The Data Availability of the Landsat 4 Satellite is All TM data January 2009.


The Channels of the Earth Radiation Budget Experiment (ERBE) Instrument is Total radiance (0.3 to 100 µm); Shortwave (0.3 to 5 µm); Window (8 to 12 µm).


The Band of the Eutelsat Quantum Satellite is Ku-band.


The Orbit of the Konnect Satellite is GEO.


The Loss of Communication of the AeroCube-3 Satellite is After 205 days on orbit.


The Operation Pause Date of the InSight Mars Lander is Around Oct. 7.


The Spatial Pixels of the Telescope Optical Instrument is 1024.


The Manufacturer of the BlackSky’s Global-4 Earth-imaging satellite is BlackSky.


The Affiliation of the SPADUS Instrument is A. J. Tuzzolino, R. B. McKibben, J. A. Simpson, S. BenZvi, H. D. Voss, H. Gursky.


The Exposure Time of the NISP Spectrograph Instrument is About 4000 seconds.


The Attitude Pointing Accuracy of the GF-2 spacecraft Satellite is 0.0025º.


The Purpose of the NanoSail-D2 Satellite is Demonstrate and test the deorbiting capabilities of a large low mass high surface area sail.


The PI of the SPARCS Satellite is Evgenya Shkolnik.


The Spectrometer Bands of the GeoCarb Instrument is 0.76 µm, 1.61 µm, 2.06 µm and 2.32 µm.


The Orbit Inclination of the HTV-8 Spacecraft is 51.6º.


The URL of the CartoSat-1 Satellite is http://www.gaf.de/.../pr_germany_euromap_antrix_01-2008.pdf.


The Data Upload Frequency of the Base Station Data Collection System is Every half an hour.


The Observation Date of the Eruption Solar Event is March 12 and 13, 2016.


The Concept Developed of the CubeSat-based Optical Crosslink Nodes Satellite is Yes.


The Solar Cells of the EPS Electric Power Subsystem is 24.


The Operation as Radar Interferometer of the TerraSAR-X and TanDEM-X Satellites is Since December 2010.


The Field of Regard of the WV60 imager Imaging System is 900 km.


The Marsquake Discovery Date of the InSight Mars Lander is 22 September 2021.


The Ion Energy Threshold of the DIDM Instrument is Certain threshold potential.


The Sample Mass of the OSIRIS-REx Spacecraft is At least 60 gram.


The Position and Attitude Determination of the Ground Station System is Automatic.


The Ability of the THEMIS Satellite is Orbit Adjustment.


The Manufacturer of the AD9694 Analog-to-Digital Converter is Analog Devices.


The Alignment of the GT Fine-Pointing Error Signal Provider is Nominally aligned with the spacecraft axes.


The Development Methodology of the TCS Thermal Control Subsystem is Corresponded to the recommendations of the ECSS.


The Short Range Navigation of the ATV-5 Spacecraft is Optical sensors on ATV.


The DEM Resolution of the Terra/ASTER system Satellite System is 30 m.


The Number of Non-Separating Components of the ORS-3 Mission is 2.


The Launch Date of the Jason-1 Satellite is Dec. 07, 2001.


The Power Dissipation of the SVM Service Module is 330 W.


The Data Transmission of the Ground Station Contact Communication is Occurs above the corresponding minimum elevation.


The Optical Link Bandwidth (Uplink) of the OICETS satellite Satellite is 2 Mbit/s.


The Mass (kg) of the RADARSAT-2 Satellite is 2200.


The Launch Mass of the EROS-A Satellite is 260 kg.


The Single Pass Mono Coverage of the QuickBird-2 Satellite is 1 strip of 350 km.


The Acta Astronautica Publication Date of the IRS-P6 Satellite is Jan. 2007.


The MTF of the Instrument General is About 20% at Nyquist frequency.


The Solar Panels of the GaoJing / SuperView minisatellites Satellite is Two on each of the pair of solar panel wings.


The Destination of the Juice mission Spacecraft is Jupiter.


The Duplex of the High-speed link Radio Link is Half.


The Energy Range of the HIT High-energy Ion Telescope is ~2 to ~40 MeV/nuc.


The Transfer Date of the BEAM Space Station Module is 21 January 2022.


The Protocol of the RF communication subsystem Communication Subsystem is AX-25.


The Mass of the PEACE Instrument is 6.5 kg.


The Status in 2004 of the OPAL Satellite is Semi-operational.


The Perigee of the BUV Sensor is 1092 km.


The Production Capacity of Factory of the Satellogic Satellite Company is 25 satellites a quarter.


The Data Storage of the MMU Memory Management Unit is 32 Gbit.


The Formation Geometry of the TDX and TSX Satellites Satellites is Bistatic Close formation with Large Perpendicular Baseline.


The Delta V of the PROP unit Propulsion System is 10 m/s.


The Orbit of the Restore-L Satellite is More than 600 km above Earth.


The Angular resolution (2 px) of the HRI Lyman-α 1216 Å Passband center is 1 arcsec.


The Moving Parts of the BRITE Telescope is None.


The Multispectral Imagery Resolution of the Satellogic Satellite Manufacturer is 1 meter.


The Mass of the Spacecraft Satellite is 1700 kg.


The Instrument size of the Spectrometer Spectrometer is 71 cm x 88 cm x 94 cm.


The Along-Track Separation of the TDX and TSX Satellites Satellites is 76 km.


The Background Concentration of the CO2 Greenhouse Gas is 415 ppm.


The Terra Carta Supporter Date of the Satellite Vu Company is September 21, 2022.


The NEΔT (K) of the ICI-6 Radiometer is 1.2.


The Power Source of the RapidScat Scatterometer Instrument is Space station.


The Covered Area of the Image Data is Approximately 30 km x 50 km.


The Comet Discovery Count of the SOHO Satellite is 2875.


The Payload of the CanX-7 Satellite is ADS-B.


The Authors of the Submerged Sources of Transient Acoustic Emission from Solar Flares Research Paper is Charles Lindsey, J. C. Buitrago-Casas, Juan Carlos Martínez Oliveros, Douglas Braun, Angel D. Martínez, Valeria Quintero Ortega, Benjamín Calvo-Mozo, and Alina-Catalina Donea.


The Update Date of the CSDA Program is January 28, 2022.


The Download URL of the Earth Observation Constellation Satellites Satellite Constellation is http://www.nspo.narl.org.tw/ICGPSRO2013/download/2nd_ICGPSRO_U3-4A-102-02_Chen-Joe_Fong_05-16-2013.pdf.


The Command Transmission Capability of the Argos System Data Collection System is S/C-to-platform.


The Launch Date of the OrbView-3 Satellite is June 26, 2003.


The Sensors of the Attitude Control Subsystem Attitude Control System is Sun sensors, star sensors and gyroscopes.


The Mission Objective of the DIDO-3 Satellite is Gather data by researching the effects of a microgravity environment on biological materials.


The Regained Contact Time of the Philae Lander is 22:19 GMT.


The Pointing Knowledge of the HY-2A Satellite is < 0.05º.


The Deployment Date of the BX-1 Microsatellite is Sept. 27, 2008.


The Measurement Category of the CryoSat Satellite is Gravity, Magnetic and Geodynamic measurements, Landscape topography, Ocean topography/currents, Sea ice cover, edge and thickness, Ice sheet topography.


The Recipient of the Payload Satellite Component is Clyde Space.


The Onboard Sensors of the LAGEOS Satellite is None.


The Mode of Operation of the EPI-Lo Electron Detector is Single parameter measurement.


The Flare List Events with Gamma-ray Line Emission of the RHESSI Satellite is 27.


The Data Processing Capacity of the IDPS Interface Data Processing Segment is 100 times the volume of legacy data.


The Launch Date of the ArgoMoon CubeSat is 16 November 2022.


The Publication Date of the SphinX Solar Photometer in X-rays is Nov. 2008.


The SIS/URE of the QZS-1 Satellite is 40 cm (rms).


The Sky Coverage of the TESS Satellite is 85 percent.


The Average Duration of the LEO-LEO Inter-satellite Link Communication System is About 20 minutes.


The Orbit Type of the ResourceSat-2A Satellite is Sun-synchronous orbit.


The Number of Hosted Payloads in Testing of the GHGSat Company is 3.


The Mission Status of the ZY 1-02C Spacecraft is Operational.


The Structure and Power Systems Provider of the SloshSat-FLEVO Satellite is Dutch Space, Leiden, The Netherlands.


The Manufacturing of the SFINKS Solar Array is Made by depositing layers of thin-film of photovoltaic material on a flexible plastic.


The Ground Monitoring Data Rate of the EROS-A Satellite is 2.5 or 15 kbit/s.


The Dimensions of the Fragments Space Debris is 2-D or 3-D.


The Parameter Estimation of the User Segment Geometrical Calibration Tool Calibration Tool is Exterior Orientation parameters and Interior Orientation deformations.


The 34 GHz Channel Function of the JMR Microwave Radiometer is Correction for non-raining clouds.


The Operation Status of the FY-3C Satellite is Operating in 2016.


The Measurement of the SSAS Sensor is Spin rate.


The Manufacturer of the VRSS-1 Satellite is CGWIC (China Great Wall Industry Corporation).


The Modulation of the RF communications Communication System is FSK.


The Accuracy of the Ionosphere Plasma Density Satellite System is < 20% (ρ=10 9  -10 11  m -3 ) – 5% (ρ >10 11  m -3 ).


The Orbit Type of the Secondary Payloads Satellites is Near-circular orbit.


The ISL Range of the CanX-4&5 Satellite is 5 km.


The Pointing Accuracies of the AOCS Attitude and Orbit Control System is Pitch and roll = 0.2º, yaw = 0.4º.


The Typical Value of the AAOD Satellite Instrument is 0-0.05.


The Launch Date of the Eutelsat Quantum Satellite is 2nd half of 2020.


The Test Date of the Galileo Satellites Satellite is 4 December 2018.


The Volume of the MiniCOR Coronagraph is ~2U.


The Mission Life of the CLARREO Pathfinder Satellite is 1 year.


The Locations of the Ground Stations Ground Stations is Oberpfaffenhofen, Neustrelitz, Adelaide/Australia and Izaña/Tenerife.


The Power Bus Voltage Range of the EPS Electric Power Subsystem is 25-32.8 VDC.


The Calibration Date of the Sentinel-1 Satellite is Sept. 9-13, 2013.


The Instrument of the Odin Satellite is OSIRIS.


The Battery Capacity of the Spacecraft Satellite is > 30Ah @ EOL.


The Presentation URL of the SVOM Satellite is https://indico.in2p3.fr/event/12490/session/3/contribution/7/material/slides/0.pdf.


The Antennas of the Yutu-2 Lunar Rover is Three 5-meter antennas.


The Unknown of the GeoSTAR-III Satellite System is Unknown.


The Launch Date of the ALBus CubeSat Satellite is December 16, 2018.


The Mission Objective of the IMAP Satellite is Learn more about the generation of cosmic rays in the heliosphere.


The Total Mass of the QuakeSat Satellite is about 4.5 kg.


The Model of the USRP Transceiver is USRP N210.


The Image Receiving Stations of the Pleiades System Satellite System is Japan, China and Canada.


The LISS-I Data Downlink of the Satellite Satellite is S-band.


The Solar Environment of the SPC (Solar Probe Cup) Sensor is More severe than all previous experience.


The Start Time of the Planning Process Satellite Mission is About three years before launch.


The Rescheduled Launch Date of the OFT-2 Uncrewed Test Flight is No earlier than Aug. 3.


The Minimum Impulse Bit of the CanX-4&5 Satellite is 0.1 mNs.


The Dead Zone Impact of the Gulf of Mexico Body of Water is Impacts fish and the regional economy.


The Total FOV of the Sensor Unit Sensor is > 2π sr.


The Spin Stabilization of the IMP-8 Spacecraft is 22.3 rpm.


The Tandem Operations Start Date of the ERS-1 and ERS-2 Satellites is September 1995.


The Number of Satellites of the Constellation Satellite Constellation is 10.


The Precision of the ALOS-4 Satellite is Five times more than ALOS-2.


The Cumulated Absolute Height Error of the TanDEM-X Satellite is 3.5 m.


The Purpose of the Biomass satellite Satellite is Chart all the forests on Earth.


The Energy Range of the IMAP Satellite is 10 eV to 100 keV.


The Artists of the Sojourner 2020 Art Payload is Nine.


The Pointing Knowledge Stability of the Instrument Satellite Instrument is ±9.7 µradians over 34 minutes.


The Resolution of the Spotlight-1B Satellite is Finest.


The Launch Provider of the SOCRATES Microsatellite is MHI (Mitsubishi Heavy Industries, Ltd.).


The Operation Basis of the SILEX Laser Communication System is Direct-detection system.


The Image Capture Date of the LRO Satellite is October 12, 2014.


The Repeat Orbit Cycle of the Sentinel-1A and Sentinel-1B Satellites is 12 days.


The CEO of the CesiumAstro Company is Shey Sabripour.


The Global Coverage of the MERSI-RM Radiometer is Once per day on VIS/NIR/SWIR channels, and twice per day on MWIR/TIR.


The Record Duration of the Landsat Satellite is Four decades.


The URL of the ISEE-1 and ISEE-2 Satellites is http://www-ssc.igpp.ucla.edu/personnel/russell/papers/ISEE_fluxgate/.


The Reference Orbit of the Spacecraft Satellite is SSO (Sun-synchronous Orbit).


The Data Contribution of the Sentinel-6 Satellite is Sea-level rise estimates.


The Provider of the YouthSat Satellite is ISRO.


The Access of the Airbus Constellation Satellite Constellation is Pléiades, SPOT, TerraSAR-X, TanDEM-X radar and DMC Constellation.


The Mission Title of the Firefly Satellite Satellite is Understanding Earth’s most Powerful Natural Particle Accelerator.


The Mass of the Max Valier Nanosatellite is 16 kg.


The New Landing Site of the Philae lander Lander is Abydos.


The FOV of the LWIR Cameras Camera is 16°.


The Engine Firing Duration of the ExoMars TGO Orbiter is 52 minutes.


The Antenna Gain of the LNA Low Noise Amplifier is 6 dBi.


The URL of the SPIDER Imaging System is https://lockheedmartin.com/content/dam/lockheed-martin/eo/documents/webt/spider-infographic.pdf.


The Slit 2 Spectral Range of the MEGS-A Spectrograph is 17.0 -37.0 nm.


The Launch Announcement Date of the MethaneSAT Satellite is 13 January 2021.


The Conference Date of the GRAIL Mission is June 11-15, 2012.


The Acquisition Year of the Amptek X123 SDD Silicon Drift Detector is 2012.


The CCD Array of the WFC CCD Camera is 512 x 512.


The Uplink Frequency of the Myriad RF board RF Board is 300 MHz up to 3.8 GHz.


The Composition of the Plasma Matter is Gaseous and highly conductive charged particles.


The Locomotion Mode of the Rosalind Franklin ExoMars rover Rover is Wheel walking.


The Uplink Rates of the LLCD PAT Systems Communication System is Up to 20 Mbit/s.


The Common Electronics of the COR1 Coronagraph1 imager is Common electronics, 1 MHz readout rate, 14 bit/pixel quantization.


The Digital I/O Pins of the CSI Data Communication is 32.


The Sampling Rate of the OVM Overhauser scalar magnetometer is 1 Hz.


The Transmitted Wavefront Distortion of the VPW42 Optical Window is λ/8 at 633 nm.


The Mass of the OPSAT-1000 satellite bus Satellite Bus is 178 kg.


The Propulsion System of the Lunar Flashlight 6U CubeSat Satellite is Novel technology developed by VACCO Industries, Inc..


The Material of the Delrin Spacers Component is Delrin.


The Payload Status of the RAVAN CubeSat is Powered off.


The Dry Mass of the Satellite Bus is 270 kg.


The Ground Resolution of the Scanner Assembly Instrument is 1 km.


The Discovery of the TESS Satellite is Young Neptune-size world orbiting AU Microscopii.


The Power for Payload of the Spacecraft Satellite is 511 W.


The Calibration of the DDM Device is Relative.


The Material of the Bulkhead Structural Component is Two shells brazed together.


The Occupation of the Max Valier Person is Science-fiction writer and an amateur astronomer.


The Program Status of the Roshydrometsatellite Satellite is Unknown.


The Volume of the Electronics volume Spectrometer is 320 mm x 210 mm x 150 mm.


The Solar Panel Type of the AprizeSat Satellite is UTJ (Ultra Triple Junction) GaAs.


The Test Subject of the Biofilms Experiment is Laser-structured metal surfaces such as steel, copper and brass.


The Eclipse Observation Date of the PROBA-2 Satellite is March 20, 2015.


The Quantity of the Iridium NEXT satellites Satellite is 10.


The Deployment Date of the BRO-2 and BRO-3 Nanosatellites is November 20, 2020.


The Inclination of the SEOSAT-Ingenio Satellite is 98º.


The End of Operations of the SPOT-2 Satellite is July 2009.


The Photon Index Below the Break of the First Broken Powerlaw Model Component is 1.54.


The Repeat Cycle of the PanMUX Instrument is 52 days.


The Pixel Size of the Acquisition and Tracking Camera (ATC) Camera is 20 µm x 20 µm.


The Conference Date of the CHIPS Satellite is Aug. 13-16, 2001.


The Diameter of the Kepler-442b Exoplanet is 33% bigger than Earth.


The Activity of the COVE payload Payload is Complete.


The Brightness of the McNaught Comet is High.


The Magnetic Field Strength of the Sunspot Solar Phenomenon is 6,250 gauss.


The Mass of the Spacecraft 3U CubeSat is 3.2 kg.


The Channels of the DAC Digital Analog Converter is 4.


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


The Observations Management Center of the XMM-Newton Satellite is ESAC (European Space Astronomy Center), formerly known as VILSPA) at Villafranca, Spain.


The Neutron Converter of the LND Particle Telescope is Natural Gd foil.


The A/D Conversion of the Satellite Satellite is 8 bit.


The Imaging Modes of the Optical Sensor Assembly (OSA) Instrument is Simultaneous imaging in both panchromatic and multispectral modes.


The Tester of the ISIM Compartment is Matt Greenhouse.


The Mass of the Photometer Instrument Instrument is ≤ 0.9 kg.


The Data Interface of the SAMPEX Satellite is SEDS (Small Explorer Data System).


The Baseline Requirement of the Interferometric Mode Observation Mode is 17 days.


The Attitude Control of the XI-IV Picosatellite is Passive stabilization of a permanent magnet.


The Average Session Time of the EAN Connectivity System is 1 hour.


The Activity Date of the GIADA Instrument is March 17-21, 2014.


The Duration of the Station Keeping Satellite Maneuver is 15+ years.


The Measurement Range of the FGM Fluxgate Magnetometer is ±64,000 nT.


The Mission Duration of the GOCE Satellite is More than four years.


The Face sheets material of the Bus structure Satellite Structure is Aluminum (AA2024-T3).


The Conference Date of the NASA Optical Communications and Sensor Demonstration Program Program is August 6-11, 2016.


The Oscillation Types of the GOLF Instrument is P and g mode oscillations.


The Tx Pulse Width of the KaRIn Instrument is 4.5 µs.


The Award Date of the Ozone Monitoring Instrument Instrument is 3 May 2019.


The Manufacturer of the EPIC Energetic Particle and Ion Composition Experiment is Not provided.


The Data Transmission of the GT Fine-Pointing Error Signal Provider is Five 250-Hz samples every 20 ms.


The Dimensions of the TEP Absorber 2 Absorber is 2.7 cm cylinder.


The Diameter (mm) of the Antenna Reflector is 600.


The Payload Module Components of the Euclid Space Telescope is Telescope, Visual Imager, Near-Infrared Spectrometer and Photometer.


The Image Resolution of the Earth Observation System Satellite System is 0.8 m.


The Position Knowledge of the GPS Receiver Satellite Component is ±60 m.


The Primary Use of the Band 6 Spectral Band is Soil humidity, provision of ice/snow cover distinguishing capability.


The Length of the Gravity Gradient Boom Attitude Actuation Device is 1.4 m.


The Type of the MSU-GS Instrument is 10-channel radiometer.


The Pointing Accuracy of the Spacecraft Satellite is 0.24 arcsec relative pointing accuracy over 1 minute.


The Swath Width of the HySI Hyperspectral Imager is 20 km.


The Attitude Control of the SOHLA-1 Microsatellite is Spin-stabilized.


The Electromagnetic Spectrum Range of the LISS-3 Imaging Sensor is Unknown.


The Fourth Set of the Iridium® NEXT Satellites Satellite Constellation is True.


The Service System Mass of the Microsatellite Satellite is 18.2 kg.


The Composition of the Ozone Molecule is Three oxygen atoms.


The Power Generation of the Spacecraft Satellite is 4 kW.


The Basis of the OBC Software Software is RTOS (Real Time Operating System).


The Receiver Channels of the Jason 2 Satellite is 8 channels.


The CCSDS ID of the GSAT-0103 Satellite is 3A7.


The URL of the ISEE-1 and ISEE-2 Satellites is http://www.ann-geophys.net/25/2633/2007/angeo-25-2633-2007.pdf.


The Orbiter Orbit of the Tianwen-1 Probe is Polar elliptical orbit (265 km x 12,000 km).


The Launch Date of the ICEYE-X1 Satellite is January, 2018.


The Grasp (500 eV) of the X-ray Imager Instrument is 27.5 cm 2 deg 2.


The Launch Date of the MICROSCOPE Satellite is April 2016.


The Closest Approach to Earth of the Bennu Asteroid is Every 6 years.


The Orbit Inclination of the SPOT-1, -2 and -3 Satellites is 98.7°.


The Measurement Range of the O3 Profile Satellite Instrument is 0-2 km(ppbv).


The Image Capture Date of the Copernicus Sentinel-2 Satellite is January 28, 2022.


The Orbit Altitude of the HY-2C Satellite is 957 km.


The Launch Date of the Chandrayaan-1 Orbiter is 2008.


The LTAN of the DMC-3 Constellation Satellite Constellation is 10:30 hours.


The Band Frequency of the OneWeb Satellite Constellation is 12 GHz.


The Firing Durations of the IEPS Ion Electric Propulsion System is Three 3-minute firings, eighteen 10-minute firings.


The Wavelength Coverage of the UVS Instrument Spectrometer Telescope is 215 nm (cha. 1), 236.5 nm (cha. 2).


The Testing of the Magnetorquers Attitude Control Device is Prototypes of the design have been successfully tested with excellent performance.


The Multispectral Mode Swath Width of the LISS-4 Camera is 23.9 km.


The Scintillator Material of the Gamma-ray Counter Detector is CsI (Tl).


The Swath of the Sentinel-2 Satellite is 290 km.


The Downlink Signal Bandwidth of the HRIT HiRID Data Receiver is 1687.1.


The Altitude of the Satellite LEO (Low Earth Orbit) is ~ 700 km.


The Absolute radiometric uncertainty of the Spectrometer Spectrometer is <0.8% (SWIR), <0.6% (MWIR), <0.45% (TIR).


The Radiation Pattern of the Antenna High-Gain Antenna is Steerable with a gimbal capable of continuously pointing toward the ground station.


The Elevation Dimension of the Active Phased Array Antenna Antenna is 1.232 m.


The Manufacturer of the SGR-ReSI Instrument is SSTL.


The Affiliation of the Hard X-Ray Burst Spectrometer Spectrometer is Solar Maximum Mission.


The Targeted Orbit of the Galileo FOC satellites Satellite is Circular, inclined at 56º with a semi major axis of 29,900 km.


The End-of-Mission (EOM) Altitude of the PUNCH Mission Satellite is Passivated and naturally reenter within 22 years.


The Signal Collection of the AIS (Automated Identification System) Hardware is Successful from space over extensive areas of open water.


The Original Mission End Date of the Kepler Space Telescope Space Telescope is 2013.


The Conference Presentation Date of the Korean Spaceborne Microwave Radiometer on STSat-2 Radiometer is July 25-29, 2005.


The Orbit Apogee of the BX-1 Microsatellite is 296 km.


The LOS Wind Error Requirement of the Mie Channel Instrument is 0.6 m/s.


The Number of Degrees of Freedom of the Grid Fins Control Surface is Two.


The Volume of the Instrument Satellite Component is 100 mm x 100 mm x 50 mm.


The Bipropellant System Total ΔV Capability of the Clementine Spacecraft is About 1900 m/s.


The Coordinator of the ESEO Satellite is University of Bologna.


The Mission Status of the ABEX CubeSat is Planned.


The AI Technology of the CIMON Astronaut Assistant is Watson from IBM Cloud.


The Pixel Sampling Interval of the Spectrometer Instrument is 28 µm.


The Solar Image Diameter of the Telescope Optical Instrument is 25 mm.


The Sensor Complement of the LAICE Satellite is In-situ measurements of wave perturbations in the ionosphere and remote sensing of the middle atmosphere.


The | of the S. Krucker Author is S. Krucker.


The Pause Time of the Lasers Light Source is 1 to 6 ms.


The Total Data Volume per Orbit of the Satellite Satellite is 77.7 Gbit.


The Applications of the HyperScout Imager is Monitoring of natural disasters such as floods delineation, forest fires hazard and desertification.


The Stowage Process Duration of the OSIRIS-REx Spacecraft is Multiple days.


The Polarization of the Antenna for Navigation Antenna is RHCP (Right Hand Circular Polarization).


The TDI (Time Delay Integration) of the Imager Imaging System is 6 selectable levels from 8 to 64 in Pan and MS.


The CCD Lines of the FPM (Focal Plane Module) Focal Plane is 3 linear CCD lines.


The Objective of the SMDC-ONE Nanosatellite is Over-the-horizon communications of unattended ground station (UGS) data.


The Design Life of the Odin Satellite is 2 years.


The Distance Traveled of the Yutu 2 Lunar Rover is 565.9 meters.


The Static RAM of the OBDH Data Handling and Processing is 256 kB.


The Data Collection Period of the Ozone Monitoring Instrument (OMI) Instrument is 150-day period from 2015 through 2019.


The Operating Modes of the IPS Instrument Pointing System is Dependent on whether the gimbal resolver or gyro was used for feedback control of attitude.


The Publication Date of the Rosetta Satellite is 26 January 2015.


The NEP of the Detector Instrument Component is < 3.7 nW at 17 Hz.


The Phase C/D Start Date of the SMOS Satellite is Mid-2004.


The Viewing Range of the TWINS Instrument is ±90º.


The Publication Date of the National Scientific Foundation (NSF) CubeSat-based science missions for Geospace and Atmospheric Research Report is October 2013.


The Ground Noise Power of the RAX-1 Satellite is -110 dBm.


The Design of the Electron Sensor Sensor is Specialized.


The Number of Stars with Multiple Planetary Candidates of the Kepler Satellite is 170.


The Volume of the Propellant Tanks Propellant is 1106 liter.


The Mission Status of the PACE Satellite is Construction and testing phase.


The Power of the Total with contingency Satellite is 18 W.


The Operational Altitude of the OneWeb Satellite Constellation is Around 1,200 km.


The Radio Occultation Profiles of the Spire Satellite Data Provider is 3,000 profiles a day for six months.


The Objectives of the DubaiSat-2 Satellite is Further develop the space program and associated sectors in the UAE, provide continuity and major improvements to the previous DubaiSat mission.


The Altitude of the Tandem-L satellites Satellite is 745 km.


The Airplane (AP) Mode of the ICESat Satellite is XG axis (plus or minus) is closely aligned with the velocity vector.


The Modulation of the Channel Communication System is QPSK, 8PSK, 16APSK, 32APSK.


The Cross-polarization Ratio of the Instrument SAR is ≤-25 dB.


The Type of the GMOD Gamma Ray Detector is Compact, silicon-based.


The Operation Start Date of the RAIDS Instrument is October 23, 2009.


The Launch Date of the InSight Satellite is May 2018.


The Client Mass of the ELSA-d Satellite Mission is ~20 kg.


The Processor of the EPS Electrical Power Subsystem is Dedicated.


The Comet Discoveries of the SOHO Satellite is 3000.


The Power Consumption of the PSU Power Supply Unit is 75 W.


The Booster's Failure Date of the Falcon 9 Rocket is Feb. 15.


The Manufacturer of the Focal Plane Detector is e2v for Astrium.


The Spectral range of the Microwave System Microwave System is 6.9, 10.6, 18.7, 23.8, 31, 36.5, 42, 48, 52.3-57.0, 89, 183.31 (GHz).


The Resolving Power of the Spectrometers Spectrometers is 15 x 10^3 for the broadband measurements.


The URL of the STEREO Satellite is http://www.nasa.gov/mission_pages/stereo/news/farside-060111.html.


The Potential Mission End Date of the InSight Seismic Experiment for Interior Structure (SEIS) is Within a year from June 22, 2021.


The Utilization of the ICI-8 Radiometer is Cloud ice water path and cirrus.


The Output of the CU Control Unit is Impulses to all channels.


The Spectral Range of the Nadir Sensor Wide-Field Telescope Sensor is 300-380 nm.


The Size of the LALT-TR Transmitter is 360 mm x 450 mm x 408 mm.


The CCSDS ID of the GSAT-0210 Satellite is 26A.


The Filter Type of the NUV channel Spectrometer is Fused Silica Window.


The Product of the Sustainability Tech Company is Satellite-connected sensors that monitor wetland hydrology.


The Technology Objectives of the ExoMars Mission is Qualification of Russian ground-based means for deep-space communications in cooperation with ESA’s ESTRACK, Adaptation of Russian on-board computer for deep space missions and ExoMars landed operations, Development and qualification of throttleable braki.


The Energy Storage Margin (120 minute window) of the RASP Maneuver Planning System is 71.1%.


The Announcement Date of the Copernicus Program is December 11, 2012.


The Type of the OBC On-Board Computer is RCM3400 of Z-World based on the microcontroller Rabbit 3000.


The Information Delivery of the Satellite Earth Observation Satellite is Actionable, affordable and timely.


The Acquisition Range of the GT Fine-Pointing Error Signal Provider is Slightly >15 arcmin.


The Gravitational Stability of the Spacecraft Satellite is < 5 x 10-11 g.


The Design Purpose of the SKOUT Ka-band Communications System is To connect government and commercial relay satellite constellations as well as direct-to-ground communications networks.


The Spatial Coverage of the SMOS Satellite is Lower at the edges of the swath.


The Data Usage of the Resurs-DK1 Earth Observation Satellite is Update and improvement of the existing geographic digital maps, offer an opportunity to enter the global market, to conduct surveys, to provide environmental monitoring, and to acquire real-time information on natural disasters or emergencies.


The Quality Requirement of the Beam Splitter and Field Widening Prisms Optical Components is Good quality over the area sampled by one spatial resolution element on the detector.


The Launch Date of the AltiKa Altimeter is 2011/12.


The Objective of the SpooQySat CubeSat is Demonstrate in-orbit a space-compatible quantum light source.


The Deployment Mission of the CubeSats Satellite is 14th.


The Manufacturer of the CDHS Command and Data Handling Subsystem is Pumpkin Inc..


The Number of Stellar Streams of the Milky Way Galaxy is At least 70.


The Provider of the NSSL Phase 2 Launch Program is ULA and SpaceX.


The User of the STK Scheduler Software is NASA.


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


The Dataset Rate of the GEOSAT Satellite is 10 Hz.


The Attitude Dynamics Analysis Presentation of the Aalto-1 Satellite is Oct. 1-5, 2012.


The Resolution of the ZY-3 Satellite is High.


The On-Ground Separation of the Slits Optical Instrument is 15.9 km.


The Accuracy of the SA Drive Mechanism Attitude Control Device is > 1%.


The Formation Start of the Azores archipelago Geographic Location is About 10 million years ago.


The Mission Status of the Sich-2 Satellite is Mission complete.


The Mass of the Instrument Spectrometer is < 10 kg.


The Utility Assess Date of the TacSat-4 Satellite is Trident Warrior 2012.


The Function of the SSPA-C Solid State Power Amplifier is Rebroadcast data processed by the EUMETSAT control center.


The Jitter of the SPARCS Satellite is 1σ ~6" over 10 minutes.


The Channels Quantity of the REM Radiation Environment Monitor is 16.


The URL of the Evaluation Process is https://earthdata.nasa.gov/esds/csdap/csdap-pilot-evaluation.


The F-number of the Telescope Optical Instrument is 2.2.


The Full Operational Service Date of the SAR-Lupe Constellation Satellite Constellation is 2008.


The Data Collection Period of the TROPOMI Tropospheric Monitoring Instrument is January 1-20, 2020 and February 10-25, 2020.


The Ellipse Axis A of the Short Wavelength Band Spectrometer is 180 mm.


The Predecessor of the TOMS Total Ozone Mapping Spectrometer is BUV.


The URL of the ExoplanetSat Satellite is https://dspace.mit.edu/handle/1721.1/61644.


The Payload Power of the EPS Electric Power Subsystem is Up to 130 W average.


The Primary Structure Components of the S/C Satellite is Central cylinder, main platform, propulsion platform, four shear panels.


The No. of Bins of the SPIM2 Spectrometer is 68, 136, or 272.


The End of Life Date of the PW-Sat CubeSat is October 28, 2014.


The Light Pollution of the Satellites Satellite is Not specified.


The Objective of the MOMA Instrument is Analyze volatile and refractory organic compounds in martian surface and subsurface sediments.


The Managing Contractor of the YES2 Satellite is Delta-Utec SRC (Space Research & Consultancy).


The Affiliation of the UiTMSAT-1 1U CubeSat is Malaysia.


The Temperature of the Red Dwarfs Star Type is Roughly a third of our Sun’s temperature.


The Resolution of the Stripmap mode (SM) Operational Mode is 5 m x 5 m.


The Measurement Domain of the HJ-1 Satellite is Atmosphere, Ocean, Land, Snow & Ice.


The Measurement Importance of the CryoSat-2 Satellite is Understanding the links between ice and climate.


The Unknown of the Asteroid Deflection Mission Mission is Unknown.


The Orbit Perigee of the Beijing-3B Satellite is 601 km.


The Revisit Cycle of the Satellite Imaging Satellite is 1-3 days (for observations at 40º latitude or higher).


The Observatory Collaboration Date of the Crab Nebula Nebula is May 10, 2017.


The Stakeholder Involvement Timeline of the Galileo Second Generation Satellite System is In the next eight months.


The Radiometric Accuracy of the Optical Scanning Design Imaging Spectrometer is <2% with reference to the sun.


The Signal Processing of the TriG receiver GNSS Receiver is Multiple reconfigurable FPGAs.


The Manufacturer of the ZY-3 Satellite is CAST/BISSE (China's Academy of Space Technology/Beijing Institute of Spacecraft System Engineering).


The Proof-mass Positioning Error of the Three-axis diagonal gradiometer Gradiometer is 6 x 10 -8  m Hz -1/2.


The Lander/Rover Landing Site of the Tianwen-1 Probe is Utopia Planitia.


The Shape of the Drag Sail Modules Satellite Component is Wedge-shaped.


The CPU Cores of the Mission Operation System Data Processing System is More than 3000.


The Lyman-alpha Forest Percentage of the Universe Cosmology is 28 percent.


The Operator of the Hellas Sat 3 Satellite is Hellas Sat.


The Coverage of the CCD Camera Imaging System is 6250 km x 300 km per scan line.


The Landing Trajectory Reconstruction of the Chang'e-4 Lunar Spacecraft is Completed.


The Calibration Function of the GMI Radiometer Radiometer is Constellation precipitation transfer standard.


The FOV (Field of View) of the Star Tracker Attitude Determination Device is 7:5º (half axis).


The Dynamic Range (Visible Channel) of the VIRR Instrument is 65 - 10,000 fL (scene brightness).


The Spectral Range of the TROPOMI Instrument is Short Wave Infrared around 2.3 µm.


The Orbit Concept of the TanDEM-X Satellite is Double helix formation.


The BCP Distribution Interval of the INTEGRAL Satellite is Every 8 s.


The Location of the GPS Network GNET Ground-based Measurement System is Greenland.


The Maximum Torque Output of the CMG Control Moment Gyroscope is 0.8 mNm.


The Earth Coverage of the Planet Satellite Imaging Company is At least 85% of the Earth’s landmass every 15 days.


The Orbital Altitude of the LDEF Satellite is 335 km.


The Data and Satellite Solutions of the SAR Satellites Satellite is Government and commercial use.


The Pixel size of the Channel 3 Sensor is 32 km x 32 km.


The Mounting Range of the WFI Camera is -24º to +24º.


The Accuracy of the Onboard Antenna Antenna is 5º.


The Form Factor Weight of the Compact Laser Comms Terminals (CLCT) Communication Device is Less than 2 kg.


The Transmission x QE of the Instrument Spectrometer is 3%.


The Operating Mode of the Solar Electric Propulsion System (SEPS) Propulsion System is Twin thruster mode.


The Operation Start Date of the PROBA-2 Satellite is July 1, 2013.


The Primary Science Missions of the MIRIS Satellite is (1) mapping of the Galactic plane with Paschen-α line (1:88 µm) for the study of warm interstellar medium and (2) measuring large angular fluctuations of cosmic near infrared background radiation with I (1:05 µm) and H (1:6 µm) bands to identify the origi.


The Member of the Jennifer Comstock Individual is True.


The Data Distribution of the Landsat-7 Satellite is ETM+ data will be distributed from the archive in an essentially raw form.


The Current Status of the Van Allen Probes Satellite is Operating in a bridge phase.


The Instrument Package Mass of the LCROSS Satellite is 12.4 kg.


The Purpose of the OB Optical Bench is Transference of the attitude from the star trackers to the magnetometer field components.


The Altitude Range of the NEOSSat Microsatellite is 15,000 and 40,000 km.


The Network of the KSAT Ground Station is S-band uplink and X-band downlink.


The Solar Panel Dust Accumulation Date of the InSight Seismic Experiment for Interior Structure (SEIS) is June 22, 2021.


The Momentum Factor of the Impact Ejecta Phenomenon is 3 to 5.


The Launch Date of the JPSS Satellite Program is March 2017.


The Grid Resolution of the L2SMP Soil Moisture Product is 36 km EASE-2.


The | of the Spanish Earth Observation Program Satellite Program is The Spanish Earth Observation Program.


The Repeat Cycle of the MTG-S Spacecraft Satellite is 10 minutes.


The Unknown of the Solar Power Technology Technology is Unknown.


The Catastrophic Burnout of the CMOS Sensors Sensor is Did not occur.


The Instrument Size of the Telescope Optical Instrument is 430 mm x 190 mm x 135 mm.


The Design Lifetime of the SPOT satellite constellation Satellite Constellation is 3 years.


The Conference Date of the InSight Mars Mission Mission is May 28-June 1, 2018.


The Quantity of the Landing Legs Landing System is 4.


The Band 3 of the RBV Instrument Spectral Band is 0.70 - 0.83 µm.


The Evaluation Date of the Evaluation Process is 8 December 2021.


The Navigation Algorithm Optimization of the Lander Spacecraft is Required.


The Frequency (GHz) of the ICI-6 Radiometer is 325.15±3.5.


The Function of the Diffraction Grating Optical Component is Disperses the light.


The Firing Tests of the AQT-D Propulsion System is Standalone and Integrated.


The Control of the Scanning LIDAR LIDAR is Predefined timeline.


The Purpose of the Microwave Imager Instrument Instrument is Remote sensing.


The Energy of the TWINS Satellite is 10 keV.


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


The Power of the EPS Electric Power Subsystem is 4.3 kW @ EOL (End of Life).


The Instrument of the Copernicus Sentinel-6 Satellite is Radar Altimeter.


The Charging and SciD Mode Operation of the ADCS Attitude Determination and Control System is Solar panels towards the sun with constrain +Y of the spacecraft pointing as close as possible towards the nadir direction.


The Design of the LINAS Ionization Gauge is IGS (Ionization Gauge Streak).


The Purpose of the RAMIS Payload is Radiation Measurements In Space.


The Test Location of the OSIRIS Device is Stuttgart and Oberpfaffenhofen.


The Goal of the Satellite Design Life is 5 years.


The Mission Preprint of the SAMPEX Satellite is 93-128.


The Focal Ratio of the Telescope Optical Instrument is F/5.


The RF Communications System of the JWST Spacecraft is CCTS (Common Command and Telemetry System).


The Bandwidth of the Bartolomeo Payload Communication System is 0.1 Mbit/s.


The Launch Date of the ALOS-3 Satellite is February 16, 2023.


The Uncertainty of the Sea Ice Concentration (SIC) Measurement is <5%.


The Number of Fires of the Fregat Upper Stage is Two.


The Telemetry Data Storage of the RF Communications Communication System is Onboard memory.


The Ground Resolution of the GeoCARB Satellite is 5 to 10 km.


The Duration of the CALET Telescope is Two to five years.


The Launch Year of the COSMO-SkyMed Satellite is 2007.


The Planned Satellite Constellation Size of the Capella Space Company is 36.


The Date of the Symposium on Small Satellite Systems and Services (4S) Conference is May 31-June 4, 2010.


The Application of the Attitude Determination System System is Small asteroid lander.


The X-ray Spectral Band of the AstroSat Astronomy Satellite is 0.3 – 100 keV.


The Interferometric Configuration of the TerraSAR-X Satellite is Single-pass.


The Design of the DCAM3 Camera is Similar to IKAROS DCAM1,2.


The Arrival Date of the DART Spacecraft is October 2022.


The Separation of the T9 Payload Fairing’s Base Ring Satellite Component is Verified.


The | of the Fred A. Best Individual is Fred A. Best, Douglas P. Adler, Claire Pettersen, Henry E. Revercomb, P. Jonathan Gero, Joseph K. Taylor, Robert O. Knuteson, John H. Perepezko.


The Detection Method of the Radio Emissions Phenomenon is Juno Waves instrument.


The Ground Resolution of the SUCHI Instrument is ~220 m.


The Spectral Range of the SOLSPEC-ATLAS Spectrometer is 210-2400 nm.


The Components of the ADE Altimeter Duplexer Equipment is Single ferrite switch on the transmit path and four ferrite switches on the receive path.


The Usage of the SOFIE and MLS Satellite Data is Categorized the inter-annual variability of winter and springtime upper stratospheric methane (CH4).


The Weight of the TxU Transmitter Unit is 8 kg.


The Communication Support of the Tianwen 1 Probe is Argentina's deep space tracking antenna, ESA's global network of ground stations.


The Link Reversion of the LLITED satellites Satellite is Passive receive mode.


The Distance from Earth of the Kepler supernova remnant Supernova remnant is About 20,000 light years.


The Publication Date of the Intercalibration of Satellite Instruments Process is March 2013.


The Exploration Date of the Ultima Thule Kuiper Belt Object is January 1, 2019.


The Components of the Second-Generation Platform Earth Observation (EO) remote sensing platform is High-resolution dual-mode optical camera, Video optical camera, Dual-band Synthetic Aperture Radar (SAR) instrument.


The Data Publication Date of the Gaia Star-Observer is February 13, 2020.


The Validation Scope of the KONNECT satellite Satellite is Complete end-to-end system of the new Spacebus Neo product line, including the fully electric orbit-raising phase.


The Design Life of the SPOT-2 Satellite is Three years.


The Availability of the Strandatoga protocol Ground-based negative acknowledgement protocol is Available.


The Technology of the SpaceLink Satellite Network is Optical communications.


The Density of the Proton Component Measurement Range of the DSCOVR Satellite is 1 –100 particles/cm3.


The Altitude of the ANUSat Satellite is 550 km.


The Dynamic Range of the CCD Camera Imaging System is 0-100% albedo.


The Netherlands-China Low-Frequency Explorer (NCLE) of the Relay Satellite Satellite is International Joint Collaboration Payload.


The Instruments of the MTG-S Satellite is Infrared Sounder (IRS) and the UV-visible- near infrared imaging spectrometer (UVN).


The FCI Instrument Testing Date of the MTG Satellite is 4 July 2018.


The Security System of the SEOSat/Ingenio Satellite is SEOSat/Ingenio Security System.


The Time in Lunar Orbit of the Service Module Module is 6-7 days.


The Operation Period of the MAG Magnetic Field Instrument is January 2012 to May 2014.


The Launch Date of the IBEX Spacecraft is October 19, 2008.


The Stray Light/Sun Disk Light Rejection of the Telescope Optical Instrument is 5 x 10^8.


The Power of the PHA Detector is 11 mW per active PHA.


The Infrared Wavelength Detection Range of the Mapping Channel Spectrometer is 0.95 µm to 5 µm.


The Size of the OPS-SAT CubeSat is 30-cm.


The Field of View of the Focal Plane Optical Instrument is 0.4º.


The Target Timeliness of the EARS Data Services Data Service is 15 to 30 minutes from instrument sensing.


The Docking Time of the Soyuz MS-17 Spacecraft is Three hours later.


The Components of the TEPCE Satellite is High voltage supplies, magnetorquers, GPS, camera, plasma sensors.


The Launch Mass of the NigeriaSat-2 Satellite is 286 kg.


The Swath Width of the EOS Camera is 12 km.


The Redundancy of the Solar Array Power Generation Device is 4 strings loss allowed.


The Orbit Altitude of the Argos-4 Satellite Instrument is 850 km.


The Technology Demonstration Boards of the AEEF Assembly is SIOS (Sistema de Interconexiones Ópticas para Satélites) optical link demonstration board and one GaN (Gallium Nitride) board.


The Debut Flight Date of the Dellingr Satellite is 2 Aug.2017.


The Operation of the CCD Readout Image Sensor is Vertical shift of the image rows.


The Weight of the Wireless Compose-2 Wireless Network Infrastructure is One kilogram.


The Phase B Completion of the Spacebus Neo Satellite is 2015.


The End of Life of the S3A Satellite is 2026.


The Revisit Time of the Platform Satellite is Within 3 days.


The Heater Power of the SVM Service Module is 80 W.


The Star Magnitude Range of the Normal Cameras Camera is Fainter than mV = 8.


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


The Spatial Scale of the GOSAT Satellite is 100-1000 km.


The Exposure Time of the Satellite Imaging Instrument is 100 ks.


The Launch Date of the SEOSAT/Ingenio Satellite is First half of 2020.


The Support Goal of the MinXSS mission Satellite is To study the "dynamics and energetics of the upper atmosphere, with particular emphasis on the hard to observe region between 80 and 150 km".


The Expected Discoveries of the Lucy Space Mission is Open new insights into the origins of our Earth and ourselves.


The Drag Sail Modules of the CanX-7 Satellite is 4.


The Compressor Units of the Stirling Cycle Cooler Cooler is Pair of linear motor reciprocating compressor units.


The Type of the TROPOMI Instrument is Passive grating pushbroom imaging spectrometer.


The Mass of the Inmarsat S – Europasat / Hellas-Sat 3 Satellite is About 5.8 tons.


The Project Status Meeting Date of the Jason-1 Satellite is Oct. 19-21, 2011.


The Operational Concept Presentation Date of the SMART-1 Satellite is Sept. 29, - Oct. 3, 2003.


The Mission Duration of the CASS Satellite is Originally planned as a two-year mission.


The Operation Status of the IBEX Spacecraft is Nominal in 2012.


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


The Cooperation Agreement of the OICETS Satellite is JAXA (formerly NASDA) and the ESA signed an agreement regarding cooperation in optical communications in space.


The Number of Research Investigations of the International Space Station Space Station is More than 2,500.


The Solar Panel Size of the EPS Electric Power Subsystem is 2.4 m2.


The Orbit Adjustment of the VNREDSat-1 Satellite is Second.


The Launch Date of the SOAR Satellite is 3 June 2021.


The Number of CubeSat Missions of the ELaNa-4 Satellite Mission is 8.


The Observation Capability of the GEO Satellite Satellite is Constant monitoring of quickly developing weather phenomena or diurnal variations in weather events.


The Objectives of the EFI Electric Fields Instrument is Study of the ambient vector electric field structure of the high-latitude magnetosphere, the cusp, and the plasma mantle.


The Optics System of the Collecting Optics Lens Assembly is f/5.


The Constellation Configuration of the UrtheCast Company is 16-satellite constellation of eight optical and eight SAR (Synthetic Aperture Radar) satellites in LEO (Low Earth Orbit).


The Ground Segment of the FormoSat-7 / COSMIC-2 Satellite Constellation is Unknown.


The Quantity of the OMPS Spectrometer is 3.


The Control Law of the ADCS Attitude Determination and Control System is B-dot control law.


The Launch Date of the TechEdSat Satellite is 21 July 2012.


The Launch Date of the ISILaunch19 Campaign is June 23, 2017.


The Development Approach of the Service Module Satellite Module is Parallel development, assembly, integration and test of the service and payload modules.


The Radio Occultation Payload of the Sentinel-6 Satellite is GPS and GLONASS satellites.


The Launch Date of the COWVR Radiometer is 21 December 2021.


The Grappling Astronaut of the SpaceX CRS-17 Mission is David Saint-Jacques.


The Date of the The Changing Seas of the Florida Keys Image is 31 May 2022.


The End of Life Date of the GovSat-1 Communication Satellite is 2033.


The Total Impulse of the SkySat-4 Satellite is 57 Ns.


The Launch Confirmation Date of the CARBONITE-2 Satellite is 12 Jan. 2018.


The Period of the SAOCOM-1A and -1B Satellites is 97.1 minutes.


The Operational Ranges for alignment / pointing of the NightPod Tracking Device is 1st:Yaw ±20º, 2nd:Roll ±20º, 3rd:Pitch nodding ±20º.


The Power Generation of the SPOT-1 Satellite is Solar array.


The Type of the Ka-band payload Communication System is Circularly polarized.


The Image Resolution of the NAVCAM Camera is 1024 x 1024 pixels.


The Descent Altitude of the MASCOT Lander is 51 meters.


The Launch Date of the Satellite Satellite is April 26.


The Ground Resolutions of the MSR Radiometer is 32 km and 23 km.


The Mission Date of the PROBA Satellite is Sept. 23-26,1999.


The Spectral Range of the SOLSPEC-SOLAR Spectrometer is 165-3080 nm.


The Revisit Period of the ZY-3A Satellite is 59 days.


The Uplink Frequency of the CMC Transceiver Communication Device is 140-150 MHz.


The Radiometric Sensitivity of the TerraSAR-X Satellite is Improved.


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


The Orbit Altitude of the CBERS-4 Satellite is 778 km.


The Components of the T3µPS Micropropulsion System is MEMS based valve and nozzle, MEMS-based pressure transducer and filter, CGG (Cool Gas Generator).


The Suburban Neighborhood Temperature of the ECOSTRESS Instrument is Averaged about 14 F (8 C) cooler than pavement.


The Maximum Daily Observations of the NEMO-AM Satellite is 2.


The Area Coverage of the EROS-B Satellite is 450 km.


The Attitude Control of the ADCS unit Satellite Component is 3-axis stabilization.


The Location of the Tyndall Glacier Glacier is Chile.


The Payload of the Planet Satellite Satellite is Telescope and a frame CCD camera equipped with Bayer-mask filter.


The Operational of the WorldView 4 Satellite is Yes.


The Capacity of the Onboard Data Storage Data Storage System is 8 GByte.


The Sample Capture Method of the TAGSAM Sample Acquisition Mechanism is Nitrogen gas will blow onto the surface to roil up dust and small pebbles, which will then be captured in the TAGSAM head.


The Design Features of the Receivers Communication is 60 GHz communication receiver, Wideband cueing receiver, >2 GHz chirp bandwidth, Hybrid 9 GHz chan. receiver with MMIC mixer, Low-noise HTS/GaAs down-converter: 7 to 1 GHz.


The Scheduled Launch Date of the Sentinel-1C Satellite is March 2024.


The Baseline Vector Accuracy of the TanDEM-X Satellite is 1 mm.


The Reflectance of the Primary Mirror Optical Component is >0.27 between 40 nm and 200 nm.


The Bus Provider of the TRACERS Satellite Mission is Millennium.


The Wavelength Range of the Band No 3 Spectral Band is 1.60 ±0.50 - 1.80 ± 0.50 µm.


The Deployment of the Solar Array Satellite Component is Elastically deployable.


The Filter of the ACS Attitude Control System is Extended Kalman filter.


The Life Expectancy of the SPOT-4 Satellite is End of 2012.


The Article Publication Date of the Solar Orbiter Satellite is 26 April 2021.


The Chamber Pressures of the LM thruster Thruster is Approximately 700,000-2,100,000 Pa.


The Density of the Venus' Orbital Dust Space Dust is About 10% more dense than in neighboring regions.


The Control Mode of the CMG Control Moment Gyroscope is Three-axis.


The Manufacturer of the Data Storage System Satellite Component is RUAG Space.


The On-board Storage Capacity of the RF Communications Communication System is 32 Gbit.


The Orbital Altitude of the HPT High Precision Telescope is 400 km.


The Imager Calibration Frequency of the TRUTHS Satellite is Daily.


The Primary Use of the Band 4 Spectral Band is SST, day/night clouds.


The Field of View of the CHIPS Spectrometer is 5º × 26.7º.


The Spectral Sampling Interval of the HSC Spectrometer Spectrometer is 1.2 nm – 16 nm.


The Energy Range of the ELS-A Electron Measurement Instrument is 400 – 490 keV.


The Nominal Cooling Capacity of the Stirling-cycle cryocooler Cryocooler is 780 mW at 75 K.


The Presentation Date of the InSight Mars Mission Mission is 27 April 2017.


The Pulse Bandwidth of the SIRAL Radar is 320 MHz.


The Launch Date of the OCO-3 Instrument is May 2019.


The Swath Mapping of the UV/VIS Camera Camera is First and second month.


The Launch Date of the EMIT Satellite is 2022.


The Sensitivity of the NIRSpec MIRI Optical Instrument is 368 nJy (3.5 μm, τ i =10,000 s, and λ/Δλ = 100).


The LTDN of the Satellite SuperView Constellation is 10:30 hours.


The Check-out Result Date of the ALOS Ground Data System Ground Data System is July 31-Aug. 4, 2006.


The Mission Duration of the IBEX Spacecraft is Seven years.


The Meeting Date of the ISS-RapidScat Satellite is May 5-8, 2013.


The Quantity of the Aluminum Spheres Satellite is 3.


The Purpose of the COSMO-SkyMed Satellite Constellation is Military and civil (research and commercial) data use.


The Launch Date of the MEV-2 Satellite is August 2020.


The Telescope Diameter of the SILEX Terminal is 25 cm.


The Design Lifetime of the TerraSAR-X Satellite is 5 years.


The Instrument type of the Meteor-M-2 Satellite is Imaging multi-spectral radiometers (vis/IR), Space environment, Imaging multi-spectral radiometers (passive microwave), Data collection, Imaging microwave radars, Atmospheric temperature and humidity sounders.


The Project of the CFOSAT Satellite is Unknown.


The Swath Width of the Antenna Subsystem Satellite Component is 180 km.


The Availability of the Star Tracker Attitude Determination Device is >99.9%.


The Number of Fluxgate Sensors of the SOSMAG Magnetometer is 2.


The News Release Date of the WFIRST Space Telescope is 30 March 2020.


The Landing Date of the Philae Lander is 12 November 2014.


The Orbit Inclination of the OPAL Satellite is 51.6º.


The Hold Period of the RISESAT Project is True.


The Purpose of the Carmen-2 Radiation Detector is Study the influence of space radiation on advanced components.


The Frequency Band of the TT&C Telemetry, Tracking and Command Subsystem is 435-438 MHz.


The Number of Cameras of the LROC Camera System is 3.


The Mass Measurement Range of the NMS Mass and Velocity Spectrometer is 1-40 AMU.


The Measurement Precision of the GNSS-RO Instrument Instrument is Higher than other radio occultation instruments.


The Output Voltage Levels of the CS-XUEPS2-41 Electrical Power Subsystem is 3.3, 5, or 12 V.


The Affiliation of the Global Navigation System GPS Satellite-based Measurement System is Various.


The Launch Date of the Alba Cluster 3 Satellite Cluster is Q2 2021.


The Mass of the Instrument Optical Bench is 18.20 kg.


The Manufacturer of the Lightspeed Satellites Satellite is Thales Alenia Space.


The Offset Angle of the Antenna Communication is 52.5º.


The Heritage of the DOSTEL Radiation Detector is Mir station (Oct. 1997 - Jan. 1998), Shuttle flights STS-76, -81, and -84, US Lab of the ISS (March to August 2001).


The Sponsors of the RECCAP-2 Activity is Global Carbon Project, European Space Agency, National Institute for Environmental Studies, International Carbon Coordination Project.


The RFI Mitigation of the MWI Instrument is Implemented at the lowest frequency channel.


The Components of the TT&C subsystem Telemetry, Tracking & Command subsystem is Low power S-band transceiver, microstrip antenna, two full duplex VHF/UHF transceivers, deployable turnstile antennas.


The Operation Characterization of the Deformable Mirror Actuator is Requires stable wavefront.


The Purpose of the FY-2 Satellite is Cloud profile and rain radars.


The Development Announcement Date of the MIRAS Radiometer is Nov. 1997.


The Max. Power of the Solar Panels Power Source is 14 W.


The Quantity of the Magnetometers Instrument is 3.


The Connection Type of the Lower Barrel and Inner Sleeve Satellite Component is Double lap shear bonded connection.


The Expansion of the Copernicus Earth Observation Program is With a suite of new, high-priority satellite missions.


The Type of the POLDER-P Instrument is Radiometer/Polarimeter.


The Mass of the Instrument DC Electric Fields Investigation is 11.5 kg.


The Spatial Resolution Comparison of the GMI Instrument is 50-60% better than TMI on TRMM.


The SDRAM of the Stamp9G20 Microcontroller is 54 MB.


The Flight Altitudes of the MERLIN Satellite is Low.


The Name of the STCUI-RAS Developer is STCUI-RAS.


The Ground Pixel Size of the VIS Camera Camera is ~100 m.


The Vertical Resolution of the Detector Instrument is 250 m to 2 km or more.


The Number of OneWeb Gen 2 satellites of the Terran R Launch Vehicle is Not Disclosed.


The Manufacturer of the Terra Satellite is Lockheed Martin Missiles and Space (LMMS).


The Quantity of the Star Tracker Heads Attitude Determination System is 3.


The Spatial Resolution of the CERES on TRMM Instrument is Approximately 10 km.


The Spatial Resolution of the Solid Earth Tectonic motions Satellite is 100 km.


The Components of the Jason-1 Ground Segment Ground Segment is Altimetric and Orbitography Mission Center (SSALTO), located in Toulouse and the Jason Science Data System at JPL in Pasadena.


The Launch Date of the Rain and Snow Satellite Satellite is Unknown.


The Perigee of the Explorer 36 Satellite is 1082 km.


The Cross-Track Swath of the OMPS Nadir Sensor Spectrometer is 2800 km.


The Density of the Giant Molecular Clouds Interstellar Medium is Up to a thousand atoms per cubic centimeter.


The Sub-Tasks of the Systematic and Radiometric Correction Processor Data Processor is Saturated pixel detection, Suspicious pixel detection and dead pixel registration, Nonlinearity response correction, Electronic offset correction and dark current subtraction, Photo response non-uniformity (PRNU) correction, Gain matching for the VNIR spe.


The Bandwidth of the Ground Station Communication System is 19.2 kbit/s CPFSK and 38.4 kbit/s BPSK/QPSK ½ k=7.


The Control Method of the ADCS Attitude Determination and Control Subsystem is Magnetic torque control.


The Objective of the NINA-2 Telescope is Measure fluxes of charged particles, in particular to detect cosmic ray nuclei of galactic, solar, or other origin from hydrogen to iron, between 10 and 200 MeV/n (contained particles) and 1 GeV/n (outside containment).


The Design Lifetime of the FLP Satellite is Two years.


The Power of the HIA Instrument is 3.0 W.


The Accuracy of the FFRF Sensor Instrument is 1 cm and 1°.


The Entrance Aperture Diameter of the Instrument Spectrometer is 29.5 x 24 mm2.


The Function of the Control and Timing Unit (CTU) Subsystem is Receives commands from the satellite platform and sends state monitoring data to it.


The Attitude Subsystem Pointing Error of the Spacecraft Satellite is 0.15º (3σ).


The IF bandwidth of the Millimeterwave receiver Receiver is 1 – 1.5 GHz.


The Article Title of the Daniel Wang Astronomer is Chandra large-scale mapping of the Galactic Centre: probing high-energy structures around the central molecular zone.


The Main Beam Efficiency (%) of the Antenna Reflector is 86.


The Capability of the ORS Office is Develop the capability to augment or replace space capabilities on very short timescales.


The Launch Vehicle compatibility of the DSX Spacecraft Payload Module  Payload Module is 12 months.


The Pixel Size of the Detector Array Assembly Detector Array is 13 µm.


The Central Transmission Frequencies of the RA Imaging System is 13.58 GHz and 5.25 GHz.


The Structure of the STPSat-1 Satellite is AeroAstro SpaceFrame.


The Program of the New Horizons Spacecraft is New Frontiers Program.


The Attitude Pointing Accuracy of the AOCS Attitude and Orbit Control Subsystem is ≤ 0.4º (3σ).


The Spatial Resolution of the Attitude Determination & Control System Satellite System is Better than 100 m.


The Mass of the Hodoyoshi-3 Microsatellite is 60 kg.


The Mission of the Colloid Micro-Newton Thrusters Thruster is Space Technology 7.


The Bus Size of the Spacecraft Satellite is 1300 mm x 1310 mm x 1988 mm.


The Payload of the PLATiNO 2 Satellite is Thermal Infrared (TIR).


The Mass Resolution of the STROFIO Instrument is m/Dm = 60.


The Programming Horizon of the MUS Subsystem is 72 hours.


The Boom Length of the NewMag Magnetometer is 2.55 m.


The Antenna Mechanism Lifespan of the SeaWinds instrument Scatterometer is More than a decade.


The Rotor Type of the Knudsen Station Ground Station is AlphaSpid's RAS rotor.


The Lifetime of the Satellite Spacecraft is Up to 12 years.


The RF Communications of the Spacecraft Satellite is VHF beacon.


The Deployment Location of the Astro Pi Computer is Columbus module and looking through a hatch window towards the Earth.


The Descent Date of the Rosetta Spacecraft is 30 September.


The Maximum Temperature Differential of the PC5 Power Supply is 85 °C.


The Position of the WFI Mosaic Plate Assembly Focal Plane is Much farther outboard towards the anti-sun side of the Observatory.


The Number of Springs and Flaps of the Dellingr mission Satellite Mission is One.


The Downlink Frequencies of the Satellite Satellite is S-band, UHF, C-band, L-band, 2048 MHz, 2225 MHz, 406 MHz, 5005 MHz, 1191.795 MHz, 1278.75 MHz, 1575.42 MHz, 1544 MHz.


The X-band Downlink Frequencies of the Landsat-6 Satellite is 8082.5, 8212.5, and 8342.5 MHz.


The Mission End Date of the D-Sat Satellite is October 10, 2017.


The Material of the Magnet Component is AlNiCo.


The Task of the Restore-L Satellite is Refuel.


The Extension Date of the ANGELS Nanosatellite is 13 October 2020.


The Formation Configuration Parameters of the SJ-9A and SJ-9B Satellites is Eccentricity difference, phase difference, ascending node difference, argument of perigee difference.


The Goal Life of the Resurs-DK1 Spacecraft is 5 years.


The Mass of the Instrument Instrument is 2.7 kg.


The Data Set of the EPIC Instrument is Single-pixel images taken multiple times per day, in 10 wavelengths, over an extended period.


The Launch Window of the SpaceX Company is 5-hour window that opens at 8:02 p.m. EDT Sept. 15.


The Purpose of the HS Heater System is Keep equipment temperatures above the minimum non-operational limits (–20 ºC for most of the units) during satellite SHM and PLM Off modes.


The Observation Date of the RHESSI Satellite is SOL2017-09-10.


The Data Output of the TDI Detector Detector is 58 Mpixel/s.


The Sensor Read Noise of the Sensor Image Sensor is 2.48 ADU.


The Operation Status of the Gokturk-2 Satellite is Nominal.


The Diameter of the Cassiopeia A Supernova Remnant is 15 light years.


The Simultaneous Check Method of the Data Processing System Instrument Component is Comparison of the known power of the reference electrical source with the precision measurement of the servo-system.


The Measurement Depth of the Juno Spacecraft is About 3,000 km.


The Total Solar Array Size of the Resurs-DK1 Spacecraft is 36 m2.


The Initial Launch Date of the Nauka Laboratory Module is 2007.


The Developer of the Venta-1 Nanosatellite is OHB Systems.


The Launch Date of the CubeSats Satellite is Dec. 9, 2013.


The Total Array Area of the Solar Panels Power Source is 9.5 m2.


The Design Life of the SA-200HP Spacecraft Platform is 5 years.


The Boresight Deviation of the PamCam Camera is -0.27° to -0.25° in horizontal and 0.40° to 0.48° in vertical direction.


The Lead Author Affiliation of the Parker Solar Probe Satellite is BWX Technologies, Inc. and University of Michigan.


The Specific Power of the SBVR Power Supply is 373 W/kg.


The Capability of the PTT-A3, PTT-ZE, PMT-A3 Argos-3 Platforms is Very low-power consumption.


The Telescope Heritage of the EUVI Extreme Ultraviolet Imager is EIT (EUV Imaging Telescope) heritage on SOHO and of TRACE (Transition Region and Coronal Explorer) mission heritage.


The Data Usage of the JAXA Organization is Precipitation Monitoring.


The Propulsion System of the BIROS Minisatellite is Equipped.


The Flight Nanosats Quantity of the SMDC-ONE program Satellite Program is 8.


The Data Rate of the Flight Modem Modem is 72 Mbit/s to 2.88 Gbit/s.


The Equity Investment of the Eutelsat Satellite Operator is $550 million.


The Grasp, refuel, and relocate of the Restore-L Servicer is Landsat-7.


The Number of Bands of the Spectral Bands Data is 15.


The Longitude of the Himawari-8 Satellite is ~140.7º east.


The Arrival Date of the Europa-UVS Ultraviolet Spectrograph is March.


The Spectral Band of the Band Photometers Photometer is 337.0 nm.


The Function of the RIU Interface Unit is Acquiring the housekeeping information of the spacecraft, managing the propulsion module items, managing the AOCS components, controlling the configuration of the satellite units.


The Orbit Type of the ZY 1-02C Spacecraft is Sun-synchronous near circular orbit.


The Ground Resolution of the HgCdTe Detector is 120m.


The Spectral bands of the UV/VIS Spectrometer Spectrometer is 248-371/387-693 nm.


The Wavelengths of the NGC 7538 Star Factory is 70 µm (blue), 160 µm (green) and 250 µm (red).


The Orbit Average Power of the COMMx Payload is 200 W.


The Impact Area of the Solar Storm Natural Phenomenon is Earth's ionosphere.


The Presentation Date of the GMES Missions Sentinel-4, Sentinel-5 and Sentinel-5p Satellites is June 18-22, 2012.


The Components of the NAOMI family of optical instruments Technology is Silicon carbide (SiC) optics and structures, multiple-line detectors, integrated focal planes and ultra-compact optical configurations.


The Wavelength Range of the Band 3 Spectral Band is 862-877 nm.


The Slew Time, 180º pitch of the ADCS Attitude Determination & Control Subsystem is ≤ 14 minutes.


The Mission Type of the MULA Satellite is EO.


The Confidence Limits of the CLARREO Satellite is 3σ or 99%.


The On-Orbit Service Time of the SAR-Lupe Constellation Satellite Constellation is More than 20 years.


The Construction Location of the BRITE Satellites Satellite is UTIAS/SFL.


The Orbital Predictions of the LARES Satellite is Unknown.


The Mass of the Bayi Kepu Weixing-1 Satellite is 2 kg.


The Sensor of the ESAIL Microsatellite is AIS (Automatic Identification System).


The Attitude Knowledge Precision of the ADCS Unit Attitude Determination and Control System is Better than 2º.


The Propellant of the Propulsion System Propulsion System is Hydrazine.


The Size of the Instrument Optical Instrument is 30 cm x 30.8 cm x 37 cm.


The Components of the PCU Power Control Unit is Antifuse FPGA.


The CCD Line Pixel Count of the FPM (Focal Plane Module) Focal Plane is 12,000 pixels.


The Volume Range of the Methane Leak Environmental Event is Between five and 20 tonnes of methane per hour.


The Launch Date of the Cheollian 2B Satellite is February 19.


The Mission Name of the ExoMars 2020 Spacecraft is ExoMars 2022.


The Launch Date of the H-IIA Launch Vehicle No. 23 Launch Vehicle is Dec. 26, 2013.


The Data Band of the GimmeRF Radio Instrument is 0-30 MHz.


The Bus Total Power of the EPS Electrical Power Subsystem is ~286 W.


The Frequency of the X-band Data Downlink is Unknown.


The Altitude of the ETS-VIII Spacecraft is 35,786 km above the equator.


The Micro Vibration Test of the Instrument Satellite Instrument is Successful.


The Volume of the AMU Altimeter Microwave Unit is 325 x 305 x 250 mm.


The Volcanic Activity of the Moon Celestial Body is Prolonged.


The Client Docking Plate of the ELSA-d Mission is Ferromagnetic.


The Field of View of the VNIR-NP channels Sensor is 70º.


The URL of the PROCYON Deep Space Probe is https://digitalcommons.usu.edu/cgi/viewcontent.cgi?article=3348&context=smallsat.


The Purpose of the STARFM Data Fusion Model is Combine MODIS data with Landsat data to produce synthetic Landsat-like imagery on a daily basis.


The Purpose of the CubeSats Satellite is Test new technologies, fly single science instruments, provide real-world space experience for students, provide daily imagery of the Earth, deploy a global broadband Internet constellation.


The Imaging Frequency of the Meteosat-10 Geostationary Satellite is Every five minutes.


The Detection Band of the XMM-Newton X-ray Observatory is Low energy part of the X-ray band.


The Hot Intergalactic Gas Percentage of the Universe Cosmology is 40 percent.


The Instrument Mass of the AATSR Instrument is 101 kg.


The Inclination of the ZY 1-02C Spacecraft is 98.5º.


The Size of the Subarray Array is 400 mm x 22 m.


The Air Pressure of the Metric Camera Camera is About 1020 mbar.


The Mission Type of the JERS-1 Satellite is EO.


The Mission Status of the Satellite EO is Planned.


The Detector Element Size of the Sounder Satellite Instrument is 10 km x 10 km.


The Dimensions of the Spacecraft Satellite is 765 x 730 x 830 mm.


The Observation Type of the TIMED spacecraft Satellite is Plasma distribution around the magnetic equator.


The Celestial Sphere Coverage of the Telescope Optical Instrument is Continuous within 5º of ecliptic poles.


The Plastic Scintillator Counters of the Veto System Particle Detector is 5 mm thick.


The Resolving Power of the IR Channel Imaging Device is 70.


The Actual Orbit Duration of the SMDC-ONE Nanosatellite is 35 days.


The Launch Date of the SpaceX CRS 14 Satellite is 16 Jan. 2018.


The Onboard Sensors of the SPOT 6-7 Satellite is HRV, HRVIR, HRG and NAOMI.


The Phase C/D Contract Signing of the Spacebus Neo Satellite is Separate Phase C/D contracts were signed with both primes at the end of 2015.


The Prime Contractor of the Sentinel-1 Satellite is TAS-I (Thales Alenia Space Italia).


The Suitability for Satellite Flight of the Silkworm Insect is Duration of the development of each stage, especially, the embryo state is well matched with the satellite flight period of SJ-10.


The Workshop Report URL of the Soil Moisture Active Passive (SMAP) Mission is http://nasascience.nasa.gov/earth-science/decadal-surveys/Volz1_SMAP_11-20-07.pdf.


The Orbit Altitude of the Genesis-2 Satellite is 560 km.


The Spin Motion of the GMS Satellite is 100 rpm.


The Mass at Launch of the Eutelsat Quantum Satellite is 3.5 tons.


The S/C Mass of the JL-1-GF03B Microsatellite is <45 kg.


The Funding of the IRIS Imager Camera is DSO National Laboratories.


The Goal of the Satellite Constellation RMIB SIMBA program is Measure the Earth radiation imbalance.


The Technology of the MiRaTA Satellite is Radio Occultation.


The Mass of the Experiment Telescope is 11 kg.


The Number of Images for Signal to Noise Ratio of the EyeSat Satellite is 10 images.


The Bulletin Date of the GEOS-1 Satellite is May 1977.


The Bandwidth of the Spacecraft Repeater Communication Device is 100 kHz.


The Total Satellite Passes of the KSAT Ground Station Network is 50,000 a month.


The B1 and B2 Tank Temperatures Increase of the Advanced Composition Explorer Spacecraft is By 5° C.


The Scan Angle of the Rotating Telescope Scanner Optical Instrument is ±53°.


The Diameter of the Main Mirror Optical Component is 64 cm.


The Observation Speed of the Solar Dynamics Observatory Satellite is 200 times faster than real time.


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


The Dual Receive Antenna Configuration of the TanDEM-X Satellite is Introduced during the TanDEM-X Science phase.


The Data Release Date of the ICESat-2 Satellite is May 2019.


The Total Mass of the Spacecraft Satellite is 25.5 kg.


The Power of the Spacecraft Satellite is 350 W.


The Detection Efficiency of the Instrument Sensor is ~90%.


The Mean Motion of the AC4-B Satellite is Higher.


The Wavelength/Frequency of the RM-08 Passive Microwave Scanning Radiometer is 0.8 cm / 36.6 GHz.


The Image Capture Date of the Solar Orbiter Satellite is 7 March.


The Number of Batch 3 Satellites of the Galileo Satellite Navigation System is 12.


The Surface Composition of the Ryugu Asteroid is Two different types of material, one slightly redder and the other slightly bluer.


The Fabrication Technology of the Solar Cells Energy Device is D-HVPE (Dynamic Hydride Vapor Phase Epitaxy).


The Manufacturer of the LINAS Ionization Gauge is Cannon Corp..


The CT Scans of the Valves Spacecraft Component is Scheduled.


The CCD Line Read-Out Rate of the FPM (Focal Plane Module) Focal Plane is 6.5 MHz.


The Power Bus System of the SpriteSat Satellite is Experienced a low voltage condition.


The Sail Assembly and Boom Mechanical Assembly of the Sail Subsystem Components is Two primary components.


The Brigthness Temperature (BT) Sensitivity of the Antenna Reflector is ±0.26 K.


The Carried Instruments of the Flying Laptop Satellite is Scientific instruments for multispectral Earth observation as well as spaceborne maritime ship surveillance.


The Number of Bands of the Optical Scanning Design Imaging Spectrometer is 21 bands (nominal Earth View).


The Launch Date of the AISSat-1 Satellite is July 2010.


The Payload Module Mass of the Euclid Spacecraft is 800 kg.


The Energy Range of the EPD-E Energetic Particle Detector - Electrons is 50 keV – 4 MeV.


The Design Life of the Spacecraft Satellite is ≥12 years in space.


The URL of the Arrokoth Celestial Body is https://www.aaas.org/news/close-arrokoth-reveals-how-planetary-building-blocks-were-constructed.


The Sample Collection Sites of the OSIRIS-REx Spacecraft is Nightingale, Kingfisher, Osprey and Sandpiper.


The Rebound Distance of the Philae Lander Spacecraft is A kilometer above the comet.


The Altitude of the Satellites Satellite is 35,786 km.


The Commercial Connectivity Services Start of the OneWeb Company is Late 2021.


The Closest Approach Time of the New Horizons spacecraft Spacecraft is 10:29 a.m. EST.


The Speed of the Solar Energetic Particles Space Weather Phenomenon is Close to the speed of light.


The Instrument Mass of the DubaiSat-1 Satellite is 38.67 kg.


The Mass of the SeaHawk-1 CubeSat is ~5 kg.


The Current Purpose of the CRS Cosmic Ray Subsystem is Study the heliosphere’s charged particles and the particles in the interstellar medium.


The Image Processing of the NASA's Solar Dynamics Observatory Satellite is Reduce noise.


The Orbit Type of the NanoRacks-QB50 CubeSats Satellite is Near-circular.


The Orbit of the JPSS-1 Satellite is Polar.


The Format of the CCD Detector Array Imaging Device is 2 k x 2 k.


The Pointing Accuracy of the ADCS Attitude Determination and Control Subsystem is ±5º.


The Monitored Parameters of the SAGE-III Monitoring Instrument is Aerosols, ozone and other gases in Earth’s high atmosphere.


The Spectral Resolution of the VIS Spectrometer is 0.63 nm.


The Testing Location of the CO2M Satellite is ESA’s ESTEC testing facilities in the Netherlands.


The Size of the AeroCube-8A Satellite is 1.5U.


The Voltage of the Power Storage Battery is 1.2 V.


The ADS-B Receiver of the CanX-7 Satellite is Included.


The Lunar Orbit Period of the Chang'e-1 Satellite is 127 minutes.


The Discovery Date of the Asteroid 162173 Ryugu Asteroid is Unknown.


The Solar Panels Area of the IRS-1A Satellite is 8.6 m2.


The Mythological Names of the Pleiades Open Cluster is Alcyone, Maia, Electra, Merope, Taygete, Celaeno, and Sterope.


The Distance from Earth of the Didymos Binary System is Within 0.08 AU.


The Spectral Coverage of the Instrument Spectrometer is 3.74 - 15.4 µm for the array grating spectrometer (IR bands).


The Single-look Resolution of the Radar Instrument is 250 m x 400 m.


The Mission Type of the ALL-STAR Satellite is Non-EO.


The Bandwidth of the Radar Sensor is 1 MHz.


The Passband of the VIS Visual Instrument is 550-900 nm.


The NDVI NIR Band to Red Band Balance of the R3 System Satellite is Off.


The Launch Site of the Sentinel-1C Satellite is Guiana Space Center, Europe’s Spaceport in French Guiana.


The Mission Phase of the PROBA-V Satellite is Operational.


The Components of the OSP Optical Sensor Package is One boresighted fixed-head star tracker and two skewed fixed-head star trackers.


The Mission Duration of the Ulysses Spacecraft is 16 years.


The Design Life of the GEISAT Precursor Satellite is Four years.


The Operation Temperature of the Calibration Motor Home Sensor Sensor is Low temperatures.


The Data Processing and Distribution Infrastructure of the GeoSat-2 Satellite is ENTICE.


The Scientific Goals of the INTEGRAL Satellite is High resolution spectroscopy with fine imaging and accurate positioning of celestial sources in the gamma-ray domain.


The Validation Data Source of the CYGNSS Satellite is GPS dropsondes, SFMR, IWARP.


The Manufacturer of the RadFET Sensor is Tyndall National Institute in Ireland.


The Magnet Configuration of the AMS-02 Instrument is Permanent.


The Yaw Axis Flip Angle of the Trail Spacecraft Spacecraft is 180º.


The Spectral Range of the SWIR Spectrometer Spectrometer is 900 nm to 2450 nm.


The Launch Date of the Oculus-ASR Satellite is 25 June 2019.


The Surface Roughness of the Mandrels Manufacturing Component is Better than 4 Å (0.4 nm).


The Mass of the KazEOSat-2 Satellite is ~185 kg.


The Function of the MCCM Multi-chip Control Module is Control the illumination coefficients (attenuation or phase) of the RF signal received from each subarray for the beam synthesis.


The Bands of the AaSI Spectral Imager is One to three.


The Contract Signing Date of the Jason-CS / Sentinel-6 Satellite Mission is May 11, 2015.


The Theoretical Performance of the Lateral Shearing Angular Period Device is 41 mas.


The Wavelength of the UVSP Instrument is About 2760 Å in first order.


The Research Topics of the MEMS Space Telescope Telescope is Unknown.


The Orbits of the Deimos-2 Earth Observation Satellite is Approximately 5,300 times during this year.


The Off-nadir tilted field of view of the OLCI Camera Assembly is Implemented for OLCI cameras.


The Impact Test Outcome of the DebriSat Satellite is Planned catastrophic outcome.


The Spatial Resolution of the TES Spectrometer is 0.43 km x 5.3 km.


The Tracking Time of the MarCO-B CubeSat is Several More Weeks.


The Typical Value of the H2CO Satellite Instrument is 10.


The Mission Productivity of the Clementine Satellite is Scientifically Productive.


The Orbit Phase Orbit Determination Date of the Chandrayaan-1 Satellite is Oct. 12-16, 2009.


The Unknown of the ZY-1-02C Satellite Images Satellite Images is Unknown.


The Mission of the TGO Trace Gas Orbiter is Measure the abundance and distribution of rare gases in the atmosphere.


The Data Resolution of the RAVAN Satellite is 10° x 10° latitude–longitude geographic grid.


The Periapsis Altitude of the Satellite Spacecraft is 879 km.


The Type of the Solar Panels Power Source is Silicon cells.


The Detector Type of the SPIRIT-III Interferometer-Spectrometer is Arsenic-doped silicon, blocked impurity-band conductor detectors.


The Mass of the ROBUSTA picosatellite Satellite is ≤ 1 kg.


The Starlink Satellites Launch Date of the SpaceX Company is 11 March 2021.


The Centre Frequency of the XSAR SAR is 9.59 GHz.


The Battery Capacity of the GHGSat-D Microsatellite is 26 W hr.


The Altitude Difference of the Swarm-A and Swarm-C Satellite Constellation is Less than 5 km.


The Mass of the Spacecraft bus Satellite is 1750 kg.


The Data Transfer of the Webb's Fine Guidance Sensor (FGS) Sensor is Up to two science instruments at a time.


The Single Pass Stereo Coverage of the QuickBird-2 Satellite is Single scene (<10º off nadir track).


The Preferred Number of Perfect Rows of the QWIP Array Sensor Array is 2.


The Operational Power Consumption of the PPU System is Approximately 15 W.


The Downlink Rate of the Sentinel-1 Satellite is Very high X-band downlink rate.


The Commencement Date of the SERVIR Program is 2004.


The Overall Relative Measurement Error of Radiance in Bands 1-3 of the Scanning geometry Instrument is 10%.


The Data Download of the STRaND-1 Satellite is 274 kB over 65 k packets.


The Antenna Diameter of the PRARE ground transponder Ground Station Equipment is 60 cm.


The Orbit Altitude of the Satellite Constellation Non-Geostationary Satellites (NGS) is 1100 and 1300 km.


The Objective of the MWI Instrument is Measure precipitation, provide measurements of cloud products, water vapor and temperature profiles, and surface imagery.


The Manufacturer of the Phasemeter Assembly Component is University of Birmingham.


The Manufacturer of the Linear Encoder Sensor is Not provided.


The Cross-Track Angle of the MSI-0 and MSI-1 MSI Instruments is 3º.


The Unknown of the DSP ASIC Data Signal Processor is Unknown.


The SNR of the Instrument Spectrometer is ≥450 @ 620 nm, ≥300 @ 2100 nm, ≥200 (for each band).


The Augmentation of the L1-SAIF+ Satellite Message is GPS satellites.


The Mass of the SeaWinds scatterometer Scatterometer is 205 kg.


The Bandwidth Allocation of the TerraSAR-NG System Satellite System is 1,200 MHz.


The Reduction in Satellite Loss of the SBSS-1 Satellite System is 66%.


The Component of the MuREM Payload is Radiation effects board.


The Navigation Payload Builder of the MTSAT-1R Satellite is Alcatel Space of France.


The Coverage of the Satellite LEO (Low Earth Orbit) is Global.


The Recent Efforts of the ICEYE Satellite Constellation is Tracking and analyzing flood events globally, launching new SAR satellites.


The Purpose of the TRIO-CINEMA Satellite Constellation is Provide stereo ENA imaging of the ring current.


The Average Ice Thickness of the Vatnajökull Glacier Glacier is More than 900 m.


The Swath of the Extra Wide Swath mode (EWS) Operational Mode is 400 km.


The Operation Status of the Van Allen Probes Satellite is Nominal.


The Launch Timeframe of the Lightspeed Satellites Satellite is Around two years.


The Onboard Mass Memory of the Solar Orbiter Satellite is Yes.


The Focal Length of the Long Wavelength Band Spectrometer is 12.5 cm (f/2.2).


The Design Life of the SEOSat Satellite is 7 years.


The Operational Date of the F-DUGS Center is 2010.


The Mounting Location of the CDE Sensor is Top of the spacecraft.


The Formation Ranges of the CanX-5 Satellite is 50 m.


The Symposium Date of the PAZ Satellite is July 26-31, 2015.


The Mission Time of the ROBUSTA picosatellite Satellite is Up to three years.


The Recovery Operation Duration of the STEREO-B Satellite is 22 months.


The Time to Full Control of the Satellite Spacecraft is Three hours.


The Launch Vehicle of the Beresheet Spacecraft is SpaceX Falcon 9 rocket.


The Impact Date of the DART Double Asteroid Redirect Test is Late 2022.


The System Focus of the Xona Company is Satellite navigation system.


The Mission Type of the Kolibri-2000 Satellite is EO.


The Architecture of the SSTI GPS Receiver is Lagrange architecture.


The Frequency (GHz) of the ICI-4 Radiometer is 243.2±2.5.


The Detector Array of the Payload 2 CMOS Camera is 640 x 480 pixels.


The ECT (Equatorial Crossing Time) of the WV-1 Satellite is 1030 hours on a descending node.


The 30 bins in polar angle direction of the Angular Resolution Sensor is Angular resolution 30 bins in polar angle direction.


The Function of the FPGA Code Software is Did not allow the motor to move without a valid home command.


The Manufacturer of the STX Communication Subsystem is Clyde Space.


The Telescope Type of the SBSS Satellite System is Two-axis, gimballed optical telescope.


The Function of the Phytoplankton Marine Organism is Absorbing atmospheric carbon dioxide into solution at the sea surface, using carbon dioxide to create their organic biomass via photosynthesis.


The Location of the GFZ Data Center is Potsdam, Germany.


The Arrival Date of the Electro-L Satellite is February 3, 2011.


The Vertical Resolution of the MLS Spectrometer is 3 km.


The Absolute Accuracy of the FFRF sensor Metrology Instrument is 1o on LOS.


The Absolute Accuracy of the Instrument Sensor is Checked at regular time intervals with stellar calibrations.


The Launch Mass of the GaoJing / SuperView minisatellites Satellite is 560 kg.


The GNOS and Radiosonde Refractivity Profile Difference of the GNOS Instrument Occultation Measurement Device is <3%.


The Mission Duration of the Galileo spacecraft Spacecraft is 1995 and 2003.


The Function of the ISSAC SOC Space Operations Center is Receive ISSAC imagery requests.


The Batteries of the EPS Electrical Power Subsystem is 2 Rose Li-ion batteries.


The Measurement of the SWAP Instrument is Interactions of Pluto with the solar wind.


The Manufacturer of the Terminator Tape Deorbit Module Deorbit Device is TUI (Tethers Unlimited Inc.).


The Number of Observations of the Claire Satellite is Over 4000.


The Publication Date of the Supercapacitors Energy Storage is 1999.


The Size of the Cygnus A jet Black Hole Jet is One of the largest and most powerful.


The Imaging of the Parker Solar Probe Satellite is Night Side of Venus.


The Development Scope of the Neosat program Satellite Program is In-orbit validation of the new satellite product lines.


The Battery Capacity of the Spacecraft Satellite is 50 Ah.


The Shape of the PM Satellite Component is Cylindrical.


The Sensor Data of the PSSCT-2 Satellite is Collected.


The IFOV/line (pixels/scan line) of the TOU Total Ozone Unit is 31.


The Magnetometer Status of the Solar Orbiter Satellite is Good health.


The Arrival Date in Final Orbit Position of the COSMO-SkyMed-4 Satellite is April 2011.


The Antenna of the GIOVE-B Satellite is 42-element planar array.


The Heat Transfer of the Cube Corner Reflectors (CCRs) Satellite Component is Mainly governed by radiation.


The Demonstration Date of the Space Weather Observation System Observation System is August 18, 2010.


The Spacecraft Bus Size of the QuickBird-2 Satellite is 3 m x 1.6 m Ø.


The Orbit of the BRO-2 and BRO-3 Nanosatellites is Sun-synchronous orbit of 500 km altitude.


The Pixel Sampling FWHM of the Instrument Spectrometer is ≥2.


The Data Downlink Rate of the SGLS Link Communication System is 1024 kbit/s.


The Components of the Recovery Subsystem Subsystem is Inflation devices, floatation devices, localization devices.


The Distribution Time of the SAR Data Products Data is ~ 6 months after launch.


The Battery Status of the Rumba Satellite is Weak.


The Instrument Type of the JPSS-2/NOAA-21 Satellite is Atmospheric chemistry, Atmospheric temperature and humidity sounders.


The Resolution of the ALI Imager is 30 m.


The Detection Depth of the SMAP Satellite is Top 5 cm (2 inches) of the ground.


The Imaging Mode of the Pushbroom System Imaging System is Continuous.


The Satellite Usage of the Surveying System Navigation System is EGNOS and Galileo satellites.


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


The Ground Segment Sections of the Helios-2 Satellite is User ground segment, programming loop.


The Frequency (MHz) of the GLONASS L1 OC Signal Carrier is 1575.42.


The Design of the Mobile Station Ground Station is Move to an adequate atmospheric condition area.


The Launch Date of the SJ-9 Technology Demonstration Satellite Satellite is Oct. 13, 2012.


The Collaboration of the AstroRad vest Radiation Protection is Lockheed Martin.


The Performance Evaluation of the Microhard MHX2420 Satellite is Unknown.


The Operating Frequency of the ALT Experiment Altimeter is 13.56 GHz.


The Purpose of the SGR-ReSI Satellite Instrument is Sensing the Earth using GNSS Signals.


The Performance Requirement of the LISA LTP Interferometer is ≤ 10-15 ms-2 Hz-1/2 in the bandwidth 10-3 to 10-1 Hz.


The Transmitter Output Power of the S-band transponder Communication Device is 5 W.


The Orbit of the MIMOSA Payload is Elliptical orbit of 820 km x 320 km.


The Additional Evidence Gathering of the Hubble Space Telescope Space Telescope is A few years later.


The Observing Duration of the IMP-8 Satellite is 28 years.


The Architecture of the AstroSat-250 Satellite is AstroBus-L.


The Spectral Region (Visible Channel) of the VIRR Instrument is 0.49 - 0.94 µm.


The X-ray Light Source of the SS 433 Cosmic Object is Bright.


The Number of Weather Centrals in the United States of the IDPS Interface Data Processing Segment is 4.


The Spotlight Scene Centre Wavelength of the SAR Antenna Antenna is 31 mm.


The Launch Date of the OSCAR-QUBE Satellite is 29 August 2021.


The Mission Goals of the ARMADILLO Satellite is Demonstrate ionospheric radio-occultation within a single CubeSat volume (10 cm x 10 cm x 10 cm) using a software-defined dual frequency GPS receiver.


The Separation Status of the BRITE-Montreal satellite Satellite is Did not separate from its Dnepr launch vehicle.


The Instrument Pointing Requirements of the Earth Radiation Budget Experiment (ERBE) Instrument is Control Knowledge Stability 720 arcsec 180 arcsec 79 arcsec/6.6 sec.


The Function of the COSMOS Mission Operations Tool is Communicates with the various payload customers to receive reports on the status of the instruments and mission accomplishment goals, as well as to receive payload tasking requests.


The Ignition Time of the ALOS-3 Satellite is 8:37 p.m. EST.


The Size of the Processed Science Data Packet Data Packet is 60 bytes.


The Mass of the Spacecraft 406 MHz Processor Processor is 27.5 kg.


The Direction of the Japan Current Ocean Current is North.


The Imager Type of the ResourceSat-2 Satellite is Multispectral pushbroom scanners.


The Constellation Expansion Plan of the ICEYE Company is More satellite additions later this year.


The Coverage of the SpinKF Attitude Determination System is Every orbit perigee-to-perigee.


The Launch Site of the Herschel Telescope Telescope is Kourou.


The Measurement Type of the GRACE-FO Satellite is Groundwater Storage and Root Zone Soil Moisture.


The Altitude of the ICEYE-X1 Satellite is 505 km.


The Launch Vehicle of the CANYVAL-X CubeSats CubeSats is PSLV-40 flight vehicle (XL configuration) of ISRO.


The SAR Payload Mass of the RCM Satellite is Approximately 600 kg.


The NEΔT of the Satellite Device Unknown is 1.0 K.


The Multi-function component assembly of the BEESAT-2 Satellite is Yes.


The Attitude Jitter of the ADCS Attitude Determination & Control Subsystem is ≤ 0.28 µrad, 0.1-1.0 Hz.


The Model Intercomparison Project (MIP) of the OCO-2 Satellite is Organized by the OCO-2 Science Team.


The Height of the Cliff Geological Feature is 50 m.


The Temperature of the Tank B2 Fuel Tank is Increased.


The Incident Spectral Passband Wavelength of the GHGSat-D Satellite is 1600-1700 nm.


The Antenna Orientation of the GPS Reflectometry Receiver Instrument is Zenith side and Nadir side.


The Nominal Value for L of the Michelson Interferometer Interferometer is Given in the table.


The Total Mass of the Microsatellite Satellite is 40 kg.


The Launch Date of the LADEE Satellite is September 7, 2013.


The URL of the Chang'E-1 Lunar Probe is http://www.cjss.ac.cn/qikan/manage/wenzhang/2008-05-03.pdf.


The Function of the MC34072 Amplifier Amplifier is Controls the gain of the intermediate amplifier.


The Data Stack Height of the Hubble Space Telescope is About 5,000 miles (8,000 km) high.


The J2000 declination (deg) of the B1617-155 (Sco X-1) Pulsar is -15.640.


The Rate of the Data Output to X-band Transmitter Data Handling System is 30.72 Mbit/s.


The Deorbit Burn Duration of the Crew Dragon spacecraft Resilience Spacecraft is 50 minutes.


The Purpose of the SWIPS Plasma Sensor is Measure the properties of solar wind ions originating from the Sun.


The HSDR Capacity of the SSTL-100 Satellite is Up to 48 GByte.


The Voltage of the Battery Energy Storage is 28 V.


The Sensor complement / remarks of the Meteor-1-2 Satellite is TV, IR, AC.


The Journal Article of the GPS-aided Automatic Landslide Monitoring System Monitoring System is Pinggen Zhou, Baishen Zhou, Jingjun Guo, Donghang Li, Zhigang Ding, Yanming Feng, "A Demonstrative GPS-aided Automatic Landslide Monitoring System in Sichuan Province," Journal of Global Positioning Systems, 2005, Vol. 4, No. 1-2: pp. 184-191.


The FIFO Buffer of the X-band transmitter Transmitter is On-board.


The Ground Sample Distance of the Carbonite-1 Satellite is 1 m.


The Communication Changes Article of the Optical Inter-orbit Communications Engineering Test Satellite (OICETS) Satellite is Takashi Jono.


The Testing Completion Date of the Parachute System Spacecraft Component is Unknown.


The Mission Objectives of the MiniCOR Instrument is Improved measurements of CME kinematics and CME-shock standoff distance, Analysis of small-scale structures in the corona and solar wind.


The Interface of the Google Earth Application is ActiveX server interface.


The Services of the MTSAT Satellite is Aeronautical communications and navigation, and meteorological observations.


The Imagery Remapping Goals of the Satellogic Satellite Company is Weekly remapping of the entire globe with high-resolution imagery in 2023, daily remapping when the full constellation is in place in 2025.


The Bus Structure Dimensions of the EURECA Spacecraft is 4.6 m x 2.6 m.


The Study Date of the Stardust Grain Particle is Last year.


The Pulse Frequency of the Laser Instrument is 500 Hz ~ 10 kHz.


The Mass of the Instrument Device is 600 g.


The Noise Levels of the SOFIE Instrument is At or below laboratory values.


The Swath of the DMC-2G imager Imager is >600 km.


The Spin of the Satellite Satellite is Up to 5 rpm.


The Dual X-band Links Speed of the NigeriaSat-2 Satellite is 105 Mbit/s.


The | of the Herbert Gunell, Charlotte Goetz, Cyril Simon Wedlund, Jesper Lindkvist, Maria Hamrin, Hans Nilsson, Kristie Llera, Anders Eriksson and Mats Holmström Researchers is | False.


The Mission Status Presentation of the COSMO-SkyMed Satellite is EUSAR 2018 (12th European Conference on Synthetic Aperture Radar), Aachen, Germany, June 4-7, 2018.


The Camera Properties of the Google Earth Application is Focus point, range, tilt, azimuth.


The Data Resolution Improvement of the New Horizons Spacecraft is Ten times.


The Detector of the Instrument CCD Imaging Camera is E2V CCD67.


The Instrument Mass of the JPL Microwave Radiometer Radiometer is 7 kg.


The Prime Contractor of the FGS Science Instrument is COM DEV Space Systems of Ottawa Canada.


The Scanning Method of the OCTS Sensor is Mechanical rotating with a mirror.


The Design of the Resistojets Propulsion System is Simple design consisting of a resistive wire wound round a mandrel.


The Contribution of the GOCE Satellite is Map changes in gravity over time.


The Program Name of the Satellite for 5G Satellite is Satellite for 5G (S45G).


The Detector of the Spectral Band A Spectrometer is Si-PIN.


The Launch Date of the Sentinel-5P Satellite is Planned for the timeframe 2020.


The Satellite Configuration of the OptiSAR™ Constellation Satellite Constellation is 8 X- and L-band SAR satellites and 8 high-resolution optical satellites.


The Large Lobe Dimensions of the Comet Celestial Body is 4.1 x 3.3 x 1.8 km.


The Measurement Speed of the OLA Instrument is Up to 10,000 measurements/s.


The Effective Active Area of Solar Arrays of the CHEOPS Satellite is Just over 2.1 m2.


The RCS Thrust of the ARTEMIS Spacecraft is 10 N.


The Launch Vehicle of the Atlas V Rocket is Atlas V.


The ADS-B Messages Received of the Aireon Air Traffic Surveillance System is 6,935.


The Purpose of the EUV Camera Observation Device is Observe Earth's plasmasphere.


The Duration of Human Presence of the International Space Station Space Station is More than 18 years.


The Design Lifetime of the ERBE Instrument is 3 years.


The Sample Collection Time of the Chang'e-5 Lander Lander is 20 hours.


The Responsivity Requirement of the Responsivity Measurement Instrument is >1.05 A/W.


The Design Lifetime of the RapidEye Satellite Constellation is 7.25 years.


The Power Consumption of the Satellite Satellite is < 5000 W (BOL) and 4500 W (EOL) without EPPS operation in GEO.


The Mission Aim of the TIMED Satellite is Provide a better understanding of the properties of energy and its redistribution in the Mesosphere and Lower-Thermosphere/Ionosphere (MLTI) region.


The Applications of Data of the KOMPSAT-2 Satellite is Unknown.


The Passes per Day of the GimmeRF Radio Instrument is About two.


The Number of Profiles/Hour of the Aeolus Satellite is 100.


The Background Energy Consumption of the FLP Satellite is 40 W.


The TGF Altitude of the RHESSI Satellite is Around 15 km.


The Estimated Mission Duration of the Spacecraft 3U CubeSat is ≤ 1 month.


The Sensor Complement of the CXBN-2 Satellite is Unknown.


The Affiliation of the Jonathan Gebbie Engineer is Unknown.


The URL of the TOI-178 Exoplanet System is https://arxiv.org/pdf/2101.09260.pdf.


The Measures of the WAF-P Device is Vertical column densities of CO2 and CH4.


The CubeSat Size of the RadFxSat Satellite is 1U.


The Size of the SERB Nanosatellite Satellite is 10 x 10 x 33 cm.


The Mission Status of the SPOT-5 Satellite is Mission complete.


The Funding Date of the BRITE Satellites Satellite is January 2011.


The Presentation Date of the ERG Satellite Satellite is Oct. 3-7, 2011.


The Operational Parameters of the ICPS Upper Stage is Data needed for the secondary payload deployment system avionics unit to perform the correct skit for the mission based on trip time to the moon and when the payloads need to be deployed.


The IFOV of the LWIR Camera Camera is 143 µrad.


The Height of the Magnetic Bottle-like Structure Magnetic Field Structure is Nearly 20,000 kilometers.


The Orbit Type of the Explorer 36 Satellite is Elliptical polar retrograde orbit.


The Communication Loss Date of the STEREO-B Satellite is Oct. 1, 2014.


The Mission Features of the TerraSAR-X NG Satellite is Full polarimetry and improved near-real-time capabilities.


The Data Analysis and Validation Duration of the GP-B mission Mission is Approximately 1 1/2 years.


The Maiden Flight Date of the Automated Transfer Vehicle Spacecraft is March 9, 2008.


The Orbital Height of the Tandem-L Satellite is 745 km.


The Orbit Altitude of the HY-2B Satellite is 963 km.


The Role of the Jared Isaacman Crew Member is Mission Commander.


The Data Product Grids of the OSCAT-2 Instrument is 25 km and 50 km.


The Monitoring of the Copernicus Sentinel-4 and Sentinel-5 Satellite Missions is Key air quality trace gases, stratospheric ozone, and aerosols.


The Landing Date of the Starliner Spacecraft is 22 December 2019.


The Weight of the SPOT satellite constellation Satellite Constellation is 1869 kg.


The Power Source of the Telemetry System System is Non-rechargeable battery.


The Manufacturer of the LISS-II Camera Imaging Device is ISRO.


The Gyros, magnetometers, sun sensors, magnetorquers of the Spacecraft Attitude Determination and Control System is Attitude sensors on board are the gyros, magnetometers and sun sensors (or photodiodes), while the only actuators are magnetorquers.


The Expansion of the Universe Cosmological Entity is Not Uniform.


The Mass of the MIS Instrument Microwave Radiometer is 475 kg.


The RF Communications Radios of the Neutron-1 Spacecraft is Gamalink Radio, GlobalStar radio, GlobalStar simplex radio.


The Member of the Phil Townsend Individual is True.


The P-PODs Quantity of the Secondary Payloads Nanosatellites and CubeSat is 4.


The Wind Speeds of the Global Models Weather Model is Higher than 20 m/s.


The Methane Detection Resolution of the Iris Satellite is 25 m on the ground.


The Non-volatile Memory of the Frame Grabber Storage is Sufficient on-board non-volatile storage.


The Orbital Periods of the TRAPPIST-1 Star System is 1.5 to 20 Earth days.