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214 results for “spacecrafts”
MMS 3 Active Spacecraft Potential Control (ASPOC), Sensors 1 and 2, Level 2 (L2), Survey Mode, 1 s Data
MMS 3 Active Spacecraft Potential Control (ASPOC) - Sensors 1 and 2 Ion Beam Current Rates, Beam Energies, and Instrument Status variables. In tenuous plasma regions, the floating potential of a sunlit spacecraft is positively charged, reaching up to tens of Volts. The corresponding electric field disturbs the ambient plasma measurements obtained from electron and ion sensors and the large fluxes of attracted photo-electrons can significantly reduce the lifetime of the micro-channel plate. The electric field measurements can be also contaminated by the high spacecraft potential values. The Active Spacecraft Potential Control neutralizes the spacecraft potential by releasing positively charged Indium ions. The ASPOCs neutralize the electrical potential of the spacecraft, limiting or eliminating spurious electric fields that can contaminate measurements. This allows observations of the more scientifically important low-energy ions and electrons.
Polar Definitive Orbit, 1 min Data, Spacecraft Position and Velocity in GCI, GSE, GSM, and HEC Coordinates
Polar Definitive Orbit, Spacecraft Position and Velocity in Geocentric Celestial Inertial, GCI, Geocentric Solar Ecliptic, GSE, Geocentric Solar Magnetospheric, GSE, Heliospheric Ecliptic, HEC, Coordinates
THEMIS-D (P3), Electric Field Instrument (EFI) Spacecraft measured Electric Field
THEMIS-D: Electric Field Instrument, EFI, Electric Field Measurements. The L2 Product is a 3D Estimate of the perpnedicular Electric Field, Eperp, derived from the Spin Plane E-Field Measurements assuming E ⋅ B = 0, using relevant Flux-Gate Magnetometer, FGM, Data. This Data Product includes Spin-Averaged, and Fast Survey Field Data. The Spin-Averaged Data, EFS_DOT0, has approximately 3 s Time Resolution. Fast Survey, EFF_DOT0, Data has 0.125 s Time Resolution.
Wind Magnetic Fields Instrument (MFI) Magnetic Field Vector and Spacecraft Position, Key Parameter (K0), 92 s Data
Wind Magnetic Fields Investigation, MFI, Key Parameter magnetic field data in GSE and GSM coordinates.References:* 1. Panetta P, GSFC, GGS Wind MFI Operators Manual, September 15, 1992.* 2. Computer Sciences Corporation, Data Format Control Document, DFCD, between the International Solar-Terrestrial Physics, ISTP, program information investigators, CSC/TR-91/6014, 560-1DFD/0190, July 1992.* 3. Behannon, K.W., International Solar Terrestrial Physics, ISTP, program investigator data analysis requirements for Wind and Geotail spacecraft magnetometer experiment, September 1987.
Microbiomes of the Dust Particles Collected from the International Space Station and Spacecraft Assembly Facilities
The safety of the International Space Station (ISS) crewmembers and maintenance of ISS hardware are the primary rationale for monitoring microorganisms in this closed habitat. The composition of the microbial community of this built environment is unique due to microgravity, space radiation, and elevated carbon dioxide levels. As built environments are known to have their own microbiomes, next-generation sequencing methods have to be utilized to explore the ISS microbial profile, and use this data for further development of safety and maintenance practices. ISS vacuum cleaner bag components (surface) and vacuum cleaner bag components of two cleanrooms at Jet Propulsion Laboratory (JPL, Pasadena, CA) were examined. 16S rRNA gene and ITS sequencing based on the 454 platform was used to elucidate the ISS microbial diversity and explore differences between the microbiomes of the ISS and Earth-based cleanrooms.
THEMIS-A (P5), Electric Field Instrument (EFI) Spacecraft measured Electric Field
THEMIS-A: Electric Field Instrument, EFI, Electric Field Measurements. The L2 Product is a 3D Estimate of the perpnedicular Electric Field, Eperp, derived from the Spin Plane E-Field Measurements assuming E ⋅ B = 0, using relevant Flux-Gate Magnetometer, FGM, Data. This Data Product includes Spin-Averaged, and Fast Survey Field Data. The Spin-Averaged Data, EFS_DOT0, has approximately 3 s Time Resolution. Fast Survey, EFF_DOT0, Data has 0.125 s Time Resolution.
LP MOON SPACECRAFT EPHEMERIS V1.0
The Lunar Prospector ephemeris data set consists of spacecraft position and velocity determinations as a function of time in Moon-centered, Earth equator, mean of J2000 coordinates. Tracking data collected by ground stations are used by the Goddard Flight Dynamics Analysis Branch (FDAB) to compute the Lunar Prospector orbit ephemeris. The Level 0 Data archive contains the ephemeris type known as the 'definitive ephemeris', which is based on an updated lunar gravity model [FDAB1997].
MMS 4 Active Spacecraft Potential Control (ASPOC), Sensors 1 and 2, Level 2 (L2), Survey Mode, 1 s Data
MMS 4 Active Spacecraft Potential Control (ASPOC) - Sensors 1 and 2 Ion Beam Current Rates, Beam Energies, and Instrument Status variables. In tenuous plasma regions, the floating potential of a sunlit spacecraft is positively charged, reaching up to tens of Volts. The corresponding electric field disturbs the ambient plasma measurements obtained from electron and ion sensors and the large fluxes of attracted photo-electrons can significantly reduce the lifetime of the micro-channel plate. The electric field measurements can be also contaminated by the high spacecraft potential values. The Active Spacecraft Potential Control neutralizes the spacecraft potential by releasing positively charged Indium ions. The ASPOCs neutralize the electrical potential of the spacecraft, limiting or eliminating spurious electric fields that can contaminate measurements. This allows observations of the more scientifically important low-energy ions and electrons.
LP MOON SPACECRAFT ATTITUDE V1.0
The Lunar Prospector attitude data set consists of values for the spacecraft spin rate and spin axis orientation (attitude) as a function of time. These values are determined from spacecraft attitude data (sun and limb crossing sensors) and ephemeris data. Spacecraft orientations are given as right ascension and declination of the spacecraft spin axis in the Mean-of-J2000 Ecliptic reference frame. The attitude data set consists of a single, cumulative file for the entire mission. Records are added to this file following each significant change in either the spin rate or spin axis orientation. The spacecraft spin rates and attitudes in this data set are orbit averages. The instantaneous spin rate can be determined from the sun pulse data set. The instantaneous spin rate varies as the spacecraft passes into and out of the Moon's shadow and after each spacecraft maneuver. Generally, an attitude record is included for times immediately before and after each maneuver.
Wind Definitive Orbit, 10 min Data, Spacecraft Position and Velocity in GCI, GSE, GSM, HEC, and HG Coordinates
Wind Definitive Orbit, Spacecraft Position and Velocity in Geocentric Celestial Inertial, GCI, Geocentric Solar Ecliptic, GSE, Geocentric Solar Magnetospheric, GSM, Heliospheric Ecliptic, HEC, and Heliographic, HG, Coordinates
PSP FIELDS Fluxgate Magnetometer (MAG) Magnetic Field Vectors, Spacecraft, SC, Coordinates, Level 2 (L2), 1 min Data
Parker Solar Probe FIELDS Instrument Suite Fluxgate Magnetometer, MAG, Data: The time resolution of the MAG time series data varies with instrument mode ranging from 2.289 samples/s to 292.9 samples/s. These two data sampling rates corresponding to 2 samples or 256 samples per 0.874 s where 0.874 s is equal to 2^25 divided 38.4 MHz. See reference [2] for a complete explanation of the MAG instrument sampling methodology. The Magnetometer has four ranges: ±1024 nT, ±4096 nT, ±16,384 nT, and ±65,536 nT. The Magnetometer Range is selected by an algorithm based on the strength of the ambient magnetic field. The magnetic field measurement precision is ±15 bits, based on the 16-bit Analog to Digital Converter, ADC.References:* 1. Fox, N.J., Velli, M.C., Bale, S.D. et al. Space Sci Rev (2016) 204: 7. https://doi.org/10.1007/s11214-015-0211-6* 2. Bale, S.D., Goetz, K., Harvey, P.R. et al. Space Sci Rev (2016) 204: 49. https://doi.org/10.1007/s11214-016-0244-5
LP MOON SPACECRAFT TRAJECTORY V1.0
Trajectory data for the Lunar Prospector spacecraft in Selenographic, SSE, GSE, and GSM coordinates. Dataset covers dates 1998-01-16 to 1999-07-29.
THEMIS-E (P4), Electric Field Instrument (EFI) Spacecraft measured Electric Field
THEMIS-E: Electric Field Instrument, EFI, Electric Field Measurements. The L2 Product is a 3D Estimate of the perpnedicular Electric Field, Eperp, derived from the Spin Plane E-Field Measurements assuming E ⋅ B = 0, using relevant Flux-Gate Magnetometer, FGM, Data. This Data Product includes Spin-Averaged, and Fast Survey Field Data. The Spin-Averaged Data, EFS_DOT0, has approximately 3 s Time Resolution. Fast Survey, EFF_DOT0, Data has 0.125 s Time Resolution.
TWINS-2 Ephemeris, Definitive Spacecraft Attitude, PT0.512S Data
Two Wide-angle Imaging Neutral-atom Spectrometers 2, TWINS 2, Spacecraft Attitude data, Earth Centered Inertial, ECI, coordinates. This TWINS data set contains spacecraft attitude data as polar and azimuthal instrument pointing vectors. The polar vector points along the TWINS rotation axis. The azimuthal vector lies in the plane normal to the polar vector and points toward the central scanning position, which is defined as the zero-point location. Such pointing is derived from both the spacecraft attitude history, SAH, file and the sensor mounting orientation. The computation employed is designed to achieve a pointing accuracy of 0.5°. Any deviation from this accuracy level is indicated in the header record metadata.
PSP FIELDS Fluxgate Magnetometer (MAG) Magnetic Field Vectors, Spacecraft, SC, Coordinates, Full Resolution, Level 2 (L2), 3.413 ms Data
Parker Solar Probe FIELDS Instrument Suite Fluxgate Magnetometer, MAG, Data: The time resolution of the MAG time series data varies with instrument mode ranging from 2.289 samples/s to 292.9 samples/s. These two data sampling rates corresponding to 2 samples or 256 samples per 0.874 s where 0.874 s is equal to 2^25 divided 38.4 MHz. See reference [2] for a complete explanation of the MAG instrument sampling methodology. The Magnetometer has four ranges: ±1024 nT, ±4096 nT, ±16,384 nT, and ±65,536 nT. The Magnetometer Range is selected by an algorithm based on the strength of the ambient magnetic field. The magnetic field measurement precision is ±15 bits, based on the 16-bit Analog to Digital Converter, ADC.References:* 1. Fox, N.J., Velli, M.C., Bale, S.D. et al. Space Sci Rev (2016) 204: 7. https://doi.org/10.1007/s11214-015-0211-6* 2. Bale, S.D., Goetz, K., Harvey, P.R. et al. Space Sci Rev (2016) 204: 49. https://doi.org/10.1007/s11214-016-0244-5
STEREO-A In-Situ Measurements of Particles and CME Transients (IMPACT) Fluxgate Magnetometer (MAG) Burst Mode, Magnetic Field Vector, Spacecraft (SC) Coordinates, Level 1 (L1), 31 ms Data
This data product contains Level 1 0.03125-s or 32 Hz burst-mode values of solar wind magnetic field data measured by the IMPACT Magnetometer on STEREO-A in Spacecraft, SC, coordinates.
MMS 1 Active Spacecraft Potential Control (ASPOC), Sensors 1 and 2, Level 2 (L2), Survey Mode, 1 s Data
MMS 1 Active Spacecraft Potential Control (ASPOC) - Sensors 1 and 2 Ion Beam Current Rates, Beam Energies, and Instrument Status variables. In tenuous plasma regions, the floating potential of a sunlit spacecraft is positively charged, reaching up to tens of Volts. The corresponding electric field disturbs the ambient plasma measurements obtained from electron and ion sensors and the large fluxes of attracted photo-electrons can significantly reduce the lifetime of the micro-channel plate. The electric field measurements can be also contaminated by the high spacecraft potential values. The Active Spacecraft Potential Control neutralizes the spacecraft potential by releasing positively charged Indium ions. The ASPOCs neutralize the electrical potential of the spacecraft, limiting or eliminating spurious electric fields that can contaminate measurements. This allows observations of the more scientifically important low-energy ions and electrons.
LP MOON SPACECRAFT POSITION V1.0
The Lunar Prospector spacecraft position data set consists of spacecraft position determinations in selenographic latitude, longitude, and altitude coordinates in one minute intervals. The data set also contains spacecraft velocity and distance from the center of the Moon as a function of time. The coordinate system is selenographic with east longitude positive. The data set is generated by the Goddard Flight Dynamics Analysis Branch.
PSP FIELDS Fluxgate Magnetometer (MAG) Magnetic Field Vectors, Spacecraft, SC, Coordinates, 4 samples/cycle, Level 2 (L2), 3.413 ms Data
Parker Solar Probe FIELDS Instrument Suite Fluxgate Magnetometer, MAG, Data: The time resolution of the MAG time series data varies with instrument mode ranging from 2.289 samples/s to 292.9 samples/s. These two data sampling rates corresponding to 2 samples or 256 samples per 0.874 s where 0.874 s is equal to 2^25 divided 38.4 MHz. See reference [2] for a complete explanation of the MAG instrument sampling methodology. The Magnetometer has four ranges: ±1024 nT, ±4096 nT, ±16,384 nT, and ±65,536 nT. The Magnetometer Range is selected by an algorithm based on the strength of the ambient magnetic field. The magnetic field measurement precision is ±15 bits, based on the 16-bit Analog to Digital Converter, ADC.References:* 1. Fox, N.J., Velli, M.C., Bale, S.D. et al. Space Sci Rev (2016) 204: 7. https://doi.org/10.1007/s11214-015-0211-6* 2. Bale, S.D., Goetz, K., Harvey, P.R. et al. Space Sci Rev (2016) 204: 49. https://doi.org/10.1007/s11214-016-0244-5
THEMIS-C (P2/ARTEMIS-P2), Electric Field Instrument (EFI) Spacecraft measured Electric Field
THEMIS-C: Electric Field Instrument, EFI, Electric Field Measurements. The L2 Product is a 3D Estimate of the perpnedicular Electric Field, Eperp, derived from the Spin Plane E-Field Measurements assuming E ⋅ B = 0, using relevant Flux-Gate Magnetometer, FGM, Data. This Data Product includes Spin-Averaged, and Fast Survey Field Data. The Spin-Averaged Data, EFS_DOT0, has approximately 3 s Time Resolution. Fast Survey, EFF_DOT0, Data has 0.125 s Time Resolution.
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Allen Brain Atlas
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Annotated Behaviour and Observability Dataset (ABODe)
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DANDI Archive for NWB datasets
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International Brain Laboratory public data
The International Brain Laboratory public data releases expose standardized mouse decision-making experiments, including Neuropixels recordings, widefield calcium imaging, behavior, and session metadata accessed through the ONE API.
OpenNeuro
OpenNeuro is a free, open platform for sharing neuroimaging datasets, with public search, dataset pages, and download paths for web, S3, DataLad, and the OpenNeuro CLI.