2.0.1 spase://vspo/displayData/P_CLUSTER_HDR_EDI_PLOTS Cluster EDI Survey Plots 2007-06-01T00:00:00 Cluster EDI high resolution survey plots, 3 hours/plot, mostly from Cluster 3, electron drift velocities, fluxes, anisotropies spase://SMWG/Person/Goetz.Paschmann GeneralContact spase://SMWG/Person/Jack.M.Quinn GeneralContact spase://SMWG/Repository/UNH Online Open EDI server at UNH http://ediweb.sr.unh.edu/hi_res.html PNG CALIBRATED spase://SMWG/Instrument/Cluster2-Rumba/EDI spase://SMWG/Instrument/Cluster2-Salsa/EDI spase://SMWG/Instrument/Cluster2-Samba/EDI ElectricField ThermalPlasma 2001-12-01T00:00:00 -P6M As of February, 2006, the plots were about 6 months behind current Earth.Magnetosphere spase://SMWG/Observatory/Cluster2-Rumba Cluster 2/FM5 (Rumba) 2000-045A FM5 Rumba Cluster-1 2009-05-20T20:00:12Z This Cluster II spacecraft, FM5 (Rumba), is also known as Phoenix, after a mythical Arabian bird which was burnt on a funeral pile and then rose from the ashes to live again. The original Cluster of four spacecraft experienced a launch failure in 1996. (NSSDC will carry the name "Cluster96" in its information files to designate the unsuccessful 1996 four-spacecraft Ariane 5 launch.) Phoenix was approved in July 1996 as a replacement for the lost four-spacecraft group. It was later (April 1997) agreed that the potential science return from a full Cluster reflight was so important that a further three near-replicas of the original spacecraft would also be built. This Cluster II spacecraft, FM5 (Rumba), was launched together with FM8 (Tango) by a Soyuz-Fregat rocket from Baikonur. The four similar spacecraft of the Cluster II mission are part of ESA's and NASA's Solar-Terrestrial Science Program (STSP). The purpose of the Cluster II mission is to study small-scale structures in three dimensions in the Earth's plasma environment, such as those involved in the interaction between the solar wind and the magnetospheric plasma, in global magnetotail dynamics, in cross-tail currents, and in the formation and dynamics of the neutral line and of plasmoids. The four Cluster II spacecraft will orbit in a tetrahedral formation in near-polar orbits of nominally 4 x 19.6 Earth radii, with period about 57 hours, and inclination about 90.7 degrees. Relative distances between the spacecraft will be adjusted in the course of the mission, depending on the spatial scales of the structures to be studied, varying from a few hundred km to a few Earth radii. The tetrahedral formation is essential for making three-dimensional measurements and for determining the curl of vectorial quantities such as the magnetic field. The orbits of all four spacecraft will be frequently maneuvered so as to achieve the targeted investigations. See http://jsoc1.bnsc.rl.ac.uk/pub/PlanningData.html for ongoing updates of orbital information and other status. Each spacecraft will be spin-stabilized, normally at around 15 rpm, and will be cylindrical in shape, with a 2.9-m diameter and 1.3-m length. It will have two rigid 5-m radial experiment booms, four 50-m experiment wire booms, and two axial telecommunications antenna booms. Telemetry downlink bit rate will be 2 to 262 kbit/s. Each spacecraft will have AC and DC magnetometers, an electric fields and waves sensor, an electron emitter/detector, an electron density sounder, electron and ion plasma analysers, an energetic particle detector, an ion emitter, and a data processing unit. Cluster operations will be performed by ESOC in Darmstadt, Germany, with support from NASA's Deep Space Network. Cluster is also an IACG mission. The scientific data are distributed by ESOC using CD-ROM as a medium to the Principal Investigators, Co-Investigators and the network of eight national data centres (6 in Europe, 1 in USA and 1 in China) that form the Cluster Science Data System (CSDS). There are approximately 80 recipients world-wide. Science operations are carried out by the Joint Science Operations Centre, co-located with the UK data centre at RAL, Didcot. A wide scientific community will have differing rights of access to the Cluster data. Scientists wishing to access Cluster data should contact their national Data Centres. The Cluster Summary Parameters are publicly available on CDAWeb at http://cdaweb.gsfc.nasa.gov/cdaweb/istp_public and the Prime Parameters are available on CDAWeb at http://cdaweb.gsfc.nasa.gov/cdaweb/ to project personnel (password-protected). See the Cluster II WWW site at http://sci.esa.int/cluster/ for more information, including spacecraft and exprient status. An article on 'The Resurrection of the Cluster Scientific Mission' was published in ESA Bulletin no. 91 (August 1997). A complete overview of the original mission, written before the loss with Ariane-5, was given in a series of articles in ESA Bulletin no. 84 (November 1995). ESA SP-1159, Paris, March 1993 is entitled "Cluster: Mission, Payload and Supporting Activities." spase://SMWG/Person/Melvyn.L.Goldstein ProjectScientist NSSDC's Master Catalog http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=2000-045A Information about the Cluster 2/FM5 (Rumba) mission CLUSTER Heliosphere.NearEarth spase://SMWG/Observatory/Cluster2-Salsa Cluster 2/FM6 (Salsa) 2000-041B FM6 Salsa Cluster-2 2009-05-20T20:00:12Z This Cluster II spacecraft, FM6 (Salsa), was launched together with FM7 (Samba) by a Soyuz-Fregat rocket from Baikonur. The four similar spacecraft of the Cluster II mission are part of ESA's and NASA's Solar-Terrestrial Science Program (STSP). The current Cluster II mission is a near-replica of the original four-spacecraft mission lost at launch in 1996. (NSSDC will carry the name "Cluster96" in its information files to designate the unsuccessful 1996 four-spacecraft Ariane 5 launch.) The purpose of the Cluster II mission is to study small-scale structures in three dimensions in the Earth's plasma environment, such as those involved in the interaction between the solar wind and the magnetospheric plasma, in global magnetotail dynamics, in cross-tail currents, and in the formation and dynamics of the neutral line and of plasmoids. The four Cluster II spacecraft will orbit in a tetrahedral formation in near-polar orbits of nominally 4 x 19.6 Earth radii, with period about 57 hours, and inclination about 90.7 degrees. Relative distances between the spacecraft will be adjusted in the course of the mission, depending on the spatial scales of the structures to be studied, varying from a few hundred km to a few Earth radii. The tetrahedral formation is essential for making three-dimensional measurements and for determining the curl of vectorial quantities such as the magnetic field. The orbits of all four spacecraft will be frequently maneuvered so as to achieve the targeted investigations. See http://jsoc1.bnsc.rl.ac.uk/pub/PlanningData.html for ongoing updates of orbital information and other status. Each spacecraft will be spin-stabilized, normally at around 15 rpm, and will be cylindrical in shape, with a 2.9-m diameter and 1.3-m length. It will have two rigid 5-m radial experiment booms, four 50-m experiment wire booms, and two axial telecommunications antenna booms. Telemetry downlink bit rate will be 2 to 262 kbit/s. Each spacecraft will have AC and DC magnetometers, an electric fields and waves sensor, an electron emitter/detector, an electron density sounder, electron and ion plasma analysers, an energetic particle detector, an ion emitter, and a data processing unit. Cluster operations will be performed by ESOC in Darmstadt, Germany, with support from NASA's Deep Space Network. Cluster is also an IACG mission. The scientific data are distributed by ESOC using CD-ROM as a medium to the Principal Investigators, Co-Investigators and the network of eight national data centres (6 in Europe, 1 in USA and 1 in China) that form the Cluster Science Data System (CSDS). There are approximately 80 recipients world-wide. Science operations are carried out by the Joint Science Operations Centre, co-located with the UK data centre at RAL, Didcot. A wide scientific community will have differing rights of access to the Cluster data. Scientists wishing to access Cluster data should contact their national Data Centres. The Cluster Summary Parameters are publicly available on CDAWeb at http://cdaweb.gsfc.nasa.gov/cdaweb/istp_public and the Prime Parameters are available on CDAWeb at http://cdaweb.gsfc.nasa.gov/cdaweb/ to project personnel (password-protected). See the Cluster II WWW site at http://sci.esa.int/cluster/ for more information, iincluding status of spacecraft and instruments. An article on 'The Resurrection of the Cluster Scientific Mission' was published in ESA Bulletin no. 91 (August 1997). A complete overview of the original mission, written before the loss with Ariane-5, was given in a series of articles in ESA Bulletin no. 84 (November 1995). ESA SP-1159, Paris, March 1993 is entitled "Cluster: Mission, Payload and Supporting Activities." spase://SMWG/Person/Melvyn.L.Goldstein ProjectScientist NSSDC's Master Catalog http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=2000-041B Information about the Cluster 2/FM6 (Salsa) mission CLUSTER Earth.Magnetosheath Earth.Magnetosphere.Main Earth.Magnetosphere.Polar spase://SMWG/Observatory/Cluster2-Samba Cluster 2/FM7 (Samba) 2000-041A FM7 Samba Cluster-3 2009-05-20T20:00:12Z This Cluster II spacecraft, FM7 (Samba), was launched together with FM6 (Salsa) by a Soyuz-Fregat rocket from Baikonur. The four similar spacecraft of the Cluster II mission are part of ESA's and NASA's Solar-Terrestrial Science Program (STSP). The current Cluster II mission is a near-replica of the original four-spacecraft mission lost at launch in 1996. (NSSDC will carry the name "Cluster96" in its information files to designate the unsuccessful 1996 four-spacecraft Ariane 5 launch.) The purpose of the Cluster II mission is to study small-scale structures in three dimensions in the Earth's plasma environment, such as those involved in the interaction between the solar wind and the magnetospheric plasma, in global magnetotail dynamics, in cross-tail currents, and in the formation and dynamics of the neutral line and of plasmoids. The four Cluster II spacecraft will orbit in a tetrahedral formation in near-polar orbits of nominally 4 x 19.6 Earth radii, with period about 57 hours, and inclination about 90.7 degrees.. Relative distances between the spacecraft will be adjusted in the course of the mission, depending on the spatial scales of the structures to be studied, varying from a few hundred km to a few Earth radii. The tetrahedral formation is essential for making three-dimensional measurements and for determining the curl of vectorial quantities such as the magnetic field. The orbits of all four spacecraft will be frequently maneuvered so as to achieve the targeted investigations. See http://jsoc1.bnsc.rl.ac.uk/pub/PlanningData.html for ongoing updates of orbital information and other status. Each spacecraft will be spin-stabilized, normally at around 15 rpm, and will be cylindrical in shape, with a 2.9-m diameter and 1.3-m length. It will have two rigid 5-m radial experiment booms, four 50-m experiment wire booms, and two axial telecommunications antenna booms. Telemetry downlink bit rate will be 2 to 262 kbit/s. Each spacecraft will have AC and DC magnetometers, an electric fields and waves sensor, an electron emitter/detector, an electron density sounder, electron and ion plasma analysers, an energetic particle detector, an ion emitter, and a data processing unit. Cluster operations will be performed by ESOC in Darmstadt, Germany, with support from NASA's Deep Space Network. Cluster is also an IACG mission. The scientific data are distributed by ESOC using CD-ROM as a medium to the Principal Investigators, Co-Investigators and the network of eight national data centres (6 in Europe, 1 in USA and 1 in China) that form the Cluster Science Data System (CSDS). There are approximately 80 recipients world-wide. Science operations are carried out by the Joint Science Operations Centre, co-located with the UK data centre at RAL, Didcot. A wide scientific community will have differing rights of access to the Cluster data. Scientists wishing to access Cluster data should contact their national Data Centres. The Cluster Summary Parameters are publicly available on CDAWeb at http://cdaweb.gsfc.nasa.gov/cdaweb/istp_public and the Prime Parameters are available on CDAWeb at http://cdaweb.gsfc.nasa.gov/cdaweb/ to project personnel (password-protected). See the Cluster II WWW site at http://sci.esa.int/cluster/ for more information, including status of the spacecraft and instruments. An article on 'The Resurrection of the Cluster Scientific Mission' was published in ESA Bulletin no. 91 (August 1997). A complete overview of the original mission, written before the loss with Ariane-5, was given in a series of articles in ESA Bulletin no. 84 (November 1995). ESA SP-1159, Paris, March 1993 is entitled "Cluster: Mission, Payload and Supporting Activities." spase://SMWG/Person/Melvyn.L.Goldstein ProjectScientist NSSDC's Master Catalog http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=2000-041A Information about the Cluster 2/FM7 (Samba) mission CLUSTER Earth.Magnetosphere.Main Earth.Magnetosheath Earth.Magnetosphere.Polar spase://SMWG/Instrument/Cluster2-Rumba/EDI Electron Drift Instrument (EDI) EDI 2009-05-20T21:10:10Z This instrument (EDI: Electron Drift Instrument) measures the drift of a weak beam of test electrons that, when emitted in certain directions, return to the spacecraft after one gyration. This drift is related to the electric field and the gradient in the magnetic field, and these quantities can, by the use of different electron energies, be determined separately. As a by-product, the magnetic field strength is also measured. Conventional tungsten cathode electron guns are used, with a beam steerable in any direction within more than a hemisphere. Each detector is axially symmetric and can cover more than 2 pi steradians. A large effective area is made possible by double focusing. Electron guns and detectors are combined in pairs into single gun/detector units (GDUs). Two GDUs are used, mounted on opposite sides of the spacecraft. The detector in each GDU detects the beam electrons from the gun in the other GDU. The emitted electron beam has a finite opening angle of approximately 1 degree. This beam spreads along the magnetic field, but perpendicular to the field the beam is focused after one gyration. To detect the beam electrons in the presence of ambient electrons, and to measure their flight time, the beam is modulated and coded. The modulation frequency can be chosen between 500 KHz and 4 MHz. The pulses received by the detectors, and the delayed format of the code, are then fed into a correlator. Its output will be different from noise only if the delay time equals the electron gyroperiod. The delay times are initialized on the basis of the on-board magnetometer data. The delay time will then drift with a selectable rate until the actual flight times are within the range of the correlators. An auto-track feature then keeps the beam electron counts in a single correlator channel. A second, different correlator scheme is also used, having the advantage that beam electrons are always counted in one of the channels, but the disadvantage that the flight time is not determined unambiguously. The fundamental time step to determine the new parameters and direct the beams and the detectors is 2 ms. In some modes, this can be lengthened, to accommodate tracking tasks that operate on longer time scales. Inter-experiment links include: magnetic field information from FGM and STAFF, a blanking pulse received from WHISPER to warn of possible interference from that active experiment, and a similar blanking pulse sent to PEACE when the EDI electron beam could interfere with the PEACE electron measurement. For more details of the Cluster mission, the spacecraft, and its instruments, see the report ``Cluster: mission, payload and supporting activities,'' March 1993, ESA SP-1159, and the included article ``The Electron Drift Instrument for Cluster,'' by G. Paschmann et al., from which this information was obtained. spase://SMWG/Person/Goetz.Paschmann PrincipalInvestigator NSSDC's Master Catalog http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=2000-045A&ex=3 Information about the Electron Drift Instrument (EDI) experiment on the Cluster 2/FM5 (Rumba) mission. ElectronDriftInstrument Electron Drift Instrument (EDI) on Cluster 2/FM5 (Rumba) spase://SMWG/Observatory/Cluster2-Rumba spase://SMWG/Instrument/Cluster2-Salsa/EDI Electron Drift Instrument (EDI) EDI 2009-05-20T21:10:16Z This instrument (EDI: Electron Drift Instrument) measures the drift of a weak beam of test electrons that, when emitted in certain directions, return to the spacecraft after one gyration. This drift is related to the electric field and the gradient in the magnetic field, and these quantities can, by the use of different electron energies, be determined separately. As a by-product, the magnetic field strength is also measured. Conventional tungsten cathode electron guns are used, with a beam steerable in any direction within more than a hemisphere. Each detector is axially symmetric and can cover more than 2 pi steradians. A large effective area is made possible by double focusing. Electron guns and detectors are combined in pairs into single gun/detector units (GDUs). Two GDUs are used, mounted on opposite sides of the spacecraft. The detector in each GDU detects the beam electrons from the gun in the other GDU. The emitted electron beam has a finite opening angle of approximately 1 degree. This beam spreads along the magnetic field, but perpendicular to the field the beam is focused after one gyration. To detect the beam electrons in the presence of ambient electrons, and to measure their flight time, the beam is modulated and coded. The modulation frequency can be chosen between 500 KHz and 4 MHz. The pulses received by the detectors, and the delayed format of the code, are then fed into a correlator. Its output will be different from noise only if the delay time equals the electron gyroperiod. The delay times are initialized on the basis of the on-board magnetometer data. The delay time will then drift with a selectable rate until the actual flight times are within the range of the correlators. An auto-track feature then keeps the beam electron counts in a single correlator channel. A second, different correlator scheme is also used, having the advantage that beam electrons are always counted in one of the channels, but the disadvantage that the flight time is not determined unambiguously. The fundamental time step to determine the new parameters and direct the beams and the detectors is 2 ms. In some modes, this can be lengthened, to accommodate tracking tasks that operate on longer time scales. Inter-experiment links include: magnetic field information from FGM and STAFF, a blanking pulse received from WHISPER to warn of possible interference from that active experiment, and a similar blanking pulse sent to PEACE when the EDI electron beam could interfere with the PEACE electron measurement. For more details of the Cluster mission, the spacecraft, and its instruments, see the report ``Cluster: mission, payload and supporting activities,'' March 1993, ESA SP-1159, and the included article ``The Electron Drift Instrument for Cluster,'' by G. Paschmann et al., from which this information was obtained. spase://SMWG/Person/Goetz.Paschmann PrincipalInvestigator NSSDC's Master Catalog http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=2000-041B&ex=3 Information about the Electron Drift Instrument (EDI) experiment on the Cluster 2/FM6 (Salsa) mission. ElectronDriftInstrument Electron Drift Instrument (EDI) on Cluster 2/FM6 (Salsa) spase://SMWG/Observatory/Cluster2-Salsa spase://SMWG/Instrument/Cluster2-Samba/EDI Electron Drift Instrument (EDI) EDI 2009-05-20T21:10:15Z This instrument (EDI: Electron Drift Instrument) measures the drift of a weak beam of test electrons that, when emitted in certain directions, return to the spacecraft after one gyration. This drift is related to the electric field and the gradient in the magnetic field, and these quantities can, by the use of different electron energies, be determined separately. As a by-product, the magnetic field strength is also measured. Conventional tungsten cathode electron guns are used, with a beam steerable in any direction within more than a hemisphere. Each detector is axially symmetric and can cover more than 2 pi steradians. A large effective area is made possible by double focusing. Electron guns and detectors are combined in pairs into single gun/detector units (GDUs). Two GDUs are used, mounted on opposite sides of the spacecraft. The detector in each GDU detects the beam electrons from the gun in the other GDU. The emitted electron beam has a finite opening angle of approximately 1 degree. This beam spreads along the magnetic field, but perpendicular to the field the beam is focused after one gyration. To detect the beam electrons in the presence of ambient electrons, and to measure their flight time, the beam is modulated and coded. The modulation frequency can be chosen between 500 KHz and 4 MHz. The pulses received by the detectors, and the delayed format of the code, are then fed into a correlator. Its output will be different from noise only if the delay time equals the electron gyroperiod. The delay times are initialized on the basis of the on-board magnetometer data. The delay time will then drift with a selectable rate until the actual flight times are within the range of the correlators. An auto-track feature then keeps the beam electron counts in a single correlator channel. A second, different correlator scheme is also used, having the advantage that beam electrons are always counted in one of the channels, but the disadvantage that the flight time is not determined unambiguously. The fundamental time step to determine the new parameters and direct the beams and the detectors is 2 ms. In some modes, this can be lengthened, to accommodate tracking tasks that operate on longer time scales. Inter-experiment links include: magnetic field information from FGM and STAFF, a blanking pulse received from WHISPER to warn of possible interference from that active experiment, and a similar blanking pulse sent to PEACE when the EDI electron beam could interfere with the PEACE electron measurement. For more details of the Cluster mission, the spacecraft, and its instruments, see the report ``Cluster: mission, payload and supporting activities,'' March 1993, ESA SP-1159, and the included article ``The Electron Drift Instrument for Cluster,'' by G. Paschmann et al., from which this information was obtained. spase://SMWG/Person/Goetz.Paschmann PrincipalInvestigator NSSDC's Master Catalog http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=2000-041A&ex=3 Information about the Electron Drift Instrument (EDI) experiment on the Cluster 2/FM7 (Samba) mission. ElectronDriftInstrument Electron Drift Instrument (EDI) on Cluster 2/FM7 (Samba) spase://SMWG/Observatory/Cluster2-Samba spase://SMWG/Repository/UNH UNH 2008-06-18T18:05:57Z spase://SMWG/Person/UNKNOWN GeneralContact spase://SMWG/Person/Melvyn.L.Goldstein 1999-08-18T00:00:00Z Dr. Melvyn L. Goldstein GSFC-Code 692 melvyn.l.goldstein@nasa.gov +1-301-286-7828 spase://SMWG/Person/UNKNOWN 1999-01-01T00:00:00Z UNKNOWN UNKNOWN spase://SMWG/Person/Goetz.Paschmann 2007-08-17T21:41:20Z Goetz Paschmann Max Planck Institut fur Extraterrestrische Physik, Garching, Germany gep@mpe.mpg.de spase://SMWG/Person/Jack.M.Quinn Dr. Jack M. Quinn University of New Hampshire