The Orbital period of the Satellite GEO (Geostationary Earth Orbit) is 24 hours.


The Launch Preparations Date of the Mission Extension Vehicle Satellite is 30 June 2020.


The Brightness Comparison of the Newly Detected Source Object is More than 1000 times fainter than Beta Pictoris.


The Challenges of the ADCS Attitude Determination and Control Subsystem is Calibrating and monitoring this subsystem across a large constellation, complexities introduced by distributed launches and multiple hardware revisions, resource constraints.


The Communication Mode of the LLITED satellites Satellite is Receive only.


The Purpose of the TRISHNA Satellite is Climate monitoring and operational applications.


The Measurement Range of the OCI Ocean Color Instrument is Ultraviolet to the shortwave infrared.


The Launch Date Risk of the ORS-6 Satellite Mission is Adds risk to the program.


The Size of the LinkSprite JPEG color VGA camera Camera is 32 mm x32 mm.


The Mission Start Date of the EURECA Satellite is August 7, 1992.


The Location of the Ground Segment Ground Station is Roof of the research lab IES (Institut d'Electronique du Sud) building located on the campus of UM2 (University Montpellier 2).


The Justification of the ACE Satellite is Providing context and supporting data to nearly all other solar, heliosphere, magnetosphere, and ionosphere/thermosphere missions both current and planned.


The Operation Principle of the Gyro Unit Attitude Control is Electrically-excited vibration of a solid cylindrical element.


The Satellite Bus of the JPSS Joint Polar Satellite System is "NPP-like".


The Daily Deep-Space Observations of the SBSS-1 Satellite System is 12,000.


The Observation Results of the Herschel Space Observatory is Intricate network of gas filaments and dark bubbles interspersed by bright hotspots.


The Quantity of the FIREBIRD-I CubeSats is 2.


The Critical Design Review Date of the Instrument Satellite Instrument is Early 2020.


The Apogee Alignment of the THEMIS Satellite is Opposing.


The Mission Lifetime of the CHIPSat Satellite is One year.


The Data Rate of the Scanning geometry Instrument is 660 kbit/s.


The Detector Array of the WiFS camera Camera is 2 x 2048 pixels.


The Detectors of the Visible Spectral Band Spectral Band is Si photodiode.


The Image Telemetry Link of the SPOT-1 Satellite is 50 Mbit/s at 8 GHz.


The Bandwidth of the SWIM Instrument Radar is 320 MHz.


The Calibration of the Scanning Optical Thermopile Calibration Device is NIST-traceable.


The Stowed Configuration Size of the KaRIN Instrument is 3.0 m x 2.8 m x 2.8 m.


The Function of the TSCT Terminal is Allows users to have a real-time interface to the TripleSat constellation database, realizing the enquiry of the data catalog, and purchase of data products online.


The Image Size of the CIPS Instrument is 1440 km x 960 km.


The Performance Characterization of the EarthCARE BBR Detectors Instrument is Unknown.


The Modulation of the RF Communications Transmitter is FSK.


The Number of Images of the SPOT-6 Satellite is More than 100 million km2.


The Field of View of the Lens Optical Instrument is 24º x 24º.


The Duty Cycle of the HPA High Power Amplifier is 12%.


The URL of the Radiation Belt Storm Probes Satellite is http://vanallenprobes.jhuapl.edu/common/content/pdfs/VanAllenProbes_FS_Press.pdf.


The Spectral Range (µm) of the Band 8 Spectral Band is 0.48 - 0.53.


The Source Data Rate per Band of the MSU-100 Camera is 9.8 Mbit/s.


The Previous Catalogue of the Gaia Catalogue of Nearby Stars Stellar Census is Gliese Catalogue of Nearby stars.


The AI Model Testing of the Φsat-2 Satellite is Run on generic GPU, Tested in targeted hardware Intel® Movidius™ Myriad™ 2 on Neural Compute Stick with OpenVINO (2020.3), Tested with FlatSat in real configuration.


The Pointing Accuracy of the NEMO-HD Satellite is 1.5 arcmin.


The Data Rate of the S-band Uplink Communication System is 9.6 kbit/s.


The Launch Date of the Satellite Vu’s second satellite Satellite is Early 2024.


The Spectral Range of the 1.61 and 2.06 µm CO2 channel Spectrometer is 1.594 to 1.619 µm and 2.042 to 2.082 µm.


The Per spacecraft mass of the WorldView-4 Satellite is 2500 kg.


The Communication System of the TanDEM-X Satellite is S-band receiver.


The Latitude Coverage of the LIS Lightning Image Sensor is ±54.33º.


The Body Size of the M1S/M2S Satellite is 2.0 m x 2.5 m x 3.6 m.


The SAR Constellation Frequency of the Spacety Company is Day and night.


The Platform of the Heinrich-Hertz satellite Satellite is SmallGEO (SGEO).


The Orbit Altitude of the GOMX-1 Nanosatellite is 600 km.


The Type of the MLS Instrument is Microwave radiometer.


The Purpose of the High-Resolution Video Camera Camera is Zoom in on the actual target of interest.


The URL of the Swarm Mission is https://earth.esa.int/c/document_library/get_file?folderId=131556&name=DLFE-3101.pdf.


The Measurement Domain of the SARAL Satellite is Atmosphere, Ocean.


The Propulsion System Commissioning Date of the PRISMA Satellites Satellite is June 24, 2010.


The Launch Date of the SRL-1 (STS-59) Mission is April 9, 1994.


The Purpose of the EPS GRAS Mission is Operational GPS Meteorology.


The Bus Dimensions of the Helios-2 satellites Satellite is 3.4 m x 3.1 m x 6 m.


The Start Date of the Methane Leak Environmental Event is 4 July 2020.


The Type of the Spectrograph Instrument is Rowland Circle style imaging spectrograph.


The Secretariat Location of the Joint Project Team (JPT) Project Team is JAXA.


The Scanning Technique of the PRISM-2 Instrument is Pushbroom.


The Pages of the Lunar Flashlight Satellite is 58–69.


The Data Link Speed of the CMS Instrument is 4 Mbit/s.


The Function of the TTC Rx Receiver is Acquire the residual carrier from the ground station and extract the 16 kHz subcarrier for the telecommand demodulator inside the CCSDS processor.


The Intersatellite Link Frequency of the Communication Communication System is S-band.


The Deployment Rounds of the NanoRacks CubeSat Deployer is 3.


The Size of the Instrument Device is 9.7 cm x 9.7 cm x 4.8 cm.


The Funding of the NorSat-3 Satellite is Norwegian Ministry of Defence.


The Wavelength Range of the S3 Spectrophotometer is 300-800 nm.


The Spatial Resolution of the TanDEM-X Satellite is 0.4 arcseconds (12 m at the equator).


The Power Consumption of the LISS-3 Camera is 70 W.


The Imaging Resolution of the Resurs-DK1 Earth Observation Satellite is 1 m.


The Forecast Duration of the HWRF Model is 120 hours.


The URL of the Can ripples on the sun help predict solar flares? News Article is https://news.berkeley.edu/2020/09/21/can-ripples-on-the-sun-help-predict-solar-flares/.


The Number of Flight Models of the MWI Instrument Instrument is Three.


The Location of the Margarita Island Landmark is Venezuela.


The Orbit of the CSG and CSK satellites Satellite is Circular sun-synchronous.


The Launch Date of the Tsubame Microsatellite is November 6, 2014.


The Instruments of the CFOSAT Satellite is SWIM (Surface Waves Investigation and Monitoring), SCAT.


The Contract Value of the ICON Satellite is $50 Million.


The Exceeded Design Life of the Jason-2 Satellite is Yes.


The Mission Design Life of the ADEOS spacecraft Satellite is 3 years.


The Spectral Bands of the Satellite Satellite is Panchromatic band, 4 MS (Multispectral) bands Pan B, G, R and NIR.


The Li-ion Battery Capacity of the EPS Electrical Power Subsystem is 30 Ah.


The Interface of the Tertiary Collimator Assembly Assembly is Optically and mechanically interfaces with the FOA.


The Mission Objective of the RADARSAT-1 Satellite is Monitor environmental change and the planet's natural resources.


The Announcement Date of the Thales Alenia Space Ground Station Builder is 9 October 2018.


The System Dynamic Range of the PMC-2 Imagers Imaging System is 20~800 DN.


The Actual Orbit Duration of the ESEO Satellite is Almost two years.


The ROM of the Model calculator Data Handling and Processing is 64kB.


The Maximum Mass of the O/OREOS nanosatellite Satellite is 5.5 kg.


The Servicing Concept of the Bartolomeo Platform Satellite Platform is Fully robotically serviceable.


The Function of the NICER Instrument is Measure light echoes.


The Re-Entry Date of the GRACE 1 Satellite is 11 March 2018.


The Meeting Date of the HY-1B Satellite is Feb. 12-14, 2008.


The Imaging Satellite of the KazEOSat-2 Satellite is Medium resolution.


The Sensor of the WorldView-3 Satellite is CAVIS.


The Bandwidth of the Channel 6 Sensor is 1000 MHz.


The Data Quantization of the Hyperion Imaging Spectrometer is 12 bit.


The Attitude Control Time of the PSSCT-2 Satellite is Two months.


The Data Rate of the Data Flow System is 2.2 Gbit/day.


The Radius of the Spacecraft Satellite is 21 cm.


The Image Acquisition Date of the NOAA-20 Satellite is June 5.


The First Flight Date of the TOMS Total Ozone Mapping Spectrometer is Oct. 24, 1978.


The Daily Acquisition Capacity of the Pléiades Neo Satellite is More than double.


The Control Node Locations of the GeneSat-1 Satellite is Multi-Mission Operations Center (MMOC) at NASA/ARC, SCU Robotic Control Center located in the NASA Research Park in Moffett Field, GeneSat-1 operations development and training laboratory on the SCU campus, SRI communication station.


The Manufacturer of the CHIPSat Satellite is SpaceDev, Inc..


The Operational Date of the MaSat-1 CubeSat is Feb. 2014.


The Entrance Slits Alignment of the OCO Instrument Spectrometer is Co-aligned.


The Period of the NEMO-AM Satellite is 97.4 minutes.


The Data Collection Duration of the GPM Satellite is Last 19 years.


The Mission Status of the ERS-2 Satellite is Unknown.


The Operation Start Date of the Tatiana-2 Satellite is Sept. 20, 2009.


The ACNS Units of the PROBA-2 Satellite is 4 reaction wheels, 2 magnetometers, a miniaturised µASC star tracker with two hot-redundant camera heads and cold-redundant DPUs, a cold redundant GPS receiver, and internally redundant magnetotorquers.


The Forward Used Angle of the Scan Assembly Assembly is 110º.


The Components of the TAMU MEMS Technology Demonstration Package is 8051 microcontrollers, 4 Mbit Magnetic RAM, and CAN-bus interface.


The Lighting Conditions of the Site Nightingale Crater is Create additional challenges for spacecraft navigation.


The Observation Type of the RHESSI Satellite is CME ejection.


The Objective of the Variant Satellite is Investigation of the lithosphere-atmosphere-ionosphere-magnetosphere coupling.


The Image Capture Date of the Sentinel-2 Satellite is 20 January 2022.


The Number of Observations of the XMM-Newton X-ray Satellite is 1,789.


The Band of the Transceivers Communication Device is DSSS 2.4 GHz.


The Preferred Location of the TEMPO Instrument is 90-110º W.


The Spatial Frequency of the Collecting Optics Lens Assembly is 70 l/mm.


The System of the Onboard Propulsion System Propulsion System is Split into two modular units.


The Pre-launch Performance of the VIIRS Instrument is Unknown.


The Payload Mass of the Eutelsat 172B Satellite is 10,865 kg.


The Positioning Accuracy of the Lunar Pathfinder's Receiver Satellite Receiver is Around 100 m.


The Lifetime Mechanism of the SWIM RMA Antenna is Unknown.


The Mission Analysis of the COSMOS Mission Operations System is Analysis and trending of spacecraft and ground network SOH data, orbital and trajectory data, and mission accomplishment data.


The Transmit Bandwidth of the Radar Instrument is 1 MHz.


The URL of the OSIRIS-REx Spacecraft is http://www.spacedaily.com/reports/OSIRIS_REx_cruising_towards_rendezvous_with_Asteroid_Bennu_999.html.


The Attitude Knowledge of the STPSat-1 Satellite is 0.03º.


The Movement of the SS 433 Cosmic Object is Wobbles on its axis - precession.


The Compression Algorithm Ratio of the Camera Imaging Device is 3.2 : 1.


The Magnetic Waves Discovery Date of the Swarm Satellite Constellation is 23 May 2022.


The Data Rates of the STAFF/DWP Instrument is 1.024 kbit/s, or 4.627 kbit/s.


The Affiliated Organizations of the InSight Lander Lander is NASA, German Aerospace Center (DLR).


The Launch Date of the Mey-Lin (C6) Satellite is 15th April.


The Satellite Launch of the AMSU Microwave Radiometer is NOAA-15.


The UV Spectral Range / Bandwidth of the SOLSPEC-SOLAR Spectrometer is 165-370/1.2.


The Beta Test of the Starlink Satellite Constellation is Ongoing.


The Mission Life of the Telescope Optical Instrument is Commissioning in < 6 months.


The Amplifier Technology of the TEMPEST-D Satellite is High-frequency microwave.


The Date of the Winter in the Appalachians Image is 25 February 2022.


The Date of the Flooding in Eastern Australia Image is 11 April 2022.


The Modification of the OCO-2 Instrument Optical Bench Assembly Process is Implemented.


The First Measurements Date of the Solar Orbiter Satellite is February 17, 2020.


The Mission Status of the Solar-B / Hinode Satellite is Unknown.


The Inclination of the WV-1 Satellite is 97.2°.


The Number of Pixels of the Optics and detector assembly Assembly is 900.


The CCD Detector Light-Sensitive Areas of the DNB Spectral Band is 4.


The URL of the Mars Terrain Simulator Simulator is https://iafastro.directory/iac/proceedings/IAC-18/IAC-18/B6/3/manuscripts/IAC-18,B6,3,5,x42837.pdf.


The Number of Asteroids of the Gaia Satellite is 150,000.


The Manufacturer of the Accelerometer Sensor is Analog Devices.


The Ka-band System of the STPSat-6 Satellite is Receive up to 64 Mbit/s.


The Launch Date of the TacSat-4 Satellite is Unknown.


The Antenna Aperture of the XPAA Phased Array Antenna is 8 x 8 array of modules.


The Battery Capacity of the UK-DMC-2 Satellite is 15 Ah.


The Pixels per FWHM of the Spectrometer Instrument is 1340.


The Mass of the Receiver Communication Device is 200 g.


The Components of the iADCS100 Attitude Determination and Control System is ST200 star tracker, RW200-series of reaction wheels, MTQ200 series of magnetorquers.


The Purpose of the TRISHNA Satellite is Increasing understanding of ecosystem stress and water use, coastal and inland waters, urban microclimate monitoring, solid earth, the cryosphere, and the atmosphere.


The Image Credit of the Vikram Lander Lander is NASA/Goddard/Arizona State University.


The ACE News No 165, Dec. 2, 2013 of the Weakest Solar Wind of the Space Age Solar Wind Event is URL: http://www.srl.caltech.edu/ACE/ACENews_curr.html.


The Application of the RISAT-2 Satellite is Earth observation.


The Measurement Domain of the IMAGE Satellite is Atmosphere.


The Power Supply Voltage of the Big Apple board Electronic Board is 5 V.


The Telemetry Downlink Rate of the SGLS Link Communication System is 32 kbit/s.


The Partnership of the LOFTID Project is NASA's Space Technology Mission Directorate and United Launch Alliance (ULA).


The Field of Research of the Parker Solar Probe Spacecraft is Heliophysics.


The | of the Anna MariaMassone Author is Anna MariaMassone.


The Resolution of the MI Meteorological Imager is 500 m.


The Sampling Duration of the CREAM Cosmic-Ray Instrument is At least three years.


The Design Lifetime of the Jason-3 Satellite is 5 years.


The Pixels per FWHM of the Spectrometer Instrument is 1420.


The Creation Technique of the Synthetic Galaxy Catalog Data is Halo Occupation Distribution technique.


The Objective of the MSS Multispectral Scanner is Provide repetitive daytime acquisition of high-resolution, multispectral data of the Earth's surface on a global basis and to demonstrate that remote sensing from space is a feasible and practical approach to efficient management of the earth's resources.


The Number of Scintillating Fibers of the Imaging Calorimeter Calorimeter is 448.


The Data Provided of the REPT Instrument is Energy bins, pulse heights, space weather packets, housekeeping telemetry.


The Spatial Resolution of the HXR Flare Ribbons Solar Phenomenon is ~2 arcsec.


The ADC Resolution of the SEVIRI Spectral Imager is 12 bit.


The Swath Width of the SPOT 1-5 Satellite is 60 km.


The Managing Organization of the Solar Probe Cup (SPC) Instrument is SAO (Smithsonian Astrophysical Observatory).


The Additional Mode of the EPI-Lo Electron Detector is Requires a Start pulse along with the SSD pulse.


The Solar Power of the PARASOL microsatellite Satellite is 180 W.


The Vector Components Stability of the Magnetic Field In-Situ Sensor is Better than 1 nT/year.


The URL of the SpaceX CRS-2 Mission Mission is http://www.spacex.com/downloads/crs2-press-kit.pdf.


The Architecture of the COSMOS Software System is Provides a number of software tools to serve well defined operational roles and applications.


The Mission Data Downlink of the QSat Satellite is Ku-band, 30 Mbit/s.


The Discovery Year of the LINEAR Project is 1999.


The Purpose of the Heat Transfer Host Experiment is Investigate convection and heat transfer through air and liquids.


The Mass of the HXT-C X-ray Optics is 13.5 kg.


The Secondary Mission Goal of the GOSAT Satellite is Thermal infrared observation.


The Angle of the Satellite Slew Satellite Maneuver is 30º.


The Cargo Delivery of the Starliner Spacecraft is 500 pounds.


The Spectral Sampling Interval of the VNIR Spectrometer Spectrometer is 6.5 nm.


The Celestial Sphere Coverage of the Telescope Optical Instrument is 100% of sphere has at least 51 contiguous days visibility.


The Baud Rate of the Science Data Interface Interface is 1 Mbit/s.


The Conference Presentation of the SPIDER Imaging System is Katherine Badham, Alan Duncan, Richard L. Kendrick, Danielle Wuchenich, Chad Ogden, Guy Chriqui, Samuel T. Thurman, Tiehui Su, Weicheng Lai, Jaeyi Chun, Siwei Li, Guangyao Liu, S. J. B. Yoo.


The Goal of the IRAS project Technology is Reduce manufacturing costs for satellites by using commercial components.


The Launch Status of the TROPICS cubesats Satellite is Failed.


The Mission Type of the COMS Satellite is EO.


The Launch Date of the Copernicus Sentinel-6 Michael Freilich Satellite is 10 November.


The Mass of the COSMO-SkyMed spacecraft Satellite is 1700 kg.


The Spatial Resolution of the SeaHawk-1 CubeSat is 130 meters.


The SNR of the Spacecraft Satellite is > 100:1.


The Mass of the CE-SAT-1 Microsatellite is 50 kg.


The Grating Frequency of the HSC Spectrometer Spectrometer is 30 lines/mm.


The Mass of the Integrated Sensor Sensor is ~ 4 g.


The Design Hypothesis of the Geometric Calibration System Calibration System is Change across the swath can be modelled with 8th order polynomials.


The Application of the FY-3 (FengYun-3) Satellite is Atmosphere.


The Start Time of the Quasi-Halo Orbits Orbit is 2020 August 30 00:00:00.00 dynamical barycentric time (TDB).


The Number of CIR Photographs of the Metric Camera Camera is 546.


The Attitude Pointing Knowledge of the QuickBird-2 Satellite is ±0.0008o (3? steady state in all three axes).


The Location of the SAGE-III Instrument is International Space Station's ExPRESS Logistics Carrier platform.


The Partnership of the Unicorn-1 PocketQube is European Space Agency (ESA).


The Mission Management of the OSIRIS-REx Spacecraft is Goddard.


The Input Voltage of the LVPS Board Power Supply is 26 - 29 V.


The Mass of the NewSat-6 Satellite is 43.5 kg.


The SRAMs Quantity of the RADMON Radiation Monitor is 16.


The Mass of the Delfi-n3Xt Nanosatellite is 3.5 kg.


The Data Availability of the ATMS Instrument is For at least 98% of all observations over an annual basis.


The Measurement Range of the Particle Detector Instrument is Tritium : 9.2 MeV/n ~ 21 MeV/n.


The Intensity of the RFI Sources Interference is Very strong power emitters.


The Command UHF-band of the RF communications Communication Subsystem is 1.2 kbit/s.


The Topographic Elevation Difference of the Lander Spacecraft is 3 km to 7 km.


The Mission End Date of the Sentinel-1B Satellite is 3 August 2022.


The Number of Antennas of the ADM Antenna Deployment Module is 2.


The Sovereignty of the Ground Segments Ground Stations is Independent.


The Link Distance of the Optical link Communication System is > 45,000 km.


The Structure Manufacturer of the Biomass Satellite is APCO Technologies in Switzerland.


The Conference Presentation Date of the Sentinel-1 Satellite is July 22-27, 2012.


The Reentry Date of the OrbView-3 Satellite is March 13, 2011.


The Solar Array of the ESPA Ring Interface is Single-panel body mounted.


The Years of Service of the Admiral Paul F. Zukunft Coast Guard Commandant is 41 years.


The Power of the Instrument General is 30 W.


The Hydrazine Mass of the Satellite Satellite is 80 kg.


The Launch Date of the PSLV-C38 Launch Vehicle is June 23, 2017.


The Power Distribution of the ALBus 3U CubeSat Satellite is 100 W.


The Mission Date of the PSLV-21 Satellite is Sept. 4, 2012.


The Launch Date of the Aeolus satellite Satellite is July 23, 2018.


The Model of the SDR Host Computer Computer is Intel Core i5.


The Power of the MTQ Instrument is 1 W/unit.


The Number of Formal Cooperation Projects of the ESA and EDA Organizations is Eight.


The Volume of the Optics volume Spectrometer is 180 mm diameter x 530 mm.


The Launch Location of the Copernicus Sentinel-6 Michael Freilich Satellite is Vandenberg Air Force Base in California.


The Technologies of the CFESat Satellite is Supercomputer equipped with field-programmable gate arrays (FPGAs), new power supply, inflatable antennas, deployable booms, new type of launch-vehicle separation system, high-density pack of AA lithium-ion batteries.


The Diameter (mm) of the Antenna Reflector is 760.


The Fiber Optics Links of the MIRAS Satellite Payload is 144.


The Host for Sentinel-4 of the MTG-S Satellite is True.


The No of bands/channels of the MWHS Microwave Humidity Sounder is 5.


The Impact of the EMIT Imaging Spectrometer is Help climate scientists better understand the impact of airborne dust particles in heating and cooling the planet’s atmosphere.


The Construction and Thermo-Regulation System Mass of the Microsatellite Satellite is 5.3 kg.


The Thrust of the Propulsion System Satellite Component is 0.3 N.


The Receiver Type of the LICEF Receiver is Frequency-selective.


The Protocol of the RF Communications Communication System is AX.25 or SRLL.


The Launch Date of the Galileo satellites Satellite is 12 October 2012.


The Number of Flights of the Foton Spacecraft is 2.


The Data Link Subsystem of the X-band SAR payload system Payload System is Included.


The Focal Length of the UVIT Telescope Telescope is ~4750 mm.


The Orbit of the Vigilance Mission (KSF1) Satellite Cluster is 525 km Sun Synchronous orbit.


The Force of the ESP Thrusters Maneuvering System is Provides a tangential component force on the exterior.


The Core Diameter of the Graded Index Multimode Fiber Fiber is 200 µm.


The Configuration of the OPSIM Operational Simulator is One RTU in the loop and the other RTUs are simulated.


The Antenna Diameter of the Satellite Satellite is 1.5 m.


The Accuracy of the Sun Sensors Sensor is ~1º.


The Propellant Consumption Rate of the RapidEye Satellite Constellation is Lower than assumed during the design phase.


The Instruments of the Sentinel-3 Satellite is Measure oceans, land, ice and atmosphere.


The Feasibility of the Global Satnav System Satellite Navigation System is Unfeasible.


The Total Impulse of the SkySat-7 Satellite is 317 Ns.


The Tests of the FG Calibration Device is Optical, electrical and mechanical.


The Mission Purpose of the PACE Satellite is Establish more confident simulation models for nanosatellites and/or CubeSats of similar configuration in LEO.


The Frequency of the XBT X-band Transmitter is 8.3025 GHz.


The Developer of the CIP Instrument is Space Payload Laboratory at NCU (National Central University) of Taiwan.


The Conference Date of the NASA Optical Communications and Sensor Demonstration Program Program is Aug. 4-9, 2018.


The Enclosure of the DarkCarb image sensor Photon Detector is Cooled Dewar.


The Frequency (GHz) of the ICI-3 Radiometer is 183.31±2.0.


The CCSDS ID of the GSAT-0101 Satellite is 3A5.


The Number of Tracked Satellites of the GPS/MET GPS Receiver is Up to eight GPS satellites.


The Instrument of the ISS-RapidScat Scatterometer is QuikSCAT scatterometer.


The Polishing, Coating, Integration of the SiC mirrors Space Telescope Component is Unknown.


The Storage Capacity of the CEU Solid-State Recorder is Much larger than 3 MB.


The Measurement of the OCI Ocean Color Instrument is Precise measurements of the ocean surface.


The Pressure Range of the DN probe Neutral Particle Probe is 10^-7 - 10^-2 Pa.


The FOV of the . Microdosimeter B Instrument is 32º.


The Launch Date of the CASSIOPE Satellite is 29 Sep 2013.


The Current Backlog of the Satellogic Satellite Imaging Company is $38 million.


The Operating Principle of the SEVIRI Imager is Collecting radiation from a target area and focusing it on detectors sensitive to 12 different bands of the electromagnetic spectrum by means of a telescope.


The Consortium Members of the Swarm Spacecraft Satellite is EADS Astrium Ltd., UK; GFZ Potsdam, Germany; DTU Space, Copenhagen, Denmark.


The Launch Date of the PACE Satellite is January 2024.


The Telescope Diameter of the Millimeterwave receiver Receiver is 30 cm.


The Beacon Frequency of the OSSI-1 Satellite is 145 Mhz.


The Operating Temperature of the Myriad RF board RF Board is -40°C to 85°C.


The Electric Field Measurement Range of the Plasma Wave Instrument Instrument is 0.5 Hz to 400 kHz.


The Frequency of the S-band Frequency Band is 2067 MHz.


The Spotlight Scene Resolution of the SAR Antenna Antenna is 0.5 m.


The Headquarters Locations of the SAR Satellites Satellite is San Francisco, California; Denver, Colorado; Washington, D.C..


The Launch Date of the BRO-1 Satellite is 20 August 2019.


The Mass of the Biobox Payload is 64 kg.


The Purpose of the Resurs-DK1 Earth Observation Satellite is Multispectral and spectrozonal mapping of the Earth's surface in the visible and near IR bands.


The Position of the AHS Airborne Hyperspectral System is Left-hand port.


The Launch Date of the Dragon Satellite is 3 April 2018.


The Power of the Voltage 6 Modulator is 0.93.


The Power of the EPS Electrical Power Subsystem is 0.2 W.


The Storage Capacity of the SSR Solid State Recorder is 4 Tbit @ BOL.


The Operating Power of the Satellite Observation Instrument is 8.5 W.


The Wavelength Bands of the Hrr. chaoviatoris Microorganism is 470, 525, and 615 nm.


The Mass Range of the MIPA Ion Mass Analyzer is Optimized to cover accelerated ionospheric ions.


The Altitude of the WorldView-3 Satellite is 617 km.


The Data Destination of the Control Units Satellite Component is SCU.


The Primary Payload of the RADARSAT-1 Satellite is Synthetic Aperture Radar (SAR) sensor.


The Launch Date of the H-II Transfer Vehicle "KOUNOTORI6" Spacecraft is Oct. 7, 2016.


The Orbit Duration of the Jason-2 Satellite is Three years.


The Development Status of the GCOM Satellites Satellite is Not provided.


The Mass of the CanX-2 S-band Transmitter/Transceiver is Unknown.


The Acceptable Location of the TEMPO Instrument is 80-120º W.


The MZ-Surface Function of the H3 and H4 Spacecraft is Location of solar cells.


The Gridding Size of the SAR Image Satellite Image is 2000 x 2000.


The Presentation Date of the Swarm Satellite Constellation is March 20-24, 2017.


The Cadence of the Dose Rate Measurement is 1 minute.


The Type of the ACE-FTS Instrument is Limb-scanning infrared spectrometer.


The Orbit Raise Maneuver No. 2 Completion Date of the CloudSat Satellite is 27 May, 2006.


The Mass Spectrometer of the Kaguya Satellite is Present.


The Deployment Date of the TacSat-4 Satellite is October 8, 2011.


The Size of the LEID Instrument is 330 mm x 150 mm x 130 mm.


The Orbit Type of the FASat-Alfa Satellite is Sun-synchronous near-circular orbit.


The Developer of the MWS, SCA, RO, MWI, ICI, 3MI Instruments is ESA.


The Orbit Altitude of the PACE Satellite is 600-800 km.


The Constellation Cost of the Lightspeed Satellites Satellite is $5 billion.


The Small Satellite Deployments of the NanoRacks Company is 217th overall.


The Diameter Increase of the BEAM Expandable Habitat is 40%.


The Mass of the Deimos-2 Satellite is 310 kg.


The Workshop Date of the GIOVE-A and GIOVE-B Satellites is October 13, 2008.


The Future Evolution of the Star and its Orbit Celestial Body is More circular and grow in size.


The Communication Method of the OUFTI-1 Satellite is Direct communication.


The Funding Amount of the Pixxel Company is $25 million.


The | of the T. Kumar Pant, R. Sridharan Authors is T. Kumar Pant, R. Sridharan.


The Number of Parameters of the PEM (Parameterized Exospheric Model) Theoretical Model is 30 parameters.


The Reentry Location of the Skylab-1 Space Station is Indian Ocean and parts of sparcely-populated western Australia.


The Beacon Transmission Frequency of the ELFIN-A Satellite is 437.450 MHz.


The Development Program of the HSB Hybrid Sensor Bus is ESA-ARTES program.


The Development Partner of the Land Information System Software is NASA's Goddard Space Flight Center.


The Full Operational Service Date of the SARah Satellite Constellation is By the end of 2019.


The Target Audience of the MoonKAM Education and Public Outreach Program is Fifth- to eighth-grade students.


The Transmission Spectra of the Optical Depth Range Atmospheric is 0.01–4.5.


The Operation Extension Date of the Cluster Satellite Mission is June 2009.


The Bump Height of the Photon Sieve Optic is h< 8∅(f/D)2.


The Operational Mode of the REPT Instrument is Continuous.


The LTAN of the Satellite PAZ is 18:00 hours.


The Collecting Area of the NICER X-ray timing instrument is > 1800 cm2.


The Field of View (Cross-track) of the MSU-100 Camera is 31º.


The Hyperspectral Instrument Resolution of the Satellogic Satellite is 30 meters.


The First Measurements of the APXS Instrument is The first X-ray and alpha spectra will be recorded.


The Integration Location of the LightSail-2 Solar Sailing CubeSat is Air Force Research Laboratory (AFRL) in Albuquerque, New Mexico.


The Battery Capacity of the TUBSAT-N Satellite is 5 Ah.


The Conference Date of the LCROSS Satellite is April 25-30, 2010.


The Components of the FEE Front End Electronic is FPPE (Focal Plane Proximity Electronics) and VAU (Video Acquisition Unit).


The Capsule Drop Location of the Hayabusa-2 Spacecraft is Australian Outback.


The URL of the Cupola Window is https://web.archive.org/web/20131207132529/http://thalesaleniaspace-issmodules.com/index.php/cupola.


The Disposal of the Monitor-E mock-up Payload is De-orbit together with Breeze into the atmosphere.


The Ionospheric Plasma Survey Hours of the DSLP Data Acquisition System is 10 thousand hours.


The Launch Date of the MetOp-B Satellite is Sept. 17, 2012.


The Objective of the HI-SCALE Instrument is Measurement of interplanetary ions and electrons.


The URL of the ExoMars Mission is https://iafastro.directory/iac/proceedings/IAC-18/IAC-18/A3/3A/manuscripts/IAC-18,A3,3A,10,x42850.pdf.


The Event of the SMOS Satellite is SMOS Results and MIRAS Evolution Studies.


The Platform of the AltiKa Altimeter is Myriade.


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


The Purpose of the GEO Geostationary Orbit is Global Positioning Systems (GPS) and communications.


The Simulation and Materials Database of the Oculus-ASR Satellite is Improved.


The Sensitivity of the LIGO/Virgo sensors Sensors is Improved.


The Pixel-Binning Spatial Resolution of the EyeSat Satellite is 0.5°-2°.


The Principal Investigator of the JEM-X X-Ray Monitor is Søren Brandt.


The Spatial Resolution of the Geodesy Levelling by GPS Satellite is 100-1000 km.


The Telescope Aperture of the SIS (Scanning Imaging Spectrograph) Spectrograph is 25 x 50 mm.


The Oceanic Crust Thickness of the Earth Planet is About 6 to 7 kilometers.


The Type of the skCube Satellite is 1U CubeSat.


The Spectral Overlap of the VNIR and SWIR bands Spectrometer is 900 nm to 1000 nm.


The Manufacturer of the Planet SkySats Satellite is Maxar Technologies.


The Principal Investigator of the TEMPO Instrument is Kelly Chance.


The Number of Simultaneous Message Processing of the Argos Communication System is Up to four (eight in next series) messages.


The Deployment Services of the NanoRacks LLC Company is J-SSOD (JEM-Small Satellite Orbital Deployer) of JAXA.


The URL of the SOLSPEC Spectrometer is http://www.ioccg.org/groups/Thuillier.pdf.


The Number of Channels of the ICI Instrument is 11.


The Data Rates of the CDL Common Data Link is Up to 274 Mbit/s.


The Qualification Nanosat Quantity of the SMDC-ONE program Satellite Program is 1.


The Launch Date of the EarthDaily Constellation Satellite Constellation is January 2024.


The S-band Transmitter Activation Time of the Satellite Spacecraft is 30 minutes after separation.


The Accuracy Range of the GOCE Satellite is 0.002 - 0.03 m.


The Electronic Gains of the Limb Sensor Sensor is Two.


The Service Module Commissioning Start Date of the Herschel Spacecraft is May 15, 2009.


The Viewing Acquisition of the XSAR SAR is 20 - 45°.


The Calibration Step of the Sensor Counts to Radiance Conversion Process is May be applied for calibration.


The Manufacturer of the BEAM Module is Bigelow Aerospace.


The Types of the Output Products Data is Ground reflectance cube, maps of the aerosol optical thickness and atmospheric water vapor, masks of land, water, haze, cloud, shadow and snow.


The Spectral Bands of the Pixxel’s planned satellites Satellite is 300 including Visible to Near Infrared (VNIR) and Short Wave Infrared (SWIR).


The Operational Since of the PVA Photovoltaic Assembly is Late 2013.


The Reaction Wheels of the S/C Satellite is Four.


The Mass of the GRACE-FO satellites Satellite is ~600 kg.


The CCSDS ID of the GSAT-0211 Satellite is 26B.


The Observation Mode Switching of the OCO Satellite is Alternate 16-day global ground-track repeat cycles.


The SNR Ratio of the Instrument Satellite Instrument is Increased.


The Wavelengths of the SOHO's EIT Extreme-ultraviolet Imaging Telescope is 171 Å, 195 Å, 284 Å and 304 Å.


The Manufacturer of the EPS Electrical Power Subsystem is Tiger Innovations.


The Function of the Ground Software Data Processing is Make finding charts with source lists.


The Platform of the ExoplanetSat Satellite is CubeSat.


The Imaging Frequency Band of the TecSAR Satellite is X.


The VNIR Spatial Resolution of the iSIM-90 Imager is 1.65 m.


The Renamed Name of the Solar Probe Plus Spacecraft is Parker Solar Probe.


The Design of the NAOMI Imaging Instrument is High-resolution pushbroom imager.


The Resolution (VIS) of the VHRR Very High-Resolution Radiometer is 2.75 km.


The Designer/Developer of the PROBA Satellite is Verhaert Design and Development N. V..


The Measurement Domain of the OSCAR-QUBE Satellite is Gravity and Magnetic Fields.


The On-board Receivers of the Sentinel-3 Satellite is Two GPS Receivers, LRR, DORIS.


The Installation Date of the ISS-RapidScat Satellite Instrument is October 6, 2014.


The Return to Science Operations Date of the Chandra X-ray Observatory X-ray Observatory is 24 October 2018.


The Conference Date of the Dellingr Satellite is Aug. 5-10, 2017.


The Mission Regions of Interest of the HyperScout® Satellite is Identified by the consortium partners.


The Purpose of the HawkEye 360 Satellite Constellation is Deliver RF data and analytics to the agency and combatant commands.


The Payload Mass of the Resurs-DK1 Spacecraft is 1200 kg.


The Structure of the S/C Satellite is Box-shaped three-axis bus.


The Expected Coolant Exhaustion of the Herschel Space Observatory is March 2013.


The Tracking Organization of the Debris Satellite Components is U.S. Air Force's 18th Space Control Squadron.


The Purpose 1 of the PW-Sat CubeSat is System test of a flexible solar generation system.


The Downlink Verification Method of the Ground System Satellite Ground System is Playing back the recorded signal to the flight unit or an engineering unit and verifying the uplinked commands.


The Access of the HTV Spacecraft is ISS crew will be able to enter and remove the supplies.


The Design Hypothesis of the Geometric Calibration System Calibration System is Seasonal change can be sufficiently modelled for a pair of months with a 1st order polynomial against sun β angle.


The | of the Miniature Integrated Camera Spectrometer (MICAS) Spectrometer is Miniature Integrated Camera Spectrometer (MICAS).


The Components of the Coronagraph Instrument Instrument is Optical Bench Assembly (CGI-OBA) and the Tertiary Collimator Assembly (TCA).


The Torque Type of the Attitude Control System Satellite System is Attitude control torque.


The Flyby Distance of the OSIRIS-REx Spacecraft is 2.1 miles (3.5 km).


The Quantity of the XTA Xenon Tank Assembly is 2.


The Processor Speed of the MPM Main Processor Module is 50 MHz.


The Affiliation of the Andreas Jung Engineer is Unknown.


The Data Archive Location of the Spitzer Space Telescope Telescope is Infrared Science Archive at IPAC at Caltech in Pasadena, California.


The Focal Length of the Primary Mirror Telescope Component is 120 mm.


The Range of the Rate sensor Sensor is ±85º/s.


The Instrument of the SMAP satellite Satellite is Radar and radiometer.


The Number of Sensors of the SloshSat Satellite is 270.


The Temporal Resolution of the MSASI Imager is 2 ms.


The Weight of the Chang'e-5 Spacecraft is 8.2 tons.


The Launch Date of the Hugo Satellite is Later this year.


The Supported Navigation Signals of the Signal Generator Subsystem Signal Generation System is E5, E6, and L1-bands.


The International Astronautical Congress Date of the 3MI Instrument is 25-29 Sept. 2017.


The Wavelengths of the Mid-IR Imagers Camera is 7 and 12.3 µm.


The Presentation Date of the A Stable Liquid Mono-Propellant based on ADN Propellant is May 11-14, 2009.


The First Observation of the XMM-Newton X-ray Observatory is June 1962.


The Diameter of the Heat Shield Parker Solar Probe Component is 8 feet (2.44 m).


The Main Rotation Period of the Philae Lander is 24 seconds.


The Launch Year of the ALOS-1 Satellite is 2006.


The Directional and Omni-directional Measurements of the MEPED Particle Detector is Available.


The Video Data Output Frequency of the MS Detectors Detectors is 58 Mpixel/s.


The Beam width of the W-band Band is 20 mrad.


The End of Life Date of the Genesis Satellite is September 8, 2004.


The Telescope Assembly of the SPEXone Spectrometer is Three-mirror segmented telescope assembly.


The Mission Focus of the Aqua Satellite is Multidisciplinary study of the Earth's water cycle.


The Regional Components of the DBNet Data Collection Network is DBNet-EUMETSAT (EARS), DBNet Asia Pacific (with two nodes in Tokyo and Melbourne), DBNet South America (with two nodes in INPE/CPTEC and Buenos Aires), DBNet-NOAA DBRTN (Direct Broadcast Real-Time Network) and partners.


The Downlink Data Rate of the TT&C S-band Communications Communication System is 722.116 kbit/s.


The End of Life Date of the SPOT-5 Satellite is 30 Mar 2015.


The Instrument Type of the GOSAT Satellite is Imaging multi-spectral radiometers (vis/IR), Atmospheric chemistry.


The Operation Status of the AprizeSat-3 and AprizeSat-4 Satellites is Nominal.


The URL of the Sentinel-1 Satellite is http://earth.eo.esa.int/workshops/fringe09/participants/1197/pres_1197_Rosich.pdf.


The Mass of the Total Payload Satellite is < 100 kg.


The Oversight of the Characterization Process Satellite Debris Analysis is Human oversight to ensure the integrity of the data.


The Bulletin Date of the GEOS-1 Satellite is Feb. 2004.


The RAAN Accuracy of the Bloostar Launch Vehicle is ±0.05º.


The Spectral Range of the TAC Camera is 500 - 800 nm.


The Components of the Electro-optical assembly Assembly is Off-axis TMA (Three Mirror Anastigmat) optical telescope unit, focal plane assembly, baffle.


The Mass of the CU Cabling Unit is 5 kg.


The Image Date of the Copernicus Sentinel-5P Satellite is 2 July 2018.


The Daily Radio Occultation Profiles of the Spire Satellite Operator is 5,000.


The Pair Orientation of the DBCP Dual Babinet Compensator Pseudo-depolarizer is The wedges of a pair are bonded with crossed crystal axes, and the first pair is rotated by 45° w.r.t. the second one.


The Impact Date of the Hayabusa-2 Spacecraft is 30 October 2020.


The Sampler Room A Close Command Date of the Hayabusa-2 Spacecraft is February 22, 2:20 UT.


The Operation Duration of the Schiaparelli Lander is Few days.


The On-Orbit Geometric Calibration of the Landsat-7 Satellite is Four Years.


The Function of the Machine Learning Algorithm Calibration Tool is Recognize a solar flare and determine how much degradation is affecting AIA's current images and how much calibration is needed.


The GPS Receivers of the NigeriaSat-2 Satellite is 2 SGR-10 (Space GPS Receiver-10) units.


The EIRP of the Isolated Spot Beams Communication System is 65 dBW.


The Detector of the DubaiSat-2 Satellite is TDI CCD detectors.


The Spatial Resolution of the CCD Camera Imaging System is 1 km x 1 km.


The Observation Results of the Herschel Space Observatory is Filaments in nearby star-forming clouds seem to be roughly all the same width – about a third of a light-year.


The Cost Savings of the Satellogic Satellite Imaging Company is 100 times cheaper than competitors.


The Thruster Type of the Starlink Satellite Satellite is Hall thrusters powered by krypton.


The Onboard Computer of the PhoneSat 2 Satellite is Samsung Nexus S phone.


The View of the SWIR/MWIR/TIR Calibration is Blackbody.


The NASA's upcoming asteroid sample return mission of the Rosetta spacecraft Spacecraft is OSIRIS-REx.


The Height of the Prometheus Volcano Plume Volcanic Plume is 60 km (40 miles).


The UV Spectral Range / Bandwidth of the SOLSPEC-ATLAS Spectrometer is 210-370/1.2/0.4.


The Inclination of the Satellite Orbit is 98º.


The Data Storage of the NSat Satellite is 2 GB SD card.


The Manufacturer of the SIMBA Satellite is Royal Meteorological Institute Belgium.


The Quantity of Cylindrical Electrostatic Deflection Analyzers of the VEIS Vector Electron Ion Spectrometers is 6.


The Duration Pulses of the LM thruster Thruster is Up to 8.0 sec.


The Data Transmission Frequency of the HRC Instrument Camera is At least once per orbit, or every 90 minutes.


The Battery Power Duration of the IXV Spacecraft is 1h 43 min.


The Receiver Sensitivity of the Galileo Satellite is Millions of times weaker than the ones received on Earth.


The Workshop Date of the MTG Mission Team (MMT) Team is Dec.3-5, 2007.


The Objective of the IRIS Imager Camera is Provide multispectral imagery in the visible and near-infrared wavelength range.


The Scheduled Launch Date of the Sentinel-6 Michael Freilich Ocean Science Satellite is Nov. 10.


The Presentation Date of the Next-Generation Formation Flying Solar Coronagraph Solar Coronagraph is May 27-28, 2014.


The Resolution of the A/D converter Data Converter is 5 bit.


The Central Wavelength of the Current GOES imager Sensor is 7.34.


The Spatial Resolution of the Solid Earth Sedimentary basins Satellite is 20-100 km.


The Dimensions of the LLITED Spacecraft is Approximately 100 x 100 x 170 mm.


The Image Capture Date of the CaSSIS Instrument is 15 January 2019.


The Operation Stop Date of the ERB Radiometer is Jan. 4, 1994.


The Contract Award Date of the Galileo Satellite System is January 7, 2010.


The Processor of the AOCS Attitude and Orbit Control Subsystem is MIL-STD 31750.


The L-band Radiometer Frequency of the SMAP Satellite is 1.4 GHz.


The Dose Measurement Range of the DDM Instrument Dosimetry System is Rad to Mrad.


The OceanObs'09 Presentation Date of the SWOT Satellite is Sept. 21-25, 2009.


The Plan Generation of the MPF System is Daily.


The Length of the ERA Robotic Arm is Over 11 m.


The Earth Surface Area Observed of the MOMS-2P Instrument is 65 million km 2.


The Ascending Node Time of the Odin Satellite is 18:00 hrs.


The Image Interval of the DECA Descent Camera is 1.5 s.


The Primary Structure of the Terra Satellite is Truss-like structure built of graphite-epoxy tubular members.


The Launch Locations of the OneWeb Satellite Constellation is Baikonur Cosmodrome in Kazakhstan, and Vostochny Cosmodrome in Russia.


The Mission of the RSP-00 CubeSat is Demonstrate technology aimed at electron density measurement and three-dimensional mapping of ionosphere and chip scale (ultra-small) atomic clock for CubeSats.


The Manufacturer of the GFO Satellite is Unknown.


The Parameter of the Channels Spectrometer is Value.


The Bandwidth of the RF Ground Network Ground Network is 500 kbit/s.


The Spacecraft Volume (Before Inflatable and Sail Deployment) of the Spacecraft 3U CubeSat is 34 cm x 10 cm x 10 cm.


The Interferometric Radiometer of the SMOS Satellite is L-band.


The Launch Date of the TUBSAT Satellite is 17 July 1991.


The Range of the LET Range Parameter is 0.2 - 7 MeV/µm.


The Presentation Date of the Sentinel-1 Satellite is Nov. 30-Dec. 4, 2009.


The Developer of the SEDS Tether Experiment Demonstration Program is NASA/MSFC and Tether Applications Co. of San Diego.


The Development Team of the BEESAT-3 Satellite is Merlin F. Barschke, Frank Baumann, Klaus Briess, Christian Nitzschke.


The Payload of the STACEM Satellite is Miniaturized multi-spectral payload for the acquisition of imagery in the visible and near infrared wavelengths and hyperspectral channels.


The Transmitter/Receiver and the Buffer Store Mass of the Microsatellite Satellite is 12.5 kg.


The Output Power of the InnoSlab amplifier Laser Amplifier is Scalable.


The Number of Pixels of the Band 3 Spectral Band is 1600.


The Number of ERS SAR Pairs of Data of the ERS Tandem Mission Satellite Mission is About 110,000.


The On-Station Time of the DSCOVR Spacecraft is 110 days.


The Design of the Telescope Telescope is Cassegrain design.


The Inclination of the ICEYE-X14 and ICEYE-X16 Satellites is 97.4º.


The Components of the JUICE Science Ground Segment (SGS) Ground Segment is Science Operation Center (SOC) and the PI instrument teams.


The Doppler Shift of the AIS System Communication System is - 4 kHz to + 4 kHz.


The Expected Mars Orbit Entry Date of the Tianwen-1 Mars Mission is February 10.


The URL of the JWST Fine Guidance Sensor Sensor is http://www.stsci.edu/jwst/instruments/fgs.


The URL of Paper of the RISESAT Satellite is http://tinyurl.com/q5hq42e.


The CCD Pixel Measurements of the Nadir Sensor Wide-Field Telescope Sensor is Summed into 35 bins.


The Spatial Resolution of the TAC Camera is 3.5 m.


The Launch Date of the LambdaSat Satellite is Unknown.


The Pixel Size (km x km) of the Antenna Reflector is 8.


The Accuracy of Cloud Echoes of the CPR Millimeter-Wave Radar is 1 m/s.


The Mission of the NIRS Instrument is RAIDS (Remote Atmospheric and Ionospheric Detection System).


The Altitude of the FormoSat-3/COSMIC-1 Satellite Constellation is 800 km.


The Deployment of the Sunshield Satellite Component is Folded against the payload module during launch, deployed around the fixed solar array after separation from the launch vehicle.


The Number of Panels of the Solar Array Power Source is 8.


The Pulse period (ms) of the B0531+21 (Crab) Pulsar is 33.085.


The Number of Sensors and Systems of the SSA Space Situational Awareness System is 375.


The Location Technique of the PTT-HD or PMT-HD High Data-rate Transmitters is Not designed to be autonomously located by Doppler technique.


The Mass of the DeMi Satellite is 2.5 kg.


The Commercial Operation Start Date of the Hiber Satellite Network is Q1 2019.


The Platform of the BRITE Satellites Satellite is GNB (Generic Nanosatellite Bus).


The Signal Assessment Modes of the Hertz Facility is Local ‘near-field' or as if the signal has crossed thousands of kilometers of space.


The Observation Date of the Herschel Telescope is 24 September 2018.


The Fix Frequency of the Novatel OEMV-1 GPS receiver GPS Receiver is Approximately once every 25 hours.


The Solar Array Status of the IXPE observatory X-ray Observatory is Not delivered.


The Technology of the LRO Mini-RF Transmitter Transmitter is MPM combines a solid state RF driver/preamplifier with a traveling wave tube amplifier.


The Instrument Type of the IMAGE Satellite is Atmospheric chemistry, Communications, Data collection.


The Telescope FOV of the BRITE Satellite is 24º diameter.


The Tracking and Cataloging of the CSpOC Space Operations Center is Immediate.


The Antenna Angle of the SWOT Satellite is ± 60º.


The Observation Data of the CryoSat-2 Satellite is Changes in ice thickness for October/November 2011, 2012 and 2013.


The Type of the NIR Camera Camera is Near Infrared.


The VHF-band FSK Channels of the UoSAT-12 Satellite is 3.


The Orbit Altitude of the A-Train Satellite Constellation is Approximately 705 km.


The Bands of the CAVIS Imager is 7 VNIR + 5 SWIR.


The IoT Services of the Astrocast Satellite Manufacturer is Track, measure, manage, communicate and control IoT assets.


The Path Length Ratio of the SST Retrieval Algorithm Algorithm is 1.54.


The Launch Date of the HY-1B Satellite is October 4, 2007.


The Acquisition Mode of the TDX and TSX Satellites Satellites is Dual Receive Antenna configuration.


The Orbit Altitude of the Envisat Satellite is ~783 km.


The Imaging Capacity of the RapidEye Satellite Constellation is 5 million km2 per day.


The URL of the Parker Solar Probe Satellite is https://blogs.nasa.gov/parkersolarprobe/2021/11/10/space-dust-presents-opportunities-challenges-as-parker-solar-probe-speeds-back-toward-the-sun/.


The Launch Date of the Minotaur-C rocket Rocket is Nov. 1, 2017.


The Antenna Mast Height of the ASAL Ground Station Ground Station is 10 m.


The Total Mass of the CMGs Attitude Control is 261.6 kg.


The Modulation of the X-band Transmitter Transmitter is BPSK or QPSK.


The Deorbiting Time of the IDEAS Deorbiting System is Within about 25 years.


The Mission Scientist of the Sentinel-6 Satellite is Craig Donlon.


The Observation Targets of the Twinkle Spaceborne Telescope is Astrophysical objects (e.g. exoplanets, solar system bodies, stars, disks).


The Team Size of the ATMS Instrument is 100 people.


The Resolution of the GOCI-II CMOS Imaging Sensor CMOS Imaging Sensor is 2720 rows by 2718 columns.


The Interval of the Observation and Calibration Process is 1.8s.


The Frequency Range of the ISEE-3 Satellite is 0.3 Hz to 100 kHz.


The Utilized Atmospheric Emissions of the MATS Satellite Instrument is O2 Atmospheric Band airglow and scattering of sunlight by NLC.


The Mission Extension Approval Date of the Kepler Satellite is April 4, 2012.


The Material of the Wire Component is Teflon-coated 29 gauge copper-stranded wire.


The Contract Signing Date of the FormoSat-5 Satellite is June 17, 2010.


The Atmospheric Phenomenon of the Planets with One Side Permanently Facing Their Star Exoplanets is Clouds of different compositions might be visible, depending on the side observed.


The Required Spacecraft Orientation for Stability of the Kepler Space Telescope Space Telescope is Nearly parallel to its orbital path around the sun.


The Impulse Peak Power of the X-band Radar is 100 kW.


The Presentation Date of the Delfi-n3Xt Satellite is June 3-5, 2013.


The SAR Measurements Spatial Resolution of the L2SMA Soil Moisture Product is About 3 km.


The Operation Duration of the Experiments Payload is 1 year to 3 years.


The Size of the GeoCarb Instrument is 1.3 m x 1.14 m x 1.3 m.


The Date of the GAUSS Satellite Launch Satellite Launch is Nov. 21, 2013.


The Release Date of the CubeSat Satellite is February 19.


The Spectrum of the FCI Optical Imager is Visible, near-infrared and infrared.


The Third Flight Date of the MEPSI Satellite is Nov. 24 to Dec. 7, 2002.


The Launch Date of the Sentinel-5P Satellite is 13 October 2017.


The Applicable Orbits of the AutoConTM Technology is Variety of orbits ranging from LEO to non-Keplerian trajectories such as libration orbits.


The Data Collection Altitude of the RainCube Satellite is About 310 km.


The Accuracy of the SSAS Sensor is 0.1º to 1º.


The Orbit Altitude of the GomX-4B Satellite is 500 km.


The Band 7 of the Landsat TM Satellite is Hydrothermal mapping, geology.


The Data Downlink Rate of the TDRSS Communication System is 20 kbit/s.


The Propulsion of the Hisea-1 Satellite is ThrustMe iodine electric propulsion.


The Thrust of the T3µPS Micropropulsion System is Up to 6 mN.


The Mass of the Nanosatellites Satellite is < 10 kg.


The Latency of the ATL06 Land Ice Height Data is 45 days.


The Mission End Date of the LISA Pathfinder Spacecraft is 25 June 2016.


The Number of Pointed Proportional Counters of the IXAE X-ray Astronomy Experiment is 3.


The FOV (Field of View) of the Instrument Sensor is 80º x 80º.


The Parameter Derivation of the Antenna Unknown is Ta = Tref - η Tn.


The Orbit Inclination of the DubaiSat-2 Satellite is 97.8º.


The Azimuth Dwell Time of the Radar Instrument is 42 ms.


The Mission Accomplished Date of the CanX-4 & CanX-5 Satellites is Nov. 5, 2014.


The Location Accuracy of the SPOT-6 Satellite is 11.9 m CE90 @30º.


The Platform Type of the Satellite Vu Satellite is DarkCarb satellite bus.


The Control Method of the Attitude Control System Satellite System is Solar radiation pressure, Optical parameters control.


The Locations and Operators of the Sentinel-1 PDGS centers Ground Segment is KSAT for X-band reception (CGS) in Svalbard (Norway) and Alaska, INTA for X-band reception in Maspalomas (Spain), E-Geos for X-band reception in Matera (Italy), Astrium Services for the PAC (Processing and Archiving Center) in Farnborough (UK), DLR for th.


The Mass of the Gyro Unit Attitude Control is 1.5 kg.


The Quantity of Reaction Wheels of the Earth Observation Compartment Compartment is 3.


The Size Comparison to Sun of the HD 93396 Star is Three times larger.


The Payload of the VisionCube-1 Satellite is Multi-anode photon multiplier tube(MaPMT), a camera, and a real-time image processing engine.


The Purpose of the Advanced Satellite Navigation Receiver Receiver is Perform the first ever satnav positioning fix in lunar orbit.


The Workshop Date of the GIOVE-B Satellite is October 13, 2008.


The Components of the XSAR Instrument is RSC (Radar Signaling and Control) system, MTT (Multi-Tube Transmitter), Deployable paraboloid mesh antenna with electronic beam steering, OBR (Onboard Recorder) of 256 Gbit capacity, DLTU (Data-Link Transmission Unit).


The Congress Date of the Megha-Tropiques Satellite Mission is Sept. 29 to Oct. 3, 2008.


The Panorama Camera (PCAM) of the Chang’e-4 Rover Rover is Payload.


The Manufacturer of the Sich-2 Satellite is Yuzhnoye SDO.


The Swath Width of the HSC CCD Imaging Camera is 700 km.


The Data Output of the TDI Detector Detector is 290 Mpixel/s total.


The Presentation Date of the PROCYON Deep Space Probe is August 6-11, 2016.


The Instrument Type of the OCI Instrument is Ocean colour instruments.


The Launch Date of the Beresheet Spacecraft is Mid-February.


The Pixel Quantization of the Telescope Optical Instrument is 12 bit plus 1 bit for low and high gain setting.


The Wavelength/Passband of the Instrument Spectrometer is 135.6; 155 nm.


The G/T of the Reception Station Ground Station is 22.7 dB/K.


The Phototransistor Sensitive Area Diameter of the DIAL Instrument LIDAR is 200 µm.


The Mission Status of the Gravity Probe B Satellite is Unknown.


The Thermistor Telemetry Data of the Satellite Spacecraft is Stable.


The Acquisition Date of the Maxar Technologies Company is June 24, 2020.


The Conference Date of the TBIRD Program Data Transfer System is August 3-8, 2019.


The Electrical Power Transfer Method of the Hinge Mechanical Component is Conducting electricity through the superelastic springs.


The Test Number of the File Transfer Test Communication is 1, 2, 3.


The TFOV of the Scan mechanism assembly Assembly is ±13º in the E-W and ±10º in the N-S direction.


The Date of the Dnepr Cluster Mission 2013 Satellite Cluster Mission is Nov. 21, 2013.


The SCOS-2000 Version of the Ground Segment Satellite Ground Segment is Version 5.


The Ready Time of the 90-satellite constellation Satellite Constellation is 24 months later.


The Aperture Diameter of the GMI Instrument is 1.22 m.


The Type of the EOVSA's Images Data is Radio emissions.


The Type of the SUCHI (Space Ultra-compact Hyperspectral Imager) Payload is Much smaller.


The Resolving Power of the 1.61 and 2.06 µm CO2 channel Spectrometer is > 20,000.


The Functionality Duration of the S/C and ground segment Satellite and Ground System is Up to 1 orbit before the final breakup.


The Resemblance of the Ichthyosaurs Marine Reptiles is Modern-day porpoises.


The Mission of the Biomass Satellite is Deliver crucial information on how the world's forests are changing.


The Propulsion System of the Lunar IceCube Spacecraft is Busek’s miniaturized electric thrusters.


The Quantity of the LEP Sensor Units Sensor Units is Three.


The Lift-off Mass of the GSLV-F05 Rocket is 415.2 tons.


The Operation Start Date of the RapidEye Satellite Constellation is Unknown.


The Participating Companies of the KOMPSAT-5 Spacecraft is Korea Aerospace Industries, Korean Air, Hanwha, Doowon Heavy Industries, and SI (Satrec Initiative).


The Passband of the VIS channel Spectrometer is 400-500 nm.


The Number of Devices Served of the Galileo Satellite Navigation System is More than 1.5 billion smartphones and devices.


The LTDN of the Resurs-P1 Satellite is 10:30 hours.


The Body Size of the Spacecraft Satellite is 2.5 m x 1.2 m x 1.1 m.


The Delta-V of the DMC Propulsion Subsystem Electric Propulsion is 10 m/s.


The Operation of the THEIA Satellite is Image Capture.


The RIN Performance Frequency of the ASM Instrument Instrument is 1 kHz.


The Ground Stations of the GIOVE-B Satellite is Dongara (Australia), Kiruna (Sweden), Santiago de Chile (Chile), South Point Hawaii (USA), and Fucino (Italy).


The Calibration Workshop Date of the KOMPSAT-5 Satellite is Aug. 25-27, 2010.


The Impact Speed of the SMART-1 Satellite is 2 km/s.


The Orbit Type of the Yubileyniy-2/MiR Satellite is Near-circular orbit.


The Dimensions of the SPOT satellite constellation Satellite Constellation is 3.5 m x 15.6 m.


The Mechanism Type of the SMA Scan Mechanism Assembly is Two-axis mechanism involving two flex pivots per axis.


The Structure Size of the S/C Satellite is 4 m x 3 m x 2 m.


The Launch Campaign Thread Date of the Falcon Heavy Rocket is 3 June 2019.


The Calibration Accuracy of the Instrument Spectrometer is Absolute: ± 5%.


The LTAN Evolution of the Swarm-A (Alpha) Satellite is 24 hours of local time coverage every 7-10 months.


The Backup Function of the BEI Systron Donner QRS100 Rate Gyro is Nutation measurement.


The LISS-2A/B Data Downlink of the Satellite Satellite is X-band.


The Attitude Determination Sensors of the X-ray Telescope Telescope is Fine sun sensor, 3-axes magnetometer.


The Dynamic range of the PHA Detector is Up to 23000.


The Publication Date of the ISEE-C Spacecraft is July 1978.


The Principal Investigator Institution of the Lucy Satellite is Southwest Research Institute in Boulder, Colorado.


The Completion Date of the CMIP5 Climate Model is 2010 to 2014.


The URL of the NASA Mission Asteroid Mining is http://www.nasa.gov/content/goddard/new-nasa-mission-to-help-us-learn-how-to-mine-asteroids/#.U4s2hXbwUkA.


The Mission Purpose of the REX-J Robot is Demonstrate technologies for Astronaut support robots.


The Operating System of the OBC On-Board Computer is FreeRTOS.


The Data Utilization and Applications Program of the RCM Satellite is Provides technical assistance to federal departments to upgrade their applications and develop new ones exploiting data generated by the RCM.


The Radar Imagery Capability of the SIR-C/X-SAR Radar System is Multifrequency (3) and multipolarization.


The Operation Period of the ALT Instrument is From launch to July 1979.


The Mission Date of the NanoRacks Satellite Deployment Service is 13 July 2018.


The Incidence Angles of the MWR Dicke Radiometer is between 52º and 58º.


The Cost of the Brexit Satellite Unknown is BS billions.


The Launch Mass of the Kanopus-V Satellite is ~ 450 kg.


The Maximum Power Consumption of the ROBUSTA picosatellite Satellite is 1 W.


The Model of the ICON FUV Instrument CCD is Dalsa FTT1010M.


The Ascending Node of the SMART-1 Satellite is 237.721º.


The Resolution Δλ (0.05º slit) of the SPIM5 Spectrometer is 2.9 nm.


The Spectral Bands of the IRIS Instrument Spectral Scanner is Green (520 - 600 nm), red (630 - 690 nm), and NIR (760 - 890 nm).


The Bias Correction of the Aeolus Satellite is Temperature variations across the instrument's telescope.


The Application of the WiFS camera Camera is Vegetation index mapping.


The Swath Width of the TeLEOS-1 Imager Imaging Device is 12 km.


The Service Spectrum of the NPOESS Program is NPOESS ground segment will acquire and store global and regional environmental imagery, specialized meteorological, climatic, terrestrial, oceanographic, solar-geophysical, and other data.


The Function of the Photo MOSFET Switch Component is DLP mission.


The Power Source of the Gaia Satellite is Solar power.


The Payloads of the PAZ Satellite is Synthetic Radar Aperture (SAR) as primary and sole payload, and included an IGOR+ advanced GPS (Global Positioning System) receiver and corresponding antennas for precise orbit determination.


The Equipped Devices of the Low Noise Amplifier Amplifier is Temperature sensor, switched load.


The Capacity of the Flash Memory Card Data Storage is 8GB.


The Aperture of the LWIR Camera Camera is 131 mm.


The Throughput of the SABR DC/DC Converter is Up to 180 W.


The Reaction Wheels of the NigeriaSat-2 Satellite is 4 SSTL Smallwheel 200SP wheels.


The Parking Orbit Achievement Date of the ARTEMIS Spacecraft is Aug. 24, 2001.


The Function of the CPOD Service Data Service is Generating precise orbital products and auxiliary data files.


The Uncertainty of the Sea Surface Salinity (SSS) Measurement is <0.3 pss.


The End of Life Date of the DeMi Satellite is 8 March 2022.


The Associated Plasma Dynamics of the Plasma Blobs Phenomenon is Investigated in the topside ionosphere.


The Debut Location of the Visualization Product is American Astronomical Society meeting in Honolulu, Hawaii.


The ADCS of the NEMO-HD Satellite is Attitude Determination and Control System.


The Absolute Accuracy of the Radiometry Sensor is < 2.4 Wm -2  sr -1.


The Thermal Design of the SWAP Instrument is Unknown.


The FPA Format of the CIRiS Instrument is 640 x 480.


The Capture Date of the Dragon Spacecraft is 8 December.


The Docking Attempt Date of the MEV-2 Servicer is 10 March 2021.


The Control Mode of the HS Heater System is SHM (Safe Hold Mode) and controlled through Proteus platform.


The RF Bandwidth (MHz) of the Antenna Reflector is 800.


The Mounting of the SWEA Solar Wind Electron Analyzer is STEREO boom.


The Band 5 of the Landsat TM Satellite is Vegetation moisture measurement, snow/cloud differentiation.


The Middle Wavelength Infrared (MWIR) and Thermal Infrared (TIR) band wavelengths of the HSRS Sensor is .


The Population of the Timbuktu City is About 55,000.


The Moon Images Acquired of the Pleiades-1A and Pleiades-1B Satellites is More than 800 images.


The UHF Downlinks Data Rate of the UoSAT-12 Satellite is 9.6 and 38.4 kbit/s.


The Manufacturer of the NanoPower Modules Satellite Component is GomSpace.


The Spectrum of the X-ray pulsars Astronomical Objects is Almost the same as predicted by the model.


The Spatial Resolution of the CO2Image Satellite is 50 m x 50 m.


The URL of the Communications with Earth Communication System is https://mars.nasa.gov/insight/mission/communications/.


The Current of the Voltage 2 Power Amplifier is 10.


The Satellite Environment Test Campaign Date of the IASI-NG PFM instrument Instrument is 2022 and 2023.


The Data Usage of the SAGE-III on ISS Satellite Instrument is Assess the performance of OMPS flying on the Suomi-NPP satellite.


The Spectral Band of the Band Cameras Camera is 391.4 nm.


The End of Life Date of the Sich-2 Satellite is 12 Dec 2012.


The Receiver Operation of the LCT Laser Communication System is Optically adding a locally generated field to the receiver field prior to photodetection.


The Total Mass of Jet Streams of the Juno Spacecraft is About 1% of Jupiter's mass.


The Purpose of the Spire Satellite Constellation is Collect global weather data.


The Launch Date of the VNREDSat-1A Satellite is January 08,2013.


The Detector of the SAGE-III Spectrometer is CCD and photodiode.


The Power of the INSAT-2A/2B Satellite is 1.18 kW.


The Operation Extension Date of the Cluster Satellite Mission is December 31, 2009.


The Power of the SeaWinds scatterometer Scatterometer is 250 W.


The Quantity of the MP6 6U CubeSat Satellite is 4.


The Development Status of the Intermediate Experimental Vehicle Spacecraft is Unknown.


The Off-nadir Angle of the SAR Synthetic Aperture Radar is 35º to the right side of the satellite.


The Function of the Interface Chip Chip is Provides a compliant implementation of the USB standard.


The URL of the POPSAT-HIP1 Satellite is http://blog.isilaunch.com/?p=885.


The Voltage of the 28V main bus Power Bus is 28V.


The Launch Date of the GOCE Satellite is Unknown.


The Mosaic Image Tile Time of the EUI Instrument is About 10 minutes.


The Pre-Flight Characterization of the TRUTHS Reference Sensor is Good level of pre-flight characterization of the sensor under test.


The Mass of the FGM Instrument is 3.0 kg.


The Number of Satellites of the Unseenlabs constellation Satellite Constellation is Between 20 and 25 by 2025.


The Angle Between Fixed Panels of the CHEOPS Satellite is 67 degrees.


The Subcontractor of the SBSS Satellite System is Ball Aerospace & Technologies Corp..


The Insertion Date of the P1 Spacecraft is August 23rd, 2010.


The Panel Quantity of the SAR Antenna Antenna is 32 slotted waveguides.


The Effective FOV of the Channel 5 Sensor is 30 km x 67 km.


The Launch Date of the BeiDou-3S Satellite is 2015/2016.


The Purpose of the JIB Antennas Antennas is Support Ship ID Capability.


The Anticoincidence CsI Crystal Thickness of the GRS Gamma-Ray Spectrometer is 30 mm.


The FOV of the Observation Instrument Telescope/Spectrograph is 0.1º x 7.3º + 0.2º x 0.2º (7.5º full length).


The Measurement Error of the Instrument Satellite Instrument is Slightly deteriorated when no ground echo was retrieved.


The Integration Time of the Radiometer Instrument is 65 ms.


The Discovery Date of the Solar Dynamics Observatory Satellite is 24 years ago.


The Honeycomb core thickness of the Bus structure Satellite Structure is t = 10. 8 mm.


The Bandwidth Transition Processing of the SAR Processor Data Processor is Process for the "lower performance" i.e. when a switch occurs between 84 MHz and lower bandwidth, it extends the acquisition with the lowest bandwidth.


The Orbital period of the KOMPSAT-3 Satellite is 98.5 minutes.


The GPS Antennas of the NOX Payload Satellite Payload is Switchable pair, one pointing to the zenith and used for POD, and a second one oriented in an anti-flight direction (pointing at the Earth horizon) devoted to occultation measurements.


The Instrument Heritage of the EPI-Hi Particle Measurement Instrument is LET (Low Energy Telescope) and HET (High Energy Telescope).


The Data Rate of the WiFS camera Camera is 2.06 Mbit/s.


The Orbital Insertion at Ganymede of the Juice Spacecraft is December 2034.


The Polarization of the ICI instrument Receiver is V and H.


The Launch Date of the ANUSat Satellite is April 20, 2009.


The Components of the Atmospheric Chemistry Suite Spectrometer is Three infrared spectrometers.


The Goal Mission Life of the PARASOL microsatellite Satellite is Two years.


The Laser Altimetry Data Processing of the Chang’E-1 Satellite is URL: ftp://202.127.24.130/pub/pjs/%D6%D0%B9%FA%BF%C6%D1%A7%D7%A8%BC%AD/AOGS-PS-0134_1.doc.


The Dimensions of the QSat-EOS bus Microsatellite bus is 492 mm x 503 mm x 502 mm.


The Registration Time of the RGD Instrument is 20 ms.


The Type of the Antenna ADS-B Antenna is Planar with two elements.


The Impact of the Argo Oceanographic Program is Change our understanding of the world's oceans, opening in fact a new era of oceanography.


The Location of the Ground Station Ground Station is Tarusa (Russia).


The Category of the PPS-1350-G Hall-effect thruster is Hall-effect thrusters.


The Distance from Earth of the Ophiuchus galaxy cluster Galaxy Cluster is 390 million light years.


The Conference Date of the Multi-satellite Operations System System is April 25-30, 2010.


The Components of the Instrument Control Unit (ICU) Control Unit is Phasemeter, Laser Ranging Processor (LRP), narrow linewidth NPRO laser, Laser Stabilization Unit (LSU), interferometer Optical Bench Assembly (OBA), Retro-Reflector Unit (RRU), scale factor measurements system (SFMS), Ultra Stable Oscillator (USO).


The Launch Date of the PACE Satellite is 19 June 2014.


The Vertical resolution of the UV/VIS Spectrometer Spectrometer is 1.7 km.


The Historical Record Publication Date of the Landsat-7 Satellite is Oct. 2006.


The Technology Integration of the SATis5 Testbed is 5G communication environment including satellite and terrestrial components.


The URL of the Grace Mission Satellite is https://web.archive.org/web/20230406203004/http://www.csr.utexas.edu/grace/operations/.


The Fuel Tank Status of the Kepler spacecraft Spacecraft is Running very low.


The Observation Type of the RHESSI Satellite is Flare.


The Student Collaboration Goal of the IMAP Mission is Provides students of diverse backgrounds with hands-on experience designing and building a CubeSat and two scientific instruments.


The URL of the Deep Space 1 Satellite is http://nmp.jpl.nasa.gov/ds1/NewsConference/04_06_99DS1.pdf.


The Antennas of the GPS receiver Receiver is 4 antennas.


The Data Archive Size of the Gaia Satellite is 1000 1 TB hard drives from a top-end home PC.


The Workshop Date of the MXGS Apparatus is May 19-22, 2009.


The Containment of the Calf Canyon-Hermits Peak Fire Fire is 40 percent.


The EPS of the SCARAB 1U CubeSat bus is Clyde Space 1U EPS w/Lithium-polymer battery.


The Mission Life of the Telescope Optical Instrument is 5-year minimum lifetime.


The Signal Processing of the NTS AIS Receiver Communication Receiver is Attempt to unravel the overlapping messages.


The Total Mass of the ASAP Nanosatellite is About 3 kg.


The Bulk Water Inventory of the Mars Planet is Global Equivalent Layer (GEL) of ~30 m.


The Orbit Type of the CeREs CubeSat Satellite is Circular.


The Altitude Accuracy of the Bloostar Launch Vehicle is ±5 km.


The Design of the OMI Instrument is Conceptual.


The Expected Completion Date of the ELSA-d Mission is April 2020.


The Operator of the TIM and SIM instruments Instruments is NOAA.


The Detector Function of the Conventional Interferometers Interferometer is Collects light over the full aperture of the critical optical components.


The UHF Carrier Detection Time of the MarCO-B Satellite is 11:41 am.


The 3-axis stabilization of the BEESAT-3 Satellite is Yes.


The Event of the Land Glacier Glacier is Part of the glacier’s ice tongue crumbled away.


The X-ray Spectrum of the AXP Anomalous X-ray Pulsar is Extends up to energies of at least 150 keV.


The Location of the Richat Structure Landmark is Mauritania.


The Maximum Data Rate of the Channel Communication System is 1674 Mbit/s.


The GSD of the DMC-2G imager Imager is 22 m.


The Accuracy of the GPS-fed high-accuracy ephemerides Data is ~5 m.


The Launch Provider of the COSMO-SkyMed-1 Satellite is ULA.


The Responsivity Measurement of the Responsivity Measurement Instrument is 1.37 A/W.


The Launch Site of the OPAL Satellite is VAFB, CA.


The Frequency Band of the COM Communications System is VHF/UHF.


The Starlink Satellites Launch Date of the SpaceX Company is 14 March 2021.


The Type of the OBC On-Board Computer is High-grade main OBC.


The Charge Range for Isotopes of the LEICA Particle Detector is 2 - 16.


The End of Life Date of the TechnoSat Nanosatellite is Operational as of February 2023.


The Data Products of the Sentinel-4 Satellite is Ozone total column and tropospheric sub-column, nitrogen dioxide total column and tropospheric sub-column, sulphur dioxide total column, formaldehyde total column, glyoxal total column, cloud optical thickness, fraction and altitude, aerosol column thickn.


The No of bands/channels of the MWTS Microwave Temperature Sounder is 4.


The Waste Capacity of the HTV-6 Spacecraft is Up to 6 metric tons.


The Location of the SPIE Office is NASA/MSFC (Marshall Space Flight Center) in Huntsville, Alabama.


The Contract Award of the Northrop Grumman Company is $692 million.


The Type of the Rate gyro Sensor is Gyro chip.


The Manufacturer of the Gonets-M No.3 Communication Satellite is JSC Academician M.F. Reshetnev Information Satellite Systems.


The Distribution of the MET data Data is HRIT/LRIT transmission within 15 minutes after image acquisition.


The Launch Time of the IDEA-OSG 1 Microsatellite is 05:41 UTC.


The Observation of the New Horizons Spacecraft is Fluxes of charged particles in Jupiter's magnetotail.


The Measurement of the Gaia Satellite is The acceleration of the Solar System.


The URL of the Earth Observation Constellation Satellites Satellite Constellation is http://www.nspo.narl.org.tw/ICGPSRO2013/.


The Wing Status of the AC4-B Satellite is Open.


The Magnitude of the Tohoku-Kanto earthquake Earthquake is 9.0.


The Number of Ozone Altitude Profiles of the UVSP Instrument is Approximately 20,000.


The Close-Up Date of the Arrokoth Celestial Body is 13 February 2020.


The Launch Vehicle of the Chang'e-5 Spacecraft is Long March 5 (CZ-5).


The Components of the ULF Sensor Sensor is Search coil, calibration coil, amplifier/filter circuit.


The Design Considerations and Programme Status of the TecSAR Satellite is Y. Sharay, U. Naftaly, “TecSAR: design considerations and programme status,” IEE proceedings of Radar, Sonar & Navigation, Vol. 153, No 2, 2006.


The URL of the TOPCAT Satellite is http://www.bath.ac.uk/elec-eng/invert/topcat.html.


The Hosted Payloads of the Prometheus Satellite Satellite is 1.5U payload module can be added to each satellite.


The Manufacturer of the ADCS Attitude Determination and Control Subsystem is Stellenbosch University.


The Bandpass Filters of the EXI Camera is 3 UV bands and 3 visible (RGB) bands.


The | of the Justin C. Kasper, Bennett A. Maruca, Michael L. Stevens, Arnaud Zaslavsky Authors is Justin C. Kasper, Bennett A. Maruca, Michael L. Stevens, Arnaud Zaslavsky.


The Orbit Distance of the 55 Cancri e Exoplanet is 0.015 astronomical units from its Sun-like star.


The Data quantization of the ALOS-3/PRISM-2 Satellite is 11 bit.


The Announcement Date of the Galileo Second Generation Satellite is 27 May 2021.


The Ground-Station Uplink Passes of the SpinSat Satellite is Within the preceding 5 days.


The Mounting Satellite of the METimage Instrument is MetOp-SG-A.


The Mission Objective of the OSMA-1 Satellite is Conduct a series of demonstrations of in-space robotic assembly of an antenna and a boom.


The Microprocessor of the TPMU Device is ADuC845.


The Operating Temperature of the VNIR Detector is 257 K.


The Power of the COPS Ka-band Communication Payload is 1077 W.


The Black Hole Jet Discovery Date of the Chandra X-ray Observatory X-ray Observatory is 9 January 2019.


The Launch Date of the NanoSail-D Satellite is Aug. 2 2008.


The Number of Satellites of the FORMOSAT-7/COSMIC-2 Satellite Constellation is 6.


The Spectral Sampling of the Ma_MISS Spectrometer is About 20 nm.


The Primary-Spacecraft Interfaces of the CubeStack Multi-Payload Adapter is 98.5 cm Ø and 61 cm Ø.


The Closest Approach Distance of the BepiColombo Spacecraft is 199 km.


The Payload Mass of the INTEGRAL Satellite is 2 t.


The Pixel Size of the Main Camera Camera is 100 m in its central field of view.


The Value of the Group Delay Uncertainty Parameter is Few nanoseconds (1-3 ns).


The Thermal Control of the ITASat CubeSat Satellite is Passive.


The Objective of the MarCO CubeSat is Relay back InSight data as it enters the Martian atmosphere and lands.


The Launch Date of the ALL-STAR-1 Satellite is April 18, 2014.


The Length of the Tianhe Space Station Module is 16.6 meters.


The LISS-2A/B Data Downlink Transfer Rate of the Satellite Satellite is 10.4 Mbit/s.


The Ground-Based Observation Sites of the ExoCube Satellite is Arecibo, Wisconsin, Kitt Peak, and Cerro Tololo.


The Components of the CCC (Coordinated Constellation Concept) Satellite Constellation is German TerraSAR-X/TanDEM-X and the Spanish PAZ satellite.


The Orbit Type of the Rideshare mission Satellite is SSO (Sun-Synchronous Orbit).


The Ground Segment of the QuakeSat Satellite is Unknown.


The Accuracy of Wind Velocity (Stratosphere) of the Aeolus Satellite is 3 m/s.


The Measurement Category of the FormoSat-1 Satellite is Ocean colour/biology.


The Calibration Method of the MWHS-II Microwave Humidity Sounder is Two points periodically.


The Operator of the OrbView-2 Satellite is ORBIMAGE.


The Observation End Time of the INTEGRAL Satellite is 22:14:36 on 25 January.


The Multispectral Bands Off-nadir Resolution of the WorldView-3 Satellite is 1.38 m.


The Height Envelope of the UKube-1 Satellite is < 108 mm.


The Manufacturer of the Heinrich-Hertz satellite Satellite is DLR-RfM (German Aerospace Center – Space Administration).


The Interaction with Matter of the Neutrinos Subatomic Particles is Incredibly rarely.


The Plastic Scintillator of the Range Calorimeter Particle Detector is Side of 15 cm.


The Carbon Sink of the Northern Forests Ecosystem is Yes.


The Altitude of the GRACE-FO satellites Satellite is ~490 km.


The Pointing Accuracy of the Resurs-P1 Satellite is 0.2 arcmin.


The Measurement Capability of the ASCAT C-band radar is Day and night.


The Length of the Telescope Assembly Optical Instrument is 100 cm.


The Resolution of the OVM Overhauser scalar magnetometer is 0.1 nT.


The Capacity of the XTA Xenon Tank Assembly is 60 liters.


The Beamwidth of the HSB Humidity Sounder is 1.1º.


The Ion Masses of the COSIMA Mass Spectrometer is Above 28 Daltons.


The Function of the Gaia Space Telescope is Scans the sky.


The Conference Date of the LPT9310 COTS cooler Cooler is May 23-27, 2016.


The Duty Cycle of the VRSS-1 Satellite is 10%.


The Length of the Hoytether Tether is 10 m.


The Power Consumption of the APD Avalanche Photodiode is Low.


The Flight Time Before Reentry of the RainCube Satellite is No more than twelve months.


The Calibration Approach Date of the MICROSCOPE Satellite is 2003.


The Orbit Reach Date of the Shenzhou-13 Spacecraft is 15 October 2021.


The Dynamic Range of the Receiver Communication System is ≤ 15 dB.


The Heritage of the OMPS UV Hyperspectral Imaging Spectrometer is SBUV/2, TOMS and GOME.


The Interface Control Document Date of the NanoRacks CubeSat Deployer Deployer is Dec. 10, 2013.


The Range of the Ozone Measurement Instrument Atmospheric Measurement Device is 50-650 Dobson Units (DU).


The Objective Aperture Diameter of the VSSC Camera is 0.25 m.


The Launch Year of the CYGNSS Satellite Mission is 2016.


The Closest Approach Distance of the Rosetta Spacecraft is 75,000 km.


The Wavelengths of the OSIRIS Infrared Imager is 1263 nm, 1273 nm, 1530 nm.


The Rate of Change of the Delta in Solar Phase of Apsides Orbital Parameter is 0.8º/year.


The Fixed Distance from CALIPSO of the CloudSat Satellite is About 460 km.


The Mass of the Flight Unit Satellite Component is 8.5 kg.


The Test Location of the Thermal Testing Test Type is Thermal vacuum chamber on USSC premises.


The Objective of the CERES Instrument is Provide continuity of the top-of-the-atmosphere radiant energy measurements.


The Outer Edge Length of the MLI Thermal Control Device is Unknown.


The Orbit Type of the NigeriaSat-2 Satellite is Sun-synchronous circular orbit.


The Responsible Orbit of the JPSS Satellite is Afternoon.


The Contract Date of the Satellite Vu’s first satellite Satellite is December 16, 2021.


The Orbit Inclination of the Optsat-3000 Satellite is 98.28º.


The Mission Objective of the AMSU Microwave Radiometer is Obtain global temperature and humidity profiles.


The Stability of the Electrical Field Satellite System is < 1 mV/m over 1 month.


The Total Mass of the SZ-7 Spaceship is ~7800 kg.


The Loch-in Zone of the Satellite Imaging Satellite is 800 km.


The Presentation Date of the UniSat-5 Satellite is April 23-25, 2014.


The Number of Launches of the Falcon 9 Rocket is Three.


The Data Quantization of the 4-band CCD Imager Instrument is 12 bit.


The Communication Architecture of the BioSentinel Spacecraft is CubeSat direct-to-ground communication, CubeSat to Tracking Data Relay Satellite System (TDRSS) communication, CubeSat constellation with Mothership direct-to-ground communication, and CubeSat Constellation with Mothership communication through KSA (K-ban.


The Presentation Date of the Micro Digital Sun Sensor Sensor is Aug 25-27, 2004.


The Wavelength FWHM of an unresolved line of the Spectrometer Instrument is 0.039 µm.


The Operation Period of the SAM-II Sun Photometer is 1978 to 1995.


The Manufacturer of the DTUSat-2 1U CubeSat is DTU (Technical University of Denmark).


The Power of the Microsatellite Satellite is 30 W (max).


The Accuracy of Atmospheric Temperature Profiles of the CrIMSS Instrument Suite is 1 K.


The Number of Experiments of the ORS-3 Mission Satellite Mission is 2.


The Resolution of the NAOMI Imaging Instrument is 2.5 m.


The Microcontroller of the Sensor Suite Payload is Shared.


The Spectral Range of the VNIR-NP channels Sensor is 380 nm to 865 nm.


The Resource Requirements of the SWiPS Sensor is Low.


The Orbit Inclination of the CubeSats Satellite is 97.6º.


The Actuators of the ADCS Attitude Determination and Control Subsystem is Magnetorquers.


The Bus Dry Mass of the Spacecraft Satellite is 410 kg.


The Total Mass of the LWIR Camera Camera is 2.1 kg.


The Solar Array Power of the THEMIS (and ARTEMIS) spacecraft Satellite is Barely moved below BOL values.


The Number of Wheels of the Yutu 2 Lunar Rover is 6.


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


The Calibration Equipment of the Monochromator Instrument is “HP 70950A”.


The Article Date of the Black Hole Celestial Object is July 12, 2016.


The Power of the Spacecraft Satellite is Up to 1065 W.


The Antenna Rotation Speed of the SWIM Real Aperture Radar is ~6 rpm.


The Propellant Type of the Chemical Propulsion Thrusters Orbit Maintenance is Monomethylhydrazine and nitrogen tetroxide.


The Sensitivity of the Interferometric Spectroscopic Instruments Spectroscopic Instruments is Typically 100 times those of conventional grating spectroscopic instruments of similar size.


The Size of the StangSat Satellite is 1U.


The Spectral Ranges of the WorldView-110 camera Camera is Eight bands of the short-wave infrared range.


The Correlation of the Spectral Angle Measurement is With the white panel when the yellow coupon is used as a reference.


The NEΔT (K) of the ICI-11 Radiometer is 1.5.


The Arrival Date of the Sentinel-1B Satellite is March 22, 2016.


The Sun Sensor Field of View of the ACS Attitude Control Subsystem is ±45º.


The Angle of the Zenith FOV Field of View is 35º.


The Laser Type of the Laser Head Unit (LHU) Laser Unit is Narrow linewidth NPRO laser.


The Imagery Resolution of the WorldView-3 Satellite is 30 cm.


The Outflow Length of the Milky Way Galaxy is Hundreds of light years.


The Supported RTOS of the RAD750 SBC Single Board Computer is VxWorks (versions 5.4, 5.5, and 6.2).


The Developer of the FSSCat Satellite is Universitat Politèctica de Catalunya (UPC).


The Manufacturer of the Hardware Quick Look SAR Processor SAR Processor is MRSA/SAC team.


The Camera Suite of the OSIRIS-REx Mission is OCAMS.


The Launch Date of the Inspiration4 Crewed Mission is Sept. 15.


The Impact on Measurements of the Thermal Effects Phenomenon is Systematic errors.


The Mass of the Transmitter Communication Device is 700 g.


The Cadence of the BRITE Satellite is < 100 minutes.


The Mass of the DebriSat Satellite is 56 kg.


The Integration Dates of the Galileo Satellites Satellite is July 11, 2018.


The Size of the Secondary Mirror Optical Component is 2.4-foot (0.74 m).


The Power Consumption of the APD detector Experiment is Low.


The Spectral Range of the AVHRR/3 Sensor is 2.225-2.275.


The Value of the MTF Performance Requirement is Better than 0.3 Nyquist.


The Attitude Control Error of the ADCS Attitude Determination & Control Subsystem is ≤ 30 µrad.


The Internal Calibration Modes of the MIRAS Instrument is Short duration, full orbit.


The Radio Type of the ELFIN-A Satellite is AstroDev Helium radio.


The Secondary Voltages of the PCM Power Control Module is +28 V, ±5 V, ±15 V, and ±12 V.


The Altitude of the TEMPO Instrument is 35,786 km.


The Number of Published Images of the MoonKAM Camera System is Nearly 120,000.


The Data Collected of the TerraSAR-X Satellite is 1.34 petabytes.


The Asia-Pacific Region Service Start Date of the BDS Satellite is 2012.


The Solar Sail Deployment Test Support of the NEA Scout Spacecraft is Helium balloons.


The Structure Dimensions of the DSP satellites Satellite is 2.1 m diameter and 1.23 m in height.


The Swath Width of the GF-2 Satellite is 45 km.


The Temperature of the Proton Component Measurement Accuracy of the DSCOVR Satellite is 50%.


The Plate Scale of the EXI instrument Imaging Instrument is 0.85 mm/º.


The Antennas of the R3 Spacecraft Satellite is Two patch antennas.


The Observation Geometry of the MOMS-02 Instrument is Stereo Triplets.


The Antennas of the RF Communications Data Transmission is Two existing two-axis gimbaled directional antennas.


The Controller Modes of the GOCE Satellite is FPM and higher DFACS modes.


The Width of the Dimorphos Asteroid is 160 meters.


The Ground Resolution (Stripmap mode) of the XSAR SAR is 3 m.


The Operation of the TCU Thermal Control Unit is Acquires parameters from sensors, monitors and commands valves, issues commands to the FCA, commands heater chains, monitors thermistors, commands valves, monitors their position, monitors pressure and temperature parameters.


The Filter Type of the VIS channel Spectrometer is Block with Aluminum.


The Latency of the ATL09 ATLAS Atmosphere Cloud Layer Characteristics Data is 45 days.


The Data Rate for Images of the IRIS Observatory is Every 5–10 s.


The Payload Complement of the ALBus CubeSat Satellite is 13 CubeSats.


The Descent Path Length of the Lander Spacecraft is 450 km.


The Temporal Resolution of the ELENA Sensor is 40 s.


The Report Release Date of the SMAP Satellite is January 2007.


The X-band radio of the InSight Spacecraft is Measure the "wobble" of Mars as it spins.


The No of bands/channels of the MERSI Medium Resolution Spectral Imager is 20.


The Bit Depth of the fADC A/D Converter is 14 bit.


The Range of the Acceleration Sensor is -50 to +50 G (3-axis).


The Accuracy of the SCM Satellite Charging Monitor is ≤0.01 pA/cm2.


The Diameter of the Holes Drill Holes is 60-centimeter.


The Edition of the Observation of the Earth and Its Environment Documentation is 4th.


The Frequency of the Radar Radar is 17 GHz.


The Date of NASA Feature of the Jupiter's Auroras Natural Phenomenon is 6 September 2017.


The Burned Area of the Calf Canyon-Hermits Peak fire Fire is 270,000 acres.


The Repeat Cycle of the Resurs-P1 Satellite is 3 days.


The Affiliation of the Ayyoob Sharifi Associate Professor is Urban Knowledge-Action Network.


The Reflectance of the Reflection Diffuser Calibration Device is ρ=100%.


The Number of Subapertures of the SMART Imaging System is 8.


The Launch Date of the Deployment Systems Satellite is July 12, 2006.


The NiH (Nickel Hydrogen) of the Battery System Type is A NiH (Nickel Hydrogen) battery system provides power for eclipse phase operations.


The TGFs Detected of the RHESSI Satellite is Over 1000.


The Announcement Date of the XMM Newton Satellite is 04 February, 2000.


The Mission Date of the FireBird Satellite is May 11-15, 2015.


The Rock Deposits Size of the LRO Satellite is Less than 500 m across.


The Wavelength FWHM of an unresolved line of the Spectrometer Instrument is 0.013 µm.


The Configuration of the µSDTN transponder Transponder is Core transponder on the left; diplexer, RF switch and test couplers on the right.


The Swath Width of the JPL Microwave Radiometer Radiometer is 9 km.


The Operation of the DMC Constellation Satellite Constellation is Share unused capacity with other Members.


The Funding Source of the NASA Heliophysics Technology and Instrument Development (H-TIDeS) Program is NASA.


The Orbit Altitude of the STARS spacecraft Satellite is 666 km.


The Launch Time of the NeuSAR Satellite is 0832 EDT.


The Prime Contractor of the Spacecraft Satellite is Airbus UK.


The Conference Presentation Date of the EnMAP Hyperspectral Imager Imaging Satellite is July 31-Aug. 4, 2006.


The Transmission Capacity of the IOV Payload Satellite Payload is Dynamic allocation.


The Period (min) of the Meteor-1-2 Satellite is 97.7.


The Frequency of the X-band Band is 10.2 GHz.


The Conference Date of the RazakSAT Satellite is Aug. 14-17, 2006.


The Launch Date of the QBITO CubeSat is 18 April 2017.


The Distance from Earth of the Kepler-442b Exoplanet is 1,100 light-years.


The GPS receiver of the TDX/TSX Satellite is IGOR GPS receiver.


The Objective of the Lemur-2 Satellite Constellation is Ship tracking via AIS (Automatic Identification System) with SENSE.


The Depth Range of the Ma_MISS Spectrometer is Between 0 and 2 m.


The Inclination of the CeREs CubeSat Satellite is 85º.


The Spectral Channel 2 of the Satellite Imaging Satellite is 0.61-0.69 µm.


The Meeting Date of the Nigerian National Geospatial Data Infrastructure Programme Programme is March 1-2, 2007.


The Ground Resolution at Apoapsis / Priapsis of the EXI instrument Imaging Instrument is 4.9 / 2.3 km per pixel.


The Interface of the CEPA Adapter is FRAM (Flight Releasable Attachment Mechanism).


The Data Rate of the VHF COTS transmitter Transmitter is 1200 to 9600 bit/s.


The Downlink Speed of the Compact Laser Comms Terminals (CLCT) Communication Device is Up to 10 Gbit/s.


The Upward Drift of the Plasma Blobs Phenomenon is Invoked away from the magnetic equator.


The Function of the Electromagnetic Calorimeter Instrument Component is Measure the energy of particles interacting in its sensitive volume and image the shape of these interactions.


The Drag-Free Performance Metric of the Drag-Free Technology Technology is Residual acceleration of the test mass in units of m/(s2Hz1/2).


The Power of the RF Output Power Communication System is 3 W.


The Type of the PRISM-2 Instrument is Stereo high-resolution instrument.


The Institute of the DAXSS Payload is LASP (Laboratory for Atmospheric and Space Physics).


The Output Open Circuit Protection of the DC-DC converter Power Converter is Yes.


The Orbit Data of the Satellite GFO is Medium Laser orbit data.


The Project Start Date of the Heinrich Hertz Satellite is Mid-2009.


The Demonstration Date of the Polar Sea Ice Detection Satellite is 3 February 2020.


The Diameter of the Antenna Satellite Component is 0.1m.


The Polarization of the Sentinel-1 Satellite is Selectable dual polarization.


The Usage of the RADMON Instrument is Used sporadically and depending on the system's instantaneous power demands.


The Solar Arrays of the TacSat Satellite is Thin Film.


The Capture Box Separation of the ASTRO Satellite is < 1 m.


The Measurement Technique of the Biological Specimens Samples is Optical absorbance and density.


The Spatial Baseline of the GF-3 SAR Satellite is 250 m.


The X-band Tx Power of the RF communications Communication System is 6 W.


The Data Update Frequency of the IMERG Algorithm is Every half-hour.


The Function of the Magnetorquer Attitude Actuation Device is Allows full 3-axis attitude control experimentation to be performed.


The Image Gain of the PMC-2 Imagers Imaging System is 1~5 levels.


The Electrical Power System of the ESTCube-1 Satellite is COTS solution.


The Gain of the Antenna Communication System is Maximum gain normal to the spin axis of the bus.


The Voltage Output of the PSU Power Supply Unit is 3.3 V.


The Scan Mirror of the TEMPO Instrument is Included.


The Beam width of the Sub-mm Band is 4.5 mrad.


The Purpose of the Kepler Mission Space Telescope is Detection of extra-solar planetary systems.


The Input Angle alpha of the Long Wavelength Band Spectrometer is 21.9º.


The Bandpass of the Short Wavelength Band Spectrometer is 900-1150 Å.


The Modulation Scheme of the VHF COTS transmitter Transmitter is BPSK.


The Identification Time of the CSpOC Catalog Catalog is 8 days after launch.


The Data Transmission Rate of the X-band Communication Band is 25 Mbit/s.


The Development Status of the Göktürk-1 Satellite is Stuck in a production facility in France.


The Retirement Date of the CBERS-2 Satellite is Late 2007.


The Orbit Shape of the XO-3b Exoplanet is Eccentric (oval).


The Role of the Central Bulkhead Assembly Satellite Component is Facilitate connectivity of the imager instrument to the spacecraft platform in the desired semi-kinematic configuration.


The Platform of the Ground Software Architecture System is Windows or Linux PCs.


The Objectives of the C3D Instrument CMOS Sensor is Provide a technology demonstrator to improve the TRL of new CMOS sensors, Correlate the effects of space radiation with ground based testing, Capture images of the Earth.


The URL of the MASCOT Lander Lander is http://arc.aiaa.org/doi/pdf/10.2514/6.2016-2386.


The Image Displacement of the Quad-cell Instrument is <10 -2π sensitivity.


The Data Mapping Period of the Envisat Satellite is 1994 to 2010.


The Location of the Polar Vortex Meteorological Phenomenon is High above the North Pole in the polar stratosphere.


The Crime Scene Investigation Start Date of the Hera Spacecraft is Late 2026.


The Attitude Determination Device of the ACS Attitude Control Subsystem is Commercial star tracker, AST (Autonomous Star Tracker).


The Sensitivity of the VT Telescope is High sensitivity, in particular at long wavelength.


The Hardware Maintenance Costs of the MEOLUT Next Local User Terminal is The lowest on the market.


The Mission Extension Announcement Date of the LADEE Satellite is Jan. 31, 2014.


The Output Power of the TXS S-band Transmitter/Transceiver is 28 dBm.


The Lunar Axial Tilt of the DSN Stations Antenna is 4.5º to 5.5º.


The End of Life Date of the MOMS Satellite is 16 August 1999.


The Communication System of the TanDEM-X Satellite is X-band inter-satellite link.


The Clock Frequency Stability of the Spacecraft Satellite is PHM (Passive Hydrogen Maser):<4.5 x 10 -14  at 30000 s.


The Mission Type of the IRIS Satellite is 3-axis stabilized, sun-pointed.


The Maneuvers per Year of the ARTEMIS Satellite is Approximately two.


The Solar Sail Size of the NEA Scout Solar Sail Technology Demonstration Spacecraft is 925 square feet (86 m2).


The Boat Detection of the VIIRS Instrument is 10,000 to 20,000 boats every night.


The Target Stars of the Gaia Space Astrometric Mission is > 1000 million.


The Launch Date of the Galileo satellites Satellite is 21 October 2011.


The Mission Type of the FalconSat-7 Satellite is Proof-of-concept.


The Purpose of the VCST Team is Provide independent evaluation of the VIIRS calibration and SDR product quality.


The Pulse Width of the Lasers Light Source is 1 to 6 ms.


The Kurs-NA Radio System Test Start Date of the Prichal Module is October 20.


The Developer of the Space Launch System Spacecraft  is NASA/MSFC.


The Ground Pixel Size of the WAOSS-B Sensor is 185 m.


The Fundraising Goal of the Inspiration4 Mission is $100 million.


The Radial Position Control of the OAP to Housing Connection is Close-fitting sleeve.


The Mission Start Date of the Deep Space Atomic Clock Clock is Oct. 9, 2012.


The End of Life Date of the FedSat Satellite is 14 Dec 2005.


The Affiliation of the CRISTAL Satellite Mission is Copernicus program.


The Look Angles of the Antenna Subsystem Communication is 42.62º and 49.38º.


The Affiliation of the Shuaib Lwasa Professor is Urban Action Lab, Makerere University.


The Discovery Date of the GRB 150101B Gamma Ray Burst is January 2015.


The Number of Operational Satellites of the HY-2 Satellite is 3.


The Size of the Miniaturized X-band transponders Communications System is 5 cm x 5 cm x 7.6 cm.


The Communication System of the CM1 and CM2 6U CubeSats is Phased array communication system.


The Data downlink of the ALOS/PRISM Satellite is 277.52 Mbit/s (Ka-band).


The Expected Extended Lifetime of the Aeolus Satellite is Another year.


The Last Chance to View of the BepiColombo Satellite is 14 June 2017.


The Presentation of the PRISMA Satellite is Flight Results from PRISMA Formation Flying and Rendezvous Demonstration Mission.


The Funding from ESA of the Copernicus Environmental Monitoring Satellites is 2.55 billion euros.


The Detection Capability of the TimePix radiation sensors Sensor is Able to detect radiation flux spikes of over 1000 times the background level during a single solar particle event (SPE).


The Frequency of the SAR Synthetic Aperture Radar is L-band (1.275 GHz).


The Location of the RF Backup Station Ground Station is Matsumoto.


The Material of the X-ray mirrors Optical Instrument is Nickel.


The Launch Date of the OneWeb Satellite Constellation is 7 February 2020.


The Length of the Spin Plane Dipole Antenna Antenna is 90 m.


The FPGA Co-processor of the SGR-ReSI GNSS Reflectometry Instrument is Virtex 4.


The Capacity of the Image Storage Data Storage is 8 GB + 32 GB of science data.


The Computing Resource of the 'Fight club' asteroid simulations Simulation is Bluecrab supercomputer cluster.


The 2.5 m of the MPO Boom Length is The 2.5 m long boom carrying the magnetometer sensors onboard ESA’s BepiColombo MPO.


The Operational Modes of the Tsubame microsatellite Satellite is Detumbling mode, Safe mode, Standby mode, Camera mode, Gamma-ray mode.


The Range of Observable Flow Angles of the FSU Solar Wind Faraday Cup is 56º FOV.


The 3 km of the Radar Data Spatial Resolution is The radar data will provide the freeze/thaw measurement with 3 km spatial resolution.


The Secondary Body Diameter of the Didymos Asteroid is About 150 m.


The Dimensions of the SAR Antenna Antenna is 1.5 m x 15 m.


The Deployment Wait Time of the Payloads Satellite Components is 15 seconds.