This file contains numerical moments computed from measurements of the Los Alamos Magnetospheric Plasma Analyzer (MPA) [Bame et al., Rev. Sci. Inst., in press 1993]. The moments are presented in s/c coordinates: the z-axis is aligned with the spin axis, which points radially toward the center of the Earth; the x-axis is in the plane containing the spacecraft spin axis and the spin axis of the Earth, with +X generally northward; and the y-axis points generally eastward. Polar angles are measured relative to the spin axis (+Z), and azimuthal angles are measured around the z-axis, with zero along the +X direction. The moments are computed for three 'species': lop (low-ener. ions, ~1eV/e-~130eV/e); hip (hi-ener. ions, ~130eV/e-~45keV/e); alle (electrons, ~30eV - ~45keV ). The electron measurements are obtained 21.5 secs after the ion measurements. Epoch is the measurement time appropriate for the ions. The moments are computed after the fluxes are corrected for background and s/c potential. Algorithms for these corrections are relatively unsophisticated, so the moments are suspect during times of high background and/or high spacecraft potential. Because the determined spacecraft potential is not very precise, the magnitude of the low-energy ion flow velocity is probably not accurate, but the flow direction is well determined. Tperp and Tpara are obtained from diagonalization of the 3-dimensional temperature matrix, with the parallel direction assigned to the eigenvalue which is most different from the other two. The corresponding eigenvector is the symmetry axis of the distribution and should be equivalent to the magnetic field direction. The eigenvalue ratio Tperp/Tmid, which is provided for each species, is a measure of the symmetry of the distribution and should be ~1.0 for a good determination. Several of the parameters have a fairly high daily dynamic range and for survey purposes are best displayed logarithmically. These parameters are indicated by non-zero 'SCALEMIN' values in this file. A quality flag value of 1 indicates that the values are suspect because of unreliable location info.
Created SEP 1992 Modified JAN 1993 Electron time tags removed Mag Latitude added Local time added Post Gap flag added Ratio variables changed Modified SEP 1994 Changes noted in mail message from M.Kessel New Dict keys added sep95 Added new global attr. and variables from M.Kessel Oct 98
This is a virtual variable generated by read_myCDF w/ useof the data in the sc_pos_geo variable and a conversion routinespecified in the function attribute, namely conv_pos
This file contains numerical moments computed from measurements of the Los Alamos Magnetospheric Plasma Analyzer (MPA) [Bame et al., Rev. Sci. Inst., in press 1993]. The moments are presented in s/c coordinates: the z-axis is aligned with the spin axis, which points radially toward the center of the Earth; the x-axis is in the plane containing the spacecraft spin axis and the spin axis of the Earth, with +X generally northward; and the y-axis points generally eastward. Polar angles are measured relative to the spin axis (+Z), and azimuthal angles are measured around the z-axis, with zero along the +X direction. The moments are computed for three 'species': lop (low-ener. ions, ~1eV/e-~130eV/e); hip (hi-ener. ions, ~130eV/e-~45keV/e); alle (electrons, ~30eV - ~45keV ). The electron measurements are obtained 21.5 secs after the ion measurements. Epoch is the measurement time appropriate for the ions. The moments are computed after the fluxes are corrected for background and s/c potential. Algorithms for these corrections are relatively unsophisticated, so the moments are suspect during times of high background and/or high spacecraft potential. Because the determined spacecraft potential is not very precise, the magnitude of the low-energy ion flow velocity is probably not accurate, but the flow direction is well determined. Tperp and Tpara are obtained from diagonalization of the 3-dimensional temperature matrix, with the parallel direction assigned to the eigenvalue which is most different from the other two. The corresponding eigenvector is the symmetry axis of the distribution and should be equivalent to the magnetic field direction. The eigenvalue ratio Tperp/Tmid, which is provided for each species, is a measure of the symmetry of the distribution and should be ~1.0 for a good determination. Several of the parameters have a fairly high daily dynamic range and for survey purposes are best displayed logarithmically. These parameters are indicated by non-zero 'SCALEMIN' values in this file. A quality flag value of 1 indicates that the values are suspect because of unreliable location info.
Created SEP 1992 Modified JAN 1993 Electron time tags removed Mag Latitude added Local time added Post Gap flag added Ratio variables changed Modified SEP 1994 Changes noted in mail message from M.Kessel New Dict keys added sep95 Added new global attr. and variables from M.Kessel Oct 98
This is a virtual variable generated by read_myCDF w/ useof the data in the sc_pos_geo variable and a conversion routinespecified in the function attribute, namely conv_pos
MAG - ACE Magnetic Field Experiment References: http://www.srl.caltech.edu/ACE/ The quality of ACE level 2 data is such that it is suitable for serious scientific study. However, to avoid confusion and misunderstanding, it is recommended that users consult with the appropriate ACE team members before publishing work derived from the data. The ACE team has worked hard to ensure that the level 2 data are free from errors, but the team cannot accept responsibility for erroneous data, or for misunderstandings about how the data may be used. This is especially true if the appropriate ACE team members are not consulted before publication. At the very least, preprints should be forwarded to the ACE team before publication.
Initial Release 9/7/01 12/04/02: Fixed description of Epoch time variable.
Data Quality Flag: 0 = good; 1 = S/C Maneuver & subsequent high-nutation period (~4 hr) 2 = Bad data/missing data
SWEPAM - Solar Wind Electron Proton Alpha Monitor References: http://www.srl.caltech.edu/ACE/ The quality of ACE level 2 data is such that it is suitable for serious scientific study. However, to avoid confusion and misunderstanding, it is recommended that users consult with the appropriate ACE team members before publishing work derived from the data. The ACE team has worked hard to ensure that the level 2 data are free from errors, but the team cannot accept responsibility for erroneous data, or for misunderstandings about how the data may be used. This is especially true if the appropriate ACE team members are not consulted before publication. At the very least, preprints should be forwarded to the ACE team before publication.
Initial Release 02/23/00. 12/04/02: Fixed alpha/proton ratio precision bug. 12/04/02: Fixed description of Epoch time variable.
ACE s/c position, 3 comp. in GSE coord.
ACE s/c position, 3 comp. in GSM coord.
Label for ACE Position (GSE)
Vp is the solar wind proton speed, or more generally just the solar wind (bulk) speed. It is obtained by integrating the ion (proton) distribution function.
Np is the proton number density in units of cm-3, as calculated by integrating the ion distribution function.
Solar Wind Velocity in GSE coord., 3 components
Solar Wind Velocity in GSM coord., 3 comp.
Solar Wind Velocity in RTN coord., 3 components
Alpha ratio (Na/Np) - is the ratio of the number density of helium++ ions to the number density of protons.
The radial component of the proton temperature is the (1,1) component of the temperature tensor, along the radial direction. It is obtained by integration of the ion (proton) distribution function.
The Electron, Proton, and Alpha Monitor (EPAM) is composed of five telescope apertures of three different types. Two Low Energy Foil Spectrometers (LEFS) measure the flux and direction of electrons above 30 keV (geometry factor = 0.397 cm2*sr), two Low Energy Magnetic Spectrometers (LEMS) measure the flux and direction of ions greater than 50 keV (geometry factor = 0.48 cm2*sr), and the Composition Aperture (CA) measures the elemental composition of the ions (geometry factor = 0.24 cm2*sr). The telescopes use the spin of the spacecraft to sweep the full sky. Solid-state detectors are used to measure the energy and composition of the incoming particles. For more information about the EPAM instrument, visit the EPAM Home Page at JHU/APL: http://sd-www.jhuapl.edu/ACE/EPAM/ The quality of ACE level 2 data is such that it is suitable for serious scientific study. However, to avoid confusion and misunderstanding, it is recommended that users consult with the appropriate ACE team members before publishing work derived from the data. The ACE team has worked hard to ensure that the level 2 data are free from errors, but the team cannot accept responsibility for erroneous data, or for misunderstandings about how the data may be used. This is especially true if the appropriate ACE team members are not consulted before publication. At the very least, preprints should be forwarded to the ACE team before publication.
Initial Public Release 01/28/03 (Version 3) 11/11/04: Improved metadata (Version 4)
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MAG - ACE Magnetic Field Experiment References: http://www.srl.caltech.edu/ACE/ The quality of ACE level 2 data is such that it is suitable for serious scientific study. However, to avoid confusion and misunderstanding, it is recommended that users consult with the appropriate ACE team members before publishing work derived from the data. The ACE team has worked hard to ensure that the level 2 data are free from errors, but the team cannot accept responsibility for erroneous data, or for misunderstandings about how the data may be used. This is especially true if the appropriate ACE team members are not consulted before publication. At the very least, preprints should be forwarded to the ACE team before publication.
Initial Release 9/6/01 12/04/02: Fixed description of Epoch time variable.
Data Quality Flag: 0 = good; 1 = S/C Maneuver & subsequent high-nutation period (~4 hr) 2 = Bad data/missing data
The Electron, Proton, and Alpha Monitor (EPAM) is composed of five telescope apertures of three different types. Two Low Energy Foil Spectrometers (LEFS) measure the flux and direction of electrons above 30 keV (geometry factor = 0.397 cm2*sr), two Low Energy Magnetic Spectrometers (LEMS) measure the flux and direction of ions greater than 50 keV (geometry factor = 0.48 cm2*sr), and the Composition Aperture (CA) measures the elemental composition of the ions (geometry factor = 0.24 cm2*sr). The telescopes use the spin of the spacecraft to sweep the full sky. Solid-state detectors are used to measure the energy and composition of the incoming particles. For more information about the EPAM instrument, visit the EPAM Home Page at JHU/APL: http://sd-www.jhuapl.edu/ACE/EPAM/ The quality of ACE level 2 data is such that it is suitable for serious scientific study. However, to avoid confusion and misunderstanding, it is recommended that users consult with the appropriate ACE team members before publishing work derived from the data. The ACE team has worked hard to ensure that the level 2 data are free from errors, but the team cannot accept responsibility for erroneous data, or for misunderstandings about how the data may be used. This is especially true if the appropriate ACE team members are not consulted before publication. At the very least, preprints should be forwarded to the ACE team before publication.
Initial Public Release 01/28/03 (Version 3) 11/11/04: Improved metadata (Version 4)
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MAG - ACE Magnetic Field Experiment References: http://www.srl.caltech.edu/ACE/ The quality of ACE level 2 data is such that it is suitable for serious scientific study. However, to avoid confusion and misunderstanding, it is recommended that users consult with the appropriate ACE team members before publishing work derived from the data. The ACE team has worked hard to ensure that the level 2 data are free from errors, but the team cannot accept responsibility for erroneous data, or for misunderstandings about how the data may be used. This is especially true if the appropriate ACE team members are not consulted before publication. At the very least, preprints should be forwarded to the ACE team before publication.
Initial Release 9/6/01 12/04/02: Fixed description of Epoch time variable.
Data Quality Flag: 0 = good; 1 = S/C Maneuver & subsequent high-nutation period (~4 hr) 2 = Bad data/missing data
SWEPAM - Solar Wind Electron Proton Alpha Monitor References: http://www.srl.caltech.edu/ACE/ The quality of ACE level 2 data is such that it is suitable for serious scientific study. However, to avoid confusion and misunderstanding, it is recommended that users consult with the appropriate ACE team members before publishing work derived from the data. The ACE team has worked hard to ensure that the level 2 data are free from errors, but the team cannot accept responsibility for erroneous data, or for misunderstandings about how the data may be used. This is especially true if the appropriate ACE team members are not consulted before publication. At the very least, preprints should be forwarded to the ACE team before publication.
Initial Release 04/04/02. 12/04/02: Fixed alpha/proton ratio precision bug. 12/04/02: Fixed description of Epoch time variable. 12/04/02: -9999.9 fill-data values changed to -1.0e+31.
ACE s/c position, 3 comp. in GSE coord.
ACE s/c position, 3 comp. in GSM coord.
Label for ACE Position (GSE)
Vp is the solar wind proton speed, or more generally just the solar wind (bulk) speed. It is obtained by integrating the ion (proton) distribution function.
Np is the proton number density in units of cm-3, as calculated by integrating the ion distribution function.
Solar Wind Velocity in GSE coord., 3 components
Solar Wind Velocity in GSM coord., 3 comp.
Solar Wind Velocity in RTN coord., 3 components
Alpha ratio (Na/Np) - is the ratio of the number density of helium++ ions to the number density of protons.
The radial component of the proton temperature is the (1,1) component of the temperature tensor, along the radial direction. It is obtained by integration of the ion (proton) distribution function.
SWICS - The Solar Wind Ion Composition Spectrometer - determines uniquely the chemical and ionic-charge composition of the solar wind, the temperatures and mean speeds of major solar wind ions, at all speeds above 300 km/s (protons) and 170 km/s (Fe+16), and resolves H and He isotopes of solar and interstellar sources. SWICS measures the distribution functions of the interstellar cloud and dust cloud pickup ions up to energies of 100 keV/e. For more information about the SWICS instrument, visit the SWICS Home Page at http://solar-heliospheric.engin.umich.edu/ace. The quality of ACE level 2 data is such that it is suitable for serious scientific study. However, to avoid confusion and misunderstanding, it is recommended that users consult with the appropriate ACE team members before publishing work derived from the data. The ACE team has worked hard to ensure that the level 2 data are free from errors, but the team cannot accept responsibility for erroneous data, or for misunderstandings about how the data may be used. This is especially true if the appropriate ACE team members are not consulted before publication. At the very least, preprints should be forwarded to the ACE team before publication.
Initial Release 11/08/05
C6to5 is the C+6/C+5 Solar Wind charge_state Ratio
avqC is the Carbon Solar Wind average charge state
FetoO is the Fe/O Solar Wind elemental abundance ratio
avqFe is the Iron Solar Wind average charge state
O7to6 is the O+7/O+6 Solar Wind charge_state Ratio
avqO is the Oxygen Solar Wind average charge state
FetoO_qual is the quality flag for the Fe/O ratio. 0: good quality. 1: low statistics. 2: very low stats.4: non-thermal dist. 5: 1 + 4. 6: 2 + 48: Insufficient data to construct dist function.
C6toC5_qual is the quality flag for the C+6/C+5 ratio. 0: good quality. 1: low statistics. 2: very low stats.4: non-thermal dist. 5: 1 + 4. 6: 2 + 48: Insufficient data to construct dist function.
avqC_qual is the quality flag for the avqC average charge state. 0: good quality. 1: low statistics. 2: very low stats.4: non-thermal dist. 5: 1 + 4. 6: 2 + 48: Insufficient data to construct dist function.
avqFe_qual is the quality flag for the avqFe average charge state. 0: good quality. 1: low statistics. 2: very low stats.4: non-thermal dist. 5: 1 + 4. 6: 2 + 48: Insufficient data to construct dist function.
O7toO6_qual is the quality flag for the O+7/O+6 ratio. 0: good quality. 1: low statistics. 2: very low stats.4: non-thermal dist. 5: 1 + 4. 6: 2 + 48: Insufficient data to construct dist function.
avqO_qual is the quality flag for the avqO average charge state. 0: good quality. 1: low statistics. 2: very low stats.4: non-thermal dist. 5: 1 + 4. 6: 2 + 48: Insufficient data to construct dist function.
C5_qual is the quality flag for the C+5 speed and thermal speed data. 0: good quality. 1: low statistics. 2: very low stats.4: non-thermal dist. 5: 1 + 4. 6: 2 + 48: Insufficient data to construct dist function.
Fe10_qual is the quality flag for the Fe+10 speed and thermal speed data. 0: good quality. 1: low statistics. 2: very low stats.4: non-thermal dist. 5: 1 + 4. 6: 2 + 48: Insufficient data to construct dist function.
O6_qual is the quality flag for the O+6 speed and thermal speed data. 0: good quality. 1: low statistics. 2: very low stats.4: non-thermal dist. 5: 1 + 4. 6: 2 + 48: Insufficient data to construct dist function.
He_qual is the quality flag for the helium speed and density data. 0: good quality. 1: low statistics. 2: very low stats.4: non-thermal dist. 5: 1 + 4. 6: 2 + 48: Insufficient data to construct dist function.
vthC5 is the thermal speed of Carbon+5 in the solar wind, in km/s.
vC5 is the mean Carbon+5 ion speed in the solar wind, in km/s.
nHe2 is the number density of He++ ions in the solar wind, in #/cm^3
vthHe2 is the thermal speed of He++ in the solar wind, in km/s.
vHe2 is the mean Helium++ ion speed in the solar wind, in km/s.
vthFe10 is the thermal speed of Fe+10 in the solar wind, in km/s.
vFe10 is the mean Fe+10 ion speed in the solar wind, in km/s.
vthO6 is the thermal speed of Oxygen+6 in the solar wind, in km/s.
vO6 is the mean Oxygen+6 ion speed in the solar wind, in km/s.
The ULEIS Instrument on ACE The Ultra Low Energy Isotope Spectrometer measures ion fluxes over the charge range from H through Ni from about 20 keV/nucleon to 10 MeV/nucleon, thus covering both suprathermal and energetic particle energy ranges. Exploratory measurements of ultra-heavy species (mass range above Ni) will also be performed in a more limited energy range near 0.5 MeV/nucleon. ULEIS will be studying the elemental and isotopic composition of solar energetic particles, and the mechanisms by which these particles are energized in the solar corona. ULEIS will also investigate mechanisms by which supersonic interplanetary shock waves energize ions. For more information about the ULEIS instrument, visit the ULEIS Home Page at JHU/APL: http://sd-www.jhuapl.edu/ACE/ULEIS/ The quality of ACE level 2 data is such that it is suitable for serious scientific study. However, to avoid confusion and misunderstanding, it is recommended that users consult with the appropriate ACE team members before publishing work derived from the data. The ACE team has worked hard to ensure that the level 2 data are free from errors, but the team cannot accept responsibility for erroneous data, or for misunderstandings about how the data may be used. This is especially true if the appropriate ACE team members are not consulted before publication. At the very least, preprints should be forwarded to the ACE team before publication.
Initial Release 07/19/04
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EPAM - ACE Electron, Proton, and Alpha Monitor References: http://www.srl.caltech.edu/ACE/ ACE browse data is designed for monitoring large scale particle and field behavior and for selecting interesting time periods. The data is automatically generated from the spacecraft data stream using simple algorithms provided by the instrument teams. It is not routinely checked for accuracy and is subject to revision. Use this data at your own risk, and consult with the appropriate instrument teams about citing it. EPAM Browse data is not validated by the experimenters and should not be used except for preliminary examination prior to detailed studies.
Initial Release 04/30/99
175-315 keV Electron Flux (5 min)
38-53 keV Electron Flux (5 min)
1060-1910 keV Ion Flux (5 min)
112-187 keV Ion Flux (5 min)
310-580 keV Ion Flux (5 min)
47-65 keV Ion Flux (5 min)
0.48-0.97 MeV (5 min)
if 0 ignore data (5 min)
Pre-generated PWG plots
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MAG - ACE Magnetic Field Experiment References: http://www.srl.caltech.edu/ACE/ ACE browse data is designed for monitoring large scale particle and field behavior and for selecting interesting time periods. The data is automatically generated from the spacecraft data stream using simple algorithms provided by the instrument teams. It is not routinely checked for accuracy and is subject to revision. Use this data at your own risk, and consult with the appropriate instrument teams about citing it. MAG Browse data is not validated by the experimenters and should not be used except for preliminary examination prior to detailed studies.
Initial Release 11/10/98
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SIS - ACE Solar Isotope Spectrometer References: http://www.srl.caltech.edu/ACE/ ACE browse data is designed for monitoring large scale particle and field behavior and for selecting interesting time periods. The data is automatically generated from the spacecraft data stream using simple algorithms provided by the instrument teams. It is not routinely checked for accuracy and is subject to revision. Use this data at your own risk, and consult with the appropriate instrument teams about citing it. SIS Browse data is not validated by the experimenters and should not be used except for preliminary examination prior to detailed studies.
Initial Release 04/10/99
Note that the energy intervals for the dominant elements C, N, and O all differ somewhat from the nominal values of 10 to 15 MeV/nuc, and that the relative abundance of the contributing elements depend on the source of the particles.
Note that the energy intervals for the most abundant elements C, N, and O all differ somewhat from the nominal values of 7 to 10 MeV/nuc.
Proton Flux E>10 MeV - During solar quiet times, these fluxes are contaminated by background from particles entering from the sides of the instrument.
Proton Flux E>30 MeV - During solar quiet times, these fluxes are contaminated by background from particles entering from the sides of the instrument.
Note that the quoted energy interval of ~9 to 21 MeV/nuc is strictly valid only for Si. For Ne the corresponding interval is ~8 to ~17 MeV/nuc, while for Fe it is ~12 to ~26 MeV/nuc.
SWEPAM - Solar Wind Electron Proton Alpha Monitor References: http://www.srl.caltech.edu/ACE/ ACE browse data is designed for monitoring large scale particle and field behavior and for selecting interesting time periods. The data is automatically generated from the spacecraft data stream using simple algorithms provided by the instrument teams. It is not routinely checked for accuracy and is subject to revision. Use this data at your own risk, and consult with the appropriate instrument teams about citing it. SWEPAM Browse data is not validated by the experimenters and should not be used except for preliminary examination prior to detailed studies.
Initial Release 12/01/98
He_ratio is the ratio of the number density of helium++ ions to the number density of protons.
Vp is the solar wind proton speed, or more generally just the solar wind (bulk) speed. It is obtained by integrating the ion (proton) distribution function.
Np is the proton number density in units of cm-3, as calculated by integrating the ion distribution function.
He_ratio is the ratio of the number density of helium++ ions to the number density of protons.
Vp is the solar wind proton speed, or more generally just the solar wind (bulk) speed. It is obtained by integrating the ion (proton) distribution function.
Np is the proton number density in units of cm-3, as calculated by integrating the ion distribution function.
The radial component of the proton temperature is the (1,1) component of the temperature tensor, along the radial direction. It is obtained by integration of the ion (proton) distribution function.
The radial component of the proton temperature is the (1,1) component of the temperature tensor, along the radial direction. It is obtained by integration of the ion (proton) distribution function.
EPAM - ACE Electron, Proton, and Alpha Monitor References: http://www.srl.caltech.edu/ACE/ ACE browse data is designed for monitoring large scale particle and field behavior and for selecting interesting time periods. The data is automatically generated from the spacecraft data stream using simple algorithms provided by the instrument teams. It is not routinely checked for accuracy and is subject to revision. Use this data at your own risk, and consult with the appropriate instrument teams about citing it. EPAM Browse data is not validated by the experimenters and should not be used except for preliminary examination prior to detailed studies.
Initial Release 08/26/99
175-315 keV Electron Flux (1 hr)
38-53 keV Electron Flux (1 hr)
1060-1910 keV Ion Flux (1 hr)
112-187 keV Ion Flux (1 hr)
310-580 keV Ion Flux (1 hr)
47-65 keV Ion Flux (1 hr)
0.48-0.97 MeV (1 hr)
if 0 ignore data (1 hr)
MAG - ACE Magnetic Field Experiment References: http:// www.srl.caltech.edu/ACE/ ACE browse data is designed for monitoring large scale particle and field behavior and for selecting interesting time periods. The data is automatically generated from the spacecraft data stream using simple algorithms provided by the instrument teams. It is not routinely checked for accuracy and is subject to revision. Use this data at your own risk, and consult with the appropriate instrument teams about citing it. MAG Browse data is not validated by the experimenters and should not be used except for preliminary examination prior to detailed studies.
Initial Release 11/10/98
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SWEPAM - Solar Wind Electron Proton Alpha Monitor References: http://www.srl.caltech.edu/ACE/ ACE browse data is designed for monitoring large scale particle and field behavior and for selecting interesting time periods. The data is automatically generated from the spacecraft data stream using simple algorithms provided by the instrument teams. It is not routinely checked for accuracy and is subject to revision. Use this data at your own risk, and consult with the appropriate instrument teams about citing it. SWEPAM Browse data is not validated by the experimenters and should not be used except for preliminary examination prior to detailed studies.
Initial Release 12/01/98
He_ratio is the ratio of the number density of helium++ ions to the number density of protons.
Vp is the solar wind proton speed, or more generally just the solar wind (bulk) speed. It is obtained by integrating the ion (proton) distribution function.
Np is the proton number density in units of cm-3, as calculated by integrating the ion distribution function.
He_ratio is the ratio of the number density of helium++ ions to the number density of protons.
Vp is the solar wind proton speed, or more generally just the solar wind (bulk) speed. It is obtained by integrating the ion (proton) distribution function.
Np is the proton number density in units of cm-3, as calculated by integrating the ion distribution function.
The radial component of the proton temperature is the (1,1) component of the temperature tensor, along the radial direction. It is obtained by integration of the ion (proton) distribution function.
The radial component of the proton temperature is the (1,1) component of the temperature tensor, along the radial direction. It is obtained by integration of the ion (proton) distribution function.
MAG - ACE Magnetic Field Experiment References: http://www.srl.caltech.edu/ACE/ ACE browse data is designed for monitoring large scale particle and field behavior and for selecting interesting time periods. The data is automatically generated from the spacecraft data stream using simple algorithms provided by the instrument teams. It is not routinely checked for accuracy and is subject to revision. Use this data at your own risk, and consult with the appropriate instrument teams about citing it. MAG Browse data is not validated by the experimenters and should not be used except for preliminary examination prior to detailed studies.
Initial Release 11/10/98
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GROUP 1 Satellite Resolution Factor
ace 720 1
Coord/ Min/Max Range Filter Filter
Component Output Markers Minimum Maximum Mins/Maxes
GSE X YES - - - - - -
GSE Y YES - - - - - -
GSE Z YES - - - - - -
GSE Lat YES - - - - - -
GSE Lon YES - - - - - -
Addtnl Min/Max Range Filter Filter
Options Output Markers Minimum Maximum Mins/Maxes
dEarth YES - - - -
Formats and units:
Day/Time format: YYYY DDD HH:MM
Degrees/Hemisphere format: Decimal degrees with 2 place(s).
Longitude 0 to 360, latitude -90 to 90.
Distance format: Kilometers with 2 place(s).
Originated 03/14/96
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This ionogram was digitized from the original ALOUETTE 2 analog telemetry data on 7-track tape using the facilities of the Data Evaluation Laboratory at GSFC (Code 500). This data restoration project is headed by Dr. R.F. Benson (GSFC, Code 692). Ionograms were digitized at the rate of 40,000 16-bit samples/sec. This sample rate is higher than the Nyquist frequency of 30 kHz. The sample frequency of 40 kHz provides a measurement every 25 microseconds corresponding to an apparent range (c*t/2) interval of 3.747 km. Each ionogram consists of a fixed-frequency and and a swept-frequency portion. The time resolution is typically 24 seconds. More information can be found at http://nssdc/space/isis/isis-status.html
created April 1998
Virtual variable.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
time of frequency markers
seperates the fixed and swept portions
This ionogram was digitized from the original ALOUETTE 2 analog telemetry data on 7-track tape using the facilities of the Data Evaluation Laboratory at GSFC (Code 500). This data restoration project is headed by Dr. R.F. Benson (GSFC, Code 692). Ionograms were digitized at the rate of 40,000 16-bit samples/sec. This sample rate is higher than the Nyquist frequency of 30 kHz. The sample frequency of 40 kHz provides a measurement every 25 microseconds corresponding to an apparent range (c*t/2) interval of 3.747 km. Each ionogram consists of a fixed-frequency and and a swept-frequency portion. The time resolution is typically 24 seconds. More information can be found at http://nssdc/space/isis/isis-status.html
created April 1998
Virtual variable.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
time of frequency markers
seperates the fixed and swept portions
This ionogram was digitized from the original ALOUETTE 2 analog telemetry data on 7-track tape using the facilities of the Data Evaluation Laboratory at GSFC (Code 500). This data restoration project is headed by Dr. R.F. Benson (GSFC, Code 692). Ionograms were digitized at the rate of 40,000 16-bit samples/sec. This sample rate is higher than the Nyquist frequency of 30 kHz. The sample frequency of 40 kHz provides a measurement every 25 microseconds corresponding to an apparent range (c*t/2) interval of 3.747 km. Each ionogram consists of a fixed-frequency and and a swept-frequency portion. The time resolution is typically 24 seconds. More information can be found at http://nssdc/space/isis/isis-status.html
created April 1998
Virtual variable.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
time of frequency markers
seperates the fixed and swept portions
This ionogram was digitized from the original ALOUETTE 2 analog telemetry data on 7-track tape using the facilities of the Data Evaluation Laboratory at GSFC (Code 500). This data restoration project is headed by Dr. R.F. Benson (GSFC, Code 692). Ionograms were digitized at the rate of 40,000 16-bit samples/sec. This sample rate is higher than the Nyquist frequency of 30 kHz. The sample frequency of 40 kHz provides a measurement every 25 microseconds corresponding to an apparent range (c*t/2) interval of 3.747 km. Each ionogram consists of a fixed-frequency and and a swept-frequency portion. The time resolution is typically 24 seconds. More information can be found at http://nssdc/space/isis/isis-status.html
created April 1998
Virtual variable.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
time of frequency markers
seperates the fixed and swept portions
This is the hourly-averaged data from the Apollo 12 Solar Wind Spectrometer instrument, reformatted by NSSDC for easier access and use. Users should refer to the data set documentation paper entitled 'ALSEP solar wind spectrometer plasma data as observed at the Apollo 12 and 15 landing sites,' by Goldstein, Clay,Snyder, and Neugebauer, which is contained in the online Data Set Catalog at ftp://nssdcftp.gsfc.nasa.gov/miscellaneous/documents
Set 1: least restrictive quality selection.
Set 2: RMS error on curve fitting < 20
Set 3: fit RMS <20 & 1 angle measured.
Set 4: fit RMS <20 & 2 angles measured.
Points into proton flow; no correction for orbital velocity.Set 1: least restrictive quality selection.
Points into proton flow; no correction for orbital velocity. Set 2: RMS error on curve fitting < 20
Points into proton flow; no correction for orbital velocity. Set 3: fit RMS <20 & 1 angle measured.
Points into proton flow; no correction for orbital velocity.Set 4: fit RMS <20 2 angles measured.
Set 1: least restrictive quality selection.
Set 2: RMS error on curve fitting < 20
Set 3: fit RMS <20 & 1 angle measured.
Set 4: fit RMS <20 & 2 angles measured.
Set 1: least restrictive quality selection.
Set 2: RMS error on curve fitting < 20
Set 3: fit RMS <20 & 1 angle measured.
Set 4: fit RMS <20 & 2 angles measured.
Set 1: least restrictive quality selection.
Set 2: RMS error on curve fitting < 20
Set 3: fit RMS <20 & 1 angle measured.
Set 4: fit RMS <20 & 2 angles measured.
Set 1: least restrictive quality selection.
Set 2: RMS error on curve fitting < 20
Set 3: fit RMS <20 & 1 angle measured.
Set 4: fit RMS <20 & 2 angles measured.
Set 1: least restrictive quality selection.
Set 2: RMS error on curve fitting < 20
Set 3: fit RMS <20 & 1 angle measured.
Set 4: fit RMS <20 & 2 angles measured.
Points into proton flow; no correction for orbital velocity.Set 1: least restrictive quality selection.
Points into proton flow; no correction for orbital velocity. Set 2: RMS error on curve fitting < 20
Points into proton flow; no correction for orbital velocity. Set 3: fit RMS <20 & 1 angle measured.
Points into proton flow; no correction for orbital velocity.Set 4: fit RMS <20 2 angles measured.
Set 1: least restrictive quality selection.
Set 2: RMS error on curve fitting < 20
Set 3: fit RMS <20 & 1 angle measured.
Set 4: fit RMS <20 & 2 angles measured.
Set 3: fit RMS <20 & 1 angle measured.
Set 4: fit RMS <20 & 2 angles measured.
Set 2: RMS error on curve fitting < 20
Set 3: fit RMS <20 & 1 angle measured.
Set 4: fit RMS <20 & 2 angles measured.
Set 2: RMS error on curve fitting < 20
Set 3: fit RMS <20 & 1 angle measured.
Set 4: fit RMS <20 & 2 angles measured.
Set 2: RMS error on curve fitting < 20
Set 3: fit RMS <20 & 1 angle measured.
Set 4: fit RMS <20 & 2 angles measured.
Set 2: RMS error on curve fitting < 20
Set 3: fit RMS <20 & 1 angle measured.
Set 4: fit RMS <20 & 2 angles measured.
Set 2: RMS error on curve fitting < 20
Set 3: fit RMS <20 & 1 angle measured.
Set 4: fit RMS <20 & 2 angles measured.
Set 2: RMS error on curve fitting < 20
Set 3: fit RMS <20 & 1 angle measured.
Set 4: fit RMS <20 & 2 angles measured.
Set 1: least restrictive quality selection.
Set 2: RMS error on curve fitting < 20
Set 3: fit RMS <20 & 1 angle measured.
Set 4: fit RMS <20 & 2 angles measured.
This 28-s data set is the highest resolution data set available from the Apollo 12 Solar Wind Spectrometer instrument, and was reformatted by NSSDC for easier access and use. Users should refer to the data set documentation paper entitled 'ALSEP solar wind spectrometer plasma data as observed at the Apollo 12 and 15 landing sites,' by Goldstein, Clay,Snyder, and Neugebauer, which is contained in the online Data Set Catalog at ftp://nssdcftp.gsfc.nasa.gov/miscellaneous/documents
These FLAG Bits of no interest to user; kept as record of original.
If IA = 0, alpha is measured; = 1, alpha is assumed; = 2, alpha is limited; = 3, cup seeing protons is too far from sun direction to be plausible.
If IB = 0, beta is measured; = 1, beta is assumed; = 2, beta is limited; = 3, cup seeing protons is too far from sun direction to be plausible.
This is the hourly-averaged data from the Apollo 15 Solar Wind Spectrometer instrument, reformatted by NSSDC for easier access and use. Users should refer to the data set documentation paper entitled 'ALSEP solar wind spectrometer plasma data as observed at the Apollo 12 and 15 landing sites,' by Goldstein, Clay,Snyder, and Neugebauer, which is contained in the online Data Set Catalog at ftp://nssdcftp.gsfc.nasa.gov/miscellaneous/documents
Set 1: least restrictive quality selection.
Set 2: RMS error on curve fitting < 20
Set 3: fit RMS <20 & 1 angle measured.
Set 4: fit RMS <20 & 2 angles measured.
Points into proton flow; no correction for orbital velocity.Set 1: least restrictive quality selection.
Points into proton flow; no correction for orbital velocity. Set 2: RMS error on curve fitting < 20
Points into proton flow; no correction for orbital velocity. Set 3: fit RMS <20 & 1 angle measured.
Points into proton flow; no correction for orbital velocity.Set 4: fit RMS <20 2 angles measured.
Set 1: least restrictive quality selection.
Set 2: RMS error on curve fitting < 20
Set 3: fit RMS <20 & 1 angle measured.
Set 4: fit RMS <20 & 2 angles measured.
Set 1: least restrictive quality selection.
Set 2: RMS error on curve fitting < 20
Set 3: fit RMS <20 & 1 angle measured.
Set 4: fit RMS <20 & 2 angles measured.
Set 1: least restrictive quality selection.
Set 2: RMS error on curve fitting < 20
Set 3: fit RMS <20 & 1 angle measured.
Set 4: fit RMS <20 & 2 angles measured.
Set 1: least restrictive quality selection.
Set 2: RMS error on curve fitting < 20
Set 3: fit RMS <20 & 1 angle measured.
Set 4: fit RMS <20 & 2 angles measured.
Set 1: least restrictive quality selection.
Set 2: RMS error on curve fitting < 20
Set 3: fit RMS <20 & 1 angle measured.
Set 4: fit RMS <20 & 2 angles measured.
Points into proton flow; no correction for orbital velocity.Set 1: least restrictive quality selection.
Points into proton flow; no correction for orbital velocity. Set 2: RMS error on curve fitting < 20
Points into proton flow; no correction for orbital velocity. Set 3: fit RMS <20 & 1 angle measured.
Points into proton flow; no correction for orbital velocity.Set 4: fit RMS <20 2 angles measured.
Set 1: least restrictive quality selection.
Set 2: RMS error on curve fitting < 20
Set 3: fit RMS <20 & 1 angle measured.
Set 4: fit RMS <20 & 2 angles measured.
Set 3: fit RMS <20 & 1 angle measured.
Set 4: fit RMS <20 & 2 angles measured.
Set 2: RMS error on curve fitting < 20
Set 3: fit RMS <20 & 1 angle measured.
Set 4: fit RMS <20 & 2 angles measured.
Set 2: RMS error on curve fitting < 20
Set 3: fit RMS <20 & 1 angle measured.
Set 4: fit RMS <20 & 2 angles measured.
Set 2: RMS error on curve fitting < 20
Set 3: fit RMS <20 & 1 angle measured.
Set 4: fit RMS <20 & 2 angles measured.
Set 2: RMS error on curve fitting < 20
Set 3: fit RMS <20 & 1 angle measured.
Set 4: fit RMS <20 & 2 angles measured.
Set 2: RMS error on curve fitting < 20
Set 3: fit RMS <20 & 1 angle measured.
Set 4: fit RMS <20 & 2 angles measured.
Set 2: RMS error on curve fitting < 20
Set 3: fit RMS <20 & 1 angle measured.
Set 4: fit RMS <20 & 2 angles measured.
Set 1: least restrictive quality selection.
Set 2: RMS error on curve fitting < 20
Set 3: fit RMS <20 & 1 angle measured.
Set 4: fit RMS <20 & 2 angles measured.
M.A. Hapgood et al, The Joint Science Operations Centre, Space Sci. Rev. 79, 487-525 (1997)
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003
JSOC predicted magnetic positions.
Back to top
M.A. Hapgood et al, The Joint Science Operations Centre, Space Sci. Rev. 79, 487-525 (1997) AP _ Apogee CY 1 Start of visibility window at Canberra (5 deg elevation) CY 2 Start of visibility window at Canberra (5 deg elevation) CY 3 Start of visibility window at Canberra (5 deg elevation) CZ 1 End of visibility window at Canberra (5 deg elevation) CZ 2 End of visibility window at Canberra (5 deg elevation) CZ 3 End of visibility window at Canberra (5 deg elevation) CZ 4 End of visibility window at Canberra (5 deg elevation) DY 1 Start of visibility window at Vilspa (5 deg elevation) DY 2 Start of visibility window at Vilspa (5 deg elevation) DY 3 Start of visibility window at Vilspa (5 deg elevation) DY 4 Start of visibility window at Vilspa (5 deg elevation) DY 5 Start of visibility window at Vilspa (5 deg elevation) DZ 1 End of visibility window at Vilspa (5 deg elevation) DZ 2 End of visibility window at Vilspa (5 deg elevation) DZ 3 End of visibility window at Vilspa (5 deg elevation) DZ 4 End of visibility window at Vilspa (5 deg elevation) GY 1 Start of visibility window at Goldstone (5 deg elevation) GY 2 Start of visibility window at Goldstone (5 deg elevation) GY 3 Start of visibility window at Goldstone (5 deg elevation) GY 4 Start of visibility window at Goldstone (5 deg elevation) GZ 1 End of visibility window at Goldstone (5 deg elevation) GZ 2 End of visibility window at Goldstone (5 deg elevation) GZ 3 End of visibility window at Goldstone (5 deg elevation) JY 1 Start of visibility window at Maspalomas (5 deg elevation) JY 2 Start of visibility window at Maspalomas (5 deg elevation) JY 3 Start of visibility window at Maspalomas (5 deg elevation) JY 4 Start of visibility window at Maspalomas (5 deg elevation) JZ 1 End of visibility window at Maspalomas (5 deg elevation) JZ 2 End of visibility window at Maspalomas (5 deg elevation) JZ 3 End of visibility window at Maspalomas (5 deg elevation) KA 1 Start of visibility window at Kourou (5 deg elevation) KA 2 Start of visibility window at Kourou (5 deg elevation) KA 3 Start of visibility window at Kourou (5 deg elevation) KA 4 Start of visibility window at Kourou (5 deg elevation) KL 1 End of visibility window at Kourou (5 deg elevation) KL 2 End of visibility window at Kourou (5 deg elevation) KL 3 End of visibility window at Kourou (5 deg elevation) KL 4 End of visibility window at Kourou (5 deg elevation) MY 1 Start of visibility window at Madrid (5 deg elevation) MY 2 Start of visibility window at Madrid (5 deg elevation) MY 3 Start of visibility window at Madrid (5 deg elevation) MY 4 Start of visibility window at Madrid (5 deg elevation) MZ 1 End of visibility window at Madrid (5 deg elevation) MZ 2 End of visibility window at Madrid (5 deg elevation) MZ 3 End of visibility window at Madrid (5 deg elevation) NS S Southbound neutral sheet NT I Enter north tail lobe from inner magnetosphere PA 1 Start of visibility window at Perth (5 deg elevation) PA 2 Start of visibility window at Perth (5 deg elevation) PA 3 Start of visibility window at Perth (5 deg elevation) PA 4 Start of visibility window at Perth (5 deg elevation) PE _ Perigee PL 1 End of visibility window at Perth (5 deg elevation) PL 2 End of visibility window at Perth (5 deg elevation) PL 3 End of visibility window at Perth (5 deg elevation) PL 4 End of visibility window at Perth (5 deg elevation) PL 5 End of visibility window at Perth (5 deg elevation) QL I Inbound critical L value for auroral zone QL O Outbound critical L value for auroral zone RA 1 Start of visibility window at Redu (5 deg elevation) RA 2 Start of visibility window at Redu (5 deg elevation) RA 3 Start of visibility window at Redu (5 deg elevation) RA 4 Start of visibility window at Redu (5 deg elevation) RL 1 End of visibility window at Redu (5 deg elevation) RL 2 End of visibility window at Redu (5 deg elevation) RL 3 End of visibility window at Redu (5 deg elevation) RL 4 End of visibility window at Redu (5 deg elevation) RL 5 End of visibility window at Redu (5 deg elevation) ST O Leave south tail lobe for inner magnetosphere TL I Inbound radiation belt entry for WEC TL O Outbound radiation belt exit for WEC VL I Inbound critical L value for EDI VL O Outbound critical L value for EDI XL I Inbound critical L value for PEACE XL O Outbound critical L value for PEACE YL I Inbound critical L value for RAPID YL O Outbound critical L value for RAPID ZL I Inbound critical L value for CIS ZL O Outbound critical L value for CIS
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003 IGRF2000 pole used to calculate GSM latitude and MLT in PSE files produced after 25 June 2001.
JSOC predicted scientific events.
Back to top
G. Paschmann et al, The Electron Drift Instrument for Cluster Space Sci. Rev., 79, pp 233 - 269, 1997)
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003
See CSDS User's Guide, DS-MPA-TN-0015, for post processing caveats 1) EDI's automated analysis algorithm has a known susceptibility to producing occasional incorrect values of the drift velocities (and electric fields). The code attempts to prevent these bad values to be output to the cdf file. No further removal is done in the validation process. 2) When drift velocities become sufficiently large, there can be a 180-degree ambiguity in drift direction that is usually flagged in bit 7 (counting from 0) of Status Byte 3. 3) There are two methods to analyze a spin's worth of EDI data. If bits 5 6 in Status Byte 3 are NOT set, the employed method was triangulation. If either bit 5 or 6 are set, then the results are from time-of-flight analysis. 4) The reported drift velocities and electric field refer to inertial coordinates, i.e., have been corrected for spacecraft velocity. However, the magnitude errors (in %) and the angle errors (in degrees), reported in Status Bytes 5 & 6, respectively, refer to the spacecraft frame and have NOT yet been converted to inertial coordinates. 5) The reduced chi-square reported as a data word is a measure of the goodness-of-fit of the triangulation analysis.
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G. Gustafsson et al, The Electric Field and Wave Experiment for Cluster Space Sci. Rev., 79, pp 137 - 156, 1997)
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003 Data calibration may be unreliable at this early stage of the mission
See CSDS User's Guide, DS-MPA-TN-0015, for post processing caveats *** CSDS data are not for publication *** Be aware that data may be reprocessed as necessary to improve quality For questions on data validity please contact sdc-adm@plasma.kth.se Fill value inserted for E_dusk__C1_PP_EFW: No reason given for time range 2005-01-01T14:58:00Z to 2005-01-01T15:01:00Z Fill value inserted for E_pow_f1__C1_PP_EFW: No reason given for time range 2005-01-01T14:58:00Z to 2005-01-01T15:01:00Z Fill value inserted for E_sigma__C1_PP_EFW: No reason given for time range 2005-01-01T14:58:00Z to 2005-01-01T15:01:00Z Fill value inserted for U_probe_sc__C1_PP_EFW: No reason given for time range 2005-01-01T14:58:00Z to 2005-01-01T15:01:00Z
Back to top
A. D. Johnstone et al, Peace, A Plasma Electron and Current Experiment Space Sci. Rev., 79, pp 351 - 398, 1997)
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003 PP & SP data is generated at MSSL, then provided to UK-CDHF
See CSDS User's Guide, DS-MPA-TN-0015, for post processing caveats This is PEACE PP/SP data version 3.1, produced at MSSL Based on onboard moments but using corrected geometric factors which account for uplinked changes of the values used in onboard calibration as well as estimated changes due to variable MCP gain performance Onboard moments are calculated for up to three energy ranges. Photoelectron contamination may affect 0, 1 or 2 of these ranges EFW PP probe-spacecraft potential was used to select the energy ranges to be excluded to remove misleading photoelectron contributions. Note that the density may be underestimated if there are both plasma electrons and photoelectrons in the lowest energy range When 88h58 is used for the HEEA sensor, sometimes the entire plasma electron population and photoelectrons are in just the lowest of the 3 energy ranges. This data has been deleted in this release of the PEACE PPs Data is deleted if the spacecraft electric potential is too large for the simple correction procedure to work or there is no EFW PP data available Measured electron energies have not been corrected for their acceleration by the spacecraft electric potential Onboard moments use onboard energy tables, efficiencies and response surfaces. Any errors in these parameters cannot be corrected in ground data processing Before 2001-09-11 the onboard energy efficiencies were not accurate, which caused the density in the solar wind to be overestimated. This data has been removed in this release of the PEACE PPs The calculation of T_par, T_perp and Q_par used PP FGM data The data is for context and information only. It is not suitable for detailed analysis, but may be used for event selection The next iteration of PP/SP moments will be of a higher quality Please see links under http://www.mssl.ucl.ac.uk/www_plasma/missions/cluster/clusterII.html for more information Please contact the PEACE PI to request science quality data Automatically validated by UKCDC Product delivered pre-validated by the PI institute
Back to top
N. Cornilleau et al, The Cluster Spatio-Temporal Analysis of Field Fluctuations (Staff) Experiment Space Sci. Rev., 79, pp 107 - 136, 1997)
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003
See CSDS User's Guide, DS-MPA-TN-0015, for post processing caveats PI Software Version 4.1, 27 March 2006
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P. M. E. Decreau et al, WHISPER, A Resonance Sounder and Wave Analyser: Performances and Perspectives for the Cluster Mission Space Sci. Rev., 79, pp 157 - 193, 1997)
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003
See CSDS User's Guide, DS-MPA-TN-0015, for post processing caveats Two types of parameters are provided by WHISPER: 1) Density values (and quality): N_e_res and N_e_res_q, are related to sounding operations. The N_e_res value is calculated from an algorithm for resonance recognition, which cannot take account of all level of information available to the experimenter. The reliability of N_e_res parameters derived at the CSDS level is thus limited in an unknown manner. The N_e_res_q parameter (one value for each N_e_res data point) provides a crude idea of the probability that the N_e_res value is actually correct. A value of 0 means that the value is probably wrong, a value above 80 that it is probably correct. Anything in between reflects a crude evaluation of the chances. Refer to PI for details. 2) Wave power values: E_pow_f4, E_pow_f5, E_pow_f6, E_pow_su and E_var_ts, are related to recording of natural wave emissions. Those parameters, not affected by variations in instrument's transfer functions, are globally OK. However, two factors can affect the precision of the measurements: a) the occasional presence of spurious emissions created by operations of the EDI instrument increases the wave power values measured on SC1, SC2 and SC3, from an unknown amount, b) the limited dynamical range of the instrument leads to an underestimation of the E_pow parameters values when the voltage difference measured by the double sphere antenna signal in the 2 - 80 kHz band is higher than 150 mVp or 600 mVp (depending of the gain chosen). As a consequence, high values have to be taken with special caution.
Back to top
M.A. Hapgood et al, The Joint Science Operations Centre, Space Sci. Rev. 79, 487-525 (1997)
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003
JSOC predicted magnetic positions.
Back to top
M.A. Hapgood et al, The Joint Science Operations Centre, Space Sci. Rev. 79, 487-525 (1997) AP _ Apogee CY 1 Start of visibility window at Canberra (5 deg elevation) CY 2 Start of visibility window at Canberra (5 deg elevation) CY 3 Start of visibility window at Canberra (5 deg elevation) CZ 1 End of visibility window at Canberra (5 deg elevation) CZ 2 End of visibility window at Canberra (5 deg elevation) CZ 3 End of visibility window at Canberra (5 deg elevation) CZ 4 End of visibility window at Canberra (5 deg elevation) DY 1 Start of visibility window at Vilspa (5 deg elevation) DY 2 Start of visibility window at Vilspa (5 deg elevation) DY 3 Start of visibility window at Vilspa (5 deg elevation) DY 4 Start of visibility window at Vilspa (5 deg elevation) DZ 1 End of visibility window at Vilspa (5 deg elevation) DZ 2 End of visibility window at Vilspa (5 deg elevation) DZ 3 End of visibility window at Vilspa (5 deg elevation) GY 1 Start of visibility window at Goldstone (5 deg elevation) GY 2 Start of visibility window at Goldstone (5 deg elevation) GY 3 Start of visibility window at Goldstone (5 deg elevation) GY 4 Start of visibility window at Goldstone (5 deg elevation) GZ 1 End of visibility window at Goldstone (5 deg elevation) GZ 2 End of visibility window at Goldstone (5 deg elevation) GZ 3 End of visibility window at Goldstone (5 deg elevation) JY 1 Start of visibility window at Maspalomas (5 deg elevation) JY 2 Start of visibility window at Maspalomas (5 deg elevation) JY 3 Start of visibility window at Maspalomas (5 deg elevation) JY 4 Start of visibility window at Maspalomas (5 deg elevation) JZ 1 End of visibility window at Maspalomas (5 deg elevation) JZ 2 End of visibility window at Maspalomas (5 deg elevation) JZ 3 End of visibility window at Maspalomas (5 deg elevation) KA 1 Start of visibility window at Kourou (5 deg elevation) KA 2 Start of visibility window at Kourou (5 deg elevation) KA 3 Start of visibility window at Kourou (5 deg elevation) KA 4 Start of visibility window at Kourou (5 deg elevation) KL 1 End of visibility window at Kourou (5 deg elevation) KL 2 End of visibility window at Kourou (5 deg elevation) KL 3 End of visibility window at Kourou (5 deg elevation) KL 4 End of visibility window at Kourou (5 deg elevation) MY 1 Start of visibility window at Madrid (5 deg elevation) MY 2 Start of visibility window at Madrid (5 deg elevation) MY 3 Start of visibility window at Madrid (5 deg elevation) MY 4 Start of visibility window at Madrid (5 deg elevation) MZ 1 End of visibility window at Madrid (5 deg elevation) MZ 2 End of visibility window at Madrid (5 deg elevation) MZ 3 End of visibility window at Madrid (5 deg elevation) NS S Southbound neutral sheet NT I Enter north tail lobe from inner magnetosphere PA 1 Start of visibility window at Perth (5 deg elevation) PA 2 Start of visibility window at Perth (5 deg elevation) PA 3 Start of visibility window at Perth (5 deg elevation) PE _ Perigee PL 1 End of visibility window at Perth (5 deg elevation) PL 2 End of visibility window at Perth (5 deg elevation) PL 3 End of visibility window at Perth (5 deg elevation) PL 4 End of visibility window at Perth (5 deg elevation) QL I Inbound critical L value for auroral zone QL O Outbound critical L value for auroral zone RA 1 Start of visibility window at Redu (5 deg elevation) RA 2 Start of visibility window at Redu (5 deg elevation) RA 3 Start of visibility window at Redu (5 deg elevation) RA 4 Start of visibility window at Redu (5 deg elevation) RL 1 End of visibility window at Redu (5 deg elevation) RL 2 End of visibility window at Redu (5 deg elevation) RL 3 End of visibility window at Redu (5 deg elevation) RL 4 End of visibility window at Redu (5 deg elevation) ST O Leave south tail lobe for inner magnetosphere TL I Inbound radiation belt entry for WEC TL O Outbound radiation belt exit for WEC VL I Inbound critical L value for EDI VL O Outbound critical L value for EDI WL I Inbound critical L value for ASPOC WL O Outbound critical L value for ASPOC XL I Inbound critical L value for PEACE XL O Outbound critical L value for PEACE YL I Inbound critical L value for RAPID YL O Outbound critical L value for RAPID ZL I Inbound critical L value for CIS ZL O Outbound critical L value for CIS
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003 IGRF2000 pole used to calculate GSM latitude and MLT in PSE files produced after 25 June 2001.
JSOC predicted scientific events.
Back to top
G. Paschmann et al, The Electron Drift Instrument for Cluster Space Sci. Rev., 79, pp 233 - 269, 1997)
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003
See CSDS User's Guide, DS-MPA-TN-0015, for post processing caveats C2 EDI only operated in ambient mode
Back to top
G. Gustafsson et al, The Electric Field and Wave Experiment for Cluster Space Sci. Rev., 79, pp 137 - 156, 1997)
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003 Data calibration may be unreliable at this early stage of the mission
See CSDS User's Guide, DS-MPA-TN-0015, for post processing caveats *** CSDS data are not for publication *** Be aware that data may be reprocessed as necessary to improve quality For questions on data validity please contact sdc-adm@plasma.kth.se Fill value inserted for E_dusk__C2_PP_EFW: No reason given for time range 2005-01-01T14:58:00Z to 2005-01-01T15:01:00Z Fill value inserted for E_pow_f1__C2_PP_EFW: No reason given for time range 2005-01-01T14:58:00Z to 2005-01-01T15:01:00Z Fill value inserted for E_sigma__C2_PP_EFW: No reason given for time range 2005-01-01T14:58:00Z to 2005-01-01T15:01:00Z Fill value inserted for U_probe_sc__C2_PP_EFW: No reason given for time range 2005-01-01T14:58:00Z to 2005-01-01T15:01:00Z
Back to top
A. D. Johnstone et al, Peace, A Plasma Electron and Current Experiment Space Sci. Rev., 79, pp 351 - 398, 1997)
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003 PP & SP data is generated at MSSL, then provided to UK-CDHF
See CSDS User's Guide, DS-MPA-TN-0015, for post processing caveats This is PEACE PP/SP data version 3.1, produced at MSSL Based on onboard moments but using corrected geometric factors which account for uplinked changes of the values used in onboard calibration as well as estimated changes due to variable MCP gain performance Onboard moments are calculated for up to three energy ranges. Photoelectron contamination may affect 0, 1 or 2 of these ranges EFW PP probe-spacecraft potential was used to select the energy ranges to be excluded to remove misleading photoelectron contributions. Note that the density may be underestimated if there are both plasma electrons and photoelectrons in the lowest energy range When 88h58 is used for the HEEA sensor, sometimes the entire plasma electron population and photoelectrons are in just the lowest of the 3 energy ranges. This data has been deleted in this release of the PEACE PPs Data is deleted if the spacecraft electric potential is too large for the simple correction procedure to work or there is no EFW PP data available Measured electron energies have not been corrected for their acceleration by the spacecraft electric potential Onboard moments use onboard energy tables, efficiencies and response surfaces. Any errors in these parameters cannot be corrected in ground data processing Before 2001-09-11 the onboard energy efficiencies were not accurate, which caused the density in the solar wind to be overestimated. This data has been removed in this release of the PEACE PPs The calculation of T_par, T_perp and Q_par used PP FGM data The data is for context and information only. It is not suitable for detailed analysis, but may be used for event selection The next iteration of PP/SP moments will be of a higher quality Please see links under http://www.mssl.ucl.ac.uk/www_plasma/missions/cluster/clusterII.html for more information Please contact the PEACE PI to request science quality data Automatically validated by UKCDC Product delivered pre-validated by the PI institute
Back to top
N. Cornilleau et al, The Cluster Spatio-Temporal Analysis of Field Fluctuations (Staff) Experiment Space Sci. Rev., 79, pp 107 - 136, 1997)
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003
See CSDS User's Guide, DS-MPA-TN-0015, for post processing caveats PI Software Version 4.1, 27 March 2006
Back to top
P. M. E. Decreau et al, WHISPER, A Resonance Sounder and Wave Analyser: Performances and Perspectives for the Cluster Mission Space Sci. Rev., 79, pp 157 - 193, 1997)
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003
See CSDS User's Guide, DS-MPA-TN-0015, for post processing caveats Two types of parameters are provided by WHISPER: 1) Density values (and quality): N_e_res and N_e_res_q, are related to sounding operations. The N_e_res value is calculated from an algorithm for resonance recognition, which cannot take account of all level of information available to the experimenter. The reliability of N_e_res parameters derived at the CSDS level is thus limited in an unknown manner. The N_e_res_q parameter (one value for each N_e_res data point) provides a crude idea of the probability that the N_e_res value is actually correct. A value of 0 means that the value is probably wrong, a value above 80 that it is probably correct. Anything in between reflects a crude evaluation of the chances. Refer to PI for details. 2) Wave power values: E_pow_f4, E_pow_f5, E_pow_f6, E_pow_su and E_var_ts, are related to recording of natural wave emissions. Those parameters, not affected by variations in instrument's transfer functions, are globally OK. However, two factors can affect the precision of the measurements: a) the occasional presence of spurious emissions created by operations of the EDI instrument increases the wave power values measured on SC1, SC2 and SC3, from an unknown amount, b) the limited dynamical range of the instrument leads to an underestimation of the E_pow parameters values when the voltage difference measured by the double sphere antenna signal in the 2 - 80 kHz band is higher than 150 mVp or 600 mVp (depending of the gain chosen). As a consequence, high values have to be taken with special caution.
Back to top
M.A. Hapgood et al, The Joint Science Operations Centre, Space Sci. Rev. 79, 487-525 (1997)
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003
JSOC predicted magnetic positions.
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M.A. Hapgood et al, The Joint Science Operations Centre, Space Sci. Rev. 79, 487-525 (1997) AP _ Apogee CY 1 Start of visibility window at Canberra (5 deg elevation) CY 2 Start of visibility window at Canberra (5 deg elevation) CY 3 Start of visibility window at Canberra (5 deg elevation) CZ 1 End of visibility window at Canberra (5 deg elevation) CZ 2 End of visibility window at Canberra (5 deg elevation) CZ 3 End of visibility window at Canberra (5 deg elevation) CZ 4 End of visibility window at Canberra (5 deg elevation) DY 1 Start of visibility window at Vilspa (5 deg elevation) DY 2 Start of visibility window at Vilspa (5 deg elevation) DY 3 Start of visibility window at Vilspa (5 deg elevation) DZ 1 End of visibility window at Vilspa (5 deg elevation) DZ 2 End of visibility window at Vilspa (5 deg elevation) DZ 3 End of visibility window at Vilspa (5 deg elevation) GY 1 Start of visibility window at Goldstone (5 deg elevation) GY 2 Start of visibility window at Goldstone (5 deg elevation) GY 3 Start of visibility window at Goldstone (5 deg elevation) GY 4 Start of visibility window at Goldstone (5 deg elevation) GZ 1 End of visibility window at Goldstone (5 deg elevation) GZ 2 End of visibility window at Goldstone (5 deg elevation) GZ 3 End of visibility window at Goldstone (5 deg elevation) JY 1 Start of visibility window at Maspalomas (5 deg elevation) JY 2 Start of visibility window at Maspalomas (5 deg elevation) JY 3 Start of visibility window at Maspalomas (5 deg elevation) JY 4 Start of visibility window at Maspalomas (5 deg elevation) JZ 1 End of visibility window at Maspalomas (5 deg elevation) JZ 2 End of visibility window at Maspalomas (5 deg elevation) JZ 3 End of visibility window at Maspalomas (5 deg elevation) KA 1 Start of visibility window at Kourou (5 deg elevation) KA 2 Start of visibility window at Kourou (5 deg elevation) KA 3 Start of visibility window at Kourou (5 deg elevation) KA 4 Start of visibility window at Kourou (5 deg elevation) KL 1 End of visibility window at Kourou (5 deg elevation) KL 2 End of visibility window at Kourou (5 deg elevation) KL 3 End of visibility window at Kourou (5 deg elevation) KL 4 End of visibility window at Kourou (5 deg elevation) MY 1 Start of visibility window at Madrid (5 deg elevation) MY 2 Start of visibility window at Madrid (5 deg elevation) MY 3 Start of visibility window at Madrid (5 deg elevation) MY 4 Start of visibility window at Madrid (5 deg elevation) MZ 1 End of visibility window at Madrid (5 deg elevation) MZ 2 End of visibility window at Madrid (5 deg elevation) MZ 3 End of visibility window at Madrid (5 deg elevation) NS S Southbound neutral sheet NT I Enter north tail lobe from inner magnetosphere PA 1 Start of visibility window at Perth (5 deg elevation) PA 2 Start of visibility window at Perth (5 deg elevation) PA 3 Start of visibility window at Perth (5 deg elevation) PE _ Perigee PL 1 End of visibility window at Perth (5 deg elevation) PL 2 End of visibility window at Perth (5 deg elevation) PL 3 End of visibility window at Perth (5 deg elevation) PL 4 End of visibility window at Perth (5 deg elevation) QL I Inbound critical L value for auroral zone QL O Outbound critical L value for auroral zone RA 1 Start of visibility window at Redu (5 deg elevation) RA 2 Start of visibility window at Redu (5 deg elevation) RA 3 Start of visibility window at Redu (5 deg elevation) RA 4 Start of visibility window at Redu (5 deg elevation) RL 1 End of visibility window at Redu (5 deg elevation) RL 2 End of visibility window at Redu (5 deg elevation) RL 3 End of visibility window at Redu (5 deg elevation) ST O Leave south tail lobe for inner magnetosphere TL I Inbound radiation belt entry for WEC TL O Outbound radiation belt exit for WEC VL I Inbound critical L value for EDI VL O Outbound critical L value for EDI WL I Inbound critical L value for ASPOC WL O Outbound critical L value for ASPOC XL I Inbound critical L value for PEACE XL O Outbound critical L value for PEACE YL I Inbound critical L value for RAPID YL O Outbound critical L value for RAPID ZL I Inbound critical L value for CIS ZL O Outbound critical L value for CIS
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003 IGRF2000 pole used to calculate GSM latitude and MLT in PSE files produced after 25 June 2001.
JSOC predicted scientific events.
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G. Paschmann et al, The Electron Drift Instrument for Cluster Space Sci. Rev., 79, pp 233 - 269, 1997)
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003
See CSDS User's Guide, DS-MPA-TN-0015, for post processing caveats 1) EDI's automated analysis algorithm has a known susceptibility to producing occasional incorrect values of the drift velocities (and electric fields). The code attempts to prevent these bad values to be output to the cdf file. No further removal is done in the validation process. 2) When drift velocities become sufficiently large, there can be a 180-degree ambiguity in drift direction that is usually flagged in bit 7 (counting from 0) of Status Byte 3. 3) There are two methods to analyze a spin's worth of EDI data. If bits 5 6 in Status Byte 3 are NOT set, the employed method was triangulation. If either bit 5 or 6 are set, then the results are from time-of-flight analysis. 4) The reported drift velocities and electric field refer to inertial coordinates, i.e., have been corrected for spacecraft velocity. However, the magnitude errors (in %) and the angle errors (in degrees), reported in Status Bytes 5 & 6, respectively, refer to the spacecraft frame and have NOT yet been converted to inertial coordinates. 5) The reduced chi-square reported as a data word is a measure of the goodness-of-fit of the triangulation analysis.
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G. Gustafsson et al, The Electric Field and Wave Experiment for Cluster Space Sci. Rev., 79, pp 137 - 156, 1997)
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003 Data calibration may be unreliable at this early stage of the mission
See CSDS User's Guide, DS-MPA-TN-0015, for post processing caveats *** CSDS data are not for publication *** Be aware that data may be reprocessed as necessary to improve quality For questions on data validity please contact sdc-adm@plasma.kth.se Fill value inserted for E_dusk__C3_PP_EFW: No reason given for time range 2005-01-01T14:58:00Z to 2005-01-01T15:01:00Z Fill value inserted for E_pow_f1__C3_PP_EFW: No reason given for time range 2005-01-01T14:58:00Z to 2005-01-01T15:01:00Z Fill value inserted for E_sigma__C3_PP_EFW: No reason given for time range 2005-01-01T14:58:00Z to 2005-01-01T15:01:00Z Fill value inserted for U_probe_sc__C3_PP_EFW: No reason given for time range 2005-01-01T14:58:00Z to 2005-01-01T15:01:00Z
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A. D. Johnstone et al, Peace, A Plasma Electron and Current Experiment Space Sci. Rev., 79, pp 351 - 398, 1997)
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003 PP & SP data is generated at MSSL, then provided to UK-CDHF
See CSDS User's Guide, DS-MPA-TN-0015, for post processing caveats This is PEACE PP/SP data version 3.1, produced at MSSL Based on onboard moments but using corrected geometric factors which account for uplinked changes of the values used in onboard calibration as well as estimated changes due to variable MCP gain performance Onboard moments are calculated for up to three energy ranges. Photoelectron contamination may affect 0, 1 or 2 of these ranges EFW PP probe-spacecraft potential was used to select the energy ranges to be excluded to remove misleading photoelectron contributions. Note that the density may be underestimated if there are both plasma electrons and photoelectrons in the lowest energy range When 88h58 is used for the HEEA sensor, sometimes the entire plasma electron population and photoelectrons are in just the lowest of the 3 energy ranges. This data has been deleted in this release of the PEACE PPs Data is deleted if the spacecraft electric potential is too large for the simple correction procedure to work or there is no EFW PP data available Measured electron energies have not been corrected for their acceleration by the spacecraft electric potential Onboard moments use onboard energy tables, efficiencies and response surfaces. Any errors in these parameters cannot be corrected in ground data processing Before 2001-09-11 the onboard energy efficiencies were not accurate, which caused the density in the solar wind to be overestimated. This data has been removed in this release of the PEACE PPs The calculation of T_par, T_perp and Q_par used PP FGM data The data is for context and information only. It is not suitable for detailed analysis, but may be used for event selection The next iteration of PP/SP moments will be of a higher quality Please see links under http://www.mssl.ucl.ac.uk/www_plasma/missions/cluster/clusterII.html for more information Please contact the PEACE PI to request science quality data Automatically validated by UKCDC Product delivered pre-validated by the PI institute
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N. Cornilleau et al, The Cluster Spatio-Temporal Analysis of Field Fluctuations (Staff) Experiment Space Sci. Rev., 79, pp 107 - 136, 1997)
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003
See CSDS User's Guide, DS-MPA-TN-0015, for post processing caveats PI Software Version 4.1, 27 March 2006
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P. M. E. Decreau et al, WHISPER, A Resonance Sounder and Wave Analyser: Performances and Perspectives for the Cluster Mission Space Sci. Rev., 79, pp 157 - 193, 1997)
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003
See CSDS User's Guide, DS-MPA-TN-0015, for post processing caveats Two types of parameters are provided by WHISPER: 1) Density values (and quality): N_e_res and N_e_res_q, are related to sounding operations. The N_e_res value is calculated from an algorithm for resonance recognition, which cannot take account of all level of information available to the experimenter. The reliability of N_e_res parameters derived at the CSDS level is thus limited in an unknown manner. The N_e_res_q parameter (one value for each N_e_res data point) provides a crude idea of the probability that the N_e_res value is actually correct. A value of 0 means that the value is probably wrong, a value above 80 that it is probably correct. Anything in between reflects a crude evaluation of the chances. Refer to PI for details. 2) Wave power values: E_pow_f4, E_pow_f5, E_pow_f6, E_pow_su and E_var_ts, are related to recording of natural wave emissions. Those parameters, not affected by variations in instrument's transfer functions, are globally OK. However, two factors can affect the precision of the measurements: a) the occasional presence of spurious emissions created by operations of the EDI instrument increases the wave power values measured on SC1, SC2 and SC3, from an unknown amount, b) the limited dynamical range of the instrument leads to an underestimation of the E_pow parameters values when the voltage difference measured by the double sphere antenna signal in the 2 - 80 kHz band is higher than 150 mVp or 600 mVp (depending of the gain chosen). As a consequence, high values have to be taken with special caution.
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M.A. Hapgood et al, The Joint Science Operations Centre, Space Sci. Rev. 79, 487-525 (1997)
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003
JSOC predicted magnetic positions.
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M.A. Hapgood et al, The Joint Science Operations Centre, Space Sci. Rev. 79, 487-525 (1997) AP _ Apogee CY 1 Start of visibility window at Canberra (5 deg elevation) CY 2 Start of visibility window at Canberra (5 deg elevation) CY 3 Start of visibility window at Canberra (5 deg elevation) CZ 1 End of visibility window at Canberra (5 deg elevation) CZ 2 End of visibility window at Canberra (5 deg elevation) CZ 3 End of visibility window at Canberra (5 deg elevation) CZ 4 End of visibility window at Canberra (5 deg elevation) DY 1 Start of visibility window at Vilspa (5 deg elevation) DY 2 Start of visibility window at Vilspa (5 deg elevation) DY 3 Start of visibility window at Vilspa (5 deg elevation) DY 4 Start of visibility window at Vilspa (5 deg elevation) DZ 1 End of visibility window at Vilspa (5 deg elevation) DZ 2 End of visibility window at Vilspa (5 deg elevation) DZ 3 End of visibility window at Vilspa (5 deg elevation) GY 1 Start of visibility window at Goldstone (5 deg elevation) GY 2 Start of visibility window at Goldstone (5 deg elevation) GY 3 Start of visibility window at Goldstone (5 deg elevation) GY 4 Start of visibility window at Goldstone (5 deg elevation) GZ 1 End of visibility window at Goldstone (5 deg elevation) GZ 2 End of visibility window at Goldstone (5 deg elevation) GZ 3 End of visibility window at Goldstone (5 deg elevation) JY 1 Start of visibility window at Maspalomas (5 deg elevation) JY 2 Start of visibility window at Maspalomas (5 deg elevation) JY 3 Start of visibility window at Maspalomas (5 deg elevation) JY 4 Start of visibility window at Maspalomas (5 deg elevation) JZ 1 End of visibility window at Maspalomas (5 deg elevation) JZ 2 End of visibility window at Maspalomas (5 deg elevation) JZ 3 End of visibility window at Maspalomas (5 deg elevation) KA 1 Start of visibility window at Kourou (5 deg elevation) KA 2 Start of visibility window at Kourou (5 deg elevation) KA 3 Start of visibility window at Kourou (5 deg elevation) KA 4 Start of visibility window at Kourou (5 deg elevation) KL 1 End of visibility window at Kourou (5 deg elevation) KL 2 End of visibility window at Kourou (5 deg elevation) KL 3 End of visibility window at Kourou (5 deg elevation) KL 4 End of visibility window at Kourou (5 deg elevation) MY 1 Start of visibility window at Madrid (5 deg elevation) MY 2 Start of visibility window at Madrid (5 deg elevation) MY 3 Start of visibility window at Madrid (5 deg elevation) MY 4 Start of visibility window at Madrid (5 deg elevation) MZ 1 End of visibility window at Madrid (5 deg elevation) MZ 2 End of visibility window at Madrid (5 deg elevation) MZ 3 End of visibility window at Madrid (5 deg elevation) NS S Southbound neutral sheet NT I Enter north tail lobe from inner magnetosphere PA 1 Start of visibility window at Perth (5 deg elevation) PA 2 Start of visibility window at Perth (5 deg elevation) PA 3 Start of visibility window at Perth (5 deg elevation) PA 4 Start of visibility window at Perth (5 deg elevation) PE _ Perigee PL 1 End of visibility window at Perth (5 deg elevation) PL 2 End of visibility window at Perth (5 deg elevation) PL 3 End of visibility window at Perth (5 deg elevation) PL 4 End of visibility window at Perth (5 deg elevation) PL 5 End of visibility window at Perth (5 deg elevation) QL I Inbound critical L value for auroral zone QL O Outbound critical L value for auroral zone RA 1 Start of visibility window at Redu (5 deg elevation) RA 2 Start of visibility window at Redu (5 deg elevation) RA 3 Start of visibility window at Redu (5 deg elevation) RL 1 End of visibility window at Redu (5 deg elevation) RL 2 End of visibility window at Redu (5 deg elevation) RL 3 End of visibility window at Redu (5 deg elevation) ST O Leave south tail lobe for inner magnetosphere TL I Inbound radiation belt entry for WEC TL O Outbound radiation belt exit for WEC VL I Inbound critical L value for EDI VL O Outbound critical L value for EDI WL B Outbound critical L value 2 for ASPOC WL I Inbound critical L value for ASPOC WL O Outbound critical L value for ASPOC XL I Inbound critical L value for PEACE XL O Outbound critical L value for PEACE YL I Inbound critical L value for RAPID YL O Outbound critical L value for RAPID ZL I Inbound critical L value for CIS ZL O Outbound critical L value for CIS
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003 IGRF2000 pole used to calculate GSM latitude and MLT in PSE files produced after 25 June 2001.
JSOC predicted scientific events.
Back to top
G. Paschmann et al, The Electron Drift Instrument for Cluster Space Sci. Rev., 79, pp 233 - 269, 1997)
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003
See CSDS User's Guide, DS-MPA-TN-0015, for post processing caveats C4 EDI switched off
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G. Gustafsson et al, The Electric Field and Wave Experiment for Cluster Space Sci. Rev., 79, pp 137 - 156, 1997)
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003 Data calibration may be unreliable at this early stage of the mission
See CSDS User's Guide, DS-MPA-TN-0015, for post processing caveats *** CSDS data are not for publication *** Be aware that data may be reprocessed as necessary to improve quality For questions on data validity please contact sdc-adm@plasma.kth.se Fill value inserted for E_dusk__C4_PP_EFW: No reason given for time range 2005-01-01T14:58:00Z to 2005-01-01T15:01:00Z Fill value inserted for E_pow_f1__C4_PP_EFW: No reason given for time range 2005-01-01T14:58:00Z to 2005-01-01T15:01:00Z Fill value inserted for E_sigma__C4_PP_EFW: No reason given for time range 2005-01-01T14:58:00Z to 2005-01-01T15:01:00Z Fill value inserted for U_probe_sc__C4_PP_EFW: No reason given for time range 2005-01-01T14:58:00Z to 2005-01-01T15:01:00Z
Back to top
A. D. Johnstone et al, Peace, A Plasma Electron and Current Experiment Space Sci. Rev., 79, pp 351 - 398, 1997)
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003 PP & SP data is generated at MSSL, then provided to UK-CDHF
See CSDS User's Guide, DS-MPA-TN-0015, for post processing caveats This is PEACE PP/SP data version 3.1, produced at MSSL Based on onboard moments but using corrected geometric factors which account for uplinked changes of the values used in onboard calibration as well as estimated changes due to variable MCP gain performance Onboard moments are calculated for up to three energy ranges. Photoelectron contamination may affect 0, 1 or 2 of these ranges EFW PP probe-spacecraft potential was used to select the energy ranges to be excluded to remove misleading photoelectron contributions. Note that the density may be underestimated if there are both plasma electrons and photoelectrons in the lowest energy range When 88h58 is used for the HEEA sensor, sometimes the entire plasma electron population and photoelectrons are in just the lowest of the 3 energy ranges. This data has been deleted in this release of the PEACE PPs Data is deleted if the spacecraft electric potential is too large for the simple correction procedure to work or there is no EFW PP data available Measured electron energies have not been corrected for their acceleration by the spacecraft electric potential Onboard moments use onboard energy tables, efficiencies and response surfaces. Any errors in these parameters cannot be corrected in ground data processing Before 2001-09-11 the onboard energy efficiencies were not accurate, which caused the density in the solar wind to be overestimated. This data has been removed in this release of the PEACE PPs The calculation of T_par, T_perp and Q_par used PP FGM data The data is for context and information only. It is not suitable for detailed analysis, but may be used for event selection The next iteration of PP/SP moments will be of a higher quality Please see links under http://www.mssl.ucl.ac.uk/www_plasma/missions/cluster/clusterII.html for more information Please contact the PEACE PI to request science quality data Automatically validated by UKCDC Product delivered pre-validated by the PI institute
Back to top
N. Cornilleau et al, The Cluster Spatio-Temporal Analysis of Field Fluctuations (Staff) Experiment Space Sci. Rev., 79, pp 107 - 136, 1997)
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003
See CSDS User's Guide, DS-MPA-TN-0015, for post processing caveats PI Software Version 4.1, 27 March 2006
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P. M. E. Decreau et al, WHISPER, A Resonance Sounder and Wave Analyser: Performances and Perspectives for the Cluster Mission Space Sci. Rev., 79, pp 157 - 193, 1997)
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003
See CSDS User's Guide, DS-MPA-TN-0015, for post processing caveats Two types of parameters are provided by WHISPER: 1) Density values (and quality): N_e_res and N_e_res_q, are related to sounding operations. The N_e_res value is calculated from an algorithm for resonance recognition, which cannot take account of all level of information available to the experimenter. The reliability of N_e_res parameters derived at the CSDS level is thus limited in an unknown manner. The N_e_res_q parameter (one value for each N_e_res data point) provides a crude idea of the probability that the N_e_res value is actually correct. A value of 0 means that the value is probably wrong, a value above 80 that it is probably correct. Anything in between reflects a crude evaluation of the chances. Refer to PI for details. 2) Wave power values: E_pow_f4, E_pow_f5, E_pow_f6, E_pow_su and E_var_ts, are related to recording of natural wave emissions. Those parameters, not affected by variations in instrument's transfer functions, are globally OK. However, two factors can affect the precision of the measurements: a) the occasional presence of spurious emissions created by operations of the EDI instrument increases the wave power values measured on SC1, SC2 and SC3, from an unknown amount, b) the limited dynamical range of the instrument leads to an underestimation of the E_pow parameters values when the voltage difference measured by the double sphere antenna signal in the 2 - 80 kHz band is higher than 150 mVp or 600 mVp (depending of the gain chosen). As a consequence, high values have to be taken with special caution.
Back to top
M.A. Hapgood et al, The Joint Science Operations Centre, Space Sci. Rev. 79, 487-525 (1997)
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003
JSOC predicted Solar cycle trends.
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M.A. Hapgood et al, The Joint Science Operations Centre, Space Sci. Rev. 79, 487-525 1997 For geometrical configuration parameters, p328 of Tetrahedron Geometric Factors by P.Robert et al, in Analysis Methods for Multi-Spacecraft Data, ed. G.Paschmann & P.Daly, pub. 1998 by the European Space Agency and the International Space Institute, Bern.
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003 IGRF2000 pole used to calculate dipole tilt and GSE-GSM angle in PGP files produced after 25 June 2001.
JSOC predicted Orbits. Using spacecraft C3 as reference spacecraft.
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Pre-generated PWG plots
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K. Torkar et al, Active spacecraft potential control for Cluster - implementation and first results Ann. Geophys., 19, pp 1289 - 1302, 2001)
none Reference Document for CSDS CDF File Design, DS-QMW-TN-0003
See CSDS User's Guide, DS-MPA-TN-0015, for post processing caveats One raw data format (5.1.5 secs) of bad data may occur when the instrument is powered on.
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Orbital Parameters Calculated from Short Term Orbit File of RDM For geometry configuration parameters, see p 328 of Tetrahedron Geometric Factors by P.Robert et al, in Analysis Methods for Multi-Spacecraft Data, ed. G.Paschmann & P.Daly, pub. 1998 by the European Space Agency and the International Space Institute, Bern.
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003 IGRF 10th generation pole used to calculate GSE-to-GSM angle and dipole tilt from 1 January 2005
See CSDS User's Guide, DS-MPA-TN-0015, for post processing caveats
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H. Reme et al, First multispacecraft ion measurements in and near the Earth's magnetosphere with the identical Cluster Ion Spectrometry (CIS) experiment Annales Geophysicae, 19, pp 1303 - 1354, 2001
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003
See CSDS User's Guide, DS-MPA-TN-0015, for post processing caveats The user of the CIS data needs to be cautious. Please refer to the CIS Home Page: http://cis.cesr.fr:8000/CIS_sw_home-en.htm , link "Caveats for the CIS data", for caveats concerning these data.
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L. J. C. Woolliscroft et al, The Digital Wave-Processing Experiment on Cluster Space Sci. Rev., 79, pp 209 - 231, 1997)
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003 Operational version of UKCDHF Pipeline software SP file for S/C Cluster 3
See CSDS User's Guide, DS-MPA-TN-0015, for post processing caveats Refer to the PI or NDC for access to ongoing caveat information Use correlator data with caution
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G. Paschmann et al, The Electron Drift Instrument for Cluster Space Sci. Rev., 79, pp 233 - 269, 1997)
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003
See CSDS User's Guide, DS-MPA-TN-0015, for post processing caveats 1) EDI's automated analysis algorithm has a known susceptibility to producing occasional incorrect values of the drift velocities (and electric fields). The code attempts to prevent these bad values to be output to the cdf file. No further removal is done in the validation process. 2) When drift velocities become sufficiently large, there can be a 180-degree ambiguity in drift direction that is usually flagged in bit 7 (counting from 0) of Status Byte 3. 3) There are two methods to analyze a spin's worth of EDI data. If bits 5 6 in Status Byte 3 are NOT set, the employed method was triangulation. If either bit 5 or 6 are set, then the results are from time-of-flight analysis. 4) The reported drift velocities and electric field refer to inertial coordinates, i.e., have been corrected for spacecraft velocity. However, the magnitude errors (in %) and the angle errors (in degrees), reported in Status Bytes 5 & 6, respectively, refer to the spacecraft frame and have NOT yet been converted to inertial coordinates. 5) The reduced chi-square reported as a data word is a measure of the goodness-of-fit of the triangulation analysis.
Back to top
G. Gustafsson et al, The Electric Field and Wave Experiment for Cluster Space Sci. Rev., 79, pp 137 - 156, 1997)
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003 Data calibration may be unreliable at this early stage of the mission
See CSDS User's Guide, DS-MPA-TN-0015, for post processing caveats *** CSDS data are not for publication *** Be aware that data may be reprocessed as necessary to improve quality For questions on data validity please contact sdc-adm@plasma.kth.se
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A. Balogh et al, The Cluster Magnetic Field Investigation Space Sci. Rev., 79, pp 65 - 92, 1997)
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003 Operational version of UKCDHF Pipeline software SP file for S/C Cluster 3
See CSDS User's Guide, DS-MPA-TN-0015, for post processing caveats *** CAUTION Preliminary calibrations used: not for publication ***
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A. D. Johnstone et al, Peace, A Plasma Electron and Current Experiment Space Sci. Rev., 79, pp 351 - 398, 1997)
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003 PP & SP data is generated at MSSL, then provided to UK-CDHF
See CSDS User's Guide, DS-MPA-TN-0015, for post processing caveats This is PEACE PP/SP data version 3.1, produced at MSSL Based on onboard moments but using corrected geometric factors which account for uplinked changes of the values used in onboard calibration as well as estimated changes due to variable MCP gain performance Onboard moments are calculated for up to three energy ranges. Photoelectron contamination may affect 0, 1 or 2 of these ranges EFW PP probe-spacecraft potential was used to select the energy ranges to be excluded to remove misleading photoelectron contributions. Note that the density may be underestimated if there are both plasma electrons and photoelectrons in the lowest energy range When 88h58 is used for the HEEA sensor, sometimes the entire plasma electron population and photoelectrons are in just the lowest of the 3 energy ranges. This data has been deleted in this release of the PEACE PPs Data is deleted if the spacecraft electric potential is too large for the simple correction procedure to work or there is no EFW PP data available Measured electron energies have not been corrected for their acceleration by the spacecraft electric potential Onboard moments use onboard energy tables, efficiencies and response surfaces. Any errors in these parameters cannot be corrected in ground data processing Before 2001-09-11 the onboard energy efficiencies were not accurate, which caused the density in the solar wind to be overestimated. This data has been removed in this release of the PEACE PPs The calculation of T_par, T_perp and Q_par used PP FGM data The data is for context and information only. It is not suitable for detailed analysis, but may be used for event selection The next iteration of PP/SP moments will be of a higher quality Please see links under http://www.mssl.ucl.ac.uk/www_plasma/missions/cluster/clusterII.html for more information Please contact the PEACE PI to request science quality data Automatically validated by UKCDC Product delivered pre-validated by the PI institute
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B. Wilken et al, RAPID, The Imaging Energetic Particle Spectrometer on Cluster Space Sci. Rev., 79, pp 399 - 473, 1997)
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003 Data processed on 2007-02-15T14:09:42Z
See CSDS User's Guide, DS-MPA-TN-0015, for post processing caveats Caveats file: CAV_3_059.DAT; Release Feb 13, 2007 RAPID Data produced with best-effort general calibration files. Expert IIMS calibration: with approx. inter-SC factors. The results are not to be considered final. Central ion head not functioning, no sensitivity near ecliptic. Corrected time stamps for ions and electrons. Energy threshold shifts have been applied. No background count rates have been subtracted. Changed EDB format, on-board anisotropies not possible in NM
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N. Cornilleau et al, The Cluster Spatio-Temporal Analysis of Field Fluctuations (Staff) Experiment Space Sci. Rev., 79, pp 107 - 136, 1997)
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003
See CSDS User's Guide, DS-MPA-TN-0015, for post processing caveats PI Software Version 4.1, 27 March 2006
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Reference to uiowa cluster site
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P. M. E. Decreau et al, WHISPER, A Resonance Sounder and Wave Analyser: Performances and Perspectives for the Cluster Mission Space Sci. Rev., 79, pp 157 - 193, 1997)
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003
See CSDS User's Guide, DS-MPA-TN-0015, for post processing caveats Two types of parameters are provided by WHISPER: 1) Density values (and quality): N_e_res and N_e_res_q, are related to sounding operations. The N_e_res value is calculated from an algorithm for resonance recognition, which cannot take account of all level of information available to the experimenter. The reliability of N_e_res parameters derived at the CSDS level is thus limited in an unknown manner. The N_e_res_q parameter (one value for each N_e_res data point) provides a crude idea of the probability that the N_e_res value is actually correct. A value of 0 means that the value is probably wrong, a value above 80 that it is probably correct. Anything in between reflects a crude evaluation of the chances. Refer to PI for details. 2) Wave power values: E_pow_f4, E_pow_f5, E_pow_f6, E_pow_su and E_var_ts, are related to recording of natural wave emissions. Those parameters, not affected by variations in instrument's transfer functions, are globally OK. However, two factors can affect the precision of the measurements: a) the occasional presence of spurious emissions created by operations of the EDI instrument increases the wave power values measured on SC1, SC2 and SC3, from an unknown amount, b) the limited dynamical range of the instrument leads to an underestimation of the E_pow parameters values when the voltage difference measured by the double sphere antenna signal in the 2 - 80 kHz band is higher than 150 mVp or 600 mVp (depending of the gain chosen). As a consequence, high values have to be taken with special caution.
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A. Balogh et al, The Cluster Magnetic Field Investigation Space Sci. Rev., 79, pp 65 - 92, 1997)
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003 Operational version of UKCDHF Pipeline software
See CSDS User's Guide, DS-MPA-TN-0015, for post processing caveats *** CL_US_FGM_20061031 HAS NOT BEEN VALIDATED - USE WITH CAUTION *** For the extended mission (starting 1/1/2006) CSDS FGM products are not validated prior to release to the science community. Spikes and other artefacts that were previously removed during validation of the FGM PP/SP data may occur in these files.
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Images and intensities. 557.7nm Images binned to geodetic grid References: 1.Rostoker, G., Samson, J.C., Creutzberg, F., Hughes, T.J., McDiarmid, D.R., McNamara, A.G., Vallance Jones, A., Wallis, D.D., Cogger, L.L.; CANOPUS - a ground based instrument array for remote sensing the high latitude ionosphere during the ISTP/GGS program, Space Sci. Rev., submitted for publication, 1993.
Created 29-DEC-1994
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North & East Velocity components at 336.5 EDFL long. from 64.2 to 67.0 EDFL lat. References: 1.Rostoker, G., Samson, J.C., Creutzberg, F., Hughes, T.J., McDiarmid, D.R., McNamara, A.G., Vallance Jones, A., Wallis, D.D., Cogger, L.L.; CANOPUS - a ground based instrument array for remote sensing the high latitude ionosphere during the ISTP/GGS program, Space Sci. Rev., submitted for publication, 1993.
Created 18-JUL-1994
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Magnetic Field Extrema and Location References: 1.Rostoker, G., Samson, J.C., Creutzberg, F., Hughes, T.J., McDiarmid, D.R., McNamara, A.G., Vallance Jones, A., Wallis, D.D., Cogger, L.L.; CANOPUS - a ground based instrument array for remote sensing the high latitude ionosphere during the ISTP/GGS program, Space Sci. Rev., submitted for publication, 1993.
Created 19-AUG-1994
More sites => greater quality
Geodetic latitude of station that measured the extrema used to compute the local auroral electrojet idex CL
Geodetic latitude of station that measured the extrema used to compute the local auroral electrojet idex CU
Geodetic longitude of station that measured the extrema used to compute the local auroral electrojet idex CL
Geodetic longitude of station that measured the extrema used to compute the local auroral electrojet idex CU
Local equivalent to AL index, but computed from magnetic field perturbations measured at stations of the CANOPUS array
Local equivalent to AU index, but computed from magnetic field perturbations measured at specific stations of the CANOPUS array
Station Status, Merged Scaled 5577A Scans and Peak Intensity Merged Scans>from 3 stations along constant Geodetic Long. of 265, from Lat. 46 to 67 References: 1.Rostoker, G., Samson, J.C., Creutzberg, F., Hughes, T.J., McDiarmid, D.R., McNamara, A.G., Vallance Jones, A., Wallis, D.D., Cogger, L.L.; CANOPUS - a ground based instrument array for remote sensing the high latitude ionosphere during the ISTP/GGS program, Space Sci. Rev., submitted for publication, 1993. 2.Samson, J.C., Lyons, L.R., Newell, P.T., Creutzberg, F. and Xu, B., Proton aurora substorm intensifications, Geophys. Res. Letters, 19, 2167, 1992. 3.Samson, J.C., Hughes, T.J., Creutzberg, F., Wallis, D.D., Greenwald, R.A. and Ruohoniemi, J.M., Observations of a detached discrete arc in association with field line resonances, J. Geophys. Res., 96, 15, 683, 1991.
Created 18-DEC-1994
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Riometer measurements and Location References: 1.Rostoker, G., Samson, J.C., Creutzberg, F., Hughes, T.J., McDiarmid, D.R., McNamara, A.G., Vallance Jones, A., Wallis, D.D., Cogger, L.L.; CANOPUS - a ground based instrument array for remote sensing the high latitude ionosphere during the ISTP/GGS program, Space Sci. Rev., submitted for publication, 1993.
Created 19-AUG-1994
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CRRES MEA Data Archive This is the re-processed version of the MEA data archive from the CRRES spacecraft. The raw data provided by Principal Investigator A. Vampola have been processed to derive 1 min average data. The data consists of counting rates from 17 energy channels in the range of 0.1-2 MeV and 19 pitch angle bins at 1 minute time intervals. The average flux, 90 degree flux and N value are included. Also included are the spacecraft geographic coordinates and altitude, L shell, and the local and equatorial magnetic field magnitudes from the 1977 Olson-Pfitzer model of the earth's geomagnetic field. The raw high resolution (0.512 sec) data and documentation of raw data can be found at:ftp://nssdcftp.gsfc.nasa.gov/spacecraft_data/crres/particle_mea.
Created May 2003
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M.A. Hapgood et al, The Joint Science Operations Centre, Space Sci. Rev. 79, 487-525 (1997) NS S Southbound neutral sheet NT I Enter north tail lobe from inner magnetosphere ST O Leave south tail lobe for inner magnetosphere
Produced in accordance with CSDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003 IGRF2000 pole used to calculate GSM latitude and MLT in PSE files produced after 25 June 2001.
JSOC predicted scientific events.
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Instrument functional description:
The spin-scan auroral imagers (SAI) comprise three photometers which
provide images of Earth at various wavelengths via interference filters
mounted on a wheel and selected by ground command. Two of the photometers
provide visible wavelength images, and the third provides images at
vacuum-ultraviolet wavelengths.
The three photometers are mounted on the spacecraft such that their
fields of view are separated by about 120 degrees in a plane oriented
perpendicular to the spin axis. Each photometer in operation collects
one scan line during each spacecraft rotation, with an internal mirror
stepping once per rotation to start a new scan line.
An auroral image is a nadir-centered two-dimensional pixel array
provided by the spacecraft rotation and the photometer's stepping mirror
which advances the field of view 0.25 degrees once per rotation in a
direction perpendicular to the plane of rotation. A change in mirror-
stepping direction signals the start of a new image. One, two, or
three photometers may be in operation at one time. The images from all
operating photometers are telemetered simultaneously with image repetition
rates that typically vary from about 3 to 12 minutes.
One of the three imaging photometers is equipped with filters and a
photocathode for observations at vacuum-ultraviolet wavelengths, in
particular emissions of the Lyman-Birge-Hopfield band of molecular
nitrogen at about 140 to 170 nm. Imaging at these wavelengths allows
coverage of the auroral oval in both the dark and sunlit ionospheres.
The filter array for the vacuum-ultraviolet imaging photometer also
includes filters for atomic hydrogen Lyman alpha at 121.6 nm and oxygen
lines at 130.4 and 135.6 nm.
The full width of the fields of view of the photometers
corresponding to a single pixel is 0.29 degrees. An image frame
consists of all scan lines obtained by mirror steps in one direction
which deflect the field of view by 0.25 degrees per rotation. The
angular separation of two consecutive pixels in the direction of
spacecraft rotation is about 0.23 degrees. A full frame has 120
scan lines or 30 degrees of width. For routine processing the
angular width along a scan line is 150 pixels, or about 34.5 degrees
of length. The frame width is occasionally adjusted to less than
120 scan lines.
Reference:
Frank, L. A., J. D. Craven, K. L. Ackerson, M. R. English, R. H. Eather,
and R. L. Carovillano, Global auroral imaging instrumentation for
the Dynamics Explorer mission, Space Sci. Inst., 5, 369-393, 1981.
Data set description:
Each DE SAI UV image CDF contains all of images collected by the
UV photometer during one day of operations. The displayable image
counts are in variable 3.
Coordinates are calculated for each position of the image count array.
These coordinates are in variables 14, 15, and 16.
To facilitate viewing of the images, a mapping of pixel value to a
recommended color table based on the characteristics of the selected
filter will be included with each image. See the description of variables
17, 18, and 19 below.
A relative intensity scale is provided by the uncompressed count
table of variable 20. Approximate intensity levels in kiloRayleighs are
given in the intensity table of variable 21.
Other variables provide orbit and attitude data and information about
the selected filter and the mirror stepping direction.
Variable descriptions:
1,2. Start time
The time assigned to an image is the start time of the initial scan
line within a resolution of one second.
3. Image counts
Image pixel counts range from 0 to 255. They are stored in a two-
dimensional byte array of 121 columns by 150 rows. Each column
contains one scan line. Images will generally not fill all of the
121 columns. When an image is displayed with row 1 at the top and
column 1 on the left, the spacecraft spin axis is oriented to the
left in the display, and the orbit normal vector is oriented to the
right.
4. Filter
Twelve filters are available for ultra-violet imaging; the filter
number, 1-12, is given here. In addition, the peak wavelength in
Angstroms is given for the selected filter.
5. Presumed altitude of emissions
The presumed altitude of the emissions seen in the image varies
with the characteristics of the filter used.
6,7. First and last mirror location counters (MLCs)
The MLC range is from 28 in column 1 (leftmost) to 148 in column 121
(rightmost). The direction of mirror stepping motion is shown by
comparing first and last MLCs.
8. Orbit/attitude time
Whenever possible, the approximate center time of the image is used
for determining the orbit and attitude parameters. If O/A data is
not available for the center time, the closest available O/A time
is used.
9. Spacecraft position vector, GCI
10. Spacecraft velocity vector, GCI
11. Spacecraft spin axis unit vector, GCI
12. Sun position unit vector, GCI
13. Orbit normal unit vector, GCI
14. Geographic longitude or right ascension
East longitude is given for each image pixel on the Earth at the
altitude given in variable 5. When the pixel altitude is greater
than the value of variable 5, the right ascension is given.
15. Geographic latitude or declination
North latitude is given for each image pixel on the Earth at the
altitude given in variable 5. When the pixel altitude is greater
than the value of variable 5, the declination is given.
16. Pixel altitude
For each image pixel on the Earth, the presumed altitude of the
emissions is used. This is equal to the value of variable 5. For each
pixel off the Earth, the altitude of the line of sight is used.
17. Pixel UT
This array gives the start time for the collection of each image pixel.
18. RGB color table
This is the recommended color table to be used with the
limits given in variables 19 and 20.
19,20. Low and high color mapping limits
The low and high color limits are recommended for remapping
the color table entries, as follows:
For pixel values less than the low limit, use the color
at table position 1.
For pixel values greater than or equal to the low limit
and less than or equal to the high limit, use the color
at table position (pix-low)/(high-low) x 255 + 1.
For pixel values greater than the high limit, use the color
at table position 256.
21. Expanded count table
The image pixel counts are quasi-logarithmically compressed to the
range 0-255. This table gives the average of the uncompressed range
for each compressed count value. Table entries 1-128 correspond to
compressed counts 0-127 respectively. Count levels greater than
127 are considered overflow.
22. Intensity table
For each of the twelve filters, approximate intensity levels in
kiloRayleighs are given for each compressed count value. Table
entries 1-128 correspond to compressed counts 0-127 respectively.
No count conversion data is available for count levels greater than
127.
Supporting software:
Directions for obtaining supporting software is available on the SAI
website at the URL .http://www-pi.physics.uiowa.edu/www/desai/software/.
Included is an IDL program that displays the images with the recommended
color bar and provides approximate intensities and coordinate data for
each pixel.
Image_Counts contains the displayable image in 121 columns by 150 rows of pixels. Most images will use 120 of the columns. The counts have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value for Image_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Approximate intensity in kR is Intens_Table(Image_Counts(i,j)+1).The appearance of the actual count value 255 is rare. When displaying an image,it works best to use the fill value as an overflow (i.e. brightest) value.
Presumed altitude of emissions for every pixel on the Earth, equal to the value of the variable AltF; altitude of line of sight for every pixel off the Earth
Approximate intensity in kR for Image_Counts(i,j) is Intens_Tables( Image_Counts(i,j)+1), Filter(1) ). Intensities cannot be computed for image count values greater than 127.
Image_Counts contains pixel counts which have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value forImage_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Compressed pixel counts greater than 127 are considered overflow.
Geographic north latitude for every image pixel on the Earth, declination for every pixel off the Earth
Geographic east longitude for every image pixel on the Earth, right ascension for every pixel off the Earth
RGBColorTable should be remapped for displaying an image using the low and high limits given for each image in Limit_Lo and Limit_Hi.Image_Counts count values less than Limit_Lo use the color at table position 1. Count values greater than Limit_Hi use the color at table position 256. For count values greater than or equal to Limit_Lo and less than or equal to Limit_Hi, the table position is (Count-Limit_Lo)/(Limit_Hi-Limit_Lo) x 255 + 1.At the selected table position C, the color components are Red at RGBColorTable(1,C), Green at RGBColorTable(2,C), and Blue at RGBColorTable(3,C).
Image_Counts contains the displayable image in 121 columns by 150 rows of pixels. Most images will use 120 of the columns. The counts have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value for Image_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Approximate intensity in kR is Intens_Table(Image_Counts(i,j)+1).The appearance of the actual count value 255 is rare. When displaying an image,it works best to use the fill value as an overflow (i.e. brightest) value.
No TEXT global attribute value.
Created October, 1995 by W.K. Peterson Add Q_FLAG_FILE_CORRUPTED variable to indicate intervals for which full data quality information is not available. 10/10/95
Information variable. Does not apply to data in this CDF. If set to 0 information about the direction of plasma motion with respect to the satellite motion may be obtained from the the full resolution EICS_STAND_ALONE_TELEMETRY_FILE_SYSTEM archived at NSSDC. This is the A data quality flag described in the EICSDATA.LIS file and other documentation accompanying the EICS_STAND_ALONE_TELEMETRY_FILE_SYSTEM from NSSDC or on line on the DE project home page on the Space Physics Data System.
Because the backgrounddoes, at times, vary rapidly on the 96 second averaging period the background counting rate has been interpolated intime to reflect the expected background counting rate at the center of the averaging interval. The ion flux may be time alised in regions of rapidly varying INTERPOLATED_BACKGROUND.
This variable is displayed as a bitwisespectrogram by the idl check_cdf.pro code available from pete@willow.space.lockheed.com Interpretation of Values: 0/1: 0=He+ data. 1=No He+ data 0/2: 0=NOT BCLIST N flag indicating that data are missing or care must be taken in processing or interpreting them. 2= N flag on. 0/4: 0=NOT BCLIST C flag indicating that data in the lowest energy channel are contaminated by extra counts from a EUV photoionization of residual gas in the input aperture. 4=C flag on. 0/8: 0=NOT BCLIST A flag indicating that full attitude are available in the full archived data file. Attitude data are not required or available for the pitch angle organized data processed into the cdf files here. 8= A flag on. 0/16: 0=Not NOISY data Flag manually entered after scan of summary spectrogram 16= Noisy flag on. 0/32: 0=NOT TOO SHORT. Interpretation of Noisy data and other problems was difficult from files containing less than about 7 minutes of data. This flag was manually set from reading summary spectrograms. 32= Data interval too short. 0/64: 0=Complete pitch angle coverage determined from visual inspection of summary spectrograms 64= Incomplete pitch angle coverage. 0/128: See Q_FLAG_FILE_CORRUPTED variable described below.
Some valid data may be included in the telemetry segment, but some of the data in the segment are invalid and must not be includedin long term average data sets.This is the N flag described in the EICSDATA.LIS file and other documentation accompanying the EICS_STAND_ALONE_TELEMETRY_FILE_SYSTEM from NSSDC or on line on the DE project home page on the Space Physics Data System. This flag is set on a telemetryinterval (segment) basis.
Values obtained from various sources.
Values obtained from various sources.
Negative fluxes reflect low count rates and background subtraction. The width of lowest energy channel is variable. Pitch angle coverage is NOT uniform. Conversion to velocity space density, calculations of density and other operations involving division by a characteristic energy are limited in accuracy by energy bands that are wide compared to the fall off of flux with energy.
The first of the 15 energy channels has a variable lower limit and center energy. The remaining 14 energy channels have fixed lower, and upper limits that are specified by Center_energy and the DELTA_PLUS_VAR and DELTA_MINUS_VAR Attribute E_delta.
He+ fluxes are available for approximately 50% of the data intervalsin this archive. He_data is set on a per record basis
Negative fluxes reflect low count rates and background subtraction. The width of lowest energy channel is variable. Pitch angle coverage is NOT uniform. Conversion to velocity space density, calculations of density and other operations involving division by a characteristic energy are limited in accuracy by energy bands that are wide compared to the fall off of flux with energy.
The first (lowest) of the 15 energy channels has a variable lower limit and center energy. The variable Low_energy_cut_off specifies the lower limit of the lowest energy channel. The remaining 14 energy channels have fixed lower, center, and upper limits that are specified by DELTA_PLUS_VAR and DELTA_MINUS_VAR Attribute E_delta. The value in this table (0.062 keV) is the normal center energy for the lowest energy channel, i.e. when Low_energy_cut_off = 0.01 keV.
The Center_energy of the lowest energy channel must be corrected for Low_energy_cut_off above 0.015 keV
Center time of 96 second accumulation intervals, starting at 0 seconds of each UT day
Negative fluxes reflect low count rates and background subtraction. The width of lowest energy channel is variable. Pitch angle coverage is NOT uniform. Conversion to velocity space density, calculations of density and other operations involving division by a characteristic energy are limited in accuracy by energy bands that are wide compared to the fall off of flux with energy.
Uncertainly estimated from the observed total signal counts. The width of lowest energy channel is variable. Pitch angle coverage is NOT uniform.
Uncertainly estimated from the observed total signal counts. The width of lowest energy channel is variable. Pitch angle coverage is NOT uniform.
Uncertainly estimated from the observed total signal counts. The width of lowest energy channel is variable. Pitch angle coverage is NOT uniform.
Determined from the total number ofbackground counts observed in the 96averaging period.
Data for some pitch angle ranges may contain fill indicating that the full pitch angle range was notsampled. This occurs when the magnetic field does not lie within the satellite spin plane. The flag is set to 1 when a visual examination of color spectrograms show that data are not available in all pitch angle bins. This flag is set on a telemetry segment basis.
Variable width Pitch Angle Bins covering 0-7.5, 7.5-15, 15-30, 30-45, 45-60, 60-75 75-90, 90-105, 105-120, 120-135, 135-150, 150-165, 165-172.5, and 172.5-180 degrees. This provides highest angular resolution along the magnetic field direction.
Quality flag information for DE/EICSwas created in a keyed file using VMSspecific file management. In the almost15 years this file has been maintained records for some time intervals have become corrupted. Some quality informationcan be found in the data catalog available with the DE/EICS Stand Alone Telemetry Files (SATF) from NSSDC
Set to 1 when a visual examination of color spectrogram showed the lowest energy channel included a spurious count rate caused by the photoionization of residual neutral gases in in the preacceleration region of the spectrometer as described in Shelley et al. Geophys. Res. Lett. 9, p942, 1982. This is the C data quality flag described in the EICSDATA.LIS file and other documentation accompanying the EICS_STAND_ALONE_TELEMETRY_FILE_SYSTEM from NSSDC or on line on the DE project home page on the Space Physics Data System.
This flag is set on a telemetryinterval basis. A visual examination of color spectrograms indicated some 96 second dataintervals with extremely high counting rates. These intervals were identified by their characteristic patchyness on energy-time and angle-time spectrograms. Data from intervals where the Noisy_flag=1 WERE NOT included in the large-scale statistical studies referenced in the global attributes.Some valid data may be included in the telemetry segment
1 indicates that a visual examination of color spectrograms was not possible because the data interval was too short. The data quality flags that depend on visual examination are: C_flag, A_flag, Noisy_flag, and PA_coverage_flag.
Center time of 96 second accumulation intervals, starting at 0 seconds of each UT day
No TEXT global attribute value.
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No TEXT global attribute value.
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No TEXT global attribute value.
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vlptm $Revision: 4.3
skeleton table implemented new formats with all the DEPEND attrs set ISTP KPGS Standard & Conventions version 1 implemented
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vlptm $Revision: 4.5
skeleton table implemented new formats with all the DEPEND attrs set ISTP KPGS Standard & Conventions version 1 implemented
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vlptm $Revision: 4.3
skeleton table implemented new formats with all the DEPEND attrs set ISTP KPGS Standard & Conventions version 1 implemented
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vlptm $Revision: 4.3
skeleton table implemented new formats with all the DEPEND attrs set ISTP KPGS Standard & Conventions version 1 implemented
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vlptm version 2.42 Ref1: Satellite Experiments Simultaneous with Antarctic Measurements (SESAME) to be submitted to Reviews of Geophysics (copy held by GGS group at NASA) Ref2:Baker et al.,EOS 70,p785 1989. Ref3: Greenwald et al.,Radio Sci.20,p63 1985 Info:Keith Morrison,GGS Scientist,British AntarcticSurvey,Cambridge,CB3 0ET,UK E-mail: 19989::MORRISON
skeleton table implemented new formats with all the DEPEND attrs set ISTP KPGS Standard & Conventions version 1 implemented
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vlptm $Revision: 4.5
skeleton table implemented new formats with all the DEPEND attrs set ISTP KPGS Standard & Conventions version 1 implemented
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vlptm $Revision: 4.3
skeleton table implemented new formats with all the DEPEND attrs set ISTP KPGS Standard & Conventions version 1 implemented
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see EQS-MPE-EDC-01, Equator-S Data Center Manual, section 4.8 AUX
Produced in accordance with ESDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003
See also `TEXT' global attr. for Caveats file location
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see EQS-MPE-EDC-01, Equator-S Data Center Manual, section 4.2 EDI
Produced in accordance with ESDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003
See also `TEXT' global attr. for Caveats file location
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see EQS-MPE-EDC-01, Equator-S Data Center Manual, section 4.5 EPI
Produced in accordance with ESDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003
See also `TEXT' global attr. for Caveats file location
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see EQS-MPE-EDC-01, Equator-S Data Center Manual, section 4.3 ICI
Produced in accordance with ESDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003 none
This file has particularly bad background problems due to intense radiation belts after 16:00 UT. This file contains both onboard calculated moments (labeled "raw" with an "*" in the name) and moments calculated on the ground from 3D distributions (labeled "final"). Quantitative analysis should be done with the "final" moments. The raw data should only be used qualitatively for identifying regions and temporal variations. It has large errors, particularly in Vz in spacecraft coordinates. O+ and He+ data should not be used in the magnetosheath or at low L-values, due to background problems. Contact the LI at Lynn.Kistler@unh.edu if the data you need is not available on-line.
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see EQS-MPE-EDC-01, Equator-S Data Center Manual, section 4.1 MAM
Produced in accordance with ESDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003
See also `TEXT' global attr. for Caveats file location
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see EQS-MPE-EDC-01, Equator-S Data Center Manual, section 4.6 PCD
Produced in accordance with ESDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003
See also `TEXT' global attr. for Caveats file location
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see EQS-MPE-EDC-01, Equator-S Data Center Manual, section 4.8 AUX
Produced in accordance with ESDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003
See also `TEXT' global attr. for Caveats file location
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see EQS-MPE-EDC-01, Equator-S Data Center Manual, section 4.5 EPI
Produced in accordance with ESDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003
See also `TEXT' global attr. for Caveats file location
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see EQS-MPE-EDC-01, Equator-S Data Center Manual, section 4.3 ICI
Produced in accordance with ESDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003 none
This file has particularly bad background problems due to intense radiation belts after 16:00 UT. This file contains both onboard calculated moments (labeled "raw" with an "*" in the name) and moments calculated on the ground from 3D distributions (labeled "final"). Quantitative analysis should be done with the "final" moments. The raw data should only be used qualitatively for identifying regions and temporal variations. It has large errors, particularly in Vz in spacecraft coordinates. O+ and He+ data should not be used in the magnetosheath or at low L-values, due to background problems. Contact the LI at Lynn.Kistler@unh.edu if the data you need is not available on-line.
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see EQS-MPE-EDC-01, Equator-S Data Center Manual, section 4.1 MAM
Produced in accordance with ESDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003
See also `TEXT' global attr. for Caveats file location
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see EQS-MPE-EDC-01, Equator-S Data Center Manual, section 4.6 PCD
Produced in accordance with ESDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003
See also `TEXT' global attr. for Caveats file location
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see EQS-MPE-EDC-01, Equator-S Data Center Manual, section 4.7 SFD
Produced in accordance with ESDS file specification Reference Document for CSDS CDF File Design, DS-QMW-TN-0003
See also `TEXT' global attr. for Caveats file location
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none yet
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Carlson et al., 1983, Adv. Space Res. 2(7), 67. Data are derived from a pair of hemisperical electrostatic analyzers with 180 degree radial FOVs that together form a single 360 deg x 4.5 deg planar FOV in the spin spacecraft plane. Sensors can deflect their FOV by up to +/-10 deg to follow the magnetic field direction which is within +/-6 deg of the spin plane for most auroral crossings. Absolute geometric factors are the best estimate at the time of key parameter data production (20% uncertainty). Key parameter data are averaged for 1 spin. Any change in sensor configuration or onboard data storage during a spin result in a rejection of the spin average. Electron Sensor Parameters: Inner Hemisphere R = 3.75 cm dR/R = 0.06 FOV = 360 deg x 4.5 (FWHM) deg Angular resolution = 11.25 deg x 4.5 deg Energy range: 4 eV to 30 keV dE/E = 0.15 (FWHM) Geometric Factor = 0.0047 x E (cm2-sr-eV) Key Parameter Data: Electron Energy-Time Spectrogram, 0-30 deg pitch angle Electron Energy-Time Spectrogram, 60-120 deg pitch angle Electron Energy-Time Spectrogram, 150-180 deg pitch angle Electron Pitch Angle-Time Spectrogram, 0.1-1.0 keV Electron Pitch Angle-Time Spectrogram, 1.0-30.0 keV Electron Energy Flux mapped along B to 100 km altitude Electron Number Flux mapped along B to 100 km altitude
Initial version April 9, 1997
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Carlson et al., 1983, Adv. Space Res. 2(7), 67. Data are derived from a pair of hemisperical electrostatic analyzers with 180 degree radial FOVs that together form a single 360 deg x 6.5 deg planar FOV in the spin spacecraft plane. Sensors can deflect their FOV by up to +/-10 deg to follow the magnetic field direction which is within +/-6 deg of the spin plane for most auroral crossings. Absolute geometric factors are the best estimate at the time of key parameter data production (20% uncertainty). Key parameter data are averaged for 1 spin. Any change in sensor configuration or onboard data storage during a spin result in a rejection of the spin average. Ion Sensor Parameters: Inner Hemisphere R = 3.75 cm dR/R = 0.075 FOV = 360 deg x 6.5 (FWHM) deg Angular resolution = 11.25 deg x 6.5 deg Energy range: 3 eV to 25 keV dE/E = 0.20 (FWHM) Geometric Factor = 0.0136 x E (cm2-sr-eV) Key Parameter Data: Ion Energy-Time Spectrogram, 0-30 deg pitch angle Ion Energy-Time Spectrogram, 40-140 deg pitch angle Ion Energy-Time Spectrogram, 150-180 deg pitch angle Ion Pitch Angle-Time Spectrogram, 0.05-1.0 keV Ion Pitch Angle-Time Spectrogram, 1.0-25.0 keV Ion Energy Flux mapped along B to 100 km altitude Ion Number Flux mapped along B to 100 km altitude
Initial version April 9, 1997
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The Time-of-Flight Energy, Angle, Mass Spectrograph (TEAMS) Experiment for FAST, D. M. Klumpar, E. Moebius, L. M. Kistler, M. Popecki, E. G. Shelley, E. Hertzberg, K. Crocker, M. Granoff, Li Tang, C. W. Carlson, J. McFadden, B. Klecker, F. Eberl, E. Kuenneth, H. Kaestle, M. Ertl, W. K. Peterson, and D. Hovestadt, to be published, Space Science Reviews, D. Reidel Publishing Co., Dordrecht, Holland, 1997. The 3-D Plasma Distribution Function Analyzers with Time-of-Flight Mass Discrimination for CLUSTER, FAST, and Equator-S, E. Moebius, L. M. Kistler, M. Popecki, K. Crocker, M. Granoff, Y. Jiang, E. Satori, V. Ye, H. Reme, J. A. Sauvaud, A. Cros, A. Aoustin, T. Camus, J. L. Medale, J. Rouzaud, C. W. Carlson, J. McFadden, D. Curtis, H. Heetdirks, J. Croyle, C. Ingraham, E. G. Shelley, D. M. Klumpar, E. Hertzberg, B. Klecker, M. Ertl, F. Eberl, H. Kaestle, E. Kuenneth, P. Laeverenz, E. Seidenschwang, G. Parks, M. McCarthy, A. Korth, B. Graeve, H. Balsiger, U. Schwab, and M. Steinacher, Measurement Techniques for Space Plasmas, J. Borovsky, R. Pfaff, D. Young, eds., American Geophysical Union, Washington, DC, in press, 1997. Data are derived from a time-of-flight mass spectrograph that determines 3-dimensional distribution functions of individual ion species over the energy range 1 - 12000 eV, within 2.5 seconds (one-half spacecraft spin). The instrument consists of a toroidal top-hat electrostatic analyzer with instantaneous acceptance of ions over 360 degrees in polar angle in 16 sectors. Ions passing through the electrostatic analyzer are postaccelerated by up to 25 kV and then analyzed for mass per charge in a foil-based time-of-flight analyzer. The data used to construct CDF data products are derived from the Survey data. Survey data consists of 4 mass groups x 48 energies x 64 solid angle segments. The 4 mass groups are H+, O+, He+, and He++. Only the 16 equatorial angle segments are used for the CDF data set. Each equatorial solid angle segment contains 2 (4) samples at each energy in the 32 (64) sweep/spin mode. The full angular range is covered in half a spin but the actual time resolution of the survey data product depends upon the telemetry mode. In the highest TM rate modes H+ and O+ survey data read out every half spin. In lowest TM rate mode these data are accumulated for 4 spins. The minimum accumulation time included in the CDF is 1 spin, so if the actual accumulation time is a half spin, two data points are averaged. Otherwise, the full resolution is included. In every mode He+ and He++ are accumulated twice as long as H+ and O+. To force the H+, O+, and He+ to have an equal number of data points when H+ and O+ have twice the time resolution, each He+ data point is written twice consecutively in the file.
none yet
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Keograms are quick-look data of an all-sky camera at Kilpisjarvi (69.02 N, 20.79 E) maintained and operated by the Finnish Meteorological Institute. Keograms show the intensity along the middle meridian of the camera field-of-view as a function of time. The camera has a fish-eye lens of 180 degrees and narrow bandpass interference filters of wavelengths 557.7 nm (green) and 630.0 nm (red). In standard operating mode, the sampling interval is 20 s and 60 s for the red and green images, respectively. The exposure time is typically 1000 ms. The time resolution of keograms is 1 min and they are constructed using only the green images. The size of a digital image is 512x512 pixels and intensity values vary between 0 and 255. At the altitude of 110 km the field-of-view (with reasonable spatial resolution) is a spherical area with the diameter of 600 km. The keograms shown here are intensity versus latitude plots while the original keograms (available in http://www.geo.fmi.fi/MIRACLE are intensity versus zenith angle plots. The conversion from zenith angle dependence to equidistant latitude grid causes occasionally artificial two-band structure to the keograms (light bands below and above the darker zenith). The artefact becomes visible especially during quiet periods, and the autoscaling color palette may even strengthen the effect. Note that some keograms show also the Moon as a sphere or ellipsoid with very high, even saturating intensities.
CDF created 31.05.1999 11:32:29 UTC.
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The NOAA Geostationary Operational Environmental Satellite (GOES) key parameters are obtained from the Energetic Particle Sensor (EPS) and the magnetometer (MAG). The key parameters are a subset of the data available from the GOES Space Environment Monitor (SEM) instruments. The energetic particle fluxes are given as five-minute averaged values and the vector magnetic field is given as one-minute average values. Flux values for three integral electron channels (E >0.6 MeV, E >2.0 MeV, and E >4.0 MeV) and one differential proton channel(0.7 MeV < E <4 MeV) are provided. These data are used by NOAA Space Environment Center (SEC) for the real-time monitoring and prediction of the conditions in the Earth's space environment. A new series of GOES spacecraft began with GOES-8 launched on 4/13/94, GOES-9 launched on 5/23/95, and GOES-10 launched on 4/25/97. Typically two satellites are maintained operational,one at about 135 degrees geographic west longitude and one at about 75 degrees geographic west longitude. The satellite inclination is typically within a few tenths of a degree of the geographic equator. However, the satellites can be moved, especially during the six months to one year following launch, and the inclination can increase after years of satellite operation. Instrument data quality flags are set from real-time telemetry, or, in the case of historically-processed data sets when telemetry is not available, fixed to a level-1 instrument status flag for all data Reference: Geostationary Operational Environmental Satellite GOES I-M System Description, compiled by John Savides, Space Systems/Loral, Palo Alto, California, December 1992. Dr. Terrance Onsager, NOAA/SEC, tonsager@sec.noaa.gov, 303-497-5713, Boulder CO 80303 USA, or Martin Black, NOAA/SEC, mblack@sec.noaa.gov, 303-497-7235, 325 Broadway, Boulder CO 80303 USA NOTICE: GOES 12 energetic particle data are not available due to the failure of two proton channels in the detectors. These channels were used for the correction and processing of the proton and electron data. Beginning April 8, 2003, the GOES energetic particle data are obtained from GOES 10 only.
Version 2.0: 1st operational version,-db, 14 Jul 92 Corrected S/C location error & added Geographic (not geodetic) & GEO S/C positions. -db, 16 Feb 93 Added unit_ptr to s/c position units fixed CATDES on SC_pos_sm, fixed GSn -db, 20 Apr 93 Version 3.0: Major re-write, added GOES-8 and GOES-9, -db 22 Feb 96. Fixed 1-character xyz label problem, -db, 8 May 96 Minor text & label changes, -db, 29 Jul 96 Added global metadata, support_data text, blank variable attrib. data per Mona Kessel sample file, -db, 5 Aug 96 Added xyz GEO,GSE,GSM labels, replacing 1 cartesian label -db, 29 Aug 96 Create 1 skeleton table for EPS for all GOES preparing for the switch from GOES-9 to 10 -anewman, 22 Jul 1998 Added GOES-10 launch date and replaced Ann Newman with me as contact person. -mblack, 18 Mar 1999
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Pre-generated PWG plots
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The NOAA Geostationary Operational Environmental Satellite (GOES) key parameters are obtained from the Energetic Particle Sensor (EPS) and and the magnetometer (MAG). The key parameters are a subset of the data available from the GOES Space Environment Monitor (SEM) instruments. The vector magnetic field is given as one-minute averaged values in three coordinate systems: (1) Spacecraft (s/c) P,E,N, (2) GSM x,y,z, (3) GSE x,y,z s/c mag. field is defined as: Hp, perpendicular to the satellite orbital plane or parallel to the Earths spin axis in the case of a zero degree inclination orbit; He, perpendicular to Hp and directed earthwards; and Hn, perpendicular to both Hp and directed eastwards. These data are used by NOAA Space Environment Center (SEC) for the real-time monitoring and prediction of the conditions in the Earth's space environment. A new series of GOES spacecraft began with GOES-8 launched on 4/13/94, GOES-9 launched on 5/23/95, and GOES-10 launched on 4/25/97. Typically two satellites are operational,one at about 135 degrees geographic west longitude and one at about 75 degrees geographic west longitude. The satellite inclination is typically within a few tenths of a degree of the geographic equator. However, the satellites can be moved, especially during the six months to one year following launch, and the inclination can increase after years of satellite operation. Instrument data quality flags are set from real-time telemetry, or, in the case of historically-processed data sets when telemetry is not available, fixed to a level-1 instrument status flag for all data Reference: Monitoring Space Weather with GOES Magnetometers, Singer, H.J, L. Matheson, R.Grubb A.Newman, and S.D.Bouwer, SPIE Proceedings, Volume 2812, 4-9 Aug 1996. For more info, contact: Dr. Howard Singer, NOAA/SEC, hsinger@sec.noaa.gov, 303-497-6959, Boulder CO 80303 USA, or Martin Black, NOAA/SEC, mblack@sec.noaa.gov, 303-497-7235, 325 Broadway, Boulder CO 80303 USA
Version 2.0: 1st operational version,-db, 15 Dec 92 Corrected S/C location error & added Geographic (not geodetic) & GEO S/C positions Fixed ADID_ref from 97 to 96 -db, 16 Feb 93 Added unit_ptr to s/c position units, fixed CATDES on SC_pos_sm, fixed GSn -db, 27 Apr 93 Version 3.0, Major re-write of text, corrected label_1 bug (now cartesian), added GOES-8 & 9 CDFs,-db,26 Jan 1996 Corrected no. of elements on lines 477-479 (labels), -db 7 May 1996 Minor text changes, -db 22 Jul 1996 Added global metadata, support_data text, blank variable attrib. data per Mona Kessel sample file, -db, 5 Aug 96 Added xyz GEO,GSE,GSM labels, replacing 1 cartesian label -db, 29 Aug 96 Create 1 skeleton table for MAG for all GOES preparing for the switch from GOES-9 to 10 -anewman, 22 Jul 1998 Added GOES-10 launch data and replaced Ann Newman with Martin Black as contact person. -mblack, 18 Mar 1999
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The NOAA GOES satellites include 2 sensors: an Energetic Particle Sensor (EPS), and a Magnetometer (MAG). The satellites are geostationary. For older satellites, inclination may be up to 15 deg. Data sometimes contains errors. especially GOES-6 EPS & possibly both GOES 6,7 magnetometers. The EPS data are 5-min. averages, the MAG data are 1-min. averages. The NOAA Space Environment Lab (SEL), Space Environ. Services Center (SESC) uses this data in real time for forecasting and monitoring. Reference: GOES Spacecraft OperationsManual, Volume I, May 1980, Hughes RefNo. D5150 SCG 00169R GOES-8, with 3 electron sensors should launch in early 93: the IE variables will be defined post-launch. For additional info., contact Dave Bouwer, NOAA/SEL, Mail Code R/E/SE, 325 Broadway, Boulder, CO 80303 USA (303)497-3899. SELVAX::DBOUWER or dbouwer@selvax.sel.bldrdoc.gov
Version 2.0: 1st operational version,-db, 14 Jul 92 Corrected S/C location error & added Geographic (not geodetic) & GEO S/C positions. -db, 16 Feb 93 Added unit_ptr to s/c position units fixed CATDES on SC_pos_sm, fixed GSn -db, 20 Apr 93
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The NOAA GOES satellites include 2 sensors: an Energetic Particle Sensor (EPS), and a Magnetometer (MAG). The satellites are geostationary. For older satellites, inclination may be up to 15 deg. Data sometimes contains errors. The EPS data are 5-min. averages, the MAG data are 1-min. averages. B s/c has undeterm. errors in x,y B field for GSM and GSE is missing while corrections are developed. The NOAA Space Environment Lab (SEL), Space Environ. Services Center (SESC) uses this data in real time for forecasting and monitoring. Reference: GOES Spacecraft OperationsManual, Volume I, May 1980, Hughes RefNo. D5150 SCG 00169R GOES-8, with 3 electron sensors should launch in early 93: the IE variables will be defined post-launch. For additional info., contact Dave Bouwer, NOAA/SEL, Mail Code R/E/SE, 325 Broadway, Boulder, CO 80303 USA (303)497-3899. SELVAX::DBOUWER or dbouwer@selvax.sel.bldrdoc.gov
Version 2.0: 1st operational version,-db, 15 Dec 92
This variable not available for GOES-6
This variable not available for GOES-6
Spacecraft coordinates (PEN), P=north, E=earth, N=normal
The NOAA GOES satellites include 2 sensors: an Energetic Particle Sensor (EPS), and a Magnetometer (MAG). The satellites are geostationary. For older satellites, inclination may be up to 15 deg. Data sometimes contains errors. especially GOES-6 EPS & possibly both GOES 6,7 magnetometers. The EPS data are 5-min. averages, the MAG data are 1-min. averages. The NOAA Space Environment Lab (SEL), Space Environ. Services Center (SESC) uses this data in real time for forecasting and monitoring. Reference: GOES Spacecraft OperationsManual, Volume I, May 1980, Hughes RefNo. D5150 SCG 00169R GOES-8, with 3 electron sensors should launch in early 93: the IE variables will be defined post-launch. For additional info., contact Dave Bouwer, NOAA/SEL, Mail Code R/E/SE, 325 Broadway, Boulder, CO 80303 USA (303)497-3899. SELVAX::DBOUWER or dbouwer@selvax.sel.bldrdoc.gov
Version 2.0: 1st operational version,-db, 14 Jul 92 Corrected S/C location error & added Geographic (not geodetic) & GEO S/C positions. -db, 16 Feb 93 Added unit_ptr to s/c position units fixed CATDES on SC_pos_sm, fixed GSn -db, 20 Apr 93
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The NOAA GOES satellites include 2 sensors: an Energetic Particle Sensor (EPS), and a Magnetometer (MAG). The satellites are geostationary. For older satellites, inclination may be up to 15 deg. Data sometimes contains errors. The EPS data are 5-min. averages, the MAG data are 1-min. averages. B s/c has undeterm. errors in x,y B field for GSM and GSE is missing while corrections are developed. The NOAA Space Environment Lab (SEL), Space Environ. Services Center (SESC) uses this data in real time for forecasting and monitoring. Reference: GOES Spacecraft OperationsManual, Volume I, May 1980, Hughes RefNo. D5150 SCG 00169R GOES-8, with 3 electron sensors should launch in early 93: the IE variables will be defined post-launch. For additional info., contact Dave Bouwer, NOAA/SEL, Mail Code R/E/SE, 325 Broadway, Boulder, CO 80303 USA (303)497-3899. SELVAX::DBOUWER or dbouwer@selvax.sel.bldrdoc.gov
Version 2.0: 1st operational version,-db, 15 Dec 92
This variable not available for GOES-6
This variable not available for GOES-6
Spacecraft coordinates (PEN), P=north, E=earth, N=normal
The NOAA GOES satellites include 2 sensors: an Energetic Particle Sensor (EPS), and a Magnetometer (MAG). The satellites are geostationary. For older satellites, inclination may be up to 15 deg. Data sometimes contains errors. The EPS data are 5-min. averages, the MAG data are 1-min. averages. B s/c has undeterm. errors in x,y B field for GSM and GSE is missing while corrections are developed. The NOAA Space Environment Lab (SEL), Space Environ. Services Center (SESC) uses this data in real time for forecasting and monitoring. Reference: GOES Spacecraft OperationsManual, Volume I, May 1980, Hughes RefNo. D5150 SCG 00169R GOES-8, with 3 electron sensors should launch in early 93: the IE variables will be defined post-launch. For additional info., contact Dave Bouwer, NOAA/SEL, Mail Code R/E/SE, 325 Broadway, Boulder, CO 80303 USA (303)497-3899. SELVAX::DBOUWER or dbouwer@selvax.sel.bldrdoc.gov
Version 1.0: 1st operational version, RLK, July 2000
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The NOAA Geostationary Operational Environmental Satellite (GOES) key parameters are obtained from the Energetic Particle Sensor (EPS) and the magnetometer (MAG). The key parameters are a subset of the data available from the GOES Space Environment Monitor (SEM) instruments. The energetic particle fluxes are given as five-minute averaged values and the vector magnetic field is given as one-minute average values. Flux values for three integral electron channels (E >0.6 MeV, E >2.0 MeV, and E >4.0 MeV) and one differential proton channel(0.7 MeV < E <4 MeV) are provided. These data are used by NOAA Space Environment Center (SEC) for the real-time monitoring and prediction of the conditions in the Earth's space environment. A new series of GOES spacecraft began with GOES-8 launched on 4/13/94 and GOES-9 launched on 5/23/95. Typically two satellites are maintained operational,one at about 135 degrees geographic west longitude and one at about 75 degrees geographic west longitude. The satellite inclination is typically within a few tenths of a degree of the geographic equator. However, the satellites can be moved, especially during the six months to one year following launch, and the inclination can increase after years of satellite operation. Reference: Geostationary Operational Environmental Satellite GOES I-M System Description, compiled by John Savides, Space Systems/Loral, Palo Alto, California, December 1992. Dr. Terrance Onsager, NOAA/SEC, tonsager@sec.noaa.gov, 303-497-5713, Boulder CO 80303 USA, or Dave Bouwer, NOAA/SEC, dbouwer@sel.noaa.gov, 303-497-3899, 325 Broadway, Boulder CO 80303 USA
Version 2.0: 1st operational version,-db, 14 Jul 92 Corrected S/C location error & added Geographic (not geodetic) & GEO S/C positions. -db, 16 Feb 93 Added unit_ptr to s/c position units fixed CATDES on SC_pos_sm, fixed GSn -db, 20 Apr 93 Version 3.0: Major re-write, added GOES-8 and GOES-9, -db 22 Feb 96. Fixed 1-character xyz label problem, -db, 8 May 96 Minor text & label changes, -db, 29 Jul 96 Added global metadata, support_data text, blank variable attrib. data per Mona Kessel sample file, -db, 5 Aug 96 Added xyz GEO,GSE,GSM labels, replacing 1 cartesian label -db, 29 Aug 96
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The NOAA Geostationary Operational Environmental Satellite (GOES) key parameters are obtained from the Energetic Particle Sensor (EPS) and and the magnetometer (MAG). The key parameters are a subset of the data available from the GOES Space Environment Monitor (SEM) instruments. The vector magnetic field is given as one-minute averaged values in three coordinate systems: (1) Spacecraft (s/c) P,E,N, (2) GSM x,y,z, (3) GSE x,y,z s/c mag. field is defined as: Hp, perpendicular to the satellite orbital plane or parallel to the Earths spin axis in the case of a zero degree inclination orbit; He, perpendicular to Hp and directed earthwards; and Hn, perpendicular to both Hp and directed eastwards. These data are used by NOAA Space Environment Center (SEC) for the real-time monitoring and prediction of the conditions in the Earth's space environment. A new series of GOES spacecraft began with GOES-8 launched on 4/13/94 and GOES-9 launched on 5/23/95. Typically two satellites are operational,one at about 135 degrees geographic west longitude and one at about 75 degrees geographic west longitude. The satellite inclination is typically within a few tenths of a degree of the geographic equator. However, the satellites can be moved, especially during the six months to one year following launch, and the inclination can increase after years of satellite operation. Reference: Monitoring Space Weather with GOES Magnetometers, Singer, H.J, L. Matheson, R.Grubb A.Newman, and S.D.Bouwer, SPIE Proceedings, Volume 2812, 4-9 Aug 1996. For more info, contact: Dr. Howard Singer, NOAA/SEC, hsinger@sec.noaa.gov, 303-497-6959, Boulder CO 80303 USA, or Dave Bouwer, NOAA/SEC, dbouwer@sec.noaa.gov, 303-497-3899, 325 Broadway, Boulder CO 80303 USA
Version 2.0: 1st operational version,-db, 15 Dec 92 Corrected S/C location error & added Geographic (not geodetic) & GEO S/C positions Fixed ADID_ref from 97 to 96 -db, 16 Feb 93 Added unit_ptr to s/c position units, fixed CATDES on SC_pos_sm, fixed GSn -db, 27 Apr 93 Version 3.0, Major re-write of text, corrected label_1 bug (now cartesian), added GOES-8 & 9 CDFs,-db,26 Jan 1996 Corrected no. of elements on lines 477-479 (labels), -db 7 May 1996 Minor text changes, -db 22 Jul 1996 Added global metadata, support_data text, blank variable attrib. data per Mona Kessel sample file, -db, 5 Aug 96 Added xyz GEO,GSE,GSM labels, replacing 1 cartesian label -db, 29 Aug 96
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The NOAA Geostationary Operational Environmental Satellite (GOES) key parameters are obtained from the Energetic Particle Sensor (EPS) and the magnetometer (MAG). The key parameters are a subset of the data available from the GOES Space Environment Monitor (SEM) instruments. The energetic particle fluxes are given as five-minute averaged values and the vector magnetic field is given as one-minute average values. Flux values for three integral electron channels (E >0.6 MeV, E >2.0 MeV, and E >4.0 MeV) and one differential proton channel(0.7 MeV < E <4 MeV) are provided. These data are used by NOAA Space Environment Center (SEC) for the real-time monitoring and prediction of the conditions in the Earth's space environment. A new series of GOES spacecraft began with GOES-8 launched on 4/13/94 and GOES-9 launched on 5/23/95. Typically two satellites are maintained operational,one at about 135 degrees geographic west longitude and one at about 75 degrees geographic west longitude. The satellite inclination is typically within a few tenths of a degree of the geographic equator. However, the satellites can be moved, especially during the six months to one year following launch, and the inclination can increase after years of satellite operation. Reference: Geostationary Operational Environmental Satellite GOES I-M System Description, compiled by John Savides, Space Systems/Loral, Palo Alto, California, December 1992. Dr. Terrance Onsager, NOAA/SEC, tonsager@sec.noaa.gov, 303-497-5713, Boulder CO 80303 USA, or Dave Bouwer, NOAA/SEC, dbouwer@sel.noaa.gov, 303-497-3899, 325 Broadway, Boulder CO 80303 USA
Version 2.0: 1st operational version,-db, 14 Jul 92 Corrected S/C location error & added Geographic (not geodetic) & GEO S/C positions. -db, 16 Feb 93 Added unit_ptr to s/c position units fixed CATDES on SC_pos_sm, fixed GSn -db, 20 Apr 93 Version 3.0: Major re-write, added GOES-8 and GOES-9, -db 22 Feb 96. Fixed 1-character xyz label problem, -db, 8 May 96 Minor text & label changes, -db, 29 Jul 96 Added global metadata, support_data text, blank variable attrib. data per Mona Kessel sample file, -db, 5 Aug 96 Added xyz GEO,GSE,GSM labels, replacing 1 cartesian label -db, 29 Aug 96
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The NOAA Geostationary Operational Environmental Satellite (GOES) key parameters are obtained from the Energetic Particle Sensor (EPS) and and the magnetometer (MAG). The key parameters are a subset of the data available from the GOES Space Environment Monitor (SEM) instruments. The vector magnetic field is given as one-minute averaged values in three coordinate systems: (1) Spacecraft (s/c) P,E,N, (2) GSM x,y,z, (3) GSE x,y,z s/c mag. field is defined as: Hp, perpendicular to the satellite orbital plane or parallel to the Earths spin axis in the case of a zero degree inclination orbit; He, perpendicular to Hp and directed earthwards; and Hn, perpendicular to both Hp and directed eastwards. These data are used by NOAA Space Environment Center (SEC) for the real-time monitoring and prediction of the conditions in the Earth's space environment. A new series of GOES spacecraft began with GOES-8 launched on 4/13/94 and GOES-9 launched on 5/23/95. Typically two satellites are operational,one at about 135 degrees geographic west longitude and one at about 75 degrees geographic west longitude. The satellite inclination is typically within a few tenths of a degree of the geographic equator. However, the satellites can be moved, especially during the six months to one year following launch, and the inclination can increase after years of satellite operation. Reference: Monitoring Space Weather with GOES Magnetometers, Singer, H.J, L. Matheson, R.Grubb A.Newman, and S.D.Bouwer, SPIE Proceedings, Volume 2812, 4-9 Aug 1996. For more info, contact: Dr. Howard Singer, NOAA/SEC, hsinger@sec.noaa.gov, 303-497-6959, Boulder CO 80303 USA, or Dave Bouwer, NOAA/SEC, dbouwer@sec.noaa.gov, 303-497-3899, 325 Broadway, Boulder CO 80303 USA
Version 2.0: 1st operational version,-db, 15 Dec 92 Corrected S/C location error & added Geographic (not geodetic) & GEO S/C positions Fixed ADID_ref from 97 to 96 -db, 16 Feb 93 Added unit_ptr to s/c position units, fixed CATDES on SC_pos_sm, fixed GSn -db, 27 Apr 93 Version 3.0, Major re-write of text, corrected label_1 bug (now cartesian), added GOES-8 & 9 CDFs,-db,26 Jan 1996 Corrected no. of elements on lines 477-479 (labels), -db 7 May 1996 Minor text changes, -db 22 Jul 1996 Added global metadata, support_data text, blank variable attrib. data per Mona Kessel sample file, -db, 5 Aug 96 Added xyz GEO,GSE,GSM labels, replacing 1 cartesian label -db, 29 Aug 96
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Fully processed Level 2 solar wind ion data at 2.5-min intervals including proton density (/cc), temperature (K), velocity vectors (km/s) in GSE and RTN systems, alpha/proton ratio, and flags for times of bi-directional electron streaming.
Equals 1 if bi-directional electron streaming is detected, 0 if not.
TBS
6/13/91 - Original Implementation 9/18/91 - Modified for new attitude file format changes. ICCR 881 2/11/92 - Used the variable name TIME and type CDF_INT4 and size 3 instead of EPOCH, CDF_EPOCH and 1 for the time tags. CCR 490 6/1/92 - Added global attributes TITLE, PROJECT, DISCIPLINE, SOURCE_NAME, DATA_VERSION, and MODS; added variable attributes VALIDMIN, VALIDMAX, LABL_PTR_1, and MONOTON; added variables EPOCH and LABEL_TIME; changed variable name TIME to TIME_PB5. CCR 1066 11/07/92 - use cdf variable Epoch and Time_PB5 6/8/93 - Added global attributes ADID_ref and Logical_file_id. CCR 1092 7/5/94 - CCR ISTP 1852, updated CDHF skeleton to CDF standards - JT 9/20/94 - Added global attributes GCI_RA_ERR and GCI_DECL_ERR. CCR 1932 11/7/94 - Merged CCR 1852 changes and corrected errors made in CCR 1852. ICCR 1884 12/7/94 - Modified MODS and LABLAXIS to follow ISTP standards. ICCR 1885
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TBS
6/13/91 - Original Implementation 9/18/91 - Modified for new attitude file format changes. ICCR 881 2/11/92 - Used the variable name TIME and type CDF_INT4 and size 3 instead of EPOCH, CDF_EPOCH and 1 for the time tags. CCR 490 6/1/92 - Added global attributes TITLE, PROJECT, DISCIPLINE, SOURCE_NAME, DATA_VERSION, and MODS; added variable attributes VALIDMIN, VALIDMAX, LABL_PTR_1, and MONOTON; added variables EPOCH and LABEL_TIME; changed variable name TIME to TIME_PB5. CCR 1066 11/07/92 - use cdf variable Epoch and Time_PB5 6/8/93 - Added global attributes ADID_ref and Logical_file_id. CCR 1092 7/5/94 - CCR ISTP 1852, updated CDHF skeleton to CDF standards - JT 9/20/94 - Added global attributes GCI_RA_ERR and GCI_DECL_ERR. CCR 1932 11/7/94 - Merged CCR 1852 changes and corrected errors made in CCR 1852. ICCR 1884 12/7/94 - Modified MODS and LABLAXIS to follow ISTP standards. ICCR 1885
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Editor-A data are only acquired with the real-time operation in Usuda Deep Space Center (UDSC),Japan, while the Editor-B data are 24-hours continuouslyrecorded in the onboard tape recorders and are dumpedover the NASA/JPL Deep Space Network (DSN) stations Please use the Editor-A LEP dataset prior to the Editor-B LEP dataset sinceplasma moments in the Editor-A data are more reliable. (Plasma moments inthe Editor-B are calculated onboard.) The ion energy analyzer (LEP-EAi) has two energy scan mode: RAM-A (60eV to 40 keV) and RAM-B (5 keV to 40 keV). The energy scan mode is automatically selected onboard depending on the incoming ion fluxes. At present, only the plasma moments in the RAM-A mode are plotted (listed) for the LEP-EAi data. (The LEP-EAi moments are presented by the solid lines in the plot.) The plasma moment data of the solar wind analyzer (LEP-SW) should be used only qualitatively. The LEP-SW plasma moments are plotted (listed) when the energy scan mode of LEP-EAi is RAM-B. (The LEP-SW moments are presented by the dotted lines in the plot.) J.Geomag.Geoelectr.,46,669,1994
Created by R. McGuire on 9/1/2003; Adapted from GE_K0_LEP
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The Bz offset is still contained in the magnetic field data. The magnitude of the Bz offset is about 0.5 nT (+-0.3 nT). The corrected version of the magnetic field data will be published soon. Kokubun et al., Geotail Prelaunch Report, ISAS, 58-70, 1992
Created by S.-H. Chen on 6/18/97; Adapted from GE_FO_MGF
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Editor-A data are only acquired with the real-time operation in Usuda Deep Space Center (UDSC),Japan, while the Editor-B data are 24-hours continuously recorded in the onboard tape recorders and are dumped over the NASA/JPL Deep Space Network (DSN) stations. Please use the Editor-A LEP dataset prior to the Editor-B LEP dataset since plasma moments in the Editor-A data are more reliable. (Plasma moments in the Editor-B are calculated onboard.) The ion energy analyzer (LEP-EAi) has two energy scan modes: RAM-A (60eV to 40 keV) and RAM-B (5 keV to 40 keV). The energy scan mode is automatically selected onboard depending on the incoming ion fluxes. At present, only the plasma moments in the RAM-A mode are plotted (listed) for the LEP-EAi data. (The LEP-EAi moments are presented by the solid lines in the plot.) The plasma moment data of the solar wind analyzer (LEP-SW) should be used only qualitatively. The LEP-SW plasma moments are plotted (listed) when the energy scan mode of LEP-EAi is RAM-B. (The LEP-SW moments are presented by the dotted lines in the plot.) J.Geomag.Geoelectr.,46,669, 1994
Created by R. McGuire on 9/1/2003; Adapted from GE_K0_MGF
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The Bz offset is still contained in the magnetic field data. The magnitude of the Bz offset is about 0.5 nT (+-0.3 nT). The corrected version of the magnetic field data will be published soon. Kokubun et al., Geotail Prelaunch Report, ISAS, 58-70, 1992
Created by S.-H. Chen on 6/18/97; Adapted from GE_FO_MGF
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GEOTAIL Prelaunch Report
April 1992, SES-TD-92-007SY
CPI-SW Solar Wind Analyzer
Key Parameters
Ion number density
Average proton energy
Bulk flow velocity
CPI-HP Hot Plasma Analyzer
Key Parameters
Ion number density
Average proton energy
Average electron energy
Bulk flow velocity
Plasma pressure
CPI-IC Ion Composition Analyzer
Key Parameters
Principal Species
H+
He++
He+
O+
CPI Survey Data will be made available
via the World Wide Web as image files
for the mission operation periods in a
compressed time resolution for viewing
and/or downloading with a WWW browser
from the URL
http://www-pi.physics.uiowa.edu/
made from ASCII files at University of IOWA, see URL: http://www-pi.physics.uiowa.edu/www/cpi/
Assuming Vp = Va, P = C * Np * mp * Vp*Vp * [1 + 4(.05)]. mp = 1.67 * 10^(-27), C = 10^(21), Np in #/cc, Vp in km/s. Pressure not provided for density less than 0.3/cc because of the poor counting statistics.
From 5 deg angular bins
Assuming no helium (0.3 - several hundred) if the density is less than 0.3/cc the higher moments (VEL,TEMP) shall not be used because of the poor counting statistics.
calculated by integrating the distribution function
Theta: polar angle in GSE coordinates -- 0 = flow toward north ecliptic pole (positive vz), 90 = flow in spin plane (within 2 degrees of ecliptic), 180 = flow toward south pole (negative vz). Phi: azimuthal angle -- 0 = flow toward sun (positive vx), 90 = flow toward dusk (positive vy), 180 = flow away from sun (negative vx), 270 = flow toward dawn (negative vy)
GEOTAIL Prelaunch Report
April 1992, SES-TD-92-007SY
CPI/HPA Hot Plasma Analyzer
High Time Resolution Moments
Ion Number density
Ion Average Temperature
Ion Bulk Flow Velocity
Electron Number Density
Electron Average Temperature
CPI Survey Data will be made available
via the World Wide Web as image files
for the mission operation periods in a
compressed time resolution for viewing
and/or downloading with a WWW browser
from the URL:
http://www-pi.physics.uiowa.edu/www/cpi/
First Delivery version, 29-JUL-1998 Final Delivery version, 17-AUG-1998
Calculated by integrating the distribution function
calculated by integrating the distribution function
GEOTAIL Prelaunch Report
April 1992, SES-TD-92-007SY
CPI-SW Solar Wind Analyzer
Key Parameters
Ion number density
Average proton energy
Bulk flow velocity
CPI-HP Hot Plasma Analyzer
Key Parameters
Ion number density
Average proton energy
Average electron energy
Bulk flow velocity
Plasma pressure
CPI-IC Ion Composition Analyzer
Key Parameters
Principal Species
H+
He++
He+
O+
CPI Survey Data will be made available
via the World Wide Web as image files
for the mission operation periods in a
compressed time resolution for viewing
and/or downloading with a WWW browser
from the URL
http://www-pi.physics.uiowa.edu/
SPDF/SPOF Supplementary Information and Notes:
First Delivery version, 7-OCT-1993
v2.0, 12-APR-1994, RLD
Changed dimensions to 3 and 2 at
recommendation of Mona Kessel
With help of Jeff Love (CDFSUPPORT)
have cleaned up dim problems
v2.1, 20-JUL-1994, RLD
Change VALIDMIN dates for CPI data
be 1 Oct 92
Added items to TEXT field to
include all KPs and defined
coordinate system used for velocities
v2.2, 24-JAN-1995, RLD
Added some new comments to the
description section
v2.3, 19-MAY-1995, RLD
Added SW_V Z-component
v2.31, 8-Jun-95, RLD
Corrected dependent variables
to differentiate between CDF's
2-D size 2 & 3 (i.e., 2 & 3-
dimensional velocities
v2.4, 28-Sep-95, RLD
Updated text & variable
min/max values for consistency
v2.41, 21-DEC-1995, RLD
Updated for KPGS v2.3 delivery
Official version of ST is v04
CPI Post Gap Flag (0: no gap immediately prior to this record; 1: gap due to inst mode; 2: gap due to missing SIRIUS data; 3: gap due to noisy SIRIUS data; 20: gap due to missing Minor Frame(s)), scalar
From 5 deg angular bins
From 5 deg angular bins
From 5 deg angular bins
From 5 deg angular bins
Geotail Prelaunch Report, April 1992 The sensor providing data here (called EFD-P in report above) measures the difference of electric potential between two electrodes (probes) immersed in the plasma. There are two sperical probes and two wire antennas each of which is extended by 50 meters from the satellite in its rotational plane. The two sperical probes are opposite each other (100 meters tip-to-tip) as are the two wire antennas. The probe pairs are orthogonal to each other. Diving the potential difference by the distance between the probes or the centers of the conducting portion of the wire antennas gives the electric field component along the probe extension. The measurement of the electric field in the satellite rotational plane gives the vector electric field when the electric field along the magnetic field is much smaller than the perpendicular component.
Version 1.0 Jan. 12, 1993 Modified on 7/18/94 and 7/29/94 by JT Modified on 9/9/94 by JT - KPGS CCR 0039
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EPIC Instrument Description:
A) Supra-Thermal Ion Composition Spectrometer (STICS) Subsystem:
1) Ion Head/Telescope Coverage
Apperature Width: 53.4 polar deg
Apperature Center: Spacecraft spin plane
B) Ion Composition Spectrometer (ICS) Subsystem:
1) Ion Head Coverage
Apperature Width: 60.0 polar deg excluding center 16.0 deg
Apperature Center: Spacecraft spin plane
2) Electron Detector Coverage
Apperature Width: 60.0 polar deg
Apperature Center: Spacecraft spin plane
3) Caution
ICS Ion channels can change between two sets of energy pass
bands from record to record; consult the associated energy
information to determine what the current values are.
Anisotropy Calculation Qualification:
A) a1, a2, phi1 and phi2 are not
calculated when the count rate
is below a threshhold, currently
8 counts/96 seconds.
v1.0 19-Sep-1991
v1.3 11-Mar-1992
v2.0 13-Jan-1993 changes for Standards and Convensions v1.1
v3.0 25-May-1994 a) corrected PDiffI_S_Eminus dimen variance FTFF -> TFFF
b) changed LABL_PTR_1 to LABLAXIS for 3 variables
c) removed several DEPEND1 attributes d) corrected indexing for M8/P2
e) corrected anisotropy min/max values from [0,2pi] to
[-pi,+pi] for phi1 and to [-pi/2,+pi/2] for phi2
f) changed ratio SCALETYP from linear to log
g) narrowed several SCALEMIN/MAX ranges
v3.1 16-Sep-1994 a) shortened TEXT entries to max of 80 char
b) removed several DEPEND0/1 attributes
c) removed value for Logical_file_id entry
9-212 keV/e H Anisotropy parameters (a0/a1/a2/phi1/phi2 from Fourier fit a0*(1 + a1*cos(theta-phi1) +a2*cos2(theta-phi2)) to H flux , EPIC/STICS)
9-212 keV/e H Anisotropy parameters (a0/a1/a2/phi1/phi2 from Fourier fit a0*(1 + a1*cos(theta-phi1) +a2*cos2(theta-phi2)) to H flux , EPIC/STICS)
Pre-generated PWG plots
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J.Geomag.Geoelectr.,46,669,1994
created Oct 1994 Modified by JT Oct. 28, 1994
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Kokubun et al., Geotail Prelaunch Report, ISAS, 58-70, 1992
Created on 8/7/92, Modified on 1/25/93, Modified on 2/19/93, Modified on 3/8/93, Modified on 4/16/93, Modified on 7/18/94 by JT
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Text description of the experiment need to be defined by the developer
7/24/92 4/4/94
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Geotail Prelaunch Report April 1992
4/6/92 - Original Implementation, CCR 935 6/12/92 - Added global attributes TITLE, PROJECT, DISCIPLINE, SOURCE_NAME, DATA_VERSION, and MODS; added variable attributes VALIDMIN, VALIDMAX, LABL_PTR_1, and MONOTON; added variables EPOCH and LABEL_TIME; changed variable name TIME to TIME_PB5. CCR 935 9/23/92 - Changed descriptor value from SPAH to SPHA. ICCR 1387 2/22/93 - Changed VALIDMAX of FAULT. CCR 1361 6/10/93 - Added ADID_ref and Logical_file_id. CCR 1092 6/14/94 - CCR ISTP 1852, updated CDHF skeleton to CDF standards - JT 11/9/94 - Correct errors made in ccr 1852. ICCR 1884
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TBS
Originated Monday, May 13, 1991 Modified June 13, 1991 for version 2.1 Modified October 2,1991 for new global attributes, incr sizes Modified 11/11/91 Add sun vector, replace space id with support id Modified 1992 Feb 11 to use the variable name TIME and type CDF_INT4 instead of EPOCH and CDF_EPOCH for the time tags CCR 490 Modified 6/2/92 add project, discipline, source_name, data_version, title, and mods to global section; add validmin, validmax, labl_ptr_1 and monoton attributes to some variables; put epoch time back in, rename time to time_pb5; add label_time to variables Modified 11/07/92 to use Epoch and Time_PB5 variable name Modified 6/2/93 add ADID_ref and Logical_file_id 7/5/94 - CCR ISTP 1852 updated CDHF skeleton to CDF standards - JT 9/21/94 - Added 24 new global attributes to log the ephemeris comparison summary report from the definitive FDF orbit file. CCR 1932 11/7/94 - Merged CCR 1852 changes and corrected errors made in CCR 1852. ICCR 1884 12/7/94 - Modified MODS to follow ISTP standards. ICCR 1885 01/05/95 - add heliocentric coordinate system. CCR 1889 2/28/95 - added COMMENT1 and COMMENT2 for CCR
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Pre-generated PWG plots
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TBS
Originated Monday, May 13, 1991 Modified June 13, 1991 for version 2.1 Modified October 2,1991 for new global attributes, incr sizes Modified 11/11/91 Add sun vector, replace space id with support id Modified 1992 Feb 11 to use the variable name TIME and type CDF_INT4 instead of EPOCH and CDF_EPOCH for the time tags CCR 490 Modified 6/2/92 add project, discipline, source_name, data_version, title, and mods to global section; add validmin, validmax, labl_ptr_1 and monoton attributes to some variables; put epoch time back in, rename time to time_pb5; add label_time to variables Modified 11/07/92 to use Epoch and Time_PB5 variable name Modified 6/2/93 add ADID_ref and Logical_file_id 7/5/94 - CCR ISTP 1852 updated CDHF skeleton to CDF standards - JT 9/21/94 - Added 24 new global attributes to log the ephemeris comparison summary report from the definitive FDF orbit file. CCR 1932 11/7/94 - Merged CCR 1852 changes and corrected errors made in CCR 1852. ICCR 1884 12/7/94 - Modified MODS to follow ISTP standards. ICCR 1885 01/05/95 - add heliocentric coordinate system. CCR 1889 2/28/95 - added COMMENT1 and COMMENT2 for CCR
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The NOAA Geostationary Operational Environmental Satellite (GOES) key parameters are obtained from the Energetic Particle Sensor (EPS) and the magnetometer (MAG). The key parameters are a subset of the data available from the GOES Space Environment Monitor (SEM) instruments. The energetic particle fluxes are given as five-minute averaged values and the vector magnetic field is given as one-minute average values. Flux values for three integral electron channels (E >0.6 MeV, E >2.0 MeV, and E >4.0 MeV) and one differential proton channel(0.7 MeV < E <4 MeV) are provided. These data are used by NOAA Space Environment Center (SEC) for the real-time monitoring and prediction of the conditions in the Earth's space environment. A new series of GOES spacecraft began with GOES-8 launched on 4/13/94, GOES-9 launched on 5/23/95, GOES-10 launched on 4/25/97, GOES-11 launched on 5/3/2000, and GOES-12 launched on 7/23/2001. Typically two satellites are maintained operational,one at about 135 degrees geographic west longitude and one at about 75 degrees geographic west longitude. The satellite inclination is typically within a few tenths of a degree of the geographic equator. However, the satellites can be moved, especially during the six months to one year following launch, and the inclination can increase after years of satellite operation. Instrument data quality flags are set from real-time telemetry, or, in the case of historically-processed data sets when telemetry is not available, fixed to a level-1 instrument status flag for all data Reference: Geostationary Operational Environmental Satellite GOES I-M System Description, compiled by John Savides, Space Systems/Loral, Palo Alto, California, December 1992. Dr. Terrance Onsager, NOAA/SEC, Terry.Onsager@noaa.gov, 303-497-5713, 325 Broadway, Boulder CO 80305 USA, or Ann Newman, NOAA/SEC, Ann.Newman@noaa.gov, 303-497-5100, 325 Broadway, Boulder CO 80305 USA
Version 2.0: 1st operational version,-db, 14 Jul 92 Corrected S/C location error & added Geographic (not geodetic) & GEO S/C positions. -db, 16 Feb 93 Added unit_ptr to s/c position units fixed CATDES on SC_pos_sm, fixed GSn -db, 20 Apr 93 Version 3.0: Major re-write, added GOES-8 and GOES-9, -db 22 Feb 96. Fixed 1-character xyz label problem, -db, 8 May 96 Minor text & label changes, -db, 29 Jul 96 Added global metadata, support_data text, blank variable attrib. data per Mona Kessel sample file, -db, 5 Aug 96 Added xyz GEO,GSE,GSM labels, replacing 1 cartesian label -db, 29 Aug 96 Create 1 skeleton table for EPS for all GOES preparing for the switch from GOES-9 to 10 -anewman, 22 Jul 1998 Added GOES-10 launch date and replaced Ann Newman with Martin Black as contact person. -mblack, 18 Mar 1999 Changed Epoch and Time_PB5 VAR_TYPEs from data to support_data, and changed CATDESC values for position variables from s/c to GOES 11. for GSE and GSM mag field vectors. These changes were requested by Mona Kessel. -mblack, 12 Apr 1999 Updated metadata with GOES-11 launch date and with a Logical_source value that includes the word GOES. This is in preparation of GOES-11 replacing GOES-10 as GOES West in late June, 2006 -anewman June 23, 2006
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The NOAA Geostationary Operational Environmental Satellite (GOES) key parameters are obtained from the Energetic Particle Sensor (EPS) and and the magnetometer (MAG). The key parameters are a subset of the data available from the GOES Space Environment Monitor (SEM) instruments. The vector magnetic field is given as one-minute averaged values in three coordinate systems: (1) Spacecraft (s/c) P,E,N, (2) GSM x,y,z, (3) GSE x,y,z s/c mag. field is defined as: Hp, perpendicular to the satellite orbital plane or parallel to the Earths spin axis in the case of a zero degree inclination orbit; He, perpendicular to Hp and directed earthwards; and Hn, perpendicular to both Hp and directed eastwards. These data are used by NOAA Space Environment Center (SEC) for the real-time monitoring and prediction of the conditions in the Earth's space environment. A new series of GOES spacecraft began with GOES-8 launched on 4/13/94, GOES-9 launched on 5/23/95, GOES-10 launched on 4/25/97, GOES-11 launched on 5/3/2000, and GOES-12 launched on 7/23/2001. Typically two satellites are operational,one at about 135 degrees geographic west longitude and one at about 75 degrees geographic west longitude. The satellite inclination is typically within a few tenths of a degree of the geographic equator. However, the satellites can be moved, especially during the six months to one year following launch, and the inclination can increase after years of satellite operation. Instrument data quality flags are set from real-time telemetry, or, in the case of historically-processed data sets when telemetry is not available, fixed to a level-1 instrument status flag for all data Reference: Monitoring Space Weather with GOES Magnetometers, Singer, H.J, L. Matheson, R.Grubb A.Newman, and S.D.Bouwer, SPIE Proceedings, Volume 2812, 4-9 Aug 1996. For more info, contact: Dr. Howard Singer, NOAA/SEC, Howard.Singer@noaa.gov,303-497-6959 325 Broadway,Boulder CO 80305 USA, or Ann Newman, NOAA/SEC, Ann.Newman@noaa.gov, 303-497-5100, 325 Broadway, Boulder CO 80305 USA
Version 2.0: 1st operational version,-db, 15 Dec 92 Corrected S/C location error & added Geographic (not geodetic) & GEO S/C positions Fixed ADID_ref from 97 to 96 -db, 16 Feb 93 Added unit_ptr to s/c position units, fixed CATDES on SC_pos_sm, fixed GSn -db, 27 Apr 93 Version 3.0, Major re-write of text, corrected label_1 bug (now cartesian), added GOES-8 & 9 CDFs,-db,26 Jan 1996 Corrected no. of elements on lines 477-479 (labels), -db 7 May 1996 Minor text changes, -db 22 Jul 1996 Added global metadata, support_data text, blank variable attrib. data per Mona Kessel sample file, -db, 5 Aug 96 Added xyz GEO,GSE,GSM labels, replacing 1 cartesian label -db, 29 Aug 96 Create 1 skeleton table for MAG for all GOES preparing for the switch from GOES-9 to 10 -anewman, 22 Jul 1998 Added GOES-10 launch data and replaced Ann Newman with Martin Black as contact person. -mblack, 18 Mar 1999 Changed Epoch and Time_PB5 VAR_TYPEs from data to support_data, changed CATDESC values for position variables from s/c to GOES 11, and added cartesian to CATDESC for GSE and GSM mag field vectors. These changes were requested by Mona Kessel. -mblack, 12 Apr 1999 Updated metadata with GOES-11 launch date and with a Logical_source value that includes the word GOES. This is in preparation of GOES-11 replacing GOES-10 as GOES West in late June, 2006 -anewman June 23, 2006
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The NOAA Geostationary Operational Environmental Satellite (GOES) key parameters are obtained from the Energetic Particle Sensor (EPS) and the magnetometer (MAG). The key parameters are a subset of the data available from the GOES Space Environment Monitor (SEM) instruments. The energetic particle fluxes are given as five-minute averaged values and the vector magnetic field is given as one-minute average values. Flux values for three integral electron channels (E >0.6 MeV, E >2.0 MeV, and E >4.0 MeV) and one differential proton channel(0.7 MeV < E <4 MeV) are provided. These data are used by NOAA Space Environment Center (SEC) for the real-time monitoring and prediction of the conditions in the Earth's space environment. A new series of GOES spacecraft began with GOES-8 launched on 4/13/94, GOES-9 launched on 5/23/95, and GOES-10 launched on 4/25/97. Typically two satellites are maintained operational,one at about 135 degrees geographic west longitude and one at about 75 degrees geographic west longitude. The satellite inclination is typically within a few tenths of a degree of the geographic equator. However, the satellites can be moved, especially during the six months to one year following launch, and the inclination can increase after years of satellite operation. Instrument data quality flags are set from real-time telemetry, or, in the case of historically-processed data sets when telemetry is not available, fixed to a level-1 instrument status flag for all data Reference: Geostationary Operational Environmental Satellite GOES I-M System Description, compiled by John Savides, Space Systems/Loral, Palo Alto, California, December 1992. Dr. Terrance Onsager, NOAA/SEC, tonsager@sec.noaa.gov, 303-497-5713, Boulder CO 80303 USA, or Martin Black, NOAA/SEC, mblack@sec.noaa.gov, 303-497-7235, 325 Broadway, Boulder CO 80303 USA
GOES 12 energetic particle data are not available due to the failure of two proton channels in the detectors. These channels were used for the correction and processing of the proton and electron data. Beginning April 8, 2003, the GOES energetic particle data are obtained from GOES 10 only.
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The NOAA Geostationary Operational Environmental Satellite (GOES) key parameters are obtained from the Energetic Particle Sensor (EPS) and and the magnetometer (MAG). The key parameters are a subset of the data available from the GOES Space Environment Monitor (SEM) instruments. The vector magnetic field is given as one-minute averaged values in three coordinate systems: (1) Spacecraft (s/c) P,E,N, (2) GSM x,y,z, (3) GSE x,y,z s/c mag. field is defined as: Hp, perpendicular to the satellite orbital plane or parallel to the Earths spin axis in the case of a zero degree inclination orbit; He, perpendicular to Hp and directed earthwards; and Hn, perpendicular to both Hp and directed eastwards. These data are used by NOAA Space Environment Center (SEC) for the real-time monitoring and prediction of the conditions in the Earth's space environment. A new series of GOES spacecraft began with GOES-8 launched on 4/13/94, GOES-9 launched on 5/23/95, and GOES-10 launched on 4/25/97. Typically two satellites are operational,one at about 135 degrees geographic west longitude and one at about 75 degrees geographic west longitude. The satellite inclination is typically within a few tenths of a degree of the geographic equator. However, the satellites can be moved, especially during the six months to one year following launch, and the inclination can increase after years of satellite operation. Instrument data quality flags are set from real-time telemetry, or, in the case of historically-processed data sets when telemetry is not available, fixed to a level-1 instrument status flag for all data Reference: Monitoring Space Weather with GOES Magnetometers, Singer, H.J, L. Matheson, R.Grubb A.Newman, and S.D.Bouwer, SPIE Proceedings, Volume 2812, 4-9 Aug 1996. For more info, contact: Dr. Howard Singer, NOAA/SEC, Howard.Singer@noaa.gov,303-497-6959 325 Broadway,Boulder CO 80305 USA, or Ann Newman, NOAA/SEC, Ann.Newman@noaa.gov, 303-497-5100, 325 Broadway, Boulder CO 80305 USA
Version 2.0: 1st operational version,-db, 15 Dec 92 Corrected S/C location error & added Geographic (not geodetic) & GEO S/C positions Fixed ADID_ref from 97 to 96 -db, 16 Feb 93 Added unit_ptr to s/c position units, fixed CATDES on SC_pos_sm, fixed GSn -db, 27 Apr 93 Version 3.0, Major re-write of text, corrected label_1 bug (now cartesian), added GOES-8 & 9 CDFs,-db,26 Jan 1996 Corrected no. of elements on lines 477-479 (labels), -db 7 May 1996 Minor text changes, -db 22 Jul 1996 Added global metadata, support_data text, blank variable attrib. data per Mona Kessel sample file, -db, 5 Aug 96 Added xyz GEO,GSE,GSM labels, replacing 1 cartesian label -db, 29 Aug 96 Create 1 skeleton table for MAG for all GOES preparing for the switch from GOES-9 to 10 -anewman, 22 Jul 1998 Added GOES-10 launch data and replaced Ann Newman with Martin Black as contact person. -mblack, 18 Mar 1999 Changed Epoch and Time_PB5 VAR_TYPEs from data to support_data, changed CATDESC values for position variables from s/c to GOES 12, and added cartesian to CATDESC for GSE and GSM mag field vectors. These changes were requested by Mona Kessel. -mblack, 12 Apr 1999
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Helios1 COHOweb connection
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Helios2 COHOweb connection
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Gurnett, D. A., and L. A. Frank, A region of intense plasma wave turbulences on auroral field lines, JGR, 82, 1031, 1977 Farrell, W. M., and J. A. Van Allen, Observations of the Earth"s polar cleft at large radial distances with Hawkeye 1 magnetometer, JGR, 95, 20945, 1990
Created by S. Chen on 2-5-97 Modified by R. Kessel on 13 June 2000
0 - not despun; 1 - optical aspect system; 2 - lepedea method; 3 - magnetometer method; 4/5 - solar array method - interpolated
may be pessimistic estimate
B field measurement range setting= 0: +/- 150 nT; 1: +/-450 nT; 2: +/- 1500 nT; 3: +/1 25000 nT.
BUILD_DATE: 1974-01-01
INSTRUMENT_MASS: 0.23 (LESS BOOMS) kg
INSTRUMENT_HEIGHT: 0.058 mt
INSTRUMENT_LENGTH: 0.140 mt
INSTRUMENT_WIDTH: 0.140 mt
INSTRUMENT_MANUFACTURER_NAME: UNIV IOWA
INSTRUMENT_SERIAL_NUMBER: VLF-05
Electric Antenna
The electric antenna on HAWKEYE consisted of two extendible beryllium copper
elements 0.025 inch in diameter which could be extended to a maximum tip-to-tip
length of 42.7 m. Except for the outermost 6.1 m of each element, which had a
conducting surface, the antenna was coated with Pyre-ML to electrically insulate
the antenna from the surrounding plasma. The insulating coating was required to
insulate the antenna from the perturbing effects of the plasma sheath
surrounding the spacecraft body. At high altitudes, the thickness of the plasma
sheath surrounding the spacecraft body was quit large, on the order of 9 m.
Since the conducting portion of the antenna must extend beyond the plasma
sheath, it was necessary that the antenna be rather long, at least 30 m.
tip-to-tip. The antenna mechanism used on HAWKEYE was the Dual-Tee extendible
antenna manufactured by Fairchild Industries. The antenna length was 42.49
meters after final deployment until the last orbit, when an attempt was made to
retract the antenna to reduce the spacecraft drag.
Magnetic Antenna
The magnetic antenna for this experiment consisted of a search coil with a high
permeability core mounted on a boom approximately 1.5 m. from the centerline of
the spacecraft body. The boom was a three element telescoping device developed
at the University of Iowa. The boom supporting the flux gate magnetometer on the
opposite side of the spacecraft was the same type. Both booms were extended
simultaneously by an electric motor.
The search coil core was .305 m. long and was wound with
approximately 20,000 turns of copper wire. The axis of the search coil was
parallel to the spin axis of the spacecraft. A preamplifier was located with the
sensor to provide low-impedance signals to the main electronics package in the
spacecraft body. The frequency range of the search coil antenna was from 1.0 Hz
to 10.0 kHz.
Electronics
The potential difference between the electric antenna elements was amplified by
a high input impedance differential amplifier to provide a 0 to 5 volt analog
voltage, V-Diff, to the spacecraft encoder. As the spacecraft rotated the
potential difference between the antenna elements varied sinusoidally at the
spacecraft rotation rate, with an amplitude proportional to the electric field
strength and a phase determined by the direction of the electric field. The
frequency response of the differential amplifier was 0.05 Hz to 10 Hz and
included the entire range of spin rates expected as the antenna was deployed.
The V-Diff signal was sampled 6 times each frame by the encoder. The gain of the
differential amplifier could be controlled by command to provide dynamic ranges
of +/-0.5 and +/-8.0 volts for the antenna potential difference measurements.
Signals from the electric antenna in the frequency range from 10 kHz
to 200 kHz were analyzed by the narrow band step frequency receiver. The primary
purpose of this receiver was to provide very good frequency resolution in the
neighborhood of the electron plasma frequency and upper hybrid resonance
frequency. The step frequency receiver consisted of 8 narrow band filters (+/-5%
band-width) which were sequentially switched into a log compressor. The log
compressor provided a 0 to 5 volt analog voltage, SFR, to the spacecraft
encoder. The switch (S4) position was controlled by clock lines from the
spacecraft encoder and was stepped through 8 frequencies, 13.3, 17.8, 23.7,
31.1, 42.2, 56.2, 100, and 178 kHz, at a rate of four frequencies per telemetry
frame (5.76 seconds). The log compressor provided a 0 to 5 volt analog voltage,
SFR, to the spacecraft encoder which was proportional to the logarithm of the
signal strength over a dynamic range of 100 db.
The 8-channel spectrum analyzer provided relatively coarse frequency
spectrum measurements of both electric and magnetic fields over a broad
frequency range of 1.0 Hz to 10.0 kHz. The primary purpose of the 8-channel
spectrum analyzer was to provide field strength measurements to complement the
high-resolution frequency-time spectra from the wide-band receiver.
Switches S1 and S2 were controlled by clock lines from the spacecraft
encoder and commutate the filter outputs to two log compressors which provided
field strength measurements SA-1 and SA-2 (0 to 5 volts) to the spacecraft
encoder. These outputs were sampled twice per telemetry frame. Switch S3, which
was controlled by a clock line, commutates the electric and magnetic field
signals to the 8-channel spectrum analyzer.
Approximately every 5 minutes the impedance of the electric antenna
was determined at a frequency of 17 Hz by driving a small AC current into the
antennas and measuring the resultant voltage on the antennas with the 8-channel
spectrum analyzer. The 17 Hz oscillator was gated on for 1 frame out of every 64
frames by a clock line.
Immediately following the impedance measurement the pulser circuit
produced a 10 volt pulse with a duration of 20 micro- seconds. This pulse was to
stimulate local plasma resonances, such as plasma oscillation, from which the
electron density could be determined. A pulse of +10 volts was applied to one
antenna element and a -10 volt pulse was applied to the opposite antenna
element. The pulser was switched on by command. The pulser was on when the
experiment was in VLF45 mode and off when the experiment was in the VLF10 mode.
The pulser voltage was coupled to the antenna through a 220 pf capacitor which
would have allowed some meaningful data to be obtained from the experiment even
if the pulser output were to short to ground. The pulse was applied at the end
of the impedance measurement frame.
The potential difference between the electric antenna elements was amplified by
a high input impedance differential amplifier to provide a 0 to 5 volt analog
voltage, V-Diff, to the spacecraft encoder. As the spacecraft rotated the
potential difference between the antenna elements varied sinusoidally at the
spacecraft rotation rate, with an amplitude proportional to the electric field
strength and a phase determined by the direction of the electric field. The
frequency response of the differential amplifier was 0.05 Hz to 10 Hz and
included the entire range of spin rates expected as the antenna was deployed.
The V-Diff signal was sampled 6 times each frame by the encoder. The gain of the
differential amplifier could be controlled by command to provide dynamic ranges
of +/-0.5 and +/-8.0 volts for the antenna potential difference measurements.
Signals from the electric antenna in the frequency range from 10 kHz
to 200 kHz were analyzed by the narrow band step frequency receiver. The primary
purpose of this receiver was to provide very good frequency resolution in the
neighborhood of the electron plasma frequency and upper hybrid resonance
frequency. The step frequency receiver consisted of 8 narrow band filters (+/-5%
band-width) which were sequentially switched into a log compressor. The log
compressor provided a 0 to 5 volt analog voltage, SFR, to the spacecraft
encoder. The switch (S4) position was controlled by clock lines from the
spacecraft encoder and was stepped through 8 frequencies, 13.3, 17.8, 23.7,
31.1, 42.2, 56.2, 100, and 178 kHz, at a rate of four frequencies per telemetry
frame (5.76 seconds). The log compressor provided a 0 to 5 volt analog voltage,
SFR, to the spacecraft encoder which was proportional to the logarithm of the
signal strength over a dynamic range of 100 db.
The 8-channel spectrum analyzer provided relatively coarse frequency
spectrum measurements of both electric and magnetic fields over a broad
frequency range of 1.0 Hz to 10.0 kHz. The primary purpose of the 8-channel
spectrum analyzer was to provide field strength measurements to complement the
high-resolution frequency-time spectra from the wide-band receiver.
Switches S1 and S2 were controlled by clock lines from the spacecraft
encoder and commutate the filter outputs to two log compressors which provided
field strength measurements SA-1 and SA-2 (0 to 5 volts) to the spacecraft
encoder. These outputs were sampled twice per telemetry frame. Switch S3, which
was controlled by a clock line, commutates the electric and magnetic field
signals to the 8-channel spectrum analyzer.
Approximately every 5 minutes the impedance of the electric antenna
was determined at a frequency of 17 Hz by driving a small AC current into the
antennas and measuring the resultant voltage on the antennas with the 8-channel
spectrum analyzer. The 17 Hz oscillator was gated on for 1 frame out of every 64
frames by a clock line.
Immediately following the impedance measurement the pulser circuit
produced a 10 volt pulse with a duration of 20 micro- seconds. This pulse was to
stimulate local plasma resonances, such as plasma oscillation, from which the
electron density could be determined. A pulse of +10 volts was applied to one
antenna element and a -10 volt pulse was applied to the opposite antenna
element. The pulser was switched on by command. The pulser was on when the
experiment was in VLF45 mode and off when the experiment was in the VLF10 mode.
The pulser voltage was coupled to the antenna through a 220 pf capacitor which
would have allowed some meaningful data to be obtained from the experiment even
if the pulser output were to short to ground. The pulse was applied at the end
of the impedance measurement frame.
CDF created Jan 1999 by Mona Kessel modified Aug 1999 by Mona Kessel, Carolyn Ng modified Oct 1999 by Mona Kessel modified Nov 1999 by Mona Kessel, final for archiving
Active emissions only affect the Electric Field measurements at 17.8 Hz and 56.8 Hz
This ionogram was digitized from the original ISIS 1 analog telemetry data on 7-track tape using the facilities of the Data Evaluation Laboratory at GSFC (Code 500). This data restoration project is headed by Dr. R.F. Benson (GSFC, Code 692). Ionograms were digitized at the rate of 40,000 16-bit samples/sec. This sample rate is higher than the Nyquist frequency of 30 kHz. The sample frequency of 40 kHz provides a measurement every 25 microseconds corresponding to an apparent range (c*t/2) interval of 3.747 km. Each ionogram consists of a fixed-frequency and and a swept-frequency portion. The time resolution is typically 24 seconds. More information can be found at http://nssdc/space/isis/isis-status.html
created April 1998
Virtual variable.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
time of frequency markers
seperates the fixed and swept portions
This ionogram was digitized from the original ISIS 1 analog telemetry data on 7-track tape using the facilities of the Data Evaluation Laboratory at GSFC (Code 500). This data restoration project is headed by Dr. R.F. Benson (GSFC, Code 692). Ionograms were digitized at the rate of 40,000 16-bit samples/sec. This sample rate is higher than the Nyquist frequency of 30 kHz. The sample frequency of 40 kHz provides a measurement every 25 microseconds corresponding to an apparent range (c*t/2) interval of 3.747 km. Each ionogram consists of a fixed-frequency and and a swept-frequency portion. The time resolution is typically 24 seconds. More information can be found at http://nssdc/space/isis/isis-status.html
created April 1998
Virtual variable.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
time of frequency markers
seperates the fixed and swept portions
This ionogram was digitized from the original ISIS 1 analog telemetry data on 7-track tape using the facilities of the Data Evaluation Laboratory at GSFC (Code 500). This data restoration project is headed by Dr. R.F. Benson (GSFC, Code 692). Ionograms were digitized at the rate of 40,000 16-bit samples/sec. This sample rate is higher than the Nyquist frequency of 30 kHz. The sample frequency of 40 kHz provides a measurement every 25 microseconds corresponding to an apparent range (c*t/2) interval of 3.747 km. Each ionogram consists of a fixed-frequency and and a swept-frequency portion. The time resolution is typically 24 seconds. More information can be found at http://nssdc/space/isis/isis-status.html
created April 1998
Virtual variable.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
time of frequency markers
seperates the fixed and swept portions
This ionogram was digitized from the original ISIS 1 analog telemetry data on 7-track tape using the facilities of the Data Evaluation Laboratory at GSFC (Code 500). This data restoration project is headed by Dr. R.F. Benson (GSFC, Code 692). Ionograms were digitized at the rate of 40,000 16-bit samples/sec. This sample rate is higher than the Nyquist frequency of 30 kHz. The sample frequency of 40 kHz provides a measurement every 25 microseconds corresponding to an apparent range (c*t/2) interval of 3.747 km. Each ionogram consists of a fixed-frequency and and a swept-frequency portion. The time resolution is typically 24 seconds. More information can be found at http://nssdc/space/isis/isis-status.html
created April 1998
Virtual variable.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
time of frequency markers
seperates the fixed and swept portions
This ionogram was digitized from the original ISIS 1 analog telemetry data on 7-track tape using the facilities of the Data Evaluation Laboratory at GSFC (Code 500). This data restoration project is headed by Dr. R.F. Benson (GSFC, Code 692). Ionograms were digitized at the rate of 40,000 16-bit samples/sec. This sample rate is higher than the Nyquist frequency of 30 kHz. The sample frequency of 40 kHz provides a measurement every 25 microseconds corresponding to an apparent range (c*t/2) interval of 3.747 km. Each ionogram consists of a fixed-frequency and and a swept-frequency portion. The time resolution is typically 24 seconds. More information can be found at http://nssdc/space/isis/isis-status.html
created April 1998
Virtual variable.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
time of frequency markers
seperates the fixed and swept portions
This ionogram was digitized from the original ISIS 1 analog telemetry data on 7-track tape using the facilities of the Data Evaluation Laboratory at GSFC (Code 500). This data restoration project is headed by Dr. R.F. Benson (GSFC, Code 692). Ionograms were digitized at the rate of 40,000 16-bit samples/sec. This sample rate is higher than the Nyquist frequency of 30 kHz. The sample frequency of 40 kHz provides a measurement every 25 microseconds corresponding to an apparent range (c*t/2) interval of 3.747 km. Each ionogram consists of a fixed-frequency and and a swept-frequency portion. The time resolution is typically 24 seconds. More information can be found at http://nssdc/space/isis/isis-status.html
created April 1998
Virtual variable.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
time of frequency markers
seperates the fixed and swept portions
This ionogram was digitized from the original ISIS 1 analog telemetry data on 7-track tape using the facilities of the Data Evaluation Laboratory at GSFC (Code 500). This data restoration project is headed by Dr. R.F. Benson (GSFC, Code 692). Ionograms were digitized at the rate of 40,000 16-bit samples/sec. This sample rate is higher than the Nyquist frequency of 30 kHz. The sample frequency of 40 kHz provides a measurement every 25 microseconds corresponding to an apparent range (c*t/2) interval of 3.747 km. Each ionogram consists of a fixed-frequency and and a swept-frequency portion. The time resolution is typically 24 seconds. More information can be found at http://nssdc/space/isis/isis-status.html
created April 1998
Virtual variable.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
time of frequency markers
seperates the fixed and swept portions
This ionogram was digitized from the original ISIS 1 analog telemetry data on 7-track tape using the facilities of the Data Evaluation Laboratory at GSFC (Code 500). This data restoration project is headed by Dr. R.F. Benson (GSFC, Code 692). Ionograms were digitized at the rate of 40,000 16-bit samples/sec. This sample rate is higher than the Nyquist frequency of 30 kHz. The sample frequency of 40 kHz provides a measurement every 25 microseconds corresponding to an apparent range (c*t/2) interval of 3.747 km. Each ionogram consists of a fixed-frequency and and a swept-frequency portion. The time resolution is typically 24 seconds. More information can be found at http://nssdc/space/isis/isis-status.html
created April 1998
Virtual variable.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
time of frequency markers
seperates the fixed and swept portions
This ionogram was digitized from the original ISIS 1 analog telemetry data on 7-track tape using the facilities of the Data Evaluation Laboratory at GSFC (Code 500). This data restoration project is headed by Dr. R.F. Benson (GSFC, Code 692). Ionograms were digitized at the rate of 40,000 16-bit samples/sec. This sample rate is higher than the Nyquist frequency of 30 kHz. The sample frequency of 40 kHz provides a measurement every 25 microseconds corresponding to an apparent range (c*t/2) interval of 3.747 km. Each ionogram consists of a fixed-frequency and and a swept-frequency portion. The time resolution is typically 24 seconds. More information can be found at http://nssdc/space/isis/isis-status.html
created April 1998
Virtual variable.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
time of frequency markers
seperates the fixed and swept portions
This ionogram was digitized from the original ISIS 1 analog telemetry data on 7-track tape using the facilities of the Data Evaluation Laboratory at GSFC (Code 500). This data restoration project is headed by Dr. R.F. Benson (GSFC, Code 692). Ionograms were digitized at the rate of 40,000 16-bit samples/sec. This sample rate is higher than the Nyquist frequency of 30 kHz. The sample frequency of 40 kHz provides a measurement every 25 microseconds corresponding to an apparent range (c*t/2) interval of 3.747 km. Each ionogram consists of a fixed-frequency and and a swept-frequency portion. The time resolution is typically 24 seconds. More information can be found at http://nssdc/space/isis/isis-status.html
created April 1998
Virtual variable.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
time of frequency markers
seperates the fixed and swept portions
This ionogram was digitized from the original ISIS 1 analog telemetry data on 7-track tape using the facilities of the Data Evaluation Laboratory at GSFC (Code 500). This data restoration project is headed by Dr. R.F. Benson (GSFC, Code 692). Ionograms were digitized at the rate of 40,000 16-bit samples/sec. This sample rate is higher than the Nyquist frequency of 30 kHz. The sample frequency of 40 kHz provides a measurement every 25 microseconds corresponding to an apparent range (c*t/2) interval of 3.747 km. Each ionogram consists of a fixed-frequency and and a swept-frequency portion. The time resolution is typically 24 seconds. More information can be found at http://nssdc/space/isis/isis-status.html
created April 1998
Virtual variable.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
time of frequency markers
seperates the fixed and swept portions
This ionogram was digitized from the original ISIS 1 analog telemetry data on 7-track tape using the facilities of the Data Evaluation Laboratory at GSFC (Code 500). This data restoration project is headed by Dr. R.F. Benson (GSFC, Code 692). Ionograms were digitized at the rate of 40,000 16-bit samples/sec. This sample rate is higher than the Nyquist frequency of 30 kHz. The sample frequency of 40 kHz provides a measurement every 25 microseconds corresponding to an apparent range (c*t/2) interval of 3.747 km. Each ionogram consists of a fixed-frequency and and a swept-frequency portion. The time resolution is typically 24 seconds. More information can be found at http://nssdc/space/isis/isis-status.html
created April 1998
Virtual variable.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
time of frequency markers
seperates the fixed and swept portions
This ionogram was digitized from the original ISIS 2 analog telemetry data on 7-track tape using the facilities of the Data Evaluation Laboratory at GSFC (Code 500). This data restoration project is headed by Dr. R.F. Benson (GSFC, Code 692). Ionograms were digitized at the rate of 40,000 16-bit samples/sec. This sample rate is higher than the Nyquist frequency of 30 kHz. The sample frequency of 40 kHz provides a measurement every 25 microseconds corresponding to an apparent range (c*t/2) interval of 3.747 km. Each ionogram consists of a fixed-frequency and and a swept-frequency portion. The time resolution is typically 24 seconds. More information can be found at http://nssdc/space/isis/isis-status.html
created April 1995
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
time of frequency markers
seperates the fixed and swept portions
A 7-track ISIS 2 analog telemetry tape from Ottawa (#561) has been digitized using the GSFC facilities of the Data Evaluation Laboratory (DEL) within the Mission Operations and Data Systems Directorate (Code 500) at Goddard. The digitization was performed using an A/D converter board and software device driver compatible with the OS/2 operating system used by the 486-based Programmable Telemetry Processor (PTP) associated software has been installed on their PTP and de-bugged so that we now have a working system for making digital ISIS ionograms directly from the telemetry tapes. Earlier, we successfully digitized the PCM and NASA 36 bit time-code data from this same tape. The ionograms were digitized at the rate of 40,000 16-bit samples/sec. This sample rate is higher than the Nyquist frequency of 30 kHz appropriate for the post-detection ISIS 2 sounder-receiver video output which extends from DC to 15 kHz (see p. 50 of the 1971 ISIS 2 report by Daniels). The sample frequency of 40 kHz provides a measurement every 25 microseconds corresponding to an apparent range (ct/2) interval of 3.747 km. With the ISIS 2 prf of 45 sounder pulses/s, there are (1/45)/(2.5**(-5)) = 888.89 samples between each of the approximately 1015 sounder pulses per ionogram (including the fixed-frequency portion) or nearly 10**6 16-bit samples/ionogram (approximately 1.8 MBytes) for just the sounder-receiver video data. Adding header information, and the pcm data containing data from the other instruments, yields about 2 MBytes of data for the 22.5 s period corresponding to one ionogram. Two steps were taken in order to reduce this large volume of nearly 2 MBytes/ionogram. First, every four 25 microsecond samples following the sounder pulse were averaged. Second, the 16 bit samples were reduced to 8 bit samples. The first step decreased the apparent-range resolution to 15 km, but yielded high-quality ionograms because of the improved S/N due to the averaging.
created April 1995
Virtual variable.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
time of frequency markers
seperates the fixed and swept portions
This ionogram was digitized from the original ISIS 2 analog telemetry data on 7-track tape using the facilities of the Data Evaluation Laboratory at GSFC (Code 500). This data restoration project is headed by Dr. R.F. Benson (GSFC, Code 692). Ionograms were digitized at the rate of 40,000 16-bit samples/sec. This sample rate is higher than the Nyquist frequency of 30 kHz. The sample frequency of 40 kHz provides a measurement every 25 microseconds corresponding to an apparent range (c*t/2) interval of 3.747 km. Each ionogram consists of a fixed-frequency and and a swept-frequency portion. The time resolution is typically 24 seconds. More information can be found at http://nssdc/space/isis/isis-status.html
created April 1995
Virtual variable.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
time of frequency markers
seperates the fixed and swept portions
A 7-track ISIS 2 analog telemetry tape from Ottawa (#561) has been digitized using the GSFC facilities of the Data Evaluation Laboratory (DEL) within the Mission Operations and Data Systems Directorate (Code 500) at Goddard. The digitization was performed using an A/D converter board and software device driver compatible with the OS/2 operating system used by the 486-based Programmable Telemetry Processor (PTP) associated software has been installed on their PTP and de-bugged so that we now have a working system for making digital ISIS ionograms directly from the telemetry tapes. Earlier, we successfully digitized the PCM and NASA 36 bit time-code data from this same tape. The ionograms were digitized at the rate of 40,000 16-bit samples/sec. This sample rate is higher than the Nyquist frequency of 30 kHz appropriate for the post-detection ISIS 2 sounder-receiver video output which extends from DC to 15 kHz (see p. 50 of the 1971 ISIS 2 report by Daniels). The sample frequency of 40 kHz provides a measurement every 25 microseconds corresponding to an apparent range (ct/2) interval of 3.747 km. With the ISIS 2 prf of 45 sounder pulses/s, there are (1/45)/(2.5**(-5)) = 888.89 samples between each of the approximately 1015 sounder pulses per ionogram (including the fixed-frequency portion) or nearly 10**6 16-bit samples/ionogram (approximately 1.8 MBytes) for just the sounder-receiver video data. Adding header information, and the pcm data containing data from the other instruments, yields about 2 MBytes of data for the 22.5 s period corresponding to one ionogram. Two steps were taken in order to reduce this large volume of nearly 2 MBytes/ionogram. First, every four 25 microsecond samples following the sounder pulse were averaged. Second, the 16 bit samples were reduced to 8 bit samples. The first step decreased the apparent-range resolution to 15 km, but yielded high-quality ionograms because of the improved S/N due to the averaging.
created April 1995
Virtual variable.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
time of frequency markers
seperates the fixed and swept portions
A 7-track ISIS 2 analog telemetry tape from Ottawa (#561) has been digitized using the GSFC facilities of the Data Evaluation Laboratory (DEL) within the Mission Operations and Data Systems Directorate (Code 500) at Goddard. The digitization was performed using an A/D converter board and software device driver compatible with the OS/2 operating system used by the 486-based Programmable Telemetry Processor (PTP) associated software has been installed on their PTP and de-bugged so that we now have a working system for making digital ISIS ionograms directly from the telemetry tapes. Earlier, we successfully digitized the PCM and NASA 36 bit time-code data from this same tape. The ionograms were digitized at the rate of 40,000 16-bit samples/sec. This sample rate is higher than the Nyquist frequency of 30 kHz appropriate for the post-detection ISIS 2 sounder-receiver video output which extends from DC to 15 kHz (see p. 50 of the 1971 ISIS 2 report by Daniels). The sample frequency of 40 kHz provides a measurement every 25 microseconds corresponding to an apparent range (ct/2) interval of 3.747 km. With the ISIS 2 prf of 45 sounder pulses/s, there are (1/45)/(2.5**(-5)) = 888.89 samples between each of the approximately 1015 sounder pulses per ionogram (including the fixed-frequency portion) or nearly 10**6 16-bit samples/ionogram (approximately 1.8 MBytes) for just the sounder-receiver video data. Adding header information, and the pcm data containing data from the other instruments, yields about 2 MBytes of data for the 22.5 s period corresponding to one ionogram. Two steps were taken in order to reduce this large volume of nearly 2 MBytes/ionogram. First, every four 25 microsecond samples following the sounder pulse were averaged. Second, the 16 bit samples were reduced to 8 bit samples. The first step decreased the apparent-range resolution to 15 km, but yielded high-quality ionograms because of the improved S/N due to the averaging.
created April 1995
Virtual variable.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
time of frequency markers
seperates the fixed and swept portions
A 7-track ISIS 2 analog telemetry tape from Ottawa (#561) has been digitized using the GSFC facilities of the Data Evaluation Laboratory (DEL) within the Mission Operations and Data Systems Directorate (Code 500) at Goddard. The digitization was performed using an A/D converter board and software device driver compatible with the OS/2 operating system used by the 486-based Programmable Telemetry Processor (PTP) associated software has been installed on their PTP and de-bugged so that we now have a working system for making digital ISIS ionograms directly from the telemetry tapes. Earlier, we successfully digitized the PCM and NASA 36 bit time-code data from this same tape. The ionograms were digitized at the rate of 40,000 16-bit samples/sec. This sample rate is higher than the Nyquist frequency of 30 kHz appropriate for the post-detection ISIS 2 sounder-receiver video output which extends from DC to 15 kHz (see p. 50 of the 1971 ISIS 2 report by Daniels). The sample frequency of 40 kHz provides a measurement every 25 microseconds corresponding to an apparent range (ct/2) interval of 3.747 km. With the ISIS 2 prf of 45 sounder pulses/s, there are (1/45)/(2.5**(-5)) = 888.89 samples between each of the approximately 1015 sounder pulses per ionogram (including the fixed-frequency portion) or nearly 10**6 16-bit samples/ionogram (approximately 1.8 MBytes) for just the sounder-receiver video data. Adding header information, and the pcm data containing data from the other instruments, yields about 2 MBytes of data for the 22.5 s period corresponding to one ionogram. Two steps were taken in order to reduce this large volume of nearly 2 MBytes/ionogram. First, every four 25 microsecond samples following the sounder pulse were averaged. Second, the 16 bit samples were reduced to 8 bit samples. The first step decreased the apparent-range resolution to 15 km, but yielded high-quality ionograms because of the improved S/N due to the averaging.
created April 1995
Virtual variable.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
time of frequency markers
seperates the fixed and swept portions
A 7-track ISIS 2 analog telemetry tape from Ottawa (#561) has been digitized using the GSFC facilities of the Data Evaluation Laboratory (DEL) within the Mission Operations and Data Systems Directorate (Code 500) at Goddard. The digitization was performed using an A/D converter board and software device driver compatible with the OS/2 operating system used by the 486-based Programmable Telemetry Processor (PTP) associated software has been installed on their PTP and de-bugged so that we now have a working system for making digital ISIS ionograms directly from the telemetry tapes. Earlier, we successfully digitized the PCM and NASA 36 bit time-code data from this same tape. The ionograms were digitized at the rate of 40,000 16-bit samples/sec. This sample rate is higher than the Nyquist frequency of 30 kHz appropriate for the post-detection ISIS 2 sounder-receiver video output which extends from DC to 15 kHz (see p. 50 of the 1971 ISIS 2 report by Daniels). The sample frequency of 40 kHz provides a measurement every 25 microseconds corresponding to an apparent range (ct/2) interval of 3.747 km. With the ISIS 2 prf of 45 sounder pulses/s, there are (1/45)/(2.5**(-5)) = 888.89 samples between each of the approximately 1015 sounder pulses per ionogram (including the fixed-frequency portion) or nearly 10**6 16-bit samples/ionogram (approximately 1.8 MBytes) for just the sounder-receiver video data. Adding header information, and the pcm data containing data from the other instruments, yields about 2 MBytes of data for the 22.5 s period corresponding to one ionogram. Two steps were taken in order to reduce this large volume of nearly 2 MBytes/ionogram. First, every four 25 microsecond samples following the sounder pulse were averaged. Second, the 16 bit samples were reduced to 8 bit samples. The first step decreased the apparent-range resolution to 15 km, but yielded high-quality ionograms because of the improved S/N due to the averaging.
created April 1995
Virtual variable.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
time of frequency markers
seperates the fixed and swept portions
A 7-track ISIS 2 analog telemetry tape from Ottawa (#561) has been digitized using the GSFC facilities of the Data Evaluation Laboratory (DEL) within the Mission Operations and Data Systems Directorate (Code 500) at Goddard. The digitization was performed using an A/D converter board and software device driver compatible with the OS/2 operating system used by the 486-based Programmable Telemetry Processor (PTP) associated software has been installed on their PTP and de-bugged so that we now have a working system for making digital ISIS ionograms directly from the telemetry tapes. Earlier, we successfully digitized the PCM and NASA 36 bit time-code data from this same tape. The ionograms were digitized at the rate of 40,000 16-bit samples/sec. This sample rate is higher than the Nyquist frequency of 30 kHz appropriate for the post-detection ISIS 2 sounder-receiver video output which extends from DC to 15 kHz (see p. 50 of the 1971 ISIS 2 report by Daniels). The sample frequency of 40 kHz provides a measurement every 25 microseconds corresponding to an apparent range (ct/2) interval of 3.747 km. With the ISIS 2 prf of 45 sounder pulses/s, there are (1/45)/(2.5**(-5)) = 888.89 samples between each of the approximately 1015 sounder pulses per ionogram (including the fixed-frequency portion) or nearly 10**6 16-bit samples/ionogram (approximately 1.8 MBytes) for just the sounder-receiver video data. Adding header information, and the pcm data containing data from the other instruments, yields about 2 MBytes of data for the 22.5 s period corresponding to one ionogram. Two steps were taken in order to reduce this large volume of nearly 2 MBytes/ionogram. First, every four 25 microsecond samples following the sounder pulse were averaged. Second, the 16 bit samples were reduced to 8 bit samples. The first step decreased the apparent-range resolution to 15 km, but yielded high-quality ionograms because of the improved S/N due to the averaging.
created April 1995
Virtual variable.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
time of frequency markers
seperates the fixed and swept portions
A 7-track ISIS 2 analog telemetry tape from Ottawa (#561) has been digitized using the GSFC facilities of the Data Evaluation Laboratory (DEL) within the Mission Operations and Data Systems Directorate (Code 500) at Goddard. The digitization was performed using an A/D converter board and software device driver compatible with the OS/2 operating system used by the 486-based Programmable Telemetry Processor (PTP) associated software has been installed on their PTP and de-bugged so that we now have a working system for making digital ISIS ionograms directly from the telemetry tapes. Earlier, we successfully digitized the PCM and NASA 36 bit time-code data from this same tape. The ionograms were digitized at the rate of 40,000 16-bit samples/sec. This sample rate is higher than the Nyquist frequency of 30 kHz appropriate for the post-detection ISIS 2 sounder-receiver video output which extends from DC to 15 kHz (see p. 50 of the 1971 ISIS 2 report by Daniels). The sample frequency of 40 kHz provides a measurement every 25 microseconds corresponding to an apparent range (ct/2) interval of 3.747 km. With the ISIS 2 prf of 45 sounder pulses/s, there are (1/45)/(2.5**(-5)) = 888.89 samples between each of the approximately 1015 sounder pulses per ionogram (including the fixed-frequency portion) or nearly 10**6 16-bit samples/ionogram (approximately 1.8 MBytes) for just the sounder-receiver video data. Adding header information, and the pcm data containing data from the other instruments, yields about 2 MBytes of data for the 22.5 s period corresponding to one ionogram. Two steps were taken in order to reduce this large volume of nearly 2 MBytes/ionogram. First, every four 25 microsecond samples following the sounder pulse were averaged. Second, the 16 bit samples were reduced to 8 bit samples. The first step decreased the apparent-range resolution to 15 km, but yielded high-quality ionograms because of the improved S/N due to the averaging.
created April 1995
Virtual variable.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
time of frequency markers
seperates the fixed and swept portions
This ionogram was digitized from the original ISIS 2 analog telemetry data on 7-track tape using the facilities of the Data Evaluation Laboratory at GSFC (Code 500). This data restoration project is headed by Dr. R.F. Benson (GSFC, Code 692). Ionograms were digitized at the rate of 40,000 16-bit samples/sec. This sample rate is higher than the Nyquist frequency of 30 kHz. The sample frequency of 40 kHz provides a measurement every 25 microseconds corresponding to an apparent range (c*t/2) interval of 3.747 km. Each ionogram consists of a fixed-frequency and and a swept-frequency portion. The time resolution is typically 24 seconds. More information can be found at http://nssdc/space/isis/isis-status.html
created April 1995
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
time of frequency markers
seperates the fixed and swept portions
A 7-track ISIS 2 analog telemetry tape from Ottawa (#561) has been digitized using the GSFC facilities of the Data Evaluation Laboratory (DEL) within the Mission Operations and Data Systems Directorate (Code 500) at Goddard. The digitization was performed using an A/D converter board and software device driver compatible with the OS/2 operating system used by the 486-based Programmable Telemetry Processor (PTP) associated software has been installed on their PTP and de-bugged so that we now have a working system for making digital ISIS ionograms directly from the telemetry tapes. Earlier, we successfully digitized the PCM and NASA 36 bit time-code data from this same tape. The ionograms were digitized at the rate of 40,000 16-bit samples/sec. This sample rate is higher than the Nyquist frequency of 30 kHz appropriate for the post-detection ISIS 2 sounder-receiver video output which extends from DC to 15 kHz (see p. 50 of the 1971 ISIS 2 report by Daniels). The sample frequency of 40 kHz provides a measurement every 25 microseconds corresponding to an apparent range (ct/2) interval of 3.747 km. With the ISIS 2 prf of 45 sounder pulses/s, there are (1/45)/(2.5**(-5)) = 888.89 samples between each of the approximately 1015 sounder pulses per ionogram (including the fixed-frequency portion) or nearly 10**6 16-bit samples/ionogram (approximately 1.8 MBytes) for just the sounder-receiver video data. Adding header information, and the pcm data containing data from the other instruments, yields about 2 MBytes of data for the 22.5 s period corresponding to one ionogram. Two steps were taken in order to reduce this large volume of nearly 2 MBytes/ionogram. First, every four 25 microsecond samples following the sounder pulse were averaged. Second, the 16 bit samples were reduced to 8 bit samples. The first step decreased the apparent-range resolution to 15 km, but yielded high-quality ionograms because of the improved S/N due to the averaging.
created April 1995
Virtual variable.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
time of frequency markers
seperates the fixed and swept portions
A 7-track ISIS 2 analog telemetry tape from Ottawa (#561) has been digitized using the GSFC facilities of the Data Evaluation Laboratory (DEL) within the Mission Operations and Data Systems Directorate (Code 500) at Goddard. The digitization was performed using an A/D converter board and software device driver compatible with the OS/2 operating system used by the 486-based Programmable Telemetry Processor (PTP) associated software has been installed on their PTP and de-bugged so that we now have a working system for making digital ISIS ionograms directly from the telemetry tapes. Earlier, we successfully digitized the PCM and NASA 36 bit time-code data from this same tape. The ionograms were digitized at the rate of 40,000 16-bit samples/sec. This sample rate is higher than the Nyquist frequency of 30 kHz appropriate for the post-detection ISIS 2 sounder-receiver video output which extends from DC to 15 kHz (see p. 50 of the 1971 ISIS 2 report by Daniels). The sample frequency of 40 kHz provides a measurement every 25 microseconds corresponding to an apparent range (ct/2) interval of 3.747 km. With the ISIS 2 prf of 45 sounder pulses/s, there are (1/45)/(2.5**(-5)) = 888.89 samples between each of the approximately 1015 sounder pulses per ionogram (including the fixed-frequency portion) or nearly 10**6 16-bit samples/ionogram (approximately 1.8 MBytes) for just the sounder-receiver video data. Adding header information, and the pcm data containing data from the other instruments, yields about 2 MBytes of data for the 22.5 s period corresponding to one ionogram. Two steps were taken in order to reduce this large volume of nearly 2 MBytes/ionogram. First, every four 25 microsecond samples following the sounder pulse were averaged. Second, the 16 bit samples were reduced to 8 bit samples. The first step decreased the apparent-range resolution to 15 km, but yielded high-quality ionograms because of the improved S/N due to the averaging.
created April 1995
Virtual variable.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
time of frequency markers
seperates the fixed and swept portions
A 7-track ISIS 2 analog telemetry tape from Ottawa (#561) has been digitized using the GSFC facilities of the Data Evaluation Laboratory (DEL) within the Mission Operations and Data Systems Directorate (Code 500) at Goddard. The digitization was performed using an A/D converter board and software device driver compatible with the OS/2 operating system used by the 486-based Programmable Telemetry Processor (PTP) associated software has been installed on their PTP and de-bugged so that we now have a working system for making digital ISIS ionograms directly from the telemetry tapes. Earlier, we successfully digitized the PCM and NASA 36 bit time-code data from this same tape. The ionograms were digitized at the rate of 40,000 16-bit samples/sec. This sample rate is higher than the Nyquist frequency of 30 kHz appropriate for the post-detection ISIS 2 sounder-receiver video output which extends from DC to 15 kHz (see p. 50 of the 1971 ISIS 2 report by Daniels). The sample frequency of 40 kHz provides a measurement every 25 microseconds corresponding to an apparent range (ct/2) interval of 3.747 km. With the ISIS 2 prf of 45 sounder pulses/s, there are (1/45)/(2.5**(-5)) = 888.89 samples between each of the approximately 1015 sounder pulses per ionogram (including the fixed-frequency portion) or nearly 10**6 16-bit samples/ionogram (approximately 1.8 MBytes) for just the sounder-receiver video data. Adding header information, and the pcm data containing data from the other instruments, yields about 2 MBytes of data for the 22.5 s period corresponding to one ionogram. Two steps were taken in order to reduce this large volume of nearly 2 MBytes/ionogram. First, every four 25 microsecond samples following the sounder pulse were averaged. Second, the 16 bit samples were reduced to 8 bit samples. The first step decreased the apparent-range resolution to 15 km, but yielded high-quality ionograms because of the improved S/N due to the averaging.
created April 1995
Virtual variable.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
time of frequency markers
seperates the fixed and swept portions
A 7-track ISIS 2 analog telemetry tape from Ottawa (#561) has been digitized using the GSFC facilities of the Data Evaluation Laboratory (DEL) within the Mission Operations and Data Systems Directorate (Code 500) at Goddard. The digitization was performed using an A/D converter board and software device driver compatible with the OS/2 operating system used by the 486-based Programmable Telemetry Processor (PTP) associated software has been installed on their PTP and de-bugged so that we now have a working system for making digital ISIS ionograms directly from the telemetry tapes. Earlier, we successfully digitized the PCM and NASA 36 bit time-code data from this same tape. The ionograms were digitized at the rate of 40,000 16-bit samples/sec. This sample rate is higher than the Nyquist frequency of 30 kHz appropriate for the post-detection ISIS 2 sounder-receiver video output which extends from DC to 15 kHz (see p. 50 of the 1971 ISIS 2 report by Daniels). The sample frequency of 40 kHz provides a measurement every 25 microseconds corresponding to an apparent range (ct/2) interval of 3.747 km. With the ISIS 2 prf of 45 sounder pulses/s, there are (1/45)/(2.5**(-5)) = 888.89 samples between each of the approximately 1015 sounder pulses per ionogram (including the fixed-frequency portion) or nearly 10**6 16-bit samples/ionogram (approximately 1.8 MBytes) for just the sounder-receiver video data. Adding header information, and the pcm data containing data from the other instruments, yields about 2 MBytes of data for the 22.5 s period corresponding to one ionogram. Two steps were taken in order to reduce this large volume of nearly 2 MBytes/ionogram. First, every four 25 microsecond samples following the sounder pulse were averaged. Second, the 16 bit samples were reduced to 8 bit samples. The first step decreased the apparent-range resolution to 15 km, but yielded high-quality ionograms because of the improved S/N due to the averaging.
created April 1995
Virtual variable.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
time of frequency markers
seperates the fixed and swept portions
A 7-track ISIS 2 analog telemetry tape from Ottawa (#561) has been digitized using the GSFC facilities of the Data Evaluation Laboratory (DEL) within the Mission Operations and Data Systems Directorate (Code 500) at Goddard. The digitization was performed using an A/D converter board and software device driver compatible with the OS/2 operating system used by the 486-based Programmable Telemetry Processor (PTP) associated software has been installed on their PTP and de-bugged so that we now have a working system for making digital ISIS ionograms directly from the telemetry tapes. Earlier, we successfully digitized the PCM and NASA 36 bit time-code data from this same tape. The ionograms were digitized at the rate of 40,000 16-bit samples/sec. This sample rate is higher than the Nyquist frequency of 30 kHz appropriate for the post-detection ISIS 2 sounder-receiver video output which extends from DC to 15 kHz (see p. 50 of the 1971 ISIS 2 report by Daniels). The sample frequency of 40 kHz provides a measurement every 25 microseconds corresponding to an apparent range (ct/2) interval of 3.747 km. With the ISIS 2 prf of 45 sounder pulses/s, there are (1/45)/(2.5**(-5)) = 888.89 samples between each of the approximately 1015 sounder pulses per ionogram (including the fixed-frequency portion) or nearly 10**6 16-bit samples/ionogram (approximately 1.8 MBytes) for just the sounder-receiver video data. Adding header information, and the pcm data containing data from the other instruments, yields about 2 MBytes of data for the 22.5 s period corresponding to one ionogram. Two steps were taken in order to reduce this large volume of nearly 2 MBytes/ionogram. First, every four 25 microsecond samples following the sounder pulse were averaged. Second, the 16 bit samples were reduced to 8 bit samples. The first step decreased the apparent-range resolution to 15 km, but yielded high-quality ionograms because of the improved S/N due to the averaging.
created April 1995
Virtual variable.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
time of frequency markers
seperates the fixed and swept portions
A 7-track ISIS 2 analog telemetry tape from Ottawa (#561) has been digitized using the GSFC facilities of the Data Evaluation Laboratory (DEL) within the Mission Operations and Data Systems Directorate (Code 500) at Goddard. The digitization was performed using an A/D converter board and software device driver compatible with the OS/2 operating system used by the 486-based Programmable Telemetry Processor (PTP) associated software has been installed on their PTP and de-bugged so that we now have a working system for making digital ISIS ionograms directly from the telemetry tapes. Earlier, we successfully digitized the PCM and NASA 36 bit time-code data from this same tape. The ionograms were digitized at the rate of 40,000 16-bit samples/sec. This sample rate is higher than the Nyquist frequency of 30 kHz appropriate for the post-detection ISIS 2 sounder-receiver video output which extends from DC to 15 kHz (see p. 50 of the 1971 ISIS 2 report by Daniels). The sample frequency of 40 kHz provides a measurement every 25 microseconds corresponding to an apparent range (ct/2) interval of 3.747 km. With the ISIS 2 prf of 45 sounder pulses/s, there are (1/45)/(2.5**(-5)) = 888.89 samples between each of the approximately 1015 sounder pulses per ionogram (including the fixed-frequency portion) or nearly 10**6 16-bit samples/ionogram (approximately 1.8 MBytes) for just the sounder-receiver video data. Adding header information, and the pcm data containing data from the other instruments, yields about 2 MBytes of data for the 22.5 s period corresponding to one ionogram. Two steps were taken in order to reduce this large volume of nearly 2 MBytes/ionogram. First, every four 25 microsecond samples following the sounder pulse were averaged. Second, the 16 bit samples were reduced to 8 bit samples. The first step decreased the apparent-range resolution to 15 km, but yielded high-quality ionograms because of the improved S/N due to the averaging.
created April 1995
Virtual variable.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
time of frequency markers
seperates the fixed and swept portions
This ionogram was digitized from the original ISIS 2 analog telemetry data on 7-track tape using the facilities of the Data Evaluation Laboratory at GSFC (Code 500). This data restoration project is headed by Dr. R.F. Benson (GSFC, Code 692). Ionograms were digitized at the rate of 40,000 16-bit samples/sec. This sample rate is higher than the Nyquist frequency of 30 kHz. The sample frequency of 40 kHz provides a measurement every 25 microseconds corresponding to an apparent range (c*t/2) interval of 3.747 km. Each ionogram consists of a fixed-frequency and and a swept-frequency portion. The time resolution is typically 24 seconds. More information can be found at http://nssdc/space/isis/isis-status.html
created April 1995
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
time of frequency markers
seperates the fixed and swept portions
This ionogram was digitized from the original ISIS 2 analog telemetry data on 7-track tape using the facilities of the Data Evaluation Laboratory at GSFC (Code 500). This data restoration project is headed by Dr. R.F. Benson (GSFC, Code 692). Ionograms were digitized at the rate of 40,000 16-bit samples/sec. This sample rate is higher than the Nyquist frequency of 30 kHz. The sample frequency of 40 kHz provides a measurement every 25 microseconds corresponding to an apparent range (c*t/2) interval of 3.747 km. Each ionogram consists of a fixed-frequency and and a swept-frequency portion. The time resolution is typically 24 seconds. More information can be found at http://nssdc/space/isis/isis-status.html
created April 1995
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
time of frequency markers
seperates the fixed and swept portions
This ionogram was digitized from the original ISIS 2 analog telemetry data on 7-track tape using the facilities of the Data Evaluation Laboratory at GSFC (Code 500). This data restoration project is headed by Dr. R.F. Benson (GSFC, Code 692). Ionograms were digitized at the rate of 40,000 16-bit samples/sec. This sample rate is higher than the Nyquist frequency of 30 kHz. The sample frequency of 40 kHz provides a measurement every 25 microseconds corresponding to an apparent range (c*t/2) interval of 3.747 km. Each ionogram consists of a fixed-frequency and and a swept-frequency portion. The time resolution is typically 24 seconds. More information can be found at http://nssdc/space/isis/isis-status.html
created April 1995
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
time of frequency markers
seperates the fixed and swept portions
A 7-track ISIS 2 analog telemetry tape from Ottawa (#561) has been digitized using the GSFC facilities of the Data Evaluation Laboratory (DEL) within the Mission Operations and Data Systems Directorate (Code 500) at Goddard. The digitization was performed using an A/D converter board and software device driver compatible with the OS/2 operating system used by the 486-based Programmable Telemetry Processor (PTP) associated software has been installed on their PTP and de-bugged so that we now have a working system for making digital ISIS ionograms directly from the telemetry tapes. Earlier, we successfully digitized the PCM and NASA 36 bit time-code data from this same tape. The ionograms were digitized at the rate of 40,000 16-bit samples/sec. This sample rate is higher than the Nyquist frequency of 30 kHz appropriate for the post-detection ISIS 2 sounder-receiver video output which extends from DC to 15 kHz (see p. 50 of the 1971 ISIS 2 report by Daniels). The sample frequency of 40 kHz provides a measurement every 25 microseconds corresponding to an apparent range (ct/2) interval of 3.747 km. With the ISIS 2 prf of 45 sounder pulses/s, there are (1/45)/(2.5**(-5)) = 888.89 samples between each of the approximately 1015 sounder pulses per ionogram (including the fixed-frequency portion) or nearly 10**6 16-bit samples/ionogram (approximately 1.8 MBytes) for just the sounder-receiver video data. Adding header information, and the pcm data containing data from the other instruments, yields about 2 MBytes of data for the 22.5 s period corresponding to one ionogram. Two steps were taken in order to reduce this large volume of nearly 2 MBytes/ionogram. First, every four 25 microsecond samples following the sounder pulse were averaged. Second, the 16 bit samples were reduced to 8 bit samples. The first step decreased the apparent-range resolution to 15 km, but yielded high-quality ionograms because of the improved S/N due to the averaging.
created April 1995
Virtual variable.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
time of frequency markers
seperates the fixed and swept portions
This ionogram was digitized from the original ISIS 2 analog telemetry data on 7-track tape using the facilities of the Data Evaluation Laboratory at GSFC (Code 500). This data restoration project is headed by Dr. R.F. Benson (GSFC, Code 692). Ionograms were digitized at the rate of 40,000 16-bit samples/sec. This sample rate is higher than the Nyquist frequency of 30 kHz. The sample frequency of 40 kHz provides a measurement every 25 microseconds corresponding to an apparent range (c*t/2) interval of 3.747 km. Each ionogram consists of a fixed-frequency and and a swept-frequency portion. The time resolution is typically 24 seconds. More information can be found at http://nssdc/space/isis/isis-status.html
created April 1995
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
time of frequency markers
seperates the fixed and swept portions
This ionogram was digitized from the original ISIS 2 analog telemetry data on 7-track tape using the facilities of the Data Evaluation Laboratory at GSFC (Code 500). This data restoration project is headed by Dr. R.F. Benson (GSFC, Code 692). Ionograms were digitized at the rate of 40,000 16-bit samples/sec. This sample rate is higher than the Nyquist frequency of 30 kHz. The sample frequency of 40 kHz provides a measurement every 25 microseconds corresponding to an apparent range (c*t/2) interval of 3.747 km. Each ionogram consists of a fixed-frequency and and a swept-frequency portion. The time resolution is typically 24 seconds. More information can be found at http://nssdc/space/isis/isis-status.html
created April 1995
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
time of frequency markers
seperates the fixed and swept portions
This ionogram was digitized from the original ISIS 2 analog telemetry data on 7-track tape using the facilities of the Data Evaluation Laboratory at GSFC (Code 500). This data restoration project is headed by Dr. R.F. Benson (GSFC, Code 692). Ionograms were digitized at the rate of 40,000 16-bit samples/sec. This sample rate is higher than the Nyquist frequency of 30 kHz. The sample frequency of 40 kHz provides a measurement every 25 microseconds corresponding to an apparent range (c*t/2) interval of 3.747 km. Each ionogram consists of a fixed-frequency and and a swept-frequency portion. The time resolution is typically 24 seconds. More information can be found at http://nssdc/space/isis/isis-status.html
created April 1995
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
time of frequency markers
seperates the fixed and swept portions
No TEXT global attribute value.
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This CDF format data set, I8_15sec_mag, version 2, ID=73-078A-01P (SPHE-00862) was made at NSSDC from the corrected ASCII version 73-078A-01O (SPHE-00861) in NSSDC's online FTP server interface NSSDCFTP. , which itself was created at NSSDC by converting the PI-provided 15.36-sec binary data set 73-078A-01N (SPHE-00860) to ASCII and simultaneously rejecting many little-used data words. With one exception (the number of detail p oints is omitted), the parameters in this CDF are exactly those included in the ASCII version 2 data set 73-078A-01O, which are: time, number of sequences, spacecraft position (GSE and GSM), field magnitude, field cartesian components (GS E and GSM), and the variances and covariances of the GSE field component averages. Unlike the original binary source data set, (73-078A-01N), this CDF data set and its ASCII version both use a common January 1 = day 1 convention throughout. The ASCII version of this data set is accessible at the NSSDCFTP interface: ftp://nssdcftp.gsfc.nasa.gov/spacecraft_data/imp/imp8/mag/15s_ascii/ In making this CDF, an intermediate data file was generated first, which duplicates the X components of the position and of the B vector, and in serts the new values explicitly in the GSM coordinate versions, so that the input to the CDF has all three components explicitly given for the G SM coordinates.
Master CDF made 10/19/99 by H. K. Hills, NSSDC. Modified to revised form v02 on 2/8/2005.
..
30-min avg flex I8 GME
v0.1 (vv01) May/Aug97 orig 30-min design V0.2 (vv02) Nov97 split protons into two vars by energies (not needed virvars) V0.3 (vv03) Jul/Aug98 cleaned up var names & set up for virvars V0.4 (vv04) Aug98 defined virvars for alternate views
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See online MIT documentation
CDF versions created August 2004
1:Non-tracking (NTMS), 2:Tracking (TMS), 3:Acquisition (AQM)
1:time solar wind, 2:time solar wind or magnetosheath, 3:time magnetosheath or magnetospheric
Pre-generated PWG plots
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Generated by SSCWeb from Heather Franz's "Second Experimental Ephemeris" as approved by IMP-8 PIs
Originated 03/14/96
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No TEXT global attribute value.
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Measurements of spectra and anisotropy of electrons witin energy ranges 20-40 keV from two time-of-flight detectors EM-1-1 and EM-1-2. The field of view of these detectors are directed oppositely and perpendicular to the satellite rotation axis. Data description: http://www.iki.rssi.ru/inte rball.html
created Sep 1998
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No TEXT global attribute value.
created Apr 1997
sensor offset at an angle 180 deg with respect to the sunward directed spacecraft spin axis
sensor offset at an angle 180 deg withrespect to the sunward directed spacecraft spin axis
sensor offset at an angle 180 deg with respect to the sunward directed spacecraft spin axis
sensor offset at an angle 180 deg withrespect to the sunward directed spacecraft spin axis
sensor offset at an angle 180 deg withrespect to the sunward directed spacecraft spin axis
The value is taken from the sensorthat can scan the angle's interval 45-180deg or can be fixed at angles 45, 90,135, 180 deg. with respect to the sunward directed spacecraft spin axis
Standard flags are used in the case ofdata absence. SFs are set to 11-15 and21-25 for all valid data values of each parameter. Most significant digit (1- low or 2 - high) indicates level of the energy threshold. Higher energy threshold will be used only in case ofdegradation of a sensor. Less significant digit indicates sensor orientation ( 1, 2, 3, 4, 5 correspondrespectively to 45, 90, 135, 180 deg.and scan)
Standard flags are used in the case ofdata absence. SFs are set to 11-15 and21-25 for all valid data values ofeach parameter. Most significant digit (1- low or 2 - high) indicates level of the energy threshold. Higher energy threshold will be used only in case ofdegradation of a sensor. Less significant digit indicates sensor orientation ( 1, 2, 3, 4, 5 correspondrespectively to 45, 90, 135, 180 deg.and scan)
Count rate of H+, O+ ions in 2 min, three directions, (1-30 keV) Status flag shows instrument mode. Data description: http://www.iki.rssi.ru/interball.html
created Sep 1998
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Full description: http://www.iki.rssi.ru/interball.html Full description: http://www.iki.rssi.ru/interball.html
created May 1997
2 min average
2 min. average, IMAP
2 min. average, IMAP
Full description: http://www.iki.rssi.ru/interball.html Full description: http://www.iki.rssi.ru/interball.html
created May 1997 edited global attributes Apr 1996
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References: 1.Troshichev O.A. et al, Planet.Space Sci., 36, 1095, 1988. 2.Vennerstrom S. et al, Report UAG-103, World Data Center A for STP, Boulder, April 1994 PC-index is an empirical magnetic activity index based on data from single near-pole station (Thule or Vostok for N or S hemispheres, respectively). Its derivation procedure is optimized to achieve the best correlation of PC-index with the solar wind electric field (SWEF) magnitude ( v*B*sin(teta/2)**2 ). The averaged horizontal magnetic disturbance vector (quiet value subtracted) is projected onto the optimal direction (defined empirically for each UT hour and each season based on the best correlation with the SWEF) and, after normalization to the equivalent value of SWEF, it gives the PC-index (expressed in mV/m). Although PC-index is formally expressed in mV/m, it actually represents the measure of magnetic activity, the normalization procedure (to SWEF) helps to reduce the seasonal/diurnal effects to facilitate the intercomparison. The resolution of the northern cap PC-index is 5 min and of the one from southern cap - 15 min. However, one time scale with the 5 min step is used for both indices and each 15 min averaged value of southern index is, hence, repeated for three times. Full description: http://www.iki.rssi.ru/interball.html
created Mar 1996
5 min. resolution
15 min averaged value of southern index is repeated for three times.
tbs
tbs
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tbs
tbs
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tbs
tbs
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tbs
tbs
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tbs
tbs
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tbs
tbs
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tbd
This is a virtual variable computed in read_myCDF
Geo = geographic coordinates
GSM = geocentric solar magnetospheric coordinates
The time in EPOCH refers to the center of the image in IMAGE. The times shown here are the actual time of exposure.
Counter-clockwise defined to be the positive direction. Represents the angle of rotation of the image field necessary to orient the North magnetic field at the top of the user's perspective.
Counter-clockwise defined to be the positive direction. Represents the angle of rotation of the image field necessary to orient the North magnetic field at the top of the user's perspective.
GSM = gencentric solar magnetospheric coordinates
Geo = geographic coordinates
No TEXT global attribute value.
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No TEXT global attribute value.
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No TEXT global attribute value.
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TBD
Master with plasmagram vv's re-integrated with data CDFs 12/6/00 REM; SKTEditor review and corrections applied to master 12/6/00 REM;
TBD
TBD
TBD
TBD
TBD
TBD
TBD
TBD
TBD
TBD
Detailed plasmagram picture has the original number of frequencies as specified by RPI measurement parameters. Frequency axis varies from plasmagram to plasmagram. Plasmagram *thumbnails* have a fixed frequency axis. The original plasmagram data often requires transformation into thumbnail format by averaging.
Number of Ranges, depending on program setting and processing.
TBD
TBD
values (numbers sequence only): 0= OFF (untuned), 1= ON (tuned)
0= OFF (untuned), 1= ON (tuned)
Translates Doppler Number to an actual Doppler Frequency. The entries are calculated from program parameters.
Translates Doppler Number to an actual Doppler Frequency. The entries are calculated from program parameters.
TBD
TBD
Values 0 to 254 cover 0 to 360 degrees
Values 0 to 254 cover 0 to 360 degrees
TBD
TBD
0= Search of quiet frequencies disabled, 1= Search of quiet frequencies enabled.
TBD
0= Fixed Gain, 1= Auto Gain.
0= Fixed Gain, 1= Auto Gain.
Most probable amplitude
TBD
Range readings
Start MET is derived using the Nadir crossing MET and the time offset from the first packet header. Might not be unique due to telemetry losses.
Most probable amplitude
MET of the last Nadir crossing before the measurement starts.
TBD
TBD
Detailed plasmagram picture has the original number of frequencies as specified by RPI measurement parameters. Frequency axis varies from plasmagram to plasmagram. Plasmagram *thumbnails* have a fixed frequency axis. The original plasmagram data often requires transformation into thumbnail format by averaging.
Number of Ranges, depending on program setting and processing.
Time in ms between start and stop of the measurement run.
Calibration, Sounding, Thermal Noise, Relaxation, Whistler, Test Pattern.
values: Calibration, Sounding, Thermal Noise, Relaxation, Whistler, Test Pattern; time-varying character data
Total RPI Peak Power Consumption Constraint.
Total RPI Peak Power Consumption Constraint.
TBD
The time in EPOCH refers to the beginning of the plasmagram. Use Duration_ms to obtain stop time of the run.
TBD
TBD
0.5 pps (1 pulse every 2 sec), 1 pps, 2 pps, 4 pps, 10 pps, 20 pps, 50 pps.
Range readings for 151 range bins
0.5 pps (1 pulse every 2 sec), 1 pps, 2 pps, 4 pps, 10 pps, 20 pps, 50 pps.
0= Search of quiet frequencies disabled, 1= Search of quiet frequencies enabled.
1= 16-chip complementary, 2= FM Chirp, 3= Staggered Pulse Sequence, 4= Long Pulse, 5= Short Pulse, 6= 0.5 s Pulse7= 1.95 s Pulse, 8= 8-chip complementary9= 4-chip complementary.
values (numbers sequence only): 1= 16-chip complementary, 2= FM Chirp, 3= Staggered Pulse Sequence, 4= Long Pulse, 5= Short Pulse, 6= 0.5 s Pulse7= 1.95 s Pulse, 8= 8-chip complementary9= 4-chip complementary.
values (numbers sequence only): 1= Radio Silence (no Tx), 2= X antenna only, 3= Y antenna only, 4= X+Y Linearly polarized, 5= X+Y Right Circularly Polarized, 6= X+Y Left Circularly Polarized, 7= X+Y Right/Left Alternated, 8= X+Y Lin/Lin90 Alternated.; time-varying character data
1= Radio Silence (no Tx), 2= X antenna only, 3= Y antenna only, 4= X+Y Linearly polarized, 5= X+Y Right Circularly Polarized, 6= X+Y Left Circularly Polarized, 7= X+Y Right/Left Alternated, 8= X+Y Lin/Lin90 Alternated.
electrons SKT version 24-July-2000 Mende et al: Far Ultraviolet Imaging from the IMAGE Spacecraft,Space Sciences Review 1999
(Omega)
Spacecraft Position at Snapshot Time
Spacecraft Position at Snapshot Time
Spacecraft Position at Snapshot Time
Spacecraft Position at Snapshot Time
direction of true spin axis at WIC Snapshot Time
direction of true spin axis at WIC Snapshot Time
direction of true spin axis at WIC Snapshot Time
direction of true spin axis at WIC Snapshot Time
Protons SKT version 24-July-2000 Mende et al: Far Ultraviolet Imaging from the IMAGE Spacecraft,Space Sciences Review 1999
(Omega)
Spacecraft Position at Snapshot Time
Spacecraft Position at Snapshot Time
Spacecraft Position at Snapshot Time
Spacecraft Position at Snapshot Time
direction of true spin axis at WIC Snapshot Time
direction of true spin axis at WIC Snapshot Time
direction of true spin axis at WIC Snapshot Time
direction of true spin axis at WIC Snapshot Time
No TEXT global attribute value.
REM - reset validmin to 250 on 11/29/00
REM - reset validmin to 250 on 11/29/00
REM - reset validmin to 250 on 11/29/00
REM - reset validmin to 250 on 11/29/00; LBH=Lyman-Birge-Hopfield
REM - reset validmin to 250 on 11/29/00; LBH=Lyman-Birge-Hopfield
Spacecraft Position at Snapshot Time
Spacecraft Position at Snapshot Time
Spacecraft Position at Snapshot Time
(Phi) flight software uses 315, analysis uses 45
(Omega)
(Theta)
(Omega)
Spacecraft Position at Snapshot Time
direction of true spin axis at WIC Snapshot Time
direction of true spin axis at WIC Snapshot Time
direction of true spin axis at WIC Snapshot Time
direction of true spin axis at WIC Snapshot Time
TBD
TBD
TBD
TBD
valid codes 1-16
TBD
values (numbers for sequence only): 0= Fixed Gain, 1= Auto Gain.
TBD
0= Fixed Gain, 1= Auto Gain.
The time in EPOCH refers to the beginning of the thermal noise measurement. Use Duration_ms to obtain stop time of the run.
Time in ms between start and stop of the measurement run.
Start MET is derived using the Nadir crossing MET and the time offset from the first packet header. Might not be unique due to telemetry losses.
MET of the last Nadir crossing before the measurement starts.
2**N, where N is RPI control parameter
Detailed plasmagram picture has the original number of frequencies as specified by RPI measurement parameters. Frequency axis varies from plasmagram to plasmagram. Plasmagram *thumbnails* have a fixed frequency axis. The original plasmagram data often requires transformation into thumbnail format by averaging.
Detailed plasmagram picture has the original number of frequencies as specified by RPI measurement parameters. Frequency axis varies from plasmagram to plasmagram. Plasmagram *thumbnails* have a fixed frequency axis. The original plasmagram data often requires transformation into thumbnail format by averaging.
2**N, where N is RPI control parameter
Time in ms between start and stop of the measurement run.
TBD
TBD
TBD
TBD
TBD
TBD
TBD
tbs
tbs
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Pre-generated PWG plots
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tbs
tbs
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Magnetic field measurements on the Interball- Tail satellites
are carried out by IZMIRAN and Space Research Institute RAS (SRI)
since 1995. Satellite has the orbits with apogee 200000 (30 Re) and
perigee 500 km. and provides measurements in the solar wind and in the different
regions of the magnetosphere at the same time with Geotail, Polar and
Interbal-A working in the magnetosphere and Wind, ACE in the solar wind.
Magnetic field measurements on-board the Interball Tail Probe are
carried out by the FM-3I and MFI instruments. FM-3I consists of two flux-gate
magnetometers M1 and M2 covering two different ranges: 200 nT and
1000 nT. The M2 instrument is mostly used to perform the attitude
control of the INTERBALL TAIL spacecraft. M1 magnetometer data are
transmitted to the scientific SSNI telemetry system at rates 0.125-16
vectors/s
depending on the instrument operating mode. The magnetic field data from
the M2 magnetometer are transmitted at the rate 1 vectors per 6 sec. to the
BNS attitude control system. MFI magnetometer has the next parameters:
measured range 0.3-37.5 nT, frequency range 0-2 Hz, sampling rate from 1/4
to 8 measurements per second. FM-3 M2 magnetometer failed in February
1996, FM-3 M1 and MFI are working until now.
Data presented here are the combination of the data of all
magnetometers. First of all FM-3 M1 data are used, if they are absent, used
MFI data
and if data of both magnetometer are absent, FM-3 M2 data presented. In
case of FM-3 M1 and MFI, data are averaged for 6 seconds intervals.
created CDF August 2000 by Mona Kessel, data provided by
Dr. Valery G. Petrov ZMIRAN,
Troitsk, Moscow region,
142092, Russia
http://antares.izmiran.rssi.ru/projects/PROGNOZ-MF/
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Radioemission flux measured in 100, 252, 500 kHz ranges, the passband 10 kHz. Loop antenna with 1.5 m2 area is used. Full description: http://www.iki.rssi.ru/interball.html
created May 1996
middle frequencies given, passbands are 10 kHz
2 min average of spectral amplitudes in three ranges, AKR-X instrument
No TEXT global attribute value.
created July 1996
2 min. resolution
2 min. resolution
2 min resolution
2 min resolution
2 min. resolution
Standard flags are used in case of data absence. For the valid data SF is in the range 10-12. 10 - good quality data. 11 - data in the spacecraft frame preliminary data.
No TEXT global attribute value.
created Mar 1996
2 min. resolution
2 min. resolution
2 min. resolution
2 min. resolution
Standard flags are used in case of data absence. For the valid data SF is in the range 10-38. Most significant digit (1-3) shows energy range used. Least significant digit shows number of the plate, data from which are used.
No TEXT global attribute value.
created Mar 1996
Electron and proton sensors of EV-3 subsystem are offset at an angle 135 deg with respect to the sunward directed spacecraft spin axis
sensor offset at an angle 180 deg with respect to the sunward directed spacecraft spin axis
sensor offset at an angle 180 deg with respect to the sunward directed spacecraft spin axis
Electron and proton sensors of EV-3 subsystem are offset at an angle 135 deg with respect to the sunward directed spacecraft spin axis
The value is taken from the sensor that can scan the angle's interval 45-180 deg or can be fixed at angles 45, 90, 135, 180 deg. with respect to the sunward directed spacecraft spin axis
sensor offset at an angle 180 deg with respect to the sunward directed spacecraft spin axis
Standard flags are used in the case of data absence. SFs are set to 11-15 and 21-25 for all valid data values of each parameter. Most significant digit (1 - low or 2 - high) indicates level of the energy threshold. Higher energy threshold will be used only in case of degradation of a sensor. Less significant digit indicates sensor orientation ( 1, 2, 3, 4, 5 correspond respectively to 45, 90, 135, 180 deg. and scan)
Standard flags are used in the case of data absence. SFs are set to 11-15 and 21-25 for all valid data values of each parameter. Most significant digit (1 - low or 2 - high) indicates level of the energy threshold. Higher energy threshold will be used only in case of degradation of a sensor. Less significant digit indicates sensor orientation ( 1, 2, 3, 4, 5 correspond respectively to 45, 90, 135, 180 deg. and scan)
Count rate of H+, O+ ions in 2 min, three directions, (1-30 keV) Status flag shows instrument mode. Data description: http://www.iki.rssi.ru/interball.html
created Feb 1996
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No TEXT global attribute value.
created Feb 1996
middle frequencies given, real ranges are 1-4, 600-850 Hz
2 min average of spectral amplitudes in two ranges, ASPI MIF-M/PRAM magnetometer
2 min. average, ASPI MIF-M/PRAM magnetometer
2 min. average, ASPI MIF-M/PRAM magnetometer
2 min. average, ASPI MIF-M/PRAM magnetometer
2 min. average, ASPI MIF-M/PRAM magnetometer
Flag values: 10 - data OK, 11 - mode with no amplitude values available
Standard values used, see description
No TEXT global attribute value.
created Feb 1997
2 min. resolution
Magnetic field averages and variance are computed from 4 Hz or 1 Hz data Mf1 magnetic field AC amplitudes are measured by fluxgate sensor. Mf2 magnetic field AC amplitudes are measured by search-coil. Mf3 plasma wave AC amplitudesare measured by Langmuir splitprobe. Full description: http://www.iki.rssi.ru/interball.html
created Jan 1998
2 min average of spectral amplitudes in five ranges, ASPI MIF-M/PRAM split Langmuir probe
middle frequencies given, real ranges are in label_Mf
middle frequencies given, real ranges are in label_Mf
2 min average of spectral amplitudes in two ranges, ASPI MIF-M/PRAM fluxgate
2 min average of spectral amplitudes in five ranges, ASPI MIF-M/PRAM search-coil
2 min. average, ASPI MIF-M/PRAM magnetometer
2 min. average, ASPI MIF-M/PRAM magnetometer
2 min. average, ASPI MIF-M/PRAM magnetometer
2 min. average, ASPI MIF-M/PRAM magnetometer
Flag values: 10 - magnetic field data in MF2, 11 - plasma current datain MF3, 2 - no filter data.
No TEXT global attribute value.
created Mar 1996
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Pre-generated PWG plots
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This file contains numerical moments computed from measurements of the Los Alamos Magnetospheric Plasma Analyzer (MPA) [Bame et al., Rev. Sci. Inst., in press 1993]. The moments are presented in s/c coordinates: the z-axis is aligned with the spin axis, which points radially toward the center of the Earth; the x-axis is in the plane containing the spacecraft spin axis and the spin axis of the Earth, with +X generally northward; and the y-axis points generally eastward. Polar angles are measured relative to the spin axis (+Z), and azimuthal angles are measured around the z-axis, with zero along the +X direction. The moments are computed for three 'species': lop (low-ener. ions, ~1eV/e-~130eV/e); hip (hi-ener. ions, ~130eV/e-~45keV/e); alle (electrons, ~30eV - ~45keV ). The electron measurements are obtained 21.5 secs after the ion measurements. Epoch is the measurement time appropriate for the ions. The moments are computed after the fluxes are corrected for background and s/c potential. Algorithms for these corrections are relatively unsophisticated, so the moments are suspect during times of high background and/or high spacecraft potential. Because the determined spacecraft potential is not very precise, the magnitude of the low-energy ion flow velocity is probably not accurate, but the flow direction is well determined. Tperp and Tpara are obtained from diagonalization of the 3-dimensional temperature matrix, with the parallel direction assigned to the eigenvalue which is most different from the other two. The corresponding eigenvector is the symmetry axis of the distribution and should be equivalent to the magnetic field direction. The eigenvalue ratio Tperp/Tmid, which is provided for each species, is a measure of the symmetry of the distribution and should be ~1.0 for a good determination. Several of the parameters have a fairly high daily dynamic range and for survey purposes are best displayed logarithmically. These parameters are indicated by non-zero 'SCALEMIN' values in this file. A quality flag value of 1 indicates that the values are preliminary and have not been checked in detail.
Created SEP 1992 Modified JAN 1993 Electron time tags removed Mag Latitude added Local time added Post Gap flag added Ratio variables changed Modified SEP 1994 Changes noted in mail message from M.Kessel
This is a virtual variable generated by read_myCDF w/ useof the data in the sc_pos_geo variable and a conversion routinespecified in the function attribute, namely conv_pos
This is a virtual variable generated by read_myCDF w/ useof the data in the sc_pos_geo variable and a conversion routinespecified in the function attribute, namely conv_pos
This is a virtual variable generated by read_myCDF w/ useof the data in the sc_pos_geo variable and a conversion routinespecified in the function attribute, namely conv_pos
Electron, proton and helium measurements are taken every 160 ms from one
of the three telescopes according to the following sequence: T1, T2, T3,
T2, T1, T2 etc. Heavy ion data accumulated from each of the three telescopes
again according to the timing and sequence above and summed for 10.24 seconds
which is approximately one spacecraft rotation. SOPA Key Parameters are
normally averaged over three telescopes for ~ 1 minute (6 - 10.24 second
data accumulation cycles) giving an average over much of the sky. The time
associated with each set of Key Parameters is determined by using the time
(in minutes of the day) at the start of each data collection cycle as an index
into an array of 1440 time slots dividing the day into 1440 one minute
intervals. The time reported is the midpoint of each interval.
We provide six fluxes:
Low energy Protons: 50 keV to 400 keV
High energy Protons: 1.2 MeV to 5 MeV
Low energy Electrons: 50 keV to 225 keV
High energy Electrons: 315 keV to 1.5 MeV
Helium : ~0.9 MeV to ~1.3 Mev
Heavy Ions : ~5 MeV to ~15 MeV (includes carbon, nitrogen,
and oxygen
We also compute two electron temperatures and densities and two proton
temperatures and densities. These are based on approximately the same energy
ranges as the fluxes given in above and are determined for relativistic
Maxwellian distributions.
Status of SOPA Instrument 1990-095: Loss of all ion data as of July 1992
All three thin, front, D1 detectors have failed, having become intolerably
noisy. The net result of this failure is the complete loss of proton,
helium, carbon, nitrogen, oxygen and other high Z Key Parameter data from
the instrument. Since all three thick, back D2 detectors are still
operating normally, the electron measurements remain only insignificantly
affected.
Data is flagged with a data quality flag as follows:
+1 Data is Good
0 Data is Suspect
-1 Data is Unusable
References: Belian, R. D., Gisler, G. R., Cayton, T. E., Christensen, R. A.,
High-Z Energetic Particles at Geosynchronous Orbit During The Great Solar
Proton Event Series of October 1989, J. Geophys. Res., 97, 16897, 1992
created 30-Nov-1992 added text to describe instrument 04-Feb-1993
alpha flux (Helium) averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
Electron flux is averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
Electron temperature determined from relativistic Maxwellian distributions and averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
Heavy Ion flux averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
Partial electron densities determined from relativistic Maxwellian distributions and averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
Partial proton densities determined from relativistic Maxwellian distributions and averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
proton flux averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
Proton temperature determined from relativistic Maxwellian distributions and averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
Pre-generated PWG plots
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This file contains numerical moments computed from measurements of the Los Alamos Magnetospheric Plasma Analyzer (MPA) [Bame et al., Rev. Sci. Inst., in press 1993]. The moments are presented in s/c coordinates: the z-axis is aligned with the spin axis, which points radially toward the center of the Earth; the x-axis is in the plane containing the spacecraft spin axis and the spin axis of the Earth, with +X generally northward; and the y-axis points generally eastward. Polar angles are measured relative to the spin axis (+Z), and azimuthal angles are measured around the z-axis, with zero along the +X direction. The moments are computed for three 'species': lop (low-ener. ions, ~1eV/e-~130eV/e); hip (hi-ener. ions, ~130eV/e-~45keV/e); alle (electrons, ~30eV - ~45keV ). The electron measurements are obtained 21.5 secs after the ion measurements. Epoch is the measurement time appropriate for the ions. The moments are computed after the fluxes are corrected for background and s/c potential. Algorithms for these corrections are relatively unsophisticated, so the moments are suspect during times of high background and/or high spacecraft potential. Because the determined spacecraft potential is not very precise, the magnitude of the low-energy ion flow velocity is probably not accurate, but the flow direction is well determined. Tperp and Tpara are obtained from diagonalization of the 3-dimensional temperature matrix, with the parallel direction assigned to the eigenvalue which is most different from the other two. The corresponding eigenvector is the symmetry axis of the distribution and should be equivalent to the magnetic field direction. The eigenvalue ratio Tperp/Tmid, which is provided for each species, is a measure of the symmetry of the distribution and should be ~1.0 for a good determination. Several of the parameters have a fairly high daily dynamic range and for survey purposes are best displayed logarithmically. These parameters are indicated by non-zero 'SCALEMIN' values in this file. A quality flag value of 1 indicates that the values are preliminary and have not been checked in detail.
Created SEP 1992 Modified JAN 1993 Electron time tags removed Mag Latitude added Local time added Post Gap flag added Ratio variables changed Modified SEP 1994 Changes noted in mail message from M.Kessel
This is a virtual variable generated by read_myCDF w/ useof the data in the sc_pos_geo variable and a conversion routinespecified in the function attribute, namely conv_pos
This is a virtual variable generated by read_myCDF w/ useof the data in the sc_pos_geo variable and a conversion routinespecified in the function attribute, namely conv_pos
This is a virtual variable generated by read_myCDF w/ useof the data in the sc_pos_geo variable and a conversion routinespecified in the function attribute, namely conv_pos
Electron, proton and helium measurements are taken every 160 ms from one
of the three telescopes according to the following sequence: T1, T2, T3,
T2, T1, T2 etc. Heavy ion data accumulated from each of the three telescopes
again according to the timing and sequence above and summed for 10.24 seconds
which is approximately one spacecraft rotation. SOPA Key Parameters are
normally averaged over three telescopes for ~ 1 minute (6 - 10.24 second
data accumulation cycles) giving an average over much of the sky. The time
associated with each set of Key Parameters is determined by using the time
(in minutes of the day) at the start of each data collection cycle as an index
into an array of 1440 time slots dividing the day into 1440 one minute
intervals. The time reported is the midpoint of each interval.
We provide six fluxes:
Low energy Protons: 50 keV to 400 keV
High energy Protons: 1.2 MeV to 5 MeV
Low energy Electrons: 50 keV to 225 keV
High energy Electrons: 315 keV to 1.5 MeV
Helium : ~0.9 MeV to ~1.3 Mev
Heavy Ions : ~5 MeV to ~15 MeV (includes carbon, nitrogen,
and oxygen
We also compute two electron temperatures and densities and two proton
temperatures and densities. These are based on approximately the same energy
ranges as the fluxes given in above and are determined for relativistic
Maxwellian distributions.
Status of SOPA Instrument 1991-080: Operating normally as of 01-Feb-1993
with the following exception. Detector D1 on Telescope 2 is becoming noisy.
This affects proton and ion data from that telescope. Bad data is disabled
thru software in the ground processing and is NOT averaged into the Key
parameter data. Therefore, the parameters given are good but do not cover
the same percentage of the sky.
Data is flagged with a data quality flag as follows:
+1 Data is Good
0 Data is Suspect
-1 Data is Unusable
LANL personnel should be contacted before using any data tagged as suspect.
References: Belian, R. D., Gisler, G. R., Cayton, T. E., Christensen, R. A.,
High-Z Energetic Particles at Geosynchronous Orbit During The Great Solar
Proton Event Series of October 1989, J. Geophys. Res., 97, 16897, 1992
created 30-Nov-1992 added text to describe instrument 04-Feb-1993
alpha flux (Helium) averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
Electron flux is averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
Electron temperature determined from relativistic Maxwellian distributions and averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
Heavy Ion flux averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
Partial electron densities determined from relativistic Maxwellian distributions and averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
Partial proton densities determined from relativistic Maxwellian distributions and averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
proton flux averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
Proton temperature determined from relativistic Maxwellian distributions and averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
This file contains numerical moments computed from measurements of the Los Alamos Magnetospheric Plasma Analyzer (MPA) [Bame et al., Rev. Sci. Inst., in press 1993]. The moments are presented in s/c coordinates: the z-axis is aligned with the spin axis, which points radially toward the center of the Earth; the x-axis is in the plane containing the spacecraft spin axis and the spin axis of the Earth, with +X generally northward; and the y-axis points generally eastward. Polar angles are measured relative to the spin axis (+Z), and azimuthal angles are measured around the z-axis, with zero along the +X direction. The moments are computed for three 'species': lop (low-ener. ions, ~1eV/e-~130eV/e); hip (hi-ener. ions, ~130eV/e-~45keV/e); alle (electrons, ~30eV - ~45keV ). The electron measurements are obtained 21.5 secs after the ion measurements. Epoch is the measurement time appropriate for the ions. The moments are computed after the fluxes are corrected for background and s/c potential. Algorithms for these corrections are relatively unsophisticated, so the moments are suspect during times of high background and/or high spacecraft potential. Because the determined spacecraft potential is not very precise, the magnitude of the low-energy ion flow velocity is probably not accurate, but the flow direction is well determined. Tperp and Tpara are obtained from diagonalization of the 3-dimensional temperature matrix, with the parallel direction assigned to the eigenvalue which is most different from the other two. The corresponding eigenvector is the symmetry axis of the distribution and should be equivalent to the magnetic field direction. The eigenvalue ratio Tperp/Tmid, which is provided for each species, is a measure of the symmetry of the distribution and should be ~1.0 for a good determination. Several of the parameters have a fairly high daily dynamic range and for survey purposes are best displayed logarithmically. These parameters are indicated by non-zero 'SCALEMIN' values in this file. A quality flag value of 1 indicates that the values are preliminary and have not been checked in detail.
Created SEP 1992 Modified JAN 1993 Electron time tags removed Mag Latitude added Local time added Post Gap flag added Ratio variables changed Modified SEP 1994 Changes noted in mail message from M.Kessel
This is a virtual variable generated by read_myCDF w/ useof the data in the sc_pos_geo variable and a conversion routinespecified in the function attribute, namely conv_pos
This is a virtual variable generated by read_myCDF w/ useof the data in the sc_pos_geo variable and a conversion routinespecified in the function attribute, namely conv_pos
This is a virtual variable generated by read_myCDF w/ useof the data in the sc_pos_geo variable and a conversion routinespecified in the function attribute, namely conv_pos
Electron, proton and helium measurements are taken every 160 ms from one
of the three telescopes according to the following sequence: T1, T2, T3,
T2, T1, T2 etc. Heavy ion data accumulated from each of the three telescopes
again according to the timing and sequence above and summed for 10.24 seconds
which is approximately one spacecraft rotation. SOPA Key Parameters are
normally averaged over three telescopes for ~ 1 minute (6 - 10.24 second
data accumulation cycles) giving an average over much of the sky. The time
associated with each set of Key Parameters is determined by using the time
(in minutes of the day) at the start of each data collection cycle as an index
into an array of 1440 time slots dividing the day into 1440 one minute
intervals. The time reported is the midpoint of each interval.
We provide six fluxes:
Low energy Protons: 50 keV to 400 keV
High energy Protons: 1.2 MeV to 5 MeV
Low energy Electrons: 50 keV to 225 keV
High energy Electrons: 315 keV to 1.5 MeV
Helium : ~0.9 MeV to ~1.3 Mev
Heavy Ions : ~5 MeV to ~15 MeV (includes carbon, nitrogen,
and oxygen
We also compute two electron temperatures and densities and two proton
temperatures and densities. These are based on approximately the same energy
ranges as the fluxes given in above and are determined for relativistic
Maxwellian distributions.
Status of SOPA Instrument 1994-084: Operating normally as of 01-Jan-1996
Data is flagged with a data quality flag as follows:
+1 Data is Good
0 Data is Suspect
-1 Data is Unusable
LANL personnel should be contacted before using any data tagged as suspect.
References: Belian, R. D., Gisler, G. R., Cayton, T. E., Christensen, R. A.,
High-Z Energetic Particles at Geosynchronous Orbit During The Great Solar
Proton Event Series of October 1989, J. Geophys. Res., 97, 16897, 1992
created 30-Nov-1992 added text to describe instrument 04-Feb-1993
alpha flux (Helium) averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
Electron flux is averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
Electron temperature determined from relativistic Maxwellian distributions and averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
Heavy Ion flux averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
Partial electron densities determined from relativistic Maxwellian distributions and averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
Partial proton densities determined from relativistic Maxwellian distributions and averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
proton flux averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
Proton temperature determined from relativistic Maxwellian distributions and averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
No TEXT global attribute value.
Created OCT 1998
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This file contains numerical moments computed from measurements of the Los Alamos Magnetospheric Plasma Analyzer (MPA) [Bame et al., Rev. Sci. Inst., in press 1993]. The moments are presented in s/c coordinates: the z-axis is aligned with the spin axis, which points radially toward the center of the Earth; the x-axis is in the plane containing the spacecraft spin axis and the spin axis of the Earth, with +X generally northward; and the y-axis points generally eastward. Polar angles are measured relative to the spin axis (+Z), and azimuthal angles are measured around the z-axis, with zero along the +X direction. The moments are computed for three 'species': lop (low-ener. ions, ~1eV/e-~130eV/e); hip (hi-ener. ions, ~130eV/e-~45keV/e); alle (electrons, ~30eV - ~45keV ). The electron measurements are obtained 21.5 secs after the ion measurements. Epoch is the measurement time appropriate for the ions. The moments are computed after the fluxes are corrected for background and s/c potential. Algorithms for these corrections are relatively unsophisticated, so the moments are suspect during times of high background and/or high spacecraft potential. Because the determined spacecraft potential is not very precise, the magnitude of the low-energy ion flow velocity is probably not accurate, but the flow direction is well determined. Tperp and Tpara are obtained from diagonalization of the 3-dimensional temperature matrix, with the parallel direction assigned to the eigenvalue which is most different from the other two. The corresponding eigenvector is the symmetry axis of the distribution and should be equivalent to the magnetic field direction. The eigenvalue ratio Tperp/Tmid, which is provided for each species, is a measure of the symmetry of the distribution and should be ~1.0 for a good determination. Several of the parameters have a fairly high daily dynamic range and for survey purposes are best displayed logarithmically. These parameters are indicated by non-zero 'SCALEMIN' values in this file. A quality flag value of 1 indicates that the values are preliminary and have not been checked in detail.
Created SEP 1992 Modified JAN 1993 Electron time tags removed Mag Latitude added Local time added Post Gap flag added Ratio variables changed Modified SEP 1994 Changes noted in mail message from M.Kessel
This is a virtual variable generated by read_myCDF w/ useof the data in the sc_pos_geo variable and a conversion routinespecified in the function attribute, namely conv_pos
This is a virtual variable generated by read_myCDF w/ useof the data in the sc_pos_geo variable and a conversion routinespecified in the function attribute, namely conv_pos
This is a virtual variable generated by read_myCDF w/ useof the data in the sc_pos_geo variable and a conversion routinespecified in the function attribute, namely conv_pos
Electron, proton and helium measurements are taken every 160 ms from one
of the three telescopes according to the following sequence: T1, T2, T3,
T2, T1, T2 etc. Heavy ion data accumulated from each of the three telescopes
again according to the timing and sequence above and summed for 10.24 seconds
which is approximately one spacecraft rotation. SOPA Key Parameters are
normally averaged over three telescopes for ~ 1 minute (6 - 10.24 second
data accumulation cycles) giving an average over much of the sky. The time
associated with each set of Key Parameters is determined by using the time
(in minutes of the day) at the start of each data collection cycle as an index
into an array of 1440 time slots dividing the day into 1440 one minute
intervals. The time reported is the midpoint of each interval.
We provide six fluxes:
Low energy Protons: 50 keV to 400 keV
High energy Protons: 1.2 MeV to 5 MeV
Low energy Electrons: 50 keV to 225 keV
High energy Electrons: 315 keV to 1.5 MeV
Helium : ~0.9 MeV to ~1.3 Mev
Heavy Ions : ~5 MeV to ~15 MeV (includes carbon, nitrogen,
and oxygen
We also compute two electron temperatures and densities and two proton
temperatures and densities. These are based on approximately the same energy
ranges as the fluxes given in above and are determined for relativistic
Maxwellian distributions.
Status of SOPA Instrument LANL-97A: Operating normally as of 01-Jul-1997
Data is flagged with a data quality flag as follows:
+1 Data is Good
0 Data is Suspect
-1 Data is Unusable
LANL personnel should be contacted before using any data tagged as suspect.
References: Belian, R. D., Gisler, G. R., Cayton, T. E., Christensen, R. A.,
High-Z Energetic Particles at Geosynchronous Orbit During The Great Solar
Proton Event Series of October 1989, J. Geophys. Res., 97, 16897, 1992
created 30-Nov-1992 added text to describe instrument 04-Feb-1993
alpha flux (Helium) averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
Electron flux is averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
Electron temperature determined from relativistic Maxwellian distributions and averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
Heavy Ion flux averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
Partial electron densities determined from relativistic Maxwellian distributions and averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
Partial proton densities determined from relativistic Maxwellian distributions and averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
proton flux averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
Proton temperature determined from relativistic Maxwellian distributions and averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
No TEXT global attribute value.
Created OCT 1998
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This file contains numerical moments computed from measurements of the Los Alamos Magnetospheric Plasma Analyzer (MPA) [Bame et al., Rev. Sci. Inst., in press 1993]. The moments are presented in s/c coordinates: the z-axis is aligned with the spin axis, which points radially toward the center of the Earth; the x-axis is in the plane containing the spacecraft spin axis and the spin axis of the Earth, with +X generally northward; and the y-axis points generally eastward. Polar angles are measured relative to the spin axis (+Z), and azimuthal angles are measured around the z-axis, with zero along the +X direction. The moments are computed for three 'species': lop (low-ener. ions, ~1eV/e-~130eV/e); hip (hi-ener. ions, ~130eV/e-~45keV/e); alle (electrons, ~30eV - ~45keV ). The electron measurements are obtained 21.5 secs after the ion measurements. Epoch is the measurement time appropriate for the ions. The moments are computed after the fluxes are corrected for background and s/c potential. Algorithms for these corrections are relatively unsophisticated, so the moments are suspect during times of high background and/or high spacecraft potential. Because the determined spacecraft potential is not very precise, the magnitude of the low-energy ion flow velocity is probably not accurate, but the flow direction is well determined. Tperp and Tpara are obtained from diagonalization of the 3-dimensional temperature matrix, with the parallel direction assigned to the eigenvalue which is most different from the other two. The corresponding eigenvector is the symmetry axis of the distribution and should be equivalent to the magnetic field direction. The eigenvalue ratio Tperp/Tmid, which is provided for each species, is a measure of the symmetry of the distribution and should be ~1.0 for a good determination. Several of the parameters have a fairly high daily dynamic range and for survey purposes are best displayed logarithmically. These parameters are indicated by non-zero 'SCALEMIN' values in this file. A quality flag value of 1 indicates that the values are preliminary and have not been checked in detail.
Created SEP 1992 Modified JAN 1993 Electron time tags removed Mag Latitude added Local time added Post Gap flag added Ratio variables changed Modified SEP 1994 Changes noted in mail message from M.Kessel
This is a virtual variable generated by read_myCDF w/ useof the data in the sc_pos_geo variable and a conversion routinespecified in the function attribute, namely conv_pos
This is a virtual variable generated by read_myCDF w/ useof the data in the sc_pos_geo variable and a conversion routinespecified in the function attribute, namely conv_pos
This is a virtual variable generated by read_myCDF w/ useof the data in the sc_pos_geo variable and a conversion routinespecified in the function attribute, namely conv_pos
Electron, proton and helium measurements are taken every 160 ms from one
of the three telescopes according to the following sequence: T1, T2, T3,
T2, T1, T2 etc. Heavy ion data accumulated from each of the three telescopes
again according to the timing and sequence above and summed for 10.24 seconds
which is approximately one spacecraft rotation. SOPA Key Parameters are
normally averaged over three telescopes for ~ 1 minute (6 - 10.24 second
data accumulation cycles) giving an average over much of the sky. The time
associated with each set of Key Parameters is determined by using the time
(in minutes of the day) at the start of each data collection cycle as an index
into an array of 1440 time slots dividing the day into 1440 one minute
intervals. The time reported is the midpoint of each interval.
We provide six fluxes:
Low energy Protons: 50 keV to 400 keV
High energy Protons: 1.2 MeV to 5 MeV
Low energy Electrons: 50 keV to 225 keV
High energy Electrons: 315 keV to 1.5 MeV
Helium : ~0.9 MeV to ~1.3 Mev
Heavy Ions : ~5 MeV to ~15 MeV (includes carbon, nitrogen,
and oxygen
We also compute two electron temperatures and densities and two proton
temperatures and densities. These are based on approximately the same energy
ranges as the fluxes given in above and are determined for relativistic
Maxwellian distributions.
Status of SOPA Instrument 1989-046: Operating normally as of 01-Feb-1993
Data is flagged with a data quality flag as follows:
+1 Data is Good
0 Data is Suspect
-1 Data is Unusable
LANL personnel should be contacted before using any data tagged as suspect.
References: Belian, R. D., Gisler, G. R., Cayton, T. E., Christensen, R. A.
High-Z Energetic Particles at Geosynchronous Orbit During The Great Solar
Proton Event Series of October 1989, J. Geophys. Res., 97, 16897, 1992
created 30-Nov-1992 added text to describe instrument 04-Feb-1993 Data reduction software updated. Temperature and Density algorithms implemented 15-dec-1993 Repaired some errors in the skeleton table 21-Feb-1995 Implemented updated algorithm for calculating Electron and Proton densities and temperatures 21-Feb-1995
alpha flux (Helium) averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
Electron flux is averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
Electron temperature determined from relativistic Maxwellian distributions and averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
Heavy Ion flux averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
Partial electron densities determined from relativistic Maxwellian distributions and averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
Partial proton densities determined from relativistic Maxwellian distributions and averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
proton flux averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
Proton temperature determined from relativistic Maxwellian distributions and averaged over 3 11deg telescopes (separated by 30deg) rotating with spacecraft
Mariner2 COHOweb connection
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Hourly averaged definitive multispacecraft interplanetary parameters data
created August 2003; conversion to ISTP/IACG CDFs via SKTEditor Feb 2000 Time tags in CDAWeb version were modified in March 2005 to use the CDAWeb convention of having mid-average time tags rather than OMNI's original convention of start-of-average time tags.
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1minute averaged definitive multispacecraft interplanetary parameters data
created November 2006; conversion to ISTP/IACG CDFs via SKTEditor Feb 2000 Time tags in CDAWeb version were modified in March 2005 to use the CDAWeb convention of having mid-average time tags rather than OMNI's original convention of start-of-average time tags.
Derived parameters are obtained from the following equations. Electric field = -V(km/s) * Bz (nT; GSM) * 10**-3
Derived parameters are obtained from the following equations. Alfven Mach number = (V * Np**0.5) / 20 * B
Derived parameters are obtained from the following equations. Flow pressure = (2*10**-6)*Np*Vp**2 nPa (Np in cm**-3, Vp in km/s, subscript p for proton)
The following spacecraft ID's are used: ACE 71, Geotail 60, IMP 8 50, Wind 51
The following spacecraft ID's are used: ACE 71, Geotail 60, IMP 8 50, Wind 51
The percent (0-100) of the points contributing to the 1-min magnetic field averages whose phase front normal (PFN) was interpolated because neither the MVAB-0 nor Cross Product shift techniques yielded a PFN that satisfied its respective tests.
Derived parameters are obtained from the following equations. Plasma beta = [(T*4.16/10**5) + 5.34] * Np / B**2 (B in nT)
Note that standard deviations for the two vectors are given as the square roots of the sum of squares of the standard deviations in the component averages. The component averages are given in the records but not their individual standard deviations.
Note that standard deviations for the two vectors are given as the square roots of the sum of squares of the standard deviations in the component averages. The component averages are given in the records but not their individual standard deviations. There are no phase front normal standard deviations in the 5-min records. This word has fill (99.99) for such records.
5minute averaged definitive multispacecraft interplanetary parameters data
created November 2006; conversion to ISTP/IACG CDFs via SKTEditor Feb 2000 Time tags in CDAWeb version were modified in March 2005 to use the CDAWeb convention of having mid-average time tags rather than OMNI's original convention of start-of-average time tags.
Derived parameters are obtained from the following equations. Electric field = -V(km/s) * Bz (nT; GSM) * 10**-3
Derived parameters are obtained from the following equations. Alfven Mach number = (V * Np**0.5) / 20 * B
Derived parameters are obtained from the following equations. Flow pressure = (2*10**-6)*Np*Vp**2 nPa (Np in cm**-3, Vp in km/s, subscript p for proton)
The following spacecraft ID's are used: ACE 71, Geotail 60, IMP 8 50, Wind 51
The following spacecraft ID's are used: ACE 71, Geotail 60, IMP 8 50, Wind 51
The percent (0-100) of the points contributing to the 1-min magnetic field averages whose phase front normal (PFN) was interpolated because neither the MVAB-0 nor Cross Product shift techniques yielded a PFN that satisfied its respective tests.
Derived parameters are obtained from the following equations. Plasma beta = [(T*4.16/10**5) + 5.34] * Np / B**2 (B in nT)
Note that standard deviations for the two vectors are given as the square roots of the sum of squares of the standard deviations in the component averages. The component averages are given in the records but not their individual standard deviations.
Pioneer10 COHOweb connection
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Pioneer11 COHOweb connection
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Pioneer6 COHOweb connection
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Pioneer7 COHOweb connection
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Important Warning: The data described below is meant for archival purposes. It should not be considered as highly accurate data. For example, accurate data requires a correction in the form of an offset to the Sunward component of the electric field. A constant offset of 1.2 mV/m has been used for all the data, this being an approximate average value. In fact, however, the offset varies with time, and must be determined by analysis of the particular time of interest. Users of this data desiring more information should get in touch with Dr. Forrest Mozer, at the Space Sciences Laboratory, University of California, Berkeley. The electric field data is at spin period time resolution. This means that there is 1 data point about every 6 seconds. However, it should be noted that there can be longer intervals between data points, due to missing data. Data gaps are not filled in. The components of the electric field are given in a coordinate system designated as Despun Spacecraft Coordinates , or DSC. This is a coordinate system for a rotating spacecraft that is in an orbit near the Earth. DSC is defined by the spacecraft's spin plane and spin axis. However, as the Despun part of the name suggests, the coordinate axes do not participate of the spacecraft's rotation. The X and Y axes are on the spacecraft's spin plane; the Z axis is along the spacecraft's spin axis. The positive X, Y, and Z axes form an orthogonal, right-handed coordinate system. The positive Z axis points in the same direction as the spacecraft's angular momentum (or spin or attitude) vector. The positive X axis points in the direction on the spin plane that is closest to the direction towards the Sun. In other words, the positive X axis points in the direction of the projection on the spin plane of the vector from the spacecraft to the Sun. The positive Y axis is determined by the requirement that the DSC system (X, Y, Z) be an orthogonal right-handed system. It follows that the positive Y axis points in the direction on the spin plane that is 90 degrees ahead of the positive X axis (in the sense of the spacecraft's rotation). The electric field data included in these files consists of 2 electric field components on the spin plane. The original data used is V34L, which typically has a time resolution of about 40 data points per second. A least-squares spin fit of V34L is performed, and the spin fit coefficients provide the spin plane components of the spin period electric field. Time is a real double-precision quantity. The units for the time are seconds. The time is time elapsed since the FAST Mission Epoch, which is May 24, 1968 (1968/05/24) at 00:00:00 UT. Each time tag indicates the mid-point of the time interval for the corresponding spin period. Data gaps are not filled; each time tag corresponds to an actual data point. X, Y, and Z are the 3 components of the attitude vector in the GSE coordinate system (note that all 3 X, Y, and Z components are present, despite the X in the file name).
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Important Warning: The data described below is meant for archival purposes. It should not be considered as highly accurate data. For example, accurate data requires a correction in the form of an offset to the Sunward component of the electric field. A constant offset of 1.2 mV/m has been used for all the data, this being an approximate average value. In fact, however, the offset varies with time, and must be determined by analysis of the particular time of interest. Users of this data desiring more information should get in touch with Dr. Forrest Mozer, at the Space Sciences Laboratory, University of California, Berkeley. The electric field data is at spin period time resolution. This means that there is 1 data point about every 6 seconds. However, it should be noted that there can be longer intervals between data points, due to missing data. Data gaps are not filled in. The components of the electric field are given in a coordinate system designated as Despun Spacecraft Coordinates , or DSC. This is a coordinate system for a rotating spacecraft that is in an orbit near the Earth. DSC is defined by the spacecraft's spin plane and spin axis. However, as the Despun part of the name suggests, the coordinate axes do not participate of the spacecraft's rotation. The X and Y axes are on the spacecraft's spin plane; the Z axis is along the spacecraft's spin axis. The positive X, Y, and Z axes form an orthogonal, right-handed coordinate system. The positive Z axis points in the same direction as the spacecraft's angular momentum (or spin or attitude) vector. The positive X axis points in the direction on the spin plane that is closest to the direction towards the Sun. In other words, the positive X axis points in the direction of the projection on the spin plane of the vector from the spacecraft to the Sun. The positive Y axis is determined by the requirement that the DSC system (X, Y, Z) be an orthogonal right-handed system. It follows that the positive Y axis points in the direction on the spin plane that is 90 degrees ahead of the positive X axis (in the sense of the spacecraft's rotation). The electric field data included in these files consists of 2 electric field components on the spin plane. The original data used is V34L, which typically has a time resolution of about 40 data points per second. A least-squares spin fit of V34L is performed, and the spin fit coefficients provide the spin plane components of the spin period electric field. Time is a real double-precision quantity. The units for the time are seconds. The time is time elapsed since the FAST Mission Epoch, which is May 24, 1968 (1968/05/24) at 00:00:00 UT. Each time tag indicates the mid-point of the time interval for the corresponding spin period. Data gaps are not filled; each time tag corresponds to an actual data point. E_X and E_Y are the X and Y components of the electric field in the DSC coordinate system (note that both the X and the Y component are present, despite the X in the file name). E_X and E_Y are real single-precision quantities. The units for the electric field components are mV/m. There are no missing data values; each data point value corresponds to an actual data point.
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Important Warning: The data described below is meant for archival purposes. It should not be considered as highly accurate data. For example, accurate data requires a correction in the form of an offset to the Sunward component of the electric field. A constant offset of 1.2 mV/m has been used for all the data, this being an approximate average value. In fact, however, the offset varies with time, and must be determined by analysis of the particular time of interest. Users of this data desiring more information should get in touch with Dr. Forrest Mozer, at the Space Sciences Laboratory, University of California, Berkeley. The electric field data is at spin period time resolution. This means that there is 1 data point about every 6 seconds. However, it should be noted that there can be longer intervals between data points, due to missing data. Data gaps are not filled in. The components of the electric field are given in a coordinate system designated as Despun Spacecraft Coordinates , or DSC. This is a coordinate system for a rotating spacecraft that is in an orbit near the Earth. DSC is defined by the spacecraft's spin plane and spin axis. However, as the Despun part of the name suggests, the coordinate axes do not participate of the spacecraft's rotation. The X and Y axes are on the spacecraft's spin plane; the Z axis is along the spacecraft's spin axis. The positive X, Y, and Z axes form an orthogonal, right-handed coordinate system. The positive Z axis points in the same direction as the spacecraft's angular momentum (or spin or attitude) vector. The positive X axis points in the direction on the spin plane that is closest to the direction towards the Sun. In other words, the positive X axis points in the direction of the projection on the spin plane of the vector from the spacecraft to the Sun. The positive Y axis is determined by the requirement that the DSC system (X, Y, Z) be an orthogonal right-handed system. It follows that the positive Y axis points in the direction on the spin plane that is 90 degrees ahead of the positive X axis (in the sense of the spacecraft's rotation). The electric field data included in these files consists of 2 electric field components on the spin plane. The original data used is V34L, which typically has a time resolution of about 40 data points per second. A least-squares spin fit of V34L is performed, and the spin fit coefficients provide the spin plane components of the spin period electric field. Time is a real double-precision quantity. The units for the time are seconds. The time is time elapsed since the FAST Mission Epoch, which is May 24, 1968 (1968/05/24) at 00:00:00 UT. Each time tag indicates the mid-point of the time interval for the corresponding spin period. Data gaps are not filled; each time tag corresponds to an actual data point. The original data used is V1L, V2L, etc., which typically have a time resolution of about 1 data point per 0.4 seconds. The spacecraft potentials come from spin period averages of the voltages V1L, V2L, etc. The spacecraft potential S_C_Pot12 is defined as follows: S_C_Pot12 = (V1 + V2) / 2 The spacecraft potential S_C_Pot34 is defined analogously. V1, V2, etc. stand for V1L, V2L, etc., respectively. One additional spacecraft potential, S_C_Pot1234, is defined as follows: S_C_Pot1234 = (S_C_Pot12 + S_C_Pot34) / 2 The plasma density n is obtained as a function of the spacecraft potential. The function is a power function, provided by Dr. Jack Scudder (University of Iowa). It comes from a fit to the POLAR Hydra particle data. The function was determined using data for 2001/04/01. The validity of the function for dates far from the date above has not been checked. Values above 75 are regarded as unphysical and re-assigned a NULL value. n will be in units of cm^(-3), i.e., number of charges per cubic centimeter.
Values above 75 are regarded as unphysical and re-assigned a NULL value.
TBS
6/13/91 - Original Implementation 9/18/91 - Modified for new attitude file format changes. ICCR 881 2/11/92 - Used the variable name TIME and type CDF_INT4 and size 3 instead of EPOCH, CDF_EPOCH and 1 for the time tags. CCR 490 6/1/92 - Added global attributes TITLE, PROJECT, DISCIPLINE, SOURCE_NAME, DATA_VERSION, and MODS; added variable attributes VALIDMIN, VALIDMAX, LABL_PTR_1, and MONOTON; added variables EPOCH and LABEL_TIME; changed variable name TIME to TIME_PB5. CCR 1066 11/07/92 - use cdf variable Epoch and Time_PB5 6/8/93 - Added global attributes ADID_ref and Logical_file_id. CCR 1092 7/5/94 - CCR ISTP 1852, updated CDHF skeleton to CDF standards - JT 9/20/94 - Added global attributes GCI_RA_ERR and GCI_DECL_ERR. CCR 1932 11/7/94 - Merged CCR 1852 changes and corrected errors made in CCR 1852. ICCR 1884 12/7/94 - Modified MODS and LABLAXIS to follow ISTP standards. ICCR 1885
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TBS
6/13/91 - Original Implementation 9/18/91 - Modified for new attitude file format changes. ICCR 881 2/11/92 - Used the variable name TIME and type CDF_INT4 and size 3 instead of EPOCH, CDF_EPOCH and 1 for the time tags. CCR 490 6/1/92 - Added global attributes TITLE, PROJECT, DISCIPLINE, SOURCE_NAME, DATA_VERSION, and MODS; added variable attributes VALIDMIN, VALIDMAX, LABL_PTR_1, and MONOTON; added variables EPOCH and LABEL_TIME; changed variable name TIME to TIME_PB5. CCR 1066 11/07/92 - use cdf variable Epoch and Time_PB5 6/8/93 - Added global attributes ADID_ref and Logical_file_id. CCR 1092 7/5/94 - CCR ISTP 1852, updated CDHF skeleton to CDF standards - JT 9/20/94 - Added global attributes GCI_RA_ERR and GCI_DECL_ERR. CCR 1932 11/7/94 - Merged CCR 1852 changes and corrected errors made in CCR 1852. ICCR 1884 12/7/94 - Modified MODS and LABLAXIS to follow ISTP standards. ICCR 1885
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Instrument functional description:
The VIS is a set of three low-light-level cameras. Two of these
cameras share primary and some secondary optics and are designed to
provide images of the nighttime auroral oval at visible wavelengths.
A third camera is used to monitor the directions of the fields-of-view
of the auroral cameras with respect to the sunlit Earth and return
global images of the auroral oval at ultraviolet wavelengths. The
VIS instrumentation produces an auroral image of 256 x 256 pixels
approximately every 24 seconds dependent on the integration time and
filter selected. The fields-of-view of the two nighttime auroral
cameras are 5.6 x 6.3 degrees and 2.8 x 3.3 degrees for the low and
medium resolution cameras, respectively. One or more Earth camera
images of 256 x 256 pixels are produced every five minutes, depending
on the commanded mode. The field-of-view of the Earth camera is
approximately 20 x 20 degrees.
Reference:
Frank, L. A., J. B. Sigwarth, J. D. Craven, J. P. Cravens, J. S. Dolan,
M. R. Dvorsky, J. D. Harvey, P. K. Hardebeck, and D. Muller,
'The Visible Imaging System (VIS) for the Polar Spacecraft',
Space Science Review, vol. 71, pp. 297-328, 1995.
[Note to first-time users: The first four variables are of primary
interest. The displayable 256 x 256 image array is in variable 3. The
correct orien- tation of a displayed image is explained in the
description of variable 3 below.]
Data set description:
The VIS Earth camera data set comprises all Earth camera images for
the selected time period. EJ-ER type files have images that have been
processed to remove the effects of penetrating radiation. In addition,
the images have been flat-fielded and fixed pattern noise has been
removed. Image pixels are median filtered with the images immediately
before and after in time. The displayable image counts are in variable
3. Some coordinate information is included for viewer orientation.
Coordinates are calculated for a grid of 18 x 18 points corresponding to
one pixel out of every 15 x 15 pixel block. In addition, a rotation
matrix and a table of distortion-correcting look direction unit vectors
are provided for the purpose of calculating coordinates for every pixel.
See the description of variables 14 and 15 below. To facilitate viewing
of the images, a mapping of pixel value to a recommended color table
based on the characteristics of the selected filter will be included with
each image. See the description of variables 19, 20, and 21 below. A
relative intensity scale is provided by the uncompressed count table of
variable 24. Approximate intensity levels in kiloRayleighs are given in
the intensity table of variable 25. Information on the availability of
more precisely calibrated intensities can be found on the VIS website at
URL .http://eiger.physics.uiowa.edu/~vis/software/.
Variable descriptions:
1,2. Center time
The time assigned to an image is the center time of the integration
period within a resolution of 50 milliseconds.
3. Image counts
Image pixel counts range from 0 to 255. They are stored in a two-
dimensional 256 x 256 byte array. Images from the Earth camera
(sensor 0) are conventionally displayed with row 1 at the top, row 256
at the bottom, column 1 on the left, and column 256 on the right. The
conventional image display for the low resolution camera (sensor 1) is
rotated 180 degrees so that the row 1-column 1 pixel is at the lower
right corner and the row 256-column 256 pixel is at the upper left
corner. When displayed in this manner, the spacecraft spin axis is
oriented to the right in the display, the X component is defined as
the center of the image look direction, and the Y component is the
4. Sensor number
0 = Earth camera,
1 = low resolution camera,
2 = medium resolution camera.
5. Half integration time
This is half the length of the integration period for the image,
measured in milliseconds.
6. Filter
Twelve filters are available for visible imaging; the filter number,
1-12, is given here. Ultra-violet imaging is done with one filter
only, designated here as filter number 0. In addition, the peak
wavelength in Angstroms is given for the selected filter.
7. Presumed altitude of emissions
The presumed altitude of the emissions seen in the image varies
with the characteristics of the filter used.
8. Platform pitch angle
This is the platform pointing angle of rotation around the spin
axis, measured from nadir.
9,10. Geographic coordinates
Geographic north latitude and east longitude are provided for the
pixels at these image array locations: every 15th row starting
with row 1 and ending with row 256, and every 15th column starting
with column 1 and ending with column 256, for a total of
18 x 18 coordinate pairs.
11,12. Spacecraft position and velocity vectors, GCI
The spacecraft position vector and velocity vector in GCI
coordinates are for the image center time as given in variables
1 and 2.
13. Spacecraft spin axis unit vector, GCI
14,15. Image-to-GCI rotation matrix and look direction vector table
The rotation matrix may be used with the look direction vector table to
obtain pointing vectors in GCI coordinates for each pixel. The
resulting vectors may be used to calculate coordinates for the observed
positions of the pixels. Software for this purpose is available at URL
.http://eiger.physics.uiowa.edu/~vis/software/. The general method
used is described below.
In the image coordinate system, the X axis is the center line-of-sight
or look direction; the Y axis is the cross product of the spin axis an
the X axis; and the Z axis is the cross product of the X axis and the
Y axis. When the display orientation conventions in the variable 3
description are applied, the low resolution camera image is rotated so
that both Earth camera and low resolution camera images are displayed
with Y axis pointing up and Z axis pointing toward the right.
To obtain the coordinates of the observed position of a pixel,
calculate the intersection of the line-of-sight with the surface
of an oblately spheroidal Earth at the altitude given as
variable 7. The equation of the spheroid is
X**2/(A+ALT)**2 + Y**2/(A+ALT)**2 + Z**2/(B+ALT)**2 = 1
where A is the Earth radius at the equator,
B is the Earth radius at the pole, and
ALT is the given altitude.
The line-of-sight equations are
(X-SCX)/DX = (Y-SCY)/DY = (Z-SCZ)/DZ
where (SCX,SCY,SCZ) is the spacecraft position vector GCI, and
(DX,DY,DZ) is the look direction unit vector GCI.
Solve the line-of-sight equations for two variables in terms
of the third; substitute into the spheroid equation; and use the
quadratic formula to solve for the third variable. Select
the solution point closer to the spacecraft.
16. Zenith angle of center line-of-sight at presumed altitude
This is the angle between the geocentric vector through the
observed point, assuming the altitude given as variable 7,
and the reverse of the image center line-of-sight vector.
17. Sun position unit vector, GCI
18. Solar zenith angle at observed point of center line-of-sight
This is the angle of the sun from zenith at the observed point
of the center line-of-sight, assuming the altitude given as
variable 7.
19. RGB color table
This is the recommended color table to be used with the
limits given in variables 20 and 21.
20,21. Low and high color mapping limits
The low and high color limits are recommended for remapping
the color table entries, as follows:
For pixel values less than the low limit, use the color
at table position 1.
assignments:
and less than or equal to the high limit, use the color
at table position (pix-low)/(high-low) x 255 + 1.
For pixel values greater than the high limit, use the color
at table position 256.
22. Data quality flag
The data quality word has bits set to 1 when the listed
conditions are true. Bit #31 is the most significant bit in the
word, and it will not be used as a flag. These are the bit
bit 0 - image data frame sync error
bit 1 - image data frame counters error
bit 2 - image data fill frame flag.
23. Post gap flag
The post gap flag has these possible values:
0 - no gap occurred immediately prior to this record,
1 - the gap occurred because the instrument was not in
a mode that allowed for the production of images for the
selected sensor,
2 - the gap occurred because level zero data were missing,
3 - the gap occurred because level zero data were too
noisy to extract images.
24. Expanded count table
The image pixel counts are quasi-logarithmically compressed to the
range 0-255. This table gives the average of the uncompressed range
for each compressed count value. Table entries 1-256 correspond to
compressed counts 0-255 respectively.
25. Intensity table
Approximate intensity levels in kiloRayleighs are given for each
compressed count value. Table entries 1-256 correspond to compressed
counts 0-255 respectively. Information on the availability of more
precisely calibrated intensities can be found on the VIS website at
URL .http://eiger.physics.uiowa.edu/~vis/software/.
Supporting software:
Supporting software is available on the VIS website at the URL
.http://eiger.physics.uiowa.edu/~vis/software/. Included is an IDL
program that displays the images with the recommended color bar and
provides approximate intensities and coordinate data for each pixel.
Initial development Updated TEXT section bug Updated some variables Added an ADID number, same as K1 changed linear validmin 0->10, validmax 255->60 to suppress dayglow - 4/12/01 - REM changed log validmin 0->1, validmax 255->18 to suppress dayglow - 4/12/01 - REM
Image_Counts contains the displayable image. The counts have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value for Image_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Approximate intensity in kR is Intens_Table(Image_Counts(i,j)+1).The appearance of the actual count value 255 is rare. When displaying an image,it works best to use the fill value as an overflow (i.e. brightest) value.
Image_Counts contains the displayable image. The counts have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value for Image_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Approximate intensity in kR is Intens_Table(Image_Counts(i,j)+1).The appearance of the actual count value 255 is rare. When displaying an image,it works best to use the fill value as an overflow (i.e. brightest) value.
Image_Counts contains the displayable image. The counts have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value for Image_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Approximate intensity in kR is Intens_Table(Image_Counts(i,j)+1).The appearance of the actual count value 255 is rare. When displaying an image,it works best to use the fill value as an overflow (i.e. brightest) value.
Image_Counts contains the displayable image. The counts have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value for Image_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Approximate intensity in kR is Intens_Table(Image_Counts(i,j)+1).The appearance of the actual count value 255 is rare. When displaying an image,it works best to use the fill value as an overflow (i.e. brightest) value.
Image_Counts contains the displayable image. The counts have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value for Image_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Approximate intensity in kR is Intens_Table(Image_Counts(i,j)+1).The appearance of the actual count value 255 is rare. When displaying an image,it works best to use the fill value as an overflow (i.e. brightest) value.
Image_Counts contains the displayable image. The counts have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value for Image_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Approximate intensity in kR is Intens_Table(Image_Counts(i,j)+1).The appearance of the actual count value 255 is rare. When displaying an image,it works best to use the fill value as an overflow (i.e. brightest) value.
Image_Counts contains the displayable image. The counts have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value for Image_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Approximate intensity in kR is Intens_Table(Image_Counts(i,j)+1).The appearance of the actual count value 255 is rare. When displaying an image,it works best to use the fill value as an overflow (i.e. brightest) value.
Image_Counts contains the displayable image. The counts have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value for Image_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Approximate intensity in kR is Intens_Table(Image_Counts(i,j)+1).The appearance of the actual count value 255 is rare. When displaying an image,it works best to use the fill value as an overflow (i.e. brightest) value.
Approximate intensity in kR for Image_Counts(i,j) isIntens_Table(Image_Counts(i,j)+1)
MSB will not be used as a flag; see TEXT for other bit assignments
Image_Counts contains the displayable image. The counts have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value for Image_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Approximate intensity in kR is Intens_Table(Image_Counts(i,j)+1).The appearance of the actual count value 255 is rare. When displaying an image,it works best to use the fill value as an overflow (i.e. brightest) value.
Image_Counts contains the displayable image. The counts have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value for Image_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Approximate intensity in kR is Intens_Table(Image_Counts(i,j)+1).The appearance of the actual count value 255 is rare. When displaying an image,it works best to use the fill value as an overflow (i.e. brightest) value.
Image_Counts contains pixel counts which have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value forImage_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1).
Filters #1-12 are visible wavelengths; filter #0 is UV for Earth camera images
Geographic N. latitude for pixels at every 15th row and column from 1 to 256
Geographic N. latitude for pixels vals - computed by CDAWeb
Geographic E. longitude for pixels at every 15th row and column from 1 to 256
Geographic E. longitude for pixels vals - computed by CDAWeb
X component is look direction,Y component is the spin axis cross X
Platform angle of rotation around spin axis, measured from nadir in tenths of degrees
RGBColorTable should be remapped for displaying an image using the low and high limits given for each image in Limit_Lo and Limit_Hi.Image_Counts count values less than Limit_Lo use the color at table position 1. Count values greater than Limit_Hi use the color at table position 256. For count values greater than or equal to Limit_Lo and less than or equal to Limit_Hi, the table position is (Count-Limit_Lo)/(Limit_Hi-Limit_Lo) x 255 + 1.At the selected table position C, the color components are Red at RGBColorTable(1,C), Green at RGBColorTable(2,C), and Blue at RGBColorTable(3,C).
No TEXT global attribute value.
CDF Master created 3/21/03
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Reference: HYDRA is a 3-Dimensional Electron and Ion Hot Plasma Instrument for the Polar Spacecraft of the GGS Mission, J. Scudder et al., Space Sci. Rev., 71,459-495, Feb. 1995. http://www-st.physics.uiowa.edu This data set contains the differential electron and proton omnidirectional fluxes per unit solid angle vs energy, at 13.8-second resolution. Multiply the given value by 4 pi to obtain the total omnidirectional differential energy flux. There are 29 energy channels from 12.5 ev to 18.3 keV. HYDRA is composed of two boxes, each housing 6 detectors. A separate stepping power supply is used for each box. The values of these steps are designed to be interlaced. Therefore, the energies designated in this file are interpolated between the values of the two power supplies. Stepping modes may also vary the number and range of steps during the mission. To accommodate these changes an interpolation is done from the steps for a particular mode to the common energy values listed in ENERGY_ELE and ENERGY_ION.
Generated March 26, 2003.
Multiply the given value by 4 pi to obtain the total omnidirectional differential energy flux.
Interpolated Electron Energies are at the center of a channel that is +/- 3% of the stated energy. Linear flux is interpolated with respect to the log of the energy.
Interpolated Ion Energies are at the center of a channel that is +/- 3% of the stated energy. Linear flux is interpolated with respect to the log of the energy.
Multiply the given value by 4 pi to obtain the total omnidirectional differential energy flux.
-
Reference:..Gurnett, D.A. et al, The Polar plasma wave instrument, Space Science Reviews, Vol. 71, pp. 597-622, 1995.GURNETT@IOWAVE.physics.uiowa.edu Note:..The electron cyclotron frequencies are derived from the following: Fce = 0.028 kHz*B, where B is the magnitude of the ambient magnetic field measured in nT. All frequencies are converted to Hz. There are 20 MCA E frequency bands, logarithmically spaced and 14 MCA B frequency bands, logarithmically spaced.
Created Dec 1997
Uses the first 14 Frequency Values
Contains Year, DOY, MSOD
TIDE data for dates 28-Mar-1996 to 30-Sep-1996 are mass resolved. TIDE data between 01-Oct-1996 and 07-Dec-1996 are not valid.
Skeleton table version 1 created 08/10/98. Skeleton table version 2 created 10/16/00. Skeleton table version 3 created 07/12/06.
Spacecraft potential file used to create this CDF file
Correction value added to each EFI spacecraft potential value.
Flux values summed or averaged over spin and polar angles. See spect_lim for sum/avg limits, see sum_avg to determine which one was used.
Available before 01-Oct-1996 only,for energy, spin angle, and polar angle calculation see moments_lim.
Only available before 01-Oct-1996. Direction of magnetic field obtained from onboard values. See moments_lim for energy, spin angle, and polar angle calculation limits.
Only available before 01-Oct-1996
Flux values summed or averaged over energy and spin angle. See spect_lim for for sum/avg limits, see sum_avg to determine which one was used.
Flux values summed or averaged over energy and polar angle. See spect_lim for for sum/avg limits, see sum_avg to determine which one was used.
Flux values summed or averaged over spin and polar angles. See spect_lim for sum/avg limits, see sum_avg to determine which one was used.
Only available before 01-Oct-1996
Available before 01-Oct-1996 only,for energy, spin angle, and polar angle calculation see moments_lim.
Only available before 01-Oct-1996. Direction of magnetic field obtained from onboard values. See moments_lim for energy, spin angle, and polar angle calculation limits.
Flux values summed or averaged over energy and spin angle. See spect_lim for sum/avg limits, see sum_avg to determine which one was used.
Flux values summed or averaged over energy and polar angle. See spect_lim for sum/avg limits, see sum_avg to determine which one was used.
magnetic field elevation
magnetic field elevation
Correction factor multiplied by each mask count in order to reduce the over subtraction.
If sub_min = 1, the minimum count in each spin of data has been subtracted as a means of reducing the noice level. If sub_min = 0, no minimum count subtraction was done.
Flux values summed or averaged over spin and polar angles. See spect_lim for sum/avg limits, see sum_avg to determine which one was used.
Only available before 01-Oct-1996
Available before 01-Oct-1996 only,for energy, spin angle, and polar angle calculation limits see moments_lim.
Only available before 01-Oct-1996. Direction of magnetic field obtained from onboard values. See moments_lim for energy, spin angle, and polar angle calculation limits.
Flux values summed or averaged over energy and spin angle. See spect_lim for sum/avg limits, see sum_avg to determine which one was used.
Flux values summed or averaged over energy and polar angle. See spect_lim for sum/avg limits, see sum_avg to determine which one was used.
PSI instrument status flag: 0 - PSI not operation or data missing, 1 - PSI fully operational, 2 - PSI on but keeper not ignited.
Polar attitude file used to create this CDF file
Polar orbit file used to create this CDF file
value either constant or from EFI K0
polar angle direction of the spacecraft
spin angle direction of the spacecraft
the number of spacecraft spins averaged for each time period
TIDE instrument status flag: 0 - TIDE not operational or data missing, 1 - TIDE fully operational, 2 - TIDE MCP high voltages lowered for passage through radiation belt, 3 - TIDE mirrors stepped down due to high counts, calibration applied to correct counts.
TIDE lz file used to create this CDF file
Type of long term calibration correction applied.
Name of file containing the instrument calibration input data.
The mask file used to subtract background noise.
Name for file containing mass calibration input data.
The energy and spin and polar angle ranges used in the moments calculations
The version of the TIDE level-zero processing software used to create the CDF file.
The b-field data (mag_az and mag_el) can either be from TIDE telemetry (0) or from MFE high time resolution data (1).
The counts in the spectrograms can be summed (1), averaged (2), or the maximum (3) of the data whose ranges are specified in spect_lim.
The energy and spin and polar angle ranges used to create the spectrogram sums
H+, O+, He+ and He++ number fluxes and statistical uncertainties processed by the TIMAS science team. Data acquired with various anglular and energy resolutions are combined here. Data Quality and other indicators are provided to allow selection of high resolution data (PA_status(ion)=0 and Energy_status(ion)=0 ) and High Quality data (Quality=0). See the VAR_NOTES for the following variables for more detailed information. Quality, PA_status, Energy_status Bcr, Fec, Even_odd, Energy_Range_ID and Spins. A PAPCO module exists that reads and displays these data and data From other POLAR instruments. See http://www.mpae.gwdg.de/mpae_projects/CCR/software/papco/papco.html and the pointer to a description of the TIMAS PAPCO module on the TIMAS home page. Reference: E.G. Shelley et al., The Toroidal Imaging Mass-Angle Spectrograph (TIMAS) for the Polar Mission, Sp. Sci. Rev, Vol 71, pp 497-530, 1995. ftp://sierra.spasci.com/DATA/timas/TIMAS_description.html Metadata provided by W.K. Peterson
Version 0 December, 1997 Version 1 July, 1998 Version 2 December, 2000 Algorithm improved to more accurately subtract backgrounds arising from spill over from H+ into He++ channel and other sources. Fill data are now inserted for limited energy and pitch angle ranges for Flux_H Flux_O Flux_He_1 and Flux_He_2 variables. The meanging of values of the of Quality variable have been slightly modified
A quality flag in the range 0-99 with the following values/meanings 0 OK. 1 Some data missing. 2 more than 5% data missing 3 not used. 4 not used. 5 Warning flags set. 6 not used. 99 No valid data. 0-1 indicate High quality data. 2 indicates adequate qualty data
Value clipped at 255% of flux.
VV - Value clipped at 255% of flux.
VV - Value clipped at 255% of flux.
Value clipped at 255% of flux.
VV - Value clipped at 255% of flux.
VV - Value clipped at 255% of flux.
Value clipped at 255% of flux.
VV - Value clipped at 255% of flux.
VV - Value clipped at 255% of flux.
Value clipped at 255% of flux.
VV - Value clipped at 255% of flux.
VV - Value clipped at 255% of flux.
TIMAS is operated in one of 3 energy ranges. Energy_Range_ID indicates which of the 3 instrumental energy ranges is currently active. Each instrumental energy range further divided into 3 Key Parameter (KP) energy channels (low - medium - and high). The table below gives the full energy range and limits of the three KP energy ranges. Energy_Range_ID=0: (Full instrumental energy range)Full range (0.015 - 33.3 keV/e)low E channel (0.015 - 0.37 keV/e)mid E channel (0.37 - 3.3 keV/e)high E channel (3.3 - 33.3 keV/e)Energy_Range_ID=1: (Reduced instrumental energy range)Full range (0.015 - 22.45 keV/e)low E channel (0.015 - 0.37 keV/e)mid E channel (0.37 - 3.3 keV/e)high E channel (3.3 - 22.45 keV/e)Energy_Range_ID=2: (Low instrumental energy range)Full range (0.015 - 2.18 keV/e)low E channel (0.015 - 0.11 keV/e)mid E channel (0.11 - 0.37 keV/e)high E channel (0.37 - 2.18 keV/e)
TIMAS data are available from operational modes with full (28 bins) or moderate (7 bins) energy resolution. These data were assembled from various data products with different energy resolution. Data are given in this file with full 28 energy step resolution EVEN IF ONLY 7 energy step resolution data are available. This flag documents the resolution of the data included in the average. Values are: 0 All single spin 14 energy step data. 1 Mostly 14 energy step data. Some 7 energy step. All one or two spin.2 Mostly 7 energy step data. Some 14 energy step. All one or two spin. 3 All one or two spin 7 energy step data.4 Mostly 14 energy step data. Some 7 energy step multispins. 5 Mostly one or two spin 7 energy step data. Some multispins. 6 Mostly multispin 7 energy step data. 7 All multispin 7 energy step data. 99 Invalid energies.Some of these conditions (1,2,4,5,6) are very rare.
TIMAS data are available from operational modes with full (28 bins) or moderate (7 bins) energy resolution. These data were assembled from various data products with different energy resolution. Data are given in this file with full 28 energy step resolution EVEN IF ONLY 7 energy step resolution data are available. This flag documents the resolution of the data included in the average. Values are: 0 All single spin 14 energy step data. 1 Mostly 14 energy step data. Some 7 energy step. All one or two spin.2 Mostly 7 energy step data. Some 14 energy step. All one or two spin. 3 All one or two spin 7 energy step data.4 Mostly 14 energy step data. Some 7 energy step multispins. 5 Mostly one or two spin 7 energy step data. Some multispins. 6 Mostly multispin 7 energy step data. 7 All multispin 7 energy step data. 99 Invalid energies.Some of these conditions (1,2,4,5,6) are very rare.
0 first (even) spin with even numbered energy steps 1 second (odd) spin with odd numbered energy steps. TIMAS samples 28 energy steps over the full energy range every two spins (12 seconds). On even numbered spins the lowest energy step (centered at 25 eV/e) and alternate energy steps over the full energy range are sampled. On odd spins the second energy step (centered at 45 eV/e) and alternate energy steps to the maximum are sampled.
CDAWeb VV - Negative values reflect low counting rates and background subtraction.
CDAWeb VV - Negative values reflect low counting rates and background subtraction.
CDAWeb VV - Negative values reflect low counting rates and background subtraction.
Value set to fill if the Fec is > 400 OR the Bcr is > the Fec OR the data value is > Sigma_He_2. Negative values reflect low counting rates and background subtraction.
Negative values reflect low counting rates and background subtraction.
VV - Negative values reflect low counting rates and background subtraction.
VV - Negative values reflect low counting rates and background subtraction.
Value set to fill if the Fec is > 400 OR the Bcr is > the Fec OR the data value is > Sigma_He_1. Negative values reflect low counting rates and background subtraction.
Negative values reflect low counting rates and background subtraction.
VV-Negative values reflect low counting rates and background subtraction.
VV-Negative values reflect low counting rates and background subtraction.
Center epoch (milliseconds since 0 ADof VARIABLE accumulation intervals for He++. See also variables Epoch_start, Epoch_stop, and Spins
Stop epoch of VARIABLE accumulation intervals for H+, O+, He+ and He++ ions. This variable is used to pass interval times to the TIMAS PAPCO module.
Number of spins of data accumulatedfor each of the 4 major ion species .
VV - Negative values reflect low counting rates and background subtraction.
VV - Negative values reflect low counting rates and background subtraction.
VV - Negative values reflect low counting rates and background subtraction.
Value set to fill if the Fec is > 400 OR the Bcr is > the Fec OR the data value is > Sigma_O. Negative values reflect low counting rates and background subtraction.
TIMAS data are available from operational modes with various anglular resolutions. These data were assembled from various data products with different angular resolutions. Data are given in this file with full 12 angular bin resolution EVEN IF 12 angular bin resolution is not available in the input data. This flag documents the resolution of the data included in the average. Values are: 0 All 22 degree data. 1 Mostly 22 degree data. 2 Mostly 45 degree data. 3 All 45 degree data. 4 Smeared 22 degree data. Not spin locked.5 Smeared 45 degree data. Not spin locked. 99 Invalid pitch angles. IMPORTANT NOTE: VALID DATA ARE INCLUDED FOR INTERVALS WITH INVALID PITCH ANGLES.When calculating the omnidirectonal flux average for intervals with invalid pitch angles the values of the pitch angles must be ignored.
TIMAS data are available from operational modes with various anglular resolutions. These data were assembled from various data products with different angular resolutions. Data are given in this file with full 12 angular bin resolution EVEN IF 12 angular bin resolution is not available in the input data. This flag documents the resolution of the data included in the average. Values are: 0 All 22 degree data. 1 Mostly 22 degree data. 2 Mostly 45 degree data. 3 All 45 degree data. 4 Smeared 22 degree data. Not spin locked.5 Smeared 45 degree data. Not spin locked.99 Invalid pitch angles.
A quality flag in the range 0-99 with the following values/meanings 0 OK. 1 Some data missing. 2 Slight MCP saturation. 3 Moderate MCP saturation. 4 Severe MCP saturation. 5 No magnetometer data available. 6 Warning flags set. 99 No valid data.
Value clipped at 255% of flux.
Total background counts per spin
The TIMAS detector has a non linear response at high count rates that is, to some extent corrected for in the software that generated the data here. The correction, however introduces some uncertainty. The FEC count rate is carried as an indication of the corrections applied to the raw data.
Value clipped at 255% of flux.
Value clipped at 255% of flux.
Value clipped at 255% of flux.
Value clipped at 255% of flux.
Negative values reflect low counting rates and background subtraction.
Negative values reflect low counting rates and background subtraction.
Negative values reflect low counting rates and background subtraction.
Negative values reflect low counting rates and background subtraction.
References -------------------- 1. M. R. Torr, et al., A far ultraviolet imager for the International Solar-Terrestrial Physics mission, Space Sci. Rev., v71, pp329 - 383, 1995 Notes ------------------------ 1. The UVI field of view is circular with an 8 degree full width. The circular image is stored in IMAGE_DATA as a rectangular array of 228 rows and 200 columns. 2. Time information is contained in EPOCH, Time_PB5, IMG_MINUS_MSEC, and IMG_PLUS_MSEC. 3. Pointing information is given in GCI_LOOK_DIR, GEODETIC_LAT, and GEODETIC_LONG.
v1.0 Initial Prelaunch Release 10/16/95 v1.0 Interim Prelaunch Release 5/8/96 Added KPGS_VERSION 3/9/97 Changed min/max valuesfor IMAGE_DATA
The time in EPOCH and Time_PB5 refer to the center of the image in IMAGE_DATA. There is an offset of up to 8 major frames between the beginning of the image exposure and the ATC telemetry time stamp. The times shown here are corrected for this and describe the actual time of exposure.
The UVI field of view is circular with an 8 degree full width. The circular image is stored in IMAGE_DATA as a rectangular array of 228 rows and 200 columns. Consequently, the corners of each image contain non-image data. The non-active corner pixel locations are identified by a corner fill value = -128. The image is oriented such that the direction of decreasing row number points along the spacecraft spin axis. The direction of decreasing column number points to the outboard direction (relative to the spin axis). The orientation is the same for both detectors.
Reference:..Gurnett, D.A. et al, The Polar plasma wave instrument, Space Science Reviews, Vol. 71, pp. 597-622, 1995.GURNETT@IOWAVE.physics.uiowa.edu There are 224 SFR frequency bands, logarithmically spaced. When SFR_MODE is Linear, the 448 linear frequency bands are mapped to 224 logarithmic bands.
Created July 2000
Linear mode data is mapped to Log Mode
TIDE data after 07-Dec-1996 are non-mass total ion contribution below 411 ev
Skeleton table version 1 created 10/16/00. Skeleton table version 2 created 07/12/06.
Spacecraft potential file used to create this CDF file
Correction value added to each EFI spacecraft potential value.
magnetic field elevation
magnetic field elevation
Correction factor multiplied by each mask count in order to reduce the over subtraction.
The mass to charge ratio used in the moments calculations.
If sub_min = 1, the minimum count in each spin of data has been subtracted as a means of reducing the noice level. If sub_min = 0, no minimum count subtraction was done.
PSI instrument status flag: 0 - PSI not operation or data missing, 1 - PSI fully operational, 2 - PSI on but keeper not ignited.
Polar attitude file used to create this CDF file
Polar orbit file used to create this CDF file
value either constant or from EFI K0
polar angle direction of the spacecraft
spin angle direction of the spacecraft
the number of spacecraft spins averaged for each time period
TIDE instrument status flag: 0 - TIDE not operational or data missing, 1 - TIDE fully operational, 2 - TIDE MCP high voltages lowered for passage through radiation belt, 3 - TIDE mirrors stepped down due to high counts, calibration applied to correct counts.
TIDE lz file used to create this CDF file
Only avaliable after 07-Dec-1996
Flux values summed or averaged over spin and polar angles. See spect_lim for sum/avg limits, see sum_avg to determine which one was used.
Available after 07-Dec-1996 only,for energy and spin angle calculation see moments_lim. Vx and Vy only.
Flux values summed or averaged over energy and polar angle. See spect_lim for sum/avg limits, see sum_avg to determine which one was used.
Avaliable after 07-Dec-1996. Direction of magnetic field obtained from onboard values.
Type of long term calibration correction applied.
Name of file containing the instrument calibration input data.
The mask file used to subtract background noise.
Name for file containing mass calibration input data.
The energy and spin and polar angle ranges used in the moments calculations
The version of the TIDE level-zero processing software used to create the CDF file.
The b-field data (mag_az and mag_el) can either be from TIDE telemetry (0) or from MFE high time resolution data (1).
The counts in the spectrograms can be summed (1), averaged (2), or the maximum (3) of the data whose ranges are specified in spect_lim.
The energy and spin and polar angle ranges used to create the spectrogram sums
References -------------------- 1. M. R. Torr, et al., A far ultraviolet imager for the International Solar-Terrestrial Physics mission, Space Sci. Rev., v71, pp329 - 383, 1995 Notes ------------------------ 1. The UVI field of view is circular with an 8 degree full width. The circular image is stored in IMAGE_DATA as a rectangular array of 228 rows and 200 columns. 2. Time information is contained in EPOCH, Time_PB5, IMG_MINUS_MSEC, and IMG_PLUS_MSEC. 3. Pointing information is given in GCI_LOOK_DIR, GEODETIC_LAT, and GEODETIC_LONG.
v1.0 Initial Prelaunch Release 10/16/95 v1.0 Interim Prelaunch Release 5/8/96 Added KPGS_VERSION 3/9/97 Changed min/max valuesfor IMAGE_DATA
The time in EPOCH and Time_PB5 refer to the center of the image in IMAGE_DATA. There is an offset of up to 8 major frames between the beginning of the image exposure and the ATC telemetry time stamp. The times shown here are corrected for this and describe the actual time of exposure.
The UVI field of view is circular with an 8 degree full width. The circular image is stored in IMAGE_DATA as a rectangular array of 228 rows and 200 columns. Consequently, the corners of each image contain non-image data. The non-active corner pixel locations are identified by a corner fill value = -128. The image is oriented such that the direction of decreasing row number points along the spacecraft spin axis. The direction of decreasing column number points to the outboard direction (relative to the spin axis). The orientation is the same for both detectors.
Reference:..Gurnett, D.A. et al, The Polar plasma wave instrument, Space Science Reviews, Vol. 71, pp. 597-622, 1995.GURNETT@IOWAVE.physics.uiowa.edu An FFT on 256 or 464 values, depending on the snapshot size, was used in calibrating the data; i.e., perform FFT, calibrate in frequency domain, perform inverse FFT to get calibrated time series. Coordinate System Used: local magnetic field-aligned, a spacecraft centered coordinate system where Z is parallel to the local B-field determined from Polar MFE, X points outward and lies in the plane defined by the Z-axis and the radial vector from the earth to the spacecraft, and Y completes a right-handed system and points eastward. The X- and Z-axes are contained in the north-south plane. The three orthogonal magnetic field components are given in units of nT/Sec rather than nT because the response of the searchcoils across the passband is not flat. In order to obtain units of nT, the data would need to be digitally filtered to the frequency of interest and then integrated over time. Integrating over the entire passband could possibly destroy the resolution of the higher frequency components since the low frequency noise, if present, will dominate. Data are bandpass filtered. The valid range of data in the frequency domain is from 0.5 to 22.5 Hz.
Created Oct 1999
When FFT is applied, Filter Rolls off at 25 kHz
When FFT is applied, Filter Rolls off at 25 kHz
When FFT is applied, Filter Rolls off at 25 kHz
When FFT is applied, Filter Rolls off at 25 kHz
When FFT is applied, Filter Rolls off at 25 kHz
When FFT is applied, Filter Rolls off at 25 kHz
Effective Bandwidth is 1.5*delta_f, where delta_f depends on the size of the FFT used to convert to the frequency domain, and delta_t.
Created Oct 1999
Applies to all 3 Magnetic Channels
Applies to all 3 Magnetic Channels
This is the number of Gain/Epoch0 Records
This is the number of Gain/Epoch0 Records
Determined by Filter Mode
Reference:..Gurnett, D.A. et al, The Polar plasma wave instrument, Space Science Reviews, Vol. 71, pp. 597-622, 1995. donald-gurnett@.uiowa.edu An FFT on 2048 values was used in calibrating the data; i.e., perform FFT, calibrate in frequency domain, perform inverse FFT to get calibrated time series. Data are lowpass filtered so that the data are valid only up to 2 kHz. The three orthogonal magnetic field components are given in units of nT/Sec rather than nT because the response of the searchcoils across the passband is not flat. In order to obtain units of nT, the data would need to be digitally filtered to the frequency of interest and then integrated over time. Integrating over the entire passband could possibly destroy the resolution of the higher frequency components since the low frequency noise, if present, will dominate. Effective Bandwidth is 1.5*delta_f, where delta_f depends on the size of the FFT used to convert to the frequency domain, and delta_t.
Created Oct 1999
Applies to all 3 Magnetic Channels
Applies to all 3 Magnetic Channels
This is the number of Gain/Epoch0 Records
Data are not continuous. 57-msec snapshotsare taken every 128.8 seconds
Reference:..Gurnett, D.A. et al, The Polar plasma wave instrument, Space Science Reviews, Vol. 71, pp. 597-622, 1995.GURNETT@IOWAVE.physics.uiowa.edu An FFT on 2048 values was used in calibrating the data; i.e., perform FFT, calibrate in frequency domain, perform inverse FFT to get calibrated time series. Data are lowpass filtered so that the data are valid only up to 16 kHz. Effective Bandwidth is 1.5*delta_f, where delta_f depends on the size of the FFT used to convert to the frequency domain, and delta_t.
Created Oct 1999
Applies to all 3 Magnetic Channels
This is the number of Gain/Epoch0 Records
There is one snapshot of data captured every 128.8 seconds. Delta_T is the time between points within one snapshot.
This data set contains 96-second averaged counting rates for H+, He++, (O+, O++ together), (O>2+), all from the MICS part of the instrument, with a +/- 1 degree field of view perpendicular to the spin axis, segmented into bins of size 1/32 of a spin. T.A. Fritz et.al, CAMMICE:The POLAR CAMMICE instruments It also contains 96-second averaged counting rates from two proton channels (0.5-1.7 MeV and 1.7-5.8 MeV), two He channels (1.4-4.3 MeV and 4.3-9.6 MeV), and six CNO channels (5-10, 6-11, 7-13, 17-92, 18-92, 21-92 MeV), from the HIT part of the instrument, with a +/- 6 degree field of view perpendicular to the spin axis, segmented into bins of 1/32 of a spin. A. Fritz et.al, CAMMICE:The POLAR CAMMICE instruments
This is the 1st version, generated on 17 November 1995.
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Data: 96 second averages J. B. Blake et.al, Comprehensive Energetic Particle & Pitch Angle Distribution
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Reference: DATA FORMAT CONTROL DOCUMENT (DFCD) BETWEEN THE INTERNATIONAL SOLAR-TERRESTRIAL PHYSICS (ISTP) PROGRAM INFORMATION PROCESSING DIVISION (IPD) GROUND DATA PROCESSING SYSTEM AND THE ISTP MISSION INVESTIGATORS SEPTEMBER 1993 Pages 3-57 through 3-60. GGS Instrument papers (DRAFT)December 1992 pages B.2.1 thru B.2.14 inclusive. The Polar Electric Field Instrument KPS will record data from two sets of Langmuir probes. The first set V12, are 130m apart, the second set V34, are 100m apart.
Avoid B algorithm was added to the ground spinfits calculations in version 4.0. Version 4.1: Update of Berkeley Modules.
ground spinfits calculations with avoid B
ground spinfits calculations with avoid B
ground spinfits calculations with avoid B
Pre-generated PWG plots
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Reference: HYDRA is a 3-Dimensional Electron and Ion Hot plasma Instrument for the Polar Spacecraft of the GGS Mission, J. Scudder et al., Space Sci. Rev., 71, 459-495, Feb. 1995. This data set contains the electron density and average energy, and the maximum and minimum Debye energies, at 1-minute resolution. J. Scudder, et.al, Space Sci. Rev., 71, 459-495, 1995, http://www-st.physics.uiowa.edu J. Scudder, et.al, Space Sci. Rev., 71, 459-495, 1995, http://www-st.physics.uiowa.edu
Created Feb. 10, 1997 3/23/97: Corrected attribute errors
1: nfit=1.0, successful patch; 2: a=intercept; 3: b=slope; 4: rchi2; 5: itop; 6: min_index; 7: max_fit_energy;
Data Quality Flag: -1 = GSFC or Berkeley SC Potential used/PSI status unknown; 0 = GSFC or Berkeley SC Potential used/PSI off; 1 = 1 Volt SC Pot. used/PSI on
Gap Flag: 0=no gap; 1=instrument mode limitations; 2=generic lz read error; 4=no EFI S/C potential available
Data Quality Flag: -1 = EFI SC Pot. used/PSI unknown; 0 = EFI SC Pot. used/PSI off; 1 = 1 Volt SC Pot. used/PSI on
Gap Flag: 0=no gap; 1=instrument mode; 2=lz data not available; 4=generic lz read error; 8=manuever mode; 16=No EFI data avail/PSI off or unknown; 32=burst mode
Data: 0.92 minute and6 second averages
version 1.0 Jan 93 Test. Modified by JT on Nov. 30, 1995Modified by XL on Feb. 18, 1997
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INSTRUMENT DESCRIPTION: The PIXIE instrument remotely images bremsstrahlung X-rays which are emitted from the earth's atmosphere. PIXIE measures the bremsstrahlung X-ray flux in two spatial dimensions and as a function of energy from 2 keV to 60 keV in 64 energy channels. The spatial resolution and sensitivity of the instrument are a function of orbital altitude. Sensitivity is optimized by the use of a variable configuration of the instrument's adjustable aperture plate. Continuous imagery will be provided, since PIXIE is mounted on the despun platform. Each X-ray photon is identified individually by the time and location at which it is detected within the focal plane. INSTRUMENT REFERENCES: 1. Instrument Description Document for the Polar Ionospheric X-ray Imaging Experiment (PIXIE) on the ISTP/GGS POLAR Satellite (submitted to Project as a PIXIE deliverable). Document number LMSC F254274 (Lockheed Space and Missiles Co.) 2. McKenzie, D. L., D. J. Gorney, and W. L. Imhof, Auroral X-ray Imaging from High- and Low-Earth Orbit, Proc. SPIE, 1745, 39, 1992. 3. McKenzie, D. L., D. J. Gorney, and W. L. Imhof, Auroral X-ray Imaging from High- and Low-Earth Orbit, Opt. Eng. (to be published in the February 1994 issue). 4. Imhof, W. L., et al., The Polar Ionospheric X-ray Imaging Experiment (PIXIE), Space Science Reviews (to be published as part of a special issue on the GGS instruments). KEY PARAMETERS DESCRIPTION: The Primary Key Parameter data consists of two 64x64 pixel X-ray image arrays and two Mean Intensity measures. The images and intensities are associated with two variable integrated energy channel ranges. The Secondary Key Parameter data contains information necessary to the appropriate interpretation of the images. This information includes geographic and geomagnetic spatial registration references, integrated energy range definitions, data quality flags, and various mode/state indicators. The spatial references include full pixel maps (providing the value of a particular coordinate, e.g., magnetic latitude, at each of the 4096 pixels) as well as simple pixel markers locating specific features (such as the geographic and geomagnetic poles).
Unified image array has been split into high & low energy image arrays. VAR_NOTES attribute entries have been included to supplement CATDESC entries where appropriate.
Represents photons detected in the energyrange specified by the second array elementof variable ENERGY_RANGE and its associated delta values
Represents photons detected in the energyrange specified by the second array elementof variable ENERGY_RANGE and its associated delta values
Represents photons detected in the energyrange specified by the second array elementof variable ENERGY_RANGE and its associated delta values
Intensity of photons detected in the energyrange specified by the first array elementof variable ENERGY_RANGE and its associated delta values
Intensity of photons detected in the energyrange specified by the first array elementof variable ENERGY_RANGE and its associated delta values
Intensity of photons detected in the energyrange specified by the first array elementof variable ENERGY_RANGE and its associated delta values
Represents photons detected in the energyrange specified by the second array elementof variable ENERGY_RANGE and its associated delta values
Represents photons detected in the energyrange specified by the second array elementof variable ENERGY_RANGE and its associated delta values
Intensity of photons detected in the energyrange specified by the first array elementof variable ENERGY_RANGE and its associateddelta values
Values are encoded with first four digitsbeing the Plate A aperture size, secondfour digits being the Plate B aperture size(in units of microns)
If no campaign in effect, value will be NONE
0=no gap, 1=instrument mode, 2=LZ missing, 3=LZ noisy, 4=telemetry mode
0=Good, 1=Questionable, 2=Poor, 99=No data
In the following, the first descriptor refers to images, the second to image registration: 0=Good/Good, 1=Questionable/Good, 2=Poor/Good, 10=Good/Questionable, 11=Questionable/Questionable, 12=Poor/Questionable, 20=Good/Poor, 21=Questionable/Poor, 22=Poor/Poor, 99=No data
0=Nominal, 1=Event count below threshold, 2=Instrument condition not nominal, 10=Secondary KPs incomplete, 99=No data
Intensity of photons detected in the energyrange specified by the first array elementof variable ENERGY_RANGE and its associated delta values
Intensity of photons detected in the energyrange specified by the first array elementof variable ENERGY_RANGE and its associated delta values
Values are encoded with first digitbeing the number of Plate A sub-images, second digit being the number ofPlate B images
Represents photons detected in the energyrange specified by the second array elementof variable ENERGY_RANGE and its associated delta values
Reference:..Gurnett, D.A. et al, The Polar plasma wave instrument, Space Science Reviews, Vol. 71, pp. 597-622, 1995.GURNETT@IOWAVE.physics.uiowa.edu Note:..The electron ion and cyclotron frequencies are derived from the following: Fce = 0.028 kHz*B, where B is the magnitude of the ambient magnetic field measured in nT. Fcp = Fce/1837 in kHz. FcO+ = Fcp/16 in kHz. All frequencies in the key parameters are converted to Hz. Since the SFR frequency steps vary with the mode, the measured SFR frequencies will be mapped to a fixed array of 160 approximately logarithmically spaced frequency values, 32 frequency values for each of the five SFR channels. In the log mode, the 64 frequency steps of the fourth and fifth frequency channels will be mapped to 32 frequency steps each, using geometric averaging. In the linear mode, the 448 linearly spaced frequency steps of the five frequency channels will be mapped to the fixed array of 160 logarithmically spaced frequency values using a windowing technique. The magnetic and electric field values corresponding to each SFR frequency step will be similarly mapped to 160-point fixed arrays corresponding to the mapped frequency array.
Created Sept 1992, modified by JT 2/15/96
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To be supplied
6/4/93 - Original Implementation 6/8/94 - CCR ISTP 1852, updated CDHF skeleton to CDF standards - JT 11/10/94 - Correct errors made in ccr 1852. ICCR 1884
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References -------------------- 1. M. R. Torr, et al., A far ultraviolet imager for the International Solar-Terrestrial Physics mission, Space Sci. Rev., v71, pp329 - 383, 1995 Notes ------------------------ 1. The UVI field of view is circular with an 8 degree full width. The circular image is stored in IMAGE_DATA as a rectangular array of 228 rows and 200 columns. 2. Time information is contained in EPOCH, Time_PB5, IMG_MINUS_MSEC, and IMG_PLUS_MSEC. 3. Pointing information is given in GCI_LOOK_DIR, GEODETIC_LAT, and GEODETIC_LONG.
v1.0 Initial Prelaunch Release 10/16/95 v1.0 Interim Prelaunch Release 5/8/96 Added KPGS_VERSION 3/9/97 Changed min/max valuesfor IMAGE_DATA
This is a virtual variable computed in read_myCDF. MLT map generated in plot_map_images.pro
This is a virtual variable computed in read_myCDF. Calling conv_map_image
This is a virtual variable computed in read_myCDF. MLT map generated in plot_map_images.pro
The UVI field of view is circular with an 8 degree full width. The circular image is stored in IMAGE_DATA as a rectangular array of 228 rows and 200 columns. Consequently, the corners of each image contain non-image data. The non-active corner pixel locations are identified by a corner fill value = -128. The image is oriented such that the direction of decreasing row number points along the spacecraft spin axis. The direction of decreasing column number points to the outboard direction (relative to the spin axis). The orientation is the same for both detectors.
This is a virtual variable computed in read_myCDF
This is a virtual variable computed in read_myCDF. Calling conv_map_image
This is a virtual variable computed in read_myCDF
This is a virtual variable computed in read_myCDF
This is a virtual variable computed in read_myCDF
(OPEN: +1, CLOSED: -1) MgF2 window in door allows viewing when closed.
QUALITY_FLAG is a bit-mapped flag in which each bit corresponds to a single quality condition. The most significant bit (minus sign) is not used. Consequently up to 31 different quality conditions can be simultaneously flagged. The flags are ordered in severity with increasing bit position. The following _hexadecimal_ values have been defined for QUALITY_FLAG: 0 = No errors or quality conditions; 1 = an error occurred writing an SFDU comment; 2 = image time was outside of selected processing window; 4 = some level zero minor frames had fill values; 8 = some level zero minor frames had sync errors; 10 = the image single frame integration period could not be determined due to bad telemetry (assumed to be 4 major frames); 20 = the despun platform was in motion or had not settled down from a motion; 40 = the pointing calculations have not been validated or may be unreliable; 80 = the time flags for this image may be unreliable; 100 = there was an error decode star mode data; 200 =some major frames were missing but an image could be partially reconstructed; 400 = calibration data is missing or otherwise invalid; 800 = a background image could not be found; 1000 = the requested output image could not be found.
0=off, 16=highest sensitivity
A gap is defined if the time between records is greater than twice the nominal output time (NOMINAL_OUTPUT_PERIOD). The following values are defined for POST_GAP_FLAG: O = No Gap; 1 = Wrong Mode; 2 = Missing Data; 3 = Noisy Data; 4-9 = undefined; 10 = High voltage not enabled; 11 = gain set to zero; 12 =The first minor frame containing UVI housekeeping was zero filled 13 = Unable to sync with telemetry stream; 14 = No background images were present; 15 = Requested filter setting was not present; 16 = Spacecraft was near perigee pass where no kp's are generated; 17 = Despun platform was pointing away from the earth; 18 = Image data lay outside requested process window (Not used for production); 19 = Unknown. Note that long gaps may be caused by multiple events. POST_GAP_FLAG attempts to represent the most severe event contributing to the gap. Also, since each image frame requires a minimum of 4 major frames (36.8 s) very short values of NOMINAL_OUTPUT_PERIOD on the order of 1 minute may always encounter a gap since the desired images may be several minutes apart. This condition is not trapped and will result in an unknown value for the post gap flag.
The UVI field of view is circular with an 8 degree full width. The circular image is stored in IMAGE_DATA as a rectangular array of 228 rows and 200 columns. Consequently, the corners of each image contain non-image data. The non-active corner pixel locations are identified by a corner fill value = -128. The image is oriented such that the direction of decreasing row number points along the spacecraft spin axis. The direction of decreasing column number points to the outboard direction (relative to the spin axis). The orientation is the same for both detectors.
The UVI field of view is circular with an 8 degree full width. The circular image is stored in IMAGE_DATA as a rectangular array of 228 rows and 200 columns. Consequently, the corners of each image contain non-image data. The non-active corner pixel locations are identified by a corner fill value = -128. The image is oriented such that the direction of decreasing row number points along the spacecraft spin axis. The direction of decreasing column number points to the outboard direction (relative to the spin axis). The orientation is the same for both detectors.
1304=2, 1356=3, LBHS=4, LBHL=5, SOLR=6
Sparse matrices (every 10 pixels) of latitude and longitude are given in GEODETIC_LAT and GEODETIC_LONG, respectively. Latitude & longitude are given in geodetic coordinates (determined from the normal to the assumed surface of the earth [assumed to be an ellipsoid of revolution]) and not in geocentric coordinates (determined relative to the center of the earth).
Sparse matrices (every 10 pixels) of latitude and longitude are given in GEODETIC_LAT and GEODETIC_LONG, respectively. Latitude & longitude are given in geodetic coordinates (determined from the normal to the assumed surface of the earth [assumed to be an ellipsoid of revolution]) and not in geocentric coordinates (determined relative to the center of the earth).
This is a virtual variable computed in read_myCDF. Calling conv_map_image w/ the component variables results in the image registered latitudes.
This is a virtual variable computed in read_myCDF. Calling conv_map_image w/ the component variables results in the image registered longitudes.
The time in EPOCH and Time_PB5 refer to the center of the image in IMAGE_DATA. There is an offset of up to 8 major frames between the beginning of the image exposure and the ATC telemetry time stamp. The times shown here are corrected for this and describe the actual time of exposure.
(1=Normal, 2=Star, 3=Idle) Normal mode produces one 200 x 228 image every 4 major frames. Star mode produces multiple miniframe images every major frame. Idle mode produces no image output.
Incremented with each update.
This is the nominal time between output records. The actual output spacing will vary depending on the nature of the observing sequences being run.
Positive in direction opposite of spacecraft rotation.
UVI has two independent systems. PRIMARY: +1, SECONDARY: -1
QUALITY_FLAG is a bit-mapped flag in which each bit corresponds to a single quality condition. The most significant bit (minus sign) is not used. Consequently up to 31 different quality conditions can be simultaneously flagged. The flags are ordered in severity with increasing bit position. The following _hexadecimal_ values have been defined for QUALITY_FLAG: 0 = No errors or quality conditions; 1 = an error occurred writing an SFDU comment; 2 = image time was outside of selected processing window; 4 = some level zero minor frames had fill values; 8 = some level zero minor frames had sync errors; 10 = the image single frame integration period could not be determined due to bad telemetry (assumed to be 4 major frames); 20 = the despun platform was in motion or had not settled down from a motion; 40 = the pointing calculations have not been validated or may be unreliable; 80 = the time flags for this image may be unreliable; 100 = there was an error decode star mode data; 200 =some major frames were missing but an image could be partially reconstructed; 400 = calibration data is missing or otherwise invalid; 800 = a background image could not be found; 1000 = the requested output image could not be found.
Calculated from S/C attitude file.
Copied from S/C orbit file.
Vector pointing to sun.
The beginning and ending time of the image is specified in msec relative to the time in EPOCH and Time_PB5 by IMG_MINUS_MSEC and IMG_PLUS_MSEC, respectively.
The beginning and ending time of the image is specified in msec relative to the time in EPOCH and Time_PB5 by IMG_MINUS_MSEC and IMG_PLUS_MSEC, respectively.
GCI_LOOK_DIR is a unit vector in GCI coordinates pointing from the spacecraft along the center of the UVI line of sight. An external utility can be used to calculate latitude and longitude for any pixel of the UVI image.The pointing utility can be found on the UVI WWW home page (URL: TBD)
Instrument functional description:
The VIS is a set of three low-light-level cameras. Two of these
cameras share primary and some secondary optics and are designed to
provide images of the nighttime auroral oval at visible wavelengths.
A third camera is used to monitor the directions of the fields-of-view
of the auroral cameras with respect to the sunlit Earth and return
global images of the auroral oval at ultraviolet wavelengths. The
VIS instrumentation produces an auroral image of 256 x 256 pixels
approximately every 24 seconds dependent on the integration time and
filter selected. The fields-of-view of the two nighttime auroral
cameras are 5.6 x 6.3 degrees and 2.8 x 3.3 degrees for the low and
medium resolution cameras, respectively. One or more Earth camera
images of 256 x 256 pixels are produced every five minutes, depending
on the commanded mode. The field-of-view of the Earth camera is
approximately 20 x 20 degrees.
Reference:
Frank, L. A., J. B. Sigwarth, J. D. Craven, J. P. Cravens, J. S. Dolan,
M. R. Dvorsky, J. D. Harvey, P. K. Hardebeck, and D. Muller,
'The Visible Imaging System (VIS) for the Polar Spacecraft',
Space Science Review, vol. 71, pp. 297-328, 1995.
[Note to first-time users: The first four variables are of primary interest.
The displayable 256 x 256 image array is in variable 3. The correct orien-
tation of a displayed image is explained in the description of variable 3
below.]
Data set description:
The VIS key parameter data set is a survey of auroral activity
provided by a series of single images showing a significant area of the
auroral zone. The displayable image counts are in variable 3.
Some coordinate information is included for viewer orientation.
Coordinates are calculated for a grid of 18 x 18 points corresponding
to one pixel out of every 15 x 15 pixel block. In addition, a rotation
matrix and a table of distortion-correcting look direction unit vectors
are provided for the purpose of calculating coordinates for every pixel.
See the description of variables 17 and 18 below.
To facilitate viewing of the images, a mapping of pixel value to a
recommended color table based on the characteristics of the selected
filter will be included with each image. See the description of variables
22, 23, and 24 below.
A relative intensity scale is provided by the uncompressed count table
of variable 27. Approximate intensity levels in kiloRayleighs are given in
the intensity table of variable 28. Information on the availability of
more precisely calibrated intensities can be found on the VIS website at
URL .http://eiger.physics.uiowa.edu/~vis/software/.
Variable descriptions:
1,2. Center time
The time assigned to an image is the center time of the integration
period within a resolution of 50 milliseconds.
3. Image counts
Image pixel counts range from 0 to 255. They are stored in a two-
dimensional 256 x 256 byte array. Images from the Earth camera
(sensor 0) are conventionally displayed with row 1 at the top, row 256
at the bottom, column 1 on the left, and column 256 on the right. The
conventional image display for the low resolution camera (sensor 1) is
rotated 180 degrees so that the row 1-column 1 pixel is at the lower
right corner and the row 256-column 256 pixel is at the upper left
corner. When displayed in this manner, the spacecraft spin axis is
oriented to the right in the display, the X component is defined as
the center of the image look direction, and the Y component is the
cross product of the spin axis and the look direction.
4. Sensor number
0 = Earth camera,
1 = low resolution camera,
2 = medium resolution camera.
5. Half integration time
This is half the length of the integration period for the image,
measured in milliseconds.
6. Filter
Twelve filters are available for visible imaging; the filter number,
1-12, is given here. Ultra-violet imaging is done with one filter only,
designated here as filter number 0. In addition, the peak wavelength
in Angstroms is given for the selected filter.
7. Presumed altitude of emissions
The presumed altitude of the emissions seen in the image varies
with the characteristics of the filter used.
8. Field stop position
The field stop may partially occlude the field of view of the low
or medium resolution cameras. The position is given in 1.5 degree
steps.
9. Platform pitch angle
This is the platform pointing angle of rotation around the spin
axis, measured from nadir.
10,11. Mirror elevation and azimuth angles
For the low or medium resolution camera, the two-axis mirror
position is given in steps measured from the instrument calibration
switches. The boresight of the instrument is located at step 68 in
azimuth and step 118 in elevation.
12,13. Geographic coordinates
Geographic north latitude and east longitude are provided for the
pixels at these image array locations: every 15th row starting
with row 1 and ending with row 256, and every 15th column starting
with column 1 and ending with column 256, for a total of
18 x 18 coordinate pairs.
14,15. Spacecraft position and velocity vectors, GCI
The spacecraft position vector and velocity vector in GCI
coordinates are for the image center time as given in variables
1 and 2.
16. Spacecraft spin axis unit vector, GCI
17,18. Image-to-GCI rotation matrix and look direction vector table
The rotation matrix may be used with the look direction vector table to
obtain pointing vectors in GCI coordinates for each pixel. The
resulting vectors may be used to calculate coordinates for the observed
positions of the pixels. Software for this purpose is available at URL
.http://eiger.physics.uiowa.edu/~vis/software/. The general method
used is described below.
In the image coordinate system, the X axis is the center line-of-sight
or look direction; the Y axis is the cross product of the spin axis an
the X axis; and the Z axis is the cross product of the X axis and the
Y axis. When the display orientation conventions in the variable 3
description are applied, the low resolution camera image is rotated so
that both Earth camera and low resolution camera images are displayed
with Y axis pointing up and Z axis pointing toward the right.
To obtain the coordinates of the observed position of a pixel,
calculate the intersection of the line-of-sight with the surface
of an oblately spheroidal Earth at the altitude given as
variable 7. The equation of the spheroid is
X**2/(A+ALT)**2 + Y**2/(A+ALT)**2 + Z**2/(B+ALT)**2 = 1
where A is the Earth radius at the equator,
B is the Earth radius at the pole, and
ALT is the given altitude.
The line-of-sight equations are
(X-SCX)/DX = (Y-SCY)/DY = (Z-SCZ)/DZ
where (SCX,SCY,SCZ) is the spacecraft position vector GCI, and
(DX,DY,DZ) is the look direction unit vector GCI.
Solve the line-of-sight equations for two variables in terms
of the third; substitute into the spheroid equation; and use the
quadratic formula to solve for the third variable. Select
the solution point closer to the spacecraft.
19. Zenith angle of center line-of-sight at presumed altitude
This is the angle between the geocentric vector through the
observed point, assuming the altitude given as variable 7,
and the reverse of the image center line-of-sight vector.
20. Sun position unit vector, GCI
21. Solar zenith angle at observed point of center line-of-sight
This is the angle of the sun from zenith at the observed point
of the center line-of-sight, assuming the altitude given as
variable 7.
22. RGB color table
This is the recommended color table to be used with the
limits given in variables 23 and 24.
23,24. Low and high color mapping limits
The low and high color limits are recommended for remapping
the color table entries, as follows:
For pixel values less than the low limit, use the color
at table position 1.
For pixel values greater than or equal to the low limit
and less than or equal to the high limit, use the color
at table position (pix-low)/(high-low) x 255 + 1.
For pixel values greater than the high limit, use the color
at table position 256.
25. Data quality flag
The data quality word has bits set to 1 when the listed
conditions are true. Bit #31 is the most significant bit in the
word, and it will not be used as a flag. These are the bit
assignments:
bit 0 - image data frame sync error
bit 1 - image data frame counters error
bit 2 - image data fill frame flag.
26. Post gap flag
The post gap flag has these possible values:
0 - no gap occurred immediately prior to this record,
1 - the gap occurred because the instrument was not in
a mode that allowed for the production of images for the
selected sensor,
2 - the gap occurred because level zero data were missing,
3 - the gap occurred because level zero data were too
noisy to extract images.
27. Expanded count table
The image pixel counts are quasi-logarithmically compressed to the
range 0-255. This table gives the average of the uncompressed range
for each compressed count value. Table entries 1-256 correspond to
compressed counts 0-255 respectively.
28. Intensity table
Approximate intensity levels in kiloRayleighs are given for each
compressed count value. Table entries 1-256 correspond to compressed
counts 0-255 respectively. Information on the availability of more
precisely calibrated intensities can be found on the VIS website at
URL .http://eiger.physics.uiowa.edu/~vis/software/.
Supporting software:
Supporting software is available on the VIS website at the URL
.http://eiger.physics.uiowa.edu/~vis/software/. Included is an IDL program
that displays the images with the recommended color bar and provides
approximate intensities and coordinate data for each pixel.
Initial development
Image_Counts contains the displayable image. The counts have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value for Image_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Approximate intensity in kR is Intens_Table(Image_Counts(i,j)+1).The appearance of the actual count value 255 is rare. When displaying an image,it works best to use the fill value as an overflow (i.e. brightest) value.
Image_Counts contains the displayable image. The counts have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value for Image_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Approximate intensity in kR is Intens_Table(Image_Counts(i,j)+1).The appearance of the actual count value 255 is rare. When displaying an image,it works best to use the fill value as an overflow (i.e. brightest) value.
Image_Counts contains the displayable image. The counts have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value for Image_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Approximate intensity in kR is Intens_Table(Image_Counts(i,j)+1).The appearance of the actual count value 255 is rare. When displaying an image,it works best to use the fill value as an overflow (i.e. brightest) value.
Image_Counts contains the displayable image. The counts have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value for Image_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Approximate intensity in kR is Intens_Table(Image_Counts(i,j)+1).The appearance of the actual count value 255 is rare. When displaying an image,it works best to use the fill value as an overflow (i.e. brightest) value.
Image_Counts contains the displayable image. The counts have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value for Image_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Approximate intensity in kR is Intens_Table(Image_Counts(i,j)+1).The appearance of the actual count value 255 is rare. When displaying an image,it works best to use the fill value as an overflow (i.e. brightest) value.
Image_Counts contains the displayable image. The counts have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value for Image_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Approximate intensity in kR is Intens_Table(Image_Counts(i,j)+1).The appearance of the actual count value 255 is rare. When displaying an image,it works best to use the fill value as an overflow (i.e. brightest) value.
Image_Counts contains the displayable image. The counts have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value for Image_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Approximate intensity in kR is Intens_Table(Image_Counts(i,j)+1).The appearance of the actual count value 255 is rare. When displaying an image,it works best to use the fill value as an overflow (i.e. brightest) value.
Image_Counts contains the displayable image. The counts have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value for Image_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Approximate intensity in kR is Intens_Table(Image_Counts(i,j)+1).The appearance of the actual count value 255 is rare. When displaying an image,it works best to use the fill value as an overflow (i.e. brightest) value.
Image_Counts contains the displayable image. The counts have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value for Image_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Approximate intensity in kR is Intens_Table(Image_Counts(i,j)+1).The appearance of the actual count value 255 is rare. When displaying an image,it works best to use the fill value as an overflow (i.e. brightest) value.
Image_Counts contains the displayable image. The counts have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value for Image_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Approximate intensity in kR is Intens_Table(Image_Counts(i,j)+1).The appearance of the actual count value 255 is rare. When displaying an image,it works best to use the fill value as an overflow (i.e. brightest) value.
Image_Counts contains the displayable image. The counts have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value for Image_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Approximate intensity in kR is Intens_Table(Image_Counts(i,j)+1).The appearance of the actual count value 255 is rare. When displaying an image,it works best to use the fill value as an overflow (i.e. brightest) value.
Image_Counts contains the displayable image. The counts have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value for Image_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Approximate intensity in kR is Intens_Table(Image_Counts(i,j)+1).The appearance of the actual count value 255 is rare. When displaying an image,it works best to use the fill value as an overflow (i.e. brightest) value.
Approximate intensity in kR for Image_Counts(i,j) isIntens_Table(Image_Counts(i,j)+1)
MSB will not be used as a flag; see TEXT for other bit assignments
Image_Counts contains pixel counts which have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value forImage_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1).
A field stop may occultsome part of a visible image
Filters #1-12 are visible wavelengths; filter #0 is UV for Earth camera images
Geographic N. latitude for pixels at every 15th row and column from 1 to 256
Geographic N. latitude for pixels vals - computed by CDAWeb
Geographic E. longitude for pixels at every 15th row and column from 1 to 256
Geographic E. longitude for pixels vals - computed by CDAWeb
X component is look direction,Y component is the spin axis cross X
Mirror pointing angle of rotation around spin axis, w/r/t platform position, in steps of ~.09375 degrees.
Mirror pointing angle out of s/c X-Y plane in steps of ~.08660 degrees
Platform angle of rotation around spin axis, measured from nadir in tenths of degrees
RGBColorTable should be remapped for displaying an image using the low and high limits given for each image in Limit_Lo and Limit_Hi.Image_Counts count values less than Limit_Lo use the color at table position 1. Count values greater than Limit_Hi use the color at table position 256. For count values greater than or equal to Limit_Lo and less than or equal to Limit_Hi, the table position is (Count-Limit_Lo)/(Limit_Hi-Limit_Lo) x 255 + 1.At the selected table position C, the color components are Red at RGBColorTable(1,C), Green at RGBColorTable(2,C), and Blue at RGBColorTable(3,C).
Image_Counts contains the displayable image. The counts have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value for Image_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Approximate intensity in kR is Intens_Table(Image_Counts(i,j)+1).The appearance of the actual count value 255 is rare. When displaying an image,it works best to use the fill value as an overflow (i.e. brightest) value.
Image_Counts contains the displayable image. The counts have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value for Image_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Approximate intensity in kR is Intens_Table(Image_Counts(i,j)+1).The appearance of the actual count value 255 is rare. When displaying an image,it works best to use the fill value as an overflow (i.e. brightest) value.
H+, O+, He+ and He++ number fluxes for survey purposes only E.G. Shelley et al., The Toroidal Imaging Mass-Angle Spectrograph (TIMAS) for the Polar Mission, Sp. Sci. Rev, Vol 71, pp 497-530, 1995. ftp://sierra.spasci.com/DATA/timas/TIMAS_description.html Metadata provided by W.K. Peterson
Version 0 June, 2001
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Instrument functional description:
The VIS is a set of three low-light-level cameras. Two of these
cameras share primary and some secondary optics and are designed to
provide images of the nighttime auroral oval at visible wavelengths.
A third camera is used to monitor the directions of the fields-of-view
of the auroral cameras with respect to the sunlit Earth and return
global images of the auroral oval at ultraviolet wavelengths. The
VIS instrumentation produces an auroral image of 256 x 256 pixels
approximately every 24 seconds dependent on the integration time and
filter selected. The fields-of-view of the two nighttime auroral
cameras are 5.6 x 6.3 degrees and 2.8 x 3.3 degrees for the low and
medium resolution cameras, respectively. One or more Earth camera
images of 256 x 256 pixels are produced every five minutes, depending
on the commanded mode. The field-of-view of the Earth camera is
approximately 20 x 20 degrees.
Reference:
Frank, L. A., J. B. Sigwarth, J. D. Craven, J. P. Cravens, J. S. Dolan,
M. R. Dvorsky, J. D. Harvey, P. K. Hardebeck, and D. Muller,
'The Visible Imaging System (VIS) for the Polar Spacecraft',
Space Science Review, vol. 71, pp. 297-328, 1995.
[Note to first-time users: The first four variables are of primary interest.
The displayable 256 x 256 image array is in variable 3. The correct orien-
tation of a displayed image is explained in the description of variable 3
below.]
Data set description:
The VIS Earth camera key parameter data set is a survey of global
auroral activity providedby a series of piled images produced by the median-
filtering of up to five consecutive images. The displayable image counts
are in variable 3.
Some coordinate information is included for viewer orientation.
Coordinates are calculated for a grid of 18 x 18 points corresponding
to one pixel out of every 15 x 15 pixel block. In addition, a rotation
matrix and a table of distortion-correcting look direction unit vectors
are provided for the purpose of calculating coordinates for every pixel.
See the description of variables 14 and 15 below.
To facilitate viewing of the images, a mapping of pixel value to a
recommended color table based on the characteristics of the selected
filter will be included with each image. See the description of variables
19, 20, and 21 below.
A relative intensity scale is provided by the uncompressed count table
of variable 24. Approximate intensity levels in kiloRayleighs are given in
the intensity table of variable 25. Information on the availability of
more precisely calibrated intensities can be found on the VIS website at
URL .http://eiger.physics.uiowa.edu/~vis/software/.
Variable descriptions:
1,2. Center time
The time assigned to an image is the center time of the integration
period within a resolution of 50 milliseconds.
3. Image counts
Image pixel counts range from 0 to 255. They are stored in a two-
dimensional 256 x 256 byte array. Images from the Earth camera
(sensor 0) are conventionally displayed with row 1 at the top, row 256
at the bottom, column 1 on the left, and column 256 on the right. The
conventional image display for the low resolution camera (sensor 1) is
rotated 180 degrees so that the row 1-column 1 pixel is at the lower
right corner and the row 256-column 256 pixel is at the upper left
corner. When displayed in this manner, the spacecraft spin axis is
oriented to the right in the display, the X component is defined as
the center of the image look direction, and the Y component is the
cross product of the spin axis and the look direction.
4. Sensor number
0 = Earth camera,
1 = low resolution camera,
2 = medium resolution camera.
5. Half integration time
This is half the length of the integration period for the image,
measured in milliseconds.
6. Filter
Twelve filters are available for visible imaging; the filter number,
1-12, is given here. Ultra-violet imaging is done with one filter only,
designated here as filter number 0. In addition, the peak wavelength
in Angstroms is given for the selected filter.
7. Presumed altitude of emissions
The presumed altitude of the emissions seen in the image varies
with the characteristics of the filter used.
8. Platform pitch angle
This is the platform pointing angle of rotation around the spin
axis, measured from nadir.
9,10. Geographic coordinates
Geographic north latitude and east longitude are provided for the
pixels at these image array locations: every 15th row starting
with row 1 and ending with row 256, and every 15th column starting
with column 1 and ending with column 256, for a total of
18 x 18 coordinate pairs.
11,12. Spacecraft position and velocity vectors, GCI
The spacecraft position vector and velocity vector in GCI
coordinates are for the image center time as given in variables
1 and 2.
13. Spacecraft spin axis unit vector, GCI
14,15. Image-to-GCI rotation matrix and look direction vector table
The rotation matrix may be used with the look direction vector table to
obtain pointing vectors in GCI coordinates for each pixel. The
resulting vectors may be used to calculate coordinates for the observed
positions of the pixels. Software for this purpose is available at URL
.http://eiger.physics.uiowa.edu/~vis/software/. The general method
used is described below.
In the image coordinate system, the X axis is the center line-of-sight
or look direction; the Y axis is the cross product of the spin axis an
the X axis; and the Z axis is the cross product of the X axis and the
Y axis. When the display orientation conventions in the variable 3
description are applied, the low resolution camera image is rotated so
that both Earth camera and low resolution camera images are displayed
with Y axis pointing up and Z axis pointing toward the right.
To obtain the coordinates of the observed position of a pixel,
calculate the intersection of the line-of-sight with the surface
of an oblately spheroidal Earth at the altitude given as
variable 7. The equation of the spheroid is
X**2/(A+ALT)**2 + Y**2/(A+ALT)**2 + Z**2/(B+ALT)**2 = 1
where A is the Earth radius at the equator,
B is the Earth radius at the pole, and
ALT is the given altitude.
The line-of-sight equations are
(X-SCX)/DX = (Y-SCY)/DY = (Z-SCZ)/DZ
where (SCX,SCY,SCZ) is the spacecraft position vector GCI, and
(DX,DY,DZ) is the look direction unit vector GCI.
Solve the line-of-sight equations for two variables in terms
of the third; substitute into the spheroid equation; and use the
quadratic formula to solve for the third variable. Select
the solution point closer to the spacecraft.
16. Zenith angle of center line-of-sight at presumed altitude
This is the angle between the geocentric vector through the
observed point, assuming the altitude given as variable 7,
and the reverse of the image center line-of-sight vector.
17. Sun position unit vector, GCI
18. Solar zenith angle at observed point of center line-of-sight
This is the angle of the sun from zenith at the observed point
of the center line-of-sight, assuming the altitude given as
variable 7.
19. RGB color table
This is the recommended color table to be used with the
limits given in variables 20 and 21.
20,21. Low and high color mapping limits
The low and high color limits are recommended for remapping
the color table entries, as follows:
For pixel values less than the low limit, use the color
at table position 1.
For pixel values greater than or equal to the low limit
and less than or equal to the high limit, use the color
at table position (pix-low)/(high-low) x 255 + 1.
For pixel values greater than the high limit, use the color
at table position 256.
22. Data quality flag
The data quality word has bits set to 1 when the listed
conditions are true. Bit #31 is the most significant bit in the
word, and it will not be used as a flag. These are the bit
assignments:
bit 0 - image data frame sync error
bit 1 - image data frame counters error
bit 2 - image data fill frame flag.
23. Post gap flag
The post gap flag has these possible values:
0 - no gap occurred immediately prior to this record,
1 - the gap occurred because the instrument was not in
a mode that allowed for the production of images for the
selected sensor,
2 - the gap occurred because level zero data were missing,
3 - the gap occurred because level zero data were too
noisy to extract images.
24. Expanded count table
The image pixel counts are quasi-logarithmically compressed to the
range 0-255. This table gives the average of the uncompressed range
for each compressed count value. Table entries 1-256 correspond to
compressed counts 0-255 respectively.
25. Intensity table
Approximate intensity levels in kiloRayleighs are given for each
compressed count value. Table entries 1-256 correspond to compressed
counts 0-255 respectively. Information on the availability of more
precisely calibrated intensities can be found on the VIS website at
URL .http://eiger.physics.uiowa.edu/~vis/software/.
Supporting software:
Supporting software is available on the VIS website at the URL
.http://eiger.physics.uiowa.edu/~vis/software/. Included is an IDL program
that displays the images with the recommended color bar and provides
approximate intensities and coordinate data for each pixel.
Initial development modified linear validmin 0=>15, linear validmax 255=>50 to suppress dayglow for UVI testing - 4/12/01 - REM modified log validmax 255=>15 to suppress dayglow - 4/12/01 - REM
Image_Counts contains the displayable image. The counts have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value for Image_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Approximate intensity in kR is Intens_Table(Image_Counts(i,j)+1).The appearance of the actual count value 255 is rare. When displaying an image,it works best to use the fill value as an overflow (i.e. brightest) value.
Image_Counts contains the displayable image. The counts have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value for Image_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Approximate intensity in kR is Intens_Table(Image_Counts(i,j)+1).The appearance of the actual count value 255 is rare. When displaying an image,it works best to use the fill value as an overflow (i.e. brightest) value.
Image_Counts contains the displayable image. The counts have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value for Image_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Approximate intensity in kR is Intens_Table(Image_Counts(i,j)+1).The appearance of the actual count value 255 is rare. When displaying an image,it works best to use the fill value as an overflow (i.e. brightest) value.
Image_Counts contains the displayable image. The counts have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value for Image_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Approximate intensity in kR is Intens_Table(Image_Counts(i,j)+1).The appearance of the actual count value 255 is rare. When displaying an image,it works best to use the fill value as an overflow (i.e. brightest) value.
Image_Counts contains the displayable image. The counts have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value for Image_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Approximate intensity in kR is Intens_Table(Image_Counts(i,j)+1).The appearance of the actual count value 255 is rare. When displaying an image,it works best to use the fill value as an overflow (i.e. brightest) value.
Image_Counts contains the displayable image. The counts have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value for Image_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Approximate intensity in kR is Intens_Table(Image_Counts(i,j)+1).The appearance of the actual count value 255 is rare. When displaying an image,it works best to use the fill value as an overflow (i.e. brightest) value.
Image_Counts contains the displayable image. The counts have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value for Image_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Approximate intensity in kR is Intens_Table(Image_Counts(i,j)+1).The appearance of the actual count value 255 is rare. When displaying an image,it works best to use the fill value as an overflow (i.e. brightest) value.
Image_Counts contains the displayable image. The counts have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value for Image_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Approximate intensity in kR is Intens_Table(Image_Counts(i,j)+1).The appearance of the actual count value 255 is rare. When displaying an image,it works best to use the fill value as an overflow (i.e. brightest) value.
Image_Counts contains the displayable image. The counts have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value for Image_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Approximate intensity in kR is Intens_Table(Image_Counts(i,j)+1).The appearance of the actual count value 255 is rare. When displaying an image,it works best to use the fill value as an overflow (i.e. brightest) value.
Image_Counts contains the displayable image. The counts have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value for Image_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Approximate intensity in kR is Intens_Table(Image_Counts(i,j)+1).The appearance of the actual count value 255 is rare. When displaying an image,it works best to use the fill value as an overflow (i.e. brightest) value.
Image_Counts contains the displayable image. The counts have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value for Image_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Approximate intensity in kR is Intens_Table(Image_Counts(i,j)+1).The appearance of the actual count value 255 is rare. When displaying an image,it works best to use the fill value as an overflow (i.e. brightest) value.
Approximate intensity in kR for Image_Counts(i,j) isIntens_Table(Image_Counts(i,j)+1)
MSB will not be used as a flag; see TEXT for other bit assignments
Image_Counts contains the displayable image. The counts have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value for Image_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Approximate intensity in kR is Intens_Table(Image_Counts(i,j)+1).The appearance of the actual count value 255 is rare. When displaying an image,it works best to use the fill value as an overflow (i.e. brightest) value.
Image_Counts contains the displayable image. The counts have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value for Image_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1). Approximate intensity in kR is Intens_Table(Image_Counts(i,j)+1).The appearance of the actual count value 255 is rare. When displaying an image,it works best to use the fill value as an overflow (i.e. brightest) value.
Image_Counts contains pixel counts which have been quasi-logarithmically compressed by the instrument. Approximate uncompressed value forImage_Counts(i,j) is ExpandedCount(Image_Counts(i,j)+1).
Filters #1-12 are visible wavelengths; filter #0 is UV for Earth camera images
Geographic N. latitude for pixels at every 15th row and column from 1 to 256
Geographic N. latitude for pixels vals - computed by CDAWeb
Geographic E. longitude for pixels at every 15th row and column from 1 to 256
Geographic E. longitude for pixels vals - computed by CDAWeb
Sequence number of image in pile of up to five images
X component is look direction,Y component is the spin axis cross X
Platform angle of rotation around spin axis, measured from nadir in tenths of degrees
RGBColorTable should be remapped for displaying an image using the low and high limits given for each image in Limit_Lo and Limit_Hi.Image_Counts count values less than Limit_Lo use the color at table position 1. Count values greater than Limit_Hi use the color at table position 256. For count values greater than or equal to Limit_Lo and less than or equal to Limit_Hi, the table position is (Count-Limit_Lo)/(Limit_Hi-Limit_Lo) x 255 + 1.At the selected table position C, the color components are Red at RGBColorTable(1,C), Green at RGBColorTable(2,C), and Blue at RGBColorTable(3,C).
Primary UVI team data products CDAWeb displayed images have time-tags shifted 51 seconds back from nominal Epoch This corrects that H2 Epochs are telemetry times, not centered collection time 51 seconds is an approximate, typical correction. Exact values depend on modes and transition status.
Initial work at SPDF 3/20-x/xx/2001 by REM This dataset was renamed from po_h2_uvi and po_l1_uvi to po_level1_uvi on 5/6/2005 in CDAWeb
1,2,3
1,2
1, 2, 4
0=OK 1=Suspect
1,2
1, 2, 4, 5, 6
0=PRIMARY, 1=SECONDARY
TBS
Originated Monday, May 13, 1991 Modified June 13, 1991 for version 2.1 Modified October 2,1991 for new global attributes, incr sizes Modified 11/11/91 Add sun vector, replace space id with support id Modified 1992 Feb 11 to use the variable name TIME and type CDF_INT4 instead of EPOCH and CDF_EPOCH for the time tags CCR 490 Modified 6/2/92 add project, discipline, source_name, data_version, title, and mods to global section; add validmin, validmax, labl_ptr_1 and monoton attributes to some variables; put epoch time back in, rename time to time_pb5; add label_time to variables Modified 11/07/92 to use Epoch and Time_PB5 variable name Modified 6/2/93 add ADID_ref and Logical_file_id 7/5/94 - CCR ISTP 1852 updated CDHF skeleton to CDF standards - JT 9/21/94 - Added 24 new global attributes to log the ephemeris comparison summary report from the definitive FDF orbit file. CCR 1932 11/7/94 - Merged CCR 1852 changes and corrected errors made in CCR 1852. ICCR 1884 12/7/94 - Modified MODS to follow ISTP standards. ICCR 1885 01/05/95 - add heliocentric coordinate system. CCR 1889 2/28/95 - added COMMENT1 and COMMENT2 for CCR 11/03/95 - deleted crn_space for CCR 2154 - RM
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TBS
Originated Monday, May 13, 1991 Modified June 13, 1991 for version 2.1 Modified October 2,1991 for new global attributes, incr sizes Modified 11/11/91 Add sun vector, replace space id with support id Modified 1992 Feb 11 to use the variable name TIME and type CDF_INT4 instead of EPOCH and CDF_EPOCH for the time tags CCR 490 Modified 6/2/92 add project, discipline, source_name, data_version, title, and mods to global section; add validmin, validmax, labl_ptr_1 and monoton attributes to some variables; put epoch time back in, rename time to time_pb5; add label_time to variables Modified 11/07/92 to use Epoch and Time_PB5 variable name Modified 6/2/93 add ADID_ref and Logical_file_id 7/5/94 - CCR ISTP 1852 updated CDHF skeleton to CDF standards - JT 9/21/94 - Added 24 new global attributes to log the ephemeris comparison summary report from the definitive FDF orbit file. CCR 1932 11/7/94 - Merged CCR 1852 changes and corrected errors made in CCR 1852. ICCR 1884 12/7/94 - Modified MODS to follow ISTP standards. ICCR 1885 01/05/95 - add heliocentric coordinate system. CCR 1889 2/28/95 - added COMMENT1 and COMMENT2 for CCR 11/03/95 - deleted crn_space for CCR 2154 - RM
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Based on the FDF DPA algorithm
6/11/93 - Original Implementation 4/1/94 - Modified VALIDMIN and VALIDMAX for ORB_ROLL, ORB_YAW, GCI_ROLL, GCI_YAW, GSE_ROLL, GSE_YAW, GSM_ROLL, and GSM_YAW 6/7/94 - CCR ISTP 1852, updated CDHF skeleton to CDF standards - JT 11/9/94 - Correct errors made in ccr 1852. ICCR 1884 04/04/96 - Added despun plat.offset and lock status
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Pioneer Venus COHOweb connection
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Ionospheric parameters derived from quarter-hourly ionograms Ref: Grubb,RN The NOAA SEL HF Radar system (ionospheric sounder) NOAA Tech Memo ERL SEL-55, Space Environ Lab, Boulder, CO, 1979 Ref: Jarvis,MJ & Dudeney ,JR Reduction of ambiguities in HF radar results through a revised receiving array & sounding pattern. Radio Sci 21, 151-158, 1986 Ref: Satellite Experiments Simultaneous with Antarctic Measurements (SESAME), in GGS Instrument Papers, submitted to Space Science Reviews Info:Keith Morrison,GGS Scientist,British Antarctic Survey,Cambridge,CB3 0ET,UK E-mail: 19989::MORRISON QUALITY_FLAG Comprised of several additive values each with a specific meaning:- 0 okay,+1 <6 echoes used for fmin,+2 <6 echoes for fEmax,+4 <6 echoes for fFmax, +8 fmin approx= min tx frequency,+16 fEmax approx= max tx frequency, +32 fFmax approx= max tx frequency (tx=transmitter) eg 37 indicates <6 echoes used for fmin & fFmax, & fFmax approx= max tx freq
This is first operational version
(-88.88=Insuff. echoes,-99.99=no echoes present)
Virtual height approx<200km. -88.88=Insufficient echoes,-99.99=no echoes present
Virtual height approx>200km. -88.88=Insufficient echoes,-99.99=no echoes present
Measurements made looking in South and East directions (positive) Ref1: Satellite Experiments Simultaneous with Antarctic Measurements (SESAME), in GGS Instrument Papers, submitted to Space Science Reviews. Ref2: Nature,317,p45 1985. Ref3: R.D.Stewart, PhD Thesis, Univ of Ulster, 1986 Info:Keith Morrison,GGS Scientist,British Antarctic Survey,Cambridge,CB3 0ET,UK E-mail: 19989::MORRISON
29-Oct-92 Changes in accordance with new Standards & Conventions document
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H, D and Z components of the earth's magnetic field Measuring variation of field relative to arbitrary baseline. Accurate to 1nT 1 minute data representing 'spot' values of the 1Hz sampling Ref: Satellite Experiments Simultaneous with Antarctic Measurements (SESAME), in GGS Instrument Papers, submitted to Space Science Reviews Info:Keith Morrison,GGS Scientist,British Antarctic Survey,Cambridge,CB3 0ET,UK E-mail: 19989::MORRISON
H=Horizontal (+)North (-)South, D=Horizontal (+)East (-)West, Z=Vertical (+)Down
H=Horizontal (+)North (-)South, D=Horizontal (+)East (-)West, Z=Vertical (+)Down
Equivalent overhead absorption measured 45 degrees to vertical in N,S,E,W directions, but in an L-shell-aligned coordinate system (ie rotated 17 degrees anti-clockwise from geographic). Preliminary Quiet-Day Curve used. 1 minute data represent 'spot' values of the 1Hz sampling Accurate to 0.05dB, but possible baseline uncertainties of +/-0.5dB Ref1: The multiple riometer system at Halley, Antarctica, in British Antarctic Survey Bulletin, no 72, p13-23, 1986 Ref2: Satellite Experiments Simultaneous with Antarctic Measurements (SESAME), in GGS Instrument Papers, submitted to Space Science Reviews Info:Keith Morrison,GGS Scientist,British Antarctic Survey,Cambridge,CB3 0ET,UK E-mail: 19989::MORRISON
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Omni-directional intensities in 2 narrow passband filters centred on 1kHz & 3kHz Ref1: Satellite Experiments Simultaneous with Antarctic Measurements (SESAME), in GGS Instrument Papers submitted to Space Science Reviews. Ref2: VERSIM Newsletter No.4, p7 1992. Info:Keith Morrison,GGS Scientist,British Antarctic Survey,Cambridge,CB3 0ET,UK E-mail: 19989::MORRISON
05-Aug-92 Changed fill values to +10.0E+30 and -2147483648 08-Oct-92 Changed DATA ENCODING to NETWORK. Added Quality and Post Gap Flags Plotting range changed to 10-80 27-Oct-92 Put in Logical_file_id, ADID_ref, DEPEND_i, VAR_TYPE
0dB is 10-33(Teslas)^2 / (Hertz)
0dB is 10-33(Teslas)^2 / (Hertz)
Barth, C. A. and S. M. Bailey, Comparison of a thermospheric photochemical model with SNOE observations of nitric oxide, J. Geophys. Res., doi:10.1029/2003JA010227, 2004.
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Barth, C. A. and S. M. Bailey, Comparison of a thermospheric photochemical model with SNOE observations of nitric oxide, J. Geophys. Res., doi:10.1029/2003JA010227, 2004.
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Data: 10 minute intervals
5/6/94 - Original Implementation 1/25/96 - Added SARVariables for CCR 2189
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Data entry every 5 minutes A description of the CELIAS instrument and scientific scope can be found on WWW athttp://ubeclu.unibe.ch/phim/ms/soho/or on the SOHO homepage http://sohowww.nascom.nasa.gov/ A written description of CELIAS will appear in the special issue of Solar Physics dedicated to SOHO
created Dec 1993 Modified by JT on 9/21/94 Modified by PW on 2/Mar/95 Modified by PW on 21/Jul/95 Modified by PW on 18/Aug/95
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Data: 5 minute averages Time tag = center of interval References 1.Kunow, H., et al., COSTEP - Comprehensive Suprathermal and Energetic Particle Analyser for SOHO, in V. Domingo, editor, The SOHO Mission - Scientific and Technical Aspects of the Instruments, ESA SP-1104, pages 75 - 80, 1988 2.Kunow, H., et al., COSTEP - Comprehensive Suprathermal and Energetic Particle Analyser for SOHO - Scientific Goals and Data Description, Proc. First SOHO Workshop, ESA SP-348, pages 43 - 46, 1992 2.Mueller-Mellin, R., et al., COSTEP - Comprehensive Suprathermal and Energetic Particle Analyser, to be published in Solar Physics, 1995 19 Dec 1996 Caveat: 1. The EPHIN E-detector developed gradually a noise problem during 1996 and was switched off logically on 1996-305-14.40. Check EPHIN status word >Ephin_Stat< bit 2 (2^2): if set to one: E detector is on, if set to zero, E detector is off. When off, the channels E3000, P41 and H41 show zero intensity, the energy of the next lower channel E1300 is the average of E1300 and E3000, the width of channel E1300 is the sum of the width E1300 and E3000; P25, and H25 are changed accordingly. Note: the KPGS calulates correctly the new fluxes in channels E1300, P25, H25. Only their interpretation needs to be changed by the user. 2. The geometric factor for the counting rate channels can be changed either by ground command or autonomously by detecting high fluxes in the center segment of detector A. Check EPHIN status word >Ephin_Stat<bits 9,10,11,12,13,17,18,19,20,21: if set to one: large geometric factor, if set to zero: small geometric factor. Note: the KPGS software calculates correctly the fluxes. No action needed by the user.
15 Feb 1994 Version 1.0
22 Nov 1994 Version 1.0 Revision 1.0 new variables
COVER, DQF, STATUS
28 Mar 1995 Version 1.0 Revision 2.0 Energy ranges
updated
15 May 1995 Version 1.0 Revision 3.0 Addition:
TEXT Correction: E_Energy [4] P_Energy [2]
P_Label
28 Nov 1995 Version 1.0. Revision 4.0 Correction: #
Var. from 24 to 25 Change: Descript. COST -> CST Var_type data -
support_data at: Epoch, PB5 at: E_energy, E_delta
at: P_energy, P_delta at: He_energy, He_delta at:
E_energy, E_delta
19 Dec 1996 Version 7.0. EPHIN E, P and He channel values adapted to new
investigations to geometry factors
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Data: 1 minute avarages Time tag = center of interval Torsti et al.: ERNE - Energetic and Relativistic Nuclei and Electron experiment, The SOHO Mission ESA SP-1104, 1988 Torsti et al.: Energetic Particle Experiment ERNEto be published in SolarPhysics, 1995 M. Lumme and Eino Valtonen: CEPAC Experiment Operations Manual, November 1994 ERNE WWW Home page http://helium.srl.utu.fi/erne.html
Version 01 19-Nov-1995. Modified by JT on Dec. 4, 1995
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TBS
Originated Monday, May 13, 1991 Modified June 13, 1991 for version 2.1 Modified October 2,1991 for new global attributes, incr sizes Modified 11/11/91 Add sun vector, replace space id with support id Modified 1992 Feb 11 to use the variable name TIME and type CDF_INT4 instead of EPOCH and CDF_EPOCH for the time tags CCR 490 Modified 6/2/92 add project, discipline, source_name, data_version, title, and mods to global section; add validmin, validmax, labl_ptr_1 and monoton attributes to some variables; put epoch time back in, rename time to time_pb5; add label_time to variables Modified 11/07/92 to use Epoch and Time_PB5 variable name Modified 6/2/93 add ADID_ref and Logical_file_id 7/5/94 - CCR ISTP 1852 updated CDHF skeleton to CDF standards - JT 9/21/94 - Added 24 new global attributes to log the ephemeris comparison summary report from the definitive FDF orbit file. CCR 1932 11/7/94 - Merged CCR 1852 changes and corrected errors made in CCR 1852. ICCR 1884 12/7/94 - Modified MODS to follow ISTP standards. ICCR 1885 01/05/95 - add heliocentric coordinate system. CCR 1889 2/28/95 - added COMMENT1 and COMMENT2 for CCR 11/03/95 - deleted crn_space for CCR 2154 - RM
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TBS
Originated Monday, May 13, 1991 Modified June 13, 1991 for version 2.1 Modified October 2,1991 for new global attributes, incr sizes Modified 11/11/91 Add sun vector, replace space id with support id Modified 1992 Feb 11 to use the variable name TIME and type CDF_INT4 instead of EPOCH and CDF_EPOCH for the time tags CCR 490 Modified 6/2/92 add project, discipline, source_name, data_version, title, and mods to global section; add validmin, validmax, labl_ptr_1 and monoton attributes to some variables; put epoch time back in, rename time to time_pb5; add label_time to variables Modified 11/07/92 to use Epoch and Time_PB5 variable name Modified 6/2/93 add ADID_ref and Logical_file_id 7/5/94 - CCR ISTP 1852 updated CDHF skeleton to CDF standards - JT 9/21/94 - Added 24 new global attributes to log the ephemeris comparison summary report from the definitive FDF orbit file. CCR 1932 11/7/94 - Merged CCR 1852 changes and corrected errors made in CCR 1852. ICCR 1884 12/7/94 - Modified MODS to follow ISTP standards. ICCR 1885 01/05/95 - add heliocentric coordinate system. CCR 1889 2/28/95 - added COMMENT1 and COMMENT2 for CCR 11/03/95 - deleted crn_space for CCR 2154 - RM
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No TEXT global attribute value.
For each of 4 flagss, 0=good data.But F1=1: Mast off; F2=1: calibrationtime; F3=1: abnormal time; F4=1 somenoisy data. If F1 or F2 or F3 is 1,data is a fill value.
For each of the 4 flags, 0=good dataBut F1=1: PET off; F2=1: calibrationtime; F3=1: abnormal time; F4=1: somenoisy data. When F1 or F2 or F3 is 1,data is a fill value.
For each of 6 flags, 0 means gooddata. But F1=1: LICA off; F2=1: calibrationtime; F3=1: excessive HV;F4=1: some noisy-SSD data; F5=1:some noisy-MCP data; F6=1: some abnormality.When F1 or F2 or F3 or F6 is 1, data is a fill value.
For each of 7 flags, 0=good data.But, F1=1: HILT off; F2=1: calibrationtime; F3=1: some noisy 4-9 MeV/n data;F4=1: some noisy 9-38 MeV/n data;F5=1: some noisy 8-42 MeV/n data;F6=1: some noisy 41-220 MeV/n data;F7=1: abnormal time. When F1 or F2or F7 is 1, data is fill value.
0=sunpoint; 1=mag_cal; 2=orb_rotation 3=coast
pet_elo(1.5-6 MeV);pet_ehi(2.5-14 MeV)
M_ = MAST; P_ = PET: M_m12(5-12 MeV/nu);P_plo(19-27 MeV/nu).Fluxes are mainly H+.
L_ = LICA; H_ = HILT; M_ = MAST. L_lopri(0.5-6.6 MeV/nu);H_he1(4-9 MeV/nu);M_z2(8-15 MeV/nu);H_he2(9-38 MeV/nu)
Data from lica_ssd channel
pet_elo_sigma (1.5-6 MeV);pet_ehi_sigma (2.5-14 MeV)
M_ =MAST; P_ =PET: M_m12_sigma(5-12);P_plo_sigma(19-27). All in MeV.
L_ = LICA; H_ = HILT; M_ = MAST. All in MeV/nu. L_lopri_sigma(0.5-6.6MeV/nu);H_he1_sigma(4-9);M_z2_sigma(8-15);H_hz2_sigma
Sigma from LICA_ssd_sigma
L_ = LICA; H_ = HILT; M_ = MAST. All in meV/nu. L_hipri_sigma(0.49-8.3MeV/nu);_H_hz1_sigma(8.2-42);M_hizr1_sigma(19.3-22.8;_hizr 2_sigma(22.8-31.0);_hizr3_sigma(31.0-51.7);_hizr4_sigma(51.7-76.2);_hizr5_sigma( 76.2-113);_hizr6_sigma(113-156);H_hz2_sigma(42-220)
L_ = LICA; H_ = HILT; M_ = MAST. L_hipri(0.49-8.3 MeV/nu);_H_hz1(8.2-42 Mev/nu);M_hizr1(19.3-22.8 MeV/nu;_hizr2(22.8-31.0 MeV/nu);_hizr3(31.0-51.7);_hizr4(51.7-76.2 MeV/nu;_hizr5(76.2-113 MeV/nu);_hizr6(113-156 MeV/nu);H_hz2(42-220 MeV/nu)
No TEXT global attribute value.
MAST flags: If '0' data is perfect But '1' is advisory to look into 30-sfluxes. PARTIAL '1' signifies thatsome 30-s fluxes were omitted;BAD '1' signifies bad or no data withentries being fill values. ADC_SATsignifies that count data mayhave had saturated values. 'Saturation' only means that the count rate inany or all channels exceeded thecalibration count rate of 10,000/s
If flag is '0' data is perfect; if '1' it is advisable to look into the30-s fluxes: PARTIAL '1' signifiesthat some 30-s data were omitted;BAD '1' signifies bad/absent data,with fill value as the entry;P1HI_SAT '1' signifies that somesaturated values. 'Saturation' simplymeans that the count rates exceededthe calibration counts of 10,000/s.
For all flags 0 means perfect data.But 1 is an advisory to look intothe 30-s flux data: PARTIAL '1' means some 30-s data were eliminated;BAD '1' means bad or no data and entryis a fill value; SSD_SAT '1' means that a small amount of saturatedSSD data is admitted; MCP_SAT '1' signifies that a small amount of saturated MCP data is admitted.So called 'Saturation' simply meansthat the count rates in the SolidState Detectors or the Micro ChannelPlates exceeded the calibrating ratesof 10,000 counts/s during any 30-s.
If entry is '0', data is perfect. But '1' is advisory to look into 30-sflux data: PARTIAL '1' signifies thatsome 30-s values were ignored; BAD '1' signifies bad/no data and entry is afill value. All flags with SAT in namesignifies that some saturated 30-s fluxes were admitted in the correspondingenergy channel. So called 'saturation' merely connotes that the count rate inthat energy channel had exceeded thecalibration rate of 10,000/s
pet_elo(1.5-6 MeV);pet_ehi(2.5-14 MeV)
M_ = MAST; P_ = PET: M_m12(5-12 MeV/nu);P_plo(19-27 MeV/nu)
L_ = LICA; H_ = HILT; M_ = MAST. L_lopri(0.5-6.6 MeV/nu);H_he1(4-9 MeV/nu);M_z2(8-15 MeV/nu);H_he2(9-38 MeV/nu)
Data from lica_ssd channel
This is the time the s/c enteredpolarcap at 70 deg inva-lat; the datais averaged over the next few minutes i.e, until the exit time. Occasionally,the trajectory may miss the polarcap.
pet_elo_sigma (1.5-6 MeV);pet_ehi_sigma (2.5-14 MeV)
M_ =mast; P_ =pet: M_m12_sigma(5-12);P_plo_sigma(19-27). All in MeV.
L_ = LICA; H_ = HILT; M_ = MAST. All in MeV/nu. L_lopri_sigma(0.5-6.6MeV/nu);H_he1_sigma(4-9);M_z2_sigma(8-5);H_hz2_sigma(41-110
Sigma from LICA_ssd_sigma
L_ = LICA; H_ = HILT; M_ = MAST. All in meV/nu. L_hipri_sigma(0.49-8.3MeV/nu);_H_hz1_sigma(8.2-42);M_hizr1_sigma(19.3-22.8;_hizr 2_sigma(22.8-31.0);_hizr3_sigma(31.0-51.7);_hizr4_sigma(51.7-76.2);_hizr5_sigma( 76.2-113);_hizr6_sigma(113-156);H_hz2_sigma(42-220)
L_ = LICA; H_ = HILT; M_ = MAST. L_hipri(0.49-8.3 MeV/nu);_H_hz1(8.2-42 Mev/nu);M_hizr1(19.3-22.8 MeV/nu;_hizr2(22.8-31.0 MeV/nu);_hizr3(31.0-51.7);_hizr4(51.7-76.2 MeV/nu;_hizr5(76.2-113 MeV/nu);_hizr6(113-156 MeV/nu);H_hz2(42-220 MeV/nu)
GROUP 1 Satellite Resolution Factor
themis a 60 1
Start Time Stop Time
2006 292 10:00 2008 254 23:59
Coord/ Min/Max Range Filter Filter
Component Output Markers Minimum Maximum Mins/Maxes
GSE X YES - - - - -
-
GSE Y YES - - - - -
-
GSE Z YES - - - - -
-
GSE Lat YES - - - - -
-
GSE Lon YES - - - - -
-
Addtnl Min/Max Range Filter Filter
Options Output Markers Minimum Maximum Mins/Maxes
dEarth YES - - - -
Formats and units:
Day/Time format: YYYY DDD HH:MM
Degrees/Hemisphere format: Decimal degrees with 2 place(s).
Longitude -180 to 180, latitude -90 to 90.
Distance format: Kilometers with 2 place(s).
Originated Feb. 16, 2006
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GROUP 1 Satellite Resolution Factor
themis b 60 1
Coord/ Min/Max Range Filter Filter
Component Output Markers Minimum Maximum Mins/Maxes
GSE X YES - - - - -
-
GSE Y YES - - - - -
-
GSE Z YES - - - - -
-
GSE Lat YES - - - - -
-
GSE Lon YES - - - - -
-
Addtnl Min/Max Range Filter Filter
Options Output Markers Minimum Maximum Mins/Maxes
dEarth YES - - - -
Formats and units:
Day/Time format: YYYY DDD HH:MM
Degrees/Hemisphere format: Decimal degrees with 2 place(s).
Longitude -180 to 180, latitude -90 to 90.
Distance format: Kilometers with 2 place(s).
Originated Feb. 16, 2006
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GROUP 1 Satellite Resolution Factor
themis c 60 1
Start Time Stop Time
2006 292 10:00 2008 254 23:59
Coord/ Min/Max Range Filter Filter
Component Output Markers Minimum Maximum Mins/Maxes
GSE X YES - - - - -
-
GSE Y YES - - - - -
-
GSE Z YES - - - - -
-
GSE Lat YES - - - - -
-
GSE Lon YES - - - - -
-
Addtnl Min/Max Range Filter Filter
Options Output Markers Minimum Maximum Mins/Maxes
dEarth YES - - - -
Formats and units:
Day/Time format: YYYY DDD HH:MM
Degrees/Hemisphere format: Decimal degrees with 2 place(s).
Longitude -180 to 180, latitude -90 to 90.
Distance format: Kilometers with 2 place(s).
Originated Feb. 16, 2006
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GROUP 1 Satellite Resolution Factor
themis d 60 1
Start Time Stop Time
2006 292 10:00 2008 254 23:59
Coord/ Min/Max Range Filter Filter
Component Output Markers Minimum Maximum Mins/Maxes
GSE X YES - - - - -
-
GSE Y YES - - - - -
-
GSE Z YES - - - - -
-
GSE Lat YES - - - - -
-
GSE Lon YES - - - - -
-
Addtnl Min/Max Range Filter Filter
Options Output Markers Minimum Maximum Mins/Maxes
dEarth YES - - - -
Formats and units:
Day/Time format: YYYY DDD HH:MM
Degrees/Hemisphere format: Decimal degrees with 2 place(s).
Longitude -180 to 180, latitude -90 to 90.
Distance format: Kilometers with 2 place(s).
Originated Feb. 16, 2006
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GROUP 1 Satellite Resolution Factor
themis e 60 1
Start Time Stop Time
2006 292 10:00 2008 254 23:59
Coord/ Min/Max Range Filter Filter
Component Output Markers Minimum Maximum Mins/Maxes
GSE X YES - - - - -
-
GSE Y YES - - - - -
-
GSE Z YES - - - - -
-
GSE Lat YES - - - - -
-
GSE Lon YES - - - - -
-
Addtnl Min/Max Range Filter Filter
Options Output Markers Minimum Maximum Mins/Maxes
dEarth YES - - - -
Formats and units:
Day/Time format: YYYY DDD HH:MM
Degrees/Hemisphere format: Decimal degrees with 2 place(s).
Longitude -180 to 180, latitude -90 to 90.
Distance format: Kilometers with 2 place(s).
Originated Feb. 16, 2006
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Geomagnetic Event Observation Network by Students (GEONS), part of the THEMIS EPO Effort.
Rev- 2006-08-16
EPOCH of 01-Jan-1970 00:00:00
Unleaped seconds
Geomagnetic Event Observation Network by Students (GEONS), part of the THEMIS EPO Effort.
Rev- 2006-08-16
EPOCH of 01-Jan-1970 00:00:00
Unleaped seconds
THEMIS Ground Based Observatory part of the THEMIS GBO effort
Rev- 2006-08-16
EPOCH of 01-Jan-1970 00:00:00
Unleaped seconds
Geomagnetic Event Observation Network by Students (GEONS), part of the THEMIS EPO Effort.
Rev- 2006-08-16
EPOCH of 01-Jan-1970 00:00:00
Unleaped seconds
THEMIS Ground Based Observatory part of the THEMIS GBO effort
Rev- 2006-08-16
EPOCH of 01-Jan-1970 00:00:00
Unleaped seconds
THEMIS Ground Based Observatory part of the THEMIS GBO effort
Rev- 2006-08-16
EPOCH of 01-Jan-1970 00:00:00
Unleaped seconds
THEMIS Ground Based Observatory part of the THEMIS GBO effort
Rev- 2006-08-16
EPOCH of 01-Jan-1970 00:00:00
Unleaped seconds
THEMIS Ground Based Observatory part of the THEMIS GBO effort
Rev- 2006-08-16
EPOCH of 01-Jan-1970 00:00:00
Unleaped seconds
Geomagnetic Event Observation Network by Students (GEONS), part of the THEMIS EPO Effort.
Rev- 2006-08-16
EPOCH of 01-Jan-1970 00:00:00
Unleaped seconds
THEMIS Ground Based Observatory part of the THEMIS GBO effort
Rev- 2006-08-16
EPOCH of 01-Jan-1970 00:00:00
Unleaped seconds
THEMIS Ground Based Observatory part of the THEMIS GBO effort
Rev- 2006-08-16
EPOCH of 01-Jan-1970 00:00:00
Unleaped seconds
THEMIS Ground Based Observatory part of the THEMIS GBO effort
Rev- 2006-08-16
EPOCH of 01-Jan-1970 00:00:00
Unleaped seconds
Geomagnetic Event Observation Network by Students (GEONS), part of the THEMIS EPO Effort.
Rev- 2006-08-16
EPOCH of 01-Jan-1970 00:00:00
Unleaped seconds
THEMIS Ground Based Observatory part of the THEMIS GBO effort
Rev- 2006-08-16
EPOCH of 01-Jan-1970 00:00:00
Unleaped seconds
THEMIS Ground Based Observatory part of the THEMIS GBO effort
Rev- 2006-08-16
EPOCH of 01-Jan-1970 00:00:00
Unleaped seconds
THEMIS Ground Based Observatory part of the THEMIS GBO effort
Rev- 2006-08-16
EPOCH of 01-Jan-1970 00:00:00
Unleaped seconds
Geomagnetic Event Observation Network by Students (GEONS), part of the THEMIS EPO Effort.
Rev- 2006-08-16
EPOCH of 01-Jan-1970 00:00:00
Unleaped seconds
THEMIS Ground Based Observatory part of the THEMIS GBO effort
Rev- 2006-08-16
EPOCH of 01-Jan-1970 00:00:00
Unleaped seconds
THEMIS Ground Based Observatory part of the THEMIS GBO effort
Rev- 2006-08-16
EPOCH of 01-Jan-1970 00:00:00
Unleaped seconds
THEMIS Ground Based Observatory part of the THEMIS GBO effort
Rev- 2006-08-16
EPOCH of 01-Jan-1970 00:00:00
Unleaped seconds
Geomagnetic Event Observation Network by Students (GEONS), part of the THEMIS EPO Effort.
Rev- 2006-08-16
EPOCH of 01-Jan-1970 00:00:00
Unleaped seconds
Geomagnetic Event Observation Network by Students (GEONS), part of the THEMIS EPO Effort.
Rev- 2006-08-16
EPOCH of 01-Jan-1970 00:00:00
Unleaped seconds
THEMIS Ground Based Observatory part of the THEMIS GBO effort
Rev- 2006-08-16
EPOCH of 01-Jan-1970 00:00:00
Unleaped seconds
Geomagnetic Event Observation Network by Students (GEONS), part of the THEMIS EPO Effort.
Rev- 2006-08-16
EPOCH of 01-Jan-1970 00:00:00
Unleaped seconds
Geomagnetic Event Observation Network by Students (GEONS), part of the THEMIS EPO Effort.
Rev- 2006-08-16
EPOCH of 01-Jan-1970 00:00:00
Unleaped seconds
THEMIS Ground Based Observatory part of the THEMIS GBO effort
Rev- 2006-08-16
EPOCH of 01-Jan-1970 00:00:00
Unleaped seconds
Geomagnetic Event Observation Network by Students (GEONS), part of the THEMIS EPO Effort.
Rev- 2006-08-16
EPOCH of 01-Jan-1970 00:00:00
Unleaped seconds
THEMIS Ground Based Observatory part of the THEMIS GBO effort
Rev- 2006-08-16
EPOCH of 01-Jan-1970 00:00:00
Unleaped seconds
No TEXT global attribute value.
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No TEXT global attribute value.
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GUVI measures FUV airglow in five spectral bands: HI(121.6nm), OI(130.4nm), OI(135.6nm), LBHS(141-152.8nm), and LBHL(167.2-181.2nm). The cross-track scanning spectrograph images a ground swath of 3000 km width providing a nearly contiguous global coverage duringone day (15 orbits). The L1CDisk (Level 1C disk, V03) data provide the calibrated, geolocated, and rectified intensities for the 5 wavelengths bands. DISPLAY OPTIONS: (1) Mapped images of the (lin or log) intensities by orbit using a transverse Mercator projection. (2) Mapped images of the (lin or log) intensities using a polar projection of the North and South pole areas. Generating thumbnails for (1) or (2) for one day takes about 1 minute. (3) Movies of plot types (1),(2): There are 15 orbits/frames per day, max is 2 days, i.e. 30 frames. (4) Images of intensitiesas scanned along the orbit. (5) Line plots of intensities at selected across-track positions. CDAWeb TUTORIAL: A tutorial on how to use CDAWeb to quickly generate GUVI plots can be found at http://cdaweb.gsfc.nasa.gov/cdaweb/cdaweb_guvi_tutorial.pdf DATA DESCRIPTION: Details about the data format and processing can be found at http://guvi.jhuapl.edu/data/understanding.shtml
15 orbits/frames per day; max allowedis 3 days (45-frame movie)
GUVI measures FUV airglow in five spectral bands: HI(121.6nm), OI(130.4nm), OI(135.6nm), LBHS(141-152.8nm), and LBHL(167.2-181.2nm). The cross-track scanning spectrograph images a ground swath of 3000 km width providing a nearly contiguous global coverage duringone day (15 orbits). This L1CDisk (Level 1C disk, V03) file provides the calibrated, geolocated, and rectified intensities for the 1st H Ly-alpha (1216 A) wavelength band. This is a movie with mapped images of the log intensities by orbit using a Transverse Mercator projection.
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GUVI measures FUV airglow in five spectral bands: HI(121.6nm), OI(130.4nm), OI(135.6nm), LBHS(141-152.8nm), and LBHL(167.2-181.2nm). The cross-track scanning spectrograph images a ground swath of 3000 km width providing a nearly contiguous global coverage duringone day (15 orbits). This L1CDisk (Level 1C disk, V03) file provides the calibrated, geolocated, and rectified intensities for the 1st H Ly-alpha (1216 A) wavelength band. This is a movie with mapped images of the log intensities by orbit using a North Polar projection.
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GUVI measures FUV airglow in five spectral bands: HI(121.6nm), OI(130.4nm), OI(135.6nm), LBHS(141-152.8nm), and LBHL(167.2-181.2nm). The cross-track scanning spectrograph images a ground swath of 3000 km width providing a nearly contiguous global coverage duringone day (15 orbits). This L1CDisk (Level 1C disk, V03) file provides the calibrated, geolocated, and rectified intensities for the 1st H Ly-alpha (1216 A) wavelength band. This is a movie with mapped images of the log intensities by orbit using a South Polar projection.
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GUVI measures FUV airglow in five spectral bands: HI(121.6nm), OI(130.4nm), OI(135.6nm), LBHS(141-152.8nm), and LBHL(167.2-181.2nm). The cross-track scanning spectrograph images a ground swath of 3000 km width providing a nearly contiguous global coverage duringone day (15 orbits). This L1CDisk (Level 1C disk, V03) file provides the calibrated, geolocated, and rectified intensities for the 2nd (1304 A) wavelength band. This is a movie with mapped images of the log intensities by orbit using a Transverse Mercator projection.
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GUVI measures FUV airglow in five spectral bands: HI(121.6nm), OI(130.4nm), OI(135.6nm), LBHS(141-152.8nm), and LBHL(167.2-181.2nm). The cross-track scanning spectrograph images a ground swath of 3000 km width providing a nearly contiguous global coverage duringone day (15 orbits). This L1CDisk (Level 1C disk, V03) file provides the calibrated, geolocated, and rectified intensities for the 2nd (1304 A) wavelength band. This is a movie with mapped images of the log intensities by orbit using a North Polar projection.
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GUVI measures FUV airglow in five spectral bands: HI(121.6nm), OI(130.4nm), OI(135.6nm), LBHS(141-152.8nm), and LBHL(167.2-181.2nm). The cross-track scanning spectrograph images a ground swath of 3000 km width providing a nearly contiguous global coverage duringone day (15 orbits). This L1CDisk (Level 1C disk, V03) file provides the calibrated, geolocated, and rectified intensities for the 2nd (1304 A) wavelength band. This is a movie with mapped images of the log intensities by orbit using a South Polar projection.
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GUVI measures FUV airglow in five spectral bands: HI(121.6nm), OI(130.4nm), OI(135.6nm), LBHS(141-152.8nm), and LBHL(167.2-181.2nm). The cross-track scanning spectrograph images a ground swath of 3000 km width providing a nearly contiguous global coverage duringone day (15 orbits). This L1CDisk (Level 1C disk, V03) file provides the calibrated, geolocated, and rectified intensities for the 3rd (1356 A) wavelength band. This is a movie with mapped images of the log intensities by orbit using a Transverse Mercator projection.
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GUVI measures FUV airglow in five spectral bands: HI(121.6nm), OI(130.4nm), OI(135.6nm), LBHS(141-152.8nm), and LBHL(167.2-181.2nm). The cross-track scanning spectrograph images a ground swath of 3000 km width providing a nearly contiguous global coverage duringone day (15 orbits). This L1CDisk (Level 1C disk, V03) file provides the calibrated, geolocated, and rectified intensities for the 3rd (1356 A) wavelength band. This is a movie with mapped images of the log intensities by orbit using a North Polar projection.
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GUVI measures FUV airglow in five spectral bands: HI(121.6nm), OI(130.4nm), OI(135.6nm), LBHS(141-152.8nm), and LBHL(167.2-181.2nm). The cross-track scanning spectrograph images a ground swath of 3000 km width providing a nearly contiguous global coverage duringone day (15 orbits). This L1CDisk (Level 1C disk, V03) file provides the calibrated, geolocated, and rectified intensities for the 3rd (1356 A) wavelength band. This is a movie with mapped images of the log intensities by orbit using a South Polar projection.
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GUVI measures FUV airglow in five spectral bands: HI(121.6nm), OI(130.4nm), OI(135.6nm), LBHS(141-152.8nm), and LBHL(167.2-181.2nm). The cross-track scanning spectrograph images a ground swath of 3000 km width providing a nearly contiguous global coverage duringone day (15 orbits). This L1CDisk (Level 1C disk, V03) file provides the calibrated, geolocated, and rectified intensities for the 4th LBH1 (1400-1500 A) wavelength band. This is a movie with mapped images of the log intensities by orbit using a Transverse Mercator projection.
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GUVI measures FUV airglow in five spectral bands: HI(121.6nm), OI(130.4nm), OI(135.6nm), LBHS(141-152.8nm), and LBHL(167.2-181.2nm). The cross-track scanning spectrograph images a ground swath of 3000 km width providing a nearly contiguous global coverage duringone day (15 orbits). This L1CDisk (Level 1C disk, V03) file provides the calibrated, geolocated, and rectified intensities for the 4th LBH1 (1400-1500 A) wavelength band. This is a movie with mapped images of the log intensities by orbit using a North Polar projection.
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GUVI measures FUV airglow in five spectral bands: HI(121.6nm), OI(130.4nm), OI(135.6nm), LBHS(141-152.8nm), and LBHL(167.2-181.2nm). The cross-track scanning spectrograph images a ground swath of 3000 km width providing a nearly contiguous global coverage duringone day (15 orbits). This L1CDisk (Level 1C disk, V03) file provides the calibrated, geolocated, and rectified intensities for the 4th LBH1 (1400-1500 A) wavelength band. This is a movie with mapped images of the log intensities by orbit using a South Polar projection.
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GUVI measures FUV airglow in five spectral bands: HI(121.6nm), OI(130.4nm), OI(135.6nm), LBHS(141-152.8nm), and LBHL(167.2-181.2nm). The cross-track scanning spectrograph images a ground swath of 3000 km width providing a nearly contiguous global coverage duringone day (15 orbits). This L1CDisk (Level 1C disk, V03) file provides the calibrated, geolocated, and rectified intensities for the 5th LBH2 (1650-1800 A) wavelength band. This is a movie with mapped images of the log intensities by orbit using a Transverse Mercator projection.
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GUVI measures FUV airglow in five spectral bands: HI(121.6nm), OI(130.4nm), OI(135.6nm), LBHS(141-152.8nm), and LBHL(167.2-181.2nm). The cross-track scanning spectrograph images a ground swath of 3000 km width providing a nearly contiguous global coverage duringone day (15 orbits). This L1CDisk (Level 1C disk, V03) file provides the calibrated, geolocated, and rectified intensities for the 5th LBH2 (1650-1800 A) wavelength band. This is a movie with mapped images of the log intensities by orbit using a North Polar projection.
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GUVI measures FUV airglow in five spectral bands: HI(121.6nm), OI(130.4nm), OI(135.6nm), LBHS(141-152.8nm), and LBHL(167.2-181.2nm). The cross-track scanning spectrograph images a ground swath of 3000 km width providing a nearly contiguous global coverage duringone day (15 orbits). This L1CDisk (Level 1C disk, V03) file provides the calibrated, geolocated, and rectified intensities for the 5th LBH2 (1650-1800 A) wavelength band. This is a movie with mapped images of the log intensities by orbit using a South Polar projection.
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No TEXT global attribute value.
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No TEXT global attribute value.
Merged Solar irradiance for XPS and EGS flux at 1nm bins with gaps filled using Woods-Rottman 2002 VUV model. Below 26 nm, flux is result of solution of linear equations involving XPS diodes and scaled to the VUV model. EGS data is used above 26 nm except 114.5-120.5 and 122.5-128.5 nm where the VUV model is scaled to the EGS Lyman-alpha line.
Merged Solar irradiance for XPS and EGS flux at 1nm bins with gaps filled using Woods-Rottman 2002 VUV model. Below 26 nm, flux is result of solution of linear equations involving XPS diodes and scaled to the VUV model. EGS data is used above 26 nm except 114.5-120.5 and 122.5-128.5 nm where the VUV model is scaled to the EGS Lyman-alpha line.
No TEXT global attribute value.
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This data set contains 1 minute data of the magnetic field components (RTN) and field magnitude from the Vector Helium Magnetometer. Units are nT. Data Set Contact: Joyce Wolf, NASA JPL Principal Investigator: A Balogh, The Blackett Laboratory, Imperial College, London, UK. Reference: Astron. Astrophys. Suppl. Ser., 92(2), 221-236 (1992). Relevant Web Sites: http://www.sp.ph.ic.ac.uk/Ulysses/
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This data set contains 1 second data of the magnetic field components (RTN) and field magnitude from the Vector Helium Magnetometer. Units are nT. Data Set Contact: Joyce Wolf, NASA JPL Principal Investigator: A Balogh, The Blackett Laboratory, Imperial College, London, UK. Reference: Astron. Astrophys. Suppl. Ser., 92(2), 221-236 (1992). Relevant Web Sites: http://www.sp.ph.ic.ac.uk/Ulysses/
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The Ulysses/SWICS instrument is a mass spectrometer combining an electrostatic analyzer with post acceleration, followed by a time-of-flight and energy measurement. The instrument covers an energy per charge range from 0.16 to 59.6 keV/e with a time resolution of about 13 minutes. SWICS is designed to determine uniquely the elemental and ionic-charge composition, the temperatures and mean speeds of all major solar wind ions, from H through Fe. For more information see G. Gloeckler, J. Geiss et al., Astron. Astrophys. Suppl. Ser. 92, 267-289, 1992. This archive consists of all 18 Matrix Rates (MR) as a function of energy per charge (E/q) and of time. Each MR represents a specific element in one or several ionization states, but it may also contain significant contributions from neighbouring elements due to spillover. The MRs are given in units of count rates only. The accompanying SAPRO (SWICS Archive Processor) software can be used both to convert the MR count rates to physical units (differential flux, phase space density), to correct for spillover between different MRs, and to obtain kinetic parameters (density, speed, thermal speed) of selected ions (to be used with caution).
1999-01-12: Initial CDF data file creation
Deflection voltage cycle non nominal flag bitmask: no bit set = all nominal, bit 0 set = DPU error - no sun puls, bit 1 set = DPU error - sun puls not within sun pulse sector, bit 2 set = DPU error - MCD address wrong, bit 3 set = DPU error - no spin rate, bit 4 set = DPU error - no bubble sync. word, bit 5 set = DPU error - no bubble HK identifier, bit 6 set = DPU error - interrupt error 2, bit 7 set = DPU error - interrupt error 1, bit 8 set = DPU error - formating error, bit 9 set = DPU error - PHA error, bit 10 set = DPU error - mode status error, bit 11 set = non nominal matrix rate value (i.e. matrix rate overflow), bit 12 set = non nominal DV mode (i.e. DV mode != 1), bit 13 set = non nominal PAPS value (i.e. PAPS value != 22.6), bit 14 set = non nominal MCP bias power supply level (i.e. MCP level != 3), bit 15 set = non nominal emergency mode (i.e. emergency mode enabled), bit 16 set = non nominal DPU mode (i.e. DPU mode != 0), bit 17 set = non nominal TAC gain adjustment (i.e. TAC gain != 0%), bit 18 set = non nominal DV stepping (i.e. step reversal), bit 19 set = non nominal aspect angle (i.e. not within range: ]0.0 .. 50.0[), bit 20 set = non nominal ADC trigger type (i.e. trigger type != T), bit 21-31 = reserved (not set)
Instrument Step duration is 12 seconds, with few exceptions.
Spacecraft Event Time (SCET) measured in sec. since 1-Jan-1950.
Instrument period duration is 12 seconds, with few exceptions.
Instrument status flag bitmask: bit 0-13: reserved (not set), bit 14-15 (2 bit): telemetry mode, bit 16-19 (4 bit): TAC gain adjustment, bit 20 (1 bit): data compression code, bit 21-22 (2 bit): emergency mode, bit 23-26 (4 bit): MCP bias power supply level, bit 27-29 (3 bit): DV mode, bit 30-31 (2 bit): DPU mode
Post gap flag: 0 = no gap immediately prior to this record, 1 = prior gap due to inappropriate instrument mode, 2 = prior gap due to missing level zero data, 3 = prior gap due to noisy level zero data, 10-255 = reserved
This data set contains 10 minute averages of the proton and Z>=1 flux data from the Ulysses Cosmic Ray and Solar Particle Investigation Anisotropy Telescope 1. Flux units are /cm2/s/sr/Mev. Data Set Contact: S Dalla, Space & Atmospheric Physics Group, Imperial College, London, UK. Principal Investigator: R B McKibben, Laboratory for Astrophysics and Space Research, Enrico Fermi Institute, University of Chicago, USA. Reference: Astron. Astrophys. Suppl. Ser., 92(2), 365-399 (1992). Relevant web sites: ftp://odysseus.uchicago.edu/WWW/Simpson/Ulysses.html http://www.sp.ph.ic.ac.uk/Ulysses/
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This data set contains 10 minute averages of the proton and Z>=1 flux data from the Ulysses Cosmic Ray and Solar Particle Investigation Anisotropy Telescope 2. Flux units are /cm2/s/sr/Mev. Data Set Contact: S Dalla, Space & Atmospheric Physics Group, Imperial College, London, UK. Principal Investigator: R B McKibben, Laboratory for Astrophysics and Space Research, Enrico Fermi Institute, University of Chicago, USA. Reference: Astron. Astrophys. Suppl. Ser., 92(2), 365-399 (1992). Relevant web sites: ftp://odysseus.uchicago.edu/WWW/Simpson/Ulysses.html http://www.sp.ph.ic.ac.uk/Ulysses/
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This data set contains 3 to 22 minute averages of the electron density and temperature data from the Ulysses Solar Wind Observations Over the Poles of the Sun instrument. Density units are /cm3, temperature units are K. Data Set Contact: B E Goldstein, NASA Ames Research Center, USA. Principal Investigator: D J McComas, Southwest Research Institute, USA. Reference: Astron. Astrophys. Suppl. Ser., 92(2), 237-265 (1992). Relevant Web Sites: http://sst.lanl.gov/nis-projects/swoops/
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This data set contains 4 to 8 minute averages of the ion density, temperature and velocity data from the Ulysses Solar Wind Observations Over the Poles of the Sun instrument. Density units are /cm3, temperature units are K, velocity units are km/s. Data Set Contact: B E Goldstein, NASA Ames Research Center, USA. Principal Investigator: D J McComas, Southwest Research Institute, USA. Reference: Astron. Astrophys. Suppl. Ser., 92(2), 237-265 (1992). Relevant Web Sites: http://sst.lanl.gov/nis-projects/swoops/
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This data set contains 10 minute averages of the proton, electron, and Z>=3 count rate data from the Ulysses Cosmic Ray and Solar Particle Investigation High Energy Telescope. Count rate units are /s. Data Set Contact: R B McKibben, Laboratory for Astrophysics and Space Research, Enrico Fermi Institute, University of Chicago, USA. Principal Investigator: R B McKibben, Laboratory for Astrophysics and Space Research, Enrico Fermi Institute, University of Chicago, USA. Reference: Astron. Astrophys. Suppl. Ser., 92(2), 365-399 (1992). Relevant Web Sites: ftp://odysseus.uchicago.edu/WWW/Simpson/Ulysses.html ftp://odysseus.uchicago.edu/WWW/Simpson/UlyDocs/HET.html
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This data set contains 10 minute averages of the ion flux data from the Ulysses Cosmic Ray and Solar Particle Investigation High Flux Telescope. Flux units are /cm2/s/sr. Data Set Contact: J D Anglin, Herzberg Institute for Astrophysics, National Research Council of Canada, Ottawa, Canada. Principal Investigator: R B McKibben, Laboratory for Astrophysics and Space Research, Enrico Fermi Institute, University of Chicago, USA. Reference: Astron. Astrophys. Suppl. Ser., 92(2), 365-399 (1992). Relevant Web Sites: ftp://odysseus.uchicago.edu/WWW/Simpson/Ulysses.html For a fuller description of the data channels and their energy levels see the format file at file://helio.estec.esa.nl/ulysses/cospin/hft/doc/ and Anglin et al., J. Geophys. Res., 102, 1 (1997).
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This data set contains 10 minute averages of the proton, helium, and electron count rate data from the Ulysses Cosmic Ray and Solar Particle Kiel Electron Telescope. Count rate units are /s. Data Set Contact: B Heber, CEA, DSM, Service d'Astrophysique, Centre d'Etudes de Saclay, 91191 Gif sur Yvette, Cedex, France. Principal Investigator: R B McKibben, Laboratory for Astrophysics and Space Research, Enrico Fermi Institute, University of Chicago, USA. Reference: Astron. Astrophys. Suppl. Ser., 92(2), 365-399 (1992). Relevant Web Sites: ftp://odysseus.uchicago.edu/WWW/Simpson/Ulysses.html http://www.ifctr.mi.cnr.it/Ulysses/
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This data set contains 10 minute averages of the ion and electron flux data from the Ulysses Cosmic Ray and Solar Particle Investigation Low Energy Telescope. Flux units are /cm2/s/sr/Mev. Data Set Contact: T R Sanderson, Solar System Division, ESA/ESTEC. Principal Investigator: R B McKibben, Laboratory for Astrophysics and Space Research, Enrico Fermi Institute, University of Chicago, USA. Reference: Astron. Astrophys. Suppl. Ser., 92(2), 365-399 (1992). Relevant Web Sites: ftp://odysseus.uchicago.edu/WWW/Simpson/Ulysses.html http://helio.estec.esa.nl/ssd/let.html
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This data set contains 10 minute averages of the average electric field intensities from the Unified Radio and Plasma Wave Instrument Plasma Frequency Receiver. Units are microVolt/Hz**0.5. Data Set Contact: R Hess, NASA Goddard Spaceflight Center, Greenbelt, Maryland, USA. Principal Investigator: R J Macdowall, NASA Goddard Spaceflight Center, Greenbelt, Maryland, USA. Reference: Astron. Astrophys. Suppl. Ser., 92(2), 291-316 (1992). Relevant Web Sites: http://urap.gsfc.nasa.gov/www/home.html
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This data set contains 10 minute averages of the peak electric field intensities from the Unified Radio and Plasma Wave Instrument Plasma Frequency Receiver. Units are microVolt/Hz**0.5. Data Set Contact: R Hess, NASA Goddard Spaceflight Center, Greenbelt, Maryland, USA. Principal Investigator: R J Macdowall, NASA Goddard Spaceflight Center, Greenbelt, Maryland, USA. Reference: Astron. Astrophys. Suppl. Ser., 92(2), 291-316 (1992). Relevant Web Sites: http://urap.gsfc.nasa.gov/www/home.html
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This data set contains 144 second averages of the electric field intensities from the Unified Radio and Plasma Wave Instrument Radio Astronomy Receiver. Units are microVolt/Hz**0.5. Data Set Contact: R Hess, NASA Goddard Spaceflight Center, Greenbelt, Maryland, USA. Principal Investigator: R J Macdowall, NASA Goddard Spaceflight Center, Greenbelt, Maryland, USA. Reference: Astron. Astrophys. Suppl. Ser., 92(2), 291-316 (1992). Relevant Web Sites: http://urap.gsfc.nasa.gov/www/home.html
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This data set contains 10 minute averages of the average electric field intensities from the Unified Radio and Plasma Wave Instrument Radio Astronomy Receiver. Units are microVolt/Hz**0.5. Data Set Contact: R Hess, NASA Goddard Spaceflight Center, Greenbelt, Maryland, USA. Principal Investigator: R J Macdowall, NASA Goddard Spaceflight Center, Greenbelt, Maryland, USA. Reference: Astron. Astrophys. Suppl. Ser., 92(2), 291-316 (1992). Relevant Web Sites: http://urap.gsfc.nasa.gov/www/home.html
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This data set contains 10 minute averages of the peak electric field intensities from the Unified Radio and Plasma Wave Instrument Radio Astronomy Receiver. Units are microVolt/Hz**0.5. Data Set Contact: R Hess, NASA Goddard Spaceflight Center, Greenbelt, Maryland, USA. Principal Investigator: R J Macdowall, NASA Goddard Spaceflight Center, Greenbelt, Maryland, USA. Reference: Astron. Astrophys. Suppl. Ser., 92(2), 291-316 (1992). Relevant Web Sites: http://urap.gsfc.nasa.gov/www/home.html
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This data set contains 10 minute averages of the averaged magnetic field intensities from the Unified Radio and Plasma Wave Instrument Waveform Analyzer Units are 1.0e-15Tesla/Hz**0.5. Data Set Contact: R Hess, NASA Goddard Spaceflight Center, Greenbelt, Maryland, USA. Principal Investigator: R J Macdowall, NASA Goddard Spaceflight Center, Greenbelt, Maryland, USA. Reference: Astron. Astrophys. Suppl. Ser., 92(2), 291-316 (1992). Relevant Web Sites: http://urap.gsfc.nasa.gov/www/home.html
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This data set contains 10 minute averages of the peak magnetic field intensities from the Unified Radio and Plasma Wave Instrument Waveform Analyzer Units are 1.0e-15Tesla/Hz**0.5. Data Set Contact: R Hess, NASA Goddard Spaceflight Center, Greenbelt, Maryland, USA. Principal Investigator: R J Macdowall, NASA Goddard Spaceflight Center, Greenbelt, Maryland, USA. Reference: Astron. Astrophys. Suppl. Ser., 92(2), 291-316 (1992). Relevant Web Sites: http://urap.gsfc.nasa.gov/www/home.html
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This data set contains 10 minute averages of the averaged electric field intensities from the Unified Radio and Plasma Wave Instrument Waveform Analyzer Units are microVolt/Hz**0.5. Data Set Contact: R Hess, NASA Goddard Spaceflight Center, Greenbelt, Maryland, USA. Principal Investigator: R J Macdowall, NASA Goddard Spaceflight Center, Greenbelt, Maryland, USA. Reference: Astron. Astrophys. Suppl. Ser., 92(2), 291-316 (1992). Relevant Web Sites: http://urap.gsfc.nasa.gov/www/home.html
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This data set contains 10 minute averages of the peak electric field intensities from the Unified Radio and Plasma Wave Instrument Waveform Analyzer Units are microVolt/Hz**0.5. Data Set Contact: R Hess, NASA Goddard Spaceflight Center, Greenbelt, Maryland, USA. Principal Investigator: R J Macdowall, NASA Goddard Spaceflight Center, Greenbelt, Maryland, USA. Reference: Astron. Astrophys. Suppl. Ser., 92(2), 291-316 (1992). Relevant Web Sites: http://urap.gsfc.nasa.gov/www/home.html
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This data set contains 1 hour averages of the ion density, temperature and velocity data from the Ulysses Solar Wind Observations Over the Poles of the Sun instrument. Density units are /cm3, temperature units are K, velocity units are km/s. Data Set Contact: B E Goldstein, NASA Ames Research Center, USA. Principal Investigator: D J McComas, Southwest Research Institute, USA. Reference: Astron. Astrophys. Suppl. Ser., 92(2), 237-265 (1992). Relevant Web Sites: http://sst.lanl.gov/nis-projects/swoops/
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This data set contains 1 hour averages of the proton and electron flux data from the Ulysses Energetic Particle Composition Experiment. Flux units are /cm2/s/sr. Data Set Contact: M Bruns, Max Planck Institut fur Aeronomie, Lindau, Germany. Principal Investigator: E Keppler, Max Planck Institut fur Aeronomie, Lindau, Germany. Reference: Astron. Astrophys. Suppl. Ser., 92(2), 317-331 (1992). Relevant Web Sites: http://www.mpae.gwdg.de/mpae_projects/ULYSSES/EPAC.html
Data version 1: Original ASCII source data. Data version 2: Applies to 1996 CDFs onwards, which have been replaced with (or now use) ASCII source files generated with a program which does not remove low event rate data, as was the case for version 1 data. Pre-1996 files are not reprocessed/replaced as version 2 as no useful low event rate data exists pre-1996. For further details contact M. Bruns, Max Planck Institut fur Aeronomie, Lindau, Germany
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This data set contains 1 hour spin averaged count rates of the electron and ion data from the Ulysses Heliosphere Instrument for Spectra, Composition and Anisotropy at Low Energies (HI-SCALE) Low Energy Foil Spectrometer at 150 degrees to the spacecraft spin axis. Count rate units are /s. Data Set Contact: T P Armstrong, Department of Physics & Astronomy, University of Kansas, USA. Principal Investigator: L J Lanzerotti, Bell Laboratories, Lucent Technologies, Murray Hill, NJ, USA. Reference: Astron. Astrophys. Suppl. Ser., 92(2), 349-363 (1992). Relevant Web Sites: http://sd-www.jhuapl.edu/Ulysses/ http://kuspa1.phsx.ukans.edu:8000/~ulysses/index.html
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This data set contains 1 hour spin averaged count rates of the electron and ion data from the Ulysses Heliosphere Instrument for Spectra, Composition and Anisotropy at Low Energies (HI-SCALE) Low Energy Foil Spectrometer at 60 degrees to the spacecraft spin axis. Count rate units are /s. Data Set Contact: T P Armstrong, Department of Physics & Astronomy, University of Kansas, USA. Principal Investigator: L J Lanzerotti, Bell Laboratories, Lucent Technologies, Murray Hill, NJ, USA. Reference: Astron. Astrophys. Suppl. Ser., 92(2), 349-363 (1992). Relevant Web Sites: http://sd-www.jhuapl.edu/Ulysses/ http://kuspa1.phsx.ukans.edu:8000/~ulysses/index.html
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This data set contains 1 hour spin averaged count rates of the ion data from the Ulysses Heliosphere Instrument for Spectra, Composition and Anisotropy at Low Energies (HI-SCALE) Low Energy Magnetic Spectrometer at 120 degrees to the spacecraft spin axis. Count rate units are /s. Data Set Contact: T P Armstrong, Department of Physics & Astronomy, University of Kansas, USA. Principal Investigator: L J Lanzerotti, Bell Laboratories, Lucent Technologies, Murray Hill, NJ, USA. Reference: Astron. Astrophys. Suppl. Ser., 92(2), 349-363 (1992). Relevant Web Sites: http://sd-www.jhuapl.edu/Ulysses/ http://kuspa1.phsx.ukans.edu:8000/~ulysses/index.html
TBD
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This data set contains 1 hour spin averaged count rates of the ion data from the Ulysses Heliosphere Instrument for Spectra, Composition and Anisotropy at Low Energies (HI-SCALE) Low Energy Magnetic Spectrometer at 30 degrees to the spacecraft spin axis. Count rate units are /s. Data Set Contact: T P Armstrong, Department of Physics & Astronomy, University of Kansas, USA. Principal Investigator: L J Lanzerotti, Bell Laboratories, Lucent Technologies, Murray Hill, NJ, USA. Reference: Astron. Astrophys. Suppl. Ser., 92(2), 349-363 (1992). Relevant Web Sites: http://sd-www.jhuapl.edu/Ulysses/ http://kuspa1.phsx.ukans.edu:8000/~ulysses/index.html
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This data set contains 1 hour spin averaged count rates of the deflected electron data from the Ulysses Heliosphere Instrument for Spectra, Composition and Anisotropy at Low Energies (HI-SCALE) Low Energy Magnetic Spectrometer at 30 degrees to the spacecraft spin axis. Count rate units are /s. Data Set Contact: T P Armstrong, Department of Physics & Astronomy, University of Kansas, USA. Principal Investigator: L J Lanzerotti, Bell Laboratories, Lucent Technologies, Murray Hill, NJ, USA. Reference: Astron. Astrophys. Suppl. Ser., 92(2), 349-363 (1992). Relevant Web Sites: http://sd-www.jhuapl.edu/Ulysses/ http://kuspa1.phsx.ukans.edu:8000/~ulysses/index.html
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This data set contains 3.5 hour averages of the solar wind ion density ratio (to O6+), velocity and temperature from the Ulysses Solar Wind Ion Composition Spectrometer. Velocity units are km/s. Temperature units are K. Data Set Contact: R von Steiger, International Space Science Institute, Bern, Switzerland. Principal Investigators: J Geiss, International Space Science Institute, Bern, Switzerland, and G Gloeckler, University of Maryland, College Park, Maryland, USA. Reference: Astron. Astrophys. Suppl. Ser., 92(2), 267-289 (1992). Relevant Web Sites: http://space.umd.edu/UMD_sensors/uls_swics.html
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This data set contains 1 hour averages of the magnetic field components (RTN) and field magnitude from the Vector Helium Magnetometer. Units are nT. Data Set Contact: R J Forsyth, The Blackett Laboratory, Imperial College, London, UK. Principal Investigator: A Balogh, The Blackett Laboratory, Imperial College, London, UK. Reference: Astron. Astrophys. Suppl. Ser., 92(2), 221-236 (1992). Relevant Web Sites: http://www.sp.ph.ic.ac.uk/Ulysses/
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This data set contains 1 hour spin averaged count rates of the proton and ion data from the Ulysses Heliosphere Instrument for Spectra, Composition and Anisotropy at Low Energies (HI-SCALE) Composition Aperture Telescope at 60 degrees to the spacecraft spin axis. Count rate units are /s. Data Set Contact: T P Armstrong, Department of Physics & Astronomy, University of Kansas, USA. Principal Investigator: L J Lanzerotti, Bell Laboratories, Lucent Technologies, Murray Hill, NJ, USA. Reference: Astron. Astrophys. Suppl. Ser., 92(2), 349-363 (1992). Relevant Web Sites: http://sd-www.jhuapl.edu/Ulysses/ http://kuspa1.phsx.ukans.edu:8000/~ulysses/index.html
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This data set contains 1 hour spin averaged count rates of the ion data from the Ulysses Heliosphere Instrument for Spectra, Composition and Anisotropy at Low Energies (HI-SCALE) Composition Aperture Telescope at 60 degrees to the spacecraft spin axis (WARTD). Count rate units are /s. Data Set Contact: T P Armstrong, Department of Physics & Astronomy, University of Kansas, USA. Principal Investigator: L J Lanzerotti, Bell Laboratories, Lucent Technologies, Murray Hill, NJ, USA. Reference: Astron. Astrophys. Suppl. Ser., 92(2), 349-363 (1992). Relevant Web Sites: http://sd-www.jhuapl.edu/Ulysses/ http://kuspa1.phsx.ukans.edu:8000/~ulysses/index.html
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Ulysses COHOweb connection
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Voyager1 COHOweb connection
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TBS
6/13/91 - Original Implementation 9/18/91 - Modified for new attitude file format changes. ICCR 881 2/11/92 - Used the variable name TIME and type CDF_INT4 and size 3 instead of EPOCH, CDF_EPOCH and 1 for the time tags. CCR 490 6/1/92 - Added global attributes TITLE, PROJECT, DISCIPLINE, SOURCE_NAME, DATA_VERSION, and MODS; added variable attributes VALIDMIN, VALIDMAX, LABL_PTR_1, and MONOTON; added variables EPOCH and LABEL_TIME; changed variable name TIME to TIME_PB5. CCR 1066 11/07/92 - use cdf variable Epoch and Time_PB5 6/8/93 - Added global attributes ADID_ref and Logical_file_id. CCR 1092 7/5/94 - CCR ISTP 1852, updated CDHF skeleton to CDF standards - JT 9/20/94 - Added global attributes GCI_RA_ERR and GCI_DECL_ERR. CCR 1932 11/7/94 - Merged CCR 1852 changes and corrected errors made in CCR 1852. ICCR 1884 12/7/94 - Modified MODS and LABLAXIS to follow ISTP standards. ICCR 1885
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TBS
6/13/91 - Original Implementation 9/18/91 - Modified for new attitude file format changes. ICCR 881 2/11/92 - Used the variable name TIME and type CDF_INT4 and size 3 instead of EPOCH, CDF_EPOCH and 1 for the time tags. CCR 490 6/1/92 - Added global attributes TITLE, PROJECT, DISCIPLINE, SOURCE_NAME, DATA_VERSION, and MODS; added variable attributes VALIDMIN, VALIDMAX, LABL_PTR_1, and MONOTON; added variables EPOCH and LABEL_TIME; changed variable name TIME to TIME_PB5. CCR 1066 11/07/92 - use cdf variable Epoch and Time_PB5 6/8/93 - Added global attributes ADID_ref and Logical_file_id. CCR 1092 7/5/94 - CCR ISTP 1852, updated CDHF skeleton to CDF standards - JT 9/20/94 - Added global attributes GCI_RA_ERR and GCI_DECL_ERR. CCR 1932 11/7/94 - Merged CCR 1852 changes and corrected errors made in CCR 1852. ICCR 1884 12/7/94 - Modified MODS and LABLAXIS to follow ISTP standards. ICCR 1885
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Wind 3dp, EESA LOW omni directional electron energy spectra
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WIND MFI Composite data file. This file contains multiple time resolution data. 1 Minute data averages 3 Second data averages 1 Hour data averages WIND MFI Instrument turn on 11/12/1994 References: 1. Lepping, R. P., et al., The WIND Magnetic Field Investigation, p. 207 in The Global Geospace Mission, ed. by C. T. Russell, Kluwer,1995 2. Panetta, P. (GSFC), GGS WIND MFI Operator's Manual, September 15, 1992. 3. Computer Sciences Corporation, Data Format Control Document (DFCD) Between The International Solar-Terrestrial Physics (ISTP) Program Information Processing Division Ground Data Processing System and The ISTP Mission Investigators, CSC/TR-91/6014, 560-1DFD/0190, July 1992. 4. Behannon, K. W., International Solar Terrestrial Physics (ISTP) Program Investigator Data Analysis Requirements For WIND and GEOTAIL Spacecraft Magnetometer Experiment, September 1987. 5. National Space Science Data Center, CDF User's Guide, Version 2.3.0, October 1, 1992. 6. Mish, W. H., International Solar-Terrestrial Physics (ISTP) Key Parameter Generation Software (KPGS) Standards & Conventions, September 1992. 7. Mish, W. H., IMP F and G Phase I Magnetic Field Analysis, April 1972
10/28/94 Initial release 01/28/97 Z-variable Release add Z correction 02/20/97 Change file name from sp to h0
Average of the magnitudes (F1)
Average of the magnitudes (F1)
Average of the magnitudes (F1)
Average of the magnitudes (F1)
Average of the magnitudes (F1)
Average of the magnitudes (F1)
RMS of the magnitudes (F1 RMS)
RMS of the magnitudes (F1 RMS)
RMS of the magnitudes (F1 RMS)
Time is centered confirmed for MFI by A. Szabo 2005 Nov 06
Time is centered confirmed for MFI by A. Szabo 2005 Nov 06
Time is centered confirmed for MFI by A. Szabo 2005 Nov 06
Explanatory notes: The electron moments included in this data set are derived from the velocity moments integration of solar wind electron distributions measured by the WIND/SWE VEIS instrument (see Ogilvie et al., "SWE, a comprehensive plasma instrument for the WIND spacecraft", Space Sci. Rev., 71, 55, 1955). Moments parameters are computed from 3s measurements which are spaced either 6s or 12s in time. Plots should therefore not exceed a time range of 2 or 3 hours in order to display the details of this high resolution data. The moments parameters which will be of value to most users of this data set are the electron temperature, the electron temperature anisotropy, and the electron heat flux vector. These quantities are reliable and citable with caution, meaning that the PI advises that the user should discuss their interpretation with a member of the SWE science team before publishing. The following comments are intended to aid in the use and interpretation of the prime quantities of this data set, the electron temperature, the electron temperature anisotropy, and the electron heat flux. (All vector quantities are in GSE coordinates.) The temperature and temperature anisotropy are normalized to the derived electron density and, therefore, are not sensitive to the uncertainty in the density determination as discussed below. The electron temperature is derived from the pressure tensor divided by the electron density and the Boltzmann constant. The three eigenvalues of the diagonalized temperature tensor are the temperature parallel to the tensor principal axis and the two perpendicular components of the temperature. The temperature anisotropy is defined here as the ratio of the parallel temperature to the average of the two perpendicular temperature components. The electron temperature is one-third of the trace of the diagonalized temperature tensor. Also included is the unit vector along the principal axis of the pressure tensor as well as the cosine of the angle between the principal axis and the magnetic field vector. An indication that the principal axis has been uniquely defined is that the temperature anisotropy is significantly different from unity and that the principal axis and the magnetic field are nearly parallel or anti-parallel. The heat flux vector included here is significant only when the magnitude rises above the noise level, i.e., above the level 0.002 to 0.005 ergs/cm/cm/s. The heat flux may be low in magnitude either due to a nearly isotropic distribution, due to electron counter-streaming, or due to a low counting rate of the instrument. An indicator of a significant net heat flux is that the heat flux direction should track with the magnetic field direction. For this purpose, the cosine of the angle between the heat flux vector and the magnetic field is included, and should be close to -1 or +1 in order for the heat flux to be significant. In some cases it will be necessary to use electron pitch angle distributions (available on request from the SWE team) to decide whether low electron flux or counterstreaming account for a low net heat flux. It is also strongly recommended that 3s magnetic field data from the WIND/MFI experiment (not included in this data set) be used in conjunction with the SWE electron heat flux data to ensure a correct interpretation of the heat flux. The electron density and electron bulk flow velocity are also included in this data set but no claim is made for their accuracy. The electron flow velocity is usually within 10% to 20% of the solar wind flow velocity derived from the SWE Faraday cup experiment and which are found in the SWE key parameter data set. The electron density, however, cannot be absolutely determined due to the spacecraft potential and the fact that the electron instrument response has varied over time. The electron density determination includes a first order attempt to determine the spacecraft potential by imposing the charge neutrality condition on the derived electron density and Faraday cup ion density. The electron density will be within a few percent of the solar wind density derived from the Faraday cup early in the mission (1994-1997), while later in the mission (1998 and onward), depending on the state of the instrument, there will be times when the derived electron density may be as much as a factor 2 too low. Although the electron density is not derived absolutely, relative changes in electron density can usually be relied on. Both the electron density and electron flow speed track with variations in the ion density and ion flow speed, respectively. However, the user is strongly advised to use the SWE ion key parameters for the bulk plasma density and flow speed.
Skeleton created 1/19/2000 Started again 3/13/2001
Te = (trace of pressure tensor)/(electron density * Boltzman constant)/3 = (2*Te_perp + Te_para)/3
Average energy = (3/2)Boltzmann constant * Te
See the global attribute TEXT.
See the global attribute TEXT.
See the global attribute TEXT.
See the global attribute TEXT.
Jan 1 = Day 1
Forst-order estimate only; se the global attribute TEXT.
Te_perp = average of the perpendicular elements of the temperature tensor. Te_para = parallel component of the temperature tensor.
SSR WAVES: The Radio and Plasma Wave Investigation on the WIND Spacecraft, Vol 71, pg 231-263,1995. Secondary file - high resplasma density
CODED JUNE 1996, C. MEETRE
No background subtraction - spin plane
High resolution plasma densities: resolution depends on instrument mode and may vary.
High resolution plasma densities: actual resolution depends on instrument mode and may vary.
SWE, a comprehensive plasma instrument for the WIND spacecraft, K.W. Ogilvie, et al., Space Sci. Rev., 71, 55-77, 1995 Solar wind proton parameters, including anisotropic temperatures, derived by non-linear fitting of the measurements and with moment techniques. Data reported within this file do not exceed the limits of various parameters listed in the following section. There may be more valid data in the original dataset that requires additional work to interpret but was discarded due to the limits. In particular we have tried to exclude non-solar wind data from these files. We provide the one sigma uncertainty for each parameter produced by the non-linear curve fitting analysis either directly from the fitting or by propagating uncertainties for bulk speeds, flow angles or any other derived parameter. For the non-linear anisotropic proton analysis, a scalar thermal speed is produced by determining parallel and perpendicular temperatures, taking the trace, Tscalar = (2Tperp + Tpara)/3 and converting the result back to a thermal speed. The uncertainties are also propagated through
12/28/94, 3/4/96, by Alan J. Lazarus John T. Steinberg Daniel B. Berdichevsky.
Goodness of fit of assumed convecting Maxwellian distribution functions to the actual observations
The Radio and Plasma Wave Investigation on the WIND Spacecraft, Sp.Sci.Rev.,Vol 71, pg, 231-263,1995.
CODED JAN,1999, SARDI
Working channels are about 20 of total 256 frequency channels. Values for other channels are interpolations
Zero value denotes channel average values are interpolated, not directly measured
Electron flux energy levels: channel 1: 0.1-.4 keV channel 2: 0.4-1.8 keV channel 3: 1.9-8.0 keV channel 4: 9.0-30 keV channel 5: 20-48 keV channel 6: 43-138 keV channel 7: 127-225 keV Ion flux energy levels: channel 1: 0.07-.21 keV channel 2: 0.25-1.1 keV channel 3: 1.3-7 keV channel 4: 8-30 keV channel 5: 20-58 keV channel 6: 58-126 keV channel 7: 115-400 keV pfu == 1/(cm^2-s-sr-keV) Created : Nov, 1991, for 3dpa kpgs testing Modified: May, 1992, to accomodate Standards and Conventions Modified: Jan, 1993, as suggested by Kessel Modified: Mar, 1993, as suggested by Kessel Modified: Jun 7, 1994, for updated 3dpa telemetry specifications Modified: Jun 9, 1994, as suggested by KITT Modified: Jul 10, 1994 Modified: Apr 3, 1995, particle temperatures from K to eV Modified: jun 12, 1995, particle flux scaling adjustments
version 1.0, october 91 version 1.0.1, summer 92 version 1.0.2, january 93 version 1.1, june 94 version 1.1.1, june 94 version 1.1.2, june 94 version 1.1.3, july 94 version 1.2, april 95 version 05, june 95
pfu=particle flux unit=1/(cm^2-s-sr-keV)
pfu=particle flux unit=1/(cm^2-s-sr-keV)
Wind/EPACT Key Parameters LEMT - Low Energy Matrix Telescope APE - Alpha Proton Electron This is a character attribute to hold some meta-data........
Created May 10, 1995 Created May 18, 1995
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Pre-generated PWG plots
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References: 1. Panetta P. (GSFC), GGS WIND MFI Operator's Manual, September 15, 1992. 2. Computer Sciences Corporation, Data Format Control Document (DFCD) Between The International Solar-Terrestrial Physics (ISTP) Program Information Processing Division Ground Data Processing System and The ISTP Mission 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.
Initial Release 7/12/93 Zvar Release 10/24/96 Zvar Update 11/12/96
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Time is for the start of the averaging interval. Computed are the avg alpha vel; avg C/O abundance ratio; avg carbon ionization temp in million degs K from C+6 & C+5 (using the tbls of Arnaud & Rothenflug, 1985); the avg oxygen ionization temp from O+7 & O+6 in million degs K (using tbls of Arnaud & Rothenflug, 1985) Above avgs are made over 4 hrs. He vel and He kinetic temp are computed every 3 min & are contained in the K1 CDF References: Space Science Reviews 71:79-124, 1995, Kluwer Academic Publishers, Belgium Instrument consist of: Solar Wind Ion Composition Spectrometer (SWICS); high resolution mass spectrometer (MASS); Supra-Thermal Ion Composition Spectrometer (STICS) & common DPU
Version 01 Feb. 1996 - whm
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To be supplied
12/17/92 - Original Implementation, CCR 87 6/14/94 - CCR ISTP 1852, updated CDHF skeleton to CDF standards - JT 11/9/94 - Correct errors made in ccr 1852. CCR 1884
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SWE, a comprehensive plasma instrument for the WIND spacecraft, K.W.
Ogilvie, et al., Space Sci. Rev., 71, 55-77, 1995
USE OF THE QUALITY VARIABLES:
*** Good data is indicated by a quality flag of 0. ***
The quality flags for each parameter are given as integers 4 bytes
long (integer*4). The individual 'bits' for each quality value are set
(or cleared) in the analysis code by adding (or subtracting) a power of
2 as follows:
To set the 1st bit, add 1.
To set the 2nd bit, add 2,
To set the 3rd bit, add 4,
To set the 4th bit, add 8, and so on.
BIT TO_SET_BIT MEANING
1 +1 = 3 point parabolic fits to proton peaks were not attempted.
2 +2 = non-linear least squares fit was not attempted.
3 +4 = 3 point parabolic fits to proton peaks FAILED.
4 +8 = non-linear least squares fit FAILED.
See http://cdaweb.gsfc.nasa.gov/wind_swe_quality.html
For the complete guide to the quality flag values.
12/28/94, 3/4/96, by Alan J. Lazarus John T. Steinberg Daniel B. Berdichevsky. Skeleton TABLE for plasma CDF SWE keyparameters, dbb, Jan., 1994. Instr. qual. flags validmax setequal to +2147483647, 12/94. Qual. flags format changed to compatible values with new validmax, jts and ajl, 12/94. Processing with instrument science modes 2 and 11 added, jts and dbb, 10/27/95. DICT_KEYs added ajl, 3/4/96.
Proton Density Quality Flag: 0=OK; 2=parabolic 3-point fit only; 130=parabolic 3-point fit only, sensor 1 only, N/S angle zero degrees assumed; Other values NOT VALID
Proton thermal speed Quality Flag: 0=OK; 2=parabolic 3-point fit only; 130=parabolic 3-point fit only, sensor 1 only, N/S angle zero degrees assumed; Other values NOT VALID
Velocity Quality Flag: 0=OK; 2=parabolic 3-point fit only; 130=parabolic 3-point fit only, sensor 1 only, N/S angle zero degrees assumed; Other values NOT VALID
SSR WAVES: The Radio and Plasma Wave Investigation on the WIND Spacecraft, Vol 71, pg 231-263,1995.
CODED MAY 1996, C. MEETRE
background subtracted using 3% lower bound across each frequency band for entire day - backgrounds given in variable E_Background. Data taken in spin plane only
Solar array current from s/c HK correlates with photoelectric effect on antennas
Solar array current from s/c HK correlates with photoelectric effect on antennas
TBS
Originated Monday, May 13, 1991 Modified June 13, 1991 for version 2.1 Modified October 2,1991 for new global attributes, incr sizes Modified 11/11/91 Add sun vector, replace space id with support id Modified 1992 Feb 11 to use the variable name TIME and type CDF_INT4 instead of EPOCH and CDF_EPOCH for the time tags CCR 490 Modified 6/2/92 add project, discipline, source_name, data_version, title, and mods to global section; add validmin, validmax, labl_ptr_1 and monoton attributes to some variables; put epoch time back in, rename time to time_pb5; add label_time to variables Modified 11/07/92 to use Epoch and Time_PB5 variable name Modified 6/2/93 add ADID_ref and Logical_file_id 7/5/94 - CCR ISTP 1852 updated CDHF skeleton to CDF standards - JT 9/21/94 - Added 24 new global attributes to log the ephemeris comparison summary report from the definitive FDF orbit file. CCR 1932 11/7/94 - Merged CCR 1852 changes and corrected errors made in CCR 1852. ICCR 1884 12/7/94 - Modified MODS to follow ISTP standards. ICCR 1885 01/05/95 - add heliocentric coordinate system. CCR 1889 2/28/95 - added COMMENT1 and COMMENT2 for CCR
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Pre-generated PWG plots
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TBS
Originated Monday, May 13, 1991 Modified June 13, 1991 for version 2.1 Modified October 2,1991 for new global attributes, incr sizes Modified 11/11/91 Add sun vector, replace space id with support id Modified 1992 Feb 11 to use the variable name TIME and type CDF_INT4 instead of EPOCH and CDF_EPOCH for the time tags CCR 490 Modified 6/2/92 add project, discipline, source_name, data_version, title, and mods to global section; add validmin, validmax, labl_ptr_1 and monoton attributes to some variables; put epoch time back in, rename time to time_pb5; add label_time to variables Modified 11/07/92 to use Epoch and Time_PB5 variable name Modified 6/2/93 add ADID_ref and Logical_file_id 7/5/94 - CCR ISTP 1852 updated CDHF skeleton to CDF standards - JT 9/21/94 - Added 24 new global attributes to log the ephemeris comparison summary report from the definitive FDF orbit file. CCR 1932 11/7/94 - Merged CCR 1852 changes and corrected errors made in CCR 1852. ICCR 1884 12/7/94 - Modified MODS to follow ISTP standards. ICCR 1885 01/05/95 - add heliocentric coordinate system. CCR 1889 2/28/95 - added COMMENT1 and COMMENT2 for CCR
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Wind 3dp, PESA LOW (~24 sec resolution) energy spectra with ion moments
Energy, for 15 channels ~0.6 to ~10 KeV
Energy, for 15 channels ~0.6 to ~10 KeV
Ion flux in 15 energy channels from about 0.6 keV to about 10 keV. Channel energies vary with time, keeping the peak flux in channel 10. Channel 15 is the lowest energy channel.
Ion flux in 15 energy channels from about 0.6 keV to about 10 keV. Channel energies vary with time, keeping the peak flux in channel 10. Channel 15 is the lowest energy channel.
Wind 3dp, PESA LOW 1 spin resolution ion (proton and alpha) moments (computed on spacecraft)
Version 3 Product, August 2005
Time is centered, confirmed for 3DP by P.Schroeder 2005 Nov 07