The S-band TxRx Data Rate (TM) of the RF communications Communication System is 1.91 Mbit/s or 329 kbit/s.


The Ground Station of the SAOCOM-1A Satellite is ETC (Estación Terrena de Córdoba), Argentina.


The Main Tasks of the OBDH OnBoard Data Handling is Processing of telecommands and telemetry, time management, navigation, management for concepts of redundancy, allocation of interfaces to all subsystems onboard SONATE, monitoring of its state with an autonomous response in case of failures or critical va.


The Prime Objective of the ZACube-2 Satellite is Demonstrate AIS (Automatic Identification System) message reception.


The Detector Orientation of the DIDM Instrument is Facing the S/C ram direction.


The Type of the Cesium Mission 1 Satellite is On-orbit testbed.


The Sensor Complement of the QSat Satellite is 2-band CMOS camera (VNIR) 3000 x 2000 pixels.


The Receiver Type of the AIS Automatic Identification System is Dual polarization.


The Imaging Capabilities of the NewSat-6 Satellite is Multispectral and hyperspectral.


The Mass of the ICEYE-X2 Microsatellite is ~ 80 kg.


The Data of the Tropomi Satellite Instrument is Used to combine with GHGSat's unique fleet of high-resolution satellites.


The Structure Material of the ESTCube-1 & -2 CubeSat is Aluminum (alloy AW 6082-T6).


The Purpose of the SMOS Satellite is Measure soil moisture and ocean salinity.


The Test Location of the Orion Spacecraft Spacecraft is Plum Brook Station in Sandusky, Ohio.


The Alignment Requirement of the SPIDER Telescope is Not required.


The Launch Date of the JPSS-1 Satellite is 2016.


The URL of the SARah project Satellite Project is https://www.army-technology.com/news/newsastrium-german-third-sarah-reconnaissance-satellite/.


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


The Image Resolution of the SPOT-6 Satellite is 1-5 m.


The Ground Control Segment Provider of the PAZ Satellite is Indra.


The Functionality Testing of the EDU Lab Testing Facility is Mission capable code.


The Observation Wavelength of the NACO Instrument is 3.6 µm.


The Velocity Regime of the Austfonna Ice Cap is Predominantly slow (~ 101 m/yr) to fast (~ 103 m/yr).


The Type of the Lithium iron phosphate (LiFePO4) battery Battery is Secondary power source.


The Mounting Method of the Avionics Satellite Components is Built up into stacks based on a generic SSTL module box design.


The Bit Size of the FPGA Processor is 32 bit.


The Integration with 5G New Radio of the Open5GCore Rel. 4 5G Core Network is NSA [S1-MME, S1-U] and SA [N1, N2, N3].


The Reprogrammable of the FPGA based parallel computing Processing Technology is Yes.


The Function of the Magnetic Field Geomagnetic Field is Protecting Earth from cosmic radiation and charged particles.


The Orbit Altitude of the GHGSat-C2 (Hugo) Nanosatellite is 560 km.


The Remaining ?V Capability of the PRISMA Satellite is More than 50 m/s.


The Weight of the OSDP Onboard Signal Data Processor is 18 kg.


The Camera Resolution of the PhoneSats Satellite is 5 Mpixel.


The Status of the WorldView-1 Satellite is Operational.


The Experiments per Day of the Satellite Satellite is 2-3.


The Testing Duration of the SAGE-III Instrument is Nearly five years.


The Attitude System of the Microsatellite Satellite is ±10º.


The Intersatellite Link Range of the CNAPS Propulsion System is 5 km.


The Frequency of the ICOM-9100 transceiver Transceiver is 144 MHz (Tx), 434MHz (Rx).


The Science Team Leader of the OSIRIS-REx Spacecraft is University of Arizona, Tucson.


The Launch Date of the TechEdSat Satellite is March 21, 2012.


The Collection Areas of the HawkEye 360 Satellite Constellation is Mediterranean, South China Sea, Korean Peninsula.


The Mass of the Diamond nanosatellites CubeSats is 6 kg.


The Data Storage of the ASAP-Light Camera System is Non-volatile memory.


The Ground Track of the MOMS-2P Instrument is 2000 km.


The Purpose of the ZACube-2 Satellite is Track boats along South Africa's coasts and detect forest fires.


The Program of the Sentinel-1C Satellite is Copernicus, a joint European Union and European Space Agency (ESA) Earth Observation program.


The Manufacturer of the Solar Panels Electrical Power Subsystem is Spectrolab.


The Main Mode Frequency of the MRSE Instrument is X-band (9.6 GHz).


The Procedure Scripts of the SATLAB Configuration is PLUTO procedure scripts.


The Manufacturer of the 3-axis magnetometer Sensor is Honeywell.


The Data Storage of the MAC Memory System Module is 32 Gbit.


The Number of Orbits of the Quasi-Halo Orbits Orbit is 14.


The Apogee (km) of the Meteor-3-1 Satellite is 1263.


The Objective of the MidSTAR-1 Satellite is Fly two payloads: ICSat (Internet Communications Satellite) and CFTP (Configurable Fault Tolerant Processor).


The Wavelength Range of the InSb Detector is 1.55 - 1.75 µm.


The Data Rate of the LEO-LEO Inter-satellite Link Communication System is 5.625 Gbit/s.


The Nominal Pointing Range of the Guider Instrument is ±30 arcsec.


The Spatial Resolution of the TerraSAR-X NG Satellite is Down to 0.25 meters.


The Spectral resolution of the UV/VIS Spectrometer Spectrometer is 0.89 nm.


The Operation Mode of the STEREO Mission is Autonomous operation - beacon mode.


The Launch Time of the Rocket 3.3 Rocket is 1:16 a.m. EST (06:16 UTC).


The Mass of the MERLIN Satellite is 400 kg.


The Estimated Code Reuse of the VMOC Mission Operations Center is Soon approach 95%.


The Mission Status Presentation Date of the SMART-1 Satellite is March 13-17, 2000.


The Measurement Domain of the CASSIOPE Satellite is Gravity and Magnetic Fields.


The Interferometric Baseline of the ERS-2 Satellite is Optimal with 30 min. separation.


The Host of the OSIRISv2 Instrument is BiROS satellite.


The Position of the Star Tracker Device is Left.


The Mass of the Photometer Instrument is ≤ 0.9 kg.


The Accuracy of the SpinKF Attitude Determination System is Best available attitude accuracy.


The Size of the SAGE-III Instrument is 73 cm x 45 cm x 93 cm.


The Launch Date of the ASTRO-H Satellite is Feb. 17, 2016.


The Number of Satellites in Orbit of the OneWeb Low-Earth-Orbit Broadband Venture is 254.


The Power Consumption of the Instrument Satellite Instrument is < 24 W.


The Bipropellant System Lunar Departure ΔV of the Clementine Spacecraft is About 540 m/s.


The Drought Impact of the OCO-2 Satellite is Increased carbon dioxide release.


The Recommendation of the Connector Savers Component is Future projects should consider their implementation for external access ports.


The Orbit Inclination of the ProSEDS Tether Demonstration Experiment is 35º.


The Announcement Date of the Photon Sieve Optics Technology is June 4, 2012.


The Data Transmission of the LT Device is Lithium radio.


The SOC Deputy Head of the Roman Space Mission is Cristina Oliveira.


The Manufacturer of the Icarus-1 Drag Sail is Cranfield University.


The Power of the Spacecraft Satellite is ~1.5 W.


The Location of the RADFET dosimeters Dosimeters is ESS (Experiment Support System) PCB.


The Data Collected of the GP-B mission Mission is Over 1 TByte.


The Launch Date of the QZS-3 Satellite is June 16, 2017.


The Pilot Program Start Date of the CubeSat Satellite is Nov. 10, 2010.


The MTF of the CCD Camera Imaging System is <=0.23.


The Field of View of the LISS-IIM Instrument is ±5º.


The Solar Generator Configuration of the MicroSCOPE Satellite is Two identical wings of one panel each, mounted on Y panels and directed toward +X.


The Power of the S-192 optomechanical scanner Scanner is 266 W.


The URL of the D-Sat Satellite is https://www.dsat.space/.


The Orbit Inclination of the LitianicaSAT-2 Nanosatellite is 97.44º.


The Objectives of the YouthSat Satellite is Provide hands-on experience to student in space experiments and data analysis, Study solar radiation, Create a common platform for aerospace students across the world to jointly conduct experiments in space.


The Measurement Range of the Particle Detector Instrument is Helium-4 : 10 MeV/n ~ 400 MeV/n.


The Spacecraft Mass of the QSat Satellite is < 50 kg.


The PUI Measurement Resolution of the IMAP Satellite is < 1 min.


The Solar Wind Speed and Beta of the ACE Satellite is ~38% lower on average from 2009 through the day 79 of 2013.


The Publication Date of the TOI-178 Exoplanet System is 25 January, 2021.


The Center Frequency of the Channel 2 Sensor is 18.7 GHz.


The Interference Nadir Gap of the NNI Synthetic Aperture Nadir Altimeter is ±4 km.


The Reliability of the Aeolus Satellite is 95%.


The Topical Team Meeting Date of the ASIM Payload System is June 26-27, 2006.


The Entrance Pupil Diameter (mm) of the FCI-TA Instrument is 300.


The SEVIRI HRV Image Date of the Meteosat-10 Satellite is 19 July 2016.


The Launch Date of the SLS with Orion Space Launch System is 8 March 2018.


The Amazon Basin Size of the Biomass satellite Satellite is Over six million km2.


The URL of the SWOT Satellite is http://smsc.cnes.fr/SWOT/.


The Mission Type of the Sentinel-4 Satellite is Geostationary component of European (EC, ESA) operational atmospheric composition monitoring missions.


The GNSS-RO of the Sentinel-6 Satellite is Instrument.


The Proposed Rate of Change of the Delta in Solar Phase of Apsides Orbital Parameter is 3.6º/ year.


The Location of the HIFI Instrument Control Center is SRON Netherlands Institute for Space Research, Groningen, the Netherlands.


The Initial Staffing of the LMOC and OGSs Ground Segment is 8 hours per day, 5 days per week.


The Period (min) of the Cosmos-1066 (Astrofizika) Satellite is 102.2.


The Observation of the STSat-1 Satellite is Airglow.


The ITR (Integrate-Than-Read) and IWR (Integrated-While-Read) of the Device Operation Modes is In ITR mode, the signal integration and the read-out cycle are separated in time, whereas in IWR mode, the device starts already a new integration cycle while the information of the previous line is read out.


The Orbit Inclination of the TecSAR SAR is 41°.


The Type of the AU Microscopii Star is M dwarf.


The Flaps Material of the Thermal Control Louvers Thermal Regulation Device is Aluminum.


The Launch Year of the SARLupe Satellite is 2006.


The Number of Lunar Landings of the Chang'e-5 Spacecraft is 3.


The Control Type of the Dual-channel Receiver Unit (DRU) Receiver is Manual or Automatic.


The Science Objectives of the LRO Lunar Reconnaissance Orbiter is Bombardment history of the Moon, Lunar geologic processes, The processes that have shaped the global lunar regolith.


The Tx Bandwidth of the KaRIn Instrument is 200 MHz.


The Surface Error of the Antenna Communication is Less than 2.4 mm rms.


The Contact Attempt Elevation Angle of the Polar Scout Satellite is Above 10 º.


The Orbit Parameters of the GEOS-1 Satellite is 1,114 x 2,273 km x 59.4º.


The Off Nadir Acquisition Capability of the Satellite Imaging Satellite is Up to 1 path off nadir.


The Nominal Scenario Orbit Phases of the PROBA-V Satellite is Geodetic attitude with yaw steering correction, Sun-bathing mode, Geodetic pointing mode, Reactivated to reach thermal stability.


The Testing Facility of the CO2M Satellite is Largest satellite test facility in Europe.


The Topics Addressed of the INTEGRAL Satellite is Compact Objects: White Dwarfs, Neutron Stars, Black Hole Candidates, High Energy Transients; Extragalactic Astronomy: Galaxies, Clusters, AGN (Active Galactic Nuclei), Seyferts, Blazars (very compact quasars associated with a presumed supermassive black h.


The Attempted ?V Maneuver of the Satellite Spacecraft is 7 m/s.


The Cross-Track Motion Control of the CloudSat Satellite is Within ±1 km of the CALIPSO ground track.


The Data Access of the Pléiades Neo constellation Satellite Constellation is Immediate.


The MLI Area Ratio of the MLI Thermal Control Device is Unknown.


The Swath of the Sentinel-2 satellites Satellite is 290 km.


The Importance of the Satellites Observation Tool is Crucial for monitoring climate-related phenomena.


The Drill Length of the Rosalind Franklin ExoMars rover Rover is 2 m.


The Data Transmission of the CubeRRT Satellite is On-board filtering requires 99% less data to be downlinked.


The Crew Size of the Skylab-1 Space Station is Three astronauts.


The Number of Orbited Satellites since May of the Starlink Communication Satellite is 420.


The Orbit Altitude of the GF-3 Satellite Satellite is 755 km.


The Data Storage of the LIRIS Laser Infrared Imaging Sensors is Hard disks in ATV's cargo hold.


The New York Second (NY sec) of the FIELDS Instrument Instrument is 217/150,000 ~ 0.873813 sec.


The Period of the LAGEOS Satellite is 225 min.


The Launch Date of the SmallGEO Satellite is Jan. 28, 2017.


The Internal Sampling Clock Frequency of the FIELDS Instrument Instrument is 150,000 Hz.


The Planned Launches in 2018 of the ICEYE Company is At least two additional missions.


The Contract Announcement Date of the Transport Layer Tranche 1 Satellite System is By the end of the month.


The Ocean Salinity Measurement of the SMOS Satellite is Unknown.


The Stability of the Deep Space Atomic Clock Atomic Clock is Time deviation of less than four nanoseconds after more than 20 days of operation.


The Design Life of the Optsat-3000 Satellite is 7 years.


The Placement of the Test Masses Components is Float freely within the spacecraft.


The Angular Velocity Stabilization Accuracy of the Resurs-DK1 Spacecraft is 0.005o/s.


The Channels of the VISSR Instrument is Water vapor (6.5 - 7.0 µm), Infrared (10.5 - 11.5 µm), Infrared (11.5 - 12.5 µm).


The Housing Dimensions of the MuREM Radiation Monitor is 10 x 6 x 6 cm.


The Mission Status of the Kaber Spacecraft is Unknown.


The Constellation Maintenance Presentation Date of the COSMO-SkyMed Satellite Constellation is Feb. 24-26, 2003.


The Frequency Range of the CubeRRT Satellite is 6-40 GHz.


The Frequency (MHz) of the Compass-BeiDou B2a Signal Carrier is 1175.00.


The Inclination of the COMPASS-1 Satellite is 98.85º.


The Operating Temperature Range of the CubeSat Satellite is -5ºC to 20ºC.


The Progress Update and Launch Plan Date of the FORMOSAT-7/COSMIC-2 Satellite Constellation is April 16-22, 2015.


The Heat Probe of the InSight Lander Lander is HP3 (Heat Flow and Physical Properties Probe).


The FOV of the FSI dual EUV 174 Å and 304 Å alternatively Passband center is 5.2º x 5.2º.


The f/D of the Limb Imager Telescope is 7.3.


The Bipropellant System Lunar Insertion ΔV of the Clementine Spacecraft is About 550 m/s.


The Size of the Flight Unit Satellite Component is About the size of a desktop computer.


The Orbital Navigation Solution of the NEMO-AM Satellite is Position: 12 m (2σ), Velocity: 6 cm/s (2σ).


The Components of the DBCP Dual Babinet Compensator Pseudo-depolarizer is Four wedges of birefringent material arranged in pairs.


The VHF-UHF Transceiver of the IOD-1 GEMS Satellite is CPUT (Cape Peninsula University of Technology) VHF-UHF Transceiver (VUTRX) with CSL ADM (Antenna Deployment Mechanism).


The Launch Date of the Landsat 9 Satellite is Unknown.


The Mass Budget of the ALBus R&R Design is Under 4 kg.


The Coverage Area of the Ground Segment Ground Control Infrastructure is Alps, Pannonian Plain, and Mediterranean region.


The Objective of the SeaWiFS Satellite is Measurement of reflected visible sunlight from the ocean surface for the derivation of ocean-color data.


The Price of the Landsat-7 Satellite is The price tag for Landsat-7 imagery is substantially lower than for the commercial products of Landsat-4 and -5.


The 1st LO of the HRIT HiRID Data Receiver is 1900.


The Input of the Onboard Neural Network Artificial Intelligence is Magnetic or electric component in the VLF range.


The Specialty of the Brian Metzger Theoretical Astrophysicist is Cosmic mergers – collisions between a variety of objects, whether they be planets and stars or two black holes.


The URL of the DeorbitSail Spacecraft Mission is http://www.athena-spu.gr/projects/DeOrbit.


The URL of the Hayabusa2 Asteroid Explorer is http://www.jspec.jaxa.jp/e/activity/hayabusa2.html.


The Presentation Date of the Miniature Ion Propulsion System Propulsion System is Oct. 10-13, 2012.


The Telescope Type of the R3 spacecraft CubeSat is Refractive.


The Agency of the SMART Satellite is Ben-Gurion University (BGU).


The Energy Band of the JEM-X X-Ray Monitor is 3 - 35 keV.


The Operation Start Date of the CryoSat-2 Satellite is April 8, 2010.


The Mass of the VPU Video Processing Unit is 3.2 kg.


The | of the EnMAP Satellite Bus Satellite Bus is EnMAP Satellite Bus - A Cost Effective Platform for Advanced Earth Observation Missions.


The Orbit Inclination of the Landsat-9 Satellite is 98.2°.


The Overview URL of the Dragon SpX-3 Cargo spacecraft is http://www.spaceflight101.com/dragon-spx-3-cargo-overview.html.


The Projected EOL of the Payload Power Power Generation is 140 W.


The Detection of the FIELDS Instrument is Natural, low-frequency radio signal.


The Launch Date of the M3MSat Satellite is April 28, 2008.


The Meeting Date of the Swarm Satellite is June 24-26, 2009.


The Service of the Spire Global UK Company is Manage busy docks safely and market traders to price the goods carried aboard.


The Gimbal Tracking of the SOTA Satellite is ±100 µradians.


The Atomic Clocks of the Indian Regional Navigation Satellite System (IRNSS) Satellite System is Replacement.


The Resolution Δλ (0.10º slit) of the SPIM5 Spectrometer is 4.3 nm.


The Dark Energy Percentage of the Universe Cosmology is 70 percent.


The -1 Order Diffraction Angle (780 nm) of the Diffracted Beam Light is 30.9 º.


The Telescope Size of the MOST Satellite is 5.9-inch (15-centimeter).


The Number of Instruments of the PIMS Plasma Instrument is 2.


The CCD Array Elements of the LISS-4 Camera is 12,288 elements for each band.


The Heat Dissipation of the Power Laser Head Subsystem is ~150 W.


The Mission Objectives of the TanDEM-X Satellite is Generating a global HRTI-3 DEM.


The Spectral Range of the Spectral Band D Spectrometer is 0.76 - 0.86 µm.


The Size of the Dellingr Nanosatellite is 6U.


The Mission Type of the GEOSAT Satellite is EO.


The Long-Term Stability of the MIRAS Radiometer is 0.18 K/year.


The Function of the Satellite STRATOS is Performs POD (Precise Orbit Determination).


The Attitude Control System Testing Date of the Odin Satellite is Oct. 18-21, 1999.


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


The Reentry Date of the HaloSat Satellite is January 4, 2021.


The Purpose of the Refocus Mechanism Assembly Mechanism is Fine-tune the instrument focus.


The GSD (Ground Sample Distance) of the Camera Payload is 1.5 m at an altitude of 650 km.


The Concept Purpose of the Dedicated Satellite Constellation Satellite Service is Exclusive control over a number of satellites over a specific geographical region.


The Arrival Date of the Meteosat-8 Satellite is 21 September, 2016.


The Cargo Mass of the SpaceX Cargo Resupply Mission is 2,910 kg.


The Testbed for Precise Onboard Orbit Determination of the SAC-C Satellite is Unknown.


The Development Status of the MULA Satellite is In progress.


The Wavelength of the Responsivity Measurement Instrument is 1495 nm.


The Bus Type of the PIC microcontroller Microcontroller is SPI (Serial Peripheral Interface).


The Differential Photometry of the BRITE Satellite is < 0.1%.


The Effect of Earth's magnetic field of the Reaction Wheels Satellite Component is Causes a weak drag.


The Spatial Resolution of the Optical Arrangement Imaging System is 250 m, 500 m, and at 1 km at nadir.


The Maneuvers of the OMOTENASHI Satellite is Two deterministic maneuvers.


The Master Clock Frequency of the FIELDS Instrument Instrument is 38.4 MHz.


The Antenna Shape of the Satellite Communication Satellite is Umbrella.


The Signal Strength of the Robusta Satellite is Weak.


The Detector Type of the ELENA Instrument is MCP (Micro-Channel Plate) detectors.


The Distance from Mars of the Tianwen-1 Mars Mission is 2.2 million kilometers (1.4 million miles).


The Modulation of the Optical Downlink Communication System is 16-ary PPM format.


The Focal Length of the Kowa LM16JC lens Lens is 16mm.


The Maximum Possible Value (MPV) Mass of the PUNCH Mission Satellite is 54.9 kg.


The Founding Year of the Kleos Space Company is 2017.


The Data Return of the IXPE Satellite is March 22, 2022.


The Confirmation of the MASCOT Asteroid Lander is Small fragments of carbon-rich asteroids are too fragile to survive entry into Earth’s atmosphere.


The Maximum Capacity of the Xenon Gas Tank Propellant Storage is 82 kg.


The Design Purpose of the Data Processing Pipeline System is Accommodate both products in each of the six spectral bands.


The Engineering Activities of the TDP Operations Satellite Operations is Not performed by Inmarsat.


The Effect of the Deep Ocean Trenches Natural Feature is Producing a dip on the sea surface.


The Measurement Rate of the Claire Satellite is 500th measurement on 09 December 2016.


The Altitude Range of the Temperature Ch. 4 difference & ch. 7 difference Measurement Device is 50 - 100 km.


The Modulation of the S-band Transmitter Transmitter is DQPSK (Differential Quadrature Phase Shift Keying).


The Telemetry Frames Received of the SONATE CubeSat Satellite is More than 5000.


The Principal Investigator of the SIMPL Investigation is Talbot Jaeger.


The URL of the VRSS-1 Satellite is http://cn.cgwic.com/VRSS-1/english/satellite.html.


The Stabilization of the Picard microsatellite Satellite is Three-axis.


The Performance of Rotation Equipment of the Satellite Spacecraft is No degradation.


The Pixel Size of the Imager Camera is 9.0 µm x 9.0 µm.


The Function of the SWEM Instrument is Load new high voltage lookup tables, trigger a switch between the operative high voltage table, load and trigger a switch between the lookup tables that determine how counts are accumulated and binned in the SPAN sensor FPGAs.


The Designation of the OPAL Satellite is OPAL OSCAR-38 (OO-38) by AMSAT.


The Capability of the ARC Active Radar Calibrator is Change the transmit frequency for the evaluation of the Doppler processing.


The Young's Modulus of the Aluminum foil layers Material is 68 GPa.


The Operator of the Bluecrab supercomputer cluster Supercomputer Cluster is Maryland Advanced Research Computing Center.


The Initial Design of the DFACS Attitude Control System is FEEP (Field Emission Electric Propulsion)-type system.


The Wind Velocity Range (Stratosphere) of the Aeolus Satellite is 2 - 16 km.


The Design Life of the GCOM-W1 Satellite is 5 years.


The Revisit Times of the HyperScout Imager is Sub-daily.


The Uplink Frequency of the SCD-2 Satellite is 401.650 MHz and 401.620 MHz.


The Ground-Station Uplink Passes of the SpinSat Satellite is Several.


The Camera Deployment Date of the TechDemoSat-1 Satellite is 31 May 2019.


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


The Land-surface Temperature Imaging of the Copernicus Sentinel-3 Satellite is Data.


The Orbit of the Satellite Imaging Satellite is Sun-synchronous dawn-dusk.


The Operation Start Date of the AlSat Nano Satellite is July 24, 2017.


The Program Partners of the SloshSat-FLEVO Satellite is ESA, the (Dutch) Ministry of Economic Affairs, NIVR (Netherlands Agency for Aerospace Programs), and NRL (National Aerospace Laboratory).


The Effective Area of Main CsI Crystal of the GRS Gamma-Ray Spectrometer is 118 mm.


The Spacecraft Type of the ABEX CubeSat is 12U CubeSat.


The Orbit of the SkySat 3 Satellite is Sun-synchronous orbit of ~ 500 km.


The Purpose of the GOLF Instrument is Study of the internal structure of the sun by measuring the spectrum of free global oscillations.


The Orbit Position of the BeiDou-1E Satellite is GEO, 160º E.


The Dispersed Images of the HETG Grating is Form a shallow X centered at the undispersed (zeroth order) position.


The Operation of the GRAS Global Navigation Satellite System Receiver for Atmospheric Sounding is Supplies atmospheric soundings of the temperature and humidity of the Earth’s atmosphere.


The Launch Date of the GPM Core spacecraft Satellite is 2014.


The Attitude Determination Accuracy of the ADCS Attitude Determination and Control Subsystem is ≤0.03º (3σ, 3-axis).


The Operational of the GENSO Ground Station Network is By the time that Delfi-n3Xt is launched.


The Power Supply of the MnACQ-2000 Miniature Network Data Acquisition System Data Acquisition System is Radiation tolerant.


The Multi-Look of the Capella SAR System is 20.


The Data Transport of the SPA-S Interface is 400~600 Mbit/s.


The Melting Effect of the Ice Material is Earth re-adjusts and immediately rises by a few millimeters.


The Led by of the Space component Component is ESA (European Space Agency).


The Purpose of the CIP Instrument is In-situ measurements of the ionospheric plasma compositions, ion concentrations, velocities, and temperatures.


The Design of the Cupola Windows Space Station Component is Four layered front to potential impactors: a debris pane, two pressure panes, and an inner scratch pane.


The Study Duration of the Odin Satellite is Over 20 years.


The Operating Organizations of the Jason-3 Satellite is NOAA, NASA, CNES, EUMETSAT.


The Launch Vehicle of the NanoSail-D Satellite is Falcon-1.


The Power to sub-experiments of the STRV-2 DHS Data Handling System is 28 V isolated.


The Orbit of the AERO and VISTA Satellites is Sun-synchronous polar orbit.


The Managing Organization of the SWEAP Investigation Investigation is SAO (Smithsonian Astrophysical Observatory).


The Bus Structure Material of the QSat-EOS bus Microsatellite bus is Aluminum alloy (A5052-H32).


The SNR of the ALOS/PRISM Satellite is >70.


The Leaders of the Cosmological Simulations Working Group Organization is Pablo Fosalba (ICE, IEEC-CSIC) and Romain Teyssier (Institute for Computational Science at the University of Zurich).


The Unknown of the Sensor System Satellite Component is Unknown.


The Pipeline Software Developer of the GBOT Project is GBOT group in Paris.


The Location of the High-Latitude Cold-Season Snowfall Campaign Field Campaign is Ontario, Canada.


The Coding of the Channel Communication System is 1/4 to 9/10 FEC.


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


The Receiver Type of the Envisat Satellite is 2nd generation receiver (11 kg), a bi-frequency system in 2 channels.


The Wavelength Range of the HgCdTe Detector is 10.4 - 12.5 µm.


The NER of the Spectral Band B Spectrometer is 6.0 x 10^-6 W/(cm^2 sr µm).


The Swath Width of the C-RADAR Phased Array Antenna System is 225 km.


The Mission Overview and Status of the TanDEM-X Satellite is Not Provided.


The Azimuth Resolution of the P Mode Observation Mode is 1 m.


The Control Type of the AOCS Attitude and Orbit Control Subsystem is Bias-wheel and magnetic torquer control.


The Reference Vector of the Sun Sensor Sensor is Coarse sun model from an astronomical almanac.


The Data Input of the Data Handling System System is 11-bit.


The Data Distribution of the Gaia Satellite is ESAC.


The Dish Size of the Chilbolton Site IOT Station is 25 m.


The Components of the SPIDER Robot is Communications antenna and MakerSat.


The Wind Direction Blur of the SAR Image Synthetic Aperture Radar Image is 180°.


The Testing Start Date of the Galileo Second Generation Satellite is 19 July 2021.


The Manufacturer of the spaceCam c4000 Video Camera is Theta System Elektronik GmbH.


The Spectral Coverage of the AIRS Atmospheric Infrared Sounder is 3.74 - 15.4 µm for the array grating spectrometer (IR bands).


The Spectral Band Centers of the Instrument Spectrometer is 415,750,900,950,1000 nm (VIS); 1000,1050,1250,1550 nm (NIR).


The Spin Rate of the DSP satellites Satellite is 15 rpm.


The Mass of the PAP Plasma Analyzer is 7 kg.


The Type of the TechEdSat-10 Satellite is 6U CubeSat.


The Operation Start Date of the RAIDS Instrument is June 2010.


The Solar Panels of the EURECA Spacecraft is Twin deployable/retractable panels of silicon solar cells.


The Security Perimeter of the DCU Data Control Unit is Excludes OBSW.


The Spatial Resolution of the LISS-3 Camera is 23.5 m.


The Mass of the SGR-ReSI Interface Unit is 1.5 kg.


The Center Frequency (GHz) of the Antenna Reflector is 23.8.


The Space Walk Duration of the Skylab Space Station is Three and a half hours.


The Objective of the OMPS UV Hyperspectral Imaging Spectrometer is Measure the total amount of ozone in the atmosphere and the ozone concentration variation with altitude.


The Calibrations of the HARP-2 Polarimeter is Frequent lunar and solar.


The Operating Frequency of the OSCAT-3 Radar Scatterometer is 13.515 GHz.


The Reaction wheels of the BEESAT-2 Satellite is Yes.


The Incidence Angle of the P Mode Observation Mode is 20º~50º.


The Propulsion Type of the Eurostar E3000 Satellite Platform is Electric (plasma) propulsion.


The Propellant Mass of the Satellite Satellite is ≤ 80 kg.


The Inclination of the Satellite Spacecraft is 56.2º.


The Wavelength Range (VIS) of the Sentinel-4/UVN Instrument is 400-500 nm.


The Antenna Facilities of the DSN Communication System is Goldstone, Madrid, and Canberra.


The Sample Rate of the QuakeSat Satellite is Unknown.


The Launch Date of the Unicorn-2L, -2M and -2N Satellites is December 1, 2023.


The Exposures of the XMM-Newton X-ray Telescope is Long, uninterrupted, detailed.


The Ground Outage Period of the INTEGRAL Satellite is 4 to 6 h.


The Altitude of the Iris Video Camera Camera is 360-460 km.


The Bandwidth of the Band 2 Spectral Band is 433-453 nm.


The FOV Azimuth of the SAGE-III Instrument is ± 185º.


The | of the Eduard P. Kontar Author is Eduard P. Kontar.


The Technology and Resource Legacy of the ZACUBE-1 Satellite is Leveraged for ZACUBE-2.


The Downlink Capacity of the Tandem-L Satellite is ~ 8 TB/day.


The Altitude of the Atmospheric Chemistry Experiment (ACE) satellite Satellite is Low.


The Satellite Count of the Dnepr Rocket Rocket is 37.


The Main Challenges of the MERLIN Satellite is Implementing a complex LIDAR instrument on a small satellite platform with limited resources.


The Data Processing Unit of the SAMPEX Satellite is Common DPU.


The Function of the GNSS-RO Instrument Instrument is Track navigation satellite radio signals as they dip below, or rise from, the horizon and detect tiny changes in the radio signal related to the density of the atmosphere.


The Measurement Error of the Temperature Sensor is ±3ºC (-50 to +400ºC), ±8ºC (+400 to +600ºC).


The Function of the MSU-MR Instrument is Global and regional cloud cover mapping, SST (Sea Surface Temperature), and LST (Land Surface Temperature).


The Total Power Requirement of the EPS Electrical Power Subsystem is Around 679 W.


The Agency of the SVOM Satellite is CNES, CNSA.


The Maximum Weight of the MS-2 Minisatellite is 200 kg.


The Architecture of the ICE Satellite Electronics is Modular design with integrated RF and digital design technologies.


The Operating Frequencies of the SMMR Microwave Radiometer is  37.0 GHz.


The Flight Experience Presentation Date of the BIRD Onboard Navigation System Navigation System is Dec. 3-7, 2001.


The Power Production with One Wing Failed of the SAWs Solar Array Wings is Unknown.


The Number of Bands of the NIR Detector is 80.


The SRP Acceleration of the M1S/M2S Satellite is 138 nm/s2.


The Measurement of the Electrostatic Gravity Gradiometer (EGG) Instrument is Gravitational field of the Earth.


The Global Capacity of the Telesat Lightspeed Satellite Constellation is 15 terabit/s (Tbit/s).


The Cargo Weight of the Crew Dragon Spacecraft is More than 500 pounds.


The Type of the On-board Computer Processing Systems Satellite is Powerful complement.


The Test Duration of the Tianzhou 2 Robotic Cargo Spaceship is 47 minutes.


The Vertical Resolution Requirement of the OMPS UV Hyperspectral Imaging Spectrometer is Not provided.


The Cargo of the CRS-19 SpaceX Dragon Mission is Microscopic organism, rotifers.


The Spatial Resolution of the SAR Sensor Subsystem SAR Sensor is 3 m x 3 m.


The Launch Date of the Simon Bolivar Satellite (VeneSat-1) Communication Satellite is October 29, 2008.


The Chinese Optical instruments of the CBERS Satellite is URL: http://dragon2.esa.int/landtraining2008/pdf/D1L3b_Optical_Li.pdf.


The Tracking Stations of the QZS-1/Michibiki Satellite is Chofu, Singapore, Sydney, Maui, and Tahiti.


The Purpose of the Microage Experiment is Examine synthetic muscle cells in orbit.


The Purpose of the GEOTAIL Satellite is Determine the role of the distant and near-Earth tail in substorm phenomena and in the overall magnetospheric energy balance and relate these phenomena to external triggering mechanisms.


The Observation Period of the RECCAP-2 Satellite Mission is 2009-2018.


The Purpose of the Next-generation telescopes Telescopes is Directly image Earth-size exoplanets.


The User Interface of the CMS Constellation Management System is Simple and robust.


The Energy Source of the Pulsar Neutron Star is Emission seen by all three telescopes.


The Mass of the Sapphire Satellite is 148 kg.


The Mirror Type of the SeaWiFS Satellite is Rotating half-angle mirror.


The Development of the RISING-2 Microsatellite is By Tohoku University and Hokkaido University.


The References of the CIMR Satellite Mission is Climate change resulting in ocean warming, sea level rise, and sea ice melting has consequences for the global economy, navigation, and security.


The Presentation Date of the ASIM Gamma-ray Detector is Jan. 21, 2009.


The Unknown of the Ground-based experimental facility Facility is Unknown.


The Transmission Profile FWHM of the Lyot-Michelson Filter System Optical Instrument is 76 mÅ.


The Demonstration Duration of the BEAM Expandable Habitat is Two years.


The Laser Technology of the DIAL Instrument LIDAR is 2.05 µm.


The Aperture Diameter of the Geoton-L1 imager Optical Subsystem is 50 cm.


The IFOV/line (pixels/scan line) of the MWHS Microwave Humidity Sounder is 98.


The Total mass of assembly of the STRV-1d DHS Data Handling System is 1.2 kg.


The PFM Manufacture Status of the MSASI Imager is Started.


The Manufacturer of the OMPS UV Hyperspectral Imaging Spectrometer is BATC (Ball Aerospace & Technologies Corp.).


The Usage of the GHOST Software Package is Routinely to support many missions (GRACE, CHAMP, TerraSAR-X, TanDEM-X, PROBA-2).


The Optics Field of View of the Wide-angle camera Camera is 65.8°.


The GSD of the Spectral Band A Spectrometer is 5.


The Field of View (FOV) of the Sun Sensor Sensor is 4º.


The Number of Satellites of the Starlink Satellite Constellation is 835.


The MS B1 of the Pushbroom imager Spectral Band is 0.45-0.52 µm.


The Operating Bands of the RCU Radiometer Calibration Unit is K- and Ka-bands.


The Deployable Antennas of the Satellite Communication Satellite is Four.


The Ground speed of the KOMPSAT-3A Satellite is 7.02 km/second.


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


The Document URL of the EUMETSAT Satellite Data Service is http://www.eumetsat.int/website/wcm/idc /idcplg?IdcService=GET_FILE&dDocName=PDF_DMT_112370&.


The Material of the Flywheel Satellite Component is Silicon nitride.


The Launch Site of the SOCRATES Microsatellite is TNSC (Tanegashima Space Center), Japan.


The Size of the PCU Power Control Unit is Compact.


The Installation Date of the Cupola Window is Feb. 2010.


The Purpose of the PLS Plasma Instrument is Measure plasma and ionized particles around the outer planets and to measure the solar wind’s influence on those planets.


The Stowage Date of the ShadowCam Instrument is 12 August 2021.


The Mission Extension of the TIMED Satellite is Fourth Time.


The Charge / Discharge Cycles of the Supercapacitor Energy Storage Device is Millions.


The Launch Date of the Himawari-8 Satellite is October 7, 2014.


The Data Collection Period of the Ozone Monitoring Instrument (OMI) Instrument is March 25 through April 25 for 2020.


The Sample Collection Date of the OSIRIS-REx Spacecraft is Oct. 20, 2020.


The Builder of the ISEE-1 Spacecraft is NASA.


The Images Acquired of the Pleiades Satellite is More than 150.


The Data of the MODIS Satellite is NDVI anomaly: it contrasts vegetation health from March 29 to April 5, 2016, against the long-term average from 2000–2015.


The Data Transfer Rate of the XCOM X-ray Communication System is Gigabits per second.


The Spin Rate of the Y-Thomson mode Control Mode is 2º/s.


The Spatial Resolution of the Sea Surface Salinity (SSS) Measurement is 5 km.


The Mission Session Date of the OceanSat-2 Satellite is February 08-19, 2010.


The Array Power Peak of the DSX Spacecraft Payload Module Satellite is 790 W.


The Delivery Date of the Argos-3 Onboard Instrumentation is 2002.


The Instrument Manufacturer of the OSCAT-3 Radar Scatterometer is ISRO.


The Creation Date of the 3D Map Map is 13 January 2021.


The Detection Capability of the OMI Satellite Instrument is Volcano Emissions.


The Spacecraft of the Orbital ATK Launch Provider is Cygnus.


The Coordinates of the Image Data is 230.77ºE/73.95ºN.


The Travel Time to Asteroid of the OSIRIS-REx Spacecraft is About two years.


The IFOV motion (jitter) of the Spectrometer Spectrometer is < 50 µrad/axis.


The Size of the BRITE spacecraft Satellite is 200 mm x 200 mm x 200 mm.


The URL of the GRAIL Mission is http://discovery.nasa.gov/grail.cfml.


The Mass of the GEISAT Precursor Satellite is 17.4 kg.


The Use of the Lemur-2 Satellite is Track maritime, aviation, and weather activity from space.


The Operating Frequency of the OSCAT Scatterometer is Ku-band of 13.515 GHz.


The Single Shot Accuracies of the TOR Payload is 3-4 cm.


The Components of the Ground Station Ground Station is 9.1m S-band antenna, 4.6 m C-band antenna, antenna controllers.


The CEO of the SpaceLink Satellite Network is David Bettinger.


The Hydrogen Gas Temperature of the Sun's Lower Atmosphere Celestial Body is 10,000ºC.


The URL of the SEXTANT X-ray Timing and Navigation Technology is http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20150001327.pdf.


The Interface of the S-band transceiver Communication Device is UART link with the RIU, 1553 RIU interface with the OBC.


The RF Power of the Ka-band Channels Communication System is 46 W/channel.


The Launch Date of the EyeSat Smallsat is 2019.


The Hot, Diffuse Gas in the Haloes Percentage of the Universe Cosmology is 5 percent.


The Coating Material of the Primary Mirror Optical Component is Boron carbide (B4C).


The Installation Date of the SpaceChain's multisignature blockchain payload Blockchain Payload is 2020.


The Launch Date of the IXPE Satellite is December 2021.


The First Marsquake Detection Date of the Seismic Experiment for Interior Structure (SEIS) Seismometer is April 6, 2019.


The Temporal Baseline of the GF-3 SAR Satellite is Nearly 4 months.


The Release Date of the HimawariCast Newsletter Document is 8 November 2016.


The Production Capacity of the OneWeb Satellites Satellite Manufacturer is Two satellites a day.


The Orbit Period of the ALMASat-1 Satellite is 103 minutes.


The Number of Detectors of the OLI Imaging System is 6500 per multispectral band, 13000 for the panchromatic band.


The Data Output of the CCD (Charge-Coupled Device) Imaging Device is 10 bits.


The Cooling Temperature of the Radiative Cooler Cooling System is 83 K.


The Downlink Data Rate of the Frontier Radio Radio is Up to 2 Mbit/s.


The Abbreviation of the HRWS SAR Instrument is High-Resolution Wide-Swath SAR.


The Purpose of the Model Scientific Model is Predict whether pulsars detected in gamma-rays could also be expected to appear in X-rays.


The ITU Approval of the Starlink Satellite Network is Required.


The Arrival Date in Europe of the ExoMars Lander Platform Lander Platform is March 21, 2019.


The Nadir Orientation Duration of the PSSCT-2 Satellite is 4 hours.


The Specific Impulse of the Chemical Propulsion Thrusters Orbit Maintenance is 291 seconds.


The Interface of the CPUT STX S-band Transmitter is 7 dBi S-band patch antenna.


The Complexity of the Micro-gravity experiment Experiment is Most complex one so far.


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


The Vision of the James Webb Space Telescope Space Telescope is Improved.


The Original Design Application of the Sabertooth Parallel Processing Unit is Machine-learning.


The Mass of the Neutrinos Subatomic Particles is Nearly massless.


The Mission Start Date of the MMS (Magnetospheric Multiscale) Mission Satellite is 2014.


The Measurement Purpose of the CryoSat-2 Satellite is Collect measurements for scientific research.


The Number of Channels of the MTVZA-GY Radiometer is 29.


The Announcement Date of the Vega Flight VV17 Rocket is 18 December 2020.


The Accuracy of the CERES Instrument is 0.5%.


The Deorbit System of the Spacecraft Satellite is Sail.


The Failure Date of the Vega Flight VV17 Rocket is 17 November 2020.


The Return Cargo Weight of the Cargo Dragon Spacecraft is 5,200 pounds.


The Total Firing Time of the Y-axis Bang-Bang Maneuver Satellite Maneuver is 60 seconds.


The Ground Sample Distance (GSD) of the MESSR Radiometer is 50 m.


The Energy Forms of the Cygnus A jet Black Hole Jet is Kinetic energy, heat or radiation.


The Launch Date of the SOHO Satellite is December 2, 1995.


The Maximum Range of the ARTEMIS Spacecraft is 1.5 million km.


The Thermal Control of the LARES Satellite is None.


The Image Capture Date of the SOHO Satellite is Jan. 14, 2014.


The Structure of the Sentinel-5P Satellite is Hexagonal.


The Development Status of the ABEX CubeSat is In development.


The Visits per Day of the Pléiades Neo constellation Satellite Constellation is Doubles the number of visits per day anywhere on Earth.


The Detector Resolutions of the FLIR Boson camera Thermal Imaging Camera is 640 x 512 or 320 x 256.


The Development Status Presentation Date of the Spacecraft Fire Experiment (Saffire) Experiment is July 13-17, 2014.


The Structure of the KOMPSAT-6 Satellite is Integrated structure with hexagonal cross section.


The Material of the SPEQS Baseplate is Titanium.


The Altitude of the Satellite PAZ is 514 km.


The Data Throughput of the BIROS Satellite is Unknown.


The Configuration of the NGAVGS Sensor is One box.


The Wavelength FWHM of an unresolved line of the Spectrometer Instrument is 0.111 µm.


The Global Coverage Time for Altimetry Observations of the Sentinel-3B Satellite is After completion of the reference ground track of 27 days.


The SAR Payload Orbital Altitude of the RCM Satellite is 600 km.


The Image Processing Rate of the ASAP-Light Camera System is 100 images/s.


The Data Product Cadence of the MAG Sensor Sensor is 1 message per 0.874 seconds.


The Angle Resolution of the FSS Fine Sun Sensor is Up to 0.03º.


The Frequency of the MWHS-2 Satellite Instrument is 183 GHz.


The Transmission Duration of the Galileo probe Space Probe is 57 minutes.


The Type of the Space Magnetometer Sensor is Anisotropic magnetoresistive hybrid sensor.


The Additional Payloads of the SENSE Satellite is CTECS (Compact Total Electron Content Sensor) and a micro dosimeter.


The Quantity of the Dove Satellites CubeSats is 88.


The BAA Framework Issuance Frequency of the NRO National Reconnaissance Office is Multiple times per year.


The Deployment Date of the QARMAN CubeSat is 2019.


The Slew Rate of the ISS Platform Platform is 0.067º/s.


The Conference Presentation of the NanoSail-D Satellite is April 9-11, 2008.


The Launch Date of the IRNSS-1D Satellite is March 27, 2015.


The RF Communications of the Spacecraft Satellite is 0.1 W (VHF beacon).


The Syndicate Members of the Heinrich Hertz Satellite is Tesat-Spacecom GmbH, Audens Telecommunications Consulting, DLR/GSOC, SciSys Deutschland GmbH, HPS, INVENT, Astrium, Inradios GmbH, Dresden, and DLR/IKN.


The Measurement Category of the VHRR Instrument is Cloud type, amount and cloud top temperature, Liquid water and precipitation rate, Radiation budget, Multi-purpose imagery (land), Surface temperature (land), Albedo and reflectance, Surface temperature (ocean), Atmospheric Winds.


The Objective of the DART Mission is Demonstrate a kinetic impact on a small asteroid.


The Last ?V Maneuver Date of the Satellite Spacecraft is July 8, 2014.


The Researchers of the SMART Satellite is Ben-Gurion University (BGU) researchers.


The URL of the Shuttle Radar Topography Mission Satellite Mission is http://www2.jpl.nasa.gov/srtm/.


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


The Enhancement of the Navigation Antenna Antenna is More powerful.


The Number of Pixels of the Imager Camera is 4008 x 2672.


The Telemetry Ku-band of the RF communications Communication Subsystem is 0.1 W, 500 kbit/s.


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


The  Spacecraft control of the DSX Spacecraft Payload Module Satellite is 3-axis stabilized.


The Launch Date of the Vigilance Mission (KSF1) Satellite Cluster is End of June.


The Polarization of the StriX-α SAR Satellite is Single polarized (VV).


The Operational Cadence of the Instrument Satellite Instrument is Rotate 120º in < 2 minutes to space view.


The Test Location of the EMC Testing Test Type is Anechoic chamber either at USSC or SSTL premises.


The Polarization Channels of the SGLI Imager is 2.


The Developer of the Temperature Sensor Sensor is High School Students of Geymonat (Tradate, VA, Italy).


The Bit Size of the Event Data Structure is 64-bit.


The Provider of the Next generation solar cells / Azur Solar Cells is Azur Space GmbH.


The Data Rate of the OGS Optical Ground Station is 80 Mbit/s.


The Orbital Position of the Meteosat-11 Geostationary Satellite is 0 º.


The Frequency Bands of the RA/HY-2 Radar Altimeter is Ku-band and C-band.


The Material of the Mandrels Manufacturing Component is Aluminum.


The Application of the LISS-3 Linear Imaging Self-Scanning Sensor is Land and water resources management.


The Design Life of the S/C Satellite is One year.


The Launch Date of the SMART-1 Satellite is 27 September 2003.


The Sensitivity of the MWHS-II Microwave Humidity Sounder is 1.1 K.


The Star Magnitude Range of the Fast Cameras Camera is 4 to 8.


The Design of the Cameras Imaging System is Monochromatic with optical filters.


The Nominal SNR of the Band 1 Spectral Band is 1000.


The Publication Year of the Observation of the Earth and Its Environment Book is 2002.


The Principal Investigator of the TROPICS Constellation of CubeSats is William Blackwell of MIT/LL (Massachusetts Institute of Technology'/Lincoln Laboratory).


The Satellite Quantity of the CM1 Satellite is 2.


The Source of Mid-tropospheric CO2 of the AIRS Satellite is Airflow into the mid-troposphere from the near surface.


The Sensor Quantity per Spacecraft of the Tri-TIP Instrument is 2.


The Launch Date of the HISUI Hyperspectral Imager is Unknown.


The Radiometric Calibration of the Payload Satellite Payload is Continues to be maintained.


The Contact Email of the MEVIµS Satellite is eoportal@symbios.space.


The Age of the Cosmic Microwave Background (CMB) Remnant of the Big Bang is 380,000 years.


The Growth Requirement of the Space Moss Moss is Only a small area for growth.


The Launch Time of the GRIFEX 3U CubeSat is 14:22:00 UTC.


The Power Supply of the SI-300 Satellite Bus is Li-ion battery and four deployable solar panels.


The Operator of the TacSat-2 Satellite is US military.


The Components of the Orion spacecraft Spacecraft is Avionic computers, harnesses, propulsion system, 12 engines, 11 parachutes, 16-foot-diameter heat shield, forward bay cover and numerous other systems and components.


The Data Usage of the SMAP Satellite is Analyzing this moisture can tell you whether there is enough water for plants to function properly and to achieve an optimal yield.


The Autonomous Maneuver Capability of the BIROS Minisatellite is Yes.


The Protocol Version of the DCPS Data Control and Processing System is SSP protocol version 2.1.


The Downlink Frequency of the EROS-A Satellite is X-band.


The Performance Prediction of the TanDEM-X Satellite is Not provided.


The Conference Session of the PSAT Satellite is Pre-Workshop Session 4: Lessons Learned.


The Function of the Kodiak system Lidar is Provide real-time images and distance-ranging information.


The Study Location of the Stardust Grain Particle is University of Arizona.


The Identification Method of the Small- and Meso-scale Ocean Features Oceanic Phenomenon is Solely using sea surface temperature properties.


The Error (RMS) of the Magnetometers Actuator is <0.0005 Am 2.


The Coverage Area of the Satellite SAR Instrument is Varies.


The Dicke Load Measurement of the MWR Noise Injection Radiometer is During the second half of the Dicke cycle.


The Launch Date of the NewMag Magnetometer is Aug. 21, 1996.


The Interface Temperature Requirement of the LCT Optical Instrument is Lower than 15ºC.


The Backscatter Coefficient of the Satellite Satellite is -10 dB to +50 dB.


The Total Mass of the LALT Laser Altimeter is 19.1 kg.


The Power Sources of the PSU Power Supply Unit is Solar panels, battery.


The DSB noise temperature of the Millimeterwave receiver Receiver is 1000 K.


The Hinge Type of the Closeout Panels Satellite Components is Spring loaded.


The Separation Time from Launch Vehicle of the Mey-Lin (C6), Gaspard (C7), and Océane (C8) Satellites is Around 63 minutes.


The In-flight Operation Start of the NIRST Instrument Radiometer is Winter of 2012.


The Lifetime of the HaloSat Satellite is Two and a half years.


The Imagers of the HySIS Satellite is Two pushbroom imagers.


The Status of the LCTs Data Relay System is In orbit.


The Pointing Requirement of the FIPEX sensor Sensor is Along the velocity vector to within 10 degrees.


The F Number of the HSC Spectrometer Spectrometer is 3.0.


The Liftoff Date of the Sentinel-1B Satellite is 22 April.


The Date of the SWOT Hydrology Workshop Workshop is Sept. 15-17, 2008.


The Attitude of the Spacecraft Satellite is Spin-stabilized and nominally sun-pointing.


The Number of Sprite satellites of the KickSat Satellite is 104.


The Primary Detector of the Spectrometer Instrument is Electrical Substitution Radiometer (ESR).


The Mass of the TEPCE Satellite is 3 kg.


The Purpose of the GNC Technology is Improvement of the guidance algorithms, coupling of inertial measurement units with GPS for navigation, exploration of the combination of flaps and thrusters for flight control.


The Bandwidth of the Channel 2 Sensor is 200 MHz.


The Data Download Rate of the First DMC generation Satellite is 8 Mbit/s.


The Measurement of the MFI Magnetometer is Intensity and direction of magnetic field vector.


The Actuation of the FDV Fill & Drain Valve is Opened using its torquing mechanism.


The Image of the Day Date of the NASA Earth Observatory Satellite is 20 May 2022.


The Field of Regard of the L-SAR Satellite is 320 km.


The Launch Year of the Voyager 2 Spacecraft is 1977.


The Capacity of the NiH2 Batteries Power Subsystem is 8 Ah.


The Control Software of the SATLAB Configuration is RAMSES software.


The Expansion of the Universe Cosmology is Speeding up.


The Imaging Payload of the NEA Scout CubeSat is Optical.


The SWIR Range Ground Resolution of the WorldView-3 Satellite is 3.7 m.


The Maximum Sulphur Dioxide Content of Ship Fuels of the International Shipping Emission Regulations Regulation is 0.5%.


The Launch Date Control of the ORS-6 Satellite Mission is Not have the ability to dictate launch date.


The Fuel Quantity of the IRS-1A Satellite is 80 kg.


The Function of the Thales MissionLINKTM Terminal is Provides a reliable connection for voice, satellite internet, cellular data, Land Mobile Radio (LMR) and location-based applications.


The Camera Position of the LightSail Satellite is Mounted to two of the four deployable solar panels.


The Signal Frequency of the Matrix Switch Signal Routing Equipment is 1.2 GHz or 720 MHz.


The Components of the Group Delay Parameter is Clock, code generator, modulator, up-converter, transmitter, satellite antenna.


The Main Control Station of the Rumpin Ground Station is True.


The Material of the FSU FC Sensor Unit is Titanium.


The Data Archive Size of the Gaia Satellite is 1 PB.


The Sensitivity of the SIM Solar Irradiation Monitor is 0.2 W m-2.


The Inclination of the Swarm-A and Swarm-C Satellite Constellation is 87.35 º.


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


The Launch Dates of the iMESA Technology is MISSE-7(ISS), iMESA 2009-2011.


The Components of the SLOSU Instrument Unit is OME (Opto-Mechanical Enclosure), thermal radiators, FEE (Front End Electronics), the cooling system, and DA (Detection Assembly).


The Launch Date of the OSCAT Scatterometer is September 2009.


The Spatial Resolution of the OSCAT-3 Radar Scatterometer is 25 km.


The Operation End Year of the SAR-Lupe Satellite System is 2017.


The Clear Aperture of Telescope of the DubaiSat-2 Satellite is 40 cm.


The Ground Coverage of the Detector Sensor is 79 m.


The Technology Development Funding of the MAST Satellite is NASA Small Business Technology Transfer (STTR) contract.


The Orbit of the SARAL spacecraft Satellite is Sun-synchronous near-circular dawn-dusk orbit.


The Unknown of the SOVIM Instrument is Unknown.


The Mission End Date of the DSCOVR Satellite is Unknown.


The Impact of the Argo Ocean Observation System is Provided data for climate projections.


The Period of Performance of the JPSS-3 and -4 Satellite is Through 2026.


The Spatial Resolution of the Geodesy Inertial navigation system Satellite is 100-1000 km.


The Orbit Inclination of the 3U CubeSat Satellite is 97.44º.


The SWIR Resolution of the PROBA-V Satellite is 1024 pixels.


The Instrument Suite of the EPI-Hi Particle Measurement Instrument is IMPACT.


The SRAM of the OBC On Board Computer is 2 MB.


The Control Handover of the Stamp9G20 microcontroller Microcontroller is Acquires control of the shared flash memory.


The Radar Measurements Spatial Resolution of the L2SMAP Soil Moisture Product is About 9 km.


The Launch Vehicle of the SOCRATES Microsatellite is H-IIA.


The Latency Requirement of the S-1 NTC Product is Within 20 days.


The Developers of the SoloHI Instrument is Russell A. Howard, Angelos Vourlidas, Clarence M. Korendyke, Simon P. Plunkett, Michael T. Carter, Dennis Wang, Nathan Rich, Donald R. McMullin, Sean Lynch, Adam Thurn,; Greg Clifford, Dennis G. Socker, Arnaud F. Thernisien, Damien Chua, Mark G. Linton, D.


The Type of Array of the NIR Detector is HgCdTe.


The Measurement Cadence of the DSCOVR Satellite is 1 sample per minute.


The Cone Half-Angle of the O/OREOS nanosatellite Satellite is Less than 13o.


The Viasat Partnership Date of the Satellite Vu Company is 28 September, 2022.


The Failure Cause of the MRSE Instrument is Arcs of the high-voltage cathode supply at the TWTA connections in the low-pressure environment (vacuum) of the Shuttle orbit.


The Detector Temperature of the TIR Subsystem Imaging System is 80 K.


The Funding of the GIDAS Project is Co-funded basis.


The Experiment of the IRT Saint Exupéry Research Institute is Using a form of artificial intelligence called ‘deep learning’ to recognize patterns such as cloud formations or fires on Earth.


The Launch Contractor of the OCO-2 Spacecraft is ULA (United Launch Services LLC).


The Redshifts of the NISP Spectrograph Instrument is About 30 million emission line galaxies.


The Control Algorithm of the EIRSAT-1 Satellite is ‘Wave based control' algorithm.


The Mass of the IOF Plasma Wave Instrumentation is 12 kg.


The Bus Name of the NorSat-1 Satellite is GNB (Generic Nanosatellite Bus).


The Retroreflectors of the Ralph and Norton Satellite Components is Mounted on the exterior surfaces.


The Deployment Sequence of the Drag Augmentation Device Satellite Component is 1) The microprocessor control board receives twice a command from the Main Unit 2) A lock mechanism for the extension boom turns off with DC motor 3) The lock mechanism for the 350 mm x 3000 mm kapton film turns off with DC motor 4) The boom extends and d.


The Antenna Size of the KaRIn Instrument is 5 m x 0.25 m.


The Error (RMS) of the Nadir sensor Sensor is <0.2º.


The Congress Date of the BEESAT-3 Satellite is Sept. 10-12, 2012.


The Establishment Date of the Sentinel Asia Disaster Risk Management System is May 2005.


The Nadir ground resolution (IFOV) of the 16 mm camera Camera is 370 m x 370 m.


The Manufacturer of the ATSR-1 Instrument is RAL, UK (British Aerospace as prime contractor); CRPE, France, and CSIRO, Australia.


The Subject of the Micro-gravity experiment Experiment is Multi-layer heat capillary convection.


The Implementation Date of the QZSS L1-SAIF Message Generator Device is Jan. 28-30, 2008.


The Active Diameter of the L3 Detector Detector is Large enough to intercept even the widest-angle trajectories defined by the L1•L2 coincidence.


The Minimum Impulse Bit of the CNAPS Propulsion System is 0.7 mNs.


The Field of View of the HPT High Precision Telescope is 1.9 km x 1.4 km.


The Orbit Inclination of the Rocket 3.3 Rocket is 86º.


The Attitude Control Algorithms of the ADCS Attitude Determination and Control Subsystem is Runs.


The Spin Axis Inclination of the Zeta Puppis Star is (24 ± 9)º.


The Modulation of the Payload Imagery Imaging is OQPSK (Offset Quadrature Phase Shift Keying).


The ROM of the OBC Onboard Data Handling is 16 kB.


The Telescope Diameter of the DIAL Instrument LIDAR is 40 cm.


The Maximum Mass of the Payload Satellite Payload is Up to 600 kg.


The Direction of the Comedia C328 Camera is Pointing in the direction of the balloon.


The Number of Geographic Sites of the PUTC Program is 69.


The Conceptualized Name of the KhalifaSat Satellite is DubaiSat-3.


The Affiliation of the JEM-X X-Ray Monitor is DSRI (Danish Space Research Institute), Copenhagen, Denmark.


The Field of View (FOV) of the WISPR Imager is 180º.


The Telescope Energy Range of the ASTRO-H Mission is E ~ 0.3-12 keV.


The Manufacturer of the NOAA-20 Satellite is Ball Aerospace.


The Diagnostic Technique of the Solar Flare Solar Event is Helioseismic holography.


The Focal Length of the 4-band CCD Imager Instrument is 32 mm.


The Time on ISS of the CIMON-1 Prototype is 14 months.


The Launch Center of the BeiDou/Compass satellites Satellite is XSLC (Xichang Satellite Launch Center).


The Existence of the Dark Radiation Hypothetical Radiation is Possible in the early cosmos.


The Energy Range of the Electron Spectrometer Instrument is 1 eV to 1400 eV.


The Funding Round Amount of the Satelles PNT Service Provider is $26 million.


The Constellation Concept of the PAZ-TerraSAR Constellation Satellite Constellation is Coordinated Constellation Concept (CCC).


The Launch Date of the Hera Mission is Unknown.


The Pointing Platform Provider of the Iris video camera Camera is RSC Energia of Kaliningrad, Russia.


The Study Importance of the Blue Ring Nebula Nebula is Show us what they look like so we can identify more of them.


The Number of Satellites of the Galileo Satellite Constellation is 8.


The Energy of the W-band Band is 0.3 meV.


The Storage Capacity of the SSR Solid State Recorder is 3.1 Tbit @ EOL.


The Spotlight High Resolution (HS) Spectral Resolution of the TSX-SAR Satellite is 1m.


The Sensor Type of the MuREM Dosimeter is RADFET (Radiation-sensitive Field Effect Transistor) solid-state dosimeters.


The Platform of the Deimos-2 Satellite is SpaceEye-1.


The Antenna Beamwidth of the Satellite Satellite is 1.33º (Ku-band), 5.25º (S-band).


The Flight Software of the SOURCE 3U CubeSat Satellite is Being developed and tested in parallel.


The Launch Date of the Aeolus Satellite is 2018.


The Calibration Method of the OVIRS Spectrometer is Using NIST traceable calibrated blackbodies and flood sources.


The Launch Vehicle of the SMART-1 Satellite is Ariane-5G.


The Deployable Solar Array Type of the UK-DMC-2 Satellite is Emcore triple-junction InGaP/InGaAs/Ge solar cells.


The SAR Interferometry Image Pair Time Interval of the Sentinel-1A and Sentinel-1B Satellites is 6 days.


The Number of Planet Candidates Identified of the Kepler Satellite is 1,235.


The In-Flight Calibration of the MSU-E Multispectral Scanner is Not Performed.


The Servicer Capture Mechanism of the ELSA-d Mission is Magnetic.


The URL of the SCARLET Advanced Array Solar Array is http://nmp.nasa.gov/ds1/tech/scarlet.html.


The Data Storage of the SSMM Solid State Mass Memory is Unknown.


The Operational Modes of the VRSS-1 Satellite is Real-time imaging mode, Quasi real-time imaging mode, Recording mode, Replay mode.


The Azimuth Resolution of the Radar Sensor is Approximately 400 m.


The Target of the External Calibration Calibration is Sky in an inertial attitude.


The Vehicle of the Orbital ATK Launch Provider is Antares.


The Alignment Type of the Helical Antenna Antenna is Self-Aligning.


The Spectral Range of the CLARREO Satellite is 5 to 50 µm.


The Value of the Agreement with ABDAS Imaging Satellite Access is $38 million.


The Presentation Date of the DLR FireBird Constellation Satellite Constellation is May 30-June 3, 2016.


The Clock Stability Requirement of the DSAC Demonstration Unit is AD of at most 2.0 x 10-14 at one day.


The Size of the TurkSat-3USat Nanosatellite is 10 cm x 10 cm x 30 cm.


The Mean Sea Level Change Error Budget of the Jason-3 Satellite is External geophysical correction: 0.1 mm/yr, Orbit drift: 0.1 mm/yr, Microwave radiometer wet troposphere correction: 0.7 mm/yr, Sigma naught (σο) drift impact on sea state bias through wind speed): 0.1 mm/yr.


The Collaboration with Other Government Agencies of the NASA Organization is National Oceanic and Atmospheric Administration (NOAA) and the National Reconnaissance Office (NRO).


The Input Power of the HET-X Hall-effect Thruster is 350 - 2500 W.


The URL of the NASA Satellite Satellite is http://www.nasa.gov/press-release/nasa-satellite-finds-unreported-sources-of-toxic-air-pollution.


The Link Establishment of the LLITED satellites Satellite is Beacon and proper serial number code.


The Diameter of the Asteroid 1999JU3 Asteroid is About 900 m.


The Minimum Battery Voltage of the IXV Spacecraft is 30.8 V.


The Sensor Complement/Experiment of the TechnoSat Nanosatellite is Camera, Fluiddynamic Actuator, S-band transmitter HISPICO, Laser Retroreflectors, Solar Generator Impact Detector, Star Tracker STELLA, Reaction Wheel System.


The Commissioning Start Date of the XRS instrumentation Instrumentation is End of November 2007.


The Pixel Pitch of the PamCam Panoramic Camera is 6.7 µm.


The Launch Date of the CBERS-2 Satellite is Oct. 21, 2003.


The Next Launch Date of the Falcon 9 Rocket is February 5.


The Measurement Data Noise of the EGG Gradiometer is Slightly higher-than-expected.


The Mission Type of the QBITO CubeSat is EO.


The Launch Date of the SEEDS-2 Satellite is April 28, 2008.


The Availability of the Matera ground station Ground Station is For L-band SAR imagery downlinks.


The Impact of the Climate Models Computer Models is Helped scientists separate natural changes in the Earth's climate from human influences.


The Packaging and Mass Efficiency of the Drag Sail Modules Satellite Component is Superior or competitive to state-of-the-art solar sails.


The Ground Target Distance Between Adjacent Passes of the KOMPSAT-5 Satellite is 95 km (at equator).


The Field of View of the UVS Instrument Spectrometer Telescope is 0.071º x 0.75º.


The Spin Rate of the Stars Celestial Bodies is Varies.


The Scintillator Size of the Gamma-ray Counter Detector is 12 cm x cm.


The Pixel Size of the Copernicus Sentinel-1 Satellite is About 30 m.


The Peak Detection Rate of the COM DEV NTS Receiver AIS Receiver is 35 Messages/s.


The Logo Release Date of the Hera Mission is 3 May 2019.


The Data Gathering Period of the Gaia Satellite is Full nominal mission plus the first 6 months of the mission extension (66 months in total).


The Interface Temperature of the Power Laser Head Subsystem is 0.5 K.


The Frequency of the Transmitter Communication Device is 5.84 GHz.


The Orbit Eccentricity of the Gravity Gradient Stabilization Attitude Control System is About 0.07.


The Maximum ΔV of the Spacecraft Satellite is 85 m/s.


The Altitude of the Satellite Imaging Satellite is 681-709 km.


The Propulsion System Capacity of the ESPA Ring Interface is 344 kg.


The Platform Type of the SSTL-300 Satellite is EO Small Satellite.


The Vertical Scan Emphasis of the MLS Microwave Limb Sounder is Lower stratosphere and upper troposphere.


The Seasonal Cycle of the Carbon Dioxide Ice Substance is Unfolds over the comet's 6.5 year orbit.


The Mission Status of the Sentinel-5P Satellite is Pre-operational.


The Storage Capacity of the KazEOSat-2 Satellite is Up to 4000 km.


The Altitude Range of the RAIDS Instrument is 100 to 200 km.


The Development Partners of the Telerobotics Space Technology is ESA, DLR.


The Bus Type of the SPOT-6 & SPOT-7 Satellite Constellation is AstroBus-L (or AstroSat250).


The EFL of the COR1 Coronagraph1 imager is f/20.


The URL of the Microsat Satellite is https://web.archive.org/web/20180125015338/https://www.isro.gov.in/Spacecraft/microsat-0.


The Conference Date of the European Re-entry Program Program is Aug. 19-22, 2013.


The Potential Forest Map Frequency of the Tandem-L Satellite is Weekly basis.


The Imaging Modes of the PAZ Satellite is Four.


The Energy Range of the EPI-Hi Particle Measurement Instrument is MeV.


The Operator of the SORCE Satellite is LASP (Laboratory for Atmospheric & Space Physics) of the University of Colorado.


The Battery Cells of the EPS Electric Power Subsystem is 4.


The Perigee of the IBEX Spacecraft is 7,000 km.


The Spatial Resolution of the LISS III Sensor is 23.5 m.


The Sample Exposure Time of the METIS Investigation is More than 200 days.


The Reentry Date of the SMDC-ONE Nanosatellite is January 12, 2011.


The LRIT and HRIT Broadcasting Service Start Date of the GK2A satellite Satellite is 2011.


The Radar Frequency of the SeaWinds Scatterometer Scatterometer is 13.4 GHz (Ku-band).


The Messaging Capability of the ODTML Data Collection System is Two-way delay-tolerant.


The Total Imaging Area of the Pleiades Satellite is 40,000 km2.


The Inclination of the Iris Video Camera Camera is 51.6º.


The Type of the VHRR Instrument is Imaging multi-spectral radiometers (vis/IR).


The Instruments of the Variant Satellite is Split Langmuir probe, Rogovsky coil, Faraday cup.


The Mission Duration of the OSIRIS-REx Spacecraft is Two years.


The Orbit Maneuvers of the THEMIS (and ARTEMIS) spacecraft Satellite is 19 maneuvers between Sept. 25 and Oct. 22, 2013.


The Mass of the EPE Energetic Particle Experiment is 3.3 kg.


The Ion Temperature of the PAP Plasma Analyzer is 500 ~ 10,000 K.


The LTAN of the QSat Satellite is 10:00 - 14:00 hours.


The Tensional Force Criterion of the Marman Clamp band SRC Separation Mechanism is Design condition change.


The Deployment Over Operating Temperature of the RDA Deployment System is Not provided.


The Sensitivity of the NIRSpec MIRI Optical Instrument is 12 nJy (1.1 μm, τ i =10,000 s, and λ/Δλ= 4).


The Swath Width of the JL-1-GF03D Microsatellite is 17 km.


The Stability of the DSAC Atomic Clock is Orders of magnitude more stable than current spaceborne navigation clocks.


The Rainfall Measurement of the IMERG Satellite Data Product is Greater than 160 mm.


The Manufacturer of the OHRIS Imaging System is Northrop Grumman.


The LTAN of the Satellite Satellite is 10:00 - 14:00 hours.


The X-ray Light of the SS 433 Cosmic Object is Enough to officially call SS 433 a ULX.


The Development Start Date of the Landsat-9 Satellite is Oct. 25, 2016.


The Frequency Range of the SGLS Link Communication System is 1755-1850 MHz.


The SAR Antenna of the KOMPSAT-6 Satellite is Fixed SAR antenna on a panel.


The Estimated SNR of the Band 8 Spectral Band is 308.10 ± 130.92.


The Measurement Concept of the OCO-3 Instrument is OCO-3 will measure the intensity of the sunlight reflected from the presence of CO2 in a column of air.


The Optical System of the PAN Camera Imaging Device is Three-mirror off-axis reflective telescope with an off-axis concave hyperboloidal primary mirror and an off-axis concave ellipsoidal tertiary mirror.


The Lunar Penetrating Radar (LPR) of the Chang’e-4 Rover Rover is Payload.


The Pointing and Stabilization System of the ExoplanetSat Satellite is Sub-arcsecond.


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


The Production Speed Improvement of the Solar Cells Energy Device is More than 20 times faster than the process now commonly used.


The IFOV of the InSb Detector is 42.5 µrad.


The Command Uplink Speed of the NorSat-3 Satellite is Up to 32 kbit/s.


The Bandwidth of the Channel 4 Sensor is 1000 MHz.


The Deployable Solar Array Power of the UK-DMC-2 Satellite is 65 W at AM0 and 28ºC.


The Mission Selection Date of the Euclid Space Telescope is October 2011.


The Second Reaction Wheel Failure Date of the Kepler Space Telescope Space Telescope is Unknown.


The Components of the Multispectral Camera Camera is Electrooptical assembly, management and control unit, signal processing unit.


The Inclina. (º) of the Meteor-1-2 Satellite is 81.2.


The Bus Structure Material of the StudSat Picosatellite is High grade aluminum alloy (Al 7075 T6).


The Type of the Horizon sensor Sensor is 2 axis IR pyro array & chopper.


The Associated Density Perturbation of the Plasma Drifts Phenomenon is Indicated by the circled arrow.


The Sub-contractor of the Laser Transmitter Laser is Quantel.


The Status of the Vesselsat-1 & -2 Satellite is Still counting.


The Readiness of the Starliner Commercial Crew Vehicle is Ready to go.


The Type of the Solar Array Power Subsystem is Single panel.


The Launch Date of the AFSPC-11 Satellite Mission is 14 April 2018.


The Inclination of the COMPASS-2 Satellite is 78.9º.


The Dimensions of the Satellite Communication Satellite is 6m high with a width of 2 m x 2.4 m.


The Function of the TCU Thermal Control Unit is Ensure the management of the TCS and of the CSS.


The Time Between Satellites of the A-Train Satellite Constellation is About 15 seconds.


The Length of Operation of the Monitoring of HIS Calibration Process is Few minutes.


The Phase of the OPS-SAT Satellite is A-B1.


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


The Duration of the Mission of the BRITE Satellite is Longer than 2 years.


The Data Rate of the TDI Detector Detector is 3.5 Gbit/s total.


The Number of CubeSat P-PODs of the CubeSat - Launch 4 Satellite is 3.


The Formation Flying Concept Presentation Date of the TanDEM-X Satellite is Jan. 23-27, 2005.


The Potential Rocket Launch Provider of the Spacety Company is Indian rockets.


The Sensitivity of the NIRSpec MIRI Optical Instrument is 10.4 nJy (2.0 μm, τ i =10,000 s, and λ/Δλ = 4).


The Instantaneous spectral coverage of the Spectrometer Instrument is 1.53 km/s.


The Observation Location of the Orbiting Carbon Observatory-2 (OCO-2) Satellite is Las Vegas.


The Inclination of the GOMS-1 Satellite is < 0.5º.


The Height of the Rocket and Payload Launch Vehicle is 196 feet.


The Data Transmission Rate of the OCM Data Transmission System is 0.3 Mbit/s.


The Total Racks of the PM Satellite Component is 23.


The Beam Reconfiguration of the Eutelsat Quantum Satellite is Enabled.


The Compression Ratio of the KazEOSat-2 Satellite is 2.5:1.


The Magnitude of the Gaia Space Astrometric Mission is G=20.


The Measurement Domain of the Kolibri-2000 Satellite is Atmosphere, Gravity and Magnetic Fields.


The Resolution Δλ (0.10º slit) of the SPIM3 Spectrometer is 1.8 nm.


The Swath Width of the TopSAR wide Imaging Mode is 220 - 350 km.


The Launch Date to ISS of the Flock 1b Nanosatellites is July 13, 2014.


The Multispectral Imagery Collection of the R3 System Satellite is Successful.


The Data Release Date of the EPIC Earth Polychromatic Imaging Camera is July 20, 2016.


The Digital Sun Sensor FOV of the AOCS Attitude and Orbit Control System is 37º.


The Specialization of the LET spectrometer Spectrometer is Highly specialised.


The Objective of the LI System Lightning Information System is Deliver information on total lightning over the full disk.


The Calibration Target of the MAC Memory System Module is Special ground targets.


The Dimensions of the Spacecraft Satellite is 2.4 m (cylinder height), 3.7 m total height, 3.2 m diameter.


The URL of the Galileo Satellite System is http://m.esa.int/Our_Activities/Navigation/Android_smartphone_app_connects_you_to_Galileo.


The Function of the MCP Multi-Channel Plate is Multiplier.


The Operator of the Bartolomeo Platform is Airbus.


The Antenna Switch Loss of the Transceivers Communication Device is 4.5 dB.


The Mass of the ROLIS Imaging Camera is 1.4 kg.


The Number of Satellites of the Iridium-4 NEXT Mission Satellite Mission is 10.


The URL of the FedSat Microsatellite is https://web.archive.org/web/20110603203559/http://www.ips.gov.au/IPSHosted/NCRS/wars/wars2000/invited/fraser.pdf.


The Average Daily Acquisition Capability of the COSMO-SkyMed Satellite Constellation is 1800 images.


The PI of the CRaTER Cosmic Ray Telescope is Harlan E. Spence.


The Secondary Attitude Sensor of the ADCS Attitude Determination and Control System is SCDM.


The Deployment Velocity of the BEESAT-4 CubeSat is 1.5 m/s.


The Next Starlink Launch Date of the SpaceX Company is February 15.


The Composition of the Plasmasphere Plasma Region is Low-energy (low-temperature) plasma.


The Observed Phenomena of the ASIM Observation Instrument is Wide variety of phenomena in Earth's upper atmosphere.


The Design of the TCS Thermal Control Subsystem is Passive methods with MLI (Multi-Layered Insulation) blankets and thermal coatings.


The Former Name of the Copernicus Program is GMES (Global Monitoring for Environment and Security) program.


The Developer of the Venta-1 Nanosatellite is Ventspils University College.


The Altitude of the Chang'e-3 lander Lander is 4 m.


The Measurement of the IASI Infrared Atmospheric Sounding Interferometer is Infrared radiation emitted from Earth’s surface.


The Timeliness of Data Availability of the Aeolus Satellite is 3 hours.


The Imaging Resolutions of the PanGeo Fleet Satellite Fleet is From 20 m to 75 cm/ pixel.


The Wavelength Range of the InSb Detector is 2.08 - 2.35 µm.


The Material of the Optical Window Component is Fused Silica.


The Cryocooler Development Leads of the MIRI Instrument is JPL, Northrop Grumman, NASA's Goddard Space Flight Center.


The Uplink Data Rate of the Spacecraft Satellite is 9.6 or 19.2 kbit/s.


The Cadence of the Normal Cameras Camera is 25 seconds.


The Launch Date of the IRIS Spacecraft is June 28, 2013.


The Orbit (Orbit control) of the Spacecraft Satellite is ≤ ± 500 m.


The End of Life Date of the QBITO CubeSat is 16 February 2019.


The Mission Status of the DMC-3 Satellite Constellation is Operational (nominal).


The CPU of the C&DH Command & Data Handling is RAD750.


The Number of Propulsive Maneuvers of the ICE (International Cometary Explorer) Spacecraft is 15.


The Targeted Orbit Altitude of the OneWeb satellites Satellites is Roughly 450 km above Earth.


The Launches of the Galileo Satellite Satellite is 11 in 10 years.


The Field Strength of the Sunspot Solar Phenomenon is More than 6,000 gauss.


The Authors of the Solar-B EUV Imaging Spectrometer Spectrometer is J. L. Culhane, L. K. Harra, G. A. Doschek, J. T. Mariska, T. Watanabe, H. Hara.


The Landing Date of the InSight Spacecraft is 26 November.


The Launch Date of the Kleos Patrol Mission (KSF2) Satellite is April 2022.


The Data Stream Speed of the Suomi-NPP Satellite is 15 Mbit/s.


The URL of the Sentinel Data Hub Data Hub is https://senthub.esa.int/.


The Status Presentation Date of the SMOS Mission is Nov. 18-20, 2009.


The Orbit Type of the Meteor-M2 Satellite is Sun-synchronous circular orbit.


The Function of the Coprocessor Satellite Component is Real-time processing of the raw reflected GNSS data into DDMs.


The Construction Completion Date of the BDS-3 Satellite System is June 2020.


The Integration Status of the ALADIN Laser is Second flight model integration was prepared.


The Relative Geometric Accuracy of the GCP Extraction Approach Image Processing is 10 m RMSE.


The Wavelength Range of the Visible Channel Imaging Device is 0.4-1.0 µm.


The First Global Coverage Completion Date of the TanDEM-X Satellite is January 2012.


The Flight Name of the Galileo FOC-3 and FOC-4 satellites Satellite is VS-11.


The Closest Approach to the Sun of the Parker Solar Probe Spacecraft is Within 4 million miles.


The Potential Impact of the SMAP Satellite is Improve the accuracy of the soil moisture characterization in the Air Force systems.


The Radiation Hardness of the Space Comb Spectroscopy Setup is Some critical fiber components will be more deeply inspected for radiation hardness.


The Detector Separation of the Detector Instrument is Less than 12.06 mm.


The Altitude Range of the MEOSAR Search and Rescue System is 19 000 to 24 000 km.


The Ground Stations of the Genesis-2 Satellite is Las Vegas, Virginia, Alaska, Hawaii.


The | of the N. Vilmer Author is N. Vilmer.


The Backwards compatibility of the Open5GCore Rel. 4 5G Core Network is Maintaining backwards compatibility with LTE and NB-IoT [IDD and NIDD].


The X-ray Map of the XMM-Newton Satellite is Extensive.


The Training Data of the Machine Learning Algorithm Calibration Tool is Images from sounding rocket calibration flights.


The Mission Duration of the O/OREOS nanosatellite Satellite is 6 months.


The Router External Links of the SpaceWire ASIC Application-Specific Integrated Circuit is 4.


The Impact of the Solar Flares Solar Phenomenon is Capable of severely disrupting technologies on Earth such as satellite operations, GPS navigation and communication systems.


The Calibration Plan Presentation of the Microscope Space Mission is Oct. 1-5, 2012.


The Instrument of the Copernicus Sentinel-6 Satellite is Advanced Microwave Radiometer.


The Navigation of the New Horizons Spacecraft is State-of-the-art.


The Field-of-View of the Scanning LIDAR LIDAR is Ranging between 1° x 1° and 40° x 40° degrees maximum.


The Recovery Status of the NEOSSat Satellite is Successful.


The Measurement Domain of the Sich-2 Satellite is Ocean, Land, Snow & Ice.


The Reflector Half Cone Angle of the AMSR-E Instrument is 47.4º.


The Field of View of the Nancy Grace Roman Space Telescope Space Telescope is Nearly 100 times larger than Hubble Space Telescope.


The Quantity of the CubeSat Yonsei team Team is 1.


The Quantity of the Magnetometers AOCS Sensors is 2.


The Data Source of the Climate Change Initiative Program is Copernicus Sentinel-1 mission, Envisat’s ASAR instrument, JAXA’s Advanced Land Observing Satellite (ALOS-1 and ALOS-2).


The Photometer Resolution of the Nanosatellite Satellite is 26.52 arcsec/pixel.


The Measurement of the LYRA Sensor is Sun's energy intensity.


The Image Sequence Acquisition Time of the COR1 Coronagraph1 imager is ≤ 8 s.


The Star Formation Rate of the Cluster XDCPJ0044.0-2033 Galaxy Cluster is Almost two thousand solar masses per year.


The Spotlight (SL) Image Size of the TSX-SAR Satellite is 10km x 10km.


The Form Factor of the Ultra-Compact Radiometer Radiometer is 1U CubeSat.


The Payload Weight Capacity of the IPS Pointing System is Up to 7,000 kg.


The Science Phase of the TanDEM-X Satellite is 2014 to mid of 2016.


The Launch Date of the Spacecraft Satellite is 2019.


The Launch Site of the OCO-2 Spacecraft is VAFB, CA.


The Project Manager of the Europa Clipper Spacecraft is Jan Chodas.


The Launch Provider of the Eutelsat Quantum Satellite is Arianespace.


The Next Phase Decision Date of the Copernicus Satellite Program is Second half of 2021.


The Antenna Diameter of the Galileo Satellite System is 13 m.


The Acceleration Tolerance of the Procyon Star Tracker is 1°/s2.


The Effect of the Rain Clouds Weather Phenomenon is Changes ocean's temperature and salinity profiles, affects the circulation of deep water and can even affect global climate events like El Niño.


The Imaging System of the NewSat Satellite is Visible and near-infrared spectrum.


The Workshop Date of the Soil Moisture Active and Passive Mission (SMAP) Satellite Mission is Nov. 18-20, 2009.


The Pointing Accuracy of the Spacecraft Satellite is 360 arcsec.


The Platform of the Intelsat 40e Satellite is Maxar's 1300-class.


The Redundancy of the Data Handling Unit Subsystem is Half Satellite.


The Observed Altitudes of the MIGHTI Instrument is 200-300 km altitude, ~100 km altitude, 100 km altitude region.


The Build, Deployment, and Operations Cost of the RainCube Satellite is Less than $10 million.


The Battery Type of the PCU Power Conditioning Unit is Li-ion.


The Operation of the OHRIS Imaging System is Can be operated in parallel with OHIS.


The Design of the Limb Imager Telescope is Single off-axis three-mirror reflective telescope.


The Global Coverage Time of the MESSR Radiometer is 17 days.


The Mission Extension Period of the XMM-Newton X-ray observatory is 1 January 2015 – 31 December 2016.


The Presentation Date of the GCOM-W1 Satellite is June 5-12, 2011.


The Number of Off-Source Pointings of the Mode 2 Pointing Mode is 24.


The Beam-Out Events of the IPA Engine is 2 per day (nominal), less than one per week on average.


The Solar Array Power of the MTM Transfer Module is 13 kW.


The Launch Dates of the Sentinel-6 Satellite is 2020 and 2026.


The Prime Contractor of the Jason-CS / Sentinel-6 Satellite Mission is Airbus Defence and Space.


The ADCS System of the DeorbitSail Satellite is First demonstration of the CubeAIM system.


The Testing Start Date of the Galileo Second Generation Hardware Hardware is July 19, 2021.


The Mass of the S/C Structure Satellite Structure is 191.4 kg.


The Age of the Rosetta Spacecraft is Over 12 years.


The Data Rate of the Payload Imagery Imaging is 32.72 Mbit/s.


The RF Bandwidth (MHz) of the Antenna Reflector is 400.


The Up to 11 kW of the MTM Solar Arrays Power Output is The MTM solar arrays are sized to provide up to 11 kW for operating the electric propulsion system.


The Affiliation of the Scientists General is UK Committee for Antarctic Place-Names.


The Data Comparison of the HyperScout® Satellite is Copernicus data, in-situ ground truth measurements and an airborne campaign.


The Unknown of the ZY-1( 02C) Satellite Satellite is Unknown.


The Operational Modes of the GIS Instrument Satellite Instrument is Simultaneous panchromatic and multispectral (pan-sharpened), Panchromatic only, Multispectral only.


The Launch Date of the Solar-B / Hinode Satellite is 23 September 2006.


The Number of MFUU of the GIOVE-A Satellite is 2.


The Band 6 of the MSS Instrument Spectral Band is 0.7 - 0.8 µm.


The Developer of the Deep-space Communications Communications System is UK.


The Exposure Time of the Camera System Sensor is 800 ms.


The Weight of the Satellite Satellite is 770 kg.


The Detector Cooling Temperature of the SWIR Spectrometer Spectrometer is 120 K.


The Spin Rate of the SCD-2 Satellite is 32 - 36 rpm.


The Planned Lifetime of the XMM-Newton Satellite is 10 years.


The Integration Time of the PROBA-V Satellite is Continuously updated.


The Antenna Type of the Altimetry Instrument Instrument is Dual-band C/Ku center-fed antenna.


The Purpose of the PAZ Satellite is Produces radar imagery of the Earth for government and commercial use, as well as ship tracking and weather sensors, enabling high-resolution mapping of large geographical areas.


The Spectral Bands of the High-Resolution Hyperspectral Imager Imager is 220 bands.


The Pixel Size of the Kruiz CCD Detector is 9 µm x 9 µm.


The Operation of the THEIA Satellite is Attitude Control.


The | of the LEOBUS-1000 Small Satellite Platform is A Generic Small Satellite Platform for High Performance LEO Missions - LEOBUS-1000.


The Temperature Range of the Juice Spacecraft is -180ºC to 250ºC.


The Delta-Velocity of the Onboard Propulsion System Propulsion System is 17 m/s.


The Purpose of the ShadowCam Instrument is Reduce stray light from making its way to the detector.


The Destruction Cause of the SEOSat Satellite is Thruster control issue led to loss of trajectory.


The Latency Requirement of the S-3 STC Product is Within 1,5 days (36 hr).


The Required Spacecraft Stability of the Push Frame Framer with a fast steering mirror Sensor is Low.


The Actuation Method of the Electrodes Position Control is Electrostatic force.


The Attitude Navigation Solution of the NEMO-AM Satellite is 0.036° (2σ).


The Launch Mass of the ResourceSat-2A Satellite is 1235 kg.


The URL of the Rosetta Satellite is http://www.esa.int/spaceinimages/Images/2015/08/Rosetta_thermal_louvres.


The Instruments of the CASSIOPE Satellite is CER, IRM, NMS, SEI, GAP, RRI, MGF, FAI.


The Meeting Date of the FalconSAT-3 Satellite is Oct. 12-16, 2009.


The Project Date of the Small Explorer (SMEX) Satellite is March 28, 1994.


The Orbital Distance of the Planet Candidate Exoplanet is Tens of times the Earth-Sun distance.


The Equator Crossing Time of the SMAP Satellite is 6:00 a.m. and 6:00 p.m. local time.


The Spectral Resolution (5-30 keV) of the Detector Instrument is 500 eV FWHM.


The End of Life Date of the Galileo Satellite Navigation System is 22 August 2026.


The Set Point Temperature of the OPAL Camera is ~10ºC.


The URL of the High Spatio-Temporal Resolution Land Surface Temperature Mission Satellite is https://web.archive.org/web/20220808212453/https://ieeexplore.ieee.org/document/8517433.


The Attitude Knowledge of the ACS Attitude Control Subsystem is ±0.02º.


The Integration Time of the Instrument Spectrometer is 12 s.


The Orbit of the EarthDaily Constellation Satellite Constellation is Sun-synchronous.


The Material of the Pin-Puller Mechanism is 17-4 PH H900 stainless steel.


The Assessment Presentation of the BepiColombo MMO spacecraft Spacecraft is 44th ICES ( International Conference on Environmental Systems), Tucson, Arizona, 13-17 July 2014.


The Function of the Video Proximity Electronics Unit Sensor Component is Conversion of the analog signal coming from the focal plane assembly into digital signals.


The Launch Date of the PSLV Satellite is 12 Jan. 2018.


The Battery of the Spacecraft Satellite is 78 AH Li-ion battery.


The Components of the Spacecraft Plug-n-Play Avionics (SPA) Standards is Special test bypass interface.


The Material of the Bus Structure Satellite is Aluminum (AA2024-T3).


The VO Protocols of the Gaia Satellite is TAP for table, Simple Access Protocol for spectra.


The Measurement Precision of the GHGSat's New Satellites Satellite is 1% of background for methane.


The Spatial Resolution of the CERES Scanner is 20 km.


The Image Resolution of the Pléiades Neo constellation Satellite Constellation is 30 cm.


The Orbit Type of the IRIS Spacecraft is Sun-synchronous orbit.


The Orbit Altitude of the Tomorrow-R1 and -R2 Satellite is 550 km.


The Lifetime of the Mission Satellite Mission is 3 years.


The Unknown of the INDEX Satellite Satellite is Unknown.


The Power of the Instrument power Spectrometer is ≤ 25 W.


The Data Routing of the EV-9 Satellite is From Panama to the NOC (Network Operations Center) located at the exactEarth facilities in Cambridge, Ontario.


The Discoveries of the MAP-PACE Plasma Analyzer is Low energy ion distribution in the dayside of the Moon, low energy ion intrusion into the lunar wake region, mapping of the lunar magnetic anomalies.


The Data Rate of the 4-band CCD Imager Instrument is 2.67 Mbit/s.


The Quantity of Mirrors of the LRA Laser Retroreflector Array is 100.


The Bandwidth of the DRT Data Relay Transponder is ± 100 kHz.


The Position of the DSCOVR Satellite is L1.


The CubeSat Size of the BRRM Satellite is 3U.


The Rover Task of the ExoMars Mission is Seek out geologically interesting sites to drill below the surface.


The Operation Environment of the SSTI GPS Receiver is Low-Earth orbit.


The Calibration Capabilities of the Instrument Calibration System is Spectral behavior, relative and absolute radiometric properties.


The Telescope of the XMM-Newton X-ray Satellite is Large Binocular Telescope (LBT) in Arizona.


The RCS Thrusters of the AOCS Attitude and Orbit Control System is 16.


The Perigee (km) of the Meteor-3-1 Satellite is 1235.


The Workshop Date of the FASTRAC Satellite is April 21-23, 2010.


The Band 2 of the Landsat TM Satellite is Green reflectance, peak of healthy vegetation, plant vigor.


The Full Sun FOV of the EUVI Extreme Ultraviolet Imager is ±1.7 Rsun.


The Developer of the NRD Navigation Radar Detector is Norwegian Defence Research Establishment (FFI) with partners.


The Cold Face Offset of the SVOM Attitude Satellite Attitude is 45° with respect to the antisolar direction.


The Quantity of the Perseus-M1 and M2 6U CubeSats is 2.


The Characterization Duration of the SpinSat Satellite is Within the first four months.


The Deployed Stiffness of the RDA Deployment System is Not provided.


The RIN Performance of the ASM Instrument Instrument is -140 dB (Hz)^1/2.


The Launch Vehicle of the TerraSAR-X Satellite is Russian/Ukrainian Dnepr-1.


The Senior Review Date of the TRMM Satellite is 2011.


The | of the Jayant Sharma, Grant H. Stokes, Curt von Braun, George Zollinger, Andrew J. Wiseman Authors is Jayant Sharma, Grant H. Stokes, Curt von Braun, George Zollinger, Andrew J. Wiseman.


The Imaging Capacity of the Satellite Satellite is 2.5 x 10^6 km^2 / day.


The Memory Use Capability of the SPOT-4 Satellite is Lost.


The Data Rate of the LISS-3 Camera is 52.5 Mbit/s.


The GPS Receiver of the ACS Attitude Control Subsystem is NovAtel OEMV-1.


The Orbit Shape of the LRO Satellite is Elliptical.


The Digitization Accuracy of the Experiment Unknown is ± 0.14 nT.


The Operational Mode of the AOCS Attitude Control System is Stellar yaw-steering.


The Near-Global Coverage of the Satellite Orbit is Every three days.


The Manufacturer of the LunIR Satellite is Lockheed Martin.


The Hyperspectral Instruments of the 90-satellite constellation Satellite Constellation is Yes.


The Frequency Band of the MEOSAR satellite constellations Satellite Constellations is 406 MHz.


The Acquisition Mode Duration of the Star Tracker Attitude Determination System is 2-3 seconds.


The End of Life Date of the GeoEye-1 Satellite is September 2023.


The Mass of the OBIS Onboard Information System is 20 kg.


The Frame Rate of the Camera Imaging Device is 500 frames/s.


The Operation Status of the WIND Satellite is Nominally.


The Goal of the Artemis Program Space Exploration Program is Land the first woman and next man on the Moon by 2024.


The Minimum Lower Band Edge of the MS1 (NIR1) Imager is 765 nm.


The Science Mission Start of the TanDEM-X and TerraSAR-X Satellites is September/October 2014.


The Orbiter Weight of the Chang’e-5 Lunar Lander is Nearly 2,000 kg.


The Spectral Line of the Deployable Membrane Telescope Telescope is Hydrogen-alpha spectral line of 656.46 nm.


The End of Life Date of the Buccaneer CubeSat is 18 November 2022.


The Detector Element Spacing of the VNIR FPA Focal Plane Array is 12 µm.


The Goal Image Resolution of the Satellite Constellation Satellite Constellation is 1 meter.


The Orbit Precession of the TRUTHS Satellite is 90 degrees.


The Lifetime of the PM Satellite Component is More than 10 years.


The Digital Recorder Dump Rate of the X-band Communication Band is 15.36 Mbit/s.


The Telescope of the Tyvak-0130 Satellite is One with a wide field of view.


The Author of the Observation of the Earth and Its Environment Documentation is Herbert J. Kramer.


The Angular resolution (2 px) of the FSI dual EUV 174 Å and 304 Å alternatively Passband center is 9 arcsec.


The Microshutter Arrays of the NIRSpec Spectroscopy Instrument is More than 200 spectra.


The Performance of the DFACS System is Excellent.


The Research Paper of the Picard Satellite is Advances in Space Research, Vol. 24, No 2, July 1999, pp. 205-214.


The L1 Detectors Purpose of the HIT Sensor is Sensitive to electrons.


The Finding Date of the Cluster Satellite is 2017.


The Accelerometer of the Satellite Spacecraft is Femto-g accurate electrostatic differential accelerometer.


The Target Market of the ANGELS Nanosatellite is Small satellite market for in orbit operational missions.


The Exposure Time of the SPARCS Satellite is ≈10 min.


The Altitude of the CanX-6/NTS Satellite is 630 km.


The Purpose of the SpaceX Crew Dragon Spacecraft is Transporting astronauts to and from the International Space Station.


The Detector Active Area of the RAMIS Radiation Detector is 0.5 cm2.


The Rates of Ice Thinning of the Austfonna Ice Cap is Exceeded 25 m/yr.


The Launch Year of the NovaSAR-1 Satellite is 2018.


The Formation of the Blue Ring Nebula Nebula is Product of two stars merging into one.


The Cooler of the Astro-APS Star Tracker is Peltier cooler.


The Wind Speed Range of the SCAT Wind Measurement System is 2 m/s - 24 m/s.


The Service Duration of the ZY-3 Satellite is Eight years.


The Mission Status of the TEMPO Satellite is Commissioning.


The Components of the VEFI Instrument is DC and AC electric fields instrumentation, burst memory, onboard signal processing, filter bank, magnetometer sensor, lightning detector, fixed-bias Langmuir probe.


The Manufacturer of the GATR-TRAC ground station antenna Antenna is GATR Technologies.


The Quantity of the Flock-4v Satellite is 4.


The Imagery Use of the SPOT 6/7 Satellite is Improved efficiency of US agriculture.


The Launch Date of the HJ-1 Satellite is 06 Sep 2008.


The Data Collection Dates of the SMAP satellite Satellite is May 27–31, 2015.


The Measurement Parameters of the SWOOPS Instrument is Density, speed and direction of the solar wind in three dimensions.


The Output Signal of the THD Horizon Detector is Analog signal.


The Orbit of the CAPSTONE 12U CubeSat is Near rectilinear halo orbit.


The Function of the CDRA Orbital Replacement Unit is Maintains the carbon dioxide partial pressure at under 5.3mm Hg for up to nine crew members.


The Purpose of the Texas Instruments MSP-430 Microcontroller is Count clock cycles over the entire lifetime of the mission.


The | Investigation Opportunities for Future Users of the MUSES Facility is MUSES facility enables investigation opportunities for future users.


The Payloads of the DarkCarb Small Satellite is MWIR.


The Frequency of the  Submillimeterwave receiver receiver is 562 GHz.


The Altitude Maintenance Duration of the Electric Thruster Thruster is One year.


The URL of the Remote Sensing Activities Activity is http://www.oosa.unvienna.org/pdf/pres/stsc2012/tech-24E.pdf.


The Monitoring Frequency of the OSIRIS Narrow Angle and Wide Angle Cameras Imaging System is Weekly.


The Data Handling of the Iridium NEXT Satellite is Near real-time transport of mission data and sensor telemetry.


The Apogee Drift Period of the Van Allen Probes Satellite is About 2 years.


The Project Team of the MiRaTA Satellite is Blackwell, Cahoy, Rebecca Bishop.


The Decommission Date of the RADARSAT-1 Satellite is 29 March 2013.


The Setup of I/O Ports of the dsPIC33F microcontroller Microcontroller is Unknown.


The Manufacturer of the TESIS Telescope-spectrometer is LPI (Lebedev Physical Institute).


The Function of the MiniRad Microwave Radiometer is Measure temperature at different levels of the atmosphere.


The Image Object Density of the Gaia Satellite is 750,000 objects/deg2.


The Presentation Date of the Quasi-Zenith Satellite System Satellite System is July 5-12, 2009.


The Fuel Consumption of the Attitude Control System Satellite System is None.


The AOCS Guidance List of the TTTC Satellite System is Included in each data take.


The Development Cost Reduction of the Software System is Large.


The Width of the Spectral Block Focal Plane Component is 100 pixels.


The Function of the GNSS-RO GNSS- Radio Occultation Instrument is Provide (with high vertical resolution) all-weather atmospheric and ionospheric soundings by tracking GNSS satellites.


The Stripmap Scene Size of the SAR Antenna Antenna is 60 km x 8 km.


The Bandwidth of the Band 8 Spectral Band is 845-885 nm.


The Total Mass of the Model 1000 Camera System Imaging System is <100 kg.


The Authors of the Multichannel Autocalibration Process is Luiz F. G. Dos Santos, Souvik Bose, Valentina Salvatelli, Brad Neuberg, Mark C. M. Cheung, Miho Janvier, Meng Jin, Yarin Gal, Paul Boerner and Atılım Güneş Baydin.


The Objective of the CMOS Camera Camera is Take occasional snapshot imagery of Earth and to use the camera for onboard event verification.


The Internal Calibration of the Mini-RF Instrument is Acquired every time that Mini-RF takes a data collect; a chirp, noise, and tone calibration is done both immediately before and immediately after a data collect.


The Formation Flight Mode of the TanDEM-X Satellite is Close formation.


The CCSDS ID of the GSAT-0204 Satellite is 264.


The Timing Pulse Frequency of the SAMPEX Satellite is 1 Hz.


The Led by of the In-situ component Component is EEA (European Environmental Agency).


The Unknown of the SCIAMACHY Instrument is Unknown.


The URL of the AstroSat Satellite is http://www.isro.gov.in/Spacecraft/astrosat.


The Accuracy of the Rate gyro Sensor is 0.02º/s.


The Components of the CDMS Command and Data Management Subsystem is SCP (Spacecraft Process Controller), SCC (Serial Communication Card), DAC (Data Acquisition Card), HSF (High Speed Formatter).


The Cut-out Depth of the Heater Thermal Control Device is 0.4 mm.


The Test Type of the Konnect satellite Satellite is Vibration.


The MS B2 of the Pushbroom imager Spectral Band is 0.53-060 µm.


The Mission of the ArgoMoon CubeSat is Deep-space.


The Total Number of Names of the InSight Satellite is 2,429,807.


The Power of the MAG Instrument is 0.2 W.


The Type of the Vector Magnetometer Instrument is CSC (Compact Spherical Coil) triaxial fluxgate magnetometer.


The Backlog Value of the Terran R Launch Vehicle is More than $1.2 billion.


The Detection Area of the Solar X-ray monitor Detector is 0.75 mm2.


The Ground Segment of the SPOT-6 & SPOT-7 Satellite Constellation is CGS (control ground segment) and EGS (exploitation ground segment).


The First Image Transmission Date of the TanDEM-X Satellite is June 25, 2010.


The Downlink Frequency of the RF Communications System is X-band.