The Purpose of the Avionics Air Assembly (AAA) Fans Hardware is Critical high speed fan spares that provides cooling to support continued operations for Environmental Control and Life Support System (ECLSS) Temperature and Humidity Control (THC) across the space station.


The Purpose of the RapidScat Satellite Instrument is Spying tropical-storm-force winds.


The Ka-band Data Rate of the CASCADE Satellite Communication System is Up to 2.1 Gbit/s using higher order modulations.


The Destination of the Queqiao Communication Satellite is EML-2.


The Launch Date of the MidSTAR-1 Satellite is 9 March 2007.


The Image Geolocation Accuracy of the SSTL-300 bus system Satellite Bus System is < 35 m (CE90 = Circular Error 90%).


The Mission Number of the Vega Launch Vehicle is 19.


The On-Orbit Useful Life of the SXI Spacecraft is 3 years with a goal of 5 years.


The Propellant Quantity of the Propulsion System Propulsion Subsystem is 103.5 kg.


The Propellant of the DMC Propulsion Subsystem Electric Propulsion is Butane.


The Thrust Duration of the LightSail-2 Spacecraft is One month.


The Bus Configuration of the QuikTOMS spacecraft Satellite is Two rings stacked together vertically.


The Development Date of the FedSat Microsatellite is 1998.


The Altitude Range of the RAIDS Instrument is 75-220 km.


The Date of the Pre-CHUVA Field Campaign is 3-24 March 2010.


The Manufacturer of the OCO-2 Satellite is JPL.


The Controller of the ADCS Attitude Determination and Control System is Kalman Estimator.


The Mass of the GOMS-1 Satellite is 2580 kg.


The Distance from Earth of the M83 Galaxy is 15 million light-years.


The Centrifugal Force Cause of the LISA Pathfinder Spacecraft is Combination of the shape of LISA Pathfinder's orbit and the effect of the noise in the signal of the startrackers used to orient it.


The Image Credit of the Kepler Mission Space Mission is NASA.


The Mission Type of the Biomass Satellite is EO.


The Power Consumption of the Receiver Communication Device is 0.125 W.


The Observation Duration of the SPARCS Satellite is 1 day to 80 days.


The Spectral Range (µm) of the Band 10 Spectral Band is 0.90 - 0.965.


The Number of Satellites of the Planet SkySats Satellite Constellation is 21.


The Contributions of the DLR Agency is X-SAR hardware, ground systems, mission operations and data processing support.


The Orbit of the CHORUS Satellite is Non-sun-synchronous.


The Purpose of the BeaverCube Satellite is Educational mission to introduce students worldwide to aerospace science and technology.


The Groove Density of the Grating Optical Component is ~646 grooves/mm at the center.


The Debris Field Location of the Vikram Lander Lander is About 750 meters northwest of the main crash site.


The Start of Operations of the CCC (Coordinated Constellation Concept) Satellite Constellation is 2014.


The Function of the Transponder Device is Track the Biomass satellite.


The SAR Data Acquisition Date of the Copernicus Sentinel-1 Satellite is 2 September 2019.


The Manufacturer of the RTAFSAT-1 Satellite is Royal Thai Air Force.


The Main Port Mechanism of the PRISMA Satellite is Unknown.


The Telemetry Downlink Data Rate of the NEMO-HD Satellite is 8 kbit/s.


The Engine Type of the IES Ion Engine System is Xe microwave discharge ion engine system.


The Spatial Resolution of the MSU-SK Radiometer is 170 m (in VIS).


The Back-up Channel of the RF Communications Communication System is S-band.


The Discovery Year of the Itokawa Asteroid is 1999.


The ρIsp of the Thruster Propulsion System is 50% greater than hydrazine.


The Attitude Command of the MicroSCOPE Satellite is Inertial.


The Redundancy of the SSTL Signal Generator Chain Signal Generator is One chain.


The URL of the IBEX Spacecraft is http://www.swri.org.


The Failure Cause of the COPV Pressure Vessel is Accumulation of oxygen between the COPV liner and over-wrap in a void or a buckle in the liner.


The Instrument Power of the Instrument Sensor is 35 W.


The Manufacturer of the MST Star Tracker Star Tracker is TU Graz.


The Publication Date of the Iridium engineering magnetometer Magnetometer is December 15, 2000.


The Photometer Field-of-View of the Nanosatellite Satellite is 24º.


The SST Spatial Resolution of the CIMR Radiometer Imager is 15 km.


The Improvement Factor of the ELFIN Satellite is Two.


The Sponsors of the NanoSail-D2 Satellite is Army Space and Missile Defense Command, the Von Braun Center for Science and Innovation, Dynetics Inc.


The Orbit Inclination of the ALBus CubeSat Satellite is 85º.


The Mission Scientist of the Aeolus Satellite is Anne Grete Straume.


The Data Application of the DAICHI Satellite is Compilation of Global Digital 3D Map with World's Best Precision.


The Workshop Location of the RECCAP-2 Activity is Gotemba, Japan.


The Orbital Separation from SPOT-5 of the SPOT-4 Satellite is 166º.


The Momentum Wheels of the NigeriaSat-2 Satellite is 4 Microwheel 10SP.


The Self-apodisation effect of the Michelson Interferometer Interferometer is Reduces the signal level when increasing the FOV and the OPD range.


The Pointing Accuracy of the Spacecraft Satellite is ≤ 3º.


The Magnetometer of the ADCS Attitude Determination and Control Subsystem is 3-axes.


The Presentation Date of the An Efficient Photoelectric X-ray Polarimeter Device is 2001.


The Components of the Downlink Optical Communication System is Off axis parabolic mirror, fast tip/tilt mirror, dichroic beam splitter, DM (Deformable Mirror), wavefront sensor, scoring camera, fiber coupled to the DPSK/PPM receiver, waveplate, slow tip/tilt mirror.


The Telecommand Data Rate Range of the TTCS Telemetry & Telecommand Subsystem is 2-8 kbit/s.


The Mission Type of the HySIS Satellite is Earth Observation.


The Provider of the Picosatellite propulsion system Propulsion System is Aerospace Innovation GmbH.


The Resumed Work Days of the Chang'e-4 Lunar Probe is 21.


The Ion Energy Range of the SWEPAM Particle Detector is 0.26 - 35 keV.


The Launch Date of the Cheops Satellite is 18 December 2019.


The Contact Time of the STSAT-3 Satellite is 89 minutes after lift-off.


The Apogee of the RBSP spacecraft Satellite is ~ 5.8 RE.


The Operating Frequencies of the SMMR Microwave Radiometer is 10.7 GHz.


The Spatial Resolution of the GF-3 SAR Satellite is 3.5 m in azimuth and 5.5 m in range.


The Conference Presentation of the Near Earth Asteroid Scout Satellite is AIAA Space 2014 Conference and Exposition.


The Omni-directional Proton Energy Ranges of the MEPED Particle Detector is > 16 MeV, > 35 MeV, > 70 MeV and > 140 MeV.


The Type of the SUCHAI-1 Satellite is 1U CubeSat.


The NASA Feature Date of the IBEX Satellite is 5 August 2020.


The Performance of the S-band link Communication Link is Successfully established even in elevations below 20 degrees.


The End of Life Date of the Odin Satellite is Dec 2023.


The Conference Presentation Date of the Space Plug-and Play Avionics Avionics is April 25–28, 2005.


The Spatial Resolution of the Hyperion Imaging Spectrometer is 30 m.


The Scan Mechanism Assembly of the TEMPO Instrument is Provides high-precision pointing.


The Developer of the ROBUSTA-1B Nanosatellite is University of Montpellier students.


The Mass of the CartoSat-2E Satellite is ~712 kg.


The Presentation of the GPM Satellite is 14th European Space Mechanisms & Tribology Symposium – ESMATS 2011.


The Arrival Date of the BepiColombo Spacecraft is 2024.


The Press Release Date of the Smile Satellite is 30 July 2019.


The Launch Date of the SpIRIT Satellite is 2023.


The Redundancy of the TT&C Receiver Communication Device is Half Satellite.


The Design of the QuakeSat Satellite is CubeSat.


The Exposure Time of the VIS Camera is 565 seconds.


The Time Resolution of the FREND Instrument is From 1 second.


The Orbital Range of the Ryugu Asteroid is Mostly between Earth and Mars.


The Frequency of the Radar Radar is X-Ku dual-frequency.


The Typical Magnetic Field Strength of the Sunspot Solar Phenomenon is 3,000 gauss.


The Stabilization of the ADCS Attitude Determination and Control Subsystem is 3-axis.


The Data Acquisition of the PROBA-V Satellite is >1015 bytes.


The Type of the Magnetometer Sensor is Flux gate.


The Mission Type of the LAPAN-A2 Satellite is EO (Earth Observation).


The Width of the Deir el-Medina Pit on Comet 67P/Churyumov–Gerasimenko is 130 m.


The Affiliation of the IASI Instrument is CNES and EUMETSAT.


The Facilities of the Coordinated Observations Satellite Mission Activity is Magnetic and optical observatories, radars, receivers and heaters.


The Observation Date of the Orbiting Carbon Observatory-2 (OCO-2) Satellite is 8 February 2018.


The Data Delivery of the GBOT Ground Based Orbit Tracking is One set of data per day.


The Data Recorders Redundancy of the Vital Layer Data System Component is Two redundant recorders.


The Subaperture Radius of the SMART Imaging System is 0.8 to 0.2 mm.


The Voltage of the MTM main power bus Power Bus is 100 V.


The End of Life Date of the ARMADILLO Satellite is 25 June 2024.


The Total Mass of the Bus Satellite Component is 128 kg.


The Measurement Domain of the CAS500 Satellite is Land.


The Satellite Orbit Types of the BeiDou-2 Satellite Constellation is 5 geostationary orbit (GEO) satellites and 30 medium Earth orbit (MEO) satellites.


The Height Data Echo Rate of the GEOSAT Satellite is 10 Hz.


The Launch Date of the Landsat-9 Satellite is September 2021.


The Bandwidth of the Band Photometers Photometer is 5.0 nm.


The Flow Rate Set Points of the FCA Flow Control Assembly is Two.


The Inclination of the Primary Payload Unknown is 69.5º.


The Required Precision of the H2CO Satellite Instrument is 10.0.


The Number of Satellites of the Capella X-SAR Constellation Satellite Constellation is 9.


The Communication Status of the Voyager 2 Spacecraft is Without receiving commands from Earth.


The URL of the Hinode Satellite is http://www.isas.ac.jp/home/solar/.


The Tandem Flight Duration of the Copernicus Sentinel-6 Poseidon-4 Radar Altimeter is 12 months.


The Deactivation Date of the RapidEye Earth Observation Constellation is March 2020.


The Quantity of the SuperDove satellites Next-generation satellites is 150.


The Spectral Range of the IIM instrument Imaging Spectrometer is 0.48-0.96 µm.


The IGARSS Presentation Date of the SMOS Satellite is July 26-31, 2015.


The Spectral Band Interval of the SMI Spaceborne Multispectral Imager is 13 nm.


The URL of the Wide-Field Imager for Solar Probe Plus Imager is http://www.nrl.navy.mil/ssd/branches/7680/WISPR.


The Mission Name of the GOCE Satellite is Gravity field and steady-state Ocean Circulation Explorer.


The Observation Type of the Spitzer Satellite is Eddington Flare from Blazar OJ 287.


The Mission of the OLCI Instrument is Sentinel-3.


The Installation of the ISL Antennas Antennas is +X surface and -X surface.


The Downlink Data Rate of the IXPE Satellite is 2.0 Mbit/s.


The Launch Date of the DART Space Probe is Last November.


The Data Applications of the BeaverCube Satellite is Improving the understanding of regional biological productivity and the effects of extreme weather events.


The Lag Period of the Pelican Satellites Satellite is Less than two hours.


The Beacon Transmission Rate of the ELFIN-A Satellite is 9600 baud.


The Launch Vehicle of the CubeStack Multi CubeSat Adapter is Minotaur I.


The Development Cycle of the CubeSats Satellite is Six to twelve months.


The Micro-switches of the Mechanism Position Indicator is Array of micro-switches.


The Spacecraft Separation of the Tri-TIP Instrument is 250-500 km.


The Development Status of the TerraSAR-NG System Satellite System is Preliminary Design Phase.


The Launch Date of the SkySat Constellation Satellite Constellation is 21 Nov 2013.


The Overall Accuracy of the ARI Infrared Spectrometer is <0.1 K 2σ.


The Test Period of the TOR Payload is January 15 through February 15, 2008.


The Ground Track Velocity of the ICIR Radiometer is Approximately 7 km/s.


The Launch Date of the Meteosat-1 Satellite is November 23, 1977.


The Quality Information of the L1C Products Satellite Data is Included.


The Attitude Sensing of the ADCS Attitude Determination and Control Subsystem is Magnetometers, gyros and photodiodes.


The Application of the GPS Satellite-based Service is Navigation.


The Re-entry Date of the Drag de-orbit sail De-orbit Device is 72 days later.


The Field-of-view of the Photometer Optical Instrument is 24º.


The Temperature Range of the Battery Energy Storage is -5º to +25º C.


The Discovery Year of the 1999JU3 Asteroid is 1999.


The Power Modes of the dsPIC33F microcontroller Microcontroller is Unknown.


The Power Requirement of the Electrodynamic Tether (Thrust System) Propulsion Device is Requires power to be injected into the tether system from an on-board power supply.


The Communication Protocol of the Deployment Systems Satellite is RF, UHF/VHF, S-band.


The Content of the L1-SAIF+ Satellite Message is Differential correction information, information for correcting orbital position and clock errors for 10 satellites, short messages for emergency cases.


The Drift Angle Correction Accuracy of the ADCS Attitude Determination and Control Subsystem is ≤ 0.1º (3σ, correction based on nadir camera).


The Pan of the Pushbroom imager GSD is 1.45 m.


The Support of the Flight Segment System Engineer Engineer is Project System Engineer.


The Developer of the Unicorn-2D PocketQube is Alba Orbital UG (Germany).


The Instrument Mass of the MSU-E Multispectral Scanner is 17 kg.


The URL of the ExoMars Mars Orbiter is http://m.esa.int/Our_Activities/Space_Science/ExoMars/Schiaparelli_crash_site_in_colour.


The Main Operations Tasks of the LMOC Ground Segment is Monitor payload and ground system telemetry, monitor atmospheric conditions, monitor link status, respond to user service requests, perform ground station handover, execute performance data monitoring, implement scheduling change requests, perform routine.


The Location of the LRAC Reference Archive Center is Kiruna.


The Data Delivery of the SENSE Satellite is Air Force Research Laboratory at Kirtland Air Force Base.


The Measurement Type of the Logarithmic Electrometers Instrument is Current.


The Trajectory Correction Maneuver of the MarCO-B CubeSat is Completed with Unexpected Challenges.


The Phase of the SPARCS Satellite is Phase B.


The Range of the Star sensor Sensor is 14.4º x 19.2º.


The Information Usage of the IIS Integrated Imaging Subsystem is Co-registration with the AVHRR.


The Science Objective of the BRITE Constellation Satellite is Provide milli-magnitude (0.1% error) differential photometry of bright stars.


The Docking Time of the Crew Dragon Spacecraft is Around a day later.


The Maximum Depth of Discharge of the TSUBAME Satellite is Estimated at no more than 50%.


The FOV (Field of View) of the Imager Imaging System is > 1.28º.


The Image Content of the CaSSIS Instrument is Light-toned bedrock.


The Manufacturer of the EROS-B Satellite is ImageSat International N.V..


The Observation Date of the XMM-Newton X-ray observatory is June 2013.


The Prime Contractor of the THEMIS Satellite Constellation is Swales Aerospace.


The Orbit of the PAMELA Instrument is Semi-polar Resurs orbit.


The Measurement Frequency of the GeoCARB Satellite is Daily.


The Voltage Output of the PSU Power Supply Unit is 5 V to supply the RF power amplifiers in C&CS.


The Swath of the HARP-2 Polarimeter is Wide.


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


The Nadir resolution of the WorldView Legion Satellite System is 29 cm.


The Operation Start Date of the AOCS Attitude and Orbit Control System is Day 5.


The Function of the CAPSTONE 12U CubeSat is Demonstration of spacecraft-to-spacecraft navigation services.


The URL of the Spacecraft Fire Experiment (Saffire) Experiment is http://orbit.dtu.dk/ws/files/97737980/2014_ICES_SFS_Demo_Paper_265_5_16_2014.pdf.


The Date of the Super Typhoon Rai Image is 18 December 2021.


The Mounting Interface Requirement of the SOSMAG Magnetometer is None.


The Purpose of the GEOTAIL Satellite is Measure the flow of energy and its transformation in the magnetotail created by the interaction between the solar wind and the Earth.


The Configuration of the Reflectarray Antenna Antenna is Three panels, electrically tied together through hinges, with an array of printed circuit board patches on them.


The Location of the OSIRIS Instrument is Odin.


The Expected Orbit Duration of the SMDC-ONE Nanosatellite is Approximately 30 days.


The California Institute of Technology Infrared Processing and Analysis Center, Pasadena, California, USA of the NASA Herschel Science Center Location is An additional center is the NASA Herschel Science Center, located at the California Institute of Technology Infrared Processing and Analysis Center, Pasadena, California, USA.


The Data Delivery of the SPOT-4 Satellite is Unreliable.


The Unknown of the Millimeter Wave Atmospheric Sounder (MAS) Sounder is Unknown.


The Mission Design of the Geosat ERM Satellite is G. H. Born, J. L. Mitchell, G. A. Heyler.


The Image Resolution of the Ikonos-2 Satellite is 1 m.


The Spectral Range of the Spectrometer Instrument is 5-28.5 µm.


The LO Frequency (MHz) of the HRIT HiRID Data Receiver is 1900.


The Number of Bands of the WFI Camera is 4.


The Preamp full scale output swing of the PHA Detector is 4.0 V.


The Tube Capacity of the Picosa Launcher Satellite Component is 2 short picosats or 1 long picosat.


The Fault Location of the Tsubame microsatellite Satellite is Peripheral circuit for communication.


The Power of the Average Payload Satellite is < 100 W.


The Mean Revisit Time of the TeLEOS-1 Imager Imaging Device is 12 to 16 hours.


The Expected Level of the TRL Technology Readiness Level is 6.


The Wave Energy of the STEREO spacecraft Satellite is 2400 megatons of TNT (1022 joule).


The User Interface of the Gaia Satellite is GUI (Graphical User Interface).


The Purpose of the OBDH On-Board Data Handling subsystem is Load the software experiment.


The Operation Date of the PRISMA Satellite is Sept. 27-Oct. 1, 2010.


The Mass of the The Horse and the Dragon Pair of distinct massive galaxies is Roughly as massive as our Milky Way.


The Swath Width (ScanSAR mode) of the XSAR SAR is Up to 100 km.


The Launch Date of the SPOT-7 Satellite is Late 2013.


The Data Storage Capacity of the Data Handling System System is 64 Gbit.


The Antenna Deployment Date of the Radar Instrument is July 28, 2018.


The Measurement Capability of the NICER X-ray Instrument is General-relativistic Shapiro delay in binary systems.


The Sample Return Date of the Hayabusa-2 Spacecraft is December 2020.


The Operation of the XMM-Newton X-ray Telescope is Must be told exactly where to point.


The Data Storage Capacity of the RISAT-2 Satellite is 240 Gbit.


The URL of the Satellite Satellite is http://journals.ametsoc.org/doi/pdf/10.1175/1520-0477%281979%29060%3C1038%3ASSOTSA%3E2.0.CO%3B2.


The Integration Time of the Scanner Assembly Instrument is About 15 seconds.


The Mass of the Field Measurement Device Electronic Unit is < 0.5 kg.


The Publication Date of the RadCalNet Calibration Network is 16 October 2019.


The MTF of the Instrument Satellite Instrument is > 0.2 @ Nyquist frequency.


The Launch Site of the STPSat-3 Satellite is MARS (Mid-Atlantic Regional Spaceport).


The Application of the AutoConTM Technology is Orbit maintenance of single spacecraft or constellations and formations.


The Measurement Category of the GF-3 Satellite is Multi-purpose imagery (land), Landscape topography.


The Observation Data of the Shikisai Satellite is Boso Peninsula SST and the seine fishing ground.


The Unapodized Spectral Resolution Requirement of the Michelson Interferometer Interferometer is I/(2L).


The Inauguration Date of the DEIMOS-2 Satellite is October 8, 2013.


The Mission Status of the Satellite HY-1B is Operational.


The Publication Date of the Cluster Mission Satellite Mission is Oct. 1988.


The Image Resolution of the Solar Orbiter Satellite is 9148 x 9112 pixels.


The Modules of the PRIMA Satellite Bus is Propulsion module (PPM), service module (SVM), payload module (PLM).


The Antenna Rotation Speed of the IRS Interferometric Radar System is 1º/s.


The Pre-flight Calibration Target of the ARTEMIS Satellite is Specially-coated panel with known absorption features.


The Dimensions of the Data Cube Data Structure is samples_wide X number of spectral_data_lines X number_of_frames.


The Launch Date of the OrbView-4 Satellite is Sept. 21 2001.


The Measurement Category of the Biomass Satellite is Vegetation.


The Side-viewing Capability of the CCD Pushbroom Camera Camera is ±32º.


The Type of the NOSS-36A Satellite is Navy Ocean Surveillance Satellite.


The Antenna Usage of the Ground Segment Ground Control Infrastructure is Transmitting and Receiving.


The Utilization of the ICI-4 Radiometer is Quasi-window, cloud ice retrieval, cirrus clouds.


The Frequency of the Ka-band Signal is 32 GHz.


The Orbit of the Spacecraft Satellite is 600-850 km altitude.


The End of Life Date of the Sentinel-5P Satellite is September 2027.


The Previous Catalogue Distance Limit of the Gaia Catalogue of Nearby Stars Stellar Census is 82 light years.


The Number of Reaction Control Thrusters of the Propulsion Subsystem Satellite is 16.


The Wind Velocity Range (PBL) of the Aeolus Satellite is ±150 m/s.


The News Article of the Robotic satellite servicer Satellite is S. Clark, "Robotic satellite servicer rehearsal underway in orbit," Spaceflight Now, April 3, 2007.


The Manufacturer of the FR-lite satellite radio Communication Device is Johns Hopkins University Applied Physics Laboratory.


The De-orbit of the Gnome Chompski Space Component is With Electron’s Kick Stage.


The Power Consumption of the Satellite Satellite is 270 W.


The Data Volume of the Mini-RF Instrument is 60 TB.


The Sail Area of the CanX-7 Drag Sail Payload is Approximately 5 m2.


The Orbit Altitude of the CartoSat-2D Satellite is 505 km.


The Voltage of the Voltage 1 Power Amplifier is 22-28 adjustable.


The Quantity of the Rate gyro Sensor is 1 unit.


The | of the Adam Szabo and Keith W. Ogilvie Individuals is Information provided by Adam Szabo and Keith W. Ogilvie of NASA/GSFC.


The Upper Module Components of the Merlin Satellite Device is `sensor board', detectors, associated front-end electronics.


The URL of the MidSTAR-1 Satellite is http://en.wikipedia.org/wiki/MidSTAR-1.


The Thickness of the RF Section Subsystem is 5 cm.


The Mass of the Eristo/Osteo Payload is 66 kg.


The Telescope Type of the ASTRO-H Mission is SXTs (Soft X-ray Telescopes).


The Shutdown Date of the IMP-8 Satellite is Oct. 31, 2001.


The Transmitter Wavelength of the DIAL Instrument LIDAR is 2 µm.


The MTF of the NEMO-HD Satellite is 0.10.


The Inclination of the 7 microsatellites Satellite is 97.45º.


The Mission Status of the LADEE Satellite is Completed.


The Thruster System of the BeaverCube CubeSat is Tiled Ionic Liquid Electrospray (TILE 2) thruster system technology, developed and manufactured by Accion Systems, Inc.


The Mission Operations Segment Date of the TanDEM-X Satellite is April 25-30, 2010.


The Field of View of the EIC Camera is ±8.5º.


The Affiliation of the STScI Science Operations Center is Association of Universities for Research in Astronomy (AURA).


The Pointing Accuracy of the PARASOL microsatellite Satellite is 0.1º.


The Manufacturer of the Lucy Discovery Program Mission is Lockheed Martin.


The Configuration of the SABR DC/DC Converter is Synchronous buck converter.


The Operating Frequency of the Antennas Communication is Not specified.


The Spatial Resolution of the Instrument Satellite Instrument is 10 m.


The Detectors of the NIRSpec Spectroscopy Instrument is Two.


The Attitude Update Mode Rate of the Star Tracker Attitude Determination System is 1.7 Hz.


The Neutron Energy Range of the Natalya-2M High energy radiation spectrometer is 20 – 300 MeV.


The Launch Date of the Sich-2 Satellite is 17 Aug 2011.


The Transmitter Fault Date of the MicroMAS-1 Satellite is August 2015.


The Perigee of the SCD-2 Satellite is 743 km.


The Primary Function of the JMR Microwave Radiometer is Measure brightness temperatures.


The CDR Date of the SMOS Satellite is Nov. 2005.


The Power Generation of the EAGLE ESPAStar Satellite is 1.2 kW.


The Measurement of the KaRIn Radar Interferometer is Water level.


The Announcement Date of the 30 Doradus in LMC Satellite is Jan. 30, 2000.


The Energy Resolution of the IMAP Satellite is 100 eV.


The Viewing Angle of the MWHS-II Microwave Humidity Sounder is ±53.35º.


The Electrical Conduction Method of the Fasteners Mechanical Component is Conduct the electricity to a copper lug.


The Projected Counting Rate of the Instrument Spectrometer is 0.5 counts/pixel/exp/R.


The Open Circuit Voltage (Voc) of the Solar Panel Satellite Component is Variable.


The Orbit Altitude of the OPAL Satellite is ~ 370 km.


The Development Date of the Resistojet Thruster Propulsion Systems Propulsion Systems is Aug. 11-14, 2003.


The Mission Type of the Solar-A / Yohkoh Satellite is Non-EO.


The Performance of the CNAPS Propulsion System Propulsion System is Out-performed expectations.


The Eclipse Power Conversion Efficiency of the SBVR Power Supply is 97%.


The Output of the DarkCarb image sensor Photon Detector is Proportional to the radiance it receives.


The Conference Presentation Date of the EO-1 Satellite is Aug. 13-16, 2007.


The Image Release Date of the SMART-1 Satellite is March 03, 2008.


The Test Locations of the FG Calibration Device is Air, vacuum conditions, 10000-class clean room, solar telescope.


The CCD Line Pixel Count of the Focal Plane Module Imaging Device is 12,000 pixels.


The Measurement Spectral Region of the Sounder Instrument Instrument is 4-5 µm.


The Launch Year of the Landsat-7 Satellite is 1999.


The Cube Size of the Orbit Your Thesis! 2019 program Education Program is 1U.


The pH of the Marine Chemistry Study Parameter is Unknown.


The Measurement Domain of the Badr-B Satellite is Gravity and Magnetic Fields.


The Mass of the ASTERIA CubeSat is 12 kg.


The Total Rock Mass Returned of the Apollo Missions Lunar Sample Return Missions is 382 kg.


The Observation Target of the Satellite Satellite is Sea wave, sea surface wind field, internal wave, frontal surface, shallow sea topography, sea surface oil spill, sea ice, green tide, coastal zone and sea surface targets, Flood submerged area, debris flow, landslide, ice or snow, extent of sea ice, droug.


The Measurement of the WISPR Instrument is Solar Wind Structures.


The S-band Downlink Modulation of the UoSAT-12 Satellite is BPSK.


The Material of the Heat Rejection Mirror Optical Component is Vacuum deposited silver.


The Article Date of the Landsat 9 Satellite is 9 January 2020.


The Size of the CAPSTONE 12U CubeSat is Small microwave oven.


The Mass of the SA-200HP Spacecraft Platform is Launch mass of 2780 kg; dry mass of 1512 kg.


The Presentation Date of the SI-200 Mini-Satellite Platform Satellite Platform is Oct. 12-16, 2009.


The Power of the Sun sensors Sensor is < 0.1 W.


The Inherited Features of the Jason-3 Satellite is Orbit, instruments and measurement accuracy.


The Inclination of the Satellite PAZ is 97.44º.


The Detector Pixel Size of the Instrument Spectrometer is 13 µm x 13 µm (VIS); 40 µm x 40 µm (NIR).


The TT&C of the Spacecraft Satellite is S-band (32 kbit/s in up- and downlink).


The Calibration Modes of the SAR Instrument SAR Instrument is Interferometric calibration mode, Amplitude/phase distortions measurement mode.


The Publication Date of the Lunar Flashlight Satellite is 15 July 2015.


The Microbe Types of the Experiment Microbiology is Halorubrum chaoviatoris and Bacillus subtilis.


The Line of Sight Range of the TIR Subsystem Imaging System is ± 8.54º in the cross-track direction of nadir.


The Payload Location of the AIS Automatic Identification System is On board PAZ.


The Purpose of the Camera System Attitude Determination and Observation is Demonstrate a star- and horizon tracker for attitude determination, as well as observe meteors to improve the understanding of the beginning of the solar system and test the system for future missions.


The Spectral Bands of the LISS-IIM Instrument is 0.45-0.52 µm, 0.52-0.59 µm, 0.62-0.68 µm, 0.77-0.86 µm.


The Diameter of the LAGEOS Satellite is 60 cm.


The Communication System of the TRMM Satellite is Four radio frequency (RF) links.


The Objective of the Experiment Satellite is Demonstrate global and real-time space weather observations of near-Earth space.


The Size of the Integrated Sensor Sensor is 8 mm x 3 mm x 19 mm.


The Operation End of the Experiment Unknown is Mid-1975.


The Data Types of the Cheollian 2B Satellite is Marine image data, Ocean color images.


The In-flight Calibration of the SOSP Satellite is Provided.


The Data Usage of the EnviSat Satellite is Studying and monitoring the Earth's environment.


The Instrument Power of the Hyperion Imaging Spectrometer is 78 W.


The Latitude Coverage of the ERS-1 Satellite is ± 81.5º.


The Consortium Lead of the Satellites around the Moon Satellite Constellation is SSTL Lunar.


The Contract Value of the HDEV High-Definition Earth-Viewing System is US$65 million.


The Image Recording of the Coronagraph Instrument is 35 mm film.


The Threat of the U.S. Midwest Region is Agricultural productivity is being threatened by climate change.


The Redundancy of the SGR-10 Space GPS Receiver is Redundant pair.


The Purpose of the Nimbus-7 Satellite is Testing of advanced systems for sensing and collecting data in the atmospheric, oceanographic and meteorological disciplines.


The Angle of the Nadir FOV Field of View is 75º.


The Function of the Exo-Brake Parachute is Enable Safe Return for Small Spacecraft.


The Function of the TechEdSat-10 Satellite is High temperature, accurate deorbit reentry.


The Orbit Apogee of the Beijing-3B Satellite is 627 km.


The Function of the Electra Radio is Relay data from a rover or stationary lander to an orbiter passing overhead.


The Purpose of the IDEA OSG 1 Microsatellite is Tracking and mapping of space debris.


The Imagery Collection of the Satellogic Satellite Imaging Company is 10 times as much imagery.


The Battery Configuration of the EPS Electric Power Subsystem is 8 in series.


The Mass of the OCM Instrument is 78 kg.


The Key Technology Elements of the MWIR Sensor Sensor is Integrated micro-cryocooler and a high temperature nBn based 1-Megapixel focal plane.


The Operations Approach of the Twinkle Satellite is Streamlined, robust, safe, and high availability.


The Realtime Access Link Speed of the IRIS Satellite is 81 Mbit/s.


The Student Collaboration Goal of the IMAP Mission is Develop hands-on research experience for students.


The Number of Solar Panels of the Yutu 2 Lunar Rover is 2.


The CO2 Emission Source Resolution of the CO2Image Satellite is Below 1 Mt/year.


The Number of Satellites of the Galileo Satellite Navigation System is 26.


The Energy Range of the HXD Detector is 10-60 keV.


The Average Concentrations in 1960s of the Ozone Layer Atmospheric Layer is 260 to 320 Dobson Units.


The Resolution of the X-ray Imager Instrument is < 0.22º.


The Length of the RF Antenna Mast Satellite Component is Nearly 12 m.


The Base Frequency of the DSN Link Signal is Approximately 9.6 MHz.


The Multispectral Bands Detector Array of the WV-3 Imager Imager is 9,300 pixel.


The Telescope Aperture of the LCT Laser Communication Terminal is 135 mm.


The Connection of the ROSA Radio Occultation Antenna Antenna is Connected to the ROSA receiver unit by two different RF cables for L1 and L2 frequency signals directly to the LNA's, without passing through the diplexer used for the navigation one.


The Altitude of the LIMS Instrument is 153 km.


The Orbit Height of the TerraSAR-X Satellite is 514 km.


The Power of the Star sensor Sensor is 4 W.


The Manufacturer of the NewSat-6 Satellite is Satellogic S.A..


The Instrument Type of the AaSI Spectral Imager is Fabry-Pérot Interferometer (FPI).


The Functions of the DFU Data Formatter Unit is CCSDS formatting, Reed-Solomon encoding.


The Number of Satellites of the OneWeb Satellite Constellation is 650.


The Primary Structure Stiffness of the COMMx Payload is 50 Hz.


The Pointing Locations of the SVOM Attitude Satellite Attitude is Near the equator, areas observable from both Hawaii, Chile and the Canary.


The Launch Date of the Meteor-M-1 Spacecraft is Sept. 17, 2009.


The Dimensions of the Node-3 Module is Diameter of 4.5 m and length almost 7 m.


The Measurement Category of the IRS-P6 Satellite is Multi-purpose imagery (land), Vegetation, Albedo and reflectance, Landscape topography, Sea ice cover, edge and thickness, Snow cover, edge and depth.


The Observation Date of the XMM-Newton Space Observatory is June 17, 2020.


The Observation of the FAUST Instrument is Large Magellanic Cloud galaxy.


The CDR Date of the TROPOMI Instrument is End of 2012, early 2013.


The Software of the ACS Attitude Control System is ACS flight software (FSW).


The Total Mass of the StudSat Picosatellite is 1.3 kg.


The ?V Capability of the ISEE-3 Spacecraft is About 310 m/s.


The Coil Cross-Sectional Area of the VLF Experiment Scientific Experiment is 42 cm2.


The Orbit Type of the SPOT 1-5 Satellite is Sun-synchronous.


The Power of the EPS Electrical Power Subsystem is 3 W (paddles closed), 5.9 W (paddles open).


The Funding Provider of the TanSat Satellite Mission is CAS (Chinese Academy of Sciences).


The URL of the Picard Satellite is http://solarnet.projet.latmos.ipsl.fr/fichiers_pdf/pro_picard_SOLSPA.pdf.


The Operation Duration of the SloshSat Satellite is 57.5 hours.


The Central Wavelength of the Current GOES imager Sensor is 3.90.


The Spectral Bands of the MESSR Radiometer is One visible (VIS) band and three thermal infrared (TIR) bands.


The TDI Lines of the R3 Sensor Sensor is 11, 19, 21, 21, 21, 21.


The Orientation of the Solar Panels Power Generation is Roll direction of the satellite.


The Presentation Date of the FORMOSAT-3/COSMIC Follow-On Mission Satellite Mission is Aug. 11-14, 2008.


The Range of the SCM Satellite Charging Monitor is -3 pA/cm2 to +3 pA/cm2.


The Number of Satellites of the JL-1-GF03D Microsatellite is 3.


The Diameter of the Schiaparelli Module is 2.4 m with heatshield, 1.65 m without heatshield.


The Communication Capability of the Prometheus Satellite Satellite is Transfer audio, video, and data files from man-portable, low-profile, remotely located field units to deployable ground stations terminals using over-the-horizon satellite communications.


The Data Acquisition Spacing of the SARAL/AltiKa Satellite is ~ every 180 m.


The Thrust of the CanX-4&5 Satellite is 5 mN.


The Number of Elements of the Collecting Optics Lens Assembly is 8.


The Mission Type of the IDEA OSG 1 Satellite is Non-EO.


The Minimum Radar Reflectivity of the CPR Millimeter-Wave Radar is -35 dBZ.


The Launch Date of the H-IIB Launch Vehicle No. 6 Launch Vehicle is Oct. 7, 2016.


The Look Angle of the SAR Synthetic Aperture Radar is 20º.


The Launch Year of the UWE-2 Satellite is 2006.


The Spectral Bands of the WFI Camera is VIS to NIR.


The Designation of the MTSAT Satellite is CNS/ATM system.


The Operation of the Thermal Control Louvers Thermal Regulation Device is Open up when the satellite needs to dissipate heat from its interior and close when the craft needs to warm up.


The Deployment Altitude of the Stingray Satellite is Approximately 500 km.


The Operation Start Year of the Argos Satellite System is 1978.


The Measurement Category of the MTSAT Satellite is Cloud type, amount and cloud top temperature, Liquid water and precipitation rate, Surface temperature (ocean), Atmospheric Humidity Fields, Atmospheric Winds.


The Mission of the CRISTAL Satellite is Measure and monitor sea-ice thickness, overlying snow depth and ice-sheet elevations.


The Launch Date of the PROBA-V-CC Satellite is October 9, 2023.


The Power Demand of the CMA/CM Component is 7.3 kW.


The Observation Target of the Tandem-L Satellite is Earth’s surface.


The Documentation Provider of the Aalto-1 Satellite is Herbert J. Kramer.


The Better Uplink Verification Method of the Ground System Satellite Ground System is Recording the uplink RF signal at the ground site using a software-defined radio.


The Material of the Gimbal Satellite Component is Silicon nitride.


The IFOV of the HIRS/4 Infrared Sounder is 10 km (0.7º).


The Average Power Generation of the EPS Electrical Power Subsystem is 2 kW.


The Function of the Star Sensors Autonomous Star Sensors is Measure and report the S/C orientation relative to an inertial reference frame.


The Deployment Timeframe of the Iridium NEXT Satellite Constellation is 2015-2017.


The Type of the Hot Jupiters Exoplanets is Star-hugging, superheated giants.


The First Light Date of the Storm Hunter Satellite is 23 May 2018.


The Calibration of the MAG Sensor Sensor is Performed over a wide range of temperatures.


The Imaging System Resolution of the GOMX-1 Nanosatellite is 35 m.


The Function of the Arduino-based processors Processors is Run other activity tasks such as interfacing with the payload, polling sensor data, and interfacing with the GPS.


The Energy of the Sub-mm Band is 1.4 meV.


The Energy Channels of the GALS-VE Particle Energy Measurement Device is > 600 MeV, > 800 MeV, > 1200 MeV.


The Principal Investigator of the SEIS Instrument Seismometer is Philippe Lognonné.


The System Name of the Whale Ecology Observation Satellite Satellite is Kanta-kun.


The Spatial Scale of the Telescope Optical Instrument is 2.8 arcsec/pixel.


The EIRP of the DRT Data Relay Transponder is 21 dBW (min).


The Purpose of the LIRIS Rendezvous Sensor is Technology demonstration for future non-cooperative rendezvous applications.


The Wavelength Region of the Instrument Spectrometer is 400-970 nm (57 bands), 900-2500 nm (128 bands).


The Boulder Strength of the Comet 67P/C-G Comet is One hundred times weaker than freshly packed snow.


The Survey Density of the VIS Visual Instrument is At least 30 galaxies per arcmin2.


The Bus Type of the OBDH On Board Data Handling is ESA standard.


The Imprint Size of the Philae Lander is 25 cm.


The Launch Date of the Crew-3 Mission is Oct. 31.


The Observation Target of the IRIS Observatory is Sun's lower atmosphere just above the surface (chromosphere).


The Mass of the Spacecraft Satellite is 2.66 kg.


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


The Series of the CartoSat-2E Satellite is Cartosat-2.


The Reaction Control Assembly of the EURECA Spacecraft is 6 x 21 mN nitrogen thrusters.


The Image Type of the CaSSIS instrument Imaging Instrument is Stereo pairs.


The Conference Date of the Space-based ADS-B Surveillance System is Nov. 19-30, 2012.


The Team Structure of the HORYU-4 Satellite is Professors-staff, and students.


The Joint Tests Date of the CBERS 3 Satellite is March 29, 2011.


The Operation Period of the S-193 Radar System is May 1973 to Feb. 1974.


The Frequency of the Communication Payload Payload is Ka-band (27.0-31.0 GHz and 18.1-21.2 GHz).


The GSD of the Instrument Satellite Instrument is 32m to 22m.


The Conference Presentation Date of the Near Earth Asteroid Scout Satellite is 1 Aug 2014.


The Data Rate of the X-band Transmitter Transmitter is 105 Mbit/s.


The Conference Frequency of the JFCT Team is Once a week.


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


The Channel Bandwidth of the TT&C Telemetry, Tracking and Command Subsystem is 25 kHz.


The Polarization Channel Transition of the SAR Processor Data Processor is When a transition from quad to single pol (or inversely) happens, the length of the single polarization channel will be increased at the cost of a reduced swath width.


The Developer of the Venta-1 Nanosatellite is VVentspils High Technology Park.


The Current of the Voltage 3 Digital is 350.


The X-band Downlink Capacity of the PDHT Payload Data Handling and Transmission is 520 Mbit/s.


The Z-axis Rotation Rate of the Satellite Spacecraft is 1 rotation per minute (rpm).


The Data Acquisition and Processing Concepts Presentation Date of the TanDEM-X Satellite is July 4-6, 2006.


The Technology of the Ground Station Communication System is SDR (Software Defined Radio).


The Area of the Solar Arrays Power Source is 18.3 m^2.


The Launch Status of the FormoSat-7/COSMIC-2 Satellite Satellite is Cancelled.


The Tracking Method of the Payload Measurement Device is Time-resolved optical density and absorbance measurements.


The Operational Period of the ISS Space Station is Until 2028.


The Operation Sensitivity of the Electron Temperature Probe Instrument is Less sensitive to the potential sheath structure of its enveloped electrodes.


The ISS Components of the EUVI Extreme Ultraviolet Imager is EUVI secondary mirror as the actuator and GT as the high-accuracy angular motion sensor.


The Operation Start Year of the CFESat Satellite is 2009.


The Experiment of the CNES Space Agency is Automatic spacecraft maneuver planning and collision prediction in space.


The Data Service of the SGR-ReSI Interface Unit is Rapidly collect and invert the data into sea state.


The Azimuth Resolution of the Spotlight Imaging Mode is 3.4 m (dual pol.).


The Balloon Status of the AeroCube-3 Satellite is Ejected but did not inflate.


The Radiation tolerance of the PHA Detector is >100 krad.


The Function of the Translation Stage Actuator is Shift the alignment of the center of mass relative to the center of pressure.


The Spectral Bandwidth of the VNIR Spectrometer Spectrometer is 10 nm.


The Control Method of the Antenna Satellite Component is Commanded from ground station.


The Passband Range of the SPIM1 Spectrometer is 113-173 nm.


The Total Cruise Phase Duration of the Solar Orbiter Satellite is < 3 years.


The Spatial resolution at nadir of the MWRI Microwave Radiation Imager is 15-70 km.


The J2000 declination (deg) of the B1509-58 Pulsar is -59.13583.


The Role of the GIPSY-OASIS Software Package is Simulating DSAC’s expected PCD performance.


The Failure Date of the ISAMS Instrument is Late July 1992.


The Year of Launch of the Landsat-7 Satellite is 1999.


The Scan Period of the Rotating Telescope Scanner Optical Instrument is 1.729 s.


The Solution of the BPP (Bi-axial Pointing Platform) Pointing Platform is Use existing gyroscopes on the HRC to improve the BPP pointing control.


The Mission Design Life of the PARASOL microsatellite Satellite is One year.


The Return Date of the Metcomp experiment Materials Science Experiment is SpaceX CRS-21.


The Manufacturer of the Solar Panels Power Generation is PrecizikaMET SC.


The Payloads of the Satellite Satellite is IOV, Communication Payload of the German Ministry of Defense.


The Date of the NASA Adds Up Alberto's Soaking Rainfall Event is 31 May 2018.


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


The Battery Model of the PSU Power Supply Unit is Lithium-ion battery of Saft (France), model: MP144350.


The Press Kit URL of the SpaceX CRS-6 Mission is http://www.nasa.gov/sites/default/files/files/SpaceX_NASA_CRS-6_PressKit.pdf.


The Check-Conflict (National Harmonization) of the CSK GS Ground Segment is Verify if any sensing request is conflicting with any others and submit the final harmonized Service Request list to the FM GS.


The Observed Emissions of the MIGHTI Instrument is O(1D)@630.0 nm, O(1S) @ 557.7 nm, 0-0 band of O2(b1Sg+) @762.0 nm.


The Type of the PHI Instrument is Diffraction limited, wavelength tunable, quasi-monochromatic, polarization sensitive imager.


The Size of the GRIFEX Satellite is 3U CubeSat.


The Normalization at 1 keV of the First Broken Powerlaw Model Component is 5.7 photon cm-2 s-1 keV-1 ster-1.


The Objective of the GEOS-2 Satellite is Measurement of fluctuations in the magnetic field.


The Mirror Technology Workshop Date of the JWST Telescope is June 16-18, 2009.


The Expected Launch Date of the LISA Space Observatory is 2034.


The Value of the Spectral Stability Performance Requirement is Better than 0.02 nm.


The ADCS Systems of the OPS-AT Satellite is Two.


The Effective Sensitive Area of the HXT-C X-ray Optics is 70 cm2.


The Launch Time of the BRO-6 Satellite is 6:49 p.m. Eastern.


The Number of Students of the University of Sankore Educational Institution is 25,000.


The Cooperation Agreement of the SSOT Satellite is Includes provision for Chilean engineers to work alongside the Astrium development team.


The Ion Isotropy Boundaries Energy Range of the ELFIN Satellite is 100-500 keV.


The Function of the HSM High-Speed Multiplexer is Collects ISP (Instrument Source Packets) in CCSDS format.


The Communication of the CICERO satellites Satellite is UHF up/downlink for TTC data.


The First Light Image Date of the SXT Soft X-ray Telescope is October 26, 2015.


The Manufacturer of the GF-2 Satellite is CAST (China Academy of Space Technology).


The Trajectory Correction Maneuver of the MarCO-A CubeSat is Completed.


The Components of the DLRE Instrument is Instrument optics bench assembly (OBA), elevation/azimuth yoke, instrument mount.


The Mass (kg) of the TanDEM-X Satellite is 1340.


The Exceeded Design Life of the QuikSCAT Satellite is Yes.


The Channels of the Magnetic Field Measurement System Instrument is 8.


The Downlinked Data of the Mission Operation System Data Processing System is 100 GB/day.


The Power of the GPS receiver Receiver is 5-7 W.


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


The Components of the Look-Up Table Model is GFS (Global Forecast System) of the NCEP (National Center for Environmental Prediction).


The Design Phase Start of the Emergency Egress System Safety System is 2019.


The Unknown of the Myriade Satellite Platform is Unknown.


The Operating Temperature of the Mid-infrared detectors Detector is 7 K.


The Mass (kg) of the ALOS-1 Satellite is 4000.


The Form Factor of the LINAS Ionization Gauge is 1U CubeSat.


The Presentation Date of the NANOSATC-BR Cubesat Program Satellite Program is Oct. 10-13, 2012.


The International Space Station Operations Update Date of the UrtheCast Company is April 3, 2014.


The Radiation Protection of the CUTE-1.7 Picosatellite is Mentioned.


The Propulsion Systems Quantity of the MTG Satellites Satellite is 6.


The Resupply Mission of the ARTEMIS Satellite is Successful.


The Scene Size of the Instrument Hyperspectral Imager is 5 km x 20 km.


The Apogee (km) of the Cosmos-1066 (Astrofizika) Satellite is 908.


The Receiver Recovery Time of the RAX-1 Satellite is Within 100 microseconds.


The Launch Date for Artemis 1 of the SLS Rocket Rocket is Unknown.


The Manufacturer of the TRMM Satellite is NASA’s Goddard Space Flight Center.


The Nominal Along-Track Separation of the EO-1 Satellite is One-minute (450 km), ± 6 s (42.5 km).


The Data Transmission Mode of the Satellite Imaging Satellite is Recording (R) with subsequent reproduction(DR).


The Types of the Data Products Data is 3-hourly, 6-hourly and daily products.


The Design Approach of the Satellite Bus Satellite Component is Commercial-off-the-shelf (COTS) products.


The Imaging Frequency of the Pelican Satellites Satellite is More than 10 photographs a day.


The Meeting Date of the GOSAT TANSO-FTS Spectrometer is June 18-20, 2012.


The Signal Wavelength of the S-band SAR Radar is About 4 inches (10 cm).


The Altitude of the ICEYE-X10 Satellite is 500 km.


The Function of the TET Radiator Thermal Interface is It is small enough to prevent an out cooling of the system during "cold" phases.


The Temporal Sampling of the Aeolus Satellite is 12 hours.


The Number of Flat Mirrors of the Refocus Mechanism Assembly Mechanism is 2.


The Modules of the IASI-NG Instrument Spectrometer is Optical Head (I-OH) and Electronics Module (I-EM).


The Platform Space of the ITASat CubeSat Satellite is 4U.


The Last Flyover Date of the OSIRIS-REx Spacecraft is April 7, 2021.


The Operation Modes of the NICER X-ray telescope Telescope is 2-axis gimbal, tracking celestial X-ray sources, pointing towards ELC 3.


The Publication Date of the Cluster Satellite is 19 December 2014.


The Noise of the Radiometry Sensor is < 0.8 Wm -2  sr -1.


The Spatial Sampling of the Instrument Spectrometer is 1 arcmin.


The Data Quantization of the WiFS camera Camera is 7-bit (radiometric resolution of 128 grey levels).


The Quantity of the NiH2 Batteries Power Subsystem is 5.


The Dimensions of the VDES Antenna Antenna is 62 x 62 x 73 cm.


The Conference Date of the Swarm Satellite is Oct. 4-8, 2010.


The Distance of X-ray jet from the Manatee’s head of the XMM-Newton X-ray Observatory is Approximately 300 light years.


The Support Initiative of the Copernicus program Satellite Program is Stocktaking exercise with a new observation-based service to monitor CO2 emissions resulting from human activities.


The Beam width of the VNIR Band is 5.5 µrad.


The Design and Operation of the Tiny Ionospheric Photometer (TIP) Instrument is Not provided.


The Operational Lifetime Requirement of the SST Satellite is 7.5 years.


The Sampleability of the Site Nightingale Crater is High.


The GSD at nadir of the Imager Satellite Instrument is PAN: ≤2.5 m, MS: ≤10 m.


The Cloud Imager of the Atmospheric-sounding instrument Spectrometer is Built-in.


The Downlink Data Rate of the NEMO-AM Satellite is 2Mbit/s.


The Agency of the ZACUBE-2 Satellite is SANSA, CPUT.


The Number of Satellites of the EDSN Swarm Satellite Network is 8.


The Measured Quantity of the SAGE-III Instrument is Chemical composition of the atmosphere and the vertical distribution of aerosols and gaseous compounds.


The Distance from Earth of the NGC 3603 Star Cluster is 20,000 light-years.


The Manufacturer of the POPSat-HIP-1 3U CubeSat is Microspace Rapid Pte Ltd..


The Spectral Bands of the Geoton-1 Imaging Instrument is 8 bands in the VNIR spectral range.


The Time to Reach Oort Cloud of the Voyager 2 Space Probe is About 300 years.


The Mission Lead of the SPARCS Satellite is Arizona State University.


The Single Shot Precision of the TDC-GPX Time-to-digital converter is 10 ps.


The EPS Board of the MinXSS Satellite is Unknown.


The Primary Star Mass of the M51-ULS X-ray Binary is 20 to 30 times the mass of the Sun.


The Flexible Mode Frequency of the Payload Satellite Component is Below 10 Hz.


The Fuel Tank Distribution of the Advanced Composition Explorer Spacecraft is One pair having approximately 20% more propellant than the other pair.


The Nominal Lifetime of the TanDEM-X Satellite is 5.5 years.


The Unknown of the Super Dual Auroral Radar Network Radar Network is Unknown.


The Spatial Resolution of the EO System Earth Observation System is ~50 m (goal).


The Deployment of the KickSat CubeSat is about 250 femtosatellites into LEO (Low Earth Orbit).


The Quantity of the BCR Battery Charge Regulator is 6.


The Secondary Structure Components of the S/C Satellite is N/S radiators, E/W panels, Earth-facing panel.


The Full Well Charge of the Imager Camera is 60,000 e -.


The Biomass Estimate Comparison of the GEDI Lidar Instrument is Compared favorably to forest inventories from the Food and Agriculture Organization of the United Nations and U.S. Forest Service Forest Inventory and Analysis data.


The Flux Limitation of the Sensor Gas Sensor is Limits the oxygen flux to the cathode.


The Guidestar Selection of the Spacelab Instrument Pointing System Pointing System is Improvements.


The Data Validation of the TanDEM-X Satellite is Used additional remote sensing data to validate the calculated results and differentiate forest areas from non-forested regions.


The Minimum Number of Satellites for Navigation Fix of the T3000G2 receiver GPS Receiver is 4.


The Design Life of the Solar Panels Power Source is Up to 15 years.


The Spectral Range (VIS) of the VHRR Very High-Resolution Radiometer is 0.55 - 0.75 µm.


The Source of the Induced Pluripotent Stem Cells Cell Type is Adult cells genetically programmed to return to an embryonic stem cell-like state.


The ESA: 2.8 x 10 -4 [cm 2 str eV/eV/10º], ISA: 4.9 x 10 -4 [cm 2 str eV/eV/10º] of the Geometrical Factor Sensor is Geometrical factor ESA: 2.8 x 10 -4 [cm 2 str eV/eV/10º], ISA: 4.9 x 10 -4 [cm 2 str eV/eV/10º].


The Data Rate of the Radio Subsystem Satellite Subsystem is Varying based on the channel capacity.


The Data Distribution Telemetry of the MTG SpaceWire Architecture Satellite Architecture is 295 Mbit/s (Imager S/C) and 557Mbit/s (Sounder S/C).


The End of Life Date of the SpaceX CRS-19 Mission is 7 January 2020.


The Antenna Array Size of the PR Phased Array System is 2 m x 2 m.


The 3 dB Beamwidth of the Satellite Device Unknown is 2.0º±0.1º.


The Type of the CITRIS Receiver is Tri-frequency.


The Operation Start Date of the SMAP Satellite is May 19, 2015.


The Surface Resolution of the FREND Instrument is ~40 m.


The Owner of the RADARSAT Constellation Satellite Constellation is Canadian Space Agency (CSA).


The CMOS Image Sensors of the C3D Instrument Imaging Device is 2.


The Detector Type of the DIDM Instrument is MCP (Microchannel Plate).


The Launch Date of the Aalto-1 Satellite is End of 2016.


The Capture and De-Orbit Capabilities of the ELSA-M Spacecraft Servicer is Innovative rendezvous, capture and de-orbit capabilities with a full-size constellation client.


The Power Consumption of the Photometer Instrument is ≤ 3.5 W.


The Coverage Area of the HawkEye 360 Satellite Constellation is Millions of square kilometers.


The Temperature of the Deep Space Calibration Reference is Approximately 4 K.


The Bedrock Formation Age of the CaSSIS Instrument is Between 3.7 and 4.1 billion years ago.


The Platform of the 118 GHz Radiometer Radiometer is Aircraft.


The URL of the Resurs-P1 Satellite is http://www.russianspaceweb.com/resurs_p.html.


The Spatial Resolution of the SMI Spaceborne Multispectral Imager is 80 m.


The Bus Name of the NorSat-1 Satellite is NEMO platform.


The Data Transmission Subsystem of the Sentinel-1, -2, and -3 Satellites is X-band TXA (Transmission Assembly).


The Solar Arrays of the UK-DMC-2 Satellite is Three body-mounted heritage solar arrays.


The Test Flight of the Orion Spacecraft is Artemis I.


The System Type of the GeoSTAR Atmospheric Microwave Sounder is 2-D spatial interferometric system.


The Data Transmission of the McMurdo Ground Station Ground Station is Real-time.


The Compression Type of the DHU Data Handling Unit is Online lossless and lossy.


The Modes of the Payload 2 CMOS Camera is VGA/QVGA.


The Project Team Size of the CIMON Astronaut Assistant is Approximately 50.


The Sensitivity of the Three-axis diagonal gradiometer Gradiometer is < 10 -12  m s -2  Hz -1/2.


The Orbit Type of the Satellite Communication is Sun-synchronous near-circular polar orbit.


The Battery Type of the Sail Power Source is Lithium-ion.


The International Headquarters Establishment Date of the Spacety Company is 2019.


The Role of the Martin Popek Individual is His photos add another dimension to the research.


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


The Power Source of the GHGSat-D Microsatellite is Body-mounted solar cells.


The Spectral Bands of the SMI Spaceborne Multispectral Imager is Visible (420–700 nm) and near infrared (650–1050 nm).


The Diameter of the Ryugu Asteroid is 900 m.


The Distance from the Sun of the Voyager 1 Space Probe is Beyond the heliosphere.


The Control Type of the Thermal Control Subsystem Subsystem is Passive.


The Components of the MOC Mission Operations Center is Mission planning software, data management system, spacecraft ground terminal.


The Effect of the Solar Storms Natural Phenomenon is Affected a variety of technological systems around the world.


The Limb-Sounding Concept/Technology Test of the OMPS UV Hyperspectral Imaging Spectrometer is ISIR (Infrared Spectral Imaging Radiometer) flown on Shuttle flight STS-85 (Aug. 7-19, 1997).


The Observation Time of the MOMS-2P Instrument is 3 minutes/day.


The Whistler Waves Energy Transfer of the Van Allen Probes Satellite is From copious low-energy particles to sparse high-energy particles.


The Science Outcomes of the NICER X-ray Timing Instrument is Establishing the existence of intermediate mass black holes, unification of stellar-mass and supermassive black holes, testing models of polar accretion onto magnetic white dwarfs, detecting photon bubble oscillations, probing galaxy evolution in clusters.


The Contract Date of the Capella Company is 17 June 2021.


The Energy Range of the ULEIS Spectrometer is About 20 keV/n to 10 MeV/n.


The Cargo Load for Return of the SpaceX Dragon Spacecraft is ~720 kg.


The Mission Status of the QBITO CubeSat is Mission complete.


The Power Lines for SVM-PDU and FPA-PDU of the MRU Main Regulator Unit is 2 x 2.


The Unknown of the FlexRX Receiver Communication Device is Unknown.


The Date of the Volcanic Eruption Lights Up Iceland Image is 23 March 2021.


The Image Capture Date of the CaSSIS camera Camera is 13 June 2021.


The Maximum Microsatellite Dimensions of the NanoRacks Microsat Deployer Satellite Deployer is 95 cm x 83 cm x 64 cm.


The Conference Presentation of the EarthCARE Multi Spectral Imager Imaging System is SPIE Remote Sensing Conference, Toulouse, France, Sept. 20-23, 2010.


The Platform Data Rates of the Argos System Data Collection System is Higher.


The Orbit Inclination of the ISS Space Station is 51.6º.


The Design Life of the GaoJing / SuperView minisatellites Satellite is 8 years.


The Accuracy of Wind Velocity (PBL) of the Aeolus Satellite is 2 m/s.


The Satellite Orbit of the Satelles PNT Service Provider is LEO.


The Growth Rate Approximation of the C/NOFS Satellite is Linear.


The Observation Geometry of the Satellite Unknown is Limb.


The Orbit Altitude of the GRIFEX 3U CubeSat is ~ 650 km.


The Purpose of the WFIRST Telescope is Directly image exoplanets by blocking out the light of their host stars.


The Approval Date of the Sentinel Asia Disaster Risk Management System is October 2005.


The Number of Terran R launches of the Terran R Launch Vehicle is More than 20.


The Polarization Measurement of the TANSO-FTS Sensor is P and S polarization.


The Mission Design Life of the Microsatellite Satellite is ≥ 2 years.


The Purpose of the Hiber-3 smallsat Satellite is Provide satellite connectivity to “internet-of-things” (IOT) devices.


The Optical Configuration of the Spectrometer Spectrometer is Czerny-Turner.


The Mirror Surfaces of the Limb Imager Telescope is Fully free-form.


The Synergy products of the OLCI Camera Assembly is Based on combination of OLCI and SLSTR data.


The Observation Date of the Orion A Nebula is 18 November 2019.


The Mass of the LISS-IIM Instrument is 80.8 kg.


The Material of the Focal Plane Array Detector Array is SiC.


The Origin of the Sample Return Capsule Capsule is NASA Stardust mission.


The End of Life Date of the Solar-A / Yohkoh Satellite is 23 April 2004.


The Mass of the MHX-2400 S-band Transmitter/Transceiver is 75 g.


The IFOV of the Satellite Communication is Very large.


The Frequency Range of the Copernicus Imaging Microwave Radiometer (CIMR) Radiometer is 1.4–36.5 GHz.


The Mission Status of the CYGNSS Satellite Constellation is On Track.


The Vertical Range of the SAGE-III Spectrometer is 0 km to 100 km.


The Mission Objective of the FASTRAC Satellite is Investigate enabling technologies crucial for satellite formations, including on-orbit micro-thrust capability, relative navigation, attitude determination, and satellite crosslink communications.


The Radar of the Soil Moisture Active Passive (SMAP) Satellite is L-band.


The Complementarity of the IMAP-Ultra Instrument is Complements the measurements of IMAP-Lo and IMAP-Hi.


The Location of the DRS Data Reception Station is Shadnagar, Hyderabad.


The Frequency Range of the Variant Satellite is 0.1 Hz to 40 kHz.


The Dimensions of the ALTIUS Satellite is 800 x 800 x 1200 nm.


The Wind Speed Accuracy of the SCAT Wind Measurement System is 10%.


The Publication Date of the Orbiting Carbon Observatory Satellite is 2004.


The Estimated Growth Opportunity of the Hiber Satellite Network is £3.5B.


The Instrument Size of the Hyperion Imaging Spectrometer is 39 cm x 75 cm x 66 cm.


The Experiment of the GeReLEO Smart Antenna Antenna is Test.


The Launch Date of the ELaNa V CubeSat is March 2014.


The Bands of the PMC Imager is NIR and three visible (blue, green and red).


The Forecast Mode Duration of the C/NOFS Satellite is 3 months required, 27 month goal.


The Payload Power of the Heinrich Hertz Satellite is 3.6 kW.


The Launch Provider Announcement Date of the TEMPO Pollution Monitoring Instrument is 18 March 2020.


The Plaque Content of the LAGEOS Satellite is Binary numbers, Earth orbiting the sun, Maps of Earth at different epochs.


The Solar Cells of the SCARAB 1U CubeSat bus is Spectrolab triple-junction CIC solar cells (body-mounted).


The Operational Requests Management of the TDP Operations Satellite Operations is Managed at a top level by ESA.


The Instrument Type of the OCO-3 Instrument is Atmospheric chemistry.


The Orbital Planes of the T1TL Prototype Constellation Satellite Constellation is 2.


The Azimuth Resolution of the Spotlight Imaging Mode is 1.7 m (single pol.).


The Spatial resolution of the Microwave System Microwave System is 19-260 km.


The Measurement of the WISPR Instrument is Solar Wind Properties.


The Technology of the Micro-gravity experiment Experiment is Important for a better understanding of the characteristics and the mechanisms of the convection movement of the fluid with a free surface or a boundary surface on the ground.


The Planned Quantity of the Surface Rovers Deployment Maneuver is Four.


The Owner of the Hosted Payload Satellite Payload is German Federal Ministry of Defense (BMVg).


The Deployment Status of the Aireon Air Traffic Surveillance System is Closer to Complete.


The Data Rate of the LEID Instrument is 1 kbit/s.


The IFOV (beam width) of the Antenna Reflector is 5.3º.


The Announcement Date of the Nearby star HR1099 Satellite is Jan. 30, 2000.


The Function of the SES Instrument is Confirm predictions of thermionic and photoelectric emission.


The Orbit Period of the Primary Mission Satellite is 101 minutes.


The Number of Satellites of the SkySat-16 to -18 Satellite is 3.


The Ground Sample Distance of the HPT High Precision Telescope is 3 m.


The Build Location of the Hardware Quick Look SAR Processor SAR Processor is Ahmedabad.


The Voltage of the Voltage 2 Power Amplifier is -5.5±5%.


The Focal Length of the Telescope Optical Instrument is 2000 mm.


The Subaperture Quantity of the SMART Imaging System is Four and eight.


The Resolution of the M-CAM 1 Monitoring Camera is 1024 x 1024 pixels.


The Observables of the LIMS Limb Infrared Monitor is O3, H2O, NO2, HNO3 and temperature.


The Stability Requirement of the Lunar Orbit Orbital Phase is Orbit where the spacecraft doesn’t impact the surface for at least 6 months.


The Image Interval of the IBIS X-ray Imager is Roughly eight minutes.


The Objective of the Sich-2 Satellite is Obtain high-resolution imaging data in the visible and infrared region.


The Sensitivity of the LDEX Instrument is Especially sensitive to the metallic compounds of minerals and any species which easily form ions (e.g. water).


The GSD of the Spectral Band B Spectrometer is 5.


The Observation Date of the Solar Dynamics Observatory Satellite is July 30, 2011.


The Launch Mass of the HY-1C Satellite is 442 kg.


The Modes of the MRSE Instrument is SAR, Scatterometer, Radiometer.


The Science Objectives of the TROPICS Constellation of CubeSats is Relate the retrieved environmental moisture measurements to coincident measures of storm structure (including size) and intensity.


The Frequency Bands of the Copernicus Sentinel-6 Poseidon-4 Radar Altimeter is C- and Ku-band.


The Bandwidth of the Spacecraft Repeater Communication Device is 25 kHz.


The Components of the Receiver Communication System is Low noise preamplifier with BFS17, LNA (Low Noise Amplifier), first mixer NE602, crystal filter, intermediate frequency amplifier A281D, last mixer NE602.


The Launch Date of the GEOS-2 Satellite is Jan. 11, 1968.


The SAR Payload Orbit Average Power Consumption of the RCM Satellite is Approximately 200 W.


The On-ground and In-orbit Calibration Presentation of the Microscope Space Mission is 2010.


The Launch Date of the SPOT-2 Satellite is January 1990.


The Distance to Galaxy of the GRB 031203 Gamma-Ray Burst is Less than 1300 million light years.


The Power of the STAFF/DWP Instrument is 5.0 W.


The Mounting of the SEP Solar Energetic Particles Instruments is On the spacecraft body.


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


The Sensitivity of the Radar Instrument is 1.7 dB.


The Orbit Altitude of the Aalto-1 Satellite is 505 km.


The Purpose of the Scale Factor Measurements System (SFMS) Measurement System is Measurement of the absolute laser frequency.


The Power of the Voltage 1 Power Amplifier is 28 @ 28 V worst-case.


The Production Rate of the Factory Facility is About one satellite per week.


The Altitude of the Schiaparelli module Spacecraft is About 3.7 km.


The Flights of the AEPI Instrument is ATLAS-1.


The Attitude Stability of the ADCS Attitude Determination and Control Subsystem is ≤0.001º/s (3σ, 3-axis).


The Occultation Duration of the CTECS Satellite is 6 minutes.


The Grant Amount of the SpaceChain Company is $596,000.


The URL of the Satellite Satellite is http://library01.gsfc.nasa.gov/gdprojs/projinfo/sage.pdf.


The Manufacturer of the InSight Lander is Lockheed Martin Space in Denver.


The Components of the G&C system Guidance and Control System is Sun sensors, a ST (Star Tracker), redundant IMUs (Inertial Measurement Units), the GT, reaction wheel assemblies, and a monopropellant hydrazine propulsion system.


The Goal Unit Cost of the Super Strypi Launch System is $12 million.


The Incident Angle of the Reflection Diffuser Calibration Device is θ inc. = 65º.


The Publication Date of the ISEE-1 Spacecraft is July 1978.


The Development Date of the PALSAR Ground Data System Ground Data System is 2004.


The Mission Goals of the ARMADILLO Satellite is Train students in best systems engineering practices by executing a complete spacecraft life cycle from concept design to mission operations.


The Manufacturer of the MWIR Imager Imaging Device is Leonardo.


The Beacon Transmission Rate of the ELFIN-B Satellite is 9600 baud.


The Orbit of the LunaH-Map Spacecraft is Stable circular orbit.


The Power Consumption of the OBIS Onboard Information System is 32 W.


The Meeting Date of the Jason-3 Satellite is Oct. 18-20, 2010.


The Signal Processing of the CCD Detector Detector is Fast electronics near the detector head.


The Arrival Date of the Dragon CRS-14 Spacecraft is April 4, 2018.


The Number of Instruments of the ISEE-3 Satellite is 13.


The Swath Width of the Spotlight-2B Satellite is 10km.


The Polarization of the ICI-7 Radiometer is V.


The Swath of the SLSTR Spectral Imaging Instrument is 750 km.


The Design Concept of the AOCS Attitude and Orbit Control System is Gyro stellar hybridation with reaction wheel actuators unloaded through magnetotorquer bars, safe hold mode only relies on kinetic momentum, coarse sun sensors and magnetic sensors and actuators, four 1N thrusters in blow down mode limited to orbit contro.


The Temperature Range of the Silicate Clouds Atmospheric Phenomenon is Between about 1,900 degrees Fahrenheit and 3,100 degrees Fahrenheit.


The Uplink Beacon of the RF Communications Communication System is CW (Continuous Wave) UHF beacon.


The Capital Market Day of the Small GEO Satellite is February 11, 2009.


The Quantity of the Cameras Imaging is 2.


The Mass of the exactView-1 Satellite is 100 kg.


The Payload Power of the Solar Orbiter Satellite is 180 W.


The Launch Date of the VRSS-1 Satellite is September 29, 2012.


The Report URL of the AAUSAT3 Satellite is http://zcuba.dk/reports/08gr633.pdf.


The Bus Manufacturer of the THEMIS Probes Satellite is Swales Aerospace.


The Diameter Uncertainty of the KELT-11b Planet is Just under 4300 km.


The Operator of the BSOCC Satellite Operation Control Center is Bowie State University.


The Launch Date of the PSLV Satellite Launch Vehicle is Dec. 16, 2015.


The Mission Type of the CryoSat Satellite is EO.


The Operational Capability of the SSPIDR Project is Power 'on demand' anywhere on the globe regardless of weather or latitude, day or night and without vulnerable logistics lines.


The Instrument 1 of the CryoSat-2 Satellite is DORIS.


The Development and Build Contractor of the SAR-Lupe Satellite System is OHB System AG.


The Project Agreement Date of the YouthSat Satellite is January 25, 2007.


The Number for Coverage Match of the LEO Satellites Satellite is Around 300.


The Image Sensor Pixel Size of the CMV4000 CMOS Color Detector is 5.5 µm.


The Frequency of the Full Calibration of HIS Calibration Process is Bimonthly.


The Power of the Spacecraft Satellite is 357 W (long-term), 1350 W (short-term).


The Power of the Magnetometer Sensor is < 0.8 W.


The Power Consumption of the Image Sensor Imaging is 1 W.


The Arrival Date of the Europa Clipper Spacecraft is Early June 2022.


The Attitude Knowledge Stability of the ADCS Attitude Determination & Control Subsystem is ≤ 0.12 µrad in 2.5 seconds.


The Safe Mode Attitude of the AOCS Attitude and Orbit Control System is Earth-oriented.


The Mission Duration of the RBSP spacecraft Satellite is 2 years.


The Satellite Mass of the Terra Bella Satellite Constellation is ~120 kg.


The NEdT Performance of the VIIRS Instrument is Excellent.


The Observation of the ALOS/PALSAR Satellite is Magnitude-9.0 Earthquake off the Pacific coast of Tohoku-Kanto District in Japan in 2011.


The Total Channels of the Spectral Bands Spectrometer is 713.


The Swath Width of the MSU-E Multispectral Scanner is 28 km.


The Data Delivery Speed of the Quasar 3000 IMU Inertial Measurement Unit is 100Hz.


The Type of the VDES Antenna Antenna is Folded dipole Yagi-Uda antenna with three elements in crossed configuration.


The TT&C Downlink Data Rate of the RF Communications Communication Subsystem is 1.6 - 4 Mbit/s.


The End of Life Date of the PSat-2 CubeSat is June, 2025.


The Scene Size of the ICEYE-X1 Satellite is 40 x 83.3 km.


The Development Time of the CubeSat Satellite is 2 years.


The Launch Date of the GFO Satellite is Feb. 10, 1998.


The | of the Capella Space Satellite Company is Capella Space Is First American Company to Send Advanced Commercial Radar Satellite to Space.


The Development Location of the LHASA Model Landslide Hazard Assessment Model is NASA/GSFC (Goddard Space Flight Center) in Greenbelt, Maryland.


The Operating Bands of the GAS Grating Spectrometer is Four NIR/SWIR bands.


The Mission Overview of the GCOM-W Satellite is Not provided.


The Image Capture Date of the ICEYE-X2 Satellite is Four days after the satellite's launch.


The Incident Angle Dependence of the Scanning Systems Optical System is Problematic.


The Extinction Cross Sections of the Species Atmospheric is Wavelength Dependent.


The Field of View of the MSC Camera is 6° x 0.3°.


The Map Resolution of the GRAIL Probes Spacecraft is Highest resolution.


The Type of the REIS (JSS-56) instrument Instrument is REIS (JSS-56).


The BeiDou Occultations of the GNOS Instrument Occultation Measurement Device is About 200 per day.


The URL of the BepiColombo Mission is http://www.issfd22.inpe.br/S10-Orbit.Determination-OD/S10_P4_ISSFD22_PF_065.pdf.


The Position Control of the CanX-4&5 Satellite is 1 m.


The Observation Date of the Spitzer Satellite is 28 April 2020.


The Timing Accuracy of the BOSS Real-time operating system is 1 ms.


The Number of Operational Satellites of the DMSP (Defense Meteorological Satellite Program) Satellite Program is 3.


The Data Rate of the HSDR High-Speed Data Recorder is 80 Mbit/s.


The Spectral Bands of the MSI-0 and MSI-1 MSI Instruments is 0.45 - 0.52 µm, 0.52 - 0.60 µm, 0.63 - 0.69 µm, 0.76 - 0.90 µm.


The Test Equipment of the ICI Instrument Instrument is Unknown.


The Launch Plan of the Arianespace Launch Provider is Launch the rest of OneWeb’s constellation this year.


The Launch Vehicle of the Kounotori Spacecraft is H-IIB vehicle of MHI (Mitsubishi Heavy Industries, Ltd.).


The Booster Landing of the SpaceX CRS-24 Mission is Successful.


The Atmosphere Mass of the Earth Planet is Less than one millionth of the total mass of Earth.


The Mission Objective of the Psyche spacecraft Spacecraft is Explore a metal-rich asteroid in the main asteroid belt between Mars and Jupiter.


The Expected Mission Duration of the RapidEye Satellite Constellation is Through 2020.


The Launch Date of the ITUpSat-1 Satellite is 23 September 2009.


The Size of the Satellite Payload Module is 954 mm x 954 mm x 1218 mm.


The Location of the Dasht-e Lut salt desert Desert is Iran.


The Frequency Band of the AMSU Microwave Radiometer is 50 to 60 GHz.


The Processor of the SCB Spacecraft Bus is Motorola 68302.


The Number of Auxiliary Signals for ECCM of the Complete Solution Antenna Configuration is 4.


The RAM of the OBC On-Board Computer is 2MByte payload data.


The Field of View of the OMPS Nadir Profile Spectrometer Spectrometer is 16.6°.


The Number of Spacecraft of the THEMIS Satellite is Three.


The Redundancy of the EPPS Electric Propulsion Subsystem is Fully redundant system.


The Thermal Control of the KOMPSAT-6 Satellite is Passive & processor-controlled thermal control.


The Purpose of the ICON Space Mission is Retrieve all of the properties of the system that both influence and result from the dynamical and chemical coupling of the atmosphere and ionosphere.


The Constellation of the TEMPO Instrument is Instruments measuring air quality over the Northern Hemisphere.


The URL of the Dellingr Satellite is http://spaceflight101.com/dragon-spx12/dellingr/.


The Thermal Management Requirement of the Invar Material is Careful attention to thermal management.


The Exposure Time of the Solar Flare Sites Imaging Device is < 10 ms.


The Type of the Satellite Orbit is Elliptical polar orbit.


The Data Rate of the RA-1 Antenna Antenna is ≤ 15 kbit/s.


The Provider of the ADCS System is CNES.


The PI of the MAHRSI Instrument is R. Conway.


The Power of the Voltage 2 Power Amplifier is 0.055.


The Leading Satellite Date of the GRACE-2 Satellite is January 2006.


The Number of Available Rows per Filter Band of the QWIP Array Sensor Array is 32.


The Altitude of the Satellites Communication is 550 km.


The Manufacturer of the TEMPEST-D Radiometer Instrument is NASA/JPL.


The Field Location of the Sunspot Solar Phenomenon is Always located at the boundary between the bright region and the umbra.


The Measurement Uncertainty of the CO2 Greenhouse Gas is Unknown.


The Pulse Repetition Frequency of the RA-1 Radar Altimeter is 1020 Hz.


The Launch Site of the BioSentinel 6U CubeSat is Kennedy Space Center, Cape Canaveral, FL.


The Purpose of the MSX/UVISI Instrument is Probe the atmospheric composition accurately.


The Solar Cell Material of the LFSA Photovoltaic Solar Array System is Copper Indium Diselinide (CuInSe2).


The URL of the TOPCAT Satellite is https://web.archive.org/web/20120306134438/http://www.bis.gov.uk/assets/bispartners/ukspaceagency/docs/space%20science/cubesats/cmos%20imager%20text.pdf.


The Manufacturer of the SSTI GPS Receiver is Laben, Milan, Italy.


The Pulse Width of the RainCube Radar is Variable.


The Propellant Mass of the RCS Reaction Control System is 320 kg.


The FOV of the COR1 Coronagraph1 imager is 1.25 - 4 R sun.


The Orbital Repeat Time of the OrbView-2 Satellite is 16 days.


The Documented On-Orbit Anomalies of the BRMM Spacecraft is 24.


The Mission Objective of the Sentinel-5 Satellite is Operational monitoring of trace gas concentrations for atmospheric chemistry and climate applications.


The Period of the ALOS-3 Satellite is 98 minutes.


The Period of the Meteor-M2 Satellite is 101.41 minutes.


The Small Window Time Resolution of the CCD Image Sensor is 0.3 seconds.


The Loss Date of the EgyptSat-2 Satellite is Unknown.


The Launch Date of the Kepler Space Telescope is March 7, 2009.


The Availability of the GPS Simulator Equipment is Not available.


The Commanding Management of the Ground Schedule Execution System System is Nominal.


The Focus of the Characterization Process Satellite Debris Analysis is Utilize automation to expedite fragment characterization process and minimize human-in-the-loop.


The URL of the NanoRacks Airlock Module Airlock Module is http://nanoracks.com/wp-content/uploads/NanoRacks-Airlock-Presentation.pdf.


The Pixel Resolution of the SPIM5 Spectrometer is 14 bit.


The Data Delivery of the ICEYE Satellite Constellation is Near real-time.


The Speed of the ICEYE-X1 Satellite is More than 7.5 km/s.


The Dimensions of the Göktürk-1A Satellite is 4.2 m x 2.5 m x 1.6 m.


The Slit Height of the Short Wavelength Band Spectrometer is 2.75 cm; 1/33 for bright target.


The Volume of the DeMi Satellite is ~4.5U.


The Download Transmission Rate of the DubaiSat-1 Satellite is 30 Mbit/s.


The Orbits of the Odin Satellite is > 60,000.


The Sensor Model of the Camera System Sensor is Aptina MT9P031 5 Mpixel CMOS sensor.


The First Noctilucent Cloud Observation of the AIM Satellite is 2007.


The Conference Presentation Date of the X-Sat Satellite is Nov. 22-26, 2004.


The Stabilization of the ZY-3 Satellite is 3-axis.


The Apoapsis Altitude of the Satellite Spacecraft is 21813.2 km.


The Type of the Propulsion System Satellite Propulsion is Chemical bi-propellant.


The Spectral Range (µm) of the Band 5 Spectral Band is 11.5 - 12.5.


The PIs of the SOVA Radiometer is D. Crommelynck, IRMB, Brussels, Belgium; C. Fröhlich, PMOD/WRC Davos, Switzerland.


The Dust Grain Width of the COSIMA Mass Spectrometer is About 50 µm and 70 µm.


The Event Cause of the LROC Camera System is Hit by a tiny meteoroid.


The Temperature of the PM Satellite Component is 18.3~26.7º.


The Purpose of the Secure Communications Satellite Satellite is Provide secure and resilient satellite communications.


The Service Infrastructure of the Airbus Defence and Space Service Provider is Commercial data exploitation and customer interfaces.


The Number of Satellites of the ICEYE Constellation Satellite Constellation is Approximately 18.


The Data Rate of the X-band Transmitter Transmitter is Up to 210 Mbit/s.


The Launch Date of the SpaceX CRS-6 Mission is April 7, 2015.


The Number of Satellites of the OHB-SSTL consortium Satellite Manufacturers is 8.


The Onboard Network Specification of the JWST Avionics Spacecraft Avionics is SpaceWire.


The Purpose of the JUICE Satellite is Explore Callisto, Europa and Ganymede.


The URL of the Spaceborne Frequency Comb Metrology Metrology System is https://www.osapublishing.org/DirectPDFAccess/DBE99771-B99B-C7D3-BC1981AC3BB40F6B-354726/optica-3-12-1381.pdf?da=1&id=354726-&seq=0&mobile=no.


The Original Purpose of the CRS Cosmic Ray Subsystem is Measure planetary systems.


The Data Averaging Period of the ELS-A Electron Measurement Instrument is 4 months from November 2008 to February 2009.


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


The Calibration Method of the OMPS Sensor is Solar illuminated diffusers.


The CPU of the STRV-1d DHS Data Handling System is 8051 rad-hard.


The Ground Pixel Sizes of the MOMS-02 Instrument is Unknown.


The Ka-band of the RF Communications Communication Subsystem is 350 Mbit/s.


The Sample Return to Earth of the OSIRIS-REx Spacecraft is Sept. 24, 2023.


The Parallel to DOTCam of the SHU Software Application Development is True.


The Rotation Speed of the AMSR-E Instrument is 40 rpm.


The Cooling Method of the Telescope Tube Assembly Telescope is Passively cooled.


The Calibration Data of the GPM Mission is Measurements from the GPM Core Observatory and rain gauge networks around the world.


The Location of the ISIS Instrument is As far aft on the spacecraft body as possible, on the ram side, just inside the umbra line.


The Uniformity of Absorber Surface of the HTS/AMSR2 Microwave Absorber is 2.5ºCp-p.


The Testing Tools of the EDSN Organization is DevSats, Flatsats, EDUs.


The Signal Frequency of the Ground Station Antenna System Antenna System is 8200.5 MHz.


The Outburst Date of the Comet 67P Comet is 2016 July 03.


The Mission Name of the LunaH-Map Satellite is LunaH-Map.


The Iron Particle Distributions of the WISPR Optics Optical System is 0.5 – 3 µm.


The Form Factor Dimensions of the Myriad RF board RF Board is 50 mm x 55 mm.


The Calibration and Validation Duration of the RapidScat Instrument is Two weeks.


The Swath of the OLCI Spectral Imaging Instrument is 1270 km.


The Components of the TCS Thermal Control Subsystem is FSSM (Flexible Second Surface Mirror coatings), MLIs (Multi-Layer Insulation Blankets), Germanium-coated black Kapton foil, black paint, aluminized tapes/low emissivity surface treatments, thermal doublers, interface fillers and thermal washers.


The Orbit Transition of the LunaH-Map Spacecraft is Several months.


The Reentry Date of the Long March 5B Rocket Stage is May 8.


The Lead Contractor of the Heinrich Hertz Satellite is OHB System AG.


The Size of the Solar Flare Natural Phenomenon is X8.2-sized.


The Main Processor Frequency of the NSat Satellite is 100 MHz.


The Data Density of the Scanning LIDAR LIDAR is Provided data at a reasonable density for the last 30 m.


The Accretion Disc Width of the V404 Cygni Black Hole is 10 million kilometers.


The Clock Signals of the CIB Interface is 1 Hz and 220 Hz.


The Antenna Gain Requirement of the FormoSat-5 Satellite is Unknown.


The Cadence of the Proton Energy Spectra Measurement is Up to around 20 MeV.


The Presentation Date of the Jaan Praks Person is Sept. 22-24, 2014.


The PNAS Publication Date of the Swarm Satellite Constellation is March 21, 2022.


The Manufacturer of the EPS Electrical Power Subsystem is GomSpace.


The Leading Noise Terms of the Satellite Spacecraft is TM-to-satellite stiffness coupling to satellite motion.


The Mission Control Location of the Odin Satellite is Stockholm.


The Dimensions of the PACE nanosatellite Satellite is 100 mm x 100 mm x 243 mm.


The Products of the CERES Instrument is Solar-reflected and Earth-emitted radiation from the top of the atmosphere to the Earth's surface.


The Power of the HIRES Instrument is 10 W.


The IFOV N/S x E/W (º) of the FCI-TA Instrument is 0.40 x 0.40.


The Managing Center of the Eu:CROPIS Satellite is DLR (German Aerospace Center).


The Platform of the exactView-1 Satellite is SSTL-100.


The Dimensions of the Instrument Spectrometer is 445 x 327 x 182 mm3.


The Total Travel Distance of the BepiColombo Spacecraft is Nine billion kilometers.


The Launch Mass of the Spacecraft Satellite is 3375 kg.


The Resolution of the MWR Dicke Radiometer is 50 km.


The Launch Date of the Nauka Development Satellite is Unknown.


The Inclination of the ALL-STAR-1 Satellite is 51.6o.


The Telescope/Spectrograph Assembly of the MAHRSI Instrument is f/7.5 Czerny-Turner spectrograph with a 75 cm focal length behind a 50 cm focal length telescope (57 cm2 aperture).


The Data Center of the GBOT Project is Observatoire de Paris.


The Supplier of the GPSP Instrument is NASA.


The Mission Extension of the Cluster Satellite Constellation is December 2005 to December 2009.


The Depth of the Holes Drill Holes is 2,450 meters.


The Mission Leader of the ASTRA LLC Organization is ASTRA LLC.


The Backup Station Frequency Bands of the PAZ SAR Processor Ground Segment Processor is S/X-band.


The Propulsion System of the Spacecraft Satellite is None.


The URL of the China High-resolution Earth Observation System (CHEOS) Satellite System is http://www.nasaspaceflight.com/2013/04/china-back-in-action-long-march-2d-gaofen-1/.


The Number of Pixels of the Band 2 Spectral Band is 1600.


The Effect of the Water Cycle Natural Process is Moves heat.


The Announcement Date of the X-ray Navigation CubeSat Mission CubeSat Mission is 3 May 2018.


The Field of View of the A Photometer Instrument is 0.2o x 2.1o.


The Launch Date of the SuperView-1 01 and Superview-1 02 Satellite is December 28, 2016.


The Response to Stresses of the Phytoplankton Marine Organism is Varying greatly in size, function, and response to environmental and ecosystem changes or stresses such as ocean acidification.


The Ground Stations of the PRISMA Satellite Network is DLR antennas at Weilheim and the antennas operated by SSC in Sweden.


The Commissioning Phase Date of the Envisat Satellite is June 2001.


The Footprint of the Telescope Instrument is Smaller than 30 m.


The RF Output Power of the Transmitter Communication Device is 12 W.


The Normalized to of the PRI Photochemical Reflectance Index is 570 nm.


The Spacecraft Power of the QuickBird-2 Satellite is 1.14 kW (EOL).


The Bandwidth of the Band Cameras Camera is 5.0 nm.


The Data of the LI Lightning Imager is Real-time data on the location and intensity of lightning flashes.


The Material of the Optical Benches Optomechanical System is Composite tubes with titanium fittings.


The Issue of the BPP (Bi-axial Pointing Platform) Pointing Platform is Difficulties in achieving the pointing control precision.


The Quantum Communication of the Micius Satellite is Enabled.


The Passband Range of the SPIM4 Spectrometer is 377-582 nm.


The Thickness of the Low LET Detector Detector is 1000 µm.


The Award Abstract Number of the OPAL CubeSat is 1242901.


The Imaging Location of the Landsat 8 Satellite is British Columbia and Alberta.


The Mission of the INSAT-3DR Satellite is Improve upon observation capabilities of its predecessors.


The Purpose of the SBUV Instrument is Determine the total amount of atmospheric ozone in a vertical column above the subsatellite point; the vertical profile of ozone above the ozone maximum; measurements of ultraviolet solar spectral irradiance and its temporal variability over the 160 - 400.


The Measurement Calibration Technique of the SAM-II Instrument is Langley technique.


The Microcontroller Speed of the CDHS Command and Data Handling Subsystem is 16 MIPS when run at 32 MHz.


The Launch Date of the GF-3 Satellite Satellite is 9 August 2016.


The Function of the Light Sensor Sensor is Confirm when the optical beacon is impinging on the satellite.


The Number of Off-Source Pointings of the Mode 1 Pointing Mode is 6.


The Mirror Material of the ALI Telescope is Silicon carbide (SiC).


The Launch Site of the SpaceX CRS-13 Mission is Cape Canaveral SLC-40.


The Number of Substorms Observed from Excellent Vantage Point of the THEMIS Constellation Satellite Constellation is 6-10.


The Profiles Per Day of the FormoSat-7 / COSMIC-2 mission Satellite Mission is 8,000 (threshold).


The Conference Presentation of the Space Test Program-1 Satellite is J. S. Wisecup, S. Stephens, "Space Test Program-1 (STP-1) - Raising the Standard," Proceedings of the 57th IAC/IAF/IAA (International Astronautical Congress), Valencia, Spain, Oct. 2-6, 2006.


The Channel Bands of the AMSU Microwave Radiometer is 50 to 60 GHz, 183.3 GHz.


The Location of the RF Ground Station Ground Station is Shinshu University in Nagano.


The Digital Data Handling Subsystem Mass of the SIR-C Phased Array is 145 kg.


The URL of the Europa Clipper Spacecraft is https://europa.nasa.gov/spacecraft/instruments/eis/.


The Reporting Frequency of the GT Fine-Pointing Error Signal Provider is 250 Hz.


The Testing Duration of the QUESS satellite Satellite is Four months.


The Support of the Test Station Testing Equipment is Ops testing and training support.


The Date of the Proximity Flyby Maneuver is June 3, 2018.


The Redundancy of the C&DH Subsystem Control System is One OBC is redundant, two TMC are redundant.


The Mass of the ZACUBE-1 CubeSat is 1.2 kg.


The Sail Deployment Time of the LightSail-2 Spacecraft is Roughly two minutes.


The Payload Volume of the STACEM Satellite is Not provided.


The Deployment Success of the DIWATA-1 Microsatellite is Yes.


The Field of View of the DarkCarb image sensor Photon Detector is Restricted.


The Publication Date of the Superconducting Submillimeter-Wave Limb-Emission Sounder Sounder is Dec. 7, 2010.


The Purpose of the SWAP and LYRA Instruments is Space Weather Observation.


The Accuracy of the Satellite Tracking Tracking System is Centimeter-scale orbital checks.


The Shareholder of the AIS Automatic Identification System is Hisdesat.


The Receiving Antenna Location of the Bukittinggi Ground Station is To cover the far Northwest of Indonesia such as the Aceh province.


The Orbit of the PhoneSat 2.5 Satellite is Low Earth Orbit.


The Altitude of the Meteosat-7 Satellite is 35,786 km.


The Spectral range of the TOU Total Ozone Unit is 308-361 nm.


The Purpose of the NAVISP Project is Strengthening European competitiveness in the navigation arena.


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


The Size of the DSN Antennas Ground Antennas is 34 m.


The Orbit Delivery of the Aeolus Spacecraft is 55 minutes later.


The Function of the Calibration Mirror TIR Subsystem Component is Block the cold space aperture during Earth view.


The Antenna Size of the Ground Station Ground Station is 3.7 m.


The Orbit Type of the Beijing-1 Satellite is Sun-synchronous circular orbit.


The Measurement Performances of the Star Tracker Attitude Determination Device is Better measurement performances than the current baseline Myriade's Star Tracker.


The Sample Collection Goal of the Chang'e-5 Moon Surface Sampling Probe is Around two kilograms of lunar samples.


The Power Consumption of the OTU Optical Telescope Unit is 15 W.


The Landing Speed of the OMOTENASHI Satellite is Approximately 30 m/s.


The Type of the FY-1C Satellite is Feng Yun-1C.


The Solar-Spectral Scan Range of the SBUV Spectrometer is 0.16 - 0.4 µm.


The Formation Control of the TerraSAR-X Satellite is Yes.


The Number of Individual Scans of the SPICE Instrument is 25.


The Reference Vector of the Magnetometer Sensor is Truncated IGRF-11 (International Geomagnetic Reference Field-11) model of the Earth's magnetic field with 2010 coefficients.


The Microcontroller of the CDHS Command and Data Handling Subsystem is PIC24.


The URL of the COMS Satellite is http://cimss.ssec.wisc.edu/cimss25th/presentations/chung.pdf.


The Eccentricity and Argument of Perigee Adjustment Method of the SJ-9A and SJ-9B Satellites is Adjusting the speed increment (position and time) and the semi-major axis.


The Solar Array Length of the PARASOL microsatellite Satellite is 1.7 m.


The Type of the MWR Radiometer is Dicke.


The Phase B2/C/D/E1 Contract of the OPS-SAT Satellite is Kicked off in February 2015.


The Components of the Comet Celestial Body is Nucleus, coma, hydrogen envelope, dust and plasma tails.


The Mass of the Polizon Payload is 144 kg.


The Stiffness of the Antenna Communication is > 20 Hz (during launch in lateral direction).


The Mission Completion Date of the ELSA-d Satellite is 4 May 2022.


The Array Size of the B1 Band Detector is 4 x 4.


The Image Acquisition Date of the MODIS Instrument is May 16, 2022.


The CW Beacon Data Rate of the RF Communications Communication Subsystem is GMSK 9.6 kbit/s / AFSK 1.2 kbit/s.


The Annual Production of the APL’s Research and Exploratory Development Department (REDD) Department is Thousands of boards, cables and assemblies.


The Full Name of the REXIS Spectrometer is Regolith X-ray Imaging Spectrometer.


The Launch Date of the Hitomi Satellite is February 17, 2016.


The Mass of the Particle Detectors Instrument is 2.5 kg.


The Area Coverage of the RADARSAT-2 Satellite is 23% over the identified area.


The Firing Control of the Picosat Launcher Satellite Component is Ground commandable.


The Launch Date of the Satellite Spacecraft is Unspecified.


The Number of Atmosphere Passes of the OCO-3 Spectrometer is 2.


The Contact Time after Launch of the Mey-Lin (C6), Gaspard (C7), and Océane (C8) Satellites is Within 90 minutes.


The Image Type of the Long-Range Reconnaissance Imager (LORRI) Camera is Color.


The Location of the NCLE Instrument is Low Earth Orbit.


The Type of the Solar Cells Power Generation is GaInP/GaAs/Ge triple junction solar cells.


The Conference Presentation Date of the JC2SAT-FF Satellite is Aug 20-24, 2007.


The Affiliation of the MHS Instrument is EUMETSAT-funded.


The Pointing Accuracy of the SILEX Terminal is Better than 1 arc second.


The Ortho-rectification Methods of the Deimos' ground segment Ground Segment is Automatic, Human-driven.


The Redundancy of the Onboard Computer Computer is One computer is nominally off as a cold spare.


The Weight of the CubeSats Satellite is 14 kg.


The Battery Recharge Method of the Sloshsat-FLEVO Satellite is Using the solar panels.


The Joining Date of the SPOT 6 Satellite is Sept. 9, 2012.


The Downlink Chains of the ResourceSat-2 Satellite is 2.


The Attitude Sensing of the OceanSat-2 Satellite is Earth horizon sensors, digital sun sensors, triaxial magnetometers and a gyroscope-based inertial reference unit.


The RF Communications of the Spacecraft Satellite is X-band for science data acquisition.


The No of bands/channels of the SBUS Solar Backscattering UV Sounder is 12.


The Alignment Tools of the Interferometer Alignment Process is Personnel from the OPC (Optical Physics Company), custom goniometer, collimated light source.


The Maneuvering Principle of the NEA Scout Solar Sail Technology Demonstration Spacecraft is Tipping and tilting its sail to change the angle of sunlight.


The Mass at Launch of the Geo Satellite Satellite is 6 tonnes.


The Number of Consecutive Deployments of the VDES Antenna Antenna is Over 100.


The Generation of the Xilinx Zynq Ultrascale+ MPSoC ZU9EG Processor is Latest.


The Calibration Techniques of the SMOS Satellite is Initial Guess based Techniques (‘Gibbs’ approaches), the Floor Error Mask, the Pre-Distorted G-matrix and the Average Pattern Reconstruction.


The Mission Type of the SciSat-1/ACE Satellite is EO.


The Mission Objectives of the LADEE Satellite is Determine the composition of the lunar atmosphere and investigate the processes that control its distribution and variability, including sources, sinks, and surface interactions. Characterize the lunar exospheric dust environment and measure any spatial a.


The Status of the Carmen-2 Instrument is Performing well.


The Bus Manufacturer of the Restore-L Satellite is Maxar.


The Alignment of the Hexapod Mounting System is Used for aligning SAGE-III.


The HIS Calibrations Frequency of the TRUTHS Satellite is On occasions, particularly during commissioning phase.


The Publication Date of the Star-circling bubble of gas Unknown is 11 June 2018.


The Initial Rotation of the Philae Lander is Slow.


The Operating Frequency Range (TM) of the EWC31 S-band transceiver module Communication Module is 2200-2290 MHz.


The Quantity of the Flock-3p x 4 Satellite is 4.


The Solid-State Recording Capacity of the Onboard Data Handling Subsystem (OBDH) Data Handling System is 90 Gbit.


The Flood Mapping Date of the Satellites Satellites is 16 July 2021.


The Mass of the Telescope Telescope is 315 kg.


The Focal Length of the Custom design lens Lens is 155.9 mm.


The Revisit Time of the Terra Bella Satellite Constellation is Three times per day.


The Power of the XI-IV Picosatellite is Average power of 1.2 W.


The Presentation Date of the ESTCube-1 Satellite is May 30, 2012.


The Application Date of the Sentinel-5P Satellite is 19 October 2020.


The PDU of the ASCAT Scatterometer is Power Distribution Unit.


The Altitude of the BeaverCube Satellite is 410 km.


The Constellation Proposal Date of the ICEYE Satellite is September 14, 2022.


The Launch Date of the SpaceX Satellite Satellite is July 14, 2009.


The Thruster Quantity of the Eutelsat 172B Satellite is Not provided.


The Response Speed of the APD detector Experiment is High.


The Launch Vehicle of the TechEdSat Satellite is H-II Transfer Vehicle "KOUNOTORI3" (HTV3) Aboard the H-IIB Launch Vehicle No. 3.


The Conference Date of the µCAT Micro-Propulsion Solution Propulsion System is August 6-11, 2016.


The Quantization of the LICEF Receiver is 1 or 0.


The Data Rates of the Channel Communication System is Variable from 37 Mbit/s to 336 Mbit/s.


The Connection of the USRP Transceiver is Interfaced with a PC.


The GSD (Multispectral) of the GF-2 Satellite is 3.24 m.


The New Finding of the Plasma Sheet Space Phenomenon is Higher-energy O+ (1–10 keV) ions.


The Effective Baselines of the TanDEM-X Satellite is Required for DEM acquisition at different latitudes.


The Scheduled Work Resume Date of the Yutu-2 Rover is March 10.


The Orbit Repeat Time of the SeaHawk-1 CubeSat is About 18-days.


The Specific Impulse of the HET-X Hall-effect Thruster is 1300 - 2200 ISP.


The Image Source of the NOAA-20 Satellite is VIIRS.


The Redundancy of the OBC On-Board Computer is Redundant.


The Conference Date of the COSMO-SkyMed Satellite is March 17-18, 2004.


The Exploration Mission Orbit of the LRO Satellite is Quasi-circular polar orbit (50 ± 15km).


The Wavelength Range of the Band 1 Spectral Band is 365-408 nm.


The Instruments of the FedSat Satellite is Communications payload (Ka and UHF band), GPS receiver, Fluxgate magnetometer.


The Power Consumption of the Total Satellite is < 75 W.


The Spectral Range of the TrueColour Imager Optical Imager is 433 nm - 907 nm.


The Biomass Estimate Accuracy of the GEDI Lidar Instrument is Well-described uncertainty for its estimates using advanced statistical models.


The Fact Sheet URL of the XMM-Newton Satellite is http://sci.esa.int/xmm-newton/47370-fact-sheet/.


The Flight Performance of the MOPITT Instrument is Unknown.


The Communication Methods of the SSETI Express Satellite is Internet, chat sessions, e-mail, news postings, dedicated news server, Internet Relay Chats (IRCs), SSETI website.


The URL of the EUMETSAT Satellite Data Service is http://www.eumetsat.int/website/home/Data/RegionalDataServiceEARS/index.html.


The Mission End Date of the GFO Satellite is October 22, 2008.


The Solar Sail Area of the NEA Scout Spacecraft is 85 m2.


The Distance from Earth of the Vigil Spacecraft is 1.5 million km.


The Ion Velocity Components of the DIDM Instrument is Normal and perpendicular.