The Material of the Site Kingfisher Crater is Fresher, minimally-altered.


The Operation Period of the Remote Agent Software is Three days.


The URL of the SWOT Satellite Satellite is https://swot.jpl.nasa.gov/flight_systems.htm.


The Capability of the TDI Feature Imaging Device Feature is Low-light observations of imagery.


The Purpose of the GIPSY-OASIS Software is Earth orbit determination using GPS data.


The Grids of the FSU Solar Wind Faraday Cup is Monolithic grids etched from single wafers of high purity W.


The X-band Downlink Transmission Frequency of the CBERS-2B Satellite is 8103 and 8321 MHz.


The Equator Crossing Time of the Satellite Satellite is 10:26 hours.


The Pulse Width of the CSG-SAR Synthetic Aperture Radar is Programmable (5-100 µs).


The Processing Format of the ICEYE-X1 Satellite is GeoTIFF.


The Data quantization of the ALOS/PRISM Satellite is 8 bit.


The Manufacturer of the CHRIS Imaging Spectrometer is Space Group of Sira Electro-Optics.


The f/number of the 50 mm camera Camera is f/1.8.


The Total Impulse of the SkySat-3 Satellite is 1,732 Ns.


The Berthing Date of the Cygnus Satellite is July 16, 1014.


The Unknown Failure Rate of the CubeSats Satellite is 33%.


The Data Downlink of the ISERV Satellite is Via TDRSS.


The Max Transmission Rate of the DTS Data Transmission Subsystem is 320 Mbit/s.


The Humidity of the PM Satellite Component is 25~70%.


The Inclination of the ICEYE-X10 Satellite is 97.4º.


The Launch Date of the PlanetiQ satellites Weather Satellites is Early 2020.


The Control Center of the Chandra X-ray Observatory is Smithsonian Astrophysical Observatory's Chandra X-ray Center.


The Data Transfer of the Pléiades Neo Satellite Constellation is Up to 40 terabytes per day.


The Critical NASA Review Date of the TEMPO Pollution Monitoring Instrument is May 6, 2015.


The End of Life Date of the Galileo Second Generation (G2) Satellite Constellation is 31 December 2039.


The Exit Slit of the UVS Instrument Spectrometer Telescope is 2 x 4 mm.


The Precision of the SAGE-III Spectrometer is 0.1 % to 10 %.


The Panchromatic Resolution of the EROS-C Satellite is Comparable to EROS B.


The Evaluation of the Disaster Monitoring Constellation Satellite Constellation is Utility in Support of Earth Observation Applications.


The Atomic Clock Accuracy of the Galileo Satellite System is Accurate to a few nanoseconds.


The Data Production Start Date of the Tatiana-2 Satellite is Early January 2010.


The Break Energy of the First Broken Powerlaw Model Component is 1.2 keV.


The Quality Comparison of the Imaging Methods System is SMART > PAIS > Direct.


The Operating Bands of the SRAL Radar Altimeter is C-band and Ku-band.


The Picosatellite Capacity of the OPAL Satellite is 6.


The Manufacturer of the EXObox Electrical Management Unit is Exolaunch.


The Period of the Explorer 36 Satellite is 112 minutes.


The Infrared Multispectral Scanner of the HJ-1B Satellite is 1.


The Mission Objective of the OSMA-1 Satellite is Refuel Landsat-7 spacecraft.


The Imagery of the Pleiades Satellite is Not Free.


The Ground Testing of the Galaxy Spacecraft is Underway.


The Full Operational Service Start Date of the GCOM-W1 Satellite is May 17, 2013.


The Date of the Space Tethers and Small Satellites Presentation is Unknown.


The Flare List Events of the RHESSI Satellite is Over 70,000.


The Path Offset/Revolution of the Satellite Communication is 26.334º.


The Altitude of the Satellite Orbit Orbit is ~666 km.


The Satellite Configuration Frequency of the HyperScout® Satellite is Once per day.


The Resolution of the MUX Camera is 20 m.


The Data Rate of the Imager Imaging System is ~3.9 Mbit/s.


The Operation Center of the SAOCOM-1A Satellite is Mission Operation Center in CETT (Centro Espacial Teófilo Tabanera), CONAE –Cordoba.


The Instrument Mass of the RAMIS Radiation Detector is 540 g.


The Thermal Operating Range of the SAGE-III Instrument is 10-30º C.


The Bandwidth (GHz) of the ICI-7 Radiometer is 3.2.


The Mission 1 of the Planet Satellite Operator is Ability to image all of Earth’s landmass every day.


The Launch Year of the MicroWave Humidity Sounder-2 Sounder is 2013.


The Cross-Track Direction Body-Pointing Capability of the Kanopus-V 1 Satellite is Yes.


The Type of the Power System Satellite is Dual battery, gallium arsenide triple-junction solar cell based.


The Altitude of the SuperView 1A and 1B Satellite is 514 km.


The Author of the Can ripples on the sun help predict solar flares? News Article is Robert Sanders.


The Purpose of the Spaceborne scalar magnetometers Instrument is Map the Earth’s magnetic field.


The Data Rate of the OGS Optical Ground Station is 40 Mbit/s.


The Pointing of the Telescope Optical Instrument is Within a 40º cone centered around the anti-sun vector.


The Required Precision of the O3 Profile Satellite Instrument is 10, 10, 5%.


The International Astronautical Congress Date of the ETS-VII Satellite is Sept.28-0ct.2, 1998.


The Orbital Slot of the GSAT-0102 Satellite is B06.


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


The Type of the Focal Plane Receiver CCD is Multi-chromatic TDI.


The Data Transmission of the Himawari-8/9 Ground Segment Ground Segment is HOPE to JMA.


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


The Operation Status of the TanDEM-X Satellite is Nominal.


The Data Tile Size of the EnMAP Satellite is 1000 x 1024 pixels.


The Solar Array Size of the DSP satellites Satellite is 6.33 m2.


The Observation Content of the MIRIS Satellite is Images of M42 (Orion Nebula) and the Rosette Nebula.


The Installation Date of the Cygnus Cargo Spacecraft is 14 Nov. 2017.


The Power Usage of the Micro-electromechanical system chip Chip is 8.5 times less than proven systems.


The Mounting Ring Location of the LWIR Camera Camera is Blue.


The Failure Date of the NRCSD CubeSat Deployer is August 2014.


The Morse Code Beacon Frequency of the OSSI-1 CubeSat is 145.980 MHz.


The Lifetime Revolutions of the MWI Instrument Scan Mechanism Assembly is 180 million cycles.


The Primary Missions of the MEOSAR Search and Rescue System is Global Navigation Satellite Systems (GPS, Galileo and GLONASS).


The Commissioning End Date of the RASAT Satellite is Late December 2011.


The Design Teams of the QSP-1 Satellite is Germany, Sweden, and the US.


The Orbit Type of the Secondary Payloads Unknown is Elliptical.


The Field of View of the Z-panel camera Camera is 25o.


The Provider of the Level 0-1b software Software is KNMI.


The Focal Length of the Telescope Optical Instrument is 522 mm.


The Data Transfer Time of the Data Transfer Interface Communication System is Approximately twenty-four hours.


The IFOV (beam width) of the Antenna Reflector is 1.81º.


The Program of the InSight Lander is Manages by JPL.


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


The Mass of the CSS Instrument is 48 gram.


The Issue Resolution of the EDSN Organization is Eliminating unnecessary connections and ensuring no floating or undefined values in the software.


The Affiliation of the ITUpSat-1 Satellite is Istanbul Technical University.


The RF Transmit Power of the RA-1 Radar Altimeter is 55 W peak.


The Cold Interstellar Gas Percentage of the Universe Cosmology is 1.8 percent.


The Mission of the ISEE-2 Spacecraft is Mother/daughter/heliocentric.


The Number of Public Images of the Ikonos Imaging Satellite is 597,802.


The Counting Ability of the Particle Detector Instrument is 5×10 4  event/s.


The Thruster System of the ERG Satellite is Hydrazine.


The Inclination of the Satellite Orbit is 80º.


The Position of the Earth Imaging Camera Device is Bottom Middle.


The Output Frequency of the PRARE space segment oscillator Quartz-Crystal Oscillator is 5 MHz.


The Manufacturer of the AstroRad vest Radiation Protection is ISA.


The Launch Date of the Inspiration4 Mission is Mid-September.


The Role of the Thales Alenia Space Company is On-board Galileo 2nd Generation.


The Image Content of the ALOS satellite Satellite is Al Jawf oasis, city, large, irrigated agricultural plots, Kufra Airport.


The Instrument Commands of the Spacecraft Satellite is Queued up at the MOC remotely from the SOCs, and uploaded to the spacecraft during the next regular contact.


The Attitude Pointing Control of the Spacecraft Satellite is 1º in pitch, roll, yaw.


The Functions of the CMN Interface is Switching of receivers and calibration network, Acquiring some housekeeping information, Providing some power conversion and distribution to the receivers, Providing the receivers with a local oscillator signal derived from DICOS.


The Payload of the SV-2 Satellite is WINCS (Winds-Ion-Neutral Composition Suite).


The Torque of the CMGs Attitude Control is Up to 6.1 Nm.


The Company Type of the Spire Satellite Constellation is Provider of space-based data, analytics, and space services.


The Accuracy of the Rangefinder Module Laser Altimeter is 20 cm.


The Functionality of the DMFC Digital Signal Processing Card is Perform a variety of mission specific functions.


The Functions of the DPS Data Processing System is Process the raw science data, generate the ocean colour data products, work order generation, online quality control, output media preparations, data quality evaluation, and feedback to mission operations.


The Telemetry Rate of the FREND Instrument is 50 Mbit/day.


The Operator of the SEOSAT-Ingenio Satellite is ESA.


The On-Orbit Performance and Application of the HJ-1A and HJ-1B Satellites is Proceedings of the 60th IAC (International Astronautical Congress), Daejeon, Korea, Oct. 12-16, 2009.


The Landing Site of the InSight Spacecraft is Homestead hollow in Elysium Planitia.


The Altitude of the Secondary Payloads Nanosatellites and CubeSat is ~325 km.


The RFI Source Levels of the SMOS Satellite Satellite is Moderate, Strong, Very Strong.


The Launch Date of the FormoSat-5 Satellite is Unknown.


The Subsystems of the SVM Service Module is Thermal environment control, power generation and storage, orbit path control, payload data handling and transmission (PDHT).


The Data Rate of the SeaWinds scatterometer Scatterometer is 40 kbit/s.


The Imager of the IBEX Satellite is Energetic Neutral Atom Imager.


The Author of the Observation of the Earth and Its Environment Book is Herbert J. Kramer.


The Number of Algorithms of the Attitude Determination Quaternion Filter Experiment is Four.


The Impact Date of the DART Spacecraft is Coming September.


The Imagery Resolution of the ALOS-3 Satellite is 0.8 m.


The Previous Catalogue Object Count (1957) of the Gaia Catalogue of Nearby Stars Stellar Census is 915 objects.


The Along-Track Slit Width of the Nadir Sensor Wide-Field Telescope Sensor is 0.27º.


The Normal Operations Duration of the SELENE/Kaguya Satellite is 10 months.


The Launch Time of the Falcon 9 Launch Vehicle is 12:16 UTC.


The Spectral Range of UVIS of the ELVIS Spectrometer is 200-650 nm.


The Orbit Revolutions/Day of the ALMASat-1 Satellite is 14.


The Battery Status of the Grace Mission Satellite is Degraded.


The Third Birthday of the SmallGEO Satellite is 14 September 2020.


The Magnetic Field Strength of the CME (Coronal Mass Ejection) Solar Phenomenon is Double that of a normal CME.


The Age of the Iridium 33 Satellite is Modern.


The Field of View (FOV) of the Instrument Instrument is 52º.


The Observation Modes of the ALOS-3 Satellite is Nadir-looking and backward-looking panchromatic imager.


The Orbit Repeat Cycle of the Altimetry Satellites Satellites is Every ten days.


The Patent Award Date of the GHGSat-D Satellite System is January 2016.


The Frequency of the Internal Satellite Diffuser Calibration Device is Potentially every orbit.


The Primary Goals of the Dellingr Nanosatellite is Develop a cost-effective Center model for CubeSat development, Develop tailored, lean, and scalable end-to-end systems, Determine lessons learned, and apply them to the next generation of satellites.


The Sun Tracking Device of the ORA Instrument Atmospheric Measurement Instrument is No.


The URL of the OSIRIS-REx Spacecraft is https://www.asteroidmission.org/asteroid-operations/.


The Separation Date of the Schiaparelli Lander is 16 October.


The Ground Station of the SAR-Lupe Satellite System is 1.


The Coordination Partner of the PAZ SAR Processor Ground Segment Processor is IGS (Ingenio Ground Segment).


The Start Time of the Solar Eclipse Event is 11:00 UTC.


The Number of X-ray Source Detections of the 3XMM Catalogue X-ray Source Catalogue is 531 261.


The Estimated SNR of the Band 7 Spectral Band is 388.29 ± 153.69.


The Loss of Momentum and Expertise of the RISESAT Project is True.


The Telescope Type of the EUVI Extreme Ultraviolet Imager is Small Ritchey-Chretien telescope.


The Provides the next increment “Slot List” of the LCT MCC Control Center is During the execution of increment N-1, the LCT MCC at GSOC provides the next increment “Slot List”.


The Data Quality of the Landsat Satellite is Unmatched in quality, detail, coverage, and length.


The Performance of the ST (Star Tracker) Instrument is 10 arcsec.


The Mission Status of the HJ-1 Satellite is Operational (extended).


The Size of the Particle Detectors Instrument is 95 mm x 122 mm x 217 mm.


The LTAN of the SARAL spacecraft Satellite is 6:00 hours.


The Compressed Data Rate of the Camera Imaging Device is 105 Mbit/s.


The Impact Date of the LADEE Satellite is April 18, 2014.


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


The Development and Qualification of the LISA Pathfinder Cage and Vent Mechanism Mechanism is B. Zahnd, M. Zimmermann, R. Spörri, "LISA Pathfinder Cage and Vent Mechanism : Development and Qualification," Proceedings of the 15th ESMATS (European Space Mechanisms and Tribology Symposium) 2013, Noordwijk, The Netherlands, Sept. 25-27, 2013, ESA, SP-.


The Effect of Gravity of the Light Electromagnetic Radiation is Energy loss, lower frequency, longer wavelengths.


The Bulletin Publication Date of the GPS/MET Satellite is April 1998.


The Wavelength Range of the Band No 5 Spectral Band is 10.5 ± 0.50 - 11.5 ± 0.50 µm.


The P-POD Deployment of the CubeSat - Launch 4 Satellite is Successful.


The Movement of the InSight's robotic arm Robotic Arm is Helped "the mole" dig nearly 2 cm over the past week.


The Design Copyright of the BRITE-PL Satellite Project is SFL.


The Analog to Digital Conversion of the Front End Electronics Electronics is 12 bit.


The Authors of the Hokkaido Satellite Project Satellite is T. Totati, T. Sakakibara, T. Yasunaka, K. Ishimura, S. Satori, K. Sugimoto, D. Igarashi, H. Hoshika, T. Uematsu, S. Era, A. Nakamura, K. Hori, R. Mitsuhashi, J. Nishidate, T. Sato, T. Yoneya, Y. Aoyanagi, T. Iwamoto.


The Health Check Completion Date of the Hitomi X-ray Astronomy Satellite is March 26, 2016.


The Radar Sensitivity of the JPL Microwave Radiometer Radiometer is 12 dBZ.


The Launch Altitude of the James Webb Space Telescope Space Telescope is Approximately 870 miles (1,400 km).


The Solar Arrays Type of the Power Subsystem Satellite is Sun-tracking.


The Project Overview Author of the Optical Inter-orbit Communications Engineering Test Satellite (OICETS) Satellite is Katsuyoshi Arai.


The File Format of the Iris Video Camera Camera is MPEG-4.


The Data Cadence of the IMPACT and PLASTIC Instruments is Approximately 1 minute.


The Lean and Collaborative of the Development Approach Satellite Instrument Development is The instrument builder and PI can openly discuss and trade available margins on design and science requirements during instrument development.


The Launch Date of the RAVAN CubeSat is November 2016.


The Launch Time of the SpaceX CRS-13 Mission is 15:36 GMT.


The Launch Location of the ShadowCam Instrument is Cape Canaveral.


The Service of the Spire Global UK Company is Predictive analysis for global shipping, aviation and weather forecasting.


The Swath Width of the StriX-α SAR Satellite is More than 10-30 km.


The Conference Presentation of the GOMX-1 Satellite is 11th Annual CubeSat Developers’ Workshop.


The Antenna Size of the Biomass Satellite is 12 m diameter.


The Authors of the Case studies of aerosol retrievals Study is J. B. Chowdhury, B. Cairns, L. D. Travis.


The Technology of the MSAS Satellite-based Augmentation System is Advanced technologies such as satellite orbit ranging, and ionospheric and tropospheric delay estimation assumption.


The Operation Duration of the RAIDS Instrument is Eight months.


The Operation Duration of the QB50 CubeSat Constellation Satellite Constellation is 3 months.


The Swath Width of the HSRS Sensor is 190 km.


The Functionality of the Core-DHS Avionics Module is Same level as heritage equivalent avionics stack.


The Transmit Frequency (MHz) of the HRIT HiRID Data Receiver is 1558.


The | of the Atmospheric Turbulence Monitoring System Monitoring System is Atmospheric turbulence monitoring at DLR.


The Design Life of the Jade Rabbit Moon Rover is 3 months.


The Output Voltage (Redundant) of the LVPS Board Power Supply is +1.5 V.


The Stabilization of the FORTE Spacecraft is Momentum-biased, gravity-gradient stabilized (nadir-pointing).


The Telemetry Downlink Data Rate of the GIOVE-B Satellite is 31.250 kbit/s.


The NLC Observation Peak of the AIM spacecraft Satellite is During solar minimum.


The End of Life Date of the KySat-2 Satellite is 28 February 2014.


The Total Number of Pixels of the MS Bands Detector Line Arrays is 7,500.


The Orbit of the ETS-VIII Spacecraft is Geostationary orbit at 146º E longitude.


The Proton Energy of the GALS-VE Particle Energy Measurement Device is > 600 MeV.


The Extension Date of the International Space Station Space Station is April 27, 2023.


The Launch Date of the XMM-Newton X-ray Space Observatory is 10 December 1999.


The Revisit Time of the LIS Lightning Image Sensor is 4 days.


The Data Reception Station of the Ground Segment Satellite Ground Segment is Svalbard (Spitzbergen).


The Launch Date of the FITSat-1 Satellite is 21 July 2012.


The Firing Direction of the Micronozzle Propulsion System is -X.


The Funding Source of the CATS Lidar Instrument is International Space Station Program.


The Status of the ResourceSat-2 Satellite is Production.


The Band 1 of the Landsat TM Satellite is Coastal water mapping, soil/vegetation differentiation, deciduous/coniferous differentiation, chlorophyll absorption.


The Clocks of the GIOVE-B Satellite is Better than 1 ns per day.


The Water Decomposition Time Scale of the Mars Planet is Centuries.


The Multispectral Mode Bands of the SPOT satellite constellation Satellite Constellation is Red, green and infrared bands of the visible spectrum.


The Purpose of the Telescope-coronagraph 304 Å Telescope is Imaging hot plasma (T ~ 10 MK) of the solar corona.


The Role of the IMU Inertial Measurement Unit is Determine initial attitude at de-boost.


The Measurement Domain of the GF-3 Satellite is Land.


The Observation Directions of the MSU-100 Camera is ±8.7º, 0º.


The Conference Presentation Date of the EO-1 Satellite is June 22-24, 2004.


The Azimuth Resolution of the High Resolution Spotlight Imaging Mode is 1.1 m (single pol.).


The Release Date of First 13 Photos of the Gaofen-1 Satellite is June 6, 2013.


The Field of View of the Lens Optical Instrument is 24º x 96º.


The Meeting Date of the GMES Sentinel-3 Satellite is Sept. 16, 2010.


The Field of View of the A Photometer Instrument is 0.1o x 2.1o.


The Function of the System satlets Satellite Subsystem Type is Designed so each satlet constitutes a complete standalone system.


The Launch Date of the Galileo FOC-3 and FOC-4 satellites Satellite is 27 March 2015.


The Properties to Investigate of the Bricks Building Material is Number and orientations of protein bridges, compressive strength, and porosity.


The Mass of the IRS-1B Satellite is 975 kg.


The Interference Source Characteristics of the SMOS RFI Team Team is Topology, Power, Behaviour.


The Planned Launch Date of the Heinrich Hertz Satellite is 2016.


The CMOS Image Sensor Type of the Imager Payload is Radiation-hardened.


The Quantity of the Electrostatic Analysers Sensor is 2.


The Traditional Delivery Time of the Polar Satellite Data Data is 2 to 6 hours after the time of measurement.


The Rx Channels of the Complete Solution Antenna Configuration is 5.


The | of the Falcon 9 Launch Vehicle is Spaceflight gears up for dedicated Falcon 9 launch.


The SAR Payload Spatial Resolution of the RCM Satellite is 5 - 50 m.


The Mission Type of the Aditya-L1 Satellite is Study the Sun.


The Polarization of the Antenna Radar Antenna is Dual (H and V).


The Mission Launch Date of the PACE Satellite is 2023.


The Data Processing Algorithm of the V5QV FPGA FPGA is MSPI algorithm.


The MLST Excursion of the Envisat Satellite is 10 minutes.


The Magnetometer Suite of the RAX-1 Satellite is Two internally mounted tri-axial magnetometers and four dual axis magnetometers mounted on external faces of the satellite.


The Antenna Size of the Biomass satellite Satellite is 5 m diameter.


The Weight of the PowerCell Hardware is 4.3 kg.


The Data Transmission Bands of the ICEYE-X1 Satellite is S- and X-band.


The Phase of the ELSA-d Satellite Mission is AIT (Assembly, Integration and Test).


The Contribution to the Orion Program of the European Service Module Spacecraft Module is IAC 2015.


The Spatial Resolution of the IRS Imager is Halved with regard to IRMSS.


The Dicke Load Phases of the MWR Noise Injection Radiometer is Three.


The Performance of the SpinKF Attitude Determination System is Very well.


The Remaining Useable Propellant of the OrbView-3 Satellite is 22.98 kg.


The Size of the OptiCube-2 Satellite is 3U.


The Launch Vehicle of the ResourceSat-2A Satellite is PSLV-C36.


The Objective of the Cluster S/C Satellite is Provision of intercalibrated measurements of the magnetic field vector B.


The Mounting Orientation of the OPS systems Sensor is Not flat to the surface but shifted inside the body of MASCOT.


The Start-up ROM Capacity of the RAD750 SBC Single Board Computer is 64 KB.


The Backscatter Coefficient Accuracy of the ALT Experiment Altimeter is 1.0 dB.


The Storage Capacity of the SSRNI Data Acquisition and Registration System is 4 Gbit.


The Battery Capacity of the DSX Spacecraft Payload Module Satellite is 60 Ah.


The Wake Up Time of the Yutu-2 Rover is 1:45 p.m. Sunday.


The Type of the Andromeda Galaxy is Spiral.


The Weight of the ALTIUS Satellite is 266 kg.


The Center Frequencies of the ICI instrument Receiver is 183 GHz, 243 GHz, 325 GHz, 448 GHz and 664 GHz.


The Power of the EPS Electric Power Subsystem is < 8.6 W.


The Docking Location of the Cargo Dragon Spacecraft is Harmony module.


The Mishap Investigation Board Creation Date of the Glory Satellite is March 7, 2011.


The RAM of the SDR Host Computer Computer is 8 GB.


The Transmission Rates of the XBT X-band Transmitter is 12.5, 25, or 50 Mbit/s.


The Arrival Date of the NIRSpec Instrument is Sept. 30, 2013.


The Performance Range of the UV-1 Spectrometer is 270 - 310 nm.


The Attitude Accuracy of the DubaiSat-1 Satellite is 0.2º.


The Measurement Duration of the Temperature Sensor is 420 s.


The Material of the WISA Woodsat Satellite is Plywood.


The Publication Date of the Orbital Formation-Keeping System System is Jan.– Feb. 1989.


The Contract Award of the Lockheed Martin Company is $700 million.


The Manufacturer of the NAOMI Imager is Airbus DS (former EADS Astrium SAS).


The Camera Resolution of the Shakuntala Satellite is One of the highest.


The Latency of the ATL18 Land/Canopy Gridded Data is 45 days from receipt of last data in product.


The Operation Center Location of the Cheops Satellite is Torrejón, near Madrid, Spain.


The Sail Deployment Time of the InflateSail Satellite is Approximately one hour after ejection.


The Mission of the Lunar Flashlight Satellite is Exploration Mission 1.


The Connection Type of the Ground Station Communication System is Ethernet over IP (Internet).


The Quantum Efficiency of the Instrument CCD Imaging Camera is 0.8 at 630 nm.


The Attitude Control of the Deimos-2 Satellite is Three-axis.


The ADC Sampling Rate of the Rx Module Digital Receiver is 40 Msamples/s.


The Purpose of the GeoCarb Satellite is Distinguish between man-made and natural emissions.


The Length of Operation of the Solar Measurements Instrument is 5–10 min per orbit.


The GaAs of the Solar Array Type is The EPS (Electrical Power Subsystem) uses GaAs solar cells.


The Developer of the ODTML Data Collection System is Praxis Inc..


The Bus Size of the Spacecraft Satellite is 1.4 m x 1.4 m x 2 m.


The Instruments of the MTG-I Satellite is Flexible Combined Imager (FCI) and Lightning Imager (LI).


The Responsivity Requirement of the Responsivity Measurement Instrument is >0.89 A/W.


The Review of the Electric Propulsion Space Experiment (ESEX) Space Experiment is Journal of Propulsion and Power, Vol.18 No.4, 2002, pp. 723-730.


The Date of the IGARSS Symposium is July 21-26, 2013.


The Rotation Rate of the Reaction Wheels Satellite Component is Up to 60,000 rpm.


The Dosimetric Results of the Eureca Satellite is Unknown.


The Propellant Expulsion of the Advanced Composition Explorer Spacecraft is The pair of the tanks with less fuel expelled all of its propellant by 2014.


The Thermal Modeling Supporter of the Edison Demonstration of Smallsat Networks Project Project is Robert F. Coker.


The Pulse Trains of the LM thruster Thruster is Pulses on the order of 500 ms.


The Resolution of the SAR Image Satellite Image is 3-meter.


The Number of Antennas of the KSAT Company is More than 130.


The Spectral Channels of the SAGE-III Instrument is 9 solar 290-1550 nm.


The Funding of the GPSP Instrument is NOAA.


The Exposure Time of the NISP Photometer Instrument is About 100 seconds per filter.


The Center Frequency of the Channel 1 Sensor is 10.6 GHz.


The Communication of the TT&C System Satellite System is Effective and reliable UHF communication with BRMM.


The Arrival Time at Space Station of the Cygnus Cargo Spacecraft is Around 6:10 a.m. Thursday, Aug. 12.


The Launch Date of the OSIRIS-REx Spacecraft is September 2017.


The Measurement Domain of the KySat-2 Satellite is Ocean, Land, Snow & Ice.


The Altitude of the 7 microsatellites Satellite is 515 km.


The Number of Satellites of the FormoSat-7/COSMIC-2 Satellite Constellation is 6.


The Target Orbit Altitude of the Bion-M1 Spacecraft is 575 km.


The Publication Date of the DESIS Instrument is October 2019.


The Data Interface and Control Design of the SWEM Satellite is Derived from the MAVEN DCB.


The Launch Date of the NigeriaSat-1 Satellite is Sept. 27, 2003.


The Contract Win Date of the Spire, GeoOptics Companies is Sept. 16, 2016.


The Inclina. (º) of the Meteor-2-1 Satellite is 81.3.


The LAM Thrust of the AOCS Attitude and Orbit Control System is 440 N.


The Cargo Delivery of the SpaceX Cargo Resupply Mission is More than 2,910 kg.


The Launch Date of the CHEOPS Satellite is 2017.


The Unboxing Date of the Mercury Magnetospheric Orbiter Spacecraft is April 29, 2015.


The Conference Presentation Date of the Appliqué Sensor Interface Module Sensor Interface Module is Aug. 13-16, 2007.


The Observation Capability of the STEREO spacecraft Satellite is More than 270º of solar longitude.


The Dimensions of the Bus Bus is 1.6 m x 1.6 m x 1.5 m.


The Sensor Complement of the RaInCube Satellite is Unknown.


The Project Partners of the SPORT CubeSat is NASA, the Brazilian National Institute for Space Research (INPE), and the Technical Aeronautics Institute under the Brazilian Air Force Command Department (DCTA/ITA).


The On-Orbit Verification Mission of the TET-1 Spacecraft is IAC 2013.


The Theory of Gravity of the General Theory of Relativity Physics is Needs a modification.


The Orbit Altitude of the STSAT-3 Satellite is ~600 km.


The Operating Ranges of the Cluster S/C Satellite is 64 to + 63.992 nT, 256 to + 255.97 nT, 1024 to + 1023.9 nT, 4096 to + 4095.5 nT, 65536 to + 65528 nT.


The Developer of the Flight Computer Satellite is GSFC.


The Data Transfer Protocol of the Ground Support System System is TFTP (Trivial File Transfer Protocol).


The Launch Date of the Odin Satellite is 20 Feb 2001.


The PRN of the GSAT-0208 Satellite is 8.


The Provider of the Mission Control System Control System is GomSpace.


The Number of Images Captured of the PolyCam Camera is 7000 images.


The Mounting of the ATLAS Sensor Sensor is Spacelab pallet(s).


The Temperatures of the Cooler Passive Cooler is 81 K for LWIR patch.


The Power Transfer of the MWI Instrument Scan Mechanism Assembly is 200 W.


The Connectivity of the 5G Network Telecommunications Network is Reliable connection for people and devices, anytime and anywhere, with increased security.


The Peak RF Power of the HPA High Power Amplifier is 120 W.


The Orbit Type of the Vstar Gravity-field Measurement Microsatellite is Near-circular.


The Number of Elements of the Ground Segment Satellite Ground Segment is 2.


The Altitude of the IRS-1B Satellite is 904 km.


The Beam Focal Length of the Spectrometer Instrument is 400 mm.


The Mission Time of the Tandem-L Satellite is > 10 years.


The Mass of the MuREM Radiation Monitor is ~400 g.


The Manufacturer of the CAPSTONE Satellite is Rocket Lab.


The Total Mass of the Eutelsat 172B Satellite is 9,969 kg.


The Measurement Altitude Range of the MLS Microwave Limb Sounder is Upper troposphere to the lower thermosphere.


The Electronics Unit Dimensions of the PRARE ground transponder Ground Station Equipment is 560 x 560 x 300 mm.


The Data Storage of the TDI Signal Processing Technique is TDI chain.


The Launch Date of the JL-1-GF03B Microsatellite is 15 September 2020.


The Analog to Digital Conversion (ADC) of the dsPIC33F microcontroller Microcontroller is Unknown.


The Bandwidth of the Band 7 Spectral Band is 735-755 nm.


The Frequency Bands of the SIR-C Radar System is C-band, L-band, X-band.


The Temperature Range of the LWIR Cameras Camera is -59°C to 113°C.


The Type of the FPP Telescope Component is Housing two filtergraphs and a spectro-polarimeter.


The Distance from Earth of the HAT-P-7 Exoplanet is About 1,000 light years.


The Solar Sail Deployment Test Environment of the NEA Scout Spacecraft is Large, low-friction table.


The Architecture of the Instrument Carrier Carrier is Leverages GSFC recent experience with the James Webb Space Telescope ISIM (Integrated Science Instrument Module) structure.


The Change Date of the ACE Realtime Solar Wind Lists Data Service is Feb. 21, 2015.


The Radiometric Resolution of the OLI-2 Instrument is 14-bit.


The Level 0-1b & Level 2 processing facility of the PDGS Payload Data-processing Ground Segment is Hosted.


The Deployment Count of the J-SSOD (JEM Small Satellite Orbital Deployer) CubeSat Deployment System is 10.


The Orbit Inclination of the Lunar Landing Vehicle Vehicle is 45º.


The Technology Basis of the Hyperspectral Imaging Remote Sensing Technology is High spectral resolution measurements of light interacting with matter.


The Spectral Range of the CLARREO Satellite is 0.32 to 2.3 µm.


The Function of the PASTEC Payload System is Study the orbital environment, studying concepts such as the measurement of satellite dynamics (MEDY) and electrostatic potentials outside the SPOT spacecraft (SILLAGE).


The Agreement of the ABB Technology Company is Signed with GHGSat to deliver the payloads for GHGSat’s next 3 methane detecting satellites.


The Power Amplifier of the Navigation Antenna Antenna is 50 W.


The Ignition Duration of the T3µPS Pressure Sensor is 10 seconds.


The Payload of the MPQ442 Satellite is Qubduino.


The Launch Year of the MTG-S satellite Satellite is 2024.


The Revisit Time for CCD Camera of the Satellite HY-1B is Seven days.


The Alternate Name of the GCOM-C Satellite is SHIKISAI.


The Number of Fixed Experiments of the EAGLE Spacecraft is 4.


The Revenue Start of the Eutelsat Quantum Satellite is Fiscal 2021.


The Number of Mirrors of the Laser Retroreflector Array (LRA) Instrument is 9.


The Orbit of the GF-3 Satellite Satellite is Sun-synchronous orbit.


The Diameter of the SpinSat Spacecraft is 558 mm.


The Manufacturer of the NewSat Satellite is Satellogic.


The Function of the Organ-Chips Device is Study organ physiology and diseases in a laboratory setting.


The Availability of the Segments Program Segments is Via AsteroidDay.org, via SES Satellite, via ESA Web TV, ESA’s YouTube channel.


The Wavelengths of the ATOMMS Spectrometer is Centimeter and millimeter.


The Measurement Coverage of the SMAP Satellite is Global land area, excluding regions of snow and ice, mountainous topography, open water, and areas of extremely dense vegetation such as tropical forests.


The Field of View of the LRR Radar is ±57.6°.


The Position Accuracy of the PROBA-2 Satellite is 200 m (2σ) on each axis.


The Hill Coordinate System of the Hayabusa-2 Spacecraft is The Sun is always to the left and outside the figure.


The Field of Regard of the Pushbroom imager Optics is ±30º.


The Publisher of the Observation of the Earth and Its Environment: Survey of Missions and Sensors Documentation is Herbert J. Kramer.


The Number of GPS Satellites of the T3000G2 receiver GPS Receiver is 8.


The Stiffness of the Antenna Communication is > 0.1 Hz (in orbit).


The Launch Date of the STARS spacecraft Satellite is January 23, 2009.


The Manufacturing Start Date of the CHEOPS Instrument is Mid-2013.


The Spacecraft Attitudes Range of the GMOD Detector is From zenith (0º) to nadir (180º).


The Purpose of the Nexus S magnetometer Attitude Determination Device is Measuring the local magnetic field.


The Type of the RADARSAT-1 Satellite is Earth-imaging radar satellite.


The Function of the Restore-L servicer Robotic spacecraft is Extend a satellite's lifespan.


The Data Latency of the MetOp Satellite Satellite is 65 minutes.


The Manufacturer of the CubeSense Attitude Determination and Control Subsystem is University of Stellenbosch, South Africa.


The Description of the Sudden Stratospheric Warming Meteorological Event is Causes the strong wind around the edge of the polar vortex to weaken or reverse, leading the temperature of the polar stratosphere to rise rapidly by tens of degrees Celsius.


The Real-Time Orbit Determination Accuracy of the GF-3 Satellite Satellite is Better than 10 m (1σ).


The Launch Date of the Philae Spacecraft is Unknown.


The Mission of the Orbiting Carbon Observatory Satellite is Unknown.


The Affiliation of the Gamma-ray Spectrometer Experiment Experiment is University of New Hampshire.


The AI Deployment Date of the CIMON-1 Prototype is 15 November 2018.


The Redundancy Type of the RPU Receiver Processor Unit is Cold internal redundancy.


The Anomaly Compensation of the Astro-APS Star Tracker is White spots.


The Angular Resolution of the CIRiS Instrument is 0.00122 radians.


The Fault Tolerant Software Developer of the FPGA Component is UFRGS (Universidade Federal do Rio Grande do Sul).


The Launch Date of the NigeriaSat-X Satellite is Unknown.


The OPD for Shortest Wavelength of the Telescope Optical Instrument is Stays below a quarter of a wave.


The Full Operational Capability Date of the Galileo Satellite Satellite is Unknown.


The Optical System of the PS2 Optical Instrument is Five element.


The Design Concept of the SHIMMER FTS Fourier Transform Spectrometer is Diffraction at the gratings results in a wavenumber-dependent tilt of the wavefronts recombining at the beamsplitter, and interference of the tilted wavefronts creates Fizeau fringes at the instrument's CCD detector.


The Mass of the DataLogger Payload is 2 kg.


The Mission Programming of the VENµS Satellite is Unknown.


The Principal Investigator of the ECOSTRESS Instrument is Simon J. Hook.


The Peak Gain of the Antenna Conically-scanning reflector is 36 dBi.


The Types of Eruptions of the Sun Star is Coronal mass ejection, jet, partial eruption.


The Patent Filing Date of the GHGSat-D Satellite System is May 2015.


The Data License of the Copernicus Sentinel-3 Satellite is CC BY-SA 3.0 IGO.


The GPS Receiver of the S/C Satellite is Provides S/C location data for accurate orbit determinations and onboard time delivery.


The Launch Year of the Sentinel-1A/B Satellite is 2016.


The Uplink Speed of the ColKa Communication Device is Up to 2 Mbit/s.


The Launch Date of the IRNSS-1C Satellite is Oct. 15, 2014.


The Mass of the Boulder Geological Feature is 230 tons.


The Mass of the Corvus-BC-3 Nanosatellite is 11 kg.


The Mass of the Instrument General is 15 kg.


The Global Service Target of the OneWeb Satellite Constellation is 2021.


The Manufacturer of the ADCS Attitude Determination & Control Subsystem is XACT, Blue Canyon Technology.


The Journal Article of the Demeter Satellite is Chorus and chorus-like emissions.


The Arrival at Mars of the ExoMars Trace Gas Orbiter Orbiter is 2016.


The Control Precision of the PCS Pointing Control System is One thousandth of a degree.


The Design Date of the CHRIS Imaging Spectrometer is Unknown.


The Article Date of the XMM-Newton Satellite is 20 January 2020.


The Trajectory Analysis and Design Presentation of the OMOTENASHI Satellite is 26th International symposium on Space Flight Dynamics.


The Discovery of the MAXI J1820+070 Black Hole is Newly discovered.


The Operation Start Date of the TET-1 Satellite is Oct. 16, 2012.


The Funding of the SRTM Shuttle mission is NIMA.


The Developer of the AstroRad vest Radiation Protection is StemRad.


The Mass of the HAT-P-7 Exoplanet is Somewhat larger than the planet Jupiter.


The Registration Time of the DUV Instrument is 100 ms.


The Purpose of the EXPORTS Satellite Mission is Advance the utility of NASA ocean color assets to predict how changes in ocean primary production will impact the global carbon cycle.


The Status Update Date of the SeaWiFS Satellite is Jan. 24, 2011.


The Spacedaily Article Date of the GRAIL Mission is Dec. 12, 2007.


The Operators of the SATis5 Satellite is Unknown.


The | of the Joseph K. Taylor 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 Spatial Resolution of the EarthDaily Optical Imager Optical Imager is 5 m.


The Launch Date of the Satellite Spacecraft is Unknown.


The Operational Start Date of the RASAT Satellite is Start of 2012.


The Manufacturer of the LALT Laser Altimeter is NEC Corporation.


The Field of View of the NFI Near Field Imager is ~2º.


The Detected Particles of the IBEX Spacecraft is Energetic Neutral Atoms (ENAs).


The Spatial Resolution of the VIS Visible region of spectrum is 400 m (at nadir).


The Considering Deals of the Rocket Lab Aerospace Company is True.


The Launches in 2021 of the Falcon 9 Rocket is 8.


The Payload of the PAZ Satellite is X-band SAR (Synthetic Aperture Radar).


The Growth Test Times of the Experiment Microbiology is Within 1-2 weeks, three months, six months after launch.


The Sensitivity to Instrument Degradation of the Occultation Techniques Atmospheric Study Method is Less sensitive than other remote sensing methods.


The Launch Vehicle of the Galileo FOC-3 and FOC-4 satellites Satellite is Soyuz-STB/Fregat-MT.


The Formation Time of the Pilbara and Yilgarn Cratons is About 2.2 billion years ago.


The J2000 declination (deg) of the J1846-0258 Pulsar is -2.97503.


The Purpose of the CIRCE Mission is Understanding the dynamics of the ionosphere.


The Annual Salt Extraction of the Saltworks Salt Production Facility is 9 million metric tons.


The Firing Pressure of the X-axis Bang-Bang Maneuver Satellite Maneuver is 1.56 bar.


The Deployment and Retrieval of the Eureca Satellite is Unknown.


The Coupling Ratio of the OGS Data Detector Detector is 90% reach the fiber and 10% the ACT.


The Most Powerful Auroras of the Jupiter Planet is Yes.


The Orbital Height of the HyperScout® Satellite is 500 km.


The Launch Date of the Restore-L Satellite is 2025.


The Lens of the LinkSprite JPEG color VGA camera Camera is 131o FOV wide angle lens.


The Type of the Orbit Centaur AV-042 upper stage is SSO.


The Announcement Date of the European Commission Satellite Technology Acquirer is 8 October 2018.


The Function of the Onboard Neural Network Artificial Intelligence is Detecting whistlers.


The Purpose of the MUSIS System is Surveillance, reconnaissance and observation.


The Orbit of the OCO-3 Satellite is Mounted on the exterior of the space station, which circles between 52º north and 52º south latitude.


The Manufacturer of the Tyvak 61C Satellite is Tyvak Inc..


The Ignition of the CGG Cool Gas Generator is By a glow plug, avoiding the use of pyrotechnics.


The Trajectory Change Start Date of the Rosetta Spacecraft is August.


The Total Mass of the PSLV-C38 Launch Vehicle is ~955 kg.


The | of the Miniature Imaging Spectrometer Imaging Spectrometer is Miniature Imaging Spectrometer for Aalto-1 Nanosatellite.


The Pass Duration of the Ground Stations Ground Station is 2.5 hours.


The Mass of the SCD-2 Satellite is 117 kg.


The Control System of the S/C Satellite is Four reaction wheels and gyro-stellar attitude determination.


The Number of Main Sections of the XMM-Newton spacecraft Satellite is 4.


The Boom Length of the AstroTube Payload is 1.5m.


The Source Data Rate of the Instrument Sensor is 200 bit/s.


The Development Date of the New maritime Galileo receiver Device is 24 June 2021.


The Atmospheric Pressure of the Galileo probe Space Probe is About 320 pounds per square inch (22 bar).


The Field of View of the AVHRR/3 Instrument is ±55.37º about nadir.


The Mode of the SAR Sensor Subsystem SAR Sensor is ST (Standard Mode).


The Accuracy of the Star Trackers Attitude Determination Device is >99.45% per orbit.


The Manufacturer of the PACE 2U CubeSat is NCKU (National Cheng Kung University).


The Launch Date of the SpaceX CRS-24 Mission is 21 December 2021.


The Circuit Board Area of the ChipSat CubeSat is 3.5 cm2.


The Data Processing Time of the CryoSat-2 Satellite is Within two days of acquisition.


The Components of the IMS-2 System Satellite System is EPS (Electric Power Subsystem) with battery and solar arrays, AOCS (Attitude and Orbit Control Subsystem), TT&C (Telemetry, Tracking & Command) subsystem, RCS (Reaction Control Subsystem), thermal subsystem for bus, mechanisms.


The Data of the SMAP Satellite is Soil moisture status, timing and extent of potential frost damage.


The Detector Type of the SIS (Scanning Imaging Spectrograph) Spectrograph is Photon-counting.


The Energy Range of the HOPE Helium Oxygen Proton Electron is From less than or equal to 20 eV or spacecraft potential (whichever is greater) to greater than or equal to 45 keV.


The Heat Shield of the Orion Spacecraft is Manufacturer Location.


The Measurement Frequency of the Global Oil Storage Monitoring Product is Weekly.


The Sea Ice Extent of the GCOM-W1 Satellite is 19.47 million km2.


The Exposure Time of the Coronal Hole Boundaries Imaging Device is < 10 seconds.


The Voltage Conversion Level of the PCDM Power Conditioning Module is ±5 V level.


The SWIR Channels of the PROBA-V Satellite is 3.


The Control Electronics of the Lander Spacecraft is Provide the interface to all the sensors and the actuator drives.


The Percentage of Stars within 100 parsecs of the Gaia Catalogue of Nearby Stars Stellar Census is 92%.


The Goal of the RHESSI Satellite is Investigating particle acceleration and energy release in solar flares.


The Data Coverage of the QuikSCAT Scatterometer is Over 90% of the global ocean.


The Potential Locations of the MiniCOR Instrument is L1 (Lagrangian Point 1), L4 and L5.


The Mission Update Date of the IBEX Satellite is Nov. 14, 2011.


The Measurement of the SSAS Sensor is Sun angle.


The Symposium Date of the MICROSCOPE Satellite is June 4-8, 2012.


The Inclination of the Rideshare mission Satellite is 97.6º.


The EarthCARE-ROSES Call of the CloudSat Satellite is Recommendation.


The Development Date of the PRARE Satellite Observation System is 1990.


The Nominal Rate of the S-band Downlink Communication System is 40 kbit/s.


The Time of the Imaging Process is 25 minutes.


The Manager of the WFIRST Mission is NASA's Goddard Space Flight Center.


The Similar To of the VIIRS Sensor is MODIS.


The Test Campaign Date of the Smile Satellite is 21 April 2022.


The Launch Date of the SSOT Satellite is Unknown.


The Global Coverage of the JPSS-1/NOAA-20 Satellite is Twice a day.


The Polarization of the ICI-3 Radiometer is V.


The Components of the Drag-free control system Control System is Shadow sensor, small cold gas thruster, ADACS.


The Structure Material of the CeREs Satellite is Aluminum.


The Measurement Datation of the Satellite Satellite is ±100 μs with respect to UTC.


The Imaging Mission of the SEOSAT–Ingenio Satellite is High-resolution images of Earth's land cover.


The Full Form of the Lemur-2 Satellite is Low Earth Multi-Use Receiver-2.


The Relative Velocity at Closest Approach of the Juno Spacecraft is 41,600 mph (67,000 km/h).


The Modes of Operation of the XSAR SAR Sensor Subsystem is High resolution mode by sliding spotlight, Standard mode by stripmap technique and Wideswath mode by TOPS (Terrain Observation with Progressive Scan) technique.


The Cadence of Images of the OSIRIS Narrow Angle and Wide Angle Cameras Imaging System is Increased in each observation.


The Experiment of the Airbus Aerospace Company is Testing a completely new onboard software system in the space environment.


The Function of the VT Data Processing is Provide GRB alerts with sub-arcsec accuracy.


The Operation of the OCO-2 Spectrometer is Pass through the atmosphere twice.


The Battery Nominal Voltage of the S/C Satellite is 3.7 V.


The Star Detection Rate of the Gaia Satellite is Up to 10,000 stars/s.


The Activity Level of the Solar Activity Natural Phenomenon is Exceptionally low and practically constant.


The Propulsion System of the EAGLE ESPAStar Satellite is Hydrazine-based monopropellant.


The Resolving Power of the Visible Channel Imaging Device is 300.


The Delay Announcement Date of the Quantum Satellite is 6 August 2019.


The URL of the Super Dual Auroral Radar Network Radar Network is http://www.superdarn.ac.uk/archive/Chisham_et_al_2007.pdf.


The Resolution of the SXI Spacecraft is 7 arcsec (on axis).


The Value of the Atmospheric Pressure Weather Parameter is 1051.6 hPa.


The Type of the Tatara Bridge Bridge is Cable-stayed.


The Presentation Date of the GMES Contributing Missions (GCM) Satellite Constellation is June 6-7, 2012.


The Regulated Voltages of the COVE Board Data Transfer Device is FPGA: 3.3 V, 2.5 V, 1.0 V; Configuration PROM: 3.3 V, 1.8 V; Magnetoresistive RAM: 3.3 V; Flash memory: 3.3 V; ADCs: 3.3 V, 1.25 V; Buffers, muxes: 3.3 V.


The Launch Vehicle of the SpaceX CRS-13 Mission is Falcon-9 FT.


The Mass at Launch of the Satellite Satellite is Dry mass = 750 kg.


The Actuation Control of the Canopus Pipper Satellite is 3-axis.


The Manufacturer of the SpaceEye-T Satellite is Satrec Initiative.


The Article Date of the CXO Satellite is 29 January 2019.


The SST Accuracy of the AATSR Instrument is Better than 0.3 K.


The Test Results of the IEPS Ion Electric Propulsion System is All 21 tests were completed faultlessly, except for the break-down protection test.


The Project Manager of the TEMPO Instrument is Stephen Hall.


The Launch Date of the EM-1 Mission is 2019.


The Developer of the EMIT Satellite is NASA’s Jet Propulsion Laboratory.


The Mass of the BugSat-1 Microsatellite is 22 kg.


The Agility of the SPOT-6 & SPOT-7 Satellite Constellation is Pitch and roll forward, backwards and sideways by 45°.


The SNR of the Band 5 Spectral Band is 110.


The Heat Production of the XO-3b Exoplanet is Unknown.


The Effective FOV of the Channel 1 Sensor is 89 km x 198 km.


The In-Track Look Capability of the NEMO-AM Satellite is Slightly less than 90º.


The Nodes of the SpaceWire Link on TacSat-4 Communication Link is PDH (Payload Data Handler) module in the CDE (Command and Data Electronics) on the bus side and the UIE (Universal Interface Electronics) on the payload side.


The Vertical Cell Size of the Ozone Measurement Instrument Atmospheric Measurement Device is 3 km.


The Technology Presentation Date of the Quantum Satellite is 21 November 2019.


The Early Data Release 3 (EDR3) of the Gaia Satellite is Data processed, validation ongoing.


The Frequency of the S-band Band is 2.45 GHz.


The Solar Panel Power Output of the AprizeSat Satellite is 7.7 W.


The Imaging Wavelength of the PROBA-2 Satellite is Extreme ultraviolet.


The Slit Width of the IRIS instrument Instrument is 1/3 arcsec.


The Affiliation of the Toshinori Kuwahara Author is Unknown.


The Operating Capability of the Teledyne’s MUSES Platform Platform is Full.


The Program Start of the SIR-C/X-SAR Payload is Seasat Synthetic Aperture Radar (SAR) in l978.


The Mass of the HIRES Instrument is 1.12 kg.


The Mission of the LunaH-Map Spacecraft is Lunar Polar Hydrogen Mapper.


The Architecture of the NRD Electronics System is Multi-board with specific functions.


The Composition Energy Range of the ECT Suite Instrument Suite is Up to 50 keV for ions, from a few to 50 MeV/nucleon for ions.


The Enclosure Size of the XPAA Phased Array Antenna is 30.5 cm x 33 cm x 7.4 cm.


The Altitude of the Spacecraft Orbit is 645 km.


The Emissivity (ε) of the FCA Flow Control Assembly is 0.8.


The Operational Status of the SAGE-III Instrument is Operational.


The SAR Payload Chirp Bandwidth of the RCM Satellite is 100 MHz.


The Channel of the Broadband Applications Experiment Communication System is 450 MHz broadband channel.


The Start Date of the Cooks Peak fire Wildfire is April 17.


The Presentation Date of the Magnetospheric Multiscale (MMS) Mission is Feb. 24-27, 2014.


The Stabilization of the Resurs-P1 Satellite is 0.005º/s.


The Beam Tracking of the Eutelsat Quantum Satellite is Enabled.


The Satellite Tracking Capacity of the MEOLUT Next Local User Terminal is Up to 30 satellites.


The Orbit Determination Accuracy of the AutoNav Autonomous Navigation System is <1000 km in position and <0.4 m/s in the velocity vector.


The Ground Projection of the Spectrometer Instrument is 0.4 km x 12 km.


The Thickness of the Dobson Unit Unit of Measurement is 0.01 mm.


The Data Contribution of the Copernicus Sentinel-1 Satellite is Included in the research.


The Length of the LMAG (Lunar Magnetometer) mast Instrument is 12 m.


The Conference Presentation Date of the On-Board Data Handling System Data Handling System is Nov. 22-26, 2004.


The Attitude Control of the Payload Satellite Payload is Slew Acceleration.


The Speed of the Spectrometer Channel Optical System is Relatively slow (f/14).


The Power Consumption of the CMS Instrument is 26 W.


The Mission Objective of the CHEOPS Satellite is Study the structure of exoplanets smaller than Saturn and measure the bulk density of super-Earths and Neptunes.


The Optical Bench Length of the Telescope System X-ray Telescope is 10 m.


The Wavelength of the Responsivity Measurement Instrument is 1850 nm.


The Beacon Frequency of the CUTE-1.7+APD Satellite is UHF (437.385 MHz).


The Mission Type of the CO2M Satellite is Monitoring and Tracking Carbon Dioxide Emissions.


The Average Payload Power of the QuikTOMS spacecraft Satellite is 107 W.


The Power Consumption of the VIRR Instrument is 7.3 W.


The Status of the Microsat-R Satellite is Destroyed.


The Number of Referred Papers Produced of the HaloSat Satellite is 7.


The Calibration Types of the ICU Internal Calibration Unit is Absolute and relative radiometric calibrations and spectral calibrations.


The Interface of the PAZ SAR Processor Ground Segment Processor is HMA (Heterogeneous Mission Access).


The Agency of the FalconSat-3 Satellite is USAF.


The Monitoring of the ISS LIS Lightning Imaging Sensor is Occurrence and changes in extreme storms.


The Range of Radiation Temperature Measured in Bands 4-6 of the Scanning geometry Instrument is 213-313 K.


The URL of the Satellite Satellite is http://badc.nerc.ac.uk/data/gedex/detail/aem2sag1.det.


The Layout of the DHS Data Handling System is Not Applicable.


The Mass of the LIMS Instrument is 68.4 kg.


The Target of Opportunity Duration of the INTEGRAL Satellite is 100,000 seconds.


The Aperture Size of the SWAP Instrument is Largest ever used to measure the solar wind.


The Frequency of the Monitoring of HIS Calibration Process is Daily.


The Launch Date of the Beijing-3A Satellite is 11 June 2021.


The Mass of the Sentinel-1C Satellite is 2.3 tons.


The Vibration Test Frequencies of the FPM Instrument is 5 Hertz and 2000 Hertz.


The Mission Type of the FedSat Satellite is EO.


The Mission Status of the Galileo Satellite Navigation System is Operational (nominal).


The Wavelength of the SAR Synthetic Aperture Radar is 23.5 cm.


The Altitude Increase of the SARAL/AltiKa Satellite is 1 km.


The Avionics Architecture of the TechEdSat Satellite is SPA (Space Plug-and-Play Avionics).


The Bias Requirements of the Aeolus Satellite is Can be expected to be met after further optimization of the instrument calibration and data processing.


The Pump Module of the GEDI Laser Laser is Below the layout.


The | of the SI Reaction Wheel Reaction Wheel is SI reaction wheel.


The Storage Capacity of the PLCDHS Data Handling System is 2 GByte.


The Distance from Jupiter's Cloud Tops of the Juno Spacecraft is 2,100 miles (3,400 km).


The Function of the SCP Satellite Communications Payload is Provide a UHF link for the ODTML services and to function as an internal S&F subsystem.


The Electric Field Measurement Frequency Range of the IOF Plasma Wave Instrumentation is 40 Hz and 178 kHz.


The Design Life of the SPOT-1 Satellite is Three years.


The Telemetry Submission Method of the GeneSat-1 Satellite is Web site.


The Purpose 2 of the PW-Sat CubeSat is Demonstration of a satellite deorbit structure.


The Deployment Framework of the Galileo Satellite System is FOC (Full Operational Capability).


The Sun sensors of the BEESAT-3 Satellite is Yes.


The Number of Telescopes of the NICER XTI X-ray Timing Instrument is 56.


The Objective of the APD Avalanche Photodiode is Observe the low energy charged particle density distribution in LEO (Low Earth Orbit).


The Measurement of the Global Positioning System Satellite System is Geopotential Heights.


The Stereo Angles of the Instrument Satellite Instrument is ±15º (fore and aft).


The Frequency of Issuing Requests for Information of the NASA Organization is About once a year to once every 18 months.


The Separation Angle of the STEREO spacecraft Satellite is 90º.


The MMAs Status of the IXPE observatory X-ray Observatory is Three of four MMAs is built.


The Launch Date of the ISS-RapidScat Instrument is 20 Sep 2014.


The Rotation Angle of the Y-axis Bang-Bang Maneuver Satellite Maneuver is 130º.


The Launch Site of the SEOSAT-Ingenio Satellite is Europe's Spaceport in Kourou, French Guiana.


The Delivery of Operational Requests of the TDP Operations Satellite Operations is Weekly.


The Payloads of the Kick Stage Rocket Stage is 34 smallsats.


The Interface of the Modem Processor Signal-Processing Chain is SPI (Serial Peripheral Interface) running at 1 MHz line rate.


The Battery Thermal Regulating System of the Neutron-1 Spacecraft is Active internal system with a sensor, heater, and controller.


The Material of the Torus/Strut Structures Satellite Component is 12 mil thick neoprene coated Kevlar.


The Agility Range of the Pleiades-1A Satellite is Up to 1500 km on either side of their path.


The Dynamic Range of the Magnetometer Instrument is 160 dB (ELF/VLF range), 130 dB (LF/MF range).


The Ground Resolution of the MWNIR Imaging System is 100 km - 18 km.


The Mission Type of the Meteor-1/Meteor-2/Meteor-Priroda Series Satellite Mission is EO.


The Maximum Operating Speed of the DCU-S(TC) module Communication Module is 128 kbit/s.


The Bus Connection of the CubeSat Satellite is I2C or CAN.


The Frequency of the S-band Transmitter Transmitter is 2234.4 MHz.


The Orbit Count of the Genesis-2 Satellite is 10,000.


The Reaction Wheel Momentum Offloading of the PROBA-V Satellite is Autonomously performed when the instrument is not imaging.


The Orbital Slot of the GSAT-0208 Satellite is C07.


The Clearing Date of the Aalto-1 Satellite is June 21, 2018.


The Spectrometer Type of the ACE-FTS Instrument is Adapted version of the classical Michelson interferometer.


The Solar Wind Speed and Beta of the ACE Satellite is ~40% lower on average from 2009 through the day 79 of 2013.


The Project Manager of the HORYU-4 Satellite is Professional staff.


The Sensitivity of the XSM X-Ray Detector is ~ 7000 cps at flux level of 10-4 W m-2 in the range 1-8 Å.


The Function of the MIU Interface is Receives payload commands and spacecraft telemetry from the FC and forwards those to the CEU.


The Modulation of the RF Communications Communication System is Bell 202.


The Orbit Determination of the CryoSat-2 Satellite is Real-time orbit determination for spacecraft attitude and orbit control (on-board).


The Data Collection Duration of the GOCI Geostationary Ocean Color Imager is Eight hours.


The Online Availability Date of the TRUTHS Satellite is 13 February 2004.


The Manufacturer of the PPS-1350-G Hall-effect thruster is SNECMA of France.


The NEΔT (K) of the ICI-10 Radiometer is 1.9.


The Launch Date of the COSMO-SkyMed-1 Satellite is June 8, 2007.


The Objectives of the EUI Extreme UV Imager is 1. Provide EUV imagery with at least a factor 2 higher spatial resolution than currently available, to reveal the fine-scale structure of coronal features. 2. Provide full-disc EUV imagery of the sun to reveal the global structure and irradiance of inacce.


The Potential Generation of the SenPot Amplifier is Maintains the IVM reference ground at the floating potential with respect to the plasma.


The Components of the NLS-2 Launch System is QuakeSat.


The Processed Resolution of the Detector Sensor is 10 bits or 8 bits.


The CGA Implementation of the MC3 Ground Station is Allowed for the ground stations to be unmanned 24/7.


The Mass of the LituanicaSAT-2 Satellite is 3 kg.


The Mass of the AMU Altimeter Microwave Unit is 8 kg.


The CCD Detector of the NMS Neutral Mass Spectrometer is 256 x 256 elements.


The Loading Temperature Change of the Helium Gas is To allow warmer temperature helium to be loaded.


The Components of the Maeva Hinges Deployment Mechanism is Carpentier elastic blades, SMA strings, Cerafil heater wires.


The Mass of the Pegasus Nanosatellite is Unknown.


The Data Rate of the Unit Communication System is 1000 bit/s.


The Purpose of the Carbon Mapper Satellite Constellation is Pinpoint, quantify and track point-source methane and CO2 emissions.


The Operational Duration of the Odin Satellite is 21 years.


The Location of the LISA Pathfinder Spacecraft is L1 (Lagrangian Point 1).


The Type of the MIRI Instrument is Mid-Infrared Camera-Spectrograph.


The Observation Date of the OMI Satellite is 15 Dec. 2016.


The Calibration Task of the Machine Learning Algorithm Calibration Tool is Recognize solar structures and determine calibration needed.


The Configuration of the SONATE nanosatellite Satellite is ASAP-L (light).


The Integration Test Date of the PROBA-V Satellite is April 15, 2013.


The Prime Contractor for A satellites of the MetOp-SG Satellite Program is Airbus Defence and Space of France.


The Purpose of the OLA Instrument is Provide high accuracy range data of Bennu for navigation and long-range scans of the asteroid surface to establish the shape and model the gravity of Bennu.


The Saturation of the Honeywell QA2000-030 accelerometers Accelerometer is Around 27.5 rpm.


The Processor of the SWEM Satellite is Coldfire.


The Data Stream of the Copernicus Sentinel-6 Satellite is Slated for distribution later this year or early next year.


The Microcontroller Clock Speed of the CC430 SoC System on Chip is 8 MHz.


The Observation Duration of the Roman Satellite is Several days.


The RF Communications of the exactView-1 Satellite is S-band TM/TC (Telemetry/Telecommand) for satellite operations.


The Purpose of the OCI Ocean Color Instrument is Examine and monitor phytoplankton communities in the ocean.


The Sensor Suite of the NEMO-AM Satellite is SFL sun sensors, SFL magnetometer, SI star tracker.


The Frequency of the RF communications Communication System is 437.27 MHz.


The Mass of the MSI-0 and MSI-1 MSI Instruments is 3 kg.


The Mass of the Microsatellite Satellite is 47 kg.


The Resolution of the PamCam Panoramic Camera is 1280 x 1024 pixels.


The Location of the Lockheed Martin Sensing and Exploration Systems Systems is USA.


The Wind Speed of the Massive Stars Stars is Millions of km/hour.


The Distance from Solar System of the Pleiades Open Cluster is About 400 light years.


The Data Transmission of the New Horizons Spacecraft is Ongoing.


The Payload Data Storage of the MERLIN Satellite is Increased.


The Data Acquisition Start Timing of the ARC Calibration System is Adequate.


The Instrument Configuration of the Ground Segment Communication System is Based on predicted crossing times of magnetospheric regions of interest in combination with various on-board trigger algorithms.


The Components of the AAE Experiment is Appliqué sensor network, adaptive wiring manifold, high-performance computing on-orbit, and software definable radio.


The Configuration of the FENIX micropropulsion device Micropropulsion Device is Can be at each corner of the CubeSat or doubled up on either side.


The Detector of the Spectral Band B Spectrometer is Si-PIN.


The Solar Array Span of the QuickBird-2 Satellite is 5.2 m.


The Image Capture of the NASA's Solar Dynamics Observatory Satellite is Full-disk Sun and the left side of the inset image.


The Mission Overview and Status Date of the WindSat Satellite is June 5, 2006.


The Instrument Size of the HySI Hyperspectral Imager is 275 mm x 275 mm x 205 mm.


The Width of the Penumbra Shadow is 100+ km.


The Conference Date of the GIOVE-B Satellite is May 3-6, 2009.


The Interaction of the Solar Orbiter Spacecraft is Crossed one of the comet’s two tails.


The Absolute Measurement Error of the Vector Magnetometer Instrument is Less than 1 nT.


The Thrust Measurement Method of the AQT-D Propulsion System is Direct.


The Article Date of the XMM-Newton Satellite is July 12, 2016.


The FOV per channel of the Eastman Kodak KLI14403 linear CCD sensor Sensor is 26.6º.


The Mass of the GCOM-W1 Satellite is ~1990 kg.


The Purpose of the IGOR+ GPS Receiver is Allows the tracking of occulting signals.


The Thermal Control of the Satellite Spacecraft is Milli-Kelvin (mK) passive thermal control of the payload.


The Extended Range Testing Distance of the GomX-4A and GomX-4B Satellites is Up to 4500 km.


The Angular Resolution of the HaloSat Satellite is 15° or less.


The Operator of the Himawari-8/9 Ground Segment Ground Segment is Himawari Operation Enterprise Corporation (HOPE).


The Pericenter Distance of the SMART-1 Satellite is 2189.702 km.


The Launch Date of the IRS-1B Satellite is August 29, 1991.


The Telemetry of the CEASE-1 Instrument is 10 byte/min.


The Expected Return near to Earth of the Satellite Spacecraft is 2029.


The Launch Date of the COMPASS-1 Satellite is Dec. 10, 2001.


The Antenna Diameter of the Satellite Communication Satellite is 4.2 meters.


The Location of the Receiver Sensor Sensor is Back side of the terminal.


The Polarization Angle of the Band 2 Spectral Band is 0/60/120 º.


The Baud Rate of the RS-422 UARTs Communication Interface is 115 kbit/s.


The Auxiliary Payload of the NorSat-3 Satellite is Navigation Radar Detector (NRD).


The Mission Type of the Hubble Satellite is Discovery of Diverse Exoplanets.


The Mission Status of the Tatiana-2 Satellite is Finished.


The Accuracy of the Gravity Satellite is mgal.


The Maximum Drill Depth of the SD2 Instrument is About 0.2 m.


The Size of the SHS Instrument Spectroscopic Instrument is Small.


The Spatial Resolution of the Geodesy Orbits Satellite is 100-1000 km.


The Attitude Accuracy of the Attitude and Orbit Control Subsystem Subsystem is 0.4º in roll and pitch.


The Imaging Capabilities of the HARP-2 Satellite is Wide swath, polarization, and multi-angular sampling.


The Malfunction Date of the Yutu Lunar Rover is March 3, 2014.


The Mission Goal of the MinXSS-2 Satellite is 5 years.


The Construction Start Year of the China’s space station Space Station is 1992.


The User of the P-POD Deployer is Unknown.


The CPU Operating Frequency of the OBC On-Board Computer is 50 MHz.


The Mass of the TCS Thermal Control Subsystem is 0.15 kg.


The Energy Range for H of the LEICA Particle Detector is 0.76 - 6.1 - - 18 - 250 MeV.


The Focal Point of the SWAVES Instrument is University of Minnesota.


The Polarization Measurement of the Sentinel-5 Satellite is First three elements of the Müller matrix.


The Diameter of the Mars' Core Seismic Analysis is About 3,660 kilometers.


The Closest Approach Distance of the Solar Orbiter Satellite is 460 km.


The Power Input Voltage Range of the COVE Board Data Transfer Device is 6.0-8.4 V.


The Status of the YOUTHSAT Satellite is Functioning Satisfactorily.


The Number of Spacecraft of the DSP Satellite Project is 2.


The Orbit Inclination of the ISS-RapidScat Scatterometer is Lower than polar sun-synchronous satellites.


The Configuration of the SARAL spacecraft Satellite is Overview shown in Figure 2.


The Albedo of the Lutetia Asteroid is Unusually low.


The Collision with Cliff of the Philae Lander is 45 minutes after landing.


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


The Closest Approach to the Sun of the Rosetta Satellite is Perihelion.


The LOS Wind Error Requirement of the Rayleigh Channel Instrument is Below a certain value.


The Data Rate of the Spacecraft Satellite is 100 Mbit/s.


The Header Size of the Raw Science Data Packet Data Packet is 23 bytes.


The Memory of the AIM Reconfigurable Computing Hardware Device is 4 M x 16 Flash for storage of multiple Xilinx configurations.


The Current Quantity of the Artificial Objects Satellite is 22,000.


The Manufacturer of the Clementine Spacecraft is US Naval Research Laboratory (NRL).


The Mission Overview of the ExoMars Trace Gas Orbiter Orbiter is URL: http://exploration.esa.int/mars/46124-mission-overview/.


The Mass of the Tether Satellite Component is 5.5 kg.


The Mission Status of the GeoEye-1 Satellite is Operational (extended).


The Swath Width at Nadir of the Telescope Optical Instrument is 30 km.


The Observation Date of the MAXI Instrument is July 13, 2011.


The 28 ±6 VDC of the Solar Array Power Generation is A regulated 28 ±6 VDC power bus distributes energy to all S/C subsystems and instruments.


The Conjunction Transition Orbit of the Hayabusa-2 Spacecraft is Placed slightly further away from the asteroid.


The Data Acquisition Period of the TanDEM-X Satellite is 2011 and 2015.


The Spatial Resolution of the ETM+ Enhanced Thermal Mapper Plus is 15 m (PAN band), 30 m (VNIR/SWIR bands), 60 m (TIR band).


The NASA Announcement of the Gravity Probe B Satellite is May 4, 2011.


The Operation Start Date of the OptiSAR™ Constellation Satellite Constellation is 2022.


The Location of the DCS Data Collection System is LEO.


The Hazard of the Site Nightingale Crater is Building-size boulder on the eastern rim.


The Number of Normal Cameras of the PLATO Telescope is 24.


The Conference Presentation of the Sensor Web Sensing System is First IEEE International Conference on Sensors 2002.


The Manufacturer of the Göktürk-1 Satellite is Telescpazio.


The URL of the Nimbus Earth Radiation Budget (ERB) Experiment Satellite Experiment is http://journals.ametsoc.org/doi/pdf/10.1175/1520-0477%281993%29074%3C0815%3ATNERBE%3E2.0.CO%3B2.


The Goal of the Solar Cells Energy Device is Enable high-efficiency space solar cells and panels to be produced in large quantity and at lower cost.


The Online Publication Date of the Herschel and Planck Telescopes is 12 September 2019.


The Mission Goal of the Tandem-L Satellite is Set new standards in Earth observation.


The Unregulated Bus Voltage of the EPS Electric Power Subsystem is 28V ±6 V DC.


The Mass of the NEOSSat Satellite is ~74 kg.


The Team Members of the CIRiS Infrared Radiometer is A. Amparan, A. Ghandour, T. Kampe, P. Kerrigan, J. Necas, D. Piqueira, G. Reavis, R. Rohrschneider, M. Veto, R. Warden.


The No of Passbands of the Channel 3 Sensor is 1.


The Orbit Altitude of the Rosetta Spacecraft is Less than 10 km from the comet's surface.


The Material of the Heatshield Thermal Protection is Al honeycomb structure.


The Operational Data Rates of the ACTS Mobile Terminal Mobile Terminal is 2.4, 4.8, 9.6, 64, to 128 kbit/s.


The Mean Separation Time from CALIPSO of the CloudSat Satellite is 15 seconds.


The Mass of the AprizeSat-9 Nanosatellite is 12 kg.


The Timing Precision of the NICER X-ray timing instrument is < 100 ns.


The Radar Altimeter of the HY-2A Satellite Satellite is Unknown.


The Auroral Potentials of the Jupiter Planet is Up to 400,000 electron volts.


The Fault-tolerant satellite design of the BEESAT-2 Satellite is Yes.


The URL of the PSLV Launch Vehicle is https://www.isro.gov.in/2018press15.html.


The Initial Orbit Altitude of the Bion-M1 Spacecraft is ~300 km.


The Wavelength of the Responsivity Measurement Instrument is 1990 nm.


The Resolution of the OLS Imaging Sensor is 2.8 km.


The SNR of the Instrument Spectrometer is > 100.


The Pixel Size of the Detector Array CCD is 13.5 µm.


The Orbital Inclination of the LDEF Satellite is 28.5º.


The Mission Type of the Sich-2 Satellite is EO.


The Imaging Rate of the Instrument CCD Imaging Camera is About 60 0.1 second exposures per minute with the NIR camera, and 1/2 second exposure per minute with the VIS camera.


The Imaging Frequency Band of the SARLupe Satellite is X.


The Location of the VIS Unit is Service Module.


The Size of the QuakeSat Satellite is 10 cm x 10 cm x 30 cm.


The Nationality of the Max Valier Person is Italian.


The Software Architecture of the AOCS Attitude and Orbit Control System is Object-oriented and modular with a static architecture.


The Development Date of the Microsized Microwave Atmospheric Satellite (MicroMAS) Satellite is April 28, 2013.


The Minimum Trigger Level of the Receiver Communication Device is -96 dBm.


The Operational Modes of the SIR-C Phased Array is ScanSAR and Spotlight.


The Latency of the Starlink Satellite Internet Service is 20 milliseconds.


The Deployment of the AstroMesh Reflector Reflector is Deployed.


The Purpose of the SSIKLOPS Launcher is Provide means to release small satellites from the ISS.


The Power Consumption of the Safe-mode System System is Very low.


The Axes of the Attitude Determination and Control System Satellite is Full 3-axis.


The Decommissioning Date of the Midcourse Space Experiment Satellite is 2010.


The Inclination of the Shakuntala Satellite is 97.4°.


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


The Additional Test of the Biomass Satellite is Thermal elastic distortion test.


The Launch Date of the MESA Technology is Aug. 2013.


The Ground Resolution (Mosaic mode) of the XSAR SAR is 1.8 m.


The Energy Optimization of the HEG Grating is High.


The Accuracy for 2000 kg payload of the IPS Pointing System is 0.5 arcseconds lateral and 41 arcseconds roll in sun mode.


The Length of the TT Telescope Tube is 6.80 m.


The Mass of the Instrument Device is < 7 kg.


The Impact of the Asia’s Summer Monsoon Weather Phenomenon is Refilling aquifers, generating hydroelectric energy, providing water for crops.


The Delivery Date of the CUTE Satellite is Mid-September 2021.


The Polarization of the MWR Radiometer is V and H.


The Spectral Region of the QWIP Detector Detector is 11-17 μm.


The Data Rate of the HEED Instrument is 0.19 kbit/s.


The Conference Date of the Sentinel-3 Satellite is 5-9 September 2011.


The Laser System Position Accuracy of the LAGEOS Satellite is About 10 cm.


The Loading Temperature of the Helium Gas is Cold.


The Payload of the SEOSat/Ingenio Satellite is Optical.


The Observation Date of the HSRL-2 Lidar is 10 October 2014.


The Instrument Architecture of the OMPS Sensor is Staring spectrometer.


The Spectral Resolution of the MEGS Spectrograph is 0.1 nm.


The P/L Power of the Repeater subsystem Communication System is < 3500 W (EOL).


The Housing Material of the Detector Stack Instrument Component is Tungsten.


The Test Transmission Data Rate of the Herschel Spacecraft is 1.5 Mbit/s.


The Spacecraft Size of the QSat Satellite is 492 mm x 503 mm x 502 mm.


The Transmission Configuration of the Data Download System Satellite System is All files (already downloaded and not yet downloaded) or only not yet downloaded files.


The International Space Station Arrival Date of the NanoRacks CubeSat Deployer Missions CubeSat Deployer is April 18, 2017.


The Last Accessed Date of the JAXA Missions Satellite Missions is March 2015.


The Presence of the Carbon Dioxide Ice Patch Surface Feature is Isolated rare case.


The Altitude of the SARAL spacecraft Satellite is ~800 km.


The Venus Flyby Types of the V7GA Mission is Resonant and non-resonant.


The Internal Harness Connectors of the ASM Satellite Component is Removed.


The Orbit Maneuver Support of the INSAT-2A/2B Satellite is Integral apogee boost motor.


The Clocks of the GIOVE-B Satellite is PHM (Passive Hydrogen Maser).


The Launch Mass of the Bion-M1 Spacecraft is ~6,840 kg.


The Number of Planned Satellites of the OneWeb Satellite Constellation is 1980.


The Spatial Resolution of the GHGSat's New Satellites Satellite is < 25 m.


The Processor FLOPS of the MPM Main Processor Module is 10 FLOPS.


The Orbit of the Himawari-9 Satellite is Geostationary.


The Center Frequency of the Channel 7 Sensor is 48 GHz.


The Time Since Formation of the Blue Ring Nebula Nebula is Millennia.


The Image of the Terminator Tape Deorbit Module Deorbit Device is Prototype version of the Terminator Tape Deorbit Module.


The Reusability of the Terran R Launch Vehicle is Both stages and its payload fairing will be reusable.


The Design of the ATLID Power Laser Head Laser Head is Sealed and pressurized.


The CCSDS ID of the GSAT-0206 Satellite is 266.


The Launch Confirmation Date of the MeteoSat Third Generation Satellite is 23 March 2021.


The Field of View of the Limb Imager Instrument is 75 to 110 km tangent altitudes, 300 km across the track.


The Location of the DPS Data Processing System is Balanagar.


The Type of the MTG-S Satellite is Sounder.


The Purpose of the Swarm Satellite Constellation is Space science studies.


The Dayside Temperature of the 55 Cancri e Exoplanet is 4,400º Fahrenheit (about 2,400º Celsius).


The Purpose of the Aerothermodynamics Technology is Validation of design tools and improvement of design performance.


The L-band Receivers Data Rate of the UoSAT-12 Satellite is 1 Mbit/s.


The Material of the Ribbon Cable Component is Unknown.


The Launch Date of the Galileo Satellites Satellite is July 25, 2018.


The Connection of the SATLAB Configuration is SATSIM is connected with the OBC through the CAN bus.


The Manufacturer of the ACLS Air and Oxygen System is Airbus.


The Pixel Pitch (Pan) of the Pushbroom imager Detectors is 12 µm x 12 µm.


The Mapping accuracy of the Spectrometer Spectrometer is < 1.5 km.


The Comet Encounter Date of the ICE (International Cometary Explorer) Spacecraft is September 11, 1985.


The Orbit Latitude Range of the NICER/SEXTANT Instrument is ±51.6 º.


The Side Slither Calibration Frequency of the Satellite Imaging Satellite is Quarterly.


The SAR Payload Peak Power Consumption of the RCM Satellite is Approximately 1270 W.


The Mass of the TSAT CubeSat is Unknown.


The Satellite Ground Track Range of the TUC Transponder Microwave Transponder is 3-5 km.


The Founding Date of the Spacety Company is 2016.


The Lead Author of the Parker Solar Probe Satellite is Justin Kasper.


The Data Downlink Speed of the Payload Satellite Payload is 800 Mbit/s.


The Material of the Satellite Structure Satellite Component is Aluminum 6061.


The Battery type of the EPS Electric Power Subsystem is Li-ion.


The Viewing Angles of the PROBA-1 Satellite is Five different.


The Orbital Altitude of the Swarm-C (Charlie) Satellite is ≤ 530 km.


The Data Communications Transceiver Frequency of the OSSI-1 CubeSat is 437.525 MHz.


The Data Product Format of the OSCAT-2 Instrument is HDF 5 (Hierarchical Data Format 5).


The Image Date of the AWiFS Imaging System is May 4, 2011.


The Conference Date of the Deorbitsail Deployable Sail is April 8-11, 2013.


The IR Energy Reflection of the Optics Assembly Dichroic Mirror is 85%.


The Camera Suite of the OSIRIS-REx Spacecraft is OCAMS (PolyCam, MapCam, and SamCam).


The Camera Type of the SLIM6 Satellite is Multispectral scanning camera.


The Memory Type of the DSU Data Storage Unit is Non-volatile memory.


The Qualification Program of the Virtex-4 FPGA Data Processing Unit is Undergoing vibration and thermal cycling tests.


The PROM of the STRV-1d DHS Data Handling System is 32 k PROM.


The Approx. peak sensitivity altitude of the Channel 2 Sensor is Unknown.


The Constellation of the UrtheCast Satellite System is Optical and SAR satellites.


The Operation of the MERIS Sensor is Only out of eclipse.


The End Year of the MDPP-2 Program is 2003.


The Orbit Altitude of the GPM Core spacecraft Satellite is 400 km.


The Operation Duration of the Yutu Lunar Rover is 972 days.


The Earth Illumination Angle Constraint of the CHEOPS Telescope is Larger than 35º.


The Instrument Builder of the TEMPEST-D Satellite is JPL.


The Rainfall Measurement of the IMERG Satellite Data Product is Over 310 mm.


The Focal length of the 1000 mm camera Camera is 1000 mm.


The Integration Time (ms) of the Antenna Reflector is 100.


The Aperture of the NESSI Telescope is 15 cm.


The Area of the GDS Light Curtain is 100 cm2.


The Data Input of the Coprocessor Satellite Component is PRN, estimated delay, and estimated Doppler of the reflection.


The Filming Locations of the UrtheCast’s Proprietary HD Video Camera Camera is More than 10 countries across four continents.


The Fix Interval of the NovAtel OEMV-1 GPS receiver GPS Receiver is Approximately once every 25 hours.


The Configurations of the Satellite Constellation Imaging Satellite Constellation is Nominal orbital configuration, Interferometric orbital configuration.


The Reorganization Date of the Maxar Space Solutions Company is February.


The Data Transfer Rate of the SpW Data Transfer Protocol is 135 Mbit between 2 consecutive image acquisitions.


The Departure Time from Space Station of the Cygnus Cargo Spacecraft is About three months after arrival.


The Operation Modes of the MPO-MAG instrument Instrument is Set of science operations modes.


The Launch Date of the Anand Satellite is 26 November 2022.


The Receiver Sensitivity of the Argos System Data Collection System is Increased.


The Trajectory Deflection of the Solar System Celestial System is Diameter of an atom every second.


The Frequency (MHz) of the GPS L1C Signal Carrier is 1575.42.


The Prime Contractor of the Spacecraft Satellite is Alenia Spazio.


The Battery Type of the EPS Electric Power Subsystem is NiH 2  battery.


The Panchromatic Resolution of the SuperView 1A and 1B Satellite is 0.5 m.


The Launch Date of the Argos ANGELS Satellite is 18 December 2019.


The Heritage of the Avionics Core Satellite Component is Multi-mission version of avionics.


The Mass of the DPU Digital Processing Unit is 14 kg.


The Ground Earth Stations of the MSAS Satellite-based Augmentation System is Kobe Aeronautical Satellite Center and the Hitachi-Ota Aeronautical Center.


The Purpose of the Gaia Satellite is Measure the positions and motions of stars in our Milky Way galaxy.


The Orbit Altitude of the CartoSat-2D Satellite is 506 km.


The Dimensions of the NanoRacks Kaber Microsat Deployer Satellite Deployer is 40 cm x 42 cm x 31 cm.


The Arrival Date of the SpaceX Dragon Spacecraft is 4 April 2018.


The Data Rate of the Transmitter Communication Device is 500 Mbit/s.


The | of the Long March 4B Launch Vehicle is "China and Brazil to launch CBERS 3 satellite in November 2012".


The Launch Date of the CXBN-2 Satellite is 18 April 2017.


The Orbit Estimator of the NigeriaSat-2 Satellite is Recursive orbit estimator.


The Detector Type of the IIR Imager is Microbolometer.


The NEΔT (K) of the ICI-5 Radiometer is 1.1.


The Propulsion System of the SkySat-3 Satellite is HPGP (High Performance Green Propulsion) system.


The Objectives of the AMSU-A Instrument is Atmospheric temperature profile measurements from the surface up to about 50 km in 15 channels.


The Impact Detection of the Apollo seismometers Seismometers is Large impacts.


The Launch Date of the IXPE observatory X-ray Observatory is 2021.


The Electronics Package Volume of the FlaPS Instrument Package is 290 cm3.


The Sensor Quantity of the ADS Attitude Determination Subsystem is 3-axis magnetometer.


The Launch Date of the CryoSat Satellite is Oct. 08, 2005.


The Next Dust Clearing Date of the InSight Mars lander Spacecraft is June 5, 2021.


The Mission Start Date of the Solar Orbiter Spacecraft is February 14, 2020.


The Accuracy of the CERES Instrument is 0.6 Wm -2  sr -1.


The Attachment Method to SA panel of the Superelastic Springs Mechanical Component is Riveted and directly soldered.


The Field of View of the WV60 imager Imaging System is 2.12°.


The Launch Date of the Venµs Satellite is Aug. 2, 2017.


The Launch Date of the TET-1 Satellite is 2012.


The Spectral Band Wavelengths of the ERIP Earth Remote-Sensing Imaging Package is 252.0, 273.5, 283.0, 292.2, 301.9, 320.0, 340.0 nm.


The Operating Status of the Envisat Satellite is Nominal.


The Launch Date of the H-IIA launch vehicle No. 37 Launch Vehicle is 23 December 2017.


The Photon Index Above the Break of the First Broken Powerlaw Model Component is 1.4.


The Launch Date of the Crew Dragon Spacecraft is 2:40 a.m. EDT Oct. 31.


The Pointing Error of the AOCS Attitude and Orbit Control Subsystem is ± 0.05º in roll and pitch.


The Approximate Time to Deorbit of the Spacecraft 3U CubeSat is 5-20 days.


The Development Lead of the HyperScout Hyperspectral Imager is cosine.


The Onset of Latchup of the CMOS Sensors Sensor is Occurs at LET values typically 16 MeV cm-2/mg and higher.


The Measurement Type of the NINA-2 Experiment is Light high-energy ions.


The Design Pressure of the Cylinders Pressure Vessel is More than double normal operation pressure - 1000 times atmospheric pressure.


The Swath Width (Individual) of the HRV Imager is 60 km.


The Payload Power of the DSX Spacecraft Payload Module Satellite is 350 W, 1.1 kW.


The Advanced Small Analyzer for Neutrals(ASAN) of the Chang’e-4 Rover Rover is International Joint Collaboration Payload.


The Objective of the RHESSI Imaging Instrument is Obtain high fidelity color movies of solar flares in X-rays and gamma rays.


The Planned Observational Capabilities of the FengYun LEO satellites Satellite is WindRAD for sea winds, GAS for greenhouse gases absorption measurement.


The Application of the Observation Target Satellite is Maritime, Disaster Monitoring, Water Conservancy, Meteorology.


The Apogee Alignment of the MMS and THEMIS Satellites is 180º apart.


The Launch Date of the Prichal Module Docking Port is 24 November 2021.


The Power of the Minisatellite Satellite is 50 W.


The Components of the Tianwen-1 Mars Mission is Mars orbiter, a lander and a rover.


The Antialiasing Filter Poles of the Rx Module Digital Receiver is 19.


The Objective of the S-020 XUV Spectrograph is Record on photographic film a spectrum of the X-ray and ultraviolet radiation from the sun in the 1-20 nm (or 10 - 200 Å) region, with modest angular resolution.


The Purpose of the Electric Propulsion Propulsion System is Propel the satellites from the orbit in which they will be launched to the final operational orbits.


The Location of the Eureka Station Weather Station is Canadian Arctic at 80 degrees north latitude.


The Experiment of the ISL Tracking Antenna Antenna is Bidirectional TM/TC data relay to a LEO satellite.


The Operation of the CAPSTONE Spacecraft is Return humans to the Moon.


The URL of the Orion Spacecraft is http://www.nasa.gov/feature/orion-passes-the-pressure-test.


The Long-Term Tracking of the LAGEOS Satellite is Yes.


The Cross-Track of the HORUS Sensor is 1.6°.


The Purpose of the GMDSS Global Maritime Distress and Safety System is Rescue mariners in emergency situations while at sea.


The Incident Angle of the Radar Radar is ~39º.


The Frequency of the Millimeterwave receiver radiometer is 190 GHz.


The Advantages of the Diffracting Optic Optic is Easing of engineering constraints, reduction in mass.


The Operation of the Frontier Radio Instrument is Hardened to continue working even in the harshest conditions.


The Maximum Rock Height of the Schiaparelli Lander is 40 cm.


The Magnetic Field of the SWFO-L1 Satellite is +10.


The Weight of the SPOT-1 Satellite is 1800 kg.


The Behavior of the SAA South Atlantic Anomaly is Gradually weakening.


The Spatial Resolution of the HSC CCD Imaging Camera is 300 m.


The Recording Resolutions of the SPOT-4 Satellite is 2.5 - 20 m.


The Multi-Look of the Capella SAR System is 30.


The Quantity of the Coarse Sun Sensor Cells Sun Sensor is 8.


The CubeSat of the Satellite PhoneSat-2.5 is 1U.


The Associated Event of the Solar Flare Natural Phenomenon is Fast coronal mass ejection (CME).


The Solar Wind Speed and Beta of the ACE Satellite is ~41% lower on average from 2009 through the day 79 of 2013.


The Mass (kg) of the IceEye-1 Satellite is 80.


The Mass of the UKube-1 Satellite is < 1080 g.


The Predicted Pmp at EOL of the KOMPSAT-6 Satellite is 2,258 W.


The Channels of the BlackJack GPS Instrument is 16.


The Conference Date of the PSAT Satellite is Aug. 5-10, 2017.


The Age of the HD 166191 Star is 10 million years.


The Completion Date of the CMIP6 Climate Model is Recent.


The Delta-V of the Water Propulsion System Propulsion System is More than 130 m/s.


The | 185 km of the MSS Instrument Swath is Swath 185 km.


The Mission Objective of the TechEdSat Satellite is Evaluate SPA (Space Plug-and-play Avionics) designed by ÅAC Microtec, and to perform a communications experiment utilizing the Iridium and Orbcomm satellite phone network.


The Formation Flying Demonstration of the PRISMA Satellite is Unknown.


The Required Tracking Interval of the TIRA Radar Tracking Station is 12 hours.


The Attitude Pointing Accuracy of the CHIPSat Satellite is ±2º.


The Testing Method of the ESP Thruster Thruster is Firing in pairs and measuring the changes to the spin rate via on-board rate instrumentation.


The Launch Date of the LunaH-Map Spacecraft is Second half of 2021.


The Quantity of X-ray Optics of the NICER/SEXTANT Instrument is 56.


The Spatial Resolutions of the FGM Fluxgate Magnetometer is About 200 or 100 m.


The Launch Year of the ERS-2 Satellite is 1995.


The Satellite Launch Date of the Kleos S.A. Company is Mid-2021.


The Wavelength of the TIR Thermal Infrared region is 0.5, 1.0, 1.0 µm.


The Purpose of the TOPSAR SAR Mode is Wide swath imaging.


The Imaging Filters of the MRO Mars Reconnaissance Orbiter is Three.


The Swath width of the SBUS Solar Backscattering UV Sounder is .


The Telescience Support Unit Presentation Date of the Foton Spacecraft is Oct. 2-6, 2006.


The Rotation Rate Measurement of the Exoplanet Celestial Body is Two to three times per orbital period for about seven orbital periods.


The Detector of the Spectral Band D Spectrometer is Si-PIN.


The Near-UV Channel Range of the IRIS Observatory is 278.0–284.0 nm.


The Orbit Type of the WorldView-3 Satellite is Sun-synchronous orbit.


The Status Update Date of the Cluster Satellite Constellation is July 2015.


The Baffles Material of the Collimator Instrument Component is Tantalum (Z=73).


The Spectral Sampling of the Telescope Optical Instrument is 2.55 nm.


The Resolution of the FSS Fine Sun Sensor is 0.005º.


The Polarizations of the Communication System Data Transmission is RHCP (Right-Hand Circular Polarization) and LHCP (Left-Hand Circular Polarization).


The Spatial Resolution (IFOV) of the ERIP Earth Remote-Sensing Imaging Package is 170 km x 70 km.


The Origin of the Stardust Grain Particle is Nova explosion more than 4.5 billion years ago.


The Mass of the CICERO satellites Satellite is Approximately 10 kg.


The Solar Panel Type of the Canopus Pipper Satellite is Triple-junction 26% efficient solar cells.


The Processor of the CryoSat Satellite is Sparc ERS 32.


The Collaboration of the MAYA-1 1U CubeSat is DOST-ASTI, KIT.


The Operating Temperature of the SWIR Detector is 257 K.


The Spectral Range of the FTS Interferometer Interferometer is 2.4-13.3 µm (or 750-4100 cm -1).


The Data Usage of the MHS Microwave Humidity Sounder is Provides the operational microwave sounding capability for the NOAA-N, -N' meteorological satellites.


The Mission Tenure of the RHESSI Satellite is 10 Years.


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


The Components of the SWIR Camera System Camera System is Integrated detector cooler assembly, MCT photodiode array, ROIC, pulse tube cooler.


The Publication Date of the Envisat's Medium-Resolution Imaging Spectrometer Spectrometer is November 1993.


The Swath Width of the TIRS-2 Sensor is 185 km.


The Polarizations of the Antenna Communication System is Ch 0, 1, 2: RHCP, Ch 3, 4, 5: LHCP.


The Spectral Bands of the EarthDaily Optical Imager Optical Imager is 6 bands in each of the visible, near-infrared (NIR) and shortwave infrared (SWIR) spectrums, and 4 in the thermal infrared (TIR) spectrum.


The Operation Duration of the SPOT-VEGETATION Satellite is 16 years.


The Modes of Operation of the CXBN-2 Spacecraft is Failure recovery, standby/uplink, downlink, and full science modes.


The Firing Duration of the Micronozzle Propulsion System is 10 s x 3.


The Antenna Footprint of the AIS Automatic Identification System is Has narrower size due to lower satellite orbit altitude.


The Solar Wind Speed and Beta of the ACE Satellite is ~48% lower on average from 2009 through the day 79 of 2013.


The Time to Point to the Sun of the TSUBAME Satellite is 33873 seconds after the separation.


The Environment of the Functional Tests Testing is Ambient (and gravity).


The Images per Capture of the EPIC Instrument is 10.


The Launch Date of the NeuSAR Satellite is June 30, 2022.


The Conference Presentation of the SWAP EUV Telescope is March 30-April 2, 2004.


The Spectral Bands of the Sentinel-2 Satellite is 13.


The Design Basis of the SWiPS Sensor is IES (Ion and Electron Sensor) flown on ESA's comet mission, Rosetta.


The Accuracy of the Lateral Shearing Angular Period Device is 206 mas.


The Integration of Physical Components of the Cooperation by Federation Data Exchange is Not Required.


The Radio Frequency of the Reception Station Ground Station is 7.8 GHz.


The Number of Satellites of the Galileo Satellite System is 14.


The Frequency Range of the MWNIR Imaging System is 6.6 GHz - 37 GHz.


The Polarization of the MTVZA-GY Radiometer is Vertical and Horizontal.


The Ability of the Black Hole Cosmic Object is Pulling things toward it and blasting material away from itself.


The Operating Bands of the MWR Microwave Radiometer is K-band and Ka-band.


The ROM/RAM of the ACU Attitude Control Unit is EEPROM(1MB x 2), SRAM(1MB x 2) for C&DH EEPROM(1MB), SRAM(1MB), MRAM(512KB) for HSS.


The Power of the CCD Camera Imaging System is <50 W.


The Sea Surface Calibration Mode of the EarthCARE satellite Satellite is CPR in Sea Surface Calibration mode.


The Mission Objective of the EROS-B Satellite is Provide high-resolution imagery to the customer base.


The Spectral Range of the Telescope Optical Instrument is 400-1000 nm.


The Software of the TPMU Device is 8051 Pascal mode.


The Partnership of the ESA and EDA Organizations is Solid.


The Inclination of the 46 nanosatellites Satellite is 97.51º.


The Frequency Bands of the DCS Data Collection System is UHF (401.9 MHz), S-band (1694.5 MHz), S-band (2034.9 MHz), UHF (468.8 MHz).


The Diameter of the VPW42 Optical Window is 1.5”.


The Orbit Determination Method of the WEOS Satellite is Uses the Keplerian elements of the satellite which are estimated from its locations measured by the onboard GPS receiver.


The CCD Array Size of the MEGS Spectrograph is 1024 x 2048 pixels.


The Downlink Transmission of the X-band telemetry subassembly Telemetry Device is Stored image data.


The Application Categories of the Sentinel-3 Ocean Surface Topography Mission is Numerical weather prediction, Climate change.


The Spatial Resolution of the Instrument SAR is ≤ 60 m x 50 m.


The Objective of the RARS Regional ATOVS Retransmission Services is Expand the RARS concept to other data types in support of a wider range of applications.


The Spectral range of the SBUS Solar Backscattering UV Sounder is 250-340 nm.


The Image Transmission Time of the New Horizons Spacecraft is More than four hours.


The Propulsion Method of the LightSail-2 Solar Sailing CubeSat is Solar sailing.


The Launch Lock of the OSIRISv3 Laser Communication Terminal is Not required.


The Update #6 Date of the JWST Telescope is April 2009.


The Power of the Instrument Spectrometer is < 17 W.


The Number of Satellites of the Galileo Satellite Constellation is 26.


The Mirror Module Assemblies Presenter of the IXPE Satellite is Brian Ramsey.


The URL of the µCAT Micro-Propulsion Solution Propulsion System is https://digitalcommons.usu.edu/cgi/viewcontent.cgi?referer=&httpsredir=1&article=3374&context=smallsat.


The Design Life of the Jason-1 Satellite is 5 years.


The Date of the The Black Fire Blows Up in New Mexico Image is 24 May 2022.


The Mounting of the HETG Grating is Concurrent.


The Mounting of the Solar Orbiter /PHI Full Disk Telescope Telescope is Unknown.


The New Program Segments Languages of the ESA European Space Agency is Dutch, French, German, Italian and Spanish.


The Displacer Unit of the Stirling Cycle Cooler Cooler is Single, similarly driven, displacer unit orthogonal to the compressor axis.


The Location of the RADARSAT MMO Mission Management Office is CSA in Saint-Hubert, Quebec.


The Technology Readiness Level of the SMDC-ONE Nanosatellite is TRL-7.


The Optical Design of the COR2 Coronagraph2 Imager is Externally occulted Lyot design.


The Spectral Bands of the SLIM6 Satellite is 0.52-0.62 µm, 0.63-0.69 µm, and 0.76-0.9 µm.


The Altitude for Satellite Release of the Falcon-9 Rocket Rocket is 450 km.


The Objective of the SENSE Satellite is Provide data for ionospheric prediction models.


The Processor Type of the SCP Spacecraft Process Controller is Honeywell VHSIC MIL-STD-1750A microprocessor.


The Launch Date of the FormoSat-3/COSMIC-1 Satellite Constellation is April 15, 2006.


The Power of the EPS Electrical Power Subsystem is ~ 2 W.


The Purpose of the LRF-S2 Laser Device is Measure the distance to the tip of the sampler horn.


The Data Transmission of the McMurdo Ground Station Ground Station is NOAA in Suitland.


The Length of the Telescope Optical Instrument is 2465 mm.


The Apogee of the Gravity Probe A Satellite is 10,000 km.


The Size of the POPSat-HIP-1 CubeSat is 3U.


The Build Location of the Near Real Time SAR Processor SAR Processor is Ahmedabad.


The Deployed Antenna Size of the IAE Experiment Satellite Component is Roughly the size of a tennis court.


The Number of Satellites of the Cluster Satellite Constellation is 4.


The Temperature Increase Objective of the Paris Agreement International Agreement is Well below 2°C above pre-industrial levels and pursuing efforts to limit the temperature increase to 1.5°C above pre-industrial levels.


The Usage of the USRP Transceiver is Access the RF signals, demodulate, and decode the signals.


The Launch Year of the RISAT-1 Satellite is 2012.


The Orbit Altitude of the HTV-8 Spacecraft is ~400 km.


The Orbital Flight Test Date of the Starliner Spacecraft is Unknown.


The Support Phase Time Period of the Mango Tango Satellite Formation is 15.06 to 19.06.2010.


The Locking Time of the Comb Oscillator Oscillator is Reached within seconds.


The ETM Output of the Landsat-6 Satellite is Two 85 Mbit/s serial composite streams.


The Presentation Date of the GPS Radio Occultation Instrument Instrument is April 3-6, 2017.


The Manufacturer of the CDHS Command and Data Handling Subsystem is University of Tartu.


The Bulletin Release Year of the OceanSat-2 Satellite is 2010.


The Field of View (Cross-track) of the MSU-50 Camera is 62º.


The First Picture Acquisition Date of the D-Sat Satellite is June 26, 2017.


The System Type of the GeoSTAR Atmospheric Microwave Sounder is Sparse array synthetic aperture radiometry.


The Pressure of the Inflation Pressure Satellite Component is 20,600 bar (3 x 104 psi).


The CRISM Spectrometer of the Mars Reconnaissance Orbiter Satellite is Spectrometer.


The Focal Length of the Telescope Optical Instrument is 167 cm.


The CCSDS ID of the GSAT-0203 Satellite is 263.


The Team Members of the Dellingr Satellite is Larry Kepko, Chuck Clagett, Luis Santos, Behnam Azimi, Daniel Berry, Todd Bonalsky, Dean Chai, Matthew Colvin, Alan Cudmore, Allison Evans, Scott Hesh, Sarah Jones, James Marshall, Nicholas Paschalidis, Zach Peterson, Juan Rodriquez, Marcello Rodriquez, S.


The Horizontal Domain of the Aeolus Satellite is Global coverage.


The Function of the Interface Chip Chip is Provides a convenient breakout interface.


The Imagery Type of the SAR Satellites Satellite is SAR.


The Coil Windings of the VLF Experiment Scientific Experiment is 1000.


The Swathwidth of the PAN Imaging System is 9.6 km.


The Location of the ISS-EMIT Instrument is Onboard the International Space Station’s (ISS) primary forward-facing hub for externally mounted instruments.


The Telemetry Bit Rates of the MPO-MAG instrument Instrument is 64, 32, 16, 8, 4, 2, 1, and 0.5 Hz.


The Orbit Altitude of the Crew Dragon Spacecraft is Approximately 575 kilometers.


The Power Generation Technology of the GaInP2/GaAs/Ge solar arrays Solar Arrays is GaInP2/GaAs/Ge.


The Imaging Concept of the OCM Instrument is Extension of the imaging concept adopted for the IRS LISS instruments.


The Number of Detectors of the Spectrometer Instrument is 4.