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 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
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 Cosmic Ray Isotope Spectrometer (CRIS) on the Advanced Composition Explorer(ACE) spacecraft is intended to be a major step in ascertaining the isotopic composition of the Galactic Cosmic Rays(GCRs) and hence a major step in determining their origin. The GCRs consist, by number, primarily of hydrogen nuclei(~92%) and helium nuclei (~7%). The energetic nuclei from He to Ni (Z=2 to 28) over the energy range from ~10 to ~100 MeV/nucleon. During large solar events, when particle fluxes can increase over quiet-time values by factors of up to 10000, CRIS measures the isotopic composition of the solar corona, while during solar quiet times CRIS measures the isotopes of low-energy Galactic cosmic rays and the composition of the anomalous cosmic rays which are thought to originate in the nearby interstellar medium. The solar energetic particle measurements are useful to further our understanding of the Sun, while also providing a baseline for comparison with the Galactic cosmic ray measurements carried out by CRIS. CRIS has a geometry factor of ~40 cm2--sr, which is significantly larger than previous satellite solar particle isotope spectrometers. It is also designed to provide excellent mass resolution during the extremely high particle flux conditions which occur during large solar particle events.
Initial Release 02/08/05
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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 SEPICA Instrument on ACE The Solar Energetic Particle Ionic Charge Analyzer is the sensor on ACE, which is used to determine the charge state distribution of energetic particle distributions. SEPICA is designed to measure the ionic charge state, Q, the kinetic energy, E, and the nuclear charge, Z, of energetic ions above 0.2 MeV/Nuc. This includes ions accelerated in solar flares as well as in interplanetary space during energetic storm particle (ESP) and co-rotating interaction region (CIR) events. For low mass numbers SEPICA also separates isotopes -- for example, 3He and 4He. For more information about the SEPICA instrument, visit the SEPICA Home Page at University of New Hampshire: http://www.ssg.sr.unh.edu/tof/Missions/Ace/index.html?sepicamain.html 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 07/27/07
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The Solar Isotope Spectrometer (SIS) is designed to provide high resolution measurements of the isotopic composition of energetic nuclei from He to Ni (Z=2 to 28) over the energy range from ~10 to ~100 MeV/nucleon. During large solar events, when particle fluxes can increase over quiet-time values by factors of up to 10000, SIS measures the isotopic composition of the solar corona, while during solar quiet times SIS measures the isotopes of low-energy Galactic cosmic rays and the composition of the anomalous cosmic rays which are thought to originate in the nearby interstellar medium. The solar energetic particle measurements are useful to further our understanding of the Sun, while also providing a baseline for comparison with the Galactic cosmic ray measurements carried out by CRIS. SIS has a geometry factor of ~40 cm2--sr, which is significantly larger than previous satellite solar particle isotope spectrometers. It is also designed to provide excellent mass resolution during the extremely high particle flux conditions which occur during large solar particle events.
Initial Release 02/08/05
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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 + 4. 8: 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 + 4. 8: 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 + 4. 8: 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 + 4. 8: 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 + 4. 8: 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 + 4. 8: 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 + 4. 8: 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 + 4. 8: 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 + 4. 8: 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 + 4. 8: 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.
SW_type is a rough classification of solar wind type based on functions of O7+/O6+ vs proton speed (Zhou 2008). 0: Streamer Wind. 1: Coronal Hole Wind. 2: Coronal Mass Ejection.
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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The Cosmic Ray Isotope Spectrometer (CRIS) on the Advanced Composition Explorer(ACE) spacecraft is intended to be a major step in ascertaining the isotopic composition of the Galactic Cosmic Rays(GCRs) and hence a major step in determining their origin. The GCRs consist, by number, primarily of hydrogen nuclei(~92%) and helium nuclei (~7%). The energetic nuclei from He to Ni (Z=2 to 28) over the energy range from ~10 to ~100 MeV/nucleon. During large solar events, when particle fluxes can increase over quiet-time values by factors of up to 10000, CRIS measures the isotopic composition of the solar corona, while during solar quiet times CRIS measures the isotopes of low-energy Galactic cosmic rays and the composition of the anomalous cosmic rays which are thought to originate in the nearby interstellar medium. The solar energetic particle measurements are useful to further our understanding of the Sun, while also providing a baseline for comparison with the Galactic cosmic ray measurements carried out by CRIS. CRIS has a geometry factor of ~40 cm2--sr, which is significantly larger than previous satellite solar particle isotope spectrometers. It is also designed to provide excellent mass resolution during the extremely high particle flux conditions which occur during large solar particle events.
Initial Release 02/08/05
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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 directory contains 3 data files of topside electron density profiles as deduced from Alouette 1 (a,b,c) topside sounder measurements. The data processing was done in the seventies at the Communications Research Center in Ottawa, Canada for all except data set a, which was processed and submitted to NSSDC by the University of California Los Angeles (UCLA), Department for Meteorology. The UCLA data set provides data from 1000km down in steps of 25km. All other data sets provide the electron density at irregular height intervals. The x- and o-traces were manually scaled from the ionograms and the inversion algorithm of J. Jackson was used to compute the density profiles from these traces.
Added to try to enable plots.
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
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
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 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 data file contains topside electron density profiles as deduced from Alouette 2 topside sounder measurements. The data processing was done in the seventies at the Communications Research Center in Ottawa, Canada This data set provides data from 1000km down in steps of irregular step size. The x- and o-traces were manually scaled from the ionograms and the inversion algorithm of J. Jackson was used to compute the density profiles from these traces.
Added to try to enable plots.
This is the hourly-averaged data from the Apollo 12 Solar Wind Spectrometer instrument, reformatted by NSSDC for easier access and use. During the lunar night there is no solar wind signal so there are data gaps of about 15 days each lunation. 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 http://nssdc.gsfc.nasa.gov/nmc/publicationDisplay.do?id=B55381-000A
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 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. During the lunar night there is no solar wind signal so there are data gaps of about 15 days each lunation. 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 http://nssdc.gsfc.nasa.gov/nmc/publicationDisplay.do?id=B55381-000A
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. During the lunar night there is no solar wind signal so there are data gaps of about 15 days each lunation. 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 http://nssdc.gsfc.nasa.gov/nmc/publicationDisplay.do?id=B55381-000A
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 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 15 Solar Wind Spectrometer instrument, and was reformatted by NSSDC for easier access and use. During the local lunar night there is no solar wind signal so there are data gaps of about 15 days each lunation. 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 http://nssdc.gsfc.nasa.gov/nmc/publicationDisplay.do?id=B55381-000A
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.
No TEXT global attribute value.
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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) 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.
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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
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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
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 Status set to 0: WEC powered off for time range 2008-07-31T15:15:06Z to 2008-07-31T23:59:59Z
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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__C1_PP_EFW: No reason given for time range 2008-03-31T23:14:00Z to 2008-03-31T23:17:00Z Fill value inserted for E_pow_f1__C1_PP_EFW: No reason given for time range 2008-03-31T23:14:00Z to 2008-03-31T23:17:00Z Fill value inserted for E_sigma__C1_PP_EFW: No reason given for time range 2008-03-31T23:14:00Z to 2008-03-31T23:17:00Z Fill value inserted for U_probe_sc__C1_PP_EFW: No reason given for time range 2008-03-31T23:14:00Z to 2008-03-31T23:17:00Z
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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 *** 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 2009-09-17T12:40:40Z Caveats file: RAP_CAV_C1_V115.DAT; Release Sep 7, 2009
See CSDS User's Guide, DS-MPA-TN-0015, for post processing caveats RAPID Data produced with best-effort general calibration files. Corrected: error that made ion fluxes 50% too large in 2006-2008 data. 1901-01-01T00:00:00.000Z/9999-12-31T23:59:59.999Z: Electrons: lowest energy channel has reduced sensitivity; see RAPID Calibration Report. 1901-01-01T00:00:00.000Z/9999-12-31T23:59:59.999Z: Electrons: there can be spurious jumps in data when integration time changes; see RAPID User Guide. 2001-09-13T00:00:00.000Z/9999-12-31T23:59:59.000Z: Central ion head not functioning since 2001-09-13, no sensitivity near ecliptic. 2007-03-16T06:00:00.000Z/9999-12-31T23:59:59.000Z: IIMS stops functioning since 2007-03-16, no ion data. Corrected time stamps for ions and electrons. Energy threshold shifts have been applied. Changed EDB format, on-board anisotropies not possible in NM In this file, the heavy ion flux J(m>4,lo) is integrated from 274 keV instead of
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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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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 *** C1_UP_FGM_20090531 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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No TEXT global attribute value.
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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) 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.
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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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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 CIS Switched-OFF on this s/c
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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
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
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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__C2_PP_EFW: No reason given for time range 2008-03-31T23:14:00Z to 2008-03-31T23:17:00Z Fill value inserted for E_pow_f1__C2_PP_EFW: No reason given for time range 2008-03-31T23:14:00Z to 2008-03-31T23:17:00Z Fill value inserted for E_sigma__C2_PP_EFW: No reason given for time range 2008-03-31T23:14:00Z to 2008-03-31T23:17:00Z Fill value inserted for U_probe_sc__C2_PP_EFW: No reason given for time range 2008-03-31T23:14:00Z to 2008-03-31T23:17:00Z
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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 WARNING - No Sun Pulse - Spin Phase is Invalid No FGM science data available
See CSDS User's Guide, DS-MPA-TN-0015, for post processing caveats *** C2_PP_FGM_20080210 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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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 2009-09-17T12:40:43Z Caveats file: RAP_CAV_C2_V115.DAT; Release Sep 15, 2009
See CSDS User's Guide, DS-MPA-TN-0015, for post processing caveats RAPID Data produced with best-effort general calibration files. Corrected: error that made ion fluxes 50% too large in 2006-2008 data. 1901-01-01T00:00:00.000Z/9999-12-31T23:59:59.999Z: Electrons: lowest energy channel has reduced sensitivity; see RAPID Calibration Report. 1901-01-01T00:00:00.000Z/9999-12-31T23:59:59.999Z: Electrons: there can be spurious jumps in data when integration time changes; see RAPID User Guide. 2001-01-12T00:00:00.000Z/9999-12-31T23:59:59.000Z: Central ion head not functioning since 2001-01-12, no sensitivity near ecliptic. Corrected time stamps for ions and electrons. Energy threshold shifts have been applied. Changed EDB format, on-board anisotropies not possible in NM In this file, the heavy ion flux J(m>4,lo) is integrated from 274 keV instead of
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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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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 *** C2_UP_FGM_20090531 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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No TEXT global attribute value.
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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) 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.
Back to top
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.
Back to top
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
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
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__C3_PP_EFW: No reason given for time range 2008-03-31T23:14:00Z to 2008-03-31T23:17:00Z Fill value inserted for E_pow_f1__C3_PP_EFW: No reason given for time range 2008-03-31T23:14:00Z to 2008-03-31T23:17:00Z Fill value inserted for E_sigma__C3_PP_EFW: No reason given for time range 2008-03-31T23:14:00Z to 2008-03-31T23:17:00Z Fill value inserted for U_probe_sc__C3_PP_EFW: No reason given for time range 2008-03-31T23:14:00Z to 2008-03-31T23:17:00Z
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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 *** 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
Back to top
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 2009-09-17T12:40:46Z Caveats file: RAP_CAV_C3_V115.DAT; Release Sep 14, 2009
See CSDS User's Guide, DS-MPA-TN-0015, for post processing caveats RAPID Data produced with best-effort general calibration files. Corrected: error that made ion fluxes 50% too large in 2006-2008 data. 1901-01-01T00:00:00.000Z/9999-12-31T23:59:59.999Z: Electrons: lowest energy channel has reduced sensitivity; see RAPID Calibration Report. 1901-01-01T00:00:00.000Z/9999-12-31T23:59:59.999Z: Electrons: there can be spurious jumps in data when integration time changes; see RAPID User Guide. 2001-12-13T00:00:00.000Z/9999-12-31T23:59:59.000Z: Central ion head not functioning since 2001-12-13, no sensitivity near ecliptic. Corrected time stamps for ions and electrons. Energy threshold shifts have been applied. Solar noise removed from electrons. Solar noise file is c3_saa_noise.dat from 2009-Sep-04 22:22:40 Changed EDB format, on-board anisotropies not possible in NM In this file, the heavy ion flux J(m>4,lo) is integrated from 274 keV instead of
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
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 *** C3_UP_FGM_20090531 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.
Back to top
No TEXT global attribute value.
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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.
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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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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
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 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 2008-03-31T23:14:00Z to 2008-03-31T23:17:00Z Fill value inserted for E_pow_f1__C4_PP_EFW: No reason given for time range 2008-03-31T23:14:00Z to 2008-03-31T23:17:00Z Fill value inserted for E_sigma__C4_PP_EFW: No reason given for time range 2008-03-31T23:14:00Z to 2008-03-31T23:17:00Z Fill value inserted for U_probe_sc__C4_PP_EFW: No reason given for time range 2008-03-31T23:14:00Z to 2008-03-31T23:17:00Z
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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 *** 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 2009-09-17T12:40:51Z Caveats file: RAP_CAV_C4_V115.DAT; Release Sep 15, 2009
See CSDS User's Guide, DS-MPA-TN-0015, for post processing caveats RAPID Data produced with best-effort general calibration files. Corrected: error that made ion fluxes 50% too large in 2006-2008 data. 1901-01-01T00:00:00.000Z/9999-12-31T23:59:59.999Z: Electrons: lowest energy channel has reduced sensitivity; see RAPID Calibration Report. 1901-01-01T00:00:00.000Z/9999-12-31T23:59:59.999Z: Electrons: there can be spurious jumps in data when integration time changes; see RAPID User Guide. 2001-12-12T00:00:00.000Z/9999-12-31T23:59:59.000Z: Central ion head not functioning since 2001-12-12, no sensitivity near ecliptic. 2006-09-15T15:04:00.000Z/9999-12-31T23:59:59.000Z: Omnidirectional electrons: excludes detectors 7 & 9, pedestal contamination. Corrected time stamps for ions and electrons. Energy threshold shifts have been applied. Changed EDB format, on-board anisotropies not possible in NM In this file, the heavy ion flux J(m>4,lo) is integrated from 274 keV instead of
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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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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 *** C4_UP_FGM_20090531 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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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.
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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 U_probe_sc__CL_SP_EFW: No reason given for time range 2008-03-31T23:14:00Z to 2008-03-31T23:17:00Z Fill value inserted for E_dusk__CL_SP_EFW: No reason given for time range 2008-03-31T23:14:00Z to 2008-03-31T23:17:00Z Fill value inserted for E_pow_f1__CL_SP_EFW: No reason given for time range 2008-03-31T23:14:00Z to 2008-03-31T23:17:00Z Fill value inserted for E_sigma__CL_SP_EFW: No reason given for time range 2008-03-31T23:14:00Z to 2008-03-31T23:17:00Z
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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 Summary parameters derived from C3_PP_RAP_20090831 Data processed on 2009-09-17T12:40:46Z Caveats file: RAP_CAV_C3_V115.DAT; Release Sep 14, 2009
See CSDS User's Guide, DS-MPA-TN-0015, for post processing caveats RAPID Data produced with best-effort general calibration files. Corrected: error that made ion fluxes 50% too large in 2006-2008 data. 1901-01-01T00:00:00.000Z/9999-12-31T23:59:59.999Z: Electrons: lowest energy channel has reduced sensitivity; see RAPID Calibration Report. 1901-01-01T00:00:00.000Z/9999-12-31T23:59:59.999Z: Electrons: there can be spurious jumps in data when integration time changes; see RAPID User Guide. 2001-12-13T00:00:00.000Z/9999-12-31T23:59:59.000Z: Central ion head not functioning since 2001-12-13, no sensitivity near ecliptic. Corrected time stamps for ions and electrons. Energy threshold shifts have been applied. Solar noise removed from electrons. Solar noise file is c3_saa_noise.dat from 2009-Sep-04 22:22:40 Changed EDB format, on-board anisotropies not possible in NM In this file, the heavy ion flux J(m>4,lo) is integrated from 274 keV instead of
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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_20090531 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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The Planar Langmuir Probe on C/NOFS is a suite of 2 current measuring sensors mounted on the ram facing surface of the spacecraft. The primary sensor is an Ion Trap (conceptually similar to RPAs flown on many other spacecraft) capable of measuring ion densities as low as 1 cm-3 with a 12 bit log electrometer. The secondary senor is a swept bias planar Langmuir probe (Surface Probe) capable of measuring Ne, Te, and spacecraft potential. The ion number density is the one second average of the ion density sampled at either 32, 256, 512, or 1024 Hz (depending on the mode). The ion density standard deviation is the standard deviation of the samples used to produce the one second average number density. DeltaN/N is the detrened ion number density 1 second standard deviation divided by the mean 1 sec density. The electron density, electron temperature, and spacecraft potential are all derived from a least squares fit to the current-bias curve from the Surface Probe. The data are PRELIMINARY, and as such, are intended for BROWSE PURPOSES ONLY. Regestering your email will allow notification of updates.
From PLP Ion Trap
From PLP Surface Probe swept bias mode
From PLP Surface Probe swept bias mode
Semi-major axis: 6378.137 km, Semi-minor axis 6356.752 km
Semi-major axis: 6378.137 km, Semi-minor axis 6356.752 km
Semi-major axis: 6378.137 km, Semi-minor axis 6356.752 km
From PLP Ion Trap
From PLP Ion Trap
Difference in geographic longitude between solar and satellite subpoints
From PLP Surface Probe swept bias mode
The DC vector magnetometer on the CNOFS spacecraft is a three axis, fluxgate sensor with active thermal control situated on a 0.6m boom. This magnetometer measures the Earth's magnetic field using 16 bit A/D converters at 1 sample per sec with a range of .. 45,000 nT. Its primary objective on the CNOFS spacecraft is to enable an accurate V x B measurement along the spacecraft trajectory. In order to provide an in-flight calibration of the magnetic field data, we compare the most recent POMME model (the POtsdam Magnetic Model of the Earth, http://geomag.org/models/pomme5.html) with the actual magnetometer measurements to help determine a set of calibration parameters for the gains, offsets, and non-orthogonality matrix of the sensor axes. The calibrated magnetic field measurements are provided in the data file here. The VEFI magnetic field data file currently contains the following variables: B_north Magnetic field in the north direction B_up Magnetic field in the up direction B_west Magnetic field in the west direction The data is PRELIMINARY, and as such, is intended for BROWSE PURPOSES ONLY. Registering your email will allow notification of updates.
Version 1.0 of the VEFI B field template.
Spherical coordinate system
Spherical coordinate system
Spherical coordinate system.
If B_flag=0, actual data.If B_flag=1, interpolated data
Geodetic altitude with respect to the WGS-84 earth model.
Geodetic latitude with respect to the WGS-84 earth model.
Geodetic longitude with respect to the WGS-84 earth model.
This data file contains information on the electric field solution as processed by the VEFI team at NASA/Goddard Space Flight Center. The data is PRELIMINARY, and as such, is intended for BROWSE PURPOSES ONLY. Registering your email will allow notification of updates.
Version 1.0 of the VEFI E field template.
Meridional direction is defined by ZxB, where Z is the zonal vector direction and B is the local magnetic field vector.
Zonal direction is defined by Bxr, where B is the local magnetic field vector and r is the radius vector from the center of the earth to the spacecraft. Sign convention is that eastward is positive.
Meridional direction is defined by ZxB, where Z is the zonal vector direction and B is the local magnetic field vector.
Zonal direction is defined by Bxr, where B is the local magnetic field vector and r is the radius vector from the center of the earth to the spacecraft. Sign convention is that eastward is positive.
Geodetic altitude with respect to the WGS-84 earth model.
Geodetic latitude with respect to the WGS-84 earth model.
Geodetic longitude with respect to the WGS-84 earth model.
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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No TEXT global attribute value.
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0 or 1 :good 2 or 3: averaging over several data points is recommended 4 or 5: data are unreliable
0 or 1 :good 2 or 3: averaging over several data points is recommended 4 or 5: data are unreliable
0-1: Ni < 2.E4 cm-3 velocity measurements are good; 2-3: 2.0E4 > Ni > 7.0E3 cm-3 averaging several data points is recommended; 4-5: Ni < 7.0E3 cm-3 data are unreliable.
0-1: Ni < 2.E4 cm-3 velocity measurements are good; 2-3: 2.0E4 > Ni > 7.0E3 cm-3 averaging several data points is recommended; 4-5: Ni < 7.0E3 cm-3 data are unreliable.
If the digit is even then the velocity was measured along the z-axis in spacecraft coordinates (approximately horizontal). If odd the direction is along the spacecraft y-axis (approximately vertical; positive for upward velocity) (y).
If the digit is even then the velocity was measured along the z-axis in spacecraft coordinates (approximately horizontal). If odd the direction is along the spacecraft y-axis (approximately vertical; positive for upward velocity) (y).
No TEXT global attribute value.
Velocity is given in spacecraft coordinates. The vertical component (Mode=5,6) is positiv in the Y-axis direction.
Density of N2 (Mass=28) or O+O2 (Mass=32); negative values should beignored.
Velocity is given in spacecraft coordinates. The horizontal component (Mode=3,4) is direction.
Velocity is given in spacecraft coordinates. The horizontal component (Mode=3,4) is positiv in the Z-axis direction. The vertical component (Mode=5,6) is positiv in the Y-axis direction.
Usually 28 or 32 (32 is assume to be mostly atomic oxygen which is recombined in the instrument)
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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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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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.
Minute averaged definitiveinterplanetary parameters data
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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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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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No TEXT global attribute value.
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
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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The IGS global system of satellite tracking stations, Data Centers, and Analysis
Centers puts high-quality GPS data and data products on line in near real time
to meet the objectives of a wide range of scientific and engineering
applications and studies. The IGS collects, archives, and distributes GPS
observation data sets of sufficient accuracy to satisfy the objectives of a wide
range of applications and experimentation. These data sets are used by the IGS
to generate the data products mentioned above which are made available to
interested users through the Internet. In particular, the accuracies of IGS
products are sufficient for the improvement and extension of the International
Terrestrial Reference Frame (ITRF), the monitoring of solid Earth deformations,
the monitoring of Earth rotation and variations in the liquid Earth (sea level,
ice-sheets, etc.), for scientific satellite orbit determinations, ionosphere
monitoring, and recovery of precipitable water vapor measurements.
The primary mission of the International GPS Service, as stated in the
organization's 2002-2007 Strategic Plan, is
The International GPS Service is committed to providing the highest quality
data and products as the standard for global navigation satellite systems (GNSS)
in support of Earth science research, multidisciplinary applications, and
education. These activities aim to advance scientific understanding of the Earth
system components and their interactions, as well as to facilitate other
applications benefiting society.
The IGS Terms of Reference (comparable to the by-laws of the organization)
describes in broad terms the goals and organization of the IGS. To accomplish
its mission, the IGS has a number of components: an international network of
over 350 continuously operating dual-frequency GPS stations, more than a dozen
regional and operational data centers, three global data centers, seven analysis
centers and a number of associate or regional analysis centers. The Central
Bureau for the service is located at the Jet Propulsion Laboratory, which
maintains the Central Bureau Information System (CBIS) and ensures access to IGS
products and information. An international Governing Board oversees all aspects
of the IGS. The IGS is an approved service of the International Association of
Geodesy since 1994 and is recognized as a member of the Federation of
Astronomical and Geophysical Data Analysis Services (FAGS) since 1996.
The IGS collects, archives, and distributes GPS observation data sets of
sufficient accuracy to meet the objectives of a wide range of scientific and
engineering applications and studies. These data sets are used to generate the
following products:
* GPS satellite ephemerides
* GLONASS satellite ephemerides
* Earth rotation parameters
* IGS tracking station coordinates and velocities
* GPS satellite and IGS tracking station clock information
* Zenith tropospheric path delay estimates
* Global ionospheric maps
IGS products support scientific activities such as improving and extending the
International Earth Rotation Service (IERS) Terrestrial Reference Frame (ITRF),
monitoring deformations of the solid Earth and variations in the liquid Earth
(sea level, ice sheets, etc.), and in Earth rotation, determining orbits of
scientific satellites and monitoring the ionosphere. For example, geodynamics
investigators who use GPS in local regions can include data from one or more
nearby IGS stations, fix the site coordinates from such stations to their ITRF
values, and more importantly, use the precise IGS orbits without further
refinement. Data from an investigator's local network can then be analyzed with
maximum accuracy and minimum computational burden. Furthermore, the results will
be in a well-defined global reference frame. An additional aspect of IGS
products is for the densification of the ITRF at a more regional level. This is
accomplished through the rigorous combination of regional or local network
solutions utilizing the Solution Independent Exchange Format (SINEX) and a
process defined in the densification section. In the future, the IGS
infrastructure could become a valuable asset for support of new ground-based
applications -- and could also contribute to space-based missions in which
highly accurate flight and ground differential techniques are required.
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This dataset contains high resolution interplanetary magnetic field data in six-second averages as measured by the Helios 1 tri-axial fluxgate magnetometer experiment. Magnetic field vector components in nanotelsa [nT] are given in solar-ecliptic (SE) spacecraft-centered coordinates with one file for each day. The magnetic field magnitude and standard deviations of the vector components are also included.
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This dataset contains high resolution interplanetary magnetic field data in six-second averages as measured by the Helios 1 tri-axial fluxgate magnetometer experiment. Magnetic field vector components in nanotelsa [nT] are given in solar-ecliptic (SE) spacecraft-centered coordinates with one file for each day. The magnetic field magnitude and standard deviations of the vector components are also included.
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The HELIOS-1 spacecraft was one of the pair of deep space probes developed by the Federal Republic of Germany (FRG) in a cooperative program with NASA. The purpose of the mission was to make pioneering measurements of the interplanetary medium from the vicinity of the Earth's orbit to 0.3 AU. (The planet Mercury is at 0.4 AU.) Data coverage for selected parameters for this data set is: interplanetary magnetic field (1974-12-14 - 1981-06-14), solar wind plasma (1974-12-12 - 1980-12-31), and spacecraft trajectory coordinates (1974-12-10 - 1981-06-14). Magnetic field data were provided by Prof. F. Mariani, Istituto di Fisica G. Marconi, Rome, Italy; Plasma data - by Dr. R. Schwenn, Max-Planck-Institut fur Aeronomie, Lindau, Germany. Time Coverage of merged files: December 10, 1974 - June 14, 1981. Helios-1 data have been reprocessed to ensure a uniformity of content and coordinate systems relative to data from other deep-space missions: All spacecraft trajectory data were transformed to a Heliographic Inertial (HGI) coordinate system. Magnetic field components were transformed to RTN system. Trajectory data, interplanetary magnetic field data, and plasma data were merged into individual hourly records. Data gaps were filled with dummy numbers for the missing hours or entire days to make all files of equal length. The character '9' is used to fill all fields for missing data according to their format, e.g. ' 9999.9' for a field with the FORTRAN format F7.1. Note that format F7.1 below really means (1X,F6.1),etc.
Seen by an Earth based observer at the start of the data interval
The HELIOS-1 spacecraft was one of the pair of deep space probes developed by the Federal Republic of Germany (FRG) in a cooperative program with NASA. The purpose of the mission was to make pioneering measurements of the interplanetary medium from the vicinity of the Earth's orbit to 0.3 AU. (The planet Mercury is at 0.4 AU.) Data coverage for selected parameters for this data set is: interplanetary magnetic field (1976-01-18 - 1980-03-04), solar wind plasma (1976-01-18 - 1980-03-04), and spacecraft trajectory coordinates (1976-01-18 - 1980-03-04). Magnetic field data were provided by Prof. F. Mariani, Istituto di Fisica G. Marconi, Rome, Italy; Plasma data - by Dr. R. Schwenn, Max-Planck-Institut fur Aeronomie, Lindau, Germany. Time Coverage of merged files: January 1, 1976 - March 4, 1980. Helios-2 data have been reprocessed to ensure a uniformity of content and coordinate systems relative to data from other deep-space missions: All spacecraft trajectory data were transformed to a Heliographic Inertial (HGI) coordinate system. Magnetic field components were transformed to RTN system. Trajectory data, interplanetary magnetic field data, and plasma data were merged into individual hourly records. Data gaps were filled with dummy numbers for the missing hours or entire days to make all files of equal length. The character '9' is used to fill all fields for missing data according to their format, e.g. ' 9999.9' for a field with the FORTRAN format F7.1. Note that format F7.1 below really means (1X,F6.1),etc.
Seen by an Earth based observer at the start of the data interval
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
This variable could be used as x-axis on amplitude spectrograms if fixed part is subtracted.
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 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 data set, provided by the Communications Research Centre (CRC) in Ottawa, Canada, consists of electron density profiles for the ionosphere above the F2 maximum (topside ionosphere). The data were computed from the orginal ionograms using Jackson's method (Jackson, Proceedings of the IEEE., p. 960, June 1969). ISIS-1 was launched on 1969-01-30 into an elliptical orbit (500-3500km) with an inclination of 88.4 degrees and ISIS-2 was launched on 1971-04-01 into an circular orbit at 1400 km with an inclination of 88.1 degrees. Both satellites were fully instrumented ionospheric observatories including sweep- and fixed-frequequency ionosondes, a VLF receiver, energetic and soft particle detectors, an ion mass spectrometer, an electrostatic analyzer, an Langmuir probe, a beacon transmitter, a cosmic noise experiment and ISIS 2 also carried two photometers. A tape recorder with 1-h capacity was included on both satellites. Data were also collected during overflights of several telemetry stations. The telemetry stations were in areas that provided primary data coverage near the 80-deg-W meridian and in areas near Hawaii, Singapore, Australia, the UK, Norway, India, Japan, Antarctica, New Zealand, and Central Africa.
Added to try to enable plots.
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
ISIS 2 was an ionospheric observatory instrumented with a sweep- and a fixed-frequency ionosonde, a VLF receiver, energetic and soft particle detectors, an ion mass spectrometer, an electrostatic probe, a retarding potential analyzer, a beacon transmitter, a cosmic noise experiment, and two photometers. Two long crossed-dipole antennas (73 and 18.7 m) were used for the sounding, VLF, and cosmic noise experiments. The spacecraft was spin-stabilized to about 2 rpm after antenna deployment. There were two basic orientation modes for the spacecraft, cartwheel and orbit-aligned. The spacecraft operated approximately the same length of time in each mode, remaining in one mode typically 3 to 5 months. The cartwheel mode with the axis perpendicular to the orbit plane was made available to provide ram and wake data for some experiments for each spin period, rather than for each orbit period. Attitude and spin information was obtained from a three-axis magnetometer and a sun sensor. Control of attitude and spin was possible by means of magnetic torquing. The experiment package also included a programmable tape recorder with a one hour capacity. For non-recorded observations, data from satellite and subsatellite regions were telemetered when the spacecraft was in the line of sight of a telemetry station. Telemetry stations were located so that primary data coverage was near the 80-deg-W meridian and near Hawaii, Singapore, Australia, England, France, Norway, India, Japan, Antarctica, New Zealand, and Central Africa. NASA support of the ISIS project was terminated on October 1, 1979. A significant amount of experimental data, however, was acquired after this date by the Canadian project team. ISIS 2 operations were terminated in Canada on March 9, 1984. The Radio Research Laboratories (Tokyo, Japan) then requested and received permission to reactivate ISIS 2. Regular ISIS 2 operations were started from Kashima, Japan, in early August 1984. ISIS 2 was deactivated effective 24, 1990. A data restoration effort began in the late 1990s and successfully saved a considerable portion of the high-resolution data before the telemetry tapes were discarted. The data set was generated from the averaged ionogram binary data (SPIO-00318) recorded by the Topside Sounder. The data are obtained with the TOPIST program, which analyzes the data, automatically scales the ionogram traces and resonances, and inverts the traces into an electron density profile. The same program is available for use to hand-scale the data if desired. Output data items include spacecraft position, electron density profile, assessment of quality, resonance and cut-off frequencies, and both the O-trace and X-trace.
mjd.time mjd - Modified Julian Date JULDAY(Month, Day, Year)-2400001L time - time converted to fraction of day (12h = 0.5d) 1.1.1990 12h : ut=47892.5d0)
This data set, provided by the Communications Research Centre (CRC) in Ottawa, Canada, consists of electron density profiles for the ionosphere above the F2 maximum (topside ionosphere). The data were computed from the orginal ionograms using Jackson's method (Jackson, Proceedings of the IEEE., p. 960, June 1969). ISIS-1 was launched on 1969-01-30 into an elliptical orbit (500-3500km) with an inclination of 88.4 degrees and ISIS-2 was launched on 1971-04-01 into an circular orbit at 1400 km with an inclination of 88.1 degrees. Both satellites were fully instrumented ionospheric observatories including sweep- and fixed-frequequency ionosondes, a VLF receiver, energetic and soft particle detectors, an ion mass spectrometer, an electrostatic analyzer, an Langmuir probe, a beacon transmitter, a cosmic noise experiment and ISIS 2 also carried two photometers. A tape recorder with 1-h capacity was included on both satellites. Data were also collected during overflights of several telemetry stations. The telemetry stations were in areas that provided primary data coverage near the 80-deg-W meridian and in areas near Hawaii, Singapore, Australia, the UK, Norway, India, Japan, Antarctica, New Zealand, and Central Africa.
Added to try to enable plots.
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
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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
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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
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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
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TBD
TBD
valid codes 1-16
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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
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Pre-generated PWG plots
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This enhanced CDF master was generated by NSSDC, with input from R. Fitzenreiter and A. F.-Vinas, to make useable a bare-bones CDF data set provided earlier to NSSDC. This current CDF master version, Oct. 5, 2007, is used for making a new CDF by selecting only certain variables from those available in the original bare-bones CDF (SPHE-00414).
Velocity units were changed to km/sec, and Hi, Mid, & Lowest energy channels above SC potential were change from velocity to the corresponding energy value in eV..
Electron Temperatue is 1/3 trace of diagonalized pressure tensor. Electron Temperature = (1/3) (parallel temp + two perpendicular eigenvalues)
Electron density is obtained 6 times during a spacecraft spin period. The six measurements are separately averaged to make the six elements of this array. We still need to know the delta t from Epoch to the first of these 6 densities.
Active Harvey experiment causes spikes in electron data.
Highest is channel 1, lowest is given by value of variable INSET, and mid is given by (INSET+1)/2, dropping any remainder.
Active Mozer experiment cause spikes in elecgtron data.
Norm. Gytotropy made by dividing by Electron Temperature
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