared Channel) of the VIRR Instrument is 10.5 - 12.5 µm.


The Location of the GSOC Operations Center is Oberpfaffenhofen.


The Positioning of the GNB Satellite is ±20º about the magnetic field vector.


The Hardware and Software Design of the OBC Onboard Computer is Exactly the same as PDH.


The Tether Length of the ATEx Tether Experiment is 22 m.


The Image Credit of the Chandra X-ray Observatory X-ray Observatory is X-ray: NASA/CXC/NCSU/K. Borkowski et al; Optical: DSS.


The Revisit Cycle of the LISS-4 Camera is 5 days.


The Band Spacing of the VNIR Detector is 11.4 nm.


The Presentation Date of the Magnetospheric Multiscale (MMS) Mission is 2008.


The Constellation Update Date of the Planet Company is 24 January 2021.


The Launch Date of the Tomorrow-R1 and -R2 Satellite is April 2023 and June 2023.


The Presentation Date of the TerraSAR-X, TanDEM-X, EnMAP Satellites is June 18-19, 2009.


The Bandwidth (GHz) of the ICI-2 Radiometer is 3.


The Unknown of the ALOS-3 Satellite is Unknown.


The Sounder Type of the MLS Instrument is Three-channel heterodyne limb sounder.


The SNR of the Instrument Spectrometer is ≥900.


The Application of the MCP Multi-Channel Plate is Measure the gas density in the upper atmosphere.


The Spectral Resolution of the MAHRSI Instrument is 0.026 nm at 215 nm.


The Functional Architecture of the EO-ALERT Satellite System is Modular, scalable and reconfigurable.


The Objective of the GAS Grating Spectrometer is Measurement of CO2, CH4, CO, N2O.


The Size of the Optical Scanning Design Imaging Spectrometer is 1.3 m3.


The Nominal SNR of the Band 5 Spectral Band is 1010.


The Launch Date of the Hisea-1 Satellite is 6 November 2020.


The Image Compression of the HyperScout Imaging System is 2x2.


The Launch Date of the Trace Gas Orbiter (TGO) Satellite is 2016.


The Exceeded Design Life of the TRMM Satellite is Yes.


The Spatial Resolution of the Geodesy Unification of worldwide height systems Satellite is 100-20000 km.


The Quantity of the Kuiper Belt Object Celestial Object is More than 100,000 objects.


The Interferometry Mode of the TerraSAR-X SAR Satellite is ATI (Along Track Interferometric) mode.


The Launch Date of the Vietnamese satellite Satellite is Unknown.


The Observation Date of the IBEX Spacecraft is Oct. 2009.


The Orbit Inclination of the KSF1 satellites Satellite is 97.6º.


The Launch Date of the Vega Launch Vehicle is 17 August 2021.


The Solar Panels of the ALTIUS Satellite is Two deployable solar panels with 120 W of power.


The Venting Date of the SXT Soft X-ray Telescope is October 2015.


The Microcontroller RAM of the CC430 SoC System on Chip is 4 kB.


The On-board Data Recording Capacity of the RF Communications Communication System is 64 Gbit.


The Control System Development and Verification of the Delfi-C3 Satellite is Oct. 2-6, 2006.


The X-ray Systems Interval of the Diagnostic Instruments Test Facility is 2 µs.


The ΔV of the Propulsion System Satellite Component is Up to 200 m/s.


The Ground System of the UNIFORM-1 Satellite is Mission Planning, Scheduling, Control, and Data Processing.


The Planned Operational Lifetime of the Heinrich Hertz Satellite is 15 years.


The Validation Data Source of the CYGNSS Satellite is IWARP.


The Data Collection of the EPIC248847494 star Star is Light Curve.


The Observation Result of the Integral Satellite is Unexpectedly strong auroras illuminating the Earth.


The End of Life Date of the Myriade/AstroSat-100 Satellite is June 2030.


The Measurement Domain of the OCO-3 Instrument is Atmosphere.


The Attitude Control of the LAGEOS Satellite is None.


The Displacement of the Boulders Geological Feature is More than 3cm.


The Input Port Field of View of the FTS Fourier Transform Spectrometer is 2.6 arcmin diameter.


The Exceeded Design Life of the GRACE Satellite is Yes.


The Mission Status of the OSCAR-QUBE Satellite is Operational (nominal).


The Types of Maneuvers of the THEMIS (and ARTEMIS) spacecraft Satellite is 4 orbit change maneuvers, one attitude, and one spin rate adjustment per probe.


The Article Release Date of the Solar Orbiter Satellite is 27 April 2021.


The Swath width of the MWRI Microwave Radiation Imager is 1400 km.


The BCRs Configuration of the DubaiSat-2 Satellite is Three BCRs in a hot redundancy configuration.


The Weight of the Yutu 2 Lunar Rover is 140 kg.


The Eruption Observation of the GOSAT Satellite is October 2017.


The Resolution of the HARP-2 Polarimeter is <6 km.


The Qualification Runs of the GaN-based Power Transistors Transistors is 15 W and 80 W.


The Experiment Time of the Sloshsat-FLEVO Satellite is Until the gas supply of the cold-gas reaction control system is exhausted.


The Mission Type of the CHORUS Satellite Constellation is EO.


The URL of the SpaceX CRS-25 Dragon Spacecraft is https://www.nasa.gov/mission_pages/station/research/news/spacex-25-research-highlights.


The Launch Date of the Biomass Satellite is 2023.


The Star Position Accuracy (3σ) of the STOs and STAEs Analog Electronic units is Random Bias 3.1 arcsec (4 mag), 9 arcsec (6 mag); 13.7 arcsec (6.5 mag).


The Orbit of the LunaH-Map Spacecraft is Elliptical science orbit.


The Conference Presentation Date of the High Spatio-Temporal Resolution Land Surface Temperature Mission Satellite is 22-27 July 2018.


The UART Channels of the CSI Data Communication is 4.


The Orbit Maintenance Capabilities of the PACE Satellite is 10 years.


The Purpose of the DCAM3 Camera is Obtain close up views of impact.


The ICU of the ASCAT Scatterometer is Instrument Control Unit.


The Platform Size of the Tsubame Microsatellite is 45 cm x 45 cm x 56 cm (H).


The Eclipse Operation of the IRIS Spacecraft is Not operated for 4 months.


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


The Inclination of the Landsat 9 Satellite is 98.2º.


The Particles Detected of the Carmen-2 Radiation Detector is e-, p+ (high-energy particle flux of electrons and protons) and ion fluxes.


The Date of the Dungeness Spit Image is 13 April 2022.


The Platform of the Inmarsat S – Europasat / Hellas-Sat 3 Satellite is Spacebus 4000 C4.


The Mass of the PSat-2 Satellite is 2 kg.


The Purpose of the TROPOMI Instrument is Map a multitude of trace gases such as nitrogen dioxide, ozone, formaldehyde, sulphur dioxide, methane, carbon monoxide and aerosols.


The Spatial Resolution of the Solid Earth Seismic hazards Satellite is 100-200 km.


The Hyperspectral Imagery Resolution of the Satellogic Satellite Manufacturer is 30 meters.


The Mass Range of the CubeSats and nanosatellites Satellite is 1-10 kg.


The Daily Operation Time of the SAOCOM-1A Satellite is 450 minutes per day.


The Flux and Energy Spectrum of the Neutrons Radiation is Variable.


The Uplink Frequency of the RF Communications Communication System is 144 MHz.


The Program Manager of the ATMS Instrument is Danielle Gallegos.


The Unknown of the AIS-PEM Payload Electronics Module is Onboard the satellite was an Automatic Identification System - Payload Electronics Module (AIS-PEM).


The Manufacturer of the Strela-3/Rodnik Military Reconnaissance Satellite is NPO Prikladnoi Mekhaniki.


The Optical Pulse Size of the LI Instrument is 10 km - 100 km circular pulse diameter.


The J2000 right ascension (deg) of the B1758-250 Pulsar is 270.284.


The Launch Schedule of the Shenzhou XV Manned Spacecraft is This year.


The PDR Date of the IXPE observatory X-ray Observatory is August 8, 2018.


The Orbit Perihelion Distance of the V7GA Mission is 9.86 RS.


The Design Goal of the EGS Ground System is Disassociate space missions from pipeline ground system approaches and standardize ground system software, hardware, and interfaces.


The Frequency Range of the ICI Instrument is 183 GHz up to 664 GHz.


The Beamwidth of the Yagi Antenna Antenna is 45º.


The Operation Duration of the EO-1 Satellite is 10 years.


The Landing Site Data Transfer Time of the Spacecraft Satellite is Two days.


The Dimensions of the S/C Structure Satellite Structure is 90 cm x 90 cm x 107 cm.


The Pointing Accuracy of the ADCS Attitude Determination and Control Subsystem is ≤0.01º (3σ, 3-axis).


The Installation Date of the Y-3 Detector is January 1974.


The Fast Plasma Experiment of the SEE-1 and ISEE-2 Spacecraft is Unknown.


The Paper Number of the ERG Satellite Satellite is 2011-r-51.


The Test Duration of the Modern ICs Electronic Components is Unrealistic 7.6 years.


The Spectral Resolution of the Spectrometer Spectrometer is <2.5 cm -1.


The Calibration Cycle Time of the LISS-3 camera Camera is 7.3 s.


The Publication Year of the Aerosol Polarimetry Sensor Sensor is 2007.


The Project Partners of the TRACERS Satellite Mission is University of Iowa (UI), SwRI, MSS, UCB, UCLA.


The Observation of the Satellite Observation Satellite is Particle energization, solar flares, reconnection and plasma jet interaction with the local magnetic field structure.


The Deployment Date of the DIWATA-1 Microsatellite is April 27, 2016.


The URL of the Landsat-9 Satellite is https://landsat.gsfc.nasa.gov/landsat-9/.


The Solar Encounters of the Parker Solar Probe Spacecraft is 7.


The Spectral Resolution of the CO2Image Satellite is 1.0 nm - 1.3 nm.


The Size of the OSCAR-QUBE CubeSat is 1U.


The Recovery Method of the Kepler Space Telescope Space Telescope is Maneuvering the spacecraft so that the solar pressure is evenly distributed across the surfaces of the spacecraft.


The SNR of the Instrument General is Between 350 and 450.


The No of bands/channels of the VIRR Visible and Infrared Radiometer is 10.


The Interaction of the CNES and ONERA centers Centers is Illustrated in Figure 34.


The f/number of the 1000 mm camera Camera is f/11.


The Launch Date of the OTB-1 minisatellite Satellite is 25 June 2019.


The Purpose of the Data Compression Method Telemetry System is Prevent crowding out payload data.


The Attitude Actuation of the QuickBird-2 Satellite is Reaction wheels.


The Resolution of the False Color Composite Image Image is 250 m.


The Conference Date of the BIROS Satellite is June 11-15, 2012.


The Camera Module Interface of the Frame Grabber Data Interface is Correct interface to the camera module.


The Amplitude Spectral Density of the DOSS system System is Measured.


The Hermetic Sealing of the Laser Optical Communication Device is True.


The Orbit of the GRACE-FO satellites Satellite is Co-planar polar orbit.


The Number of Transmission Attempts of the Fixed Platforms Ground Segment is 3.


The Instrument Type of the AVHRR/3 Instrument is Whiskbroom-type.


The Center Frequency of the Satellite Device Unknown is 89.0 GHz.


The Spacecraft pointing capability of the ALOS-3/PRISM-2 Satellite is ±60º (cone, max).


The Launch Date of the ResourceSat-2A Satellite is December 7, 2016.


The Orbit of the Eutelsat 172B Satellite is GEO at 172ºE longitude.


The First Pictures Date of the XMM-Newton X-ray Space Observatory is Feb. 9, 2000.


The Components of the Ground Segment Ground Station is Laptop computer, radio/RF unit, antenna rotator and antennas.


The Conference Date of the LUMIO CubeSat is 1-5 October 2018.


The Masses of the Aluminum Spheres Satellite is 1 kg, 1.5 kg, 2 kg.


The Swath Width of the HIRDLS Spectrometer is 2000 - 3000 km.


The Technology Readiness Level of the DSAC Atomic Clock is 5 to 7.


The Design, AIT, Launch & Early-Operations of the Galassia Nanosatellite Satellite is Unknown.


The Angular Resolution of the IBEX-Lo sensor Sensor is 3.5º x 3.5º FWHM.


The Requirement of the EUMETCast Data Dissemination Service is Users to purchase new satellite reception equipment and pay for the transmission fee.


The Capacity of the Battery Power Storage is 12 Ah.


The Methane Detection of the Copernicus Sentinel-5P Satellite is True.


The NEΔT @ specified scene temperature of the Instrument Spectral Imager is 0.15-0.4 K @ 250 K.


The Backup Power Output of the Solar Array Power Generation is 55Ah NiCd (Nickel-Cadmium) battery charge power requirement.


The Communication System of the Bartolomeo Payload Communication System is OSIRISv3.


The Optics Design of the ACE-FTS Instrument is Highly folded design.


The Solar F10.7 cm fluxes Range of the PEM (Parameterized Exospheric Model) Theoretical Model is 80-230 x 10-22 W m-2 Hz-1.


The Grating Order of the Spectrometer Instrument is 3.


The Launch Date of the MMS Satellite is March 13, 2015.


The Mounting of the SCM Instrument is 1 m deployable boom.


The Orbital Slot of the GSAT-0204 Satellite is B03.


The Attitude Control of the Satellite Spacecraft is Hybridization of star sensor and accelerometer measurements.


The Telemetry Monitor of the SpaceX CRS-17 Mission is Christina Koch.


The Flight Computers of the Payload Instruments Satellite Components is Dual redundant flight computers based on Intel 80386EX processors, configured with 32 MByte capacity.


The Internal Data Speed of the DHU Data Handling Unit is Up to 10 Mbit/s.


The Data Collection of the ASTRO-H Satellite is Gas dynamics, particle acceleration, maximum energy of the accelerated particles.


The Mission Duration of the CM1 Satellite is September 2021 through 2026.


The Conference Presentation Date of the TanDEM-X Satellite is April 23-26, 2012.


The Launch Mass of the Konnect Satellite is 3619 kg.


The Date of the Space-based Automatic Identification System Experiment (SPAISE) Experiment is June 5-12, 2011.


The Number of Satellites of the HawkEye 360 Satellite Constellation is Not Provided.


The Location of the ESA Data Node is Esrange, Kiruna, Sweden.


The Spectral Range of the UV-1 Spectrometer is 270 - 314 nm.


The Number of Cells per Array of the Solar Panel Power Generator is 26.


The Frequency Range of the MTVZA-GY Radiometer is 10-48 GHz.


The Endurance of the TSUBAME Satellite is Able to endure the Dnepr rocket vibrations.


The Datasheet Release Date of the ADS-B Receiver Space Application Receiver is 22 Sept. 2015.


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


The Orbit of the Resurs-P1 Satellite is Sun-synchronous near circular orbit.


The Duration of the Calibration Phases Process is Not specified.


The Required Spacecraft Stability of the Framer Sensor is Low.


The Spectral Sampling Distance of the SWIR Spectrometer Spectrometer is 10 nm.


The Spatial Resolution of the GMI Instrument is Excellent.


The Data Delivery Time of the SafetyNetTM Data Collection Architecture is 75% within 15 minutes, 95% within 26 minutes.


The Total Volume of the Comet Celestial Body is 21.4 km3.


The Size of the Triton-1 Nanosatellite is 3U.


The Orbit of the Herschel Telescope Telescope is Large Lissajous orbit around the L2 point at a distance of around 1.5 million km from Earth.


The Mission Operator of the SPOT 6-7 Satellite is Airbus Defence and Space.


The Orbit Decay Cause of the GOCE mission Satellite Mission is Uncompensated atmospheric drag.


The Monitoring Purpose of the SMOS Satellite is Ocean acidification.


The End of Life Date of the FormoSat-1 Satellite is June 17, 2004.


The Power Consumption of the ODTML Data Collection System is < 0.1 Joule per bit transmitted.


The Conference Date of the Space Technology 5 Satellite is Feb. 3-7, 2007.


The Components of the SIR-2 Instrument is Sensor unit, power unit, ICU.


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


The Weight of the RPU Receiver Processor Unit is 16 kg.


The Mission Status of the Philae Lander is Active.


The Slew Maneuvers of the MicroSat-70 Satellite is Within ±15º about the roll axis (or ±180º about the yaw axis).


The Number of Passes over Stations of the SPOT-6 Satellite is 4 passes over the Toulouse station and 8 passes over the Kiruna station.


The Service of the Spire Global UK Company is Predict vessel locations and the ship’s estimated time of arrival at port.


The Mission of the INSAT-3DR Satellite is Provide service continuity to earlier ISRO meteorological missions.


The Satellite of the Sentinel-4 Mission is MTG.


The Planned Operation Duration of the Tiangong Space Station is 15 years.


The Manufacturer of the SPOT 7 Satellite is Astrium.


The Nodal Period of the Satellite HY-1B is 100.8 minutes.


The Wavefront Error of the Sentinel-4 GRU Grating Reflection Unit is 19.8 nm (rms).


The Operation of the OBC Architecture On-Board Computer Architecture is Independent real time tasks to be executed simultaneously.


The Usage of the Iris Radio is Raw measurements transfer and remote control of the spacecraft.


The 2.5 W/sensor head of the Instrument Power Sensor is Instrument power 2.5 W/sensor head.


The Pore Size of the ICON FUV Instrument MCP is 6 mm.


The Launch Site of the COPPER CubeSat Satellite is MARS (Mid-Atlantic Regional Spaceport), located at NASA's Wallops Flight Facility,Wallops Island, VA.


The Current of the Voltage 6 Modulator is 200.


The URL of the Dellingr Satellite is http://digitalcommons.usu.edu/cgi/viewcontent.cgi?article=3614&context=smallsat.


The Purpose of the SPIDER Imaging Sensor is Provide a 10 x to 100 x SWaP (Size, Weight, and Power) reduction alternative to the traditional bulky optical telescope and focal-plane detector array.


The Size of the Kodak KAI-11002 CCD CCD is 37.25 mm (H) by 25.7 mm (V).


The Propellant of the Aquajet Satellite Propulsion System is Water & anti-freeze.


The Integration Time of the Optics Device is 15 ms.


The Sensitivity of the Channel 1 Sensor is 0.5 K/pixel.


The Manufacturer of the Hiber-3 Satellite is Hiber.


The Stages of the Cooler Passive Cooler is 4.


The Spectral Channels of the CERES Scanner is 3.


The Data Collection of the Galileo Spacecraft is Flyby of Europa in 2000.


The Level-1 GRD Products of the Sentinel-1 Satellite is Focused data projected to ground range, detected and multi-looked.


The Launch Date of the Artemis-I Mission is 16 November 2022.


The Observation of the Suomi NPP satellite Satellite is Huge Saharan dust plume streaming over the North Atlantic Ocean.


The Interface of the MuREM Radiation Monitor is CAN bus.


The Capacity of the Solid-State Recorder Data Storage is 3 Gbit.


The Release Date of the Imja glacier, Himalayas Location is March 14, 2014.


The Advance in Accuracy Over Current Instruments of the CLARREO’s infrared and reflected solar spectrometers Spectrometers is Unknown.


The Data Handling of the Stensat Satellite is Keeps the most recent science packet as part of a beacon packet.


The Bus Type of the BILSAT-1 Satellite is MicroSat-100 bus.


The Launch Date of the Chandra X-ray Observatory X-ray Observatory is July 23, 1999.


The Communication Links of the GomX-4A and GomX-4B CubeSats is UHF and S-band.


The Number of Supersites of the MAPS Satellite is 19.


The Components of the Astro-APS Star Tracker is Camera head, electronics, and a shorter baffle.


The Communication of the LightSail 2 Satellite is Successful.


The Purpose of the Pumbaa and Timon smallsats Satellite is Obtain images of solar corona.


The Backscatter of the Mie co-polar channel Channel is 8 x 10 -7 sr -1 m -1.


The Ranges of the MAG Sensor Sensor is ±1024, ±4096, ±16,384, ±65,536 nT.


The Data Rate of the HIA Instrument is 3.12 kbit/s.


The Roundness of the Kepler 11145123 Star is More round than the Sun.


The Attitude Restitution of the Attitude Control Subsystem (ACS) Attitude Control System is 6 x 10-5 radians.


The Communication Failure of the Hitomi Satellite is March 26, 2016.


The SDR Validation of the VIIRS Instrument is Unknown.


The Examples of Technologies of the CubeSats Satellite is Advanced multi-junction solar cells and carbon nanotube batteries.


The Apogee of the Satellite Orbit is 1500 km.


The URL of the James Webb Space Telescope Telescope is http://www.roe.ac.uk/ukatc/consortium/miri/index.html.


The Battery Capacity of the Spacecraft Bus (Avionics Module=AM) Satellite is 60 Ah.


The Brightness Temperature Channels of the GCOM-W1 Satellite is 89.0 GHz, 23.8 GHz.


The Speed Before Jettisoning of the Orion Spacecraft is 480 km/hr.


The Launch Date of the FormoSat-5 Satellite is July 17, 2017.


The Orbit Decay of the LAGEOS Satellite is Won't decay.


The Development Period of the Argo Float Oceanographic Instrument is 1990-1997.


The Observation of the New Horizons Spacecraft is How the volcanic gases from Io are ionized, trapped and energized by Jupiter's magnetic field, then ultimately ejected from the system.


The Not specified of the HTSSE-II Sensor is Not specified.


The Accuracy of the MEMS Rate Sensor Sensor is High.


The Number of Tests of the SuperDraco Engines Spacecraft Component is Hundreds.


The Mass of the Landmapper-BC CubeSat is 11 kg.


The Rotation Period of the Zeta Puppis Star is 1.78 days.


The Orbit Inclination of the CBERS-4 Satellite is 98.55º.


The Purpose of the SPOT-4 Satellite is Environmental studies, crop monitoring and management, environmental forecasting.


The Type of the Magnetorquers Attitude Control Device is Two cylindrical coils with ferrite cores, one flat square with no core.


The Instrument of the Tandem-L Satellite is L-band Synthetic Aperture Radar (L-SAR).


The A/D Conversion of the VEU Video Electronic Unit is 12-bit.


The Field of View of the INTEGRAL Satellite is Large.


The EMC Testing Configuration of the MPO Orbiter Spacecraft is Mercury orbiting mode.


The Spatial Resolution of the Stripmap Imaging Mode is 10 m.


The Download Transmission Rate of the DubaiSat-2 Satellite is 160 Mbit/s.


The Components of the Spacecraft Bus Satellite is Star tracker, GPS receiver, IMU, fine sun sensor, magnetometer, reaction wheels, EPS, batteries, radio, antenna.


The Communications Link of the James Webb Space Telescope Space Telescope is Malindi ground station in Kenya.


The Inclination of the IDEA-OSG 1 Microsatellite is 98º.


The Resolution of the A/D converter Data Converter is 16 MHz.


The Design Goals Met of the SHIMMER Spectroscopy Instrument is Yes.


The Final Flyby Date of the Parker Solar Probe Satellite is November 2024.


The Actuators of the Slew Mode Satellite Mode is Reaction wheels as the primary actuators, and torque rods.


The Post-Project Careers of the SAPPHIRE Satellite is Three are involved in strong system-based research and management in industrial or government laboratories.


The Purpose of the UN Disaster Charter Agreement is Gives front-of-the-line access to information needed to respond to major disasters.


The Operation of the MERIS Sensor is Only out of eclipse and when the sun's zenith angle at the subsatellite point is less than 80º.


The Spectral Range of the Current GOES imager Sensor is 7.24-7.44.


The Imaging Frequency Band of the TanDEM-X Satellite is X.


The Unknown of the AIDA Mission is Unknown.


The Function of the CAL LR Calibration Launch Restraint is Provide an alternate load path to support the mass of the calibration targets without over loading the Despin Assembly.


The Mirror Shell Material of the ART-XC Instrument Telescope is Nickel-cobalt alloy with iridium coating.


The Manufacturer of the IREM Radiation Environment Monitor is ESA.


The Partnership Date of the SpaceChain Company is Sept. 28.


The Student Collaboration Goal of the IMAP Mission is Provides scientific involvement in studying the origin of EPs in the innermost magnetosphere.


The Configurations of the SATSIM Simulation System is GAS, SATLAB.


The Spatial Resolution of the HPT Sensor is High.


The URL of the Hayabusa2 Asteroid Explorer is http://global.jaxa.jp/activity/pr/brochure/files/sat33.pdf.


The Soil Moisture Accuracy of the SMAP Satellite is 0.04 cm3/cm3.


The Agreement Date of the BRITE-PL Satellite Project is May 2010.


The LTDN of the Optsat-3000 Satellite is 10:30 hours.


The 3D Visualization of the Exploded Star Celestial Object is Built with Help from NASA's Great Observatories.


The Distance from the Sun of the New Horizons Spacecraft is 50 AU.


The Mass of the J1820 Black Hole is Lower than supermassive black holes.


The Material of the Habitat Structure is Regolith mixed with water and bovine serum albumin.


The Power Consumption of the FREND Instrument is 14 W.


The Electric Power of the FLP Satellite is 270 W.


The Output Voltage of the PPM Power Processing Module is 28 V.


The Agency of the Galileo Satellite Navigation System is ESA.


The Swath of the WV60 imager Imaging System is 17.9 km.


The Launch Date of the Kaber Spacecraft is Unknown.


The Output Power of the PPM Power Processing Module is 300 W.


The Deformation Mode of the Tandem-L Satellite is Repeat-pass interferometry.


The Swath Width of the TrueColour Imager Optical Imager is 120 km.


The Field-of-View of the ISEM Instrument is 1°.


The Field of View (Individual) of the HRV Imager is 4.13°.


The ADC type of the PHA Detector is Wilkinson ADC.


The Eclipse Encounters of the Hinode Satellite is Total: 3.


The Size of the QBSout-1S FemtoSat is 2.5U.


The RAM of the STRV-2 DHS Data Handling System is 512 k.


The Observation Method of the Global Positioning System Satellite System is Radio occultation.


The Spectral Channels of the HSI Hyperspectral Imaging System is Variable.


The Orbital Period of the Juno Spacecraft is 43 days.


The Instrument Control Document of the Advanced Data Collection System Data Collection System is Advanced Data Collection System Instrument Control Document, (A-DCS ICD).


The Communication of the Dove-2 Satellite is TT&C over UHF radio.


The Landing Accuracy of the Chang'e-3 lander Lander is Better than 0.6 km.


The Launch Date of the MoonLIGHT Satellite is 2024.


The Download Marking Behavior of the Data Download System Satellite System is All downloaded files are marked as downloaded after the completion of the download.


The Solar Elongation Range of the NEOSSat Satellite is 45º to 55º.


The GNC 2011 Conference Date of the SEOSat/Ingenio Satellite is June 5-10, 2011.


The Embankment Height of the Ataturk Dam Dam is 184 m.


The Transmit Frequency (MHz) of the Imager data Data Receiver is 1677.0.


The Flare List Events with Emission above 300 keV of the RHESSI Satellite is 35.


The Original Orbit Parameters of the ARTEMIS Spacecraft is Perigee: 592 km, Apogee: 17,518 km, Inclination: 3º.


The Atmospheric Species of the UVS Instrument is K, Na, Al, Si, Ca, Li, OH, H2O.


The Altitude of the ELaNa-4 CubeSats Satellite is 500 km.


The Energy Range of the ECT Suite Instrument Suite is 1 eV to 10's of MeV.


The Solar Panels Configuration of the LF spacecraft Spacecraft is Shown in Figure 2(a).


The Kick-off Meeting Date of the SMILE Satellite is Sept. 3-4, 2015.


The Time Uncertainty of the Deep Space Atomic Clock Atomic Clock is One nanosecond.


The Partners of the ExoMars Program is ESA and Roscosmos.


The Launch Date of the CartoSat-2D Satellite is February 15, 2017.


The Resolution of the Scatterometer Antenna Antenna is 25 km.


The Deployment Date of the Flock 1a Nanosatellites is February 2014.


The Launch Date of the EMIT Satellite is Unknown.


The Data Sharing of the ISS LIS Lightning Imaging Sensor is National forecast offices, NOAA/AWA.


The Objectives of the S 331 Satellite is Measurement of the three components of the DC and ULF magnetic field.


The Planned Docking Date of the Nauka Laboratory Module is 23 July 2021.


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


The Length Increase of the BEAM Expandable Habitat is Nearly doubled.


The Failure Rate of the CubeSats Satellite is 40%.


The Science Operations Support Conference Date of the IBEX Satellite is March 3-10, 2012.


The Installation Date of the UrtheCast Cameras Camera is Jan. 28, 2014.


The Unknown of the FEE Power Convertors Power Convertors is Unknown.


The Launch Vehicle of the OneWeb Satellite Communications Company is PSLV (Polar Satellite Launch Vehicle) and GSLV-MkIII (Geosynchronous Satellite Launch Vehicle).


The Observation Date of the XMM Newton telescope Telescope is June 29, 2021.


The External Parts of the WISA Woodsat Satellite is Corner aluminum rails, metal selfie stick.


The Data User's Manual Edition of the IRS-P6 Satellite is Oct. 1, 2003.


The Polarization of the C-RADAR Phased Array Antenna System is V and H.


The Dimensions of the Carbon Dioxide Ice Patch Surface Feature is 80 m x 60 m.


The Design Life of the Jason-2 Satellite is 3 years.


The Mission Number of the CubeSat Satellite is 17.


The Type of the OSIRIS Instrument is Atmospheric chemistry.


The Dynamic Range of the SXI Spacecraft is 1000.


The Development of the TRISHNA Satellite is Joint by the French Space Agency (CNES) and the Indian Space Research Organization (ISRO).


The L1-SAIF Signal Augmentation Performance Presentation of the QZSS Satellite System is ION NTM (National Technical Meeting) 2007, San Diego, CA, USA, January 22-24, 2007.


The Goal of the Small Photon Entangling Quantum System (SPEQS) Quantum Light Source is Enable a QKD link between satellites, or between a satellite and an optical ground station.


The Mass of the Space Comb Spectroscopy Setup is Below 10 kg.


The Orbit Lagging Time of the Observatories Satellite is About 1 month later.


The Type of the Kurushima Kaikyo Bridge Bridge is Continuous suspension.


The Deep Space Maneuver Date of the OSIRIS-REx Spacecraft is 3 July 2018.


The Development Initiation Date of the IRIS Imager Camera is April 2002.


The Data Distribution Start Date of the GOCI Geostationary Ocean Color Imager is April 20, 2011.


The Launch Date of the GRACE-FO Satellite is Early 2018.


The Pixel Size at Nadir of the CIPS Instrument is ~2 km.


The Spectral Resolution of the ICON FUV instrument Spectrometer is High enough to reject unwanted contamination by the bright optically thick 130.4 nm O line.


The SNR Saturation of the SCATSat-1 Satellite is 50%.


The Thruster of the Clementine Spacecraft is 489 N.


The Data rate of the Spectrometer Spectrometer is 1.5 Mbit/s (average), 1.5 Mbit/s (max).


The Presentation Date of the Small Satellites Satellite is Sept. 29 to Oct. 3, 2008.


The Update Date of the LROC Robotic Spacecraft is Sept. 25, 2013.


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


The Downlink Subsystem Interface of the Frame Grabber Data Interface is Ethernet.


The Coating of the FPI Mirrors Component is Silver coating (thickness 50 nm).


The URL of the Aleph-1 Constellation Satellite Constellation is https://satellogic.com/technology/constellation/.


The Provider of Earth observation data of the Copernicus Environmental Monitoring Satellites is Yes.


The Status Update Date of the James Webb Space Telescope Space Telescope is May 19, 2009.


The Function of the Hyperspectral Imaging Remote Sensing Technology is Enables the observation and monitoring of surface measurements.


The Image Capture Date of the CaSSIS Imaging System is 31 May 2018.


The Installation Location of the REM Radiation Environment Monitor is Externally on the fore panel.


The Design Philosophy of the SMEX Satellite Program is Emphasis on design simplicity, functional independence at subsystem level, and flexibility to accommodate growth.


The Type of the T2L2 Time Transfer Device is Laser Link.


The Technology Demonstrations of the BeaverCube Satellite is Use of low-cost commercial cameras to obtain measurements and operation of Tiled Ionic Liquid Electrospray (TILE) propulsion technology.


The Components of the Ground Station Ground Segment is Receiving antenna, antenna rotating and control system, low noise amplifier, receiver, ground station control software.


The Deployment Methods of the Argo Floats Oceanographic Instrument is Volunteer Observing Ships (VOS), aircraft, naval ships and research vessels.


The Orbit Altitude of the ResourceSat-1 Satellite is 817 km.


The Manufacturer of the OBI Component is EADS Astrium.


The Orbit (Local Sun Time) of the Spacecraft Satellite is 12:00 ± 15 min.


The Orbit of the JPSS Joint Polar Satellite System is Afternoon (13:30 hours).


The | of the Michele Piana Author is Michele Piana.


The Polarization of the Atmospheric-sounding instrument Spectrometer is Lower than 0.1% in both nadir and glint modes.


The Operational Control of the MEV-1 Satellite is Full 6-DOF (Degree of Freedom).


The Flight Status Presentation Date of the IKAROS Solar Sail Demonstrator is Sept. 27-Oct. 1, 2010.


The Launch Mass of the Falcon-9 Rocket Rocket is 13,620 kg.


The Manufacturer of the SOAR Satellite is GomSpace.


The URL of the ARTEMIS satellite Satellite is http://telecom.esa.int/telecom/www/object/index.cfm?fobjectid=31816.


The Observation Frequency of the ALOS-2 Satellite is Four times a year.


The Image Type of the ALOS-3 Satellite is Pan-sharpened images with simultaneous acquisition of panchromatic images and four-band multi-spectral images.


The Propulsion System of the Psyche Spacecraft is Solar Electric.


The Target Markets of the Satellite for 5G Satellite is Transport sector (maritime, aviation and land), public safety, and media and broadcasting.


The Data Allocation of the Remote Sensing Instruments Instruments is Insufficient to downlink the full raw data.


The Cross-Track Tilt of the Geoton-1 Imaging Instrument is ± 30º.


The Canister Size of the IAE Experiment Satellite Component is 2.04 m x 1.08 m x 0.5 m.


The Mission Proposal Year of the Euclid Space Telescope is 2007.


The Science Focus of the IMPACT Instrument is Magnetic connections to the sun, topology of interplanetary CME-related interplanetary disturbances, and the energetic particles.


The Detector Focus of the SHS System Interferometer is Nearly focused.


The Spectral Resolution of the Miniature High-Resolution Imaging Spectrometer Imaging Spectrometer is 0.1 nm.


The Travel Distance of the Yutu 2 Lunar Rover is 590 meters.


The Acquisition Planning follow-up of the CSK GS Ground Segment is Provide the S-IM with the planning of its acquisition requests.


The Communication System of the TRMM Satellite is Telemetry, Tracking and Control (TT&C) transponders.


The Acquisition Date of the OHB AG Company is June 28, 2011.


The Science Data Collection Start Date of the CloudSat Satellite is June 2, 2006.


The Material of the Tether Satellite Component is Spectra woven around yarn.


The Mission Duration of the TIMED Satellite is Ongoing.


The Image Capture Frequency of the Elektro-L Satellite is Every 15-30 minutes.


The Relative Positioning Accuracy of the PRISMA Satellite is Sub-centimeter level.


The URL of the Galileo Satellite System is http://m.esa.int/Our_Activities/Navigation/Europe_s_next_Galileo_satellites_in_place_atop_Ariane_5.


The Solar Array Type of the TacSat-2 Satellite is Thin-film.


The Transmitting Power of the Transmitter Device is Use of power monitor.


The Function of the Galileo App Mobile Application is Overlaid Satellites in Real Time.


The Launch Date of the SpaceX CRS-13 Mission is December 15, 2017.


The Orbit Inclination of the HY-2C Satellite is 66º.


The Data Rate of the IPS Pointing System is 16 Mbit/s.


The Number of Panels of the SAR Antenna Antenna is 8.


The Ground Resolution of the LISS-IIM Instrument is 32 m x 37 m.


The Design Requirement 1 of the OCO-3 PMA Pointing Mirror Assembly is Allow quick movement through a large range of angles.


The Yaw Flip Frequency of the Spacecraft Satellite is Twice during the one-year mission.


The Polarization of the VDES Antenna Antenna is Circular.


The Remarks/Sensors of the OrbView-1 Satellite is OTD.


The Manufacturer of the MEOLUT Next Local User Terminal is Thales Alenia Space.


The Presentation Date of the SLS-Orion Missions Space Missions is Oct.12-16, 2015.


The Band of the RF Communications Transmitter is Ku-band and S-band.


The URL of the Chandra Satellite is https://www.nature.com/articles/s41467-018-06558-7.pdf.


The Size of the CHEFSat-2 CubeSat is 3U.


The Precision of the Ozone Measurement Instrument Atmospheric Measurement Device is 3 DU+0.5% total ozone or better.


The Safety Criterion of the EO-1 Satellite is The six-second tolerance.


The Model of the Laser Rangefinder Device is Jenoptik DLEM-SR.


The Purpose of the CDE Sensor is Measure the temporal variability of meteoric material.


The Size of the ExoCube Satellite is 3U CubeSat.


The Mission Duration of the SeaWiFS Satellite is Thirteen Years.


The Data Communications Transceiver Frequency of the OSSI-1 Satellite is 435 MHz.


The Number of Satellites per Orbital Plane of the T1TL Prototype Constellation Satellite Constellation is 21.


The Magnitude Random Error of the Magnetic Field In-Situ Sensor is < 0.3 nT.


The Observation Demonstration of the FORTE Satellite is Multisatellite observations of oceanic lightning.


The Internet Demonstration Time Frame of the UoSAT-12 Satellite is April-June 2000.


The Data Set Release Date of the GEOSAT Satellite is June 1997.


The TT&C Downlink of the Spacecraft bus Satellite is 30 kbit/s.


The Range of the Magnetometer Sensor is ±60 µTesla.


The FPGA of the SHU Science Handling Unit is Altera EP3SL70F780I3 (Stratix-III).


The Central Hole Diameter of the XMM Service Module Satellite Module is 2.10 m.


The Daily Visibility of the Galileo Satellites 13 and 14 Satellites is Three to nine hours.


The Ultimate Goal of the BRITE Constellation Satellite is Provide photometric data on all 286 stars brighter than visual magnitude +3.5.


The Daughterships Shape of the OPAL Satellite is Similar to a hockey puck.


The Bands of the SEM Particle Detector is 2 XRS bands, 5 EUV bands, 7 proton bands, 6 alpha particle bands, 3 electron bands.


The Predecessor Organization of the DLR German Aerospace Center is DFVLR.


The Tracking Rates of the Astro-APS Star Tracker is 10 Hz.


The Upper and Lower End Masses Configuration of the ATEx Tether Experiment is In orbit as one object connected by a 22 m tether.


The Member of the Gary Egbert Individual is True.


The Operating Center Frequencies of the Satellite Satellite is 13.575 GHz (Ku-band), and 3.2 GHz (S-band).


The Mass of the Miniature High-Resolution Imaging Spectrometer Imaging Spectrometer is 5.4 kg.


The Data Processing of the GPSP Instrument is No changes.


The Telescope Aperture of the NEOSSat Microsatellite is 15 cm.


The Sun Angle of the OLCI Spectral Imaging Instrument is 12.2°.


The Data Encryption Capability of the NPOESS Program is Capable of encrypting selected mission data in all satellite links, excluding the S&RSAT and ADCS real-time downlinks.