CDPP / CNES

Commit 1544e7732140d37af126d9ba94526c555ce00d57

Authored by Elena.Budnik
1 parent 8f30a2b3
Exists in master and in 12 other branches amdadev, aschulz, autocommit, bepi_master, bepi_update, branch_q, cleanup_registry, cleanup_registry_master, cleanup_registry_merged, juice_jdc, juno_jade, soar

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Showing 21 changed files with 229 additions and 61 deletions   Show diff stats
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NumericalData/AMDA/ACE/MFI/ace-imf-all.xml
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58 58 <TemporalDescription>
59 59 <TimeSpan>
60 60 <StartDate>1997-09-02T00:00:12Z</StartDate>
61   - <StopDate>2016-09-17T23:59:54Z</StopDate>
  61 + <StopDate>2016-09-24T23:59:53Z</StopDate>
62 62 </TimeSpan>
63 63 <Cadence>PT16S</Cadence>
64 64 </TemporalDescription>
... ...
NumericalData/AMDA/ACE/MFI/ace-mag-real.xml
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... ... @@ -51,7 +51,7 @@
51 51 <TemporalDescription>
52 52 <TimeSpan>
53 53 <StartDate>2014-01-06T00:00:00Z</StartDate>
54   - <StopDate>2016-09-25T23:59:59Z</StopDate>
  54 + <StopDate>2016-10-05T23:59:59Z</StopDate>
55 55 </TimeSpan>
56 56 <Cadence>PT60S</Cadence>
57 57 </TemporalDescription>
... ...
NumericalData/AMDA/ACE/SWEPAM/ace-swe-all.xml
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... ... @@ -59,7 +59,7 @@
59 59 <TemporalDescription>
60 60 <TimeSpan>
61 61 <StartDate>1998-02-04T00:00:31Z</StartDate>
62   - <StopDate>2016-03-29T23:59:27Z</StopDate>
  62 + <StopDate>2016-04-25T23:59:23Z</StopDate>
63 63 </TimeSpan>
64 64 <Cadence>PT64S</Cadence>
65 65 </TemporalDescription>
... ...
NumericalData/AMDA/ACE/SWEPAM/ace-swepam-real.xml
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... ... @@ -44,7 +44,7 @@
44 44 <TemporalDescription>
45 45 <TimeSpan>
46 46 <StartDate>2014-01-06T00:00:00Z</StartDate>
47   - <StopDate>2016-09-25T23:59:59Z</StopDate>
  47 + <StopDate>2016-10-05T23:59:59Z</StopDate>
48 48 </TimeSpan>
49 49 <Cadence>PT60S</Cadence>
50 50 </TemporalDescription>
... ...
NumericalData/AMDA/ACE/SWEPAM/ace-swp-all.xml
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... ... @@ -59,7 +59,7 @@
59 59 <TemporalDescription>
60 60 <TimeSpan>
61 61 <StartDate>2001-01-01T00:00:00Z</StartDate>
62   - <StopDate>2016-09-17T23:55:00Z</StopDate>
  62 + <StopDate>2016-09-24T23:55:00Z</StopDate>
63 63 </TimeSpan>
64 64 <Cadence>PT5M</Cadence>
65 65 </TemporalDescription>
... ...
NumericalData/AMDA/ACE/ephemeris/ace-orb-all.xml
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... ... @@ -33,7 +33,7 @@
33 33 <TemporalDescription>
34 34 <TimeSpan>
35 35 <StartDate>1997-08-26T00:00:00Z</StartDate>
36   - <StopDate>2016-11-28T23:47:00Z</StopDate>
  36 + <StopDate>2016-12-19T23:47:00Z</StopDate>
37 37 </TimeSpan>
38 38 <Cadence>PT12M</Cadence>
39 39 </TemporalDescription>
... ...
NumericalData/AMDA/MEX/ELS/mex-els-all.xml
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... ... @@ -4,23 +4,23 @@
4 4 <NumericalData>
5 5 <ResourceID>spase://CDPP/NumericalData/AMDA/MEX/ELS/mex-els-all</ResourceID>
6 6 <ResourceHeader>
7   - <ResourceName>electron spectra</ResourceName>
8   - <ReleaseDate>2015-10-15T09:46:00</ReleaseDate>
9   - <Description>The data consist of fluxes of electrons at several tens (time-
10   -variable number) of energy steps in the 0.01-20keV energy range, in 16 look directions.
11   -The data are organized in csv ASCII format for spreadsheet usage. Any given
12   -spreadsheet may have hours of ~1-sec distributions from the low energy range or
13   -high energy range. Deflection voltages used, between 1.31 and 21 V or between 21
14   -and 2800 V are given in the data arrays, with conversion factors to transform to
15   -particle energy being given in documentation files. No spacecraft trajectory
16   -data are included in these Level 2, reduced data records but see
17   -http://www.rssd.esa.int/index.php?project=PSA&amp;page=ancillary. As of June 2012, these data were available for mid-2003 through Jun 2011, although for the 2003 cruise phase, a total of only several hours of data were generated and are available.</Description>
18   - <Acknowledgement>The Mars Express ASPERA team, R. Lundin, Swedish
  7 + <ResourceName>electron spectra : 16 anods</ResourceName>
  8 + <ReleaseDate>2016-10-15T09:46:00</ReleaseDate>
  9 + <Description>Level2 data. This dataset is generated directly from the MEX telemetry with IRAP software</Description>
  10 + <Acknowledgement>The Mars Express ASPERA team, S.Barabash, Swedish
19 11 Institute of Space Physics, PI, and the European Space Agency</Acknowledgement>
20 12 <Contact>
21   - <PersonID>spase://SMWG/Person/Rickard.Lundin</PersonID>
  13 + <PersonID>spase://SMWG/Person/Stas.Barabash</PersonID>
22 14 <Role>PrincipalInvestigator</Role>
23 15 </Contact>
  16 + <Contact>
  17 + <PersonID>spase://CDPP/Person/Rudy.Frahm</PersonID>
  18 + <Role>GeneralContact</Role>
  19 + </Contact>
  20 + <Contact>
  21 + <PersonID>spase://CDPP/Person/Elena.Budnik</PersonID>
  22 + <Role>TechnicalContact</Role>
  23 + </Contact>
24 24 <InformationURL>
25 25 <Name>Project-Archive Interface Control Document</Name>
26 26 <URL>http://pds-ppi.igpp.ucla.edu/search/view/?f=yes&amp;id=pds://PPI/MEXASP_1100/DOCUMENT/MEX_ASPERA3_PSA_ICD_V01_02</URL>
... ... @@ -33,28 +33,142 @@ Institute of Space Physics, PI, and the European Space Agency&lt;/Acknowledgement&gt;
33 33 <AccessURL>
34 34 <URL>http://amda.cdpp.eu</URL>
35 35 </AccessURL>
36   - <Format>NetCDF</Format>
  36 + <Format>Text</Format>
  37 + <Acknowledgement> AMDA is a science analysis system provided by the Centre de Donnees de la
  38 + Physique des Plasmas (CDPP) supported by CNRS, CNES, Observatoire de Paris and
  39 + Universite Paul Sabatier, Toulouse
  40 + </Acknowledgement>
37 41 </AccessInformation>
38 42 <ProviderName>IRAP</ProviderName>
39 43 <InstrumentID>spase://CDPP/Instrument/AMDA/MEX/ELS</InstrumentID>
40   - <MeasurementType>EnergeticParticles</MeasurementType>
  44 + <MeasurementType>ThermalPlasma</MeasurementType>
41 45 <TemporalDescription>
42 46 <TimeSpan>
43 47 <StartDate>2003-06-23T18:42:48Z</StartDate>
44   - <StopDate>2016-09-12T15:55:37Z</StopDate>
  48 + <StopDate>2016-09-25T03:10:42Z</StopDate>
45 49 </TimeSpan>
46   - <Cadence>PT4S</Cadence>
  50 + <Cadence_Min>PT1S</Cadence_Min>
  51 + <Cadence_Max>PT4S</Cadence_Max>
47 52 </TemporalDescription>
48 53 <ObservedRegion>Mars</ObservedRegion>
  54 + <Caveats>
  55 + * Concerning ELS NEV Data
  56 +
  57 +
  58 + Before 2003/190 (09 July 2003), operational engineering tests were being executed on the ELS instrument. Before 2100 hours on that date,
  59 +the ELS science data should be all zero (except for day 2003/183,
  60 +02 July 2003, between 0100 hours and 0200 hours). For all times other
  61 +than the 2003/183 (2003-07-02) time listed above, ELS was undergoing the
  62 +Near Earth Verification tests. These tests adjusted the ELS instrument
  63 +voltages and the ELS science data was monitored to be sure that the
  64 +science data were all zero. If ELS science data had not been zero, it
  65 +would have been an indication that there was something wrong with the
  66 +instrument. Thus, the zeroes in the ELS science data are normal and
  67 +expected during these times.
  68 +
  69 +The exception for day 2003/183 (02 July 2003) between 0100 hours and 0200 hours was when the deflection plates were not stepping and the
  70 +instrument voltages were increased such that a science signal could be seen. Since the ELS was not sweeping but held at a fixed value, there
  71 +should be science data only at one energy (although the numeric value for
  72 +each sector should be different). Science data values should show in all
  73 +sectors of ELS, not just in sector zero. Tests were to include sweeping
  74 +of the deflection plates at this time, but a small bug in the operations
  75 +software prevented sweeping. This was not fixed until after 2100 hours
  76 +on day 2003/190 (09 July 2003).
  77 +
  78 +
  79 + * Concerning ELS January 2004 Data:
  80 +
  81 + The Mars Express commissioning period for ASPERA-3 occurred in January 2004. Since operational engineering tests were being executed on the ELS instrument during this time, some of the ELS science data are all zeroes. The zeroes are normal and expected during January 5, 12, and 14, 2004. If the ELS science data had not been zero during these times, it would have been an indication that there was something wrong with the instrument.
  82 +
  83 + * Note on Noise Levels:
  84 +
  85 + The ELS sectors which view across the spacecraft and into the spacecraft
  86 +body measure electrons escaping the spacecraft either due to outgassing by
  87 +the spacecraft, emissions from the spacecraft surfaces, scattered primary
  88 +electrons reflected from the spacecraft, or secondary electrons that had
  89 +been absorbed and then re-emitted by the spacecraft. From launch until
  90 +about mid-2004, spacecraft outgassing is observed as an increase in the
  91 +background values to higher than normal levels in those sectors which view
  92 +across the spacecraft.
  93 + These background levels of each sector are known to vary in time. This
  94 +is caused when some ELS sectors view across the spacecraft or at spacecraft
  95 +objects. In launch configuration, ELS sectors 15, 14, 13, 12, 1, and 0
  96 +view over the spacecraft. In addition ELS sector 1 includes a spacecraft
  97 +sun sensor within its field of view, and ELS sector 13 views the spacecraft
  98 +solar array attachment arm. The ELS was in its launch configuration until
  99 +January 24, 2006 when the scanner platform was activated. After this date,
  100 +the angle which the scanner is rotated determines the degree of blockage by
  101 +the spacecraft for each sector.
  102 + The scanner angle is set at 90 deg for the launch configuration (this is
  103 +0 deg in the Unit Reference Frame). When the scanner rotates, it moves
  104 +toward the 0 deg position (+90 deg in the Unit Reference Frame). At this
  105 +time, ELS sectors 15, 14, 13, and part of sector 12 rotate to view the
  106 +spacecraft body. ELS sector 0 and 12 view across the spacecraft. The
  107 +scanner then rotates toward its 180 deg position (-90 deg in the Unit
  108 +Reference Frame) when active. As the scanner rotation passes the 90 deg
  109 +position, ELS sectors 0, 1, 2, and part of sector 3 view the spacecraft
  110 +body. ELS sector 15 and 3 view across the spacecraft.
  111 + It should also be noted that the relative calibration factors (relative
  112 +efficiency coefficients for Anode 13 in CALINFO.TXT) indicate that the
  113 +sensitivity of sector 13 is lower than the rest of the sectors by a factor
  114 +of about 2 or 3. A rough estimate of the orientation of the particle
  115 +entrance geometry to the MCP indicated that the electrons in this sector
  116 +penetrate deeper into the MCP chevron than the other sectors. This means
  117 +that there are fewer electrons generated by the MCP during the cascade
  118 +(electron multiplication) process. Thus, this intensity difference has
  119 +been compensated for by the relative calibration factors for this sector.
  120 +
  121 +
  122 + * Note on Artificial Peaks in Spectra:
  123 +
  124 + At about 150 eV, there is an artificial effect which is caused by the
  125 +transition between control states of the ELS power supplies. This
  126 +artificial effect appears as a peak, drifting in amplitude, shape, and
  127 +affected energy range. The artificial peak occurs because the controlling
  128 +signal to ELS exceeds its designed specifications and exhibits enough
  129 +drift so that the controlling voltage sent to ELS does not accurately
  130 +reflect the control voltage reported by the ASPERA-3 Main Unit. This
  131 +results in an error in the measurement energy which occurs at the lowest
  132 +control voltage (where the drift is a larger part of the control signal).
  133 +The flux measured at the expected energy is actually measured at a lower
  134 +energy than expected (where the flux is slightly higher). The region
  135 +affected by the artificial spike at about 150 eV rarely exceeds 200 eV.
  136 + The ELS stepping power supply has two ranges. The stepping voltage
  137 +value is controlled by an analog signal sent to ELS by the ASPERA-3 Main
  138 +Unit. The power supply range is controlled by a digital bit. ELS converts
  139 +the analog control voltage into a voltage across its deflection plates
  140 +which relates to the particle energy. Thus, an error in the control
  141 +voltage translates into an error in the particle energy.
  142 + ELS has a voltage monitor that reports every sample, but it is accessed
  143 +by the ASPERA-3 main unit only about every 32 sec. ELS was to use the
  144 +monitor value along with the science data value to correct for any drift
  145 +within the sweep voltage. Unfortunately due to telemetry restrictions,
  146 +a decision was made to not telemeter the step voltage monitor the same
  147 +time as the science data, so no correction can be determined between the
  148 +voltage monitor drift and the energy shift observed in the science data.
  149 + This same effect is likely to be hidden in the low range deflection,
  150 +below about 10 eV. Its existence and magnitude can not be accurately
  151 +assessed because the ASPERA-3 main unit does not sample the simultaneous
  152 +sweep, monitor, and science data for ELS. An artificial spike is noticed
  153 +at about 150 eV because any drift in the control voltage is a larger
  154 +fraction on the low voltage side of the high range and a smaller fractional
  155 +fluctuation on the higher voltage side of the low range. The ELS sweep is
  156 +a decay step from its highest voltage value to its lowest voltage. The
  157 +spike is seen by the observer because it is highlighted by the transition
  158 +between the sweep high range (larger fractional error) to the low range
  159 +(smaller fractional error). </Caveats>
49 160 <Parameter>
50 161 <Name>spectra</Name>
51 162 <ParameterKey>mex_els_spec</ParameterKey>
52   - <Description>Averaged energy-time spectrogram of electron counts</Description>
  163 + <Description>energy spectrogram of electron counts</Description>
53 164 <Ucd>phys.count;phys.electron</Ucd>
54 165 <Units>counts</Units>
55 166 <RenderingHints>
56 167 <DisplayType>Spectrogram</DisplayType>
57 168 </RenderingHints>
  169 + <Structure>
  170 + <Size>128</Size>
  171 + </Structure>
58 172 <Particle>
59 173 <ParticleType>Electron</ParticleType>
60 174 <ParticleQuantity>Counts</ParticleQuantity>
... ...
NumericalData/AMDA/MEX/IMA/mex-ima-extra.xml
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33 33 <TemporalDescription>
34 34 <TimeSpan>
35 35 <StartDate>2004-01-05T06:16:06Z</StartDate>
36   - <StopDate>2016-09-11T20:00:56Z</StopDate>
  36 + <StopDate>2016-09-24T23:29:49Z</StopDate>
37 37 </TimeSpan>
38 38 <Cadence>PT192S</Cadence>
39 39 </TemporalDescription>
... ...
NumericalData/AMDA/MEX/IMA/mex-ima-param.xml
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... ... @@ -27,7 +27,7 @@
27 27 <TemporalDescription>
28 28 <TimeSpan>
29 29 <StartDate>2004-06-26T19:37:50Z</StartDate>
30   - <StopDate>2016-09-11T20:04:07Z</StopDate>
  30 + <StopDate>2016-09-24T23:32:59Z</StopDate>
31 31 </TimeSpan>
32 32 <Cadence>PT192S</Cadence>
33 33 </TemporalDescription>
... ...
NumericalData/AMDA/MEX/ephemeris/mex-orb-all.xml
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... ... @@ -27,7 +27,7 @@
27 27 <TemporalDescription>
28 28 <TimeSpan>
29 29 <StartDate>2004-01-10T07:54:21Z</StartDate>
30   - <StopDate>2016-11-09T23:40:47Z</StopDate>
  30 + <StopDate>2016-11-21T01:30:23Z</StopDate>
31 31 </TimeSpan>
32 32 <Cadence>PT60S</Cadence>
33 33 </TemporalDescription>
... ...
NumericalData/AMDA/MGS/Proxy/mgs-proxy-drap.xml
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... ... @@ -4,7 +4,7 @@
4 4 <NumericalData>
5 5 <ResourceID>spase://CDPP/NumericalData/AMDA/MGS/PROXY/mgs-proxy-drap</ResourceID>
6 6 <ResourceHeader>
7   - <ResourceName>IMF draping direction</ResourceName>
  7 + <ResourceName>imf draping direction</ResourceName>
8 8 <ReleaseDate>2015-10-12T10:48:29Z</ReleaseDate>
9 9 <Description>Draping direction is calculated on an orbit-by-obit basis using MGS data from time periods when the spacecraft was above 50-60 N planetary latitude on the Martian dayside. We use this small latitude range in an attempt to minimize the contaminating effects of crustal magnetic fields, which are weakest in this latitude band. Draping direction is reported as the median azimuth angle from each orbit, with 0o pointing locally Eastward from the spacecraft, and 90o pointing locally Northward.
10 10  
... ... @@ -42,7 +42,7 @@ We have tried several other methods of determining draping direction - all have
42 42 <StopDate>2006-10-27T14:20:34Z</StopDate>
43 43 </TimeSpan>
44 44 <Cadence_Min>PT1H</Cadence_Min>
45   - <Cadence_Max>PT2H</Cadence_Max>
  45 + <Cadence_Max>PT2H</Cadence_Max>
46 46 </TemporalDescription>
47 47 <ObservedRegion>Mars</ObservedRegion>
48 48 <Caveats>
... ...
NumericalData/AMDA/MGS/Proxy/mgs-proxy-euv.xml
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... ... @@ -4,7 +4,8 @@
4 4 <NumericalData>
5 5 <ResourceID>spase://CDPP/NumericalData/AMDA/MGS/PROXY/mgs-proxy-euv</ResourceID>
6 6 <ResourceHeader>
7   - <ResourceName>EUV</ResourceName>
  7 + <ResourceName>euv</ResourceName>
  8 + <AlternateName>Extreme Ultraviolet Proxy</AlternateName>
8 9 <ReleaseDate>2015-10-12T10:48:29Z</ReleaseDate>
9 10 <Description>The F10.7 radio flux measured at Earth is used to estimate the solar EUV flux from 2-100 nm at Earth. These values are then scaled to Mars' orbital distance from the Sun using a 1/r2 scaling, and time-shifted to account for the solar longitude difference between the Earth and Sun. A 26-day solar rotation rate is assumed.
10 11 </Description>
... ...
NumericalData/AMDA/OMNI/omni-5min-all.xml
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... ... @@ -47,7 +47,7 @@ for creating the OMNI data set.&lt;/Acknowledgement&gt;
47 47 <TemporalDescription>
48 48 <TimeSpan>
49 49 <StartDate>1981-01-01T00:00:00Z</StartDate>
50   - <StopDate>2016-09-06T23:55:00Z</StopDate>
  50 + <StopDate>2016-09-26T23:55:00Z</StopDate>
51 51 </TimeSpan>
52 52 <Cadence>PT5M</Cadence>
53 53 </TemporalDescription>
... ...
NumericalData/AMDA/OMNI/omni-hour-all.xml
  Diff comments   View file @1544e77
... ... @@ -47,7 +47,7 @@ for creating the OMNI data set.&lt;/Acknowledgement&gt;
47 47 <TemporalDescription>
48 48 <TimeSpan>
49 49 <StartDate>1970-01-01T00:00:00Z</StartDate>
50   - <StopDate>2016-09-08T13:00:00Z</StopDate>
  50 + <StopDate>2016-09-27T14:00:00Z</StopDate>
51 51 </TimeSpan>
52 52 <Cadence>PT1H</Cadence>
53 53 </TemporalDescription>
... ...
Observatory/AMDA/Geotail.xml
  Diff comments   View file @1544e77
... ... @@ -10,13 +10,9 @@
10 10 <AlternateName>GTL</AlternateName>
11 11 <AlternateName>ISTP/Geotail</AlternateName>
12 12 <AlternateName>GGS/Geotail</AlternateName>
13   - <ReleaseDate>2010-08-05T18:19:18Z</ReleaseDate>
14   - <Description>The solar wind draws the Earth's magnetic field into a long tail on the nightside of the Earth and stores energy in the stretched field lines of the magnetotail. During active periods, the tail couples with the near-Earth magnetosphere, sometimes releasing energy stored in the tail and activating auroras in the polar ionosphere.
15   - The Geotail mission measures global energy flow and transformation in the magnetotail to increase understanding of fundamental magnetospheric processes. This includes the physics of the magnetopause magnetospheric boundary regions, the lobe and plasma sheet, and reconnection and neutral line formation, i.e., the mechanisms processes of input, transport, storage, release and conversion of mass, momentum and energy in the magnetotail.
16   - Geotail, together with Wind, Polar, SOHO, and Cluster projects, constitute a cooperative scientific satellite project designated the International Solar Terrestrial Physics (ISTP) program which aims at gaining improved understanding of the physics of solar-terrestrial relations.
17   - Geotail is a spin-stabilized spacecraft utilizing mechanically despun antennas with a design lifetime of about four years. The nominal spin rate of the spacecraft is about 20 rpm around a spin axis maintained between 85-89 degrees to the ecliptic plane. Geotail is cylindrical, approximately 2.2 m in diameter, and 1.6 m high. with It has body-mounted solar cells. Geotail also has and a back-up battery subsystem which that operates when the spacecraft is in the Earth's shadow (limited to 2 hrs). Real-time telemetry data transmitted in X-band are received at the Usuda Deep Space Center (UDSC) in Japan. There are two tape recorders on board, each with a capacity of 450 Mb, which allows daily 24-hour data coverage and are collected in playback mode by the NASA Deep Space Network (DSN).
18   - The Geotail mission is divided into two phases. During the two-year initial phase, the orbit apogee was kept on the nightside of the Earth by using the Moon's gravity in a series of double-lunar swing-by maneuvers that result in the spacecraft spending most of its time in the distant magnetotail (maximum apogee about 200 Earth radii) with a period varying from one to four months. Then, in November 1994, there were a series of maneuvers that reduced the apogee to 50 Re. After three more months in the magnetotail the spacecraft was put in a 10 by 30 Re orbit where it has remained except that the perigee was reduced from 10 to 9 Re in June 1997.
19   - Details on the Geotail mission and instrumentation are given in the Journal of Geomagnetism and Geoelectricity (Vol. 46, No. 1, 1994); online from JGG at http://www.terrapub.co.jp/journals/EPS/JGG</Description>
  13 + <ReleaseDate>2016-08-05T18:19:18Z</ReleaseDate>
  14 + <Description>The GEOTAIL mission is a collaborative project undertaken by the Institute of Space and Astronautical Science (ISAS), Japan Aerospace Exploration Agency (JAXA), and the National Aeronautics and Space Administration (NASA). The Geotail spacecraft was designed and built by ISAS and was launched on July 24, 1992. After fulfilling Its original objective of studying the dynamics of the Earth's magnetotail over a wide range of distance, extending from the near-Earth region (8 Earth radii (Re) from the Earth) to the distant tail (about 200 Re) its orbit was changed. Since February 1995 Geotail has been in an elliptical 9 by 30 Re orbit where it has provided data on most aspects of the solar wind interaction with the magnetosphere.
  15 + </Description>
20 16 <Contact>
21 17 <PersonID>spase://SMWG/Person/Guan.Le</PersonID>
22 18 <Role>ProjectScientist</Role>
... ... @@ -26,10 +22,19 @@
26 22 <Role>ProjectScientist</Role>
27 23 </Contact>
28 24 <Contact>
29   - <PersonID>spase://SMWG/Person/Jan.Merka</PersonID>
30   - <Role>MetadataContact</Role>
  25 + <PersonID>spase://CDPP/Person/A.Nishida</PersonID>
  26 + <Role>ProjectScientist</Role>
  27 + </Contact>
  28 + <Contact>
  29 + <PersonID>spase://CDPP/Person/D.Fairfield</PersonID>
  30 + <Role>ProjectScientist</Role>
31 31 </Contact>
32 32 <InformationURL>
  33 + <Name>Geotail home page at ISAS</Name>
  34 + <URL>http://www.stp.isas.jaxa.jp/geotail/</URL>
  35 + <Description>Information about the Geotail mission</Description>
  36 + </InformationURL>
  37 + <InformationURL>
33 38 <Name>NSSDC's Master Catalog</Name>
34 39 <URL>http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1992-044A</URL>
35 40 <Description>Information about the Geotail mission</Description>
... ... @@ -37,7 +42,13 @@
37 42 </ResourceHeader>
38 43 <Location>
39 44 <ObservatoryRegion>Earth.Magnetosphere</ObservatoryRegion>
  45 + <ObservatoryRegion>Earth.Magnetosphere.Magnetotail</ObservatoryRegion>
40 46 <ObservatoryRegion>Heliosphere.NearEarth</ObservatoryRegion>
41 47 </Location>
  48 + <OperatingSpan>
  49 + <StartDate>1992-07-24T00:00:00</StartDate>
  50 + <!--<StopDate>2014-12-16T00:00:00</StopDate>-->
  51 + <Note>Deep Tail Phase : from launch up to beginning of 1995</Note>
  52 + </OperatingSpan>
42 53 </Observatory>
43 54 </Spase>
... ...
Observatory/AMDA/POLAR.xml
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... ... @@ -8,22 +8,16 @@
8 8 <AlternateName>Polar Plasma Laboratory</AlternateName>
9 9 <AlternateName>GGS/Polar</AlternateName>
10 10 <AlternateName>ISTP/Polar</AlternateName>
11   - <ReleaseDate>2010-08-05T18:19:11Z</ReleaseDate>
12   - <Description>POLAR is one of four spacecraft in the Global Geospace Science (GGS) program.
13   - These are among the six spacecraft in the International Solar Terrestrial Physics (ISTP)
14   - program. POLAR provides multi-wavelength imaging of the aurora, measuring plasma entry
15   - into the polar magnetosphere and geomagnetic tail, the flow of plasmas to and from the
16   - ionosphere, and the deposition of particle energy in the ionosphere and upper atmosphere.
17   - POLAR has on-board propulsion systems and a design lifetime of three to five years, with
18   - redundant subsystems. POLAR is cylindrical, approximately 2.8 m in diameter by 1.25 m
19   - high (plus 1.25 m for its two despun platforms), with body-mounted solar cells,
20   - weighs 1250 kg and uses 333 W of power. The spin rate is 10 rpm around an axis
21   - approximately normal to the orbital plane. It has long wire spin-plane antennas,
22   - inertial booms, and spin-plane appendages to support sensors.
23   - POLAR has two despun gimbaled instrument platforms, and booms are deployed along both Z axes. Data are stored using on-board tape recorders and are relayed to the Deep Space Network at 600 kbps maximum (250 kbps nominal) although the average real-time data rate for POLAR is 41.6 kbps. POLAR has a 22.6-h polar orbit (90 deg inclination), with perigee and apogee of 11,500 and 57,000 km. Polar was launched to observe the polar magnetosphere and, as its orbit has precessed with time, has observed the equatorial inner magnetosphere and is now carrying out an extended period of southern hemisphere coverage. Details on the POLAR mission and instrumentation are provided in Space Science Reviews (Vol. 71, Nos. 1-4, 1995) and reprinted in The Global Geospace Mission, edited by C. T. Russell (Kluwer, 1995).</Description>
  11 + <ReleaseDate>2016-08-05T18:19:11Z</ReleaseDate>
  12 + <Description> The Polar satellite, launched on February 24, 1996, is in a highly elliptical, 86 deg inclination orbit with a period of about 17.5 hours.
  13 +
  14 + Within the Sun-Earth Connections fleet, Polar has the responsibility for multi-wavelength imaging of the aurora, measuring the entry of plasma into the polar magentosphere and the geomagnetic tail, the flow of plasma to and from the ionosphere, and the deposition of particle energy in the ionosphere and upper atmosphere. Polar was launched to observe the polar magnetosphere and, as its orbit has precessed with time, has observed the equatorial inner magnetosphere and southern hemisphere. </Description>
24 15 <Contact>
25   - <!-- John Sigwarth -->
26   - <PersonID>spase://SMWG/Person/John.B.Sigwarth</PersonID>
  16 + <PersonID>spase://SMWG/Person/Robert.A.Hoffman</PersonID>
  17 + <Role>ProjectScientist</Role>
  18 + </Contact>
  19 + <Contact>
  20 + <PersonID>spase://CDPP/Person/John.B.Sigwarth</PersonID>
27 21 <Role>ProjectScientist</Role>
28 22 </Contact>
29 23 <InformationURL>
... ... @@ -43,5 +37,9 @@
43 37 <ObservatoryRegion>Earth.Magnetosphere.Polar</ObservatoryRegion>
44 38 <ObservatoryRegion>Earth.Magnetosphere.RadiationBelt</ObservatoryRegion>
45 39 </Location>
  40 + <OperatingSpan>
  41 + <StartDate>1996-02-24T11:24:00</StartDate>
  42 + <StopDate>2008-04-28T00:00:00</StopDate>
  43 + </OperatingSpan>
46 44 </Observatory>
47 45 </Spase>
... ...
Person/A.Nishida 0 → 100644
  Diff comments   View file @1544e77
... ... @@ -0,0 +1,11 @@
  1 +<?xml version="1.0" encoding="UTF-8"?>
  2 +<Spase xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance" xmlns="http://www.spase-group.org/data/schema" xsi:schemaLocation="http://www.spase-group.org/data/schema http://www.spase-group.org/data/schema/spase-2_2_0.xsd">
  3 + <Version>2.2.0</Version>
  4 + <Person>
  5 + <ResourceID>spase://CDPP/Person/A.Nishida</ResourceID>
  6 + <ReleaseDate>2016-08-05T17:35:46Z</ReleaseDate>
  7 + <PersonName>Prof. Atsuhiro Nishida</PersonName>
  8 + <OrganizationName></OrganizationName>
  9 + <Note>Original Japan Project Scientist</Note>
  10 + </Person>
  11 +</Spase>
... ...
Person/D.Fairfield 0 → 100644
  Diff comments   View file @1544e77
... ... @@ -0,0 +1,11 @@
  1 +<?xml version="1.0" encoding="UTF-8"?>
  2 +<Spase xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance" xmlns="http://www.spase-group.org/data/schema" xsi:schemaLocation="http://www.spase-group.org/data/schema http://www.spase-group.org/data/schema/spase-2_2_0.xsd">
  3 + <Version>2.2.0</Version>
  4 + <Person>
  5 + <ResourceID>spase://CDPP/Person/D.Fairfield</ResourceID>
  6 + <ReleaseDate>2016-08-05T17:35:46Z</ReleaseDate>
  7 + <PersonName>Dr. Donald H.Fairfield</PersonName>
  8 + <OrganizationName></OrganizationName>
  9 + <Note>Original US Project Scientist</Note>
  10 + </Person>
  11 +</Spase>
... ...
Person/John.B.Sigwarth
  Diff comments   View file @1544e77
... ... @@ -2,11 +2,10 @@
2 2 <Spase xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance" xmlns="http://www.spase-group.org/data/schema" xsi:schemaLocation="http://www.spase-group.org/data/schema http://www.spase-group.org/data/schema/spase-2_2_0.xsd">
3 3 <Version>2.2.0</Version>
4 4 <Person>
5   - <ResourceID>spase://SMWG/Person/John.B.Sigwarth</ResourceID>
6   - <ReleaseDate>2010-08-05T17:35:46Z</ReleaseDate>
  5 + <ResourceID>spase://CDPP/Person/John.B.Sigwarth</ResourceID>
  6 + <ReleaseDate>2016-08-05T17:35:46Z</ReleaseDate>
7 7 <PersonName>Dr. John B. Sigwarth</PersonName>
8   - <OrganizationName>NASA Goddard Space Flight Center</OrganizationName>
9   - <Address>NASA/GSFC, Code 674, Greenbelt, MD 20771</Address>
10   - <Email>pwg_project@nssdc.nasa.gov</Email>
  8 + <OrganizationName></OrganizationName>
  9 + <Note>Original Project Scientist</Note>
11 10 </Person>
12 11 </Spase>
... ...
Person/Robert.A.Hoffman 0 → 100644
  Diff comments   View file @1544e77
... ... @@ -0,0 +1,12 @@
  1 +<?xml version="1.0" encoding="UTF-8"?>
  2 +<Spase xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance" xmlns="http://www.spase-group.org/data/schema" xsi:schemaLocation="http://www.spase-group.org/data/schema http://www.spase-group.org/data/schema/spase-2_2_0.xsd">
  3 + <Version>2.2.0</Version>
  4 + <Person>
  5 + <ResourceID>spase://SMWG/Person/Robert.A.Hoffman</ResourceID>
  6 + <ReleaseDate>2010-08-05T17:35:47Z</ReleaseDate>
  7 + <PersonName>Dr. Robert A. Hoffman</PersonName>
  8 + <OrganizationName>GSFC-Code 696</OrganizationName>
  9 + <Email>bob_barb@earthlink.net</Email>
  10 + <PhoneNumber>+1-301-286-7386</PhoneNumber>
  11 + </Person>
  12 +</Spase>
... ...
Person/Rudy.Frahm 0 → 100644
  Diff comments   View file @1544e77
... ... @@ -0,0 +1,11 @@
  1 +<?xml version="1.0" encoding="UTF-8"?>
  2 +<Spase xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance" xmlns="http://www.spase-group.org/data/schema" xsi:schemaLocation="http://www.spase-group.org/data/schema http://www.spase-group.org/data/schema/spase-2_2_0.xsd">
  3 + <Version>2.2.0</Version>
  4 + <Person>
  5 + <ResourceID>spase://CDPP/Person/Rudy.Frahm</ResourceID>
  6 + <ReleaseDate>2016-08-05T17:35:45Z</ReleaseDate>
  7 + <PersonName>Dr. Rudy Frahm</PersonName>
  8 + <OrganizationName>SWRI, USA</OrganizationName>
  9 + <Email>rudy.frahm@swri.org</Email>
  10 + </Person>
  11 +</Spase>
... ...