The Shipping Date of the ALD Flight Model Flight Model is 8 May.


The Boom Length of the RIME Radar is 16-m.


The Frequency Band of the RF Communications Communications is S-band.


The Operation Modes of the AIP (Advanced Ionospheric Probe) Probe is RPA and IT.


The Purpose of the NICER Payload is Provide both unique insights into neutron star physics and validation of a technology that may one day lead humanity into deep space.


The Designers of the Attitude Determination Quaternion Filter Experiment is Students of the Technical University of Delft.


The Switched Off Date of the Spitzer Space Telescope Telescope is 2020.


The GSD (Ground Sample Distance) of the ALOS-3/PRISM-2 Satellite is 0.8 m.


The Swath width of the TOU Total Ozone Unit is .


The Latency of the ATL20 Arctic/Antarctic Gridded Sea Ice Freeboard Data is 45 days from receipt of last data in product.


The Number of Channels of the IIR Imager is 3.


The IFOV (Instantaneous FOV) of the Instrument Sensor is 4 km.


The Launch Plan of the Pixxel Company is Commercial hyperspectral imaging constellation of 24 satellites in 2024 - 2025.


The No of Passbands of the Channel 8 Sensor is 1.


The Global Land Color Data Recording Time of the Sentinel-3B Satellite is Less than 1.1 days at the equator, and less than 0.9 days in latitudes higher than 30º.


The PCB Size of the CubeSense Attitude Determination and Control Subsystem is PC104-sized.


The Perigee of the RBSP spacecraft Satellite is ~ 630 km.


The Data Rate of the GeoCarb Instrument is 10 Mbit/s.


The User Types of the Iridium NEXT Satellite Constellation is Commercial and government users.


The Number of Land Regions of the RECCAP-2 Satellite Mission is 10-14.


The Data Rate Adjustment of the Electra Radio is Can maximize data volume by actively adjusting the data rate to be slower when the orbiter is near the horizon from the surface robot's perspective, faster when it is overhead.


The Purpose of the Prime Instrument Ozone Monitor is Monitor the distribution of ozone.


The Contract Signing Date of the Alphabus Telecommunications Platform is June 2005.


The Radiation Mitigation of the Observation Instrument Telescope/Spectrograph is Contiguous High-Z shielding (4π sr @detector and electronics).


The Acoustic Test of the BepiColombo Satellite is 12 June 2017.


The Purpose of the Gallium Black Bodies Calibration Source is Track the long-term degradation of the radiometer sensors.


The NLC Observation Bottom-Out of the AIM spacecraft Satellite is During solar maximum.


The Harmful Interference to Starlink Users of the 5G Network Telecommunication Network is 77% of the time.


The Launch Date of the JUICE Satellite is 2022.


The Avoided Objects of the Observation Restrictions Satellite is Earth and its atmosphere, the Moon, the bright planets, the Milky Way, the galactic band within ± 30° from the galactic plane.


The Use of the Radar Altimeter Spaceborne Sensor is Monitoring glaciers.


The Electronics Package Mass of the FlaPS Instrument Package is 0.5 kg.


The Argument of periapsis of the Satellite Spacecraft is 270º.


The Passband of the NUV channel Spectrometer is >159 nm.


The Operating Status of the Yutu 2 Lunar Rover is Operating.


The Inclination of the FASat-Alfa Satellite is 82.5º.


The Three-axis accelerometer of the Spacecraft Attitude Determination and Control System is Mounted to the inside face of each solar panel.


The Number of the Columbus ESA ISS Science & System Operations Report is 79.


The Number of Detectors of the MHS Instrument is 4.


The Height of the Sand Dunes Landform is Up to 300 m.


The Optimization Problem of the LUMIO Satellite is Nonlinear Programming Problem (NLP) method.


The Observation Date of the Giant Meterwave Radio Telescope (GMRT) Radio Telescope is Unknown.


The Phase of the UV2VIS SO Instrument is PDR (Preliminary Design Review).


The Purpose of the RAVAN Satellite is Measure the amount of reflected solar and thermal energy that is emitted into space.


The Location of the Svalbard Ground Station is 78º North.


The Operation Mode of the S-band transponder Communication Device is Full duplex.


The Capacity of the NiCd Battery Energy Storage is 55Ah.


The Rx Channels of the Reduced Solution Antenna Configuration is 2.


The Brigthness Temperature (BT) of the Antenna Reflector is 100~330 K.


The Number of Investigations of the SMART-1 Satellite is 10.


The Configuration of the Spare Lithium-1 Radio Radio is Reconfigured to monitor the crosslink activity.


The Orbit Inclination of the Colorado Student Space Weather Experiment (CSSWE) Satellite is Highly Inclined.


The Cooling Temperature of the Focal Plane Instrument Component is 150 K.


The Secondary Diameter of the Didymos Binary System is 160 m.


The Measurement Date of the GRACE-FO Satellite is 22 June 2020.


The Operating Temperature of the MIRI Instrument is 7K.


The Data Transmission Rate of the ITU Image Transmission Unit is 160 Mbit/s.


The Power Storage of the CS-XUEPS2-41 Electrical Power Subsystem is Rechargeable 30 W hr lithium polymer batteries.


The Event Nickname of the IceCube Detector Particle Detector is Hydrangea.


The Battery Type of the Spacecraft Satellite is Li-ion 12 Ah.


The CubeSat Size of the LEDSAT Satellite is 1U.


The Attitude Control Stability of the Spacecraft Satellite is 1 arcmin rms (or FWHM of ~2.2 arcmin).


The Heat Rejection Method of the CASSIOPE spacecraft Satellite is From strategically placed radiator surfaces along the bus hex sidewalls.


The NIR Channel Detectors of the SEVIRI Spectral Imager is InGaAs photovoltaic diodes.


The Orbit Eccentricity of the UniCubeSat Satellite is About 0.07.


The Coverage Area of the Kleos Scouting Mission (KSM1) Satellite is South China Sea and Strait of Hormuz.


The First Flight Date of the MEPSI Satellite is February of 2000.


The Number of CubeSats Released of the NRCSD CubeSat Deployer is 33.


The Launch Date of the TIMED Satellite is December 2010.


The Design Life of the GRACE Satellite is 8 years.


The Orbit Formation of the CloudSat Satellite is Tight formation with CALIPSO.


The Pulse period (ms) of the B1617-155 (Sco X-1) Pulsar is 3.200.


The Pan Resolution at Nadir of the QuickBird-2 Satellite is 0.61 cm.


The Fuel Consumption of the Van Allen Probes Satellite is Unknown.


The Measurement Domain of the GOSAT Satellite is Atmosphere, Land.


The Secondary Mirror Diameter of the Optics Assembly Telescope is 56 mm.


The Delivery Frequency of the SpinKF Attitude Determination System is Daily.


The Spatial resolution at nadir of the IRAS Infrared Atmospheric Sounder is 17 km.


The Design of the DDMI Instrument is Based on the SGR-ReSI design.


The Instrument of the CYGNSS observatory Observatory is DDMI (Digital Doppler Mapping Instrument).


The Information of the Unresolved Imagery Data is Contains spectral and photometric information.


The Launch Date of the SMAP Satellite is 2015.


The Mass of the HY-2A Satellite is ~ 1500 kg.


The Mass of the EPS Electrical Power Subsystem is 0.28 kg.


The Re-adjustment Time of the Earth Planet is Several thousand years.


The Systematic Error of the MIRAS Radiometer is Several Kelvin.


The Redundancy Principle of the SSR Solid State Recorder is Division of the total storage space into several banks of memory.


The Platform Type of the Carbonite Smallsat Satellite is High performance generic.


The Training Location of the Crew Dragon Spacecraft is NASA’s Neutral Buoyancy Laboratory near the Johnson Space Center in Houston.


The Development Funding of the iMESA Technology is AFOSR and AFRL.


The Lifetime of the OFEQ-1 Satellite is 6 months.


The Features of the Prometheus Satellite Satellite is Four deployable solar arrays and a deployable helix antenna.


The Data Rate of the GimmeRF Radio Instrument is Up to about 24 Tbit per orbit.


The Data Throughput of the AIS Data Collection System Data Collection System is 16 MB per day.


The Payloads of the NSSL Phase 2 Launch Program is Large military and intelligence agency satellites.


The Antenna Type of the PR Phased Array System is 2 m slotted waveguide (WG) antenna.


The Manufacturer of the OSIRIS-REx Spacecraft is Lockheed Martin Space.


The Offset temperature coefficient of the PHA Detector is <0.1 channel/ºC.


The Mass of the Jason-3 Satellite is 550 kg.


The Report Recommendation of the SMAP Satellite is Highest priority among all proposed missions.


The Owner of the PAZ Satellite is Ministry of Defence.


The Operational Availability Improvement of the MTP Transponder is True.


The Flight Path of the BioSentinel Satellite is Past the moon and then subsequently into an Earth trailing, Heliocentric orbit.


The Raw Video Data Bandwidth of the Camera Imaging Device is 12.5 Gbit/s.


The Orbit Inclination of the AFSPC-11 Satellite Mission is 0º.


The Spectral Sensitivity of the WUPPE Spectrophotometer is 1400 to 3200 Å.


The Frequency of the S-band Communication Band is 1.67-1.71 GHz.


The PAN-F of the CartoSat-1 Satellite is Panchromatic Forward-pointing Camera.


The Ground Resolution of the NIUSAT Nanosatellite is 25 m.


The Number of Occluded Rows per Filter Band of the QWIP Array Sensor Array is 76.


The Payload Data Storage Capacity of the BRITE spacecraft Satellite is up to 256 MB.


The Material of the Satellite structure Structure is Aluminum frame.


The Design Lifetime of the Spacecraft Satellite is 5 years.


The Demonstration Satellites of the Falcon 9 rocket Rocket is Two.


The Manufacturer of the CubeSats Satellite is Technische Universität Berlin.


The Sponsor of the Diwata-1 Satellite is Philippine government.


The Observation Area of the FORMOSAT-7/COSMIC-2 Satellite Constellation is Global meteorology, climate and ionosphere.


The Mass of the ESTCube-1 & -2 CubeSat is 1.050 kg.


The Spacewalk Installation Date of the UrtheCast Satellite is Jan. 2014.


The Data Processing of the HyperScout Hyperspectral Imager is Onboard image processing and data compression.


The Lossy Compression Ratio of the HSDR FPGA Hardware is 4:1 or higher.


The False Event Rate of the Instrument Sensor is <5%.


The Mission Status of the CASSIOPE Satellite is Operational (extended).


The Manufacturer of the PIMS Plasma Instrument is Johns Hopkins Applied Physics Laboratory (APL).


The Predecessor of the ROBUSTA-1B Nanosatellite is ROBUSTA satellite, which was launched in February 2012.


The Launch Rate Goal of the Starlink Satellite Constellation is Roughly two Starlink launches a month.


The Ground System of the TET-1 Satellite is Unknown.


The Launch Date of the ICEYE X1 Satellite is 17 Jan. 2018.


The Panel Size of the Solar Panels Power Subsystem is 432 mm x 243 mm.


The Configuration of the NGAVGS Sensor is Two box.


The Mission Duration of the LCROSS Satellite is 26 months.


The Commissioning Time of the AprizeSat-3 and AprizeSat-4 Satellites is 1 hour after separation.


The Performance of the GEOSAT Follow-On Water Vapor Radiometer Radiometer is Not Specified.


The Image Color Diversity of the CaSSIS Imaging System is Present.


The Servicer Mass of the ELSA-d Satellite Mission is ~180 kg.


The Conference Presentation of the Laser Communications Relay Demonstration Project Communication System is URL: http://www.spaceops2012.org/proceedings/documents/id1261897-paper-001.pdf.


The Design of the Atmospheric-sounding instrument Spectrometer is Dispersive spectrometer, using a reflexive grating for spectral bands dispersion.


The Peak Fluency of the InnoSlab laser Laser is Smaller than 2.5 J/cm2.


The Altitude of the Orbit Satellite is 720 km.


The Number of dual-gain PHAs of the PHA Detector is 16.


The Launch Date of the Soyuz-2.1b rocket Rocket is 6 February 2020.


The Slew Rate of the  Spacecraft Bus (Avionics Module=AM) Satellite is 0.25 to 1.0º/s.


The Maneuvering System of the NEA Scout Solar Sail Technology Demonstration Spacecraft is Small cold-gas thrusters.


The Launch Date of the Tianwen-1 Mars Mission is July.


The Ground Station Location of the CFESat Satellite is LANL.


The Detection Capability of the OMI Satellite Instrument is Sulfur Dioxide.


The Linearity/Noise Level or Bias/NF of the Receiver Device is Use of noise sources.


The Grid Size of the ASCAT coastal winds Data Product is 12.5 km.


The Components of the PLS Plasma Instrument is Four Faraday cups.


The Trigger Altitude of the Parachute System is About 5 km.


The Launch Date of the Queqiao Relay Satellite is May 21, 2018.


The Science Objectives of the SAGE-III Instrument is Retrieve global profiles of atmospheric aerosols, ozone, water vapor, NO2, NO3, OClO, temperature and pressure.


The Slope Error of the Aeolus Satellite is 0.7%.


The Launch Date of the BIROS Satellite is 2016.


The Formation of the Ionosphere Atmospheric Layer is Photodissociation of thermospheric air by solar extreme ultraviolet radiation.


The Data Availability of the EPIC Earth Polychromatic Imaging Camera is June 2015 through the current day.


The Launch Date of the Eutelsat Quantum Satellite is 26 July 2021.


The Number of Computers of the SAOCOM-1A Satellite is 6.


The Launch Date of the Trasser AOS Instrument is July 5, 1988.


The Cycle Life Test of the SMA Hinge Spring Component is 130 cycles.


The Additional Solar Panel of the MicroMAS-1 Satellite is Another 2U solar panel will be body-mounted on the zenith side of the satellite bus.


The Functions of the Electric Propulsion Test Subsystem Monitoring Unit is Measurement of the plasma parameters around the satellite (exhaust plume) during the operation of electric propulsion, Directly measure pollution caused by electric propulsion, Monitor satellite floating potentials influenced by electric propulsion.


The Optical Axis of the Metric Camera Camera is Vertically down to the Earth's surface.


The Conference Date of the KOMPSAT-3A Satellite is May 16-20, 2016.


The Launch Date of the COSMO-SkyMed Di Seconda Generazione Satellite is 18 December 2019.


The Micro Vibration Correction of the Instrument Satellite Instrument is Confirmed.


The Power of the RA-1 Radar Altimeter is 130 W.


The Dry Mass of the QZS-1 Satellite is 1800 kg.


The Shape of the Ceres Dwarf Planet is Almost spherical.


The Temporal Sampling of the Sea Surface Salinity (SSS) Measurement is Monthly.


The Budget Allocation of the Copernicus Environmental Monitoring Satellites is 4.81 billion euros.


The Test Results of the ALTIKA Instrument is Unknown.


The Date of the IGARSS Symposium is July 26-31, 2015.


The Baseline Determination of the TanDEM-X Satellite is Two years.


The Number of Instruments of the JEM-X X-Ray Monitor is 2.


The Event of the Paris Glacier Memorial Glacier is Agreement of a legally binding treaty in 2015.


The Purpose of the HEO Highly Elliptical Orbits is Communications services and other uses at high northern latitudes.


The Full Year in Orbit of the COMS Satellite is Late summer of 2011.


The Downlink Frequency of the SafetyNetTM Data Collection Architecture is Ka-band (26.7 GHz).


The Range of the Temperature Sensor is -50 to +600ºC.


The Communication Signal of the FLP Satellite is S-band RF.


The PRN of the GSAT-0206 Satellite is 30.


The Image Color Representation of the Shikisai Satellite is Coolest waters in blue, warmest temperatures in red.


The Image Calibration of the HyperScout Imaging System is Not yet calibrated.


The Lens Surfaces Coatings of the Instrument Spectrometer is Narrow-band AR coatings with R<0.2%.


The Arrival Date of the European Service Module Spacecraft Module is November 7, 2018.


The Mission Type of the Badr-B Satellite is EO.


The Argument of Pericenter of the SMART-1 Satellite is 292.930º.


The Width of the Instrument Instrument is 413 mm.


The Imaging of the XRT X-Ray Telescope is Captured the black moon in the shape of a crescent in front of the solar corona brightened by X-rays.


The Data Input Data Rate of the Data Handling System System is 336 Mbit/s.


The Basis of the MLFMM (Multilevel Fast Multipole Method) Algorithm is Method of Moments.


The Launch Date of the OneWeb Satellite is 2022.


The Upper Stage Deployment Time of the Rocket Launch Vehicle is More than a half-hour.


The Launch Date of the Ulysses Spacecraft is 1990.


The Volume of the CROP Filter Water Filtration System is 600 mL.


The Developer of the KickSat-2 CubeSat is Stanford University and NASA/Ames.


The Functionality of the Active Calibration Source Calibration Equipment is Equivalent to a very large known reflector on the surface.


The Video Imaging Duration of the Iris Video Camera Camera is Up to 60 seconds.


The Ground Resolution of the PAN Detector is 1m.


The Transmission Security of the Satellite Satellite is Used polarization as a means of transmission security.


The Accuracy of Moisture Profiles of the CrIMSS Instrument Suite is 15%.


The Launch Year of the ERS-1 Satellite is 1991.


The Orbital Period of the NigeriaSat-2 Satellite is About 99.5 min.


The URL of the An Efficient Photoelectric X-ray Polarimeter Device is https://doi.org/10.1038/35079508.


The Sun Elevation for Operations of the Metric Camera Camera is Never exceeded 30º.


The Manufacturer of the MWI Instrument Instrument is CGS (Carlo Gavazzi Space) S.p.A.


The Detection Area of the HXD Detector is 16cm2.


The Short Circuit Current of the CSS Coarse Sun Sensor is 34 mA.


The Operational Protocols of the ISERV Satellite is Image data acquisition, storage, and downlink.


The Memory of the Controller card C&DH Subsystem Component is Several MB of RAM and EEPROM.


The Attitude Control of the UniSat-1 Satellite is Spin-stabilized at 5 rpm with the spin-axis normal to the orbital plane.


The Justification of the ACE Satellite is New science that can be accomplished with three solar wind satellites near L1.


The Average Power of the JAWSAT Satellite is 80 W.


The Program Overview of the GCOM-Al Satellite is Not provided.


The Data Input Interface of the Modem Processor Signal-Processing Chain is SpaceWire over LVDS (Low Voltage Differential Signaling) link with minimal NRE (Non-Recurring Engineering).


The Manufacturer of the GFO Satellite is BATC (Ball Aerospace &.


The Focal Length of the Telescope Optical Instrument is 320 mm.


The Thermomagnetic Perturbations of the ASM Satellite Component is 20-30 pT +/- 5 pT peak-to-peak range.


The Pointing Range of the ADCS Attitude Determination and Control Subsystem is ±32º.


The Frequency (GHz) of the ICI-10 Radiometer is 448±1.4.


The | 80 m of the MSS Instrument Spatial Resolution is Spatial resolution 80 m.


The Insertion Date of the P2 Spacecraft is October 22, 2010.


The Spectral Sampling Interval of the LR Spectrometer Spectrometer is 0.6 nm/pixel.


The Plastic Scintillator of the Range Calorimeter Particle Detector is 16 planes.


The Focal Plane Format of the EXI instrument Imaging Instrument is 12.6 MP 4:3 format.


The Main Role of the CryoSat Satellite is Provide detailed measurements of the height of the world’s ice.


The Time Between Launches of the Falcon 9 Rocket is a little more than 72 hours.


The Project of the Firefly Satellite Satellite is NSF CubeSat Project.


The Stars in Galaxies Percentage of the Universe Cosmology is 7 percent.


The Mission Goal of the EMIT Satellite is Map where the dust originates and estimate its composition.


The TEB Detector Nonlinearity of the VIIRS Instrument is Excellent.


The Responsible Orbit of the DWSS Satellite is Early Morning.


The Radiation Qualification of the GomX-4 Satellite is 20 krad TID (Total Ionizing Dose).


The Channel Wavelengths of the IIR Imager is 8.65 µm, 10.6 µm, 12.05 µm.


The Bandwidth (GHz) of the ICI-8 Radiometer is 6.


The Mass of the OTU Optical Telescope Unit is 45 kg.


The Electron Density of the RAX-1 Satellite is Very quiet.


The Channels of the Spectrometer Instrument is 385, 454, 600, 1020, 940, 448, 525 nm.


The Science Operations Location of the Spitzer Space Telescope Telescope is Spitzer Science Center at IPAC at Caltech.


The Quantity of the Fragments Debris is In excess of 115 k.


The Exact Repeat Cycle of the Satellite Orbit is 8 days.


The Maximum Sustained Event Rate of the ISS-LIS Instrument is 300 events/s.


The Science Objectives of the SAGE-III Instrument is Provide atmospheric data essential for the calibration and interpretation/correction of other satellite sensors.


The Alignment Milestone Date of the Webb Satellite is 16 March 2022.


The Data Delivery of the Command and Telemetry Interface Interface is 3-byte commands and 64-byte ancillary data.


The Wavelength Sensitivity of the Polarimeter Instrument is 1170 - 1800 Å in second order and up to 3600 Å in first order.


The Location of the Science Operations Center (SOC) Data Center is LASP.


The Objective 1 of the EPS (EUMETSAT Polar System) Satellite System is Ensure continuity and availability for operational purposes of polar meteorological observations from the "morning" orbit to the global user community.


The Nominal Voltage of the NiH2 Batteries Power Subsystem is 12.5 V.


The Repeat Cycle of the Satellite Imaging Satellite is 12 days.


The Proposal Year of the Geospace Dynamics Constellation Mission is 2013.


The Power to sub-experiments of the STRV-1d DHS Data Handling System is +5 V, ±12 V.


The Principal Investigator of the NICER Payload is Keith Gendreau.


The Search Duration of the YES Satellite is About 96 hours.


The Slit Width of the Spectrometer Spectrometer is 25 µm.


The Atmosphere of the 55 Cancri e Exoplanet is Possibly made of oxygen or nitrogen, or a very thin atmosphere of mineral vapor, such as silicon oxide.


The Drift Distance of the ASTRO Satellite is More than 6 km.


The Function of the S-193 Radar System is Combination of passive microwave radiometer with an active scatterometer, and radar altimeter.


The Accuracy Specification of the ASM Satellite Component is 300 pT (2σ).


The Levels of the Data products Data is 0 and 1.


The Orbit Accuracy of the DORIS-DIODE Satellite System is Ten Centimeters.


The Deployment of the NanoSail-D2 Satellite is Shortly after deployment of the NanoSail-D2, the solar sail will deploy.


The Seal Material of the Sample Container Container is Aluminum metal.


The Release Date of the BEESAT-4 CubeSat is Sept. 9, 2016.


The Spectral Band of the Camera Imaging Device is 762 nm.


The Design Concept Overview of the ASTER Instrument is Not Provided.


The Calibration Scheme of the In-flight Radiometric Calibration Calibration is Two points calibration.


The Article Date of the Small Water Ice Reservoirs Lunar Surface Feature is 26 October 2020.


The Peak Power of the Radar Radar is 200 W/150 W.


The Presentation Date of the Taiwan Weather Monitoring Satellites Satellite Constellation is March 1-8, 2008.


The Mission Goals of the ALBus 3U CubeSat Satellite is Technology demonstration, Power distribution, Battery charging, Shape Memory Alloys deployment.


The Data Rate of the UHF Transceiver Transceiver is 4Kbps.


The CPU of the STRV-2 DHS Data Handling System is 8086 rad-hard.


The Name of the CubeSat Satellite is Unknown.


The Outer Diameter of the PM Satellite Component is 4.4 m.


The Issue of the Medium-Resolution Camera Camera is Telemetry issues.


The Installation Date of the ACLS Air and Oxygen System is 2 November 2018.


The Components of the Spacecraft Plug-n-Play Avionics (SPA) Standards is Data transport, power delivery, time synchronization, single point ground connection, minimal "hooks" for self-description.


The ECT (Equatorial Crossing Time) of the WV-1 Satellite is 1330 hours.


The Developers of the MR-FOD Deployer is Morehead University, Morehead, KY, USA and GAUSS.


The Purpose of the CHEOPS Satellite is Search for transits of exoplanets by means of ultrahigh precision photometry on bright stars already known to host planets.


The Measurement Locations of the IMPACT Instrument is Two STEREO spacecraft locations.


The Unknown of the Automatic Registration Method Image Processing Method is Unknown.


The Speed of the Internet Connection Communication is At least 25 Mbit/s.


The URL of the CICERO Satellite System is http://www.prweb.com/releases/2009/12/prweb3295414.htm.


The Operator of the TanDEM-X Satellite is German Space Operations Center (GSOC).


The p-FETs Quantity of the RADMON Radiation Monitor is 4.


The Location of the Ground Segment Ground Control Infrastructure is University of Ljubljana and Pomjan.


The Pixel Size (km x km) of the Antenna Reflector is 6.


The Observation Period of the BRITE Nanosatellite Network is Six-month.


The Capability of the CHEOPS Satellite is Determine accurate radii for exoplanets.


The Energy Range of the SXD and solar X-ray monitor Detector is 1-10 keV.


The Image Capture of the Iris Camera Camera is Barcelona, Spain.


The Orbit Altitude of the ERBS Satellite is 610 km.


The Transfer of the EMEA FleetBroadband Satellite Communication is To Alphasat.


The Development Contract Date of the Alphasat Satellite is November 2007.


The Wavelength Range of the Lens Optical Instrument is 600 - 1000 nm.


The Launch Date of the ABEX CubeSat is Planned for 2024.


The Challenges of the Maritime AI-NAV Program is Significant increases in transport volumes, more stringent environmental requirements and a shortage of seafarers in the future.


The Spectral Range of the HR Spectrometer Spectrometer is 677–697nm.


The Function of the Instrument Calibration System is Monitor instrument response and enable high data quality and reliability.


The AIV System Reuse of the PROBA Project Satellite Project is Ground segment software is used both as the AIV system and as the operations system.


The East-West Scan Swath Time of the Instrument Satellite Instrument is Less than 10 seconds.


The Configuration of the IEPS Ion Electric Propulsion System is Single-string system.


The Number of Retired Satellites of the DMSP (Defense Meteorological Satellite Program) Satellite Program is 16.


The Mass of the MEPSI Satellite is < 1 kg.


The Establishment of the State Vectors Data is Using Deep Space Network (DSN), Orbit Determination and ground uplink.


The Spatial Resolution of the LEND Neutron Detector is 5 km.


The Orbit Type of the Shakuntala Satellite is Sun-synchronous.


The Mass of the Ralph Satellite End-body is 37.7 kg.


The Filter Wheel Rotation Frequency of the GOES Sounder Radiometer is 10 times per second.


The Launch Date of the Nancy Grace Roman Space Telescope Space Telescope is Mid-2020s.


The Power Consumption of the CU Cabling Unit is 10W.


The Exclusion Angles of the STOs and STAEs Analog Electronic units is ±35º (sun), ±25º (S/C secondary reflection) ±25º (moon), ±35º (Earth).


The Data of the Potential Instrument Unknown is Included in TT&C data.


The Power Input of the CU Control Unit is 6-36 VDC.


The Along-Track Coverage of the MSI-0 and MSI-1 MSI Instruments is 30 km.


The Change of the Test Profile Test Procedure is Started on a warm temperature plateau to enable a valid home command.


The Lunar Orbit Entry Date of the Chang'e-5 Spacecraft is Nov. 28.


The Telescope Aperture of the IRIS Satellite is 20 cm.


The Power Output of the Fission Surface Power System Power System is At least 40 kilowatts.


The Be Filter Thickness of the X123-SDD X-ray Spectrometer is 8 µm.


The Modulation and Coding Scheme of the Sentinel-1, -2, and -3 Satellites is Accommodated within the 300 MHz X-band bandwidth.


The RF Power of the Unit Communication System is 8 W.


The Number of Satellites of the Long March 6 Rocket is 13.


The Data Handling of the LT Satellite is Deletes SOH and science data from its crosslink queue.


The Redundancy of the Data Recording System System is Dual-redundant.


The Band Design of the Antenna Communication is L-band: circularly polarized dual-patch antenna, UHF-band : array of four inverted F antennas with capacitive loading.


The Design Life of the QuikSCAT Satellite is 2 years.


The Data Usage of the HIRS Infrared Spectral Radiance Instrument is Calculate atmospheric vertical temperature profiles, determine ocean surface temperatures, total atmospheric ozone, precipitable water, cloud height and coverage, and surface radiance.


The Altitude of the PAZ Satellite is 514 km.


The Control Modes of the IPS Instrument Pointing System is Automatic, Manual.


The Spectrum of the Starlink and OneWeb Satellite Constellations is Ku-band.


The Deployment Date of the Pulsar satellites Satellite is Early 2025.


The Full Frame Integration Time of the CCD Image Sensor is 2.6 seconds.


The Presentation of the Global Change Observation Missions Satellite is June 25-29, 2007.


The Anniversary of the Swarm Satellite is 4th.


The Public Listing Date of the Astra Small Launch Vehicle Developer is July 1.


The | of the GOSAT Satellite is Space.based Carbon Monitoring by GOSAT and GOSAT-2.


The Launch Date of the SARAL Satellite is Feb. 25, 2013.


The Design Life of the MERLIN Satellite is Approximately three years.


The Roll Nadir Pointing Accuracy of the Attitude Control Satellite Subsystem is ±15º.


The TGF Energy of the RHESSI Satellite is Beyond 20 MeV.


The Power Supply of the Readout Electronics Electronics is Individual.


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


The Number of Satellites per Mission of the Copernicus Environmental Monitoring Satellites is 2.


The Spectral Bands of the Eastman Kodak KLI14403 linear CCD sensor Sensor is 0.52-0.62 µm (green), 0.63-0.69 µm (red), and 0.76-0.9 µm (NIR).


The Manufacturer of the GNSS Receiver Navigation Device is Syrlinks.


The Program Date of the European Student Earth Orbiter Satellite is Aug. 10-15, 2013.


The Telescope Diameter of the Euclid Space Telescope is 1.2 m.


The Development Status of the Webb Space Observatory is Not provided.


The URL of the GOCE Satellite is http://www.esa.int/Our_Activities/Observing_the_Earth/GOCE/Earth_s_gravity_scarred_by_earthquake.


The PRS Element of the Galileo Satellite Navigation System is Unknown.


The URL of the STEREO Satellite is http://science.nasa.gov/science-news/science-at-nasa/2011/06feb_fullsun/.


The Power Generation of the SPOT-2 Satellite is Solar array.


The Vehicle Dockings Per Year of the Orion spacecraft Spacecraft is 12-15.


The No of Passbands of the Channel 9 Sensor is 1.


The Launch Date of the Galileo Satellite Constellation is 25 July.


The Downlink Frequency of the Communication Communication System is X-band.


The Momentum Offloading Management of the PROBA-V Satellite is De-activated 10 s before the next imaging sequence.


The Remote Sensing Image Record Change Date of the Tongzhou Beijing Location is 13 Oct. 2017.


The Observation Start Time of the INTEGRAL Satellite is 15:30:59 on 24 January.


The Travel Time of the Hayabusa-2 Space Probe is Six years.


The In-Orbit Fleet of the OneWeb Company is 110 satellites.


The Scientific Payload Mass of the Microsatellite Satellite is 10.8 kg.


The Swath Width of the CO2Image Satellite is 50 km.


The Volume of the RMU Radiometer Microwave Unit is 180 x 170 x 50 mm.


The Dimensions of the SGR-ReSI Interface Unit is Approx 300 x 160 x 30 mm.


The Number of Satellites of the Flight Satellites Satellites is 8.


The Mission Condition of the PROBA-V Mission Satellite Mission is Excellent after six months of operations and one year after launch.


The Dust Measurement Period of the Ulysses Spacecraft is 1992 to 1998.


The Heat Shield Type of the Skylab Space Station is Temporary parasol-type.


The Content of the VN-rapport Report is Methaanreductie een van de meest kosteneffectieve maatregelen tegen opwarming.


The Reception Rates of the AIS Receiver Device is Above 13,000 AIS messages per hour.


The Oscillation Modes of the Gaia Satellite is Radial and Nonradial.


The Acoustic Chamber Testing Location of the Crew Dragon Spacecraft is NASA’s Plum Brook Station test facility at Glenn Research Center in Ohio.


The Downlink Frequency Band of the Svalbard Ground Station Ground Station is L-band.


The Orbital Period of the CBERS-4 Satellite is 100.26 minutes.


The True Anomaly of the Satellite Spacecraft is Arbitrary.


The Swath of the MWRI Microwave Radiometer Imager is 1400 km.


The End of Observing Mission of the PROBA-V Satellite is June.


The Impact Speed of the Schiaparelli module Spacecraft is 540 km/h.


The Spin Rate of the CINEMA satellites Satellite is 2 rpm.


The NS FOV: max channel of the AHI Scanner is 16,311 µrad.


The Launch Date of the PW-Sat Satellite is Unknown.


The Weight of the MESSR Radiometer is 140 kg.


The Components of the C&DH Subsystem Command & Data Handling is IEM (Integrated Electronics Module), PIE (Payload Interface Electronics), SSR, and two OCXO (Oven Controlled Crystal Oscillators).


The Launch Date of the SWOT Satellite is Unspecified.


The Mission Status of the TUBSAT Satellite is Mission complete.


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


The Power of the Horizon sensor Sensor is 2.8 W.


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


The Frame Coverage of the spaceCam c4000 Video Camera is 12 km x 12 km.


The Imager Manufacturer of the HySIS Satellite is ISRO’s Space Application Centre (SAC).


The Use of Shadows of the Bennu Global Mosaic Map is Needed to make the surface features pop.


The Effective Detector Area of the HXCP Hard X-ray Polarimeter is 7 cm 2.


The Network of Direct Readout Stations of the EARS Data Service is Around the Atlantic and Arctic Oceans.


The Energy Range of the X-ray Satellite Navigation Navigation System is 1-15 keV.


The Manufacturer of the Resurs-DK1 Spacecraft is TsSKB Progress.


The Solar Array Type of the EPS Electric Power Subsystem is Fixed.


The Avionics Unit of the ICPS Upper Stage is Unknown.


The Chirp Bandwidth of the RA-1 Radar Altimeter is 330 MHz (for ocean mode) and 82.5 MHz (for ice mode).


The Purpose of the IMERG Precipitation Product is Add up the large rainfall totals.


The Mission Concept of the FLuorescence EXplorer Satellite is ESA’s Earth Explorer 8.


The Operational Status of the Carbonite-1 Satellite is Still operational after two years.


The Aperture of the UVIT Telescope Telescope is ~375mm.


The CCD Detector of the PS2 Optical Instrument is 29MP.


The Sampling Rate of the CIP Instrument is 1 and 8 Hz.


The Data Collection of the Geospace Dynamics Constellation Mission is Earth’s ionosphere and thermosphere.


The Mission Status of the RaInCube Satellite is Unknown.


The Remote Operations Location of the ExoMars Mission is France.


The Mission Operations Location of the OPAL Satellite is SSDL ground station at Stanford University.


The On-Orbit Temperatures of the TacSat-4 Satellite is ±150o C.


The Wavelength Range of the Band 4 Spectral Band is 1360-1390 nm.


The Instrument Mass of the S-192 optomechanical scanner Scanner is 57 kg.


The Maximum Beam Scanning Angle of the P Mode Observation Mode is ± 1.9º.


The Purpose of the MMS Satellite is Study magnetic reconnection in collisionless plasmas.


The Output Voltage of the Charge Regulator Power Management Device is Unregulated 14 V.


The Incidence Angle of the Iris Video Camera Camera is < 40º.


The Affiliation of the Shobhakar Dhakal Vice President is Asian Institute of Technology.


The Instrumentation of the IMPACT Instrument is Solar wind electron and solar energetic particle instrumentation.


The System Architecture of the SOHLA-1 Microsatellite is ACS, COM, EPS, Experiment connected to CCU and ECU.


The Date of the Geometric Calibration of the MICAS CCD Sensor Calibration is July 16-23, 2000.


The Provider of the Lithium Polymer battery Battery is ASP Equipment GmbH.


The Launch Date of the ICEYE-X2 Satellite is December 2018.


The Conference Date of the Operationally Responsive Space Concept is August 8-13, 2015.


The Number of Satellites of the OneWeb Satellite is 34.


The Orbital period of the KOMPSAT-3A Satellite is 95.2 minutes.


The Purpose of the MLS Microwave Limb Sounder is Chemistry of the middle and upper stratosphere, Monitoring of ozone chemistry, Measuring radicals, reservoirs, and source gases in chemical cycles which destroy ozone, Measuring SO2 and other gases in volcanic plumes.


The Communication Recovery Efforts of the Hitomi Satellite is Ongoing.


The Deployment Time of the Antenna System Antenna is Few seconds.


The Launch Date of the GOSAT-GW Satellite is Early 2024.


The Mass of the Aquahab Payload is 18 kg.


The Data Transmission of the Landsat-5 Satellite is X-band direct downlink only.


The Number of Missions of the Buccaneer CubeSat is 2.


The Objectives of the MAESTRO Instrument is Measuring ozone, nitrogen dioxide and aerosol/cloud extinction in the atmosphere.


The Image Capture Time of the EUI Instrument is More than four hours.


The Optical Power of the Temperature-and-current-stabilized LD Laser Diode is Unknown.


The Response Time of the System SAR is Less than 36 hours.


The Ascent-Back ΔV of the Hayabusa-2 Spacecraft is 0.64 m/s.


The Observation Duration of the BRITE satellites Satellite is 15 minutes.


The URL of the NASA Orbiting Carbon Observatory-2 Satellite is http://meetingorganizer.copernicus.org/EGU2015/EGU2015-6804.pdf.


The Development Location of the Grating Reflection Unit Spectrometer Component is Fraunhofer IOF (Institute of Applied Optics and Precision Engineering), Jena, Germany.


The Resolution of the Spacecraft Module Satellite Module is Eight-times greater than any previous X-ray telescope.


The Wavelength FWHM of an unresolved line of the Spectrometer Instrument is 0.126 µm.


The Noise Performance of the CCD Camera Imaging System is SNR <= 128 at 100% albedo.


The Wavelength of the Radio Waves Phenomenon is Decameter.


The Prime Contractor of the Galileo 2nd Generation Satellites Satellite is Thales Alenia Space in Italy.


The Swath of the Satellite Satellite is 55 km.


The Inclination of the NanoRacks-QB50 CubeSats Satellite is 51.6º.


The Data Uplink Bands of the SDR (Software Defined Radio) Communication Device is USB (Universal S-Band) and SGLS (Space Ground Link System, L-band).


The Repetition Cycle of the WiFS camera Camera is 5 days.


The Control Center Location of the Odin Satellite is Esrange.


The Quantity of the OSL Dosimeter Dosimeter is 1.


The Number of Satellites of the Lightspeed Satellite Constellation is 198.


The Knowledge of the PARASOL microsatellite Satellite is 0.02º.


The First Light Images Date of the Landsat-9 Satellite is October 31.


The Antenna Baseline of the KaRIn Radar is 10 m.


The Launch Date of the SpaceX CRS-25 Dragon Spacecraft is 24 May 2022.


The Communication Approach of the CAN Bus Data Communication is Wait-on-send.


The Function of the Shutter Calibration System Component is Oscillates in synchronization with the scan mirror and crosses the optical axis at the end of each scan.


The Measurement Range of the SEI Electron Imager is 2-200 eV electrons or ions.


The Laser Transmitter of the Aeolus satellite Satellite is World's first.


The Conference Presentation of the CSG SAR instrument Synthetic Aperture Radar is EUSAR 2016, 11th European Conference on Synthetic Aperture Radar, Hamburg, Germany, June 6-9, 2016.


The Launch Year of the TecSAR Satellite is 2008.


The Acquisitions per Day of the SAOCOM-1A Satellite is 225.


The Shape of the Procellarum Lunar Region is Rectangular.


The Precision Formation Flight of the CanX-4 & CanX-5 Nanosatellites is Demonstrated.


The Structure Shape of the UniSat-5 Satellite is Cuboid.


The Solar Array Normal Vector and Sun Vector Difference of the Spacecraft Satellite is Up to 40 degrees during the first two years of operations.


The Analyzer of Particles and Electric Fields Mass of the Microsatellite Satellite is 0.8 kg.


The Operational Modes of the TechEdSat Satellite is Basic operation and computationally demanding payloads.


The References of the GeoSTAR-III Satellite System is Observation of the Earth and Its Environment: Survey of Missions and Sensors.


The Distance of X-ray jet from the Manatee’s head of the XMM-Newton X-ray Observatory is About 100 light years.


The Wavelength of the SAR antenna Antenna is ~ 10 cm.


The Timing Time Resolution of the CCD Image Sensor is ~10 -3 seconds.


The Manufacturer of the IXV Recorder Recorder is Curtiss Wright.


The Frequency of the X-band Communication Band is 8.320, 8.064 or 8.192 GHz.


The Purpose of the Roman Satellite is Make similar measurements of stars in both the Milky Way and other galaxies.


The Daily Image Acquisitions of the Pleiades-1A Satellite is Approximately 1300.


The Orbit Altitude of the NMS Neutral Mass Spectrometer is 300-400 km.


The Type of the S-193 Radar System is Spaceborne Ku-band scatterometer.


The Wavelengths of the EPIC Instrument is 10.


The Standard Interface of the CEASE-1 Instrument is RS-422 or MIL-STD-1553B.


The Observation Wavelengths of the Herschel Telescope is Far-infrared and sub-millimeter.


The URL (presentation) of the Cute-1.7+APD Nano-Satellite is http://lss.mes.titech.ac.jp/ssp/cute1.7/paper/aca2007_p.pdf.


The Closest Pass Distance to the Sun of the Solar Orbiter Satellite is 0.32 au.


The Precision of Ozone Density Profile Determination of the ERIP Earth Remote-Sensing Imaging Package is 10-15%.


The Data Output of the Mid-IR Imagers Camera is PAL format (384 H x 288 V pixels).


The Bus Calibration and Validation Duration of the TeLEOS-1 Satellite is Two weeks.


The First Light Date of the CaSSIS Imaging System is Unknown.


The FPGA of the SCU Satellite Central Unit is XQ2V1000-4FG456N (Virtex2).


The Function of the Kazachok Lander Platform is Remain stationary to investigate the climate, atmosphere, radiation and possible presence of subsurface water.


The Presentation Location of the TanDEM-X Satellite is Fort Worth, Texas, USA.


The Wavelength of the SWIR Short Wave Infrared region is 0.1 µm.


The Paper Number of the ERG Satellite Satellite is 2011-r-50.


The Contractor of the M3MSat Satellite is COM DEV International Ltd..


The Duplex of the RF Communications Communication System is Half.


The Operation Duration of the nanoRTUTM Safe Mode Computer is Six months.


The Number of Computer Consoles of the Control Room Facility is 9.


The Spatial Resolution of the Global DEMs Digital Elevation Models is About 30 m.


The Prime Contractor of the QZS-1 Satellite is MELCO (Mitsubishi Electric Corporation) Kamakura Works, Kamakura-City, Japan.


The Power Generation Anomaly Date of the DAICHI (ALOS) Satellite is April 22, 2011.


The Typical Value of the SO2 Satellite Instrument is 10.


The Mission Objective of the New Horizons Spacecraft is Explore Pluto and its system of moons.


The Components of the JEM Module is Pressurized Module (JEM-PM), Exposed Facility (JEM-EF), Experiment Logistics Module-Pressurized Section (ELM-PS), Experiment Logistics Module-Exposed Section (ELM-ES), Remote Manipulator System (JEM-RMS), Inter-orbit Communication System (JEM-ICS).


The Total mass of assembly of the STRV-2 DHS Data Handling System is 2 kg.


The Operator of the Arktika-M N1 Satellite is ROSCOSMOS.


The Swath Width of the Sentinel-5P Satellite is 2600 km.


The AOCS Mode of the TTTC Satellite System is Precise mode.


The Function of the Resistojets Propulsion System is The gas is forced to spiral down the resistojet to increase the travel path and thus the heat transfer.


The Hardware Changes of the Satellite Satellite is Addition of a bolt-hole pattern and two ruggedized connectors.


The Swath Width of the WFC CCD Camera is 61 km.


The ISS of the EUVI Extreme Ultraviolet Imager is Included.


The Aviation Market Growth of the India Country is Sustained double-digit growth for the last 50 months.


The Control Strategy of the Passive Attitude Control System Attitude Control System is Robust, simple.


The Type of the Test Facility Testing Equipment is Vertical test facility.


The Power Generation of the Spacecraft Satellite is 5.2 kW.


The Data Availability of the ATMS Instrument is Within 180 minutes of observation.


The Sample Image Locations of the NovaSAR-1 Satellite is Cebu city and the nearby Mactan-Cebu International Airport, Masbate Island in the Bicol region of the Philippines.


The Operational Phase End Date of the HyperScout® Satellite is 2018.


The Power Amplifier of the Ka-band Signal is 2.2 W.


The Downlink Data Rates of the NEMO-AM Satellite is 32kbit/s to 2Mbit/s.


The Founder of the Kleos Space Company is Luxembourg government.


The Spectral Sampling Distance of the UV-2 Spectrometer is 0.15 nm.


The Stabilization of the ALTIUS Satellite is Three-axis.


The Boulder Width of the Tycho central peak Lunar Feature is Over 100 m.


The AstroTube Boom of the AlSat Nano Satellite is Deployed and stowed multiple times, including full 1.5 m length.


The Imaging Frequency Band of the RADARSAT-1 Satellite is C.


The Affiliation of the Santiago Urueña Engineer is Unknown.


The Brochure Release Year of the OceanSat-2 Satellite is 2007.


The Operational Date of the Ikonos-2 Satellite is December 1999.


The Scientific Sensors of the SAMPEX Satellite is 4.


The Purpose of the PIMS Plasma Instrument is Measure the plasmas in Europa's ionosphere and Jupiter's magnetosphere.


The Location of the Euclid Consortium Organization is Institut de Ciències de L’Espai (ICE, IEEC-CSIC) and Port d’Informació Científica (PIC) in Barcelona.


The Orbit of the HaloSat Satellite is 93-minute orbit around Earth.


The Mirror Module Assemblies Presentation Date of the IXPE Satellite is 2019.


The Constellation Type of the ICEYE Satellite Constellation is Synthetic-aperture radar (SAR).


The Resolving Power of the Instrument Spectrometer is 10,000.


The Launch Date of the Galaxy Spacecraft is Late 2008.


The Data Download of the STRaND-1 Satellite is 372 kB in 5 weeks and 1 day.


The Digital Recorder Dump Rate of the X-band Communication Band is 61.44 Mbit/s.


The Measurement of the SMAP Satellite is Land and ocean measurements.


The Swath Width of the WiFS camera Camera is 810 km.


The Swath Width of the ERIP Earth Remote-Sensing Imaging Package is 170 km.


The Data Return of the LIRIS Laser Infrared Imaging Sensors is September 2014.


The Purpose of the Aeolus Satellite is Measure wind from space.


The Number of Unmanned Global Ground Stations of the C3S Command, Control and Communications Segment is 15.


The Creation Method of the 3D Model of the Asteroid Model is Inferred the shape based on multiple photo angles.


The Orbit of the TEMPO Instrument is Geostationary orbit.


The Workshop Date of the Herschel Satellite is Dec. 17-18, 2009.


The Mission URL of the GRACE Satellite is https://www.nasa.gov/feature/jpl/wet-winters-may-not-dampen-small-wildfires.


The Bandpass of the Telescope Optical Instrument is 540–590 nm.


The Splashdown Date of the Crew Dragon spacecraft Spacecraft is Sept. 18, 2021.


The Service of the Spire Global UK Company is Track the identity, position, course and speed of each vessel.


The Signal Modulation Causes of the IMAP Satellite is 1) the small inclination of the ISN gas inflow direction to ecliptic 2) due to the latitudinal structure of solar wind flux (Ly-α) and the solar wind electron density and temperature (He 58.4).


The Power of the Spacecraft Satellite is 1.75 kW (EOL).


The Temperature Range of the ExoMars Analytical Laboratory Drawer Laboratory Drawer is -120°C to -60°C.


The Antenna Mounting Plane Dimensions of the KySat-1 Satellite is Maximum 10 x 10 x 10cm.


The Solar Environment of the Electric Field Antennas Sensor is More severe than all previous experience.


The Launch Date of the DeMi Satellite is 15 February 2020.


The RF Trunkline of the LCRD Satellite Communication System is High data rate.


The Location of the CDN2 Site Ground Station is 35° 20.729' N, 23° 46.577'E.


The Design Life of the Resurs-DK1 Spacecraft is 3 years.


The Gd Electron Energies of the LND Particle Telescope is 29, 72, 78, and 132 keV.


The Size Comparison to Milky Way of the Leo I Galaxy is 30 times smaller.


The Partnership of the Webb Space Observatory is European Space Agency ESA, US space agency NASA, and the Canadian Space Agency CSA.


The Energy Range of the Satellite Imaging Instrument is Hard X-ray.


The Capacity of the MUSES Platform is Up to four Earth observation instruments.


The Data Quantization of the Instrument Spectrometer is 10 bit (VIS); 12 bit (NIR).


The Inclination of the QuakeSat Satellite is 98.73º.


The Bus Type of the NigeriaSat-2 Satellite is SSTL-300.


The Livestream Date of the InSight Seismic Experiment for Interior Structure (SEIS) is July 23.


The PPTs Max Current of the EPS Electrical Power Subsystem is 2.5 A.


The Angular Resolution of the XRT X-Ray Telescope is Improved.


The Incidence at the ground about of the S-193 Altitude is 35º.


The Wavelength Range of the VNIR Detector is 0.45 - 0.905 μm.


The Propulsion Efficiency of the DRACO Demonstration Rocket is Two to five times the efficiency of chemical propulsion.


The Conference Presentation of the Lunar Laser Communication Demonstration Communication System is Unknown.


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


The Temporal Matchup Window of the CYGNSS Satellite is 3 hours.


The Implementation of the Sentinel Asia Pilot Project is First Step.


The Quote of the ESA's Director of Earth Observation Programs Director is "In the public sector, the use of observed data on methane emissions instead of untested assumptions on methane intensity, will improve the accuracy of annual inventories of greenhouse emissions. For governments and regulators, this technology will enable.


The Presentation Date of the Quasi Zenith Satellite Bus System Satellite Bus System is June 1-8, 2008.


The Observation Time of the Tri-TIP Instrument is Night-side portion of the orbit.


The Components of the Radiometric Calibration Calibration is Radiance Calibration Coefficients, Response Linearity, Noise, Detector PRNU, Detector DSNU.


The Dark Calibration of the ICU Internal Calibration Unit is Implemented by means of a lightweight shutter placed in front of the optical slit.


The Mass of the Payload Satellite Component is 100 kg.


The Bandwidth of the Crystal Filter Signal Processing Component is 3 kHz.


The Bandwidth (GHz) of the ICI-1 Radiometer is 6.


The Presentation Date of the BepiColombo Mission is Feb. 28-March 4, 2011.


The Orbital Lifetime of the KE-2M satellite Satellite is Approximately six months.


The Interface Types of the SGR-ReSI Interface Unit is CAN, RS422, SpaceWire.


The Data Processing of the CartoSat-1 Satellite is Advanced.


The Orbit of the IRNSS-1C Satellite is GTO and then raised into GEO.


The Capacity of the Data Storage System is Flash memory 8 Mbit x 2 (redundancy).


The Attitude Determination and Control System Performance of the Claire Satellite is Exceeded specifications.


The Band of the Telemetry Data Data Transmission is X-band.


The Wave Height of the STEREO spacecraft Satellite is 100,000 km.


The Deployment Method of the Tether Spacecraft Component is Rolled up and housed within the end mass of the EDT system.


The Designer of the Driver IC Component is Brazilian software house located on the campus of UFSM (Federal University of Santa Maria).


The Photon Energy Spectrum of the PSR B0531+21 Pulsar is 0.5-5 keV.


The Size of the Assembly Satellite Component is 310 mm x 200 mm x 480 mm.


The Instrument of the Sentinel-1 Satellite is Imaging microwave radar.


The Average Power of the Solar Cell Assemblies Power Source is ~1.5 W.


The Data Quantization of the Scanning geometry Instrument is 10 bit.


The Along-Track Resolution of the SIRAL Radar is 250 m.


The Study Duration of the Exoplanets Celestial Bodies is More than 27 months.


The Final Image Distance of the Rosetta Spacecraft is 24 meters.


The Data Point Interval of the GEOSAT Satellite is 6.7 km.


The Experience of the Keith Masback Individual is Over 30 years.


The Collection Area of the CUTE Telescope is 20 cm x 8.5 cm.


The Primary Science Objectives of the Solar-A / Yohkoh Satellite is 1) to further the understanding of the magnetofluid dynamics of the repeated expansion of the solar corona, 2) clarification of the changes in the shape of the solar corona, and 3) the study of the mechanism underlying the occurrence of plasma disturbance.


The Bus Impedance of the SBVR Power Supply is <100 kHz.


The Typical Value of the O3 Profile Satellite Instrument is 40, 50, 8 x 10 3.


The Service Start Date of the Lightspeed Satellites Satellite is 2023.


The Transport Layer Protocols of the IXV Communications Network Network is TCP and UDP.


The Size of the SPATIUM-I CubeSat is 2U.


The CPU of the SHU Science Handling Unit is HD64F7145FW50.


The Number of X-ray Sky Fields Observed of the HaloSat Satellite is 334.


The Planned Improvement of the Radio Subsystem Satellite Subsystem is Adapting the waveform for better channel capacity utilization.


The Target Launch Date of the MMO Spacecraft is JFY 2016.


The Sensitivity (Infrared Channel) of the VIRR Instrument is 4 K with a scene at 185 K, 1 K with a scene at 300 K.


The Type of the Second FPGA FPGA is Co-processor.


The Publication Date of the Experimental Satellite System for Earth Monitoring Satellite System is 1981.


The Resolution of the Magnetic Field Sensor Magnetoresistive Sensor is 100 pT.


The Type of the Space Micro µSTDN S-band Transponder is Digitally intensive.


The Design Cycle of the SpooQySat Satellite is Shorter development cycle.


The Time to be Pulled towards the Black Hole of the Earth-sized clump of matter Unknown is About a day.


The Step 1 Operation of the TRUTHS Satellite is LDs illuminate (underfill) first the CSAR cavity and then the transfer radiometer (TR).


The Predecessor of the PPS-1350-G Hall-effect thruster is SPT-100 (Stationary Plasma Thruster).


The Inclination of the Orbit Satellite is 98.28º.


The Observation Mode Switching of the OCO-2 Satellite is Alternate 16-day global ground-track repeat cycles.


The Polarization Measurements of the GOME-2 Satellite Instrument is Advanced.


The Resolution of the CAVIS Imager is 30 m.


The Date of the Dynamic Dunes Phenomenon is 15 March, 2021.


The Power Generation of the MTM Transfer Module is More than 11 kW.


The Handled Products of the Mission Operation System Data Processing System is Approximately 1 TB/day.


The Improved by of the Electron Temperature Probe Instrument is K. Oyama.


The Pointing Control of the Attitude System Satellite System is One arc-minute.


The Responsivity Measurement of the Responsivity Measurement Instrument is 1.36 A/W.


The Memory Capacity of the SLIM6 Satellite is 2 x 2 GByte.


The Measurement Domain of the SkySat Constellation Satellite Constellation is Ocean, Land.


The Vacuum Test Completion Date of the Prichal Module is October 28.


The Purpose of the TIRS Sensor is Identify clouds and focus on the real land surface.


The Solar Array Type of the UK-DMC-2 Satellite is GaAs/Ge single-junction solar cells.


The Platform of the SAR spacecraft Satellite is CAST-2000 bus with necessary modifications and upgrades.


The Type of the FIREBIRD-2 A and B Payload is Focused Investigations of Relativistic Electron Burst Intensity, Range, and Dynamics.


The Observation Frequency of the EPIC instrument Instrument is About 13 times per day.


The Image and Video Capture of the DoT-1 Satellite is Managed by Raspberry PI Camera.


The Antenna Thickness of the Subarray Array is 9 mm.


The Conference Date of the Earth Observation Constellation Satellites Satellite Constellation is 14-16 May 2013.


The Purpose of the Lunar Flashlight CubeSat is Detect naturally occurring surface ice believed to be at the bottom of craters on the Moon.


The Temperature at Closest Approach to the Sun of the Heat Shield Parker Solar Probe Component is Nearly 2,500 degrees Fahrenheit (1370 ºC).


The Orbit Inclination of the STARS spacecraft Satellite is 98.06º.


The Energy Gain of the InSight Mars lander Spacecraft is About 30 watt-hours per sol.


The Orbit of the STPSat-3 Satellite is Near-circular orbit.


The Flight Heritage of the Passive Attitude Control System Attitude Control System is Extensive.


The Number of Channels of the Dual-channel Receiver Unit (DRU) Receiver is 2.


The Mirror Oscillation Frequency of the TIR Subsystem Imaging System is About 7 Hz.


The Rate of the Material Release Rate Volcanic Activity is One ton per second.


The Nominal Mode Data Rates of the LunaH-Map Satellite is 1 kbit/s to 128 kbit/s.


The Wave Height of the Satellite Satellite is 0.5 m to 20 m.


The Launch Date of the OceanSat-1 Satellite is May, 26, 1999.


The Release Date of the Giant solar flare Solar Event is Sept. 15, 2014.


The Delivery Date of the IASI-NG Instrument is Early 2022.


The Designer and Builder of the IRIS Imager Camera is SI (Satrec Initiative Co. Ltd.) of Daejeon, Korea.


The PAN-A of the CartoSat-1 Satellite is Panchromatic Aft-pointing Camera.


The GSD (Panchromatic) of the EOS Camera is 1 m.


The Operator of the MSG-3 Satellite is Hughes Network Systems.


The Mean LTAN of the KOMPSAT-3 Satellite is 13:30 hours.


The Internal Water Evidence Date of the Moon Celestial Body is August 27, 2013.


The Spectral Sensitivity of the SXI Spacecraft is 6 to 20 Å.


The Building Exterior Temperature of the ECOSTRESS Instrument is A few degrees cooler than paved surfaces.


The Swath of the Interferometric Wide Swath mode (IWS) Operational Mode is 240 km.


The Unknown of the Atomic Clock Timekeeping Device is Unknown.


The Mission Overview of the Sentinel-3 Satellite is Unknown.


The Efficiency of the Solar Array Regulator Regulator is 94%.


The Efficiency of the DC-DC converter Power Converter is Greater than 85% across load range of 75% to 100%.


The PRN of the GSAT-0209 Satellite is 9.


The Launch Date of the MetOp-A Satellite is Oct. 19, 2006.


The Field of View of the Herschel Space Observatory is Little more than two times the width of the full Moon.


The SAR antenna of the Payload Satellite Payload is Nominal operations.


The Operation Start Date of the LRO Satellite is 2009.


The Instrument Type of the ISS-RapidScat Instrument is Scatterometers.


The Mission Type of the Solar-B / Hinode Satellite is Non-EO.


The Launch Dates of the Sentinel-2 Satellite is 23 June 2015 (Sentinel-2A), end of 2016 (Sentinel-2B).


The Launch Date of the Buccaneer CubeSat is 18 November 2017.


The Number of Stars of the Upper Scorpius Star Cluster is 83.


The Requirement of the Monitoring and shutdown system Power Protection is Detect and shutdown any power line which has encountered a fault.


The Sensors of the ADCS Attitude Determination and Control Subsystem is Magnetometers and gyroscopes.


The Mission Duration of the Sentinel-2 Satellite is 20 years.


The Launch Date of the QB50-ISS CubeSats Satellite is Dec. 9, 2016.


The Contact Check Frequency of the CSpOC Space Operations Center is Daily.


The Resolution of the IRMSS Instrument is 150 m.


The Sensitivity of the LEND Neutron Detector is 100 ppm or better.


The Mission Type of the PAZ Satellite is Dual use (civil/defense).


The Modulation Type of the High-rate Modulation Communication System is 4 Mbit/s with DQPSK modulation.


The Size of the Spacecraft Satellite is 100 mm x 100 mm x 227 mm.


The Polarization Angle of the Band 5 Spectral Band is 0/60/120 º.


The Position of the SASI-600 Shortwave Infrared Airborne Spectrographic Imager is Right-hand port.


The Function of the TES Satellite Instrument is Collecting measurements of ozone's greenhouse effect.


The Communication Protocol of the Nanosatellite Satellite is FMCW.


The Data Use of the PROBA-V Satellite is Global vegetation data for operational and scientific use.


The Launch Date of the H-II Transfer Vehicle "KOUNOTORI3" (HTV3) Cargo Craft is July 20, 2012.


The Acquisition Range of the Guider Instrument is 1.2º.


The Range of the AeroCube-OCSD-B and -C Satellites is Unknown.


The Mass of the GeoCarb Instrument is 138 kg.


The Frequency Range of the Magnetic Field Measurement System Instrument is 20 Hz - 1 kHz.


The Absolute Radiometric Accuracy of the Hyperion Imaging Spectrometer is <6% (1σ).


The Operation of the NICER Satellite is Space Station Twist.


The Downlink Frequency of the S-band Frequency Band is 2.402 GHz.


The Member of the Richard Miller Individual is True.


The ILS Spectral Resolution of the Instrument Spectrometer is ≤11 nm, ≤16 nm.


The Energy Range of the ELENA Sensor is <0.02-5 keV.


The Attitude Control of the ADCS unit Satellite Component is Satellite detumbling.


The Signal Conversion of the MEV Electronics Module is 12 bit.


The Downlink Frequency Band of the Svalbard Ground Station Ground Station is S-band.


The Operations Concept of the OPS-SAT Satellite is Transition from supporting educational missions to supporting operational ones.


The Launch Date of the Ax-1 mission Mission is No earlier than January 2022.


The Data Set of the RAVAN Satellite is Episodic.


The Navigation Capability of the SEXTANT Technology Demonstration is GPS-like navigation.


The Launch Date of the WorldView-3 Satellite is August 13, 2014.


The Tracking Passes Occurrence of the CAPSTONE Satellite is When nearer to periapse.


The Backup Laser Activation Date of the CALIPSO Satellite is March 12, 2009.


The Flatness Target of the Euclid Spacecraft is 0.05 mm.


The Technical Problems of the Nauka Module is Several.


The Expected Location of Strongest Magnetic Field of the Sunspot Solar Phenomenon is In the dark part of the umbra.


The Size of the Eagle-1 (BeakerSat) FemtoSat is 1.5U.


The Function of the GPS Receiver Receiver is Provide ECEF position and velocity solutions to GNC SW.


The Measurement Domain of the Myriade/AstroSat-100 Satellite is Atmosphere, Gravity and Magnetic Fields.


The Production Dependency of the Neutrons Radiation is Variable high-energy charged particle fluxes and properties of the upper atmosphere.


The Mission Goal of the OICETS Satellite is Conduct interorbit laser communications experiments with ARTEMIS of ESA.


The COVP of the Propulsion Subsystem Propulsion System is 1.


The Effective FOV of the Channel 4 Sensor is 35 km x 76 km.


The Primary Objective of the SDA Agency is Speed.


The Field of Regard of the RISAT-2 Satellite is Wide.


The Image Capture Date of the LRO Satellite is Jan. 29, 2014.


The Departure Date from Bennu of the OSIRIS-REx Spacecraft is May 10.


The Cross-Track Swath of the OMPS Nadir Profile Spectrometer Spectrometer is 250 km.


The Volume of the The Astronomical Journal Journal is 155.


The Frequency of the Radar Radar is 9.6 GHz.


The Typical high cadence of the HRI dual EUV 174 Å and 335 Å alternatively Passband center is 2 s.


The Mass of the BIROS Minisatellite is Roughly 130 kg.


The Construction Time of the Nanosatellite Tracking Ships Nanosatellite is Seven Months.


The Focal Length of the Pushbroom imager Optics is 5131 mm.


The Publication Year of the WMO World Meteorological Organization is 2016.


The Altitude of the Satellite HY-1B is 798 km.


The Orbit of the NorSat-3 Satellite is 550-650 km sun synchronous.


The Schematic of the Hayabusa and Hayabusa-2 Missions is Figure 3.


The Instrument of the CryoSat Satellite is Radar altimeter.


The Mission Purpose of the Heinrich Hertz satellite Communication Satellite is Test the behavior of new technologies under extreme conditions in space.


The Proposed Doubleheader Launch Date of the Falcon 9 Rocket is February 4.


The Program Start of the SIR-C/X-SAR Payload is SIR-B in l984.


The Antenna Diameter of the Ground Segment Satellite Ground Segment is As small as 2.4 m.


The Dimensions of the Kubik Miniaturized Laboratory is 40 cm cube.


The Average Power of the S/C Power Satellite Power System is 171 W.


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


The Orbit Inclination of the ResourceSat-2A Satellite is 98.78º.


The Closest Approach to Sun's Surface in 2021 of the Solar Orbiter Satellite is More than 20 million km.


The CMOS Image Sensor Data Retrieval of the Imager Payload is Field gate programmable array with 32 MB RAM.


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


The Mission Launch Year of the IMAP Interstellar Mapping and Acceleration Probe is 2024.


The Telescope Image Cadence of the EUVI Extreme Ultraviolet Imager is Higher image cadence.


The Objective of the RUBI Fluid Science Experiment is Investigate the fundamentals of boiling fluids in microgravity.


The Design Life of the Spacecraft Satellite is 5 years.


The Launch Date of the GEOS-1 Satellite is Nov. 6, 1965.


The | of the SGR-ReSI GNSS Receiver is Remote Sensing Using GPS Signals – The SGR-ReSI Instrument.


The Services of the MSS Mobile Serving System is Power, video and data transfer functions, robotic manipulation.


The Onboard Memory of the COSMO-SkyMed-1 Satellite is 300 Gbit.


The Diameter of the Kepler-438b Exoplanet is Less than 1.5 times the diameter of Earth.


The Sensor Operating Temperature Range of the FIPEX Instrument is 600-700ºC.


The Spectral Range of the AaSI Spectral Imager is Visible.


The Frequency of the Uplink Signal is 749f0.


The Slit 1 Spectral Range of the MEGS-A Spectrograph is 5-20 nm.


The Conference Presentation Date of the CDHS Nanosatellite is Oct. 2-6, 2006.


The Ground Station of the ARTEMIS Satellite is UHF tactical communications ground station.


The Image Capture Date of the TopSat Satellite is Unknown.


The Provider of the Two-frequency GPS (NOX) GPS is DLR/GSOC.


The Battery Support for Nominal Operations of the RapidEye Satellite Constellation is After 2020.


The Food Consumption of the Desert Locusts Insect is Same amount of food in one day as about 35,000 people.


The Number of CubeSats of the QB50 Project Satellite Constellation is 50.


The Inclination of the Satellite Constellation Satellite Constellation is 105.6º.


The Peak Quantum Efficiency of the Image Sensor Imaging is 50%.


The Magnetic Field Strength of the Pulsar Celestial Object is 70 quadrillion times stronger than that of Earth.


The Output Voltage (Nominal) of the LVPS Board Power Supply is +3.3 V.


The Image Recording Capability of the SAR Antenna Antenna is All weather conditions, both during the day and the night.


The Safe Mode Entry Date of the InSight Mars Lander is 11 January 2022.


The Launch Date of the CAPSTONE Satellite is June 28, 2022.


The Edition of the Tethers In Space Handbook Handbook is Third.


The Inclina. (º) of the Meteor-3-1 Satellite is 82.5.


The specification of the Bus Satellite Component is  MethaneSAT.


The | of the J. F. Carbary, D. Morrison, G. J. Romick, J.-H. Yee Authors is J. F. Carbary, D. Morrison, G. J. Romick, J.-H. Yee.


The Frequency of the RF communication subsystem Communication Subsystem is 435.325 MHz/145.95 MHz.


The Size of the Bus Structure Satellite Component is ~2 m x 0.8 m in diameter.


The Communication Protocol of the UHF/VHF data frame Data Frame is AX.25.


The URL of the ExoMars Mars Orbiter is http://www.jpl.nasa.gov/news/news.php?feature=6663&utm_source=iContact&.


The Number of Boards of the OBC On-Board Computer is 4.


The Inclination of the FormoSat-3/COSMIC-1 Satellite Constellation is 72º.


The Height of the Resurs-DK1 Spacecraft is 7.4 m.


The Resolution of the JWST MIRI Detector Array is 1024 x 1024.


The Boresight Look Angle of the KaRIn Instrument is ±2.7º.


The Launch Mass of the ALOS-3 Satellite is 2120 kg.


The Mission Update Date of the GovSat-1 Satellite is 31 Jan. 2018.


The Cadence of the Housekeeping Measurement is 1 minute.


The Publication Date of the Blue Ring Nebula Nebula is Nov. 18.


The Solar Calibration Frequency of the Satellite Imaging Satellite is Roughly weekly.


The House-keeping (HK) Data of the Control Units Satellite Component is Voltage, current, and temperature.


The Insulation Purpose of the BepiColombo Spacecraft is Protect the spacecraft from extreme thermal conditions.


The Agility Performance of the CSG System Satellite System is Very high.


The Attitude Control of the QSat Satellite is 3-axis stabilization by using RWs (nominal), magnetorquers (detumbling).


The Control of the ERA Robotic Arm is Can be controlled from both inside and outside the Space Station.


The Number of Satellites of the Galileo Constellation Satellite Constellation is 24.


The Accuracy of the VISION Instrument is 5%.


The Peak Energy Deposition Separation of the Solar SXR Spectra Solar Phenomenon is About 5 km.


The Type of the Optical Scanning Design Imaging Spectrometer is Pushbroom.


The Re-entry Module Verification of the Chang'e-5 Lunar Mission is Aerodynamic design, heat-resistant materials, flight control system.


The Bus Components of the Jason-2 Satellite is Altimeter and the DORIS receiver.


The Touchdown Time of the Philae Lander is 17:25 GMT.


The Width of the Pas Moraine Moraine is Up to 12 miles (20 km).


The Characterization of the OCO-2 Satellite is Before Observatory launch.


The Radio Signals of the Hitomi Satellite is 3/27 01:23~01:27 (for 4 min) @USC, 01:21~01:27 (for 6 min) @ KTU.


The Latency of the ATL10 Arctic/Antarctic Sea Ice Freeboard Data is 45 days.


The Docking Date of the HTV-1 Spacecraft is Unknown.


The Detector Type of the MM Radiometer Sensor is Schottky diode detectors.


The Operational Date of the TerraSAR-X Satellite is January 2011.


The Unique Capability of the HPCA Electrostatic Analyzer is Uses radio frequency oscillations to sweep the majority of solar wind protons away from the detector, without affecting the magnetospheric oxygen.


The Altitude of the SCI Spacecraft is Approximately 500 m.


The X-Ray Jet of the M87 Black Hole is Superluminal Motion.


The Developer of the Venta-1 Nanosatellite is Bremen University of Applied Sciences.


The Automation Flexibility of the VMOC Mission Operations Center is Full automation to complete manual scheduling.


The Extended Mission Start Date of the SELENE/Kaguya Satellite is November 2008.


The Number of Members of the OSCAR-QUBE Team is 15 students.


The Deployment Mechanism of the IXPE observatory X-ray Observatory is Deployable boom.


The Unknown of the NASA/JPL Organization is Unknown.


The Orbit Period of the ERBS Satellite is 96.8 min.


The Launch Date of the Earth-Observation Satellite Satellite is Nov. 6, 2010.


The Concentration Range of the DN probe Neutral Particle Probe is 10^5 - 10^12 cm^-3.


The 3-D Structure Mode of the Tandem-L Satellite is Fully-polarimetric SAR interferometry.


The Power of the Pushbroom Imager Imaging Device is 250 W.


The URL of the EO-1 Satellite is http://ase.jpl.nasa.gov/public/papers/chien_aamas2005_lessons.pdf.


The Mass of the VIRR Instrument is 8.1 kg.


The Frequency Band of the S-band radio frequency Communication is S-band.


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


The Observation Duration of the Cal_doppler Observation Instrument is One entire day side of the orbit.


The Operation Duration of the Yutu 2 Lunar Rover is 321 Earth days.


The Structure Size of the PARASOL microsatellite Satellite is 60 cm x 60 cm x 80 cm.


The Mission Success Confirmation Date of the GIOVE-A Satellite is April 2, 2008.


The Number of Reflectors of the RRA Retroreflector Array is 264.


The Average Power Consumption of the Instrument Sensor is 11 W.


The Comparison of the Variant Satellite is DEMETER mission.


The BSL Entry of the MCU Microcontroller Unit is Provides BSL (BootStrap Loader) entry for payload and EPS.


The Control Capability of the Attitude Control System Satellite Subsystem is Two axes at any given time.


The Publication Date of the LARES satellite Satellite is December 2017.


The Manufacturer of the Star Tracker Attitude Determination Device is Sodern.


The Staffing of the On-call Operations Operations is Initially 24/7, eventually reduced to 8 hours on weekdays.


The Error Detection and Correction Scheme of the SSR Solid State Recorder is EDAC (Error Detection and Correction).


The AIV Completion Date of the IOD CubeSat Satellite is June 2017.


The Data Retrieval of the LIRIS Laser Infrared Imaging Sensors is 29 August.


The Memory of the Onboard Computer Computer is 1 GB.


The Mass of the Cospas-Sarsat search and rescue package Device is 8 kg.


The Output Voltage Behavior of the OPS systems Sensor is Decreases for distances smaller than 10 mm.


The Performance of the FSS Instrument is ±0.35º.


The Orbit Inclination of the CHORUS Satellite is 53.5°.


The Attitude Control of the JL-1-GF03D Microsatellite is 3-axis, 4 flywheels.


The Mission of the SOTA Small Optical Transponder is SOCRATES (Space Optical Communications Research Advanced Technology Satellite) microsatellite mission of NICT.


The FOV of the HRI Lyman-α 1216 Å Passband center is 1000 arcsec x 1000 arcsec.


The Spectral Range of the O2 A-band channel Spectrometer is 0.758 to 0.772 µm.


The ADCS System of the DeorbitSail Satellite is Orientation Suitable for Sail Deployment.


The Center Frequency (GHz) of the Antenna Reflector is 6.6.


The Field of View of the FSS Fine Sun Sensor is ±32º.


The Sub-Experiments of the EuTEF European Technology Exposure Facility is DEBIE-2, DOSTEL, EuTEMP, EVC, EXPOSE, FIPEX, MEDET, PLEGPAY, TriboLab.


The Provider of the Next generation solar cells / Astrium Solar Cells is EADS Astrium GmbH.


The Digital Data Handling Subsystem Power Consumption of the SIR-C Phased Array is 800 W.


The Technique Developer of the Solar Flare Solar Event is Francoise Roddier.


The Duration of Proximity of the DICE nanosatellites Satellite is Up to six months.


The Volume Efficiency of the Reflectarray Antenna Antenna is Leaves plenty of room for payloads such as science instruments or imaging systems.


The Remote Operation of the TUC Transponder Microwave Transponder is Yes.


The Instrument Type of the CryoSat Satellite is Precision orbit, Radar altimeters.


The Variant of the Lunar Photon Spacecraft is High energy.


The Mass of the Phoka-D Instrument is 3 kg.


The Distance Measurement Accuracy of the Laser Altimeter (LIDAR) Altimeter is Several hundred meters.


The Sensor Type of the FIPEX Instrument is Solid oxide electrolyte micro-sensors.


The Power Consumption of the SOLSPC Radiometer is 32 W.


The Start Year of the MDPP-2 Program is 2000.


The Configuration of the FPGAs Electronic Components is Columnized FPGAs.


The Date of the North Pole Observations Observation is 23 and 24 April 1994.


The Capability of the Unseenlabs’ maritime monitoring system Satellite System is Monitor three different areas of interest simultaneously.


The Antenna Configuration of the Satellite Satellite is Two nadir antennas.


The Age of Rocks in Landing Zone of the Chang’e-5 Lunar Lander is Much younger than those returned by the Apollo astronauts.


The Battery Charging Voltage Range of the SABR DC/DC Converter is 5-34 V.


The Average Stationkeeping Cost of the ISEE-3 Spacecraft is 8.5 m/s per year.


The Area of the RESTEC Distributor is Asia and Russian area.


The Effect of the Moonlight Lunar Telecommunications and Navigation Satellite Network is Lowering the ticket price to lunar exploration.


The Operation End Date of the Midcourse Space Experiment Satellite is July 22, 2008.


The Public Listing Date of the Satellogic Satellite Company is Dec. 22.


The Payload Accommodation of the Minisatellite Satellite is 50 kg (max).


The Expected Lifetime of the SpinSat Satellite is >6 months.


The Funding Agency of the OPAL CubeSat is National Science Foundation (NSF).


The Porosity of the Comet Celestial Body is 70-80%.


The Downlink of the Image Location Knowledge Satellite Component is < 300 m.


The Mission Objective of the PROBA Satellite is Address issues of on-board operational autonomy.


The Number of Sensor Elements of the Chem-sensor housing Sensor is 32.


The Nominal Lifetime of the Sentinel-5P Satellite is 7 years.


The Calibration Status of the Satellite Spacecraft is Uncalibrated.


The Function of the AMI Instrument is Provides continuous monitoring capability for the near real-time generation of high-resolution meteorological products and long-term change analysis of sea surface temperature and cloud coverage.


The Conference Date of the IASI-NG Satellite is 4-8 February 2013.


The Conference Presentation Date of the Sentinel-1 Satellite is June 7-10, 2010.


The Access Availability of the Inmarsat BGAN Service Satellite Communication Service is 24/7.


The Data Rate of the S-band Transmitter Transmitter is 32 kbit/s to 256 kbit/s.


The Swath Width of the ETM+ Scanner Imaging Device is 185 km.


The Image Size of the VIS Camera Camera is 1910 x 1270 pixels.


The Imaging Frequency Band of the ERS-2 Satellite is C.


The Integrated Irradiance Values of the Solar SXR Spectra Solar Phenomenon is 0.1-7 nm.


The Number of Instruments of the Nimbus-7 Satellite is 9.


The Image Resolution of the Satellogic Satellite is 1 meter.


The SNR of the Instrument Satellite Instrument is > 100.


The Projected Distance of the Newly Detected Source Object is 8 times the Earth-Sun distance.


The Nominal Voltage of the NiH2 batteries Power Source is 10 V.


The Observation Data of the SAGE-II Satellite is Stratospheric ozone, aerosol, water vapor, nitrogen dioxide.


The Launch Date of the GovSat-1 Satellite is 31 Jan. 2018.


The Spectral Bandwidth of the MAHRSI Instrument is About 4 nm.


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


The Number of CubeSats of the CubeSat - Launch 4 Satellite is 7.


The Renamed In Honor Of of the KhalifaSat Satellite is His Highness Sheikh Khalifa Bin Zayed Al Nahyan.


The Characteristics of the Eruption Solar Event is Ejection of a hot layer of solar material above a magnetically active region on the Sun's surface.


The Configuration of the Propulsion System Satellite Component is ESPA and T2E-compatible.


The Function of the High-Resolution Camera Camera is Capture Earth imagery.


The Launch Site of the DubaiSat-2 Satellite is Dombarovsky launch site in Russia.


The Function of the ShadowCam Instrument is Acquire images of shadowed regions of the moon.


The Stationkeeping Accuracy of the AOCS Attitude and Orbit Control Subsystem is ±0.5º in longitude and latitude.


The Launch Date of the OptiSAR™ Constellation Satellite Constellation is 2020-2021.


The Image of the ATMS Instrument is Figure 9: Danielle Gallegos, ATMS program manager for Northrop Grumman, with the ATMS instrument behind her.


The Infrared Channels of the AATSR Imaging Radiometer is 1.6, 3.7, 10.8, and 12.0 μm.


The Staff Count of the GHOSt Constellation Satellite Constellation is Unknown.


The Frequencies of the DORIS Receiver is 400 MHz and 2 GHz.


The Developers of the FLEX Mission Performance Simulator is J. Vicent, N. Sabater, C. Tenjo, J. Acarreta, M. Manzano, J. Rivera, P. Jurado, R. Franco, L. Alonso, J. Verrelst, J. Moreno.


The Tip Mass of the Gravity Gradient Boom Attitude Actuation Device is 40 g.


The Detection Announcement of the Hubble Space Telescope Space Telescope is 2013.


The Swath Width of the Imager Imaging System is 16.4 km.


The Field of View of the Solar-B / Hinode Satellite is Unknown.


The | 80 m of the RBV Instrument Spatial Resolution is Spatial resolution 80 m.


The Function of the IM Interconnect Module is Combines and splits the RF energy and serves as the interface between the transmitter, receiver, and antenna.


The Field of View (FOV) of the BEO Back-End Optics is 0.32º.


The Mission Phases of the Satellite Spacecraft is Commissioning phase, Science phase.


The Travel Distance Requirement of the Google Lunar X-Prize Competition is 500 meters.


The Area Coverage of the Copernicus Sentinel-3 Satellite is 100 000 km2.


The Touchdown Date of the Hayabusa-2 Spacecraft is February 22, 2019.


The Investment Focus of the UrtheCast Company is Constellation of Earth-imaging satellites.


The Uncertainty of the Responsivity Measurement Instrument is ± 5%, 2σ confidence level.


The Power Source of the Rosetta Spacecraft is Solar cells.


The Data Return of the Van Allen Probes Satellite is More than twice the expected.


The Unknown of the NRO/MSD Sponsor is Unknown.


The Observation Date of the HSRL-2 Lidar is TCAP 2012.


The Configurable GNSS Signals of the GNSS-RO Receiver Receiver is GPS, GLONASS, and additional GNSS signals.


The Target Launch Date of the Crew-5 Spacecraft is Fall of '22.


The Observation Resolution of the IRIS Observatory is Unprecedented.


The Ground Sample Distance of the Satellite Satellite is ≤ 2.5 m (Pan), ≤ 10 m (MS).


The Data Acquisition of the TanDEM-X Satellite is 300 TByte.


The Center Frequency of the KaRIn Instrument is 35.75 GHz.


The Number of Satellites with FCC Application of the OneWeb Satellite Constellation is 48000.


The URL of the IPv6 and IPsec on a satellite in space Presentation is http://www.cisco.com/web/strategy/docs/gov/wood-iac-07-B-2-6-06-paper.pdf.


The Field of View of the Limb Channel Imaging Channel is Wide (along the limb) and short (in the vertical direction).


The Quantity in PPU of the StrongARM SA1110 Processor is 20.


The Pixel Size of the SAR Synthetic Aperture Radar is 25 x 25 m.


The Data Type of the TanDEM-X Satellite is Quicklook images.


The Power Capability of the Buck-Boost Converter Solar Array Regulator is 450 W per Converter.


The ROM/RAM of the SCU Satellite Central Unit is EEPROM(128KB x 2), SRAM(512KB x 4, 8MB x 1).


The Band of the IASI Infrared Atmospheric Sounding Interferometer is 2.


The Imaging Capability of the Tandem-L Satellite is Exceeds that of TanDEM-X by a factor of 100.


The Operator of the RapidEye Earth Observation Constellation is BlackBridge.


The Documentation Source of the MEVIµS Satellite is "Observation of the Earth and Its Environment: Survey of Missions and Sensors" (Springer Verlag).


The Effective Absorption of the MLI Thermal Control Device is α < 0.05.


The Launch Date of the Rosetta Spacecraft is March 2, 2004.


The Number of Satellites of the OneWeb Satellite Constellation is 110.


The Onboard Network of the JWST Avionics Spacecraft Avionics is FPE (Focal Plane Electronics).


The Function of the Gaia Space Telescope is Measure the position, movement, distance, and characteristics of billions of stars.


The Start of Science Operations of the NICER-SEXTANT Mission is 17 July.


The Pit Diameter of the Ma'at Region on Comet 67P/Churyumov–Gerasimenko is More than 100 m.


The Dynamic Range of the Radiometry Sensor is 0-380 Wm -2  sr -1.


The Mass of the SAOCOM-1A Satellite is 3,000 kg.


The Monitoring Duration of the NASA Organization is Several decades.


The Function of the Poseidon-4 Radar Altimeter is Measure the range between the satellite and the mean ocean surface, determine significant wave height and wind speed, and provide the correction for the altimeter range path delay in the ionosphere.


The Integration of the Reflectarray Antenna Antenna is Solar cells have been added on the opposite side.


The Bus Voltage of the SBVR Power Supply is 100 V.


The Launch Year of the Sentinel-4B Satellite is 2032.


The Frequency Band of the TT&C Tracking, Telemetry, and Control is S-band.


The Proof Mass Distance of the LISA Pathfinder Satellite is 35 cm.


The Measurement of the Vector Sensor Instrument is Amplitude and phase of radio emission.


The Mission Objectives of the M3MSat Satellite is 1) augment existing maritime surveillance capabilities through the space-based monitoring of ship Automatic Identification System (AIS) 2) foster Canadian capabilities by providing an opportunity for the contractor to propose and demonstrate a new technol.


The Rainfall Measurement of the GPM Satellite is Up to 50 mm per hour.


The Website of the GOCE Satellite is http://op.gfz-potsdam.de/champ/systems/main_SYSTEMS.html.


The Design Life of the RISAT-2 Satellite is 5 years.


The Importance of the Micro-gravity experiment Experiment is Development of fluids, space material science, space life science.


The Reflector Size of the Biomass satellite Satellite is 12 m across.


The Field of Regard of the GF-2 spacecraft Satellite is Not specified.


The Frequency (GHz) of the ICI-7 Radiometer is 325.15±1.5.


The Mass of the CanX-6 / NTS Satellite is 6.5 kg.


The Maximum Cube Size of the Orbit Your Thesis! 2019 program Education Program is 4U.


The Global Services Delivery of the OneWeb Company is 2022.


The Information of the GeoSat Follow-On Satellite is http://enterprise.spawar.navy.mil/UploadedFiles/gfo_fs.pdf.


The Launch Date of the IRNSS-1D Satellite is March 28, 2015.


The Depth of the Great Blue Hole Underwater Sinkhole is About 123 m.


The Article Date of the Micro cold traps Lunar Surface Feature is 26 October 2020.


The Launch Date of the Flying Laptop Satellite is 2017.


The Control Method of the ACS Attitude Control Subsystem is Magnetic control.


The Mass of the Freqbone Payload is 10 kg.


The Photodiode Cant Angle of the Sun Sensor Suites Sensor is 45º.


The Bus Rail Voltage of the Spacecraft Satellite is 26 ±6 V.


The Band of the miniKaAR-C Radar is Ka-band.


The Time Resolution of the PIXIE Satellite is 60 seconds or better.


The Input Angle alpha of the Short Wavelength Band Spectrometer is 21.9º.


The Powering Up Start Date of the Prichal Module is October 11.


The Footprint Distance of the CloudSat and CALIPSO Satellites is Always within 2 km.


The Exposure Time of the Coronal Loops Imaging Device is < 1 second.


The Time Between Observations of the SCIAMACHY Spectrometer is 150 seconds.


The Measurement Range of the SOLSPC Radiometer is 200-2400 nm.


The Vision of the Eu:CROPIS Satellite is To derive the greatest benefit from long- term human space exploration.


The SAR Payload Accessible Swath Width of the RCM Satellite is 500 km.


The Pointing Stability Requirements of the TEMPO Instrument is High precision.


The Ticket Date of the Exoplanet mission Satellite is April 6, 2017.


The Detector Array of the VNIR Spectrometer Spectrometer is 60 x 250 pixels.


The Measurement Height of Atmosphere of the ERIP Earth Remote-Sensing Imaging Package is 0 - 55 km.


The VPU Cores of the Ubotica CogniSAT-XE1TM CubeSat Board Satellite Device is 12 vector cores.


The Architecture Components of the MSAS Satellite-based Augmentation System is MRS (Monitor and Ranging Stations), GMS (Ground Monitor Stations), MCS (Master Control Stations).


The Purpose of the SpaceLink Satellite Network is Provide real-time connectivity between space and the ground.


The Current Size of the Cerro Pelado fire Wildfire is More than 25,000 acres.


The Status of the DWSS Satellite Program is Canceled.


The Imaging Capability of the ICON Space Mission is Provide the ability to explain how these drivers set the stage for the extreme conditions of solar-driven magnetic storms.


The Function of the GEDI Lidar Instrument is Produces detailed observations of the three-dimensional structure of the Earth's surface.


The Data Resolution of the GeoSTAR Atmospheric Microwave Sounder is Very high temporal resolutions.


The Receiver Type of the SPOT-2 Satellite is 1st generation receiver (18 kg), a bi-frequency system in 1 channel.


The URL of the Airborne Lunar Spectral Irradiance (air-LUSI) Instrument Instrument is https://www.nist.gov/measuring-cosmos/airborne-lunar-spectral-irradiance-air-lusi-instrument.


The Driving Distance of the Yutu-2 Lunar Rover is 367.25 meters.


The Launch Date of the MMS Satellite is Fall of 2014.


The Publication Date of the Ministers back ESA's bold ambitions for space with record 17% rise News Article is 23 November 2022.


The Thermal Measurement Accuracy of the HTS/AMSR2 Microwave Absorber is 0.4ºC (3σ).


The Multi-Look of the Capella SAR System is 10.


The Manufacturer of the ESAJECT Mechanism Satellite Deployment Mechanism is Verhaert of Kruibeke, Belgium.


The Delivery Date of the µCAT Hardware is Sept. 2015.


The Provider of the MetOp-A Satellite is EUMETSAT.


The Near-UV Channel Spectral Resolution of the IRIS Observatory is 8 x 10-3 nm.


The Li-ion Battery Capacity of the EPS Electrical Power Subsystem is ~20 Ah.


The Operational of the Galileo Satellites 13 and 14 Satellites is Yes.


The Interface of the Service Module Satellite Module is Power and data handling bus.


The URL of the Jason-2 Satellite is http://www.aviso.oceanobs.com/fileadmin/documents/newsstand/Newsletter/aviso_special_issue_3years_Jason2.pdf.


The Spectral Range of the Fourier transform spectrometer Infrared Spectrometer is 645 to 2760 cm-1.


The Application of the Supercapacitors Energy Storage is Space.


The Minimum Lower Band Edge of the MS8 (NIR2) Imager is 856 nm.


The Data Transmission Time of the COSIMA Mass Spectrometer is About 40 minutes.


The Mission Status of the FalconSat-3 Satellite is Mission complete.


The Downlink Data Rate of the RF Communications Communication System is 32 kbit/s.


The Blog Post Date of the International Space Station Space Station is 27 April 2023.


The DOI of the SOFIE Satellite Instrument is 10.1002/2014JD021763.


The Bandwidth of the Ka-band Channels Communication System is 900 MHz each channel, 2.7 GHz total.


The Service Continuity of the Pléiades Neo Satellite Constellation is 15 years.


The Member of the Susan Ustin Individual is True.


The Operation Time of the NorAIS-2 Receiver AIS Receiver is Four and a half years.


The Quantity of the SpaceBEE Picosatellites is 12.


The Type of the NigeriaSat X Remote Sensing Instrument is Imaging multi-spectral radiometers (vis/IR).


The Delivery Start Date of the Starlink Premium Satellite Internet Service is Second quarter of 2022.


The Interaction of the Coronal Mass Ejections Solar Phenomenon is Interacting in the interplanetary space with another Coronal Mass Ejection.


The Experiment Renewal of the SPOT-5 Satellite is TAKE5 experiment.


The Optical Pulse Dynamic Range of the LI Instrument is 6.7 - 670 mW/m 2 /sr.


The Spatial Resolution of the MSU-E Multispectral Scanner is 28 x 28 m.


The Flux Measurement Error of the HaloSat Satellite is 2.5%.


The Science Data Rates of the Ka-band Downlink Communication System is 7, 14, or 28 Mbit/s.


The Slew Angle of the MiRaTA Satellite is 90-105°.


The Orbit Inclination of the Monitor-E Spacecraft is 97.5º.


The Function of the TDC Time to Digital Converter is Processing valid photon events and rejecting subthreshold or incomplete events.


The Primary Density of the Didymos Binary System is 2.1 g/cm3.


The EREP Investigations of the Skylab Space Station is Unknown.


The Number of Cameras of the Imaging System Imaging System is 6.


The SNR of the Telescope Optical Instrument is 205.


The Delta Velocity of the Steam Propulsion Unit Propulsion is Up to 10 meter per second.


The Launch Control of the ORS-6 Satellite Mission is Not co-lead.


The Voltage Range of the Suppressor Grid Grid is 0 to -12 V.


The Objective of the EFILE Experiment is Study the thermocapillary effect at the liquid-gas phase-change interface on evaporation in the space environment.


The Attitude Control Stability of the GF-2 spacecraft Satellite is 5 x10-4 º/s.


The Polarization of the MTVZA-GY Radiometer is Horizontal.


The CONOPS and FDIR Features of the Twinkle Satellite is Robustness and redundancy; on-board autonomy and simple satellite safe-modes; extensive use of proven, off-the-shelf components; modularity.


The Overpass Timing Prediction Accuracy of the ARC Calibration System is Less than 1 second.


The Payloads of the EIRSAT-1 Satellite is Trio of Irish payloads.


The Publication Date of the TRUTHS Satellite is December 2003.


The Sensor Type of the MuREM Dosimeter is Two large area PIN diodes.


The Peak Season of the AgCam/ISSAC Imaging System is April - October.


The Value of the Straylight Performance Requirement is Less than 2%.


The Altitude of the KOMPSAT-3A Satellite is 528 km.


The Vehicle of the SpaceX Launch Provider is Falcon 9.


The Image Capture Method of the NAC Camera is One line at a time.


The Impact of the EMIT Imaging Spectrometer is Help scientists understand which kinds of dust dominate each region and advance their understanding of dust’s impact on climate and the Earth system.


The Formation Flying Algorithms of the Formation Flying Computer Computer is Runs.


The In-Orbit Demonstration Date of the ELSA-M Spacecraft Servicer is Late 2024.


The Number of Instruments of the MetOp Satellite is 11.


The Spectral Bands of the SLSTR Spectral Imaging Instrument is 11.


The Imaging Frequency Band of the ALOS-1 Satellite is L.


The Moon Angle Constraint of the CHEOPS Telescope is Larger than 5º.


The Dimensions of the Satellite Satellite is 4 m x 3 m x 2 m.


The Presentation Date of the VIIRS Satellite Instrument is June 20-24, 2005.


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


The Conference Presentation Date of the JC2Sat & MIRAD Satellite is Sept. 29 to Oct. 3, 2008.


The Design Discussion of the MSX/UVISI Instrument is Three-paper series.


The Adapter and Separation System Type of the ALMASat-1 Satellite is 2-clamp separation method.


The Instrument Mass of the Scanning geometry Instrument is ≤ 70 kg.


The J2000 declination (deg) of the B0540-69 Pulsar is -69.33171.


The Shielding Material of the EPI-Lo Electron Detector is Aluminum flashing of ~2 µm thickness.


The Launch Date of the PROBA-V Satellite is Unknown.


The End of Life Date of the CryoSat Satellite is 08 Oct 2005.


The Mass of the UGATUSat Microsatellite is 30 kg.


The Development Date of the PRARE-2 Satellite System is August 1995.


The Location of the Igloo Container is In front of the pallet.


The URL of the China High-resolution Earth Observation System (CHEOS) Satellite System is http://www.oosa.unvienna.org/pdf/pres/stsc2014/tech-47E.pdf.


The Passband Range of the SPIM2 Spectrometer is 162-252 nm.


The Team Members of the CLARREO Mission is D. F. Young, M. G. Mlynczak, K. J. Thome, S. Leroy, C. O. Ao, R. Bantges, F. Best, H. Brindley, J. Butler, R. Cageao, W. Collins, R. Cooke, J. Corliss, J. C. Currey, J. A. Dykema, D. R. Doelling, B. Dunn, D. R. Feldman, D. Goldin, H. Huang, R. Holz, Y. Hu.


The Ka-band Disadvantages of the SARAL/AltiKa Satellite is Attenuation due to water/water vapour in case of rain, resulting loss of data.


The Launch Date of the AAUSat-1 CubeSat is June 30, 2003.


The Dish Size of the NASA Wallops field Ground Station is 18.29 m.


The Ground Station Antenna of the KySat-1 Satellite is 21 m SPA (Space Tracking Antenna).


The Wavelength of the Instrument Spectrometer is 2.3-3.8 µm.


The Debut Flight Date of the Rail-guided space launcher Space Launcher is October.


The Type of the Imager Imaging System is Pushbroom imager (or a line scan imaging system).


The Conference Presentation Date of the GPS/MET Satellite is Sept. 12-15, 1995.


The Noise Temperature of the System Communication System is Unknown.


The OBC Processor of the X-Sat Satellite is StrongARM processor.


The Amplifier of the Phoenix GPS Receivers GPS Receiver is Independent low noise amplifier (LNA).


The Observation Target of the PROBA-2 Satellite is Sun.


The Manufacturer of the iADCS-100 ADCS System is BST (Berlin Space Technologies) and Hyperion Technologies B.V..


The Components of the Cooling System System is Pulse-tube cooler, symmetric compressor.


The Ejection Velocity of the ICU Container is At least 0.5 m/s.


The Mass Resolution of the HPCA Electrostatic Analyzer is Accurately separates and identifies the minute amounts of hydrogen, helium, and oxygen ions.


The SAR Payload Radar Center Frequency of the RCM Satellite is 5.405 GHz.


The Effect on Sea Levels of the El Niño Weather Phenomenon is More than a 30 cm higher than normal.


The Instrument Type of the Biomass Satellite is Imaging microwave radars.


The Data Bus of the OBDH Subsystem Satellite Subsystem is Dual redundant CAN bus.


The Mass of the Capability Satellite is 14.0 kg.


The Purpose of the Kepler Mission Space Telescope is Detecting other planetary systems.


The Post-flight Calibration of the Gas Scintillation Proportional Counter Instrument is Unknown.


The Attachment Time of the Centaur Second Stage and Spacecraft Rocket Components is 4 minutes, 33 seconds after launch.


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


The Constellation Size of the Kleos Space Satellite Operator is Up to 20 clusters.


The Instrument Performance Parameters of the HIT High-energy Ion Telescope is Summarized in Table 10.


The Responsibilities of the SSDC Space Science Data Center is Science data processing, managing, archiving, permanent preservation and distribution of data.


The Telemetry of the RF Communications Communication System is CW.


The AOI Sensitivity of the PF1 Passband Filter is Unknown.


The Mission of the OSIRIS Instrument is Odin.


The Heat Management of the BepiColombo Spacecraft is Heat generated by spacecraft subsystems and payload components, as well as heat that comes from the Sun and Mercury and ‘leaks’ through the blankets into the spacecraft, will be conducted to the radiator by heat pipes and ultimately radiated into space.


The Data Release Date of the Cheollian 2B Satellite is May 25, 2020.


The Planned Mission Duration of the New Horizons Spacecraft is 2023 through 2025.


The Objective of the VAT (Vacuum Arc Thruster) Thruster is On-orbit demonstration of a trigger-less vacuum arc thruster.


The Mass of the Instrument Satellite Instrument is < 10 kg (with MI).


The Inclination of the IRS-1B Satellite is 99.09º.


The Dimensions of the Field Measurement Device Electronic Unit is 150 mm x 85 mm x 40 mm.


The Manufacturer of the SEOSAT/Ingenio Satellite is Airbus.


The Number of Spectral Bands of the S-192 optomechanical scanner Scanner is 13.


The Velocity Change of the Solar System Celestial System is 0.23 nm/s2.


The Output of the NGAVGS Sensor is Real-time video.


The Managing Center of the GPM Satellite is NASA's Goddard Space Flight Center in Greenbelt, Maryland.


The Payload Mass of the TCS Thermal Control System is 7.26 kg.


The Field of View of the EPD-E Energetic Particle Detector - Electrons is < 28°.


The Temporal Sampling of the Sea Ice Concentration (SIC) Measurement is Sub-daily.


The Date of the Satellites Spot Tornado Tracks Across Midwest Image is 14 December 2021.


The Cross-Calibration of the CloudSat Satellite is Additional Funds.


The Resolution of the iMTQ Magnetorquer is 15 nT.


The Spectral Range of the Hyperspectral Imager Radiometer is 0.4 – 2.5 µm.


The ESPA Ring Mass of the DSX Spacecraft Payload Module Satellite is  240 kg.


The Modulation of the RF communication subsystem Communication Subsystem is AFSK (Audio Frequency Shift Keying).


The RF Model Date of the MTG-I Satellite is 03 July 2019.


The Orbital Plane of the Orbital Phase 2 Orbit is Moved to the terminator plane.


The S/C Structure of the Payload Satellite Payload is Main elements.


The Number of Doves Onboard of the PSLV-C37 Satellite Launch Vehicle is 88.


The Particle Measurement Ranges of the STAFF/DWP Instrument is Electrons = 20 keV - 400 keV; Protons = 40 keV - 1500 keV; Helium = 40 keV - 150000 keV; Oxygen = 40 keV - 4000 keV.


The Release Method of the Sail Closeout Panels Subsystem is Spring-loaded hinges.