The Bulk Velocity of the Proton Component Measurement Range of the DSCOVR Satellite is 200 – 1250 km/s.


The Platform of the BILSAT-1 Satellite is Three-axis controlled platform with agile maneuvering capability.


The Mass of the Corvus-BC 1 Satellite is 10 kg.


The GSD of the Spectral Band D Spectrometer is 5.


The Communication Loss Time of the Philae Lander is 09:58 GMT.


The Data Volume of the SEIS Instrument Seismometer is ~38 Mbit/day.


The Energy Range of the HEAO-1 A2 X-ray Detector is 3 to about 45 keV.


The Imaging Date of the CaSSIS Camera Imaging Device is 7 June 2021.


The Wildfires of the British Columbia Province is More than 40 wildfires.


The Size of the Solar Panels Power Source is 320 mm x 320 mm.


The Spectral Coverage of the WFC CCD Camera is 620-670 nm.


The Location of the MCF Mission Control Facility is CSA in Saint-Hubert, Quebec.


The Convolutional Encoding of the X-band Transmitter Transmitter is ½ rate k=7.


The Detector Type of the X-ray Spectrometer Spectrometer is Microcalorimeter.


The Navigation Information Utilization Time of the Lander Spacecraft is Unknown.


The Number of Satellites of the NLS-8 Nanosatellite Launch Services program is 3.


The Location of the Ground Segment Data Processing is Belgian user Support and Operation Centre (B.USOC) in Brussels, Belgium.


The Components of the COPV Pressure Vessel is Aluminum inner liner with a carbon over-wrap.


The Swath of the AVHRR/3 Instrument is 2900 km.


The URL of Presentation of the RISESAT Satellite is http://digitalcommons.usu.edu/cgi/viewcontent.cgi?.


The Number of Sensors of the Experiment Layer Data Management System is Hundreds.


The Quantity of the Debris Satellite Components is More than 250 pieces.


The Operation Status of the China's Moon Rover Rover is Awaken.


The Excitation Frequency of the MCAc Mode is 0.005 Hz.


The Typical Value of the H2O Satellite Instrument is 3 x 10 8.


The Imagery Capture Date of the WorldView-3 and GeoEye-1 Satellites is Northern California Firestorm.


The Generation of the MetOp Satellite is Second.


The Partners of the STPSat-1 Satellite is Northrop Grumman TASC, and Avidyne.


The Form Factor of the Lunar Flashlight 6U CubeSat Satellite is 116.2 x 239.4 x 366 mm.


The Initial Services in the United Kingdom of the Lightspeed Satellite Constellation is 2026.


The Purpose of the Star Simulator Simulator is Improvement of the HILS environment.


The Imaging Date of the STEREO-A Spacecraft is June 5, 2020.


The Field Change Detection Capability of the SQUID Magnetometer is 5 x 10-14 Gauss.


The Goal of the SERVIR Program is Supplement local facilities, technology, and skills with expanded satellite imagery and tools.


The Function of the Sentinel MCS Mission Control System is Monitoring and control of all spacecraft.


The Name of the VNIIFTRI Developer is VNIIFTRI (All-Russian Scientific Research Institute of Physical and Radio-Engineering Measurements).


The Launch Date of the EnviSat Satellite is Unknown.


The Owner of the SAOCOM constellation Satellite Constellation is CONAE (Comision Nacional de Actividades Espaciales).


The Acquisition Cost of the Maxar Technologies Company is $140 million.


The Aperture Diameter of the Telescope Optical Instrument is 30 cm.


The Frequency (MHz) of the GPS L5 Signal Carrier is 1176.45.


The Installation Date of the NICER-SEXTANT Mission is June 13.


The Data Collection Capacity of the Gaia Satellite is 100 TB.


The Science Mode Start Date of the Colorado Student Space Weather Experiment (CSSWE) Satellite is Oct. 4, 2012.


The Data Coverage Area of the OCO-3 Instrument is 80 km2.


The Location of the Land Glacier Glacier is West Antarctica.


The Design Life of the SORCE Satellite is 5 years.


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


The Solar Wind Speed and Beta of the ACE Satellite is ~34% lower on average from 2009 through the day 79 of 2013.


The Orbit Altitude of the LitianicaSAT-2 Nanosatellite is 505 km.


The Bandwidth (GHz) of the ICI-6 Radiometer is 4.8.


The Support Mode of the SLIM6 Imager is Strip Real-Time Imaging.


The Data of the ICEYE Satellite is SAR data.


The Payload Mass of the IMS-2 Instrument is 147 kg.


The Carbon Temperature of the Sun's Lower Atmosphere Celestial Body is 32,000ºC.


The Focal Length of the NESSI Telescope is 893 mm.


The Start Date of the ColAIS Experiment is Summer of 2010.


The Quantity of the Magnetotorquers AOCS Actuators is 3.


The Campaign Location of the KORUS-OC Korea-United States Ocean Color Mission is East Sea (Sea of Japan), South Sea, and Yellow Sea.


The Hall Effect Propulsion of the Electric Propulsion Test Subsystem Satellite Subsystem is Isp = 1600 s ± 160 s.


The Parachute Size of the ExoMars 2020 Mission is Largest ever to fly on a Mars mission.


The Antenna Type of the Spacecraft Satellite is Steerable medium gain antenna.


The Imaging Frequency Band of the Sentinel-1A/B Satellite is C.


The Test Completion Date of the ExoMars Analytical Laboratory Drawer Laboratory Drawer is Unknown.


The Years in Orbit of the TerraSAR-X Satellite is 11 years.


The Number of Pulses per Angle Bin of the PR Phased Array System is 32.


The GPS Receiver of the BEESAT-4 CubeSat is Phoenix.


The Field-Widened Gains of the Spatial Heterodyne Spectroscopy (SHS) Interferometric Fourier transform technique is Typically 100.


The Energy Suppression of the IBEX-Lo sensor Sensor is External electrons below ~600 eV and the external ions below 10 keV.


The Uncertainty of the Sea Surface Temperature (SST) Measurement is <0.3 K.


The URL of the INTEGRAL Satellite is http://sci.esa.int/integral/57257-integral-x-rays-earths-aurora/.


The Hole Diameter of the Optical Head Optical Device is 0.2 mm.


The Mission Type of the Tatiana-2 Satellite is EO.


The Tradeoffs of the Ground-based Analysis Techniques Data Collection is Between spatial and temporal resolution.


The Status of the ExoMars Mission is Performing flawlessly.


The FOV of the FSS Fine Sun Sensor is 128º x 128º.


The Energy Storage of the Lithium ion battery Battery is Two to four times more than proven technology.


The Company Headquarters of the SAR Satellites Satellite is San Francisco, California.


The Mass of the Mass Satellite is 241 kg.


The Orbit Altitude of the Starlink Group 4-14 Satellite Group is 550 km.


The Receiving Antenna Location of the Pontianak and Biak Ground Station is To cover the satellite operation in the Central and Eastern part of Indonesia.


The Shutdown Date of the Spitzer Space Telescope Telescope is January 30, 2020.


The Frequency of the LED Light Source Linearity Checks Calibration is Weekly.


The Calibration Date of the Resourcesat-2A Satellite is July 12-19, 2016.


The Development Status of the 1 N Thruster Propulsion System is Flight-ready.


The Data of the Rosetta Spacecraft is 2015, 2016.


The Operation Mode of the ASAR Sensor is High-rate mode.


The Orbit of the AERO-VISTA mission Satellite Mission is Sun-synchronous, near-polar orbit.


The Application Categories of the Sentinel-3 Ocean Surface Topography Mission is Marine meteorology, Operational oceanography, Climate change.


The Type of the DDR2 SDRAM Memory is Double Data Rate Synchronous Dynamic Random Access Memory.


The Documentation Concern of the RISESAT Project is True.


The Area of the Icarus-1 Drag Sail is Approximately 6.7 m2.


The Components of the TEMPO Instrument is Off-axis reflective Schmidt telescope and an Offner spectrometer.


The Geolocation Error Requirement of the Satellite Satellite is Smaller than approximately 10% of the footprint size.


The Orbit of the JASON-3 Satellite is Same as JASON-2.


The Capacity of the Lithium-polymer battery assembly Power Storage is 3.4 Ah.


The Power Consumption of the CEASE-1 Instrument is 1 W.


The Requirement of the Spectral Channel Detector is >200.


The Data Delivery of the Command and Telemetry Interface Interface is 19-byte status of health information of the AIP.


The Boom Status of the IXPE observatory X-ray Observatory is Delivered.


The Torque Coils of the ACS Attitude Control Subsystem is Six.


The Lossless Compression Ratio of the HSDR FPGA Hardware is 2.8:1.


The Launch Date of the Orion/ EFT-1 Spacecraft is 5 Dec 2014.


The Height of the Tvashtar Volcano Plume Volcanic Plume is 290 km (180 miles).


The Degradation of the Piezoelectric Cantilevers Component is Systematic errors.


The Ovenized Crystal USO Frequency Drift of the DSAC Demonstration Unit is Below 1 x 10 -10/day.


The Focal Length of the Geoton-L1 imager Optical Subsystem is 400 cm.


The Descent Speed of the MASCOT Lander is Slower than an earthly pedestrian.


The Agency of the QBITO CubeSat is UPM (Universidad Politécnica de Madrid).


The Downlink Baud Rate of the CMC Transceiver Communication Device is 9600 baud.


The Telescope of the VIRUS-W Instrument is McDonald Observatory’s 2.7-meter Harlan J. Smith Telescope.


The ESA: electrons, ISA: ions of the Particle Species Sensor is ESA electrons, ISA: ions.


The Pulse period (ms) of the GROJ1744-28 Pulsar is 467.000.


The Purpose of the Thermal Protection and Hot Structures Technology is Validation of the flight performance of thermal protection materials and complex design solutions.


The Orbit Repeat Cycle of the TSX and TDX Satellites is 11 days.


The Unknown of the DART Spacecraft is Unknown.


The Shutter of the Satellite Instrument Instrument is Not used.


The Power of the SSPA Solid-State Power Amplifier is 8 W.


The Mezzanine Size of the GHGSat-D Microsatellite is 7 x 18 x 42 cm.


The Sensor complement / remarks of the Meteor-1-1 Satellite is TV, IR, AC.


The Battery Type of the GHGSat-D Microsatellite is Li-Ion.


The Global Forest/Non-Forest Map Publication Date of the TanDEM-X Satellite is Feb. 2018.


The Accuracy of the CLARREO Satellite is 0.1 K in brightness temperature.


The Flexural Rigidity of the Aluminum-polymer laminate Material is 5.6 x 10-4 Nm.


The Inclination of the STPSat-3 Satellite is 40.5º.


The Orbital Plane of the CSG and CSK satellites Satellite is Same.


The Mass (kg) of the Sentinel-1A/B Satellite is 2300.


The Patrick Blau of the Global Precipitation Measurement (GPM) Satellite is GPM Core - Mission & Spacecraft Overview.


The Error (RMS) of the Coarse sun sensor Sensor is <10º.


The Solving Scheme of the MLFMM (Multilevel Fast Multipole Method) Algorithm is Recursive.


The Programming Language of the SCIP Processor is Forth.


The Installation Date of the SpaceX CRS-17 Mission is May 6.


The Communication Method of the Voyager 2 Spacecraft is Deep Space Network's 70-meter-wide (230-feet-wide) radio antenna in Canberra, Australia.


The ADCS System of the DeorbitSail Satellite is First demonstration of this Cubesat-specific ADCS.


The Mission Purpose of the HORYU-4 Satellite is Estimate the photo-electron emission current influence on spacecraft charging.


The Purpose of the SMAP Satellite is Measure freeze/thaw timing, soil moisture, monitor droughts.


The Photon Index Below the Break of the Second Broken Powerlaw Model Component is 1.96.


The Number of RF Hybrids of the TTDL Component is 3.


The Imaging Instrument of the Landsat-7 Satellite is ETM+ (Enhanced Thermal Mapper Plus).


The Material of the Thermal Protection System System is Ceramic materials.


The Attitude Determination of the S/C Satellite is Magnetometer and sun sensors.


The SGSD Goal of the HYPSO-1 Satellite is Better than 100 m/pixel.


The | of the Novatel GPS Receiver GPS Receiver is Novatel GPS receiver.


The Dimensions of the IPEX-II boom ADAM mast is 2.35 m x 0. 3 m x 0.3 m.


The Avionics of the Platform Satellite is SSTL-100, SSTL-150 and SSTL-300.


The Observation Date of the Murchison Widefield Array (MWA) Radio Telescope is Unknown.


The Function of the MARIN Inertial Measuring Unit is Monitor the position, orientation, and movement of the satellite.


The Ozone Concentration Measurement Altitudes of the UVSP Instrument is 50 - 75 km.


The Launch Date of the MetOp-SG Satellite is 2024-2039.


The Bi-directional sharing of the TT&C Services Communication Services is Enhances effectiveness and reduces the risk for both agencies.


The RIN Performance of the ASM Instrument Instrument is -105 dB (Hz)^1/2 at 2 mW of output power around 1 kHz.


The Total Column Ozone Data Resolution of the Nadir Sensor Wide-Field Telescope Sensor is About 50 km x 50 km at nadir.


The Size of the Solar Panels Power Generation is 0.81m x 0.72 m.


The Accuracy of the CERES Instrument is 1.0%.


The Program Partners of the MYriade Satellite is CNES, Alcatel, Astrium.


The Downlink communications (Ka-band) of the Spacecraft Satellite is 278 Mbit/s (QPSK).


The Member of the Hans-Peter Marshall Individual is True.


The Scheduled Lift Off of the EM-2 Exploration Mission-2 is As soon as 2021.


The Arrival Date of the SpaceX-CRS-4 Dragon capsule Cargo Capsule is Sept. 23, 2014.


The Sensitivity of the NICER X-ray Timing Instrument is 30 times the sensitivity of RXTE to background-dominated sources.


The Launch Time of the Cesium Satellite 1 Satellite is 18:12 UTC.


The Pointing Control of the QuikTOMS spacecraft Satellite is 0.5º.


The PAN Spatial Resolution of the PMC Imager is 2 m.


The URL of the ExoMars Mission is http://www.russianspaceweb.com/exomars2018-2017.html.


The Manufacturer of the NEXT-C Ion Propulsion System is NASA's Glenn Research Center.


The Development Start Date of the Jason-CS / Sentinel-6 Satellite Mission is Late 2013.


The Main Beam Efficiency (%) of the Antenna Reflector is 88.


The Components of the BepiColombo Spacecraft is Star trackers, spectrometer, magnetometer boom.


The Meeting Date of the TriG GNSS Receiver is September 22-25, 2009.


The Release Date of the Arctide2017 Tidal Model is 15 September 2018.


The PRN of the GSAT-0102 Satellite is 12.


The Incidence Angle Measurement of the Radiometer Sensor is From the surface.


The Formation Flying Separation of the TanDEM-X Satellite is 200m.


The Mission Date of the O/OREOS Sat Satellite is Oct. 12-16, 2009.


The New Avionics of the TDS-1 Satellite is 25.


The Splashdown Time of the Crew Dragon spacecraft Resilience Spacecraft is 7:06 p.m. EDT.


The Video Resolutions of the NEMO-HD Satellite is 1920 x 1080 pixels, 2.8 m GSD, 75 m GSD.


The Ground Segment of the BRITE-Austria Satellite is Unknown.


The Project Team Members of the AzTechSat Nanosatellite is Maria de la Luz Garcia Cruz, Rosa Reyna Gonzalez Cancino, Ana Belen Urrutia Bartsch.


The Number of satellites per system of the WorldView Legion Satellite System is 6.


The End of Life of the THEIA Satellite is Shutdown Procedure.


The Downlink Frequency of the Payload Imagery Imaging is 8246.56 MHz.


The Affiliation of the Nicolas Multan Director of Space Systems and Vice President is Nexeya.


The Project Management of the Jason-2 Satellite is NASA and CNES.


The Unknown of the COIN Collaboration Research Collaboration is Unknown.


The Size of the CUNYSAT-1 CubeSat is 1U.


The Test Duration of the Myriad 2 Vision Processing Unit is 36 straight hours.


The Installation Date of the Dragon Spacecraft is 27 July 2019.


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


The Instantaneous Field of View (IFOV) of the Detector Sensor is 0.182 mrad.


The Launch Date of the Falcon 9 Rocket is March 14, 2021.


The Operation Review Date of the Grace Mission Satellite is June 30, 2011.


The Battery Energy of the QuikTOMS spacecraft Satellite is 10 Ah.


The Mission Selection Date of the ICON Satellite is April 12, 2013.


The Number of Accelerometers of the Truss Structure is 22.


The Mission Data Downlink of the Spacecraft bus Satellite is 120 Mbit/s.


The Bus Structure of the SOHLA-1 Microsatellite is Isogrid panels.


The Close Approach Complaint of the OneWeb Company is Filed in Federal Communications Commission.


The URL of the Exo-Brake Parachute is https://gameon.nasa.gov/2016/12/13/nasas-exo-brake.


The Spectral Sample of the SUCHI Instrument is Seven wave channels between 7 and 14 µm.


The Mass of the PTOLEMY Evolved Gas Analyzer is 4.5 kg.


The URL of the VNREDSat-1 Satellite is https://vast.gov.vn/web/vietnam-academy-of-science-and-technology/tin-chi-tiet/-/chi-tiet/vnredsat-1-orbit-second-adjusted-to-avoid-collision-9103-871.html.


The Spatial Resolution of the Sea Surface Temperature (SST) Measurement is 15 km.


The Input Data of the CYGNSS Satellite Constellation is Winds.


The Manufacturer of the Stamp9G20 Microcontroller is Taskit.


The Publication Date of the Galassia Nanosatellite Satellite is 31 May 2016.


The Data Downlink Speed of the NorSat-3 Satellite is Up to 2 Mbit/s.


The Telescope of the Tyvak-0130 Satellite is One with a narrow field of view.


The Deployment Date of the Flock 1b Nanosatellites is August 19, 2014.


The Error Assimilation Purpose of the LI System Lightning Information System is Improve very short range forecasts of severe convective events.


The Downlink communications (X-band) of the Spacecraft Satellite is 800 Mbit/s (16 QAM), 400/200 Mbit/s (QPSK).


The Pulse period (ms) of the B1509-58 Pulsar is 150.658.


The Limitation of the Optical Telescopes Instrument is Orbiting objects become unresolvable at high orbits or small telescope apertures.


The Age of the Cassiopeia A (Cas A) Supernova Remnant is 320 years.


The Manufacturer of the Scanning LIDAR LIDAR is Jena-Optronik GmbH.


The Alignment of the OSIRIS Optical Sensor is Tracking sensor aligned to the collimator.


The Power Consumption of the Scientific Payload Satellite Payload is High.


The Power Consumption of the RAMIS Radiation Detector is 3 W – 4 W.


The Efficiency of the Solar Cells Power Generation is 30%.


The Burn Altitude Change of the EURECA Satellite is From 420 km to 508 km.


The Observation Purpose of the MIRIS Satellite is Functional test purposes without any proper calibration process.


The Impact Speed of the DART Spacecraft is Approximately 3.7 miles per second.


The Data Bus of the C&DH Subsystem Command & Data Handling is MIL-STD-1553B.


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


The Design and Operational Concept of the Mission Operations Facility Facility is The Mission Operations Facility design and operational concept for EUMETSAT’s next generation geostationary satellite program (MTG).


The Wind Direction Range of the SCAT Wind Measurement System is ±20º.


The Implementation Complexity of the Occultation Techniques Atmospheric Study Method is Easy to implement in principle.


The Launch Date of the Chang'e-4 Lunar Spacecraft is December 8, 2018.


The Consortia of the Moonlight Lunar Telecommunications and Navigation Satellite Network is Telespazio leads the first consortium.


The Frequency Range of the Spectrum Analyzer Device is ± 7 MHz.


The Social Value of the COS Climate Observing System is Lost if information is not used.


The Conference Location of the CubeSat Laser Communication Crosslink Pointing Demonstration Satellite Communication System is Logan, UT, USA.


The Orbital Deviation of the Sentinel-1A and Sentinel-1B Satellites is ±50 m radius.


The Manufacturer of the Phi-Sat-1 Satellite is Φ Department of the Earth Observation Directorate.


The Location of the DFD Data Center is Germany.


The Separation Distance of the ASTRO and NextSat Satellites is 10 m.


The Testing Location of the Solar Orbiter Spacecraft is IABG facilities in Ottobrunn, Germany.


The Number of Satellites of the Indian rocket Rocket is 31.


The End of Life Date of the Meteor-1/Meteor-2/Meteor-Priroda Series Satellite Mission is 01 Jan 2001.


The Sensitivity of Ion Density Fluctuation of the PAP Plasma Analyzer is 1 x 10^27.


The Repeat Cycle of the SPOT 1-5 Satellite is 26 days.


The Mission Extension of the Megha-Tropiques Satellite is 2 years.


The Technology of the RAVAN Satellite is Carbon nanotubes that absorb outbound radiation and a gallium phase change blackbody for calibration.


The Setup of the Integrated Firing Test Test is Spacecraft installed the propulsion system was mounted on the thrust stand.


The Data Processing Requirement of the SVOM Satellite is Super-computers to process the data in real-time and smart algorithms to broker which transients to focus on with follow-up facilities.


The URL of the Chandra X-Ray Observatory Satellite is https://www.nasa.gov/sites/default/files/108075main_REVchandra.pdf.


The Installation Location of the ELF Device is Upper part of MSPR-2, called the Work Volume (WV).


The Mounting Technique of the MPO-MAG instrument Instrument is Boom mounting technique.


The Color of the Transmit Collimator Optical Component is Yellow.


The Data Products of the Jason-1 Mission Mission is Sea surface topography, Significant wave height, Surface wind speed, Ocean tides, Vertically integrated atmospheric water vapor, Vertically integrated ionospheric electron content.


The Power Generation of the SPOT-3 Satellite is Solar array.


The Operating Frequencies of the NorAIS-2 Receiver AIS Receiver is Set to any frequency within the maritime VHF band.


The Expected O3 Recovery of the SAGE-III on ISS Satellite Instrument is About half of the amount lost from pre-1980 levels by the 2020s.


The Absolute Height Accuracy of the TanDEM-X Satellite is About 1m.


The Data Acquisition Channels of the PDS Data Services is X-band channel, ARTEMIS data-relay satellite's Ka-band channel.


The Material of the Phantoms Mannequin Torsos is Mimic human bones, soft tissues, and organs of an adult female.


The Telemetry Information of the Attitude Determination Quaternion Filter Experiment is Probability distributions for the selection of each different measurement matrix.


The Purpose of the GPM Satellite is Provide advanced measurements about the rain and snow particles within clouds, Earth’s precipitation patterns, extreme weather and myriad ways precipitation around the world affects society.


The Mission Goals of the PACE Satellite is Making climate-quality global ocean color measurements, understanding the carbon cycle and global ocean ecology, determining the ocean’s role in global biogeochemical cycling and ocean ecology in relation to climate change.


The Observation of the ExoplanetSat Satellite is Exoplanets.


The Steps of the Deployment Sequence Process is 1) Prior to launch, the inflatable tubes and the membrane are placed into the hold structure.


The Measurement Range of the IRM Mass Spectrometer is 0.5-100 eV ions.


The Revisit Time with Orbital Manoeuvres of the Cartosat-2E Satellite is One day.


The Formation Control of the TSX and TDX Satellites is Precise.


The Leading Noise Terms of the Satellite Spacecraft is Optical sensing.


The Mission Overview of the STEREO Satellite is  Solar Terrestrial Relations Observatory.


The First Stage Landings of the Falcon 9 Rocket is 9.


The Responsible Agency of the JPSS Satellite is NOAA.


The Wavelengths of the OLI-2 Instrument is Nine.


The 1–3 electron guns of the Positive Tether Charging Mode Test Procedure is The positive mode will need additionally 1–3 electron guns.


The Azimuth Resolution of the High Resolution Spotlight Imaging Mode is 2.2 m (dual pol.).


The Operation Time of the HPS Hall-thrust Propulsion Subsystem is Under 10 minutes.


The Satellite Manufacturer of the Surrey Satellite Technology Limited Company is True.


The Material of the Bus Satellite Structure is Aluminium honeycomb panels.


The Launch Date of the ELISA Satellite is Unknown.


The Estimated SNR of the Band 1 Spectral Band is 845.85 ± 89.97.


The Thermal Gradients of the FG Filtergraph is Unknown.


The Download Flag Reset of the Data Download System Satellite System is Download flag can easily be set back to “not downloaded”.


The Mission Status of the ISS:LIS Lightning Imaging Sensor is Operational (extended).


The Radiation Resistance of the Bdelloids Species of Rotifers is Extremely resistant to radiation.


The Contract Signing Date of the Three high-priority environmental missions Missions is 13 November 20220.


The Size of the Gnome Chompski Space Component is 150 mm.


The Conference Date of the Roshydromet Program Satellite Program is Sept. 19-23, 2005.


The Responsibilities of the ALMASpace Consortium is Managing the project, formal interfaces to ESA/ESTEC, payload selection, qualification and integration onboard the spacecraft, mission implementation management.


The Destination of the CE-4R satellite Satellite is Moon Earth L2 point.


The Maximum Misalignment of the Optical Sensor Systems Calibration Laboratory is 0.001º.


The Instantaneous spectral coverage of the Spectrometer Instrument is 2.16 km/s.


The Advantages of the Coherent Detection Technology is Enables the maximum data rate at minimum power.


The Affiliation of the DTU's Geomagnetic Measuring Stations Ground-based Measurement System is DTU.


The Size of the FIREBIRD-2 A and B Satellite is 1.5U CubeSat.


The Bandwidth of the Channel 7 Sensor is 1000 MHz.


The Launch Date of the ARTEMIS Satellite is July 12, 2001.


The Article Date of the Herschel Satellite is July 1, 2014.


The Proximity of the POPACS Satellite is DANDE.


The Purpose of the KMSL smallsat Satellite is Experiments in microgravity.


The Selects the interesting opportunities to execute links during increment N of the LCT Operations Team Operations Team is The LCT Operations Team at TES selects the interesting opportunities to execute links during increment N.


The System Status of the Pleiades Satellite is Unknown.


The Location of the Spectral Calibration Calibration is Ground.


The Staff Count of the Orbital Sidekick Company is 33.


The Supplier of the TT&C transponders Communication is COM DEV.


The System of Systems Presentation Date of the UrtheCast Satellite is October 20-24, 2014.


The Instrument of the Aeolus satellite Satellite is Space Doppler wind lidar.


The Length of the Spin Axis Dipole Antenna Antenna is 15 m.


The Electrical Connection of the SPA Components Components is SPA standard connector.


The Number of Detectors of the ULEIS Spectrometer is Six.


The Wavelength of the SWIR Detector is 3.75 µm.


The Material of the Bushings Component is Polyimide plastic with impregnated graphite.


The Number of Satellites of the Landsat Next Satellite Constellation is 3.


The Accuracy of the Laser Rangefinder Device is Better than 1 meter.


The Power Initialization of the Satellite Spacecraft is Autonomously perform the initialization sequence.


The Tracking System of the MMS Satellite is GPS signals.


The Swath Width of the AATSR Instrument is 500 km.


The Deployment Duration of the ATEx Tether Experiment is 18 minutes.


The Sensor of the ZY 1-02C Spacecraft is PMS (Panchromatic/Multispectral) Camera.


The Mass of the VesselSat-1 Microsatellite is 29 kg.


The Landing Location of the Starliner Spacecraft is White Sands Space Harbor in New Mexico.


The Presentation Date of the KOMPSAT-5 Satellite is July 25-30, 2010.


The Pointing Accuracy of the QuickBird-2 Satellite is ±0.016o (3? steady state in all three axes).


The Main Imager Spatial Resolution of the PROBA-1 Microsatellite is 17 m.


The Customer Industries of the Climavision Company is Delivery companies and airlines.


The MS B4 of the Pushbroom imager Spectral Band is 0.76-0.89 µm.


The Quantity of the CM1 and CM2 6U CubeSats is 2.


The Position Accuracy (RMS orbit) of the S-2 NRT Product is < 3 m (3D) 3-sigma.


The Quantity of the Solar Panels Power Source is 4.


The Optics Presentation Date of the Imaging X-ray Polarimetry Explorer Satellite is 2017.


The Presentation of the IXV Mission and Flight Mechanics is Mission and Flight Mechanics of IXV from design to postflight.


The Orbit Altitude of the ALOS-3 Satellite is 618 km.


The Satellite Type of the EUMETCast Dissemination System is Geostationary.


The Mission of the SWOT Satellite is Surface Water and Ocean Topography.


The Operating Status of the Odin Satellite is Nominal.


The ADC Resolution of the RADFET Circuit Circuit is 10 bit.


The Meeting Date of the SMOS Satellite is Sept. 30, 2015.


The Launch Date of the Aeolus Spacecraft is 22 August 2018.


The Conference Presentation Date of the JC2Sat-FF Satellite is 18 - 21 August 18-21, 2008.


The Passband Range of the SPIM3 Spectrometer is 251-388 nm.


The Telemetry Module Mode of the TTCS Telemetry & Telecommand Subsystem is PCM/DPSK/PM.


The PRF of the Radar Instrument is 2.9 kHz.


The Image Capture of the Rosetta Satellite is 76,000 high-resolution images.


The Manager of the Chandra Program is NASA's Marshall Space Flight Center.


The Data Acquisition Rate of the HARP-2 Satellite is Minimum two frames/second.


The Orbit Inclination of the Primary Mission Satellite is 98.7º.


The Mission Objective of the FASTRAC Satellite is Demonstrate autonomous thruster operation using single-antenna on-orbit real-time GPS attitude determination.


The ILP of the Instrument Spectrometer is 0.5 cm -1.


The Mission of the LunaH-Map Satellite is Map hydrogen within craters and other permanently shadowed regions throughout the moon's south pole.


The Center Frequency of the Channel 6 Sensor is 42 GHz.


The Data Samples of the DSLP Data Acquisition System is More than 35 million.


The Attitude Control of the EURECA Spacecraft is Magnetorquers.


The Scan of the VISSR Mirror Instrument is 20º x 20º.


The Development Status of the SwRI Small Satellite Satellite is Unknown.


The Ground Segment Design Presentation Date of the EnMAP Satellite is March 17-19, 2010.


The Detection Capability of the JJ-FAST Forest Early Warning System is Areas of deforestation in the order of a few hectares.


The Estimated SNR of the Band 6 Spectral Band is 427.81 ± 136.32.


The Mission Aim of the SOAR Satellite is Test and characterize new materials that can reduce the experienced drag and increase aerodynamic performance in low altitude orbits.


The Calibration of the DDM Device is Absolute.


The Attached to of the PEST Satellite is JAWSAT.


The Announcement Date of the OceanFinder Vessel Identification and Route Prediction System is 18 September 2019.


The 1 Second Labels of the SSRNI Data Acquisition and Registration System is Yes.


The Power of the STRV-2 DHS Data Handling System is 6 W.


The Power of the Instrument Spectral Imager is 129 W.


The Primary Use of the Band 7 Spectral Band is Ocean color.


The Service Prime Capacity of the Surrey Satellite Technology Limited Company is Lunar services brand SSTL Lunar.


The Duration of the Transient Luminous Events Atmospheric Phenomena is Less than a millisecond to two seconds.


The Antenna Pattern of the Antenna Device is Cross-track direction.


The Constellation Size of the ESAIL Microsatellite is More than 60.


The Estimated SNR of the Band 2 Spectral Band is 797.02 ± 53.34.


The Local Equator Crossing Time of the QuakeSat Satellite is 6:00 and 18:00.


The Objective 3 Purpose of the Jason-CS Satellite Mission is For determining tides, ocean circulation, climate change and sea level rise.


The Target Asteroid Size of the NEA Scout Spacecraft is Less than 100 meters (330 feet) across.


The Corrected FOV of the SPARCS Satellite is 1°.


The Launch Date of the AeroCube-4 Satellite is Sept. 13, 2012.


The Checkout Date of the Y-3 Detector is January 15 to 17, 1974.


The Orbit Altitude of the GEISAT Precursor Satellite is 520 km.


The Resolution of the TeLEOS-1 Imager Imaging Device is 1m nominal at nadir.


The End of Life Date of the HJ-1 Satellite is 31 Dec 2022.


The Detection Capability of the PROBA-V Satellite is Aircraft.


The Position Control of the CNAPS Propulsion System is 1 m.


The Total Mass of the XPAA Phased Array Antenna is 5.5 kg.


The Launch Date of the Estonia's student cubesat satellite Satellite is Unknown.


The Image Lines of the Focal Plane Array Detector Array is Recorded Simultaneously.


The Peak Distance from the Sun of the Water Production Comet Activity is About 1.7 au.


The Spectral Bands of the Hyperspectral Imager Sensor is 150.


The Discovery of the Hubble Space Telescope is Myriad galaxies beyond our own.


The Maximum Depth of the Lake Cedar Lake is 10 meters (32 feet).


The Distance of the Closest Approach Parameter is 0.71 km.


The Earth Footprint of the NEMO-AM Satellite is 35 km x 95 km.


The Instrument Operations of the Spacecraft Satellite is Performed "offline" of the MOC.


The File Transfer Capability of the JAXA Flight Controller Control System is Between SSIPC and JAXA laptops in JEM.


The Environment of the ISS Space Station is Permanently crewed operational environment.


The Modulation Schemes of the Lithium 2 radio Communication Device is GMSK for low Earth to near Earth orbit, theoretically supports BPSK.


The Failure of the STM32 microcontroller Microcontroller is Loss of communication.


The Launch Year of the OCO-2 Satellite is 2014.


The Size of the Duchifat-1 CubeSat is 1U.


The Distance from Earth of the Crab Nebula Nebula is 6,500 light-years.


The J2000 declination (deg) of the B1813-140 Pulsar is -14.036.


The Reentry Date of the MaSat-1 CubeSat is January 9, 2015.


The Nominal SNR of the Band 4 Spectral Band is 1070.


The Launch Date of the JPSS Satellite is 2017.


The Mass of the ADCS Attitude Determination and Control System is 0.78 kg.


The Efficiency of the Solar Array Regulator Buck-Boost Converter is Above 94%.


The Mass of the Nanosatellite Satellite is 5.5 kg.


The Function of the ISSAC SOC Space Operations Center is Convert these requests into specific sets of commands for uplink to ISSAC.


The Power of the DC Power Communication System is 1.0 W conditioned power (standby).


The Funding Status of the Chandra X-ray Observatory X-ray Observatory is Funded through 2025 with options to extend through 2030.


The Amplification of the SSPA Solid State Power Amplifier is 2 W.


The Doppler and differential VLBI techniques of the Kaguya (SELENE) Satellite is 4-way.


The News Release of the TecSAR Satellite is IAI news, First Quarter 2008, Issue 25.


The Preference for Working with U.S. companies of the NASA Organization is Strong.


The Contents of the Level-1B Data is Granule scene radiance data after radiometric correction and geometric correction processing.


The Resolving Power of the CHIPS Spectrometer is f/150.


The Mass of the GHOSt satellites Satellite is 91.4 kg.


The Spectral Band of the Instrument Spectrometer is MWIR.


The X-band Tx Data Rate of the RF communications Communication System is 76.53 Mbit/s.


The Manufacturer of the ATLID Lidar Instrument is Airbus DS.


The Repeat Cycle of the CBERS-4 Satellite is 26 days.


The Service of the KSAT Satellite Operations Provider is Satellite operations as-a-service for ESA's Arctic Weather Satellite.


The Number of Satellites of the OptiSAR™ Constellation Satellite Constellation is 16.


The Launch Date of the STREAK Satellite is Sept. 23, 2005.


The Diameter of the T6 thrusters Ion Thrusters is 22 cm.


The Payload Volume of the GOMX-1 Nanosatellite is 9 cm x 9 cm x 12 cm.


The Launch Date of the Vega Launch Vehicle is 28 April 2021.


The Capture Method of the ASTRO and NextSat Satellites is Docking mechanism.


The Design Incorporations of the Automated Transfer Vehicle Spacecraft is About 30.


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


The Dimensions of the Slits Optical Instrument is 84 µm x 44.1 mm.


The Instruments of the SciSat-1/ACE Satellite is MAESTRO, ACE-FTS.


The Provider of the Sensor bus system System is Kayser-Threde GmbH.


The Baffle Material of the TX Telescope Telescope is CFRP.


The Telescope Aperture of the QuickBird-2 Satellite is 60 cm Ø.


The Power Consumption of the CMG Control Moment Gyroscope is 3 W (peak).


The OLI Bands of the Landsat-8 Satellite is 7-5-2.


The Renaming Date of the Solar Probe Plus Spacecraft is May 31, 2017.


The Tail Ray Length of the Parker Solar Probe Satellite is Nearly 5,000 miles.


The Title of the Kevin Murphy Individual is NASA Earth Science Division chief science data officer.


The Testing of the Prometheus Satellite is 3-axis random vibration and lengthy thermal vacuum cycling.


The Current Position of the Solar Orbiter Satellite is Between the orbits of Venus and Mercury.


The CH4 Relative Accuracy of the GOSAT Satellite is 2%.


The Mobility of the TUC Transponder Microwave Transponder is Mobile.


The Discovery of the Gaia Satellite is Detection of Starquakes.


The EIRP of the Steerable Beam Communication System is 57 dBW.


The Reflector Diameter of the L-band SAR instrument Instrument is 12-m.


The Imaging Frequency Band of the IceEye-1 Satellite is X.


The Orbit Type of the Main Payload Satellite is Sun-synchronous near-circular orbit.


The RF Communications Band of the ETS-VIII Spacecraft is S-band.


The Power of the Voltage 7 Power Amplifier is 1.66.


The Array Size of the Detector Instrument is 1k x 1k.


The SSBUV Instrumentation Flights of the Space Shuttle Spacecraft is Multiple.


The Data Provider of the RADMON Radiation Monitor is Aalto-1.


The Proton Dynamic Pressure of the ACE Satellite is ~1.4 nPa.


The Avoidance Targets of the SVOM Attitude Satellite Attitude is Sco X1 source, Galactic Plane.


The Orbit Eccentricity of the UniCubeSat Satellite is Less than 0.2.


The Orbit Inclination of the Sentinel-2 satellites Satellite is 98.6°.


The Flight Duration of the Spacecraft Satellite is About two months.


The Deorbiting of the NanoSail-D2 Satellite is Ongoing.


The Design Life of the SCD-2 Satellite is 2 years.


The Spatial Resolution of the Sea Ice Concentration (SIC) Measurement is 5 km.


The Formation Event of the Blue Ring Nebula Nebula is Stellar merger between a star similar to our Sun and another star only about one-tenth that size.


The Location of the CubeSat Yonsei team Team is Korea.


The Formation Flying Mission of the CanX-4/CanX-5 Satellite is One Month.


The Deployment of the Langmuir Probe Plasma Measurement Device is Must be made deployable.


The Diameter of the Primary Mirror Telescope is 450 mm.


The Payload of the Cesium Satellite 1 Satellite is Cesium Nightingale 1 active phased array.


The Orbit Altitude of the Sentinel-2 satellites Satellite is 786 km.


The Measurement Type of the CryoSat-2 Satellite is Height of ice.


The Review Date of the GEOS-1 Satellite is 1978.


The FOV in Transverse Spin Plane of the THD Horizon Detector is 6º.


The Location of the Yutu-2 Lunar Rover is Arrived at preset location A.


The Bistatic Recordings of the TanDEM-X Satellite is Since June 2020.