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1) AMPTE/CCE Spin-averaged Magnetic Field Measurements maxmize
Resource ID:spase://VMO/NumericalData/AMPTE_CCE/MFE/PT5.83S
Start:1984-08-20 23:59:54 Observatory:AMPTE/CCE Cadence:5.83 seconds
Stop:1989-01-09 23:59:34 Instrument:AMPTE/CCE Magnetic Field Experiment (MFE) Resource:NumericalData
AMPTE/CCE spin-averaged DC magnetic field at ~5.83 second resolution.

2) AMPTE/IRM Magnetic Field maxmize
Resource ID:spase://VMO/NumericalData/AMPTE_IRM/MAG/PT4.4S
Start:1984-08-21 00:48:41 Observatory:AMPTE/IRM Cadence:4.4 seconds
Stop:1986-08-11 21:45:07 Instrument:AMPTE/IRM Magnetometer Resource:NumericalData
AMPTE/IRM spin-averaged magnetic field at ~4.4 second resolution.

3) AMPTE/IRM Plasma Data maxmize
Resource ID:spase://VMO/NumericalData/AMPTE_IRM/Plasma/PT4.4S
Start:1984-08-22 12:58:03 Observatory:AMPTE/IRM Cadence:4.4 seconds
Stop:1986-08-11 21:32:28 Instrument:AMPTE/IRM Plasma Instrument Resource:NumericalData
AMPTE/IRM spin-averaged plasma moments at ~4.4 second resolution.

4) CRRES Ephemeris Information maxmize
Resource ID:spase://VMO/NumericalData/CRRES/Ephemeris/PT5M
Start:1990-10-11 00:00:00 Observatory:CRRES Cadence:5 minutes
Stop:1991-10-13 00:00:00 Instrument:CRRES Spacecraft Position Resource:NumericalData
This data set contains orbital information from the CRRES spacecraft. The ephemeris data is at 5 min resolution. The files include the magnetic coordinates, spacecraft radial locaton, the L shell information, the spacecraft position in ECI coordinates, and the northern and southern hemisphere foot print location in geographic latitutde and longitude coordinates at 100 km in altitude.

5) Cluster Auxiliary Data maxmize
Resource ID:spase://VMO/NumericalData/Cluster/Ephemeris/SummaryParameter/PT1M
Start:2000-08-22 00:00:30 Observatory:Cluster FM5 (Rumba) Cadence:1 minute
Stop:2014-08-01 01:01:11 Instrument:Cluster-Rumba Positions Resource:NumericalData
Cluster Auxiliary Parameters are produced by the Cluster Hungarian Data Center in Budapest. These data are the primary orbit product supplied to users by the Cluster Active Archive. The data contain Position, Velocity and Attitude of four Cluster spacecraft. For additional details on the methodology behind these data see: Robert P., et al., "Tetrahedron Geometric Factors", p. 328, Analysis Methods of Multi-Spacecraft Data, ed. G. Paschmann and P. Daly, 1998, ESA and the International Space Institute, Bern.

6) Double Star 1 Spacecraft Auxiliary Summary Parameters Data maxmize
Resource ID:spase://VMO/NumericalData/DoubleStar1/Ephemeris/SummaryParameters/60S
Start:2004-01-05 00:00:30 Observatory:Double Star 1 Cadence:60 seconds
Stop:2007-09-19 23:59:30 Instrument:Double Star 1 Spacecraft Position Resource:NumericalData
The Double Star 1 auxiliary summary parameter data set contains various parameters in GSE coordinates at 60 s resolution. These parameters include universal time, orbit number, GSE position, GSE spacecraft velocity vector, longitude, and dipole tilt. These parameters are available through Double Star Science Data Centre The Data Ring with restricted access.

7) Double Star 2 Spacecraft Auxiliary Summary Parameters Data maxmize
Resource ID:spase://VMO/NumericalData/DoubleStar2/Ephemeris/SummaryParameters/60S
Start:2004-07-27 00:00:30 Observatory:Double Star 2 Cadence:60 seconds
Stop:2008-06-30 23:59:30 Instrument:Double Star 2 Spacecraft Position Resource:NumericalData
The Double Star 2 auxiliary summary parameter data set contains various parameters in GSE coordinates at 60 s resolution. These parameters include universal time, orbit number, GSE position, GSE spacecraft velocity vector, longitude, and dipole tilt. These parameters are available through Double Star Science Data Centre The Data Ring with restricted access.

8) DE1 8 sec Position Data maxmize
Resource ID:spase://VWO/NumericalData/DynamicsExplorer1/Ephemeris/PT8S
Start:1981-09-16 05:21:48 Observatory:Dynamics Explorer 1 Cadence:8 seconds
Stop:1984-06-28 20:35:55 Instrument:DynamicsExplorer1 Positions Resource:NumericalData
Two Dynamics Explorer (DE) spacecraft were launched August 3, 1981, and placed into coplanar polar orbits with DE-1 in a highly elliptical orbit and DE-2 in a lower more circular orbit. The primary objective of the DE program was to investigate magnetosphere-ionosphere-atmosphere coupling processes. The DE mission provided a wealth of new information on a wide variety of magnetospheric plasma wave phenomena including auroral kilometric radiation, auroral hiss, Z mode radiation, narrow-band electromagnetic emissions associated with equatorial upper hybrid waves, whistler mode emissions, wave-particle interactions stimulated by ground VLF transmitters, equatorial ion cyclotron emissions, ion Bernstein mode emissions, and electric field turbulence along the auroral field lines. These files contain 8 second resolution emphemeris and spacecraft attitude parameters that coincide with DE-1 telemetry frames containing PWI lowrate data. These parameters are not to be taken as an authoritative set, but are convenient when working with PWI science data products. Most of these data are provided in the Geocentric Equatorial Inertial (GEI) TOD reference frame. The Z axis of the GEI frame is parallel to Earth's spin axis; the X axis points towards the First Point of Aries with the Y axis aligned so as to generate a right-handed coordinate system.

9) FAST Spacecraft Positions maxmize
Resource ID:spase://VMO/NumericalData/FAST/Ephemeris/PT1M
Start:1996-01-26 00:00:00 Observatory:FAST Cadence:1 minute
Stop:2011-12-31 00:00:00 Instrument:FAST Position Resource:NumericalData
FAST Positions

10) GOES 10 high-resolution magnetometer data maxmize
Resource ID:spase://VMO/NumericalData/GOES/10/MAG/PT0.512S
Start:2006-12-31 23:59:58 Observatory:GOES 10 Cadence:0.512 seconds
Stop:2008-12-31 23:59:58 Instrument:GOES 10, Triaxial Fluxgate Magnetometer Resource:NumericalData
GOES 10 magnetic field data at 0.512 second time resolution. The vector magnetic field is given in the spacecraft (s/c) earth-referenced coordinate system: Hp, He, Hn, and Ht, where Hp is perpendicular to the satellite orbital plane, or parallel to Earth's spin axis in the case of a zero degree inclination orbit; He is perpendicular to Hp and directed earthwards; Hn is perpendicular to both Hp and He and directed eastwards; and Ht is the total field. This data product also provides GOES 10 satellite positions and velocities derived from SSCWEB GEI ephemeris, interpolated to one minute time resolution. The magnetometer data are downlinked from the spacecraft in real-time to the NOAA Space Weather Prediction Center (SWPC) in Boulder, CO. The data from the raw Command and Data Acquisition (CDA) telemetry stream are processed by pre-processors at SWPC and from there 1-minute averages are distributed to SWPC Space Weather Operations, as well a archived at NOAA?s National Geophysical Data Center (NGDC) and NASA?s Coordinated Data Analysis Web (http://cdaweb.gsfc.nasa.gov/). The raw high-resolution data are corrected and processed at NOAA?s SWPC, and later archived at NGDC. The major issue for processing the high-resolution data is correction for the magnetic signature of spacecraft torquer currents as briefly discussed in the magnetometer instrument descriptions. In normal operation, the magnetometer samples its three axes every 0.512 seconds, synchronized with the telemetry frames. The magnetometer has an anti-aliasing low-pass filter on each axis. As part of the attitude control on the spacecraft, there are two magnetic torquers. At the magnetometers, these torquers can generate magnetic fields larger than the ambient fields to be measured. Therefore signals from these torquer currents need to be removed. The torquer currents are measured at the same rate as the magnetometer rate, and the currents are used to correct the magnetometer measurements. However, the torquer currents were not low-pass filtered. As a result, large instantaneous steps in the torquer currents show up in the magnetometer data as a delayed, slowly rising wave with some ringing, just what one would expect from the magnetometer low-pass filters. The so-called ?Farthing coefficients? simulate, from a short past history of the torquer measurements, the effects of the magnetometer filters. The torquer current changes are asynchronous with the telemetry frames and the timing between these events must be measured to a eighth of a telemetry frame interval for good performance. The transient responses in changes in torquer currents are reduced, but not eliminated for large changes in torquer currents. There exists one opportunity at the beginning of each mission to perform a spacecraft rotation maneuver to determine magnetometer offsets. These offsets are used through the duration of each satellite's lifetime. Approximate coefficients are: * 0.8 milliampere per torquer current count * 4 counts per torquer current command step (3.2 milliampere per command step) * 410 milliamperes full scale current * 32 magnetometer counts per nT (approximate) * 8 torquer step counts can be up to approximately 0.5 nT (depends on axis, which torquer, which satellite, etc.)

11) GOES 10 Magnetometer 1-Minute Data maxmize
Resource ID:spase://VMO/NumericalData/GOES/10/MAG/PT1M
Start:1999-03-21 00:00:30 Observatory:GOES 10 Cadence:1 minute
Stop:2006-06-22 23:59:30 Instrument:GOES 10, Triaxial Fluxgate Magnetometer Resource:NumericalData
The NOAA Geostationary Operational Environment Satellite (GOES) key parameters. This data is a subset of the data available from the GOES Space Environment Monitor (SEM) instruments. It contains vector magnetic field in three coordinate systems: * (1) Spacecraft P,E,N * (2) GSM x,y,z and * (3) GSE x,y,z. Spacecraft magnetic field is defined as: * P - perpendicular to the spacecraft orbital plane or parallel to the Earth's spin axis in the case of a zero degree inclination orbit; * E - perpendicular to P and directed earhtwards; and * N - perpendicular to both P and E and directed eastwards.

12) GOES 11 high-resolution magnetometer data maxmize
Resource ID:spase://VMO/NumericalData/GOES/11/MAG/PT0.512S
Start:2007-09-15 23:59:58 Observatory:GOES 11 Cadence:0.512 seconds
Stop:2008-06-30 23:59:58 Instrument:GOES 11, Triaxial Fluxgate Magnetometer Resource:NumericalData
GOES 11 magnetic field data at 0.512 second time resolution. The vector magnetic field is given in the spacecraft (s/c) earth-referenced coordinate system: Hp, He, Hn, and Ht, where Hp is perpendicular to the satellite orbital plane, or parallel to Earth's spin axis in the case of a zero degree inclination orbit; He is perpendicular to Hp and directed earthwards; Hn is perpendicular to both Hp and He and directed eastwards; and Ht is the total field. This data product also provides GOES 11 satellite positions and velocities derived from SSCWEB GEI ephemeris, interpolated to one minute time resolution. The magnetometer data are downlinked from the spacecraft in real-time to the NOAA Space Weather Prediction Center (SWPC) in Boulder, CO. The data from the raw Command and Data Acquisition (CDA) telemetry stream are processed by pre-processors at SWPC and from there 1-minute averages are distributed to SWPC Space Weather Operations, as well a archived at NOAA?s National Geophysical Data Center (NGDC) and NASA?s Coordinated Data Analysis Web (http://cdaweb.gsfc.nasa.gov/). The raw high-resolution data are corrected and processed at NOAA?s SWPC, and later archived at NGDC. The major issue for processing the high-resolution data is correction for the magnetic signature of spacecraft torquer currents as briefly discussed in the magnetometer instrument descriptions. In normal operation, the magnetometer samples its three axes every 0.512 seconds, synchronized with the telemetry frames. The magnetometer has an anti-aliasing low-pass filter on each axis. As part of the attitude control on the spacecraft, there are two magnetic torquers. At the magnetometers, these torquers can generate magnetic fields larger than the ambient fields to be measured. Therefore signals from these torquer currents need to be removed. The torquer currents are measured at the same rate as the magnetometer rate, and the currents are used to correct the magnetometer measurements. However, the torquer currents were not low-pass filtered. As a result, large instantaneous steps in the torquer currents show up in the magnetometer data as a delayed, slowly rising wave with some ringing, just what one would expect from the magnetometer low-pass filters. The so-called ?Farthing coefficients? simulate, from a short past history of the torquer measurements, the effects of the magnetometer filters. The torquer current changes are asynchronous with the telemetry frames and the timing between these events must be measured to a eighth of a telemetry frame interval for good performance. The transient responses in changes in torquer currents are reduced, but not eliminated for large changes in torquer currents. There exists one opportunity at the beginning of each mission to perform a spacecraft rotation maneuver to determine magnetometer offsets. These offsets are used through the duration of each satellite's lifetime. Approximate coefficients are: * 0.8 milliampere per torquer current count * 4 counts per torquer current command step (3.2 milliampere per command step) * 410 milliamperes full scale current * 32 magnetometer counts per nT (approximate) * 8 torquer step counts can be up to approximately 0.5 nT (depends on axis, which torquer, which satellite, etc.)

13) GOES 12 high-resolution magnetometer data maxmize
Resource ID:spase://VMO/NumericalData/GOES/12/MAG/PT0.512S
Start:2007-09-15 23:59:58 Observatory:GOES 12 Cadence:0.512 seconds
Stop:2008-06-30 23:59:58 Instrument:GOES 12, Triaxial Fluxgate Magnetometer Resource:NumericalData
GOES 12 magnetic field data at 0.512 second time resolution. The vector magnetic field is given in the spacecraft (s/c) earth-referenced coordinate system: Hp, He, Hn, and Ht, where Hp is perpendicular to the satellite orbital plane, or parallel to Earth's spin axis in the case of a zero degree inclination orbit; He is perpendicular to Hp and directed earthwards; Hn is perpendicular to both Hp and He and directed eastwards; and Ht is the total field. This data product also provides GOES 12 satellite positions and velocities derived from SSCWEB GEI ephemeris, interpolated to one minute time resolution. The magnetometer data are downlinked from the spacecraft in real-time to the NOAA Space Weather Prediction Center (SWPC) in Boulder, CO. The data from the raw Command and Data Acquisition (CDA) telemetry stream are processed by pre-processors at SWPC and from there 1-minute averages are distributed to SWPC Space Weather Operations, as well a archived at NOAA?s National Geophysical Data Center (NGDC) and NASA?s Coordinated Data Analysis Web (http://cdaweb.gsfc.nasa.gov/). The raw high-resolution data are corrected and processed at NOAA?s SWPC, and later archived at NGDC. The major issue for processing the high-resolution data is correction for the magnetic signature of spacecraft torquer currents as briefly discussed in the magnetometer instrument descriptions. In normal operation, the magnetometer samples its three axes every 0.512 seconds, synchronized with the telemetry frames. The magnetometer has an anti-aliasing low-pass filter on each axis. As part of the attitude control on the spacecraft, there are two magnetic torquers. At the magnetometers, these torquers can generate magnetic fields larger than the ambient fields to be measured. Therefore signals from these torquer currents need to be removed. The torquer currents are measured at the same rate as the magnetometer rate, and the currents are used to correct the magnetometer measurements. However, the torquer currents were not low-pass filtered. As a result, large instantaneous steps in the torquer currents show up in the magnetometer data as a delayed, slowly rising wave with some ringing, just what one would expect from the magnetometer low-pass filters. The so-called ?Farthing coefficients? simulate, from a short past history of the torquer measurements, the effects of the magnetometer filters. The torquer current changes are asynchronous with the telemetry frames and the timing between these events must be measured to a eighth of a telemetry frame interval for good performance. The transient responses in changes in torquer currents are reduced, but not eliminated for large changes in torquer currents. There exists one opportunity at the beginning of each mission to perform a spacecraft rotation maneuver to determine magnetometer offsets. These offsets are used through the duration of each satellite's lifetime. Approximate coefficients are: * 0.8 milliampere per torquer current count * 4 counts per torquer current command step (3.2 milliampere per command step) * 410 milliamperes full scale current * 32 magnetometer counts per nT (approximate) * 8 torquer step counts can be up to approximately 0.5 nT (depends on axis, which torquer, which satellite, etc.)

14) GOES 8 Magnetometer 1-Minute Data maxmize
Resource ID:spase://VMO/NumericalData/GOES/8/MAG/PT1M
Start:1995-12-01 00:00:30 Observatory:GOES 8 Cadence:1 minute
Stop:2003-04-08 23:59:30 Instrument:GOES 8, Triaxial Fluxgate Magnetometer Resource:NumericalData
The NOAA Geostationary Operational Environment Satellite (GOES) key parameters. This data is a subset of the data available from the GOES Space Environment Monitor (SEM) instruments. It contains vector magnetic field in three coordinate systems: * (1) Spacecraft P,E,N * (2) GSM x,y,z and * (3) GSE x,y,z. Spacecraft magnetic field is defined as: * P - perpendicular to the spacecraft orbital plane or parallel to the Earth's spin axis in the case of a zero degree inclination orbit; * E - perpendicular to P and directed earhtwards; and * N - perpendicular to both P and E and directed eastwards.

15) GOES 9 Magnetometer 1-Minute Data maxmize
Resource ID:spase://VMO/NumericalData/GOES/9/MAG/PT1M
Start:1995-12-01 00:00:30 Observatory:GOES 9 Cadence:1 minute
Stop:1998-07-27 23:59:30 Instrument:GOES 9, Triaxial Fluxgate Magnetometer Resource:NumericalData
The NOAA Geostationary Operational Environment Satellite (GOES) key parameters. This data is a subset of the data available from the GOES Space Environment Monitor (SEM) instruments. It contains vector magnetic field in three coordinate systems: * (1) Spacecraft P,E,N * (2) GSM x,y,z and * (3) GSE x,y,z. Spacecraft magnetic field is defined as: * P - perpendicular to the spacecraft orbital plane or parallel to the Earth's spin axis in the case of a zero degree inclination orbit; * E - perpendicular to P and directed earhtwards; and * N - perpendicular to both P and E and directed eastwards.

16) All GOES Longitudinal Locations at 1 Day Resolution as West Geographic longitude. maxmize
Resource ID:spase://VMO/NumericalData/GOES/Ephemeris/PD1
Start:1986-01-01 00:00:00 Observatory:GOES 2 Cadence:31 days
Stop:2010-02-28 00:00:00 Instrument:GOES 2 Positions Resource:NumericalData
The GOES longitudinal location information consists of the west geographic longitude in degrees. The data are separated into spacecraft (GOES 2-12), year, and month. The location is given for each day of the month is in units of degrees and the geographic latitude is assumed to be zero degrees.

17) Geotail Spacecraft Definitive Positions maxmize
Resource ID:spase://VMO/NumericalData/Geotail/Ephemeris/PT10M
Start:1992-07-27 16:00:00 Observatory:Geotail Cadence:10 minutes
Stop:2014-08-01 01:01:38 Instrument:Geotail Spacecraft Position Resource:NumericalData
Definitive Geotail spacecraft positions in various coordinate systems

18) IMP 8 Spacecraft Positions maxmize
Resource ID:spase://VMO/NumericalData/IMP8/Ephemeris/PT12M
Start:1973-10-30 00:00:00 Observatory:IMP 8 Cadence:12 minutes
Stop:2014-08-01 01:01:38 Instrument:IMP 8 Spacecraft Position Resource:NumericalData
IMP-8 spacecraft positions in various coordinate systems

19) ISEE 3 12-min Trajectory Data maxmize
Resource ID:spase://VEPO/NumericalData/ISEE3/Ephemeris/PT12M
Start:1978-08-16 00:00:00 Observatory:ISEE 3 Cadence:12 minutes
Stop:1984-02-01 00:00:00 Instrument:ISEE 3 Position Resource:NumericalData
ISEE 3 positions.

20) Interball Tail definitive orbital data maxmize
Resource ID:spase://VMO/NumericalData/Interball-Tail/Ephemeris/PT2M
Start:1995-08-07 00:00:00 Observatory:Interball-1 Cadence:2 minutes
Stop:2000-10-16 13:55:00 Instrument:Interball-1 Orbit Resource:NumericalData
Definitive Interball Tail satellite and subsatellite (Interball-1 and Magion-4) orbital data: Spacecraft position, velocity, and status flags.

21) PolarEFI_SpacecraftAttitude_GEI maxmize
Resource ID: spase://VWO/NumericalData/POLAR/EFI/S_C_GEI_Attitude
Start:1996-03-16 00:00:00 Observatory: Cadence:600 seconds
Stop:2008-04-14 00:00:00 Instrument: Resource:NumericalData
The the Polar spacecraft positive spin axis direction vector (normalized to magnitude 1), in GEI coordinates.

22) PolarEFI_SpacecraftAttitude_GEI maxmize
Resource ID: spase://SMWG/NumericalData/POLAR/EFI/S_C_GEI_Attitude
Start:1996-03-16 00:00:00 Observatory: Cadence:600 seconds
Stop:2008-04-14 00:00:00 Instrument: Resource:NumericalData
The the Polar spacecraft positive spin axis direction vector (normalized to magnitude 1), in GEI coordinates.

23) PolarEFI_SpacecraftPosition_GEI maxmize
Resource ID: spase://SMWG/NumericalData/POLAR/EFI/S_C_GEI_Position
Start:1996-03-16 00:00:00 Observatory: Cadence:60 seconds
Stop:2008-04-14 00:00:00 Instrument: Resource:NumericalData
The Polar spacecraft position, in GEI coordinates.

24) PolarEFI_SpacecraftPosition_GEI maxmize
Resource ID: spase://VWO/NumericalData/POLAR/EFI/S_C_GEI_Position
Start:1996-03-16 00:00:00 Observatory: Cadence:60 seconds
Stop:2008-04-14 00:00:00 Instrument: Resource:NumericalData
The Polar spacecraft position, in GEI coordinates.

25) PolarEFI_SpacecraftVelocity_GEI maxmize
Resource ID: spase://SMWG/NumericalData/POLAR/EFI/S_C_GEI_Velocity
Start:1996-03-16 00:00:00 Observatory: Cadence:60 seconds
Stop:2008-04-14 00:00:00 Instrument: Resource:NumericalData
The Polar spacecraft velocity, in GEI coordinates.

26) PolarEFI_SpacecraftVelocity_GEI maxmize
Resource ID: spase://VWO/NumericalData/POLAR/EFI/S_C_GEI_Velocity
Start:1996-03-16 00:00:00 Observatory: Cadence:60 seconds
Stop:2008-04-14 00:00:00 Instrument: Resource:NumericalData
The Polar spacecraft velocity, in GEI coordinates.

27) PolarEFI_SpacecraftAttitude_GSE maxmize
Resource ID: spase://SMWG/NumericalData/POLAR/EFI/S_C_GSE_Attitude
Start:1996-03-16 00:00:00 Observatory: Cadence:600 seconds
Stop:2008-04-14 00:00:00 Instrument: Resource:NumericalData
The the Polar spacecraft positive spin axis direction vector (normalized to magnitude 1), in GSE coordinates.

28) PolarEFI_SpacecraftAttitude_GSE maxmize
Resource ID: spase://VWO/NumericalData/POLAR/EFI/S_C_GSE_Attitude
Start:1996-03-16 00:00:00 Observatory: Cadence:600 seconds
Stop:2008-04-14 00:00:00 Instrument: Resource:NumericalData
The the Polar spacecraft positive spin axis direction vector (normalized to magnitude 1), in GSE coordinates.

29) PolarEFI_SpacecraftPosition_GSE maxmize
Resource ID: spase://SMWG/NumericalData/POLAR/EFI/S_C_GSE_Position
Start:1996-03-16 00:00:00 Observatory: Cadence:60 seconds
Stop:2008-04-14 00:00:00 Instrument: Resource:NumericalData
The Polar spacecraft position, in GSE coordinates.

30) PolarEFI_SpacecraftPosition_GSE maxmize
Resource ID: spase://VWO/NumericalData/POLAR/EFI/S_C_GSE_Position
Start:1996-03-16 00:00:00 Observatory: Cadence:60 seconds
Stop:2008-04-14 00:00:00 Instrument: Resource:NumericalData
The Polar spacecraft position, in GSE coordinates.

31) PolarEFI_SpacecraftVelocity_GSE maxmize
Resource ID: spase://SMWG/NumericalData/POLAR/EFI/S_C_GSE_Velocity
Start:1996-03-16 00:00:00 Observatory: Cadence:60 seconds
Stop:2008-04-14 00:00:00 Instrument: Resource:NumericalData
The Polar spacecraft velocity, in GSE coordinates.

32) PolarEFI_SpacecraftVelocity_GSE maxmize
Resource ID: spase://VWO/NumericalData/POLAR/EFI/S_C_GSE_Velocity
Start:1996-03-16 00:00:00 Observatory: Cadence:60 seconds
Stop:2008-04-14 00:00:00 Instrument: Resource:NumericalData
The Polar spacecraft velocity, in GSE coordinates.

33) PolarEFI_SpacecraftAttitude_GSM maxmize
Resource ID: spase://SMWG/NumericalData/POLAR/EFI/S_C_GSM_Attitude
Start:1996-03-16 00:00:00 Observatory: Cadence:600 seconds
Stop:2008-04-14 00:00:00 Instrument: Resource:NumericalData
The the Polar spacecraft positive spin axis direction vector (normalized to magnitude 1), in GSM coordinates.

34) PolarEFI_SpacecraftAttitude_GSM maxmize
Resource ID: spase://VWO/NumericalData/POLAR/EFI/S_C_GSM_Attitude
Start:1996-03-16 00:00:00 Observatory: Cadence:600 seconds
Stop:2008-04-14 00:00:00 Instrument: Resource:NumericalData
The the Polar spacecraft positive spin axis direction vector (normalized to magnitude 1), in GSM coordinates.

35) PolarEFI_SpacecraftPosition_GSM maxmize
Resource ID: spase://SMWG/NumericalData/POLAR/EFI/S_C_GSM_Position
Start:1996-03-16 00:00:00 Observatory: Cadence:60 seconds
Stop:2008-04-14 00:00:00 Instrument: Resource:NumericalData
The Polar spacecraft position, in GSM coordinates.

36) PolarEFI_SpacecraftPosition_GSM maxmize
Resource ID: spase://VWO/NumericalData/POLAR/EFI/S_C_GSM_Position
Start:1996-03-16 00:00:00 Observatory: Cadence:60 seconds
Stop:2008-04-14 00:00:00 Instrument: Resource:NumericalData
The Polar spacecraft position, in GSM coordinates.

37) PolarEFI_SpacecraftVelocity_GSM maxmize
Resource ID: spase://SMWG/NumericalData/POLAR/EFI/S_C_GSM_Velocity
Start:1996-03-16 00:00:00 Observatory: Cadence:60 seconds
Stop:2008-04-14 00:00:00 Instrument: Resource:NumericalData
The Polar spacecraft velocity, in GSM coordinates.

38) PolarEFI_SpacecraftVelocity_GSM maxmize
Resource ID: spase://VWO/NumericalData/POLAR/EFI/S_C_GSM_Velocity
Start:1996-03-16 00:00:00 Observatory: Cadence:60 seconds
Stop:2008-04-14 00:00:00 Instrument: Resource:NumericalData
The Polar spacecraft velocity, in GSM coordinates.

39) PolarEFI_OtherOrbitData maxmize
Resource ID: spase://SMWG/NumericalData/POLAR/EFI/S_C_OtherOrbit
Start:1996-03-16 00:00:00 Observatory: Cadence:60 seconds
Stop:2008-04-14 00:00:00 Instrument: Resource:NumericalData
The Polar non-positional, non-velocity ephemeris data

40) PolarEFI_OtherOrbitData maxmize
Resource ID: spase://VWO/NumericalData/POLAR/EFI/S_C_OtherOrbit
Start:1996-03-16 00:00:00 Observatory: Cadence:60 seconds
Stop:2008-04-14 00:00:00 Instrument: Resource:NumericalData
The Polar non-positional, non-velocity ephemeris data

41) POLAR Predicted Orbit maxmize
Resource ID:spase://VMO/NumericalData/POLAR/Ephemeris/PT01M
Start:1996-02-27 00:00:00 Observatory:POLAR Cadence:01 minutes
Stop:2014-08-01 01:02:21 Instrument:POLAR Orbit Resource:NumericalData
Polar predicted orbit data

42) Pioneer10 Positions maxmize
Resource ID:spase://VEPO/NumericalData/Pioneer10/Ephemeris/P1D
Start:1972-01-01 00:00:00 Observatory:Pioneer 10 Cadence:1 day
Stop:2014-07-31 01:00:44 Instrument:Pioneer10 Positions Resource:NumericalData
Pioneer10 satellite positions.

43) Pioneer11 Positions maxmize
Resource ID:spase://VEPO/NumericalData/Pioneer11/Ephemeris/P1D
Start:1972-01-01 00:00:00 Observatory:Pioneer 11 Cadence:1 day
Stop:2014-07-31 01:00:43 Instrument:Pioneer11 Positions Resource:NumericalData
Pioneer11 satellite positions.

44) Prognoz 6 Magnetic Field Data maxmize
Resource ID:spase://VMO/NumericalData/Prognoz6/MAG/PT10S
Start:1977-09-26 14:56:48 Observatory:Prognoz 6 Cadence:10.24 seconds
Stop:1978-01-21 15:26:40 Instrument:Three-Axis Fluxgate Magnetometer Resource:NumericalData
Magnetic field data obtained in the outer magnetosphere and in the solar wind by Prognoz 6 between 1977/09/26 and 1978/01/22. The data were obtained by an SG-70 fluxgate magnetometer provided by IZMIRAN's Space Magnetic Research Laboratory. The magnetometer had a range of +/- 60 nT and an accuracy of about 0.3 nT. It made one vector measurement every 10.24 sec.

45) Prognoz 7 Magnetic Field Data maxmize
Resource ID:spase://VMO/NumericalData/Prognoz7/MAG/PT10S
Start:1978-11-11 17:25:37 Observatory:Prognoz 7 Cadence:10.24 seconds
Stop:1979-05-31 03:00:54 Instrument:Three-Axis Fluxgate Magnetometers Resource:NumericalData
Magnetic field data obtained in the outer magnetosphere and in the solar wind by Prognoz 7 between 1978/11/11 and 1979/05/31. The data were obtained by an SG-70 fluxgate magnetometer provided by IZMIRAN's Space Magnetic Research Laboratory. The magnetometer had a range of +/- 60 nT and an accuracy of about 0.3 nT. It made one vector measurement every 10.24 sec.

46) Prognoz 9 Magnetic Field Data maxmize
Resource ID:spase://VMO/NumericalData/Prognoz9/MAG/PT10S
Start:1983-07-02 22:26:33 Observatory:Prognoz 9 Cadence:10.24 seconds
Stop:1984-02-10 12:05:51 Instrument:Triaxial Fluxgate Magnetometer Resource:NumericalData
Magnetic field data obtained in the outer magnetosphere and in the solar wind by Prognoz 9 between 1983/07/02 and 1984/02/10. The data were obtained by an SG-70 fluxgate magnetometer provided by IZMIRAN's Space Magnetic Research Laboratory. The magnetometer had a range of +/- 60 nT and an accuracy of about 0.3 nT. It made one vector measurement every 10.24 sec.

47) SCATHA Spacecraft Positions maxmize
Resource ID:spase://VMO/NumericalData/SCATHA/Ephemeris/PT1M
Start:1979-02-06 00:00:00 Observatory:SCATHA Cadence:1 minute
Stop:1986-12-31 23:59:00 Instrument:SCATHA Positions Resource:NumericalData
SCATHA satellite positions.

48) SCATHA Science Summary Data maxmize
Resource ID:spase://ViRBO/NumericalData/SCATHA/SC1/SC2/SC3/SC4/SC10/SC11/PT1M
Start:1979-02-06 00:00:00 Observatory:SCATHA Cadence:
Stop:1990-05-23 00:00:00 Instrument:SCATHA Engineering and Wave Experiment (SC1) Resource:NumericalData
SCATHA Science Summary Data

49) SCATHA Science Full Resolution Data maxmize
Resource ID:spase://ViRBO/NumericalData/SCATHA/SC1/SC2/SC3/SC4/SC10/SC11/PT1S
Start:1979-02-06 00:00:00 Observatory:SCATHA Cadence:1 second
Stop:1990-05-23 00:00:00 Instrument:SCATHA Engineering and Wave Experiment (SC1) Resource:NumericalData
SCATHA Science Full Resolution Data

50) SCATHA Science Summary Data maxmize
Resource ID:spase://VMO/NumericalData/SCATHA/summary
Start:1979-02-06 00:15:29 Observatory:SCATHA Cadence:
Stop:1986-06-16 23:59:30 Instrument:SCATHA Engineering and Wave Experiment (SC1) Resource:NumericalData
Summary science data from SCATHA instruments (SC1, SC2, SC3, SC10, and SC11). One minute resolution processed at Aerospace from full-resolution data files.

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