The FOV for VNIR-NP pushbroom scanning of the VNIR-NP Imager is 70º.


The | of the Upper Atmospheric Research Radar Facility Radar Facility is National Science Foundation Awards a Grant to SRI International for Upper Atmospheric Research Radar Facility.


The Exposure Levels of the CCD Detector Imaging Device is Six non-zero levels.


The Conference Presentation Date of the STSat-2 Satellite is Aug. 11-14, 2003.


The Mass of the Tyvak-0171 Satellite is 138 kg.


The Potential Loss Time of the NextSat Satellite is First day of the mission.


The Rotation of the Scanning Platform Platform is Continuous.


The Quantity of the CSS Solar Cells is 6.


The Docking of the Pirs ISS Module is Autonomously docked to the Zvezda service module’s nadir.


The Coded Masks Distance of the JEM-X X-Ray Monitor is 3.2 m.


The Cargo Capacity of the HTV-8 Spacecraft is Up to six tons.


The Swath Width of the SLIM6 Satellite is 600 km.


The Monitoring Frequency of the Gaia Space Astrometric Mission is About 70 times.


The Launch Time of the COPPER CubeSat Satellite is 01:15:00.


The Number of Stars with Parallax and Proper Motion of the Gaia EDR3 Satellite Data is Almost 1.5 billion.


The Intensity Variation of the STL-11000M SBIG Camera CCD Camera is Approximately 6%.


The Sensitivity of the Detector E2V CCD-22 (Frame Store) is 10 µCrab or better.


The Spectral Coverage of the AIRS Atmospheric Infrared Sounder is 0.4 - 1.0 µm for photometer (4 VNIR bands at: 0.41-0.44, 0.58-0.68, 0.71-0.92, 0.49-0..


The End of Mission of the PROBA-V Satellite is April 20, 2020.


The Mission Start Date of the Van Allen Probes Satellite is 2012.


The Operator of the Bartolomeo Platform is Airbus DS.


The Resolution Δλ (0.10º slit) of the SPIM4 Spectrometer is 2.8 nm.


The Noise Equivalent σ0 of the Instrument SAR is ≤ –27 dB.


The Close Call Classification of the Starliner Spacecraft is High-visibility close call.


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


The Temperature of the CCDs Detector is -22ºC.


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


The Real-time Downlink Speed of the RF Communications Communication System is 150 Mbit/s.


The Inclination of the SkySat-16 to -18 Satellite is ~98º.


The Purpose of the VWFC Camera is Take wide-angle ultraviolet-light photographs of vast regions of sky not observable from Earth.


The Thrust of the Thrusters Attitude Control is 10 N.


The Quantity of the IOV Units Satellite Payload is 10.


The Altitude of the AMSR-E Instrument is 705 km.


The Surface Movement Detection of the NISAR Satellite is As small as 0.4 inches (1 cm).


The Battery Type of the EPS Electrical Power Subsystem is Rechargeable lithium ion 18650.


The Period of the IRS-1B Satellite is 103.2 minutes.


The Science Team Lead of the MIRI Instrument is George Rieke with the University of Arizona.


The Instruments of the NPOESS-C1 Mission is CERES and TSIS.


The Beam Width of the RA-1 Instrument is 1.3º.


The Thrust of the Thrusters Satellite Component is ~10 µN.


The Design of the SMP Sampler Mechanism is Small projectile to be shot as soon as the tip of a cylinder-shaped horn touches the asteroid surface.


The Launch Date of the KOMPSat-5 Satellite is August 22, 2013.


The Expected Lifetime of the TSX Satellite is Several more years.


The Publication Date of the Solar XUV grazing incidence spectrograph Spectrograph is April 1977.


The Reaction Wheel Test of the SONATE CubeSat Satellite is Successful.


The Mission Cost Cap of the IMAP Interstellar Mapping and Acceleration Probe is $492 million.


The Energy Range of the FSU Solar Wind Faraday Cup is Modulator sized to withstand 8 kV.


The Inclination of the BUV Sensor is 80.1º.


The Absolute / Relative Misalignment of the Three-axis diagonal gradiometer Gradiometer is 10 -3  rad / 10 -5  rad.


The Launch Date of the FormoSat-1 Satellite is January 26, 1999.


The RFU of the ASCAT Scatterometer is Radio Frequency Unit.


The Mass of the Infinity-shaped loop Gas and Dust Formation is 30 million solar masses.


The Purpose of the AIS Automatic Identification System is Broadcasts a ship's identification, position and other maritime navigational data.


The Modularity of the BCR Battery Charge Regulator is Can be combined in parallel.


The Launch Date of the Jason-3 Satellite is March 16, 2016.


The Installation Location of the Data Storage System Satellite Component is Coudé laboratory of the OGS.


The Observation Capability of the KOMPSAT-5 Satellite is Left or right-looking.


The URL of the Sentinel-5 Satellite is http://www.space-airbusds.com/media/document/10607tl-sentinel-5-lr.pdf.


The Launch Vehicle of the OCO-2 Spacecraft is Delta-2 7320-10C.


The Function of the Node-3 Module is Provides a pressurized passageway between berthed habitable volumes.


The Resolution Δλ (0.10º slit) of the SPIM1 Spectrometer is 0.8 nm.


The Data Quality of the TriG receiver GNSS Receiver is Increased.


The Angular Speed of the Polar Scout Satellite is Higher at high elevation angles.


The Connector Type of the Satellite Satellite is 51-pin connector.


The Data Gathering Start Date of the GEDI Lidar is 1 February 2019.


The Mass of the LISS-3 Camera is 106.1 kg.


The Collision Risk CONOPS Presentation of the OneWeb Satellite Constellation is Mike Lindsay, ”OneWeb Collision Risk CONOPS,” SSA Operators' Workshop, Denver, Colorado, Nov. 3-5, 2016.


The Function of the DPE Data Processor Element is Ingests mission data, ancillary data, and auxiliary data to produce NPOESS data products.


The Purpose of the Orion spacecraft Spacecraft is Return astronauts to the Moon and eventually take the first humans to Mars.


The | of the COTS EEE components Radiation Test is Application specific radiation tests for COTS EEE components.


The Expected GRB Detections per Year of the GMOD Detector is Approximately 20.


The Launch Date of the ALOS-3 Satellite is 7 March 2023.


The Principal Investigator of the Heat Probe Instrument is Tilman Spohn.


The Landing Site of the Rosetta Spacecraft is Comet 67P/Churyumov–Gerasimenko.


The Weight of the SPOT-2 Satellite is 1800 kg.


The Star Formation Rate of the M83 Galaxy is A handful of new stars being born every year.


The Imaging Capability of the Terra Bella Satellite Constellation is Sub-meter color imagery and up to 90-second clips of HD video with 30 frames/s.


The Ground Segment Software of the GeoSat-2 Satellite is gs4EO.


The Quantity of Telescopes of the Imaging X-ray Polarimetry Explorer (IXPE) Space Telescope is 3.


The Conference Presentation Date of the UK Disaster Monitoring Constellation Satellite Satellite is September 2002.


The Quantity of the Virtex-4 FPGA Data Processing Unit is 2.


The Star Formation of the The Horse and the Dragon Pair of distinct massive galaxies is Teeming with star formation, 10 to 100 times more massive than most galaxies at the same epoch.


The Mean Sea Level Rise Measurement of the Jason-3 Satellite is About 3mm per year.


The Date of the OneWeb Partnership is 2 November 2021.


The Data Retrieval Time of the DMSP and POES systems Data Retrieval Systems is About two hours.


The Technology of the SHIMMER Spectroscopy Instrument is SHS (Spatial Heterodyne Spectroscopy).


The Microcontroller of the SCARAB 1U CubeSat bus is PIC24-based CubeSat Kit.


The Command and Data Path of the Iridium NEXT Satellite is MPLS cloud.


The Maximal Power Consumption of the PPU System is 22 W.


The Spectral Band of the Instrument Spectrometer is SWIR.


The Design Basis of the NRD Navigation Radar Detector is Experimental terrestrial navigation radar detector systems developed by FFI.


The Structure Material of the IRS-1A Satellite is Aluminum/aluminum honeycomb.


The International Astronautical Congress Date of the BepiColombo Mercury Probe is Sept. 29-Oct. 3, 2014.


The Undock Date of the H-II Transfer Vehicle "KOUNOTORI3" (HTV3) Cargo Craft is Sept. 17, 2012.


The Global Coverage Time of the MSR Radiometer is 5 days.


The Propellant of the HEMPT Thruster Assembly Electric Propulsion Thruster is Xenon.


The Uplink Verification Method of the Ground System Satellite Ground System is Transmitting signals in a safe direction while verifying their emissions from the antenna with an on-site technician and a hand-held spectrum analyzer.


The Mass of the RMU Radiometer Microwave Unit is 1.6 kg.


The Launch Date of the HYLAS-2 Communication Satellite is August 2, 2012.


The Position Accuracy (RMS orbit) of the S-1 NRT Product is < 10 cm (2D).


The Requirement of the RCM Satellite is High-volume automated information processing capacity at the users’ premises.


The Number of Satellites of the First Batch of Satellites Satellite is 1600.


The FOV of the MSU-E Multispectral Scanner is 2.5º.


The Number of Spectral Bands of the Instrument Hyperspectral Imager is Up to 200.


The Light Levels of the Rosetta Spacecraft is 4% of those on Earth.


The Quantity of the Star Trackers Attitude Sensing is 2.


The Testing Environments of the Bricks Building Material is Microgravity, 1 g, less than 1 g.


The Autonomous Functionality of the INTEGRAL Satellite is Yes.


The Safe Mode Entry Date of the Chandra Satellite is 12 October 2018.


The Release Date of the Zaatari Refugee Camp, Jordan Location is May 23, 2014.


The Application of the Mie Scattering Theory Theory is Estimation of specific attenuation and radar reflectivity for Ku-band.


The Launch Date of the Hinode Satellite is Sept. 23, 2006.


The Controller Type of the Knudsen Station Ground Station is Green Heron RT-21 Az-El controller.


The IFOV of the SiPD Detector is 0.45 - 0.52 µrad.


The Dynamic Range of the NewMag Magnetometer is ±65536 nT.


The Inclination of the LAGEOS Satellite is 109.84º.


The Data Frequency of the FGS Sensor is 1 Hz.


The Mass of the Dove Satellites CubeSats is 4.7 kg each.


The Field of View Map of the EPI-Lo Instrument is Unknown.


The Date of the Bistatic Radar Experiment Experiment is April 9-10, 1994.


The Launch Year of the HJ-1C Satellite is 2012.


The Operation Status of the China's Lunar Lander Lander is Spotted.


The Downlink Data Rate of the X-band phased array antenna Antenna is 105 Mbit/s.


The Number of Exposures of the Exposures Data Collection is 3.


The Jitter Values of the ASTERIA Satellite is 1σ ~5".


The Grating Type of the Offner-type spectrometer Spectrometer is Mechanically ruled.


The Period of Orbit of the ICIR Radiometer is Approximately 1.55 hours.


The Function of the MOT Communication System is Communicates with spacecraft engineers to assist in SOH (State-of-Health) matters, such as anomaly resolution, and reports of the condition of the spacecraft and receives in return any constraints or tasking that may be required.


The Calibration Methods of the Pleiades Program Satellite Program is Unknown.


The S-band 1Mbit/s Downlink Data Rate Range of the UoSAT-12 Satellite is 1 Mbit/s - 64 kbit/s.


The Industrial grade embedded computers of the Frame Grabber Type is Industrial grade embedded computers were selected for this application.


The Propulsion System of the TanDEM-X Satellite is Cold gas propulsion system.


The Test Duration of the D-Orbit Company is Four months.


The Mass of the FSS Instrument is 87.5 g.


The Operations Start of the Galileo Second Generation (G2) Satellite Constellation is Later in this decade.


The Views of the Calibration Mirror TIR Subsystem Component is Cold space, "warm" blackbody.


The Solar Cells Type of the Power Subsystem Satellite is Triple-junction.


The Power, Thermal, Propulsion, Mechanisms of the Bus Satellite Bus is Nominal.


The Lifespan of the Sentinel-2 Satellite is 7 years.


The Impulse Density of the Thruster Propulsion System is High.


The Spatial Resolution (Band 1) of the PanMUX Instrument is 5 m.


The Satellite Network Provider of the Kongsberg Satellite Services Company is True.


The Models of the FengYun LEO satellites Satellite is FY-3A/B, FY-3C/D/E/F.


The Mission Duration of the WIND Satellite is Almost two complete solar cycles.


The Density of the Proton Component Measurement Accuracy of the DSCOVR Satellite is 20%.


The Estimated Mass of the Subarray Array is 80 gram.


The Mass of the COPPER CubeSat is 1.3 kg.


The Checksum Size of the Processed Science Data Packet Data Packet is 1 byte.


The Exceeded Design Life of the Aqua Satellite is Yes.


The Orbit Position of the BeiDou-1A Satellite is GEO, 140º E.


The Launch Date of the SuperView-1 Observation Satellites is 9 Jan. 2018.


The Launch Date of the IDEA-OSG 1 Microsatellite is 28 Nov. 2017.


The Development Date of the Embedded Systems Satellite Component is 2010.


The Orbital Slot of the GSAT-0205 Satellite is A08.


The Field of View of the FGS Fine Guidance System is ±3 arcmin.


The Pulse Length of the Radar Instrument is 15 µs.


The Line-of-Sight Distance to Mars of the ExoMars TGO Trace Gas Orbiter is 41 million km.


The Structure of the CXBN-2 Spacecraft is Robust 2-wall structure matched to a central mounting block.


The Interconnection of the Heinrich Hertz Satellite Technology is Direct single-hop.


The Location of the Cendrillon Crater is Eastern Hemisphere near the meridian.


The Launch Date of the OFEQ-3 Satellite is April 15, 1995.


The Unknown of the PROBA-2 Satellite is Unknown.


The Conference Presentation of the TacSat-4 Satellite is Space, Propulsion and Energy Sciences International Forum (SPESIF 2009).


The Average Daily Observations of the SBSS Satellite System is 15,000.


The Model of the UVIT Telescope Assembly is Engineering model.


The Repeatability of the MWI Instrument Scan Mechanism Assembly is Unknown.


The Scientific Instruments of the Trace Gas Orbiter Satellite is High-resolution color imaging system, High-resolution neutron detector, Two spectrometer suites.


The Storm System Analysis Date of the NASA Organization is March 7, 2016.


The Propellant Consumption Rate of the XMM-Newton Satellite is Approximately 6 kg per year.


The Mission Status of the Myriade/AstroSat-100 Satellite is Operational (extended).


The Activation of the He-repressurization system Propulsion Subsystem is Shortly after the LOI maneuver is completed.


The Number of Spare Satellites of the Galileo Constellation Satellite Constellation is 6.


The Red Giant Oscillations of the HD 181068 Star System is Not detected.


The Orbit Control and Maintenance of the Spacecraft Satellite is TCS (Thermal Control Subsystem).


The Central Wavelength of the Current GOES imager Sensor is 6.95.


The Measurement of the Ka-band ground station Ground Station is High data rate by SNR (Signal-to-Noise) measurement.


The Radar Reflector Antenna Diameter of the NISAR Satellite is 40 feet (12 meters).


The Size of the Spacecraft Satellite is 2.6 m x 1.8 m x 2.8 m.


The Diameter of the [65803] Didymos Asteroid is ~160 m.


The Containment of the Calf Canyon-Hermits Peak fire Fire is 29 percent.


The Project Management of the TRISHNA Satellite is Joint Indian-French project team.


The Experimental Area of the ARC Calibration System is Can be changed.


The Launch Date of the H-IIB Launch Vehicle No. 3 Launch Vehicle is July 21, 2012.


The Date of the OA-7 Space Station Cargo Resupply Mission is April 18, 2017.


The Function of the µC Control Unit is Regulates the direct current power supply of the pump.


The Magnetic Footprint Displacement of the MGF Instrument is Up to 5 km for every 100 km of altitude.


The Calibration Cycle of the LISS-3 camera Camera is 2048 scan lines.


The Temperature Stability of the Filter Wheel Optics Subsystem is ±1 K.


The Flux of the Small Near-Earth Objects Space Debris is Unknown.


The Operation of the Automated Beacon Network Anomaly Detection System is Forwards the message to a central monitoring workstation.


The Composition of the Cloud of gas and dust Protoplanetary Nebula is Mostly hydrogen and helium, with a small amount of heavier elements such as carbon, nitrogen, oxygen and iron.


The Perigee Altitude of the Satellite Orbit Orbit is Above 7.3 RE.


The Operator of the TIMED Satellite is Johns Hopkins University Applied Physics Laboratory (JHU/APL).


The Processor of the Spacecraft Satellite is Mongoose V processor.


The Power Consumption of the MWR Dicke Radiometer is 96 W.


The Image Acquisition of the ALOS-3 Satellite is Satellite body-pointing.


The Data of the Aeolus Satellite is Profiles of Earth's wind on a global scale.


The Antenna Type of the AISSat-1 Satellite is VHF monopole payload antenna.


The Bandwidth of the Satellite Device Unknown is 1500 MHz.


The Application of the OLCI Instrument is Supporting global land and ocean monitoring services.


The Organizational Interfaces of the MSX Flight Operations Team Team is Figure 38.


The Function of the MASCOT Science Landing Package is Augment the science capabilities of the Hayabusa-2 mission.


The Main Node Location of the Ground System Ground System is IKI of Moscow.


The Orbit Analysis and Control of the Sentinel-1 Satellite is Unknown.


The Number of BW Photographs of the Metric Camera Camera is 473.


The Response Time of the XMM-Newton Observatory is A few hours later.


The Orbit Inclination of the IRIS Spacecraft is 97.9º.


The Central Output Angle of the Short Wavelength Band Spectrometer is -5.28º.


The Global Average Detection Rate of the Complex Receiver AIS Receiver is 6 Messages/s.


The Period of the COMPASS-2 Satellite is 93.5 minutes.


The Differential Velocity of the LARES Satellite is 0.75 ± 20% m/s.


The AC Current of the FSU Faraday Cup Sensor Unit is Produced on the collector plates.


The Spectral range of the IRAS Infrared Atmospheric Sounder is 0.69-15.5 µm.


The Partners of the Jason-2 Satellite is NASA, CNES, NOAA, EUMETSAT.


The Inclination of the NigeriaSat-2 Satellite is 98.24º.


The Electron Energy Range of the REPT Instrument is 1.6 to 18.9 MeV.


The LTAN of the GCOM-W1 Satellite is 13:30 hours.


The Dynamic Range of the Instrument Spectrometer is Saturated at ≥70% albedo.


The Mission Control Center Location of the Odin Satellite is Solna, Sweden.


The Image Capture Date of the NigeriaSat-2 Satellite is 8 days after launch.


The Horizontal Baseline of the TanDEM-X Satellite is 200 m to 3000 m.


The Deployment Date of the SOAR Satellite is 14 June 2021.


The NRT Data Freshness of the Sentinel-6 Satellite is Not older than 3 hours.


The Managed By of the TEMPEST-D Satellite is NASA/JPL.


The Prediction of the Magnetic Field Models Geophysical Models is Pole will continue to drift towards Siberia.


The Number of Cicero Satellites of the GeoOptics Satellite Manufacturer is At least two.


The Number of Satellites of the HY-2 Satellite is 8.


The Power On of the Smartphone Device is 45 minutes after deployment.


The INR Performance of the GOES-N spacecraft Satellite is Improved.


The Function of the LRA Instrument is Acts as a reference target for laser tracking measurements.


The Number of Payloads of the Spaceflight SSO-A: SmallSat Express Satellite is 64.


The Hardware Platforms of the Open5GCore Rel. 4 5G Core Network is Common hardware platforms.


The Design and Build Contributors of the SAPPHIRE Satellite is Students at Stanford University.


The Launch Status of the Al Amal Mars Probe is Launched.


The Readings of the Magnetometer Sensor is Unknown.


The Speed of the Rosetta Spacecraft is 31 000 km/h.


The Commercial Availability of the Iridium Certus Satellite Communication Service is Mid-2018.


The Observation Capabilities of the Herschel Space Observatory is Far-infrared imaging.


The Time to Reach Temperature of the PICNIC IR detector Detector is About nine hours.


The Sensitivity of the Phoenix receiver Navigation Device is High levels of radiations.


The Thrust of the ADCS Thrusters Attitude Determination and Control Subsystem is 150 N.


The L1B, L1C and L2A Product Destination of the EnMAP Satellite is Temporary storage on the pick-up points for delivery.


The Range of the MAG Magnetometer is -350 nT to +350 nT.


The Deployment Phases of the VDES Antenna Antenna is Two phases of approximately two seconds and 30 seconds duration.


The Vertical Resolution (PBL) of the Aeolus Satellite is 0.5 km.


The Protocol of the IXV Communications Network Network is IP.


The J2000 declination (deg) of the B0531+21 (Crab) Pulsar is 22.01449.


The Camera Installation Date of the OPTSAT 3000 Satellite is Dec. 6, 2012.


The Measurement Locations per Day of the OCO-3 Instrument is Up to 40.


The Article Date of the CXO Satellite is 14 February 2019.


The Affected Activities of the CPOM Data Processing Center is Shipping, tourism, Arctic exploration, search and rescue.


The CCD Pixel Format of the HIRES Instrument is 384 x 288.


The Inclination of the GRACE Satellite Satellite is 89º.


The Band Spacing of the SWIR Detector is 11.4 nm.


The Design Lifetime of the QuakeSat Satellite is One year.


The Operation with MUIR radar of the Receiver Device is Yes.


The Manufacturer of the AATSR Instrument is Astrium Ltd., UK.


The Partner Organizations of the OPS-SAT Satellite is BST (Berlin Space Technologies) and MEW Aerospace (Germany), GOMSPACE (Denmark) as well as MAGNA STEYR Engineering and Unitel (Austria).


The Benefits Categories of the Landsat 7 Satellite is Technical, Scientific, Programmatic, Organizational.


The Fringe Distortions of the SHS Interferometer is Degrade the instrumental profile and reduce the signal-to-noise ratio.


The Filter Wheel Filters of the GOES Sounder Radiometer is 18.


The Solar cells of the EPS Electric Power Subsystem is 20 x Triple Junction GaAs.


The Publication Date of the GNSS in Space Satellite is Nov/Dec. 2008.


The Chair of the George Hurtt Individual is True.


The Mission Service of the Bartolomeo External Payload Hosting Facility is Fast, cost-efficient and reliable access to low Earth orbit.


The Mission Objectives of the FSSCat Satellite is Polar Ice and Snow monitoring, soil moisture monitoring, terrain classification and terrain change detection.


The Geo-location Accuracy of the SEOSat Satellite is 20 m.


The Satellite Development Locations of the MetOp-SG Satellite Program is Toulouse, France and Friedrichshafen, Germany.


The Cost of the Dellingr Nanosatellite is Fraction of the cost of more traditional satellite missions.


The Launch Date of the OFEQ-2 Satellite is April 1990.


The Mass (kg) of the RADARSAT-1 Satellite is 2200.


The Orbit Inclination of the ALOS-3 Satellite is 97.9°.


The Measurement Proxy of the ClO Chemical Compound is Dynamical effects on the high-latitude upper stratosphere.


The Operation Mode of the Radar Instrument is Standby.


The Structure Dimensions (Deployed) of the FY-3 series spacecraft Satellite is 4.4 m x 10 m x 3.8 m.


The Deployed Configuration Size of the KaRIN Instrument is 5.0 m x 10.6 m x 1.5 m.


The Aperture Diameter of the Lenses Optical System is 26 cm.


The Wavelength Range of the RAVAN Radiometer is UV (200 nm) to far infrared (200 µm).


The Configuration of the RISESat Satellite is Launch and deployed.


The Inventor of the Electron Temperature Probe Instrument is K. Hirao.


The Measurement of the Swarm Satellites Satellite is Earth's magnetic field strength and direction.


The Launch Date of the R3 CubeSat Satellite is December 16th, 2018.


The Dimensions of the COVE Board Data Transfer Device is 90 mm x 90 mm.


The Detection Area of the SXD Detector is 1 cm2.


The Launch Date of the Stingray satellite Satellite is January 2024.


The Service Emphasis of the Lacuna Space Satellite Company is Lowest price.


The Observation Data Acquisition Date of the SHIKISAI Satellite is Jan. 12, 2018.


The Band 1 of the RBV Instrument Spectral Band is 0.48 - 0.58 µm.


The Unexpected Observation Date of the Integral Satellite is 10 November 2015.


The Subsystem Selection Aspects of the MERLIN Satellite is Power consumption, mass and volume allocations, thermal behaviour, radiation hardness.


The Mass of the AprizeSat-10 Nanosatellite is 12 kg.


The Observation Capability of the MTEL Space Telescope Telescope is Space-time development of TLEs.


The Workshop Date of the Megha-Tropiques Satellite is October 7-10, 2014.


The Publication Date of the The Space Mission at Kwajalein Space Mission is 2012.


The Booked for Launch Date of the SpIRIT Satellite is Early 2023.


The LTDN of the NEMO-AM Satellite is 9:30 hours.


The Swath of the TES Spectrometer is 5.3 km x 8.5 km.


The Operation Modes of the CCD Detector Imaging System is TDI.


The Performance of the SAR Mode Synthetic Aperture Radar Mode is Excellent.


The Spectral Coverage of the Atmospheric Chemistry Suite Spectrometer is From 0.7 to 17 micrometers.


The Snapshot Frequency of the TESS Satellite is Every two minutes.


The Thruster Type of the Propulsion Subsystem Propulsion is Water micro-resistojet.


The Spatial Resolution of the Multispectral Instrument (MSI) Instrument is 60 m.


The Transport Destination of the Yuanwang-21 and -22 Cargo Ships is Qinglan, Hainan island.


The Mass of the LAGEOS Satellite is 411 kg.


The Lives Saved Annually of the Galileo Satellite Constellation is More than 2000.


The Satellite Ocean-Color Data Record of the NASA Organization is Data.


The Stations of the Ground Network Network is Aussaguel (France), Fairbanks (AK, Poker Flats location), Wallops Island, VA, and Hartebeesthoek, South Africa.


The Data Generation of the MicroCarb Satellite is 500 Gbit/day.


The Antennas of the Starlink Satellite Satellite is Multiple high-throughput.


The Timing Precision of the NICER X-ray Instrument is Few µs.


The Development to Commercialization Date of the AIS Technology is Nov. 19, 2010.


The Sample Collection Date of the Hayabusa-2 Spacecraft is February 21, 2019.


The Number of Satellites of the Starlink Group 4-14 Satellite Group is 53.


The Design of the Telescope Optical Instrument is Compact, folded optical path, no optical obstruction.


The Spatial Resolution of the OLCI Spectral Imaging Instrument is 300 m.


The Launch Date of the SVOM Satellite is Scheduled for Mid-2023.


The Battery Capacity of the BRITE spacecraft Satellite is 5.3 Ah.


The Data Rate (Uplink) of the S-band telemetry system Telemetry System is 256 kbit/s.


The Ownership Stake in OneWeb of the Eutelsat Satellite Operator is 17.6%.


The Size of the Spacecraft Satellite is 320 mm x 340 mm x 362 mm.


The Status Report Date of the OSIRIS-REx Mission is Sept. 15, 2016.


The Cion Power of the CICERO-6 6U CubeSat is 8 W.


The Science Requirements Document Date of the SWOT Satellite is March 19, 2009.


The Orbit Altitude of the AERO-VISTA mission Satellite Mission is Approximately 450 - 600 km.


The Battery Type of the EPS Electrical Power Subsystem is Li-ion.


The Ground Range x Product Length of the High Resolution Spotlight Imaging Mode is 10 x 5 km.


The Anomaly Duration of the ASTRO Satellite is 22 hours.


The Manufacturer of the AMBER IOD-3 CubeSat is Horizon Space Technologies (UK).


The Data Destination of the EMIT Satellite is NASA Land Processes Distributed Active Archive Center (DAAC).


The IFOV/line (pixels/scan line) of the MERSI Medium Resolution Spectral Imager is 2048/8192.


The Enclosure Shape of the CanX-7 Satellite is Circular.


The Launch Date of the ETS-VIII Spacecraft is Dec. 18, 2006.


The CCD Detector Array of the PAN Camera Imaging Device is 12,288 pixels.


The Ground Swath of the ALI Telescope is 185 km.


The Encounter of the Solar Orbiter Satellite is First time that we have encountered a comet tail inside Earth's orbit.


The Ground Sample Distance of the Resurs-P1 Imaging Satellite is 1 m.


The Oscillation Frequencies of the GOLF Instrument is Between 10-7 and 6 x 10-2 Hz.


The Transmit and Receive Frequencies Offset of the Satellite Communication Device is 0.5 MHz in the 24 GHz channel, and by 0.67 MHz in the 32 GHz channel.


The Payloads of the SLS Rocket is 13 CubeSats/Nanosatellites.


The Range of the Ozone Measurement Instrument Atmospheric Measurement Device is 0.1 - 15 ppmv.


The Cell Type of the AzurSpace 3G30 Triple Junction GaAs/Ge cells Solar Cell is AzurSpace 3G30 Triple Junction GaAs/Ge cells.


The Sensitivity of the Channel 8 Sensor is 0.4 K/pixel.


The Deployment Timeline of the NRCSD Payload is 1 month after berthing.


The Support of the Test Station Testing Equipment is Rapid AI&T (Assembly, Integration, and Test).


The Provider of the MAG Instrument is SwRI (Southwest Research Institute) and the University of New Hampshire in cooperation with the Austrian Academy of Sciences.


The Spin Rate Change of the Satellite Spacecraft is Large, easily detectable change in the spin rate after a few hours or less.


The Parachute of the Schiaparelli Module is Disk-Gap-Band canopy, 12 m diameter.


The Data Release of the TESS Satellite is Sectors 1 and 2, observed between July 25 and September 20, 2018.


The Mass of the SFINKS Solar Cell Array is 30 grams.


The Band of the LICEF Receiver is L-band.


The S/C Bus of the IRS-1C and IRS-1D Spacecraft is Central cylinder (930 mm diameter x 1123 mm).


The Power Source of the Integrated Firing Test Test is Battery.


The Manufacturer of the Scanning Shack Hartmann Sensor Wavefront Measurement Device is AMO WaveFront Sciences, LLC.


The Bus Design of the QuickBird-2 Satellite is BCP 2000 (Ball Commercial Platform 2000).


The Sky Coverage of the INTEGRAL Satellite is Almost full-sky coverage for brief events.


The Detection Date of the GRB 031203 Gamma-Ray Burst is 3 December 2003.


The Quantity of the Fluxgate Sensors Sensor is 3 orthogonal sensors per unit.


The Purpose of the Copernicus Sentinel-6 Michael Freilich Satellite is Provide accurate measurements of sea-level change.


The Manufacturer of the SCD-2 Satellite is INPE/Brazil.


The Function of the European Mission Tasking Center Center is Receives observation requests and incorporates them into its tasking/planning cycle.


The Sensor Quantity of the MAG Magnetometer is 2.


The Detector Area of Interest of the BEO Back-End Optics is 200 x 200 pixels.


The Instrument Type of the ICEYE-X2 Satellite is SAR (Synthetic Aperture Radar).


The Arrival Location of the STPSat-3 Satellite is Wallops Flight Facility in Virginia.


The Number of Missions of the MISSE Experiment is Nine.


The FOV of the X-ray Imager Instrument is 4.6º x 4.6º.


The Focal Length of the LISS-IIM Instrument is 324.4 mm.


The Dynamic Range of the Iris Video Camera Camera is 16 bit.


The Ground Stations of the LAPAN-TUBSAT Satellite is Biak (Papua, east of Indonesia) and Rumpin (near Jakarta, Indonesia).


The Redundancy Support of the DPU Data Processing Unit is Full duplication of DPU hardware.


The Flight Operations Location of the Chandra X-ray Center Center is Burlington, Massachusetts.


The Unknown of the Spot-1/5 –Spot-6 Satellite Constellation is Unknown.


The Integral non-linearity of the PHA Detector is <0.05% of full scale.


The Autonomy of the RapidScat Scatterometer Instrument is Autonomous.


The Spectral Range of the Spectrally modified current sounder Sensor is 8.3-8.7.


The Altitude at Final Breakup of the S/C Satellite is Little more than 100 km.


The Number of Wire Boom Deploys of the THEMIS Constellation Satellite Constellation is 20.


The Agency of the TechEdSat Satellite is JAXA, NASA, ARC.


The Interface Standard of the GSCG Ground Station Control System is CCSDS SLE.


The Speed of the PhiSat-1 Satellite is Over 17,000 mph (27,500 km/h).


The Downlink Data Rate of the Satellite Satellite is 115.2 kbit/s.


The Monitoring Program of the MicroCarb Satellite is CNES / MicroCarb Atmospheric CO2 Monitoring Program.


The Effect of the Sea Surface Natural Feature is Mimics the ocean floor.


The Operation of the DSA Device is Not designed to support its own weight in the one-g environment at Earth's surface.


The Revenue Projection of the Satellogic Satellite Imaging Company is $7 million in 2021 to $787 million in 2025.


The L1 Detectors Active Area of the HIT Sensor is 2 cm2.


The Collaboration of the Hinode, IRIS and SOHO Solar Missions is Provide a suite of complementary instruments to study our Sun.


The Platform Shape of the Spacelab Pallet Equipment is Open, U-shaped.


The Product Levels of the Sentinel-3 Ocean Surface Topography Mission is Level 1, Level 2.


The Upgrades of the NIRSpec Instrument is New detectors and microshutters.


The PRF of the SAR Radar is About 18 kHz.


The No of Passbands of the Channel 6 Sensor is 1.


The Data Collection Purpose of the ATOVS Advanced TIROS Operational Vertical Sounders is Support regional NWP over Europe.


The Resolution of the Planet SkySats Satellite is 50-centimeter-per-pixel.


The Peak strength of the EEJ (Equatorial Electrojet) Phenomenon is ~80 nT at 12:00 hours LT (Local Time).


The Field of View of the OMPS Nadir Sensor Spectrometer is 110°.


The First Actuation Pressure of the T3µPS Pressure Sensor is 711 mbar.


The Types of the Satlet Satellite Subsystem is Single-function satlets, System satlets.


The Planned Connection of the Ground Communication Links Communication System is Between ISTRAC and MOSDAC.


The Frequency Band of the ELFIN-A Satellite is 435-438 MHz.


The Type of the Hiber-3 Satellite is 3U CubeSat.


The Calibration Date of the NOAA-11 Satellite is 1989 to 1993.


The Launch Date of the Crew-4 Spacecraft is Spring of 2022.


The Power Consumption of the STOs and STAEs Analog Electronic units is 150.4 W (for 3 STO configuration).


The Mass of the Biopan Payload is 27 kg.


The Optical Pulse Spectral Range of the LI Instrument is 777.4 ± 0.17 nm.


The Propulsion System of the CASSIOPE mission Satellite Mission is None.


The Orbit Prediction Accuracy of the Picosatellite Satellite is Meter Level.


The Number of Sensors of the SEIS Seismometer is Six.


The Attitude Accuracy of the Procyon Star Tracker is 5 arcsec on X/Y and 50 arcsec on Z.


The Pulse period (ms) of the J1846-0258 Pulsar is 325.684.


The Investigation Duration of the SpaceX Falcon-9 Rocket is Over the past four months.


The Mass of the SPROUT Nanosatellite is ~7 kg.


The Orbital Path of the Juno spacecraft Spacecraft is Over Jupiter's poles.


The Data Processing Unit of the PLASTIC Solar Wind Ion Instrument is IMPACT IDPU.


The LTAN of the Satellite Orbit Orbit is 6:00/18 hours.


The Mass of the AU Mic b Planet is Less than 58 times Earth's mass.


The DEM Resolution of the SRTM Satellite is 30 m.


The Spectral Bands of the NEMO-HD Satellite is 450-520 nm, 520-600 nm, 630-690 nm, and 760-900 nm.


The Mission Type of the Moon Impact Probe Probe is Surface Impact.


The Mass of the Instrument Telescope is 967 kg.


The Filter Thickness of the FUV channel Spectrometer is 2.50 mm.


The Potential Use of the Space Moss Moss is Space and future bases on the Moon or Mars.


The Coverage of the Payload Satellite Component is Eight spot beams.


The Mission Operations Blocks of the HyperScout® Satellite is Radiometric Calibration, Line of Sight Model Correction and Instrument Functionality Testing; Intensive Observations L2 Data Validation; On Board Processing Experiments.


The Launch Date of the COPPER CubeSat Satellite is Nov. 20, 2013.


The Control Method of the Barber Pole Friction Device is Tether deployment.


The Changes of the iMESA-R Flights Technology is New electrostatic analyzer (ESA) design, Improved temperature measurements, Reduces number of plates, Switchable range on ESA, Programmable gain amplifier, Higher transimpedance amplifier gain, New power supply design, Added dosimeter, Rewritten software.


The Apogee Alignment of the MMS and THEMIS Satellites is Roughly 90º.


The Application of the Generic Radio-Frequency Subsystem Subsystem is High-Altitude Formation-Flying Missions.


The Downlink Speed of the COSMO-SkyMed-1 Satellite is 300 Mbit/s.


The Orbit Type of the Satellite HY-1B is Sun-synchronous near-circular orbit.


The Presentation Date of the RazakSAT Satellite is Nov. 7-11, 2005.


The Total Ionized Dose Radiation of the TacSat-4 Satellite is 100 MRad.


The Climate Patterns of the XO-3b Exoplanet is Map provided by Spitzer data.


The Type of the Earth sensor Sensor is CMOS camera with a fisheye lens and an image sensor of 1.3 Mpixel.


The Operation Status of the TSX (TerraSAR-X) Satellite is Nominal.


The Measurement of the Sea and Land Surface Temperature Radiometer Instrument is Real amount of energy radiating from Earth.


The Consumable Supply Life of the SA-200HP Spacecraft Platform is 10 years.


The Longitudinal Dimension of the HXT-C X-ray Optics is 1400 mm.


The Revisit Time for Ocean Color Scanner of the Satellite HY-1B is Every day.


The Form Factor of the TechEdSat Satellite is 1U CubeSat.


The Components of the Automatic target pointing mode Observation Mode is Star sensor assembly, GPS receiver, attitude control actuator.


The Contract Amount of the HawkEye 360 Company is $15.5 million.


The Data Quantization of the MSU-100 Camera is 8 bit.


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


The URL of the RHESSI Satellite is http://berkeley.edu/news/media/releases/2005/02/18_magnetar.shtml.


The Body Size of the NorSat-2 Satellite is Smaller than 62 x 62 x 73 cm.


The Gain of the Antenna ADS-B Antenna is 11.2 dBi.


The Polarization of the SAR Synthetic Aperture Radar is HH.


The Storage Memory of the Satellite Satellite is > 512 Gbit.


The Cargo Return of the Starliner Spacecraft is 600 pounds.


The Closest Separation Distance of the Cluster spacecraft Satellite is 4 km.


The Mass of the QB50P1 and QB50P2 2U CubeSats is 2 kg each.


The Previous Sea Ice Coverage Record of the Global Change Observation Mission 1st – Water “SHIZUKU” Satellite is 19.44 million km2.


The Capture Date of the WorldView-1 Satellite is 19 August 2021.


The Launch Date of the FedSat Satellite is 14 Dec 2002.


The Thermal Control Methods of the Neutron-1 Spacecraft is Passive, Conducting heat through copper strapping, Using external spacecraft surfaces as thermal radiators, Turning off subsystem hardware.


The Size of the LightSail-2 Spacecraft is Small washing machine.


The FOV in Vertical Plane of the THD Horizon Detector is 22º.


The Operator of the IceCube Radiometer is NASA and GSFC (Goddard Space Flight Centre).


The Previous Believed Speed of the Heliosphere Interstellar Medium is Faster than 52,000 miles per hour.


The Proton Energy Range of the REPT Instrument is 17 to >100 MeV.


The Formation Flight of the CanX-4 & CanX-5 Satellites is Accomplished.


The Orbit of the Prox-1 Spacecraft is Circular, 720-kilometer-high.


The Repeat Cycle of the SARAL spacecraft Satellite is 35 days.


The Size of the TechEdSat Satellite is 10 cm x 10 cm x 11.3 cm.


The Launch Date of the LRO Satellite is June 18, 2009.


The Detector Size of the Long Wavelength Band Spectrometer is 2.5 cm x 2.5 cm.


The Formation Type of the TanDEM-X Satellite is Bistatic interferometric.


The Interface of the Spacecraft Emulator Testing Equipment is MCS to OBC and back again.


The Thermal Control of the Telescope Tube Assembly Telescope is On-board heaters.


The CEO of the Maxar Space Solutions Company is Jablonsky.


The Spectral Resolution of the EPIC Cameras Imaging System is E/ΔE ~ 20-50.


The Required Contacts of the PROBA Project Satellite Project is 2 or 3 per day for S-band (U/D).


The Communication Disruption of the Hayabusa-2 Spacecraft is During solar conjunction operation.


The Function of the RISE Experiment is Uses the spacecraft's radio connection with Earth to assess perturbations of Mars' rotation axis.


The Redundancy of the CIB Control and Interface Board is Cold.


The Cadence of the Alpha-Particle Spectrum Measurement is Up to around 20 MeV /nuc.


The Data Latency of the SENSE Satellite is Operational SEM data latency requirements are satisfied.


The Data Rate of the SSDRs Solid-State Data Recorders is 20 Mbit/s.


The Catalyst for Establishing a Nanosatellite Manufacturing Sector of the MDASat-1 Satellite is Yes.


The Requirements of the LunaNet Device is No extra requirements on the hardware.


The Arrival Date at ISS of the HTV-7 Cargo Vessel is 27 September.


The Beam width of the UHF Band is 3.6 rad.


The Field of View of the OMPS Limb Profiler Spectrometer is 8.5°.


The Propellant of the Propulsion System Propulsion Subsystem is Hydrazine.


The Distance of the Cassiopeia A Supernova Remnant is 10,000 light years.


The Peak Temperature of the Orion Spacecraft is 2,200°C.


The Stereo Observations Area of the GIS Instrument Satellite Instrument is Up to 6270 km2 daily.


The Publication Date of the Dual Gimbal Antenna Antenna is January 2009.


The System Level Specifications Retained of the SCATSat-1 Satellite is OSCAT instrument.


The Applications of the Satellite STRATOS is Weather model assimilation of RO, space weather monitoring, ionosphere corrections for navigation, thermospheric density (POD).


The Solar Array of the Starlink Satellite Satellite is Single.


The Components of the Thermal Control Louvers Thermal Regulation Device is Front and back plates, flaps, springs.


The Mission Type of the Flying Laptop Satellite is EO.


The Orbit Control of the MEV-2 Satellite is Does not control the orbit.


The Orbit Reach of the Akatsuki Spacecraft is 2016.


The SAR Payload Repeat Cycle of the RCM Satellite is 12 days.


The Signal Type of the Radar Altimeters Instruments is Pulses of radio waves (microwaves).


The Diameter after Expansion of the Genesis-2 Spacecraft is 2.54 m.


The Bedrock Rise Rate of the Earth Planet is About 10 mm a year.


The Power of the ASPOC Instrument is 3.0 W.


The Attitude Control of the Payload Satellite Payload is Pointing Accuracy.


The Bit Rate of the S-band Transmitter Transmitter is Up to 1 Mbit/s.


The Smile and Keystone of the Instrument Spectrometer is ≤1 image pixel.


The Data Relay System of the Alphasat and Sentinel-1A Satellites is LCTs.


The Mission of the OSCAT-3 Radar Scatterometer is Oceansat-3.


The Foot Print of the RA-1 Instrument is 16 - 20 m.


The Rock Deposits Age of the LRO Satellite is Less than 100 million years old.


The Satellite Launch Vehicle of the Kleos S.A. Company is SpaceX Falcon 9.


The New Launch Date of the Starliner Spacecraft is Unknown.


The Power On of the Watchdog Device is Immediately after the spacecraft has been ejected from the launch vehicle.


The Mean Anomaly at Epoch of the Swarm-A (Alpha) Satellite is Δt = 2-10 s difference between A and B.


The Imaging Capability of the BILSAT-1 Satellite is Stereoscopic.


The Sample Collection Attempt Date of the OSIRIS-REx Spacecraft is Late August.


The Beam Pointing Accuracy of the MWHS-II Microwave Humidity Sounder is ≤0.1º.


The Presentation Date of the SCARLET Solar Array Solar Array is 2000.


The Live Mammals of the Dragon Spacecraft is 20 rodents.


The Manufacturer of the Sentinel-5 Satellite is Airbus DS.


The Configuration of the Spacecraft Satellite is 3U CubeSat carrying a Ka-band payload.


The Mass of the Experiment Payload is 55 kg.


The Operational Interface of the SWOT Satellite is Unique.


The Tracking Capability of the OEM628 Receiver Receiver is Up to 120 signals (60 dual frequency satellites) at any time.


The Time Synchronization Accuracy of the Data Handling Subsystem Subsystem is < 10 µs.


The Cables, Connectors Mass of the Microsatellite Satellite is 5.1 kg.


The NASA Participation of the DRACO Demonstration Rocket is Goal of using nuclear thermal propulsion for long-duration human spaceflight missions.


The Release Date of the Gaia EDR3 Satellite Data is 3 December 2020.


The Actuation of the ADCS Attitude Determination & Control Subsystem is 6 reaction wheels and 3 torque rods.


The Packet modulation of the RF communication subsystem Communication is FSK 1200 baud.


The Mission of the Neutron-1 Satellite is Study low energy neutron flux in Low Earth Orbit (LEO) as a function of time and location.


The Peak Detection Rate of the Complex Receiver AIS Receiver is 19 Messages/s.


The Launch Date of the COSMO-SkyMed Second Generation Satellite is 18 December 2019.


The On-board Computer of the Microsatellite Satellite is Not implemented.


The Launch Year of the Pléiades Neo constellation Satellite Constellation is 2020.


The Resolution of the Z-panel camera Camera is 3 Mpixel.


The Experiment Approach of the Scientific Payload Satellite Payload is Baseline is to run most of the experiments sequentially.


The Approx. peak sensitivity altitude of the Channel 7 Sensor is Unknown.


The Horizontal Cell Size of the Ozone Measurement Instrument Atmospheric Measurement Device is 250 km.


The Antenna Mounting Plane Clearance of the KySat-1 Satellite is 6.5 mm.


The Conference Location of the SWAP EUV Telescope is Toulouse, France.


The Frequency of the VHF Transmitter Radio Transmitter is 137 MHz.


The Number of Satellites of the MSG Satellite Fleet is 6.


The Target Observation Frequency of the OCO-2 Satellite is Roughly once each day.


The Algorithm Type of the Control algorithm ADCS is B-dot based algorithm.


The Purpose of the NICT's New OGS Ground Station is Satellite Laser Communication and SOTA/Socrates experiment.


The Deployment Method of the NanoRacks CubeSat Satellite is JEM airlock slide table.


The Installation Date of the Capella Company is 9 November 2021.


The Dimensions of the GOMX-1 Nanosatellite is 10 cm x 10 cm x 20 cm.


The Sale Approval of the ARTEMIS Satellite is ESA approves sale of Artemis telecom satellite to Avanti.


The Image Frequency of the Data Flow System is One image per minute.


The Mass of the FLIR Boson camera Thermal Imaging Camera is <38 g.


The Acquisition Timeline of the TanDEM-X Satellite is Not provided.


The Launch Date of the Chang'e-5 Spacecraft is 23 November 2020.


The Research Focus of the MMS Satellite is How electrons move through the magnetosphere.


The Hydrazine Fuel Mass of the MERLIN Satellite is 28 kg.


The Location of the LPVEx Field Campaign is Helsinki Testbed and the Gulf of Finland.


The Orbit Altitude of the Max Valier Satellite is 600 km.


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


The Mass of the IITMSAT Microsatellite is 11 kg.


The Power Consumption of the Passive Attitude Control System Attitude Control System is None.


The Publication Date of the Copernicus Imaging Microwave Radiometer (CIMR) Radiometer is December 2021.


The CubeSat of the Satellite SporeSat is 3U.


The Mission Budget of the Carruthers Geocorona Observatory Spacecraft is $75 million.


The Revisit Period of the CBERS-2B Satellite is 26 days.


The Velocity Resolution of the IRIS Satellite is 0.4 km/s.


The SNR of the RBV Instrument Radiometric Signal is 33 dB in bands 1 and 2, 30 dB in band 3.


The Bandwidth (GHz) of the ICI-3 Radiometer is 3.


The Acquisition of the Maxar Technologies Company is Vricon.


The Local Time of the Tandem-L Satellite is 6 h / 18 h.


The Size of the Spacecraft Satellite is 80 cm x 60 cm x 60 cm.


The Mission Start Date of the Eu:CROPIS Satellite is May 24, 2016.


The Pixel size of the Channel 6 Sensor is 32 km x 32 km.


The SNR of the Band 4 Spectral Band is 180.


The Modulation Scheme of the XMOD X-band Modulator is QPSK.


The Launch Date of the Megha Tropiques Satellite is Oct. 12, 2011.


The Location of the Precipitation Processing System Data Processing System is GSFC.


The Conference Presentation Date of the PROBA-2 Satellite is April 25-27, 2006.


The Ground-Controlled Formation Geometry of the ATI Experiments Satellite Experiment is Minimum satellite distances of 150 m in the plane perpendicular to the flight direction.


The Tracking Capability of the Hinode Satellite is Continuous tracking of sunspots with high spatial resolution for several days.


The Mass of the CMG Control Moment Gyroscope is 500 g.


The Gamma-ray Energy Range of the MGNS Neutron and Gamma-ray Spectrometer is 300 keV to 10 MeV.


The Required Reception System of the UHRIT Data Dissemination System is X-band reception system.


The Detectable Count Rates of the Gamma-ray Counter Detector is > 10 Hz.


The Size of the VisionCube-1 Satellite is 2U.


The Launch Date of the Kolibri-2000 Satellite is March 20, 2002.


The Non-Group Comet Sightings per Year of the SOHO Satellite is Over 100.


The General Manager of the GHGSat-C2 Satellite is Marc Corriveau.


The Mission Duration of the GPM Satellite is Expected to last to the mid-2030’s or beyond.


The Mass of the Sterkh-2 Microsatellite is ~ 171 kg.


The Execution Responsibility of the TDP Operations Satellite Operations is Inmarsat.


The Mass of the PicSat CubeSat is 3.5 kg.


The Altitude of Initial Orbit of the OneWeb Satellites Satellite Manufacturer is 450 kilometers.


The Predicted Reentry Date of the Chinese Rocket Stage Rocket Stage is May 8, 2021.


The Heliacal Rising Significance of the Pleiades Open Cluster is Marked the opening of seafaring and farming seasons.


The Image Segment Location of the CaSSIS Imaging System is Margin of the South PLD.


The Orbit Inclination of the HY-2A Satellite is 99.3º.


The Spatial Resolution of the Observation Instrument Telescope/Spectrograph is 0.16º (Airglow Port), 0.06º (High-spatial-resolution Port).


The Report Date of the GEOS-1 Satellite is Jan. 1977.


The Controlled Axes of the Permanent Magnets Attitude Control is Two.


The Orbit of the SEOSAT-Ingenio Satellite is Sun-synchronous circular orbit.


The Objective of the GEOSAT Radar Altimeter (GRAS) Instrument is Study the marine gravity field as accurately as possible.


The Mission Status of the SwRI Small Satellite Satellite is Forward.


The Field of View (FOV) of the Electron Spectrometer Instrument is 10º-170º with respect to the spin axis by 30º in azimuth.


The Spectral Bands of the IRS Imager is 4.


The Observing Capability of the Ground-based Telescopes Telescopes is Decreases as air mass increases at low altitudes.


The Purpose of the TeLEOS-1 Satellite is Environmental Monitoring.


The Design of the Antenna Payload is Pre-deployed and designed to survive launch conditions in any orientation.


The Ground Segment of the Himawari-8/9 Satellite is Unknown.


The Data Provided of the MetOp Satellites Satellites is ATOVS, AVHRR, ASCAT and IASI Data.


The Resilience Strategy of the Dellingr Satellite is 25-hour reset.


The Technology Readiness Levels of the KaRIn Instrument is 3 to 5.


The Conference Presentation Date of the PROBA-2 Satellite is Oct. 17-20, 2005.


The Total Student Contributors of the SAPPHIRE Satellite is More than 70 Stanford students and 30 WU students.


The Operating Voltage of the NovAtel OEMV-2 L1/L2-F GPS unit GPS Unit is 3.3 VDC.


The Mission Title of the LUMIO CubeSat is Characterizing lunar meteoroid impacts.


The CEO of the Lacuna Space Company is Rob Spurrett.


The Symposium Date of the ECOSTRESS Instrument is July 23–28, 2017.


The CCD array size of the 16 mm camera Camera is 750 x 580 pixels.


The Radius of Circular Scan of the S-192 optomechanical scanner Scanner is 42 km.


The End of Life Date of the ST5 Satellite is 30 June 2006.


The Receiver Locking Sequence of the Transponder Communication Device is Residual carrier, command subcarrier.


The Power of the Spacecraft Repeater Communication Device is 53 W.


The Crest Height of the Yellowstone River River is 13.88 feet.


The Angular Resolution of the Vector Magnetometer Instrument is 1 arcsec.


The Spectral Resolution of the HySI Hyperspectral Imager is ≤ 15 nm.


The Multiplexed Subchannels of the Optical Downlink Communication System is Up to 16.


The Data Rates (TC) of the EWC31 S-band transceiver module Communication Module is 8 kbit/s to 256 kbit/s.


The Altitude of the DMC-3 Constellation Satellite Constellation is 651 km.


The Purpose of the NEMO Bus Nanosatellite is Earth Monitoring and Observation.


The Data Measurement of the Sentinel-6 Satellite is Ocean Heat, Movement, Sea Level.


The Agency of the Arachne Satellite is USAF.


The Latency Requirement of the S-2 NRT Product is Restituted 90 minutes before Sentinel-2 A/B ANX is crossed.


The Support Phase Time Period of the Mango Tango Satellite Formation is 02.07 to 02.08.2010.


The Distance from Earth of the MarCO CubeSat is 1 million kilometers.


The Stray Light/Disk Light Rejection of the COR1 Coronagraph1 imager is 10 -6  B sun.


The Impact Site of the MRO Mars Reconnaissance Orbiter is Confirmed.


The Number of Ground Station of the PRISMA Satellite Network is 2.


The Pixel Size (km x km) of the Antenna Reflector is 32.


The Apogee (km) of the Intercosmos- Bulgaria 1300 (Intercosmos-22) Satellite is 906.


The Flight Operation Date of the Cute-1.7+APD Nano-Satellite is June 25-29, 2007.


The Operation Power Level of the Scanning LIDAR LIDAR is Not operated at its highest power-level.


The Power of the Instrument Satellite Instrument is 6 W.


The Launch Date of the SEOSAT-Ingenio Satellite is November.


The Mass (Dry) of the Satellite Satellite is ≤ 1700 kg.


The Observation Target of the EUV Imager Imaging System is Plasmasphere.


The Frequencies of the Low Noise Amplifier Amplifier is L1 and L2.


The Objectives of the ACE-FTS Instrument is Measure the vertical distribution of atmospheric trace gases, in particular the regional ozone budget, as well as temperature and pressure.


The Antenna Size of the DART Spacecraft is 4.5 m.


The Image Bands of the Herschel Space Observatory is 70 µm (blue), 160 µm (green) and 250 µm (red).


The Multispectral Resolution of the Resurs-P1 Imaging Satellite is 3-4 m.


The Contact Date of the TerraSAR-X Satellite is June 19, 2007.


The Output Power of the Satellite Navigation Satellite is Equivalent to the light from a 60 watt lamp.


The Purpose of the PRIma (PR-Imager) Camera is Earth observation and to test the camera in space.


The Object Detection Limit of the NEOSSat Microsatellite is 20th V magnitude.


The Dimensions of the Instrument CEB (Common Electronics Box) is 120 mm x 300 mm x 250 mm.


The Wavelengths of the PACS and SPIRE Instruments is 250, 350 and 500 µm.


The Power of the S-band Transmitter Transmitter is 0.5 W.


The Function of the BRO-1 Satellite is Maritime monitoring.


The Electron Energy Ranges of the EPE Energetic Particle Experiment is 30-90 keV, 100-200 keV.


The Swath Width of the ALOS-3 Satellite is 50 km.


The Rover Mass of the Tianwen-1 Probe is ~240 kg.


The Mission Goals of the Heinrich Hertz Satellite is See List.


The Manufacturer of the SOLSPC Radiometer is CNRS, France.


The LTDN of the PRISMA Satellite is 1030 hours.


The Communication Range of the SATTLA-2 PocketQube is Over 600 km.


The Data Rate (max) of the MHX-2400 S-band Transmitter/Transceiver is 83 kbit/s.


The Spatial Resolution of the ICEYE-X1 Satellite is 10 m x 10 m.


The Mass of the FPU Focal Plane Unit is 16 kg.


The Operating Orbits of the MS-2 Minisatellite is Near-Earth orbits in the altitude range from 500 to 700 km.


The Quantity of the Solar Panels Power Generation is 2.


The Latency of the ATL01 Reformatted Telemetry Data is 2 days.


The Approx. peak sensitivity altitude of the Channel 4 Sensor is Unknown.


The True Anomaly of the SMART-1 Satellite is 180.000º.


The Function of the IDHS and CNM Facilities is X-band payload data reception, processing and archiving/delivering the PRISMA data and products.


The Conference Presentation of the GOMX-1 Satellite is 4S (Small Satellites Systems and Services) Symposium.


The Duration of the Experiment Space Station Experiment is Up to 4 months.


The Purpose of the FREND Neutron Detector is Fine-Resolution Epithermal Neutron Detector for ExoMars Project.


The Transfer Parameters of the LUMIO Satellite is Cj = 3.09.


The Deployment Date of the NanoRacks CubeSat Deployer is March 11, 2015.


The Reentry Date of the OCSE Satellite is March 5, 2001.


The Contract Value of the JPSS-3 and -4 Satellite is $460 million.


The Project Management of the Power subsystem Satellite Subsystem is Osaka Prefecture University, Kagawa University, Keio University, Tokyo Metropolitan College, Osaka Prefecture College.


The Closest Approach Time of the Rosetta Satellite is 18:10 CEST.


The Configuration of the MPO Satellite is Equipment panel perpendicular to radiator.


The Delayed TM Playbacks of the Telemetry Data Transmission is Five complete during the visibility window.


The Duration of the Satellite Orbit Orbit is Ten years.


The Material of the Platform Structure Satellite Component is Composite honeycomb aluminium panels.


The Image Capture of the EPIC European Photon Imaging Camera is Figure 81.


The Development Authors of the CubeSats for Technology Maturation Satellite is Charles D. Norton, Steve A. Chien, Paula J. Pingree, David M. Rider, John Bellardo, James W. Cutler, Michael P. Pasciuto.


The Owner of the WorldView-1 Satellite is Maxar Technologies Inc..


The Data Rate of the ALOS-3 Satellite is 800 Mbit/s.


The Publication Date of the NICER Satellite is 14 August 2018.


The Development Team of the EnMAP Hyperspectral Imager Imaging Satellite is S. Hofer, H. J. Kaufmann, T. Stuffler, B. Penné, G. Schreier, A. Müller, A. Eckardt, H. Bach, U. C. Benz, R. Haydn.


The Attitude and Orbit Control System of the CHAMP Satellite is Unknown.


The Design Life of the Landsat-7 Satellite is 5 years.


The Affiliation of the Stephane Dussy Engineer is Unknown.


The Payload Mass of the ADEOS spacecraft Satellite is 1300 kg.


The Altitude of Front Heat Shield Release of the Schiaparelli Lander is About 7 km.


The Attitude Stability of the Nanosatellite Satellite is Arc-Minute.


The Expected Initial Tumbling Rates of the Satellite Spacecraft is Less than 30º/s.


The Thruster Type of the Eutelsat 172B Satellite is Electric.


The Characteristics of the Data Products Satellite Data is High-accuracy, high spatial resolution, fast global coverage.


The ΔV Decrease of the Bloostar Launch Vehicle is ~8%.


The Minimum Exposure Time of the Sensor Image Sensor is 10 µs.


The Launch Year of the S3D Satellite is 2028.


The Size of the Spacecraft Repeater Communication Device is 0.034 m3.


The Manufacturer of the TRXU Communication Subsystem is Space Quest.


The Planned Launch Date of the SAOCOM-2B Satellite is 2026.


The Mission Preparation Date of the REX-J Robot is June 5-12, 2011.


The Transverse Dimensions of the HXT-S Detector Modules is 465 mm x 392 mm.


The Objective of the Optical Payload Imaging System is Detection and quantitative analysis of HTE (High Temperature Events) like wildfires and volcanoes.


The Project Lead of the TEMPO Instrument is Kelly Chance from the Smithsonian Astrophysical Observatory (SAO).


The Increase in Observations of the SBSS-1 Satellite System is Fivefold.


The Launch Date of the TEMPO Satellite is 7 April 2023.


The Operation Extension Deadline of the Cluster Satellite Mission is October 1, 2010.


The Electric Field Measurement of the GEOTAIL Satellite Satellite is Unknown.


The Latency of the ATL19 Mean Sea Surface (MSS) Data is 45 days from receipt of last data in product.


The Objectives of the Rosetta Mission Space Mission is Global characterization of the nucleus, determination of its dynamic properties, surface morphology and composition, determination of chemical, mineralogical and isotopic compositions of volatiles and refractories in the cometary nucleus, determination of.


The Nominal Lifetime of the HY-2A Satellite is 3 years.


The Vertical Coverage of the Ozone Measurement Instrument Atmospheric Measurement Device is Tropopause height to 60 km.


The Ground Segment Platforms of the Argos/DCS Satellite System is Buoys, free-floating balloons, wildlife, remote weather stations.


The Watch Start Date of the Space Station Satellite is June 15, 2010.


The Payload Power of the Spacecraft Satellite is 40 W.


The Size of the MMS Satellite is The size of a baseball field.


The Wavelength Range (NIR) of the Sentinel-4/UVN Instrument is 750-775 nm.


The Roll Maneuver Capability of the ADCS Attitude Determination and Control Subsystem is ±35º.


The Overpass Duration of the ARC Calibration System is Less than 1 second.


The URL of the Global Ocean Observing System (GOOS) Ocean Observing System is http://www.gosic.org/goos/Argo-data-access.htm.


The Mass of the ICEYE-X1 Satellite is <100 kg.


The Mass of the Field Measurement Device Sensor is < 0.1 kg.


The Design Life of the EROS-A Satellite is 4 years.


The Off-Track Look Capability of the NEMO-AM Satellite is 30º.


The Mirror Material of the PAN Camera Imaging Device is Zerodur glass.


The Launch Date of the NigeriaSat-2 Satellite is November 2011.


The Orbital Altitude of the IceCube Satellite is Approximately 400 km.


The Pressure and Temperature Monitoring of the Propulsion System Satellite Component is Inside the plenum.


The Measurement Range of the FLEX Mission is 500–600 nm.


The Ascending Node Crossing Time Differences of the Swarm-A and Swarm-C Satellite Constellation is Between 4 and 10 seconds.


The Construction Material of the LORRI Imaging Instrument is Silicon carbide.


The Power Consumption of the OBC-Combo On-board Computer is 10 W.


The Importance of the Full Width at Half Maximum (FWHM) Parameter is Critical for telescope performance.


The Thruster Configuration of the GPIM Propulsion System is Single primary divert thruster centered on an upper deck topping the payload’s box-like primary structure flanked by four attitude-control thrusters mounted one each at the adjacent corners.


The Mass of the Imager Imaging System is ~130 kg.


The Avionics Architecture of the CHEOPS Satellite is OBC, RIU, two redundant 1553 buses.


The Spatial Resolution of the Spectrometer Instrument is 4.5 km x 9 km.


The Objective 2 of the EMIT Mission is Predict how future climate scenarios might change the amount and type of mineral dust emitted into the Earth’s atmosphere.


The Mission Date of the NASA's First Mission to the Trojan Asteroids Spacecraft is Unknown.


The SAR Bands of the NISAR Earth Observation Satellite is L and S-band.


The Anniversary Date of the LRO Orbiter is June 18, 2014.


The First Perihelion of the Solar Orbiter Satellite is 15 June.


The Mass of the LAP Instrument is 6.3 kg.


The Orbit Inclination of the Beijing-3B Satellite is 97.94°.


The Imaging System of the NewSat Satellite is Hyperspectral imagery.


The Conference Presentation of the EarthCARE Multispectral Imager Imaging System is ICSO 2010 (International Conference on Space Optics), Rhodes Island, Greece, Oct. 4-8, 2010.


The Drift Rate of the IRS-1C and IRS-1D Spacecraft is 3.6 x 10-4 º/s.


The Sample Collection of the Chang'e-5 Lunar Probe is Completed.


The Horizontal Cell Size of the Ozone Measurement Instrument Atmospheric Measurement Device is 50 km @ nadir.


The Arrival Date at RRSW of the MSV bus and payloads Satellite is May 2013.


The Cost per Flight of the Super Strypi Launch System is $15 million.


The Operational Input Voltage Range of the DC-DC converter Power Converter is 22 to 34 V.


The Platform Fixings of the Hard Stack Satellite Assembly is Torqued to correct levels.


The Data Collection of the ISS-EMIT Instrument is Composition of minerals that become airborne dust.


The Sensitivity of the NIRSpec MIRI Optical Instrument is 3.4 x 10 -21  Wm -2  (9.2 µm, τ i =10,000 s, R=2400).


The Launch Date of the JWST James Webb Space Telescope is 2019.


The Number of Satellites of the OneWeb Low-Earth-Orbit Broadband Venture is 648.


The IR Spectral Range / Bandwidth of the SOLSPEC-SOLAR Spectrometer is 650-3080/8.


The Number of Koranic schools of the University of Sankore Educational Institution is 180.


The PRN of the GSAT-0205 Satellite is 24.


The Inclination of the ANUSat Satellite is 41º.


The Manufacturer of the exactView-1 Satellite is SSTL.


The Orbit Inclination of the ALMASat-1 Satellite is 69.5º.


The Ship Detection of the RADARSAT Constellation Mission Satellite Mission is Operational.


The Data Source of the Ursa Space Systems Space Data Analytics Company is Space-based data from satellites.


The Sensitivity of the SCM Sensor is 3000 nT.


The Downlink Frequency of the Cadet-U UHF radio RF Communication Device is 468 MHz.


The Temporal Decorrelation of the Interferometric Mode Observation Mode is Within the requirements.


The Purpose of the Emergency Egress System Safety System is Provide quick escape in the unlikely event of an emergency.


The Scientific Goal of the TanSat Satellite is Improve the understanding on the global CO2 distribution and its contribution to the climate change, and also to monitor the CO2 variation on seasonal time scales.


The Location of the Lockheed Martin Solar and Astrophysics Lab Lab is USA.


The Developer of the RUBI Fluid Science Experiment is Airbus.


The Input Voltage of the Instrument Power Unit Power Converter is 28 V DC.


The End of Life Date of the IRS-P6 Satellite is 07 Dec 2013.


The Mass of the Tsubame Microsatellite is 49 kg.


The Decommission Date of the Carbonite-1 Microsatellite is November 2018.


The Mission Status of the CAPSTONE Satellite is Unknown.


The URL of the LIDAR Instrument is http://www.hou.usra.edu/meetings/lpsc2015/pdf/1863.pdf.


The Optics of the Imager Imaging System is TMA telescope with an aperture diameter of 1.1 m, focal length = 13.3 m, f/12.


The Focal length of the 16 mm camera Camera is 16 mm.


The Qualification Approach of the Curtiss Wright Manufacturer is Space COTS Qualification.


The Location of Exoplanets of the WFIRST Telescope is Between three and 10 times Earth’s distance from the Sun.


The Size of the Satellite Bus is 954 mm x 954 mm x 1000 mm.


The Conference Date of the Meteosat Second Generation (MSG) Radiometer/Imager Satellite is May 16-20, 2016.


The Launch Date of the SPOT-5 Satellite is 04 May 2002.


The Orbit of the CICERO-4 Satellite is 500 km orbit.


The Data Generation Rate of the Artemis I mission Space Mission is About 100 MB/s.


The Payload Data System of the KazSTSAT Satellite is Delivered.


The URL of the First Arab mission to Mars Satellite is https://www.marsdaily.com/reports/First_Arab_mission_to_Mars_designed_to_inspire_youth_999.html.


The Atmospheric Constituents of the Sentinel-5 Satellite is Ozone, nitrogen dioxide, sulphur dioxide, carbon monoxide, methane, formaldehyde, and aerosol properties.


The End of Life Date of the Satellite EO is 30 Sep 2023.


The Ka-band Advantages of the SARAL/AltiKa Satellite is Reduction of ionosphere effects, smaller footprint, better horizontal resolution, higher vertical resolution.


The Type of the Power Storage Battery is NiCd.


The Angle Resolution of the FSS Photodiode Detector is Up to 0.03º.


The Nominal Eclipses of the Cluster Satellite Constellation is 12.


The First Light Image Capture Date of the MAXI X-ray Telescope is Aug. 18, 2009.


The Data Collection Frequency of the DCS Data Collection System is UHF (~401 MHz).


The Impact of the Attitude Control System Satellite System is Hindered the performance of the GPS receiver.


The Number of Alerts Per Day of the LSST Large Synoptic Survey Telescope is Thousands.


The Frame Size of the NIUSAT Nanosatellite is 50 km x 50 km.


The Program of the CRISTAL Satellite is Copernicus Expansion program.


The Navigation Technology of the ATV-5 Spacecraft is Cooperative rendezvous technology.


The Detector of the skCUBE Satellite is Very-low-frequency radio waves.


The Repeat Cycle of the Optsat-3000 Satellite is 2 days.


The Lunar Orbit Distance of the Probes Spacecraft is Approximately 400,000 km.


The Operating Wavelengths of the X-ray Navigation Navigation System is Ground cannot be seen.


The Inclination of the WorldView-3 Satellite is 98º.


The Spectral Band of the Band Photometers Photometer is 650-740 nm.


The Transmitted Information of the NorAIS-2 Receiver AIS Receiver is Identity, position, speed and heading.


The Beam size of the Millimeterwave receiver Receiver is 22 arcmin.


The Development Cost of the Lucy Discovery Program Mission is Approximately $450 million.


The End of Life Date of the SVOM Satellite is Planned for 3 Years.


The Shape Options of the SPIDER Telescope is Squares to hexagons and even conformal concepts.


The Information Date of the Swarm Satellite is June 22, 2017.


The Spacecraft Body Shape of the GOCE Satellite is Aerodynamic.


The Power Consumption of the SEIS Instrument Seismometer is Up to 8.5 W.


The Spectral Range of the VIS Spectrometer is 350 - 500 nm.


The Latency of the ATL03 Global Geolocated Photon Data Data is 21 days.


The Entrance Aperture Location of the INMS Ion-neutral Mass Spectrometer is +Y 2U face.


The Launch Date of the NPP Satellite is October 28, 2011.


The Date of the Wolf Awakens at Night Image is 8 January 2022.


The Single Pol Swath Width of the SAR Processor Data Processor is 350 km.


The Formation Shape of the MMS Satellite Formation is Tight pyramid.


The Date of the Floods Swamp Bangladesh Natural Event is 24 June 2022.


The Diameter of the RRA RetroReflector Array is 60 mm.


The MCS of the FOS Satellite is Multi-domain distributed system.


The Observation Focus of the Solar Dynamics Observatory Satellite is Solar flares and sunquakes.


The Wavelength Range of the Visible Spectral Band Spectral Band is 0.55 - 1.05 µm.


The View of the VNIR Calibration is Spectralon plate at the poles.


The Launch Date of the Meteor-M2-2 Satellite is 5 July 2019.


The Ground Cross-Track Range Resolution of the KaRIn Radar is 70 m to 10 m.


The Presentation Date of the Small Satellite Constellation for Environment and Disaster Monitoring and Forecasting Satellite Constellation is Sept. 14-16, 2009.


The Solar Arrays Length of the BepiColombo Spacecraft is 15 m.


The Spectral Range (Band 1) of the PanMUX Instrument is 0.51-0.85 µm.


The Total Fleet Size of the OneWeb Satellite Constellation is 648.


The Interoperable Signals of the QZS Satellite is L1C, L1-C/A, L2C, L5.


The Lunar Calibration Method of the SeaWiFS Satellite is S/C maneuver to view the moon during the nighttime portion of an orbit.


The Operation Start Date of the SAMPEX Satellite is Before 1997.


The Supply Voltage of the Myriad RF board RF Board is 5 V.


The Original Launch Date of the Crew-1 Commercial Crew Mission is Oct. 31.


The Effect on Marine Ecosystem of the Ocean Acidification Environmental Phenomenon is Potential damaging knock-on effects.


The Technology Objective of the NICER/SEXTANT Instrument is Demonstrate celestial-based XNAV ( X-ray Navigation).


The Environment of the Cluster Satellite is Magnetosheath.


The Resolution of the AEISS-A Instrument is 0.5 m for panchromatic imagery.


The Purpose of the Moonlight Lunar Telecommunications and Navigation Satellite Network is To create a lasting lunar link to enable sustainable space exploration.


The Operational Modes of the Ground Station Ground Station is Command and Control (C2) and UGS (Unattended Ground Sensor).


The Quantity of Cameras of the Earth Observation Compartment Compartment is 3.


The Tether Angle Sensor of the ATEx Tether Experiment is Triggered the jettison mechanism.


The Launch Site of the HTV Spacecraft is Tanegashima Space Center.


The Sail Surface Area of the Spacecraft 3U CubeSat is 10 m^2.


The Number of Universities of the ESEO Satellite is 13.


The Launch Date of the GIOVE-B Satellite is April 27, 2008.


The Earth Imaging Mode of the Imaging System Camera is Scheduled snapshot basis.


The Oxygen Temperature of the Sun's Lower Atmosphere Celestial Body is 320,000ºC.


The Ground Sampling Distance of the NEMO-AM Satellite is Approximately 42 m.


The Instrument Type of the Myriade/AstroSat-100 Satellite is High resolution optical imagers, Other, Atmospheric chemistry, Communications, Data collection, Lightning sensors.


The Inclination of the KOMPSAT-6 Satellite is 97.42º.


The No of bands/channels of the TOU Total Ozone Unit is 6.


The Geometric Factor of the Particle Detector Instrument is 0.0085 cm 2  sr.


The Inclination of the Tatiana-2 Satellite is 98.8º.


The Geometric Factor of the Particle Detector Instrument is 0.0442 cm 2  sr.


The Measurement Range of the Cluster S/C Satellite is DC to 10 Hz.


The URL of the Solar Dynamics Observatory Satellite is http://science.nasa.gov/science-news/science-at-nasa/2010/05feb_sdo/.


The Bandpass of the CIPS Instrument is UV bandpass of 265 nm (±5 nm).


The Builder of the OneWeb Teleport is Telstra.


The Primary Orbit Period of the Didymos Binary System is 11.9 hours.


The Instrument Swath of the Optsat-3000 Satellite is 27 km x 27 km.


The Measurement Range of the Field Measurement Device Sensor is ± 64 000 nT.


The Expected Orbit Lifespan of the Meteosat Satellites Geostationary Satellites is At least seven years.


The Image Resolution of the EROS-B Satellite is Up to 50 cm.


The Instrument of the Odin Satellite is SMR (Sub-Millimeter Radiometer).


The Launch Year of the DSAC Demonstration Unit is 2015.


The Wavelength Range of the HSC Spectrometer Spectrometer is 450-900 nm.


The URL of the Argos-3 Data Collection and Location System is https://web.archive.org/web/20110814035457/http://www.argos-system.org/html/system/enhancements_en.html.


The Voltage of the Spacecraft Bus Spacecraft Component is Monitored.


The First Signal Received of the Robusta Satellite is Feb. 16, 2012.


The Mission Status of the BRITE-Austria Satellite is Unknown.


The Power Savings of the ADCS Attitude Determination and Control Subsystem is Individual OBCs can be powered off without the operation of the others.


The Required Eb/No of the Unit Communication System is 5 dB.


The Launch Date of the AgilSpace GeoPortal E-commerce Hub is May 31, 2016.


The Power of the HI-SCALE Instrument is 4.0 W.


The Function of the Machine Learning Algorithm Calibration Tool is Compare specific structures across the wavelengths and strengthen its assessments.


The Microcontroller/Processors of the SSR Solid State Recorder is None.


The Spacecraft Bus Type of the QuickBird-2 Satellite is BCP-2000.


The Predictability of the Solar Energetic Particles Space Weather Phenomenon is Extraordinarily hard to predict.


The Lens Focal Length of the Camera System Sensor is 16 mm.


The Command Type of the TDP Commanding Process is Time tagged commands (TTC).


The Solar Total Irradiance Variability of the SOVA Experiment is Detected.


The Programming Space of the SCP Spacecraft Process Controller is 64K words.


The L-band Radar Frequency of the SMAP Satellite is 1.26 GHz.


The Pointing Accuracy of the Antenna Antenna is 0.1º.


The Spatial resolution at nadir of the MERSI Medium Resolution Spectral Imager is 1.1/0.250 km.


The Altitude of the CBERS-2B Satellite is 778 km.


The Operating System of the OBC On-Board Computer is RTEMS (Real-Time Executive for Multiprocessor Systems).


The Manufacturing Facility of the Pelican Satellite Constellation is San Francisco.


The Fourth Flight Date of the MEPSI Satellite is July 4-17, 2006.


The Instruments of the MOMS Satellite is GPS receiver.


The Slit Width of the Instrument Spectrometer is 4 arcmin.


The Spectral Resolution of the MSASI Imager is 80,000 (λ/Δλ).


The Sensors of the Coarse ADCS ADCS System is Sun sensors and magnetometers.


The Nadir-pointing face of the PSSCT-2 Satellite is +Z face.


The Limb Sounder of the EnviSat Satellite is MIPAS.


The Parameters of the Optional Payloads Payloads is Mass, Power, Data Requirements.


The Size of the Spacecraft Satellite is Ø 1,500 x 1,940 mm height.


The Age of the Atmospheric Chemistry Experiment (ACE) satellite Satellite is 15 years.


The Scheduled Launch of the Space Comb Spectroscopy Setup is 2017.


The Measurement Accuracy of the SAR Instrument SAR Instrument is 3.5 cm/year, 1.6 cm/year.


The Launch Date of the CartoSat-2B Satellite is July 21, 2010.


The Beam size of the Submillimeterwave receiver Receiver is 7 arcmin.


The Power of the Transmitters Communication Device is 40 W.


The Input Buffer Size of the Transmission Module FPGA Module is 1115 bytes.


The Mass of the BLITS Satellite is 7.5 kg.


The Spectral Range of the HeII Coronagraph Coronagraph is 295-315 Å.


The Data Processing Time of the CPOM Data Processing Center is Within two days of acquisition.


The Location of the Ground Station Ground Segment is ITU.


The Downlink Transmission of the L-band telemetry subassembly Telemetry Device is Image data.


The Operational Duration of the Jason-3 Satellite is More than 25 years.


The Mission Status of the Philae Spacecraft is Unknown.


The Perimeter Length of the Calf Canyon-Hermits Peak fire Fire is 50 miles (80 km).


The S-band TxRx Power of the RF communications Communication System is 5W.


The Mission Lifetime of the Platform Satellite is ~ 15 years.


The Function of the PDD Payload Data-Downlink is Payload data acquisition and high rate downlink in Ka-band.


The Inclination of the Bion-M1 Spacecraft is 64.9º.


The Detector Array of the SCIAMACHY Spectrometer is 1024-pixel.


The Instrument of the Sentinel-6 Michael Freilich Satellite is GNSS-RO.


The Capacity of the BAT Battery is 50 Ah.


The Nitrogen Dioxide Emission Reduction of the Copernicus Sentinel-5P Satellite is Around 40% over Chinese cities.


The Listening Duration of the CPT Data Processing System is Entire transaction duration.


The Perigee (km) of the Intercosmos- Bulgaria 1300 (Intercosmos-22) Satellite is 825.


The Developer of the skCube 1U CubeSat is SOSA (Slovak Organization for Space Activities ) at the University of Zilina.


The Function of the Dual-Frequency Synthetic Aperture Radar (DF-SAR) Synthetic Aperture Radar is Studying planetary surfaces and subsurface.


The Spectral Band of the Instrument Spectrometer is TIR.


The HSTX of the IOD-1 GEMS Satellite is CPUT HSTX (High-Speed S-Band Transmitter) with SANT (S-band Patch Antenna).


The Data Rate of the SIOS Optical Link Demonstration Board Technology Demonstration Board is 1 Mbit/s.


The XY Accuracy of the Planimetric Accuracy Assessment Assessment is <0.2 m.


The Frequency Band of the S-band system Communication System is S-band.


The IF Bandwidth (MHz) of the Antenna Reflector is 400.


The Size of the Lunar Flashlight CubeSat is About the size of a briefcase.


The Telemetry of the YES Satellite is Not Switched On.


The Sensor Type of the RPA Retarding Potential Analyzer is Planar sensor with a circular aperture.


The Antennas of the ESPA Ring Interface is 2 S-band omni antennas, and 2 medium-gain horns.


The Image Credit of the RISESat Satellite is RISESat consortium.


The Cross Correlation Validation of the Image Processing Facility Facility is Global Landsat Survey GLS 2000 cloud free dataset.


The Movement Between Observations of the SCIAMACHY Spectrometer is About 1000 km.


The Ground Segment Operation of the Helios-2 Satellite is Image acquisition, priority discussion, transmission of plans, satellite control, image processing.


The Energy of the X-band Band is 42 µeV.


The Location of the VIS Unit is Payload Module.


The Data Rate of the VHF Transmitter Radio Transmitter is 64 kbit/s.


The Center Radar Frequency of the SAR-RCM Synthetic Aperture Radar is 5.405 GHz.


The Program of the Skylab-1 Space Station is Apollo Applications Program (AAP).


The Number of Libraries of the C&DH Subsystem Command and Data Handling is 8.


The Affiliation of the OSCAR-QUBE Team is Hasselt University (Belgium).


The Solar Array Efficiency of the PARASOL microsatellite Satellite is 26%.


The Presentation Location of the SERB Nanosatellite is Guadalajara, Mexico.


The Emissions Measurement of the GHGSat-D Satellite is Carbon dioxide and methane.


The Number of Satellites of the Swarm Satellite Constellation is Three.


The Interface Protocol of the DHU Data Handling Unit is 1553 link.


The Relative Semi-Diameter Precision of the Instrument Optical Instrument is Better than 1 marcsec.


The Cell Efficiency of the Solar Array Power Generation is 28.7%.


The SNR of the Eastman Kodak KLI14403 linear CCD sensor Sensor is > 100.


The Orbit Period of the Satellite Imaging Satellite is 97 minutes.


The Version of the Alexander, Graham, Bell PhoneSats is 1.0, 1.0, 2.0 β.


The Spectral range of the MWHS Microwave Humidity Sounder is 150-183 GHz.


The Mass of the X-band Transmitter Transmitter is 3.25 kg.


The Number of Verified Fragments of the DebriSat project Satellite is Close to 3,000.


The Host of the Bartolomeo Platform is ESA.


The Responsibilities of the SC Science Center is Scientific experimental plan proposal, high-level data products generation, research and application functions organization.


The Type of the OTA Telescope Component is 50 cm aperture Gregorian telescope with a collimating lens unit and an active tip-tilt mirror for image-stabilization.


The URL of the MicroMAS Project Satellite is http://digitalcommons.usu.edu/cgi/viewcontent.cgi?article=1015&context=smallsat.


The Purpose of the FY-3 (FengYun-3) Satellite is Cloud profile and rain radars.


The Detector Size of the MSI-0 and MSI-1 MSI Instruments is 1024 x 1024 pixels.


The Solar Panel Fixing Tool of the Skylab Space Station is Pair of wire cutters at the end of a 8 m long pole.


The Margin of the Unit Communication System is 2.52 dB.


The Mission End Date of the Triana Satellite is Unknown.


The Manufacturer of the STPSat-1 Satellite is Comtech-AeroAstro Inc..


The Acquisition Date of the Iris Satellite is January 15, 2016.


The Function of the GIADA Instrument is Grain Impact Analyser and Dust Accumulator.


The Function of the EGS Ground System is Run from any Space Operations Center and work with the Air Force Satellite Control Network or Universal Space Network ground stations.


The Number of Lowest-Mass, Tiniest, and Dimmest Cluster Members' Rotation Rates Measured of the Kepler Telescope is About 500.


The Swath Width of the PMC Imager is 69 km.


The Construction and Temperature Control System Mass of the Microsatellite Satellite is 9.3 kg.


The Solar X-ray Flux Level of the XRS instrumentation Instrumentation is A0.3.


The Observation Duration of the Observation Region Satellite is One year.


The Pointing Accuracy of the CeREs Satellite is Exceeds mission requirements.


The Measurement Category of the CAS500 Satellite is Multi-purpose imagery (land).


The Maximum Frame Rate of the PamCam Panoramic Camera is Up to 27 images per second.


The On-orbit Mass of the INSAT-2A/2B Satellite is 911 kg.


The Orbit Period of the HY-2A Satellite is 104.5 minutes.


The Number of Sub-Processes of the EMOC Process is Five.


The Imaging Modes of the Imager Imaging System is Panchromatic (Pan), Multispectral (MS).


The Graduate Student Contributors of the SAPPHIRE Satellite is Dozen graduate students.


The Mass of the MKA-N 1 Satellite is 10 kg.


The Type of Detector of the Instrument Sensor is Solar blind MgF2 / CsI Cathode - Multi-anode MCP.


The Observation Capability of the SUSIM Spectrometer Instrument is Ozone and molecular oxygen profiles.


The Current Consumption of the LinkSprite JPEG color VGA camera Camera is 80-100 mA.


The Launch Year of the 118 GHz Radiometer Radiometer is 2019.


The Altitude of the NigeriaSat-2 Satellite is 700 km x 733 km.


The Total Deployments from Space Station of the CubeSats Satellite is 185.


The Primary Use of the Band 10 Spectral Band is Water vapor.


The Capability of the TacSat-4 Satellite is Transmitting and receiving multiple carriers simultaneously.


The Testing Location of the XMM-Newton mirror modules Optical Instrument is Panter facility of the MPE (Max-Planck Institut für Extraterrestrische Physik) Garching, Germany.


The Controller Gains of the GOCE Satellite is Unknown.


The Tasking Priority of the SPOT or Pleiades constellations Satellite Constellations is Highest.


The Technology of the Micro-gravity experiment Experiment is Important for developing the methods of space crystal material growth.


The RF Communications Data Rate of the Kanopus-V 1 Satellite is 300 Mbit/s.


The Total Channels of the Spectral Bands Spectrometer is 159.


The Leads of the Project System Engineer Engineer is Mission-level engineering efforts.


The Data Delivery of the Mini-RF Instrument is More than 40 TB.


The Celestial Sphere Coverage of the Telescope Optical Instrument is Observatory ~80.7%.


The Date of the U.S. Drought Monitor Report is April 26, 2022.


The Interface Specification of the QZSS Satellite System is http://qzss.jaxa.jp/is-qzss/index_e.html.


The Components of the DLP System Satellite System is Probe biasing circuit, analog measurement circuit, controlling electronics.


The Operative Detector Temperature of the Detector Instrument is 238 K ±0.10 K.


The Launch Date of the Solar Probe Plus Spacecraft is 2018.


The Quantity of the MTs Magnetic Torquers is 3.


The Launch Date of the Spitzer Space Telescope Telescope is August 25, 2003.


The Attitude Accuracy of the DubaiSat-2 Satellite is 0.15º.


The Science Mission End of the TanDEM-X and TerraSAR-X Satellites is End of 2015.


The Dead Zone Area of the Gulf of Mexico Body of Water is Variable, average size about the same as the state of Connecticut.


The Eutectic Point of the Galinstan Eutectic Liquid Metal Alloy is T= -19.5°C.


The Bands of the HRV Imager is PAN, Green, Red and Near Infrared (NIR).


The S-band 1Mbit/s Downlink Data Rate of the UoSAT-12 Satellite is 1Mbit/s.


The URL of the FalconSAT-3 Satellite is http://www.globalsecurity.org/space/library/news/2009/space-091216-afns01.htm.


The System and Software Integration and Testing Duration of the PhiSat-1 Satellite is Four months.


The Function of the MSPR-2 Rack is Provides power and communication interface to each experiment device.


The Mounting Orientation of the Sensor Satellite Component is Approximately along the satellite velocity.


The Mass of the ZACube-2 Satellite is 4 kg.


The Observation Date of the NICER Telescope Telescope is 8 March 2022.


The Purpose of the Hiber-3 Satellite is Providing connectivity for IoT sensors and devices.


The Extension Approval Date of the Swarm Satellite is 20 Nov. 2017.


The Detector Array Elements of the IRIS Instrument Spectral Scanner is 5000 active elements.


The Objective of the LRR Instrument is Spacecraft POD (Precise Orbit Determination) to cm-level accuracy by SLR (Satellite Laser Ranging).


The Presentation Date of the Gravity Probe B Satellite is 1991.


The Maiden Flight Date of the CubeSat Satellite is Unknown.


The Ballistic Coefficients Comparison of the POPACS Satellite is DANDE mission results.


The CCD Cameras of the HJ-1B Satellite is 2.


The Instrument Mass of the SEVIRI Imager is 270 kg.


The Field of View Map of the EPI-Hi Instrument is Unknown.


The Quantity of the 4 piggyback microsatellites Satellites is 4.


The Design Life of the SPOT-3 Satellite is Four years.


The Sun Sensors of the S/C Satellite is 8.


The Typical cadence of the FSI dual EUV 174 Å and 304 Å alternatively Passband center is 600 s.


The URL of the James Webb Space Telescope Telescope is http://ircamera.as.arizona.edu/MIRI/miricooler.pdf.


The Structure Type of the Satellite Communication is Monoblock frame.


The Purpose of the MANTIS Nanosatellite is Provide low-latency and targeted imagery tailored to the data needs of the oil and gas sector.


The Focal length of the 50 mm camera Camera is 50 mm.


The FOV for SWIR/TIR for whiskbroom scanning of the VNIR-NP Imager is 80º.


The Power Consumption of the CLARA Instrument Satellite Instrument is 5.6 W.


The Pioneering Mission Concluded Date of the LISA Space Observatory is June 2017.


The Mission Type of the PhoneSat-1 and -2 Satellite is Non-EO.


The Objective 3 Requirement of the Jason-CS Satellite Mission is Global sea surface height to an accuracy of < 4 cm every 10 days.


The Power of the Satellite Spacecraft is 250 - 1000 W.


The Precision of the S-193 Beam Scanning is Better than 5%.


The URL of the SMAP Satellite is http://www.nasa.gov/press-release/nasa-soil-moisture-mission-begins-science-operations.


The Dimensions - Sensor head assembly of the Instrument Sensor is 20 x 37 cm.


The Onboard Data Storage of the QuickBird-2 Satellite is 128 Gbit.


The Resolution of the FGM Fluxgate Magnetometer is 1 to 2 nT.


The Development Date of the Microelectromechanical System Small Satellite Thermal Control is May 6, 2004.


The Grating Structure of the OCO-3 Spectrometer is Very regularly-spaced series of grooves on a very flat surface.


The Purpose of the SPS Spacecraft Potential Sensor is Understand Dione’s charging environment.


The Pit Depth of the Ma'at Region on Comet 67P/Churyumov–Gerasimenko is 50–60 m.


The Instrument Type of the TEMPO Satellite is Spectrometer.


The Purpose of the ExoMars Trace Gas Orbiter Spacecraft is Hunting for atmospheric gases linked to biological or geological activity, as well as understanding the past and present water inventory of the planet.


The Image Acquisition Date of the MODIS Instrument is January 30, 2022.


The Sensitivity of the NIRSpec MIRI Optical Instrument is 120 nJy (3.0 μm, τ i =10,000 s, and λ/Δλ = 100).


The Operation of the HTV Spacecraft is Unloading and Loading.


The Onboard Software Reset of the Kepler Spacecraft is Five-day break in science data collection.


The Mass of the Athena Satellite is 138 kg.


The Ice Loss of the CryoSat Satellite is 76 Gt per year for Gulf of Alaska, 28 Gt of ice per year for High Mountain Asia.


The Data Types of the EO-ALERT Satellite System is Optical and SAR data.


The Gain Control Method of the Ranging Channel Communication System is Apportioning the ranging channel the correct predetermined modulation index in the transmit modulator.


The Data Collection Period of the Cluster, Polar, Geotail, THEMIS Spacecraft is 1995–2012.


The Mission of the Beresheet Spacecraft is Journey to the moon.


The Propellant of the FENIX micropropulsion device Micropropulsion Device is Solid.


The Standard Deviation of Time Between Resets of the BRMM Spacecraft is 6 days.


The Antenna Fields of View of the Van Allen Probes Spacecraft is Initially from boresight to 70º.


The Measurement Scenario of the MIPAS Instrument is Enhanced Vertical Resolution and Regularization.


The GSD (Ground Sample Distance) of the ALOS/PRISM Satellite is 2.5 m.


The Launch Preparations Date of the Galaxy 30 Satellite Satellite is 30 June 2020.


The Doppler Beacon of the GFO Satellite is CW (Continuous Wave) transmitter.


The Supplies Capacity of the HTV Spacecraft is Up to 6,000 kg.


The Radiometric Resolution of the AATSR Instrument is 0.1 K.


The Power of the CICERO satellites Satellite is Around 21 W.


The Development Date of the Microscope Mission Satellite is Unknown.


The End of Life Date of the Biomass Satellite is April 2029.


The Range of the Rangefinder Module Laser Altimeter is 500 km.


The Operation of the F-DUGS Center is Request programming and pre-feasibility analysis, satellite data acquisition, data processing and distribution, archiving and cataloguing.


The Black Hole Mass of the OJ 287 galaxy Galaxy is 18 billion times the mass of our Sun.


The Affiliation of the Nuria Pérez Engineer is Unknown.


The Velocity After Engine Shutdown of the Schiaparelli Lander is Less than 2 km/h.


The Conference Date of the GIOVE-B Satellite is Sept. 22-25, 2009.


The TT&C Downlink Rate of the MERLIN Satellite is 625 kbit/s.


The Noise of the Thrusters Satellite Component is 0.1 µN / Hz.


The Number of Components of the JEM Module is 6.


The Material of the ICON FUV Instrument Photocathode is CsI.


The Size of the OptiCube-1 Satellite is 3U.


The SDRAM of the GomSpace NanoMind A3200 Onboard Computer is 32 MB.


The Pointing Accuracy of the ACS Attitude Control Subsystem is 0.14º (8.4 arcmin).


The Launch Contract Date of the SpaceIL Nonprofit Group is October 2015.


The Onboard Time Code of the SSRNI Data Acquisition and Registration System is Yes.


The Service Life of the FY-3E Satellite is At least eight years.


The Imaging Spectrum of the Elektro-L Satellite is Infrared (MWIR, TIR) and VNIR.


The Vulnerable Species of the Pteropods Marine Snails is True.


The Mass of the Microsatellite Satellite is ~ 10 kg.


The Frequency Range of the Chibis-M Microsatellite is ULF-VLF.


The Components of the Microwave Calibration System Calibration System is Small mirror and a hot reference absorber.


The Size of the MEOLUT Next Local User Terminal is Less than six square meters.


The Accuracy of the Geoid Satellite is cm.


The Function of the OCO-3 Satellite is Monitors carbon dioxide and its changes throughout space and time.


The Components of the OTES Instrument is Sunshade, telescope, aft optics plate, electronics board, instrument enclosure.


The Reaction wheels of the BEESAT-1 Satellite is Yes.


The Observation Date of the Earth from Space: Lofoten, Norway Imaging is 11 March 2022.


The Measurand of the HIS Hyperspectral Imaging Spectrometer is Spectrally resolved incoming and Earth-reflected solar radiation.


The Description of the R. R. Hodges-model Theoretical Model is Describes the terrestrial hydrogen exosphere up to ~60,000 km from the geocenter, based on a third-order spherical harmonic expansion.


The Presentation Date of the Hera Mission is November.


The Launch Date of the BioSentinel 6U CubeSat is Second half of 2021.


The Launch Site of the GeneSat-1 Satellite is NASA's Wallops Flight Facility, Wallops Island, VA, USA.


The URL of the ExoMars Mars Orbiter is http://m.esa.int/spaceinimages/Images/2016/10/Thumbs_up.


The Orbital Period of the SARAL spacecraft Satellite is 100.6 minutes.


The Purpose of the Odin Satellite is Aeronomy and astronomy minisatellite with applications for atmospheric research, stratospheric ozone chemistry, mesospheric ozone science and summer mesospheric science.


The Sensor Types of the Trishna Satellite is Thermal InfraRed (TIR) telescope, optical Visible and Near Infrared (VNIR)/Short Wave InfraRed (SWIR) sensor (VSWIR).


The Power Consumption of the KGI-4C Instrument is 6.8 W.


The Purpose of the Hyperspectral Imaging Remote Sensing Technology is Characterization and quantification of Earth's surface materials.


The Launch Vehicle of the GeneSat-1 Satellite is Minotaur.


The Funding of the SEXTANT Technology Demonstration is NASA funded.


The Mass of the AltiKa Altimeter is 150 kg.


The Participation of the Vision-1 Satellite is International Disasters Charter.


The Inclusion of Aeolus data of the ECMWF Forecast Center is Since January.


The Overall Absolute Measurement Error at 333 K in Bands 4-6 of the Scanning geometry Instrument is 0.5 K.


The Launch Date of the HY-2 (Haiyang-2) Satellite is Aug. 15, 2011.


The SNR of the VSSC Satellite is Around 100.


The Unknown of the SOLSPEC Instrument is Unknown.


The Concept and International Collaboration of the Chinese Environment and Disaster Monitoring Satellite System (EDMSS) Satellite System is UNESCAP Meeting, Bangkok, Thailand, June 22-24, 2005.


The Instrument 2 of the CryoSat-2 Satellite is LRR.


The Video Format of the Iris Video Camera Camera is Ultra High Definition and High Definition (H.264 encoding).


The Mode of the Solar Panels Power Generation is Nominally in sun-pointing mode.


The Orbit Altitude of the NEMO-HD Satellite is 600 km.


The Operation of the Staggered SAR Radar Mode is Continuously varying the PRI in a cyclic manner.


The Shareholding of the Eutelsat Communications Company is 22.9%.


The Technology of the SAR Antennas Antennas is DBF (Digital Beam Forming).


The Type of the Battery Energy Storage is Li-ion.


The Focal Length of the UVS Instrument Spectrometer Telescope is 125 mm.


The Communication Network Type of the EDSN Swarm Satellite Network is Hub-and-spoke network.


The Inclination of the Chang'e-1 Satellite is 31º.


The Number of Users of the EAN Connectivity System is 16.5 million IAG passengers.


The Operation Start Date of the RAIDS Instrument is October 22, 2009.


The Mass of the Iris Radio Communication Device is 0.4 kg.


The Launch Date of the OCO-2 Spacecraft is July 2, 2014.


The Sun-Earth based spin axis determination of the IKAROS Interplanetary Mission is Not provided.


The Development Date of the ROCSat-1 Satellite is Unknown.


The Type of the Antenna Communication is Dual-feed collocated UHF and L-band antenna.


The Operation of the LRF-S2 Laser Device is During touchdown, the sampler horn will compress as it touches the surface of Ryugu.


The Downlink Data Rate of the Payload Communication System is 278 Mbit/s.


The News Release Date of the Webb Telescope Telescope is 12 July 2022.


The Launch Vehicle of the OCO-3 Instrument is Falcon 9 rocket.


The Antenna Radiating Area Dimensions of the SAR Synthetic Aperture Radar is 10 m by 3.5 m.


The Application Topics of the Cross-track SAR Interferometry Application is Land environment, Navigation, Crisis and security management, Urban areas, Glaciology/hydrology Ice and snow, Sea-ice, Morphology/hydrology Geology Geological mapping/morphology, Earthquakes/volcanoes, Landslides, Subsidence (land and urban areas) Land co.


The Energy Loss of the Neutron-Element Collisions Particle Interaction is More like a ping pong ball hitting a bowling ball.


The Swath Width of the CCD Pushbroom Camera Camera is 60 km.


The Mission Status Report Date of the QuikSCAT Satellite is Nov. 23, 2009.


The Design Life of the PROBA-1/-2 Satellite is Nominal mission life of 2.5 years (with a possible extension of up to 5 years).


The Image Capture of the OLI-2 Imaging Device is During the wildfires.


The Polarization Purity of the Array Radiator Antenna is Cross-polar better than -20 dB.


The Battery Charge Current of the SBVR Power Supply is Up to 40 A.


The Application of the RISAT-2 Satellite is Resource conservation & sustainable development planning.


The Team Members of the Advanced On-Board Calibration of Space Systems Calibration System is John C. Fleming, Sandra Collins, Beth Kelsic, Nathan Schwartz, David Osterman, Bevan Staple.


The Spectral Range of the HIRDLS Spectrometer is 6 - 18 μm.


The Operation Status of the TacSat-2 Minisatellite is Nominal as of 2007.


The Imagined View of the Planet Kepler-10b Exoplanet is Artist's depiction.


The Mission Status of the Vesselsat-1 & -2 Satellite is Completed.


The Mission Type of the ST5 Satellite is EO.


The Dependency of the Signal to Noise Ratio (SNR) Performance Metric is Dependent on the choice of GIFOV and spectral bandwidth.


The Altitude at Supersonic Parachute Opening of the Experiment Data Telemetry is 25 km.


The Continuous Attitude Mode Duration of the ICESat Satellite is Approximately six months.


The Mission of the PROBA-V Satellite is Vegetation monitoring.


The Resolution Improvement of the EIS Imaging System is 100 times better.


The URL of the OMI Satellite is http://www.atmos-meas-tech.net/9/6035/2016/amt-9-6035-2016.pdf.


The Successor Instruments of the TES Satellite Instrument is CrIS instrument on the NOAA-NASA Suomi-NPP satellite and the IASI series.


The Detectors of the INTEGRAL Satellite is Imager (IBIS) and a Spectrometer (SPI).


The Filter Band Pass Targets of the EXI Camera is Blue: 437±5 nm CW, ≤20 nm FWHM; Green: 546±5 nm CW, ≤20 nm FWHM; Red: 635±5 nm CW, ≤20 nm FWHM; UV1: 260±5 nm CW, ≤30 nm FWHM; UV2: 320±5 nm CW, ≤30 nm FWHM.


The Eclipses of the Cluster Satellite Constellation is 19.


The Conference Date of the CHIPS Satellite is Aug. 21-24, 2000.


The Retirement Date of the FY-3A Satellite is January 5, 2015.