This page summarizes information about the selected resource and its origin based on SPASE metadata.
SPASE version 2.0.0
THEMIS-A: The Solid State Telescope (SST) measures the incoming intensity (flux per solid angle) of superthermal electrons and ions. The spacecraft is fitted with two units (heads), each SST unit has two pairs of opposing ion and electron sensors. Each single sensor covers an angle of 36 degrees. The units are oriented such that one pair is always centered in the rotation plane, the other oriented at a maximum angle of 54 degrees off the plane. Each pair of units are oriented opposite each other allowing both ion and electron sensors to sweep out a maximum of 92% of the sky (45x45 degree required Elevation by Azimuth FOV, 108x22 raw) . The ion and electron sensors primarily measure particles between 30-300 keV and 30-100 keV respectively with a maximum capability of 20-6000 keV and 25-1000 keV. Full distribution data is measured over 128 angles and 16 energy bins, reduced distribution uses 6 angles and 16 energy bins, and burst mode data has 64 angles in 16 energy bins. Matched and paired electron broom magnets produce quadrapole fields reducing magnetic contamination. A mechanical attenuator is used to increase the instruments dynamical range avoiding oversaturation near the plasma sheet edge.
NASA Contract NAS5-02099
| Role | Person | |
|---|---|---|
| 1. | Principal investigator | Dr. Vassilis Angelopoulos |
| 2. | CoInvestigator | Mr. Davin Larson |
| 3. | CoInvestigator | Prof. Robert P. Lin |
NASA/GSFC CDAWeb ftp access to the data.
Access to ASCII, CDF, and plots via NASA/GSFC CDAWeb
Calibration for the SST is not complete. Currently there are no corrections for the dead layer. Other data products will be added later as calibration continues. Total list of expected data types can be found on the THEMIS website.
SST Ion energy spectrogram in DSL (Despun Spacecraft) coordinates. Spectrogram data is averaged over solid angle.
DSL coordinates: The Z-axis points towards the spacecraft spin axis and the Y-axis is obtained from the cross product of Z and the Spacecraft-Sun direction as viewed from the probe; X completes a right handed system.
| Index | Name | Valid min | Valid max | Fill value |
|---|---|---|---|---|
| 1 | tha_psif_en_eflux_1 | 0.0 | 1.0E10 | NaN |
| 2 | tha_psif_en_eflux_2 | 0.0 | 1.0E10 | NaN |
| 3 | tha_psif_en_eflux_3 | 0.0 | 1.0E10 | NaN |
| 4 | tha_psif_en_eflux_4 | 0.0 | 1.0E10 | NaN |
| 5 | tha_psif_en_eflux_5 | 0.0 | 1.0E10 | NaN |
| 6 | tha_psif_en_eflux_6 | 0.0 | 1.0E10 | NaN |
| 7 | tha_psif_en_eflux_7 | 0.0 | 1.0E10 | NaN |
| 8 | tha_psif_en_eflux_8 | 0.0 | 1.0E10 | NaN |
| 9 | tha_psif_en_eflux_9 | 0.0 | 1.0E10 | NaN |
| 10 | tha_psif_en_eflux_10 | 0.0 | 1.0E10 | NaN |
| 11 | tha_psif_en_eflux_11 | 0.0 | 1.0E10 | NaN |
| 12 | tha_psif_en_eflux_12 | 0.0 | 1.0E10 | NaN |
| 13 | tha_psif_en_eflux_13 | 0.0 | 1.0E10 | NaN |
| 14 | tha_psif_en_eflux_14 | 0.0 | 1.0E10 | NaN |
| 15 | tha_psif_en_eflux_15 | 0.0 | 1.0E10 | NaN |
| 16 | tha_psif_en_eflux_16 | 0.0 | 1.0E10 | NaN |
Ion energy spectrogram: Number intensity is graphed against energy on the Y-axis; ranges from 30-300 keV.
| Index | Name | Valid min | Valid max | Fill value |
|---|---|---|---|---|
| 1 | tha_psif_en_eflux_yaxis_1 | 0.0 | 1.0E10 | NaN |
| 2 | tha_psif_en_eflux_yaxis_2 | 0.0 | 1.0E10 | NaN |
| 3 | tha_psif_en_eflux_yaxis_3 | 0.0 | 1.0E10 | NaN |
| 4 | tha_psif_en_eflux_yaxis_4 | 0.0 | 1.0E10 | NaN |
| 5 | tha_psif_en_eflux_yaxis_5 | 0.0 | 1.0E10 | NaN |
| 6 | tha_psif_en_eflux_yaxis_6 | 0.0 | 1.0E10 | NaN |
| 7 | tha_psif_en_eflux_yaxis_7 | 0.0 | 1.0E10 | NaN |
| 8 | tha_psif_en_eflux_yaxis_8 | 0.0 | 1.0E10 | NaN |
| 9 | tha_psif_en_eflux_yaxis_9 | 0.0 | 1.0E10 | NaN |
| 10 | tha_psif_en_eflux_yaxis_10 | 0.0 | 1.0E10 | NaN |
| 11 | tha_psif_en_eflux_yaxis_11 | 0.0 | 1.0E10 | NaN |
| 12 | tha_psif_en_eflux_yaxis_12 | 0.0 | 1.0E10 | NaN |
| 13 | tha_psif_en_eflux_yaxis_13 | 0.0 | 1.0E10 | NaN |
| 14 | tha_psif_en_eflux_yaxis_14 | 0.0 | 1.0E10 | NaN |
| 15 | tha_psif_en_eflux_yaxis_15 | 0.0 | 1.0E10 | NaN |
| 16 | tha_psif_en_eflux_yaxis_16 | 0.0 | 1.0E10 | NaN |
tha_psif_en_eflux_time, UTC, in seconds since 01-Jan-1970 00:00:00; marks center time of data sample
Unleaped seconds. Sample start and end time can be calculated from tha_peif_delta_time (sample duration).
Duration in seconds of sample.
SST survey mode
SST Electron energy spectrogram in DSL (Despun Spacecraft) coordinates. Spectrogram data is averaged over solid angle.
DSL coordinates: The Z-axis points towards the spacecraft spin axis and the Y-axis is obtained from the cross product of Z and the Spacecraft-Sun direction as viewed from the probe; X completes a right handed system.
| Index | Name | Valid min | Valid max | Fill value |
|---|---|---|---|---|
| 1 | tha_psef_en_eflux_1 | 0.0 | 1.0E10 | NaN |
| 2 | tha_psef_en_eflux_2 | 0.0 | 1.0E10 | NaN |
| 3 | tha_psef_en_eflux_3 | 0.0 | 1.0E10 | NaN |
| 4 | tha_psef_en_eflux_4 | 0.0 | 1.0E10 | NaN |
| 5 | tha_psef_en_eflux_5 | 0.0 | 1.0E10 | NaN |
| 6 | tha_psef_en_eflux_6 | 0.0 | 1.0E10 | NaN |
| 7 | tha_psef_en_eflux_7 | 0.0 | 1.0E10 | NaN |
| 8 | tha_psef_en_eflux_8 | 0.0 | 1.0E10 | NaN |
| 9 | tha_psef_en_eflux_9 | 0.0 | 1.0E10 | NaN |
| 10 | tha_psef_en_eflux_10 | 0.0 | 1.0E10 | NaN |
| 11 | tha_psef_en_eflux_11 | 0.0 | 1.0E10 | NaN |
| 12 | tha_psef_en_eflux_12 | 0.0 | 1.0E10 | NaN |
| 13 | tha_psef_en_eflux_13 | 0.0 | 1.0E10 | NaN |
| 14 | tha_psef_en_eflux_14 | 0.0 | 1.0E10 | NaN |
| 15 | tha_psef_en_eflux_15 | 0.0 | 1.0E10 | NaN |
| 16 | tha_psef_en_eflux_16 | 0.0 | 1.0E10 | NaN |
Electron energy spectrogram: Number intensity is graphed against energy on the Y-axis; ranges from 30-300 keV.
| Index | Name | Valid min | Valid max | Fill value |
|---|---|---|---|---|
| 1 | tha_psef_en_eflux_yaxis_1 | 0.0 | 1.0E10 | NaN |
| 2 | tha_psef_en_eflux_yaxis_2 | 0.0 | 1.0E10 | NaN |
| 3 | tha_psef_en_eflux_yaxis_3 | 0.0 | 1.0E10 | NaN |
| 4 | tha_psef_en_eflux_yaxis_4 | 0.0 | 1.0E10 | NaN |
| 5 | tha_psef_en_eflux_yaxis_5 | 0.0 | 1.0E10 | NaN |
| 6 | tha_psef_en_eflux_yaxis_6 | 0.0 | 1.0E10 | NaN |
| 7 | tha_psef_en_eflux_yaxis_7 | 0.0 | 1.0E10 | NaN |
| 8 | tha_psef_en_eflux_yaxis_8 | 0.0 | 1.0E10 | NaN |
| 9 | tha_psef_en_eflux_yaxis_9 | 0.0 | 1.0E10 | NaN |
| 10 | tha_psef_en_eflux_yaxis_10 | 0.0 | 1.0E10 | NaN |
| 11 | tha_psef_en_eflux_yaxis_11 | 0.0 | 1.0E10 | NaN |
| 12 | tha_psef_en_eflux_yaxis_12 | 0.0 | 1.0E10 | NaN |
| 13 | tha_psef_en_eflux_yaxis_13 | 0.0 | 1.0E10 | NaN |
| 14 | tha_psef_en_eflux_yaxis_14 | 0.0 | 1.0E10 | NaN |
| 15 | tha_psef_en_eflux_yaxis_15 | 0.0 | 1.0E10 | NaN |
| 16 | tha_psef_en_eflux_yaxis_16 | 0.0 | 1.0E10 | NaN |
tha_psef_en_eflux_time, UTC, in seconds since 01-Jan-1970 00:00:00; marks center time of data sample
Unleaped seconds. Sample start and end time can be calculated from tha_peif_delta_time (sample duration).
Sample duration in seconds.
SST survey mode
SPASE version 2.0.0
THEMIS-A: The Solid State Telescope (SST), identical to that on the WIND spacecraft, measures the incoming intensity (flux per solid angle) of superthermal electrons and ions. The spacecraft is fitted with two units (heads), each SST unit has two pairs of opposing ion and electron sensors. Each single sensor covers an angle of 36 degrees. The units are oriented such that one pair is always centered in the rotation plane, the other oriented at a maximum angle of 54 degrees off the plane. Each pair of units are oriented opposite each other allowing both ion and electron sensors to sweep out a maximum of 92% of the sky. The ion and electron sensors primarily measure particles between 30-300 keV and 30-100 keV respectively with a maximum capability of 20-6000 keV and 25-1000 keV. Matched and paired electron broom magnets produce quadrapole fields reducing magnetic contamination. A mechanical attenuator is used to increase the instruments dynamical range avoiding oversaturation near the plasma sheet edge.
Spacecraft description from NSSDC database
Instrument (SST) description from NSSDC database.
NASA contract NAS5-02099, V. Angelopoulos for use of data from the THEMIS Mission, Davin Larson, and Robert P Lin for their work on the SST.
| Role | Person | |
|---|---|---|
| 1. | Principal investigator | Dr. Vassilis Angelopoulos |
| 2. | CoInvestigator | Mr. Davin Larson |
| 3. | CoInvestigator | Prof. Robert P. Lin |
Calibration for the SST has not been completed.
SPASE version 2.0.0
The Time History of Events and Macroscale Interactions during Substorms (THEMIS) mission is a five-satellite Explorer mission whose primary objective is to understand the onset and macroscale evolution of magnetospheric substorms. Most importantly, THEMIS will find out which magnetotail process is responsible for substorm onset: (a) a local disruption of the plasma sheet current; or, (b) that current's interaction with the rapid influx of plasma emanating from lobe flux annihilation at ~25Re. Three inner probes at ~10Re will monitor current disruption onset, while two outer probes, at 20 and 30Re respectively, will remotely monitor plasma acceleration due to lobe flux dissipation. The five small satellites were launched together on a Delta II rocket and they carry identical sets of instruments including an electric field instrument (EFI), a flux gate magnetometer (FGM), a search coil magnetometer (SCM), a electro-static analyzer, and solid state telescopes (SST). The mission consists of several phases. In the first phase, the spacecraft will all orbit as a tight cluster in the same orbital plane with apogee at 15.4 Earth radii (RE). In the second phase, also called the Dawn Phase, the satellites will be placed in their orbits and during this time their apogees will be on the dawn side of the magnetosphere. During the third phase (also known as the Tail Science Phase) the apogees will be in the magnetotail. The fourth phase is called the Dusk Phase or Radiation Belt Science Phase, with all apogees on the dusk side. In the fifth and final phase, the apogees will shift to the sunward side (Dayside Science Phase).
All five satellites will have similar perigee altitudes (1.16-1.5 Re) but varying apogee altitudes (P1: ~30 RE, P2: ~20 RE, P3 & P4: ~12 RE, P5: ~10RE) with corresponding orbital periods of ~4, 2, and 1 days, respectively. This results in multi-point magnetic conjunctions. Every four days the satellites will line up along the Earth's magnetic tail with magnetic foot points in the North American sector, allowing the tracking of disturbances through different geospace regions from tail to ground.
The satellite data will be combined with observations of the aurora from a network of 20 ground observatories (all sky imagers, magnetometers) across the North American continent. In addition to its primary goal, THEMIS will answer critical questions in radiation belt physics and solar wind - magnetosphere energy coupling. THEMIS is complementary to MMS in terms of the temporal and spatial scales of the phenomena observed by these two constellation missions. THEMIS's focus is macroscale, whereas MMS will observe micro/meso scale features.
THEMIS Mission Homepage
NSSDC Master Catalog information on the THEMIS Mission
National Aeronautics and Space Administration/United States
| Role | Person | |
|---|---|---|
| 1. | Principal investigator | Dr. Vassilis Angelopoulos |
| 2. | Project scientist | Dr. David G. Sibeck |
SPASE version 2.0.0
SPASE version 2.0.0
SPASE version 2.0.0
SPASE version 2.0.0
SPASE version 2.0.0
SPASE version 1.2.0
Coordinated Data Analysis Web (CDAWeb) supports not only interactive plotting of variables from multiple instruments on multiple investigations simultaneously on arbitrary, user-defined time-scales. It also supports data retrieval in various formats using its interactive web interface or ftp service.
Coordinated Data Analysis Web (CDAWeb) home page at Space Physics Data Facility of the NASA Goddard Space Flight Center.
| Role | Person | |
|---|---|---|
| 1. | Project scientist | Dr. Robert E. McGuire |