The Designer of the BGO Calorimeter Detector is Prof. LIU Shubin from USTC.


The Orbit Inclination of the BX-1 Microsatellite is 42.4º.


The Launch Date of the Carruthers Geocorona Observatory (GLIDE) Satellite is 2025.


The Height of the TOGS Telescope is 3.5 m.


The Data Transmission of the McMurdo Ground Station Ground Station is Darmstadt.


The Source of Scatter for LαD of the IMAP Satellite is Dim unresolved stars.


The Mission Heritage of the POLDER-P Instrument is ADEOS and ADEOS-II.


The Spacing Between Consecutive Lines of the MS Bands Detector Line Arrays is 936 µm.


The Mission Status of the Eutelsat 172B Satellite is Entered full commercial service.


The Direct Data Reception Locations of the TerraSAR-X Satellite System is US, Japan, and Germany.


The S-band 1Mbit/s Downlink of the UoSAT-12 Satellite is 1.


The Development Period of the Neutrally Buoyant Floats Oceanographic Instrument is Mid-1950s.


The Release Date of the DIWATA-1 Microsatellite is Spring.


The Publication Date of the Gravity Recovery and Interior Laboratory (GRAIL) Mission is 2013 Feb 8.


The Data Supply Agreement of the TerraSAR-X Satellite is Until the end of 2020.


The Material of the Main Tank Propulsion Subsystem is Ti.


The Measurement Interval of the FTS Fourier Transform Spectrometer is Approximately every two minutes.


The Launch Date of the Genesis Satellite is August 8, 2001.


The Camera Types of the Optical Payload Imaging System is One in the VNIR (Visible Near Infrared) range and two imagers in the infrared region.


The Laser-Illuminated Area Movement Time of the Spectral Bands Measurement Device is Corresponding to the desired mapping resolution of water ice (10 km or less).


The Power Supply for ISM Release of the Satellite Spacecraft is Two activations.


The Technology of the VNIR Range Imaging System is Photodiode-silicon readout.


The Distance from Mercury of the Monitoring Camera 3 Camera is 2687 km.


The Displacement Range of the Piezo Instrument is ±6 µm (±1 arcmin).


The Payload Capacity of the Terran R Launch Vehicle is More than 20,000 kg.


The Launch Date of the SAOCOM-1A Satellite is 2015.


The Conference Date of the Tandem-L SAR System is June 4-7, 2018.


The On Orbit Noise Power of the RAX-1 Satellite is -113 dBm.


The Purpose of the MIPA Ion Mass Analyzer is Provide monitoring of the precipitating ions.


The Bands of the Spectral Bands Spectrometer is SWIR, MWIR, TIR.


The URL of the PSLV Satellite is https://www.isro.gov.in/mission_PSLV_C40.html?timeline=timeline#:~:text=PSLV%2DC40%2FCartosat%2D2%20Series%20Satellite%20Mission&text=India's%20Polar%20Satellite%20Launch%20Vehicle,613%20kg%20at%20lift%2Doff.


The Unknown of the MAXI/SEDA Experiment is Unknown.


The Paper Title of the Nikolai A. Tsyganenko Researcher is Data-based modeling of the geomagnetosphere with an IMF-dependent magnetopause.


The End of Operations of the Resurs-P1 Satellite is 2021.


The Remarks/Sensors of the OrbView-1 Satellite is GPS.


The Autonomous Abort Response Distance of the ASTRO Satellite is 120 m.


The Mission Planned Life-cycle of the SAMPEX Satellite is Three years.


The Array Size of the Camera Sensor Imaging System is 578 x 576 array.


The Instrument Mass of the HySI Hyperspectral Imager is 4 kg.


The Function of the XFS Xenon Gas System is Stores xenon gas in a high pressure vessel and provides the xenon gas for the thruster head.


The Role of the UNM (University of New Mexico) team Organization is Integrators of the CubeSat.


The Hamamatsu PMTs of the Range Calorimeter Particle Detector is 2 per plane.


The Filter of the BRITE Telescope is Different from Another BRITE Satellite.


The Managing Office Location of the Lucy Discovery Program Mission is NASA's Marshall Space Flight Center in Huntsville, Alabama.


The Time Resolution of the X-ray Satellite Navigation Navigation System is 1 µs.


The Back Plate Coating of the Thermal Control Louvers Thermal Regulation Device is Highly emissive coating.


The Operating Mode of the CIRiS Infrared Imaging System is Pushbroom.


The Edge Design of the Hayabusa-2 Sampler Horn is Folded back inward.


The D-STAR Capability of the OUFTI-1 Satellite is Provides a repeater functionality to any D-STAR equipped ham-radio operator.


The Mission Status of the Rosetta Spacecraft is Active.


The Purpose of the RHESSI Satellite is Imaging spectroscopy of hard X-ray (HXR) and gamma-ray continua emitted by energetic electrons, and gamma-ray lines produced by energetic ions.


The Type of the ELaNa X Payload is 3 P-PODs (Poly Picosatellite Orbital Deployers) containing a total of four CubeSats.


The Grating Figure of the Short Wavelength Band Spectrometer is Ellipse of rotation.


The Sensor Type of the Astro-APS Star Tracker is CMOS Active Pixel Sensor.


The Purpose of Orbit Parameters of the LAGEOS Satellite is Minimizing the effects of disturbing forces.


The Time to Scan a Full Disk of the GK-2A Satellite is About one-fifth of the current 28 minutes.


The Attitude Control Error of the ETS-VIII LRRA Satellite is Roll (< ±0.05º), Pitch (< ±0.05º), Yaw (< ±0.15º).


The Physical Baseline Length of the KaRIn Instrument is 10 m.


The Rotation Period of the Kepler 11145123 Star is Three times more slowly than the Sun.


The Installation Date of the DESIS Instrument is July 2, 2018.


The Tracking Direction of the NEOSSat and Sapphire Satellites is Antisolar direction.


The Missions of the Altimetry Satellites Satellites is TOPEX/Poseidon (1992-2006), Jason-1 (2001-2013), Ocean Surface Topography Mission/Jason-2 (2008-2019), and Jason-3 (2016 to present).


The Partner Responsibilities of the Jason-2 Satellite is Overall system integration, Earth terminals and part of the ground network, near-real-time product processing, archiving, product dissemination, user support, science algorithm development, calibration and validation activities.


The Discovery Date of the Andrew Vanderburg, Pamela Rowden, Steve Bryson, Jeffrey Coughlin, Natalie Batalha, Karen A. Collins, David W. Latham, Susan E. Mullally, Knicole D. Colón, Chris Henze, Chelsea X. Huang, and Samuel N. Quinn Astronomers is 28 February 2020.


The Cooperative Research and Development Agreement Partner of the SpaceX Company is U.S. Space Force.


The Robotic Arms Function of the Satellite Platform is Orientation of the satellite's electric propulsion thrusters and to control thrust direction and attitude.


The Task of the Restore-L Satellite is Manipulate its fill and drain valve.


The Structure of the Sojourner 2020 Art Payload is Three-layer telescoping structure.


The Function of the DPP Signal Processing Device is Digitizes the preamplifier output, applies real-time digital processing to the signal, detects the peak amplitude, and bins this in its histogram memory.


The Diameter of the South Pole-Aitken Basin Impact Region is Roughly 2,500 km.


The Disaggregation Capability of the Cellular Satellite Architecture Satellite Architecture is Allows the disaggregation of typical space vehicles into as many or as few cardinal pieces (called satlets) as required.


The Observation Location of the ENVISAT satellite Satellite is Luzon Strait.


The Orbit Type of the DSX spacecraft Satellite is Elliptical MEO.


The Wind Random Errors of the Aeolus Satellite is Compliant to the mission requirements in the free troposphere for the Mie channel for laser output energies above about 65 mJ.


The Aperture Diameter of the IRIS Instrument Spectral Scanner is 120 mm.


The Number of Docking Ports of the Prichal Module Docking Port is 5.


The Cryogen Lifespan of the Instrument Dewar/Heat Exchanger is 15 months.


The CCSDS ID of the GSAT-0102 Satellite is 3A6.


The Inclination of the Anand Satellite is 97.4°.


The Ownership of the TecSAR Satellite is Government owned.


The Slit Width of the Short Wavelength Band Spectrometer is 150 µm.


The Data Quantization of the Instrument Satellite Instrument is 10 bit.


The FWHM at 40 nm of the EUV Simulation Simulation is 5.1 arcmin.


The Design Life of the Satellite Spacecraft is 3-5 years.


The Material Collision Speed of the Cassiopeia A (Cas A) Supernova Remnant is 10 million miles per hour.


The Spectral Range of the Instrument Spectral Imager is 3.92-4.64 µm.


The Database of the Payload Data Processing Software is MongoDB.


The Establishment Date of the MERSEA Project is January 2003.


The Development Status of the ALTIKA Instrument is Unknown.


The Wavelength Range of the PAN Detector is 0.50 - 0.90 µm.


The Number of Star Images of the Star Tracker Optical Sensor is One or two.


The Diameter of the Ceres Dwarf Planet is 950 km.


The News Date of the SCD-2 Satellite is Dec. 17, 2014.


The Control Devices of the Attitude Control Subsystem Attitude Control System is Reaction wheels and magnetic torquers.


The Installation Date of the Bartolomeo Platform is 2 April 2020.


The Data Rate from OBC to FPGA of the Transmission Module FPGA Module is 10 Mbit/s.


The Bays of the Bus Structure Satellite Component is 9.


The Mission Type of the Hera Space Probe is Rendezvous with a binary asteroid system.


The Orbital Tube Diameter of the Tandem-L Satellite is 500 m.


The Location of the F-DUGS Center is France.


The Re-entry Date of the AeroCube-3 Satellite is January 6, 2011.


The Spatial resolution at nadir of the MWTS Microwave Temperature Sounder is 50/75 km.


The Formation of the MMS Satellite is Four spacecraft flown around Earth in a pyramid formation.


The TEC of the X123-SDD X-ray Spectrometer is Active 2 stage.


The Effective Emissivity of the MLI Thermal Control Device is ε < 0.05.


The Chang'e 5 Weight of the Chang'e-5 Lunar Mission is 8.2 metric tons.


The Abundance in Plasmasphere of the He+ ions Ion is Up to 15% of the total plasma density.


The URL of the SwissCube Satellite is https://phys.org/news/2016-09-swisscubeseven-years-space.html.


The Timing Accuracy of the STOs and STAEs Analog Electronic units is ±1 µs.


The Capacity of the Memory Data Acquisition System is 50 GB.


The Momentum Capacity of the Reaction Wheels Attitude Control is 80 mNms.


The Manufacturer of the TecSAR Satellite is Israel Aerospace Industries Ltd (IAI).


The SpaceOps 2010 Conference Date of the Resourcesat-1 Satellite is April 25-30, 2010.


The Normal Matter Percentage of the Universe Cosmology is Under 5%.


The Inclination of the BeaverCube Satellite is 51.6°.


The Attitude Control Accuracy of the Spacecraft Satellite is < 1.0º.


The URL of the Galileo Satellite System is http://m.esa.int/Our_Activities/Space_Engineering_Technology/Combined_orbital_Galileo-GPS_position_fix_achieved_aboard_ISS.


The Test Location of the Power Subsystem Satellite Subsystem is Thruster manufacturer's vacuum chamber.


The Status Report Date of the Space Situational Awareness System is Oct. 8, 2015.


The Diameter at the Base of the Nimbus-7 S/C Satellite is 1.52 m.


The Structure Assembly Time of the CXBN-2 Spacecraft is Months rather than years.


The Low-Energy Transmitter Range of the OLA LIDAR Instrument is 500 m to 1 km.


The Bandwidth of the Radar Radar is 5 MHz.


The Number of HTS Experiments of the HTSSE-II cryogenic subsystem Cryogenic Subsystem is 8.


The Components of the Offner Spectrometer Optical System is Relay mirror and a spherical convex diffraction grating.


The Justification of the ACE Satellite is Better understand the consequences of the declining phase of the solar cycle and a very low solar minimum.


The Affiliation of the ALMASat Microsatellite is University of Bologna.


The Control Location of the FORTE Satellite is Sandia Labs.


The Starlink Satellites Launch Date of the SpaceX Company is 16 February 2021.


The Command Data Rate of the S-band transponder Communication Device is 2 kbit/s.


The Total Mass of the DSX Spacecraft Payload Module Satellite is 600 kg.


The Horizontal Baselines of the Tandem-L Satellite is 1 km to 18 km.


The Targets of the GSPC Instrument is Cyg X-2, 4U1636-53, Her X-1, Coma, Cyg X-3, Perseus, Cyg X-1, Cas A, Crab, Cen X-3, Cen X-2, and Vela X-1.


The Conference Presentation Date of the THEMIS Satellite is Aug. 8-11, 2005.


The Photoresistor of the Solar Panel Power System is Mounted to its outer face.


The Diameter of the Bennu asteroid Asteroid is 525-m.


The Instrument Mass of the EIC Camera is 2.5 kg.


The Orbit Altitude of the CubeSats Satellite is 550 km.


The Separation Time from Hayabusa-2 of the MASCOT Lander is 03:58 CEST.


The Communication Protocol of the Nanosatellite Satellite is Bluetooth.


The Principal Investigator of the GIADA Contamination Monitor is Luigi Colangelo.


The Function of the ISIS Instrument is Provide access to the nominal direction of the Parker Spiral magnetic field.


The Antenna of the Phoenix GPS Receivers GPS Receiver is L1/L2 antenna.


The Output of the HET-X Hall-effect Thruster is 20 - 150 millinewtons.


The Uplink Lock Time of the LLCD PAT Systems Communication System is Within seconds.


The Orbit of the EnviSat Satellite is Not provided.


The Microcontroller Flash Memory of the CC430 SoC System on Chip is 32 kB.


The Locking Time of the Carrier Offset Frequency Frequency is T0+84 s.


The Eccentricity of the SMART-1 Satellite is 0.359146.


The Design Presentation Date of the Microsatellites Satellite is Oct. 10, 2002.


The Subswaths of the C-RADAR Phased Array Antenna System is 4 C-band subswaths.


The Antennas of the SOURCE 3U CubeSat Satellite is 2.


The Power Area of the Solar Panels Power Source is 80 square meters.


The Product Announcement Date of the Spire Global Satellite Operator is September 11, 2019.


The Data Transmission Rate of the X-band Communication Band is 5 Mbit/s.


The Area of the Colorado River basin Basin is 246,000 square miles (637,000 km2).


The Orbit Date of the Cluster Satellite Constellation is December 29, 2006.


The Transmitted Wavefront Distortion of the Optical Window Component is λ/8 at 633 nm.


The Color of the Laser Source Optical Component is Orange.


The Disintegration Recording of the ATV-5 Satellite is Camera.


The Orbits of the DSLP Data Acquisition System is 5500.


The Freeboard Measurement Data Source of the A-68A Iceberg is ESA’s CryoSat mission, US ICESat-2 mission.


The Band 7 Wavelength of the OCM Payload is From 760 nm to 740 nm.


The Unpressurized Trunk Mass of the Dragon Resupply Vehicle Resupply Vehicle is 960 kg.


The Mass of the Spacecraft structure Satellite Subsystem is 0.48 kg.


The Power Supply of the RAMIS Radiation Detector is 12 V (M1), 28 V (M2).


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


The Ground speed of the KOMPSAT-3 Satellite is 6.78 km/second.


The Cargo Weight of the Dragon Spacecraft is More than 5,700 pounds.


The Pointing Accuracy of the Spacecraft Satellite is < 0.02º.


The Conference Date of the Solar Orbiter /PHI Full Disk Telescope Telescope is Oct. 7-10, 2014.


The Launch Location of the SpaceX Launch Provider is Cape Canaveral Air Force Station in Florida.


The Mission of the ALADIN LIDAR Instrument is AEOLUS.


The Depth of the South Pole-Aitken Basin Impact Region is 13 km.


The DPU of the ASCAT Scatterometer is Digital Processing Unit.


The Date of the Close Approach Event Orbital Event is April 9, 2015.


The URL of the Cosmic Ray Isotope Spectrometer Spectrometer is http://www.srl.caltech.edu/ACE/CRIS_SIS/cris.html.


The Swath Width of the ScanSAR-1 Mode is 100 x 2500 km.


The Launch Date of the H-IIB Launch Vehicle No. 2 Launch Vehicle is Jan. 22, 2011.


The Deployment of the Flock-4v Satellite is ISL’s QuadPack deployers and D-Orbit’s InOrbit Now (ION) free-flying deployment platform.


The Channels of the MIS Instrument Microwave Radiometer is 39.


The Data Transport of the SPA-1 Interface is Unknown.


The Instruments of the CAS500 Satellite is CSAR, Compact Advanced Payload Wide Swath, High Resolution Optical Sensor.


The Image License of the CaSSIS Instrument is CC BY-SA 3.0 IGO.


The Spatial Resolution of the SST Product Dataset is 2 km.


The Types of Environmental Data Records (EDRs) of the IDPS Interface Data Processing Segment is Cloud coverage, temperature, humidity, ozone distribution, snow cover, vegetation, sea surface temperatures, aerosols, space environment, earth radiation budget information.


The Sun Aspect Sensors of the ERG Satellite is 2.


The Mission of the Medium Energy Neutral Atom (MENA) Imager Imager is IMAGE.


The Observable Particle of the Particle Detector Instrument is Proton, deuteron, tritium, helium.


The Transport Destination of the Beresheet Spacecraft is Cape Canaveral Air Force Station.


The RF Communications of the Spacecraft Satellite is 0.5 W (S-band downlink).


The Energy of the S-band Band is 10 µeV.


The Measurement Error of the Angular Rate Sensor is Random < 0.1º/s (1σ), Bias < 0.6º/s, Nonlinearity < 0.5%.


The Probe Type of the Electron Temperature Part Experiment is Three simple circular planar probes with guarding rings.


The Observation Date of the Space Sparkle Supernova Remnant is 7 January 2019.


The Type of the LituanicaSAT-2 Satellite is 3U CubeSat.


The Flare Eruption Time of the IRIS Observatory is 19:40 UTC.


The Agreement Date of the COMSAT, Inc. Service Provider is February 19, 2018.


The Communication Links of the TT&C subsystem Satellite Subsystem is S-band (2 GHz, command uplink and telemetry downlink).


The Mission Type of the TacSat-3 Satellite is Technology demonstration.


The Launch Date of the CIMON-2 Crew Interactive MObile companioN is 5 December 2019.


The Solar Array Power of the Power Subsystem Subsystem is 35 W.


The Manufacturer of the SCM Instrument is CNRS/CETP.


The Instrument Size of the SBVR Power Supply is 750 mm x 247 mm x 348 mm.


The Redshift Range of the NISP Spectrograph Instrument is 0.7 to 2.0.


The Heritage of the ADCS Attitude Determination and Control Subsystem is Previous GNB missions.


The Number of Photo MOSFET Switches of the DLP System Satellite System is 5.


The Atmospheric Species of the SciSat-1/ACE Satellite is Over sixty.


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


The Launch Date of the Global Surface Water Survey Mission Satellite Mission is Unknown.


The Closest Approach Distance to Ganymede of the Juno Spacecraft is 645 miles (1,038 km).


The Mission Status of the SOHLA-1 Satellite is Retired.


The Power of the ADEOS spacecraft Satellite is 4.5 kW.


The Number of Venus Flybys of the V7GA Mission is 7.


The Planning Window Length of the RASP Maneuver Planning System is 60 minutes.


The Bus Structure of the Tsubame Microsatellite is Lattice structure (CFRP material).


The Brochure URL of the Optical Inter-orbit Communications Engineering Test Satellite (OICETS) Satellite is http://global.jaxa.jp/activity/pr/brochure/files/sat09.pdf.


The Cumulative Absolute Height Error of the TanDEM-X Satellite is 0.9 m.


The Jet Behavior of the V404 Cygni Black Hole is Strange.


The Launch Dates of the GeoOptics Satellite Manufacturer is June 2017 and January 2018.


The T/R Modules Design and Performance Presentation Date of the TanDEM-X Satellite is June 2-5, 2008.


The Team Communication of the HORYU-4 Satellite is Problems.


The Microcontroller Architecture of the CDHS Command and Data Handling Subsystem is 16 bit, modified Harvard architecture.


The Hosting Spacecraft Provider of the DSAC Demonstration Unit is Surrey Satellite Technologies US LLC.


The Population of the Kolkata City is Over 14 million inhabitants.


The Altitude of the PhoneSat-2.5 1U CubeSat Satellite is ~400 km.


The Photometric Precision of the CHEOPS Satellite is Similar to the Kepler mission of NASA.


The Launch Date of the ALTIUS Satellite is May 2025.


The Pointing Axis Off-Pointing Angle of the Spectrometer (SPI) Spectrometer is 2.17º.


The Propellant Tank Capacity of the Cold Gas System Attitude and Orbit Control Subsystem is 132 l.


The Design of the Transceivers Communication Device is Dual receive (Rx)/transmit (Tx).


The Travel Time from Ganymede to Jupiter of the Juno Spacecraft is 14 hours, 50 minutes.


The Number of PHM Clocks of the GIOVE-A Satellite is 2.


The Availability of the Global Satellite Mapping of Precipitation (GSMaP) Satellite Data is Since March 2000.


The Observation Continuation of the SoloHI Heliospheric Imager is Until it leaves its field of view on 22 December.


The Payload of the MetOp Second Generation Satellite is Unknown.


The Funding Source of the ELFIN Satellite is AFRL (Air Force Research Laboratory).


The Rotation per Image of the M-CAM 1 Monitoring Camera is 3º.


The Operating Temperature of the FEU Faraday Cup Electronics Unit is Approximately 70ºC.


The Number of Rows to Make Two Perfect Rows of the QWIP Array Sensor Array is 3.


The Satellite Mass of the ADEOS spacecraft Satellite is 3560 kg.


The Data of the Aeolus Satellite is Vertical distribution of aerosol and cloud layers.


The Photodetector Technology of the Optical Head Optical Device is CMOS Active Pixel Sensor (APS).


The Grating Order of the Spectrometer Instrument is 1.


The Program Start of the SIR-C/X-SAR Payload is SIR-A in l98l.


The URL of the SARah project Satellite Project is https://www.ohb.de/en/news/2019/satellite-based-radar-reconnaissance-for-germany.


The Year of Launch of the GRACE Satellite is 2002.


The Components of the ACU Control and Data Handling Subsystem is Flash FPGA, CPU, star CCD sensors (HSS-1,2), gyro sensor (GYRO), high-precision sun sensors (SASH-1,2,3,4), reaction wheel unit (RW).


The Handover Date of the Diwata-1 Satellite is January 13, 2016.


The Payload Data Modulation of the Satellite Satellite is PCM/BPSK.


The Swath width of the MWHS Microwave Humidity Sounder is 2700 km.


The Data Backup of the ASAP-Light Camera System is Non-volatile flash memory.


The Solar Panels of the EPS Electrical Power System is 3.


The Renaming Date of the GCOM-C Satellite is July 14, 2017.


The Energy Measurement Range of the Telescope Telescope is 1-40 MeV/n.


The Interest of the SDA Agency is Algorithms and compute capabilities on orbit.


The Maximum Torque of the Reaction Wheels Attitude Control is 5 mNm.


The In-Orbit Calibration Types of the MIRAS Instrument is External, internal.


The Constellation of the Strela-3/Rodnik Military Reconnaissance Satellite is Strela.


The Coverage of the ERS Tandem Mission Satellite Mission is Nearly the whole global land surface.


The Position of the AMSR3 Instrument is Fourth in the AMSR series.


The Clock Frequency of the AIM Reconfigurable Computing Hardware Device is 48 MHz.


The Data Download Speed of the NEMO-HD Satellite is Up to 50 Mbit/s.


The Azimuth Coverage of the SWIM Real Aperture Radar is 180 km.


The Optics Presenter of the Imaging X-ray Polarimetry Explorer Satellite is Brian D. Ramsey.


The Length of the Secondary Mirror Support Structure Support Structure is Almost 25 feet.


The Flashes Measurement of the Tatiana-2 Satellite is More than 1000.


The Stage Type of the Soyuz Rocket is Kerosene-fueled first stage boosters.


The Lunar Eclipse Date of the Spacecraft Satellite is June 4.


The Telescope Sensitivity of the EUVI Extreme Ultraviolet Imager is Higher sensitivity.


The Duration of the Solar Eclipse Event is About two hours.


The Design of the Skylab-1 Space Station is Use leftover Apollo lunar hardware.


The Observing Frequency of the L-SAR Satellite is 1.275 GHz.


The End of Life Date of the TUBSAT Satellite is Spring 2007.


The Mass of the LCT instrument Instrument is 53 kg.


The Length of the Graded Index Multimode Fiber Fiber is 30 meters.


The Mass of the IPEX-II boom ADAM mast is 112 kg.


The Unknown of the Table 1 Information Table is Unknown.


The Swath of the Stripmap mode (SM) Operational Mode is 80 km.


The Full Form of the ESP-MACCS Satellite is Earth System Processes Monitored in the Atmosphere by a Constellation of CubeSats.


The Functions of the Electronics Imager Electronics is Detector and image data operation, calibration mechanism operation and temperature control, cryocooler operation and supervision.


The Design Components of the CHRIS Imaging Spectrometer is Catadioptric telescope, imaging spectrometer, area detector array.


The NORAD ID of the BX-1 Microsatellite is 33392.


The Objective of the Electron Spectrometer Spectrometer is Provide high time resolution (<1 s) solar wind electron, full 3D distribution function observations.


The Onboard Data Storage Capacity of the DTS Data Transmission Subsystem is 128 Gbit.


The Meeting Date of the SHIZUKU and IBUKI Satellites is May 30-June 1, 2012.


The Capacity of the Battery Energy Storage is 11.8 Ahr.


The Mass of the EPS Electrical Power Subsystem is 167 g.


The Telemetry Data Rate Range of the TTCS Telemetry & Telecommand Subsystem is 4-16 kbit/s.


The Sampling Coordination of the Magnetometer Instrument is Coordinated with pulsing by the magnetorquers.


The Maximum Slope of the Schiaparelli Lander is 12.5º.


The Validation Date of the NASA ESTO technologies Technologies is July 22-27, 2012.


The Width of the Umbra Shadow is 50-100 km.


The Maneuver Execution Time (60 minute window) of the RASP Maneuver Planning System is 176.7 minutes.


The Purpose of Funding of the Brazilian Ministry of Defense Government Agency is Buy an undisclosed satellite imaging system for Amazon monitoring, both for civilian and military use.


The End of Life Date of the DMC-3 Satellite Constellation is 10 Oct 2022.


The Number of Lunar Flybys of the ICE (International Cometary Explorer) Spacecraft is 5.


The Spatial Resolution of the Satellite Imaging Instrument is High.


The Spotlight High Resolution (HS) Image Size of the TSX-SAR Satellite is 5-10km x 5km.


The Components of the Stack Level Testing Configuration is MPO (and Japanese orbiter MMO), MTM ion propulsion with twin thruster operation.


The Mass of the PRESat Satellite is ~4.5 kg.


The Volume of the Radio and Antenna Communication System is 0.25U (2.5 cm x 2.5 cm x 10 cm).


The Use as Transfer Radiometer of the S-NPP VIIRS Satellite Instrument is Unknown.


The Spectral Calibration of the SUCHI Instrument is Pre-flight.


The Design Life of the Spacecraft bus Satellite is 5 years.


The Launch Date of the JPSS-2/NOAA-21 Satellite is 10-11-2022.


The Mass of the S-band Transmitter Transmitter is 0.1 kg.


The Unknown of the Formosat-2 Satellite is Unknown.


The Swath Width (Simultaneous) of the HRV Imager is 117 km.


The Propellant Transfer of the Tianzhou-2 Cargo Spacecraft is 1.95 tons.


The SpaceWire Transfer Rate of the OBC On-Board Computer is 10 Mbit/s.


The Orbit Inclination of the ResourceSat-1 Satellite is 98.7°.


The Power Dissipation of the LCT Optical Instrument is Varies.


The Detector Type of the OSIRIS Infrared Imager is One-dimensional InGaAs (128 pixel) linear arrays.


The Electronics Package Power of the FlaPS Instrument Package is 1.5 W.


The URL of the Resurs-P1 Satellite is http://eng.ntsomz.ru/news/news_center/resurs-p_images_gallery_201308.


The Based on of the Beijing-3B Satellite is Beijing-3A.


The Launch Date of the Envisat Satellite is March 1, 2002.


The Image Capture Time of the Monitoring Camera 3 Camera is 23:44:57 UTC.


The No. of Detectors/Channels of the Visible Spectral Band Spectral Band is 4 (+4 spare).


The Mass (kg) of the RISAT-1 Satellite is 300.


The Mass of the STX-01 S-band Transmitter/Transceiver is 80 g.


The Launch Date of the JERS-1 Satellite is 11 Feb 1992.


The Launch Date of the Resurs-P3 Satellite is March 2016.


The Bit Rate of the LIMS Instrument is 4 kbit/s.


The Camera FOV of the Observation of non-cooperative objects Experiment is 14o.


The Frequency Response of the SCM Sensor is ELF/VLF range.


The Deployment Switches of the Radar Instrument is 4.


The Calibration of the AVHRR/3 Instrument is Calibration of the IR channels is performed with four internal blackbodies every scan line.


The Spatial Resolution of the Lunar Flashlight Spacecraft is 10 km or better.


The Exceeded Design Life of the Terra Satellite is Yes.


The Radio Signals of the Hitomi Satellite is 3/28 22:06 (for about 10 sec) @ USC.


The Number of Rows of the QWIP Array Sensor Array is 512.


The Location Accuracy of the LIS Lightning Image Sensor is Within one pixel.


The Number of Focal Plane Modules of the OLI Imaging System is 14.


The Function of the Array of Cylindrical Lenses Optical Component is Image the telescope pupil onto the detector.


The Break-out Time of the Hitomi Satellite is 10:42±11M.


The Polarization, Left Swath of the KaRIn Instrument is HH.


The Post-Flight Analysis Recommendations of the Automated Transfer Vehicle Spacecraft is 130 technical recommendations.


The Sample Collection Opportunities of the OSIRIS-REx Spacecraft is 3.


The Lead Author of the Kepler space telescope Telescope is Steve Bryson.


The Heat Shield Maximum Temperature of the Orion Spacecraft is 2750ºC.


The Band 5 of the MSS Instrument Spectral Band is 0.6 - 0.7 µm.


The Observation Range of the Limb Sensing Instrument Spectrometer is Tangent radius upward.


The Provider of the MetOp-B Satellite is EUMETSAT.


The Science Objective of the MinXSS Satellite is Better understand the solar irradiance energy distribution of solar flare SXR (Soft X-Ray) emission and its impact on Earth's ITM (Ionosphere, Thermosphere, and Mesosphere).


The Ground Segment Design Presentation Date of the EnMAP Satellite is 7 March 2013.


The Measurement Category of the SkySat Constellation Satellite Constellation is Multi-purpose imagery (ocean), Multi-purpose imagery (land).


The Fabrication Finesse of the Etalon Filter is ≥ 30.


The Downlink Data Volume of the IXPE Satellite is ~600 MB/day.


The Launch Date of the OneWeb Satellite Communications Company is From 2022.


The Number of Channels of the AMSU Microwave Radiometer is 15.


The Launch Date of the ORS-3 Mission Satellite Mission is August 2013.


The Manufacturer of the SARah system Satellite System is OHB and Astrium.


The Control Type of the Tom 2U CubeSat is Active.


The Contract Award of the PlanetIQ Satellite Manufacturer is $3.5 million.


The Depth of the Tohoku-Kanto earthquake Earthquake is 32 km.


The Output Data Rate of the Spacecraft 406 MHz Processor Processor is 2.4 kbit/s.


The Launch Time of the Crew Dragon Spacecraft is 8:02 p.m. EDT.


The DET System of the EPS Electric Power Subsystem is 21-35 V.


The Launch Date of the Parker Solar Probe Satellite is Summer of 2018.


The Orbit Inclination of the CINEMA satellites Satellite is High.


The URL of the XMM-Newton Satellite is http://www.esa.int/Science_Exploration/Space_Science/XMM-Newton_maps_black_hole_surroundings.


The Design Features of the Channelizers/filters Signal Processing is 4 channel input multiplexer @ 4 GHz, 4 channel filter @ 4GHz, 5 channel input multiplexer @ 8 GHz.


The Current of the Voltage 7 Power Amplifier is 475.


The View of Venus of the Parker Solar Probe Spacecraft is Stunning.


The Orbits of Planets of the Kepler-11 Star System is Smaller than Venus and Mercury's.


The Calibration Activities Duration of the SGLI Sensor is First year.


The Unknown of the NASA Cargo Cargo is Unknown.


The Number of Satellites of the CIMR Satellite is Three.


The Torque of the Canopus Pipper Satellite is 1.6 x 10 -4 Nm.


The Beam Pointing Error of the Antenna Communication is Less than 0.83º (static)/0.0045º (dynamic).


The Temperature Uncertainty of the Instrument Spectrometer is 0.1K at the bottom of the limb to 13 K at 140 km.


The Purpose of the Grating Reflection Unit Spectrometer Component is Manipulation and compression of high-power ultra-short laser pulses.


The Number of Channels of the NorAIS-2 Receiver AIS Receiver is Four.


The Measurement Domain of the JPSS-2/NOAA-21 Satellite is Atmosphere, Land.


The SNR Linearity of the SCATSat-1 Satellite is Even at SNRs as low as -45 dB.


The Design and Performance Presentation of the QZSS Satellite System is ION NTM (National Technical Meeting) 2007, San Diego, CA, USA, January 22-24, 2007.


The Number of Deorbited Relay Stations of the Starlink Communication Satellite is 3.


The Prototype Name of the BEAM Module is Bigelow Expandable Activity Module.


The Spectral Resolution of the UV-2 Spectrometer is 0.45 nm.


The Structure Material of the HIT-Sat Satellite is Aluminum alloys, AL2219 and AL5052.


The Power of the GeoCarb Instrument is 128 W.


The Operation Start Date of the Cluster Satellite Mission is 1 September 2000.


The CCD Cameras of the HJ-1A Satellite is 2.


The Magnetic Field Measurement Channels of the IOF Plasma Wave Instrumentation is 7.


The Architecture of the TechEdSat Satellite is 1U cubesat.


The Operational Capability of the MRC (Medium-Resolution Camera) Camera is Achieved.


The Motion of the Blue Ring Nebula Nebula is One cone moving almost directly toward Earth, while the other is moving almost directly away.


The Imaging Target of the COR-2 Coronagraph is Sun’s outer atmosphere, or corona.


The Frequency of the MPA Calibration System is After every burn.


The News Release Date of the NASA's Spaceborne Carbon Counter Satellite is Dec. 18, 2014.


The Data Rate of the VIS Visible region of spectrum is 7.2 Mbit/s.


The Orbit of the OTB-1 minisatellite Satellite is Earth's orbit.


The Operating System of the Control Room Facility is Linux.


The Solar Panels of the MicroMAS-1 Satellite is Four 3U double-sided deployable solar panels oriented at 120º angles to the structure.


The Speed of the Heliosphere Interstellar Medium is 52,000 miles per hour.


The Mission Status of the Satellite Spacecraft is Unknown.


The Measure of Precision Cosmology of the Gravitational Weak Lensing Phenomenon is Yes.


The Scanning Frequency of the Scanning LIDAR LIDAR is Varied according to a predefined scanning scheme.


The Altitude of the IVM Ion Velocity Meter is Above 250 km.


The Insulators of the FSU Solar Wind Faraday Cup is Machined sapphire rods.


The Measurement Domain of the SPOT-5 Satellite is Ocean, Land, Snow & Ice.


The Volume of the Instrument Device is < 6800 cm^3.


The Retirement Date of the Ikonos Imaging Satellite is March 31, 2015.


The Structure Material of the QuakeSat Satellite is 6061 aluminum.


The Film Transmission of the MXT Instrument is t70.


The Antenna Aperture of the Radar Radar is 1.5 m x 1.5 m.


The Operational Temperature Range of the Instrument Hyperspectral Imager is 293.15 K ± 2 K.


The Bandwidth (GHz) of the ICI-9 Radiometer is 4.


The Stage Type of the Soyuz Rocket is Core stage.


The Additional Capability of the SMOS Satellite is Map the extent and thickness of sea ice.


The Architecture of the CubeSat Satellite is Decentralized.


The Swath Width of the DubaiSat-1 Satellite is 20 km.


The Development Status of the Orion Vehicle Spacecraft is Unknown.


The Provider of the HW-BOSS System is Fraunhofer-Gesellschaft FIRST.


The Copyright Year of the eoPortal Website is 2024.


The Manufacturer of the OBC On-Board Computer is Atmel.


The Maximum Simultaneous CDMA Channels of the Mission Uplink Subsystem Communication System is 6.


The Time of the Mirror Retrace Process is 2.5 minutes.


The Data Rate of the X-band transmitter Transmitter is Up to 100 Mbit/s.


The Mission Type of the NEMO-HD Satellite is High Definition Video and Multispectral Earth Imaging.


The Observation Geometry of the MIPAS Instrument is Limb.


The Research Area of the B2-1 Experiment is Gravitational Biology.


The Ignition Power of the T3µPS Pressure Sensor is 10.1 W.


The Documentary Team Member of the AzTechSat Nanosatellite is Ana Belen Urrutia Bartsch.


The Injection Errors of the PUNCH Mission Satellite is 10 km on the injection apse, 80 km on the non-injection apse, and 0.15° on inclination.


The Spectral Range (µm) of the Band 6 Spectral Band is 1.58 - 1.64.


The Reflector Technology of the SARah Satellite Constellation is Based on SAR-Lupe and enhanced for SARah.


The Mass of the FREND Instrument is 36 kg.


The Launch Site of the Yubileyniy-2/MiR Satellite is Plesetsk Cosmodrome, Russia.


The Progress Update of the TET-1 Satellite is Aug. 10, 2012.


The Experiment of the Kyoto University Organization is Robot teleoperation experiment.


The Spacing of the GRACE-FO satellites Satellite is 220 km.


The Warming Cause of the Earth Planet is Human influences, such as deforestation, particulate pollution, and the release of greenhouse gases from the burning of fossil fuels.


The Maximum Displacement of the Disturbed Areas Geological Feature is 10 cm.


The 20 ms / 16 energy steps of the Time Resolution Sensor is Time resolution 20 ms / 16 energy steps.


The ADC Resolution of the Rx Module Digital Receiver is 14 bit.


The Launch Date of the KazSTSAT Microsatellite is 3 December 2018.


The Locations of the PDHS Data-Handling Station is Frascati (Ka-band), Kiruna, Sweden (X-band), Svalbard.


The Orbit Stability of the LAGEOS Satellite is Very stable.


The Reason for Concept Change of the ALBus R&R Design is Critical thermal issue and mass budget constraints.


The X-band Downlink Data Rate of the Spacecraft Satellite is 320 Mbit/s.


The Swath of the Megha-Tropiques Satellite is ~1700 km.


The Attitude Sensing of the X-ray Navigation Navigation System is High-accuracy without optics.


The Number of Confirmed Exoplanets of the Kepler Satellite is 100+.


The Capability of the Remote Agent Software is Detected, diagnosed and fixed simulated problems.


The Quantity Used of the ALACE Floats Oceanographic Instrument is About 1000.


The Launch Date of the OrbView-2 Satellite is August 1, 1997.


The Track Duration of the CTECS Satellite is 30.6 minutes.


The End of Operation of the LS-7 Satellite is 2012.


The RF Communications of the Spacecraft Satellite is 145.89 MHz.


The Instruments of the Europa Clipper Spacecraft is EIS, E-THEMIS, Europa-UVS, MISE, ECM, PIMS, Gravity & Radio Science, REASON, MISE, MASPEx, SUDA.


The Thermal Control of the Göktürk-1A Satellite is Passive radiators along with a heater system.


The Voltage of the Main Power Bus Power Distribution is 28 to 33 V.


The Model of the GSE Power Supplies Power Supply is Solar eclipse.


The Funding Allocation of the Brazilian Ministry of Defense Government Agency is 145 million real.


The URL of the HITSAT Satellite is http://astronomy.activeboard.com/forum.spark?aBID=58381&p=3&topicID=18351197&page=1&sort=newestFirst.


The Orbit Type of the Primary Payload Unknown is Circular.


The Article Date of the Earth-observing satellite Satellite is 25 May 2022.


The Instrument Mass of the Telescope Optical Instrument is 88 kg.


The Mass of the AISSat-3 Nanosatellite is 6.5 kg.


The FDC (Failure Detection and Correction) Scheme of the Dellingr Satellite is 25-hour reset.


The Navigation Accuracy of the Spacecraft Satellite is 60 m.


The Platforms of the Satshot GIS Mapping Engine is Mapcenter, Landscout and iCue.


The Orbit Transition Duration of the WorldView-1 Satellite is 18 months.


The Cd-Ni Battery Capacity of the EPS Electrical Power Subsystem is 55 Ah.


The Protocol of the TT&C S-band Communications Communication System is CCSDS.


The Congress Date of the ADM-Aeolus Satellite is Oct. 2-6, 2006.


The Launch Date of the Observer Mission (KSF3) Satellite Cluster is Mid-2022.


The Components of the Group Delay Parameter is Data generator, modulator, up converter, travelling-wave tube amplifier (TWTA), cable, and integration components.


The Award Date of the Parker Solar Probe Satellite is 1 July 2021.


The Latency of the ATL07 Arctic/Antarctic Sea Ice Elevation Data is 45 days.


The Transition Orbit Inclination of the LUMIO Satellite is Lies within the parking orbit bounds.


The Mass of the Card Mass Communication System is <0.6 kg.


The Balloon Diameter of the AeroCube-3 Satellite is ~ 60 cm.


The Impact of the Aeolus Satellite is Amongst the most important satellite missions.


The Manufacturer of the MSU-GS Instrument is FSUE/RISDE (Federal State Unitary Enterprise) / Russian Scientific Institute of Space Device Engineering.


The Scanning Technique of the WV-3 Imager Imager is Pushbroom.


The Solar Wind Speed and Beta of the ACE Satellite is ~11% lower on average from 2009 through the day 79 of 2013.


The Crew Capacity of the Space Station Space Station is 7 members.


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


The Attitude Control of the KOMPSAT-6 Satellite is 3-axis attitude control with zero momentum bias.


The Data Access of the Vision-1 Satellite is Free basis to a range of stakeholders.


The Successful Swings around the Sun of the Parker Solar Probe Spacecraft is 7.


The Size of the PPL1 and PPL2 Hyperspectral Camera Systems is 131 x 221 x 262 mm.


The Mission Type of the Sentinel-5 Satellite is European operational atmospheric chemistry mission in polar orbit.


The Electron energy of the Microdosimeter A Instrument is > 50 keV.


The Feasibility Analysis Frequency of the MUS Subsystem is Daily.


The Importance of the Soil Moisture Measurement is Relevant for a variety of applications, particularly farming.


The Integration Time of the WiFS camera Camera is 28.42 ms.


The Data Flow Start Date of the SMAP Satellite is November 19.


The Conical scanning period of the Microwave System Microwave System is 2.88 s.


The Swath Width of the Pushbroom imager Optics is 10.15 km.


The Observation Spectrum of the Herschel Space Telescope is Far-infrared and submillimeter.


The Latency of the ATL21 Arctic/Antarctic Gridded Sea Surface Height within Sea Ice Data is 45 days from receipt of last data in product.


The Grating Lines of the Offner-type spectrometer Spectrometer is 500 lines/mm.


The Current User of the Ground Station Ground Segment Component is IRS.


The Function of the Payload Control Unit Sensor Component is Provide the command and control interface between the platform and the payload.


The Goal of the MoonKAM Education and Public Outreach Program is Engage middle schools in the GRAIL mission and lunar exploration.


The Swath Width of the Main Camera Camera is 2250 km.


The Measurement Range of the PRI Photochemical Reflectance Index is 500–600 nm.


The Number of Transponders of the Inmarsat S – Europasat / Hellas-Sat 3 Satellite is 44 Ku and 1 Ka.


The Development Status of the MEP Main Electronics Package is Not provided.


The Mass (kg) of the ERS-1 Satellite is 2384.


The Number of Channels of the FODB Data Interface is 12.


The Prime Mission Duration of the EMIT Satellite is One year.


The CCD Type of the Pan band Detector Array is PhotoMOS-type.


The Developers of the Carruthers Geocorona Observatory (GLIDE) Satellite is Ball Aerospace and University of California (UC) Berkeley.


The Testing Location of the Galileo Satellites 13 and 14 Satellites is Oberpfaffenhofen, Germany.


The Spatial Resolution of the Ma_MISS Spectrometer is 120 µm.


The Perigee Altitude of the Satellite Constellation Satellite Constellation is ~ 300 km.


The Measurement Objectives of the Cluster Satellite Mission is Study of small-scale plasma structures and current densities.


The Manufacturer of the Hyperion HSI (Hyperspectral Imager) is Northrop Grumman (formerly TRW).


The GSD at Nadir of the Telescope Optical Instrument is 30 m.


The Location of the IDPS Integrated Data Processing System is NOAA Satellite Operations Facility in Suitland, MD.


The Role of the Jason-3 Satellite is High Precision Ocean Altimetry reference mission.


The Power Source of the Electronics Imager Electronics is Spacecraft 28 V bus.


The Spectral Range of the Spectral Band A Spectrometer is 0.45 - 0.52 µm.


The Number of Infrared Detectors of the CrIS Instrument is 27.


The Mission Type of the Oculus-ASR Satellite is Non-EO.


The Laser Connection of the SpaceDataHighway Communication System is More than 50,000 within the first five years.


The Presentation Location of the Micro Digital Sun Sensor Sensor is Banff, Alberta, Canada.


The Ground Target Coverage of the KOMPSAT-5 Satellite is Up to 490 km width in a single orbit.


The Observation Duration of the Integral Satellite is Four weeks.


The Time in Orbit of the Vesselsat-1 & -2 Satellite is 3 years.


The Expected Number of Tracked Cargo Vessels of the MDASat-i Satellite is 60000.


The Calibration Concept of the Atmospheric-sounding instrument Spectrometer is Extensive on-ground characterization and in-flight calibration concept.


The Latency of the ATL08 Land Water Vegetation Elevation Data is 45 days.


The Baseline Design of the SpooQySat Satellite is GomX-313 with modifications.


The Planned Launch Year of the ESP-MACCS Satellite is 2024.


The Swath Width of the ScanSAR-2 Mode is 200 x 2500 km.


The Retirement Date of the CBERS-1 Satellite is Aug. 2003.


The Field of View of the Optics Device is 10º.


The Survey of the Herschel Space Observatory is Hi-GAL, the Herschel infrared Galactic Plane Survey.


The Expected Orbit Duration of the Skylab-1 Space Station is 8-10 years.


The Mission End Date of the Envisat Satellite is May 9, 2012.


The MTF at Nyquist Frequency of the Spacecraft Satellite is > 10% for Pan.


The Mission Type of the Deimos-1 Satellite is Fully Commercial EO Mission.


The Launch Date of the Meteor-2-1 Satellite is 11.07.1975.


The Radio Glitch of the AeroCube-3 Satellite is The satellite radio suffered a glitch where it would not acknowledge that the ground station was talking to it.


The URL of the PSAT Satellite is http://digitalcommons.usu.edu/cgi/viewcontent.cgi?article=3549&context=smallsat.


The Image Capture Location of the CaSSIS Imaging System is 26.8ºS/34.8ºW.


The Revisit Time of the Satellite Constellation Constellation is Better than 10 hours globally.


The Data Distribution Start Date of the Meteosat-8 Satellite is 4 October.


The Topology of the FODB Data Interface is Ring.


The Resolution of the ScanSAR-2 Mode is 6 x 20m.


The Slew Angles of the TeLEOS-1 Imager Imaging Device is Up to ±45º from nadir.


The Output Range of the DAC Digital Analog Converter is 0-5 V.


The In-track Separation of the AeroCube-OCSD-B and -C Satellites is 151 meters.


The Development Cost of the EPS-MACCS Satellite Mission is Maximum of €30 million.


The Program Overview of the CBERS Satellite is URL: http://www.dpi.inpe.br/gilberto/present/cbers_overview.ppt.


The Total Mass of the Secondary Payloads Satellites is 243 kg.


The Functionality of the Software System is Networking, file I/O operations, low-level hardware configuration, and many basic commands.


The Challenge of the DarkCarb image sensor Photon Detector is Wavelengths to which it is sensitive are emitted by all objects that are at the Earth’s temperature.


The Size of the OCM Instrument is 701 mm x 527 mm x 470 mm.


The LTAN of the Spacecraft Satellite is 10:30 hours.


The Downlink Frequency of the RF Communication System Communication System is 437.490 MHz.


The Number of X-class flares of the SOHO Satellite is 11.


The Ground Resolution of the SiPD Detector is 1m.


The Main Beam Efficiency (%) of the Antenna Reflector is 89.


The NiCd Batteries of the EURECA Spacecraft is 4 NiCd batteries.


The Type of the MAESTRO Instrument is Dual channel optical spectrometer.


The Data Policy of the NPOESS Program is Large subset of data available free of charge.


The Capacity of the Battery Power is 12 Ah.


The Components of the STP-H6-NISTEx II Hardware is Sun-shade, optical shutter, interferometric components, housing for the Stingray custom designed optics, electronics processing and power interface using a radiation hardened BAE CIS1910 detector.


The Spectral Range of the Spectral Band C Spectrometer is 0.62 - 0.68 µm.


The Mission Lifetime of the Instrument Spectrometer is 7.5 years.


The Housekeeping Computers of the GNB Satellite is 1 ARM7.


The Data Type of the CMOS Camera Camera is UYVY, 8 bit.


The Leakage current balancing of the PHA Detector is Up to 32 µA with 10-bit resolution.


The Payload of the MPQ442 Satellite is SuperLab.


The S-band Downlink of the Spacecraft Satellite is Completed.


The Quasi-Periodic Oscillations of the Sw J1644+57 Black Hole is Present.


The End of Life Date of the Ikonos-2 Satellite is 31 Mar 2015.


The Depth Requirement of the Heat Probe Instrument is At least 10 feet (3 meters).


The Orbit Type of the NEMO-AM Satellite is Sun-synchronous orbit.


The Perigee of the UK-DMC-2 Satellite is ~ 632 km.


The Quantity of the RADFET dosimeters Dosimeters is 2.


The Dynamic Range of the Limb Sensor Sensor is 4-5 orders in magnitude variation.


The Function of the Low-Frequency Radio Spectrometers Spectrometer is Detect the 21 cm hydrogen line radiation.


The Mission Duration of the CATS Lidar Instrument is 33 months.


The Altitude of the Satellite Communication is 1012 km.


The Spacecraft Controller of the TNS-0 Nanosatellite is Single chip microcontroller (C8051F022) of the Silicon Laboratories Company.


The Publication Date of the Super Dual Auroral Radar Network Radar Network is 2007.


The Launch Date of the Starliner Spacecraft is Thursday, May 19.


The Number of Accelerometers of the SloshSat Satellite is 6.


The Mass of the Instrument Optical Instrument is 27.7 kg.


The Proposed Altitudes of Operation of the Starlink Satellite Constellation is Between 340 and 614 kilometers.


The Telescope Type of the GOES Sounder Sounder is Cassegrain telescope.


The Modulation of the CBERS-1 Satellite is QPSK for HRCC and WFI data streams and BPSK for IRMSS.


The Science Goals of the Psyche Mission Space Mission is 1. Understand a previously unexplored building block of planet formation: iron cores. 2. Look inside terrestrial planets, including Earth, by directly examining the interior of a differentiated body, which otherwise could not be seen. 3. Explore a new typ.


The Geolocation Accuracy of the PROBA-V Mission Satellite Mission is RMSE accuracy <50 m.


The Number of Nanosatellites Launched of the Astrocast Satellite is 5.


The URL of the MidSTAR-1 Satellite is http://www.usna.edu/Satellite/midstar/downloads/ops/MidSTAR-1%20Ops%20Concept.doc.


The Development Timeline of the EPS-MACCS Satellite Mission is From kick-off to launch within three years.


The Mission Type of the Sentinel-6 Satellite is Reference.


The Range of the Spectral Bands Sensor is 0.32 - 4.0 µm.


The Objective of the CAPS SW Software is Provide full autonomous navigation onboard the CAPSTONE spacecraft.


The Principal Investigators of the SMILE Satellite is Graziella Branduardi-Raymont from MSSL/UCL (Mullard Space Science Laboratory/University College London), UK, and Chi Wang from the State Key Laboratory of Space Weather, NSSC/CAS (National Space Science Center/Chinese Academy of Sciences).


The Number of Antennas of the TRACKER Ground Station is Multiple.


The Number of Fast Cameras of the PLATO Telescope is 2.


The Innovation Spin-off of the BepiColombo Satellite is Terrestrial industry products.


The URL of the NASA Moon Mission Mission is http://www.jpl.nasa.gov/news/news.php?feature=6662&utm_source=iContact&utm_medium=email&utm_campaign=NASAJPL&utm_content=weekly20161028-5.


The Energy: 0.53 keV (2.3 nm) of the O K-edge Atmospheric Cross Section Feature is O at 0.53 keV (2.3 nm).


The Integration of the OB Optical Bench is Instruments are calibrated as stand alone, and once integrated in the OB, an intercalibration and system verification is carried out.


The Calibration of the MADRAS Instrument is Unknown.


The Number of Supported Satellite Missions of the KSAT Company is More than 100.


The Subaperture Area Percentage of the PAIS Imaging System is Above some value.


The No. of Bins of the SPIM5 Spectrometer is 68, 136, or 272.


The Firing Pressure of the Y-axis Bang-Bang Maneuver Satellite Maneuver is 1.62 bar.


The Deployable Solar Array Angle of the UK-DMC-2 Satellite is 110º.


The Mission of the BeeSat Satellite is Berlin Experimental Educational Satellite.


The Mission Status of the TechnoSat Nanosatellite is Operational (extended).


The Orbit Position of the BeiDou-1B Satellite is GEO, 80º E.


The Principal Investigator of the IMPACT Instrument is Janet G. Luhmann.


The Detection of the Debris Cloud Space Object is Mid-2018.


The Gain of the Antenna Communication System is 15 dBi per polarization.


The Containment of the Cooks Peak fire Wildfire is 72 percent.


The Purpose of the CICERO-4 Satellite is Weather satellite.


The Purpose of the Gaia Satellite is Precisely measuring the distance and movement of more than a billion stars in our galaxy.


The Launch Site of the AeroCube-4 Satellite is VAFB, CA.


The Cadence of the Thermal Neutron Counts Measurement is 5 minutes.


The Testing Duration of the GaN-based Power Transistors Transistors is More than 3000 hours.


The Multispectral Bands Ground Resolution of the WorldView-3 Satellite is 1.24 m.


The SFE of the ASCAT Scatterometer is Scatterometer Front End.


The Altitude Range of the Atomic Oxygen (AO) Density Measurement Device Instrument is 180-200 km.


The Design of the Antenna Dish Satellite Component is Rib consists of an inner and outer portion, connected by a spring-loaded hinge joint.


The Altitude of the Tsubame Microsatellite is 504 km.


The Purpose of the Integral Satellite is Observing particles thrown off by extreme phenomena such as black holes, neutron stars, and supernova explosions.


The Orbit Altitude of the 3U CubeSat Satellite is 505 km.


The Brightness Temperature Stability of the MWR Dicke Radiometer is 1 K.


The Nominal Angular Momentum of the MW Momentum Wheel is 0.125 Nms.


The Deployment Orbit of the OG2-1 Satellite is Lower than intended.


The Laser Diodes Power of the SILEX Terminal is 60 mW.


The S-band TxRx Data Rate (TC) of the RF communications Communication System is 64 kbit/s.


The Instrument of the TEMPEST-D Satellite is Radiometer.


The Science Data Duration of the Colorado Student Space Weather Experiment (CSSWE) Satellite is 3 weeks.


The Back-up Ground Station of the IXPE Observatory Satellite is NEN ground station in Singapore.


The Photometric Sensitivity of the Instrument Sensor is 0.75 counts /s /Rayleigh /1º pixel.


The Downlink Rate of the ResourceSat-1 Satellite is 1-16 kbit/s.


The Sensor Complement of the Solar-B / Hinode Satellite is Unknown.


The Catalog Use of the XMM-Newton X-ray Satellite is Get new information about their research objects and to search for rare and as yet unknown sources of X-rays.


The Sensor Type of the ECOSTRESS Instrument is Radiometer.


The Photometric Precision of the PicSat Satellite is Sub-milimag.


The Nominal Lifetime of the Sentinel-6 Satellite is 5.5 years.


The CCD Detectors of the COR1 Coronagraph1 imager is EEV 42-40, 2k x 2K, 13.5 μm pixels, backside illuminated, AR coated (except EUVI), >100 k e -  full well.


The Pointing Accuracy of the ADCS Attitude Determination and Control System is ±3º.


The Onboard Data Storage of the Spacecraft Satellite is 128 GB.


The Array Power Peak of the Spacecraft Bus (Avionics Module=AM) Satellite is 790 W.


The Elevation/Azimuth Coudé-mount Telescope Size of the OCTL Telescope is 1 m.


The Detector Unit Components of the MSASI Imager is High speed CMOS image sensor and an image intensifier.


The Mass of the Herley MD2000C-1 Transponder Module is 425 gram.


The Launch Date of the PSLV-C37 Satellite Launch Vehicle is Unknown.


The Ellipse Axis C of the Long Wavelength Band Spectrometer is 242.6 mm.


The Image Re-sampling Methods of the Product Level 1C (L1C) Data is Bi-cubic convolution interpolation and nearest neighbor.


The Data Compression of the TTTC Imaging System is Optional.


The New Applications of the SMOS Satellite is Permafrost and thawing monitoring in the boreal forest, ice thickness determination in the Arctic Ocean, hurricane wind observations.


The | of the Tim Fuller-Rowell, Mihail Codrescu, Bela G. Fejer, W. Borer, F. Marcos, D.N. Anderson Authors is Tim Fuller-Rowell, Mihail Codrescu, Bela G. Fejer, W. Borer, F. Marcos, D.N. Anderson.


The Instrument mass of the Optical System Imaging System is 120 kg.


The Task of the OBC On-Board Computer is Marshalling of images from the smartphone, via the HPC to the transmitter.


The Containment of the Cerro Pelado fire Wildfire is 10 percent.


The Output Power of the MHX-2400 S-band Transmitter/Transceiver is 30 dBm.


The Type of the HD 93396 Star is Subgiant yellow.


The Display Location of the Copernicus Sentinel-6 Satellite is IAGB space test center in Ottobrunn near Munich.


The EFI Deployment Completion Date of the THEMIS Constellation Satellite Constellation is 14 January 2008.


The Visual Magnitude Limit of the BRITE Satellite is +3.5.


The Spectral Band of the Band Photometers Photometer is 762.4 nm.


The Time of the Spacecraft Stabilization Process is 2.5 minutes.


The Objective of the LALT Laser Altimeter is Measure the vertical distance between the Main Orbiter and the subsatellite point on the lunar surface.


The Radiometric Resolution of the SAR Synthetic Aperture Radar is 5-bit raw data.


The Image Credit of the Orbiting Carbon Observatory-2 (OCO-2) Satellite is NASA/JPL-Caltech/University of Utah.


The Detection Capability of the OMI Satellite Instrument is Emissions Changes.


The Orbit Duration of the LRO Spacecraft is Four Years.


The Torque Coil Power of the Canopus Pipper Satellite is ~ 500 mA.


The Launch Date of the Sentinel-6A Satellite is November 2020.


The Operation Mode of the SMOS Satellite is Autonomous mode using the FDIR (Failure Detection Isolation and Recovery) concept.


The Data Collection Date of the GOCI Geostationary Ocean Color Imager is May 12, 2016.


The Sunphotometers of the SOVA Experiment is Degradation in Space.


The Orbit Duration of the SMOS Satellite is Almost 1 Year.


The Pulse period (ms) of the B1758-250 Pulsar is 3.000.


The Operator of the UWE-1 Satellite is Student team at the University of Würzburg.


The Cal_solar data Collection of the OCO-2 Satellite is Spectral Wavelength Calibration.


The Chief Strategy Officer of the HawkEye 360 Company is Kari Bingen.


The Instrument of the CO2M Satellite is Near-infrared and shortwave-infrared spectrometer.


The Band Frequency of the Starlink Satellite Constellation is 10.7 GHz to 12.7 GHz.


The Tuning of the Focal Plane Skew Settings of the R3 System Satellite is Possible cause of noise in the NIR band.


The Array Size of the Detector Optical Instrument is 256 x 256 pixels.


The Experiment Date of the ETS-VII Satellite is March 14, 2000.


The Data Source of the OMI (Ozone Monitoring Instrument) Instrument is OMI (Ozone Monitoring Instrument) on NASA’s Aura satellite.


The Type of the SCIP Processor is Stack based.


The Meeting Date of the GMES Sentinel-3 Satellite is 18-20 January 2010.


The Additional Component of the GomX-4B Satellite is Extra transceiver in the Software Defined Radio for ISL operations.


The Quantity of the NiH2 batteries Power Source is 4.


The Journey Time to Earth of the Solar Energetic Particles Space Weather Phenomenon is Under an hour.


The Alkalinity of the Marine Chemistry Study Parameter is Unknown.


The Uplink Speed of the Communication links Communication subsystem is 9.6 kbit/s.


The ΔRAAN of the Swarm-A (Alpha) Satellite is 1.4º difference between A and B.


The Mission Scenario of the DLR SAR Satellite is Climate research and environmental monitoring.


The Origin of the SPA Architecture is Expanded and refined from the appliqué sensor network.


The Expected Outcome of the TEPCE Satellite is New propulsion capability for spacecraft.


The Mode of the SAR Sensor Subsystem SAR Sensor is HR (High Resolution).


The Quantity of the Secondary Payloads Nanosatellites and CubeSat is 4 nanosatellites and 1 CubeSat.


The Tether Length of the TEPCE Satellite is 1 km.


The Citation of the SOLSPEC Spectrometer is G. Thuillier, M. Herse, D. Labs, T. Foujols, W. Peetermans, “The Solar Spectral Irradiance from 200 to 2400 nm as measured by the SOLSPEC spectrometer from the ATLAS and EURECA missions,” Solar Physics, Vol. 214, pp. 1-22, 2003.


The Formation of the Equatorial Ridge Surface Feature is During a period when it only took Ryugu 3 hours to rotate.


The Data Processor Developer of the GOME Instrument is German Remote Sensing Data Center (DFD) of DLR.


The Swath Width of the TAC Camera is 51 km.


The Operation Status of the KOMPSAT-5/Arirang-5 spacecraft Satellite is Nominal.


The Revisit Time at 1 m - 0.5 m GSD of the WV60 imager Imaging System is 1.7 days.


The Timer Validity of the MOBC Main On-board Computer is 200 days.


The Mission Type of the SOHO Satellite is Solar Study.


The Original Manifest of the Falcon-9 CRS-2 Rocket is ELaNa-4 CubeSats.


The Data Policy of the Copernicus Space Component Satellite Component is Open access to Sentinel data by anybody and for any use.


The Wavelengths of the SPIRE Far-infrared camera is 160 µm (green).


The Size of the LICIACube CubeSat is Hand-sized.


The Footprint Size of the CNSCAT Scatterometer is 19 km x 24 km.


The Rotation Period of the Stars Celestial Bodies is Ranged from one to as many as 11 Earth-days.


The Date of the Data Distribution Policy Agreement Agreement is 2008.


The Operational Status of the PhoneSat 2.5 Satellite is Operational.


The Period of the ExoMars Orbiter Satellite is ~2 hours.


The Symposium Location of the WatER Satellite Mission is Venice, Italy.


The Multispectral Resolution of the EROS-C Satellite is 2.8 m GSD.


The Time in Spacecraft of the Valves Spacecraft Component is 46 days.


The Secondary Mirror Size of the Telescope Telescope is 0.3 m.


The Developer of the TransHab Space Habitat is William Schneider.


The Development Team of the BioSentinel Satellite is Hugo Sanchez, James Chartres, Robert Hanel, Sharmila Bhattacharya, Antonio Ricco.


The Temperature Control of the OBA Instrument Component is Yes.


The Swath Width of the Spacecraft Satellite is 23 km.


The Type of the Telescope Optical Instrument is Zeiss 1 m ∅ Ritchey-Chrétien/Coudé telescope.


The Telescope Optics of the EUVI Extreme Ultraviolet Imager is Fully baffled.


The Function of the TET Radiator Thermal Interface is Allows the complete radiation of all thermal energy into free space during the "hot" phases.


The Function of the PIC Device is Create images of extended scenes.


The Attitude Control of the Bus Satellite Bus is Control using magnetorquers only, except short term.


The Energy Dissipation Location of the Cluster Satellite is Swirling vortices, or O-lines.


The Components of the ADCS Attitude Determination and Control Subsystem is 3-axis gyro sensor, 3-axis magnetometer, sun sensor, Earth sensor.


The Number of Holes of the Optical Head Optical Device is 1 / 100 (enhanced configuration).


The Frequencies of the MM Radiometer Sensor is 89, 165, 176, 180 and 182 GHz.


The Measurement of the Imaging Spectrometer Instrument is Visible and infrared light reflecting from surfaces below.


The Winding of the Torque Rods Attitude Control is Dual-wound.


The Project of the SumbandilaSat Satellite is First national satellite, First opportunity for SAC to operate a satellite, First opportunity to put the newly developed MCS architecture to test, First time in SunSpace's history where the day-to-day health monitoring of a satellite had to be transferred.


The Propulsion System Performance of the Advanced Composition Explorer Spacecraft is Nominally for the first 16 years of the mission.


The Swath Width of the Satellite Imaging Satellite is 80 km.


The Antenna Position of the SIR-C Radar System is 38º.


The Operation Hours of the Ion Engine Propulsion System is 1346 hours.


The Mission Design of the RapidEye Satellite is G. Tyc, J. Tulip, D. Schulten, M. Krischke, M. Oxfort.


The Mission Type of the IMAGE Satellite is EO.


The Quantity of the Commercial Off-the-Shelf (COTS) Air Tanks Hardware is Sixteen.


The Volcano Status of the Hofsjökull Glacier is Largest active volcano in Iceland.


The Service Availability of the OneWeb Satellite Constellation is Before the end of the year.


The Mission Altitude of the MicroSat-2b Satellite is 1125 km.


The Satellite Dimensions of the Terra Bella Satellite Constellation is 60 x 60 x 95 cm.


The NEDT (Noise Equivalent Differential Temperature) at 300 K of the Scanning geometry Instrument is Band 4 - Band 5 - Band 6 ≤ 1 K ≤ 0.2 K ≤ 0.2 K.


The Orbit Coverage of the JPSS Satellite Program is Global.


The Celestial Sphere Coverage of the Spacecraft Satellite is 64% during the first two years of the mission.


The Elliptical Orbit Dimensions of the Lunar Landing Vehicle Vehicle is 100 km x 15 km.


The Thermal Operating Range of the Earth Radiation Budget Experiment (ERBE) Instrument is 38±0.1ºC (detectors).


The Location Accuracy of the Autonomous star tracker Star Tracker is Less than 50 m.


The Peak Detection Rate of the Simple Receiver AIS Receiver is Not tabulated.


The Material of the HiRAIS Optical Instrument is CFRP.


The Hypothetical Energy Component of the Dark Energy Cosmology is Unknown.


The Period of the Resurs-P1 Satellite is 94 minutes.


The Instrument Power of the ERIP Earth Remote-Sensing Imaging Package is 3 W.


The Visible Spectral Range / Bandwidth of the SOLSPEC-ATLAS Spectrometer is 350-880/1.4/1.


The Website of the Kolibri-2000 Microsatellite is http://www.energia.ru/english/energia/sci-education/microsat/microsat-02.html.


The Frequency Band of the AltiKa Radar Altimeter is Ka-band.


The Precision of the Ozone Measurement Instrument Atmospheric Measurement Device is 3%, 15-50 km.


The Avionics Components of the Microsatellite Satellite is Four boards for C&DH, and power.


The Gain of the Yagi Antenna Antenna is 7.5 dBi.


The Memory of the OBC On-Board Computer is 16 MByte.


The Pumping Scheme of the Laser Device is Unknown.


The Altitude of the ResourceSat-2 Satellite is 817 km.


The PI of the SORCE Satellite is G. J. Rottman.


The Spectral Bands of the VIIRS Instrument is 22.


The Website of the TUBSAT Satellite is http://www.raumfahrttechnik.tu-berlin.de/tubsat.


The Mission Duration of the Van Allen Probes Satellite is 3 years.


The Global Average Detection Rate of the Simple Receiver AIS Receiver is 2 to 3 Messages/s.


The Gravity of the Mars Planet is About one-third that of Earth’s.


The Attitude Variation During Docking Operations of the ISS Satellite is Several degrees.


The Inclination of the Secondary Payloads Satellites is ~51.6º.


The Components of the FGS Science Instrument is Two Guider channels and one Near-Infrared Slitless Spectrometer (NIRISS) channel.


The Release Date of the HTV-6 Resupply Ship is January 27.


The Orbit of the MKS-PN2 (Relek) Satellite is Elliptical orbit of 632 km x 824 km.


The First Stage Flights of the Rocket Launch Vehicle is 15.


The Altitude of the OrbView-3 Satellite is ~435 km.


The Launch Site of the Galileo FOC-3 and FOC-4 satellites Satellite is Europe's Spaceport (Kourou, ELS) in French Guiana.


The Launch Status of the Galaxy Spacecraft is Not Launched.


The Orbit Altitude of the Fregat Upper Stage is Around 450 km.


The Grating Figure of the Long Wavelength Band Spectrometer is Ellipse of rotation.


The Number of Elements of the MS Bands Detector Line Arrays is 1,500.


The Communication Network of the Spacecraft Satellite is NASA's Deep Space Network.


The Time Resolution of the IMAP Satellite is Six-month timescales.


The Pixel Size of the IFOV Sensor is 44.6 km x 39.3 km.


The Material of the Reaction Wheels Satellite Component is Mu-metal.


The Swath Width of the JL-1-GF03B Microsatellite is 17 km.


The XNAV Type of the SEXTANT Technology Demonstration is X-ray Pulsar-based Navigation.


The Launch Date of the GEOS-3 Satellite is 9 April 1975.


The Observation Distance of the Herschel Telescope is Within 1500 light years from the Sun.


The Challenges of the Langmuir Probe Plasma Measurement Device is Ground handling equipment and testing methods.


The Average Spacing of the GNOS-2 Satellite is 710 km.


The Chirp Generation Method of the Ty module Module is Direct digital synthesis at an IF of 150 MHz.


The Type of the SMMR Instrument is Scanning Multichannel Microwave Radiometer.


The Range of the NGAVGS Sensor is Up to 3000 meters.


The URL of the Star-circling bubble of gas Unknown is http://m.esa.int/spaceinimages/Images/2018/06/Star-circling_bubble_of_gas.


The Primary Mirror Size of the Telescope Telescope is 3.5 m.


The | Very high-resolution imagery and machine learning of the Trees Mapping Method Mapping Method is The use of very high-resolution imagery and machine learning represents a significant breakthrough.


The Global Scan Frequency of the NISAR Satellite is Every 12 days.


The Orbit Type of the Viasat Satellite Operator is Geostationary.


The Frequency Band of the AIS Automatic Identification System is VHF.


The Total Cost of the LEO Constellation Satellite Constellation is $5 billion.


The Unique Capability of the Cluster Satellite Mission is Allows multipoint measurements of the magnetosphere in different regions and at different scales.


The Total Satellites in Orbit of the OneWeb Satellite Constellation is 182.


The Airlock Cycle Dates of the NanoRacks CubeSat Deployer Missions CubeSat Deployer is May 16-17, 2017.


The Launch Site of the SpaceX CRS-19 Mission is Space Launch Complex 40 (SLC-40) at Cape Canaveral Air Force Station, Florida.


The Number of Detected Marsquakes of the InSight lander Seismic Instrument is More than a thousand.


The Conference Date of the Supercapacitors Energy Storage is 2011.


The Transmitting Power of the Iris Radio Communication Device is 2 W.


The Readiness Date of the EUMETSAT ground segment Ground Segment is 5 December 2017.


The Data Rate of the Satellite Satellite is 25 Mbit/s.


The Partnership Date of the CICERO Satellite System is Dec. 4, 2009.


The Components of the TOU Telescope Optical Unit is 6 lenses.


The Soil Moisture Refresh Rate of the SMAP Satellite is 3 days.


The Gyro Tilt Detection of the SQUID Magnetometer is 0.1 milliarcseconds.


The Meeting Date of the NPOESS Satellite System is Sept. 29 to Oct. 3, 2008.


The Mission of the SMOS Satellite is Soil Moisture and Ocean Salinity.


The Principal Investigator of the OSIRIS-REx Spacecraft is Dante Lauretta.


The Optical Windows Coatings of the Instrument Spectrometer is Broadband AR coatings with R < 2%.


The Base carrier board of the C&DH subsystem Onboard Computer System is Contains all the peripheral ports.


The Institute of the CIP Payload is NCU (National Central University), Taiwan.


The Chopper Wheels Frequency of the SBUV Spectrometer is 25 Hz.


The Royal Institute of Technology in Stockholm, Sweden of the Odin Mission Archive Location is The archive of the Odin mission is located at the Royal Institute of Technology in Stockholm, Sweden.


The Gain of the TEC Antennas Antennas is Not less than 45 dB.


The Operator of the CPOD Service Data Service is GMV-led consortium of Spain.


The Data Transmission Rate of the S-band Communication Band is 1 Mbit/s.


The Presentation of the NROL-36/OUTSat Satellite is Workshop.


The Memory of the AIM Reconfigurable Computing Hardware Device is 128 k x 16 EEPROM for boot and application code.


The Support Phase Time Period of the Mango Tango Satellite Formation is 11.08 to 08.09.2010.


The Mission Extension Approval Date of the XMM-Newton X-ray observatory is November 20, 2014.


The Payload Number of the Inmarsat S EAN Satellite is Ninth.


The Country of Origin of the KOMPSat-5 Satellite is South Korea.


The Presentation Date of the MERLIN Climate Mission is Oct. 3-7, 2011.


The Control Function of the PCU Power Control Unit is Controls the power supply subsystem.


The Microprocessor Speed of the RAD750 SBC Single Board Computer is 132 MHz.


The Aperture of the FUV Channel Telescope Channel is ~380 mm.


The Data Rate of the Ka-band telecom system Telecom System is 3.5 Gbit/s.


The Landing Technology Status of the Tianwen-1 Mars Lander is Ready for 2020.


The Deployment Options of the Open5GCore Rel. 4 5G Core Network is Containers or virtual machines on top of a large number of virtualization environments.


The Sensor Description and Mission Overview of the WindSat Spaceborne Polarimetric Radiometer is The WindSat Space Borne Polarimetric Microwave Radiometer: Sensor Description and Mission Overview.


The Swath width of the VIRR Visible and Infrared Radiometer is 2800 km.


The Spatial Resolution of the Ice sheets Rock basement Satellite is 50-100 km.


The Event of the Incheon Glacier Memorial Glacier is Meeting of the IPCC to consider the special report of global warming of 1.5°C in 2015.


The Berth Duration of the Kounotori H-II Transfer Vehicle is Until November.


The Beamwidth of the Antenna Satellite Component is 2.2º (Nyquist-sampling in both along-scan & down-track directions).


The Payload Fairing Material of the Minotaur Launch Vehicle is Carbon fibers and epoxy.


The Battery of the QuickBird-2 Satellite is 40 Ah NiH2.


The Gyroscopic Attitude Control Channels of the Electro-L Satellite is 4.


The Required Precision of the AAOD Satellite Instrument is 0.03.


The Deployment Date of the CYGNSS Satellite Constellation is Dec. 15, 2016.


The Extended Mission Duration of the Juno Spacecraft is Through September 2025.


The Thermal Operational Range of the Instrument Satellite Instrument is 0 / +20ºC.


The Data of the RapidScat Satellite is Semi-diurnal differences.


The Operation Periods of the VWFC Camera is Orbits 84 to 91, 94 to 96, and 98.


The Algorithms of the Instrument Computer Data Processing is Lossless (2:1 Rice compression) and lossy (JPEG).


The Solar Cycle Observation of the SOHO Satellite is 24.


The Function of the Remote Agent Software is Planned DS1 activities on-board and carried out the plan without ground intervention.


The Ice Thickness of the Landsat 8 Satellite is 12 to 28 inches (30 to 71 cm).


The Launch Date of the ZY-3 Satellite is January 9, 2012.


The Purpose of the KE Ground Station Ground Station is Support the singular KE Block I satellite.


The Data Archive of the XMM-Newton X-ray Telescope is Rich.


The Main Engine Thrust of the ExoMars TGO Orbiter is 424 N.


The RF Output Power of the EWC31 S-band transceiver module Communication Module is +27 to +33 dBm.


The Dimensions of the GNB Satellite Platform is 20 cm side length.


The Optimum Bandwidth of the Etalon Filter is 80-120 mÅ.


The Manufacturer of the Iridium NEXT Satellite Constellation is Thales Alenia Space.


The Application of the CMT Imager is Localized Real-Time Security Assessment.


The Data Rate of the X-band transmitter Transmitter is Up to 384Mbit/s.


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


The Orbit Frequency of the Space Station Satellite is About 16 times per day.


The Closest Distance to ISS of the SZ-7 Spaceship is Within 47 km.


The Data Processing of the RPW Radio and Plasma Waves Instrument is Relatively easy and quick once behavior is known.


The ISS Onboard Waiting Period of the MicroMAS-1 Satellite is 8 months.


The Conference Presentation Date of the PnP Cube Satellite CubeSat is March 3-10, 2012.


The Funding of the MAST Satellite is Combination of private and government research funds.


The Clock Frequency of the X-band transmitter Transmitter is 48 MHz.


The Type of the HISUI Instrument is Hyperspectral and multispectral pushbroom imager.


The Drift Speed of the Great Blue Spot Magnetic Anomaly on Jupiter is About 2 inches (4 cm) per second.


The Imaging Frequency of the AgCam/ISSAC Imaging System is 2-4 images per orbit for 4 consecutive orbits.


The Number of Arms of the Spectrometer Arms Optical Component is 4.


The Orbit Type of the LAGEOS Satellite is Near-circular.


The Basis of the Kappa Scheme Flare Prediction Method is Theory of "double-arc instability," a magnetohydrodynamic (MHD) instability triggered by magnetic reconnection.


The Percentage of Detections from Vessels without AIS or VMS of the VIIRS Instrument is More than 85 percent.


The Calibration Update of the Ikonos-2 Satellite is 2007.


The Model Building of the Oculus-ASR Satellite is 3D Predictive Satellite Models.


The Mission Scenarios of the Ground Station System is Links to and from aircraft, UAVs, and satellites.


The Authors of the NISAR Spaceborne SAR Mission is Paul Rosen, Yunjin Kim, Howard Eisen, Scott Shaffer, Louise Veilleux, Scott Hensley, Manab Chakraborty, Tapan Misra, R. Satish, Deepak Putrevu, Rakesh Bhan.


The Mission Status of the LightSail 2 Satellite is Unknown.


The Mass of the D-SAT CubeSat is 3.5 kg.


The Agency of the CAS500 Satellite is KARI.


The Orbit Period of the Genesis-2 Satellite is 96 minutes.


The Calibration of the Calibration Satellite is Total calibration of instrument artifacts <0.5% at top-of-atmosphere.


The Operating Temperature of the Near-infrared instruments Instrument is About 30 K.


The Operations with 2 satellites of the Dove-2 Satellite is True.


The Symposium Date of the WatER Satellite Mission is March 13-18, 2006.


The Signal Reception Time of the MarCO-B Satellite is 11:16 am.


The Requirement of the Focus Mechanism Satellite Component is Independent feedback on movement.


The Air Quality Prediction Accuracy Improvement of the TEMPO Instrument is 50 percent.


The Launch Date of the XMM-Newton Satellite is December 1999.


The Prioritized Science Goals of the ACE Satellite is 1. Discover the nature and consequences of the changes in the space environment in this unusual solar cycle; 2. Determine where and how energetic particle populations are accelerated; 3. Determine the spatial variations of particles and field in the inner.


The Thruster Pairs of the Propulsion Subsystem Propulsion System is 3.


The Office Locations of the Spire Satellite Constellation is San Francisco, Boulder, Washington DC, Cambridge, Ontario, Glasgow, Oxfordshire, Luxembourg, and Singapore.


The Mission Status of the OSIRIS-REx Spacecraft is Rehearsal Time for NASA’s Asteroid Sampling Spacecraft.


The Manufacturer of the SPOT 6 Satellite is Astrium.


The Up-Conversion Frequency of the Ty module Module is Nominal 5.405 GHz center frequency.


The Center Wavelengths of the AATSR Instrument is 0.55 µm, 0.66 µm, 0.87 µm, 1.6 µm, 3.7 µm, 11 µm, 12 µm.


The Manufacturer of the Falcon 9 Launch Vehicle is SpaceX.


The Ground-Truth Characterization of the Oculus-ASR Satellite is Successful.


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


The Stability of the AOCS Attitude and Orbit Control Subsystem is < 5 arcsec/s of the X and Y axis.


The Frequency Range of the Field Measurement Device Sensor is DC to 10 Hz.


The Distance from Sun at Arrival of the Parker Solar Probe Satellite is 18.8 solar radii (around 8.1 million miles).


The Resolution of the LISS-4 Imaging System is 6 m.


The Accuracy of the NIDEM Elevation Model is Less accurate for rocky shores.


The Cross-talk between PHAs of the PHA Detector is <0.2%.


The Design Life of the ACTS/TOS Communication Technology Satellite is 4 years.


The Positioning Accuracy of the Argos DCS Satellite System is Up to 150 m.


The Attitude Modes of the Spacecraft Satellite is Nadir-pointing, Ram-pointing, Inertial-pointing, Slew-pointing.


The Neutron Production of the Lunar Surface Surface is Constant bombardment by cosmic ray protons.


The Space Act Agreement Partner of the SpaceX Company is NASA.


The Technology of the LRO Mini-RF Transmitter Transmitter is MPM (Microwave Power Module).


The Distance Traveled of the InSight Spacecraft is 172 million miles (277 million kilometers).


The Quantity of the Magnetorquers Attitude and Orbit Control Subsystem is 3.


The Authors of the Magnetospheric Multiscale (MMS) Satellite is J. L. Burch1, R. B. Torbert, T. D. Phan, L.-J. Chen, T. E. Moore, R. E. Ergun, J. P. Eastwood, D. J. Gershman, P. A. Cassak, M. R. Argall, S. Wang4, M. Hesse, C. J. Pollock, B. L. Giles, R. Nakamura, B. H. Mauk, S. A. Fuselier, C. T. Russell, R. J. Strang.


The Instrument Type of the RadMon Radiation Monitor is Miniature Particle Telescope.


The Development Team of the Binar-1 CubeSat is Team of students and engineers at Curtin University's Space Science and Technology Centre.


The Data Center Members of the Euclid Satellite is 1000+ members of the Euclid Consortium.


The Background Components of the Optical Receiver Receiver is Detector dark current, detected thermal emission of the receiver, detected solar illumination reflected from the lunar surface.


The HPBW AZ of the Antenna ADS-B Antenna is 33º.


The Development of the Galileo App Mobile Application is Internal Competition for ESA Trainees.


The Mission Type of the KySat-2 Satellite is EO.


The Cross-Track Coverage of the MSI-0 and MSI-1 MSI Instruments is 60 km.


The Satellite Launch Dates of the AMSU Advanced Microwave Sounding Unit is NOAA-15 (1998), NOAA-16 (2000), NOAA-17 (2002).


The Launch Date of the CAS500 Satellite is 22 March, 2021.


The Average Concentration of the Ozone Layer Atmospheric Layer is 220 Dobson Units.


The Thermal Stability of the Euclid Satellite is Maintained during slew maneuvers.


The Kinematic properties of the Ejecta cloud Materials on the Mercury surface, regolith is > 0 km/s.


The Polarization Channels of the SGLI Imager is 3 directions.


The Ground Station of the CanX-7 Satellite is SFL ground station in Toronto.


The GaN Manufacturing Process of the UMS Company is Placed onto the European Preferred Parts List of the European Space Components Coordination.


The Field of View (FOV) of the PamCam Panoramic Camera is 20º x 16º.


The Heater Rings of the FPA Focus Control System is Lower and upper sides of the telescope attachment.


The Cube Corner Reflectors (CCRs) of the LARES Satellite is 92.


The Launch Year of the Sentinel-1A/B Satellite is 2014.


The Mission Duration of the STEREO Satellite is 5 years.


The Expected Lifespan of the Automation System System is Another decade of safe operations with XMM-Newton.


The Objective of the TanSat Satellite is Retrieve the atmosphere column-averaged CO2 dry air mole fraction (XCO2) with precisions of 1% (4 ppm) on national and global scales.


The Orbit Capability of the Spacecraft Bus (Avionics Module=AM) Satellite is LEO, MEO.


The Radiation hardness of the STRV-2 DHS Data Handling System is about 100 krad.


The Data Release 3 and Data Release 4 of the Gaia Satellite is In production.


The Matchpoint Maneuver Altitude of the OSIRIS-REx Spacecraft is Approximately 246 ft (75 m).


The Resolution of the TerraSAR-X SAR Satellite is 3 m or better in stripmap and spotlight mode.


The Observation Period of the BRITE satellites Satellite is Hours to Months.


The Cell Type of the Photo-Voltaic Array Power Generation is Triple junction GaAs cells (3G-28%).


The Gd Cross Section for Thermal Neutrons of the LND Particle Telescope is 48’890 b.


The Measurement Capabilities of the Copernicus Sentinel-3 Satellite is Earth’s oceans, land, ice and atmosphere.


The Emission Types of the Pulsars Neutron Stars is Radio, other types of radiation, thermal radiation, non-thermal radiation.


The Radiometric stability of the Spectrometer Spectrometer is <0.65% (SWIR, <0.5% (MWIR), <0.4% (TIR).


The Sampling Arm Length of the OSIRIS-REx Spacecraft is 11-foot (3.35-meter).


The Speed of Particles of the SS 433 Microquasar is Close to a quarter the speed of light.


The Mono Mode Swath of the LISS-4 Camera is 70 km.


The Thermal Environment After Separation of the MMO Spacecraft is High temperature, illuminated by sunlight.


The Location of the MOC Mission Operations Center is Darmstadt.


The Length of the Heat Probe Instrument is 16 inches (40 centimeters).


The Orbit Altitude of the CHORUS Satellite is Approximately 588-602 km.


The Launch Date of the SMART-1 Satellite is September 27, 2003.


The Mission Status of the Tandem-L Satellite is Proposal.


The URL of the Near Earth Asteroid Scout Satellite is https://web.archive.org/web/20220815171855/https://ieeexplore.ieee.org/document/8742190.


The Function of the Device Sample and Hold Stage is Transfer information at the end of the integration cycle.


The Number of RadFETs of the CDE Dosimeter is 8.


The Mission Overview Date of the Sentinel-1 Satellite is July 12-17, 2009.


The Observation Range of Doppler Velocity of the CPR Millimeter-Wave Radar is ±10m/s.


The Components of the Integrated Navigation System Navigation System is INS, star tracker (2), altimeter (2), velocimeter (2) and image sensor (2).


The Size of the Satellite Observation Instrument is 35.7 x 36.2 x 15.8 cm.


The Contact Initiation Time of the Microhard Ground Station Ground Station is Five to ten minutes after the expected scheduled contact.


The Data Rate of the Optical link Communication System is 2.8 Gbit/s (1.8 Gbit/s user data).


The Band of the IASI Infrared Atmospheric Sounding Interferometer is 3.


The Wavelength Range (UV) of the Sentinel-4/UVN Instrument is 305-400 nm.


The Mass of the SpinSat Microsatellite is 57 kg.


The Operating Distance of the OE Satellite is Up to 7 km.


The Orbit Position of the BeiDou-1C Satellite is GEO, 110.5º E.


The Instrument Type of the AWiFS Instrument is High resolution optical imagers.


The Phase of the UV2VIS SO Instrument is Engineering and Qualification Model.


The Computer Interface of the ADCS Attitude Determination and Control Subsystem is Attitude sensors and actuators.


The Launch Date of the Jason-3 Satellite is 2014.


The LRIT and HRIT Broadcasting Service of the GK2A satellite Satellite is L-band.


The Inclination of the Satellite Orbit is 97.7°.


The Parachute Manufacturer of the ExoMars mission Mars Mission is Arescosmo.


The Maximum Microsatellite Mass of the NanoRacks Microsat Deployer Satellite Deployer is 100 kg.


The Thrusters of the KOMPSAT-6 Satellite is 1 N thrusters for precise orbit correction.


The Duty Cycle of the Instrument Satellite Instrument is 100%.


The Use of the Turnstile antennas Antenna is Communications with the spacecraft bus.


The Conference Location of the Sentinel-3 Satellite is Oslo, Norway.


The Bandwidths of the Ku-band Radar Altimeter Frequency Band is 320, 80 and 20 MHz.


The Background Area of the Detector Imaging Device is 10 x.


The Payload of the Sich-2 Satellite is Multispectral scanner, middle IR scanner, platform command & data handling subsystem, X-band communication subsystem.


The Simulation Models of the PRISMA project Satellite Project is Reaction Wheels (RW), Magnet Torquers (MT), Hydrazine Thrusters, Micro propulsion Thrusters, Sun Sensors (SS), Magnetometer (MAG), Accelerometer (ACC), GPS models, FFRF (Formation Flying Radio Frequency) model, Startracker (ST) and Visual based sensor (VB.


The Science Objectives of the SAGE-III Instrument is Extend the SAM II, SAGE I and SAGE II self-calibrating solar occultation data sets.


The Manufacturer of the Resurs-P1 Satellite is NTs OMZ (Research Center for Earth Operative Monitoring).


The Correction Level of the Sun and Galactic Glint Optical Phenomenon is Level-2.


The Swath per channel of the Eastman Kodak KLI14403 linear CCD sensor Sensor is > 300 km.


The Battery Capacity of the EPS Electric Power Subsystem is 125 Ah.


The RAM of the STRV-1d DHS Data Handling System is 1024 k.


The Temperature Difference of the WISPR Imaging Instrument is 85 degrees Fahrenheit.


The Data of the UKube-1 Satellite is < 36 kB per orbit.


The Sailboat (SB) Mode of the ICESat Satellite is YG axis (plus or minus) is closely coincident with the satellite velocity vector.


The Mission Life of the ANUSat Satellite is 2 years.


The Cross-Calibration Precision of the Copernicus Sentinel-6 Satellite is Within 1 mm.


The Measurement Domain of the VHRR Instrument is Atmosphere, Ocean, Land.


The Daily system capacity of the WorldView Legion Satellite System is 3x.


The Design Life of the MEV-1 Satellite is Redundant and high reliability 15+ years.


The Rendezvous Target of the OSMA-1 Satellite is Landsat-7 spacecraft.


The Voltage of the Voltage 4 Modulator is 5.5±2%.


The Solar cells type of the EPS Electrical Power Subsystem is GaAs multijunction cell.


The Approach of the New Space Companies Companies is Make access to space affordable through innovation, flexibility, and miniaturization.


The Band 13 Detector of the S-192 optomechanical scanner Scanner is Photoconductive HgCdTe.


The URL of the SpaceX 2 Mission is http://www.nasa.gov/pdf/729030main_spacex_2_cargo_manifest.pdf.


The Mission Planning Verification System of the KOMPSAT-2 Satellite is Unknown.


The Altitude of Checkpoint Rehearsal of the OSIRIS-REx Spacecraft is 246 feet (75 meters).


The Standards of the Data Processing Chain Satellite System is OGC (Open Geospatial Consortium) standards, EO GML meta data, OGC WPS, ESA's Generic Interface for Instrument Data Processing.


The Builders of the SCIAMACHY Spectrometer is DASA/DSS, Fokker Space, TNO, SRON.


The Launch Date of the PSLV Launch Vehicle is 12 Jan. 2018.


The Management of the InSight Spacecraft is JPL, a division of Caltech in Pasadena, California.


The Image Segment Size of the CaSSIS Imaging System is 7 x 38 km.


The Dimensions of the Trius SX9 Package is 70 mm long and 75 mm in diameter.


The Energy Storage of the Electric Power Subsystem Power System is Lithium-ion batteries.


The Presentation Date of the Prisma Satellites Satellite is June 4-8, 2012.


The Mounting Locations of the OPS systems Sensor is 5 different sides of the cuboid.


The Spectral Range (µm) of the Band 4 Spectral Band is 10.3 - 11.3.


The Spatial Resolution of the JL-1-GF03B Microsatellite is 1 m.


The Number of Additional Satellites of the OneWeb Satellite Constellation is 34.


The Wavelength Range of the Spectral Channels Satellite Instrument is 0.55 - 0.75 µm.


The M1 Mirror Diameter of the TX Telescope Telescope is ~220 mm.


The Orbital Plane Interval of the S/C Satellite is 19 minutes.


The Propulsion System of the GFO Satellite is Hydrazine.


The Mission Status of the ST5 Satellite is Mission complete.


The Power Requirement of the DORIS Instrument is 20 W.


The Technology of the Cesium Mission 1 Satellite is Electronically steerable, multibeam APA (Active Phased Array).


The F Number of the CIRiS Instrument is F/1.8.


The Manufacturer of the HRC High-Resolution Camera is ESA.


The Velocity Measurement Range of the NMS Mass and Velocity Spectrometer is 0.1-2 km/s.


The URL of the ICEYE X1 Satellite is https://www.iceye.com/press/press-releases/first-iceye-x1-radar-image-from-space-published.


The Build Date of the IUE (International Ultraviolet Explorer) Satellite is 1970s.


The Performance Range of the VIS Spectrometer is 365 - 500 nm.


The Coverage of the Ka-band Channels Communication System is Two contiguous sectors in north-eastern US plus sixteen isolated spot beams.


The Imaging Resolution of the Direct Imaging System Imaging System is Lower than PAIS with eight subapertures.


The Orbit of the OSIRIS-REx Spacecraft is Bennu’s orbital plane.


The Pass Frequency of the Satellite Orbit Type is Once per orbit.


The Next Release of the Request for Information Process is Q2 of CY 2022.


The Telescope Diameter of the S-192 optomechanical scanner Scanner is 30 cm.


The Pointing Adjustment of the Kepler Spacecraft is Slight.


The Spectral Bands of the Imager Satellite Instrument is PAN: 0.45-0.90 µm, B1/blue: 0.45-0.52 µm, B2/green: 0.52-0.59 µm, B3/red: 0.63-0.69 µm, B4/NIR: 0.77-0.89 µm.


The Size of the NanoAvionics M6P 6U satellite bus Satellite Bus is 6U.


The Not Used for Payload Synchronization of the SpaceWire Data Distribution is Not used for payload synchronization.


The Telemetry Data Rate of the Instrument Sensor is 8 kbit/s.


The Date of the Manam Volcano, Papua New Guinea Image is 30 May 2022.


The Orbit Type of the Rstar Data Relay Microsatellite is Elliptical.


The Measurement Goal of the Lunar Flashlight Satellite is Measure the surface abundance of water ice on the lunar South Pole with concentrations of 5 wt% or less, down to as little as 0.5 wt%, with a spatial resolution of 10 km or better.


The Responsibilities of the X-band stations Ground Stations is Scientific satellite tracking, science data reception, raw data recording, formatted outputting, data transfer to the Mission Center.


The Image Center Coordinates of the CaSSIS Instrument is 28.36ºS/79.75ºE.


The Instrument power of the Optical System Imaging System is 200 W.


The Tracking of the FPM Fine Pointing Mechanism is ±20 µradians.


The Components of the NRD Navigation Radar Detector is Antenna and receiver electronics.


The Orbit of the NigeriaSat-X Satellite is Unknown.


The Cargo Capacity of the Canadarm2 Robotic Arm is About 4500 kg.


The Polarimetric SAR Interferometry of the TDX/TSX Satellite is Combines interferometric with polarimetric measurements.


The Support Phase Time Period of the Mango Tango Satellite Formation is 20.06 to 01.07.2010.


The Power of the LCT instrument Instrument is 160 W.


The Mission of the GRACE-FO Satellite is Gravity Recovery and Climate Experiment Follow-On.


The Structure of the SCD-2 Satellite is Aluminum honeycomb.


The Date of the 28th Annual AIAA/USU Conference on Small Satellites Conference is August 2014.


The Components of the C3S Command, Control and Communication Segment is Ground Station (GS) element, Mission Management Center (MMC) element, Data Routing and Retrieval (DRR) element.


The Thrust of the Propulsion System Satellite Propulsion is 10 N.


The Configuration of the O/OREOS nanosatellite Satellite is 3U CubeSat.


The Powering of the Valves Controller Board Propulsion System is Telecommands.


The Service Area of the ASF Data Node is North, Central and South America.


The Type of the NISP Near Infrared Spectrometer and Photometer is Instrument.


The NEΔT @ specified scene temperature of the Instrument Spectral Imager is 0.1-0.7 K @ 250 K.


The Historic Landing Date of the Philae lander Lander is 12 November 2014.


The Image Resolution of the Herschel Telescope is 2 arcmin by 2 arcmin.


The Frequency Range of the MWRI Microwave Radiometer Imager is 10.65-89 GHz.


The Frequency of Stellar Mergers of the Blue Ring Nebula Nebula is Once every 10 years in our Milky Way galaxy.


The Performance Evaluation of the ASTER Instrument is Not Provided.


The Mission Objective of the TWINS Satellite is Investigate the distribution of the extended neutral hydrogen (H) exosphere and the relative contributions of hydrogen and oxygen to the terrestrial ring current (RC) and plasma sheet.


The XCO2 Changes of the CO2 Greenhouse Gas is < 1 ppm.


The J2000 declination (deg) of the B1758-250 Pulsar is -25.079.


The Mass of the Spacecraft Satellite is ~2500 kg (launch mass).


The Planned Total In-Orbit Lifetime of the GHOSt satellites Satellite is Just over 5 years.


The Objective 2 of the CITRIS Receiver is Provide a global map of ionospheric densities and irregularities to improve current models of the ionosphere.


The Board Standard of the MuREM Radiation Monitor is PC104.


The Partner of the ELSA-d IOD Mission is SSTL.


The Operation Duration of the SuperDARN HF Radar is Not specified.


The Manufacturer of the SoftRide Isolation System Satellite Component is CSA Engineering.


The Quantity of the GPS receiver Receiver is 1 unit.


The Data Rate of the Earth Radiation Budget Experiment (ERBE) Instrument is 10.5 kbit/scanner (average).


The Number of Stations of the DRDC Ground Station Network Ground Station Network is 6.


The Program Affiliation of the IMAP Satellite is Solar Terrestrial Probes (STP) Program.


The Shape of the Heliosphere Space Phenomenon is Deflated croissant.


The Number of Solar Panels of the AprizeSat Satellite is 6.


The Data Release Date of the GRAIL Satellite is 2014.


The Transmitter Power of the RF Communications Data Transmission is 1.5 W.


The Regulated Bus Voltage of the Power Subsystem Subsystem is 5 V.


The Communication Objective of the QUESS satellite Satellite is "hack-proof" quantum communications.


The Speed of the 5G Network Telecommunications Network is Faster than current data speeds.


The Development Date of the GMV Company is 24 June 2021.


The Field of View of the Lightning Imager Camera is Atlantic Ocean, a small part of Africa and part of South America.


The Payload of the MANTIS Satellite is High resolution Earth observation camera.


The Final Terrestrial Trip Date of the SmallGEO Communications Satellite is Dec. 1, 2016.


The Cargo of the Kounotori H-II Transfer Vehicle is Six new lithium-ion batteries and corresponding adapter plates.


The Common Functionality of the KazEOSat-2 Satellite is Antenna scheduling, user office and image processing facilities.


The Focal Length of the Telescope Optical Instrument is 234.5 mm.


The Toxin Production of the Blue-Green Algae Microorganism is Can produce toxins that can make you or your pets sick if swallowed or possibly cause skin and/or eye irritation due to contact.


The Proximate Cause of the Fairing Satellite Component is Fairing separation failed.


The Period of the Satellite Satellite is 103.2 minutes.


The Conference Presentation Date of the Trailblazer CubeSat is March 29-31, 2011.


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


The Laser Altimeter of the OSIRIS-REx Spacecraft is OLA.


The Owner of the NeuSAR Satellite is DSO National Laboratories, Singapore, with support from the Office for Space Technology and Industry (OSTIn).


The Polarization Measurement of the WUPPE Spectrophotometer is Function of wavelength.


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


The Purpose of the LRO Satellite is Observing the moon.


The Event Rates of the LET Low Energy Telescope is Up to ~10 kHz.


The Orbital Period of the IBEX Spacecraft is 7.5 days.


The Image Release Date of the Spitzer Space Telescope Space Telescope is 27 January 2020.


The Peak Manufacturing Rate of the SSTL-300 S1 Satellite is 4 units per year.


The Monitoring of Technology Advancement of the Proving Ground Space is Close.


The Wavelength of the EUV Imager Imaging System is 30.4 nm.


The Bus of the Suomi-NPP Satellite is Ball Commercial Platform 2000 (BCP 2000).


The Operation of the Mx Satellite Instrument is For most of the orbits based on the user demands.


The Asteroid Survey of the Gaia Satellite is 156 thousand rocky bodies.


The Advantages of Optical Communications of the OICETS Satellite is Support of much higher data rates and transmission capacities than in conventional radio links, lower risk of link interference with other optical communication systems, as well as in more compact and lighter designs of communication equipment.


The Presentation Date of the Magnetospheric Multiscale (MMS) Mission is Feb. 28 - March 4, 2011.


The Heliocentric Range of the S/C Spacecraft is 1.34 to 5.4 AU.


The Period (min) of the Meteor-3-1 Satellite is 110.3.


The Total Satellites of the OneWeb Satellite Constellation is 218.


The Expected Resume Date of the Yutu-2 Lunar Rover is Next Thursday (10 January).


The Altitude at Entry Interface Point of the Experiment Data Telemetry is 120 km.


The Geometric Error Types of the PROBA-V Mission Satellite Mission is Absolute, inter-band and multi-temporal.


The Mission Status of the Megha-Tropiques Satellite is Operational (extended).