The Lock Establishment Time of the STEREO-B Satellite is 6:27 p.m. EDT.


The Image Resolution of the DEIMOS-2 Satellite is 0.75 m per pixel.


The Flight Preparation Contributors of the SAPPHIRE Satellite is Students at Washington University (WU) in St. Louis, MO.


The Average Power of the 4-band CCD Imager Instrument is 6 W.


The Manufacturer of the Torque Rod Attitude Control Device is SSTL.


The Band Frequency of the MicroWave Humidity Sounder-2 Sounder is 118 GHz.


The Wind Measurement of the InSight Spacecraft is Continuous.


The Number of Load Cells of the Truss Structure is 6.


The | of the Zhongkan Tang, Rakhitha Chandrasekara, Yue Chuan Tan, Cliff Cheng, Kadir Durak & Alexander Ling Authors is | False.


The Control Method of the ADCS Attitude Determination and Control Subsystem is Magnetic torque coils (magnetorquers).


The Conference Date of the Solar Orbiter Mission is Oct. 14-17, 2008.


The Operational Modes of the MIRAS Instrument is Dual-polarization mode, Full polarimetric mode, Calibration modes.


The Antenna Diameter of the DORIS Instrument is 160 mm.


The Z Accuracy of the Planimetric Accuracy Assessment Assessment is <0.3 m.


The Battery Type of the EPS Electric Power Subsystem is 2 x 66 Ah Li-ion batteries.


The Spectral Resolution of the SOSP Satellite is 1 nm in UV/VIS, 20 nm in IR.


The Solar Wings Span of the Satellite Spacecraft is 25 m.


The Launch Date of the AstroSat Satellite is Unknown.


The Bus Type of the DSP satellites Satellite is CAST968.


The Launch Vehicle of the Galileo Satellite Constellation is Ariane 5.


The Expansion Rate of the Universe Cosmological Entity is Accelerating.


The Additional Experiments of the Kounotori H-II Transfer Vehicle is Upgrade to the Cell Biology Experiment Facility (CBEF-L), a small-sized satellite optical communication system (SOLISS), and a payload for testing the effects of gravity on powder and granular material (Hourglass).


The FPGA of the OBC On-Board Computer is Radiation-hardened.


The Data Fusion Center of the Satellite GFO is ADFC (Altimeter Data Fusion Center) also located at NavOceano.


The Pointing Stability of the Spacecraft Satellite is 0.3 arcsec/s.


The Orbit Type of the Unicorn-2L, -2M and -2N Satellites is Low-Earth.


The Image Capture Date of the DESIS Instrument is 29 November 2019.


The Phosphine Upper Limit of the Mars Planet is Unknown.


The Quantity of the S&F antennas Communication is 4.


The Width of the Large Space Simulator (LSS) Vacuum Chamber is 10 m.


The Pulse Width of the Laser Instrument is 1~999 µs.


The Alignment and Testing of the NIRSpec Filter and Grating Wheel Assembly Space Mechanism is Unknown.


The Launch Contract Date of the Muninn Satellite is Early 2023.


The VHF Band Frequency of the RF Communications Communication Subsystem is 144 MHz.


The Description of the Gravitational Lensing Method Space Exploration Tool is Photons deviate from the rectilinear direction when passing near a massive body under the influence of its gravitational field.


The Instruments of the GPM Constellation Satellite Constellation is Radiometers.


The Objective of the NanoSatC-BR Satellite is Provide monitoring of Earth's magnetosphere by measuring the magnetic field over Brazil and to study the magnetic phenomena of the SAA (South Atlantic Anomaly) and the EEJ (Equatorial Electrojet).


The Prime Developer of the Laser Transmitter Laser is Selex Galileo.


The Provider of the ODTML Data Collection System is ONR (Office of Naval Research).


The Downlink Capacity of the Bartolomeo Payload Communication System is Up to 1 GB per day.


The Type of the OCI Instrument is Hyperspectral radiometer.


The Locations of the IOT Stations Ground Station is Redu, Belgium and Chilbolton, UK.


The Electronic Unit Mass of the Instrument Sensor is 2.82 kg.


The Swath Width of the ALT Experiment Altimeter is Varies from 2.4 to 12 km.


The ELF Signal Energy of the QuakeSat Satellite is Between 10 Hz and 150 Hz.


The SIS/URE of the QZS-1 Satellite is 34 cm (rms).


The Mission Status of the NeuSAR Satellite is Operational (nominal).


The Application Fields of the HJ-1 minisatellite constellation Satellite Constellation is Environmental monitoring and prediction, solid waste monitoring, disaster monitoring and prediction (flood, drought, typhoon and wind damage, sand storm, earthquake, landcreep, frost and grassland fires, coal fires, crop pest monitoring, ocean disaster mo.


The Flare Class of the IRIS Observatory is X-class.


The Fine-Pointing Range of the GT Fine-Pointing Error Signal Provider is Approximately 70 arcsec.


The Launch Date of the Orbiting Carbon Observatory-2 Satellite is Unknown.


The Orbit of the Kestrel Eye-2M Microsatellite is Near the ISS.


The Data Download Capacity of the GimmeRF Radio Instrument is About 10 Mbit per orbit.


The Announcement Date of the New Method Process is 20 July 2021.


The Calibration of the Advanced Land Imager Imaging Device is Spatial.


The Eccentricity of the Satellite Communication is 0.0024.


The Antenna Type of the Eutelsat Quantum Satellite is Electronically steerable.


The Frequency Conversion of the Microwave Assembly Signal Processing Device is 24 and 32 GHz.


The Side Panel Thickness of the ESTCube-1 & -2 CubeSat is 1 mm.


The Search Coil Length of the ULF Sensor Sensor is 20 cm.


The Al Shielding Thickness of the RADFET Dosimeters Dosimeter is 165 µm.


The Capability of the AeroCube-4 Satellite is Can slew and maintain pointing at a specific ground target.


The Nominal Rate of the S-band Uplink Communication System is 16 kbit/s.


The Launch Date of the SPARCS Satellite is Not earlier than October 2021.


The Function of the Digital Beam Forming (DBF) Application is Wide swath imaging and ambiguity suppression.


The Type of the SPOT-6 Satellite is Optical imaging specialist.


The Wavelength of the Responsivity Measurement Instrument is 1064 nm.


The Field of View of the Star Tracker Optical Sensor is 2º x 2º.


The Stabilization Rate of the FORTE Spacecraft is 1 Hz.


The Cross-track FOV of the TIR Subsystem Imaging System is ±11.5º.


The Power Source of the CubeSats Satellite is Does not require any extra power from the rocket.


The Orbital Period of the Suomi-NPP Satellite is 101 minutes.


The Orbital Phase of the Sentinel-1A and Sentinel-1B Satellites is 180º.


The Ride Capability of the CubeStack Multi CubeSat Adapter is Tertiary canisterized.


The Presentation Date of the Delfi-n3Xt Nanosatellite is Sept. 29 to Oct. 3, 2008.


The Science Objectives of the SAGE-III Instrument is Characterize tropospheric and stratospheric aerosols and upper tropospheric and stratospheric clouds.


The Frequency Bands of the Antenna for Navigation Antenna is L1/L2.


The Data Rate of the Uplink Communication System is 1 kbit/s.


The Interaction in Atmosphere of the Neutrons Radiation is Absorption by nuclear reactions, decay, Earth albedo neutron flux.


The Speed of the Proximity Flyby Maneuver is 800 m/day.


The Accuracy of the SeaWinds scatterometer Scatterometer is 2 m/s.


The Design Purpose of the CrIS Optical System is Provide an optimum combination of optical performance and compact packaging.


The Average Download Capacity of the Panama ground station Ground Station is 1.2 GB/day.


The Orbit Placement Date of the Galileo 2nd Generation Satellites Satellite is End of 2024.


The Data Availability of the Landsat 7 ETM+ SLC-off and Landsat 5 TM Satellites is New global acquisitions July 2008.


The Image Resolution of the Visual Sensor Array Sensor Array is 13376 x 10000 pixels.


The Size of the PSat-2 Satellite is 1.5U.


The Positive and Negative of the Tether Charging Modes Test Procedure is Both positive and negative tether charging modes will be tested during this phase.


The Expected Operation Duration of the MASCOT Lander is Approximately 16 hours.


The FWHM at 80 nm of the EUV Simulation Simulation is 7 arcmin.


The Capability of the iADCS100 Attitude Determination and Control System is Precisely pointing and slewing a 3U CubeSat.


The Electric Field of the FSU Faraday Cup Sensor Unit is Set up between the modulator grid and the adjacent ground grids.


The Measurement Detailed of the VHRR Instrument is Precipitation intensity at the surface (liquid or solid), Cloud type, Land surface imagery, Upward long-wave irradiance at TOA, Earth surface albedo, Land surface temperature, Sea surface temperature, Wind profile (horizontal).


The Project Start Date of the Argos-3 Onboard Instrumentation is 1997.


The Ballistic Coefficient of the PUNCH Mission Satellite is Increased by adding ballast.


The Requirements of the KE Ground Station Ground Station is Enable the user to easily choose a target of interest (point-and-click) and receive the satellite image during the same satellite access time (pass).


The Detection of the MOMA Instrument is Direct detection of indigenous martian organic molecules and some thermally released inorganic molecules or laser-desorbed fragments of inorganic minerals.


The Overview Seminar of the Gravity Probe B Satellite is June 17, 2009.


The Video Capabilities of the Carbonite Series Small Satellite Platforms is High-performance.


The Payload Capacity of the Super Strypi launcher Launcher is 300 kg.


The Retrieval Date of the EURECA Satellite is June 21 - July 1, 1993.


The Manufacturer of the Canadarm-1 Remote Manipulator System is Canadian Space Agency.


The Spectral Bands of the TrueColour Imager Optical Imager is 9 bands.


The Assembly Location of the BRITE Satellites Satellite is Space Research Center in Warsaw.


The URL of the Galileo Satellite Navigation System is https://www.esa.int/Applications/Navigation/406_Day_celebrating_Galileo_saving_lives.


The Mass of the Dove-1 Nanosatellite is ~ 5.8 kg.


The Fairing Recovery of the Falcon 9 Rocket is Two recovery vessels were dispatched to sea to retrieve the fairing halves from Tuesday night’s mission.


The Operations Manager of the GOES-O Satellite is National Oceanic and Atmospheric Administration (NOAA).


The Components of the PMS System is TPU (Thermal Power Unit) and MMU (Memory Management Unit).


The Program of the TacSat-3 Satellite is ORS (Operational Responsive Space).


The Communication Relay Terminals of the Pléiades-Neo satellites Satellite is Tesat Spacecom laser.


The Calibration Steps of the Detector Calibration Process is Apply bad pixel map, followed by gain and offset correction to flat-field the sensor output.


The Orbit Inclination of the Odin Satellite is 97.77º.


The Operational Altitude of the GNOMES-1 Satellite is 650 km.


The Quantity of the Flock-4v CubeSats is 14.


The Main Detector of the GRS Gamma-Ray Spectrometer is 12 cm diameter x 7.6 cm long CsI (Tl) crystal.


The Coronal Mass Ejections Observed of the SOHO Satellite is More than 20,000.


The Angular Resolution of the IMAP-Ultra Instrument is Comparable or better angular resolution than IMAP-Hi.


The Band 6 of the R3 Sensor Sensor is Green.


The Inclination of the Yubileyniy-2/MiR Satellite is 82.5º.


The Launch Date of the New Horizons Spacecraft is January 19, 2006.


The Concentration Range of the DE probe Charged Particle Probe is 10^4 - 10^7 cm^-3.


The Spectral Resolution of the Spectrometer Spectrometer is <1.25 cm -1.


The Mission End Date of the Deep Space 1 Satellite is Unknown.


The Detector Unit of the DOSTEL Radiation Detector is Five silicon sensors.


The Launch Mass of the Satellite Communication Satellite is ~5.8 tons.


The S-band Usage of the CBERS-2B Satellite is TT&C services.


The Levels of the CSI Data Communication is 4.


The Rocket Weight of the Chang'e-5 Lunar Mission is 870 metric tons.


The Types of the RFI Sources Interference is In-band emissions, Excessive out-of-band emissions, Spurious emissions.


The Number of Deployable Subsatellites of the EAGLE Spacecraft is 1.


The Launch Date of the GOES-T Satellite is March 2022.


The Launch Date of the Sentinel-3A Satellite is Unknown.


The Publication Year of the Case studies of aerosol retrievals Study is 2002.


The Development Start Date of the BDS Satellite is 1990s.


The Calibration Images of the PROBA-V Satellite is 2.622.


The Data Transmission Protocols of the ETS-VIII Spacecraft is CCSDS.


The Output Power of the RF communications Communication System is ~ 1W.


The Moving Parts of the LORRI Imaging Instrument is No.


The First Stage Landing Location of the Falcon 9 Rocket is Atlantic Ocean.


The Propellant of the Busek’s miniaturized electric thrusters Propulsion System is Iodine.


The Launch Date of the Galileo Second Generation (G2) Satellite Constellation is 31 December 2024.


The Detector Type of the Camera Imaging Device is CMOS.


The Measurement Objective of the EPISEM Instrument is Measure the omnidirectional integral flux.


The Maximum Temperature of the Xenon Gas Tank Propellant Storage is 50ºC.


The Presentation Date of the NANOSATC-BR Cubesat Program Satellite Program is Oct. 1-5, 2012.


The Internal Data Storage of the RAMIS Radiation Detector is 2.


The Battery Capacity of the EPS Electrical Power Subsystem is 108 Wh.


The Exposures per Field of the Euclid Reference Survey Survey is 4.


The IFOV of the AVHRR/3 Instrument is 1.1 km at nadir.


The Battery pack capacity of the EPS Electric Power Subsystem is 3.6 Ah.


The Instrument Types of the Instruments EO is Multiple direction/polarisation radiometers, Imaging multi-spectral radiometers (vis/IR), High resolution optical imagers, Earth radiation budget radiometers, Atmospheric chemistry.


The Booster Reuse of the Falcon 9 Rocket is 7 trips to space and back.


The Instrument Power of the HySI Hyperspectral Imager is 16 W.


The B/H of the Instrument Satellite Instrument is 0.57.


The Number of Satellites of the Spire Satellite Constellation is Over 100.


The Data Applications of the NISAR Satellite is Monitoring of agricultural biomass, assessing disasters, studying snow and glaciers, studying Indian coastal and near-shore oceans.


The Touchdown Time of the Philae Lander is 17:25:26 GMT.


The Maximum Upper Band Edge of the Pan (WorldView-1) Imager is 900 nm.


The Binary Star Catalogue of the Gaia Satellite is More than 800 thousand binary systems.


The Accuracy of the SubWave Underground Geolocation System is 10m.


The Time Resolution of the Particle Detector Instrument is 1 s.


The Area of the X-ray Satellite Navigation Navigation System is 2000 cm2.


The Signal Health of the Galileo Satellite Navigation System is 97.33%.


The Effective Focal Length of the Telescope Optical Instrument is 1150 mm.


The Image Sensor Resolution of the Wide-angle camera Camera is VGA resolution (640 x 480 pixels).


The Material of the IDA Dewar is Titanium.


The Frequency of the Solar Calibration Calibration is Daily.


The Mass of the UVS Instrument is 3.98 kg.


The Data Stack Height of the Nancy Grace Roman Space Telescope is 330 miles (530 km) high after a single day.


The Location of the TIRA Radar Tracking Station is FGAN site in Wachtberg near Bonn, Germany.


The Owner of the Lemur-2 Satellite is Spire Global.


The Pupil Diameter of the Telescope Optical Instrument is 75.6 mm.


The Type of Array of the SWIR Detector is HgCdTe.


The Detector Quantity of the TIR Subsystem Imaging System is 10.


The Measurement Error of the Acceleration Sensor is Random <0.1 G (1σ), Bias < 0.25 G, Nonlinearity < 2%.


The Transmission Speed of the KIZUNA Satellite Communication Technology is 3.2 Gbit/s.


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


The GPS/UTC Accuracy of the Data Handling Subsystem Subsystem is 100 µs.


The Mass Resolution of the INMS sensor Ion Mass Spectrometer is The mass resolution is limited by uncertainties in energy dispersion, time resolution and time of flight path.


The Solar Panels Power Generation (Average) of the EURECA Spacecraft is 1 kW.


The Partners of the Rosalind Franklin Rover is ESA and the Russian State Space Corporation, Roscosmos.


The Efficiency of the 28 V Regulator Regulator is 93%.


The Orbital Altitude of the Swarm-A (Alpha) Satellite is ≤ 460 km.


The Profiles Per Day of the FormoSat-3 / COSMIC mission Satellite Mission is 1,600~1,800.


The Stated Capabilities of the Honeywell Sensor Sensor is Unknown.


The Orbital Slot of the GSAT-0103 Satellite is C04.


The Orbit of the Sentinel-1C Satellite is Sun-synchronous orbit with an altitude around 690 km.


The Incidence Angle Range of the SAR Synthetic Aperture Radar is 32º at the near range and 38º at the far range.


The Sensor Update Date of the ROCSat-1 Satellite is Unknown.


The Exploration Start Date of the Cluster Satellite Constellation is July 1, 2015.


The Prize Amount of the Google Lunar X-Prize Competition is $20 million.


The Potential of the ORS Office is Rapidly fly a spare replacement instrument to provide continued temporal measurements.


The Periherm of the MMO Spacecraft is 400 km.


The Purpose of the European Service Module Spacecraft Module is Propel NASA’s Orion spacecraft to the Moon.


The Dimensions of the TEP Absorber 1 Absorber is 5.4 cm cylinder.


The Bandwidth of the FIELDS suite Sensor Suite is 20 MHz.


The Launcher of the Sentinel-1B Satellite is Soyuz-STA/Fregat vehicle (VS 14) of Arianespace.


The Science Objectives of the TROPICS Constellation of CubeSats is Relate the occurrence of intense precipitation cores (convective bursts) to storm intensity evolution.


The Response Time of the Pleiades-1A Satellite is Within four hours.


The Atmospheric Penetration Depth of the GNSS-RO Instrument Instrument is Greater than other radio occultation instruments.


The Departure Date from MSSS of the ShadowCam Instrument is 13 August 2021.


The Data Collection of the Radar Altimeters Instruments is Monitor ocean surface topography.


The Orbit Altitude of the SpaceX CRS-17 Mission is ~ 400 km.


The Mass of the Star Tracker Attitude Determination Device is ~90 gram.


The Current of the Voltage 1 Power Amplifier is 1000.


The Launch Date of the ISS:LIS Lightning Imaging Sensor is 19 Feb 2017.


The Payload of the Falcon 9 rocket Rocket is Spain’s PAZ satellite.


The Size of the PAN Camera Imaging Device is 150 cm x 850 cm x 100 cm.


The Lunar Calibration Frequency of the Satellite Imaging Satellite is Monthly.


The Launch Year of the TanDEM-X Satellite is 2010.


The Deputy Project Scientist of the OCO-2 Satellite is Annmarie Eldering.


The Mission Goal of the ExoCube Satellite is Measure the densities of all significant neutral and ionized atom species in the ionosphere.


The Launch Site of the Deployment Systems Satellite is Dombarovsky Missile Site, Yasny.


The Mounting Height of the Panoramic Camera system Camera is 2 m above ground level.


The Microcontroller RAM of the On-board Computer Computer is 1 MB.


The Measurement Parameters of the TROPICS CubeSat Satellite is Temperature, Humidity, Precipitation.


The Function of the NGA Organization is Ensures safety of navigation in the air and on the seas.


The SSS Temporal Sampling Period of the CIMR Radiometer Imager is Once per month.


The Data Quantization of the WV60 imager Imaging System is 11-bit.


The Installation Location of the EMIT Satellite is International Space Station.


The Air Traffic Volume Scenario of the Model Atmospheric Model is 10 times higher than actual.


The Ground Resolution of the InSb Detector is 30m.


The Ground Range Resolution of the Radar Sensor is Approximately 250 m.


The Orbital Period of the Solar Orbiter Satellite is 3:2 resonance with Venus.


The Image Credit of the CanX-7 nanosatellite Nanosatellite is UTIAS/SFL.


The Partner of the ROSA Roll-Out Solar Array is Deployable Space Systems.


The Spectral Resolution of the DMC-3 Satellite Constellation is Four bands.


The Primary Mission Status of the OPAL Satellite is Successful.


The Deployment Status of the PhoneSat 2.5 Satellite is Successful.


The Launch Date of the EuTEF European Technology Exposure Facility is Feb. 7 2008.


The Design Life of the Iridium NEXT bus platform Satellite Bus is 12.5 years.


The Civil SAR System of the SAR spacecraft Satellite is First of China.


The Bandwidth of the Channel 5 Sensor is 1000 MHz.


The Mass of the HI-SCALE Instrument is 5.8 kg.


The IEEE Transactions on Geoscience and Remote Sensing of the SAMPEX Satellite is Vol. 31, No. 3, May 1993, pp. 531-541.


The Number of Satellites of the OneWeb Satellite Constellation is 322.


The Responsivity Requirement of the Responsivity Measurement Instrument is >0.47 A/W.


The Presentation Date of the SWIM Scatterometer is Sept. 23-27, 2013.


The Power Consumption of the STAFF/DWP Instrument is 4.5 W.


The Diameter of the Focal Plane Optical Instrument is 11.23 mm.


The Actuation of the OceanSat-2 Satellite is Four reaction wheels in a tetrahedral configuration, two magnetic torquer coils and monopropellant hydrazine thrusters.


The Wavelength of the SOTA Satellite is 1.5 µm.


The Position of the Side-Looking Camera Device is Right Side.


The Relative Aperture of the Lenses Optical System is 1/10.


The Solar Panel Power of the Canopus Pipper Satellite is 15 W.


The Thruster Burn Arcs of the BepiColombo Spacecraft is 22.


The Sample Transfer Date of the Chang'e-5 Spacecraft is Around Dec. 15-16.


The Peak Daily Acquisition Capability of the COSMO-SkyMed Satellite Constellation is 10 minutes of continuous operation in Stripmap or ScanSAR modes or alternatively 20 spotlight images.


The Power System of the GNB Satellite is Direct energy-transfer.


The Spacecraft Size of the TCS Thermal Control System is 64.7 cm diameter, 40.3 cm height.


The Vertical Separation of the TanDEM-X Satellite is Achieved by a relative shift of the eccentricity vectors of the satellites.


The Total Mass of the FOTINO Capsule is 6 kg.


The Imaging Date of the OPS-SAT Satellite is 14 August 2020.


The Test Service Start of the OneWeb Satellite Constellation is Late 2021.


The Navigation Signal Bandwidth of the Spacecraft Satellite is 3 bands (E5, E6, L1).


The Resolution of the Optical Satellite Satellite is 0.5 m GSD.


The Revisit Capacity of the Pléiades Neo Satellite is Twice.


The Pan-Sharpening Capability of the Hyperion Spectral Instrument is 10 m.


The Launch Date of the Tatiana-2 Satellite is 17 September 2009.


The Launch Date of the LDEF Satellite is April 6, 1984.


The Data Rates (Downlink) of the RF Communications Communication System is 9.6 kbit/s.


The Launch Date of the ROCSat-1 Satellite is Unknown.


The Link Performance of the Alphasat TDP1 GEO-relay is More than 200 successful links.


The Structure of the S/C Satellite is Cube (60 cm x 60 cm x 60 cm).


The Spotlight Scene Size of the SAR Antenna Antenna is 5.5 km side.


The Power Range of the Small-GEO Satellite is 2.5 kW to 7.5 kW.


The Definition of the Signal to Noise Ratio (SNR) Performance Metric is Commensurate with the overall uncertainty required by the application and its observational characteristics.


The Pointing Requirements (Control and Stability) of the Aquarius Radiometer System is 0.5º.


The Mass of the Spacecraft Satellite is 138 kg.


The Power On Date of the Carmen-2 Instrument is June 22, 2008.


The Launch Date of the Glory Satellite is March 4, 2011.


The Detector Elements of the Imager Satellite Instrument is 8.


The Data Reception of the DRS Data Reception Station is Real-time and playback from the onboard memory.


The Development Team of the BeaverCube CubeSat is Undergraduate and graduate students at the Massachusetts Institute of Technology.


The Orbit Altitude of the BRO-4 Satellite is 551 km.


The Expected Parameter Measurement of the CDE Sensor is Cosmic dust influx, PMC nucleation sites.


The URL of the Arctide2017 Tidal Model is https://tinyurl.com/y2axpw8c.


The Focal Length of the Instrument Spectrometer is 65 mm.


The URL of the SOLSPEC Spectrometer is http://lasp.colorado.edu/sorce/workshops/09_19_06/pdf_presentations/14_Thuillier_SOLSPEC-ISS.pdf.


The Mode of the SAR Sensor Subsystem SAR Sensor is WS (Wide Swath).


The Funding of the IceCube Radiometer is Co-funded by ESTO (Earth Science Technology Office).


The GSD of the Iris Video Camera Camera is Resampled to 1 meter.


The Usage of the TacSat-4 Satellite is SATCOM between many platforms.


The Coverage of the Predictive Avoidance Request Message Product is Next few days of laser activity by the LCRD payload optical terminal.


The Launch Year of the Kent Ridge 1 Microsatellite is 2013.


The Displacement between Exposures of the Euclid Reference Survey Survey is 100 arcsec.


The Launch Vehicle of the OrbView-2 Satellite is Pegasus XL rocket.


The Energy Measurement Range for Nuclei of the Telescope 3 Telescope is 20-500 MeV/n.


The Measurement Coverage of the CryoSat-2 Satellite is Arctic.


The Purpose of the Proving Ground Space is Practice with, innovate on, and demonstrate the technologies and capabilities needed to send humans to Mars.


The Aperture Dimension of the Radar Radar is Approximately 1.5 m.


The Time Resolution of the MAG Magnetometer is ≤0.1 s.


The Launch Date of the PISAT nanosatellite Nanosatellite is July 2016.


The Capacity of the Battery Power Source is 40 Ah NiCd.


The Inclination of the Explorer 36 Satellite is 105.8º.


The Engineering Model Availability of the EDR-2 European Drawer Rack is Available at CADMOS.


The Proposed Doubleheader Launch Time of the Falcon 9 Rocket is Less than four and a half hours apart.


The Development Completion Date of the S-band SAR Synthetic Aperture Radar is March 9, 2021.


The | of the Poker Flat Incoherent Scatter Radar Radar is Initial results from Poker Flat Incoherent Scatter Radar (PFISR).


The Altitude of the SEOSAT-Ingenio Satellite is 670 km.


The Data Storage of the Instrument Photometer is On the spacecraft.


The Apogee (km) of the Meteor-1-1 Satellite is 713.


The Thickness of the IS Diaphragm is 0.5 mm.


The Mass of the Spacecraft Satellite is < 2 kg.


The Swath Width of the OLS Imaging Sensor is 2960 km.


The Measurement Domain of the CHORUS Satellite Constellation is Ocean, Land, Snow & Ice.


The Camera Resolution of the Change-2 Satellite Satellite is One Meter.


The Inclination of the INTEGRAL Satellite is 52.246º.


The J2000 right ascension (deg) of the J1846-0258 Pulsar is 281.60392.


The Data Depth of the Infrared Sensors Sensor is 8 bit.


The Image of the Day Date of the NASA Earth Observatory Satellite is 11 May 2022.


The Effect of the Hysteresis (Memory) Material Attitude Control is Provides the needed damping effect to stabilize KySat-2 on the two control axes, and resist changes on the uncontrolled axis as well.


The SAR Measurements Grid Resolution of the L2SMA Soil Moisture Product is 3 km EASE-2.


The Fundraising of the Irazú CubeSat Satellite is Aluminum plate is placed on one of the sides of the CubeSat and another one inside of the spacecraft for fund-raising purposes.


The Batteries of the IRIS spacecraft Satellite is Spares from the GRAIL program.


The Date of the MC3E Field Campaign is April 15 -June 1, 2011.


The Optical Imager of the DebriSat Satellite is 1.


The Antenna Gain (dB) of the Antenna Reflector is >37.


The Wind Speed of the Calf Canyon-Hermits Peak fire Fire is 65 miles (105 km) per hour.


The Cooling Method of the SWIR Detectors Detector is Cryocooler.


The Launch Vehicle of the HTV Spacecraft is H-IIB.


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


The Function of the SLCPE Instrument Unit is Controls all subsystems and manages the data interface with the satellite.


The Land-Mobile Service Providers of the Iridium Certus(SM) Broadband Service is True.


The Uplink Receivers of the UoSAT-12 Satellite is 5.


The Flash Brightness of the OJ 287 galaxy Galaxy is Brighter than a trillion stars.


The Resolution of the NewMag Magnetometer is 16 bit (±0.2 nT).


The Ground Stations of the GimmeRF Radio Instrument is Puerto Rico, Florida, Texas, California, Hawaii, and Guam.


The Observation Record of the Landsat-9 Satellite is Last half-century.


The Inertial Measurement Unit of the ADCS Attitude Determination and Control System is 1.


The Project Partners of the SIR-C/X-SAR Payload is NASA/JPL, DARA/DLR, and ASI (Agenzia Spaziale Italiana).


The Orbit of the DELPHINUS Satellite is Halo orbit around the EML2.


The Quake Magnitude of the SEIS Seismometer is 3.3.


The Purpose of the ISS Power Augmentation (IPA) Mod Kit Hardware is Critical hardware to be installed during the upcoming ISS Roll-Out Solar Array (IROSA) spacewalks, allowing the space station program to continue deploying the upgraded solar arrays.


The Energy Resolution of the SXD and Solar X-ray monitor Detector is ≤ 600 eV at 5.95 keV.


The Satellite Network Provider of the SES Company is True.


The Affiliation of the Michel Sarthou CNES Argos Project Manager is CNES.


The Image Content of the OPS-SAT Satellite is Uninhabited island north of Russia.


The Orbital Altitude of the QuickBird-2 Satellite is 450 km.


The Frequency of the Antenna ADS-B Antenna is 1090 MHz.


The Article Date of the XMM-Newton Satellite is 21 November 2018.


The Launcher of the GPM Core spacecraft Satellite is JAXA.


The Frame Rate of the Iris Video Camera Camera is 30 frames/s.


The Number of Mini-Solenoid Valves of the NCSU Nano ChemSensor Unit is 3.


The Power of the OCM Instrument is 134 W.


The Contract Award Date of the SBSS-1 Pathfinder Satellite is March 2004.


The Image Date of the TWINS Satellite is June 15, 2008.


The Manufacturer of the GPS Receiver Device is Surrey.


The Frequency of the Dark Current Measurements Measurement is Twice a day.


The Launch Window of the Juice Spacecraft is 5–25 April 2023.


The X-band Data Rate of the VRSS-1 Satellite is 190 Mbit/s.


The Contractor of the NigeriaSat-2 Satellite is National Space Research and Development Agency (NASRDA) of Nigeria.


The PI of the ULEIS Spectrometer is G. Mason, U. of Maryland, R. Gold, JHU/APL.


The Image Sensor Resolution of the CMV4000 CMOS Color Detector is 2048 x 2048 pixels.


The Altitude at Checkpoint of the OSIRIS-REx Spacecraft is Approximately 410 feet (125 m).


The Number of Planned Satellites of the HY-2 Satellite is 4.


The Data Authorization of the Satellite GFO is Unconditional (and unclassified) release.


The Spatial resolution of the Optical System Imaging System is 1.1 km.


The Image Resolution of the On-board Image Processing Satellite System is Better than 100 m/pixel.


The Spectral Resolution of the Channels Spectrometer is 0.0002 Å/pixel.


The Development Team of the MiniCOR Instrument is NRL (Naval Research Laboratory), NASA/JPL, the University of Michigan, and JHU/APL (Johns Hopkins University/Applied Physics Laboratory).


The Required Precision of the NO2 Satellite Instrument is 1.00.


The Data Rate of the Instrument General is 600 kbit/s.


The Test Location of the CO2M Satellite is ESA’s Test Centre in the Netherlands.


The Antenna Requirement of the CITRIS Receiver is Unobstructed hemisphere.


The Detector Array Bands of the FTS Fourier Transform Spectrometer is 194-324 µm and 316-672 µm.


The Five-Year Average Arctic Sea Ice Volume of the CryoSat-2 Satellite is Relatively stable.


The Number of Runs of the Monte Carlo Simulation Analysis Tool is 3000.


The Altitude of the ISS Space Station is ~400 km.


The L-band Receivers of the UoSAT-12 Satellite is 2.


The Size of the Planet Orbiting AU Microscopii Exoplanet is About as large as Neptune.


The Swath Width of the AMSR-E Instrument is 1445 km.


The Calibration Method of the Ranging Channel Communication System is Calibration model can be derived from the data of transponder's RF front end, digital processing and the RF back end as well as the delay in the various passive elements in the RF chain such as the diplexer.


The Completeness of the Einstein's theory of gravity Scientific Theory is May be incomplete.


The Sensor Quantity of the ADS Attitude Determination Subsystem is 6 sun sensors.


The Planning Duration of the MOPITT Satellite Instrument is 12 Years.


The Design Options of the Microsatellite Satellite is NFI + STEAM, or a WFI.


The Field of View of the ART-XC Instrument Telescope is 0.3º x 0.3º.


The Geometric Calibration/Validation of the PROBA-V Satellite is Implemented.


The Objective 1 of the EMIT Mission is Deliver a new improved assessment of the heating and cooling effects of mineral dust in the Earth’s atmosphere.


The Ground Sample Distance (GSD) of the GIS Instrument Satellite Instrument is 41 cm for Pan and 1.64 m for MS.


The Mission Operations Location of the Spitzer Space Telescope Telescope is NASA’s Jet Propulsion Laboratory, a division of Caltech.


The Passband of the Instrument Spectrometer is 4 nm.


The Distance from Earth of the HD 93396 Star is 320 light-years.


The Function of the QKD Quantum Key Distribution is Generate private random encryption keys and share them between only two parties.


The Bandwidth of the Channel 3 Sensor is 400 MHz.


The RF output power (max) of the RF communication subsystem Communication is 1 W.


The Demonstration Date of the LIRIS Sensor is March 19, 2014.


The Diameter of the Aluminum Spheres Satellite is 10 cm.


The Affiliation of the Hiroyuki Shindou Unknown is JAXA.


The Bit Error Rate of the LEO-LEO Inter-satellite Link Communication System is < 10-9.


The Conference Presentation Date of the CANYVAL-X Satellite is 28 May - 1 June 2018.


The Latency Requirement of the S-3 NRT Product is Within 30 minutes.


The Telemetry Packet Forwarding of the Delfi-n3Xt Satellite is Worldwide amateur radio community.


The Antenna Type of the MSR Radiometer is Offset Cassegrain-type antenna.


The Observation Duration of the Kepler Telescope is 72 days.


The Entanglement Test Performer of the QUESS Satellite is Chinese team.


The Launch Date of the SPOT-3 Satellite is September 1993.


The Field of View of the HaloSat Satellite is Near 100 square degrees.


The Number of Satellites of the 90-satellite constellation Satellite Constellation is 90.


The Calibration of the MAC Memory System Module is In-orbit radiometric calibration.


The Attitude Control of the Payload Satellite Payload is Pointing Agility.


The Spectral Domains of the Sentinel-4/UVN Instrument is UV (305-400 nm), VIS (400-500 nm) and NIR (750-775 nm).


The Communication of the DCAM3 Camera is One-way to the mother ship.


The Director of the ArgoMoon CubeSat is David Parker.


The Phase A Feasibility Study of the SMOS Satellite is 2000-2001.


The Dimensions of the Instrument Interface Module Interface Module is 90 mm x 95 mm x 12 mm.


The Size of the Nanoracks BlackBox Platform is Locker-sized.


The Journey Duration of the NEA Scout Spacecraft is Approximate two years.


The Measurement Domain of the TUBSAT Satellite is Atmosphere, Ocean, Land, Gravity and Magnetic Fields.


The Transition Date of the Pilot Program Program is CSDA.


The Planet Diameter of the ExoMars TGO Trace Gas Orbiter is 34 arcseconds.


The Data Transmission of the British Antarctic Survey (BAS) Customer is Remote measurement stations.


The Window Spectral Region of the CERES Instrument is 8 - 12 µm.


The Objective of the SWEA Solar Wind Electron Analyzer is Measure the distribution function of the solar wind core and halo electrons from about 1 eV to several keV, with high spectral and angular resolution over practically the full spherical range.


The Stability of the AOCS Attitude and Orbit Control Subsystem is 2 arcmin/s about the Z-axis.


The Detection of the REXIS Spectrometer is Newly flaring black hole in the constellation Columba.


The Workshop Location of the SSETI Express Satellite is Noordwijk at ESA/ESTEC.


The Purpose of the Frontier Software Defined Radio Radio is Communication.


The Microcontroller of the Big Apple board Electronic Board is Controls the operations, power distribution, and data saving.


The Evacuated People of the Calf Canyon-Hermits Peak fire Fire is Thousands.


The Image Acquisition Date of the ALOS satellite Satellite is 29 March 2011.


The Nominal Altitude of the DubaiSat-2 Satellite is 600 km.


The Nominal Mission Duration of the Vega Rideshare Mission Satellite Launch is 1 hour, 44 minutes and 56 seconds.


The Detection Time of the Ground System Communication System is 7 days.


The Data Processing Time of the Ground Segment Ground System is Within an hour.


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


The Aperture Size of the Antenna Communication is 13 m.


The Power of the SILEX Terminal is 130 W.


The Beacon Power of the RF Communication System Communication System is 100mW.


The MCU of the C&DH Command and Data Handling is Freescale MCU (HCSX12).


The Connection of the ICON Satellite is Physical connection between our world and the immediate space environment around us.


The Data Compression of the Instrument Hyperspectral Imager is None.


The Mean Time Between Resets of the BRMM Spacecraft is 8 days.


The Communication Protocol of the PIC microcontroller Microcontroller is CAN bus.


The Geopotential Mission of the CHAMP Satellite is Unknown.


The Functionality of the PCU Power Control Unit is High.


The De-Orbit Lifetime of the Secondary Payloads Satellite is 25 years.


The Location of the HSC Herschel Science Center is ESAC (ESA/European Space Astronomy Centre) in Villafranca, Spain.


The Manufacturer of the Vector Magnetometer Instrument is DTU (Danish Technical University).


The Power Source of the XI-IV Picosatellite is Body-mounted solar cells.


The Orbit of the AVUM Spacecraft is Transfer Orbit.


The Wavelength Range of the OMI Spectrograph is 270 nm to 500nm.


The Operational Declaration Date of the Kanopus-V Satellite is Jan. 29, 2013.


The Data Rate of the L-band Transmitter Radio Transmitter is 1 Mbit/s.


The Polarization Modes of the Coronagraph Instrument is Unpolarized light or one of three possible orientations of plane polarized light.


The Bandwidth of the Band 5 Spectral Band is 650-670 nm.


The X-band antenna of the TT&C Tracking, Telemetry, and Command is 1.


The Level-2 Ocean products of the Sentinel-1 Satellite is Ocean wind field, swell wave spectra and surface currents information as derived from SAR data.


The Effects of the CCD Imager is Noise, and dark current.


The Number of Preliminary Geophysical Products of the Tandem-L Satellite is 26.


The Wavelength FWHM of an unresolved line of the Spectrometer Instrument is 0.021 µm.


The Orbit Altitude of the PRISMA Satellite is 614 km.


The Gamma-ray Energy Resolution of the MGNS Neutron and Gamma-ray Spectrometer is Approximately 3.5% at the energy of 662 keV.


The Power Consumption of the RMU Radiometer Microwave Unit is < 4 W.


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


The Period of the ISS Space Station is ~ 93 minutes.


The Advantage of the Staggered SAR Radar Mode is Allows the imaging of a wide continuous swath without the need for a long antenna with multiple apertures.


The Window Damage of the Cupola Space Station Module is Minor.


The Amplification Factor of the Op-amp Operational Amplifier is 2.4.


The Launch Loads of the SRMSat Satellite is ± 11 g longitudinal and ± 6 g lateral.


The Configuration of the Pin-Puller Mechanism is Double-shear.


The Quantity of the FPGAs Electronic Components is 6.


The Average Power Consumption (Standby Mode) of the COMIS Satellite is 8 W.


The Weight of the HRC High-Resolution Camera is 2.1 kg.


The Launch Date of the FY-2 Satellite is May 29, 2012.


The Orbital Slot of the GSAT-0206 Satellite is A05.


The Launch Date of the EROS-C Satellite is Not set so far.


The Solar Eclipses Duration of the SPARCS Satellite is 25 minutes per year.


The Ku-band repeater of the Repeater subsystem Communication System is 24 (BOL) / 20 (EOL) simultaneously operating transponders at saturation.


The Heritage of the LET Low Energy Telescope is More than 14 years of successful operation in space.


The SIC Spatial Resolution of the CIMR Radiometer Imager is 5 km.


The Mission Presentation Date of the CYGNSS Satellite Constellation is March 2-9, 2013.


The Frequency of the Satellite Communication is 435 MHz.


The Number of Satellites of the BeiDou-2 Satellite Constellation is 35.


The Aperture of the NUV & VIS Channels Telescope Channels is ~380 mm.


The Launch Date of the GOSAT-GW Satellite is 2024.


The Image Acquisition Capability of the Pleiades System Satellite System is More than 500 images per day and per satellite.


The Purpose of the SUBSA-BRAINS Brazing Alloy Solidification Experiment is Examine differences in capillary flow, interface reactions, and bubble formation during the solidification of brazing alloys in microgravity.


The Journey Time to the Moon of the Chang'e-5 Spacecraft is Estimated 112 hours.


The Responsible Team of the Parker Solar Probe Satellite is Modeling teams.


The Objectives of the WISDOM Instrument is To investigate the three-dimensional geology and geological evolution of the landing site, characterize the electromagnetic properties of Martian soil, and observe the local distribution of well-compacted, sedimentary deposits.


The Spectral Sampling Interval of the HSC Spectrometer Spectrometer is 5 nm.


The Core Speed of the Stamp9G20 Microcontroller is 400 MHz.


The Funding Approval Year of the MiRaTA Satellite is 2013.


The Year of Launch of the ACRIMSat Satellite is 1999.


The Sampling Time of the Chang'e-5 Lander Lander is 48 hours.


The Instrument Mass of the STOs and STAEs Analog Electronic units is 39.8 kg (for 3 STO configuration).


The Integral Geometric Factor of the ELENA Sensor is 6 x 10 -4 cm 2 sr.


The Heat Up Monitoring of the S/C Satellite is Yes.


The MTF of the Imager Satellite Instrument is ≥0.18(PAN), ≥0.2(MS).


The S-band Uplink Frequency of the MSX Satellite is 1827.8 MHz.


The Components of the BSA Beam Steering Assembly is BSMFE, BSME, BSH.


The Rocket of the Landsat-9 Satellite is United Launch Alliance Atlas 5.


The Mission Status of the GovSat-1 Communication Satellite is Operational (nominal).


The Manufacturer of the Instrument Hyperspectral Imager is Northrop Grumman.


The Partial Pressure of Carbon Dioxide in the Water of the Marine Chemistry Study Parameter is Unknown.


The Mass of the BLITS Nanosatellite is 7.53 kg.


The Cooling of the FPA Focal Plane Array is Cryogenic module (three-stage radiative cooler).


The Hardware Cost of the Starlink Premium Satellite Internet Service is $2,500.


The Function of the Charge Sensitive Preamplifier Instrument is Convert total charge Q created by the passage of ionizing radiation to an electric impulse.


The Wavelength Range of the MIRI Spectrometer Spectrometer is 4.8-29 µm.


The Subaperture Radius of the PAIS Imaging System is 0.2 mm.


The Orbit Inclination of the KSM-1 satellites Satellite is 37º.


The Ground Stations of the Spacecraft Satellite is AFSCN (Air Force Satellite Control Network) and the USN (Universal Satellite Network).


The Distance from Sun of the Kuiper Belt Celestial Object is 5 billion kilometers (and beyond).


The Revisit Time of the Satellite Constellation Constellation is Much better in higher latitudes.


The Contract Volume of the MWI Instrument Instrument is € 134 million.


The Gas Temperature of the Cassiopeia A (Cas A) Supernova Remnant is 50 million degrees.


The Solar Arrays of the Satellite Communication Satellite is Two arrays with a total wingspan of 37 m.


The Cross-Track Detection Range of the Spectrometer Instrument is -30º to 10º.


The Type of the Aalto-1 Nanosatellite is 3U CubeSat.


The Payload Development Manager of the CloudSat Satellite is NASA/JPL.


The Imager Ranges of the HySIS Satellite is Visible Near Infrared (VNIR) range and the other in the Shortwave Infared (SWIR) range.


The Imager Resolution of the Satellite Vu Satellite is 3.5 m.


The 2 Gbit of the Satellite Data Storage Capacity is Data storage capacity of 2 Gbit (EOL).


The Deployment Time of the SpinSat Satellite is Few minutes after the plunger inhibit switches disengage from the Cyclops pusher plate.


The Hyperspectral Imager of the HJ-1A Satellite is 1.


The International Code of the BX-1 Microsatellite is 2008-047G.


The Waveband of the CO2Image Satellite is Shortwave infrared (SWIR): 1100 nm - 3000 nm.


The Preamplifier Manufacturer of the SCM Device is 3D Plus.


The SAR Data Acquisition of the X-UGS UGS is Absence of acquisition and processing functionalities.


The ESA Announcement Date of the Hitomi Satellite is July 6, 2016.


The Number of Channels of the ERB Earth Radiation Budget Experiment is 22.


The Mission Objectives of the SOHLA-1 Satellite is Completed.


The Spatial Resolution of the ECOSTRESS Instrument is 38 m in-track by 69 m cross-track.


The Presentation Date of the Disaster Monitoring Constellation Imagers Satellite is Oct. 3-7, 2011.


The Cell Type of the Solar Arrays Power Generation is Triple-junction GaAs design.


The Effect of the Solar Storms Natural Phenomenon is Cause the regolith in the moon's PSRs to accumulate charge in two layers until explosively released.


The DOI of the Onboard Processing Satellite System is https://doi.org/10.1109/JPROC.2018.2802438.


The Mass of the Spacecraft Satellite is 6.5 kg.


The Total Budget of the ESA Space19+ ministerial conference Conference is €14.5 billion for ESA for the next three years.


The Field of View of the RRA RetroReflector Array is More than 30º.


The Sensitivity of the ASTRO-H Satellite is 2 orders of magnitude better than previous instruments.


The Reaction Wheel Problem Start Date of the SARAL/AltiKa Satellite is July 2016.


The Cross-Track of the HSRS Sensor is 19°.


The Distance from Earth of the Ryugu Asteroid is 300 million km.


The Data Products of the TOMS Instrument is Vertical distribution of ozone, global maps of total ozone and 200-mb height fields; incident solar ultraviolet irradiance and ultraviolet radiation backscattered from the Earth.


The Number of Images Selected of the PolyCam Camera is Just over 2,100 images.


The Bus Type of the MEV-1 Satellite is GEOStar 3.


The Maximum Operating Temperature of the RDM Sensor Radiation Damage Monitor is +80ºC.


The Project Manager of the Fission Surface Power System Power System is Todd Tofil.


The Body-pointing Capability of the Spacecraft Satellite is Up to ±45º.


The Rotation Speed of the Filter Wheel Optics Subsystem is 600 rpm.


The Mission Status of the Landsat-9 Satellite is Continuing the legacy - 2020 and beyond.


The Straylight Measurement of the Sentinel-5 Satellite is Laser and filter measurements.


The End of Life Date of the HTV-9 Cargo Transfer Spacecraft is 20 August 2020.


The Function of the Microcontroller Controller is Collects data from the OSL, from the temperature sensors and from measurements issued from the DUTs.


The Weight of the SPOT-3 Satellite is 1800 kg.


The Mission Operations Center of the XMM-Newton Satellite is ESA/ESOC (European Spacecraft Operations Center) in Darmstadt, Germany.


The Orbit Inclination of the CANYVAL-X CubeSats CubeSats is 97.55º.


The Mass of the HEED Instrument is 2.2 kg.


The Science Goal of the HaloSat Satellite is Estimate the mass of the hot halo surrounding the Milky Way galaxy.


The Observation Date of the SGLI Polarimetric Radar Radar is 23 March 2018.


The Spectral Band of the AstroSat Astronomy Satellite is Hard X-ray to visible bands.


The Launch Date of the SciSat-1/ACE Satellite is 12 August 2003.


The Signal Filtering of the LICEF Receiver is RF and IF.


The Non-Thermal Radiation Creation Processes of the Pulsars Neutron Stars is Synchrotron emission and curvature emission.


The Ground Area Coverage of the TIR Subsystem Imaging System is 156 km by 8 km.


The Design Reference of the IRIS spacecraft Satellite is Prior missions and design studies.


The Built-in Flash of the GomSpace NanoMind A3200 Onboard Computer is 512 kB.


The Risk of the ASAP Autonomous System is Loss of Mission.


The Uplink Data Rate of the NSat Satellite is 1.2 kbit/s.


The Advantages of the Magnetic Capture Technology Capture Technology is Improves on the shortcomings of both tethered systems and robotic systems.


The Array of the Onboard Antenna Antenna is 2 x 2 patch array.


The Mission Status of the STPSat-3 Satellite is Unknown.


The Cion Mass of the CICERO-6 6U CubeSat is 1.2 kg.


The Launch Date of the SPIRRAL Experiment is 2023.


The Presentation Date of the Indian Remote Sensing Satellite Missions (IRS) Satellite is Sept. 24-28, 2007.


The Manufacturer of the CHORUS Satellite Constellation is MDA Ltd. (MacDonald, Dettwiler and Associates Ltd.).


The Location of the Sandpiper Sample Collection Site is Bennu’s southern hemisphere.


The Language of the Payload Data Processing Software is Java.


The High Energy Particle Strikes of the Computer System Payload is 2.


The AOI Sensitivity of the Etalon Etalon is Unknown.


The Contract Award Date of the RADARSAT Constellation Mission Satellite is May 29, 2009.


The Downlink Frequency of the Payload Communication System is Ka-band.


The Command Types of the DCU Data Control Unit is Plain TCs, authenticated and encrypted messages.


The Camera Function of the Imaging X-ray Polarimetry Explorer (IXPE) Space Telescope is Measure the polarization of cosmic X-rays.


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


The In Orbit Commissioning (IOC) End Date of the CHEOPS Satellite is March 26, 2020.


The Total ΔV of the CanX-4&5 Satellite is 14 m/s.


The Function of the BCA Baffle and Cover Assembly is Minimizes stray-light and includes a protective cover and release mechanism.


The Thruster of the S/C Satellite is 100 mN resistojet.


The Mission of the Spectrometer Telescope Telescope is Solar Orbiter.


The Corona Temperature of the Sun Celestial Body is On average 1 million degrees Celsius.


The Mass Data Storage of the DubaiSat-1 Satellite is 32 Gbit.


The Software of the Phoenix GPS Receiver GPS Receiver is eXtended Navigation System (XNS).


The Observation Campaign of the Kepler spacecraft Spacecraft is 18th.


The Calibration Images of the PROBA-V Satellite is 2.674.


The On-Board Calibrators Performance Duration of the Terra MODIS Satellite Instrument is Not Provided.


The TDI Stages of the Kruiz CCD Detector is 128, 64, 32, 16, 8.


The Ground Control Network of the R3 spacecraft CubeSat is Multi-station.


The Data Acquisition Sites of the VSSC Satellite is Existing or planned experimental sites with sizes ranging from 27 km x 27 km to 27 km x 54 km or more.


The Spectral Resolution of the HPT Sensor is Multispectral.


The Bandwidth (GHz) of the ICI-4 Radiometer is 6.


The Power of the EPDP Technology Payload is 18 W.


The Calibrators of the Instrument Calibration is Solar diffuser, solar diffuser stability monitor, blackbody.


The Downlink Transmission of the CBERS-1 Satellite is X-band.


The Mass of the CLARA Instrument Satellite Instrument is 2.63 kg.


The Scan Time of the VISSR Mirror Instrument is 30 minutes.


The Image Archive of the SPOT-4 Satellite is 100 billion km2.


The Rocket Engine Test Date of the PRISMA Satellites Satellite is June 24, 2010.


The Scan Mirror Controller of the TEMPO Instrument is Closed-loop control.


The Launch Date of the Monitor-E Spacecraft is June 30, 2003.


The Collaboration Date with Turkey of the SPOT 6 & 7 Satellite Constellation is Dec. 20, 2012.


The Chip Set of the GPS receiver Receiver is MITEL chip set.


The Vacuum Chamber Volume of the SEIS Instrument Seismometer is 3 liters.


The Video Data Conversion Rate of the MS Detectors Detectors is 7 Mpixel/s.


The Pulse Peak Output Power of the Laser Instrument is 500~1000 W.


The Imagery of the Landsat-8 OLI Satellite is Data.


The Orbit of the Kleos Patrol Mission (KSF2) Satellite is Sun synchronous.


The Manufacturer of the SkySat Satellite is Terra Bella.


The Data Collection Frequency of the Sentinel-6/Jason-CS Satellite is Every 10 days.


The Value of the Polarization Sensitivity Performance Requirement is Less than 2%.


The Mission Aim of the NeuSAR Satellite is Pathfinder mission for a potential constellation of small SAR satellites.


The Crust Thickness of the Mars Planet is Between 24 and 72 kilometers.


The Retention Mechanism of the Deployment Systems Satellite is Pyro cutters.


The Power Subsystem Manufacturer of the MicroMAS-1 Satellite is Clyde Space.


The Data Processing Time of the PDS Data Services is Within 3 hours after sensing.


The Solar Array Surface Area of the IRIS Satellite is 1.7 m2.


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


The Spectral Range and Resolution of the OCI Ocean Color Instrument is Advance the ability to distinguish between different species of phytoplankton compared to predecessor satellite instruments.


The Launch Time of the SEOSAT-Ingenio Satellite is 02:52 CET / 22:52 local time on 16 November.


The Applications of the NIDEM Elevation Model is Coastal risk mitigation, ecological conservation, habitat mapping, hydrographic surveying.


The Antenna Gain of the GPSRO Sensor Sensor is Over 10 dBi.


The Apogee of the SCD-2 Satellite is 768 km.


The Type of the VIIRS Telescope Assembly is Three Mirror Anastigmatic.


The Installation Location of the Wireless Compose module Communication Module is Space Station.


The Wavelength of the VIS Detector is 0.675 µm.


The Instrument Package Data Rate of the LCROSS Satellite is 554.5 kbit/s.


The Components of the Satellite Communication Satellite is More than 600 electronic and radio-frequency units.


The Anomaly Updates of the Copernicus Sentinel-1B Satellite is 2.


The Data Relay of the TGO Satellite is Second ExoMars mission.


The Mission Type of the FormoSat-7 / COSMIC-2 Satellite Constellation is Non-EO.


The Voltage levels of the EPS Electric Power Subsystem is 3.3 V, 5 V, battery output (nominal 3.7 V).


The Structure Dimensions (Stowed) of the FY-3 series spacecraft Satellite is 4.4 m x 2.0 m x 2.0 m.


The Total Energy Channels of the GRS Gamma-Ray Spectrometer is 512.


The Capacity of the Onboard Mass Data Storage Data Storage is 24 GByte.


The Duration of the Radiation Effects Tests Testing Process is Months to execute.


The Operating Voltage of the C&DH Subsystem Subsystem is 3.3 V.


The Detection of the X-ray pulsars Astronomical Objects is Detected.


The Date of the Superresolution Far-field Imaging Imaging Technique is 18 December 2018.


The Workshop Date of the Brazilian EO Satellite Program Satellite Program is April 17-19, 2012.


The Image Quality of the SMART Imaging System is Better than direct imaging and PAIS.


The Micro-Roughness of the Primary Optics Optics is Better than 0.2 nm.


The IFOV of the Eastman Kodak KLI14403 linear CCD sensor Sensor is 32.07 µm.


The Orbital Altitude of the LDEF Satellite is 477 km.


The Production Frequency of the SST Product Dataset is Every 10 minutes.


The Conference Presentation Date of the DebriSat Fragments Space Debris is 25-29 Sept. 2017.


The Years in Orbit of the TanDEM-X Satellite is 8 years.


The Interface Options of the Ubotica CogniSAT-XE1TM CubeSat Board Satellite Device is Gigabit Ethernet or USB2.0/3.0.


The URL of the GIADA Instrument is http://sci.esa.int/rosetta/35061-instruments/?fbodylongid=1639.


The Spectral Resolution of the Instrument Spectral Imager is 1.25 cm -1.


The Long-Term Stability Drift of the MIRAS Radiometer is 0.49 K or 1.46 K.


The Partnership of the Astrocast and iWire Group Companies is Development and production of devices equipped with both Sigfox terrestrial connectivity and Astrocast Satellite IoT (SatIoT) services.


The Image Credit of the GOES 2nd generation spacecraft Satellite is NOAA.


The Solar Array of the EPS Electric Power Subsystem is Single deployable with single-axis articulation capability.


The Accretion of the V404 Cygni Black Hole is Material from a companion star.


The Processing Frequency of the RPU Receiver Processor Unit is 401.6 MHz.


The Mission Objective of the GNOS GNSS Occultation Sounder is Remote sensing of Earth’s neutral atmosphere and the ionosphere.


The Data Access of the Airbus Satellite Satellite is Near real-time.


The Frequency (GHz) of the ICI-2 Radiometer is 183.31±3.4.


The Led by of the GMES Initiative is EC (European Commission).


The Operation Principle of the LENA Instrument is Neutral particles enter the instrument through a collimator which filters charged particles. LENA converts neutrals to negative ions through a near specular glancing reflection from a tungsten surface. Negative ions from the surface are then collected by .


The Architecture of the DPSK Transmitter Transmitter is MOPA.


The Usage of the Doppler Velocity Sensor Velocity Measurement Device is Terminal landing phase.


The Instantaneous spectral coverage of the Spectrometer Instrument is 1.37 km/s.


The Spectral Resolution (86 keV) of the Detector Instrument is 1.2 keV.


The Measurement Range of the MIS Instrument Microwave Radiometer is 6 GHz to 183 GHz.


The Location of the Astrobiology Analytical Laboratory Laboratory is NASA’s Goddard Space Flight Center in Greenbelt, Maryland.


The Spatial Resolutions of the GOCE Satellite is Half-wavelength.


The IFOV of the HgCdTe Detector is 170 µrad.


The Thermal Vacuum Test Environment of the Flight Model Satellite Model is Vacuum.


The Function of the Photo MOSFET Switch Component is Probe cleaning.


The Thermo-elastic Stability of the FG Filtergraph is Unknown.


The Detection of the LI Lightning Imager is Cloud to cloud, cloud to ground, and intra-cloud flashes.


The Use Case of the Specialized Asset Trackers Tracking Device is Knowing where your assets are and how your assets are being treated.


The Function of the Spacecraft Bus Satellite Component is Supply electrical power to the science instruments, orient and stabilize the telescope, store and compress the data from the science instruments for later transmission to Earth, execute the stored commands to carry out the planned observing schedule, and .


The Development Time of the SCIP Processor is Too long.


The Vector Sample Rates of the NewMag Magnetometer is Internal = 1000/s, Standard = 10/s, Burst mode = 100/s.


The Observation Technique of the SHIMMER FTS Fourier Transform Spectrometer is Limb scanning can be avoided since the detector simultaneously records interferograms in each horizontal row of the CCD, corresponding to discrete altitudes in the range subtended by the field-of-view (FOV) of the instrument.


The Latency Requirement of the S-2 NRT Product is Within 30 minutes.


The Manufacturer of the CMV4000 CMOS Color Detector is CMOSIS.


The Data Delivery of the SWAP Payload is About 70 images per contact, delivered within 30 minutes to the SOC.


The Baseline of the Wind Speed Retrieval Algorithm Algorithm is Extension of one previously developed for the UK-DMC spaceborne mission.


The Orientation Accuracy of the Tethered System Attitude Control System is Within ±10 degrees of the vertical.


The Bit Depth of the Signal Digitization Process is 10 bit.


The SNR @Lref [EOL] of the Spectral Channel Detector is 202-408.


The URL of the ISIM Compartment is http://www.jwst.nasa.gov/isim.html.


The Revisit Time at 20° off nadir or less (0.51 m GSD) of the WV60 imager Imaging System is 5.9 days.


The Second Flight Date of the MEPSI Satellite is July 2001.


The Measurement Range of the Aerosol Index (AI) Satellite Instrument is -1 to +5.


The Search Coil Diameter of the ULF Sensor Sensor is 5 cm.


The Power Consumption of the SGR-ReSI Interface Unit is 10 W.


The Wavelength Range of the Instrument Sensor is 115-180 nm.


The Frequency of the S-band Transmitter Transmitter is S-band.


The Data Retrieval Time Improvement of the SafetyNet Ground Data Receptor Network is More than 32 minutes.


The Imaging of the RADARSAT-1 Satellite is Radar Imagery.


The Voltage of the Voltage 6 Modulator is 3.8±2%.


The Deployment Mechanism of the STRaND-1 Satellite is ISIPOD CubeSat dispenser of ISIS.


The Output Voltages of the EPS Electrical Power Subsystem is 8.4 V, 5 V, 3.3 V.


The Joint Endeavor of the ExoMars Mission is ESA and Roscosmos.


The Launch Date of the CO2M Satellite is 2025.


The Purpose of the RF Crossover Switch Switch is Hedge against loss of one of the redundant UHF command and telemetry transceivers.


The ADC Resolution of the MuREM Radiation Monitor is 10 bit.


The Description of the SV-6 System Resource Flow Matrix DoDAF 2 Viewpoint is Tabular description of each data element exchange between two system function actions.


The Arrival Date of the JUICE Spacecraft is 2029.


The Power of the Spacecraft Satellite is 2.5 kW (EOL).


The Conference Presentation Date of the TechnoSat Nanosatellite is Aug. 10-15, 2013.


The NER of the Spectral Band C Spectrometer is 1.7 x 10^-5 W/(cm^2 sr µm).


The Focal Plane Temperature of the TIR Instrument Telescope is 60 K.


The Area of the . Wave mode (WM) Operational Mode is 20 km x 20 km.


The Subsystems of the IRPE Image Reception and Processing Element is Antenna and RF equipment, DIS (Data Ingestion Subsystem), DAS (Data Acquisition Subsystem), ICPS (Image Collection Planning Subsystem), WMS (Workflow Management Subsystem), DPS (Data Processing Subsystem), UIS (User Interface Subsystem).


The Mission of the Lunar Reconnaissance Orbiter Satellite is LRO mission.


The Spectral Range (µm) of the Band 1 Spectral Band is 0.58 - 0.68.


The Mirrors of the Telescope Optical Instrument is Conics with a fourth-order aspherical term.


The Operation of the MAP-PACE Plasma Analyzer is Continuous.


The Resolution of the Iris Satellite is 100 times higher than any other satellite.


The Manufacturer of the Suomi-NPP Satellite is Ball Aerospace and Technologies Corporation (BATC).


The Power Input of the PDC Power/Data Controller is 28 VDC.


The Revisit Time at Equator of the HyperScout® Satellite is Around 45 days.


The Far-Field Pattern Irradiance Drop of the OGS Ground Station is Does not exceed 3dB.


The Telescope Aperture of the Nanosatellite Satellite is 30 mm.


The Cross-Calibration Time Difference of the CloudSat Satellite is 30 minutes.


The Unknown of the Kaber Spacecraft is Unknown.


The Address Space of the LEON3 Processor is >24 bit.


The Discovery Date of the Rosetta Satellite is 26 Oct. 2017.


The Clocks of the GIOVE-B Satellite is 2 RAFS (Rubidium Atomic Frequency Standard).


The Observation Period of the STEREO-A Spacecraft is May 25 – June 1.


The Disciplines of the Spacelab-1 Satellite Mission is Atmospheric science, solar science, materials science, space plasma physics, the life sciences, astrophysics.


The Power of the GOMS-1 Satellite is 1.5 kW.


The Power of the STRV-1d DHS Data Handling System is 3 W.


The Target Stars of the CHEOPS Satellite is Small exoplanets previously detected by accurate Doppler surveys and known transiting Neptune-size planets detected by ground-based photometric surveys.


The Altitude of the LLITED CubeSat Satellite is Lower altitudes.


The Mission of the Arktika-M N1 Satellite is Monitor the Earth’s atmosphere and surface in the Arctic, collect and relay information from Arctic facilities, monitor cosmic rays, and assist in the international search and rescue service, COSPAR-SARSAT.


The Bus Type of the GF-2 Satellite is CAST-CS-L3000A.


The Orbit Inclination of the DubaiSat-1 Satellite is 98.13º.


The Length of the Scandinavian Peninsula Landform is Approximately 1850 km.


The Study Level of the Stardust Grain Particle is Atomic.


The Distance from the Sun of the Galactic Center Center of the Milky Way is Almost 30,000 light years.


The Orbit of the Spacecraft Satellite is MEO.


The Spectral Resolution of the MAHRSI Instrument is 0.018 nm at 310 nm.


The Spatial Resolution of the GOES Imager Imager is 4 km x 4 km on MWIR and TIR bands, 1 km x 1 km on VIS band.


The Authors of the Proposed visible emission line space solar coronagraph Solar Coronagraph is Jagdev Singh, B. Raghavendra Prasad, P. Venkatakrishnan, K. Sankarasubramanian, Dipankar Banerjee, Raja Bayanna, Shibu Mathew, Jayant Murthy, Prasad Subramaniam, R. Ramesh, S. Kathiravan, S. Nagabhushana, P. K. Mahesh, P. K. Manoharan, Wahab Uddin, S. Sri.


The Subsystems of the AVUM Upper Module is GNC (Guidance Navigation and Control), SAS (Electric Safeguard Subsystem), TMS (Telemetry Subsystem).


The Data Usage of the Carbonite-2 Satellite is UK’s Royal Air Force (RAF) for use by the Joint Force Command National Centre for Geospatial Intelligence.


The Anticipated Global Connectivity Timeline of the Starlink Satellite Constellation is A few months after the 28th launch.


The Sensitivity of the GOLF Instrument is 1 mm/s.


The Location of the MEMS 3-axis Gyro Device is Zenith end assembly.


The Attitude Sensors of the SUNSAT Satellite is 3-axis fluxgate magnetometer, 2-axis horizon sensor, fine slit sun sensor, second star sensor.


The Number of Stars of the M33 galaxy Galaxy is Forty billion.


The Standard of the OOK Modulated Optical Satellite Communications System Communication System is CCSDS.


The Orbit Type of the IBEX Spacecraft is Highly Elliptical Orbit.


The Satellite Launch Date of the AMSU/HSB Advanced Microwave Sounding Unit/Humidity Sounder for Brazil is May 4, 2002.


The Data Processing of the EPD Sensors Sensors is Manual for first data release, future automation planned.


The Observation Speed of the XMM-Newton X-ray Observatory is Speeded up for illustration purposes.


The 15% FWHM of the Energy Resolution Sensor is Energy resolution (delta E/E) 15% FWHM (Full Width Half Maximum).


The Operation Start Year of the SAR-Lupe Satellite System is 2008.


The Resolution Cell, Vertical of the Instrument Spectrometer is 4 km.


The Function of the ROSA Radio Occultation Antenna Antenna is Receive signals from the GPS constellation during their occultation time window.


The Design Verification of the ESA Young Engineers Satellite 2 Satellite is FEM Analysis.


The Accumulated Firing Time of the LM thruster Thruster is Over 6.0 minutes.


The Sensor Type of the TANSO-FTS Sensor is Fourier Transform Spectrometer.


The Orbit of the SEOSAT/Ingenio Satellite is Low Earth Orbit.


The Mission Principal Investigator of the IMAP Interstellar Mapping and Acceleration Probe is David McComas.


The Launch Year of the Himawari-9 Satellite is 2016.


The Location of the IRNSS-1C Satellite is 83ºE.


The Operation of the Sentinel-6 Satellite is Fly in tandem with the Jason-3 spacecraft.


The Full SAR Access Range of the SAR Synthetic Aperture Radar is Ten swaths in quad-pol (QP) mode and nine swaths in dual-pol mode.


The Star Calibration Frequency of the Satellite Imaging Satellite is During commissioning.


The Data Capture Rate of the MinXSS-2 Satellite is At least 6%.


The Data Collection of the Mission Satellite Mission is Atmospheric and oceanic data.


The Initial Orbit Altitude of the Satellite PUNCH Mission is 570 km.


The Brightness Change Time Scales of the XMM-Newton X-ray Satellite is Up to 14.5 years.


The Pixels per FWHM of the Spectrometer Instrument is 580.


The Sensor Type of the TET-1 Satellite is Mid-wave and longwave infrared.


The Purpose of the Switch Matrix Experiment is On-Orbit-Verification.


The Benefits of the EGS-CC Space Control System is Faster transitions between the life stages of a mission, reduced cost and risk for missions, evolving ground systems for missions of the future, working towards a ‘European Network of Centers’, providing European industry with a powerful tool with which t.


The Size of the X-band transmitter Transmitter is m3-sized.


The Mission Lifetime of the NEMO-HD Satellite is One year.


The Data Update Frequency of the GPM Global Precipitation Measurement mission is Every 30 minutes.


The Gain of the Antennas Antenna is –4 dBic minimum.


The Design Lifetime of the CIMR Satellite is 7 years.


The Pixel Pitch of the GOCI-II CMOS Imaging Sensor CMOS Imaging Sensor is 6.8μm.


The Orbital Inclination of the Solar Orbiter Spacecraft is 17º (by 2025), 33º (by the end of the decade).


The Ground Sample Distance (GSD) of the PAN Imaging System is 1 m.


The Manufacturer of the WorldView-1 Satellite is DigitalGlobe Inc..


The Bandwidth of the Instrument Spectrometer is 20 nm (for 415, 750, 900,950 nm); 30 nm (for 1000, 1050, 1250 nm)  50 nm (1550 nm).


The Gain of the Onboard Antenna Antenna is 13.5 dBi.


The Orbit Perigee of the BX-1 Microsatellite is 280 km.


The Funding Source of the SPIDER Telescope is DARPA (Defense Advanced Research Projects Agency).


The Regions of the AAI Air Navigation Service Provider is Mumbai, Chennai and Kolkata's oceanic airspaces.


The Operation of the Laser Retro Reflector (LRR) Tracking Device is Enabled tracking by ground-based satellite laser ranging stations.


The Dimensions of the Grating Optical Component is 10 cm x 20 cm.


The Coverage of the Copernicus Sentinel-5P Satellite is Global.


The GSD of the Eastman Kodak KLI14403 linear CCD sensor Sensor is 22 m.


The Swath Width of the OLI-2 Sensor is 185 km.


The Payload Uplink of the Dove-2 Satellite is 30 kbit/s over 2.4 GHz radio.


The Program Start Date of the DRACO Demonstration Rocket is Over a year ago.


The Mass of the CONSERT Experiment is 1.8 kg.


The Closest Approach to Sun's Surface in 2022 of the Solar Orbiter Satellite is Within 48 million km.


The Microcontroller Clock Speed of the On-board Computer Computer is 16 MHz.


The Sensor of the SWOT Satellite is KaRIn (Ka-band Radar Interferometer).


The Conference Presentation Date of the Delfi-C3 Nanosatellite is June 9-11, 2005.


The Launch Year of the GOES-U Satellite is 2024.


The Member of the Ana Barros Individual is True.


The Orientation Deviation of the Collimator Optical Device is -0.27° to -0.25° in horizontal and 0.40° to 0.48° in vertical direction.


The Orbit Inclination of the KySat-1 Satellite is 98.2º.


The Mass of the NIUSAT Nanosatellite is 15 kg.


The Presentation Date of the Small Satellites Satellite is April 3-6, 2017.


The Cryocooler of the WFIRST Observatory is Eliminated in favor of passive cooling of the WFI cold electronics.


The On-orbit Calibration Target of the ARTEMIS Satellite is Panel with relatively flat spectral reflectance and measured reflectance characteristics.


The Image of the Day Date of the NASA Earth Observatory Satellite is 21 May 2022.


The Transfer Phase Start of the LUMIO Satellite is Stable Manifold Injection Maneuver.


The Video Camera Assembly of the LAPAN-A2 Satellite is Two cameras, featuring analog and digital outputs respectively.


The Data Distribution Center of the SAMPEX Satellite is UMSOC (University of Maryland Science Operation Center).


The Components of the C&DH subsystem Command & Data Handling Subsystem is Controller card (CC), data handling card, Power Supply Card (PSC), Input/Output Card (IOC), Mission Interface Card (MIC).


The Bus Platform of the Restore-L Satellite is 1300-class.


The Quad Pol Swath Width of the SAR Processor Data Processor is 175 km.


The Manager of the CGS Ground System is Raytheon.


The Design of the GPSP Instrument is Blackjack.


The Inclination of the FY-3E Satellite is 98.7º.


The Deployment Confirmation Time of the STSAT-3 Satellite is About 6 hours after lift-off.


The First Signal Reception Date of the Pico Dragon CubeSat is Nov. 20, 2013.


The Dimensions of the Card Size Communication System is 15.3 cm x 23 cm.


The Duration of the Chirp Signal is ~100us.


The Design Life of the Kanopus-V Satellite is 5 years.


The Dipole Antenna Length of the IOF Plasma Wave Instrumentation is 121.8 m.


The Measurement Category of the OCO-3 Instrument is Trace gases (excluding ozone).


The Power Conversion of the PPM Power Processing Module is Converts electrical power (300 W) provided by solar panels of STSat-3 to the power required for accelerating charged particles inside the channel of the thruster head.


The Mass of the Flock-1c CubeSat is 5 kg.


The Horizontal Sampling of the TanDEM-X Satellite is 12 m by 12 m.


The Sampling of the Satellite LEO (Low Earth Orbit) is Poor spatial and temporal sampling: each point on globe sampled just once every day on dayside, once nightside.


The Tx-TNC Cache Memory of the RF Communication System Communication System is 128 byte.


The Coating of the Grating Optical Component is 200 nm gold.


The Data Transmission Frequency of the Instrument Photometer is About once a month.


The Size of the Pelican Constellation Satellite Constellation is Not revealed.


The Launch Date of the EgyptSat-2 Satellite is May 5, 2014.


The User Consultation Working Groups of the Sentinel-1 Satellite is Marine Core Services, Land Monitoring and Emergency Services.


The DOI of the GRAIL Satellite is 10.1038/nature13697.


The URL of the Spectrometer Telescope Telescope is http://www.esep.pro/sites/esep/IMG/pdf/poster_spie12_stix_8443-131_v3.pdf.


The Spectral Range of the SWIR bands Satellite is Shortwave (SW) infrared (IR) bands include: 940, 1038, 1250, 1378, 1615, 2130, and 2260 nm.


The Altitude of the MCAM-2 Camera is 200 km.


The Number of Institutions of the ASTRO-H Mission is 58.


The Far-UV Channel Spectral Resolution of the IRIS Observatory is 4 x 10-3 nm.


The Publication Date of the Can ripples on the sun help predict solar flares? News Article is 21 September 2020.


The Number of Publicly Released X-ray Source Catalogues of the XMM-Newton Survey Science Center Consortium is 6.


The Light-Shade Cycle Frequency of the Solar Panels Power Source is 16 times per day.


The Data Rate of the MTG-S Spacecraft Satellite is 3 GByte/s at instrument output.


The Filter of the BRITE Telescope is Single Color.


The Shortwave Range of the CERES Instrument is 0.3 - 5.0 µm.


The BER (Bit Error Rate) of the S-band Transmitter Transmitter is 10 -5.


The Cadence of the Neutral Particle Dose Rate Measurement is 1 minute.


The Antenna Polarization of the GPS Reflectometry Receiver Instrument is RHCP (Right-Hand Circular Polarization) and LHCP (Left-Hand Circular Polarization).


The Publication Date of the S-054 X-ray Telescope X-ray Telescope is Feb. 1977.


The Data Interface of the OBC On-Board Computer is I2C bus.


The Sensor Provider of the Near-Infrared Spectroscopy and Photometry Instrument (NISP) Instrument is NASA.


The Number of Analyzers of the FlaPS Instrument Package is 16.


The Spectral Bands of the Anand Satellite is Over 150.


The Transmission Profile of the PF2 Passband Filter is Unknown.


The Diameter of the Pleiades Open Cluster is About 35 light years.


The Importance of Temporal Domain of the SVOM Satellite is Recognized in recent reports by the Chinese Space and Technology Roadmap, the European Union ASTRONET group and the USA National Research Council Decadal Survey.


The Operation Status of the Genesis-2 Satellite is Nominal in 2012.


The Number of Lunar Transit Images of the EPIC Earth Polychromatic Imaging Camera is Two.


The Beam width of the S-band Band is 0.64 rad.


The Average Incidence Angle of the Convex Holographic Grating Grating is Approximately 38.2 º.


The Ground Sampling Distance of the Telescope Optical Instrument is 30 m.


The Total Velocity Change of the Propulsion Subsystem Propulsion is ΔV = 334 m/s.


The Composition of the Psyche Asteroid is Mostly iron and nickel.


The Type of the BSA Beam Steering Assembly is 2-axis small range pointing mechanism.


The Usage of the INS Navigation System is First burn, second burn.


The Location of the Payload Modules Satellite Components is Section close to the antenna.


The Resolution Δλ (0.05º slit) of the SPIM2 Spectrometer is 0.9 nm.


The Mission Status of the MOMS Satellite is Mission complete.


The Name Change of the SRTM Shuttle mission is NIMA (National Intelligence Mapping Agency) changed its name to NGA (National Geospatial-Intelligence Agency).


The Fringe Distortions for Monochromatic Light of the SHS Interferometer is Provide a measure of the grating figure errors.


The Point-Spread-Function Hold Requirement of the Attitude System Satellite System is Within 3 pixels of the original point locations.


The Last Launch Year of the Space Shuttle Spacecraft is 2011.


The Propellant for Station Keeping of the Geo Satellite Satellite is 1 ton.


The Orbit Type of the ARTEMIS Probes Spacecraft is Lissajous orbit near the Earth-Moon Lagrange points.


The Activation Method of the TEMBOTM EMC Material is Heat-activated.


The Design of the BRITE Telescope is Low Cost and Risk Mitigation.


The Launch Date of the Falcon Heavy Rocket is 25 June 2019.


The Power of the VHF Transmitter Radio Transmitter is 8 W.


The Wavelength/Frequency of the X-band Radar is 32 mm/9.7 GHz.


The Landing Date of the Falcon 9 first stage Rocket is Jan. 11, 2015.


The SWIR Spatial Resolution of the iSIM-90 Imager is 13 m.


The Center Frequency of the Radiometer Instrument is 1.41 GHz.


The Satellite Type of the Hyper-Angular Rainbow Polarimeter Polarimeter is 3U CubeSat.


The Mission Status of the EO-1 Satellite is Operational.


The Spatial Resolution of the Atmospheric-sounding instrument Spectrometer is Better than 50 km2 over several across-track pixels.


The Swath Width of the S-192 optomechanical scanner Scanner is 72.4 km.


The Number of Transiting Super-Earths of the K2-155 M Dwarf Star is 3.


The Horizontal Integration of the Aeolus Satellite is 50 km.


The FOV of the Instrument Spectrometer is 11º.


The Polarization of the ICEYE SAR (Synthetic Aperture Radar) Sensor is Circular.


The Clear Aperture of Telescope of the DubaiSat-1 Satellite is 30 cm.


The Location of the MC3E Field Campaign is DOE-ASR Central Facility in Oklahoma.


The Actuators of the IRS-1C and IRS-1D Spacecraft is Four reaction wheels, two magnetic torquers, 16 one Newton hydrazine trusters, one 11 Newton thruster.


The Quantity of the AMICalSat Satellite is 1.


The Optimal PMT Temperature of the Detector Box Instrument is -20°C.


The Centrifugal Force of the LISA Pathfinder Spacecraft is Small.


The Measurement Range of the Particle Detector Instrument is Helium-3 : 21 MeV/n ~ 84 MeV/n.


The Journal Publication Date of the LISA Technology Package LTP Technology Package is 2006.


The Perigee of the Satellite Orbit is 324 km.


The Panchromatic Image Data of the Optical Sensor Assembly (OSA) Instrument is 6500 lines/s.


The Distance from Mars of the Tianwen-1 Mars Mission is 1.1 million kilometers.


The Redundancy of the Phoenix GPS Receivers GPS Receiver is Cold redundant pair.


The Power Source of the EPS Electrical Power Subsystem is Rechargeable Li-ion battery.


The Manufacturer of the EUTELSAT KONNECT Satellite is Thales Alenia Space.


The URL of the GRAIL Mission is http://science.nasa.gov/headlines/y2008/22may_grail.htm.


The Total Mass of the GeneSat-1 Satellite is Not provided.


The Type of the Magnetic Field Sensor Sensor is Two-axis.


The Conference Date of the NICT's New OGS Ground Station is May 16-20, 2016.


The Transmission Profile of the PF1 Passband Filter is Unknown.


The PRN of the GSAT-0210 Satellite is 1.


The Manufacturer of the Vector Magnetometer Instrument is DRSI (Danish Space Research Institute).


The Rainfall Impact of the OCO-2 Satellite is More carbon being released into the atmosphere.


The Brigthness Temperature (BT) Sensitivity of the Antenna Reflector is ±0.42 K.


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


The Energy Range of the EPD-I Energetic Particle Detector - Ions is 50 keV – 300 keV.


The SAR Tandem Mission Date of the ERS-2 Satellite is September 2007 to February 14, 2008.


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


The Components of the SWE Sensor Web is SensorML, Observations and Measurements.


The Data Collection Duration of the RAVAN CubeSat is 20 months.


The PGDS Location of the FOS Satellite is ESRIN.


The Expected Nitrogen Dioxide Emissions Restriction of the International Shipping Emission Regulations Regulation is Coming years.


The Structure Material of the UniSat-5 Satellite is Aluminum honeycomb reinforced by aluminum internal panels.


The ADCS System of the DeorbitSail Satellite is First in-orbit demonstration of the CubeComputer.


The Pixel Size of the IIR Imager is 1 km.


The Payload Volume of the Supernova-Beta Satellite is 7000 cm3.


The Capacity of the Batteries Electrical Power Subsystem is 5.2 Ah.


The Development Status of the 3MI Instrument is PDR completed in October 2015, moving toward a CDR scheduled in January 2018.


The Mission Duration of the SPOT-3 Satellite is Three years.


The Size of the OptiCube-3 Satellite is 3U.


The Products in Nominal Phase of the Mission Operation System Data Processing System is About 2 PB.


The Communication Standard of the CFESat Satellite is IP (Internet Protocol).


The Frequency of the Pyxis-RO Instrument is 1575.42 MHz (L1 GPS), 1227.6 MHz (L2 GPS), 1575.42 MHz (E1 Galileo), 1207.14MHz (E5 Galileo), 1602 MHz (L1 GLONASS), 1246 MHz (L2 GLONASS), 1561.1 MHz (B1 BeiDou), 1207.14 MHz (B2 BeiDou).


The Mission Type of the PW-Sat CubeSat is Non-EO.


The Funding of the GeoXO Satellite System is NOAA.


The Names of the Phantoms Mannequin Torsos is Helga and Zohar.


The Data Set Duration of the Global Satellite Mapping of Precipitation (GSMaP) Satellite Data is Less than twenty years.


The URL of the SOHO Satellite is http://www.nasa.gov/content/goddard/soho-captures-jan-14-2014-cme/#.Uz0sNaKegkA.


The Manufacturer of the ASIM Instrument is Danish company Terma, the Danish Technical University, the University of Bergen in Norway and the University of Valencia in Spain.


The Message Format of the SpW Data Transfer Protocol is ECSS PUS.


The Battery Operations Presentation of the TET-1 Spacecraft is SpaceOps 2014.


The Common Methods of the Deployment Mechanisms Satellite Component is Nichrome burn wires, breakable links made of plastic retaining bars.


The Measurement Accuracy of the ATOMMS Spectrometer is 1% or better.


The FOV of the STAFF/DWP Instrument is ±3ºx 180º(IIMS), ±17.5º x 180º (IES).


The Principal Investigator of the Carruthers Geocorona Observatory Spacecraft is Lara Waldrop.


The Reaction Wheel Spin of the Integral Satellite is 5 times its maximum when under control.


The De-orbiting End Date of the ERBS satellite Satellite is August 15, 2003.


The Propulsion System of the Jason-3 Satellite is Hydrazine.


The Data Storage of the Satellite Spacecraft is At least two and a half orbits of mission data.


The Imaging Camera of the DSCOVR satellite Satellite is Earth Polychromatic Imaging Camera.


The Launch Date of the HySIS Satellite is 29 November 2018.


The Phased-Array Technology of the SARah Satellite Constellation is Developed by Airbus DS GmbH.


The SNR Improvement of the PAIS Imaging System is When the subaperture area is increased.


The Joint Instrument of the MIRI Mid-Infrared Camera-Spectrograph is JPL and ESA.


The Field of View of the IRIS Satellite is 171 arcsec.


The Accuracy of the DORIS Receiver is About 1m.


The Gain Control of the MCP (Microchannel Plate) Detector Detector is Voltage applied to the front surface.


The Attitude Subsystem Stability of the Spacecraft Satellite is 0.009º/s (3σ).


The Spatial Resolution of the DMC-3 Satellite Constellation is 1 m.


The Band 2 of the R3 Sensor Sensor is Blue.


The Expected Data Collection of the Nancy Grace Roman Space Telescope Space Telescope is More than any of NASA’s other astrophysics missions.


The Debut Date of the CIMON Astronaut Assistant is 15 November 2018.


The Rotation Period of the Asteroid 1999JU3 Asteroid is Around 7.6 hours.


The Unknown of the LDRS-PEM Payload Electronics Module is Low Data Rate System - Payload Electronics Module (LDRS-PEM).


The Publication Date of the Spaceborne Frequency Comb Metrology Metrology System is Dec. 2016.


The Mass of the ASPOC Instrument is 2.5 kg.


The Launch Readiness of the Emirates Mars Mission Satellite is Ready for Launch.


The Telescope Diameter of the Submillimeterwave receiver Receiver is 30 cm.


The Clocks of the GIOVE-B Satellite is 10 ns per day.


The Design Lifetime of the Tianwen-1 Spacecraft is One Martian year, or 687 Earth days.


The Communication of the BIROS Minisatellite is On board AVANTI experiment programs.


The Remapping Frequency of the 90-satellite constellation Satellite Constellation is Weekly.


The Picosat Distribution of the OPAL Satellite is 4 short and 2 long.


The Arrival Date of the Rosetta Satellite is August 6, 2014.


The Cell Resolution of the OSCAT Scatterometer is 25 km x 25 km.


The Global Coverage Frequency of the Sentinel-2 Satellite is Every 10 days with one satellite, every 5 days with two satellites.


The Apogee of the Molniya Orbit Orbit is 39750 km.


The Space Situational Awareness Increase of the SBSS-1 Satellite System is Factor of three.


The Manufacturer of the Second FPGA FPGA is Xilinx.


The Vector Inputs of the Slew Mode Satellite Mode is Magnetometer and sun sensor vectors.


The Initiative Date of the Small GEO Satellite Satellite is April 16, 2007.


The Time Delay of the Deep Space Atomic Clock Atomic Clock is About five times better than what the team reported in the spring of 2020.


The Mass of the STRaND-1 Satellite is ~ 4.3 kg.


The Image Capture Date of the CaSSIS Instrument is 18 November 2018.


The Downlink RF Output Power of the RF Communication System Communication System is 1 W.


The Purpose of the SWOT Satellite is Study small-scale features of ocean surface.


The Number of Beams for Standard Imaging Mode of the COSI SAR Mission is 31.


The Band 4 of the R3 Sensor Sensor is NIR.


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


The Launch Date of the MULA Satellite is 2025.


The Partnership Date of the Capella Space Company is August 5, 2019.


The Bandwidths of the AATSR Instrument is 20 nm, 300 nm, 1000 nm.


The Quantity of the LED-arrays Lighting System is 3.


The Number of Ocean Regions of the RECCAP-2 Satellite Mission is 5.


The Spatial Resolution of the DubaiSat-1 Satellite is 2.5 m (Pan), 5 m (MS).


The Design Lifetime of the EO-1 Satellite is 1.5 years.


The Dimensions of the Instrument Optical Bench is 900 mm x 600 mm x 230 mm.


The Measurement Range of the Particle Detector Instrument is Proton : 1.5 MeV ~ 250 MeV.


The Communication of the Schiaparelli Module is UHF link with the ExoMars Orbiter (with 2 antennas).


The Data Downlink Mechanism of the Experiment Layer Data Management System is Store and playback.


The Observation Continuity of the WFIRST Satellite is More-or-less continuously.


The Anniversary Symposium Date of the TRMM Satellite is Nov. 12, 2012.


The Redundancy of the Battery Power Storage Device is 1 pack loss allowed.


The Attitude Determination of the S/C Satellite is Two STA (Star Tracker Assembly).


The Data Rate Control of the Radio Subsystem Satellite Subsystem is Manual and Automatic.


The Mission of the ARIEL Satellite is Study the composition of exoplanets, how they formed and how they evolve.


The Volume of the Lunar Flashlight Satellite is 255.


The Camera Type of the OPTSAT 3000 Satellite is Unknown.


The Features of the Prometheus Block 2 CubeSats Satellite is Four deployable solar panels, an active attitude control system with stellar sensors, and a SDR (Software Defined Radio) with a footprint sufficiently small for tactical operations.


The Prime Contractor of the NIRSpec Near-Infrared multi-object Spectrograph is EADS Astrium GmbH.


The Ground Pixel Size of the HSRS Sensor is 372 m.


The Project Team Member of the SHIZUKU Satellite is Matsuaki Kato.


The Profiles Per Day Goal of the FormoSat-7 / COSMIC-2 mission Satellite Mission is 10,000.


The Previous Catalogue Object Count (1991) of the Gaia Catalogue of Nearby Stars Stellar Census is 3803 celestial objects.


The Minimum Detectable Pulse of the Rangefinder Module Laser Altimeter is 6 photons.


The IR Channel Detectors of the SEVIRI Spectral Imager is HgCdTe.


The Cell Efficiency of the Solar Arrays Power Generation is 27%.


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


The Function of the PSS Power Supply Subsystem is Stores, distributes and manages electrical power for all electrical equipment.


The Coordination Location of the GBOT Project is Heidelberg.


The Mass of the Shakuntala Satellite is Less than 15 kg.


The Separation Distance of the Optics Assembly Telescope is 285 mm.


The Affiliation of the Şiir Kılkış Associate Professor is Urban Knowledge-Action Committee Network.


The Form Factor of the Dove-1 Nanosatellite is 3U CubeSat.


The Altitude Range of the LEO Altitudes Satellite Orbit is 150 km to 800 km.


The Spatial Resolution of the PMC Imager is 8 m.


The Date of the Maui’s Iconic Waves Image is 16 May 2022.


The Ellipse Axis C of the Short Wavelength Band Spectrometer is 242.6 mm.


The Spectral Range of the MEGS Spectrograph is 5-105 nm.


The Slew Capability of the CMG Control Moment Gyroscope is Up to ±30º.


The Thermal Cycle Test Environment of the Flight Model Satellite Model is -20 to 50 degrees.


The Mass of the STAFF/DWP Instrument is 5.6 kg.


The Attitude Calculation of the RAX-1 Satellite is Not yet been calculated.


The Groundstation Pass Sharing of the Carbonite-1 Satellite is With other commercial satellites operated by SSTL.


The Mass of the QSat-EOS Microsatellite is 49 kg.


The Activation Date of the ISERV Pathfinder EO Sensor is March 3, 2013.


The Launch Site of the GHGSat-D Satellite is Satish Dhawan Space Center (SDSC) in India.


The Flexibility of the Coprocessor Satellite Component is Can be programmed in orbit for different purposes.


The Measurement Record Start Date of the Copernicus Sentinel-6 Michael Freilich Satellite is 1992.


The Days in Space of the Genesis-2 Satellite is More than 150 days.


The Launch Date of the XMM-Newton Satellite is April 2, 2015.


The Mass of the Arkyd-3 CubeSat is 4 kg.


The Wavelength Range of the Band No 2 Spectral Band is 0.70 ± 0.2 - 1.10 ± 0.2 µm.


The Number of Stacer Boom Systems of the THEMIS Constellation Satellite Constellation is 10.


The Distance IAR Duration of the Integer Ambiguity Resolution Process is Roughly 15 minutes.


The First European Mission to Launch Multiple Small Satellites Date of the Vega Launch Vehicle is 3 September 2020.


The Operation Status of the Ikonos-2 Satellite is Nominal.


The Orbit of the AVUM Spacecraft is Required Disposal Orbit (1450 km x 304 km, i=69.5º).


The Orbit Altitude of the WFIRST Satellite is One million miles.


The Orbit of the GOMS-1 Satellite is Geostationary orbit.


The Unknown of the BepiColombo Laser Altimeter Instrument is Unknown.


The Data Downlink Speed of the Payload Satellite Payload is 4 Gbit/s.


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


The Development Location of the SPIDER Telescope is Advanced Technology Center in Silicon Valley.


The Power Transmission of the IOV Payload Satellite Payload is Flexible.


The Function of the SES Instrument is Confirm the energy resolution and measurement noise are unaffected by changes in light level and temperature.


The Stiffness of the Antenna Communication is > 40 Hz (during launch in longitudinal direction).


The ROM of the OBDH Data Handling and Processing is 64kB.


The Mass of the ST (Star Tracker) Instrument is 1.2 kg.


The Next Step Date of the Air Quality Monitoring Activity is March 28, 2014.


The Design Lifetime of the Rover Rover is Around 90 Earth days.


The Ground Operations Provider of the CloudSat Satellite is USAF/STP (Space Test Program).


The Attitude Control of the ADCS unit Satellite Component is Magnetic detumbling.


The Type of the Lithium ion battery Power Source is Rechargeable.


The Length of the PM Satellite Component is 11.2 m.


The Time to Reduce Pressure from 95% to 80% of the Thruster Propulsion System is Approximately two seconds.


The Managing Entity of the MoonLIGHT Satellite is ESA.


The Function of the BSA Beam Steering Assembly is Deviating a pulsed high-energy UV laser beam to compensate for the pointing misalignment between the emission and reception paths of ATLID.


The Solar Sail Deployment Test Date of the NEA Scout Spacecraft is 28 June 2018.


The Development Status of the Pelican Satellite Constellation is Expected to begin launching early next year.


The Mass of the SOLSPC Radiometer is 32 kg.


The Function of the AIU Subsystem is Monitors the operating state of the electronics subsystem and the operating state of the antenna subsystem.


The Instrument Type of the Satellite EO is Cloud profile and rain radars, High resolution optical imagers, Earth radiation budget radiometers, Space environment, Magnetic field, Other, Atmospheric chemistry, Communications, Precision orbit, Data collection, Radar altimeters, Imaging microwave rada.


The Assembly of components of the Metering Truss Structural Component is Brazed assembly of components.


The URL of the OPS-SAT Satellite is http://www.esa.int/ESA_Multimedia/Videos/2019/12/OPS-SAT_the_flying_laboratory.


The Orbit Inclination of the EAGLE Secondary Payload is 0º.


The Diameter of the Antenna Instrument is 1 m.


The Daily Coverage of the GeoCarb Instrument is CONUS > once per day.


The Orbital Altitude of the SPOT-4 Satellite is Increased slightly.


The URL of the BepiColombo Mission is http://www.stp.isas.jaxa.jp/mercury/index-e.html.


The Total Channels of the Spectral Bands Spectrometer is 433.


The Launch Delay of the Landsat-9 Satellite is Liquid nitrogen shortage.


The Deorbit Timeline of the NRCSD Payload is Within 18 months.


The Bandwidth of the Radiometers Instrument is 10 kHz.


The Pass Over of the RainCube Satellite is North-eastern edge.


The Binning of the ICON FUV Instrument CCD is 4 x 4.


The 3rd Lunar Night Time Hibernation Period Start Date of the Yutu Lunar Rover is Feb. 22, 2014.


The Presentation of the IXV Avionics is IXV avionics, from design to mission results.


The Mission Objective of the SpooQy-1 CubeSat is Demonstrate an entangled photon light source.


The Inclination of the Resurs-P1 Satellite is 97.3º.


The Perilune Altitude of the Rstar Data Relay Microsatellite is ~100 km.


The Components of the Look-Up Table Model is Radiative transfer simulations by MODTRAN.


The FOV of the Instrument Spectrometer is 4 x 150 arcmin.


The Type of the Schiaparelli Module is Entry, Descent and Landing Demonstrator.


The Cross-Track Orientation of the ISA Sensor is Up to 30º.


The Mission Date of the PAZ Satellite is Sept. 6-11, 2010.


The Purpose of the SPEXone Instrument is Improve OCI measurements.


The Structure of the Milky Way Galaxy is Warped galactic disc with hundreds of billions of stars.


The Launch Date of the Galileo Satellite Navigation System is Unknown.


The Key Applications of the GHOSt Satellite Constellation is Capturing critical environmental and situational awareness information for defence, detecting minute real-time changes in physical infrastructure, monitoring energy infrastructure and regulatory compliance, detecting environmental erosion and degradation,.


The Confidence Level of the IRS Sounder Satellite is 68.26%.


The Data Quantization of the DubaiSat-1 Satellite is 8 bit.


The Equipment Modules of the Terra Satellite is Populated on the zenith face of the spacecraft.


The Number of Satellites of the FormoSat-3/COSMIC-1 Satellite Constellation is 6.


The Number of Panels of the Solar Array Power Generation is 3.


The Inclination of the Swarm-B Satellite is 87.75º.


The Orbit Accuracy of the Gaia Satellite is Within 150 m at 1.5 million km.


The Diameter of the 55 Cancri e Exoplanet is Almost twice that of Earth.


The Mission Status of the SkySat Constellation Satellite Constellation is Operational (nominal).


The Manufacturer of the FASat-Alfa Satellite is SSTL.


The Band 3 of the CIRiS Instrument is 11.77 µm to 12.6 µm.


The Number of the TDI Stages Imaging System is 8.


The Azimuth Dimension of the Active Phased Array Antenna Antenna is 15 m.


The Launch Date of the JPSS-1/NOAA-20 Satellite is Nov. 18, 2017.


The Global Average Detection Rate of the COM DEV NTS Receiver AIS Receiver is 14.8 Messages/s.


The Quantity of the Secondary Payloads Satellites is 30.


The Structure Material of the TUBSAT-N Satellite is Carbon fiber.


The Cadence of the Imaging Instrument Instrument is Fast.


The Downlink Data Rate of the NSat Satellite is 9.6 kbit/s.


The Launch Date of the Weather Observation Satellite Satellite is April 17.


The Front Face Diameter of the MoonLIGHT Retroreflector Space Device is 100 mm.


The Number of Detectors of the Focal Plane Module Satellite Component is ~500 multispectral, 1000 panchromatic.


The Design and Status Presentation Date of the PAZ Ground Segment Ground Segment is June 3-5, 2014.


The Object Detection Capability of the Imaging System Imaging System is Objects as small as 2 mm in length.


The Payload Data Memory of the SAR antenna Antenna is 544 GByte.


The Mission Date of the Chandrayaan-1 Satellite is April 25-30, 2010.


The Award Date of the Reef Support Project is 10 December 2020.


The Power Consumption of the UPM-1T card Mass Memory is 3 W on average.


The Mass of the SIR-2 Instrument is 2.3 kg.


The Next Testing Steps of the TEMPEST-D Radiometer Instrument is TVAC (Thermal Vacuum) testing and antenna radiation pattern testing.


The Effect of the Clouds Weather Phenomenon is Can cause scattered clouds resulting in links that are only partly available.


The Filter Banks of the Dual-channel Receiver Unit (DRU) Receiver is Same as LGU.


The Frequency of the UHF Band is 435 MHz.


The Imaging of the DAVINCI and VERITAS missions Missions is Near-infrared imaging.


The Instrument Type of the GeoEye-1 Satellite is High resolution optical imagers.


The Launch Date of the MMS Satellite is Spring 2015.


The Solar Sail Flyby Velocity of the NEA Scout Spacecraft is Less than 100 feet, or 30 meters, per second.


The Mission Operation Phase of the TET-1 Satellite is One Year.


The Function of the LFS (Low Frequency Spectrometer) Scientific Payload is Low-frequency radio frequency spectrum analyzer for detection of low-frequency radio frequency characteristics of the sun and the moon's low-frequency radio environment to perform low-frequency radio astronomy observations.


The Orbital Drift of the SPOT-4 Satellite is Tolerated.


The Compatible Launch Vehicles of the CubeStack Multi-Payload Adapter is Athena, Minotaur I, Taurus, Pegasus and Falcon 1.


The Observation Field of the Kepler Spacecraft is Constellation Aquarius.


The Application of the HISEA-1 Satellite is Ocean and coastal observations.


The Observation Target of the IBEX Satellite is Heliosheath.


The Mass of the UniSat-1 Satellite is 12 kg.


The Article Publication of the NanoSail-D Satellite is October 2008.


The Panchromatic GSD of the CCD Pushbroom Camera Camera is 5m.


The Operation of the OGS Ground Segment is Ground segment laser communication experiment of SOTA/SOCRATES mission.


The CCD Line Pixel Pitch of the FPM (Focal Plane Module) Focal Plane is 6.5 µm.


The Launch Date of the AERO-VISTA mission Satellite Mission is April 7, 2021.


The Eccentricity of the Explorer 36 Satellite is 0.03165.


The PRN of the GSAT-0103 Satellite is 19.


The Sensor Type of the IDM Ion Drift Meter is Planar sensor.


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