The Calibration Date of the SSBUV Solar Backscatter Ultraviolet is 1989 to 1993.


The No of bands/channels of the MWRI Microwave Radiation Imager is 6.


The Launch Site of the SEEDS-2 Satellite is SDSC (Satish Dhawan Space Centre), the SHAR launch range (Sriharikota, India).


The Release Date of the LRO Satellite is Nov. 16, 2011.


The Emission Sources of the CH4 Greenhouse Gas is Intense emission plumes from pipelines to large scale, weakly emitting wetlands and agricultural sources.


The Regulated Output of the EPS Electrical Power System is +5 Vdc.


The Size of the Phoenix Satellite is 2U.


The Launch Date of the DMC-3 Constellation Satellite Constellation is July 10, 2015.


The Frequency of the EMOC Process is Monthly.


The FOV of the Telescope Optical Instrument is 4.4º.


The S/C Subsatellite Point Travel of the AMSR-E Instrument is 10 km in 1.5 seconds.


The Energy Deposition of the RAMIS Radiation Detector is Minimal ionizing protons up to relativistic iron nuclei.


The Interface Type of the Bus Interface Communication System is PCI.


The Perigee (km) of the Meteor-2-1 Satellite is 872.


The Relative Position Determination of the CNAPS Propulsion System is 10 cm.


The Radar Antenna Length of the Copernicus Sentinel-1C Satellite is 12 m.


The Image Credit of the CaSSIS Imaging System is ESA/Roscosmos/CaSSIS.


The FOV of the LEICA Particle Detector is 24 x 20 º.


The Spacecraft of the MHS Instrument is MetOp-A spacecraft of EUMETSAT.


The Mass of the Instrument Sensor is 25 kg.


The Mission Status of the IMAGE Satellite is Cancelled.


The Additional Role of the CryoSat-2 Satellite is Measure the height of the surface of the sea.


The Instruments of the SARAL Satellite is A-DCS3, AltiKa.


The Flight Experiment Date of the TUBSAT Satellite is Sept. 25-29, 2006.


The Sensor Operating Temperature of the FIPEX Instrument is Approximately 660°C.


The URL of the GeoEye-1 Satellite is http://launch.geoeye.com/LaunchSite/assets/documents/geoeye1_factsheet.pdf.


The Sensor Distance of the MAG Magnetometer is 80 cm apart.


The Temperature of the Cas A Supernova Remnant is 50 million degrees.


The Challenges of the LCRD Laser Communications Relay Demonstration is Susceptibility to cloud cover, scintillation, scattering and other atmospheric effects.


The Number of Private Launch Companies Prepared to Make First Attempts to Reach Orbit of the China Country is 4.


The | of the Advanced Modular Incoherent Scatter Radar Radar is The Advanced Modular Incoherent Scatter Radar (AMISR).


The Launch Date of the GEOS-2 Satellite is 11 January 1968.


The Power Consumption of the Imager Imaging System is 85 W.


The Measured Gases of the GeoCarb Satellite is CO2, CH4, CO.


The Status Report Date of the PRARE Satellite Observation System is Sept. '90.


The Spatial Resolution & Stability of the Telescope Optical Instrument is Strehl ratio of ~ 0.86 at 2 µm.


The Attitude Control of the O/OREOS nanosatellite Satellite is Permanent magnets and hysteresis rods.


The Conference Presentation Date of the SJ-9 Technology Demonstration Satellite Satellite is Sept. 23-27, 2013.


The FOV Resolution of the HORUS Sensor is 5.35 arcsec.


The Life Expectancy of the Almaz-1B Satellite is 5 years.


The Mission Status of the Buccaneer CubeSat is Mission complete.


The Incorporation of Laser Intersatellite Links of the Starlink Satellite Constellation is Undergoing Technology Improvements.


The Primary Use of the Band 3 Spectral Band is Heat source, night cloud.


The Power Generation of the ALBus 3U CubeSat Satellite is 5 - 20 W.


The Command Uplink Data Rate of the NEMO-HD Satellite is 4 kbit/s.


The Description of the Inertial Attitude Control Mode (IRC) Control Mode is Provided spacecraft control using a propagated inertial quaternion.


The Mass of the SAOCOM-1B Satellite is 3050 kg.


The Data Analysis of the ICON Satellite is First year of observations coincided with solar minimum.


The Confirmation of the Hot Jupiters Exoplanets is Across the galaxy and even in our stellar neighborhood.


The Materials for Photo-Electron Current Measurement of the HORYU-4 Satellite is Gold, KaptonR (polyimide), and Black KaptonR.


The Components of the Infrared Imager Sensor is Telescope, filter wheel, optical focal plane assembly, cryostat, video proximity electronics unit, payload control unit, X-band payload telemetry chain.


The Workspace Volume of the Research Facility Facility is 15 cubic feet.


The Slit 1 Material of the MEGS-A Spectrograph is Mo/C.


The Mission Support Start Date of the RRA RetroReflector Array is 1 May 2002.


The Number of Satellites of the BDS-3 Satellite System is 30.


The Battery Voltage of the EPS Electrical Power Subsystem is 4.2 V.


The Discovery Date of the ExoMars Trace Gas Orbiter Spacecraft is February 10, 2021.


The Resonance Ratio of the Satellite Orbit Orbit is 3:1.


The Release Date of the Haa Alif Atoll, Maldives Location is June 5, 2014.


The Processor of the ICM Instrument Control Module is Leon ll processor.


The Power Supply System Mass of the Microsatellite Satellite is 1.9 kg.


The Presentation Date of the MICROSCOPE Spacecraft is Oct. 2-6, 2006.


The Image Processing Time of the SMOS Satellite is Less than a second.


The Filter Type of the NUV channel Spectrometer is Block with Aluminum.


The Launch Date of the RHESSI Satellite is Jun 13, 2012.


The Study Purpose of the SJ-10 satellite Satellite is Enhance the comprehension of fire mechanism under microgravity.


The Total Satellites of the Planet Satellite Operator is 149.


The Spatial Resolution of the LISS-4 Camera is 5.8 m.


The Wavelengths of the Spectrometer Instrument is 1020, 940, 600, 525, 453, 448, and 385 nm.


The Spacecraft Operations Location of the Spitzer Space Telescope Telescope is Lockheed Martin Space in Littleton, Colorado.


The Measurement of the Gaia Satellite is The trajectory of the Solar System.


The Signal-to-Noise Ratio of the Atmospheric-sounding instrument Spectrometer is High.


The Platform Orientation of the Sich-2 Satellite is Sun-oriented in standby mode.


The Field of View of the Trigger Camera Camera is Wide.


The Direction of the Wire Boom Deployment System is Counterclockwise.


The Agency of the FedSat Satellite is CSIRO, CRCSS.


The Swath Width of the Stripmap Imaging Mode is 20 - 40 km.


The Uplink Frequency of the TT&C Data Communication is 2089 MHz.


The Transient Classification of the FORTE Satellite is Rf transients in space using digital signal processing and neural network techniques.


The Ground Systems of the CU-E3 Satellite is Two separate ground systems.


The CubeSat Size of the FITSat-1 Satellite is 1U.


The Mission of the MicroCarb Satellite is MicroCarb mission: a CNES initiative for monitoring the CO2 exchanges.


The Mode of the EPIC CCDs Imaging Device is Photon counting mode.


The Structure of the Schiaparelli Module is Aluminum sandwich with CFRP skins.


The Tracking System Position of the MMS Satellite is Far side of Earth.


The Monitoring Capability of the Satellite Constellation Satellite Constellation is Daily facility-scale methane monitoring.


The URL of the Iridium NEXT Satellite Constellation is http://multivu.prnewswire.com.


The Available Consumables Lifetime of the Spacecraft Satellite is 7 years.


The Mass of the Instrument Interface Module Interface Module is 75 g.


The Daily Soundings of the GeoCarb Instrument is ~10,000,000 soundings per day.


The Architecture of the DU Detector Unit is Figure 37.


The Quantity of the SmallSats Satellite is 38.


The Maximum Elevation Slewing Rate of the OCTL Telescope is 10º/s.


The Alpha (α) of the FCA Flow Control Assembly is 0.2.


The Service of the Maxar Space Solutions Company is Providing a high-power solar electric propulsion spacecraft chassis.


The Altitude of the GCOM-W1 Satellite is 699.6 km.


The Contract Award of the York Space Company is $382 million.


The European Principal Investigator of the MIRI Instrument is Gillian Wright.


The Speculated Size of the Planet Candidate Exoplanet is The size of Saturn.


The Image Type of the Image Data is 360° colored image of the Milky Way.


The Temperature of the Farside Hemisphere Moon's Hemisphere is Cooler.


The Purpose of the Telescope-coronagraph 132 Å Telescope is Imaging hot plasma (T ~ 10 MK) of the solar corona.


The Operation Completion Date of the DAICHI (ALOS) Satellite is May 12, 2011.


The Neutron Moderation of the Lunar Regolith Regolith is More enriched in hydrogen.


The Platform Series of the GovSat-1 Communication Satellite is Advanced GEOStar-3.


The Processor of the SCP Spacecraft Process Controller is Honeywell 1750A processor.


The Natural Targets for Calibration of the EarthCARE satellite Satellite is Sea surface, Desert.


The Thruster Quantity of the GPIM Propulsion System is 5.


The Operation Life of the FG Filtergraph is Unknown.


The URL of the PSLV Satellite is https://spaceflightnow.com/2018/01/12/pslv-c-40-coverage/.


The Mission Count of the Solar Terrestrial Probes (STP) Program Program is 5.


The Launch Mass of the GHGSat-D Microsatellite is 15 kg.


The Quantity of the Lithium-cobalt cells Energy Storage is 8.


The Mass of the Kepler-442b Exoplanet is About twice the mass of the Earth.


The Solar Elevation Angle in TC Operation of the Instrument Satellite Instrument is < 40º.


The Cosmic Ray Susceptibility Occurrences of the Kepler Spacecraft is Four.


The Date of the Rain Drenches Kauai Event is 2 May 2018.


The Destination Count of the Lucy Space Mission is Unknown.


The Minimum SNR of the NEMO-HD Satellite is 75.


The Launch Date of the CanX-6/NTS Satellite is Apr. 28, 2008.


The Functions of the FMC FOS Monitoring and Control is Segment monitoring and G/S interfacing.


The Contact Number of the Randomizer for High Data Rates Device is 20959/07/D/MRP.


The Spectral Resolution of the Optical Scanning Design Imaging Spectrometer is 1.25 nm.


The Spacecraft Type of the ARMADILLO Satellite is Nanosatellite (3U CubeSat).


The Tracking of the TRSR GPS Receiver is Dual-frequency code and cross-correlation, data output of up to eight GPS satellites simultaneously.


The Overview Meeting Date of the CLARREO Mission is October 20-22, 2009.


The Size of the AeroCube-8B Satellite is 1.5U.


The Manufacturer of the Nauka Laboratory Module is RSC Energia.


The Commanded Rate of the MicroSCOPE Satellite is 5 x 10-3 rad/s around the X-axis.


The Mass of the E1P-2 CubeSat Satellite is ≤ 1 kg.


The Modes of the Instrument Coronagraph is Four.


The Observation Data of the TANSO-3 Ground Segment is AMSR3.


The Perigee (km) of the Cosmos-1066 (Astrofizika) Satellite is 848.


The Design of the APD Optical Radiation Detector is Compact, lightweight, mechanically hard, low power consumption, high quantum efficiency.


The Control of the Satellite Spacecraft is Full 3-axes and continuous drag-free satellite control.


The Cameras of the Hypatia Satellite is Sub-meter multispectral and 30 m hyperspectral.


The Analog channel of the STRV-1d DHS Data Handling System is Sixteen.


The Frequency L2 of the GPS receiver Receiver is 1227.6 MHz.


The Mission Update of the Gravity Probe B Satellite is Nov. 12, 2009.


The Launch Date of the KOMPSAT-3A Satellite is April 14, 2015.


The Mass of the Service Module Spacecraft Component is 35 ton.


The Function of the Signal Processor Signal Processing System is Works only when the MAPMTs and the APDs detect a signal simultaneously.


The Battery Energy of the Satellite Spacecraft is 60 Ah.


The Maximum Satellites Launched of the Falcon 9 Rocket is 15-16 to an inclined orbit, "something like 13” to a polar orbit.


The Location of the SDC Redundant operations capability is LASP.


The Wavelength FWHM of an unresolved line of the Spectrometer Instrument is 0.124 µm.


The Year of Launch of the Aqua Satellite is 2002.


The Long-term Stability of the Ozone Measurement Instrument Atmospheric Measurement Device is 1% over 7 years or better.


The First Selfie Date of the InSight Mars Lander is 11 December 2018.


The Coverage Area of the Ikonos Imaging Satellite is More than 400 millionkm2.


The Valve Upgrade of the Propulsion System Satellite Component is Number and Flow Capacity.


The Data Transfer Capability of the CASCADE Satellite Communication System is Large digital data files (10s to 100s of GBytes) within hours.


The Main Control Capabilities of the Antenna Satellite Component is Providing the TM (Telemetry), Processing the TC (Telecommands), Controlling the switching on/off of the active subassemblies.


The Ground Stations of the Herschel Spacecraft is New Norcia (Australia) and Cebreros (Spain).


The Radiometric SNR of the Instrument Spectrometer is 400 at the bottom of the limb to 40 at the top.


The Type of the PWI Instrument is Plasma Waves Investigation.


The ISL Data Rate of the CanX-4&5 Satellite is 10 kbit/s.


The CPU Model of the OBC On-Board Computer is LEON2-FT.


The Method of the Cluster spacecraft Satellite is 3D electric field measurements.


The Instrument Speed of the MMS Satellite is Incredibly fast.


The Data Rate of the HID Instrument is 0.64 kbit/s.


The Maximum Velocity of the Dust Accelerator Testing Facility is Up to 60 km/s.


The Formation Flying of the DelFFi Satellite is QB50 Constellation.


The Tracking Direction for Geostationary satellites of the NEOSSat and Sapphire Satellites is Antisolar direction.


The Service Start Year of the Satelles PNT Service Provider is 2016.


The Purpose of the COWVR Radiometer is Forecast ocean surface winds.


The Primary Use of the Band 8 Spectral Band is Ocean color.


The Mass of the Payload Satellite Subsystem is 3.00 kg.


The Uplink of the Miniaturized X-band transponders Communications System is 1 kbit/s.


The Installation Date of the STP-H7 and H8 Scientific Payloads is Unknown.


The Observation Capability of the MIGHTI Instrument is Day and night.


The Dimensions of the GCOM-W1 Satellite is 5.1 m (X) x 17.5 m (Y) x 3.4 m (Z).


The Image Span of the Herschel Satellite is Over 1º on the long side.


The Resolution of the Altimeter Sensor is About 0.9 m.


The Conference Date of the SOTA Optical Transponder is May 11-13, 2011.


The Function of the SSTs Stellar Star Trackers is Derive the satellite attitude.


The Operating System of the PhoneSats Satellite is Android.


The Conference Presentation Location of the Earth Observation System of the Republic of Kazakhstan Satellite System is Beijing, China.


The Bus Height of the OSAM-1 Satellite is 14-foot-tall.


The Frequency Compatibility of the TUC Transponder Microwave Transponder is European and international altimetry missions in the microwave range.


The Light Energy Separation Method of the OCO-3 Instrument is Diffraction grating.


The Internal Surface Treatment of the Instrument Spectrometer is Flat-black surface treatments, e.g. Z306 paint with diffuse reflectance Rdiff ~ 5%.


The Data Rate of the Solar Orbiter Satellite is 100 kbit/s.


The Orbit Altitude of the SPOT 6-7 Satellite is 694 km.


The Responsivity Measurement of the Responsivity Measurement Instrument is 0.51 A/W.


The Linearity of the Position Sensing and Actuation System is Along the instrument sensitive axis.


The Family of the TEMBOTM EMC Material is Booms.


The Groove Density of the Convex Holographic Grating Grating is 1450 grooves/mm.


The Position of the Reference Absorbers Calibration Components is Mounted on the non-rotating part of the instrument.


The Slit Image Coalignment Requirement of the Spectrometer Channel Optical System is Within a small fraction of their size on the focal plane (~250 µm).


The Capacity of the SSDRs Solid-State Data Recorders is 2 GByte.


The Sample Dispersal Deadline of the JAXA Organization is By the close of 2021.


The ACS Parameters of the MarCO Satellite is Working for both TCMs and flight.


The Spectral Range of the SWIR Short Wave Infrared region is 843-1043 nm.


The Position in Constellation of the GCOM-W1 Satellite is Prior to the Aqua spacecraft.


The Main Processor of the Command and Data Handling Subsystem Subsystem is Nexus S smartphone.


The Payload Fairing Diameter of the GSLV-F05 Rocket is 3.4 m.


The Sea Surface Salinity Accuracy of the SMOS Satellite is 0.3-0.5 psu.


The Time of the Calibration Cycle Camera Calibration is Approximately 1.8 s.


The Panels of the SAR Antenna Antenna is One fixed and four deployable panels.


The Downlink Transmission Data Rates of the CBERS-1 Satellite is 2 x 53 Mbit/s.


The Predicted Mass of the White Dwarf Celestial Body is Two tenths the mass of the Sun.


The Developer of the Kappa Scheme Flare Prediction Method is Professor Kanya Kusano.


The Cell Configuration of the Battery Energy Storage is 2P24S.


The Development Time of the SAOCOM-1A Satellite is since 2011.


The Current of the Solar Array Power System is Unknown.


The High-Gain Dish Link Speed of the TGO Trace Gas Orbiter is 2 Mbit/s.


The Wavelength Calibration Frequency of the TRUTHS Satellite is At least one wavelength per orbit.


The Spatial Resolution of the HySI Hyperspectral Imager is 80 m.


The Viewing Angle Range of the Moon Calibration Site is -115º to +115º.


The Spectral Range of the LWIR Camera Camera is 8-9.5 µm.


The Value of the Geometric factor Parameter is 0.1 cm^2 sr.


The Number of Maneuvers of the SkySat-4 Satellite is 3.


The Attachment Duration of the SpaceX Dragon Spacecraft is 18 days.


The Detection Date of the InSight lander Seismic Instrument is Late 2018.


The Installation Date of the Dragon Spacecraft is 8 December 2019.


The Operation of the Interferometer Arrays Imaging Technology is Take a snapshot, process it and there's your image.


The Control of the CMOS Camera Camera is I2C I/F.


The Mass of the NorSat-1 Satellite is < 30 kg.


The Redundancy of the Buck-Boost Converter Solar Array Regulator is 2 of 3 Red..


The Imaging Mode of the FAI Camera is Slew.


The Opening Date of the ESA's first UK Center Center is July 9, 2015.


The Mission Goals of the ARMADILLO Satellite is Characterize in-situ sub-millimeter level dust and debris particles in LEO (Low Earth Orbit) by sensing impacts at varying times, directions and locations.


The Mass of the Baumanets-2 Microsatellite is 86 kg.


The Solar Cells Power Conversion Efficiency of the EPS Electric Power Subsystem is 27%.


The Memory of the C&DH Command and Data Handling is 16 MByte Flash.


The Stabilization of the COMS Satellite is 3-axis.


The Operational Status of the TSX Satellite is Operational.


The Altitude of the COMPASS-1 Satellite is 830 km.


The Operation Mode of the Camera Sensor Imaging System is Snapshot or staring mode.


The Orbit of the MinXSS-2 Satellite is Sun-synchronous, polar orbit.


The Altitude of the Hodoyoshi-4 Satellite is 600 km.


The Diameter of the Telescope Optical Instrument is 620 mm.


The Inclination of the SZ-7 Spaceship is 42.4º.


The Number of Satellites of the Iridium NEXT Satellite is 70.


The Slew Time, 15º roll of the ADCS Attitude Determination & Control Subsystem is ≤ 4.5 minutes.


The Data Rates (Uplink) of the RF Communications Communication System is 1.2 kbit/s.


The Prime Minister of India of the OneWeb Satellite Communications Company is Narendra Modi.


The Power Output of the EPS Electric Power Subsystem is 550 W.


The Image Transmission of the Spacecraft Satellite is X-band with 160 Mbit/s downlink rate.


The Navigation of the Lander Spacecraft is Configured for inertial navigation from separation to the end of rough braking.


The Communication Protocol of the Nanosatellite Satellite is FM.


The Initial Separation of the TanDEM-X and TerraSAR-X Satellites is 15700 km.


The Design Storage Time of the Valves Spacecraft Component is Up to 60 days.


The Distress Signal Detection Range of the MEOLUT Next Local User Terminal is More than 5,000 km.


The Communication Test of the ArgoMoon CubeSat is Optical communication capabilities between the CubeSat and Earth.


The Operation Time on Primary Batteries of the Philae Lander is Approximately 5 days.


The Focal Plane of the R3 Sensor Imaging System is ON Semiconductor LUPA 1300-2 Si:CMOS focal plane.


The Launch Date of the Planet Orbit Partner Program is October 14, 2019.


The Cross-Track Swath of the OMPS Limb Profiler Spectrometer is 500 km.


The Manufacturer of the ICEYE-X2 Satellite is ICEYE Ltd..


The Planned Number of the Future Satellites Satellite is 2200.


The Manufacturer of the GomX-4A and GomX-4B CubeSats is GomSpace.


The Spectral Sampling Distance of the UV-1 Spectrometer is 0.32 nm.


The Data Quantization of the Spacecraft Satellite is 10 bit.


The Mission Duration of the SORTIE CubeSat is 6 months.


The Serial Production Initiation Date of the OneWeb Satellite Constellation is June 27, 2017.


The Presentation Date of the Tuomas Tikka Person is October 14-16, 2014.


The Polarizations of the SAR antenna Antenna is HH,VV,HV,VH.


The Utilization of the ICI-1 Radiometer is Water vapor profile and snowfall.


The Voltage of the Solar Arrays Power Generation is 23 to 37 Volts.


The Unknown of the Multispectral Camera Camera is Unknown.


The Deployment Readiness of the DoD Human Space Flight Support Office Rescue Division Organization is Prepared to deploy at a moment’s notice.


The Grating Type of the MEGS Spectrograph is Single, holographic, spherical grating.


The Power Topology of the Bus Satellite Component is Direct Energy Transfer (DET).


The Distance from Earth of the Kepler-186 Star System is About 500 light-years.


The Battery Capacity of the Spacecraft Satellite is 5.3 Ah.


The Attitude Control of the STPSat-1 Satellite is Momentum-biased about the pitch axis.


The Period of the Satellite Orbit is 98.5 minutes.


The Next Proposal Due Date of the New Horizons Spacecraft is Early 2022.


The Date of the Ground Segment Coordination Body Workshop Workshop is June 19-20, 2007.


The Mass of the Spacecraft Satellite is 670 kg.


The Image Resolution of the WMC Camera is 16 m.


The Communication Network of the SBSS Satellite System is Air Force Satellite Control Network and commercial USN (Unified Space Network) ground stations.


The Power Consumption of the FPU Focal Plane Unit is 85 W.


The Data Rate (max) of the HiSPiCO S-band Transmitter/Transceiver is 2000 kbit/s.


The Testing Start Date of the OCK (Orbit Control Kit) Orbit Control System is Summer of 2007.


The Conference Presentation Date of the SJ-9 Technology Demonstration Satellite Satellite is Oct. 1-5, 2012.


The Close Passes of the Mariner 10 Spacecraft is 3.


The Mission Status of the PIXL-1 mission Satellite is In commissioning.


The Arrival Method of the Dragon CRS-14 Spacecraft is Snagged by the orbiting lab's huge Canadarm2 robotic arm.


The Operating Voltage Range of the LVPS Board Power Supply is 26 - 29 V.


The Field of View of the Optical Head Optical Device is 52º x 28º / 90º x 74º (multi-hole mask: 10 x 10 spots / 3 x 3 spots).


The Bands of the Multispectral Instrument (MSI) Instrument is 13.


The Focus of the RECCAP-2 Satellite Mission is Regional GHG budgets.


The Assembly Options of the HISat Satellite is Flexible assembly options resulting in multiple possible configurations.


The Communication System of the Ground Station Ground Segment is MHX modem (Microhard Systems).


The Image Resolution of the Infrared Sensors Sensor is 6688 x 2500 pixels.


The Band of the Trasser AOS Instrument is Visible.


The Ability to Support HDLC Framing of the UoSAT-12 Satellite is True.


The Technology Options of the ORS Communication Bus Communication Bus is Firewire, SpaceWire, and Ethernet.


The Purpose of the EnviSat Satellite is Earth observation.


The Type of the Payload Accommodation Satellite is Large.


The Importance of the SMAP Satellite is Timely and accurate knowledge of the root-zone soil moisture is very important for farmers, stakeholders, and agricultural agencies.


The URL of the RHESSI Satellite is http://hesperia.gsfc.nasa.gov/hessi/news/aug_11_03.htm.


The Launch Time (UTC) of the ESAIL Microsatellite is 01:51.


The Resolution of the Satellite LEO (Low Earth Orbit) is Δx = 1.2 km for Δθ = 0.1º.


The G&C System of the STEREO spacecraft Satellite is Three-axis-stabilized with fixed solar arrays for power generation as well as a steerable HGA (High Gain Antenna) for heliocentric orbit communications.


The Mission Objective of the Chang'e-3 Moon Lander is One year operation on the lunar surface.


The Purpose of the GRNS Instrument is Detect, measure, and map Psyche’s elemental composition.


The Data Correction of the Aeolus Satellite is Corrected certain biases.


The Arrival Date of the Juice Spacecraft is 2029.


The Spectral Range of the UV to NIR Satellite is Ultraviolet (340 nm) to near-infrared (890 nm).


The Data Loss Tolerance of the EDSN Data Network is Accepts data packet loss.


The Distance Traveled of the D-Sat Satellite is More than 12 million km.


The URL of the Alphabus Satellite Platform is http://telecom.esa.int/telecom/www/object/index.cfm?fobjectid=30203.


The Value of the Peak Power Consumption Instrument is < 35 W.


The Precision of the Method Calibration Method is Better than 0.5%.


The Release Date of the Halloween Space Weather Storms of 2003 Space Weather Event is June 2004.


The Image Acquisition Date of the MODIS Instrument is March 2002 and February 2022.


The Calibration Method of the ARTEMIS Satellite is Solar radiation-based.


The Orientation Adjustment of the PSSCT-2 Satellite is Continuous.


The Spatial Resolution of the AATSR Instrument is 1 km x 1 km.


The First Entry Date of the BEAM Expandable Habitat is June 6, 2016.


The Wavelength of the S-band Band is 12 cm.


The Spatial Resolution - Pan of the Spacecraft Satellite is 1 m GSD.


The Components of the Reaction Dynamics Study Experiment is 1) Manipulator operation that yields minimum reaction on the base satellite 2) Manipulator endpoint control for inertial target under the free-floating environment 3) Terminal state control for free-floating space robot 4) Base attitude control for quick .


The Spectral Range of the S-192 optomechanical scanner Scanner is 0.4-12.5 µm.


The Quantity of the Patch Antennas Antennas is 2.


The Data Products of the CRaTER Cosmic Ray Telescope is LET spectra of galactic and solar cosmic rays (particularly above 10 MeV).


The Mass of the GHGSat-C2 (Hugo) Nanosatellite is 16 kg.


The Conference Date of the SPARCS Satellite is Aug. 4-9, 2018.


The Payload Fairing Technology of the Minotaur Launch Vehicle is Advanced Grid-Stiffened Composite.


The Mission End Date of the ICESat Satellite is Aug. 31, 2010.


The Presentation Date of the Hokkaido Satellite Project Satellite is June 4-11, 2006.


The User Workshop Date of the GOCE Satellite is Nov. 6-8, 2006.


The Data Compression Algorithm of the HRC Instrument Camera is JPEG2000.


The Launch Date of the BRO-4 Satellite is 17 August 2021.


The Payload of the SV-1 Satellite is CTIP (Compact Tiny Ionospheric Photometer).


The Number of Decommissioned Satellites of the HY-2 Satellite is 1.


The Bearing Assemblies Configurations of the Central Bulkhead Assembly Satellite Component is 2 and 3 degree-of constraint.


The Swath Width of the DubaiSat-2 Satellite is 12 km.


The Rainfall Accumulation of the IMERG Product is April 12 to April 19.


The Resumed Work Days of the Chang'e-4 Lunar Probe is 23 days.


The Conference Presentation Date of the GRAIL Mission is March 10-14, 2008.


The Power Consumption of the Photometer Instrument Instrument is ≤ 3.5 W.


The width of the Detector Instrument is 32 pixels.


The Pixel Size of the CCD Detector Array Imaging Device is < 12 µm.


The Camera of the Pico Dragon CubeSat is OmniVision CMOS VGA color sensor with low power consumption.


The Launch Date of the Chandrayaan-1 Satellite is Oct. 22, 2008.


The Imaging Frequency Band of the RISAT-1 Satellite is X.


The Measurement of the IMPACT Instrument is Solar wind ion measurements.


The Operation End Date of the Metcomp experiment Materials Science Experiment is 17 December.


The Spatial Resolution of the AWiFS sensor Sensor is 56 m.


The Components of the Spacecraft Satellite is Solar panels, spacecraft bus.


The Controllers of the ACS Attitude Control System is Proportional–Integral–Derivative.


The Power Range of the ROSA Roll-Out Solar Array is Hundreds of watts to the megawatt range.


The Workshop Frequency of the SSETI Express Satellite is Twice a year.


The Torque Rods Status of the NEOSSat Satellite is Failed.


The Manufacturer of the Resurs-P1 Satellite is TsSKB Progress (Progress State Research and Production Space Center).


The Design of the SCM Device is Very compact.


The Altitude of the Secondary Payloads Unknown is 354 km x 1450 km.


The Dimensions of the SAR antenna Antenna is 3 m x 1 m.


The Mass of the Payload Satellite is 149 kg.


The Perigee Altitude of the IDEA-OSG 1 Microsatellite is 600 km.


The Bands of the MSU-MR Instrument is Six bands in the VIS and IR spectral regions.


The Integration Partner of the LightSail-2 Solar Sailing CubeSat is Prox-1.


The Seismic Exploration of the InSight Spacecraft is Can feel whirlwinds pulling on the surface.


The Data Sources of the Green City Watch Application is Copernicus Sentinel-2 mission, Sentinel-1 SAR imagery, SkySat and RapidEye.


The Revisit Time of the OSCAT Scatterometer is 2 days.


The Spatial Resolution of the Multispectral Instrument (MSI) Instrument is 10 m.


The Modulation Schemes of the MTP Transponder is 4.


The Construction Time of the Carbonite-1 Satellite is 6 months.


The Body Shape of the Bus Satellite Component is Square-shaped.


The Mass of the Kestrel Eye-2M Microsatellite is ~50 kg.


The Date of the 32nd Space Symposium Conference is April 11-14, 2016.


The Peak Quantum Efficiency of the Imager Camera is 50%.


The Operation Start Date of the BIRD Satellite is October 2001.


The Development Consortium of the HyperScout Hyperspectral Imager is cosine, VITO, S&T, Technical University of Delft.


The Orbit Maneuvers Frequency of the GRACE Satellite Satellite is About every 50 days.


The Data of the Roman Satellite is More than 10 million galaxies.


The Image Capture Time of the TESS Satellite is Over the course of 17 hours on July 25.


The Satellite Size of the ANGELS Nanosatellite is 12U.


The SSS Spatial Resolution of the CIMR Radiometer Imager is 5 km.


The Quantity of the Laser Transmitters Device is 2.


The Mission of the Kepler Satellite is K2.


The Photo and Measurement Activities of the Beresheet Spacecraft is Landing Site.


The Nominal Focal Parameters of the PamCam Camera is Unknown.


The Location of the Ground Stations Communication is New Norcia, Australia (DSA 1), Cebreros, Spain (DSA 2), Malargüe, Argentina (DSA 3), Kourou, Maspalomas and Perth.


The Development Status of the Arachne Satellite is Unknown.


The Return Date of the Crew-1 Mission is April 2021.


The Earth Station Location of the WINDS Satellite is Higashimatsushima.


The Structure Components of the HIT-Sat Satellite is Four angle bars, six surface panels and two inner panels.


The Launch Date of the Vega Launch Vehicle is Aug. 2, 2017.


The Thermal Spectrometer of the OSIRIS-REx Spacecraft is OTES.


The Number of Cameras of the spaceCam c4000 Video Camera is 2.


The Fault Isolation of the SSR Solid State Recorder is The division of the storage space into independent banks.


The Image Type of the LROC Camera is Black-and-white and color.


The Intended Use of the Laser Oscillators Component is DWL, GIFTS and ALADIN.


The Measurement Domain of the IRS-P6 Satellite is Land, Snow & Ice.


The Technology of the EUMETCast Dissemination System is Standard DVB-S2.


The Observation of the New Horizons Spacecraft is Tons of material from Io's volcanoes move down the tail in large, dense, slow-moving blobs.


The Nominal Magnetic Moment of the MTs Magnetic Torquers is 1 Am2.


The Partnership with Spire Global of the Myriota IoT Service Provider is Myriota will use Spire's constellation of smallsats to expand its network.


The Agency of the Myriade/AstroSat-100 Satellite is CNES, ASTRIUM.


The Mission Type of the Hera Satellite is Surveying Didymos.


The Beamforming Technology of the TriG receiver GNSS Receiver is Digital.


The Purpose of the Tereza's Computer Model Simulation Model is Simulate the various perturbations that escaping stars in the cluster might feel during their hundreds of millions of years in space.


The Sponsor of the STPSat-3 Satellite is ORS (Operationally Responsive Space) Office.


The Precision of the Laser System Measurement Device is Subatomic scale.


The Survey Date of the Gaia Satellite is 13 June 2022.


The Image Type of the UV/VIS Camera Camera is UV/VIS.


The Image Content of the OPS-SAT Satellite is Arctic Laptev Sea with large amounts of drift ice.


The Mirror Position Measurement of the SMA Scan Mechanism Assembly is Differential Impedance Transducers.


The Frequency Range of the Plasma Wave Instrument Instrument is 5 Hz - 800 kHz.


The Observation Frequency of the ALOS-4 Satellite is More frequent than ALOS-2.


The Start Year of the SOHLA Initiative is 2002.


The Manufacturer of the GHGSat-C2 Satellite is ABB.


The Power Consumption of the RCU Radiometer Calibration Unit is < 3 W.


The Management Interface of the DCU Data Control Unit is PUS (Packet Utilization Standard) TCs.


The Orbit Type of the SPOT 6-7 Satellite is Sun-synchronous.


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


The Actual Lifetime of the QuakeSat Satellite is 1 ½ years.


The Number of Experiment Cultures of the Biofilms Experiment is 24.


The Expertise of the ICEYE Satellite Constellation is Risk finance, climate risk management.


The Meeting Date of the ICON Satellite is Dec. 3-7, 2012.


The Expected Number of Final DEM Geocells of the TanDEM-X Satellite is Nearly 20,000.


The Free Space Loss of the Unit Communication System is 182.7 dB.


The End of Operations Date of the Rosetta Spacecraft is 30 September.


The Experiment of the VisionSpace Company is Testing the use of artificial intelligence to allow a spacecraft to analyze images on board and schedule and plan activities autonomously.


The Quantity of the LPT Light Particle Telescope is 1.


The Number of Collected Fragments of the DebriSat project Satellite is Over 20,000.


The Image Distances of the Rosetta Satellite is 80-100 km.


The Bandwidth of the Band 4 Spectral Band is 545-565 nm.


The Structure of the Tether Spacecraft Component is Mesh.


The 2022 Acres Burned of the U.S. Drought Monitor Report is 230,000 acres.


The Solar Array Power of the DSP satellites Satellite is 260 W (BOL) and 210 W (EOL).


The SNR (Signal to Noise Ratio) of the Instrument Sensor is 6.


The Dimensions - Electronics box of the Instrument Sensor is 31 x 22 x 27 cm.


The Data Distributor of the Resurs-P1 Satellite is Sovzond JSC of Moscow.


The Presentation Date of the VIIRS Satellite Instrument is April 28, 2015.


The Pointing Performance of the CALIPSO Satellite is < 0.02º about each axis.


The Design of the SpinSat Satellite is Spherical.


The Article Date of the XMM-Newton Satellite is 18 May 2018.


The Development Location of the ATLID Lidar Instrument is Selex-Galileo, Florence, Italy.


The URL of the FalconSAT-3 Satellite is http://www.satnews.com/cgi-bin/story.cgi?number=207495260.


The Behavior of the Alpha Circini Star is Shows complex behavior due to both rotation and pulsation.


The Type of the GRIFEX Payload is 3U CubeSat flight test experiment.


The Operating Modes of the DCS Data Collection System is Random access to collect messages transmitted at fixed times (self-timed DCP) or in emergency (alert DCP), Message acquisition only after interrogation of the DCP.


The Channels of the AMSU Microwave Radiometer is 20.


The Program of the MYriade Satellite is Performances, Missions, Tool for education and cooperation.


The Inclination of the Solar Orbiter Satellite is Increasing to a minimum of 30º.


The Spectral Range of the Spectral Band B Spectrometer is 0.52 - 0.60 µm.


The Range Resolution of the SIRAL Radar is Approximately 0.45 m.


The Launch Time of the OCO-2 Spacecraft is 09:56:23 UTC.


The Entities of the GMES program Initiative is ESA, CNES, DLR, EUMETSAT, ASI, INTA, CSA, DMCii.


The Noise of the EZ probe Electric Field Probe is 0.4 µV/Hz^(1/2).


The Components of the ATMS Instrument is Antenna, motor, radio frequency system, electronic system.


The Yaw Pointing Accuracy of the Attitude Control Satellite Subsystem is ±0.3º.


The Design of the Terminator Tape Deorbit Module Deorbit Device is Cubesat tether design.


The Spatial Distribution of the EPISEM Instrument is 54% in the SAA, 26% in the Polar Regions, 20% Galactic Cosmic Rays.


The Inclination of the IBEX Spacecraft is 11º.


The Purpose of the OPS&GRND Subsystem is Planned operation of the satellite and the infrastructure required to operate the ground segment.


The Position Accuracy of the Detector E2V CCD-22 (Frame Store) is 30 arcsec.


The Drifted Orbit of the ERS-2 Satellite is Reference Orbit.


The Orbit Altitude of the STP-S26 mission Satellite Mission is 650 km.


The Wavelength Range of Sensitivity of the MAHRSI Instrument is 195-320 nm.


The Mission Definition Date of the NICER Satellite is June 22, 2014.


The Spatial Resolution of the EOS-T Instrument is 0.3 m in its panchromatic band and 1.2 m in its multispectral bands.


The Number of Essential Ground-Support Equipment Containers of the BepiColombo Spacecraft is Approximately 40.


The Coordination Office of the ARTEMIS Satellite is Air Force International Affairs Office.


The CubeSat of the Satellite TSAT is 2U.


The Data Receiver of the TRMM Satellite is NASA/GSFC and JAXA/EORC (Earth Observation Research Center).


The Apogee of the Transfer Orbit Orbital Maneuver is 1.5 x 10^6 km.


The Number of Launches for Booster of the Falcon 9 Rocket is Fifth flight.


The Image Capture Date of the TopSat Satellite is March 2, 2007.


The Mean Dark of the NISP IR Detector Detector is Around 0,005 e–/pix/s at 100 K.


The Resolution of the OSIRIS Camera is About 3 m per pixel.


The Launch Vehicle of the CHAMP Satellite is Kosmos-3M.


The Formation Ranges of the CanX-5 Satellite is 1000 m, 500 m, 100 m.


The Ground Swath of the Miniature High-Resolution Imaging Spectrometer Imaging Spectrometer is 15 km.


The Avionics of the ESPA Ring Interface is Independent set.


The Resolution of the AEISS-A Instrument is 2.0 m for multispectral MWIR images.


The Entrance Pupil Diameter of the Lens Optical Instrument is 10.5 cm.


The Mass of the MSU-50 Camera is 2.3 kg.


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


The Purpose of the Göktürk-1 Satellite is reconnaissance, homeland surveillance, intelligence, environmental monitoring, forest control, cadastral surveys, identifying illegal construction sites, crop management, damage assessment after natural disasters, and management of natural resources.


The URL of the Emirates Mars Mission Satellite is https://aetoswire.com/en/news/emirates-mars-mission-hope-probe-ready-for-launch-from-japans-tanegashima-space-centre.


The Nominal Mission Start of the Observatories Satellite is About 90 days after launch.


The Instrument Subsystems of the CSG-SAR Satellite is SES (SAR Electronic Subsystem) and SAS (SAR Antenna Subsystem).


The Satellite Connection Distance of the SpaceDataHighway Communication System is Up to 45,000 km.


The Splashdown Location of the Crew Dragon Spacecraft is Atlantic Ocean or Gulf of Mexico.


The Angular Resolution of the Channels Spectrometer is 3''.


The Launch Window of the Launch Mission Event is 12 days.


The Power of the GCOM-W1 Satellite is 4.05 kW at EOL (End of Life).


The Frequency Band of the ISA Accelerometer is 3 x 10-5 — 1 x 10-1 Hz.


The Affiliations of the Keith Masback Individual is Mapping Sciences Committee of The National Academies of Sciences, Engineering, and Medicine.


The Mass of the HID Instrument is 2.2 kg.


The Ocean Measurements of the Copernicus Sentinel-3 Satellite is Temperature, colour and height of the sea surface.


The Research Targets of the SJ-10 Satellite Satellite is Gene expression pattern, Proteome, Mutation discovery, Embryo development.


The IFOV of the Sensor Unit Sensor is 25 pixels of 1º x 1º = 5º x 5º.


The Image Creation Date of the SwRI-led team Team is 18 July 2018.


The Detection Date of the IceCube Satellite is 10 March 2021.


The Publication Date of the Solar-B EUV Imaging Spectrometer Spectrometer is 2005.


The Industrial Consortium of the GOME Instrument is Officine Galileo, Laben, British Aerospace, TPD.


The Launch Date of the Pleiades-1A Satellite is Unknown.


The Image Resolution of the CaSSIS Imaging System is 5 x 10 km.


The RAM Capacity of the FC Computer is 3 MB.


The Transformation Factor of the Field Measurement Device Sensor is 64 ± 0.6 (µV/nT).


The Purpose of the Coronagraph Instrument is Block out the image of the sun's disc and take pictures of the faint corona.


The Spectral Band of the Band Photometers Photometer is 391.4 nm.


The Extended Mission Start Date of the LISA Pathfinder Spacecraft is 1 November.


The Operating Frequency of the Herley MD2000C-1 Transponder Module is 5.4–5.9 GHz.


The Spatial Resolution at Nadir of the Scanning geometry Instrument is 1 km.


The Report Recommendation of the SMAP Satellite is Recommended for implementation in the first phase of new missions (2010-2013).


The Mass of the MBA Satellite is 418 kg.


The Frame Read-out Frequency of the EPIC CCDs Imaging Device is Fixed, mode dependent.


The Sensor Type of the CMOS Camera Camera is CMOS.


The First Photo of the MarCO-B CubeSat is 9 May.


The Measurement Domain of the MOMS Satellite is Ocean, Land.


The Objectives of the Deployment Mechanism Satellite Component is 1) Deploy each pair of nodes on command, so as to guarantee appropriate formation on orbit; 2) Do so without inducing a torque on the mule; and 3) Ensure appropriate deployment velocity for ideal cross-track separation while traversing the Auroral region.


The Launch Vehicle of the ArgoMoon CubeSat is NASA's Orion EM-1.


The Multispectral GSD of the CCD Pushbroom Camera Camera is 10m.


The Mass of the Total Satellite is 40 kg.


The Gyroscope Range of the ACS Attitude Control Subsystem is ± 200º/s.


The Average Power of the Solar Panels Power Source is 28.5 W.


The Measurement Coverage of the CryoSat-2 Satellite is Polar oceans, Greenland, Antarctica.


The Intersection Frequency of the ISS-RapidScat Scatterometer is Approximately every hour.


The Band of the EUTELSAT KONNECT Satellite is Ka-band.


The Architecture of the LCRD Laser Communications Relay Demonstration is Optical-to-optical relay.


The Electrical Connection of the SMA Heaters Deployment Control is In series.


The Launch Date of the COMS Satellite is 26 June 2010.


The Frequency Bands of the RF Communications Communication System is UHF/VHF (436/145 MHz).


The Focus of the Astroscale Company is Developing technologies to service satellites and remove orbital debris.


The Mission Status of the CAS500 Satellite is Operational (nominal).


The Type of the Solar Array Power Source is Triple-junction GaAs cells.


The Band Number of the Himawari-8 Geostationary Satellite is 16 bands.


The Completion Date of the Canberra DSN station Antenna is January 2021.


The Data Rate of the LLCD Laser Communication System is High.


The Sky Coverage of the SPARCS Satellite is 60% over a year.


The Diameter of the Didymos Asteroid is 780 meters.


The Gyroscope of the ADCS Attitude Determination and Control Subsystem is 12.5 mV/º/s, ±150º/s.


The Propellant Status of the CanX-4 Satellite is Close to a full tank.


The Payload Mass of the SmallGEO Satellite Platform is Up to 300 kg.


The Active Thermal Control of the TCS Thermal Control Subsystem is Polyimide heating film.


The Image Capture Date of the Small Monitor Camera (CAM-H) Camera is 14 August.


The Response Time of the Magnetic Field Sensor Sensor is <200 ns.


The Size of the Transmit Antenna Antenna is 3.3 m dish.


The Main Processor of the DHU Data Handling Unit is MA 31750.


The Instrument Type of the OSCAT-3 Radar Scatterometer is Radar scatterometer.


The Development Team of the PALSAR Ground Data System is Hiroshi Watanabe, Shiro Ohkawa, Kenji Tatsumi, Hidekuni Kikuchi, Yasutaka Onoda.


The Communication Band of the SPOT-6 & SPOT-7 Satellite Constellation is S-band.


The Malfunction Date of the OHRIS Imager is March 4, 2007.


The Onboard Instruments of the Voyager 2 Spacecraft is Cosmic ray subsystem, low energy charged particle instrument, magnetometer.


The Measurement of the Electric Field Instrument Instrument is 25 km-wide ribbon of gas flowing westward at about 6 km/s.


The ADCS System of the DeorbitSail Satellite is Stabilized.


The Revolutions/Day of the Iris Video Camera Camera is 16.


The Thermal Survival Range of the Instrument Satellite Instrument is -50 / +40ºC.


The Maximum Acquisition Rate of the STOs and STAEs Analog Electronic units is 0.1º/s.


The Components of the ROE Observatory is UKTAC, Institute of Astronomy, ROE Visitor Center.


The Solar Array Voltage Input of the SABR DC/DC Converter is Up to 65 V.


The Noise Figure of the TOTEM SDR SDR Platform is 2 dB.


The ERBS S/C Operational on One Battery Date of the ERBE Instrument is June 2001.


The Number of Strings per Panel of the Solar Array Power Generation is 11.


The Center Wavelength of the Band No. 17 Spectral Band is 644.64 nm.


The Prime Contractor of the SEOSAT-Ingenio Satellite is Spain.


The Collaboration Director of the Astrocast Satellite Operator is Renaud de Watteville.


The Cost of the Kestrel Eye II Microsatellite is Approximately $2 million per spacecraft.


The Architecture Elements of the FORUM Mission is Platform, payload and main mission performance.


The Purpose of the ALMA Atacama Large Millimeter/submillimeter Array is High-resolution observations.


The Additional Protection of the Avionics Components Components is Error correcting code on all memories and triple modular redundancy on logic gates in the used FPGAs.


The Mass of the Starlink Satellite Satellite is ~227 kg.


The Mass of the HORYU-2 Nanosatellite is 7.1 kg.


The Planned Number of Microsatellites of the PlanetIQ Satellite Manufacturer is 12.


The Absolute Accuracy Requirement of the CLARREO’s infrared and reflected solar spectrometers Spectrometers is Unknown.


The Components of the Electrical System System is C&DH (Command & Data Handling), PSS (Power Supply Subsystem), ADCS (Attitude Determination and Control Subsystem), Structures and Mechanisms, TCS (Thermal Control System), Communication subsystem including the TT&C (Telemetry, Tracking & Command) and the .


The Acquisition Frequency of the Navigation Images Imaging System is About every 4 hours.


The Number of Images Transmitted of the Tyvak-0130 Satellite is More than 4,500.


The Launch Date of the EXPORTS Satellite Mission is July, 2018.


The Module of the RAIDS Instrument is Kibo module of the ISS.


The Years on Orbit of the AISSat-1 Satellite is 3 years.


The Conference Location of the Space Plug-and Play Avionics Avionics is Los Angeles, CA, USA.


The Function of the MPACS Micro Propulsion Attitude Control System is Attitude control of the spacecraft.


The Ejection Mechanism of the Picosat Launcher Satellite Component is Latched door with a dual-release mechanism.


The Apogee Altitude of the Satellite Constellation Satellite Constellation is ~ 4,500 km.


The Brightness of the Quasars Energetic Sources is Up to 10 000 times brighter than the Milky Way.


The Objective of the PanCam Camera is Acquire 3D imagery of the lunar surface.


The Spacing of the EDSN Swarm Satellite Network is ~20 km.


The Mass of the ISEE-1 Spacecraft is 340 kg.


The Date of the LPVEx Field Campaign is September and October 2010.


The Type of the AIDA Impact Detector Assembly is Advanced.


The Initial Launch Service Procurement Plan of the Transport Layer Tranche 1 Satellite Network is Under commercial contracts.


The Reliability of the CERES Instrument is Highly reliable.


The Orbit Altitude of the AFSPC-11 Satellite Mission is 39,000 km.


The 0.035º of the Satellite Pointing Accuracy is S/C pointing accuracy = 0.035º.


The Wave Speed of the STEREO spacecraft Satellite is 250 km/s.


The Ensquared Energy of the Lens Optical Instrument is 90% within 60 x 60 µm.


The Number of Satellites of the RapidEye Earth Observation Constellation is 5.


The FOV of the FTS Interferometer Interferometer is 1.25 mrad.


The Extension Approval Date of the XMM-Newton Satellite is Nov. 14, 2007.


The Test Transmission Distance from Earth of the Herschel Spacecraft is 280,000 km.


The Data Distribution of the Aeolus Satellite is Near-real time.


The Wavelength Threshold of the CFOSAT Satellite is Larger than about 70 m.


The URL of the ARTEMIS satellite Satellite is http://www.esa.int/Our_Activities/Operations/Artemis_the_ATV_whisperer.


The Data Usage of the CFOSAT Satellite is Improve the inversion algorithms for estimating wind speed and significant wave height, characterize the small scale roughness of all types of surfaces.


The URL of the Aalto-1 Nanosatellite is http://blogs.aalto.fi/satellite/.


The Ambient Ionosphere Forecast of the C/NOFS Satellite is Several hours ahead.


The Image Repetivity of the CCD Camera Imaging System is One scan line per minute.


The Measurement Category of the ZACUBE-2 Satellite is Multi-purpose imagery (land).


The Modulation of the XBT X-band Transmitter is QPSK.


The Orbit Altitude of the Long March 5B Rocket Stage is 162 by 306 kilometers.


The Planned Date of the Maneuvers Orbital Adjustment is June 2015.


The Measurement Category of the KySat-2 Satellite is Multi-purpose imagery (land).


The Objective of the SAGE-III Satellite is Provide global, long-term measurements of key components of the Earth's atmosphere.


The Perigee (km) of the Meteor-1-1 Satellite is 644.


The Band Spacing of the OHIS Imaging System is 25 nm.


The Boresight Pointing Accuracy of the SXI Spacecraft is Within 3 arcmin elevation, within 3.5 arcmin azimuth.


The Image Capture Date of the Small Monitor Camera Camera is August 14, 2018.


The Image Telemetry Link of the SPOT-3 Satellite is 50 Mbit/s at 8 GHz.


The Power Supply of the LinkSprite JPEG color VGA camera Camera is 3.3 -5 V.


The Function of the AMR-C Microwave Radiometer is Provide a correction for the wet tropospheric path delay for the altimeter range measurement.


The Retrieval Planned Time of the LDEF Satellite is 10 months.


The Testing of the Valves Spacecraft Component is Ongoing.


The Spatial Resolution & Stability of the Telescope Optical Instrument is Encircled Energy of 75% at 1 µm for 150 mas radius.


The Funding of the NorSat-3 Satellite is NCA (Norwegian Coastal Administration).


The URL of the Van Allen Probes Satellite is http://www.nasa.gov/feature/goddard/2016/nasa-s van-allen-probes-revolutionize-view-of-radiation-belts.


The Cargo Mass of the CREAM Cosmic-Ray Instrument is 1,258 kg.


The Data Encryption of the SeaWiFS Satellite is Real time LAC data are encrypted.


The Conference Date of the Alphasat Concept Hosted Payload Operations is May 5-9, 2014.


The Function of the Target Sensor Photodiode is Solar and lunar acquisition.


The Distribution Function of the PDU Power Distribution Unit is Distributes power to the equipment.


The Spatial Resolution of the HIRES Instrument is About 2 km at 400 km altitude.


The Transmitting Pulses of the Instrument Radar Instrument is H or V.


The Sensitivity of the SEIS Seismometer is High.


The Instrument Type of the Hyperion HSI (Hyperspectral Imager) is Pushbroom.


The Manufacturer of the ION CubeSat Carrier Satellite is D-Orbit.


The Reception of the Receive Chain Radar Instrument is Either H or V.


The Registration Time of the RFA Instrument is 50 ms.


The | of the SpectraAalto-1 Spectral Imager Spectral Imager is Miniature SpectraAalto-1 Spectral Imager.


The Spectral Resolution of the Hyperion Imaging Spectrometer is 10 nm in VNIR and SWIR.


The Digitization of the Camera Electronics Data is 10 bits.


The Redundancy of the TT&C Transmitter Communication Device is Half Satellite.


The Operation Status of the NEOSSat Satellite is Operating well.


The Interface of the Instrument Control Unit (NI-ICU) Control Unit is 1553 bus.


The Output Information of the AVGS Laser System is Azimuth, elevation, range, and relative attitude.


The Connector Type of the Satellite Satellite is Second connector provides access to the battery and charging circuitry.


The Mode of the LISS-4 Imaging System is Mx mode.


The Function of the Satellite Satellite is Create a random string of numbers to represent an encryption key.


The Launch Date of the Carbonite-2 Microsatellite is January 2018.


The Mission of the SPATIUM-I CubeSat is Demonstrate technology aimed at electron density measurement and three-dimensional mapping of ionosphere.


The Resolution of the WorldView 4 Satellite is High.


The Solar Wind Speed and Beta of the ACE Satellite is ~55% lower on average from 2009 through the day 79 of 2013.


The Measurement Components of the LI System Lightning Information System is IC (Intra Cloud) and CG (Cloud Ground).


The Orbit Type of the MMO Spacecraft is Polar elliptical orbit.


The Solar Cells per Panel of the TCS Thermal Control System is 19.


The FRAM of the GomSpace NanoMind A3200 Onboard Computer is 32 kB.


The Components of the ADCS Attitude Determination and Control Subsystem is Attitude sensor, actuator interface assembly, four digital sun sensors, magnetic coils, momentum wheel.


The Pass Frequency of the Satellite Orbit Type is Between two and four times per day.


The Deployment Duration of the RDA Deployment System is Not provided.


The Solar Cells Manufacturer of the EPS Electric Power Subsystem is Emcore.


The Data Coverage of the AMSU Microwave Radiometer is Vertical temperature profiles up to 50 km.


The Focus of the Bigelow Aerospace Aerospace Company is Space Agencies, Commercial Users.


The entrance slit width of the Spectrograph Instrument is  6º.


The Band of the RF Communications Data Transmission is X-band.


The Spectral Range of the Observation Instrument Telescope/Spectrograph is 55-210 nm.


The Name Meaning of the Watoga Lake Lake is Cherokee word for “starry waters”.


The Design Life of the QuikTOMS spacecraft Satellite is Three years.


The Optimal Ground Condition of the HP3 (Heat Flow and Physical Properties Package) Heat-flow probe is Level ground without rocks larger than about 1.5 cm.


The Power Generation of the IRIS Satellite is 340 W.


The Mission Type of the FalconSat-3 Satellite is Non-EO.


The Actual Starlink Terminals of the Starlink Satellite Internet Service is Much lower than 200,000 or even zero.


The Calibration and Validation Approach Date of the Envisat Satellite is Oct. 2000.


The Fishing Spot of the Shikisai Satellite is Japanese pilchard (Sardinops melanostictus).


The Funding Round Amount of the Aleph-1 Constellation Satellite Constellation is $27 million.


The Period of the BUV Sensor is 107.2 minutes.


The Message Bus Function of the MCS Communication System is Provides a publish/subscribe mechanism.


The Years on Orbit of the Landsat-7 Satellite is 19 years.


The Construction of the Focal Plane Structure Structural Component is Complex 3d structures built rapidly from sheet metal primitives.


The Location of the X-band antenna Antenna is Nadir face.


The CPU of the ACU Attitude Control Unit is HD64F7145FW50.


The End of Life Date of the FalconSat-3 Satellite is 1 April 2017.


The Issue of the Starliner Spacecraft is Timing error in the software.


The Spatial Resolution of the TIRS-2 Sensor is 100 m.


The Data Release Frequency of the COSMIC-2 Satellite Constellation is Daily.


The Image Acquisition Date of the ExoMars Trace Gas Orbiter Orbiter is 27 June 2018.


The Mission Date of the GRACE Satellite is 21 Dec. 2017.


The X-band Downlink Transmission Data Rates of the CBERS-2B Satellite is 60 Mbit/s.


The Seismometer of the InSight Lander Lander is SEIS (Seismic Experiment for Interior Structure).


The Type of the TANSO-CAI Instrument is Atmospheric chemistry.


The Design Improvement of the HARP Imaging Polarimeter is Advance over POLDER’s (POLarization and Directionality of the Earth's Reflectances) filter wheel system.


The Nonlinear Wave Structures Effect of the Van Allen Probes Satellite is Rapidly energize very low energy (~10 electron volts) electrons up to intermediate energies (~100 keV).


The Testing Duration of the JUICE Spacecraft is Several weeks.


The Specific Impulse of the CanX-4&5 Satellite is 35 s.


The Integration Status of the Optical Module Subsystem is Completed.


The Objectives of the ATLAS-1 Satellite Mission is Study of the chemical makeup of the atmosphere, measurement of the total energy contained in sunlight, investigation of how the Earth's electric and magnetic fields and atmosphere influence one another, examination of sources of ultraviolet light in the u.


The Energy Conversion of the Electrodynamic Tether (Power or Drag System) Propulsion and Power Generation Device is Converts the orbital energy of the host S/C into electrical power.


The Design Life of the Tsubame Microsatellite is 1 year.


The TM/TC Interface of the RAMIS Radiation Detector is RS-485.


The Mass of the TDS-1 Satellite is 150 kg.


The Thickness of the Aluminum Film Optical Instrument Component is 70 nm.


The Period (min) of the Meteor-1-1 Satellite is 97.9.


The Launch Date of the INSAT-3DR Satellite is Sep 9, 2016.


The Signal Usability of the Galileo Satellite Constellation is Usable in all new mobile phones.


The Global Coverage of the GNOS-2 Satellite is 2 weeks.


The Size of the Psyche Asteroid is About the size of Massachusetts.


The Lead of the Science Office Office is “Science Systems Engineering” effort.


The Post-Project Careers of the SAPPHIRE Satellite is Nine hold significant spacecraft systems or management responsibilities with aerospace contractors, the Air Force or academia.


The Mission Extension of the Envisat Satellite is Yes.


The Purpose of the SMAP Satellite is Measure soil moisture.


The Number of Satellites of the Unseenlabs' Constellation Satellite Constellation is 3.


The Spatial Resolution of the MSU-50 Camera is 120 m.


The Function of the OBCS On-Board Computer Subsystem is Main flight computer which runs the flight software (FSW).


The Distance from Bennu of the OSIRIS-REx Spacecraft is 155 miles (250 km).


The Contract Value of the Planet Satellite Imaging Company is $20 million.


The Probe Development Location of the Electron Temperature Part Experiment is IKI (Institute of Space Research) Moscow, Russia.


The Measurement Domain of the Odin Satellite is Atmosphere.


The Planned Mission Duration of the Wind Satellite is 5 years.


The Purpose of the GEOTAIL Satellite is Determine the overall plasma, electric and magnetic field characteristics of the distant and geomagnetic tail.


The Launch Time of the Galileo FOC-3 and FOC-4 satellites Satellite is 21:46 UTC.


The Angular resolution (2 px) of the HRI dual EUV 174 Å and 335 Å alternatively Passband center is 1 arcsec.


The | of the SGR-ReSI GNSS Receiver is Introducing the SGR-ReSI: A Next Generation Spaceborne GNSS Receiver for Navigation and Remote-Sensing.


The Position of the ULF Sensor Sensor is Tip of the gravity gradient boom.


The Operational Orbit of the Spacecraft Satellite is Lissajous orbit at an average distance of 800,000 km from L2.


The VPU of the Ubotica CogniSAT-XE1TM CubeSat Board Satellite Device is Intel® Movidius™ Myriad™ 2.


The Side Length of the HIT-Sat Satellite is 12 cm.


The Form Factor of the 6U CubeSat Satellite is 6U.


The Horizon Sensing of the X-ray Navigation Navigation System is Only the upper atmosphere is traversed by a ray grazing the effective horizon.


The Status of the M3MSat Satellite is In storage.


The Launch Date of the TOPEX/Poseidon Satellite is Aug. 10, 1992.


The Volume Occupation of the Solar Sail Subsystem Spacecraft Subsystem is Lower 2/3 of the spacecraft.


The Relative Position of the AC4-B Satellite is Catch up with and pass AC4-A.


The Launch Date of the HyperScout Hyperspectral Imager is 2 February 2018.


The Orbit of the SuperView-1 Observation Satellites is Low Earth.


The Propulsion Subsystem of the SGEO Satellite is Electric.


The Pointing Capability of the Satellite Imaging Satellite is Allows calibration using the sun, moon and stars.


The Spectral Bands of the OLCI Spectral Imaging Instrument is 21.


The Mission of the Solar Orbiter Spacecraft is Perform unprecedented close-up observations of the Sun.


The Annual Spending on Commercial Data of the NASA Organization is Roughly $30 million.


The Type of the Beacon station antenna Antenna is 7-element Yagi antenna.


The Key Technologies of the SATis5 Testbed is Distributed NFV orchestration, distributed, edge oriented 5G control plane, diverse, dynamic data path support, local offload, multicast, efficient small messages distribution, device management for slice-selection, secure and isolated multi-slice environ.


The Layout of the Transponder Communication System Component is Downconverter, LNA, RF switch matrix, Upconverter, channel amplifier, TWT.


The Launch Date of the Alphabus Satellite Platform is Jan. 29, 2010.


The Mission Duration of the Crew Dragon Spacecraft is Three days.


The Downlink Frequency of the RF Communications Communication System is 430 MHz.


The Operating Altitude of the Sentinel-6 and Jason-3 Satellites is 1330 km.


The Measurement Range of the Cloud Top Pressure Satellite Instrument is 200-900 hPa.


The Measurement Difference of the CDN1 transponder Transponder is Less than 2 mm.


The Measurement of the Electric Field Instrument Instrument is Temperature 300 km above Earth’s surface jumped by 3000ºC.


The Operating Frequency of the 183 GHz radiometers Radiometer is 183 GHz.


The Previous Record Crest Height of the Yellowstone River River is 11.5 feet.


The Data Rate of the X-band downlink system Communication System is Up to 80 Mbit/s.


The Operation Period of the Nimbus-7 Satellite is 1978 until 1994.


The Data Resolution of the TanDEM-X Satellite is 50 m x 50 m.


The Force of the Thrusters Attitude Control is 10 Newton.


The Pointing Accuracy of the Alphasat TDP1 and Sentinel-1A Optical Link is Better than 500 µrad.


The Launch Date of the GOSAT-2 Satellite is October 2018.


The Purpose of the QSAT Satellite is Polar Plasma Observation.


The Launch Year of the RemoveDebris Mission is 2018.


The Objectives of the ISEE-1 Spacecraft is Observation of the near-Earth magnetosphere and its boundaries, better understanding of many phenomena, such as the Earth's bow shock, the magnetosheath and magnetopause, interactions between the tail and aurorae, and particle populations and flows in the.


The EUV Imager of the SWAP Instrument is Unknown.


The Data Transfer Rate of the SSRNI Data Acquisition and Registration System is 7.68 Mbit/s.


The Launch Date and Time of the GHGSat-C2 (Hugo) Nanosatellite is January 24, 2021, at 15:00 UTC.


The Image Resolution Comparison of the Solar Orbiter Satellite is Ten times better than what a 4k TV screen can display.


The Survey Mode Duration of the C/NOFS Satellite is 9 months.


The FPA NEDT of the CIRiS Instrument is < 50 mK.


The Priority of the LEP-EA and LEP-E Instruments is High.


The Application of the Falcon Neuro Neuromorphic Cameras is Sprite and lightning detection on the International Space Station.


The Thrust Level of the Satellite Spacecraft is Varying.


The Propellant of the Lunar Flashlight CubeSat is "Green" propellant.


The Commissioning Completion Date of the RAIDS Experiment is October 22, 2009.


The Type of the HPCA Electrostatic Analyzer is Toroidal top-hat.


The Temporal Sampling of the Sea Surface Temperature (SST) Measurement is Sub-daily.


The Manufacturer of the Sich-2 Satellite is Yuzhnoye State Design Office (SDO).


The Constellation Builder of the UrtheCast Company is SSTL (Surrey Satellite Technology Ltd.),UK.


The Route of the A-68A Iceberg is Across the Drake Passage.


The Scheduled Launch of the Hugo Satellite is By the end of the year.


The SNR in bands 1 and 2, in band 3 of the Scanning geometry Instrument is ≥ 200, ≥ 100.


The Distance from Bennu of the OSIRIS-REx Spacecraft is 1,635 miles (2,200 km).


The Data Rate (max) of the CanX-2 S-band Transmitter/Transceiver is 1024 kbit/s.


The Coverage Zones of the Scientific Payload Satellite Payload is Ka-band (20/30 GHz): one steerable spotbeam over South Germany and the H2KAR antenna (IOV) over North Germany, ISL (23/26 GHz): one ISL tracking antenna, steerable over the whole Earth and the receive GeReLEO Smart antenna (IOV), Ku-band (11/14 GHz): anch.


The Applications of the ASAR Instrument is Measuring sea-state conditions, Mapping ice-sheet characteristics and dynamics, Mapping sea-ice distribution and dynamics, Detecting large-scale vegetation changes, Monitoring natural and man-made pollution over the oceans, Offshore operations in sea ice,.


The Grid Size of the RAS Product Data Product is 25 km.


The Spatial Resolution of the GHOSt Satellite Constellation is 8 m.


The URL (paper) of the Cute-1.7+APD Nano-Satellite is http://lss.mes.titech.ac.jp/ssp/cute1.7/paper/aca2007.pdf.


The Spatial Resolution of the MSC Camera is 5.8 m.


The Mission Operations Date of the SkySat Satellite is May 28-June 1, 2018.


The | 100 x100 km2 of the IASI-NG Instrument Field Of View (FOV) Size is The resulting FOV is in the order of 100 x100 km2.


The Spatial Resolution of the DubaiSat-2 Satellite is 1.0 m (Pan), 4 m (MS).


The Jitter of the GOCI Instrument Instrument is Less than 10 µrad.


The Observation Results of the Herschel Space Observatory is Gas filaments become unstable and form clumps of material bound together by gravity.


The Range of the Horizon sensor Sensor is ±5.5º.


The Aperture of the Instrument Optical Instrument is 8 cm.


The Agency of the MidSTAR-1 Satellite is USNA (United States Naval Agency).


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


The Mission of the PAZ Satellite is Dual-use (civil/defence).


The Image Size of the NAVCAM Camera is 866 x 866 m.


The Protection of the Batteries Power Storage is Integrated over current protection.


The Thrust of the DMC Propulsion Subsystem Electric Propulsion is 50 mN.


The Mass of the SpinSat Spacecraft is 57 kg.


The Particle Detection Location of the IBEX Spacecraft is Outer heliosphere.


The Role of the Martin Popek Individual is Passionate about capturing sprites, jets and elves on camera.


The Transportation Capacity of the HTV-9 Cargo Transfer Spacecraft is World's largest.


The LTAN of the NEMO-HD Satellite is 10:30 hours.


The Close Approach Coordination of the Starlink Satellite Constellation is With multiple government and commercial satellite operators.


The Scanning Capability of the ISAMS Instrument is Vertically and to either side of the UARS observatory.


The Wavelength Range of the BEO Back-End Optics is 400-1100 nm.


The Optics Design of the NFOV Imagers Imaging System is Cassegrain design.


The Data Acquisition Method of the CCD Detector Imaging System is Rotating the imaging system, including the CCD, at a rated synchronization with a vertical charge transfer of the CCD detector.


The Launch Date of the ZACUBE-2 Satellite is 27 Dec 2018.


The Center Frequencies of the Bandpass Filters Signal Processing is 1.5, 4.5, 7.5, 10.5, 13.5, 16.5, 19.5, 22.5, 25.5, 28.5, 31.5 and 34.5 MHz.


The Development Cost of the SAOCOM-1A Satellite is $500 million.


The Mission Status of the FormoSat-7 / COSMIC-2 Satellite Constellation is Unknown.


The Dataset Sizes of the EO-ALERT Satellite System is Wide range.


The Number of Elements of the PR Phased Array System is 128.


The Measurement Targets of the GeoCARB Satellite is Carbon dioxide, carbon monoxide, methane and Solar-Induced Fluorescence quantities.


The Frame Rate of the ROIC/FPA Imaging System is 16 kHz.


The Data Downlink Rate of the MinXSS-2 Satellite is At least a factor of 6 increase from 1 MB per day.


The Antenna pointing accuracy of the AOCS Attitude and Orbit Control System is < 0.1º (3σ) half cone.


The Duration of the Ground Station Passes Ground Station is 8 hours.


The Wave Height Measurement Accuracy of the ALT Experiment Altimeter is 10% or 0.5 m, whichever was greater.


The Bandwidth of the Aperture Function Image Processing is 2D.


The First Image Download Date of the LightSail Satellite is June 2, 2015.


The Measurement of the FORUM Satellite Mission is Far-infrared radiation emitted from Earth.


The Orbit Type of the DMC-3 Constellation Satellite Constellation is Sun-synchronous orbit.


The Leader of the Marsquake Service Service is ETH Zurich.


The Measurement Category of the OSCAR-QUBE Satellite is Gravity, Magnetic and Geodynamic measurements.


The Journey Duration of the Hayabusa-2 Spacecraft is 42 months.


The Control Methods of the ADCS Attitude Determination and Control System is Unique control method using aerodynamic drag.


The Voltage of the HVSA High Voltage Experiment System is 350 V.


The Purpose of the Humanity Star Artistic Light Beacon is Purely artistic.


The Composition of the TRAPPIST-1 Planets Planets is Similar Stuff.


The Pointing Jitter of the ASTERIA Satellite is 1σ ~0.5".


The Wavelength Stability of the LD Output Laser Diode is <0.1%.


The Manufacturer of the C3D Imager Imager is Clyde Space.


The Residual Acceleration of the GP-B satellite Satellite is 4×10-11 m s-2.


The Instruments of the FORUM Satellite is Cloud Radar, Imager, Sounder.


The Design of the BRO-1 Satellite is 6U CubeSat.


The Development Status of the GCOM-C1 Satellite System is Unknown.


The Manufacturer of the NanoRacks Airlock Module Airlock Module is NanoRacks.


The Size Comparison of the ORS-3/STPSat-3 Satellite is 6 times bigger than TechEdSat.


The Development Partners of the SGR-ReSI Instrument is SSTL, University of Surrey, National Oceanographic Centre, University of Bath, Polar Imaging Ltd..


The Return to NASA's Kennedy Space Center of the Orion Spacecraft is Will return to NASA's Kennedy Space Center.


The Low-Energy Threshold of the Detector Instrument is 2.5 keV.


The Power Consumption of the SIR-2 Instrument is 2.2 W.


The Safe Mode Operation of the ADCS Attitude Determination and Control System is Coarse sun pointing.


The Ground Station of the Nanosatellite Satellite is Kagawa University.


The Reaction Wheel Spin Rate of the Integral Satellite is About 17 degrees per minute.


The Discovery Year of the W– boson Particle is 1983.


The Mass of the TechnoSat Satellite is 18 kg.


The Anniversary of the TIMED Satellite is 10 Years.


The Manifestation Date of the HICO and RAIDS Instruments is Spring of 2007.


The Compatibility of the Frontier Radio Radio is NASA's STRS (Space Telecommunications Radio System) architecture.


The Mask Thickness of the Optical Head Optical Device is 0.1 mm.


The Publication Date of the Colliding star clusters Article is 3 January 2022.


The Telemetry of the LEICA Particle Detector is 1.3 kbit/s.


The Mission Purpose of the SPARCS Satellite is Understand the Impact of Stars in Exoplanets.


The Launch Date of the Iridium-4 NEXT Mission Satellite Mission is December 2017.


The Manufacturer of the Cupola Window is TAS-I.


The Data Bus Interface of the PCU Power Control Unit is SpaceWire type.


The Range of the Laser Rangefinder Device is Up to 2 km.


The Wavelength of the FAI Auroral Imager is 630 nm.


The Cost (sensor + spacecraft) of the Pushbroom Sensor is High.


The Interface Requirement Document of the FORMOSAT-7/COSMIC-2 Satellite is FS7-IRD-0002.


The Spatial Resolution of the Ikonos-2 Satellite is 0.82 m.


The Image Segment Size of the CaSSIS Imaging System is 22.7 x 6.6 km.


The Unknown of the MIPAS Instrument is Unknown.


The Country of the skCube Satellite is Slovakia.


The International Cooperation Presentation of the COSMO-SkyMed Satellite is 68th IAC (International Astronautical Congress), Adelaide, Australia, 25-29 Sept. 2017.


The Launch Date of the Starliner Spacecraft is Dec. 20.


The Mass of the Comet Celestial Body is 10 billion tons.


The Data Transmission of the EUMETCast Dissemination System is Multicast files.


The Data Usage of the ISS LIS Lightning Imaging Sensor is Air-traffic advisories, climate monitoring.


The Conference Date of the TanDEM-X Satellite is May 29-31, 2013.


The Power Requirement of the Payload Satellite Component is 100 W.


The Architecture of the GomSpace NanoMind A3200 Onboard Computer is AVR32.


The Mass of the BRITE-Austria Satellite is 6.5 kg.


The Length of the Krishna River River is 1,300 km.


The Initiator of the CSD Satellite Component is Reusable.


The Bus Type of the GFO Satellite is BCP 600 (Ball Commercial Platform).


The Designed for of the Landsat-7 Satellite is Earth-observing.


The Remarks/Sensors of the OrbView-2 Satellite is SeaWiFS.


The Spectral Range of the DNB Spectral Band is 0.5-0.9 µm.


The Magnetometer Status of the NEOSSat Satellite is Failed.


The Sigma 0 Range of the Radar Radar is HV, VH: +5~-35 dB.


The Lagrange Point of the Gaia Satellite is Lagrange point 2.


The Components of the OBDH On Board Data Handling and Communications is Microcontroller and the other circuits needed for data storage, communication, conversions, timing and execution of the tasks.


The Propulsion of the Spacecraft Satellite is Slanted N2H4 monopropellant thrusters.


The Launch Date of the NigeriaSat-X Satellite is 17 Aug 2011.


The Separation Date of the STRaND-1 Satellite is February 25, 2013.


The NDVI Map Spatial Resolution of the RISING-2 Satellite is About 10 m.


The Function of the Fluxgate and search coil magnetometers Sensor is Measure low frequency and wave magnetic fields.


The Assistants of the COMS Satellite is Astrium, KARI (Korean Aerospace Research Institute), and KIOST (Korean Institute of Ocean Science and Technology).


The Attitude Control of the ACS Attitude Control Subsystem is ±0.05º.


The Components of the SIA Science Instrument Assembly is Four quartz gyroscopes aligned in a fused-quartz block.


The Data Rate of the OSIRISv3 Laser Communication Terminal is Up to 1 Gbit/s.


The Manufacturer of the NESSI Telescope is Spectral Applied Research Inc..


The Bus Dimensions of the PRISMA Satellite is 1.751 x 1.545 x 3.4 m.


The Footprint of the LWIR Cameras Camera is 9911 km2.


The Bands of the Poseidon 4 Radar Altimeter is Ku- and C- band.


The Launch Date of the VNREDSat-1A Satellite is Unknown.


The Mission Objective of the CALIPSO Satellite is Assess the impact of aerosols on Earth’s radiation budget through the aerosol direct and indirect effects.


The Focal Planes of the ETM+ Scanner Imaging Device is 2.


The Orbit of the Spacecraft Satellite is GEO (Geostationary Orbit).


The Launch Initiative of the MoonLIGHT Satellite is NASA's Commercial Lunar Payload Services.


The Spectral Band of the Spectral Block Focal Plane Component is 758 – 768 nm.


The CEO of the Lacuna Space Satellite Company is Rob Spurrett.


The Capacity of the Solid-State Recorder Data Storage is 58.9 GB.


The Probability Value of the Contamination Probability Mission Requirement is Smaller than 10–2.


The Image Center Coordinates of the CaSSIS Instrument is 28.79ºS/193.84ºE.


The Solar Cells Type of the Solar Array Power Subsystem is High-efficiency dual-junction gallium-arsenide (GaAs).


The Status of the LND Lunar Lander Neutrons and Dosimetry is Turned on for testing.


The Detector Array of the LWIR Camera Camera is HgCdTe detector array of 128 x 128 pixels.


The Mass of the Corvus-BC 2 Satellite is 10 kg.


The Mass of the UniSat-5 Satellite is 28 kg.


The Telescope Diameter of the CE-SAT-1 Microsatellite is 40 cm.


The Image Capture Period of the DEIMOS-2 Satellite is 12 hours.


The Applications of the Landsat TM Satellite is Global change research, agriculture, forestry, geology, resources management, geography, water quality, and oceanography.


The RF Communications of the Kanopus-V Satellite is X-band (8.2 GHz) downlink of payload data, data rate of 300 Mbit/s, onboard data storage of 24 GB.


The Daily Reset of the Dellingr Satellite is Part of daily operations.


The Redundancy of the OBC On-Board Computer is Each board is available twice for redundancy reasons.


The Length of the Instrument Instrument is 204 mm.


The Pixel Size of the Kodak KAI-11002 CCD CCD is 9 µm x 9 µm.


The URL of the Whale Ecology Observation Satellite Satellite is http://www2.nict.go.jp/mt/b150/SJR/English/eng12-1/smallsatelliteweose.pdf.


The Mass of the SEIS Instrument Seismometer is 3 kg.


The Ground Architecture of the SENSE Satellite is SMC/SD.


The Developer of the JPSS-1 Satellite is NASA.


The Antenna Type of the OPAL Satellite is 1/4 wavelength monopole.


The Components of the PMC Camera Set is Camera mainframe, camera management & control unit, DC/DC converter, baffle.


The Constellation Size of the Aurora Satellite is Six-satellite.


The SAR Data Acquisition of the X-UGS UGS is Lack of capability to acquire directly SAR data.


The Battery of the XI-IV Picosatellite is Manganese type lithium-ion battery.


The Purpose of the CZCS Multichannel Scanning Radiometer is Ocean colour measurements.


The Downlink Data Rate of the ERBS Satellite is 128 kbit/s.


The Operations Date of the MCubed-2 CubeSat is April 22, 2014.


The Altitude Above Ground of the Lunar Landing Vehicle Vehicle is 100 m.


The Control Interface of the Yaesu G-5500 rotators Rotators is Yaesu GS-232.


The Center Frequency of the Channel 8 Sensor is 52.80 GHz.


The Frequency (GHz) of the ICI-1 Radiometer is 183.31±8.4.


The Operating temperature range of the PHA Detector is -30 to +50ºC.


The Size of the Millimeterwave receiver radiometer is ~ 1.6 mm.


The Spatial Matchup Window of the CYGNSS Satellite is 25 km.


The Geographic Site Sizes of the PUTC Program is Vary from 100 km2 up to 3500 km2.


The Battery Storage of the EPS Electrical Power Subsystem is Capable of sustaining subsystems during operating loads and orbit eclipses.


The Launch Date of the Exoplanet mission Satellite is Unknown.


The Model of the GPS Receiver Payload Module is SGR-10.


The Earth Observation Constellation Type of the Spacety Company is Microwave-based (Synthetic Aperture Radar) satellite.


The Downlink Acquire Time of the IXPE Satellite is 60 s.


The Conference Date of the SMEX-LITE Satellite is Sept. 16-19, 1996.


The Formation Size of the MMS Satellite Formation is 10 km.


The Mean Altitude of the Vstar Gravity-field Measurement Microsatellite is ~100 km.


The Operation Time of the MEPSI Satellite is Up to 24 hours.


The Mass of the SOHLA-1 Microsatellite is 50 kg.


The Communication Bus of the SMEX Satellite Program is MIL-STD-1553 data bus.


The Observation Duration of the SPARCS Satellite is 1 to 3 stellar rotations.


The Mission Purpose of the GomX-1 Nano-satellite is Demonstrate Improved Situational Awareness for Air Traffic Control.


The Developer of the Electronic Unit Component is Shandong Institute of Aerospace Engineering.


The Sensor Mode of the HyperScout® Imaging System is Pushbroom.


The Propulsion System Fuel Capacity of the EAGLE ESPAStar Satellite is Up to 310 kg.


The Purpose of the Sentinel-6 Satellite is Ensure the ‘continuity of service' of the Jason missions.


The Pixel Scale of the Telescope Optical Instrument is 15 µm.


The Source of the Arrokoth Celestial Body is AAAS.


The Prime Contractor of the Euclid Space Telescope is Thales Alenia Space.


The Thrusters of the Satellite Bus Spacecraft Component is 12 hydrazine thrusters.


The Downlink Frequency Band of the GPS-DASS Payload is 2226 MHz (S-band).


The Designing Institution of the WeissSat 1 CubeSat is Weiss School.


The Crew Return Time to Earth of the Proving Ground Space is Matter of days.


The Function of the SCL Spacecraft Command Language is Enable event-driven processing and low-level autonomy.


The Dimensions of the PowerCell Hardware is ~21 x 29 x 8 cm.


The Solar Array Output of the EPS Electrical Power Subsystem is 1418 W (EOL).


The Satellite Cost of the Astrocast Satellite Manufacturer is Half a million dollars.


The On-Orbit Spare Lifetime of the GOES-R Satellite is 5 years.


The Purpose of the TESIS Telescope-spectrometer is Registration of solar images in narrow spectral bands and monochromatic emission lines of HeII, SiXI, FeXXI – FeXXIII, MgXII ions in high temperature plasma of the transition region and corona.


The Validation Facilities of the SWOT Satellite is Efficient.


The Function of the PMC Payload Module Computer is Controls all PLM equipment and instruments.


The Interfaces of the HMA Project is Catalog Service, Ordering Service, Programming Service, Mission Planning Service, Online Data Access Services.


The Signal-to-Noise Ratio of the NISP Photometer Instrument is At least 5.


The Radiometer of the OLS Imaging Sensor is VIS/IR.


The Data Storage Capacity of the Data Transmission Subsystem Satellite Subsystem is 128 Gbit.


The Mission Status of the EXPORTS Satellite Mission is Operational (nominal).


The Leader of the GRNS Team is David Lawrence.


The Luminosity of the Sw J1644+57 Supermassive Black Hole is Temporarily boosted.


The Altitude of the Suomi-NPP Satellite is 824 km.


The Distance from Earth of the Kepler-442b Exoplanet is Around 1,200 light years.


The Complex Investigation of the Chibis-M Microsatellite Satellite is Unknown.


The Launch Date of the Nauka Module is No earlier than 15 July.


The Ordering of the CSK GS Ground Segment is Allow S-IM to submit production requests towards the FM when receiving confirmation that the acquisition is planned.


The Solar Array Capacity of the MERLIN Satellite is Unknown.


The Image Capture Date of the MERIS Satellite is April 2, 2012.


The Workshop Date of the Soil Moisture Active and Passive (SMAP) Mission Satellite Mission is Sept. 22-23, 2008.


The Conference Presentation Date of the TacSat-4 Satellite is Aug. 10-15, 2013.


The Presentation Date of the Scalable Payload Downlink Chain Data Communication System is June 11-13, 2009.


The Update Date of the Jason-3 Satellite is Feb. 11, 2016.


The Algorithm Selection Criteria of the Attitude Determination Quaternion Filter Experiment is Maximum trace of the associated information rate matrix.


The Resolution of the Aurora Sensor Hyperspectral Sensor is Approximately 30 metres per pixel.


The Launch Date of the Psyche spacecraft Spacecraft is Next year.


The Downlink Chains Data Rate of the ResourceSat-2 Satellite is 105 Mbit/s.


The Launch Services Contract Date of the Jason-3 Satellite is July 16, 2012.


The Number of Turrets of the Mechanical Turrets Mounting is 3 for each spectral range.


The Affiliation of the Nico Fleurink Engineer is Unknown.


The Modulation Factor of the HXCP Hard X-ray Polarimeter is 47.8%.


The Radiation Pattern of the Ka-band payload Communication System is Modified to distribute higher power at angles ± 50º from boresight.


The Mass of the Instrument Satellite Instrument is 202 kg with the NG reflector and 275 kg with the HC reflector.


The Distance from the Sun of the New Horizons Spacecraft is Almost 5 billion miles (7.5 billion kilometers).


The Dimensions of the Microsatellite Satellite is 540 mm (height), 370 mm (full diameter).


The Map Projection of the L1C Products Satellite Data is User Selectable.


The LTDN of the Polar Scout 6U CubeSat Satellite is 10:30 hours.


The Outer Shell Temperature of the Dewar Component is ~254.5 K.


The Design of the Interferometer Device is Birefringent gratings, Wollaston prisms, and LSI spacers to create the grating lateral shearing interferometer.


The Redundancy of the Thrusters Propulsion Device is 1 THR loss allowed.


The Mass of the HORYU-4 Nanosatellite is 10 kg.


The IFOV of the S-192 optomechanical scanner Scanner is 79 m.


The Authors of the HyperScout Hyperspectral Imaging System is Michael Soukup, Janis Gailis, Daniele Fantin, Arnoud Jochemsen, Christina Aas, Pieter-Jan Baeck, Iskander Benhadj, Stefan Livens, Bavo Delauré, Massimo Menenti, Ben Gorte, Seyed Enayat Hosseini Aria, Marco Esposito, Chris van Dijk.


The Responsibilities of the SatsimIF Application is Establishing a TCP/IP connection with the Satsim computer, Uploading the simulated model on to the xpcTarget machine, Listening on the RAMSES multicast UDP network and redirecting all commands required to control the simulation.


The Purpose of the Interposer Board Interface is Provide the interface between the 51-pin connector, the second connector, and the payload.


The Voltage of the Electrodynamic Tether Propulsion and Power Generation Device is Up to several hundred volts per km.


The Timeline of Events of the SpaceX Falcon-9 Rocket is 93 milliseconds from the first sign of anomalous data to the loss of the second stage.


The Location of the PACS Instrument Control Center is MPE (Max Planck Institute for Extraterrestrial Physics), Garching, Germany.


The FOV of the Earth Radiation Budget Experiment (ERBE) Instrument is ±78º cross-track, 360º azimuth.


The Sensor Operating Pressure of the FIPEX Instrument is Down to 10-10 mbar.


The Collision Date of the Small Near-Earth Objects Space Debris is 21 November 2002.


The Frequency of the RA-1 Radar Altimeter is 13.8 GHz.


The RCS Thrusters Fuel of the AOCS Attitude and Orbit Control System is 12 years.


The Operating Temperature of the Telescope Optical Instrument is -50ºC to ~ 100ºC.


The SNR of the Band 3 Spectral Band is 400.


The FMC (Forward Motion Compensation) system of the Metric Camera Camera is Not added.


The Along-Track Resolution of the OMI Spectrograph is 13 km x 48 km to 13 km x 12 km.


The Peak Transmit Power of the KaRIn Instrument is 1500 W.


The Channels of the GPS receiver Receiver is 24 channels.


The Mystery Solve Date of the Cluster Satellite Constellation is July 14, 2015.


The Purpose of the Automated Transfer Vehicle (ATV) Spacecraft is Provided reliable cargo deliveries to the Space Station.


The Component Detection of the SPA System System is Automatic.


The Tests of the Characterization Process Satellite Debris Analysis is Repeatability and reproducibility tests.


The Design Life of the RADARSAT-1 Satellite is 5 years.


The Conference Date of the Telemetry Monitoring and Analysis System System is April 25-30, 2010.


The Services of the NanoRacks LLC Company is On-board and on-ground services to the general 'small payload' research community of the International Space Station (ISS).


The Spectral Resolution of the Instrument Spectral Imager is 2.5 cm -1.


The Quantity of the Ithaco Inc. 60 Am2 electromagnetic torque rods Torque Rods is Three.


The Power of the PPS-1350-G Hall-effect thruster is Nominal input power (in Watt).


The Stability of the ADCS Attitude Determination and Control Subsystem is ≤ 5 x10-4 º/s.


The Sensor Complement of the BRITE-Austria Satellite is Unknown.


The Frequency of the Formation Flying Maintenance Maneuver is Once per week or longer.


The Payload Data Downlink Rate of the MERLIN Satellite is 180 to 310 Mbit/s.


The In Orbit Operations Duration of the RapidEye Constellation Satellite Constellation is 10 years.


The Size of the APD Avalanche Photodiode is Very small.


The Payloads of the Aditya-L1 Satellite is Particle payloads, magnetometer payload.


The Chirp Bandwidths of the Satellite Satellite is 320, 80, 20 MHz (Ku-band), 160 MHz (S-band).


The SRAM Capacity of the RAD750 SBC Single Board Computer is 36 MB.


The Orientation of the µSCIA Monitoring Instrument is Nadir-oriented.


The Launch Date of the Global Precipitation Measurement (GPM) Mission Satellite Mission is Unknown.


The Number of Satellites of the Iridium Communications Inc. Company is 5.


The Technique Developer of the Solar Flare Solar Event is Alina-Catalina Donea.


The Mass of the Satellite Spacecraft is 100-400 kg.


The Lunar Orbit Altitude of the Chang'e-3 Lunar Lander is 100 km.


The Measurement Regions of the Cluster Satellite Mission is Solar wind and bow shock, magnetopause, polar cusps, magnetotail, auroral zone.


The Award Date of the Ozone Monitoring Instrument Instrument is 29 April 2019.


The Bandwidth of the ODTML Data Collection System is > 50 kbit per node per day.


The Services of the GMES Global Monitoring for Environment and Security is Meteorology, agricultural monitoring, food supply forecasting, fisheries, ship-routeing, urban planning, climate change studies, emergency response, humanitarian aid, external EU actions, border surveillance, maritime security.


The Instrument Type of the SEIS Seismic Experiment for Interior Structure is Seismic.


The Mounting of the GRNS Instrument is 6-foot (2-meter) boom.


The URL of the Omni-Directional Differential Sun Sensor Sensor is http://citeseerx.ist.psu.edu/viewdoc/download?doi=10.1.1.34.9657&rep=rep1&type=pdf.


The Power Bus Voltage of the PCDU Power Control and Distribution Unit is 28 V.


The Design Life of the Aqua Satellite is 6 years.


The Altitude of the Himawari-8 Satellite is ~35,800 km.


The URL of the SphinX Solar Photometer in X-rays is http://www.cbk.pan.wroc.pl/body/publikacje/2008/JC_JS_Sphinx_2008_11_06.ppt.


The Parking Orbit Altitude of the ARTEMIS Spacecraft is 31,000 km.


The Function of the SES Instrument is Demonstrate that the instrument can survive the extreme thermal gradients and mechanical strains.


The Operational Cadence of the Instrument Satellite Instrument is Stare nadir for 30-40 minutes.


The Number of Stars of the Upper Centaurus Lupus Star Cluster is 134.


The Pressure Change of the Airtight Vessel Satellite Component is 1.6%.


The Magnetometer of the ADCS Attitude Determination and Control Subsystem is 1.0 V/gauss, ±1.9 gauss.


The Funding Source of the ELFIN Satellite is NASA/NSF.


The Project Manager of the CO2M Satellite is Valerie Fernandez.


The Functionalities of the UIS System is Reception, management of product order, generating image collection proposal, image collection request, submitting product generation request.


The Load Range of Shaker Tests of the Boom Structure is 0.048 to 0.00055 kg.


The Concept of the TransHab Space Habitat is URL: http://spaceflight.nasa.gov/history/station/transhab/.


The Average Sigma Naught of the SAR Instrument is -7.5 dB.


The Launch Date of the IRS-P6 Satellite is 17 Oct 2003.


The Mission Duration of the D-Sat Satellite is More than three months.


The Consideration of the Eutelsat Communications Company is $165 million.


The Quantity of the GEMSat/ELaNa-2 Satellite is 12 CubeSats/nanosatellites.


The Mission Objectives of the M3MSat Satellite is The primary mission objective is to provide maritime surveillance for both commercial customers, and for the Canadian government, by detecting AIS messages from space.


The Gain of the Antenna for Navigation Antenna is Greater than – 4 dBic for elevations > 5°.


The Channels of the ALTIUS Instrument Satellite Instrument is Three channels.


The Stability Requirements of the Individual Spectrometers Instrument is 15 pm.


The User Mission Operations Center Simulator of the LCRD Satellite is UMS.


The Power On Command of the SPAN Sensors Sensor is Via command from the SPP DPU to the SWEM.


The Beacon Packet Content of the StenSat Satellite is The most recent science packet.


The Data Relay Services Start of the ExoMars Trace Gas Orbiter Orbiter is 2023.


The Principal Investigator of the Cluster S/C Satellite is A. Balogh.


The Image Orientation of the CaSSIS Instrument is North is up.


The Temporal Resolution of the Visible Spectral Band Spectral Band is 30 minutes (frame time).


The Radiation Exposure of the O/OREOS Satellite is Unknown.


The Developer of the NorSat-3 Satellite is FFI in collaboration with Kongsberg Seatex.


The Mid-tropospheric CO2 Measurements per Day of the AIRS Satellite is About 15,000.


The Magnetic Field Behavior of the Comet 67P Comet is Became stronger and more turbulent when the forming bow shock washed over Rosetta.


The Geographic Region of Interest of the ZACUBE-2 Satellite is Southern African coastal regions.


The Signal Frequency of the Clementine Satellite is 2.273 GHz.


The Pavement Temperature of the ECOSTRESS Instrument is Exceeded 122 F (50 C).


The Senior Review Date of the Heliophysics Operating Missions Satellite is June 11, 2015.


The Mission of the MMS Satellite is Magnetospheric Multiscale Mission.


The Number of Orbits of the Envisat Satellite is 10,000.


The Direction of the Spool Deployment System is Counterclockwise.


The Launch Date of the VIIRS Sensor is Oct. 28, 2011.


The Launch Date of the Intelsat 20 Communication Satellite is August 2, 2012.


The Pixel Size (km x km) of the Antenna Reflector is 11.


The Interface Module of the Non-SPA COTS components Components is ASIM (Appliqué Specific Interface Module).


The Hardware Source of the TBIRD Satellite is Existing commercial, telecommunications hardware products.


The Battery Discharge of the Integral Satellite is The first estimates of the charge remaining before blackout and the loss of the satellite was just three hours.


The Event Date of the ALOS Data Utilization is Dec. 5-7, 2006.


The Field of View of the Optical Head Optical Device is 94º x 81º (1-hole mask).


The Public Data Release Date of the Global Precipitation Measurement (GPM) Mission Satellite Mission is Unknown.


The Orbit Determination Accuracy of the GF-3 Satellite Satellite is 4 cm.


The Voltage of the MTM main power bus Power Bus is 28 V.


The Wavelength Bandpass of the UVS Instrument Spectrometer Telescope is 1:3.8 (cha. 1); 2:3.7 (cha. 2).


The Launch Date of the SARah-1 Earth Observation Satellite is 13 June 2022.


The Black Hole Mass of the OJ 287 galaxy Galaxy is Over 18 billion times the mass of our Sun.


The Developer of the PLEGPAY Instrument is Thales Alenia Space.


The Spin of the ICU Container is 1 to 10 rpm.


The Mass of the Hodoyoshi-4 Microsatellite is 65 kg.


The Internal Average Temperature of the SVM Service Module is 15°C.


The Distance Range of the MCAM-2 Camera is 920 km – 6099 km.


The URL of the XMM-Newton Satellite is http://sci.esa.int/xmm-newton/60950-from-gamma-rays-to-x-rays-new-method-pinpoints-previously-unnoticed-pulsar-emission/.


The Roll Maneuvers of the RapidEye Satellite Constellation is ±20º.


The Communication Links of the SSR Satellite Subsystem is UART link to OIM module, high speed differential LVDS links to XBT subsystem and IRIS and PPU payloads.


The Deployment System Material of the LFSA Photovoltaic Solar Array System is Shape Memory Alloys (SMA).


The Prime Contractor for B series of the MetOp-SG Satellite Program is Airbus Defence and Space of Germany.


The Mission Purpose of the SPORT CubeSat is Understand the preconditions leading to equatorial plasma bubbles.


The Hibernation Duration of the Rosetta Spacecraft is 31 months.


The Number of Earth Stations of the LAGEOS Satellite is 14.


The Operational Countries of the JJ-FAST Forest Early Warning System is 77.


The Beam width of the VIS (red) Band is 3.4 µrad.


The Video Camera Assembly of the LAPAN-A2 Satellite is COTS (Commercial-of-the-Shelf) RGB medium format video camera.


The Radiometric Accuracy of the Calibration Techniques Satellite Instrument Calibration is Specified.


The Instrument Type of the SkySat Constellation Satellite Constellation is High resolution optical imagers.


The URL of the Hayabusa 2 Project Mission is https://web.archive.org/web/20120222130748/http://b612.jspec.jaxa.jp/hayabusa2/e/hayabusa2_e.html.


The Spectral Bands of the HyperScout Hyperspectral Imager is 45 visible and near-infrared.


The Water Ice Concentration Useful Quantity of the Lunar Flashlight Spacecraft is 0.5 wt%.


The Printed Circuit Board Area of the Sprite Tiny Spacecraft is 3.5 by 3.5 cm.


The Components of the ERA Robotic Arm is Two end effectors, two wrists, two limbs, one elbow joint, electronics, and cameras.


The Delegated Regulation Date of the GMES-S Satellite is December 2013.


The Resolution of the Interferometric Wide Swath mode (IWS) Operational Mode is 5 m x 20 m.


The Projected Payload Capacity of the Terran R Launch Vehicle is In the same class as SpaceX’s Falcon 9.


The G/T of the System Communication System is Unknown.


The Fuel Supply of the TSX (TerraSAR-X) Satellite is Until at least 2026.


The Pixel Offset of the Band-64 Satellite Instrument is 34 pixels out of 256 pixels.


The Launch Date of the JPL-Built Earth Science Experiment Earth Science Experiment is Nov. 2, 2011.


The Input and Output of the CCD (Charge-Coupled Device) Imaging Device is LVDS (Low Voltage Differential Signaling).


The Observation Purpose of the TARANIS Microsatellite is To observe luminous, radiative and electromagnetic phenomena occurring at altitudes of 20 to 100 km over thunderstorms.


The Data Inputs of the Front End Electronics Electronics is 5.


The Power Efficiency of the VGT-P Instrument is Required to be very efficient in its power use.


The Pointing Knowledge of the DSP satellites Satellite is <0.5º.


The End of Life Date of the FORUM Satellite is December 2031.


The Mission Start Date of the SMOS Satellite is Unknown.


The Launch Date of the FORUM Satellite is July 2027.


The Revisit Time of the BlackSky's Satellites Microsatellites is Every 30 minutes.


The Swath of the Radar Radar is > 1000 km.


The Mass of the COSAC Evolved Gas Analyzer is 4.9 kg.


The Conference Date of the CubeSat Laser Communication Crosslink Pointing Demonstration Satellite Communication System is August 3-8, 2019.


The Systems of the WIND Satellite is Equipped with heavy shielding and double-redundant systems.


The Detection Energy of the CZTI Instrument is Greater than about 60 keV.


The Spatial Resolution of the WiFS camera Camera is 188 m.


The Orientation of the Magnetic Field Sensor Sensor is Four different orientations.


The Launch Date of the SPOT-1 Satellite is February 1986.


The Number of Extragalactic Sources of the Gaia EDR3 Satellite Data is More than 1.6 million.


The Telescope Mirror Diameter of the Euclid Spacecraft is 1.2 m.


The Closest Approach Time of the BepiColombo Spacecraft is 23:34:41 UTC.


The Cooling Method of the Chamber with a heat exchanger Air Ventilation System is Direct contact to the base plate of the payload compartment.


The Resolution of the TeLEOS-1 Satellite is Down to one-meter.


The Deployment Date of the EURECA Satellite is Aug. 2, 1992.


The Maximum Capacity of the DSU Data Storage Unit is Up to 8 Tbit at EOL.


The Red-IR/UV Ratio of the Tatiana-2 Satellite is Varies.


The Mass of the Cabling/harness Satellite Subsystem is 0.1 kg.


The Data Rate (max) of the TXS S-band Transmitter/Transceiver is 100 kbit/s.


The Power of the Rate gyro Sensor is 1.4 W.


The Frequency Tracking of the Phoenix GPS Receivers GPS Receiver is Single-frequency.


The Alignment of the Spacecraft Satellite is Nominally aligned with the instrument LoS.


The Phase Angle of the JL-1-GF03D Microsatellite is 120º.


The Launch Vehicle of the Meteosat-1 Satellite is Thor-Delta.