The CsI Shield Thickness of the GRS Gamma-Ray Spectrometer is Approximately 3 cm.


The URL of the RADARSAT Constellation Mission Satellite Constellation is https://www.youtube.com.


The Ground Range x Product Length of the Spotlight Imaging Mode is 10 x 10 km.


The Antennas of the ASCAT Scatterometer is 6.


The Bistatic X-band Experiment Result of the TerraSAR-X Satellite is Success.


The Mission Objective of the Lucy Satellite is Explore the diversity of Trojan asteroids and their satellites.


The Thickness of the Aperture Function Image Processing is a.


The User Information Presentation of the Himawari-8/9 Satellite is May 13, 2013.


The Launch Date of the GPM Satellite is 27 February 2014.


The Launch Date of the Gravity Probe A Satellite is June 18, 1976.


The Selection Criteria of the Hexapod Mounting System is Lifetime and lubrication tests.


The Attitude Control of the FY-3 series spacecraft Satellite is Three-axis stabilization (bias momentum control).


The F-number of the Instrument Spectrometer is F73.7.


The Components of the GARI-1 Instrument is Two cerium-doped gadolinium aluminum gallium garnet (GAGG (Gd3(Al,Ga)5O12 :Ce)) scintillation detectors.


The Measurement Frequency of the TROPICS CubeSat Satellite is Higher than previous satellites.


The URL of the CNES Satellite is http://www.ies.univ-montp2.fr/robusta/satellite/IMG/pdf/DD_GN_2010.02.16__ISU2010.pdf.


The Average Power Level of the EDFA Amplifier is 0.5 W.


The Phase Transition Temperature of the Gallium Calibration Source Radiometer Calibration is 29.76°C.


The Wavelength Shift of the FG (Filtergraph) Instrument is Up to 26 km/s.


The URL of the James Webb Space Telescope Space Telescope is http://www.sciencecodex.com/james_webb_space_telescope_begins_to_take_shape_at_goddard.


The Components of the Instrument Optical Subsystems is Two sets of electronics, two cryogenic coolers for the detectors.


The Spectral Bands of the EarthDaily Constellation Satellite Constellation is Over 21.


The Thruster Location of the CanX-4&5 Satellite is One face only.


The Attitude Maneuver of the Hayabusa-2 Spacecraft is Around the Z-axis.


The Power Generation of the SPOT satellite constellation Satellite Constellation is 1,000 W.


The Future Satellite of the TIM and SIM instruments Instruments is NPOESS series spacecraft.


The Total Height of the ESM Module is 4.0 m.


The Event of the MATS Satellite is SPIE Astronomical Telescopes + Instrumentation, 2018, Austin, Texas, United States.


The Transfer Time from CSAR to TR of the LD Output Laser Diode is About 1 min.


The Data Collection Period of the OMI Ozone Monitoring Instrument is More than 15 years.


The Volume of the DPU Digital Processing Unit is 230 x 300 x 250 mm.


The Imaging Mode of the TanDEM-X Satellite is Left-looking.


The Revisit Time of the SuperView-1 01 and Superview-1 02 Satellite is 4 days.


The Orbit Sunlight of the ALMASat-1 Satellite is About 75%.


The Depth of Field of the CMOS Camera Camera is 120 cm.


The Designed Depth of the "the mole" Heat Probe is 5 meters underground.


The Spatial Resolution of the SMMR Microwave Radiometer is Ranged from 22 km at 37 GHz to 100 km at 6.6 GHz.


The Launch Date of the HREP Payload is Sept. 10, 2009.


The Detection Type of the Spaceborne Detection System Satellite System is Localized carbon dioxide sources.


The Purpose of the GRAIL Probes Spacecraft is Learn about the moon's internal structure and composition.


The Network Support and Space Operations Services of the GISTDA and NSPO Organizations is Provided to each other.


The Image Resolution of the NAVCAM Camera is 84.6 cm/pixel.


The Mounting of the TWINS Instrument is Rotating actuator platform.


The Magnetic Field Strength of the 1E1547.0-5408 Magnetar is 1014G -1015G.


The Availability of the Visualization Product is Worldwide to planetariums and other centers of informal learning.


The Presentation Date of the Small Satellites Satellite is Oct. 4-8, 2004.


The Flight Demonstration Goal of the DRACO Demonstration Rocket is Fiscal year 2026.


The Scalability of the Open5GCore Rel. 4 5G Core Network is Raspberry PI to a complete rack of servers.


The Provider of the FIPEX Sensor is Institute of Aerospace Engineering of TU Dresden, Germany.


The Orbital Period of the Planet Orbiting AU Microscopii Exoplanet is Just over a week.


The Performance of the Cold Gas Pressurization System Satellite Component is Satisfactory.


The Function of the PCM Module Module is Dissipates the thermal power emitted by the lasers during operation, forms the mechanical structure to which the receiver module is attached.


The Launch Date of the Flying Laptop Satellite is 14 Jul 2017.


The Protocol of the Communication System Satellite System is AX25 radio-amateur protocol.


The Conference Date of the LARES Satellite is Sept. 23-25, 2003.


The Launch Mass of the Spacecraft Satellite is 790±30kg.


The NEΔT (K) of the ICI-2 Radiometer is 0.7.


The Orbital Period of the Secondary Payloads Unknown is 103 minutes.


The Swath Width of the CCD Camera Optical Device is 700 km.


The FOV Resolution of the HSRS Sensor is 2.22 arcmin.


The Earth Rotation Effect of the Band-64 Satellite Instrument is Limit to about 0.1 pixels.


The Operation Start Date of the Cheops Satellite is Beginning of April.


The Structure Type of the WFS&C Wavefront Sensing and Control Subsystem is Semi-rigid.


The Target of the Periselene-1 Spacecraft is Sun-Earth WSB (Weak Stability Boundary).


The Material of the Enclosure Optical Unit Enclosure is Black anodized aluminum.


The Semimajor Axis of the SMART-1 Satellite is 3416.853 km.


The Modes of the BlackJack GPS Instrument is C/A, P, or codeless.


The End of Operations Date of the GEOS-3 Satellite is July 1979.


The Spatial Resolution of the HRV Imager is 10 m for PAN, 20 m for MS.


The Type of the Satellite Orbit Orbit is Sun-synchronous near circular dawn-dusk.


The End of Life Date of the HySIS Satellite is 5 years.


The Mission of the CSSWE Satellite is Measure outer belt electrons and SEP protons.


The Photodiode Rotation of the Sun Sensor Suites Sensor is 90º.


The Mission Manager of the RADARSAT Constellation Mission Satellite Constellation is Daniel De Lisle.


The Payload of the SciSat/ACE spacecraft Satellite is Instruments provide information about more than 30 different molecular species.


The Data Rate of the GSN Ground Station Network is Up to 622 Mbit/s.


The Imaging Frequency Band of the HJ-1C Satellite is S.


The Energy Range for C of the LEICA Particle Detector is 0.44 - 11.4 7.2 - 160 14 - 210 34 - 120 MeV/n.


The Interface of the Star Sensor Sensor is MIL-STD-1553 bus.


The Energy Resolution of the GRS Gamma-Ray Spectrometer is ≤ 9% at 662 keV.


The Purpose of the He-repressurization system Propulsion Subsystem is Raise the pressure in the main tank to an adequate pressure to complete the GRAIL mission.


The Number of Interferometric Pairs of the ERS Tandem Mission Satellite Mission is Five or six for Europe and North America.


The Country of the Aalto-1 Nanosatellite is Finland.


The Distance Range of the MCAM-3 Camera is Approximately 984 km – 6194 km.


The Operations Duration of the MOPITT Satellite Instrument is 2.5 Years.


The Attitude Pointing Requirements of the CanX-4&5 Satellite is Placed on the attitude determination and control system for accurate thruster pointing.


The Inclination of the Satellite Constellation Satellite is 98.2°.


The Experimental Mode Spatial Resolution of the TSX-SAR Satellite is 1m.


The Launch Date of the Chandra X-Ray Observatory Satellite is 22 November 2021.


The Development Status Presentation of the James Webb Space Telescope Space Telescope is Jon Arenberg, "JWST Development Status," 213th AAS (American Astronomical Society) Meeting, Long Beach, CA, USA, Jan. 4-8, 2009.


The Accuracy of the Magnetometer Sensor is 30 nT (3σ).


The Spatial Resolution of the Instrument Hyperspectral Imager is 8 m.


The Orbit of the Himawari-8 Satellite is Geostationary orbit.


The Orbit Altitude of the Rocket 3.3 Rocket is 500 km.


The Overlapping Swath of the WFI Camera is 830 km.


The Telescope Type of the Swift Satellite is High-resolution X-ray.


The Development Start Year of the MiRaTA Satellite is 2012.


The Number of Channels of the Spectral Channels Satellite Instrument is 5.


The Presentation Date of the MICROSCOPE Spacecraft is Oct.12-16, 2015.


The Number of Satellites in Orbit of the OneWeb Company is 74.


The Survey Sample of the ARIEL Satellite is About 1000 extrasolar planets.


The Distance to Seismically Active Region of the InSight lander Seismic Instrument is More than 1,000 kilometers.


The Launch Date of the Beijing-3B Satellite is 24 August 2022.


The Test Conduct of the Integrated Firing Test Test is ΔV thruster and RCS thrusters.


The Number of Wavelength Positions of the FG (Filtergraph) Instrument is Six.


The Objective of the SWOOPS Instrument is Observation of the solar-wind flow at middle-to-high solar latitudes for the construction of a representative model of the heliosphere.


The Presentation Date of the SERB Nanosatellite is Sept. 26-30, 2016.


The Roll Maneuver Frequency of the EarthCARE satellite Satellite is Once a month.


The Data Gathered of the Global Navigation Satellite System - Radio Occultation (GNSS-RO) Instrument is Temperature and humidity.


The Microchannel Plate Area of the FlaPS Instrument Package is 25 cm2.


The Data Availability of the Landsat 7 ETM+ SLC-off and Landsat 5 TM Satellites is All data September 2008.


The Electrical Isolation Method of the Hinge Pin Mechanical Component is Shrink tube.


The Access of the Antenna Dish Satellite Component is Cannot be readily accessed from the front due to the mesh.


The Core Processors of the Hayabusa-1 SRC Instrument Module is Discontinued.


The User Data Link Speed of the GEO LCT Laser Communication Terminal is 1.8 Gbit/s.


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


The Probe Types of the ISL Instrument Langmuir Probe is One cylindrical, one spherical with a 6 cm diameter segmented probe.


The Observation Directions of the MSU-50 Camera is ±17º, 0º (nadir).


The Orbit MLST of the Envisat Satellite is 22:00 ANX ± 5 minutes.


The Merger Date of the Planet Company is 7 July 2021.


The Launch Time of the Falcon 9 Rocket is 1:19 a.m. Eastern (06:19 UTC).


The Observation Period of the NASA Satellite Sensors Sensors is May 29 to June 6.


The Swath Width of the SIR-C Phased Array is 15 to 65 km for calibrated images.


The Operation Frequency of the SONATE CubeSat Satellite is Daily.


The URL of the INTEGRAL Satellite is http://iopscience.iop.org/article/10.3847/2041-8205/820/2/L36/pdf.


The Mass (kg) of the ALOS-2 Satellite is 2120.


The In-flight Performance of the Gas Scintillation Proportional Counter Instrument is Unknown.


The Economic Impact of the Silkworm Insect is More than 30 billion dollars income for silkworm breeders, commercial as well as industry.


The Altitude Range of the Detector Instrument is Limited to 30 km.


The Spectral Response of the VACNTs Radiometer Absorber is Extremely flat over a wide wavelength range.


The Location of the FAI Camera is Novaya Zemlya, Russia.


The Splitting of the Baseband Signal Signal Type is Three ways.


The Spectral Bands of the MTG-S Spacecraft Satellite is 16.


The Members of the SPEXone Steering Committee Committee is Two Airbus DS NL and two SRON members including the Principle Investigator.


The Data Format of the HSM High-Speed Multiplexer is Virtual Channel Data Units.


The Inclination of the Vstar Gravity-field Measurement Microsatellite is 90º.


The Attachment of the ENT EVR Nozzle Tool is Attached to a spring-loaded pressurized hose.


The Memory Space of the NanoSat MO Framework Software Framework is Dedicated memory space allocated specifically for them.


The Smaller Black Hole Mass of the OJ 287 galaxy Galaxy is About 150 million times the mass of our Sun.


The Detector Elements Downlinked of the AHI Scanner is 7,856.


The Conference Presentation of the CSG System Synthetic Aperture Radar is EUSAR 2016, 11th European Conference on Synthetic Aperture Radar, Hamburg, Germany, June 6-9, 2016.


The Size of the BioSentinel Spacecraft is 6U.


The Importance of the Cluster Satellite is Study turbulence and its role in fundamental processes.


The Image Assessment System (IAS) of the Landsat-7 Satellite is Provides users with ancillary information needed to generate useful, radiometrically calibrated and geometrically corrected ETM+ digital imagery.


The Structure Material of the Bus Satellite Component is Graphite.


The Attitude Control Accuracy of the GFO Satellite is 0.25º (3σ).


The Function of the SES Instrument is Validate the optical and thermal performance of the instrument.


The Spatial Resolution of the SGR-ReSI Instrument is Lower.


The Mission of the PhiSat-1 Satellite is Monitor polar ice and soil moisture, test intersatellite communication systems.


The Number of Subscribers of the SecureWatch Service is 20.


The Altitude of the Shakuntala Satellite is 480 km.


The Frequency Band of the RF Communications Communication System is X-band for the payload data downlink.


The Date of the Arabian Night Lights Image is 17 May 2021.


The Horizontal Resolution of the JPL Microwave Radiometer Radiometer is 3.1 km.


The Altitude of the Computer System Payload is 120,000 feet.


The Spatial Resolution of the Miniature High-Resolution Imaging Spectrometer Imaging Spectrometer is Under 50 m.


The Number of Objects of the Gaia Catalogue of Nearby Stars Stellar Census is 331,312.


The Estimated Time Before Blackout of the Spacecraft Satellite is Just three hours.


The Radio Signals of the Hitomi Satellite is 3/26 23:49~23:52 (for 3 min) @USC,23:48~23:51(for 3 min) @ KTU.


The Gaia's Position Accuracy of the GBOT Ground Based Orbit Tracking is Good to 20 m arcsec.


The Primer Version of the James Webb Space Telescope Space Telescope is 1.0.


The Capacity Establishment Deadline of the GMES Initiative is 2008.


The Volume of the Gas Cartridge Component is 20 ml.


The Spectral Bands of the CHRIS Imaging Spectrometer is Up to 63.


The Stage Type of the Soyuz Rocket is Payload shroud.


The Extension of the Gaseous Atmosphere Atmospheric Feature is Several hundred miles from the neutron star.


The Frequency Band of the Telemetry, Tracking and Command System Telemetry, Tracking and Command System  is S-band.


The Size of the Telescope Optical Instrument is 17 cm x 12 cm x 12 cm.


The Measurement of the MHS Microwave Humidity Sounder is Microwave radiation emitted from Earth’s surface.


The Data Transfer Capacity of the Satellite Communication is 100 MByte/day.


The Orbit Reach Date of the Cheollian 2B Satellite is March 6.


The Design of the Telescope Optical Instrument is Off-axis unobscured TMA without intermediate focus locations.


The Orbit Maintenance System of the GOCE Satellite is Ion Propulsion Unit.


The URL of the ANTRIX Corporation Limited Corporation is http://www.antrix.gov.in/irsonline/eosatellites.html.


The Downlink Data Rate of the Spacecraft Satellite is From 9.6 kbit/s to 8.0 Mbit/s.


The Diameter of the Haydn crater Crater is 251 km.


The RF Communications of the Satellite Satellite is S-band and X-band.


The Geolocation accuracy of the ALOS/PRISM Satellite is 6.1 m (rms).


The Project Partners of the DSP Satellite Project is ESA (European Space Agency), CNSA (China National Space Administration).


The Material of the Faraday Cup Sensor is Refractory metals and sapphire crystal insulators.


The Number of Targets of the IXPE Satellite is 6.


The Pixel Angular View of the EXI instrument Imaging Instrument is 23 arcsec per pixel.


The CubeSat Deployments of the NanoRacks Company is 185th from the Space Station.


The Sensitivity of the Channel 2 Sensor is 0.4 K/pixel.


The Pointing Accuracy of the Satellite Satellite is Better than 200 m.


The Number of Scientists or Institutional Teams of the PUTC Program is More than 60.


The Instruments of the JERS-1 Satellite is L-band SAR, OPS, JERS-1 Comms.


The Rescaling Method of the Landsat images Images is Bilinear interpolation.


The Deputy Director of the Roman Space Mission is Nancy Levenson.


The EEPROM of the OBC Onboard Data Handling is 524 kB.


The Max Power of the PM Satellite Component is 24 kW.


The Image Acquisition Date of the VIIRS Instrument is June 3 and 5, 2022.


The Magnetometers of the S/C Satellite is Two 3-axis magnetometers.


The Mission Duration of the Iris Radio Communication Device is Nominal 90 days.


The Objective of the XI-IV Picosatellite is Demonstrate and validate a picosatellite bus system and the space use of commercial-of-the-shelf (COTS) parts.


The Launch Date of the SpaceX CRS-17 Mission is 04 May 2019.


The Number of Planets Discovered of the UBC student Astronomer is 17.


The Size of the HIRES Instrument is 17 cm x 18 cm x 36.5 cm.


The Ground Surface Side Length of the LSI-1 Camera is 342 km.


The Tandem Flight Duration of the Sentinel-3B Satellite is 4-5 months.


The Panel Quantity of the SAR Antenna Antenna is 5.


The Spatial Resolution of the SAM-II Instrument is 1 km (vertical).


The Number of Commands of the Admiral Paul F. Zukunft Coast Guard Commandant is 8.


The Management Contractor of the IMAP Mission is SwRI (Southwest Research Institute).


The Total Small Satellite Deployments by NanoRacks of the CubeSats Satellite is 217.


The Orbital Life Goal of the Nanosatellite Satellite is 25 years.


The No of bands/channels of the IRAS Infrared Atmospheric Sounder is 26.


The Distance from Earth of the OSIRIS-REx Spacecraft is More than 200 million miles (321 million km).


The Thermal Vacuum Test Duration of the MMO Spacecraft is Three weeks.


The Article Date of the Nav Canada Air Navigation Service Provider is March 8, 2010.


The Purpose of the Oxygen Generator Assembly (OGA) Pump Assembly Hardware is Critical spare to a support oxygen generation capability in support of the crew on board the International Space Station.


The Swath of the SLSTR Spectral Imaging Instrument is 1420 km.


The Strategic Partnership of the Spire Company is ICEYE.


The Detection Type of the EPISEM Instrument is Detects penetrating beta/gamma radiation from energetic particles above a certain energy threshold.


The Data Rate of the MTG-S Spacecraft Satellite is Around 60 Mbit/s.


The Pointing Stability of the VT Telescope is High.


The Maximum Distance from the Sun of the Rosetta Spacecraft is Over 850 million km.


The Launch Date of the Hitomi Satellite is Unknown.


The Function of the ROLIS Camera is Down-looking imager that acquires images during the descent and doubles as a multispectral close-up camera after the landing.


The Incoming Energy Range of the INMS Ion and Neutral Mass Spectrometer is 0-50 eV.


The Purpose of the Copernicus Programme Earth Observation Program is Monitor and collect information across different parts of the Earth.


The Orbital Speed of the Cluster spacecraft Satellite is Up to 23,000 km/h.


The Mass of the Norton Satellite End-body is 10.8 kg.


The Spectral Bands of the WiFS camera Camera is 0.62 - 0.68 µm, 0.77 - 0.86 µm.


The Release Date of the Argos-3 Instrument is May 24, 2005.


The Intended Replacement of the TOPSAR SAR Mode is Conventional ScanSAR mode.


The Modulation Scheme of the RF Communications Communication System is FSK.


The Locations of the TT&C stations Ground Stations is Saint-Hubert and in Saskatoon, Saskatchewan.


The Data Source of the Chandra X-ray Observatory X-ray Observatory is Astronomers obtained this result using data from NASA's Chandra X-ray Observatory.


The Launch Date of the AlSat Nano CubeSat is September 2016.


The Communication of the LAGEOS Satellite is None.


The Purpose of the SVOM Satellite is Observe and characterize gamma-ray bursts.


The Purpose of the CFOSAT Satellite is Study ocean surface wind and wave conditions.


The Expected Duration of the Lunar Orbit Orbital Phase is Minimum of 6 months.


The Launcher of the MEPSI Satellite is MightySat II.1.


The Ground Network of the FormoSat-7 / COSMIC-2 mission Satellite Mission is USN ground stations for the first 2 years, and then service provision by NOAA's ground stations for the following 3~5 years.


The Mass of the PM Satellite Component is 14,800 kg.


The Size of the Cluster XDCPJ0044.0-2033 Galaxy Cluster is Over one and half million light years across.


The Bands of the HawkEye Ocean Color Instrument is 8-band multispectral.


The Contractor of the CAPSTONE Satellite is Advanced Space of Boulder, Colorado.


The Medium-sized Aperture Camera (MAC) of the RazakSAT Satellite is Unknown.


The Destination of the Sample Return Capsule Capsule is Earth.


The Execution Start Date of the CIBORG Program is Early 2017.


The Transmitter Power of the Spacecraft Repeater Communication Device is 8 W.


The Mission Name of the Radiation Belt Storm Probes Satellite is Radiation Belt Storm Probes.


The Position of the ADACS Attitude Determination and Control System is Front of the satellite.


The Interplanetary Vector Magnetic Field Measurement Range of the DSCOVR Satellite is 0 – 100 nT.


The Function of the Astronode S Integration Device is Allow remote monitoring and significant maintenance cost reduction.


The Observation Operation Completion of the MTSAT-2 Satellite is Around 2015.


The Publication Date of the Supercapacitors Energy Storage is 2009.


The Pointing Knowledge Stability of the Instrument Satellite Instrument is ±9.7 µradians over 2.5 seconds.


The Orbit Period of the SEOSat Satellite is 98 minutes.


The Principal Investigators of the SCIAMACHY Spectrometer is J. P. Burrows, H. van Dop.


The Wavelength of the Laser Instrument is 1556 nm.


The Launch Year of the Aeolus Satellite is 2018.


The Interstellar Dust Measurements of the Ulysses Spacecraft is October 20, 2015.


The Nadir image size (1000 km altitude) of the 16 mm camera Camera is 110 km x 120 km x 92.8 km.


The LVDS Link Speed of the IRIS Satellite is 50 Mbit/s.


The Shadow of the Debris Spacecraft Debris is One pixel.


The Function of the CSS Consumable Storage Subsystem is Provides potable water, oxygen and nitrogen to the CM.


The Agency of the Biomass Satellite is ESA.


The Wind Speed Range of the Numerical Weather Model Weather Model is 3 m/s to approximately 20 m/s.


The Size of the Vizcaíno Biosphere Reserve Biosphere Reserve is Largest protected area in Mexico.


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


The Launch Date of the NigeriaSat-2 Satellite is Unknown.


The Payloads of the ZACube-2 CubeSat is Medium resolution matrix imager and a number of communication subsystems.


The End of Life Date of the CAPSTONE Satellite is June 28, 2023.


The Black Hole Mass of the PG211+143 Galaxy is 40 million solar masses.


The Data Management Plan of the Small Explorer (SMEX) Satellite is Unknown.


The Target Reflectivity of the NEMO-HD Satellite is 30%.


The Telescope FOV of the Telescope Optical Instrument is 166 arcmin x 166 arcmin.


The Beamwidth of the Antenna Satellite Component is 1.1º.


The Number of Subapertures of the PAIS Imaging System is 4.


The Ground Instantaneous Field of View (GIFOV) of the Climate Observatory Satellite is 50 m.


The Size of the NEA Scout CubeSat is 6U.


The Funding Renewal Date of the CUTE Satellite is May 2019.


The Ground Station Communication of the IXPE Observatory Satellite is ASI-contributed Malindi ground station via S-band link.


The URL of the RADARSAT Constellation Mission Satellite Constellation is http://eofsac.org/sites/default/files/2018-02/McNairn%20Delisle%20RADARSAT%20Constellation_0.pdf.


The Type of the Attitude Subsystem Satellite Subsystem is Passive magnetic stabilization.


The AMOS Terminator Passes of the SpinSat Satellite is 3.


The Possible Mission Extension of the SELENE/Kaguya Satellite is Half a year.


The Mission of the Parallel Processing Unit (PPU) Computing Payload is Secondary.


The Efficiency of the Secondary Converter Converter is 70%.


The RF Communications of the Spacecraft Satellite is UHF.


The Measurement Frequency of the Dark Reference Calibration Device is Every 2–3 orbits.


The Launch Date of the SARAL/AltiKa Satellite is February 2013.


The Distance from Earth of the Kepler-438b Exoplanet is 475 light-years.


The Field of View of the Roman Satellite is Wide.


The Slit Length of the Spectrometer Spectrometer is 3 mm.


The Operation Duration of the KOMPSAT-2 Satellite is Until the mission end.


The Control Method of the Solar or drag sails Deorbiting Device is Constantly controlled relative to either the solar vector for steered sailing or the satellite velocity vector to maximize drag.


The Operating Altitude of the GRAIL Satellite is 23 km.


The Formation Flight Mission of the CanX-4/CanX-5 Satellite is Unknown.


The Arrival Date at Europe’s Spaceport of the BepiColombo Spacecraft is May 11, 2018.


The Purpose of the Storage Box Component is Store the inflatable tubes and the membrane.


The Announcement Date of the PROBA-V Satellite is 9 July 2020.


The Launch Mass of the IAE Experiment Satellite Component is 60 kg.


The Inclination of the Satellite Communication is 99.63º.


The Integrating Time of the GOCI Instrument Instrument is Up to 8 seconds.


The Material of the Baffles Instrument Component is SiC.


The Braking Burn Time of the Queqiao Communication Satellite is 13:32 UTC.


The Number of Photographs of the Metric Camera Camera is 1019.


The Mission End Date of the IBEX Spacecraft is Unknown.


The Aperture Diameter of the SOT Telescope is 50 cm.


The Orbit of the SMAP Satellite is Near-polar, sun synchronous.


The Number of User Terminals of the OneWeb Satellite Constellation is Unknown.


The Ground Segment Design Team of the EnMAP Satellite is M. Habermeyer, T. Storch, S. Eberle, C. Makasy, S. Maslin, A. de Miguel, K.-D. Missling , H. Mühle, R. Müller, S. Engelbrecht, J. Gredel, U. Heiden.


The Power Bus of the EPS Electric Power Subsystem is Unregulated 22 V - 36 V.


The Spectral Range of the HSC CCD Imaging Camera is 450 - 850 nm.


The URL of the SPOT 7 Satellite is http://www.astrium-geo.com/files/pmedia/edited/r18072_9_spot_6_technical_sheet.pdf.


The Purpose of the Military Payload Satellite Payload is Provision of military Satcom services over the whole visible Earth.


The Planned Launch of the Chang'e-5 Lunar Probe is 2020.


The Composition of the Dark Matter Cosmological Component is ~27%.


The Imaging Area Pixels of the CCD Image Sensor is 600 x 600.


The Microgravity Environment of the O/OREOS nanosatellite Satellite is Below 500 µg.


The Spatial Resolution of the MSI-0 and MSI-1 MSI Instruments is 32.5 m.


The Energetic-Particle Detector of the Juno Spacecraft is Instrument.


The Communication Status of the Robusta Satellite is No further communication has been received.


The Tracking Capabilities of the Phoenix receiver Navigation Device is Good.


The Rob Gutro Article Date of the JWST Telescope is March 20, 2014.


The Composition of the Dark Energy Cosmological Component is ~68%.


The Pixel Resolution of the SPIM1 Spectrometer is 14 bit.


The Mission Number of the Vega Launch Vehicle is 18.


The Frequency Band of the RF Communications Communication System is S-band for TT&C data.


The Detector Format of the Camera Imaging Device is 512 x 512 pixels.


The Discovery Year of the Blue Ring Nebula Nebula is 2004.


The Mission Purpose of the Euclid Satellite is Investigate dark matter and dark energy.


The Latency of the ATL13 Inland Water Elevation Data is 45 days from receipt of last data in product.


The 3D Map Compilation Capacity of the DAICHI project Satellite Project is 150,000 maps per month.


The Output Voltage of the Buck-Boost Converter Solar Array Regulator is 65 - 106.6 V.


The Code Memory Storage of the CPU Board Processor is 3 MB of EEPROM.


The Extension Date of the International Space Station Space Station is 27 April 2023.


The Purpose of the SFINKS Solar Array is Test the efficiency of thin film solar arrays.


The Wavenumber of the Instrument Spectrometer is 4250–2630 cm -1.


The Global DEM Production Completion Date of the TanDEM-X Satellite is September 2016.


The Data Rate of the S-band downlink system Communication System is 8 Mbit/s.


The Imaging Date of the New Horizons Spacecraft is July 14, 2015.


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


The Plastic Scintillator of the Range Calorimeter Particle Detector is 1cm thick.


The Function of the DDA Delay-Doppler Altimeter is Measure the across-track angle of the range measurement.


The Pollutants Monitored of the Copernicus Sentinel-5P Satellite is Nitrogen dioxide, ozone, formaldehyde, sulphur dioxide, carbon monoxide, methane.


The Uplink Rate of the ResourceSat-1 Satellite is 100 bit/s.


The Estimated SNR of the Band 4 Spectral Band is 544.65 ± 88.66.


The Deployment Date of the DarkCarb MWIR Payload Payload is 2022.


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


The Power Consumption of the MSU-100 Camera is 6.8 W.


The Ground Pointing Accuracy of the NEMO-HD Satellite is Approximately 260 m.


The Resupply Mission Finish Date of the Cygnus Commercial Cargo Ship Cargo Ship is August 15, 2014.


The First Instrument Placement Date of the InSight Mars Lander is 19 December 2018.


The Meeting Date of the LunaH-Map Satellite is 20-22 October, 2015.


The Signing Date of the Statement of Intent Agreement is March 28, 2019.


The Polarization of the ICI-11 Radiometer is V, H.


The Descent Distance of the OSIRIS-REx Spacecraft is About a half-mile (805 meters).


The Altitude of the ALL-STAR-1 Satellite is ~350-400 km.


The Antenna Type of the Biomass Satellite is SAR antenna with a large deployable reflector.


The Delay Variation of the Ranging Channel Communication System is Varies slightly with RF uplink power and temperature.


The Launch Date of the OPS-SAT Satellite is Unknown.


The Purpose of the GFP Satellite Payload is FSS (Fixed Service Satellite), DBS (Direct Broadcast Satellite) and broadband missions.


The Electrical Power of the CanX-2 S-band Transmitter/Transceiver is 5 W.


The Mission Status of the OPS-SAT Satellite is Operational.


The Mission Duration of the Kolibri-2000 Satellite is 45 days.


The Detector of the Telescope Optical Instrument is FDCCD (Full-depletion CCD).


The Sensor of the TSX Satellite is X-band SAR sensor.


The Wavelength of the EUV Simulation Simulation is 80 nm.


The Orbit Type of the Euclid Satellite is Large-amplitude libration halo orbit.


The f/d Ratio of the Reflector Assembly Satellite Component is 0.5.


The Activation Date of the TOR Payload is February 16, 2009.


The Orbiter Observation Duration of the Tianwen-1 Probe is One Martian year.


The Total Uncertainty Cone of the Alphasat TDP1 and Sentinel-1A Optical Link is Initially set to 2250 µrad and reduced to 1000 µrad.


The Image Rejection of the Image-Reject Mixer Mixer is > 40 dB.


The Ion Acceleration of the Extraction Lens Component is 20 kV.


The Folding Method of the Inflatable boom Component is Origami pattern.


The FPGA of the AIM Reconfigurable Computing Hardware Device is Xilinx XQR4062XL.


The Data Reduction Factor of the GimmeRF Radio Instrument is About 2.4 x 10^6.


The Detector's Temperature of the EyeSat Satellite is 0°C.


The Science Objectives of the TROPICS Constellation of CubeSats is Relate the precipitation structure evolution, including the diurnal cycle, to the evolution of the upper-level warm core and associated intensity changes.


The Imaging Modes of the TeLEOS-1 Satellite is Various.


The Input Power of the X-123SDD Detector is +5 VDC, 300 mA.


The Mission Status of the OCO-3 Instrument is Operational (nominal).


The Mass of the TurkSat-3USat Nanosatellite is ~ 4 kg.


The Boom Length of the SOSMAG Magnetometer is 1m.


The Operation Duration of the FAST Program Technology Demonstration Program is Up to 12 months.


The Unknown of the Reference Mass Material is Material that will not degrade in a LEO.


The Energy Range of the LAXPCs X-ray Proportional Counters is 3-80 keV.


The Mission Position of the IMAP Interstellar Mapping and Acceleration Probe is One million miles (1.5 million kilometers) away from Earth towards the Sun.


The Total Power of the Satellite Satellite is 161 W.


The Total Cargo Mass of the Dragon Resupply Vehicle Resupply Vehicle is 2490 kg.


The Mission Overview Date of the ICON Satellite is 3 Nov. 2017.


The Science Goals of the Euclid Satellite is Capture a 3D picture of the evolving distribution of both dark and ordinary matter in the cosmos, reconstruct the past few billion years of the Universe's expansion history, estimate the acceleration caused by the mysterious dark energy to percent-level a.


The Campaign Duration of the KORUS-OC Korea-United States Ocean Color Mission is 18 days.


The Date of the NASA's IMERG Shows Devastating Rainfall Over East Africa Event is 4 May 2018.


The Power Consumption of the Transponders Device is 2.7 W.


The Flybys of the BepiColombo Spacecraft is 9 (at Earth, Venus and Mercury).


The Architecture of the Frontier Radio Radio is SDR (Software Defined Radio).


The Manufacturer of the CMC Transceiver Communication Device is ClydeSpace.


The Bus Provider and Integrator of the ALTAIR and AQUILA satellites Satellite is Millennium.


The Dynamic Range of the Target Sensor Photodiode is Six orders of magnitude.


The Function of the HSRC Reentry Capsule is Demonstrate reentry technology and cargo recovery from the ISS.


The Operational Status of the WorldView-1 Satellite is Operational as of July 2022.


The Mass of the Pushbroom Imager Imaging Device is 380 kg.


The Function of the AutoConTM Technology is Automated EO-1's maneuver planning and formation control.


The Operation Modes of the TRSR GPS Receiver is C/A and P code, P-codeless (cross-correlation).


The Receiver Type of the CryoSat Satellite is DIODE added another feature: inertial J2000 on-board position and velocity bulletins to be used by the AOCS.


The Plenum Pressure of the T3µPS Micropropulsion System is 4.5 bar.


The Mission Duration of the Chang'e-4 Lunar Spacecraft is 2019.


The Data Latency of the MetOp Satellite Satellite is 130 minutes.


The Onboard Computers of the Nanosatellite Satellite is 2.


The Contact Attempt Options of the UFF TLE Data Product is Inertial Pointing or Scanning.


The Anomaly Updates of the Copernicus Sentinel-1B Satellite is 1.


The Energy Measurement Range for Nuclei of the Telescope 2 Telescope is 4-20 MeV/n.


The Hosting Location of the CTDA Component is GMES Security Coordination Center.


The Propellant for Initial Orbit Raising of the Geo Satellite Satellite is 2 tons.


The Optics System of the Telescope Optical Instrument is Ritchey-Chretien type, with 2 aspherical mirrors and 3 folding mirrors.


The FOV of the Telescope Optical Instrument is 1.02 R sun ± 2.7/3 R sun.


The Carbon Dioxide Absorption of the Earth's Forests Natural Feature is Around 8 Gigatons a year.


The Source of Skills and Innovation for MDASat-i missions of the CPUT/F'SATI nanosatellite program Program is Yes.


The Size of the Manatee Nebula Supernova Remnant is Spanning the equivalent size of four full Moons.


The Scanning Type of the Instrument Spectral Imager is 58 pixels / scan line, arranged in 2 x 2 arrays.


The Flare Intensity of the Solar Dynamics Observatory Satellite is X1.


The Date of the NASA’s Exploration Enterprise Workshop Workshop is May 2010.


The Body-Pointing Capability of the Resurs-DK1 Spacecraft is ± 30o into the cross-track direction.


The Atmospheric Water Equivalent of the Mars Planet is Global layer 10 µm thick.


The Launch Date of the Jugnu Nanosatellite is October 12, 2011.


The Instruments of the Meteor-M-2 Satellite is DCS, KMSS, IKFS-2, MTVZA-GY, MSU-MR, GGAK-M, Severyanin-M.


The Redundancy of the MMU Memory Management Unit is Two MSM (Memory System Module) in cold redundancy.


The Look Angle of the Antenna Conically-scanning reflector is 35.5º.


The Scan Mechanism Rate of the Antenna Subsystem Communication is 20.5 rpm.


The Propulsion System Contract Date of the Skybox Imaging Company is Jan. 15, 2013.


The Parachute System Qualification Team of the ExoMars Mission is ESA, TASinI, TASinF, Vorticity, Arescosmo.


The Orbit (Inclination) of the Spacecraft Satellite is 97.9º.


The Thermal Stability Requirement of the PAS Payload Assembly Subsystem is Better than 2 mK at fep (peak to peak value).


The Objectives of the COTS 3 Mission is On-Orbit Operations — Approach, ISS — Attached Operations, On-Orbit Operations — Departure, Recovery.


The Mission Type of the SPIDER Imaging Sensor is EO.


The Downlink Modulation of the NEMO-AM Satellite is Variable.


The Radiation Levels of the LEO Satellites Satellite is More amenable to Commercial-Of-The-Self (COTS) components of automotive or industrial grade.


The Data Relay of the TGO Satellite is NASA rovers.


The Detector of the GHGSat-C1/-C2 Satellite is IR camera.


The Interval of Writing Timer Information to ROM of the MOBC Main On-board Computer is Unknown.


The Half-Power Half-Beamwidth of the High Gain Antenna Antenna is 4.0º.


The Orbit Altitude of the Primary Mission Satellite is 824 km.


The Energy Release of the Ophiuchus Galaxy Cluster Galaxy Cluster is Hundreds of thousands of times more than typical clusters.


The Responsible Parties of the ESEO Satellite is ALMASpace and UniBO.


The Error Requirement of the Wind Speed Retrieval Algorithm Algorithm is 2 m/s or 10% of the wind speed, whichever is greater.


The Spectral Range (Band 2) of the MUX Instrument is 0.52-0.59 µm.


The Developer of the skCube Satellite is SOSA (Slovak Organization for Space Activities ) .


The Type of the BLITS Satellite is Ball Lens In The Space.


The Altitude of the LAGEOS Satellite is 5858 km x 5958 km.


The Manufacturer of the ALICE UV Spectrometer is SwRI.


The Downlink Speed of the EV-9 Satellite is 2 Mbit/s.


The Cadence of the Fast Neutrons Measurement is In the range 1-20 MeV.


The Launch Site of the NigeriaSat-1 Satellite is Plesetsk, Russia.


The Teamwork Importance of the AzTechSat Nanosatellite is Crucial.


The Number of Experiments of the ORS-3 Mission is 26.


The Orbit Type of the CBERS-2B Satellite is Sun-synchronous orbit.


The Collaboration Announcement Date of the Astrocast Satellite Operator is December 14, 2021.


The Deployment of the Origami booms Component is Straight-line.


The Material of the Gnome Chompski Space Component is Titanium.


The Launch Mass of the Ascent Vehicle Vehicle is Roughly 500 kg.


The Impact on ACS Algorithm Test-Replace Cycle of the Ground Station Ground Equipment is Almost twice as fast.


The Frequency of the VIS (red) Band is 460 THz.


The Launch Date of the TechDemoSat-1 Satellite is 2014.


The DC Power Consumption of the Channel Communication System is 50 W.


The Magnetorquer of the ADCS Attitude Determination and Control Subsystem is ±0.2 Am 2.


The Mission Team of the New Horizons Spacecraft is Southwest Research Institute’s Space Studies Department, Boulder, CO; Johns Hopkins University Applied Physics Laboratory in Laurel, Md.; Stanford University, Palo Alto, Calif.; Ball Aerospace Corp., Boulder; NASA Goddard Space Flight Center, Greenbelt, M.


The Pixel size of the Channel 8 Sensor is 48 km x 48 km.


The Launch Date of the TeLEOS-1 Satellite is Dec 16, 2015.


The Attitude Control of the Payload Satellite Payload is 3-axis control.


The RAM of the Model calculator Data Handling and Processing is 512 kB.


The Spatial Resolution of the Multispectral Instrument (MSI) Instrument is 20 m.


The Field of View of the LSI-1 Camera is 29º.


The Concept Presentation of the ALTIKA Instrument is Unknown.


The Member of the Liz Ritchie Individual is True.


The Operation of the Automated Beacon Network Anomaly Detection System is Receives the health message.


The 3He Separation of the LET Low Energy Telescope is ~1%.


The Prime Objective of the ZACube-2 CubeSat is Demonstrate AIS (Automatic Identification System) message reception using its SDR-based payload.


The Manufacturer of the SPL Deployment System is Astro und Feinwerktechnik Adlershof GmbH.


The Aperture Diameter of the Telescope Optical Instrument is 0.7 m.


The Mass of the Tatiana-2 Microsatellite is 100 kg.


The Redundancy of the Ka-band Channels Communication System is 1 standby channel (4 for 3 redundancy).


The Satellite of the VIIRS Imaging Radiometer Suite is NOAA-NASA Suomi NPP.


The GPS Receivers of the TanDEM-X Satellite is Dual-frequency.


The Coplanar Orbit of the Landsat 9 Satellite is Landsat-8, 180º apart.


The Business Opportunities of the Satellogic Satellite Imaging Company is $2.1 billion in the near and longer term.


The Short Circuit Current of the CSS Solar Cells is 34 mA.


The Total Mass of the Satellite Satellite is 110 kg.


The Band 1 of the CIRiS Instrument is 7.4 µm to 13.72 µm.


The Image Scale of the Galileo Spacecraft is 1.6 km/pixel.


The Size, Weight and Power (SWaP) of the Small Photon Entangling Quantum System (SPEQS) Quantum Light Source is Miniaturized.


The Design Life of the Chang'e-3 Moon Lander is Exceeded by 14 months.


The Landing Date of the Chang'e-3 Moon Lander is December 2013.


The Energy Storage Margin (60 minute window) of the RASP Maneuver Planning System is 62.9%.


The Headwaters of River of the Saskatchewan Glacier Glacier is North Saskatchewan River.


The Quantity of the U.S. Weather Satellites Satellite is 2.


The Mission of the MTG-S Satellite is Sounding.


The Acceleration of the iCPS engine Engine is 0.5 g.


The Data Amount of the Experiment Data Telemetry is 130 Mbit.


The Polarization of the ICI-5 Radiometer is V.


The Instrument Type of the METIS Telescope is Multi-Element Telescope for Imaging and Spectroscopy.


The Mass of the STAFF/DWP Instrument is 5.0 kg.


The Delivery Latency of the Tactical Mode Satellite Mode is Less than 30 minutes.


The Formation Distance of the TanDEM-X and TerraSAR-X Satellites is 20 km.


The Attitude Control Accuracy of the BRITE spacecraft Satellite is better than 1.0º.


The Measurement Category of the Satellite EO is Multi-purpose imagery (ocean), Radiation budget, Multi-purpose imagery (land), Surface temperature (land), Vegetation, Gravity, Magnetic and Geodynamic measurements, Surface temperature (ocean), Landscape topography, Ocean topography/currents, Atmospheric.


The Latency of the ATL17 ATLAS Atmosphere Monthly Data is 45 days from receipt of last data in product.


The Reflector Manufacturers of the Biomass Satellite is Harris Corporation (HC) and Northrop Grumman (NG).


The Explosion Date of the Cassiopeia A Supernova Remnant is 320 years ago.


The Detector Line Arrays of the Whiskbroom Scanner Imaging Device is 16 for VNIR bands, 32 for PAN, and 8 detectors for TIR.


The First Earth Imagery Release Date of the UrtheCast Company is April 3, 2014.


The Power of the Travelling Wave Tube Amplifier Device is 20 W.


The Orbit Raising of the ARTEMIS Satellite is In-Flight Experience with Ion Propulsion.


The Operation of the BCR Battery Charge Regulator is Independent.


The Purpose of the LEO Network Communication Network is Minimize or eliminate the need for new satellite companies to develop their own ground network.


The Attitude and Pointing Control System of the Skylab Space Station is Unknown.


The Spatial Resolution of the TopSAR wide Imaging Mode is 50 - 100 m.


The Detectors of the FTS Interferometer Interferometer is InSb, HgCdTe.


The Distance Traveled of the Yutu 2 Lunar Rover is 600 meters.


The Purpose of the CIRAS Instrument is Demonstrate a critical science and meteorological measurement in a significantly smaller package enabling use in constellations for improved latency.


The Mission Objective of the FASTRAC Satellite is Demonstrate two-way intersatellite crosslink with verified data exchange.


The Rainfall Impact of the OCO-2 Satellite is Increased carbon release.


The Monitoring Method of the Bioburden Monitoring System System is Essays taken at regular intervals.


The Polarization Directions of the POL Linear Polarizer is -60°, 0° and +60°.


The Launch Success Rate of the OneWeb Satellite Constellation is 100%.


The Testing Duration of the JUICE Spacecraft is 1 month.


The Coverage of the International Space Station Space Station is Areas where thunderstorms are common.


The Mission Status of the GRIFEX Satellite is Operational.


The Observation Date of the INTEGRAL Satellite is 27 Jan. 2009.


The Office Launch Date of the ESA Organization is 9 February 2022.


The Data Usage of the Iridium Constellation Satellites Satellite is Characterize the large scale FACs in both hemispheres on time scales of several hours or less.


The Viewing Angle Range of the POLO data set Image Dataset is -115º to +115º.


The Power of the HEPD Instrument is 2.0 W.


The Accuracy for 2000 kg payload of the IPS Pointing System is 0.4 arcseconds lateral and 11.2 arcseconds for roll under star tracker control.


The Mass of the LISS-4 Camera is 169.5 kg.


The Year of Launch of the Jason-2 Satellite is 2008.


The Moon Image Resolution of the Pleiades-1A and Pleiades-1B Satellites is ~300 m.


The Cloud Profiling Radar (CPR) Transition to Operate Mode Date of the CloudSat Satellite is May, 20, 2006.


The Availability of the Pleiades System Satellite System is Close to 100%.


The Unique Label of the CAN Bus Data Communication is Yes.


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


The Maximum Acquisition Capability of the Satellite Imaging Satellite is 1800 images in a 24 hour period.


The | of the SFL Boom-Mounted Magnetometer Magnetometer is SFL boom-mounted magnetometer.


The Comets Discovered of the SOHO Satellite is More than 3000.


The Image Quality of the SPOT 6 Satellite is Unknown.


The Observation Goal of the SHIMMER Satellite is Observe the equatorward edge of the polar mesospheric cloud (PMC) region.


The Total Maneuvering Mass of the Swarm-A Satellite is Approximately 80 g.


The Mission Completion Date of the CRS-18 Dragon Spacecraft is 27 August 2019.


The Load Regulation of the DC-DC converter Power Converter is ±1% from 40% load to 100% load.


The Geostationary Data Relay System of the Sentinel-1, -2 Satellites is EDRS (European Data Relay System).


The Unknown of the Universat-Tatyana-2 Small Spacecraft is Unknown.


The Daily Atmospheric Profiles of the TOR Payload is About 250.


The Presentation Date of the Long-term stable internal calibration chain for a space-borne Integrated Path Differential Absorption LIDAR system Calibration System is Oct. 3-7, 2011.


The Affiliation of the Steven De Cuyper Engineer is Unknown.


The Purpose of the AERO-VISTA Interactive Spectrogram Display Software is Scientific Operations of Twin 6U CubeSats.


The X-ray Source Obscuration of the The Teacup Quasar is Heavily obscured.


The Average Crust Density of the InSight Satellite is 2,582 kg/m3.


The Sensor Performance of the Landsat-7 Satellite is Not provided.


The Conference Presentation Date of the SEXTANT X-ray Pulsar Navigation Testbed is March 7-14, 2015.


The User Platform Simulator of the LCRD Satellite is UPS.


The SAR Technology of the ICEYE Company is Synthetic Aperture Radar.


The Downlink Frequency of the CUTE-1.7+APD Satellite is UHF (437.505 MHz).


The Bandwidth of the Spacecraft Repeater Communication Device is 46 kHz.


The Planned Launch of the Resurs-P5 Satellite is 2023.


The Software of the TIE Payload is Payload Control (PLC) software.


The Power Consumption of the DSU Data Storage Unit is Significantly reduced compared to the traditional solid state mass memory solutions.


The Drill Depth of the Rosalind Franklin rover Mars Rover is 2 m underground.


The Service Life of the Prometheus Satellite Satellite is 3 to 5 years.


The Mission Type of the ExoMars TGO Satellite is Red Planet Investigation.


The Precision of the Satellite Position MOD is < 1.5 m (rms).


The Impact Point of the Vikram Lander Lander is Unknown.


The Camera Modes of the Optical Satellite Satellite is Multi-spectral pushbroom and RGB color video.


The Conference Presentation of the UK Disaster Monitoring Constellation Satellite Satellite is ION 2003.


The Operation Mode of the CCDs Detector is Frame-transfer mode.


The Sun sensors of the BEESAT-2 Satellite is Yes.


The Mission Update Date of the GPM Core Satellite is Feb. 27, 2014.


The Size of the Kepler 11145123 Star is More than twice the size of the Sun.


The Announcement Date of the Copernicus Sentinel-5P Satellite is May 04, 2020.


The Purpose of the COSMOS Software System is Support the development and operations of one or more small spacecraft throughout the life cycle.


The Temperature of the CCD Cooling Cooling System is -20°C.


The Overhead Pass Time of the WorldView-1 Satellite is Approximately 13:30 hours local time.


The Gain Control of the MCP (Microchannel Plate) Detector Detector is Voltage applied across the MCP.


The Realtime Data Availability of the SAPHIR Instrument is Since May 2013.


The Orbit Determination Accuracy of the DORIS Receiver is 0.2 m - 0.6 m.


The Material of the Canopy Satellite Component is 1/4 mil mylar.


The Signal Strength of the AAUSat-1 CubeSat is Very weak.


The Wind Sensor Failure Date of the QuikSCAT Satellite is Nov. 24, 2009.


The Mission Presentation Date of the Deep Space Atomic Clock Clock is Oct. 29- Nov. 2, 2012.


The Avionics of the Microsatellite Satellite is PUNCH avionics.


The Tool of the GPS Spoofing Activity is STK (Satellite Tool Kit).


The Perigee of the Chang'e-1 Satellite is 200 km.


The Boresight Pointing Measurement of the OVIRS Spectrometer is With respect to an optical alignment cube on OVIRS.


The | of the Aalto-1 Nanosatellite is Aalto-1 nanosatellite – technical description and mission objectives.


The Dynamic Spectrum Production of the SWAVES Instrument is 1 minute averaged.


The  Spacecraft control of the  Spacecraft Bus (Avionics Module=AM) Satellite is 3-axis stabilized.


The Distance from the Moon of the Satellite Spacecraft is 18,000 km.


The Array Width of the ICEYE SAR Antenna Antenna is 3.2 m.


The Dynamic Range of the Detector Imaging Device is 16 bit.


The Speed of the Telemetry Data Data Transmission is 640 Mbps.


The Instrument Type of the ACE-FTS Instrument is Compact high performance instrument.


The Spectral Range of the Instrument Hyperspectral Imager is 0.4 - 2.5 μm.


The Hold Distance of the Canadarm2 Robotic Arm is 10 m.


The Date of Malfunction of the MeteoSat-8 Weather Satellite is Oct. 17, 2002.


The Objectives of the ExoMars Mission is EDL (Entry, Descent, and Landing) of a payload on the surface of Mars, Surface mobility with a Rover, Access to the subsurface to acquire samples, Sample acquisition, preparation, distribution, and analysis.


The Altitude of the Galileo Navigation Satellite is 23,222 km.


The Mission of the Lunar Flashlight Satellite is Look for ice deposits and identify locations where resources may be extracted from the lunar surface.


The Resonance of the Satellite Orbit Orbit is 3:1.


The Image Orientation of the Galileo Spacecraft is The north pole of the moon is to the right.


The Measurement Capability of the NICER X-ray Instrument is Neutron star's rotation rate.


The Orbit of the ISS Satellite is Diurnal and sub-diurnal cycles.


The Calibration Method of the TIR Subsystem Calibration System is Light from the ground enters the TIR subsystem through the “Earth window” and is reflected into the imaging optics by a calibration mirror.


The Solar Observation of the SOHO Satellite is March 19, 2015.


The Launch Date of the QuickBird-2 Satellite is Oct. 21, 2001.


The Pixel Size (km x km) of the Antenna Reflector is 16.


The Operating Band of the VDES Antenna Antenna is VHF maritime band.


The Type of the UT 699 LEON 3 FT microprocessor Microprocessor is UT 699 LEON 3 FT.


The Direction Accuracy of the SeaWinds scatterometer Scatterometer is 20º.


The Operational Autonomy Period of the Spacecraft Satellite is 24 hours.


The Kinematic properties of the IPD Interplanetary Dust is < 77 km/s.


The Ground Resolution of the P Mode Observation Mode is 2.29 m~0.98 m.


The Data Rate of the HI-SCALE Instrument is 160 bit/s.


The RF Communications of the Spacecraft Satellite is S-band for TT&C support.


The Rotation Range of the Pointer Mirror Device is 0 to 360º.


The Spectral range of the Optical System Imaging System is 0.37-0.45, 0.45-0.51, 0.58-0.68, 0.68-0.78, 3.55-3.93 µm.


The Quantity of Silicon Detectors of the NICER/SEXTANT Instrument is Not provided.


The Number of Nodes of the FODB Data Interface is 2 to 128.


The Observation Type of the RHESSI Satellite is Global wave generation.


The Solar Cell Average Power of the S/C Satellite is 1.4 W.


The CCSDS ID of the GSAT-0208 Satellite is 268.


The Data Playback Frequency of the SAMPEX Satellite is Twice per day.


The Date of the Impact Event SCI is 5 April 5 at 2:37 UT.


The Mass of the Kestrel Eye II Microsatellite is ~50 kg.


The Current Location of the Voyager 1 Spacecraft is Interstellar space.


The Operation Duration of the SWFO Satellite is 5 years.


The Function of the Hertz Chamber Test Chamber is Assess radio signals from antennas.


The Function of the Propulsion Subsystem Spacecraft Subsystem is Support trajectory maneuvers to L2 and maintain the halo orbit at L2.


The Number of International Joint Collaboration Payloads of the Chang’e-4 Mission is 3.


The Testing Date of the Orion Spacecraft is May 11, 2016.


The Discovery Date of the Cluster Satellite is Spring of 2009.


The Effective FOV of the Channel 8 Sensor is 21 km x 48 km.


The Size of the PR-CuNaR2 CubeSat is 3U.


The Spacewalk Duration of the UrtheCast Cameras Camera is Six Hours.


The Application of the Supercapacitor Energy Storage Device is Launchers and satellites.


The Applications of the Drag-Free Technology Technology is Navigation, Earth science, fundamental physics, and astrophysics.


The Power/energy provider for EDM of the TGO Satellite is Yes.


The Distance from the Sun of the Vigil Spacecraft is 150 million km.


The Detector Head Assembly Footprint of the Sounder Satellite Instrument is 10 km x 40 km.


The Bus Type of the NorSat-1 Satellite is Next-generation satellite bus.


The Launch Date of the Myriade/AstroSat-100 Satellite is 29 June 2004.


The IFOV/line (pixels/scan line) of the MWRI Microwave Radiation Imager is 240.


The Return Link Delivery Time of the Galileo Satellite Constellation is A couple of minutes in the majority of cases, up to 30 minutes maximum.


The Primary Use of the Band 1 Spectral Band is Daytime clouds, ice and snow, vegetation.


The Member of the Peter Cornillon Individual is True.


The Leveraging of the COTS technology Technology is Reuse of commercial design tools, foundry, processes, masks.


The Slew Rate of the TeLEOS-1 Imager Imaging Device is 2.5º/s.


The Thermal Isolation of the VGT-P Instrument is Multi-layer insulation (MLI) and titanium quasi isostatic mounting feet.


The Type of the POLAS-128 AOS Instrument is Polarization-sensitive Acousto-optic Spectrometer.


The Number of Beams of the SWIM Instrument Radar is 6.


The Time Accuracy of the NICER X-ray telescope Telescope is Better than 100 ns.


The Units of the CO2 Concentration Atmospheric Parameter is ppm (parts per million).


The Age of the Manatee Nebula Supernova Remnant is Around 30,000 years.


The Launch Year of the IceEye-1 Satellite is 2018.


The UHF Lithium-1 Radio of the RAX-1 Satellite is Performed extremely well.


The Launch Year of the SWFO Satellite is 2025.


The Minimum Elevation Horizon Mask of the Panama ground station Ground Station is 3º.


The Galaxy Catalog Size of the Euclid Satellite is More than 2 thousand million galaxies.


The Operation Mode of the GeoSTAR Atmospheric Microwave Sounder is Continuous.


The Objective of the NewMag Magnetometer Experiment is Measure electrical currents and perturbations in the Earth's magnetic field.


The Topology of the IXV Communications Network Network is Star.


The Maximum Data Volume of the ALOS-3 Satellite is 1400 Gbit per day.


The Testing Date of the GEOS-1 Satellite is Unknown.


The URL of the ELSA-d IOD Mission is https://astroscale.com/missions/elsa-d/.


The Operations Workflow of the Optical Inter-Satellite Links (OISL) Satellite Communication System is Joint concept for the ASA-S1A Optical Inter-Satellite Links operations, based on the two missions’ planning cycle and operations execution scenario.


The Launch Date of the SEOSat Satellite is Unknown.


The First Light Image Date of the SeaHawk-1 Satellite is 22 March 2019.


The Orbit Determination Accuracy of the QZS-1 Satellite is Sub-meter.


The Launch Date of the Megha-Tropiques Satellite is 12 Oct 2011.


The Lava Area of the Image Data is Roughly 10 km2.


The Contact of the LAPAN Organization is Robertus Heru Triharjanto.


The Number of Maneuvers of the SkySat-7 Satellite is 14.


The Actual Mission Duration of the Jade Rabbit Moon Rover is 31 months.


The Orbit Altitude of the ALMASat-1 Satellite is 354 km x 1450 km.


The Power of the HEED Instrument is 2.0 W.


The Emergency Support Data Rate of the IXPE Satellite is 32 kbit/s.


The Location of the Batteries Device is Below the laser.


The Oblateness of the Kepler 11145123 Star is Less than implied by its rotation rate.


The URL of the LUMIO CubeSat is https://iafastro.directory/iac/proceedings/IAC-18/.


The Type of the Attitude Determination System System is Histogram filter.


The Detector Module Temperature Change Limit of the Neutron-1 Spacecraft is 0.5°C/min.


The Spectral Scans of the ISEE-3 Satellite is Two per second.


The Meeting Location of the ICON Satellite is San Francisco, CA, USA.


The Dimensions of the CLARA Instrument Satellite Instrument is 114 mm x 141 mm x 155 mm.


The Mission Status of the Biomass Satellite is Approved.


The Presentation of the Atlas V Aft Bulkhead Carrier & Operationally Unique Technologies Satellite Satellite is Workshop.


The Precision of the Satellite Position POD is < 10 cm (rms).


The Methods of the Image Smearing Correction Image Processing is Fast readout, binning, skipping rows outside the region of interest, post-processing.


The Passes Less Than 150 Seconds of the GNOMES-1 Satellite is Less than 5% of passes are less than 150 seconds for either sets of ground stations.


The Principle of the Magnetometer Instrument is Magneto-inductive.


The On-orbit performance evaluation of the Propellant-free attitude control system Attitude Control System is Not provided.


The Original Launch Date of the Spacelab-1 Satellite is Summer of 1980.


The URL of the SXI Imager is http://www.research.noaa.gov/spotlite/archive/spot_sxi.html.


The Sun's Activity of the ICON Satellite is Quiet phase during solar minimum.


The Spectral Resolution of the OMPS Limb Profiler Spectrometer is 0.75 nm to 25 nm.


The Altitude of the FY-3 (FengYun-3) Satellite is +105.


The Regulator of the IMSO International Mobile Satellite Organization is GMDSS.


The Field of View of the Data Receiver Satellite Component is 15 µrad.


The S/C Mass of the JL-1-GF03D Microsatellite is <45 kg.


The Mass of the MicroSat-2a Satellite is 400 kg.


The Type of the GeoCarb Instrument is 4-Infrared channel, single-slit imaging spectrograph.


The Mass of the Optsat-3000 Satellite is 368 kg.


The Duration of the Simulation Test is About 11 days.


The Purpose of the Global Carbon Cycle Earth Science is Understanding the global carbon cycle and how it responds to human and natural forcing.


The Attitude Control Duration of the Active solar or drag sails Deorbiting Device is Months or even years.


The Sensor Complement of the HJ-1B Satellite is Wide View CCD Cameras (WVC), Infrared Multispectral Scanner (IRMSS).


The Enclosure Color of the VLF Receiver Receiver is White.


The Design Life of the Genesis-2 Spacecraft is 5 years.


The Services of the ALTAIR bus Satellite Bus is Navigation, propulsion, data processing and communications for the five TRACERS science instruments.


The Solar Cell Quantity of the TUBSAT-N Satellite is 34 cells per string.


The Instrument Types of the Solar Orbiter Satellite is In situ and remote sensing.


The Sea Level Rise of the Topex-Poseidon and Jason missions Satellite Missions is 3.2 mm per year.


The Detector Type of the WUPPE Spectrophotometer is Intensified diode-array.


The Wide Survey Coverage of the Euclid Reference Survey Survey is 15000 deg2.


The | of the A. Gordon Emslie Author is A. Gordon Emslie.


The URL of the IXV Spacecraft is http://esamultimedia.esa.int/multimedia/publications/ixv/offline/download.pdf.


The Altitude of the CSG and CSK satellites Satellite is 620km.


The Contractor of the BRITE-PL Satellite Project is UTIAS/SFL.


The Observation of the FAUST Instrument is Galaxy clusters in the Virgo, Telescopium, Dorado, and Ophicus constellations.


The Number of Images Collected of the Landsat-9 Satellite is More than 57,000.


The Temperature of the Solar Corona Solar Feature is More than a million degree Kelvin.


The Lead Scientist of the GPM Satellite is George Huffman.


The Launch Date of the SMOS Satellite is May 21, 2010.


The Test Date of the ISIM Compartment is April 2013.


The Diameter of the Dimorphos Asteroid is 160 meters.


The Mounting Location of the VWFC Camera is Spacelab scientific airlock.


The Protocol of the Downlink Framer Communication System is CCSDS compatible protocol.


The Field of View of the CMOS Camera Camera is 58º.


The Operation Duration of the RadSat Satellite is ~12 months.


The Band-3 Data of the LISS-4 Camera is Nominally observed and transmitted in mono mode.


The Pulse Duration of the SIRAL Radar is 50 µs.


The Number of Radiation Belts Discovered of the Van Allen Probes Satellite is 3.


The FPGA of the ACU Attitude Control Unit is Xilinx XC4VFX12-10FFG668I (Virtex4).


The Potential Cost of the Geomagnetic Storm Space Weather Event is Up to several trillion dollars.


The Locations of the POCs Instrument Operations Centers is Navel Research Laboratory in Washington, DC (SECCHI); the University of California, Berkeley (IMPACT), the University of Minnesota, Minneapolis (SWAVES); and the University of New Hampshire, Durham (PLASTIC).


The Landing Location of the Falcon 9 first stage Rocket is Autonomous spaceport drone ship.


The Launch Date of the Cosmos-1066 (Astrofizika) Satellite is 23.12.1978.


The Manager of the PAZ Satellite is HISDESAT.


The Data Bus of the JWST Avionics Spacecraft Avionics is MIL‐STD‐1553.


The Elevation Difference of the Burroughs Crater Crater is About 400 km.


The Spatial Resolution of the GK-2A Satellite is 2 km for the 10 infrared channels and 1 km for 6 visible channels.


The Downlink Data Rate of the Satellite Communication System is 620 Mbit/s.


The Number of satellites per system of the WorldView-4 Satellite is 1.


The Components of the MCCM Multi-chip Control Module is Thin film passive circuits, MMIC low-noise amplifiers (LNAs), phase shifter and attenuator chips, ASICs and other discrete components for control and telemetry.


The Illumination of the Solar Panels Satellite Component is Provided during rotation.


The Qualification Status of the Virtex-4 FPGA Data Processing Unit is Not space-qualified in Europe.


The Manufacturer of the Gyros Sensor is Analog Devices.


The Spectroscopy Range of the CUTE NUV Imaging Spectrograph is 255 to 330 nm.


The Period of the Orbit Satellite is 99.31 min.


The Mission Start Date of the Eu:CROPIS Satellite is April 24, 2014.


The Stability of the Optomechanical System Optomechanical System is Athermal and actively temperature-controlled.


The Number of Lines of the CCDs Detector is 576.


The Journal Publication Date of the OCEANSAT-2 Satellite is October, 2007.


The Primary Contribution of the Orbital Astronomical Observatories Telescopes is Enable humanity to explore beyond our frontier of knowledge.


The Orbital Inclination of the International Space Station Satellite is Between 52 degrees north and 52 degrees south latitudes.


The Presentation Date of the NPOESS Satellite is Oct. 4-8, 2004.


The Spatial Resolution of the SLSTR Imaging Device is 500 m.


The Wind Direction Blur of the LG-mod Wind and Wave Information Calculation is 180°.


The Core Objective of the SMOS Satellite is Improving our understanding of Earth’s water cycle.


The Launch Date of the Konnect Satellite is 16 January 2020.


The Issue of the Diagnostic Port Port is Beginning to separate the mechanical ground connectors from the PCB.


The Application of the CMT Imager is Support for Local Emergencies.


The Launch Date of the Beijing-3 Satellite Constellation is 11 June 2021.


The Launch Date of the Beijing-1 Satellite is Oct. 27, 2005.


The Downlink Data Rate of the TT&C Communications RF Communications is Up to 8 kbit/s.


The Image Sequence Cadence of the COR1 Coronagraph1 imager is ≥ 1 min.


The Approx. peak sensitivity altitude of the Channel 1 Sensor is Unknown.


The Command Communication Band of the SWFO-L1 Satellite is S-band.


The Velocity before being Swallowed up by the Hole of the Earth-sized clump of matter Unknown is A third of the velocity of light.


The Orbit Type of the EarthDaily Constellation Satellite Constellation is Sun-synchronous.


The Antenna Performance Verification of the Spacecraft Satellite is TRL 7.


The Function of the UrtheCast Camera System is Offer near-live images of Earth.


The Payloads of the Orion Vehicle Spacecraft is Unknown.


The Measurement Domain of the FedSat Satellite is Gravity and Magnetic Fields.


The Launch Date of the PSLV-C34 Satellite is June 22, 2016.


The URL of the ExoMars Mission is http://exploration.esa.int/mars/48088-mission-overview/.


The Envelope Dimensions of the MIRAD Instrument is 100 mm x 105 mm x 105 mm.


The Purpose of the Attitude Determination Quaternion Filter Experiment is Perform spacecraft attitude tests in LEO.


The Launch Date of the Ariane 5 ECA Launch Vehicle is August 2, 2012.


The Retirement Date of the CBERS-2B Satellite is May 10, 2010.


The Spectral Range (Band 3) of the MUX Instrument is 0.63-0.69 µm.


The Topology of the Buck-Boost Converter Solar Array Regulator is Buck-Boost.


The Mission Position of the IMAP Interstellar Mapping and Acceleration Probe is First L1 (Lagrange point).


The Typical Value of the AOD Satellite Instrument is 0.1-1.


The Technology of the OSCAR-QUBE Experiment is Diamond-based quantum technology.


The Task of the Restore-L Satellite is Lock on to it.


The PLC Cargo of the HTV-7 Cargo spacecraft is 4.3 metric tons.


The FMC Mode Rotation Speed of the Telescope Optical Instrument is 0.6º/s.


The Antenna Configuration of the Satellite Satellite is Single downward pointing antenna.


The Test Cost of the Modern ICs Electronic Components is >$46 M.


The Deadtime per trigger of the PHA Detector is 4–67 µs.


The Spectral Range of the M16 filter Infrared Filter is 11.5 - 12.5 µm.


The Resolution of the T1 Trigger Camera is 20 km x 20 km.


The Components of the Prime Instrument Ozone Monitor is Two nadir-pointing UV cameras, one operating with CCD detectors, the other with UV photodiodes.


The Altitude of the Satellite SuperView Constellation is 530 km.


The IFOV/line (pixels/scan line) of the SBUS Solar Backscattering UV Sounder is 240.


The Thermal Capacitance of the Sensor Node Node is Large.


The Sampling Frequency of the fADC A/D Converter is 80 MHz.


The Magnetic Field Profile of the Solar Flare Natural Phenomenon is Matched the theoretical prediction.


The Maiden Flight Date of the Vega Launcher is Feb. 13, 2012.


The Height of the Nimbus-7 S/C Satellite is 3.04 m.


The Dimensions of the IMP-8 Spacecraft is 135.6 cm diameter and 157.4 cm high.


The Absolute Pointing Required of the COR1 Coronagraph1 imager is 7 arcsec.


The Launch Date of the CFOSAT Satellite is 2018.


The Peak Transmit Power of the Radar Instrument is 500 W.


The Authors of the Aerosol Polarimetry Sensor Sensor is Richard J. Peralta, Carl Nardell, Brian Cairns, Edgar E. Russell, Larry D. Travis, Michael I. Mishchenko, Bryan A. Fafaul, Ronald J. Hooker.


The Number of Satellites of the Terran R Launch Vehicle is Not Disclosed.


The Swath (nadir) of the Payload Satellite Subsystem is ≥30 km.


The Optical Performance of the Euclid Satellite is Very stable under extreme attitude changes.


The Data Collected of the Juno Spacecraft is About three terabits.


The Power Consumption of the NewMag Magnetometer is 3 W.


The Phase C Review Date of the SVOM Satellite is Unknown.


The Maximum Satellite Demand of the Satellite Satellite is 850 W.


The Battery Type of the HTV Spacecraft is Lithium ion.


The Mirror Module Assemblies URL of the IXPE Satellite is https://doi.org/10.1117/12.2531956.


The Memory of the AIM Reconfigurable Computing Hardware Device is 64 kbyte I/O space mapped into Xilinx FPGA.


The Unique Identifiers of the LT Device is J and K.


The Total Satellite Launch Mass of the Vega Rideshare Mission Satellite Launch is 1,327 kg.


The Attitude Sensing of the IRS-1C and IRS-1D Spacecraft is Star sensors, Earth sensors and gyros.


The Information Collected of the TechDemoSat-1's radiation monitor Radiation Monitor is Total ionizing dose, dose rate, and particle flux (protons and heavy ions).


The Launch Date of the BRITE-Austria Satellite is Unknown.


The Array Power Average of the DSX Spacecraft Payload Module Satellite is 650 W.


The Accuracy of the GPS receiver Receiver is 50 m (1σ).


The Interface of the ACU Control and Data Handling Subsystem is CAN bus.


The End of Life Date of the CXBN-2 Satellite is 1 March 2019.


The Type of the M83 Galaxy is Barred spiral galaxy.


The Instrument of the Cheops Satellite is Detector.


The Function of the Heat Pipes Thermal Control System is Transport waste heat to the radiator.


The Mission Objective of the DART Space Probe is Collide with an asteroid and deflect it from its orbit.


The Size of the REXJ Astrobot is Small as a microwave oven.


The Spatial Resolution of the Solid Earth Rifts Satellite is 100-500 km.


The Health Check Date of the SEIS Seismometer is July 19.


The Earth-Moon Transfer Distance of the Probes Spacecraft is Up to 1.6 million km.


The Ground of the Data Transmission Process is Real time.


The Launch Date of the Atlas V Rocket Rocket is Dec. 6, 2013.


The Image Formats of the C3D2 Payload is Compressed and uncompressed.


The Altitude Above Ground of the Lunar Landing Vehicle Vehicle is 4 m.


The Purpose of the TTTC Time-Tagged Telecommand is Commanding tasks with parameters and time tag.


The Agency of the PhoneSat-1 and -2 Satellite is NASA.


The Mission of the BRITE Nanosatellite Network is BRIght Target Explorer.


The Launch Date of the PSat-2 CubeSat is June 25, 2019.


The Project Duration of the ESEO Satellite is 1.5 years.


The Absolute Attitude Sensors of the PSSCT-2 Satellite is Aerospace-developed sun and Earth nadir sensors, plus COTS (Commercial-of-the-Shelf) magnetic field sensors from Honeywell.


The Science Data Processing Center of the XMM-Newton Satellite is XMM-Newton Survey Science Center at the University of Leicester, England.


The Purpose of the EMIT Imaging Spectrometer is Map the world’s mineral dust source regions and provide information on the color and composition of dust sources.


The URL of the Rosetta Satellite is http://sci.esa.int/rosetta/12198-new-louvers-ensure-that-rosetta-is-real-cool/.


The Mass of the Sundancer Spacecraft is about 8,200 kg.


The Release Date of the Wide-Field Imager for Solar Probe Plus Imager is July 2016.


The Downlink Rates of the LLCD PAT Systems Communication System is 622 Mbit/s.


The Length of the Gravity-Gradient Boom Stabilization Device is 3 m.


The Radar Measurements Grid Resolution of the L2SMAP Soil Moisture Product is 9 km EASE-2.


The Satellite Size of the OMS Radiometer Radiometer is 3U.


The Electric Power of the Satellite Spacecraft is 2.8 kW.


The Processes of the BJ3A1 satellite ground pre-processing system Data Processing System is Image data separation, attitude and orbit parameter analysis, system radiation and sensor geometry correction, band registration, modulation transfer function (MTF) restoration, product packaging and more.


The Calibration Lamp Wavelength of the Telescope Optical Instrument is 546.1 nm.


The Location of the Tracking and Control Center (TACC) Control Center is Tsukuba Space Center.


The Orbit Altitude of the ISS International Space Station is 405km.


The Connection Time of the Deployment Specialists Personnel is 11 hours.


The Failure Date of the MWTS-2 Satellite Instrument is Feb. 2, 2015.


The Optics of the CASPR Experiment is iSIM-90 optics.


The Data Quantization of the Instrument Hyperspectral Imager is 12 bit.


The NEΔT (K) of the ICI-3 Radiometer is 0.7.


The CCSDS ID of the GSAT-0209 Satellite is 269.


The LTDN of the Tsubame Microsatellite is 11:00 hours.


The Prototype Development Status of the ELSA-M Spacecraft Servicer is Ongoing.


The Avionics Subsystems Manufacturer of the CHORUS Satellite is Magellan Aerospace Corporation.


The Components of the Instrument Carrier Carrier is IOA, WFI, CGI, and the Spacecraft’s Star Tracker/Inertial Reference Unit.


The Radius of the Orbital Phase 2 Orbit is Ca. 19 km.


The Components of the PACE nanosatellite Satellite is COTS (Commercial off-the-Shelf) components as well as in-house developed parts.


The Temperature of the Jupiter's Atmosphere Planetary Atmosphere is Much higher than it is at the top.


The NiH2 Batteries Capacity of the DSP satellites Satellite is 36 Ah.


The TLE Maintenance of the Orbit Dynamic System System is 5.5 hours to 10 hours.


The Maximum Data Rate of the Instrument Satellite Instrument is 115 Mbit/s.


The Camera Type of the GF-2 Satellite is PAN/MS.


The Launch Date of the GovSat-1 Communication Satellite is 31 Jan 2018.


The Quantity of the SMDC-ONE-2.3 and SMDC-ONE-2.4 CubeSats is 2.


The Update of the Accelerometer and Gyro Sensors is Before the first burn.


The Mass (kg) of the ERS-2 Satellite is 2384.


The Mass of the DPU Digital Processing Unit is 9 kg.


The Expected Perihelion of the Comet ATLAS Comet is 31 May.


The Development Date of the Miniature Ion Propulsion System Propulsion System is Unknown.


The Orbital Energy Source of the Juice mission Spacecraft is Earth, Venus and Mars.


The Measurement Domain of the CryoSat Satellite is Ocean, Land, Gravity and Magnetic Fields, Snow & Ice.


The Degree of Coverage of the Partially Overlapping Contrails of the Model Atmospheric Model is Four times greater.


The Orbit Altitude of the IRIS Spacecraft is 620 km x 670 km.


The Funding Cycle of the New Horizons Spacecraft is Every three years.


The Compatibility of the Iris Radio Communication Device is Deep-space and CubeSat.


The Mission Operations Review Date of the Landsat 9 Satellite is Unknown.


The Peak of the Drift Ice Season Natural Phenomenon is February.


The Orbit Type of the MPO Spacecraft is Lower elliptical orbit.


The Radiometric Calibration of the OBA Instrument Component is Provided by views of blackbody and solar targets mounted on the yoke.


The Orbit Count of the Envisat Satellite is 50,000.


The Launch Mass of the Kanopus-V 1 Satellite is 450 kg.


The RF Output Power of the Channel Communication System is 1 W per polarization.


The Spatial Resolution of the High-Resolution Hyperspectral Imager Imager is 30-meter.


The Meeting Date of the AMPERE System is December 14, 2010.


The Date of the Mackenzie River Location is 01 October 2021.


The Sample Rate of the MPO-MAG instrument Instrument is 128 Hz.


The Spectral Range (Band 4) of the MUX Instrument is 0.77-0.89 µm.


The Deployment Start Date of the Galileo Second Generation Satellites Satellite is By 2024.


The 25 hours of the Minor Cycle Duration Satellite Operation is Nine full minor cycles of 25 hours each.


The Number of Propellant Tanks of the XMM-Newton Satellite is 4.


The Transmission Profile of the FG Filtergraph is Unknown.


The Components of the INMS Ion and Neutral Mass Spectrometer is Front-end optics, post acceleration, gated time of flight, ESA (Electrostatic Analyzer) and CEM (Channel Electron Multiplier) or MCP (Micro Channel Plate) detectors.


The TLE Accuracy of the Orbit Dynamic System System is Low distance difference of the appropriate time zone.


The Orbit Type of the GNSS Satellites Satellite is Medium Earth Orbit (MEO).


The Launch Date of the ARMADILLO Satellite is 25 June 2019.


The Data Quantization of the DubaiSat-2 Satellite is 10 bit.


The Maturity Prediction of the SPIDER Telescope is Five to ten years away from being fully matured.


The Application of the Loop Heat Pipe Radiator (LHPR) Heat Rejection Technology is Future spacecraft.


The Activation Window of the Experiment Data Telemetry is 1200 seconds.


The Launch Date of the TechnoSat Nanosatellite is 14 July 2017.


The Release Date of the Dusty deities Image is 6 August 2018.


The Measurement domain of the Meteor-M-2 Satellite is Atmosphere, Ocean, Land, Gravity and Magnetic Fields, Snow & Ice.


The Planned Overlap of the Sentinel-6 Satellite is At least 6 months.


The Issue of the File Transfer Test Communication is Long strings of zeros in various places in each file.


The Mission Status of the OCSE Satellite is Completed.


The Observation Duration of the IBEX Spacecraft is Six months.


The Activation Distance of the LIRIS Laser Infrared Imaging Sensors is 3500 m from the Space Station.


The Frequency Bands of the Communication System UAS Communication is Ku-/Ka-bands.


The Image Time Interval of the Rosetta Satellite is 25 and 27 February 2015.


The Body-Pointing Capability of the Pushbroom Imager Imaging Device is ±40º into the along-track and cross-track directions.


The Wind Profiling of the Aeolus Satellite is Yes.


The Stiffness Requirement of the COMMx Payload is 50 Hz or greater.


The Mirror Material of the SMA Scan Mechanism Assembly is Silicon carbide.


The Announcement Date of the Boeing Pico-Satellite Mission Satellite Mission is April 19, 2007.


The Spin Rate of the AlSat Nano Satellite is Low.


The Number of Satellites of the Satellite Constellation Satellite Constellation is 8.


The Modification Time of the SCIP Processor is Too long.


The Data Rate of the TT&C Telemetry Tracking & Command is 9600 baud.


The Angular Resolution of the ART-XC Instrument Telescope is HPD~ 30” on-axis at 8 keV.


The Altitude of the Spacecraft Satellite is 650 km.


The Developer of the Neutron Dosimeter Dosimeter is Germany.


The Orbit Altitude of the SEOSat Satellite is 670 km.


The Coverage of the TT&C System Tracking, Telemetry and Command System is Full spherical coverage in uplink and downlink.


The Manufacturer of the CIRiS CubeSat is Utah State University.


The Ground Resolution of the VIS Camera Camera is 150 m.


The Provider of the LICIA CubeSat is ASI, the Italian Space Agency.


The Solar Panel Connection of the Phoenix EPS Electrical Power System is COTS buck/boost voltage regulator.


The Number of Ground Receptors of the SafetyNetTM Data Collection Architecture is 15.


The Mission of the NEA Scout Satellite is Reconnaissance of an asteroid, take pictures and observe its position in space.


The Award Date of the Ozone Monitoring Instrument Instrument is 1 April 2019.


The Orientation of the Metric Camera Camera is Open cargo bay oriented towards Earth.


The Launch Vehicle of the COPPER CubeSat Satellite is Minotaur-1 of OSC (Orbital Sciences Corporation).


The Mission Date of the LCROSS Satellite is May 31-June 4, 2010.


The Development and Launch Funding of the HyperScout 1 Hyperspectral Imager is Through the ESA GSTP program with contributions from the Dutch, Belgian and Norwegian national space organizations.


The On-board and Ground Time Management System Presentation of the QZSS Satellite System is ION NTM (National Technical Meeting) 2007, San Diego, CA, USA, January 22-24, 2007.


The Payload Data Transmission Rate of the ResourceSat-1 Satellite is 105 Mbit/s.


The Function of the Copernicus Sentinel-5P Satellite is Maps a multitude of air pollutants around the globe.


The Main Reflector Size of the MIS Instrument Microwave Radiometer is 1.8 m.


The Type of the L-SAR Instrument Sensor is SAR.


The Forecast Duration of the JPSS Satellite Program is 3-7 days.


The Diameter of the Lorentz Chamber Testing Chamber is 2.8 m.


The Mass (Wet) of the Satellite Satellite is ≤ 3200 kg.


The Components of the DEM (Digital Electronics Module) Electronics Module is ICU (Instrumental Control Unit) and a DPU.


The Components of the EPAM Electron, Proton, and Alpha-particle Monitor is LEMS (Low Energy Magnetic Spectrometers), LEFS (Low Energy Foil Spectrometers), CA (Composition Aperture).


The Polarization of the ICI-4 Radiometer is V, H.


The Presentation Date of the ADM-Aeolus Satellite is April 24-28, 2006.


The Function of the Torque Rods Satellite Component is Apply constant open-loop dipole to counteract the body-fixed residual dipole disturbance torque.


The | of the AMISR Radar is http://isr.sri.com/iono/amisr/.


The Accuracy of the EO System Earth Observation System is 0.3%, k = 2.


The Instruments of the GEO-KOMPSAT-2A Satellite is Advanced Meteorological Imager (AMI) and the Korean Space Environment Monitor (KSEM).


The Mass of the Zeta Puppis Star is 60 times more massive than our sun.


The Number of Satellites of the GPS Receiver Navigation Device is 4 or more.


The Cost Scaling of the Ground Station Network Communication System is Does not scale with the size of the satellites.


The Type of the RA/SCAT Antenna is Paraboloidal reflector antenna.


The Communication Sessions of the Kolibri-2000 Satellite is Over 230.


The Program Start of the SIR-C/X-SAR Payload is MRSE (Microwave Remote Sensing Experiment) flown aboard the Shuttle on the first SPACELAB mission in l983.


The End Date of the SRL-1 (STS-59) Mission is April 20, 1994.


The Rotor Type of the Knudsen Station Ground Station is AlphaSpid's Big RAS rotor.


The Early-2024 of the Lightning Imager Data Availability is Data from the Lightning Imager will be available for operational use in early-2024.


The Aspect Ratio of the Iris Video Camera Camera is 16:9.


The Exposure Time Range of the COR1 Coronagraph1 imager is (0.1, 1).


The Interface of the ROE Device is 3 CCDs.


The Pulse Transmission Rate of the SAR Synthetic Aperture Radar is 1,500 pulses/s.


The Access of the Copernicus EMS Service is Planet’s SkySat constellation.


The Integration Status of the Instrument Flight Model System is Near completion.


The Type of the NEXT-C Ion Propulsion System is Solar electric ion propulsion system.


The Swath width of the MERSI Medium Resolution Spectral Imager is 2800 km.


The Total Mass of the Tsubame Microsatellite is ~ 49 kg.


The Presentation Date of the OCAMS Camera Suite is March 18-22, 2013.


The Wet Mass of the Standard 3U CubeSat Satellite is < 3.78 kg.


The Redundancy of the OSDP Onboard Signal Data Processor is Fully redundant.


The Communication Standard of the OBC On-Board Computer is CCSDS (Consultative Committee for Space Data Systems) protocols.


The Cargo Weight of the HTV-7 Cargo Vessel is 6200 kg.


The Boresight Direction of the MIRO Instrument is Aligned with the Rosetta payload line of sight.


The Altitude of the Yubileyniy-2/MiR Satellite is ~ 1400 km.


The Ground Segments of the TanDEM-X Satellite is Mission Operations Segment (MOS), Payload Ground Segment (PGS), Instrument Operations and Calibration Segment (IOCS).


The Manufacturer of the Resistojets Propulsion System is SSTL.


The Manufacturer of the Space Micro µSTDN S-band Transponder is Space Micro.


The Orbit Inclination of the SpaceX CRS-17 Mission is 51.6º.


The Mission Objectives of the Picard Satellite is Solar Diameter, Irradiance, Climate, Differential Rotation, Solar Constant and their variations.


The Purpose of the Lucy Space Mission is Show us the diversity of the primordial bodies that built the planets.


The Task of the OPS&GRND Subsystem is Automate as much work as possible to simplify the future operation of the satellite.


The Orbit Altitude of the Starlink Satellite Satellite is 550 km.


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


The Orbit of the Asteroid 1999JU3 Asteroid is From just inside the orbit of the Earth to just outside the orbit of Mars.


The Predicted Operational Life of the SAR spacecraft Satellite is Three years.


The Mission Objective of the ARIEL Satellite is Measure the chemical composition and thermal structures of exoplanets, linking them to the host star’s environment.


The Image Credit of the TEMPO Instrument is BATC.


The Structure Material of the SRMSat Satellite is Al-6061 alloy.


The Mapping Duration of the TIMED Satellite is 10 Years.


The Start of Science Operations Date of the RAIDS Experiment is October 22, 2009.


The Operation Start Date of the Hitomi Satellite is March 26, 2016.


The Capacity of the Battery Energy Storage is 10.5 Ah.


The Progenitor Type of the GRB 130925A Gamma-Ray Burst is PopIII-like.


The Year of Launch of the TRMM Satellite is 1997.


The Design Life of the SMDC-One Satellite is 1 year.


The Presentation Date of the CXBN-2 Satellite is April 22-24, 2015.


The Date of the Electrodynamic Tethers for Space Propulsion Presentation is Jan. 12-15, 1998.


The 1024 bit/s of the TT&C Communications Telemetry Capacity is Telemetry capacity - 1024 bit/s.


The Imaging Capability of the ICON Space Mission is Provides the ability to separate the drivers and pinpoint the real cause of ionospheric variability.


The Antenna Size of the MWI Instrument is Moderate.


The Number of Satellites in Production of the Eurostar E3000 Satellite Platform is 6.


The Size of the LCRD Payload is About the size of a king-sized mattress.


The Launch Date of the Stingray Satellite is Early 2024.


The Target for Researchers of the Silkworm Insect is Development of new silkworm strains for multiple purposes.


The Battery Capacity of the Canopus Pipper Satellite is 2200 mAh.


The Announcement Date of the NASA Moon Mission Mission is Oct. 27, 2016.


The Number of Sun-grazing comets discovered by amateurs of the SOHO Satellite is Over 1100.


The Deployment Date of the Kestrel Eye II Microsatellite is 24 October 2017.


The Power Usage of the Instrument Device is < 4 W.


The Function of the CMS Constellation Management System is Analysis of orbit data and planning of orbit correction maneuvers.


The Purpose of Point-to-Point Communication of the MCS Communication System is Commanding.


The Launch Date of the CBERS-2B Satellite is Sept. 19, 2007.


The Accuracy of Wind Velocity (Troposphere) of the Aeolus Satellite is 2-3 m/s.


The Publication Date of the IceCube Satellite is 10 March 2021.


The Antennas of the SGR-10 Space GPS Receiver is Two antennas.


The | of the Automatic Packet Reporting System (APRS) Satellite Communication System is | False.


The Mass of the PAN Camera Imaging Device is 200 kg.


The Quantity of the Hiber-1 and Hiber-2 CubeSats is 2.


The Canting Angle of the SAWs Satellite Component is -60º / 0º.


The Affiliation of the Harrison Agrusa PhD Student is University of Maryland.


The Retroreflector Coating of the Norton Satellite Component is Reflects both transmitted wavelengths.


The Orbit Altitude of the Landsat-9 Satellite is 705 km.


The Battery Type of the TUBSAT-N Satellite is NiCd.


The Planned Timeframe of the Mars Sample Return Mission Mission is Around 2028-30.


The Passive Temperature Control of the SVM Service Module is Mirror solar reflectors on the Sun-side, white paint on the anti-sun side.


The Indicators of the Atmospheric Measurements Climate Data is Surface temperature, water vapor, sea ice.


The Propellant of the Propellant Tank Tank is AF-M315E.


The Launch Date of the EduSat Satellite is 2012.


The Design and Development Organizations of the MOMS Optical Camera is DLR, LMU, EADS Astrium GmbH.


The TX Power of the Myriad RF board RF Board is Max. 10 dBm.


The Mounting of the S-band receive and transmit antenna Antenna is Nadir-facing deployable boom.


The Range of the . Magnetometer Instrument is ± 100,000 nT.


The Expanded Applications of the SMOS Satellite is Monitoring and improving forecasting of large storms.


The URL of the PAZ and TerraSAR-X Satellite Constellation is http://www.dlr.de/dlr/en/desktopdefault.aspx/tabid-10081/151_read-7994/year-2013/%23gallery/12103#gallery/12103.


The Components of the EPS Electrical Power System is COTS (Commercial-off-the-Shelf) components, MPTT (Maximum Power Point Tracking) ICs, FRAM (Ferroelectric Random Access Memory), AVR microcontroller.


The Data Transmission of the VT Data Processing is Immediate downlink to the ground through the VHF network.


The Minimum Detectable Polarization of the HXCP Hard X-ray Polarimeter is 6.2%.


The Operator of the CASA-212-200 aircraft Aircraft is Spanish National Institute for Aerospace Technology (INTA).


The Presentation Date of the GSC Missions Satellite Missions is June 6-7, 2012.


The Operating Frequencies of the SMMR Microwave Radiometer is 6.6 GHz.


The Total Mass of the SILEX Terminal is 150 kg.


The New Orbit Date of the SPOT-4 Satellite is Jan. 29, 2013.


The Eastward Movement of the Band-64 Satellite Instrument is 17.4 km.


The Launch Year of the TerraSAR-X Satellite is 2007.


The Antenna Type of the S-band Transmitter Transmitter is SFL-developed patch antennas.


The Image Scene Length of the Geoton-1 Imaging Instrument is Up to 2000 km.


The Internal Power Lines of the MuREM Radiation Monitor is +1.5V, +3.3V, -5V, ±10V, +20V.


The Sensor Type of the LPT Light Particle Telescope is Light Particle.


The Pixels per FWHM of the Spectrometer Instrument is 1720.


The Operating Modes of the Coronagraph Instrument is "Video mode" for display for the astronauts or TV transmission to the ground.


The Launch Date and Time of the Spaceflight SSO-A: SmallSat Express Satellite is Monday, December 3rd at 10:34 a.m. PST (18:34 GMT).


The Deorbiting Requirement of the IDEA OSG 1 Satellite is IDEA OSG 1 should, after termination of its mission, attempt to deorbit in order to meet the 25 year debris mitigation guideline.


The Failure Cause of the S-band antenna Antenna is Lightning strikes.


The Circumstellar Gas Disk of the HD 172555 Star is Contains Exocomets.


The Solar Panels Lifespan of the InSight Mars Lander is Over four years.


The Type of the Terminator Tape Deorbit Module Deorbit Device is Passive de-orbit device.


The Swath Width of the SAR Synthetic Aperture Radar is 100 km.


The Launch Date of the ST5 Satellite is 22 March 2006.


The SAR Payload Polarization of the RCM Satellite is Hybrid polarimetry.


The Background of the NICER X-ray timing instrument is < 0.2 counts/s.


The Mission Status Date of the James Webb Space Telescope Space Telescope is Dec. 5. 2012.


The Mass of the Dove-2 Nanosatellite is ~ 5.8 kg.


The Largest Feature Size of the Eureca Satellite is 2 mm hole in the ESA/ERNO logo plate.


The Design Life of the Chang'e-4 lunar probe Lunar Probe is Three years.


The Manufacturer of the CubeSat power module Power Control is Clyde Space Ltd.


The Launch Vehicle of the NeuSAR Satellite is ISRO Indian Polar Satellite Launch Vehicle.


The Purpose of the HARP-2 Instrument is Improve OCI measurements.


The Launch Site of the Aeolus Spacecraft is Kourou, French Guiana.


The Data Processing Center of the Satellite GFO is POC (Payload Operations Center) located at NavOceano (Naval Oceanographic Office).


The Size of the APL’s Frontier radio Radio is Smaller than other deep-space radios.


The Bandwidth of the OCM Payload is Not specified.


The EMC Qualification Date of the Instrument Satellite Instrument is Summer 2021.


The Measurement Target of the OCO-3 Spectrometer is Sunlight reflected off the Earth's surface.


The Data Collection of the Aqua Satellite is Cloud formation, precipitation, radiative properties, air-sea fluxes of energy, carbon and moisture, sea ice concentrations and extents.


The Weight of the HET-X Hall-effect Thruster is Less than 2 kg.


The Redundancy of the EPS Electrical Power System is MPPT system and regulators had been duplicated.


The Quantity of the Propulsion Tanks Spacecraft Component is 2.


The Propellant of the GPIM Propulsion System is AF-M315E advanced green monopropellant.


The Time Lost for Maneuvering of the Telescope Observation Equipment is Significant for tens of thousands of satellites.


The Bandwidth of the SCM Instrument is 10 Hz-8 kHz.


The Radar Antenna Length of the Spacecraft Satellite is 16 m.


The Contributions of the Cluster Satellite is Measurements of electric currents in space, revealed the nature of black aurorae, discovered plasma waves.


The Image Acquisition Date of the DSCOVR Satellite is June 3 and June 4.


The Implementation of the SIM Simulator is ESA SIMULUS Simulation framework.


The Mass of the RCU Radiometer Calibration Unit is 2.3 kg.


The Program Date of the COSMO-SkyMed Satellite is May 18, 2001.


The Attitude Control of the CNAPS Propulsion System is 5º (3σ).


The Validation Data Source of the CYGNSS Satellite is SFMR.


The Spectroscopy of the RHESSI Imaging Instrument is Up to γ-ray energies of about 17 MeV.


The Format of the Detector E2V CCD-22 (Frame Store) is 600 x 600 pixels.


The Power Consumption of the MCU Microcontroller Unit is 65 mA - active.


The First Stage Booster Flights of the Falcon-9 Rocket Rocket is 3.


The Launch Date of the FY-3 (FengYun-3) Satellite is Sep 10, 2023.


The Upgrade Duration of the Voyager 2 Spacecraft is About 11 months.


The Size of the Canberra DSN station Antenna is 70-meter.


The Azimuth Resolution of the Radar Sensor is 1500 m.


The Ground Segment of the CO2Image Satellite is Earth Observation Centre (EOC).


The Launch Vehicle of the CubeSat - Launch 4 Satellite is Dnepr.


The Observation Date of the Perseus Satellite is 29 October 2018.


The Calibration Approach of the Sentinel-1 Satellite is In-orbit.


The Function of the µCPT Spectrometer is Measure radiation flux.


The Size of the NanoSatC-Br1 CubeSat is 1U.


The Purpose of the Euclid Space Telescope is Measure the shapes and distances of billions of galaxies.


The Optical Configuration of the ELVIS Spectrometer is Czerny-Turner.


The Host of the OSIRISv3 Instrument is ISS.


The Output Short Circuit Protection of the DC-DC converter Power Converter is Yes.


The Design of the MAG Instrument Magnetometer is "Dual mag" implementation of two identical racetrack magnetometers on a 6-meter boom.


The Image Content of the LROC Camera is Earth and moon.


The Mission Ground Segment of the Ground Segment Communication is CLS network.


The Test Date of the James Webb Space Telescope Space Telescope is Summer 2014.


The Antialiasing Filter Cut-off Frequency of the Rx Module Digital Receiver is 18 MHz.


The SAR system of the Payload Satellite Payload is Nominal operations, no redundancy.


The Image Acquisition Date of the MODIS Instrument is May 5, 2022.


The Velocity Before Engine Shutdown of the Schiaparelli Lander is Nearly 270 km/h.


The Sensor System of the EPI-Hi Particle Measurement Instrument is Ion-implanted silicon SSDs.


The Subsystems of the CrIS Optical System is Step and settle two-axis scene selection module with image motion compensation capability, full-aperture internal calibration source, large-aperture Michelson interferometer, three-element all reflective telescope, cooled aft optics module, multiple-stage.


The Swarm Size of the Desert Locusts Insect is 40 million locusts.


The Central Wavelength of the Spectrally modified current sounder Sensor is 8.5.


The Calibration of the Suomi NPP VIIRS Satellite is Unknown.


The Power Experiment Conditions of the Scientific Payload Satellite Payload is Adequate Solar Illumination.


The Authors of the Wide-Field Imager for Solar Probe+ Imager is Angelos Vourlidas, Russell A. Howard, Simon P. Plunkett, Clarence M. Korendyke, Michael T. Carter, Arnaud F. R. Thernisien, Damien H. Chua, Peter Van Duyne, Dennis G. Socker, Mark G. Linton, Paulett C. Liewer, Jeffrey R. Hall, Jeff S. Morrill, Eric M. DeJ.


The Optical Cavity Layout of the GEDI Laser Laser is 22 bounce slab and a GRM.


The Onboard Means of the Internal Calibration Calibration is Matched loads in each of the receivers, Centralized noise source/network on the hub, Distributed noise sources/networks in the arms, Fringe wash function in the CCU.


The Spatial Resolution of the Earth Radiation Budget Experiment (ERBE) Instrument is 20 km at nadir.


The Control Center of the Aeolus Spacecraft is ESA's ESOC (European Space Operations Center) in Darmstadt, Germany.


The Angular Resolution of the JEM-X X-Ray Monitor is 3 arcmin.


The Redundancy Type of the Computer System Fault-Tolerant System is Cold redundant.


The Speed of the Reconnecting Jets Plasma Phenomenon is Up to 100 kilometers per second.


The Mission Life of the Spacecraft Satellite is 1 year min (2 year goal).


The Strongest Winds of the Tropical Cyclone Nathan Cyclone is 40 knots.


The Manufacturer of the GomX-4B Satellite is GomSpace in Denmark.


The Band 6 of the Landsat TM Satellite is Plant heat stress, thermal mapping, soil mapping.


The Instrument Mass of the SBVR Power Supply is 54.5 kg.


The Type of the Antennas Communication is Microstrip.


The Location of the SPIRE Instrument Control Center is RAL (Rutherford Appleton Laboratory, Didcot, UK.


The Establishment Date of the GMES Initiative is 1998.


The Mission Goals of the Sentinel-6 Michael Freilich Satellite is Gather data for atmosphere information, climate change, and environment monitoring.


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


The Communication of the CAPSTONE Satellite is Two-way, coherent range and Doppler measurements.


The Orientation of the Burroughs Crater Crater is North is up.


The Student Collaboration Goal of the IMAP Mission is Contributes to diversifying space science.


The Mass of the CubeSats Satellite is 14 kg.


The Orbit Position of the GCOM-W1 Satellite is International A-Train orbit.


The Launch Date of the ExoMars Mission is September 2022.


The Ground Station-pointing Mode Downlink Data Rate of the S-band system Communication System is Up to 204 MB/day.


The Parasitic Bias of the Keithley 6430 Femtoammeter is <1 mV.


The Number of Magnetometers of the FIELDS suite Sensor Suite is 3.


The Plasma Instrument Status of the Voyager 1 Spacecraft is Damaged during a fly-by of Saturn.


The Distance from Earth of the New Horizons Spacecraft is More than 5 billion miles.


The Total Mass of the IMS-2 Instrument is 199 kg.


The Resolution Time of the LAP Instrument is < 2 minutes.


The Launch Date of the SARAL Satellite is 25 Feb 2013.


The Data Input Interface of the Modem Processor Signal-Processing Chain is SpaceWire over LVDS (Low Voltage Differential Signaling) link.


The Latency Requirement of the S-3 NTC Product is Within 28 days.


The Antenna Type of the CTAGS Antenna Array Antenna Array is Patch antennas.


The Overview of the Aditya I Satellite is URL: http://www.iiap.res.in/meet/sol2011/sol_ppt/RPrasad.pdf.


The Spectral Range of the SOSP Satellite is 170 - 3200 nm.