The Purpose of the GOES-West Satellite is Provide an infrared look at the clouds.


The End of Life Date of the CAS500 Satellite is 2029.


The Orbit Period of the Beta Pictoris b Planet is 21 years.


The Mission Goal of the FASTRAC Satellite is Demonstrate enabling technologies for nanosatellites that work together in space.


The Probe Orientation of the TPMU Device is In the direction of the velocity vector.


The Support Phase Time Period of the Mango Tango Satellite Formation is 03.08 to 10.08.2010.


The Components of the Electric Propulsion Test Subsystem Monitoring Unit is Quartz crystal microbalance, Langmuir probe and retarding potential analyzer.


The Time to Reach Intelsat 901 of the MEV-1 Satellite is Approximately four months.


The Original Design Orbit Duration of the ESEO Satellite is 6 months.


The Bandwidth of the Communication Bus Data Communication is 100 Mbit/s.


The Support Tools of the ARTEMIS Satellite is Tools developed under multiple airborne experiments.


The Orbital Inclination of the Long March 5B Rocket Stage is 41.5 degrees.


The Location of the MOC Mission Operations Center is ESOC (Darmstadt, Germany).


The Role of UNM of the SORTIE Satellite is Integrators of the CubeSat.


The GSD (Ground Sample Distance) of the Camera Payload is 1 m.


The Equator Crossing Time of the OceanSat-1 Satellite is 12:00 hours on the descending node.


The Launch Date of the RADARSAT-2 Satellite is 2007.


The Control Method of the GSS GPS Signal Generator is Attitude and orbit commands from SATSIM.


The Angle Bin Interval of the PR Phased Array System is 0.71º.


The Observing Opportunity of the Ground-based Telescopes Telescopes is Only brief windows exist near the Sun as the Earth rotates through 15º every hour.


The Mass at Launch of the INTEGRAL Satellite is 4 t.


The Mount Type of the Telescope Optical Instrument is English mount.


The Affiliation of the Kazaya Yoshida Author is Unknown.


The Peatland Area of the Indonesia Country is Over 14 million hectares (140,000 km2).


The Components of the REPT Instrument is Stack of high-performance silicon solid-state detectors, collimation aperture, thick case, charge-sensitive amplifiers, pulse-shaping circuits, field-programmable gate array, low- and high-voltage power boards.


The Downlink Data Rate of the EROS-A Satellite is 70 Mbit/s.


The Number of Channels of the Filter Wheel Optics Subsystem is LWIR (7 channels), SWIR (6 channels) and the MWIR (5 channels).


The Antenna and Camera Temperature of the Yutu Lunar Rover is Below -180ºC.


The General Theory of Relativity of the Gaia Space Astrometric Mission is Test.


The Measurement Range - Electron Temperature of the ISL Instrument Langmuir Probe is 500-3000 K.


The Star Sensitivity Range of the STOs and STAEs Analog Electronic units is 4 ~6.5 magnitude.


The Effect of the Undersea Mountain Natural Feature is Attract a mound of water several meters high over the seamount.


The Activation Date of the HDEV High-Definition Earth-Viewing System is April 30, 2014.


The URL of the SWIM Scatterometer is http://smsc.cnes.fr/CFOSAT/GP_swim.htm.


The Imaging Capability of the Hubble Space Telescope Space Telescope is Shows only blurry patches of light and dark materials on Pluto’s surface.


The Article Date of the INTEGRAL Satellite is 2016 April 1.


The TT&C Subsystem of the CBERS-1 Satellite is S-band and UHF-band data transmission.


The Back Up User of the Canadarm2 Robotic Arm is ESA astronaut Thomas Pesquet.


The Platform of the DESIS Instrument is Multiple User System for Earth Sensing (MUSES).


The Imaging Date of the Landsat 8 Satellite is October 31, 2021.


The Launch of the OSIRIS-REx Spacecraft is Required considerable power.


The Frequency Range of the EZ probe Electric Field Probe is 0 - 1000 Hz.


The Bandwidth of the MWR Radiometer is 500 MHz.


The Satellite of the MODIS Imaging Spectroradiometer is NASA’s Terra.


The Download Speed of the Starlink Satellite Internet Service is 100-200 Mbit/s.


The Presentation Date of the MIPAS Instrument Instrument is Jan 1999.


The URL of the InSight Mars Lander Mars Lander is https://www-robotics.jpl.nasa.gov/projects/InSight.cfm?Project=7.


The Launch of the Coronal Mass Ejections Solar Phenomenon is Launched in sequence one after another from the same active region.


The Stabilization of the NigeriaSat-2 Satellite is 3-axis.


The Spectral Bands of the TIR Instrument Telescope is 8-12 µm range.


The Polarization of the ICI-1 Radiometer is V.


The Launch Date of the Sentinel-3 Satellite is 2013.


The Description of the CEASE-III-RR Experiment is CEASE-III-RR will use a suite of instruments to identify conditions in the space environment that could affect the operation of a satellite. Consisting of high and low-energy proton/electron telescopes and an electrostatic analyzer, CEASE will measure the.


The Data Mode of the TanDEM-X Satellite is Stripmap single polarization (HH) mode.


The Function of the Node-3 Module is Accommodates the items necessary for the distribution of commands and data, audio, video, electrical power, atmosphere, water and thermal energy to adjacent elements.


The Field-of-View of the PanCam WAC Camera is 37° x 37°.


The Pointing Accuracies of the AOCS Attitude and Orbit Control Subsystem is ±0.05º in all axes.


The Solar Array of the Orion Spacecraft is Designed to bend up to 60º forward and backward.


The Control Functions of the MECA Electronics Controller Assembly is Management of the command data interface, control of the dust door, scanning mirror, rotating polarizing filter, and scanned grating.


The Height of the CubeStack Multi-Payload Adapter is 10 inches (25 cm).


The Storage Capacity of the Data Buffer Board Data Storage Device is Up to 46+46 averaged frames with telemetry and ancillary data.


The FOV Elevation of the SAGE-III Instrument is -24.81 to -31.02º.


The URL of the Beidou Satellite Navigation System is http://www.globalsecurity.org/space/world/china/beidou.htm.


The Parts of the CubeSat Satellite is Overall management, mechanical structure, power supply and power management subsystem, radio communication subsystem, controller subsystem, payload, ground station, public communication and value of the project.


The Event of the SMOS Satellite is SMOS MIRAS - return to nominal data quality.


The Mass of the SERB Nanosatellite Satellite is 4.5 kg.


The Purpose of the HEMPT Thruster Assembly Electric Propulsion Thruster is Satellite position maintenance.


The URL of the MMO Orbiter is http://www.stp.isas.jaxa.jp/mercury/p_mmo.html.


The End of Life Date of the CASSIOPE Satellite is 01 Apr 2024.


The Image Source of the PLEGPAY Instrument is ESA.


The Structure of the Spacecraft Satellite is Aluminium honeycomb H-structure.


The Inclina. (º) of the Cosmos-1066 (Astrofizika) Satellite is 81.2.


The EIRP of the Contiguous Sectors Communication System is 60-65 dBW.


The Attitude Control of the ADCS unit Satellite Component is Only attitude sensor during eclipse.


The Resolution of the CUTE CCD Array is 2048 x 515 pixel.


The Closest Approach to the Sun of the SOHO Spacecraft is 1,165,000 km.


The Operational Goals of the ISERV Satellite is Reduce the amount of time required for each step.


The Number of Activation Cycles of the Electric Thruster Thruster is About 2500.


The Eccentricity of the Secondary Payloads Unknown is 0.075.


The Retirement Date of the SAR-Lupe Constellation Satellite Constellation is After November 2017.


The Number of Ranging Stations of the LAGEOS Satellite is 183.


The Spectral Range of the Instrument Satellite Instrument is 450-700 nm.


The Minimum Battery Voltage of the IXV Spacecraft is 30.4 V.


The Function of the Instrument Control Unit (NI-ICU) Control Unit is General power supply.


The Capacity of the High capacity solid-state recorder Recorder is 9 Tbit.


The Solar Irradiance Measurements of the TRUTHS Satellite is Direct measurements of Earth incident solar irradiance, total and spectrally resolved.


The Weight of the SUCHAI-1 Satellite is 1 kg.


The Li-ion Battery Capacity of the PARASOL microsatellite Satellite is 15 Ah.


The Location of the Ground Station Ground Station is Montpellier University campus.


The Instrument mass of the Spectrometer Spectrometer is 152 kg.


The Activation Sequence of the ISM Satellite Component is Two diagonal corners, then the other two.


The Mission Type of the Rosetta Spacecraft is Non-EO.


The Data Returned of the Clementine Satellite is ~ 330 Gbit total.


The Ka-band Communication Link Speed of the GEO LCT Laser Communication Terminal is 600 Mbit/s.


The Structure Dimensions of the Baumanets-2 Microsatellite is 460 mm in diameter and 530 mm high.


The Development Collaboration of the Satellite Platform is ESA and CNES.


The Orbit Determination Goals of the GEOSAT Follow-On Satellite is High Accuracy and Near-Real-Time Processing.


The Data Capacity of the MOMS-2P Instrument is 4 Gbyte.


The TT&C Communications of the Spacecraft Satellite is 4 kbit/s (uplink), 32 kbit/s to 6.25 Mbit/s (downlink).


The Optical Link Bandwidth (Downlink) of the OICETS satellite Satellite is 50 Mbit/s.


The Mounting Interface of the Active Pointing Control Mechanism Mechanism is Invar ring.


The Conference Presentation Date of the EO-1 Satellite is Mar. 6-13, 2004.


The Predecessor of the SAR-Lupe system Satellite System is SARah system.


The Launch Date of the CHAMP Satellite is July 15, 2000.


The Measurement of the Van Allen Probes Satellite is Sudden pulse of electrons energized to extreme speeds.


The Storage Location of the TEMPO Instrument is Maxar’s satellite manufacturing facility in Palo Alto, California.


The Scanning of the MIS Instrument Microwave Radiometer is Conical scanning at 31.6 rpm.


The Extinction of the Ichthyosaurs Marine Reptiles is The creatures are now extinct.


The Near Incidence Angle of the Instrument SAR is >23º.


The Monitoring Capability of the SBSS Satellite System is Objects as small as a 1 m cube all the way out to the Geosynchronous belt at 35, 786 km from Earth.


The On-axis Unapodized Spectral Resolution Requirement of the Michelson Interferometer Interferometer is ≤to the values given in Table 5.


The TT&C Communication Band of the TTCS Telemetry & Telecommand Subsystem is S-band.


The Mounting Location of the HDEV High-Definition Earth-Viewing System is External Payload Facility of the European Space Agency’s Columbus module.


The Number of Subapertures of the PAIS Imaging System is 8.


The Extended Mission Duration of the LISA Pathfinder Spacecraft is Seven months.


The Liftoff Date of the Landsat-9 Satellite is Sept. 27.


The Quantity of the DSN Antennas Ground Antennas is 7.


The Spatial Resolution of the IRIS Satellite is 0.33 arcsec.


The Development Cost of the FORUM Satellite Mission is €160 million.


The Article Publication Date of the Magnetospheric Multiscale Mission Satellite is 3 Jan. 2018.


The URL of the NASA's Spaceborne Carbon Counter Satellite is http://www.jpl.nasa.gov/news/news.php?release=2014-435.


The Data Compression of the Ground Segment Communication System is Prior to transmission to the ground.


The PRN of the GSAT-0203 Satellite is 26.


The Temperature of the Primary Sensor Sensor is >1300ºC.


The Volume of the X-band Transmitter Transmitter is 240 mm x 196 mm x 185 mm.


The Emissive Band Uses of the VIIRS Satellite is Cloud imagery, precise geolocation, surface temperature determination, cloud top pressure determination, fire detection.


The Orbit Type of the Tsubame Microsatellite is Sunynchronous.


The International Astronautical Congress Date of the Odin Satellite is October 6-10, 1997.


The Soil Moisture Resolution of the SMAP Satellite is 10-km.


The Interface Compatibility of the Spacecraft Avionics EDU Avionics is Matches the power and data interfaces of the flight spacecraft, and the command interface of the flight system.


The Diameter of the T5 thruster Ion Thruster is 10 cm.


The Launch Location of the Bloostar Launch Vehicle is Above 99% of the mass of the atmosphere.


The Solar Cells Type of the EPS Electric Power Subsystem is Triple-junction surface-mounted.


The Imaging Frequency of the Meteosat-11 Geostationary Satellite is Every 15 minutes.


The Tolerable Misalignment of the Spectrometer Channel Optical System is On the order of the slit width.


The Dimensions of the NorSat-3 Satellite is 0.62 m x 0.56 m x 0.33 m.


The Spatial Resolution of the Instrument Spectrometer is 20 m (VIS); 62 m (NIR).


The Fly Over Precipitation of the RainCube Satellite is 6σ certainty within the first two days of payload operations.


The Wavelength of the UVSP Instrument is About 1380 Å in second order.


The Expected End of Life Date of the STARLETTE and Stella Satellites is At least 2050.


The Measurement Domain of the Megha-Tropiques Satellite is Atmosphere, Ocean.


The Launch Mass of the IMP-8 Spacecraft is 410 kg.


The Wing Status of the AC4-A Satellite is Closed.


The Technology Demonstrator Mission of the Delfi-C3 Satellite is April 6-8, 2005.


The Stowed Dimensions of the Spacecraft Bus (Avionics Module=AM) Satellite is 1.1 m x 0.8 m x 0.8 m.


The Precision Measurement Method of the Servo-system Instrument Component is Measurement of the electrical power applied to each channel for the two cases.


The Array Size of the Detector Array CCD is 2048 x 4096 square pixels.


The Validation Date of the SCARLET Advanced Array Solar Array is Aug. 2, 1999.


The Use Cases of the Satellite for 5G Satellite is Disaster response, relieving ground network congestion, serving areas with poor terrestrial links.


The Technology of the C3D Instrument CMOS Sensor is CMOS.


The Channel Centre Wavelengths of the LIMS Limb Infrared Monitor is 6.25, 6.75, 9.65, 11.35, 15.25 µm and one broad channel from 13.3 - 17.2 µm.


The Swath Width of the IIM instrument Imaging Spectrometer is 25.6 km.


The Operating Mode of the Sich-2 Satellite is Program tilt mode during imaging.


The Mission of the SMOS Satellite is Soil moisture and ocean salinity data.


The Operation Basis of the LCT Laser Communication System is Coherent (homodyne digital receiver and BPSK modulation).


The Deployment of the Reflectarray Antenna Antenna is Can be folded down against the CubeSat.


The Dynamic Alignment System of the Michelson Interferometer Interferometer is Equipped.


The Mission Funding of the SORTIE Satellite is NASA Heliophysics Technology and Instrument Development (H-TIDeS) program grant.


The Mounting Location of the ShadowCam Instrument is Korean Aerospace Research Institute (KARI).


The Launch Date of the PSLV-C33/IRNSS-1G Satellite is April 28, 2016.


The Data Transfer of the ASAP-Light Camera System is Ground station communication passes.


The Power of the Solar Panels Power Subsystem is 14 W (max).


The Inclination of the Main Payload Satellite is 98º.


The Objective of the EPAM Electron, Proton, and Alpha-particle Monitor is Measurement of solar and interplanetary particle fluxes with a wide dynamic range and a directional coverage of nearly a full unit sphere.


The Lead Organization of the LCRD Payload is NASA’s Goddard Space Flight Center.


The VBB Performance of the SEIS Instrument Seismometer is -9 m s-2 Hz-½ from 10-3 up to 10 Hz.


The Testing Completion Date of the RapidEye Satellite is Unknown.


The Spectral Resolution of the FTS Fourier Transform Spectrometer is 0.04 to 1 cm-1.


The Average Data Rate Over Ocean of the KaRIN Instrument is ~3 Mbit/s.


The Mission Name of the XI-V CubeSat is X-factor Investigator-V.


The Metrology Metric of the Drag-Free Technology Technology is Measurement of the absolute position of a drag-free test mass or the differential measurement of the distance between two drag-free test masses.


The Bistatic X-band Experiment Date of the TerraSAR-X Satellite is November 2007.


The Conference Presentation Date of the GIOVE-A Satellite is June 11-14, 2006.


The Wavelengths of the NuSTAR X-ray Telescope is Almost the whole range of X-ray wavelengths.


The Size of the Aalto-1 Nanosatellite is 3U CubeSat.


The Swath Width of the EOS-T Instrument is 14 km.


The Number of Linear Arrays of the Radiating Board Antenna Component is 8.


The Evaluation Data of the AVTP and AVMP retrievals Data Products is Global ECMWF analysis fields, radiosonde (RAOB) measurements, and AIRS (Aqua-Atmospheric Infrared Sounder) heritage algorithm retrievals.


The Maximum of the Power Consumption System is 12 W.


The Globally Averaged Sea Level Measurement Goal of the Jason-3 Satellite is Zero bias ±1 mm (standard error).


The Function of the Resistojets Propulsion System is Acts as a vaporizer to ensure no liquid propellant is expelled, as well as increasing the specific impulse of the system.


The Water Vapor Emission of the Patch on Comet Surface Surface Feature is 3% of the total amount.


The CEO of the HawkEye 360 Company is John Serafini.


The Launch Date of the SWFO-L1 Satellite is 31 October 2024.


The Number of Micro-g Accelerometers of the Boom Structure is 24.


The Wheel Configuration of the CartoSat-2 Satellite is Tetrahedral.


The MSP/MGN Operation Data of the Hitomi X-ray Astronomy Satellite is Only HK data during visible time.


The Objective of the FITSat-1 Satellite is Demonstrate a high-speed transmission module for a small satellite and a visible light communication experiment using high power LEDs.


The Polarization of the ScanSAR Imaging Mode is Single.


The Shaping of the PHA Detector is Bipolar, 1.9 µs to peak.


The Angle Measurements of the TED Particle Detector is 0º and 30º from the local vertical.


The Measurement of the GEDI Lidar Instrument is Forest canopy height, canopy vertical structure, and surface elevation.


The Operations Manager of the GOES-N Satellite is United States Space Force (USSF).


The Bus Voltage of the EPS Power Subsystem is 28 to 33 V.


The Channels of the TopStar-3000 G1 GPS Receiver is 12.


The Mass of the KickSat CubeSat is ~5.5 kg.


The Uplink Baud Rate of the CMC Transceiver Communication Device is 1200 baud.


The Design of the Signal Processing System Signal Processing System is High performance and ultra low-power analog VLSIs that can processes multi signals simultaneously.


The Satellite Type of the LEMUR-2 constellation Satellite Constellation is 3U CubeSats.


The Baud Rates of the High-speed link Radio Link is 600 - 19200 baud.


The Maximum Number of Racks of the JEM/Kibo Japanese Experiment Module is Up to 23 racks.


The Data Gathered of the MAHRSI Instrument is New vertical profile data on the distribution of OH in the mesosphere and upper stratosphere.


The Purpose of the Optical Ground Station Ground Station is Initial thrust testing.


The Period of Performance of the Joint Polar Satellite System Common Ground System contract Contract is September 30, 2022.


The Peak Time of the Water Production Comet Activity is Between the end of August and early September 2015.


The PRF of the CSG-SAR Synthetic Aperture Radar is Programmable (500-7000 Hz).


The Solar Panel Orientation of the X-Sat Satellite is Pointed towards the sun, except during imaging or downlinking operation during certain orbits over a small portion of its period.


The Roll Tilt Capability of the Satellite Satellite is ±35º.


The Instrument Type of the TUBSAT Satellite is High resolution optical imagers, Other, Data collection, Hyperspectral imagers.


The Depth of the Firn Drill Drilling Tool is About 50 meters.


The Net Present Value (NPV) of the Climate Damages N/A is Tens of trillions of US dollars.


The MTF of the Telescope Optical Instrument is < 3 nm.


The Source of the Most Intense Auroras of the Jupiter Planet is Not the observed electric potentials.


The Scriptable Interface of the Gaia Satellite is Python, C, Java.


The Transmit Pulse Length of the SCA Calibration System is 600 µs.


The Data Source of the GPM Satellite Mission is IMERG.


The Timeframe of the Operation Practice/Rehearsal Activity is Year 2017.


The Primary Sensor of the SpinSat Spacecraft is The spacecraft itself.


The Distance Limit of the Gaia Catalogue of Nearby Stars Stellar Census is 326 light years.


The Onboard Data Storage of the RF Communication System Communication System is Up to 64 kbyte.


The Bandwidth of the HDR Terminal Communication Equipment is 900 MHz.


The Components of the Spectral Calibration Calibration is ISRF Shape, SSI, SR, Smile, CU.


The Duration of the Inspiration4 Mission is Three days.


The Mission Status of the ISS-RapidScat Instrument is Mission complete.


The Docking Status of the ATV-5 Satellite is De-docked.


The Launch Date of the IRIS Satellite is June 27, 2013.


The Additional Downlink Subsystem of the Sentinel-1, -2 Satellites is Optical Communications Payload (OCP).


The Image Acquisition Date of the Sentinel-1A Satellite is 2014.


The Intensity Levels of the LISS-3 camera Camera is Six.


The Swath Width of the ALOS-4 Satellite is 50 km.


The Spatial Resolution of the MWIR Imager Imaging Device is 3.5 m.


The Attachment Method of the LWIR Camera Camera is Room temperature vulcanizing silicone-566 (RTV).


The Development, Test and Flight Results of the RF Systems Communication Systems is Unknown.


The Orbit of the Spacecraft Satellite is SSO, altitude of 623 km x 650 km, inclination = 98º, LTDN= 10:30 hours.


The LTDN of the SEOSAT-Ingenio Satellite is 10:30 hours.


The Event of the SMOS Satellite is SMOS gains clearer view as illegal transmitters shut down.


The Navigation Payload Power of the GNSS Satellites Satellite is Kilowatt.


The Swath Width of the Satellite Imaging Satellite is 63 km.


The Bandwidth of the Instrument SAR is 6 MHz.


The Duration of the Passivation Phase Spacecraft is About 700 s.


The Mass Resolution of the INMS Ion and Neutral Mass Spectrometer is Approximately 12.


The Description of the At-Sensor-Radiance Product (L1B) Data Product is The product is radiometrically calibrated, spectrally characterized, geometrically characterized, quality controlled and annotated with preliminary pixel classification (usability mask).


The Adjusted EBITDA of the Satellogic Satellite Company is –$30.7 million.


The Purpose of the OCI Instrument is Derive optical properties of chlorophyll-sensitive species in the ocean and ocean color.


The Orbit Inclination of the Max Valier Satellite is 98º.


The Areas of Focus of the Copernicus Programme Earth Observation Program is Climate change and global warming.


The Inter-Orbit Communication Experiment of the Eureca Satellite is Unknown.


The Measurement Principle of the OLME Ozone Monitor is Solar Backscatter Ultraviolet (SBUV).


The Mission Status of the LAICE Satellite is Planned.


The Contact Success of the CYGNSS Satellite Constellation is 100%.


The ADC resolution of the PHA Detector is 11 bits, 12th bit overflow.


The Mission End Date of the SMOS Satellite is Unknown.


The Data Release Start Date of the RPW Radio and Plasma Waves Instrument is After 15 June.


The Focal Length of the Telescope Optical Instrument is 2626 mm.


The Accuracy of Position Determination of the Gamma-ray Counter Detector is < 5º.


The Rotation of the Calibration Mirror TIR Subsystem Component is Rotatable.


The Altitude of the SARAL/AltiKa Satellite is 800 km.


The ADCS Status of the AlSat Nano Satellite is Verified and activated.


The Pointing Altitude of the FAI Camera is 110-km.


The Frequency (GHz) of the ICI-8 Radiometer is 448±7.2.


The Fiber Core Diameter of the Data Storage System Satellite Component is 200 µm.


The Operation Status of the TerraSAR-X Satellite is Nominal as of 2010.


The End of Life Date of the MidSTAR-1 Satellite is 30 April 2009.


The Pointing Stability of the AOCS Attitude and Orbit Control Subsystem is 10 µrad (N/S and E/W) peak to peak over 8 s period.


The Data Relay of the Trace Gas Orbiter (TGO) Satellite is NASA’s Curiosity Mars rover and InSight lander.


The Collision Avoidance Requirement of the IDEA OSG 1 Satellite is If there is sufficient probability that IDEA OSG 1, during its operations, will collide with an uncontrollable resident space object, then IDEA OSG 1 should control its own orbit to the best of its ability to avoid the collision.


The CCD Line Read-Out Rate of the Focal Plane Module Imaging Device is 6.5 MHz.


The Black Hole Mass of the Leo I Galaxy is Nearly as massive as the Milky Way's.


The Orbit Type of the SPARCS Satellite is Sun-synchronous terminator orbit.


The Protocol of the OBC On-Board Computer is CSP (CubeSat Space Protocol).


The Power Generation of the IRIS Satellite is 28 V.


The Solar Array Demand of the MTM Transfer Module is 2 x 5 kW.


The Spectrometer of the The Rossi Explorer Satellite is Device used to uncover properties of the light source, such as speed and rapid variations in the order of milliseconds.


The Planning Start of the Jason-CS Satellite Mission is 2009/10.


The Purpose of the S-WPIA Wave Particle Interaction Analyzer is Measure the wave-particle interactions.


The Detector Assembly of the Sounder Satellite Instrument is 4.


The Launch Date of the Tandem-L satellites Satellite is End of 2022.


The Deployment Test Location of the Copernicus Sentinel-1C Satellite is Airbus’ facilities in Germany.


The Issue of the TT&C System Satellite System is Spacecraft ignoring commands from the ground stations.


The Water Detection Date of the Bullialdus Crater Lunar Crater is August 25, 2013.


The Mass of the NanoRacks Kaber Microsat Deployer Satellite Deployer is 10 kg.


The Location of the STScI Science Operations Center is Baltimore, Maryland.


The Removal from Service Date of the Monitor-E Spacecraft is August 2008.


The Provider of the MORE Memory Orbit Radiation Experiment is IDA TU Braunschweig.


The Dust Measurement Altitude of the UVS Instrument is Down 300 m.


The Machining Technique of the Satellite Communication is WEDM (Wire Electrical Discharge Machining).


The Position Accuracy (RMS orbit) of the S-3 STC Product is 4 cm threshold with a target of 3 cm (radial).


The Functions of the G/S Ground Station is S- and X-band functions for signal modulation/demodulation.


The Launch Time of the SOCRATES Microsatellite is 03:05 UTC.


The Presenter of the GCOM-W Satellite is Toru Fukuda.


The Image Downlink Time of the AgCam/ISSAC Imaging System is Several hours of powered operations immediately following collection.


The Conference Date of the OMI Ozone Monitoring Instrument is Oct. 14-17, 2008.


The Sample Delivery Date to Earth of the OSIRIS-REx Spacecraft is September 24, 2023.


The Flight Path of the Gravity Probe A Satellite is Ballistic (sub-orbital).


The Purpose of the BeaverCube CubeSat is Gather important ocean and atmospheric measurements.


The Instrument Type of the GovSat-1 Communication Satellite is Communications.


The Conference Presentation of the NanoSail-D Satellite is Aug. 11-14, 2008.


The TLE Generation of the Orbit Dynamic System System is By mean processing of a 6 lap orbit.


The Viewing Constraint of the Spacecraft Satellite is Cannot point to sources closer than 50º to the sun and to the anti-sun during nominal lifetime, 60º if eclipse seasons and extended lifetime.


The Lunar Swing-by Date of the Queqiao Communication Satellite is May 25, 2018.


The Altitude of the Satellite Imaging Satellite is 619km.


The Image Size of the Imager Camera is 37.25 mm x 25.70 mm.


The Orbit Type of the WV-1 Satellite is Sun-synchronous circular.


The Image Size of the Image Sensor Imaging is 37.25 mm x 25.70 mm.


The Operator of the Hinode Spacecraft is JAXA/NASA.


The Electric Charge of the Tether Tether is 500 V.


The Focus of the EIAST Organization is Satellite development, manufacturing, integration and application utilization.


The Detector Type of the Spectral Channels Satellite Instrument is Silicon.


The Performance of the MAG Instrument is ±30 nT.


The Launch Date of the PROBA-V Satellite is Before July 2013.


The URL of the Nimbus Earth Radiation Budget (ERB) Experiment Satellite Experiment is http://badc.nerc.ac.uk/data/gedex/detail/erb_soli.det.


The Observations for Performance Verification Dates of the Hitomi X-ray Astronomy Satellite is March 25 & 26, 2016.


The SNR for CH4 of the Instrument Spectrometer is ≥400.


The Inclination of the Orbit Satellite is 123º.


The TT&C Transmission of the PRISMA Satellite is S-band.


The Primary Images of the PROBA-V Satellite is 8.345.


The MLI Surface Material of the ERG Satellite is Black polyimide film.


The Heater Lines of the OTC Thermal Control System is 13.


The Space Segment of the Sentinel-6 Satellite is Two successive Jason-CS satellites (A and B).


The Initial Touchdown Point of the Philae lander Lander is Agilkia.


The Dimensions of the FPGA Processing Device is 42.5 mm x 42.5 mm.


The S-band transmitter of the BEESAT-3 Satellite is Yes.


The Wavelength of the Laser Instrument is 1570 nm.


The Deployment System of the GeneSat-1 Satellite is P-POD (Poly¿Picosatellite Orbital Deployer).


The Purpose of the MinXSS-2 Satellite is Study how coronal soft X-rays vary over solar cycle timescales and what impact those variations have on the earth's upper atmosphere.


The Objective of the VEFI Instrument is Provide in-situ measurements of Vector AC and DC electric fields related to plasma drift and irregularity development, Vector magnetic fields related to plasma irregularities.


The Dust Flux Measurement of the GIADA Contamination Monitor is Direct and Reflected Grains.


The Power Source of the RapidScat Satellite Instrument is Columbus module power circuit.


The Exceeded Design Life of the ACRIMSat Satellite is Yes.


The Housing Mass of the MuREM Radiation Monitor is 0.5 kg.


The Star Masses of the Iota Orionis Binary Star System is 23 and 13 times the Sun's mass.


The Educational Objective of the ESEO Satellite is For university students to acquire hands-on experience of the full life cycle of a real space project.


The Number of Planes of the FormoSat-3/COSMIC-1 Satellite Constellation is 6.


The Launch Date of the SkySat 3 Satellite is June 22, 2016.


The CCD Line Pixel Pitch of the Focal Plane Module Imaging Device is 6.5 µm.


The Launch Site of the Falcon 9 rocket Rocket is Vandenberg Air Force Base.


The Temperature of the CCD Imager is As low as -110ºC.


The Partners of the TacSat-3 Satellite is NRL (Naval Research Laboratory), AFRL (Air Force Research Laboratory), DARPA (Defense Advanced Research Projects Agency), the Army Space and Missile Defense Center, and the USAF Space and Missile Systems Center.


The Band 1 of the R3 Sensor Sensor is Pan.


The Birth Year of the Max Valier Person is 1895.


The Operational Lifetime of the Jugnu mission Satellite Mission is 1 year.


The Total Mass of the BA 330 module Space Module is 23,000 kg.


The Number of Maneuvers of the Swarm-A Satellite is 9.


The Detector Type of the FUV Instrument Spectrometer is Intensified CCD.


The Data Merge Start Year of the CryoSat-2 and SMOS Satellites is 2010.


The Camera Type of the Gaia Satellite is CCDs.


The Scanning Angle of the Scanning geometry Instrument is 108º, 54º.


The Size of the APD detector Experiment is Very small.


The Mission Difficulty of the BepiColombo Satellite is Most difficult.


The Components of the IVM Ion Velocity Meter is Two planar thermal ion sensors, a RPA (Retarding Potential Analyzer) and an IDM (Ion Drift Meter).


The Purpose of the Frontier Radio Lite Radio is Communication.


The Spectral Resolutions (FWHM) of the Limb Sensor Sensor is 0.75 nm at 290 nm to 25 nm at 1000 nm.


The Mass of the BILSAT-1 Satellite is Around 120 kg.


The Keystone of the System Optical System is Less than 0.4 µm.


The Launch Preparation Date of the Rain and Snow Satellite Satellite is Jan. 27, 2014.


The Methane Emissions of the Hugo Satellite is Approximately 4000 kg per hour.


The Purpose of the GomX-4B Satellite is Testing a micro-propulsion system, testing an inter-satellite radio link, carrying a hyperspectral imager.


The DEM Generation of the ALOS PRISM Satellite is Precise.


The Number of Satellites of the Pléiades Neo Satellite Constellation is 4.


The Image Credit of the Analog-1 rover Rover is ESA–A. Koehler.


The Thrust Capability of the MICROSCOPE Satellite is Micronewton.


The Period (min) of the Intercosmos- Bulgaria 1300 (Intercosmos-22) Satellite is 101.9.


The Solar Sail Deployment Test Location of the NEA Scout Spacecraft is NeXolve, a space materials company near Marshall Space Flight Center in Huntsville, Alabama.


The CPU of the OBC On-Board Computer is 16-bit CPU of Siemens.


The URL of the OPS-SAT Satellite is http://esamultimedia.esa.int/docs/gsp/C4000108683ExS.pdf.


The Laser Transmitter Range of the OLA Instrument is ~7.5 km down to ~1km.


The Energy Received from Star of the Kepler-186f Exoplanet is One-third of the energy Earth gets from the sun.


The Launch Date of the GEOSAT Satellite is 12 March 1985.


The Ionization Efficiency of the MCP Multi-Channel Plate is 80-120 eV.


The Output Power of the CC1101 UHF transceiver Transceiver is Up to 10 mW.


The Bit Error Rate of the Optical link Communication System is 10 -8.


The Drawback of the Photon Sieve Optic is Limited bandwidth.


The Frequency (MHz) of the Compass-BeiDou B1 Signal Carrier is 1575.42.


The Purpose of the LDEX Instrument is Detect presence of water ice in the permanently shadowed lunar craters.


The Applications of the TRISHNA Satellite is Peat or coal fires mapping, geothermal exploration, possibly earthquake precursors, monitoring of volcanic activity, monitoring of snow and ice in polar regions, monitoring of glaciers and glacial high altitude lakes, deriving information on atmosphere an.


The Operation Commands of the SSRNI Data Acquisition and Registration System is Yes.


The Purpose of the GIRO GSICS Implementation of the ROLO model is Address the increasingly challenging calibration needs for the next generation of satellite instruments.


The Imagery Geolocation Accuracy without GPCs of the WV60 imager Imaging System is 5.8 m-7.6 m.


The launch date of the RASAT Satellite is August 17, 2011.


The Bands of the GOES Sounder Sounder is 1 VIS band, 3 SWIR bands, 6 MWIR bands, 9 TIR bands.


The Thruster Type of the Cold Gas System Attitude and Orbit Control Subsystem is 16 attitude control thrusters, 4 orbit control thrusters.


The Spectral Sampling Distance of the VIS Spectrometer is 0.21 nm.


The Data Downlink Band of the SWFO-L1 Satellite is X-band.


The Purpose of the ERA Robotic Arm is Provide installation and removal of target loads on the surface of the station and monitoring of the state of the external surface of the station, as well as remotely controlled movement of astronauts in a portable workplace during spacewalks.


The End Date of the CubeRRT mission CubeSat is 30 November 2020.


The Radiation Diminishment of the The Teacup Quasar is 50 to 600 times over the last 40,000 to 100,000 years.


The Visible and Near-Infrared Imaging Spectrometer (VNIS) of the Chang’e-4 Rover Rover is Payload.


The Managing Center of the SMAP Satellite is NASA's Jet Propulsion Laboratory in Pasadena, California.


The Substrate Material of the Grating Optical Component is SiC.


The | of the Robert O. Knuteson 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 Arrival Date of the Hayabusa-2 Space Probe is December 7, 2020.


The Lifetime of the Instrument Satellite Instrument is 3.25 years.


The Objective of the COR2 Coronagraph2 Imager is Explore the outer corona (2-15 Rsun) in white light and pB with high spatial and temporal resolutions.


The Total Addressable Market of the Satellogic Satellite Imaging Company is $140 billion.


The Ion Energy Range of the EPAM Particle Detector is Ei ≳50 keV.


The Mission Profile Presentation Date of the SVOM Satellite is 10-15 April 2016.


The Spectral Resolution of the Instrument Spectrometer is 1200 (lambda/delta lambda).


The Launch Date of the IDEA OSG 1 Satellite is 28 November 2017.


The Composition of the White Dwarf Celestial Body is Rich in helium.


The Power Consumption of the MIRAD Instrument is 500 mW.


The Control Loop Input of the ADACS Attitude Determination and Control Subsystem is GPS position knowledge.


The Purpose of the ArgoMoon CubeSat is Demonstrate the ability to perform operations in close proximity of the ICPS.


The Services of the General Purpose Communication Network Communication Network is Data exchange with any other external system.


The Magnitude of the FGS Sensor is Brighter than the magnitude of 15 (MV).


The Resonance of the TOI-178 Exoplanet System is Laplace.


The Number of Detections of the Methane Leak Environmental Event is 12.


The X-band Transmitter Data Rate of the Measurement Data Data Transmission is 10 Mbit/s.


The Launch Vehicle of the ORS-3 Mission Satellite Mission is Minotaur I.


The Orientation Accuracy of the GOMS-1 Satellite is ±2-5 arcmin.


The LTDN of the JL-1-GF03B Microsatellite is 09:20.


The Announcement Date of the UrtheCast Company is July 16, 2014.


The Redundancy of the Star Sensors Autonomous Star Sensors is Redundant units may be implemented with some minor penalties.


The Total Mass of the Microsatellite Satellite is 20.5 kg.


The Planned Image Production of the GOCI Geostationary Ocean Color Imager is 8 times per day.


The Spectral Calibration of the SUCHI Instrument is On orbit using atmospheric absorption features.


The Developer of the Carruthers Geocorona Observatory Spacecraft is Ball Aerospace.


The Separation of the OB Optical Bench is About 40 cm.


The C3D2 Camera Images of the AlSat Nano Satellite is 105 image files downloaded in total so far, including 16 full size images.


The Purpose of the Inter-satellite Links Communication System is Routinely cross-check their performance and reduce their dependency on the availability of ground installations.


The Orbit Inclination of the CanX-6/NTS Satellite is 97.83º.


The BDH Subsystem of the ResourceSat-2 Satellite is Baseband Data Handling.


The Hydropower of the Glen Canyon Dam Dam is Electricity to about 5 million people in seven states.


The Maneuvers Performance of the Advanced Composition Explorer Spacecraft is Periodically underperform by as much as 50% in 2014.


The Revisit Time of the Landsat-9 Satellite is 16 days.


The Energy Range for Electrons of the Spectrometer Instrument is 250 keV to 4 MeV.


The Detector Thickness of the RAMIS Radiation Detector is 300 µm.


The Inclination of the DSX spacecraft Satellite is 43º.


The Provider of the Megha Tropiques Satellite is CNES and ISRO.


The End of Life Date of the ISS-RapidScat Instrument is 19 Aug 2016.


The SNR in SO of the ELVIS Spectrometer is >1000.


The Mass of the LEID Instrument is 3.1 kg.


The Operation Period of the Herschel Space Telescope is 2009 until 2013.


The Launch Date of the Carbon Mapper Satellite is April 2021.


The Data Downlink of the BRITE spacecraft Satellite is up to 256 kbit/s.


The Objective of the LIMS Limb Infrared Monitor is Measurement of vertical gas concentrations and temperature profiles in the stratosphere.


The Application of the Argos DCS Satellite System is Environmental monitoring, Wildlife monitoring, Oceanography, Climatology.


The Validation Data Source of the CYGNSS Satellite is GPS dropsondes.


The Number of Science Instruments of the IMAP Satellite is 10.


The Design Life of the GOMS-1 Satellite is 3 years.


The Angular Resolution of the Scanning geometry Instrument is 1.2 +0.2 mrad.


The Launch Date of the SAOCOM-1B Satellite is August 2020.


The On-board SSRs Compact Flash Cards of the Telemetry Data Recovery is Successful.


The Tracking Frequencies of the GPS/MET GPS Receiver is L1 and L2.


The Derived Parameters of the MiniRad Microwave Radiometer is Surface skin temperature/emissivity, sea ice edge/concentration, total precipitable water, the hydrometeor products of non-precipitating cloud liquid, rain and cloud ice, and indirect detection of the rate and phase distribution of precipitation.


The End of Nominal Operations of the Aeolus Satellite is 30 April 2023.


The Quantity of the KickSat CubeSat is 1.


The Operation of the Monitoring and Control Segment Ground Segment Component is 24/7 monitoring.


The Application of the PPT System is SAR application such as interferometry, ATI/GMTI, the fusion of SAR data with AIS data.


The Control Presentation Date of the COSMO-Skymed Satellite Constellation is Oct. 4-8, 2004.


The Satellite of the Sentinel-5 Mission is MetOp-SG.


The Operational Temperature Range of the Payload Platform Satellite Component is -10°C to +30°C.


The On-board Data Storage of the Spacecraft Satellite is 2 GByte.


The EEPROM of the Model calculator Data Handling and Processing is 256 kB.


The Proximity GPS Approach of the Mango and Tango Satellites is 2 m in Dec. 2010.


The Orbit Insertion of the Periselene-1 Spacecraft is Lunar orbit.


The Considered Data of the NOAA Agency is Microwave Sounding Data.


The Ground Station Operator of the RF Communications Communication System is TI-Tech.


The Number of Megapixels of the HAWAII-2RG 4 Megapixel array Infrared Sensor Array is 4.


The Telescope Aperture of the Pan Camera Imaging System is 0.5 m.


The NEΔT (K) of the ICI-7 Radiometer is 1.4.


The Spectral Range of the Imager Imaging System is 450-800 nm.


The Study Topic of the MSI and Proba-V Satellite is Radiation Influence.


The Resolution of the X-band Radar is 2.1 - 2.8 km in flight direction, 1.2 - 0.7 km in cross track direction.


The Launch of the SEEDS-2 Satellite is Secondary payload to the CartoSat-2A primary spacecraft of ISRO.


The Measurement Date of the Gaia Satellite is 3 December 2020.


The Unveiling Date of the ZACUBE-01 Satellite is Oct. 1, 2011.


The Heliocentric Orbit Distance of the Observatories Satellite is Nearly 1 AU.


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


The Time Resolution of the Electrostatic Analysers Sensor is Up to 0.5 s.


The Beam Steering of the XSAR SAR Sensor Subsystem is Electronic scanning capabilities in the azimuth and the elevation planes.


The Calibration Method of the On Board Calibrator Calibration Device is Flat fielding.


The Operation Status of the SPOT-4 Satellite is Nominal.


The URL of the Unknown Satellite is http://www.dso.org.sg/cmsresource/20110309337087956336.pdf.


The Website of the Roman Satellite is Interactive.


The Material of the SPEQS Optical Unit is Titanium.


The Manufacturer of the OBC On-Board Computer is EADS Astrium SAS.


The Rainfall Totals of the IMERG Rainfall Analysis Tool is Over 8 inches (203 mm).


The Attitude Sensing of the ACS Attitude Control Subsystem is Sun sensors, star sensors and gyroscopes.


The Data Delivered of the LRO Satellite is 325 TB.


The TRL of the ROIC Read-Out Integrated Circuit is 7.


The Department of Defense Users of the Iridium Certus(SM) Broadband Service is True.


The Free Flyers Quantity of the CubeStack Multi CubeSat Adapter is 26.


The Mass of the PPL1 and PPL2 Hyperspectral Camera Systems is 5.96 kg.


The Flare Class of the IRIS Observatory is M-class.


The Redundancy of the TCU Control Unit is Internally redundant.


The Function of the Peregrine Electronics Electronics is Provide C&C (Command and Control) of the payload, as well as data handling.


The Instrument Type of the OSIRIS Optical, Spectroscopic, and Infrared Remote Imaging System is Imaging System.


The Instrument of the Sentinel-1 Satellite is C-band SAR (Synthetic Aperture Radar).


The Coatings of the EIRSAT-1 Satellite is Protective oxide coatings.


The Arrival Date of the ECOSTRESS Science Payload is 17 April 2018.


The Maximum Number of Satellites of the Telescope Observation Equipment is Feasible if there are 1,000 satellites.


The Orbit Type of the Argos-4 Satellite Instrument is Sun-synchronous orbit.


The Eccentricity of the LAGEOS Satellite is 0.0045.


The Detector Annealing Date of the RHESSI Satellite is Jan. 16, 2008.


The On-Orbit Life of the NigeriaSat-2 Satellite is 5th year.


The PRN of the GSAT-0204 Satellite is 22.


The Number of Switches of the DLP System Satellite System is 5.


The Burst Alert System Response Time of the INTEGRAL High Energy Observatory is Within a record 18 seconds.


The Optics Design of the UV WFOV Imager Imaging System is Off-axis three-mirror design.


The Instrument Mass of the Instrument Sensor is 25 kg.


The Signal Reception Time of the MarCO-B Satellite is 11:31 am.


The Microphone Quantity of the Megastar Satellite is Trio.


The Founding Date of the Timbuktu City is 5th century.


The Collision Date of the A-74 iceberg Iceberg is 20 August 2021.


The Multi-function component assembly of the BEESAT-1 Satellite is Yes.


The Design and Testing Duration of the Gyro Unit Attitude Control is Three and a half years.


The Mission Objective of the OICETS Satellite is Conduct on-orbit demonstrations of high-accuracy pointing, acquisition and tracking technologies.


The Hydrazine Duration of the PARASOL Satellite is > 10 years.


The Total of the Satellite Mass is 500 kg.


The Planned System of the SARah Satellite System is SARah.


The Participants of the Soil Moisture Active Passive (SMAP) Mission is Dara Entekhabi, Eni G. Njoku, Peggy E. O'Neill, Kent H. Kellogg, Wade T. Crow, Wendy N. Edelstein, Jared K. Entin, Shawn D. Goodman, Thomas J. Jackson, Joel Johnson, John Kimball, Jeffrey R. Piepmeier, Randal D. Koster, Neil Martin, Kyle C. McDonald, Maht.


The Orbit Confirmation of the YES Satellite is Confirmed.


The Article Date of the AstroSat Satellite is February 25, 2013.


The Accuracy of the Ozone Measurement Instrument Atmospheric Measurement Device is 15 DU or better.


The Actual Speed of the Heliosphere Interstellar Medium is Roughly 7,000 miles per hour slower than previously thought.


The Radiation Effects of the THEMIS (and ARTEMIS) spacecraft Satellite is No permanent effects, occasional resets due to Single Event Upsets.


The Mission Tasks of the Chang'e-5 Lunar Probe is Number of Firsts for China.


The Model of the Second FPGA FPGA is Virtex 4.


The Nadir resolution of the WorldView-4 Satellite is 31 cm.


The Architecture of the MM Radiometer Sensor is Direct-detection.


The Effect of the CH4 Chemical Compound is Lower summertime CH4.


The Functionality of the UrtheCast Website User Interface is Fast-forward, pause, rewind and skip the near-live footage.


The Type of the Astrolabe Rupes Feature is Lobate scarp.


The Energy Range of the TED Particle Detector is 0.05 to 20 keV.


The Propulsion of the EUTELSAT KONNECT Satellite is All-electric.


The Xenon Quantity of the XTA Xenon Tank Assembly is 110 kg.


The -1 Order Diffraction Angle (677 nm) of the Diffracted Beam Light is 21.3º.


The Attitude Stability of the AOCS Attitude and Orbit Control Subsystem is ≤ 0.01º/s (3σ).


The Navigation Purposes of the Vision Based Sensors Instrument is Long distance detection and tracking of a moving target (VBS FR), relative position/attitude estimation of a cooperative target (VBS CR).


The Mission of the MANTIS Satellite is Demonstration.


The Antenna Footprint of the SIRAL Radar is 15 km.


The Fifth Flight Date of the MEPSI Satellite is 2007.


The Composition of the Layered Mounds Geological Formation is Nearly pure water ice.


The Redundancy Management Software of the S-193 Radar System is Yes.


The Deployment Date of the Gravity Boom and VLF Antenna Satellite Components is Feb. 4, 2009.


The Parallelism of the VPW42 Optical Window is ≤5 arcsec.


The Presentation Date of the ASIM Payload Facility is Sept. 24-28, 2007.


The URL of the ISS-RapidScat Satellite is URL: http://www.nasa.gov/jpl/rapidscat/nasas-new-winds-mission-installed-gathers-first-data/.


The Regional Service Start Date of the BeiDou-2 Navigation Satellite System Satellite System is Unknown.


The Instrument of the SMOS Satellite is Microwave instrument.


The Operation Status of the FY-3B Satellite is Operating in 2016.


The Frequency of the CPR Millimeter-Wave Radar is 94GHz.


The Capacity of the HSDR High-Speed Data Recorder is 8 GByte.


The Orbit Duration of the SMOS Satellite is Almost 10 years.


The Launch Date of the Sentinel-3B Satellite is 25 April 2018.


The URL of the Rosetta Satellite is http://www.esa.int/spaceinimages/Images/2014/11/Rosetta_solar_wing.


The Launch Date of the OTB-1 Satellite is 2015.


The Responsible Organization of the SPAN (Solar Probe Analyzers) Instrument is UCB/SSL (University of California, Berkeley /Space Sciences Laboratory).


The Manufacturer of the TIRS Sensor is Northrop Grumman.


The Turn-On Time of the GEDI Laser Laser System is Not specified.


The URL of the SWOT Satellite Satellite is http://scienceandtechnology.jpl.nasa.gov/newsandevents/newsdetails/?NewsID=3201.


The Public Archive Images of the ICEYE Satellite Operator is Nearly 18,000 images taken between mid-2019 and the present.


The Center Wavelength of the MS8 (NIR2) Imager is 908 nm.


The Surface Requirements of the Reflector Optic is 60 times more stringent than a photon sieve.


The Diameter of the Ryugu asteroid Asteroid is 1-km.


The Data Analysis Lead of the ROMAP Instrument is Philip Heinisch.


The Practicality of the Specialized Asset Trackers Tracking Device is Not always the most practical solution.


The Operating Distance from Earth of the Euclid Space Telescope is 1.5 million km.


The Deployment Date of the Drag de-orbit sail De-orbit Device is June 23, 2017.


The Bandwidth of the Channel 8 Sensor is 400 MHz.


The Location of the Ground Segment Ground Station is Huntsville AL.


The Spectral Bands of the Optical Arrangement Imaging System is 36 bands between 0.4 and 14.5 µm.


The Maneuvers of the ESP Thrusters Maneuvering System is Spin-up (de-spin) maneuver and a normal thrust maneuver.


The Stabilization of the Microsatellite Satellite is 3-axis stabilized + passive stabilization of the gravity gradient boom.


The Mission Overview of the Hinode Satellite is June 2007.


The Orbit Inclination of the Electron rocket Launch Vehicle is 85º.


The View Swath of the TIR Instrument Telescope is 68 degrees-wide nadir cross-track swath.


The Start of Operation of the LS-7 Satellite is 2010.


The Architecture of the QSP-1 Satellite is 4-Tray.


The Speed of the Solar Wind Phenomenon is Up to 800 km/s.


The Instantaneous spectral coverage of the Spectrometer Instrument is 1.06 km/s.


The URL of the Medium Energy Neutral Atom (MENA) Imager Imager is http://twins.swri.edu/pubs/MENA.pdf.


The Repeated ground track of the KOMPSAT-3 Satellite is 28days/423revolutions.


The Mounting Location of the MIRO Instrument is On the spacecraft payload plane.


The Conference Presentation Date of the EnMAP Hyperspectral Imager Imaging Satellite is Sept. 2006.


The Flyby Duration of the OSIRIS-REx Spacecraft is 5.9 hours.


The Bandwidth of the ODTML Data Collection System is Higher than Argos DCS.


The Minimum Impulse Bit of the T3µPS Micropropulsion System is 30µNs.


The Payload of the ResourceSat-2 Satellite is LISS-3, LISS-4 and AWiFS.


The Possibility of Cross-Tagging of the UFF TLE Data Product is Good.


The End of Life Date of the JPSS-2/NOAA-21 Satellite is 10-11-2029.


The Instrument Power of the MWHS-II Microwave Humidity Sounder is 116 W.


The Function of the Formation Flying Application is Precise baseline determination and orbit control.


The Solar Cells Efficiency of the EPS Electric Power Subsystem is 28%.


The Payload of the Atlas V Launch Vehicle is Classified NROL-39 & 12 CubeSats.


The Sail Size of the Solar Cruiser Solar Sail Mission is 16 times larger.


The Expected Wake Up Date of the Yutu-2 Rover is 28 April.


The Equatorial Crossing Time of the Orbit Satellite is 12:00 hours.


The Focal Length of the Short Wavelength Band Spectrometer is 12.5 cm (f/2.2).


The Manufacturer of the NigeriaSat-2 Satellite is SSTL (Surrey Satellite Technology Ltd.).


The Resolution of the Spotlight-2B Satellite is 1m.


The Ensquared Energy of the Lens Optical Instrument is 50% within 15 x 15 µm.


The Orbital Decay Prediction of the POPACS Satellite is Three years after launch.


The Lifespan of the Red Dwarfs Star Type is Generally do not live long enough for complex life to evolve.


The Role of the CE-4R satellite Satellite is Relay satellite for a rover.


The Date of the Severe Rainfall and Flooding in Japan Event is 10 July 2018.


The Distance from Earth of the Voyager 1 Spacecraft is About 5.9 billion km.


The Photodetector Pixel Size of the Optical Head Optical Device is 5.2 µm x 5.2 µm.


The Range of the Sun sensors Sensor is ±50º.


The Magnetometer of the ADCS Attitude Determination and Control System is 1.


The Bloom Intensity Change of the Phytoplankton Microorganism is Rose considerably in 48 out of the 71 lakes (68 percent).


The Electric Fields Forecast of the C/NOFS Satellite is Pre-reversal enhancement strength.


The Spectral Resolution of the XSM X-Ray Detector is ~ 250 eV at 6 keV.


The Lens Configuration of the WISPR Imager is Split into two separate imaging assemblies.


The Parachute Manufacturer of the ExoMars mission Mars Mission is Airborne Systems.


The Exceeded Design Life of the SORCE Satellite is Yes.


The Date of the Asteroid Day Awareness Campaign is 30 June.


The Location of the Goonhilly Earth Station Earth Station is UK.


The Deposition Time of the Fortescue, Hamersley, and Turee groups Rock Groups is Between 2.7 billion and 2.3 billion years ago.


The Size of the SIR-2 Instrument is 260 mm x 171 mm x 143 mm (EO module), 146 mm x 125 mm x 33.5 mm (electronics box).


The Yaw Knowledge of the GFO Satellite is Sun sensors.


The Calibration Frequency of the OMPS Sensor is Weekly for working diffuser, Twice annually for reference diffuser.


The FOV of the Long Wavelength Band Spectrometer is 8º x 5'.


The Components of the HPS Bus System is OBC (On-Board Computer), TCTM (Telecommand & Telemetry) module, PDU (Power Distribution Unit).


The Number of Satellites in Constellation of the Satellogic Satellite Company is 34.


The Distance from Earth of the The Teacup Quasar is 1.1 billion light years.


The Article Date of the NASA Organization is 23 July 2021.


The Incidence Angle of the Antenna Conically-scanning reflector is 40.0º.


The Geographical Coverage of the EARS Data Service is Large.


The Mass of the HIA Instrument is 3.0 kg.


The Optimal Ground Condition of the SEIS (Seismic Experiment for Interior Structure) Seismometer is Level ground without rocks larger than about 1.5 cm.


The Number of Recommendations of the Starliner Spacecraft is 60.


The End of Life Date of the Artemis-I Mission is 11 December 2022.


The Ground Resolution of the IIM instrument Imaging Spectrometer is 200 m/pixel.


The Shielding of the Radiator Thermal Control System is Specially shaped titanium fins.


The Field of View Width of the Spectrometer Spectrometer is ~0.0001 radians.


The Sovereignty of the PAZ and TerraSAR Satellites is Independent.


The Head Switch-over Time of the STOs and STAEs Analog Electronic units is 3 s.


The Constellation of the GCOM-W1 Satellite is A-Train.


The Purpose of the Delfi-n3Xt Nanosatellite is Space Weather Research and Qualification of Microtechnology.


The Manufacturer of the NRCSD CubeSat Deployer is NanoRacks.


The Log Amp Bias of the Signal Processing System is Log Amp termination mode.


The Launch Date of the LADEE Lunar Mission is Fall 2013.


The Attitude Control of the CanX-4&5 Satellite is 0.5º.


The Manufacturer of the ALTIUS Instrument Satellite Instrument is Optique et Instruments de Précision (OIP) Sensor Systems.


The Default Mode of the TRXU Communication System is Receive mode.


The Band of the KaRPDA Antenna is Ka-band.


The Measurement Target of the OCO-2 Spectrometer is Gases.


The Number of Characterized Fragments of the DebriSat project Satellite is Over 13,000.


The Data Usage of the SMOS Satellite is All-weather microwave data.


The Dark Current of the Instrument CCD Imaging Camera is Can be kept insignificant for normal instrument operating temperatures.


The Spectral Resolution (60 keV) of the Detector Instrument is 1.0 keV.


The Band of the RF Communications TT&C is S-Band.


The Unknown of the LRR Laser Retroreflector is Unknown.


The Spatial resolution at nadir of the VIRR Visible and Infrared Radiometer is 1.1 km.


The Orbits Completed of the MaSat-1 CubeSat is 10,000.


The Number of Beams for HR Mode of the COSI SAR Mission is 19.


The Constraint of the Instrument Payload is Avoid the sunlight intrusion in the payload CCD.


The Experiment Proposals of the OPS-SAT CubeSat is 55.


The Development Organizations of the NINA-2 Telescope is INFN (Italian National Institute of Nuclear Physics) of Rome, Italy and MEPhI (Moscow Engineering and Physics Institute).


The Arrival Year of the Nauka mini-research module Module is 2021.


The Length of the Antenna Satellite Component is 0.5m.


The Power Supply of the RM Radiation Monitor is Single unregulated 28 V supply.


The Payload of the Satellite Spacecraft is Unknown.


The Frequency of the Ka-band payload Communication System is 30 GHz (receive) and 20 GHz (transmit).


The Type of the Batteries Electrical Power Subsystem is Lithium-ion 18650.


The Location of the PDAS Data-Acquisition Station is Fucino (Italy).


The Design Hypothesis of the Geometric Calibration System Calibration System is Change within an orbit can be sufficiently modelled with a 3rd order polynomial against the time since the eclipse’s exit.


The X-band Downlink of the Satellite Satellite is 280 Mbit/s.


The Lagrange Point of the SWFO Satellite is Lagrange Point 1.


The Ground Stations of the DICE Mission Satellite is NASA Wallops field, Stanford Research International.


The Spectral Range of the Current GOES imager Sensor is 3.80-4.00.


The Design of the SLIM6 Line Scan Imager Imager is COTS (Commercial Off The Shelf) optics design and a COTS detector.


The Configuration of the Star Sensors Autonomous Star Sensors is Hot redundant, cross-strapped.


The Components of the GOLF Instrument is Sodium vapor resonance scattering filter, Longitudinal magnetic field.


The Additional Information Source of the Remote Sensing Observation Method is Emission of fluorescence from the chlorophyll of assimilating leaves.


The Design of the SILEX Communication System is ESA.


The Observation Frequency of the ALOS-4 Satellite is Once every two weeks.


The PFM Delivery Date of the SMOS Satellite is End of 2006.


The Current Flow of the Electrodynamic Tether Propulsion and Power Generation Device is Determines if the interaction contributes to drag or to propulsion.


The Control Method of the SMA Scan Mechanism Assembly is Close-loop controlled using realtime attitude data supplied by the host spacecraft.


The Rotation Rate of the O/OREOS nanosatellite Satellite is 1 to 2 rpm.


The Number of Confirmed Planets of the Kepler spacecraft Spacecraft is 2,650.


The Function of the BJ3A1 satellite ground pre-processing system Data Processing System is Receives raw data received by the ground station for processing.


The Imaging Time of the CHORUS Satellite is About 20 minutes earlier each day.


The End of Life Date of the PhoneSat-1 and -2 Satellite is 27 April 2013.


The Effective FOV of the Channel 3 Sensor is 42 km x 94 km.


The Control Accuracy of the Mango Satellite is Within 0.3 m from the commanded approach.


The Operation of the Antonov 124 Aircraft is Carry the spacecraft.


The Retrieval Altitude of the EURECA Satellite is 476 km.


The Orbit Type of the ALL-STAR-1 Satellite is Near-circular orbit.


The Conference Date of the LISA Pathfinder Satellite is Oct. 17-20, 2005.


The Antenna Temperature of the WISPR Imager is ~1800ºC.


The Nitrogen Dioxide Concentrations Change of the Copernicus Sentinel-5P Satellite is Beijing: -35%, Chongqing: -45%.


The ADCS System of the DeorbitSail Satellite is Second use of CubeSense after STRaND-1.


The Location of the Ground Station Ground Station is Villafranca, Spain.


The Resolution of the Interferometric Wide Swath mode (IWS) Operational Mode is 25 m x 80 m.


The Launch Vehicle of the Göktürk-1 Satellite is Vega VV08.


The Launch Date of the UWE-1 Satellite is Unknown.


The Nominal Operating Voltage of the GHGSat-D Microsatellite is 12.3 V.


The First 883-GHz Cloud Radiance Map Date of the ICIR IceCube Cloud–Ice Radiometer is June 20, 2017.


The Altitude Decay Date of the InflateSail Satellite is 3 September 2017.


The Telemetry of the CEASE-2 Instrument is 10 byte/min.


The Power Consumption of the Space Comb Spectroscopy Setup is Below 30 W.


The Orbit Average Power of the Power System Satellite Subsystem is 65 W.


The Along-Track Resolution of the Nadir Sensor Wide-Field Telescope Sensor is 50 km at nadir.


The Drift Accuracy of the DPU Data Processing Unit is ~ 0.1 arcsec.


The Orbit Type of the PhoneSat-2.5 1U CubeSat Satellite is Near-circular orbit.


The DC Measurement Uncertainty of the Magnetometer Instrument is 14 nT.


The Retroreflector Coating of the Ralph Satellite Component is Reflects only one of the two transmitted laser wavelengths.


The Radio Occultation Data Purchase of the NOAA Organization is Expanded on 19 February 2021.


The Function of the SSR Solid State Recorder is Data storage and retrieval.


The Status of the NIRSpec instrument Instrument is Prepped for Micro-Shutter Array and Focal Plane Assembly replacement.


The Ground-Based Test Duration of the Modern ICs Electronic Components is More than 40 days per mode.


The Impact Angle of the WISPR Optics Optical System is 0º, 45º, 70º.


The Clock 2 Anomaly Date of the QZS-1 Satellite is Dec. 19, 2012.


The Spatial Resolution (Elevation) of the Radar Radar is 15 km.


The ALMASat-1 Mass of the ALMASat-1 Satellite is 13.56 kg.


The Operation Status of the Paraguaná Refinery Complex Refinery Complex is In limbo.


The Primary Use of the Band 9 Spectral Band is Ocean color.


The Altitude of the FY-3E Satellite is ~ 800 km.


The Science Phase Duration of the EQUULEUS Satellite is At least 180 days.


The Spectral Channel 3 of the Satellite Imaging Satellite is 0.79 - 0.92 µm.


The Size of the ADEOS spacecraft Satellite is 4 m x 4 m x 5 m.


The Instrument Type of the ISS:LIS Lightning Imaging Sensor is Lightning sensors.


The Components of the LF Receiver Receiver is Laser diodes, collimation lenses, electrical and mechanical hardware, copper heatsink, aluminum-alloy chassis, PCM module.


The Revolutionize View Date of the Van Allen Probes Satellite is Jan. 19, 2016.


The Spatial Resolution at 20° off-nadir of the WV60 imager Imaging System is 0.55 m.


The Camera Position of the PSSCT-2 Satellite is +Z face.


The Delivery Date of the BRITE Satellites Satellite is June 2011.


The High/Low gain ratio of the PHA Detector is 68 or 40.


The Distance from Neutron Star to Companion of the Absorption Signatures Spectral Feature is 0.04% of the distance from the neutron star to the companion.


The Objectives of the AATSR Instrument is Continuation of precise measurement of Sea Surface Temperature (SST) started with ATSR-1 and ATSR-2.


The Rate of the Data Sensor is 50.6 kbit/s.


The Mission Count of the NanoRacks Satellite Deployment System is 17.


The Launch Mass of the QuikTOMS spacecraft Satellite is 166 kg.


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


The Conference Presentation of the Near Earth Asteroid Scout Satellite is 2019 IEEE Aerospace Conference.


The Uplink Frequency of the Communication Communication System is S-band.


The Design Life of the VENµS Satellite is 4 and a half years.


The Pointing Stability of the MTG-S Spacecraft Satellite is Over 10 s.


The LTDN of the SkySat-16 to -18 Satellite is 10:30 hours.


The Designer of the BGO Calorimeter Detector is Prof. AN Qi from USTC.


The Thermal Gradients of the Etalon Etalon is Unknown.


The Subsystems of the TRISHNA Satellite is French Space Agency (CNES).


The Spectral Band of the Band Cameras Camera is 650-740 nm.


The Launch Date of the OPAL CubeSat is Not provided.


The Data Rate of the Instrument Spectrometer is 1.27 Mbit/s.


The Detector Type of the CERES Instrument is Thermistor bolometers.


The Number of Spectral Bands of the ALI Telescope is 10.


The Quantity of the Horizon sensor Sensor is 1.


The Study of the ISEE-1/2 spacecraft Spacecraft is An unusual flux transfer event.


The ICRA Requirement of the MTG-I Satellite is Inter-Channel Co-registration Accuracy.


The Affiliation of the Eugene Parker Astrophysicist is University of Chicago.


The Ground Segment Component of the Delfi-C3 Satellite is Radio amateur network.


The Design Life of the FY-3 series spacecraft Satellite is 3 years.


The Purpose of the APSS-1 Satellite is Monitor electrical activity in Earth’s upper atmosphere to test whether ionospheric disturbances can predict earthquakes.


The Microchip Quantity of the InSight Satellite is 2.


The Components of the IRIS spacecraft Satellite is Bus structure, harness and interconnects, MLI blanketing, ACS flight software, fault management scheme, EGSE, solar arrays, deployment mechanisms, reaction wheel assemblies, torque rods, IAU, coarse and digital sun sensors, magnetometer, star trackers.


The Additional Lateral Displacement for the Fourth Exposure of the Euclid Reference Survey Survey is 50 arcsec.


The Plasma Particle Data Analysis of the Reimei Satellite is URL:  https://web.archive.org/web/20161222025705/http://www.iugonet.org/meetings/2010-02-25/05_Reimei_EISA_Hirahara_20100225.pdf.


The Data Stream Availability of the Sentinel-6 Satellite is A couple of days after collection.


The Deputy Project Scientist for Applications of the GPM Satellite is Dalia Kirschbaum.


The Type of the Solar panel release mechanism Deployment System is New implementation method.


The Integration Distance of the Radar Instrument is 10 km.


The Capability of the Payload OBC On-Board Computer is Support of payloads with FPGA computing capability.


The Diameter of the Crater Surface Feature is 11 km.


The Orbit Control of the MEV-1 Satellite is Controlled the orbit of the customer satellite.


The Number of Prisms of the LAGEOS Satellite is 426.


The | of the Absolute Scalar Magnetometer Magnetometer is Magnetic Cleanliness and thermomagnetic effect: Case staudy of the Absolute Scalar Magnetometer and its environment on Swarm satellites.


The December 2015 Value of the CO2 Concentration Atmospheric Parameter is 400.2 ppm.


The Projected Growth of the Arctic vessel traffic Maritime Traffic is 250 percent by 2025.


The Partners of the Kepler Mission is 6.


The Mission Type of the Sentinel-5P Satellite is EO.


The De-orbit Date of the GFO Satellite is End of 2008.


The Launch Date of the SeaHawk-1 CubeSat is 3 December 2018.


The Orbit Lifetime of the NRCSD Payload is 8-12 months.


The Orbit Maintenance of the JERS-1 Satellite is TACC.


The Field of View of the Telescope Optical Instrument is Below 75 µrad.


The Detectable Minimum Energy of the Gamma-ray Counter Detector is < 30 keV.


The S/C Pointing of the Spacecraft Bus (Avionics Module=AM) Satellite is 1.0º, 1.0º.


The Disperser Type of the Instrument Spectrometer is Prism.


The Data Rate of the MIS Instrument Microwave Radiometer is 500 kbit/s.


The Launch Time of the SpaceX CRS-19 Mission is 17:29:24 UTC.


The Performance Characteristics of the Small Optical Transponder (SOTA) Optical Transponder is Unknown.


The Functionalities of the PMS System is Catalog data generation, product generation status control and monitoring, standard product generation.


The Satellite Bus of the EarthDaily Constellation Satellite Constellation is Modified OneWeb satellite buses.


The Side Panels Surface Area of the UniSat-5 Satellite is 50 cm x 50 cm.


The Data Access of the Sentinel-1 Satellite is Full and open access.


The Weight of the Cargo Dragon Spacecraft is 6,553 pounds (2,972 kg).


The URL of the TechnoSat Nanosatellite is http://digitalcommons.usu.edu/cgi/viewcontent.cgi?article=2986&context=smallsat.


The Purpose of the Alinco UHF Transceiver Transceiver is Monitor the spacecraft beacon messages.


The Firing Direction of the Micronozzle Propulsion System is +Y.


The Minimum Lower Band Edge of the Pan (WorldView-1) Imager is 400 nm.


The Side to Side of the S-193 Ground Coverage is 48º.


The Spectral Ranges of the MSU-E Multispectral Scanner is 0.5 - 0.7 µm, 0.7 - 0.8 µm, and 0.8 - 1.0 µm.


The Circuitry of the SWEM Satellite is Standard designs used extensively in previous missions.


The Study Date of the Small Sun Structures Space Phenomenon is 19 January 2021.


The Mission Payloads of the HORYU-4 Satellite is Multiple.


The Observation of the ALOS/PALSAR Satellite is Magnitude-6.5 Earthquake in Southeastern Iran, 2010.


The Wavelength Interval of the PAN Imaging System is 0.50 - 0.85 µm.


The Application of the SMAP Satellite is Flood potential forecasting, drought monitoring.


The Maximum Distance of Galaxies of the Euclid Space Telescope is Up to 10 billion light years away.


The Imaging Bands of the EOS-T Instrument is Five bands, one panchromatic as well as four multispectral.


The Mass of the PCU Power Control Unit is Low.


The Emission Band of the Herschel Telescope is Far-infrared (at 100 µm).


The Team of the LightSail-2 Solar Sailing CubeSat is Planetary Society-led team.


The Attitude Hardware of the BRITE satellites Satellite is Reaction wheels and star trackers.


The Spectra of the SP Spectrograph is Dual-line (Fe i 630.25 nm and Fe i 630.15 nm).


The Required Precision of the Cloud Top Pressure Satellite Instrument is 100.


The URL of the ICARE Radiation Monitor is http://wwwe.onecert.fr/craterre/radiation_monitors/ICARE.html.


The Frequency Range of the VLF Experiment Scientific Experiment is 3-30 kHz.


The Inclination of the SCD-2 Satellite is 25.0o.


The Mass of the M1S/M2S Satellite is ~1000 kg.


The Purpose of the Muninn Satellite is Expand the geographical regions that we are testing in, and also test more advanced user scenarios on the ground with multiple satellites in view.


The Type of the Tethered System Space Propulsion System is Momentum-exchange.


The Power of the PPL1 and PPL2 Hyperspectral Camera Systems is 30 W peak power.


The Ground Segment Chain of the Deimos-2 Satellite is Flight operations chain.


The Supporting GPS/GLONASS Multi-Constellation Augmentation of the QZSS L1-SAIF System is ITM 2013 (International Technical Meeting) of The Institute of Navigation, San Diego, Ca, USA, January 28-30, 2013.


The Regional Hubs of the SERVIR Program is CATHALAC in Panama, RCMRD in Nairobi, ICIMOD in Kathmandu.


The 3D-HDTV Broadcasting and Broadband VSAT Communication Trial Services of the COMS Satellite is Summer of 2011.


The Computational Units of the Electrical System System is Distributed processors and FPGAs.


The Location of the Hertz Chamber Test Chamber is ESA's ESTEC technical heart in the Netherlands.


The Image Acquisition Frequency of the AutoNav Autonomous Navigation System is About once per week.


The Role Assignment of the OBDH OnBoard Data Handling is Assigned to a specific OBDH-board.


The Orbit Period of the AU Mic b Planet is 8.5 days.


The Antenna Gain (dB) of the Antenna Reflector is 29.3.


The Maximum Distance from Crater Center of the Disturbed Areas Geological Feature is Up to 15 m.


The Number of Processors of the EnMAP Satellite is 4.


The Bandwidth of the Radiometers Instrument is 3 kHz.


The Flight Above the Surface of the Philae Lander is More than an hour.


The Detector Line Array of the SLIM6 Satellite is 10,000 silicon element cells in cross-track.


The Hibernation Duration of the Rosetta Satellite is 2010-2014.


The Field of View of the SBUV Spectrometer is 0.20 rad.


The Benefits of the Mission Satellite Mission is Ecological forecast, water quality, air quality.


The Scintillation Data Frequencies of the CITRIS Receiver is VHF, UHF, and at L-band frequencies.


The Operator of the Odin Satellite is OHB Sweden, on behalf of the Swedish National Space Agency (SNSA) and the Swedish Space Corporation (SSC).


The Chip size of the PHA Detector is 7.4 mm x 7.4 mm.


The Components of the ACS Attitude Control Subsystem is Three magnetic torquers (MTQ, total mass of 90 gram), a magnetometer (Honeywell HMC2003), a sun sensor (FOV ±45º) and a gyroscope (range of ± 200º/s).


The End of Operations of the Resurs-P2 Satellite is 2018.


The Publication Date of the Solar Mass Ejection Imager Imager is Jan. 22, 2002.


The Swath Width of the SAR Synthetic Aperture Radar is Larger than 40 km.


The Minimum Value of the Spectral Angle Measurement is Achieved when the blue panel is prominent.


The Launch Vehicle of the MSG-3 Satellite is Ariane-5 ECA.


The Control Algorithms Implementation of the Coarse ADCS ADCS System is Nanomind OBC.


The Launch Date of the Dauria Aerospace and Samsung Satellite is Oct. 15, 2013.


The Communication Frequencies of the Nanosatellite Satellite is UHF, VHF.


The J2000 right ascension (deg) of the B0531+21 (Crab) Pulsar is 83.63303.


The Launch Date of the NorSat-1 Satellite is July 2017.


The Field of View of the FOV Satellite is 0.08º along track and 1.42º cross track.


The Pressurized Cargo Bay Mass of the Dragon Resupply Vehicle Resupply Vehicle is 1530 kg.


The Shutter Requirement of the AgCam/ISSAC Imaging System is US Laboratory Window external shutter to be open.


The Function of the MC3 Ground Station is Signal for assistance if a ground engineer was needed to resolve a problem.


The Symposium Date of the Air Force Academy Department of Physics Space Technologies Development and Research Research Project is May 19-22, 2014.


The Period of the WorldView-3 Satellite is 97 minutes.


The Eccentricity of the Satellite Spacecraft is 0.8.


The Spectral Range of the Current GOES imager Sensor is 6.75-7.15.


The Name of the CERN Radiation Testing Facility is VESPER (Very energetic Electron facility for Space Planetary Exploration missions in harsh Radiative environments).


The Article Date of the Tooley Crater Lunar Crater is 26 January 2021.


The Orbit Type of the LEO Satellites Satellite is Low Earth Orbit (LEO).


The Primary Mirror Type of the Shafer Telescope Optical System is Scanning mirror.


The Location of the Monitoring and Control Segment Ground Segment Component is Tromsø, Norway.


The Field of View of the Telescope Optical Instrument is 0.5º x 0.5º.


The Experiment Duration of the SIOS Optical Link Demonstration Board Technology Demonstration Board is 3-5 years.


The Antenna (Gr/T) of the Unit Communication System is -17.4.


The URL of the H. Kuninaka Individual is http://www.nasa-usa.de/pdf/604314main_6-GER_WS_JAXA-RoboticPrecursor-Kuninaka.pdf.


The Difference in Radius of the Kepler 11145123 Star is 3 km.


The Measurement Range of the Cloud Fraction Satellite Instrument is 0-1.


The Sampling Rate of the TRSR GPS Receiver is 10 Hz.


The Views of Star Formation Date of the Herschel and Planck Telescopes is 5 July 2020.


The Launch Site of the NanoSail-D Satellite is Omelek Island in the Kwajalein Atoll.


The Spectral Passband of the Miniature High-Resolution Imaging Spectrometer Imaging Spectrometer is 1600-1700 nm.


The Publisher of the Observation of the Earth and Its Environment: Survey of Missions and Sensors Documentation is Springer Verlag.


The IFOV/line (pixels/scan line) of the MWTS Microwave Temperature Sounder is 15.


The Data Location of the JERS-1 Satellite is ESA Earth Online website and the OpenSearch Datasets on NASA Earthdata website.


The Perihelion Radius of the Solar Orbiter Satellite is < 0.25 AU and > 0.20 AU.


The Design Life of the Satellite Satellite is Ten years.


The Signal Processing System of the NorSat-3 Satellite is Zynq Ultrascale+ system-on-chip.


The Instruments of the CryoSat Satellite is DORIS-NG, Laser Reflectors (ESA), SIRAL.


The Launch Date of the Intercosmos- Bulgaria 1300 (Intercosmos-22) Satellite is 07.08.1981.


The Quantity of the Thrusters Attitude Control is 24.


The Stabilization of the JAWSAT Satellite is Three-axis.


The URL of the Radiation Belt Storm Probes Satellite is http://rbsp.jhuapl.edu/index.php.


The Conference Presentation Date of the THEMIS Satellite is Aug. 14-17, 2006.


The Intersatellite Communication System of the CanX-4&5 Satellite is Must relay position, velocity and attitude information.


The Type of the Fluxgate Sensors Sensor is Ring core-types.


The Navigation Method of the Interplanetary spacecraft Spacecraft is Pulsars.


The Total ΔV of the CNAPS Propulsion System is 12 m/s.


The Energy Measurement Range for Electrons of the Telescope 1 Solid-State Telescope is >0.15, 0.35, 0.75 MeV.


The Mass of the AIST-2 Microsatellite is 39 kg.


The Test Schedule of the Orion Spacecraft Spacecraft is Accelerated.


The Frequency Range of the Electric Field Measurement System Instrument is 20 Hz - 100 kHz.


The Onboard Propulsion of the QuickBird-2 Satellite is 4 x 4.4 N hydrazine thrusters.


The Data downlink of the ALOS-3/PRISM-2 Satellite is 800 Mbit/s (X- and Ka-band).


The Pointing Performance of the ACS Attitude Control Subsystem is ≤ 150 arcsec.


The Payload of the Solar Orbiter Satellite is 180 kg.


The Number of Digital Delays of the TTDL Component is 5.


The Instrument Type of the GF-3 Satellite is Imaging microwave radars.


The Mass of the Jugnu Satellite is ~ 3 kg.


The Quantity of the Solar Panels Power Subsystem is 4.


The Diameter at Launch of the Genesis-2 Spacecraft is 1.9 m.


The Measurement Category of the TEMPO Satellite is Ozone, Trace gases (excluding ozone).


The Launch Timeframe of the Aditya-L1 Satellite is 2019 – 2020.


The Examples of the Passive Deorbiting Devices Deorbiting Devices is Tethers and drag sails.


The Discovery Date of the Chang'e-4 Lunar Probe is 21 July 2020.


The Microprocessor of the Beresheet lander Lander is LEON3 cores.


The Focal Length of the LWIR Cameras Camera is 13.5 mm.


The Imaging Frequency Band of the COSMO-SkyMed Satellite is X.


The Fairing Manufacturer of the Ariane 5 Launch Vehicle is RUAG Space.


The Distance to EML-2 of the Queqiao Communication Satellite is 60-80,000 km.


The Design of the Rotating Telescope Scanner Optical Instrument is Three-mirror anastigmat, rotating at constant speed about an axis parallel to the line-of-sight, followed by a HAM (Half-Angle-Mirror), a plane mirror rotating at half of the telescope speed.


The Leading Noise Terms of the Satellite Spacecraft is Electric disturbances.


The Energy Range for Protons of the Spectrometer Instrument is 8 to 120 MeV/(mg/cm2).


The Frequency of the External Calibration Calibration is Two events every two weeks.


The Brochure Date of the GOCE Satellite is June 2006.


The Design Factors of the ELSA-d Mission is Mission safety, market leadership, engagement in discussions for doctrine, standards, and regulation, interface with legal structures.


The Imagery Geolocation Accuracy with GPCs of the WV60 imager Imaging System is 2 m.


The Image Credit of the CU Control Unit is GWU, USNA.


The Swath Width of the X-band Radar is 450 km.


The Bands of the Spectral Bands Sensor is 2.


The Material of the Sprite’s antenna Antenna is Nitinol.


The Data Collection Period of the CPT Data Processing System is Fixed period of time.


The Event Identification of the CZTI Instrument is Compton scattering criteria.


The Drag Sails of the CanX-7 Satellite is Four.


The Contribution of the LARES Satellite is Laser Relativity Satellite.


The Data Retrieval Location of the FOS Satellite is Ground stations.


The Impact Date of the DART Spacecraft is 2022.


The Conference Location of the PnP Cube Satellite CubeSat is Big Sky, Montana, USA.


The Spectral Sampling of the LR Bands (500–697 nm) Spectral Bands is Equal to the slit with (84 µ ).


The Dimensions of the Spacecraft bus Satellite is 2.0 m x 1.8 m x 3.7 m.


The Storage Location of the Processed science data Data is DAAC located at GSFC.


The Measurement Domain of the ST5 Satellite is Atmosphere, Gravity and Magnetic Fields.


The Power of the LISS-IIM Instrument is 34 W.


The Number of CCDs of the Focal Plane Array Detector Array is 36.


The GPS Data Collection Location of the ICESat-2 Satellite is 88 degrees south.


The Purpose of the GOSAT-GW Satellite is Monitor greenhouse gases in the atmosphere and improve understanding of the water cycle.


The Data Collection of the ECOSTRESS ECOsystem Spaceborne Thermal Radiometer is Morning data for the summer season.


The Orbit Type of the LAGEOS Satellite is MEO (Mean Earth Orbit).


The Power of the DubaiSat-2 Satellite is 100 W.


The Effect Size of the Aerosol Direct Radiative Effect Atmospheric Phenomenon is Unknown.


The Launch Date of the ESAIL Satellite is 12 June 2020.


The Number of Satellites Waiting to be Launched of the GHGSat Company is Two.


The Unknown of the Chang'E-1 Lunar Probe is Unknown.


The Displacement Resolution of the Boulders Geological Feature is ~1 cm.


The Daily Scenes of the System SAR is More than 30.


The Mass of the STP-H5 Payload Package is Unknown.


The Sustained Surface Winds of the RapidScat Scatterometer is 46.9 mph (21 meters per second/75.6 kph).


The Operational Phase Start Date of the Himawari-8 Geostationary Satellite is 7 July 2015.


The Calibration Equipment of the Monochromator Instrument is “Yokogawa AQ6376”.


The Project and Mission Overview of the GOSAT Satellite is Not provided.


The Power of the LEICA Particle Detector is 4.9 W.


The Pass Frequency of the Satellite Orbit Type is Three to five times per day.


The Altitude of the Swarm-B Satellite is Circa 516 km.


The Attachment Duration of the Cargo Dragon Spacecraft is About one month.


The PRN of the GSAT-0101 Satellite is 11.


The Typical Short Outburst Duration of the X-ray Source Celestial Object is Unknown.


The Purpose of the RAIDS Instrumentation is Acquire a global database of airglow intensities.


The Operation Mode of the ASAR Sensor is High-rate mode for up to 30 minutes per orbit, including 10 minutes in the eclipse phase.


The Conference Presentation Date of the Radio Aurora Explorer Satellite is Aug. 8-11, 2011.


The Temperature of the Proton Component Measurement Range of the DSCOVR Satellite is 40,000 – 2,000,000 Kelvin.


The Memory of the Transceivers Communication Device is 2 Mbit.


The Entrance Aperture Diameter of the COR2 Coronagraph2 Imager is 30.5 mm.


The Contracting Company of the PP Twin Telescopes Telescope is SENER.


The On-board Processing Procedures of the Optical Payload Imaging System is Radiometric correction, Inter-channel co-registration, Geo-referencing, Background classification, Hotspot detection, Consolidation of hot pixels, Extraction of attributes of hot clusters.


The Payload Mass of the GHGSat-D Microsatellite is 9 kg.


The Composition of the Ionosphere Atmospheric Layer is Electrically charged gases or plasma.


The Attitude Stabilization of the Spacecraft Satellite is 3-axis stabilized.


The Target of the Cal_doppler Observation Instrument is Sun.


The Contributions of the NASA Agency is SIR-C hardware, the Shuttle launch, ground systems, mission operations and data processing support.


The Deployment Status of the InflateSail Satellite is Not Deployed.


The Operation of the MSS Multispectral Scanner is Opto-mechanical scanning instrument (whiskbroom technique, unidirectional operation).


The Phases of the In-orbit Calibration and Validation Satellite Process is Two.


The Data Link Subsystem of the XSAR SAR Sensor Subsystem is DLS.


The Data Quantization of the VIS Visible region of spectrum is 12 bit.


The Tank Length of the Launcher Test Facility is 283.5 m.


The Vertical Resolution of the Tomorrow-R1 and -R2 Satellite is 250 m.


The Use of Commercial off the Shelve subsystems or subsystems composed of automotive grade parts of the Development Approach Satellite Instrument Development is Sometimes a choice is made to implement Commercial off the Shelve subsystems or subsystems composed of automotive grade parts, rather than state-of-the-art dedicated space applications.


The Pixel size of the Channel 1 Sensor is 32 km x 32 km.


The Spectral Bands of the CCD Camera Imaging System is 0.62 - 0.68 µm, 0.77 - 0.86 µm, 1.55 - 1.69 µm.


The ADCS Suite of the CanX-4 or CanX-5 Satellite is Tray Housing.


The Number of Maneuvers of the SkySat-5 Satellite is 5.


The Margin of the EV-9 Satellite is 3 dB.


The High-Gain Dish Diameter of the TGO Trace Gas Orbiter is 2.2 m.


The Earth Mapping Cycle of the OCO-2 Satellite is 32 days.


The Material of the HiRAIS Optical Instrument is Zerodur.


The Processor of the ACS Attitude Control Subsystem is Dedicated.


The Battery Type of the S/C Satellite is Lithium-iodine.


The Sensor Type of the MuREM Dosimeter is Dose rate sensitive photodiode.


The EEPROM of the OBDH Data Handling and Processing is 128 kB.


The Mission Status of the Herschel Satellite is Ongoing.


The Energy Resolution of the HXD Detector is ≤ 10% at 59.5 keV.


The Spatial Variations in XCO2 of the OCO-2 Satellite is <2%.


The End-of-life Date of the SPOT-4 Satellite is June 29th, 2013.


The Magnetic Onboard Recorders of the SPOT-4 Satellite is Operational.


The Orbit Altitude of the Alba Cluster 3 Satellite Cluster is 500 to 600 km.


The Focal Length of the Instrument Satellite Instrument is 72.5 mm.


The Type of the Solar Arrays Power System is Surface-mounted.


The Function of the EON-IR Satellite is Earth Observation Nanosatellite -Infrared.


The Inclination of the Tandem-L Satellite is 98.4º.


The Type of the Sun sensors Sensor is 2 axis slit & photo cell.


The Channels of the Electric Field Measurement System Instrument is 16.


The Distance from Sun of the New Horizons Spacecraft is Unknown.


The Body-mounted solar cells of the CLAVIS Power Generation is True.


The Battery Voltage of the SBVR Power Supply is 55 to 96 V.


The Operation Duration of the CanX-7 Nanosatellite is Approximately six months.


The 185 km x 185 km of the RBV Instrument Image Size is Image of 185 km x 185 km.


The Instrument Provider of the SPARCS Satellite is NASA's Jet Propulsion Laboratory.


The Function of the Baffle Telescope Component is Thermal.


The Configuration of the Michelson Interferometer Interferometer is Flat-mirror Michelson.


The Processor of the OBC On-Board Computer is ERC-32 processor of ATMEL.


The Model Validation of the Oculus-ASR Satellite is Successful.


The External Panels of the GNB Satellite Platform is 6.


The Landing Attempt of the Falcon 9 first stage Rocket is Mostly successful.


The Freshwater Release of the A-68A Iceberg is 152 billion (152 x 10^9) tonnes.


The Mission Operation Concept of the VENµS Satellite is Unknown.


The Communication Restoration Date of the LightSail Satellite is May 31, 2015.


The Number of Cells of the Battery Energy Storage is 24.


The Pointing Restrictions of the CHIPSat Satellite is Sun, Earth, moon and in the orbital RAM direction.


The Signal Augmentation of the MTSAT Satellite is GPS wide-area signal augmentation.


The Count Rate of the EPD-E Energetic Particle Detector - Electrons is 10,000 to 50,000 counts/s.


The Purpose of the Low-Resolution Video Camera Camera is Spot the general location of interest.


The Tracking Support of the Debris Satellite Components is Joint Force Space Component Command.


The Altitude of the Noctilucent Clouds Atmospheric Phenomenon is 50 miles (80 km).


The Launch Date of the SwissCube Satellite is 2009.


The Symbolism of the Emirates Mars Mission Mission is Named as a symbol of hope for all Arab youth.


The Pixel Exposure Time of the Instrument Spectrometer is 2.0, 4.1, 8.2 ms (VIS); 6.6, 13.2, 26.4 ms (NIR).


The Altitude Range of the LEMUR-2 constellation Satellite Constellation is 400-600 km.


The Critical Activities of the Spacecraft Satellite is Performed in contact with the ground.


The Observation Period of the SoloHI Heliospheric Imager is 17-19 December.


The Data Quantization of the Imager Imaging System is 11 bit.


The Daily Acquisition Capacity of the SPOT-6 Satellite is 3 million km2.


The Influence on Exoplanets of the Stars Celestial Bodies is Can influence the climates and habitability of a star’s hosted exoplanets.


The Imaging Capability of the NovaSAR-1 Satellite is SAR and AIS (Automatic Identification System) data.


The Location of the TT&C Station Ground Station is Kiruna, Sweden.


The URL of the BioSentinel Satellite is http://digitalcommons.usu.edu/cgi/viewcontent.cgi?article=3453&context=smallsat.


The URL of the Solar Backscatter Ultraviolet/Total Ozone Mapping Spectrometer (SBUV/TOMS) Spectrometer is http://nssdc.gsfc.nasa.gov/nmc/experimentDisplay.do?id=1978-098A-09.


The Altitude of the Tatiana-2 Satellite is 825 km.


The Travel Date of the Smile Satellite is 16 March 2022.


The Observed Atoms of the IBEX Spacecraft is Hydrogen, oxygen, neon and helium.


The Launch Date of the GHGSat-D Satellite is June 22, 2016.


The Off-nadir Angle of the ICESat Satellite is 0.3º.


The End of Life Date of the IMAGE Satellite is 18 December 2005.


The Spectral Resolution of the OVIRS Spectrometer is R>2,000.


The Inner Temperature of the Dewar Component is ~ 256.6 K.


The Land Measurements of the Copernicus Sentinel-3 Satellite is Maps land, provides indices of vegetation state and measures the height of rivers and lakes.


The Altitude of the SPOT-1, -2 and -3 Satellites is 832 km.


The Number of Candidate Planets of the Kepler Space Telescope Space Telescope is More than 4,000.


The Presentation Date of the Agile data downlink solutions Data Communication System is June 4-8, 2012.


The Frequency (MHz) of the Galileo E1-B/C Signal Carrier is 1575.42.


The Nickname of the SpriteSat Satellite is Rising.


The Technology Development Start Year of the MOMS Optical Camera is 1979.


The Deep Survey Coverage of the Euclid Reference Survey Survey is ~40 deg2.


The Detection Capability of the InSight Seismic Experiment for Interior Structure (SEIS) is Marsquakes every day.


The Terrain Camera (TCAM) of the Chang’e-4 Lander Lander is Payload.


The Data Transmission Speed of the OceanSat-2 Satellite is 4 kbit/s.


The Attitude Control of the Payload Satellite Payload is Star Tracker, Gyroscopes & Control Moment Gyros.


The Aperture of the Telescope Assembly Optical Instrument is 45 cm.


The Global UTC Time Dissemination of the Galileo Satellite Navigation System is Within 30 billionths of a second.


The Cooling System of the Focal Plane Assembly Sensor Component is Active cooling subsystem.


The Radiator Function of the BepiColombo Spacecraft is Reflect heat directionally.


The ECCM Configurations of the Complete Solution Antenna Configuration is SPAN 5, SPAN 4 through digital beamforming, SPAN 2b, SPAN 3b+3, STRX.


The Wavelength of the FAI Auroral Imager is Near infrared (650-1100 nm).


The Testing Purpose of the Flying Laptop Satellite is New technologies and scientific Earth observation.


The Crew Capacity of the OWS Space Station is 3-person.


The Altitude Range of the Cluster Satellite Constellation is 25 000 km to 125 000 km.


The Components of the Uplink Optical Communication System is Slow tip/tilt mirror, dichroic mirror.


The Launch Date of the 3U CubeSat Satellite is 23rd June 2017.


The Bandwidth of the RF Ground Network Ground Network is Up to ten times the UHF radio.


The Features of the AIS Automatic Identification System is Simultaneous reception and decoding of any two channels in the maritime VHF band, as well as a software-defined radio architecture.


The Parameter Representation of the GEOS Model Weather and Climate Model is Mathematical equations that represent physical processes.


The URL of the Terrestrial Imaging Spectroscopy Missions Missions is doi:10.1109/IGARSS.2013.6723584.


The Vertical Resolution of the Limb Sensor Sensor is 2.2 km.


The Calibration Aim of the SODISM Solar Imaging Instrument is Provide long term sensitivity calibration.


The Downlink Speed of the ColKa Communication Device is Up to 50 Mbit/s.


The Announcement Date of the NASA Mission Asteroid Mining is August 8, 2013.


The Conference Presentation Date of the GOMX-1 Satellite is May 26-30, 2014.


The Frequency of the X-band phased array antenna Antenna is 8125 MHz.


The Launch Date of the FORUM Mission is 2026.


The Product Assurance/Quality Assurance Standards of the GomX-4 Satellite is ESA on nanosatellite missions.


The S-band antenna of the TT&C Tracking, Telemetry, and Command is 1.


The Impulse Duration of the X-band Radar is 3 µs.


The Cataloged X-ray Sources of the XMM-Newton X-ray Satellite is 71,951.


The Apogee Altitude of the IDEA-OSG 1 Microsatellite is 800 km.


The NLC Observation Start Date of the AIM spacecraft Satellite is May 13, 2013.


The Size of the Raw Science Data Packet Data Packet is 280 bytes.


The Orbit Distance from Earth of the SWFO-L1 Satellite is Approximately 1.5 million kilometers.


The Information Kit Date of the OasISS Space Module is May 2009.


The Bus Speed of the RAD750 SBC Single Board Computer is 66 MHz.


The Current Policy of the Meteosat Satellites Geostationary Satellites is Keep two operable satellites in orbit and to launch a new satellite close to the date when the fuel in the elder of the two starts to run out.


The Number of Satellites of the JL-1-GF03B Microsatellite is 6.


The Weight of the Venta-1 Nanosatellite is ~5 kg.


The Design Life of the Spacecraft Satellite is 7 years.


The Launch Date of the IMAGE Satellite is 25 March 2000.


The SSDR Capacity of the SLIM6 Satellite is 1.5 GB.


The Function of the ND Neutral Density Filter is Adjust the transmission of each spectral channel.


The Function of the Interface Modules Software Layer is Interface to the hardware components and the ONS module.


The Role of the MiWarS Device is Backup.


The FPA of the COR1 Coronagraph1 imager is 1024 x 1024 (2k x 2k array summed 2 x 2).


The Number of Gateway Stations of the OneWeb Satellite Constellation is Unknown.


The Market of the EarthSTAR Inc. Company is People's Republic of China, including Hong Kong and Macao.


The Type of the Sprite’s antenna Antenna is Half-wave V-dipole.


The Trail Time from Aqua of the CloudSat Satellite is ≤ 120 s.


The RF Output Power of the VHF COTS transmitter Transmitter is 22 dBm.


The Science Phase of the TanDEM-X Satellite is Three consecutive periods of different formation geometries.


The Number of Instruments of the ISIM Instrument Module is 4.


The Symposium Date of the WatER Satellite Mission is March 13-16, 2006.


The Beamwidth of the Onboard Antenna Antenna is 20º.


The Band of the TerraSAR-X SAR Satellite is X-band.


The Spatial Resolution of the WFC CCD Camera is 1 km.


The Object Detection Threshold of the Star Tracker Attitude Determination Device is Visual (or apparent) magnitude Mv 11.


The Launch Date of the Odin Satellite is February 2001.


The Measurement Interval of the Copernicus Sentinel-6 Poseidon-4 Radar Altimeter is Every 10 days.


The Grating Order of the Spectrometer Instrument is 2.


The Modulation Scheme of the High-speed link Radio Link is GFSK (Gaussian Frequency Shift Keying).


The Placement of the Patch Antennas Antennas is On opposite side of the spacecraft.


The Responsibilities of the ITF Instrument Test Facility is Instrument builds and tests, building a repository of engineering information.


The On Orbit Star Calibration of the Instrument Spectrometer is Once per week.


The Prototype of the L1 Detector Detector is Photograph.


The Transmit Power of the KaRIN Instrument is ~1.5 kW.


The Operation Status of the Chang'e-3 Moon Lander is Devices still work well.


The URL of the Chinese satellite Satellite is http://www.spaceflightinsider.com/.


The Number of Deorbited Prototypes of the Starlink Communication Satellite is 2.


The Imaging Frequency of the Dove Satellites Satellite is Once a day for the entire planet, up to 10 times a day for a particular location.


The Image Resolution of the CaSSIS camera Camera is Unknown.


The First Image Transmission Date of the LADEE Satellite is Feb. 13, 2014.


The Vibration Test Completion Date of the Quantum Satellite is 2 March 2020.


The Brochure URL of the Global Precipitation Measurement (GPM) Satellite is http://www.nasa.gov/sites/default/files/files/GPM_Mission_Brochure.pdf.


The Switched Lines for MTCU of the MRU Main Regulator Unit is 1 x 2.


The Calibration Status of the HRC (High-Resolution Camera) Camera is Ongoing.


The Inclination of the DMC-3 Constellation Satellite Constellation is 97.8º.


The Depth of Spectrometer Measurements of the Galileo probe Space Probe is About 75 miles (120 kilometers).


The Operation of the ADS-B Surveillance Technology is Aircraft determines its position via satellite navigation and periodically broadcasts it.


The Data Downlink of the Payload Satellite Payload is X-band.


The f/No of the CMOS Camera Camera is 2.8.


The Heater Systems of the TCS Thermal Control Subsystem is HM and HS.


The Anniversary of the X-ray Astronomy Field of Study is 50th anniversary in June 2012.


The Contract Period of the ELSA-d Mission is 12 months.


The Promoter of the SOHLA-1 Satellite is NEDO.


The Image Acquisition Date of the Landsat-8 Satellite is May 21, 2022.


The Power Dissipation of the IEC ISIM Electronics Compartment is 200 W.


The Number of Observations per Year of the 3XMM Catalogue X-ray Source Catalogue is 600-700.


The Power Consumption of the CEASE-2 Instrument is 1.7 W.


The Design Tolerance of the D3 D-Orbit Decommissioning Device is The alignment of the motor with the spacecraft's center of gravity resulted to be outside the designed tolerance.


The Resolving Power of the Spectrometer Instrument is R = 100.


The Signal Wavelength of the L-band SAR Radar is Around 10 inches (25 cm).


The Launch Date of the Starlink Communication Satellite is March 18, 2020.


The Area of the Vatnajökull Glacier Glacier is 8400 km2.


The Image Location of the CaSSIS Imaging System is Melas Chasma.


The IR Spectral Range / Bandwidth of the SOLSPEC-ATLAS Spectrometer is 800-2400/20./4.


The Power of the Solar Panels Power Generation is About 230 W.


The Launch Status of the DirecTV 15 Satellite is To be launched in a few weeks.


The Video Capability of the MWIR Imager Imaging Device is Yes.


The Characteristic Impedance of the Sprite’s antenna Antenna is 50 ohm.


The Pointing Angle of the ADACS Attitude Determination and Control Subsystem is 21.5º below the orbital normal.


The Crosses the Equator of the JPSS-1/NOAA-20 Satellite is About 14 times daily.


The Duration of the Nimbus Earth Radiation Budget (ERB) Experiment Satellite Experiment is 1975 to 1992.


The Propulsion Subsystem of the Spacecraft Satellite is > 10 mN of thrust, > 1000 s of I sp, 3 kg of Xenon.


The Fuel of the IRS-1A Satellite is Hydrazine.


The SNR in Nadir of the ELVIS Spectrometer is >500.


The Effective Area at 40 nm of the EUV Simulation Simulation is 28 cm2.


The Usage of the Spectral Imager Instrument is Not used.


The Telescope Aperture of the Pan Camera Imaging System is 0.7 m.


The Surface of the Flight Mirror Assemblies Optical System is Non-reflective surfaces are procured un-anodized and will be wrapped in polyimide tape for increased emissivity.


The Launch Date of the SpaceX CRS-19 Mission is 5 December 2019.