The Calibration Views of the CIRiS Infrared Imaging System is 1) deep space 2) an on-board source at a selectable and controlled temperature and 3) an on-board source at the instrument temperature.


The Image Credit of the VIIRS Imaging Radiometer is NASA Earth Observatory image by Lauren Dauphin, using VIIRS data from NASA EOSDIS LANCE, GIBS/Worldview, and the Joint Polar Satellite System (JPSS).


The Minimum Value of the Spectral Angle Measurement is Achieved when the red panel is prominent on the satellite.


The Modulation Format of the Flight Modem Modem is DPSK (Differential Phase Shift Keying).


The Image Types of the SGLI Satellite Instrument is True color composite, Near-ultraviolet, Degree of polarization.


The Number of Satellites in Orbit of the Satellogic Satellite Company is 60+.


The Size of the Instrument Telescope is 107 cm diameter x 360 cm in length.


The Depth of the HXT-S Detector Modules is 223 mm.


The Measurement of the Conducted EMC Test Test is Conducted emissions.


The Tester of the ISIM Compartment is Randy Kimble.


The Inclination of the NEMO-AM Satellite is 97.64º.


The On-board data storage of the Second generation spacecraft UK-DMC-2 and Deimos-1 Satellite is HSDR (High Speed Data Recorder) capable of storing up to 8 GByte worth of data.


The Planned Quantity of the Kinetic Impact/Crater Generation Maneuver is One.


The Number of Wavelength Bands of the OCO-2 Spectrometer is 3.


The Number of Satellites of the Eurostar E3000 Satellite Platform is 7.


The Group Delay of the Receiver Communication System is ≤ 13 µs.


The Signal Power of the Clementine Satellite is 6 W.


The Solar b-angles of the SPARCS Satellite is Up to 40°.


The Number of Satellites of the GPM (Global Precipitation Measurement) Mission Satellite Constellation is 12.


The 23.8 GHz Channel Function of the JMR Microwave Radiometer is Primary water vapor sensor.


The Preorder Count of the Starlink Satellite Internet Service is Over 750,000.


The Design of the Optical Benches Optomechanical System is Truss-type.


The Data Transmission of the Magnetometer Instrument is Real-time.


The Modules of the Spacecraft Satellite is Service module (bus) and payload module.


The Swath Width of the Swath width Spectrometer is 50 km.


The X-band Frequency of the MSX Satellite is 8475 MHz.


The Structure of the TurkSat-3USat Nanosatellite is 3U CubeSat.


The Energy Release of the Ophiuchus Galaxy Cluster Galaxy Cluster is Factor of five more than the previous record holder.


The Symposium Date of the Small Satellites Satellite is May 4-7, 2009.


The Dimensions of the Picard microsatellite Satellite is 90 cm x 80 cm x 110 cm.


The Transit Time to Jupiter of the Juno spacecraft Spacecraft is About three years.


The Orbit Inclination of the CartoSat-2D Satellite is 97.44º.


The Baseline Altitude of the SPARCS Satellite is 550 km.


The Design Improvements of the SRC Instrument is New HK telemetry, backup timer.


The Power of the GaN-based Power Transistors Transistors is 15W and 80W.


The Deployment Priority of the Argo Floats Oceanographic Instrument is World ocean as their highest priority.


The COSMIAC Role of the SORTIE Satellite is Build the satellite and collect the data from it.


The Launch Date of the Sentinel-1D Satellite is First half of 2024.


The Architecture of the Attitude Control System Satellite System is FPGA Based.


The FSR of the Radiometry Sensor is 240 Wm -2  sr -1.


The Function of the HemoCue Blood Cell Counting Device is Provide quick and accurate counts of total and differentiated white blood cells.


The Deployment Date from ISS of the Light-1 Satellite is February 3, 2022.


The Landing Location of the Falcon 9's first stage Rocket Stage is "Just Read the Instructions" droneship, which was stationed in the Pacific Ocean.


The Stabilization of the AOCS Attitude and Orbit Control Subsystem is 3-axis.


The Communication Ability of the Propulsion System Satellite Component is With the satellite to get instructions and to send telemetry data.


The 2.0 m (L) x 2.1 m (W) x 1.9 m (D) of the Spacecraft Bus Size is Bus size - 2.0 m (L) x 2.1 m (W) x 1.9 m (D).


The Spatial Resolution of the Ice sheets Ice vertical movements Satellite is 100-1000 km.


The Mass of the CINEMA-3 Nanosatellite is 4 kg.


The Launch Vehicle of the Gravity Probe A Satellite is Scout-D.


The FOV of the HRI dual EUV 174 Å and 335 Å alternatively Passband center is 1000 arcsec x 1000 arcsec.


The Max Data of the S-band Transmitter Transmitter is 2 MB/day.


The Programming Loop Operation of the Helios-2 Satellite is Daily.


The Noise Performance of the Visible Spectral Band Spectral Band is SNR=6.5 (albedo=2.5%).


The Expected Result Publication Date of the MICROSCOPE Satellite is End of 2019.


The URL of the Foton-M3 Mission Mission is http://esamultimedia.esa.int/docs/foton/FOTON-M3_brochure.pdf.


The Modes of Operation of the ADCS Attitude Determination and Control Subsystem is Magnetic control, 3-axis control.


The Coating of the Aluminum Spheres Satellite is Space-rated flat white paint (AZ-93 white paint).


The Launch Date of the SAOCOM-1A Satellite is October 2018.


The Solar Corona Observation Date of the PROBA-2 Satellite is March 16, 2015.


The Flyby Imaging of the Parker Solar Probe Satellite is Bonus data.


The Downlink Frequency of the CMC Transceiver Communication Device is 430-440 MHz.


The Parachute Deployment Time of the MarCO-B Satellite is 11:51 am.


The Structure Integration and Builder of the Biomass Satellite is Airbus in the UK.


The Electron Isotropy Boundaries Energy Range of the ELFIN Satellite is 0.5-5 MeV.


The Altitude of the WV-1 Satellite is 496 km.


The Launch Date of the Resourcesat-2A Satellite is Unknown.


The Aperture of the Optical Parabolic Mirror or Telescope Optical Instrument is ~1 m.


The Spatial Resolution of the Maps Data is 0.5° to 2°.


The Launch Mass of the Spacecraft Satellite is ~310 kg.


The DOI of the Spaceborne Frequency Comb Metrology Metrology System is 10.1364/optica.3.001380.


The Purpose of the SEM Space Environment Monitor is Monitor the space environment.


The Usage of the IU Guidance and Sequencing Unit is Only during launch and the initial phases of operation.


The Material of the Decks Satellite Component is Aluminum honeycomb sandwich bonded between Gr/E skins.


The Participants of the SRTM Shuttle mission is NASA, DoD/NGA, DLR, ASI.


The Mission Presentation Date of the FalconSat-7 Satellite is Oct. 1-5, 2012.


The Components of the AOCS Attitude and Orbit Control Subsystem is Four reaction wheels, a dual redundant AIM (AOCS Interface Module), dual redundant gyros, dual redundant ST (Star Trackers) and four sun sensors.


The Mission Duration of the SciSat/ACE spacecraft Satellite is 10 years.


The URL of the SARah-1 Earth Observation Satellite is https://www.airbus.com/en/newsroom/press-releases/2022-06-airbus-built-earth-observation-satellite-sarah-1-ready-for-launch.


The GSD of the CIRiS Instrument is 0.166 km.


The URL of the SP-402 A New Sun Book is http://history.nasa.gov/SP-402/ch4.htm.


The Sensitivity of the MWR Dicke Radiometer is 0.5 K.


The Orbital Period of the Landsat-9 Satellite is 99 minutes.


The Mission of the Voyager Spacecraft is Outer heliosphere research.


The Campaign Duration of the CryoSat-2 Satellite is Up to four months.


The Landing Location of the Falcon 9 Rocket is "Just Read the Instructions" droneship, which was stationed in the Pacific Ocean.


The UHF Downlinks of the UoSAT-12 Satellite is 3.


The Authors of the Double Asteroid Redirection Test (DART) Mission is Justin A. Atchison, Matthew Abrahamson, Martin T. Ozimek, Brian L. Kantsiper, Elena Y. Adams, Andrew F. Cheng, Andrew S. Rivkin, Cheryl L. Reed, Shyam Bhaskaran, Zahi Tarzi, Dianna Velez, Julie Bellerose, Frank Laipert, Daniel Grebow.


The Purpose of the CATS Lidar Instrument is Measure clouds and aerosols.


The Collision Avoidance Date of the Swarm Satellite Constellation is 14 July 2022.


The Planned Operation Date of the METimage Instrument is 2021.


The Brightness of the Sw J1644+57 Supermassive Black Hole is Exceptionally bright for a few weeks.


The Size of the Cesium Satellite 1 Satellite is Six-unit CubeSat.


The Relation to Single-Detector Integration Time of the Integration Time Detector Array is m times longer, where m is the number of stages in a row.


The Number of Unique X-ray Sources of the 3XMM Catalogue X-ray Source Catalogue is 372 728.


The Contract Release of the JPSS Common Ground System Ground System is C18-10.


The Formation Time of the TanDEM-X and TerraSAR-X Satellites is ~ 3 seconds.


The Shift Length of the On-call Operations Operations is 12 hours.


The Measurement of the TROPOMI Instrument is Trace gases, aerosol and cloud properties.


The 2021 Acres Burned of the U.S. Drought Monitor Report is 124,000 acres.


The Intersatellite Link of the CM1 and CM2 6U CubeSats is In LEO.


The Solar Panels of the LF spacecraft Spacecraft is Four.


The Particle Contamination Level of the VSSC Satellite is Maximum of 300 ppm.


The Date of the Tohoku-Kanto earthquake Earthquake is March 11, 2011.


The Prime Contractor of the Göktürk-1 Satellite is Telespazio of Italy.


The URL of the DEIMOS-2 Satellite is http://www.elecnor.es/en/press/press/elecnor-deimos-inaugurates-its-puertollano-integration-and-satellite-operation-centre-and-presents-its-deimos-2-satellit.


The Maximum Crew Duration of the OWS Space Station is 84 days.


The Type of the EDI Instrument is Electron Drift Instrument.


The Spectral range of the MERSI Medium Resolution Spectral Imager is 0.41-12.5 µm.


The Image Release Date of the SMART-1 Satellite is Oct. 5, 2015.


The Estimated SNR of the Band 3 Spectral Band is 745.12 ± 92.15.


The Onboard System of the CAPSTONE 12U CubeSat is Communications system.


The Spectral Responsivity of the SPIRIT-III Interferometer-Spectrometer is 2.5 to 28.0 µm.


The Date of Event of the Solar Flare Solar Event is September 6, 2017.


The Published Article Date of the Eugene Parker Astrophysicist is 1958.


The Purpose of the Herschel Telescope is Map the star formation in clusters by measuring the far-infrared emission from the particles of dust.


The Publication Date of the Shuttle Radar Topography Mission Satellite Mission is 1998.


The Launch Date of the HORYU-2 Nanosatellite is May 17, 2012.


The Material of the LAGEOS Satellite is Aluminium sphere with a brass core.


The Attitude Determination Accuracy of the X-ray Telescope Telescope is 0.5º.


The Linear Resolution of the Satellite Imaging Satellite is 34 m x 24 m.


The Developers of the Level 2 products Data Products is KNMI, SRON, DLR and BIRA.


The Launch Vehicle of the CHOMPTT Satellite is Rocket Lab USA Electron.


The Total Mass of the DSP satellites Satellite is 330 kg at launch.


The Orthorectification Requirement of the EROS-A PIC Instrument is Required.


The Launch Date of the Aeolus Satellite is August 2018.


The Spectral Band of the Band Cameras Camera is 336.2 nm.


The Designs of the Antenna Satellite Component is Omnidirectional, high gain and arrays.


The Data Reception and Distribution Agreement Date of the CartoSat-1 Satellite is January 14, 2008.


The Tank Type of the ACE propulsion system Propulsion System is Blow-down hydrazine tanks.


The Data Uses of the RADARSAT-1 Satellite is Disaster management, interferometry, agriculture, cartography, hydrology, forestry, oceanography, ice studies and coastal monitoring.


The Evaluation Date of the CrIMSS OPS-EDR Product Data Product is 02/24/2012.


The Attitude Control System Stability of the CFESat Satellite is Up to 60% of the orbit.


The Cargo Weight of the Dragon CRS-14 Spacecraft is More than 2630 kg.


The Flash ROM of the OBC On-Board Computer is Updated applications.


The On-Orbit Performance of the ATMS Instrument is All performance parameters are within expected values.


The Drag Sail Deployment Date of the CanX-7 Satellite is May 4, 2017.


The Definition of the dBZ Unit is Z is the equivalent radar reflectivity that gives a mean power equal to the standard deviation after integration and noise subtraction.


The Launch Date of the Vigil Spacecraft is Mid-2020's.


The Data Rate of the Communication links Communication subsystem is 3 single channel RCV, 2 synthesized RCV 2 synthesized transmitters.


The Clarity of the EPIC Data Exoplanet Imaging Data is Exceptionally clear view of Earth, largely unfettered by light from other sources.


The Predicted Target Error of the LRR Radar is Below 6 mm.


The Tuning Positions Separation of the Lyot-Michelson Filter System Optical Instrument is 69 mÅ.


The Function of the Camera Sensor Imaging System is Anti-blooming and electronic integration control.


The Rotation Speed of the Antenna Subsystem Satellite Component is 5.6 rpm.


The Manufacturer of the Star Trackers Attitude Sensing is CAL Corp, Canada.


The Color of the Electronics Mainboard Electronic Component is Green.


The Components of the European Service Module Spacecraft Module is Built and integrated in Italy and Germany, with smaller components delivered from several European nations, including the solar arrays from the Netherlands.


The Size of the Lake Atatürk Dam Reservoir is 817 km2.


The Orbital Slot of the GSAT-0203 Satellite is B08.


The Data Downlink of the GNOMES Instrument is Via commercial ground station networks.


The Deployment of the MUPUS-PEN Instrument is Will be deployed.


The Funding of the QARMAN CubeSat is European Space Agency.


The Signal Delay of the Analog-1 Experiment is More than 0.8 seconds.


The Number of Satellites Launched of the OneWeb Satellite Constellation is 36.


The Observation Data of the CryoSat-2 Satellite is Arctic sea-ice thickness measurements.


The Planning Cycle of the TDP Operations Satellite Operations is Weekly incremental cycle.


The Operator of the Copernicus Programme Earth Observation Program is European Commission.


The Instruments of the GEO-KOMPSAT-2B Satellite is Geostationary Environment Monitoring Spectrometer (GEMS) and the Advanced Geostationary Ocean Colour Imager-II (GOCI-II).


The Perigee of the FASat-Alfa Satellite is 651 km.


The Spatial Resolution of the LIS Lightning Image Sensor is 4km.


The URL of the TSU Telescience Support Unit is http://www.prismasatellites.se/?id=8202.


The Discovery Date of the Kepler-1649c Exoplanet is April 15, 2020.


The Contamination Distance of the Sun and Galactic Glint Optical Phenomenon is Up to 1000 km from the coastlines.


The Mass of the MAXI J1820+070 Black Hole is About eight times that of the Sun.


The Sampling Mechanism Duration of the OSIRIS-REx Spacecraft is Approximately five seconds.


The URL of the NICER Neutron star Interior Composition Explorer is https://smd-prod.s3.amazonaws.com/science-red/s3fs-public/atoms/files/nicer-factsheet-final.pdf.


The Restructure Date of the NPOESS Satellite Program is February 2010.


The Average Cabin Temperature of the Metric Camera Camera is 22º C.


The Uplink Data Rate of the RF Communication System Communication System is 1.2 kbit/s.


The Components of the LENA Instrument is Collimator, conversion unit, extraction lens, dispersive energy analyzer, time-of-flight mass analyzer with position-sensitive particle detection.


The Time Resolution of the CCD Image Sensor is 2.6 seconds.


The Type of the Tranet Tracking System is Two-frequency Doppler.


The FEC Coding Scheme of the Transmitter Communication Device is 5/6 TCM.


The Purpose of the Bigelow Aerospace BEAM Inflatable Module is Provide operational experience with inflatable modules in a crewed environment.


The Operation Date of the Analog-1 Experiment is Late 2019.


The Spectral Resolution of the Instrument Spectral Imager is 0.625 cm -1.


The Ring Memory (RM) of the Groza Instrument is Fixed size sufficient to record a few events.


The Focal Length of the VSSC Camera is 1.75 m.


The Information Provided of the µSCIA Monitoring Instrument is Total column amount.


The Functions of the ICU Instrument Control Unit is Controlling the detector modules, reading-out, processing and forwarding science data, providing thermal control to all instrument units, controlling the calibration light sources and mechanisms, providing engineering data for instrument health status.


The FY22 Budget of the CloudSat Satellite is Unknown.


The Resolution of the Nadir Sensor Wide-Field Telescope Sensor is 0.42 nm.


The Orbital period of the Satellite LEO (Low Earth Orbit) is 98.8 minutes.


The Planet Sizes of the TRAPPIST-1 Star System is Very close to the size of Earth.


The Launch Date of the NASA Space Station Cargo Resupply Mission is April 18, 2017.


The Scientific Objective of the QUESS satellite Satellite is Provide insight into the strangest phenomenon in quantum physics — quantum entanglement.


The Radar Type of the Biomass satellite Satellite is Fully polarimetric P-band synthetic aperture radar.


The Mode of the Yutu-2 Lunar Rover is "Napping" mode.


The URL of the Docking Module Space Station Module is https://blogs.nasa.gov/spacestation/2021/11/26/russias-new-docking-module-arrives-at-station/.


The Accuracy of the MAG Magnetometer is ≤1 nT.


The International ID of the SpriteSat Satellite is 2009-002C 33494.


The URL of the Solar X-ray Imager Imager is http://goes.gsfc.nasa.gov/text/databook/section06.pdf.


The Spacecraft Mass at Launch of the QuickBird-2 Satellite is 931 kg.


The Size of the Standard 3U CubeSat Satellite is 100 x 100 x 340.5 mm.


The Software of the TriTel CPU Central Processing Unit is CAN communication protocol.


The Design of the EPIC CCD Cameras is Capture both low- and high-energy X-rays.


The Data Storage of the EPICHyper Constellation Satellite Constellation is At least 4 GB on platform and 128 GB on payload.


The Total of the IASI-NG Instrument Optical Path Difference (OPD) is About 8 cm.


The Data Packet Loss Rate of the Analog-1 Experiment is 1%.


The Health Status of the Hitomi Satellite is Not Confirmed.


The Objectives of the COTS 2/3 Mission is Complete Licenses and Certifications, Rocket Launch and Spacecraft Inserted into Orbit, On-Orbit Operations, De-orbit Burn & Separation, Controlled Entry, Descent, and Landing, Recovery.


The Program Date of the Meteosat Third Generation (MTG) Satellite is Oct. 1-5, 2012.


The Type of the RF communication subsystem Communication is Non-coherent, half-duplex, 20K00F1D.


The Detector Type of the Observation Instrument Telescope/Spectrograph is 2D MCP (solar blind), Csl photocathode, cross-delay-line (XDL) readout, full array size 4096 spectral x 4096 spatial x 256 PHD.


The Awarded Funding of the OPS-SAT CubeSat is 12.


The Mission Requirements Document of the Next Generation Gravity Mission Satellite is URL: https://www.asi.it/wp-content/uploads/2021/03/MAGIC_NGGM_MCDO_MRD_v1_0-signed2.pdf.


The Memory Card Capacity of the DSU Data Storage Unit is 1 Tbit at EOL.


The Initial Plenum Pressure of the T3µPS Pressure Sensor is 1 bar.


The Maximum Signals Tracked of the BlackJack GPS Instrument is 48.


The Impact on Thrust of the Solar Activity Natural Phenomenon is Isolated peaks of IPA thrust.


The Pixel Pitch (MS) of the Pushbroom imager Detectors is 48 µm x 48 µm.


The Earth Incidence Angle of the AMSR-E Instrument is 55.0º.


The Performance Area of the Nadir Profile Spectrometer Spectrometer is 250 km x 250 km.


The Management of the EDRS Data Relay Satellite System is Managed through a dedicated segment.


The Field of View of the WFI Wide Field Imager is ~40º.


The Size of the SPACE HAUC CubeSat is 3U.


The Resolution of the HRMX Imaging System is 2 m.


The Predicted Pmp at BOL of the KOMPSAT-6 Satellite is 2,874 W.


The Sensitivity of the XMM-Newton X-ray Telescope is Incredibly sensitive to signals.


The New Debt Issued of the Maxar Technologies Company is $150 million.


The Low Temperature Limit of the Batteries Power System is -10°C.


The Communication System of the SPOT-6 & SPOT-7 Satellite Constellation is AstroTerra system.


The Link Loss Behavior of the LLITED satellites Satellite is Try up to 3 seconds to complete the last packet transmitted.


The Article URL of the XMM-Newton Satellite is https://doi.org/10.1051/0004-6361/201832664.


The | of the VIRGO Helioseismology and Solar Irradiance Monitoring Experiment is VIRGO: Experiment for Helioseismology and Solar Irradiance Monitoring.


The Design Presentation URL of the Microsatellites Satellite is http://cddis.nasa.gov/lw13/docs/presentations/target_nicholas_1p.pdf.


The In-flight Disconnect of the CSD Satellite Component is Unknown.


The Number of Pristine Vantage Points of the THEMIS Constellation Satellite Constellation is 12.


The Measurements of the RA-1 Instrument is Precise altitude, Significant wave height, Ocean surface wind speed, Various ice parameters.


The Radiation hardness of the STRV-1d DHS Data Handling System is about 100 krad.


The Resolution of the Visual Imager Instrument is More than 600 mega pixels.


The End of Life Date of the EXPORTS Satellite Mission is July, 2025.


The Publication Date of the Cluster STAFF experiment Experiment is 1997.


The Elevation Mask of the GNOMES-1 Satellite is 5 degrees.


The Temporal Coverage of the Geostationary Infrared Sounder Satellite Instrument is Good.


The Orbit Type of the GEISAT Precursor Satellite is Sun-synchronous.


The Swath Width of the PP Instrument is Approximately 28 km.


The Mass of the Satellite Payload is 180 kg.


The Launch Date of the Monitor-E Spacecraft is Aug. 26, 2005.


The Function of the U-GEO Algorithm is Combines Copernicus Sentinel data with urban planning, resource management, and green infrastructure.


The Max. Data Rate of the RF Communications Communication Subsystem is 100 kbit/s.


The Open Call Year of the OPS-SAT Satellite is 2013.


The Fuel Endurance of the Wind Satellite is Until 2074.


The Power Consumption of the RM Radiation Monitor is ~1.4 W.


The Stowed Dimensions of the DSX Spacecraft Payload Module Satellite is 3.6 m x 2 m x 1.1 m.


The Conference Date of the Laser Communication Terminals Communication Device is 8-13, 2007.


The Modulation Schemes of the Transponder Communication Device is PCM/PSK/PM, PSK.


The Submission Date of the MinXSS CubeSat is August 15, 2013.


The Functions of the FOS Flight Operations Segment is Operation and control of the satellite, provision of telemetry.


The CO2 Annual Flux Estimation Error of the GOSAT Satellite is 0.54GtC/yr to 0.27GtC/yr.


The Counting Ability of the Particle Detector Instrument is 5 x10 4  event/s.


The URL of the Cluster Satellite is http://www.esa.int/Our_Activities/Operations/Rejigging_the_Cluster_quartet.


The Avionics of the STRaND-1 Satellite is Smartphone.


The Wavelength of the VNIR Band is 1.06 µm.


The On-board Orbit Computation of the DORIS-DIODE Satellite System is Operational.


The Operation Mode of the NAOMI Imaging Instrument is TDI (Time Delay Integration) mode in the Pan band.


The Slew Rate of the NigeriaSat-2 Satellite is 6°/s.


The Payload Mass of the DSP satellites Satellite is 30 kg.


The Development Tools of the EDSN Organization is JIRA, static analysis tools, peer reviews, central repository with subversion tracking, virtual machines.


The Launch Date of the Pléiades Satellite is Dec. 17, 2011.


The Conference Presentation of the MASCOT Lander Lander is May 16-20.


The Daily Data Volume of the Instrument Satellite Instrument is 50 Gbit.


The North Polar Region Name of the Charon Moon is Mordor Macula.


The Data Bandwidth of the RTEPs On-board Image Processing System is 6 Mbit/s.


The Mission Type of the High-Resolution Microsatellite Satellite is Earth Monitoring and Observation.


The Revisit Frequency of the Spacecraft Orbit is Maximum of 4 days.


The Satellite Cluster Quantity of the Kleos S.A. Company is 4.


The Inclination of the PhoneSat-2.5 1U CubeSat Satellite is 51.6°.


The Sensor Type of the OSA Optical Sensor Assembly is Optical.


The Sample Rate of the Angular Rate Sensor is 125 Hz.


The Antenna Type of the Knudsen Station Ground Station is Quad array 436CP42UG cross polarized UHF Yagis.


The Absolute Pointing Uncertainty of the Spectral Block Focal Plane Component is ±0.25º.


The Ground Station Transmission of the CanX-7 Satellite is Next Access.


The URL of the Sierra Nevada Corporation Corporation is https://www.sncorp.com/press-releases/snc-hardware-on-nasa-insight-mission/.


The Sun sensors of the BEESAT-1 Satellite is Yes.


The Purpose of the OCO-2 Satellite is Making unprecedented, accurate global measurements of carbon dioxide levels in the atmosphere and providing unique information on the natural processes controlling carbon exchange between land and air and between the atmosphere and ocean.


The End of Life Date of the AstroSat Astronomy Satellite is 28 September 2025.


The Top Temperature of the Meteosat-10 Satellite is 33.5 °C.


The Data Interface of the CCD (Charge-Coupled Device) Imaging Device is Special-purpose serial interface using data/strobe arrangement.


The Model of the IXV Recorder Recorder is COTS SSR-500.


The Type of the KOMPSat-5 Satellite is SAR.


The Maximum Tracking Rate of the STOs and STAEs Analog Electronic units is 0.1º/s.


The ARGOS Support of the ESEX Satellite is Attitude control, communications, radiation-hardened data storage, and housekeeping power.


The Purpose of the Aeolus Satellite is Measure Earth's wind on a global scale.


The URL of the Shuttle Radar Topography Mission Satellite Mission is http://www.shuttlepresskit.com/STS-99/payload56.htm.


The Software Shutdowns of the IPA Engine is Twice in 20 months of operation.


The Rotation Rate of the Pulsar Neutron Star is 30 times per second.


The Article Date of the INTEGRAL Satellite is 26 Jan. 2016.


The Hibernation Start Time of the Philae Lander is 00:36 GMT.


The Coherence Change Detection of the TerraSAR-X Satellite is Significantly Enhanced.


The Purpose of the Copernicus Sentinel-2 Satellite is Methane hotspot detection.


The Amplifier Type of the SSPA Solid-State Power Amplifier is S-band power amplifier.


The Platform Type of the Göktürk-1A Satellite is Aluminium chassis with honeycomb panels.


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


The Mounting of the OCSE Satellite is JAWSAT payload.


The Launch Provider of the MethaneSAT Satellite is SpaceX.


The Mission Name of the Solar Probe Plus Satellite is Solar Probe Plus.


The Orbital Altitude Decay of the ProSEDS Tether Demonstration Experiment is At least 5-15 km in altitude per day.


The Launch Mass of the MSG-3 Satellite is ~2000 kg.


The Light Sensitivity of the DNB Sensor is Up to 10 million times fainter than daylight.


The Deployment Date of the LDEF Satellite is April 7, 1984.


The Downlink Contact Duration of the IXPE Satellite is 8 minutes.


The Planned Duration of the Science Operations Satellite Phase is At least 2 years.


The User Interface Manual Version of the DAPS Data Collection System is 1.1.


The Activation of the AutoNav Autonomous Navigation System is Immediate upon activation of the S/C.


The Laser Link of the Sentinel-1A Satellite is Excellent stability and robustness.


The Failure Date of the Sensor Flipper Unknown is March 23, 1978.


The Power Consumption of the OSDP Onboard Signal Data Processor is 28 W.


The Imaging Resolution of the NEMO-HD Satellite is 2.8 m GSD.


The Spatial Resolution (MS) of the PP Instrument is 10 m.


The Wavelength Range of the Band No 1 Spectral Band is 0.50 ± 0.2 - 0.70 ± 0.2 µm.


The Number of Retroreflectors of the STARLETTE and Stella Satellites is 60.


The Application of the SAR Sensor Sensor is Counting parked vehicles.


The Low Voltage Occurrence of the SpriteSat Satellite is After the deployment of the gravity mast.


The Managing Office of the IMAP Satellite is Heliophysics Program Office at NASA's Goddard Space Flight Center.


The Orbit Capability of the DSX Spacecraft Payload Module Satellite is 6,000 km to 12,000 km any inclination.


The Mounting Method of the Avionics and Payloads Satellite Components is Directly onto three equipment radiator panels.


The Launch Date of the SkySat-16 to -18 Satellite is 13 June 2020.


The Ground Segment Location of the KazEOSat-2 Satellite is Astana, Kazakhstan.


The Test Image Time of the WFC CCD Imager is Almost 12 hours before the boom deployment.


The Power Consumption of the Transmitter Communication Device is 61.1 W (max).


The GSD (Multispectral) of the EOS Camera is 4 m.


The URL of the Solar Orbiter/METIS Coronagraph/Spectrometer is http://congrex.nl/icso/2012/papers/FP_ICSO-089.pdf.


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


The URL of the EP-107 Skylab Space Station is http://history.nasa.gov/EP-107/ch5.htm.


The Function of the TEMBOTM EMC Material is Both the primary deployment mechanism and the principal structural members of the boom.


The Revisit Time of the Tandem-L Satellite is 16 days.


The Mission Life of the QSat Satellite is 2 years.


The Redundancy of the Telemetry Data is High.


The Orbit Altitude of the Almaz-1B Satellite is ~ 600 km.


The Impact of Satellite Constellations of the ESO Telescopes Telescope is Not specified.


The Measurement Type of the GEOSAT Radar Altimeter (GRAS) Instrument is High-precision range measurements between the satellite and the subsatellite point at nadir.


The Mass of the Prichal Module Docking Port is 4 metric tons.


The Industries of the OSG Company is Aerospace, automotive, die/mold, and many others.


The Launch Date of the CartoSat-2 Satellite is Jan. 10. 2007.


The Payload of the MDASat-1 Satellite is SDR-based payload that will provide AIS and VDES services.


The Battery System of the EPS Electrical Power Subsystem is 2 NiCd batteries of 19 Ah each.


The Mass of the LEO Vantage Microsatellite is 70 kg.


The Calibration Date of the HISUI Hyperspectral Imager is 10-15 July 2016.


The Payload Space of the Bartolomeo Platform is 50+ liters.


The Purpose of the Unresolved Imagery Data is Observe and characterize orbiting objects with the goal of determining their attitude and detecting configuration changes.


The Launch Date of the Pleiades-1B Satellite is More than one and a half years before October 2013.


The Design Purpose of the Compact Intersatellite Link Communication System Communication System is For satellites operating in swarms.


The Interface Type of the MSV Combined Router and Power Distribution Unit is SPA-S (SPA-SpaceWire) compliant.


The Number of Successful Landings of the Falcon-9 Rocket is 20.


The Operating Status of the RISING-2 Satellite is Nominal.


The Impact on Results of the Subapertures Imaging System Component is Larger subapertures yield better results than smaller subapertures.


The Revisit Time of the S/C Satellite is One day.


The Transmitter Power of the Radio Communication Device is 5 W.


The Goal of the Neosat program Satellite Program is Build a European supply chain which optimizes costs and guarantees on-time delivery of satellites.


The Platform Size of the 6U CubeSat Satellite is 6U.


The Launch Date of the OneWeb Satellite Constellation is 14th of October.


The Solar Panels of the Picard microsatellite Satellite is Single.


The Components of the PowerCell Hardware is 48-segment 3-color optical density or absorbance measurement system, grow light system, microfluidic system for nutrient delivery and waste flushing, thermal control and internal environmental sensing including temperature, pressure, humidity, and acceler.


The Heat Shield Manufacturer of the Orion Spacecraft is Lockheed Martin.


The Instrument Type of the COR1 Coronagraph1 imager is Internally occulted Lyot coronagraph.


The Proton Dynamic Pressure of the ACE Satellite is ~2.4 nPa.


The Altitude of the Rideshare mission Satellite is 560 km.


The Power Output of the IPS Pointing System is Up to 1.25 kW.


The Quantification Method of the Lunar Meteoroid Impact Flash Detection Detection System is Using the apparent magnitude of the light flash.


The Size of the Spacecraft Satellite is 9.9 m (x) x 16.5 m (y) x 3.7 m (z).


The Presentation Date of the Global Climate Observing System (GCOS) Climate Observing System is July 21, 1999.


The Development Time Frame of the GOME Instrument is 1990-1994.


The Size of the Debris Spacecraft Debris is About 1.3 meter pixels.


The Distance from Earth of the GSN 069 Black Hole is About 250 million light years.


The Segments of the ICU Container is Bottom, Middle, Top.


The Geolocation Knowledge of the QuickBird-2 Satellite is < 15 m (3?) after ground processing.


The Type of the THI (Thermal Hyperspectral Imager) Payload is Relatively large.


The Uplink Frequency of the Iris Radio Communication Device is Standard X-band.


The Ionising Doses of the TimePix radiation sensors Sensor is 4 to 5 krads.


The Ground System of the FormoSat-7 / COSMIC-2 mission Satellite Mission is High degree of automation.


The Altitude of the ICEYE-X14 and ICEYE-X16 Satellites is Approximately 500 km.


The Solar Array Deployment of the TSUBAME Satellite is Automatically deployed after the rocket separation.


The Capability of the Attitude & Orbit Control Subsystem (AOCS) Control System is Orienting the dual-gimballed data transmission antenna to point towards the required data reception station during the overpass of the CartoSat-2.


The Type of the Micro Systems Technology Experiment is In-Orbit.


The Testing Environment of the CuPID spacecraft Spacecraft is Helmholtz cage.


The Date of the SMAPVEX12 Experiment is 2012.


The Peak Power of the 4-band CCD Imager Instrument is 30 W.


The SASAR System of the DRT Data Relay Transponder is Not Carried.


The Propulsion of the Schiaparelli Module is 3 clusters of 3 hydrazine engines (400 N each), operated in pulse-modulation.


The Structure of the XI-IV Picosatellite is Conforms to the requirements of the CubeSat program in size and mass.


The Manufacturer of the GPS/MET GPS Receiver is Allen Osborne Associates Inc..


The Avionics Redundancy of the TDS-1 Satellite is Fully redundant.


The | of the SSO-A SmallSat Express is Spaceflight - Introducing SSO-A: The smallsat express.


The length of the Detector Instrument is 1024 pixels.


The Antenna Type of the Tandem-L Satellite is Digital radar antenna.


The Failure Analysis of the Taurus Frangible Joint Design Satellite Component is Detailed fault tree or failure mode analysis.


The Mean Mission Life of the SBSS Satellite System is 5.5 years.


The Type of the Primary Mirror Telescope Component is Off-axis paraboloid.


The Quantity of the Sun sensors Sensor is 4.


The IF Frequency of the Receiver Communication System is 112.5 MHz.


The Launch Date of the SPOT-6 Satellite is September 2012.


The Observation Area of the T1 Trigger Camera is 160 km x 160 km.


The Protection of the Flywheel Housing Satellite Component is Capton tape.


The Modulation Indices of the Transponder Communication Device is Command and ranging (for uplink), telemetry and ranging (for downlink).


The URL of the Xatcobeo CubeSat is http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20100021944_2010023813.pdf.


The Data Integration of the CDE Sensor is Over several days.


The Energy Range of the X-ray Background Spectrum Spectrum is 3-300 keV.


The Pointing Accuracy of the IRS-1C and IRS-1D Spacecraft is Roll and pitch = ±0.15º, yaw = ±0.2º.


The Filter Type of the VIS channel Spectrometer is VIS 3.


The Example of the Coordinated Observations Satellite Mission Activity is Study of trans-ionospheric radio propagation using the RRI on e-POP in conjunction with SuperDARN and CADI (Canadian Advanced Digital Ionosonde) transmitters on the ground.


The Accuracy of the Sun sensors Sensor is 0.2º (3σ).


The Resolution of the CHRIS Imaging Spectrometer is 17 to 34 meter.


The Launch Date of the Meteosat-7 Satellite is September 1997.


The Ground Footprint of the RA Imaging System is 16 km.


The Image Capture Date of the ALOS satellite Satellite is February, 2014.


The Data of the Aeolus Satellite is Altitude and vertical extent of the aerosol layer.


The Battery unit of the EPS Electrical Power Subsystem is 8 series NiMH (750 mAh, 9.6V).


The Platform of the SOVA Experiment is Eureca.


The Attitude of the Satellite Spacecraft is BBQ-attitude.


The Thrusters of the LISA Pathfinder Spacecraft is µN.


The First Flight of the SIMBA Satellite RMIB SIMBA program is 2016.


The Operation Mode of the GeoSTAR Atmospheric Microwave Sounder is Nowcasting and very short range weather forecasts.


The Information Provided of the Copernicus Sentinel-4 and Sentinel-5 Satellite Missions is Air quality, solar radiation and climate monitoring.


The Position Control of the CanX-4&5 Satellite is 10 cm.


The Parachute Quantity of the ExoMars mission Mars Mission is Two main parachutes.


The Confirmed Transiting Planets of the Kepler-11 Star System is 6.


The Satellite of the Spire Global UK Company is Nanosatellites.


The Mass of the SOCRATES Microsatellite is 48 kg.


The Calibration Method of the Meteosat Second Generation (MSG) Radiometer/Imager Satellite is Dedicated Moon/Sun/Deep-space Scans.


The Footprint of the Millimeterwave receiver Receiver is 15 m.


The Scanning Period of the MWHS-II Microwave Humidity Sounder is 2.667 s ± 50 ms.


The Power Usage of the Microelectronic device Device is 20 times less than proven technology.


The Operator of the GovSat-1 Communication Satellite is LuxGovSat S.A..


The URL of the TOPCAT Satellite is https://web.archive.org/web/20120306134448/http://www.bis.gov.uk/assets/bispartners/ukspaceagency/docs/space%20science/cubesats/astrium%20payload%20text%20and%20picture.pdf.


The Attitude Control of the SCD-2 Satellite is Spin-stabilized.


The Equipment Modules of the Terra Satellite is Sized and partitioned to facilitate pre-launch integration and test of the spacecraft.


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


The Solar Array Dimensions of the IRIS Satellite is 0.6 m x 1.3 m.


The Absolute Accuracy of the OVM Overhauser scalar magnetometer is 0.5 nT.


The Ops Renewal Contract of the SeaHawk-1 Satellite is Received.


The Statistical Accuracy Goal of the HaloSat Satellite is ±0.5 LU.


The Pointing Accuracy of the AOCS Attitude and Orbit Control Subsystem is < 36 arcsec for the Z-axis.


The Separation Distance from Earth of the Reentry Vehicle Vehicle is Around 5,000 km.


The Conference Date of the WorldView-1 Satellite is Nov. 11-14, 2007.


The Potential Data of the Tandem-L Satellite is Forest height, structure, and biomass.


The Data Rate of the S-band Communication Band is 66.54 kbit/s.


The Power of the solar panels solar panels is Average power of 10 W.


The Spatial Resolution of the SAR Sensor Subsystem SAR Sensor is 1 m x 1 m.


The Orbit Type of the EURECA Satellite is Low Earth Orbit (LEO) circular.


The Launch Site of the KazSTSAT Microsatellite is VAFB (Vandenberg Air Force Base) in California.


The Purpose of the SCAR TSI Calibration Device is Improve the long-term stability of TSI measurements.


The End of Life Date of the Kolibri-2000 Satellite is 3 May 2002.


The Launch Date of the M3MSat Satellite is 2016.


The Mission Type of the SEOSAT-Ingenio Satellite is Optical Earth-observation.


The SIC Temporal Sampling Period of the CIMR Radiometer Imager is Sub-daily.


The Mass of the CALET Telescope is 650 kg.


The Mission Phase of the Biomass Satellite is Last phases of development.


The Number of Sensors of the Rosetta Plasma Consortium Instrument Suite is Five.


The Data Rate of the SAGE-III Instrument is 115 kbit/s.


The Launch Date of the Mars Hope probe Spacecraft is February 2021.


The Purpose of the Matroshka AstroRad Radiation Experiment (MARE) Radiation Experiment is Provide valuable data on radiation levels during missions to the Moon and test the effectiveness of the new vest.


The | of the D. M. Smith Author is D. M. Smith.


The Science Instruments of the Landsat-9 Satellite is Operational Land Imager 2 (OLI-2) and the Thermal Infrared Sensor 2 (TIRS-2).


The Manufacturer of the XMM-Newton Satellite is ESA.


The Number of Mirrors of the Korsch telescope Telescope is 5.


The Constraint of the Instrument Payload is Keep the instrument radiators away from Nadir direction for thermal stability purposes.


The Mirror Type of the Long Wavelength Band Spectrometer is Off-axis parabolic cylinder.


The Principle of the Momentum-exchange Tethers Space Propulsion System is Based on the gravity gradient force.


The Data Usage of the Aeolus Satellite is Climate Research, Weather Forecasting.


The Sewing of the MLI Thermal Control Device is Connection Method.


The Presentation Date of the CNES Satellite is Feb. 16-18, 2010.


The Applications of the LAPAN-TUBSAT Satellite is Disaster monitoring, vegetation monitoring.


The URL of the Kepler Satellite is https://kepler.nasa.gov/news/nasakeplernews/index.cfm?FuseAction=ShowNews&NewsID=226.


The Composition of the SloshSat Investigators' Working Group (IWG) Team is Academic researchers from Groningen State University (NL), Delft Technical University (NL), Technion (Israel), and investigators from ESA, NASA and NLR.


The Panchromatic Band Ground Resolution of the WorldView-3 Satellite is 31 cm.


The Filter Thickness of the VIS channel Spectrometer is 3.00 mm.


The Launch Time of the KazSTSAT Microsatellite is 18:34:05 GMT.


The Nr. of spectral or frequency bands of the Microwave System Microwave System is 22 MW channels.


The Science and Mission Overview of the STEREO Satellite is  URL: http://www.jhuapl.edu/techdigest/TD/td2802/Kaiser.pdf.


The Operation Start Date of the ICE-Cubes facility Research Facility is December.


The Detector Type of the Instrument Satellite Instrument is 1D CCD (4098 pixels).


The Emissivity of the Calibration Mirror TIR Subsystem Component is Near-perfect zero radiance reference.


The Pointing Requirements (Knowledge) of the Aquarius Radiometer System is 0.1º.


The Battery Life of the AAUSat-1 CubeSat is Two and a half months.


The Mission Duration of the BEAM Module is Two years.


The Contribution of the GOCE Satellite is New view of the remnants of lost continents hidden deep under the ice sheet of Antarctica.


The Number of Rocket Motors of the Super Strypi rocket Rocket is 3.


The Observation Date of the Van Allen Probes Satellite is March 17, 2015.


The Head of the Astronomy Missions Division of the Integral Satellite is Andreas Rudolph.


The Operation Start Date of the SARah system Satellite System is End of 2019.


The Designers of the ISIM Compartment is Matthew Garrison, Keith Parrish, Charles Perrygo.


The Element Size of the CCD Detector Matrix Detector is 22.5 µm x 22.5 µm.


The Production Frequency of the Nighttime SST Product Dataset is Hourly.


The Launch Date of the BepiColombo Satellite is October 2018.


The Mission Type of the IRIS Satellite is Solar Study.


The Solar Calibration Components of the SeaWiFS Satellite is Solar radiation diffuser, input port.


The Mass of the KazSTSAT Microsatellite is <100 kg.


The Open Pores Fraction of the MXT Instrument is 50.


The FOV of the 16 mm camera Camera is 6.9º x 5.336º.


The Launch Mass of the QZS-1 Satellite is 4100 kg.


The Orbit Altitude of the Beijing-3A Satellite is 500 km.


The Mounting Date of the IASI-NG PFM instrument Instrument is 2022.


The Passbands of the HIRES Instrument is 395 - 435 nm, 535 - 585 nm, 625 - 675 nm, 725 - 775 nm, and 450 - 800 nm.


The Program of the MiRaTA Satellite is In-Space Validation of Earth Science Technologies.


The Cal_limb data Collection of the OCO-2 Satellite is Solar and Atmospheric Absorption Lines.


The Center Wavelength of the Band No. 4 Spectral Band is 504.96 nm.


The Area Collection Rate of the Framer Sensor is Very low.


The Program of the SMAP Satellite is ESSP (Earth System Science Pathfinder).


The Last-Second Abort Date of the Falcon 9 Rocket is Oct. 2.


The Positioning Precision of the Galileo Satellite System is Meter-scale.


The Type of the Star sensor Sensor is CCD matrix.


The Altitude of Rear Heatshield and Parachute Jettison of the Schiaparelli Lander is 1.3 km above the surface.


The Location of the BSOCC Satellite Operation Control Center is Just about 10 miles northeast of the GSFC.


The Manufacturer of the LISS-I Camera Imaging Device is ISRO.


The Mass of the IDEA OSG-1 Microsatellite is 22 kg.


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


The Track Duration of the DSN Communication System is 3.5-5 hours.


The Number of Scientific Payloads of the Chang’e-4 Mission is 6.


The Launch Date of the DSCOVR Satellite is Feb. 9, 2015.


The Data Delivery of the LIS Lightning Imaging Sensor is Once operations begin.


The Measurement Quality of the Lunar Meteoroid Impact Flash Detection Detection System is High signal-to-noise ratios (SNR).


The Map Area Coverage of the Copernicus Sentinel-1 Satellite is 176 km by 170 km.


The ADCS of the IOD-1 GEMS Satellite is Attitude Determination and Control Subsystem.


The URL of the ALOS PRISM Satellite is http://www.isprs-ann-photogramm-remote-sens-spatial-inf-sci.net/II-4/71/2014/isprsannals-II-4-71-2014.pdf.


The Thickness of the GDS Light Curtain is 3 mm.


The Mass of the ITUpSat-1 Satellite is ≤ 1 kg.


The Application of the TEMPEST Sensor is Numerical models and characterizing the moisture surrounding tropical cyclones.


The Data Rate of the ASPOC Instrument is 0.13 kbit/s.


The Processing Location of the OSIRIS Data Processing is University of Saskatchewan, Saskatoon, Canada.


The Next Launch Date of the Soyuz Spacecraft is Spring of 2022.


The Size of the Antennas Communication Equipment is 9.1 m.


The Owner of the Deep Space Tracking Antenna Antenna is China.


The Back-up Channel Data Rates (Downlink) of the RF Communications Communication System is 38.8 kbit/s.


The Operator of the Meteosat-7 Satellite is EUMETSAT.


The Polarization of the ICEYE-X1 Satellite is Single VV.


The Voltage of the Battery Power System is Unknown.


The Integration Date of the IRIS Satellite is Jan. 18, 2013.


The Solar Power of the EPS Electrical Power Subsystem is at BOL: 1390 W (max), at EOL: 1100 W.


The Resolution of the ASTRO-H Satellite is 30-50% of the hard X-ray Cosmic Background.


The Re-Entry Date of the Aeolus Satellite is Before the end of August.


The Cargo Capacity of the HTV-9 Cargo Transfer Spacecraft is Up to six tons.


The Objective of the CAVIS Imager is Monitor the atmosphere and provide correction data to improve WorldView-3's high-resolution imagery.


The Travel Path of the X-ray emission Phenomenon is Towards us through dusty regions of our Galaxy.


The Bandwidth of the Radiometer Instrument is 22 MHz.


The Location of the Reykjavík City is Seltjarnarnes Peninsula, in southwest Iceland.


The Usage of the Pelican Satellites Satellite is Mapping services, environmental tasks, defense, support rescue operations.


The VHF-band FSK Channels Data Rate of the UoSAT-12 Satellite is 9.6 kbit/s.


The Content of the High-level Activity Schedule Product is Times the LCRD payload will operate and any operational events that may impact host spacecraft flight or ground operations.


The Data rate of the Optical System Imaging System is 665.4 kbit/s.


The Time Resolution of the NICER X-ray Timing Instrument is Highest of any astronomy instrument flown.


The Number of Phase-B Contracts of the Galileo Second Generation Satellite System is 11.


The Composition of the Rocklea Dome Geological Formation is Light-colored granites.


The Pixel Exposure Time of the Instrument Satellite Instrument is 1.625, 3.25, or 6.5 ms.


The Rainfall Data URL of the TRMM Satellite is http://pmm.nasa.gov/TRMM/realtime-3hr-7day-rainfall.


The Mass of the SD2 Sample Drill and Distribution System is 4.8 kg.


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


The Launch Site of the Sentinel-1B Satellite is Kourou.


The Measurement Precision of the SOFIE Instrument is T 0.2 K, O3 11 ppbv, H2O 70 ppbv, CH4 5 ppbv, PMC extinction 5 x 10 -8 km -1.


The Imaging Capability of the Kestrel Eye-2M Microsatellite is Spot objects on Earth's surface about the size of a car.


The Operating Hours of the LMOC Ground Segment is 24 hours per day, seven days per week.


The Correction Factor of the Sun and Galactic Glint Optical Phenomenon is 0.98.


The Ground Instantaneous Field of View (GIFOV) of the Climate Observatory Satellite is ~250 m spatial resolution.


The Orbit of the TRUTHS Satellite is Asynchronous.


The Temperature Sensitivity of the SOHO's EIT Extreme-ultraviolet Imaging Telescope is 1 million, 1.5 million, 2 million and 60,000–80,000ºC.


The Main Imager Spectral Wavelengths of the PROBA-1 Microsatellite is 18 programmable visible and near-infrared wavelengths.


The Location of the GOMS-1 Satellite is 76.5º East.


The Capacity of the Node-3 Module is Up to eight ISS equipment racks.


The Pointing Requirement of the Imaging Payload Satellite Component is Towards nadir.


The Manufacturer of the T6 thrusters Ion Thrusters is QinetiQ.


The Use Case of the Specialized Asset Trackers Tracking Device is Big productivity gains with a specific asset type.


The Wind Velocity Range (Troposphere) of the Aeolus Satellite is 0 - 2 km.


The Presentation Date of the CBERS Satellite is Feb. 4, 2009.


The Purpose of the TOPCAT Payload is Ionospheric study based on GPS measurements.


The Sensitivity to Multipath of the FFRF Sensor Instrument is May lead to initial range biases up to 1 m and bearing bias variations in the 0.5° range for 30° attitude changes.


The LTDN of the SuperView-1 01 and Superview-1 02 Satellite is 10:30 hours.


The Type of the Sun Sparc microprocessor Microprocessor is Radiation-hardened.


The Function of the SDR (Software Defined Radio) Communication Device is Dynamically change its receive and transmit frequencies.


The Launch Date of the GOSAT Satellite is 23 Jan 2009.


The Design Requirements of the Swarm Spacecraft Satellite is Magnetic cleanliness, Magnetic field vector attitude knowledge, Ballistic coefficient, Accelerometer proof-mass vs satellite CoG location.


The Type of the CRATEX (C-band Radar Transponder Experiment) Payload is Eliminated.


The Sweep Angle of the Sensor Sensor is 10.4º.


The Downlink Frequency of the TT&C Data Communication is 2089 MHz.


The Planned Position of the TEMPO Satellite is 91° West, above the equator.


The Typical Value of the NO2 Satellite Instrument is 6.


The Coverage of the ISS-LIS Lightning Detection Instrument is CONUS (CONtinental US).


The Conference Presentation of the MMS Phase 2B Navigation Performance Navigation Performance is AAS/AIAA Astrodynamics Specialist Conference.


The Delta V of the Propulsion Subsystem Propulsion is 20 m/s.


The Operating Voltage of the Herley MD2000C-1 Transponder Module is 22–32 VDC.


The Soft Start Up of the DC-DC converter Power Converter is Typically greater than 1ms/V.


The Nominal SNR of the Band 8 Spectral Band is 750.


The Operating Distance from the Sun of the Rosetta Spacecraft is Over 800 million km.


The Operation Mode of the Ground Segment Communication System is Store-and-forward.


The Calibration and Validation Date of the DubaiSat-2 Satellite is Early March 2014.


The Mission Type of the Buccaneer CubeSat is Non-EO.


The Age of the Chamaeleon I Star-forming Region is Two million years-old.


The Array of the Fluidic Card Device is 4 x 12.


The On Board Calibrator (OBC) of the OCO-2 Satellite is Calibration Data Collection.


The Mission Duration of the Solar Maximum Mission Satellite is 14 Oct.. 1984 - 15 April 1986.


The Date of the Cloud-free Iceland Weather Phenomenon is 28 August 2020.


The Current of the Voltage 4 Modulator is 250.


The J2000 declination (deg) of the GROJ1744-28 Pulsar is -28.741.


The Consortia of the Moonlight Lunar Telecommunications and Navigation Satellite Network is The consortium includes: satellite operators Inmarsat and Hispasat; manufacturing companies such as Thales Alenia Space Italy, OHB System in Germany and Canadian space technology company MDA; Italian Aerospace Logistics Technology Engineering Company (ALT.


The SAR Techniques of the TanDEM-X Satellite is Digital beamforming (DBF) with two satellites, single-pass polarimetric SAR interferometry, single-pass along-track interferometry with varying baseline.


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


The Pointing Accuracy of the iADCS-100 ADCS System is Well below 1°.


The Comet of the Rosetta Spacecraft is 67P/Churyumov-Gerasimenko.


The Brighter Areas Indicator of the Image Data is Changes in amplitude.


The Function of the MXS Modulated X-ray Source is Demonstration of X-ray communication in space.


The Operating Frequencies of the SMMR Microwave Radiometer is 18.0 GHz.


The Energy of the VIS (red) Band is 1.9 eV.


The Principal Investigator of the New Horizons Spacecraft is Alan Stern.


The Spectral Bands of the CIMR Radiometer Imager is 1.4, 6.9, 10.65, 18.7, and 36.5 GHz.


The Cost (sensor + spacecraft) of the Push Frame Framer with a fast steering mirror Sensor is Low.


The Payload Data of the ASAP Nanosatellite is High-resolution image data, in the order of 100 MB/day.


The Orbit Inclination of the GHGSat-C2 (Hugo) Nanosatellite is 97.6º.


The Propulsion of the CAPSTONE Satellite is Solar and the Sun’s gravity.


The Swath Width of the HRMX Imaging System is 10 km.


The Coarse Stabilization of the S/C Satellite is Gravity gradient boom (actuator, 6 m long).


The Performance of the GPSP Instrument is Same or better as on Jason-2.


The GNSS Signals of the Pyxis-RO Instrument is GPS (L1 at 1575.42 MHz and L2 at 1227.6 MHz), Galileo (E1 at 1575.42and E5 at 1207.14MHz), GLONASS (FDMA signals centered at L1 at 1602 MHz and L2 at 1246 MHz), and BeiDou (B1 at 1561.1 MHz5and B2 at 1207.14 MHz).


The Solar Wind Measurements of the IMAP Satellite is Electron, proton, heavy ion, and magnetic field.


The Launch Vehicle of the ETS-VIII Spacecraft is H-IIA F11.


The Wide Band Receiver Tunable Frequencies of the IOF Plasma Wave Instrumentation is 2000, 500, 125, and 31.1 kHz.


The Imaging Opportunities of the TeLEOS-1 Satellite is Up to 6 within a day.


The Downlink Frequency of the RF Communications Communication System is UHF band (437.5 MHz).


The Manufacturer of the Near Real Time SAR Processor SAR Processor is MRSA/SAC team.


The Objective 2 of the EPS (EUMETSAT Polar System) Satellite System is Provide enhanced monitoring capabilities (complimentary to ENVISAT) to fulfil the requirements to study the Earth climate system.


The Type of the DU Detector Unit is CMOS APS (Active Pixel Sensor).


The Coherence of the Optical Terminal Communication Device is True.


The Temperatures of the Cooler Passive Cooler is 98 K for MWIR/SWIR patch.


The Image Production of the SECCHI Instrument is About 7 images/hour.


The URL of the Galassia Nanosatellite Satellite is http://digitalcommons.usu.edu/cgi/viewcontent.cgi?article=3418&context=smallsat.


The Platform of the GaoJing / SuperView minisatellites Satellite is CAST3000B light agile platform.


The Date of the 30th Annual AIAA/USU SmallSat Conference Conference is August 6-11, 2016.


The Hydrazine Usage of the SPOT-4 Satellite is 2.8 kg.


The Weight of the Satellite Communication is 95 grams.


The Fiber Optic Cable Type of the Detector Box Instrument is Various lengths.


The Platform of the MANTIS Satellite is Nanosatellite.


The LTDN of the ALOS-3 Satellite is 1030 hours.


The Channels of the Communication System Data Transmission is Two.


The Bus Design of the Restore-L Satellite is Maxar's decades-proven 1300-class platform.


The Main Body Volume of the Solar Orbiter Spacecraft is 2 m3.


The Origin of the ERA Robotic Arm is Europe.


The Sensitivity of the MTVZA-GY Radiometer is Factor 2.


The Emission Detection Capability of the Iris Satellite is 100 times smaller than any other satellite.


The Anomaly Date of the RapidScat Team Investigation Team is Sept. 9, 2016.


The Rotation of the Captain Role Satellite Operation is Every spacecraft holding the role of Captain at least once and one spacecraft being Captain twice.


The Battery Endurance of the Satellite Spacecraft is 5 years.


The Solar Panels of the Microsatellite Satellite is Four deployable solar panels of 0.5 m2.


The No of revolutions of the KOMPSAT-3 Satellite is 14.6 revolutions/day.


The Wear-in Test Cycles of the Redesigned SMA Component is 15 cycles.


The Landing Date of the CIMON-1 Prototype is 27 August 2019.


The Launch Date of the Oculus-ASR Satellite is Unknown.


The SNR of the Imager Satellite Instrument is PAN: ≥48 dB, MS: ≥48 dB.


The Ground Resolution (Spotlight mode) of the XSAR SAR is Less than 1 m.


The Mission Duration of the LLITED Spacecraft is One year.


The Re-entry Date of the SENSE Satellites Satellite is May 4, 2015.


The Operation Mode of the IXAE X-ray Astronomy Experiment is Pointed mode observations.


The Microcontroller of the OBC On Board Computer is ARM7.


The Data Consumption of the EAN Connectivity System is 150 MB.


The Development Workshop of the UNISAT Satellite is 5th Annual CubeSat Developers' Workshop.


The Operational Date of the Scanning Sky Monitor (SSM) Payload is October 12th, 2015.


The Mission of the IOV (In-Orbit Verification) Payload Payload is Developing system capability for communications payloads on small geostationary satellites.


The Bandwidth of the MWR Radiometer is 1 GHz.


The Number of Gyroscopes of the SloshSat Satellite is 3.


The Launch Vehicle of the Aditya-L1 Satellite is PSLV-XL.


The Mission Design Life of the Spacecraft Bus (Avionics Module=AM) Bus is 12 months.


The Detector Temperature Range of the MSU-E Multispectral Scanner is -30 to -50ºC.


The LO Precision of the Satellite Device Unknown is 50 MHz.


The Location of the Pre-CHUVA Field Campaign is Alcântara Launching Center in northeastern Brazil.


The Platform Size of the Satellite Satellite is 2.26 m x 1.9 m x 2.53 m.


The Lifetime of the MTG-S satellite Satellite is Around 8.5 years.


The Data Access of the Twinkle Spaceborne Telescope is Exclusive access, via encrypted transfer, to the data within days of the observation.


The Data Set of the Gaia Satellite is Third.


The Error (RMS) of the Pitch momentum wheel Actuator is <0.001 mNms.


The Frequency L1 of the GPS receiver Receiver is 1575.42 MHz.


The Operator of the MANTIS Satellite is Open Cosmos.


The Unknown of the Argos-3 Data Collection and Location System is Unknown.


The Ion Composition of the Plasma Sheet Space Phenomenon is Mainly H.


The Frequency Range of Shaker Tests of the Boom Structure is 9-300 Hz.


The Air Pollution Observation of the GOSAT Satellite is December 2016.


The URL of the GPM Core Satellite is http://www.spaceflight101.com/gpm-core-mission-updates.html.


The Distance from Milky Way of the Andromeda Galaxy is 2.5 million light-years.


The Uplink Modulation of the Iris Radio Communication Device is BPSK.


The Primary Diameter of the Didymos Binary System is 780 m.


The Freeboard Definition of the A-68A Iceberg is The height of the ice above the sea surface.


The Repetition Rate of the Fixed Platforms Ground Segment is 200 seconds.


The On-Ground Postprocessing Requirements of the Satellite Spacecraft is < 5 cm 3D rms.


The URL of the SCD-2 Satellite is http://www.inpe.br/programas/mecb/ingl/satellite/scd2/scd2.htm.


The Product Specification Date of the Planet Imagery Satellite Imagery is April 2017.


The Application Date of the Sentinel-5P Satellite is 18 September 2020.


The Data Processing of the Delay/Doppler Altimeter Altimeter is Unknown.


The Launch Date of the Meteor-3-1 Satellite is 24.10.1985.


The Data Quantization of the AATSR Instrument is 12 bit.


The Temperature of the Infinity-shaped loop Gas and Dust Formation is 15 degrees above absolute zero.


The Debut Date of the Opti-SAR Satellite is Unknown.


The Resolution Δλ (0.05º slit) of the SPIM3 Spectrometer is 1.5 nm.


The Date of the Seroja Slams Australia Image is 13 April 2021.


The Cloud Albedo Measurement of the AIM Satellite is Yes.


The Location of the GPS patch antenna Antenna is Wake surface of the satellite.


The Volume of the Herley MD2000C-1 Transponder Module is 13.8 cm3.


The Mounting of the MFI Magnetometer is 12 m radial boom.


The Purpose of the FLexRX Flexible Receiver is In-orbit test, demonstration, and qualification of a product.


The Satellite Launch Date of the Capella Space And Rocket Lab Companies is Not Provided.


The Usage of the Tiny Ionospheric Photometer (TIP) Instrument is Not provided.


The Launch Date of the JL-1-GF03D Microsatellite is 03 July 2021.


The Pixel Pitch of the MS Bands Detector Line Arrays is 52 µm.


The Ovenized Crystal USO Stability of the DSAC Demonstration Unit is Between 1 – 100 seconds.


The Temperature Derivation Samples of the Instrument Spectrometer is 20 samples per spectrum.


The Developer of the Sentinel-5 Instrument is ESA.


The Mission Extension Period of the Aura spacecraft Satellite is Ongoing.


The Manufacturer of the CICERO-4 Satellite is Tyvak Nanosatellite Systems.


The Along-Track of the WAOSS-B Sensor is ±25°.


The Resolution of the Pleiades-1A Satellite is 50 cm.


The Tracking Targets of the Hexapod Tracking Device is Sun and Moon.


The Instruments of the Almaz-1B Satellite is 2 Ekor-A, a 4-band optical imager, etc..


The Output Power of the Instrument Power Unit Power Converter is 463 W.


The Required Precision of the O3 Profile Satellite Instrument is FT (ppbv).


The Heaters Addition of the Valves Spacecraft Component is Under Consideration.


The Imaging Modes of the SPOT satellite constellation Satellite Constellation is Multispectral and panchromatic.


The Individual Subchannel Data Rate of the Optical Downlink Communication System is 38.55Mbit/s.


The Launch Location of the Orbital ATK Launch Provider is Wallops Flight Facility in Virginia.


The Mass of the TechEdSat Satellite is 1.2 kg.


The SAR Payload Imaging Time of the RCM Satellite is 12 minutes per orbit.


The Interface of the Personal Computer Computer is USB.


The Inter-satellite Links of the Iridium PRIME Satellite Platform is 4.


The Client Mass of the ELSA-d Mission is ~17 kg.


The Effect on Pteropods of the Ocean Acidification Environmental Phenomenon is Shell damage has been observed.


The Attitude Control of the GFO Satellite is Three-axis stabilized.


The Debris Disk of the AU Microscopii Star is Yes.


The URL of the SIXS Spectrometer is http://www.cosmos.esa.int/web/bepicolombo/sixs.


The Required Spacecraft Stability of the Pushbroom Sensor is High.


The Energy Range of the GRS Gamma-Ray Spectrometer is 300 keV - 9 MeV.


The Date of the JAXA Earth Observation Missions Workshop is March 8, 2013.


The Global Coverage of the HARP-2 Polarimeter is 2 days.


The Pre-Flight Performance Characterization of the Medium-sized Aperture Camera Camera is Unknown.


The Frequency of the AltiKa Altimeter is 35.75 GHz.


The Launch Manifest of the Ariane Launch Vehicle is Unknown.


The Energy Measurement Range for Protons of the Telescope 2 Telescope is 0.8-4 MeV.


The Lunar Orbit Inclination of the Chang'e-1 Satellite is 90º.


The Project Management of the Communication subsystem Satellite Subsystem is Kagoshima University Soka University, Akita University.


The Scintillation Climatology Model of the C/NOFS Satellite is Improve scintillation climatology model.


The Data Processing Center Lead of the INCUS Satellite is Phil Partain.


The Mission Expansion Date of the Juno Spacecraft is 13 January 2021.


The Frequency Range of the APL’s Frontier radio Radio is Wide range of frequencies.


The Number of Radar Beams of the COSI SAR Mission is 50.


The Power of the Spacecraft 406 MHz Processor Processor is 33 W.


The Payload Mass of the Heinrich Hertz Satellite is 435 kg.


The Plasma Instrument of the Voyager 2 Spacecraft is Will provide the first-ever plasma measurements of the interstellar medium.


The Autonomy of the ESEX Satellite is Somewhat autonomous.


The Solar Cells of the GNB Satellite is Up to six triple-junction solar cells on each face.


The CubeSat Size of the MiRaTA Satellite is 3U.


The Accuracy of the CERES Instrument is 0.3 Wm -2  sr -1.


The Image Credit of the OMI Instrument is KNMI.


The Number of X-ray detector arrays of the IXPE observatory X-ray Observatory is 3.


The URL of the Emirates Mars Mission (Hope) Satellite is https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=EMM-HOPE.


The Interference filter - Wavelength of the Instrument Sensor is 777.4 nm.


The Utilization of the ICI-11 Radiometer is Quasi-window, cirrus clouds, cloud ice water path.


The Data Bus Speed of the Spacecraft Satellite is 1 Mbit/s.


The Ground Sampling Distance of the TET-1 Satellite is 160 m.


The Image Release Date of the Crab Nebula Nebula is May 10, 2017.


The Orbit Altitude of the Monitor-E Spacecraft is 540 km.


The Launch Date of the Kounotori Spacecraft is August 19, 2015.


The Orbit Determination Accuracy of the LEO Satellites Satellite is Sub-decimeter.


The Purpose of the Proposed Constellations Satellite Constellations is Enhance Arctic weather observations.


The Mass of the OceanSat-2 Satellite is 970 kg.


The Orbit Raise Rate of the LightSail-2 Spacecraft is Several hundred meters per day.


The Image Capture of the Worldview-4 Satellite is SpaceX's first stage.


The URL of the Shuttle Radar Topography Mission Satellite Mission is http://www.shuttlepresskit.com/sts-99/payload57.htm.


The Orbit Decay Time of the MicroMAS-1 Satellite is Within the required 25 year time period.


The Launch Mass of the Spacecraft Satellite is 2040 kg.


The Data Path of the Antenna System Communication System is Primary path for L1b data from WCDAS to NSOF.


The Wavelength Range of the Band No 6 Spectral Band is 11.5 ± 0.50 - 12.5 ± 0.50 µm.


The Fuel of the Propulsion System Satellite Component is Green monopropellant fuel blend based on ADN (Ammonium Dinitramide).


The Relevance of the MinXSS mission Satellite is NSF Division of Atmospheric and Geospace Sciences (AGS).


The Temperature of the Japan Current Ocean Current is High.


The Manufacturer of the COWVR Radiometer is NASA’s Jet Propulsion Laboratory.


The SWIR Off-nadir Resolution of the WorldView-3 Satellite is 4.1 m.


The Produces of the Services component Component is Information services in response to European policy priorities in environment and security.


The Number of Filter Windows of the Filter Wheel Optics Subsystem is 18.


The Printed Circuit Board Mass of the Sprite Tiny Spacecraft is A few grams.


The Impact Speed of the DART Spacecraft is Around 24,000 km/h.


The Power Consumption of the FLIR Boson camera Thermal Imaging Camera is Low.


The Bandwidth of the Dual-channel Receiver Unit (DRU) Receiver is Variable.


The Design and Test of the BRITE Constellation Space Telescope Telescope is Wide Field, High Resolution, Low Noise.


The Orbit Reconstruction Accuracy of the GBOT Ground Based Orbit Tracking is 150 m in position and 2.5 mm/s in motion.


The Attitude Determination of the BRITE spacecraft Satellite is 10 arcseconds.


The Moisture Sensors per Site of the Sensor Node Data Collection System is 3.


The Data Uses of the Aeolus Satellite is Predicting the weather, improving climate models, tracking events in near-realtime.


The Tracking Support of the ESA Organization is Essential to Chinese mission.


The Publication Date of the Cluster and Phoenix Missions Satellite Missions is 1997.


The Operating Hours of the Electric Thruster Thruster is More than 1000.


The Focus of the RECCAP-2 Satellite Mission is Global stocktake and tracking towards net zero emissions.


The Unknown of the SUSIM Experiment is Unknown.


The Number of Scientists and Engineers of the ASTRO-H Mission is 266.


The Instantaneous spectral coverage of the Spectrometer Instrument is 2.37 km/s.


The Installation of the MSPR-2 Rack is Already installed to Kibo.


The Launch Date of the Juno Spacecraft is Aug. 5, 2011.


The Active Temperature Control of the SVM Service Module is Heaters controlled by thermostats.


The Kapton Heaters of the Thermal Management Subsystem Thermal Management System is Multiple.


The Spectral Resolution of the FTS Interferometer Interferometer is <0.028, 0.056, 0.11, 0.55 cm -1.


The Operational Status of the Carbonite-2 Satellite is Operational.


The Operational Orbit Altitude of the OneWeb satellites Satellites is 1,200 km.


The Designers of the CHRIS Imaging Spectrometer is M. A. Cutter, D. R. Lobb.


The Antenna Composition of the SAOCOM-1A Satellite is 140 smaller antennas.


The Signal-to-Noise Ratio of the GOCI-II CMOS Imaging Sensor CMOS Imaging Sensor is Not provided.


The Years in Orbit of the Landsat 7 Satellite is 20 Years.


The Channels of the FCI Optical Imager is 16.


The Operating Modes of the SRAL SAR Radar Altimeter is Conventional radar-altimeter mode, advanced SAR mode.


The Launch Agency of the ERG (Arase) spacecraft Satellite is JAXA (Japan Aerospace Exploration Agency).


The Operational Status of the CDH and EPS subsystems Satellite Subsystems is Always ON.


The Topology of the Power Subsystem Subsystem is DET (Direct Energy Transfer).


The Purpose of the TDI Signal Processing Technique is Boosting object signal-to-noise ratio (SNR) by coherently adding the outputs of detectors aligned in the scan direction of the sensor.


The Launch Date to ISS of the Flock 1a Nanosatellites is January 9, 2014.


The Loss Date of the SEOSAT-Ingenio Satellite is 17 November 2020.


The Sampling Distance of the HIRS/4 Infrared Sounder is 18 km.


The Radiometric Linearity of the Telescope Optical Instrument is >95%.


The Temperature of the Verkhoyansk Town is 38°C.


The Development Status of the GeoXO Satellite System is In progress.


The Data Rate of the DUST sensor Cosmic Dust Sensor is 8 bit/s.


The Observation Date of the Herschel Space Observatory Space Observatory is September 24, 2018.


The Atomic Clock Panel Temperature Control of the Thermal Control Subsystem Thermal Control is Within 0.4º C.


The Solar Array Power of the UK-DMC-2 Satellite is 65 W at AM0 and 25ºC.


The Latency of the ATL04 Calibrated Backscatter Profiles Data is 21 days.


The Conference Date of the GPS Receivers Receiver is August 13-16 2007.


The Conference Presentation Date of the Imaging System Satellite System is Sept. 15-18, 2015.


The Spectral range of the MWRI Microwave Radiation Imager is 10.65-150 GHz.


The Execution Location of the Image acquisition and HSI calibration Task is Anywhere on the satellite orbit.


The Funding of the SPOT-6 Satellite is Government funding or pre-sales agreements.


The Ground Track of the Orbit Satellite Orbit is ± 2 km.


The Propellant of the Cold Gas System Attitude and Orbit Control Subsystem is Nitrogen.


The Conference Date of the CanX-4 & CanX-5 Nanosatellites is April 25-27, 2006.


The Stray Light of the GHGSat-D Satellite is Up to 5%.


The Proportional Control of the ADCS Attitude Determination and Control System is Magnetic field value or sun vector error.


The Ground Stations of the Colony I Satellite is Melbourne, Florida, and Fort Huachuca, Arizona.


The Downlink Frequency of the DRT Data Relay Transponder is 4506.05 MHz.


The Platform of the InnoSat Satellite is Mesospheric Tomography and Spectroscopy.


The Imaging Subject of the PROBA-V Satellite is Drakensberg mountains.


The Magnetic Field Tilt of the MGF Instrument is Up to 2º or 3º.


The Producing Team of the Visualization Product is Space Telescope Science Institute (STScI) in Baltimore, Maryland; the Caltech/IPAC in Pasadena, California; and the Center for Astrophysics, Harvard & Smithsonian (CfA) in Cambridge. Massachusetts.


The Operating Lifetime of the SPOT-6 Satellite is 10 years.


The Principle of Operation of the INMS sensor Ion Mass Spectrometer is Neutral particles are first ionized with compact thermionic filament ionizer. Post acceleration by voltage V gives all ions same energy E=qV, much greater than initial energy dispersions dE. Thus, the ions are ordered in velocity according to their mass o.


The Image Credit of the MODIS Instrument is NASA Earth Observatory image by Lauren Dauphin.


The Operational Autonomy of the COSMO-SkyMed spacecraft Satellite is 24 hours.


The Launch Time of the Iridium-5 Satellite Launch is 7:17 am PDT (14:17 UTC).


The Design Life of the SARAL spacecraft Satellite is 5 years.


The Uplink of the STRaND-1 Satellite is Not optimal during the first two weeks.


The Feedhorns of the MIS Instrument Microwave Radiometer is 12.


The Launch Date of the Göktürk-1 Satellite is 2015.


The Boom Length of the CHAMP Satellite is 4 m.


The Resolving Power of the O2 A-band channel Spectrometer is > 17,000.


The Heat Emission of the Magma Ocean Planets Planets is Enough to be observed with the next generation of infrared telescopes.


The Sensitivity of the NIRSpec MIRI Optical Instrument is 5000 nJy (21 μm, τ i =10,000 s, and λ/Δλ = 4.2).


The Experiment of the Toshiba Co. Organization is Vision data processing experiment.


The Size of the MSU-50 Camera is 210 x 200 x 140 mm.


The Neutrino Energy of the Glashow Resonance Phenomenon is 6.3 PeV.


The Mass of the SAGE-III Instrumentation is Unknown.


The Designers of the Small Satellite Platform Satellite Platform is F. Dannemann, M. Jetzschmann.


The Location of the Transponder Device is Australia.


The Return Date of the NRCSD CubeSat Deployer is Mid-September.


The Operators of the SAPPHIRE Satellite is Students at the USNA (US Naval Academy) and at SCU (Santa Clara University).


The Mission Unique Feature of the EQUULEUS Satellite is Measure the LIF at the far side of the moon from EML2 and control trajectory within the Sun-Earth-Moon region.


The Design of the Herschel Telescope Telescope is Classic Cassegrain with a 3.5 m primary mirror.


The AOCS of the MERLIN Satellite is Improved.


The Quote of the Ericson Unknown is “This mission will be looked at as the first mission of the opening of the second space age, where space travel became much more accessible to average men and women across the world,”.


The Launch Date of the STPSat-3 Satellite is November 20, 2013.


The Planned Trajectory Correction Maneuvers of the Juno spacecraft Spacecraft is 13.


The Size of the DART Spacecraft is About the size of a small car.


The Reentry Outcome of the InflateSail Satellite is Destroyed.


The Instrument Status of the GEDI Lidar is Operational.


The Objective of the PSat-2 CubeSat is Use a two way communications transponder for relaying remote telemetry, sensor and user data from remote environmental experiments or other data sources back to experimenters via a global network of internet linked volunteer ground stations.


The Attitude Controller Design Presentation Date of the IKAROS Solar Sail Demonstrator is July 20-22, 2010.


The Electrical Power of the STX-01 S-band Transmitter/Transceiver is 6 W.


The Publication Date of the Kappa Scheme Flare Prediction Method is July 31, 2020.


The Unknown of the JSS Multispectral Imagers Imaging System is Unknown.


The Measurement Types of the MSX/UVISI Instrument is Refraction and Extinction.


The Status of the Teledesic Program is Cancelled.


The Spatial Resolution of the CCD Camera Optical Device is 30 m.


The Apogee Motor Type of the Propulsion Subsystem Satellite is Bipropellant liquid.


The Orbit Type of the XMM-Newton Satellite is Highly eccentric.


The Data Quantization of the Visible Spectral Band Spectral Band is 6 bit.


The Modulation of the RF Communications Transmitter is BPSK.


The External RAM of the OBC Onboard Data Handling is 524 kB.


The Effective Area of the GMOD Detector is Function of off-axis angle and azimuth of the source GRB.


The Gas Storage Capability of the Propulsion System Satellite Component is Until it is used for thrusting.


The Instrument Power of the SEVIRI Imager is 123 W.


The Measurement Category of the SPOT-5 Satellite is Multi-purpose imagery (ocean), Multi-purpose imagery (land), Vegetation, Albedo and reflectance, Landscape topography, Sea ice cover, edge and thickness, Ice sheet topography.


The Location of the ISSAC SOC Space Operations Center is UND.


The Vertical Resolutions of the SciSat-1/ACE Satellite is One of the world’s highest.


The Cube Mass of the LISA Pathfinder Spacecraft is 2 kg.


The Purpose of the FIELDS Instrument is Measure electric and magnetic fields in the Sun's atmosphere.


The Orbit Type of the STARS spacecraft Satellite is Sun-synchronous near-circular orbit.


The Operation of the E-Sail Electric Solar Sail is Repelled charged plasmas found in space.


The URL of the Eutelsat Quantum Satellite is https://www.eutelsat.com/en/news.html#/blog_posts/four-things-you-should-know-about-eutelsat-quantum-69078.


The Offices of the EROS-B Satellite is Limassol, Cyprus, and in Tel Aviv, Israel.


The Sensitivity of the NIRSpec MIRI Optical Instrument is 3.1 x 10 -20  Wm -2  (22.5 µm, τ i =10,000 s, R=1200).


The Polarization of the Radar Radar is HH, VV, HV/VH.


The Primary Mirror Diameter of the WUPPE Spectrophotometer is 0.5 m.


The Band 3 of the R3 Sensor Sensor is CA.


The Sensitivity of the GMOD Detector is Simulated.


The Orbit Altitude of the Polar Scout 6U CubeSat Satellite is 575 km.


The Recording Date of the SEIS Seismometer is July 25, 2019.


The Pass Frequency of the Satellite Orbit Type is 16 passes per day.


The Imager Stabilization Requirement of the ExoplanetSat Satellite is Same fraction of a pixel.


The Detector Size of the DIAL Instrument LIDAR is 200 µm.


The Channels of the SEVIRI Imager is VIS 0.6 µm, VIS 0.8 µm, IR 1.6 µm, HRV (High Resolution Visible), IR 3.9 to IR 13.4 µm.


The CubeSat Structure Manufacturer of the Irazú CubeSat Satellite is Costa Rica.


The Function of the SGR-ReSI Interface Unit is Platform GNSS receiver.


The Dynamic Range of the Kodak KAI-11002 CCD CCD is 66 dB.


The Launch Date of the Genesis-2 Satellite is June 28, 2007.


The Mirror Angle of the SUNSAT Satellite is 45º.


The Quantity of the PMDs Polarization Measurement Device is 2.


The Propellant Status of the CanX-5 Satellite is Very large fraction remaining.


The Support Program of the Maritime AI-NAV Program is Navigation Innovation and Support Program (NAVISP).


The Unknown of the PMS Camera Camera is Unknown.


The Shaken but not disturbed of the Inertial Sensor Head Sensor is "Inertial Sensor Head shaken but not disturbed," ESA, Dec. 12, 2013.


The Output Energy of the InnoSlab amplifier Laser Amplifier is About 30 mJ.


The Function of the DLP Double Langmuir Probe is Surface cleaning.


The Launch Date of the Foton Spacecraft is May 31, 2005.


The Field of View Length of the Spectrometer Spectrometer is ~0.0146 radians.


The Advisory Group Call Date of the EarthCARE Mission is April 4, 2017.


The Hardware Modification of the TBIRD Satellite is Modified for the extreme environment of space.


The General Environmental Verification Specification of the Drag-free CubeSat Satellite is 14.1 g-rms for the lightest satellites.


The Development and Flight Results of the On-Board Computer Computer System is Unknown.


The Mission Duration of the OPAL Satellite is > 9 months.


The Publication Date of the High Altitude Observatory white-light coronagraph Coronagraph is April 1977.


The Celestial Sphere Coverage of the Telescope Optical Instrument is 39.7% at any given time.


The Orbit Altitude of the Secondary Payloads Satellite is ~410 km.


The Orbit Period of the ResourceSat-2A Satellite is 101.35 minutes.


The Transmission Rates of the TT&C subsystem Satellite Subsystem is Uplink: 4 kbit/s, Downlink: Up to 500 kbit/s.


The Development Status of the SMAP Satellite is Under development.


The Altitude Data Set of the GEOSAT Satellite is 5 cm orbits based on GRACE gravity model.


The Experiment Types of the OPS-SAT Satellite is Artificial Intelligence (AI), data compression, and even financial transactions.


The Orbit of the SkySat-16 to -18 Satellite is Sun-synchronous circular orbit with an altitude of 575 km, inclination of ~98º, LTDN (Local Time of Descending Node) of 10:30 hours.


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


The Avionics of the AstroSat-250 Satellite is Astrium AS250 new generation avionics.


The Type of the ACS Attitude Control Subsystem is Passive magnetic attitude control system.


The Surface Velocities of the Wilkins Ice Shelf Ice Shelf is 1994–96 and between 2006 and 2010.


The Control Systems of the ANUSat Satellite is Magnetic torquers.


The Location of the Avionics Stack Device is Below the laser.


The Previous Observations of the Lunar Flashlight Satellite is Surface reflectance variations measured by the LOLA 1064 nm laser altimeter and the ice-like reflectance spectra measured by M3.


The End of Life Date of the MTSAT Satellite is 31 Dec 2018.


The Coordination Responsibilities of the Executive Position is Coordination with EC and GSA, analysis of operational requirements, dissemination of joint information papers at IMO and IALA.


The Contract Value of the Northrop Grumman Company is $692 million.


The Launch Date of the Sentinel-5P Satellite is October 2017.


The Type of the COVE Payload Processor is Reconfigurable FPGA-Based.


The Publication Date of the Extreme UV spectroheliometer Spectroheliometer is April 1977.


The Coverage of the Satellite GEO (Geostationary Earth Orbit) is Not global: observes only one region of globe.


The Conference Date of the GMES-Sentinels System is April 25-30, 2010.


The Attitude Knowledge Error of the ADCS Attitude Determination & Control Subsystem is ≤ 29 µrad.


The Purpose of the IBEX Spacecraft is Examine how our heliosphere interacts with interstellar space.


The Resolution of the Photometer Optical Instrument is 26.52 arcsec/pixel.


The Ground Segment Chain of the Deimos-2 Satellite is Data processing chain.


The Power Consumption of the AIM Reconfigurable Computing Hardware Device is 1.5 to 5 W.


The Presentation Date of the Gravity Probe B Satellite is June 23-29, 1991.


The Battery Type of the UK-DMC-2 Satellite is Li-ion battery.


The Developer of the TEMPO Instrument is Ball Aerospace.


The Radiation Monitoring of the SPA-1 Dosimeter Dosimeter is Depletion mode, p-channel RADFET from REM.


The Mass of the NanoACE Satellite is 5.2 kg.


The Observation Wavelengths of the Herschel Satellite is 70 µm (blue), 160 µm (green) and 250 µm (red).


The Launch Date of the Meteor-M-2 Satellite is 08 Jul 2014.


The Type of the VISION Instrument is CubeSat optical payload.


The Commissioning Date of the PRISMA POD Facility is Fall of 2010.


The Dimensions of the RPU Receiver Processor Unit is 195 mm x 280 mm x 365 mm.


The Number of Stars Observed of the Kepler Telescope is Approximately 1,000.


The Launch Date of the Satellite Vu’s first satellite Satellite is June 2023.


The Number of Checkouts of the EDM Lander is Three.


The Planned Measurement Rate of the Claire Satellite is Double as of early 2017.


The Rotation of the Scan Assembly Assembly is 360º.


The Signal Bands of the BeiDou-3S Satellite is Legacy B1 signals, modernized signals in the L1, E5, and B3 band.


The Flyby Speed of the NEA Scout Solar Sail Technology Demonstration Spacecraft is Less than 100 feet [30 meters] per second.


The Location of the Gateway Outpost is Orbiting the Moon.


The End of Operations Date of the GEOS-1 Satellite is January 1968.


The Size of the EPS Electrical Power Subsystem is 96 x 90 x 20 mm.


The Deployment From of the DIWATA-1 Microsatellite is ISS Kibo.


The Solar Arrays of the EPS Electrical Power Subsystem is 6.


The Mission Type of the MOMS Satellite is EO.


The Behavior of the Interfaces Communication is Nominally.


The Noise Level at 1 Hz of the Field Measurement Device Sensor is ≤ 10 pT Hz -1/2.


The Monitoring Method of the Ocean Acidification Environmental Phenomenon is Satellites.


The Purpose of the WISPR Wide-field Imager for Solar Probe is Study the solar wind.


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


The Business Model of the Astrocast Satellite Manufacturer is Monthly subscription fee for every device connected.


The Sensor Types of the EO ASI Satellite is SAR and hyperspectral.


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


The Uplink Frequency of the Astrodev Lithium 2 Radio RF Communication Device is 449.75 MHz.


The Current Detection Range of the MGF Instrument is 0.1 µAm-2 or stronger.


The Data Rate of the Payload Downlink Communication System is 20 Mbit/s.


The Margin for Smear of the BAE Detector Detector is 473%.


The Payload of the SLS Rocket is Orion spacecraft, astronauts, and supplies.


The Swath Width of the ALOS-4 Satellite is 200 km.


The Mass of the UNISat-6 Microsatellite is 26 kg.


The Lunar gravity field detection of the Kaguya (SELENE) Satellite is Unknown.


The Maximum Electrical Power Production of the SAWs Solar Array Wings is 11.2 kW.


The Instrument Mass of the ERIP Earth Remote-Sensing Imaging Package is 1.80 kg.


The Platform Mass of the MERLIN Satellite is 260 kg.


The Temperature Stabilization of the UVNS Spectrometer is Better than 1oK during one orbit.


The Development Support Programs of the Galileo Second Generation Satellite System is ESA European Global Navigation Satellite System Evolutions Program (EGEP), EU's GNSS and Horizon 2020 HSNAV Programs.


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


The Components of the PIC Device is Back-illuminated scene, projector, lenslets, PIC interferometers, detector, thermoelectric phase modulators, Fast-Steering Mirror, three-row mask.


The First Data Release Date of the Solar Orbiter Satellite is September 30, 2020.


The RF Wideband Downlink of the QuickBird-2 Satellite is 320 Mbit/s.


The Period of the COMPASS-1 Satellite is 102 minutes.


The UHF Band Frequency of the RF Communications Communication Subsystem is 430 MHz.


The Design Basis of the OAP (Off-Axis Parabola) mirrors Optical System is COTS (Commercial Off-The-Shelf ) diamond-turned.


The Duty Cycle Reduction of the NEOSSat Satellite is Modest.


The Planned Launch Year of the ProSEDS Satellite is 2003.


The Attachment Method to Radiator of the Superelastic Springs Mechanical Component is Attached to the radiator with screws.


The Projected Quantity of the Artificial Objects Satellite is Double.


The Magnetic-Gravitational Stabilization and One-Axis Orientation System Mass of the Microsatellite Satellite is 2.7 kg.


The Dark Current of the Image Sensor Imaging is 4 e- /s/pixel.


The Components of the MCS Mission Control Software is Database and associated programs.


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


The Technology Types of the CFESat Satellite is Supercomputer, power supply, antennas, booms, launch-vehicle separation system, lithium-ion batteries.


The Grasp of the HaloSat Satellite is 26 cm2deg2.


The Payload Instruments of the Chibis-M Microsatellite is "Thunderstorm" and "Wave Package".


The OneWeb Business of the Hughes Company is More than $300 million.


The Prime Contractor of the CHEOPS Satellite is Airbus in Spain.


The Temperature Range of the ANUSat Satellite is 10º C – 30º C.


The Spin Axis Tilt Angle of the Cluster spacecraft Satellite is 45º.


The Speed of the Rosetta Spacecraft is 8.6 km/s.


The Operating Status of the SMOS mission Satellite Mission is Nominally.


The Mass of the Monitor-E Spacecraft is 700 kg.


The Communication of the GPM Core Satellite is S-band RF.


The Launch Mass of the Resurs-DK1 Spacecraft is about 6570 kg.


The Launch Site of the SkySat-16 to -18 Satellite is Cape Canaveral.


The Function of the Housekeeping Computer On Board Computer is Responsible for communications with the ground station and collecting satellite telemetry.


The Spectrum of the Lightspeed Satellite Constellation is Ka-band.


The Capability of the LRO Mini-RF Transmitter Transmitter is Dual-band.


The Session of the "Report of the Committee on the Peaceful Uses of Outer Space Report is Sixty-second.


The Radius of the Ground Station Coverage Ground Station is 2000 km.


The Observation Time of the Tycho Supernova Remnant is More than four centuries.


The Mass of the Deimos-2 Satellite is 300 kg.


The Spatial Resolution at Nadir of the Imager Imaging System is 0.46 m GSD.


The Scheduled Lift Off of the EM-1 Exploration Mission-1 is November 2018.


The Eruption Date of the Calbuco volcano Volcano is April 22, 2015.


The Minimum Relative Distance of the CNAPS Propulsion System is 50 m.


The Operation Environment of the Frontier Radio Telecommunications System is Very harsh environment.


The Continuum Spectrum of the GRS 1915+105 X-ray Binary with a Black Hole is Figure 6.


The Data Rate of the TDI Detector Detector is 700 Mbit/s per detector.


The Year of the CryoVEx Campaign is 2003.


The Size of the CubeSats Satellite is About the size of a boot box.


The Constellation Size of the Kleos Space S.A. Company is Up to 20 clusters.


The Size of the LCT instrument Instrument is 0.6 m x 0.6 m x 0.7 m.


The f/Number of the Custom design lens Lens is f/5.


The Planned Quantity of the Touch Downs/Sample Collections Maneuver is Three.


The Designer of the Driver on/off IC Component is Santa Maria Design House.


The Operation Duration of the m-NLP system Langmuir Probe System is 10 years.


The Telemetry Data of the Hitomi Satellite is Not Received.


The Update Date of the Juno Spacecraft is 11 December 2020.


The Orbit Altitude of the GeoCARB Satellite is Approximately 35,786 km above the equator.


The Number of Maneuvers of the SkySat-3 Satellite is 13.


The Design Hypothesis of the Geometric Calibration System Calibration System is Thermoelastic distortions change slowly, smoothly and not a lot.


The Retargeting Frequency of the Platform Satellite is Twice per orbit.


The Phase B of the SMOS Satellite is 2002.


The Spectrum Observation of the CubeRRT Satellite is 1 GHz wide portion of the electromagnetic spectrum.


The Orbit Parameters of the GEOS-3 Satellite is 816 km x 850 km x 115.0º.


The Swath Width of the RM-08 Passive Microwave Scanning Radiometer is 550 km.


The Antenna Version of the BlackJack GPS Instrument is 4-antenna.


The Suitability of the DarkCarb Mission is Well suited.


The Temporal Resolution of the EIS Sensor is 30 s.


The Objective of the Slew Mode Satellite Mode is Slew the satellite from its arbitrary attitude after detumble into an attitude where the correct body panel is nadir-pointing and the satellite is oriented correctly along-track.


The Prime Contractor of the Swarm Spacecraft Satellite is EADS Astrium GmbH, Friedrichshafen, Germany.


The Form Factor of the Ubotica CogniSAT-XE1TM CubeSat Board Satellite Device is PC/104.


The Launch Date of the Sentinel-1B Satellite is April 25, 2016.


The Closure Reason of the Factory Facility is Pandemic.


The Location of the Ground Station Ground Station is Panska Ves (Czech Republic).


The End of Life Date of the NigeriaSat-X Satellite is 31 Dec 2021.


The Mission Purpose of the Tandem-L Satellite is Climate research and environmental monitoring.


The Presentation Date of the Small Satellites Satellite is Oct. 2-6, 2006.


The Launch Date of the RapidEye Earth Observation Constellation is August 2008.


The | of the P. Jonathan Gero 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 Launch Mass of the CartoSat-2D Satellite is 714 kg.


The Array of the Spacecraft Satellite is 3 panel/Si with GaAs/articulating/5.25 m.


The Purpose of the GOCE Satellite is Measure the pull of Earth's gravity.


The Packaging Weight of the MRM Magnetometer is 1.6 kg.


The Sensor complement / remarks of the Meteor-3-1 Satellite is MR-2000M, MR-900B, IR, SM, RMK-2.


The Measurement Capabilities of the ALADIN Instrument is Cloud characteristics, aerosol measurements, cloud top height, cloud cover, cloud and aerosol extinction and optical thickness, multi-layer clouds identification, lower troposphere aerosol stratification, height of the tropopause, height of the PBL.


The Unique Capability of the Gaia Satellite Mission is Performing the most precise astrometric survey ever realized.


The Subsystem of the NanoSail-D2 Satellite is Sail.


The Spectral Range of the TIR Thermal Infrared region is 8.4-8.5, 10.3-11.3, 11.5-12.5 µm.


The Observation Mode of the IXPE Satellite is Pointed viewing of known X-ray sources.


The Status of the RESOURCESAT-2 Satellite is Functioning Satisfactorily.


The Role of the MONTE Software is Independent check of GIPSY-OASIS results.


The Detector Array Temperature of the LWIR Camera Camera is 65 K.


The Deployment Services Start Date of the NanoRacks LLC Company is October 2012.


The Attitude Stabilization Method of the NanoSail-D2 Satellite is Passive attitude stabilization of the spacecraft will be achieved using permanent magnets to detumble and orient the body with the magnetic field lines and then rely on atmospheric drag to passively stabilize the sailcraft in an essentially maximum drag a.


The Publication Date of the S056 X-ray telescope X-ray Telescope is April 1977.


The Instrument Size of the Imager Imaging System is 3 m tall.


The Ratio of the Aperture Function Image Processing is D/a.


The Functionality of the Software Control System is Object recognition, satellite alignment, fine pointing, target recognition, stage recognition, image capture, image transmission, attitude acquisition.


The Purpose of the ETB Electronics Test Bed is Evaluate and demonstrate a number of new electronic components, processors, and memory devices.


The Initiation Connector of the CSD Satellite Component is Unknown.


The Processing Mode of the SAR Processor Data Processor is Complete processing for the trigger application and possibly repeated processing for other applications.


The Radio Link Testing Distance of the GomX-4A and GomX-4B Satellites is Up to 750 km.


The Use of the Thermal Waveband Imaging System is Track cold clouds in the upper atmosphere as well as forest fires on the Earth's surface.


The Spectral Band of the Infrared Channel is approx. 3.6 km at nadir.


The Duration of the OSCAR-QUBE Experiment is 8 months.


The Third Full Data Release (DR3) Date of the Gaia Satellite is 13 June.


The Spectral Resolution of the Instrument Sensor is Better than 0.01Å (resolving power 105).


The Stabilization of the Spacecraft Satellite is 3-axis.


The Article Date of the Lunar Reconnaissance Orbiter Spacecraft is 11 February 2021.


The Closest Approach Distance of the Rosetta Spacecraft is 800 km.


The Funds Raised of the Inspiration4 Mission is $29.2 million.


The Software Glitches of the Starliner Spacecraft is Major software error, communications dropouts, another software mistake.


The Launch Date of the Falcon 9 Rocket is February 4, 2021.


The Effective Area at 80 nm of the EUV Simulation Simulation is 6 cm2.


The Sensitivity of the LISA Space Observatory is Lower frequency than LIGO.


The Components of the Coronagraph Instrument is Four coaxial occulting discs and photodetectors.


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


The Responsible Teams of the ADCS Attitude Determination and Control Subsystem is Mission Operations (health monitoring and reporting), ADCS team (performance maintenance).


The FOV of the SXI Spacecraft is 42 arc min x 42 arcmin.


The Frequency of the IGOR GPS receiver GPS Receiver is Dual.


The User Locations of the OUFTI-1 Satellite is Must be within the footprint of the satellite.


The Field of View (FOV) of the Genesis Ion Monitor Instrument is 26º starting along the spin axis by about 3º in azimuth.


The Temperature of the SWAP Imager is One million degrees.


The EEPROM Capacity of the RAD750 SBC Single Board Computer is 4 MB.


The Pixels per Line of the CCDs Detector is 740.


The Measurement Category of the ST5 Satellite is Atmospheric Temperature Fields, Gravity, Magnetic and Geodynamic measurements, Atmospheric Humidity Fields, Atmospheric Winds.


The Power of the DUST sensor Cosmic Dust Sensor is 2.2 W.


The Band of the SWIM Instrument Radar is Ku-band.


The Swath Width of the Antenna Conically-scanning reflector is 1000 km.


The Mass of the GCOM-W1 Satellite is About 1991 kg at launch.


The Detector Telescope Head of the DOSTEL Radiation Detector is Two PIPS detectors and one PIN diode.


The CCD Detector Temperature of the MEGS Spectrograph is -100º C.


The Observation Date of the Lake Okeechobee Lake is July 3, 2022.


The Construction Completion of the Emergency Egress System Safety System is TBD.


The Data Rates (TM) of the EWC31 S-band transceiver module Communication Module is 10 kbit/s to 1 Mbit/s.


The Mass of the Instrument Spectrometer is 9.4 kg.


The Power Source of the EAGLE ESPAStar Satellite is 96 Ahr battery.


The Orbit Inclination of the GPM Core spacecraft Satellite is 65º.


The Operational Lifetime of the MicroMAS-1 Satellite is One year.


The Components of the TM Thermal Calibration System Calibration System is Single onboard cavity blackbody, black, highly emissive shutter, toroidal mirror, thermistors.


The Number of Experiments of the OPS-SAT Satellite is Over 100.


The Purpose of the WIND Satellite is Measure the plasma and fields around the spacecraft, including energetic particles and radio waves.


The Presentation Date of the 3MI Instrument is October 16, 2013.


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


The Expected End of Operations of the MICROSCOPE Satellite is Autumn 2018.


The Battery Temperature of the SpriteSat Satellite is Can go up to a critical level.


The Phase Angle of the JL-1-GF03B Microsatellite is 60º.


The Payloads of the FY-3E Satellite is Microwave and infrared sounders, instrument to derive atmospheric conditions and ocean winds, spectral imager.


The Purpose of the RAVAN Satellite is Measure Earth outgoing radiation.


The Number of Additional Containers of the BepiColombo Spacecraft is 15.


The Panel 5 Function of the CSTB1 Satellite is Payload panel.


The Launch Date of the SpaceX Falcon-9 Rocket is Jan. 14, 2017.


The Observation Date of the Wilkins Ice Shelf Ice Shelf is Dec. 1, 2016.


The Altitude at Launch of the GRACE Satellite Satellite is 485 km.


The Presentation Date of the GNSS Reflectometry Instrument Instrument is Sept 18-20, 2012.


The Position Accuracy (RMS orbit) of the S-2 NRT Product is < 10 m (2D) 3-sigma.


The Start Date of the ELFIN Satellite is 2012.


The URL of the AAUSat3 Satellite is http://www.space.aau.dk/aausat3/index.php?n=Tech.AAUSAT3InDetails.


The Orbital Period of the MPO Spacecraft is 2.3 hours.


The Image of the Day Date of the NASA Earth Observatory Satellite is 17 May 2022.


The Swath Width of the Instrument Satellite Instrument is 17.5 km (half mode).


The Destination of the MoonLIGHT Satellite is Reiner Gamma region of the Moon.


The Storage Capacity of the PDHT Payload Data Handling and Transmission is 1410 Gbit.