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MMS 3 Electric Double Probe (EDP) Spacecraft Potential, Level 2 (L2), Fast Mode, 31.25 ms Data

Electric Double Probe, Dual Probe Spacecraft Potential, Level 2, Fast Survey Data. Spacecraft potential is etstimatrd by averaging measurements of the probe-to-spacecraft potential from several probes.

STEREO-B In-Situ Measurements of Particles and CME Transients (IMPACT) Fluxgate Magnetometer (MAG) Magnetic Field Vectors, in Spacecraft (SC) Coordinates

STEREO Behind In-situ Measurements of Particles and CME Transients, IMPACT, Magnetometer Instrument, MAG, Magnetic Field Vectors, Level 1 Data

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Spacecraft Material Outgassing Data

This compilation of outgassing data of materials intended for spacecraft use were obtained at the Goddard Space Flight Center (GSFC), utilizing equipment developed at Stanford Research Institue (SRI) under contract to the Jet Propulsion Laboratory (JPL). SRI personnel developed an apparatus for determining the mass loss in vacuum and for collecting the outgassed products. Their report (Reference 1), which contained data from June 1964 to August 1967, served well as a foundation for selecting spacecraft materials with low outgassing properties. The apparatus was also constructed at GSFC and, based on the SRI data and GSFC data, a GSFC report (Reference 2) was published. That report included data for those materials meeting two criteria: a maximum total mass loss (TML) of 1.0 percent and maximum collected volatile condensable material (CVCM) of 0.10 percent. After a series of tests and verification of procedures, an American Society for Testing and Materials (ASTM) Standard Test Method was developed, based upon this apparatus. The method, 'Total Mass Loss (TML) and Collected Volatile Condensable Materials (CVCM) from Outgassing in a Vacuum Environment,' is identified as E 595-77/84/90. The data developed through the years have been reported in References 3, 4, 5, 6, 7, 8, and 9 as a means of assisting in selecting materials for space flight use.

ACE Electron Proton Alpha Monitor (EPAM) LEFS150 MFSA, Spacecraft Frame, Sectored Z>1 Ion Fluxes, 17 min Averages

17-min-averaged sectored Z>1 ion fluxes from the MF Spectrum Analyzer of the ACE/EPAM LEFS150 instrument. All energies thresholds take into account the incident particle type, shielding, and inactive dead-layer of the solid state detector. All fluxes are background corrected and are in the spacecraft rest frame.

ACE Electron Proton Alpha Monitor (EPAM) LEMS120 MFSA, Spacecraft Frame, Sectored Proton Fluxes, Hourly Averages

Hourly-averaged sectored proton fluxes from the MF Spectrum Analyzer of the ACE/EPAM LEMS120 instrument. All energies thresholds take into account the incident particle type, shielding, and inactive dead-layer of the solid state detector. All fluxes are background corrected and are in the spacecraft rest frame.

ACE Electron Proton Alpha Monitor (EPAM) LEMS30 MFSA, Spacecraft Frame, Sectored Proton Fluxes, Hourly Averages

Hourly-averaged sectored proton fluxes from the MF Spectrum Analyzer of the ACE/EPAM LEMS30 instrument. All energies thresholds take into account the incident particle type, shielding, and inactive dead-layer of the solid state detector. All fluxes are background corrected and are in the spacecraft rest frame.

ACE Electron Proton Alpha Monitor (EPAM) LEFS/LEMS MFSA, Spacecraft Frame, Spin-Averaged Electron Fluxes, 17 min Averages

17-min-averaged electron fluxes from the MF Spectrum Analyzer of the ACE/EPAM instrument. All energies thresholds take into account the incident particle type, shielding, and inactive dead-layer of the solid state detector. All fluxes are background corrected and are in the spacecraft rest frame.

ACE Electron Proton Alpha Monitor (EPAM) LEFS60 MFSA, Spacecraft Frame, Sectored Proton Fluxes, Hourly Averages

Hourly-averaged sectored proton fluxes from the MF Spectrum Analyzer of the ACE/EPAM LEFS60 instrument. All energies thresholds take into account the incident particle type, shielding, and inactive dead-layer of the solid state detector. All fluxes are background corrected and are in the spacecraft rest frame.

ACE Electron Proton Alpha Monitor (EPAM) LEFS/LEMS MFSA, Spacecraft Frame, Spin-Averaged Z>1 Ion Fluxes, Daily Averages

Daily-averaged ion fluxes from the MF Spectrum Analyzer of the ACE/EPAM instrument. All energies thresholds take into account the incident particle type, shielding, and inactive dead-layer of the solid state detector. All fluxes are background corrected and are in the spacecraft rest frame.

MMS 1 Electric Double Probe (EDP) Spacecraft Potential, Level 2 (L2), Burst Mode, 0.1220703125 ms Data

Electric Double Probe, Dual Probe Spacecraft Potential, Level 2, Burst Mode Data. Spacecraft potential is etstimatrd by averaging measurements of the probe-to-spacecraft potential from several probes.

ACE Electron Proton Alpha Monitor (EPAM) LEFS/LEMS MFSA, Spacecraft Frame, Spin-Averaged Proton Fluxes, Daily Averages

Daily-averaged proton fluxes from the MF Spectrum Analyzer of the ACE/EPAM instrument. All energies thresholds take into account the incident particle type, shielding, and inactive dead-layer of the solid state detector. All fluxes are background corrected and are in the spacecraft rest frame.

Polar Electric Fields Instrument (EFI), 6-sec Electric Field in Despun Spacecraft Coordinates

This set of data from the Polar EFI (Electric Field Instrument) contains two electric field components on the spin plane in despun spacecraft coordinates at 6-sec intervals.

ACE Electron Proton Alpha Monitor (EPAM) LEFS60 MFSA, Spacecraft Frame, Sectored Electron Fluxes, 17 min Averages

17-min-averaged sectored electron fluxes from the MF Spectrum Analyzer of the ACE/EPAM LEFS60 instrument. All energies thresholds take into account the incident particle type, shielding, and inactive dead-layer of the solid state detector. All fluxes are background corrected and are in the spacecraft rest frame.

Polar Electric Fields Instrument (EFI), Spacecraft Attitude in GSE coordinates

the Polar spacecraft positive spin axis direction vector (normalized to magnitude 1), in GSE coordinates.

ACE Electron Proton Alpha Monitor (EPAM) LEFS150 MFSA, Spacecraft Frame, Sectored Proton Fluxes, Daily Averages

Daily-averaged sectored proton fluxes from the MF Spectrum Analyzer of the ACE/EPAM LEFS150 instrument. All energies thresholds take into account the incident particle type, shielding, and inactive dead-layer of the solid state detector. All fluxes are background corrected and are in the spacecraft rest frame.

MMS 2 Electric Double Probe (EDP) Spacecraft Potential, Level 2 (L2), Burst Mode, 0.1220703125 ms Data

Polar Electric Fields Instrument (EFI), Spacecraft Potential and Plasma Density, Spin Resolution

This data consists of the Spacecraft Potential and the Plasma Density, at spacecraft spin resolution, where the Plasma Density is obtained as a function, provided by Dr. Jack Scudder, the PI of the POLAR Hydra investigation. This function was determined by a fit to the POLAR Hydra particle data for 2001/04/01. The relative accuracy of the Plasma Density, estimated from the spacecraft potential on short time scales is ~10-30% depending on plasma conditions. The absolute accuracy is better than a factor of two for densities less than about 20 particles/cm^3. Density values greater than 30 particles/cm^3 are not plotted because they are inaccurate due to the steep slope of the curve of density versus spacecraft potential. If the value of the argument to the function is too large, then the Plasma Density is set to a filler value of 1.0e+20. Also, if the value returned by the function is too large, then the result is not reliable, and therefore the Plasma Density is set to a filler value of 1.0e+20. If the value of the argument to the function is too small, then the Plasma Density is set to a filler value of 1.0e-20. So, a value of the Plasma Density is a filler value if and only if it is either larger than 1.0e+2 (100.0) or smaller than 1.0e-4 (0.0001); otherwise, it is a true value. Note that all values of the Spacecraft Potential are true values. There is no filler.

MMS 3 Electric Double Probe (EDP) Spacecraft Potential, Level 2 (L2), Slow Mode, 0.125 s Data

Electric Double Probe, Dual Probe Spacecraft Potential, Level 2, Slow Survey Data. Spacecraft potential is etstimatrd by averaging measurements of the probe-to-spacecraft potential from several probes.

TWINS-1 Ephemeris, Definitive Spacecraft Attitude, PT0.512S Data

Two Wide-angle Imaging Neutral-atom Spectrometers 1, TWINS 1, 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.