observatory

Elena.Budnik
Showing 54 changed files with 2021 additions and 0 deletions Show diff stats
Observatory/AMDA/ACE.xml
Observatory/AMDA/Cassini.xml
Observatory/AMDA/Cluster-Rumba.xml
Observatory/AMDA/Cluster-Salsa.xml
Observatory/AMDA/Cluster-Samba.xml
Observatory/AMDA/Cluster-Tango.xml
Observatory/AMDA/Cluster.xml
Observatory/AMDA/DoubleStar.xml
Observatory/AMDA/DoubleStar1.xml
Observatory/AMDA/Ephemerides.xml
Observatory/AMDA/Galileo.xml
Observatory/AMDA/Geotail.xml
Observatory/AMDA/Giotto.xml
Observatory/AMDA/ICE.xml
Observatory/AMDA/IMP.xml
Observatory/AMDA/IMP8.xml
Observatory/AMDA/ISEE.xml
Observatory/AMDA/ISEE1.xml
Observatory/AMDA/ISEE2.xml
Observatory/AMDA/Indices.xml
+++ a/Observatory/AMDA/ACE.xml
@@ -0,0 +1,64 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/ACE</ResourceID>
+    <ResourceHeader>
+      <ResourceName>ACE</ResourceName>
+      <AlternateName>Advanced Composition Explorer, NASA</AlternateName>
+      <AlternateName>1997-045A</AlternateName>
+      <AlternateName>Explorer 71</AlternateName>
+      <ReleaseDate>2010-08-05T18:19:16Z</ReleaseDate>
+      <Description>Advanced Composition Explorer (ACE) observes particles of solar, 
+        interplanetary, interstellar, and galactic origins, spanning the energy range 
+        from solar wind ions to galactic cosmic ray nuclei. &lt;br/&gt;&lt;br/&gt;
+        The Advanced Composition Explorer (ACE) spacecraft carries six high-resolution 
+        sensors and three monitoring instruments that sample low-energy particles of solar
+        origin and high-energy galactic particles with a collecting power 10 to 1000 times 
+        greater than past or planned experiments. From a vantage point approximately 1/100 of the 
+        distance from the Earth to the Sun, ACE performs measurements over a wide range of energy 
+        and nuclear mass, under all solar wind flow conditions and during both large and small
+        particle events including solar flares.
+        
+ACE provides near-real-time solar wind information 
+over short time periods. When reporting space weather, 
+ACE can provide an advance warning (about one hour) of geomagnetic 
+storms that can overload power grids, disrupt communications on Earth, 
+and present a hazard to astronauts.
+
+The prime objective of ACE is 
+to measure and compare the composition of several samples of matter, 
+including the solar corona, the solar wind, and other interplanetary particle populations, 
+the local interstellar medium (ISM), and galactic matter. While there has been great progress 
+addressing these objectives, the changing conditions over the solar cycle present new opportunities. 
+In addition, new observations and theoretical advances, new missions, and the evolving goals of NASA 
+and the Sun-Solar- System Connection (S3C) Theme have introduced new challenges, including the goal 
+of achieving the scientific understanding needed to forecast space weather in the coming years when 
+humans will venture beyond Earth's protective magnetosphere.
+      </Description>
+      <Contact>
+        <PersonID>spase://SMWG/Person/Edward.C.Stone.Jr</PersonID>
+        <Role>PrincipalInvestigator</Role>
+      </Contact>
+      <InformationURL>
+        <Name>ACE Home Page</Name>
+        <URL>http://www.srl.caltech.edu/ACE</URL>
+        <Description>ACE mission home page at Caltech with data download</Description>
+      </InformationURL>
+      <InformationURL>
+        <Name>NSSDC's Master Catalog</Name>
+        <URL>http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1997-045A</URL>
+        <Description>Information about the ACE mission</Description>
+      </InformationURL>
+      <PriorID>spase://vspo/observatory/2</PriorID>
+    </ResourceHeader>
+    <Location>
+      <ObservatoryRegion>Heliosphere.NearEarth</ObservatoryRegion>
+      <ObservatoryRegion>Heliosphere.Inner</ObservatoryRegion>
+    </Location>
+    <OperatingSpan>
+      <StartDate>1997-08-25T00:00:00</StartDate>
+      <Note></Note>
+    </OperatingSpan>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/Cassini.xml
@@ -0,0 +1,32 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/Cassini</ResourceID>
+    <ResourceHeader>
+      <ResourceName>Cassini</ResourceName>
+      <AlternateName>Cassini-Huygens, NASA mission to Saturn</AlternateName>
+      <ReleaseDate>2010-08-05T18:19:17Z</ReleaseDate>
+      <Description>The Cassini spacecraft, launched in October 1997, entered 
+        a Saturn-centered orbit in July 2004.  It is instrumented for a wide range of 
+        remote sensing and in situ observations. It delivered the ESA-built Huygens Probe
+        to investigate Titan.</Description>
+      <Contact>
+        <PersonID>spase://SMWG/Person/Dennis.L.Matson</PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>
+      <InformationURL>
+        <URL>http://saturn.jpl.nasa.gov/home/index.cfm</URL>
+        <Description>Cassini page at JPL</Description>
+      </InformationURL>
+      <PriorID>spase://nssdc/observatory/1997-061A</PriorID>
+    </ResourceHeader>
+    <Location>
+      <ObservatoryRegion>Saturn</ObservatoryRegion>
+    </Location>
+    <OperatingSpan>
+      <StartDate>1997-10-15T00:00:00</StartDate>
+      <Note></Note>
+    </OperatingSpan>    
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/Cluster-Rumba.xml
@@ -0,0 +1,33 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/Cluster-Rumba</ResourceID>
+    <ResourceHeader>
+      <ResourceName>Cluster 1</ResourceName>
+      <AlternateName>Cluster 2/FlightModel5 (Rumba)</AlternateName>
+      <AlternateName>2000-045A</AlternateName>
+      <AlternateName>FM5</AlternateName>
+      <AlternateName>Rumba</AlternateName>     
+      <ReleaseDate>2011-02-04T15:21:30Z</ReleaseDate>
+      <Description></Description>
+      <Contact>
+        <PersonID>spase://SMWG/Person/Melvyn.L.Goldstein</PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>
+      <InformationURL>
+        <Name>NSSDC's Master Catalog</Name>
+        <URL>http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=2000-045A</URL>
+        <Description>Information about the Cluster 2/FM5 (Rumba) mission</Description>
+      </InformationURL>
+      <PriorID>spase://SMWG/Observatory/Cluster2-Rumba</PriorID>
+    </ResourceHeader>
+    <ObservatoryGroupID>spase://CDPP/Observatory/AMDA/Cluster</ObservatoryGroupID>
+    <Location>
+      <ObservatoryRegion>Heliosphere.NearEarth</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosheath</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosphere.Main</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosphere.Polar</ObservatoryRegion>
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/Cluster-Salsa.xml
@@ -0,0 +1,54 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/Cluster-Salsa</ResourceID>
+    <ResourceHeader>
+      <ResourceName>Cluster FM6 (Salsa)</ResourceName>
+      <AlternateName>Cluster 2/FM6 (Salsa)</AlternateName>
+      <AlternateName>2000-041B</AlternateName>
+      <AlternateName>FM6</AlternateName>
+      <AlternateName>Salsa</AlternateName>
+      <AlternateName>Cluster-2</AlternateName>
+      <ReleaseDate>2011-05-16T20:49:00Z</ReleaseDate>
+      <Description>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."</Description>
+      <Contact>
+        <PersonID>spase://SMWG/Person/Melvyn.L.Goldstein</PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>
+      <InformationURL>
+        <Name>NSSDC's Master Catalog</Name>
+        <URL>http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=2000-041B</URL>
+        <Description>Information about the Cluster 2/FM6 (Salsa) mission</Description>
+      </InformationURL>
+      <PriorID>spase://SMWG/Observatory/Cluster2-Salsa</PriorID>
+    </ResourceHeader>
+    <ObservatoryGroupID>spase://CDPP/Observatory/AMDA/Cluster</ObservatoryGroupID>
+    <Location>
+      <ObservatoryRegion>Heliosphere.NearEarth</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosheath</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosphere.Main</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosphere.Polar</ObservatoryRegion>
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/Cluster-Samba.xml
@@ -0,0 +1,54 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/Cluster-Samba</ResourceID>
+    <ResourceHeader>
+      <ResourceName>Cluster FM7 (Samba)</ResourceName>
+      <AlternateName>Cluster 2/FM7 (Samba)</AlternateName>
+      <AlternateName>2000-041A</AlternateName>
+      <AlternateName>FM7</AlternateName>
+      <AlternateName>Samba</AlternateName>
+      <AlternateName>Cluster-3</AlternateName>
+      <ReleaseDate>2011-02-04T15:23:52Z</ReleaseDate>
+      <Description>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."</Description>
+      <Contact>
+        <PersonID>spase://SMWG/Person/Melvyn.L.Goldstein</PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>
+      <InformationURL>
+        <Name>NSSDC's Master Catalog</Name>
+        <URL>http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=2000-041A</URL>
+        <Description>Information about the Cluster 2/FM7 (Samba) mission</Description>
+      </InformationURL>
+      <PriorID>spase://SMWG/Observatory/Cluster2-Samba</PriorID>
+    </ResourceHeader>
+    <ObservatoryGroupID>spase://CDPP/Observatory/AMDA/Cluster</ObservatoryGroupID>
+    <Location>
+      <ObservatoryRegion>Heliosphere.NearEarth</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosphere.Main</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosheath</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosphere.Polar</ObservatoryRegion>
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/Cluster-Tango.xml
@@ -0,0 +1,54 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/Cluster-Tango</ResourceID>
+    <ResourceHeader>
+      <ResourceName>Cluster FM8 (Tango)</ResourceName>
+      <AlternateName>Cluster 2/FM8 (Tango)</AlternateName>
+      <AlternateName>2000-045B</AlternateName>
+      <AlternateName>Cluster-4</AlternateName>
+      <AlternateName>Tango</AlternateName>
+      <AlternateName>FM8</AlternateName>
+      <ReleaseDate>2011-05-16T20:49:04Z</ReleaseDate>
+      <Description>This Cluster II spacecraft, FM8 (Tango), was launched together with FM5 (Rumba) 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.
+
+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."</Description>
+      <Contact>
+        <PersonID>spase://SMWG/Person/Melvyn.L.Goldstein</PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>
+      <InformationURL>
+        <Name>NSSDC's Master Catalog</Name>
+        <URL>http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=2000-045B</URL>
+        <Description>Information about the Cluster 2/FM8 (Tango) mission</Description>
+      </InformationURL>
+      <PriorID>spase://SMWG/Observatory/Cluster2-Tango</PriorID>
+    </ResourceHeader>
+    <ObservatoryGroupID>spase://CDPP/Observatory/AMDA/Cluster</ObservatoryGroupID>
+    <Location>
+      <ObservatoryRegion>Heliosphere.NearEarth</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosheath</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosphere.Main</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosphere.Polar</ObservatoryRegion>
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/Cluster.xml
@@ -0,0 +1,32 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/Cluster</ResourceID>
+    <ResourceHeader>
+      <ResourceName>Cluster</ResourceName>
+      <AlternateName>Cluster II, ESA Magnetospheric Mission</AlternateName>
+      <ReleaseDate>2011-02-07T00:50:41Z</ReleaseDate>
+      <Description>Cluster is a constellation of four spacecraft flying in formation around Earth. 
+        They relay the most detailed information ever about 
+        how the solar wind affects our planet in three dimensions. 
+        The solar wind (the perpetual stream of subatomic particles given out by the Sun) 
+        can damage communications satellites and power stations on Earth. 
+        The original operation life-time of the Cluster mission ran from February 
+        2001 to December 2005. However, in February 2005, 
+       </Description>
+      <Contact>
+        <PersonID>spase://SMWG/Person/Melvyn.L.Goldstein</PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>
+    </ResourceHeader>
+    <Location>      
+      <ObservatoryRegion>Earth.Magnetosphere</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosheath</ObservatoryRegion>
+      <ObservatoryRegion>Heliosphere.NearEarth</ObservatoryRegion>
+    </Location>
+    <OperatingSpan>
+      <StartDate>2000-12-01T00:00:00</StartDate>
+    </OperatingSpan>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/DoubleStar.xml
@@ -0,0 +1,25 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/DoubleStar1</ResourceID>
+    <ResourceHeader>
+      <ResourceName>Double Star</ResourceName>
+      <AlternateName>Chinese/ESA Magnetospheric mission</AlternateName>
+      <ReleaseDate>2010-10-01T20:40:09Z</ReleaseDate>
+      <Description></Description>
+      <Contact>
+        <PersonID>spase://SMWG/Person/Christophe.Philippe.Escoubet</PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>
+      <InformationURL>
+        <Name>NSSDC's Master Catalog</Name>
+        <URL>http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=2003-061A</URL>
+        <Description>Information about the Double Star 1 mission</Description>
+      </InformationURL>
+    </ResourceHeader>   
+    <Location>
+      <ObservatoryRegion>Earth.Magnetosphere</ObservatoryRegion>
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/DoubleStar1.xml
@@ -0,0 +1,30 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/DoubleStar1</ResourceID>
+    <ResourceHeader>
+      <ResourceName>Double Star 1</ResourceName>
+      <AlternateName>2003-061A</AlternateName>
+      <AlternateName>Tan Ce1</AlternateName>
+      <AlternateName>TC 1</AlternateName>
+      <ReleaseDate>2010-10-01T20:40:09Z</ReleaseDate>
+      <Description>Double Star 1 (also known as Tan Ce 1, and TC 1) is a Sino-European (CSNA-ESA) satellite that was launched by a Long March 2C/SM rocket from Xichang Satellite Launch Center in the Sichuan province of China (PRC) at 19:06 UT on 29 December 2003. The 330 kg, 260 W satellite is cylindrical, with a diameter of 2.1 m, a height of 1.4 m, and spins at a rate of 15 rpm. It carries eight instruments to probe Earth's magnetosphere, five from ESA and three from CNSA. (The ESA instruments are legacies from ESA's Cluster mission.) The data from all instruments will be stored on-board and dumped over three grounds stations: Shanghai and Beifing in China, and Villafranca in Spain. There will be coordination between the Cluster and Double Star missions. For more information, see
+
+http://www.esa.int/export/esaSC/120381_index_0_m.html</Description>
+      <Contact>
+        <PersonID>spase://SMWG/Person/Christophe.Philippe.Escoubet</PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>
+      <InformationURL>
+        <Name>NSSDC's Master Catalog</Name>
+        <URL>http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=2003-061A</URL>
+        <Description>Information about the Double Star 1 mission</Description>
+      </InformationURL>
+    </ResourceHeader>
+    <ObservatoryGroupID>spase://CDPP/Observatory/AMDA/DoubleStar</ObservatoryGroupID>
+    <Location>
+      <ObservatoryRegion>Earth.Magnetosphere.Main</ObservatoryRegion>
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/Ephemerides.xml
@@ -0,0 +1,20 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/Ephemerides</ResourceID>
+    <ResourceHeader>
+      <ResourceName>Astronomical Objects Ephemerides</ResourceName>
+      <AlternateName>Planets/Moons Orbitography</AlternateName>
+      <ReleaseDate>2010-09-27T18:45:12Z</ReleaseDate>
+      <Description></Description>
+      <Contact>     
+        <PersonID> </PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>      
+    </ResourceHeader>
+    <Location> 
+      <ObservatoryRegion>Heliosphere</ObservatoryRegion>      
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/Galileo.xml
@@ -0,0 +1,182 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<Spase xmlns="http://www.spase-group.org/data/schema" xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance" xsi:schemaLocation="http://www.spase-group.org/data/schema http://www.spase-group.org/data/schema/spase-2_2_6.xsd" lang="en">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/Galileo</ResourceID>
+    <ResourceHeader>
+      <ResourceName>Galileo</ResourceName>
+      <AlternateName>Galileo Orbiter</AlternateName>
+      <AlternateName>Jupiter Orbiter-Probe</AlternateName>
+      <ReleaseDate>2012-11-27T00:00:00Z</ReleaseDate>
+      <Description>
+Science Objectives
+==================
+The Galileo mission consists of two spacecraft: an orbiter and an atmospheric probe. The orbiter will be the sixth spacecraft to explore the Jovian magnetosphere, but the first to be placed into orbit around the giant planet. Scientific objectives addressed by the orbiter are to: (1) investigate the circulation and dynamics of the Jovian atmosphere; (2) investigate the upper Jovian atmosphere and ionosphere; (3) characterize the morphology, geology, and physical state of the Galilean satellites; (4) investigate the composition and distribution of surface minerals on the Galilean satellites; (5) determine the gravitational and magnetic fields and dynamic properties of the Galilean satellites; (6) study the atmospheres, ionospheres, and extended gas clouds of the Galilean satellites; (7) study the interaction of the Jovian magnetosphere with the Galilean satellites; and, (8) characterize the vector magnetic field and the energy spectra, composition, and angular distribution of energetic particles and plasma to a distance of 150 Rj.
+
+Spacecraft Overview
+===================
+
+The structure of the orbiter is divided into two sections. The main body of the spacecraft, comprised of the electronics bays, propellant system, RTG and science booms, and high-gain antenna, rotates at rates of 3.25 or 10.5 rpm. The despun section, aft of the main body, uses an electric motor to drive it counter to the rotation of the main section. This dual spin attitude control system accommodates instruments which require stable, accurate pointing (the imaging instruments) and those which benefit from repetitive, broad-angular coverage (the various particles and fields instruments). The length of the spacecraft is 9 m and, with the high-gain antenna (HGA) deployed, is 4.6 m in diameter.
+
+Power is provided to the spacecraft through the use of two radioisotope thermal generators (RTGs), each of which is located at the end of a short boom. The magnetometer sensors and plasma wave antenna are located on yet another boom, 10.9 m in length.
+
+Although it was intended that communications with the Deep Space Network (DSN) would be primarily through the HGA (which would remain pointing toward the Earth at all times), thermal constraints forced the use of the two low-gain antennas prior to the first Earth flyby. HGA deployment was planned thereafter, but at least three of the HGA "ribs" were unable to be moved much beyond their launch configurations, thereby jeopardizing the total science return of the mission. Several attempts have been made to deploy the antenna through a variety of techniques.
+
+QUICK FACTS
+===========
+
+Spacecraft
+==========
+
+Dimensions: 5.3 meters (17 feet) high; magnetometer boom extends 11 meters (36 feet) to one side
+
+Weight: 2,223 kilograms (2.5 tons, or 4,902 pounds), including 118 kilograms (260 pounds) of science instruments and 925 kilograms (2040 pounds) of propellant
+
+Power: 570 watts (at launch) from radioisotope thermoelectric generators
+
+Science instruments: Solid-state imaging camera, near-infrared mapping spectrometer,
+ultraviolet spectrometer, photopolarimeter radiometer, magnetometer, energetic particles detector, plasma investigation, plasma wave subsystem, dust detector, heavy ion counter
+
+Atmospheric Probe
+=================
+
+Size: 127 centimeters (50 inches) diameter, 91 centimeters (36 inches) high
+
+Weight: 339 kilograms (750 pounds)
+
+Science instruments: Atmospheric structure, neutral mass spectrometer, helium abundance,
+nephelometer, net flux radiometer, lightning/energetic particles, doppler wind experiment
+
+Mission
+=======
+
+Launch: Oct. 18, 1989 from Kennedy Space Center, Fla., on space shuttle Atlantis on mission STS-34
+
+End of Mission: Sep. 21, 2003
+
+Primary mission: October 1989 to December 1997
+
+Extended missions: Three, from 1997 to 2003
+
+Venus flyby: Feb. 10, 1990, at altitude of 16,000 km (10,000 mi)
+
+Earth flybys: Dec. 8, 1990, at altitude of 960 km (597 mi); Dec. 8, 1992 at altitude of
+303 km (188 mi)
+
+Asteroid Gaspra flyby: Oct. 29, 1991, at 1,601 km (1,000 mi)
+
+Comet Shoemaker-Levy 9: Impacts of comet fragments into Jupiter observed while en route
+in July 1994
+
+Asteroid Ida flyby: Aug. 28, 1993, at 2,400 km (1,400 mi)
+
+Atmospheric probe release: July 12, 1995
+
+Probe speed into Jupiter's atmosphere: 47.6 km per second (106,000 mi per hour) Jupiter arrival and orbit insertion: Dec. 7, 1995
+
+Probe atmospheric entry and relay: Dec. 7, 1995
+
+Number of Jupiter orbits during entire mission: 34
+
+Number of flybys of Jupiter moons: Io 7, Callisto 8, Ganymede 8, Europa 11, Amalthea 1
+
+  Mission Overview
+  ================
+
+The Galileo mission utilizes a single launch of a combined
+    Orbiter and Probe using the space shuttle Atlantis and an
+    inertial upper stage (IUS) to inject the Galileo spacecraft
+    on its interplanetary trajectory to Jupiter. The launch
+    window occurs from October 12, 1989 to November 21, 1989.
+    Since the IUS does not have the energy to inject Galileo on
+    a direct trajectory to Jupiter, the spacecraft will instead
+    be launched first towards Venus for the first leg of its
+    Venus-Earth-Earth gravity assist (VEEGA) trajectory to
+    Jupiter. Target-of-opportunity science observations will be
+    made at Venus (closest approach February 10, 1990), the
+    first Earth encounter (closest approach to Earth and Moon
+    December 8, 1990), the asteroid Gaspra (closest approach
+    October 29, 1991), the second Earth encounter (closest
+    approach to Earth and Moon December 8, 1992), and the
+    asteroid Ida (closest approach August 28, 1993).
+
+    At about 150 days before Galileo arrives at Jupiter, the
+    Probe is separated from the Orbiter. From this moment in
+    time, the Probe is on a ballistic trajectory to the Probe
+    entry point, about 6 degrees north latitude, into the
+    atmosphere of Jupiter. Using its 400 Newton engine for the
+    first time, the Orbiter executes an Orbiter deflection
+    maneuver to keep from following the Probe into the
+    atmosphere of Jupiter, and to retarget the Orbiter to the
+    proper encounter conditions required for the Jupiter Orbit
+    Insertion phase of the mission.
+
+    A close flyby (about 1,000 kilometer altitude) of the Jovian
+    satellite Io occurs in this phase for the purpose of science
+    observations as well as to slow the Orbiter down relative to
+    Jupiter by nearly 200 meters/second in order to reduce the
+    propellant required during the Jupiter Orbit Insertion (JOI)
+    400 Newton engine burn to capture Galileo into Jupiter's
+    orbit. Perijove of about 4 Jupiter radii occurs about 4
+    hours after Io encounter. A few minutes after perijove
+    passage, the Probe entry and beginning of the relay of data
+    from the Probe to the Orbiter occurs.
+
+    The Probe mission and data relay lasts 75 minutes, after
+    which JOI is performed, slowing the Orbiter down relative to
+    Jupiter by about 630 meters/second. The initial orbit period
+    is about 200 days. A large 400 Newton engine burn is
+    performed at the first apojove in order to raise perijove
+    from 4 Jupiter radii to about 9 Jupiter radii, thus allowing
+    at least 11 orbits with 10 targeted satellite encounters to
+    be completed by the Orbiter without exceeding the allowed
+    total accumulated radiation exposure at the spacecraft. Only
+    three orbits would be allowed before exceeding this limit if
+    perijove were allowed to stay at 4 Jupiter radii, where the
+    radiation environment is very severe. Also during this
+    perijove raise maneuver, Galileo is targeted to the
+    satellite Ganymede, the first of its Galilean satellite
+    encounters following JOI.
+
+    At this point, the targeting to satellite encounters begins,
+    such that a satellite tour consisting of a minimum of 10
+    targeted satellite encounters is achieved within the 23
+    month period allotted for the satellite tour. During the
+    course of the satellite tour, the orientation, shape and
+    size of the spacecraft orbits around the Jovian system,
+    referred to as petals because of how the spacecraft orbits
+    appear on a plan view of the Jovian satellite tour
+    trajectory, is controlled almost exclusively by gravity
+    assists of the satellites themselves. The orbit periods are
+    pumped down by successive encounters with the satellites
+    from the initial 200 days to approximately 35-40 days
+    between encounters. At the 8th orbit, when the orbit petal
+    orientation is approximately in the anti-sun direction, the
+    period is again pumped up to about 100 days, allowing one of
+    the primary objectives, probing the Jovian magnetotail, to
+    be accomplished. After this magnetotail orbit, the period is
+    again pumped down, by gravity assist encounters with the
+    Jovian satellites, to 35-40 days for the final 2-3 targeted
+    encounters.
+          </Description>
+      <Acknowledgement/>
+      <Contact>
+        <PersonID>spase://SMWG/Person/Torrence.V.Johnson</PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>
+      <InformationURL>
+        <Name>NSSDC's Master Catalog</Name>
+        <URL>http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1989-084B</URL>
+        <Description>Information about the Galileo Orbiter mission</Description>
+      </InformationURL>
+    </ResourceHeader>
+    <Location> 
+      <ObservatoryRegion>Jupiter</ObservatoryRegion>   
+      <ObservatoryRegion>Jupiter</ObservatoryRegion>
+      <ObservatoryRegion>Asteroid</ObservatoryRegion>
+      <ObservatoryRegion>Heliosphere</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosphere</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosphere.Magnetotail</ObservatoryRegion>
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/Geotail.xml
@@ -0,0 +1,43 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/Geotail</ResourceID>
+    <ResourceHeader>
+      <ResourceName>Geotail</ResourceName>
+      <AlternateName>1992-044A</AlternateName>
+      <AlternateName>GTL</AlternateName>
+      <AlternateName>ISTP/Geotail</AlternateName>
+      <AlternateName>GGS/Geotail</AlternateName>
+      <AlternateName>Geomagnetic Tail Lab</AlternateName>
+      <ReleaseDate>2010-08-05T18:19:18Z</ReleaseDate>
+      <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.
+            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.
+            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.
+            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).
+            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.
+            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>
+      <Contact>
+        <PersonID>spase://SMWG/Person/Guan.Le</PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>
+      <Contact>
+        <PersonID>spase://SMWG/Person/Masaki.Fujimoto</PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>
+      <Contact>
+        <PersonID>spase://SMWG/Person/Jan.Merka</PersonID>
+        <Role>MetadataContact</Role>
+      </Contact>
+      <InformationURL>
+        <Name>NSSDC's Master Catalog</Name>
+        <URL>http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1992-044A</URL>
+        <Description>Information about the Geotail mission</Description>
+      </InformationURL>
+    </ResourceHeader>
+    <Location>
+      <ObservatoryRegion>Earth.Magnetosphere</ObservatoryRegion>
+      <ObservatoryRegion>Heliosphere.NearEarth</ObservatoryRegion>
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/Giotto.xml
@@ -0,0 +1,20 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/Giotto</ResourceID>
+    <ResourceHeader>
+      <ResourceName>Giotto</ResourceName>
+      <AlternateName> </AlternateName>
+      <ReleaseDate>2010-09-27T18:45:12Z</ReleaseDate>
+      <Description></Description>
+      <Contact>     
+        <PersonID> </PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>      
+    </ResourceHeader>
+    <Location> 
+      <ObservatoryRegion>Comet</ObservatoryRegion>      
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/ICE.xml
@@ -0,0 +1,20 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/ICE</ResourceID>
+    <ResourceHeader>
+      <ResourceName>ICE</ResourceName>
+      <AlternateName> </AlternateName>
+      <ReleaseDate>2010-09-27T18:45:12Z</ReleaseDate>
+      <Description></Description>
+      <Contact>     
+        <PersonID> </PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>      
+    </ResourceHeader>
+    <Location> 
+      <ObservatoryRegion>Comet</ObservatoryRegion>      
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/IMP.xml
@@ -0,0 +1,34 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/IMP8</ResourceID>
+    <ResourceHeader>
+      <ResourceName>IMP</ResourceName>
+      <AlternateName>Interplanetary Monitoring Platform (Explorer), NASA</AlternateName>
+      <ReleaseDate>2010-09-27T18:45:12Z</ReleaseDate>
+      <Description></Description>
+      <Contact>
+        <!-- Robert McGuire -->
+        <PersonID>spase://SMWG/Person/Robert.E.McGuire</PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>
+      <InformationURL>
+        <Name>IMP-8 Project Information</Name>
+        <URL>http://spdf.gsfc.nasa.gov/imp8/project.html</URL>
+      </InformationURL>
+      <InformationURL>
+        <Name>NSSDC's Master Catalog</Name>
+        <URL>http://nssdc.gsfc.nasa.gov/nmc/masterCatalog.do?sc=1973-078A</URL>
+        <Description>Information about the IMP-J mission</Description>
+      </InformationURL>
+      <PriorID>spase://vspo/observatory/63</PriorID>
+    </ResourceHeader>
+    <Location> 
+      <ObservatoryRegion>Earth.Magnetosphere</ObservatoryRegion>
+      <ObservatoryRegion>Heliosphere.NearEarth</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosheath</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosphere.Magnetotail</ObservatoryRegion>
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/IMP8.xml
@@ -0,0 +1,39 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/IMP8</ResourceID>
+    <ResourceHeader>
+      <ResourceName>IMP 8</ResourceName>
+      <AlternateName>IMP-J</AlternateName>
+      <AlternateName>Explorer 50</AlternateName>
+      <AlternateName>1973-078A</AlternateName>
+      <ReleaseDate>2010-09-27T18:45:12Z</ReleaseDate>
+      <Description>IMP 8 (IMP-J or Explorer 50), the last satellite of the IMP series, was a drum-shaped spacecraft, 135.6 cm across and 157.4 cm high, instrumented for interplanetary and magnetotail studies of cosmic rays, energetic solar particles, plasma, and electric and magnetic fields. Its initial orbit was more elliptical than intended, with apogee and perigee distances of about 45 and 25 earth radii. Its eccentricity decreased after launch. Its orbital inclination varied between 0 deg and about 55 deg with a periodicity of several years. The spacecraft spin axis was normal to the ecliptic plane, and the spin rate was 23 rpm. The data telemetry rate was 1600 bps.
+            The spacecraft was in the solar wind for 7 to 8 days of every 12.5 day orbit. Telemetry coverage was 90% in the early years, but only 60-70% through most of the 1980's and early 1990's. Coverage returned to the 90% range in the mid to late 1990's.
+            The objectives of the extended IMP-8 operations were to provide solar wind parameters as input for magnetospheric studies and as a 1-AU baseline for deep space studies, and to continue solar cycle variation studies with a single set of well-calibrated and understood instruments.
+            In October, 2001, IMP 8 was terminated as an independent mission. Telemetry acquisition resumed after about three months at Canberra only (30-50% coverage), as an adjunct to the Voyager and Ulysses missions. As of August 2005 IMP 8 continued in this mode.</Description>
+      <Contact>
+        <!-- Robert McGuire -->
+        <PersonID>spase://SMWG/Person/Robert.E.McGuire</PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>
+      <InformationURL>
+        <Name>IMP-8 Project Information</Name>
+        <URL>http://spdf.gsfc.nasa.gov/imp8/project.html</URL>
+      </InformationURL>
+      <InformationURL>
+        <Name>NSSDC's Master Catalog</Name>
+        <URL>http://nssdc.gsfc.nasa.gov/nmc/masterCatalog.do?sc=1973-078A</URL>
+        <Description>Information about the IMP-J mission</Description>
+      </InformationURL>
+      <PriorID>spase://vspo/observatory/63</PriorID>
+    </ResourceHeader>
+    <ObservatoryGroupID>spase://CDPP/Observatory/AMDA/IMP</ObservatoryGroupID>
+    <Location>
+      <ObservatoryRegion>Heliosphere.NearEarth</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosheath</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosphere.Magnetotail</ObservatoryRegion>
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/ISEE.xml
@@ -0,0 +1,22 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/ISEE</ResourceID>
+    <ResourceHeader>
+      <ResourceName>ISEE</ResourceName>
+      <AlternateName>International Sun-Earth Explorer; NASA</AlternateName>
+      <ReleaseDate>2010-10-01T20:05:54Z</ReleaseDate>
+      <Description>The ISEE (International Sun-Earth Explorer) program was an international cooperative program between NASA and ESA to study 
+        the interaction of the solar wind with the Earth's magnetosphere.                  
+       </Description>
+      <Contact>
+        <PersonID>spase://SMWG/Person/Keith.W.Ogilvie</PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>
+    </ResourceHeader>
+    <Location>
+      <ObservatoryRegion>Heliosphere.NearEarth</ObservatoryRegion>
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/ISEE1.xml
@@ -0,0 +1,29 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/ISEE1</ResourceID>
+    <ResourceHeader>
+      <ResourceName>ISEE 1</ResourceName>
+      <AlternateName>1977-102A</AlternateName>
+      <AlternateName>International Sun-Earth Explorer-A</AlternateName>
+      <AlternateName>Explorer 56</AlternateName>
+      <AlternateName>ISEE-A</AlternateName>
+      <ReleaseDate>2010-10-01T20:06:06Z</ReleaseDate>
+      <Description>The Explorer-class mother spacecraft, International Sun-Earth Explorer 1, was part of the mother/daughter/heliocentric mission (ISEE 1, ISEE 2, ISEE 3). The purposes of the mission were: (1) to investigate solar-terrestrial relationships at the outermost boundaries of the Earth's magnetosphere, (2) to examine in detail the structure of the solar wind near the Earth and the shock wave that forms the interface between the solar wind and the Earth's magnetosphere, (3) to investigate motions of and mechanisms operating in the plasma sheets, and (4) to continue the investigation of cosmic rays and solar flare effects in the interplanetary region near 1 AU. The three spacecraft carried a number of complementary instruments for making measurements of plasmas, energetic particles, waves, and fields. The mission thus extended the investigations of previous IMP spacecraft. The mother/daughter portion of the mission consisted of two spacecraft (ISEE 1 and ISEE 2) with station-keeping capability in the same highly eccentric geocentric orbit with an apogee of 23 Earth radii. During the course of the mission, the ISEE 1 and ISEE 2 orbit parameters underwent short-term and long-term variations due to solar and lunar perturbations. These two spacecraft maintained a small separation distance, and made simultaneous coordinated measurements to permit separation of spatial from temporal irregularities in the near-Earth solar wind, the bow shock, and inside the magnetosphere. By maneuvering ISEE 2, the inter-spacecraft separation as measured near the Earth's bow shock was allowed to vary between 10 km and 5000 km; its value is accurately known as a function of time and orbital position. The spacecraft were spin stabilized, with the spin vectors maintained nominally within 1 degree of perpendicular to the ecliptic plane, pointing north. The spin rates were nominally 19.75 rpm for ISEE 1 and 19.8 rpm for ISEE 2, so that there was a slow differential rotation between the two spacecraft. The ISEE 1 body-mounted solar array provided approximately 175 watts initially and 131 watts after three years, at 28 volts during normal operation. The ISEE 1 data rate was 4096 bps most of the time and 16384 bps during one orbit out of every five (with some exceptions). Both ISEE 1 and ISEE 2 re-entered the Earth's atmosphere during orbit 1518 on September 26, 1987. Seventeen of 21 on-board experiments were operational at the end. For instrument descriptions written by the investigators, see IEEE Trans. on Geosci. Electron., v. GE-16, no. 3, July 1978.</Description>
+      <Contact>
+        <PersonID>spase://SMWG/Person/Keith.W.Ogilvie</PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>
+      <InformationURL>
+        <Name>NSSDC's Master Catalog</Name>
+        <URL>http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1977-102A</URL>
+        <Description>Information about the ISEE 1 mission</Description>
+      </InformationURL>
+    </ResourceHeader>
+    <ObservatoryGroupID>spase://CDPP/Observatory/AMDA/ISEE</ObservatoryGroupID>
+    <Location>
+      <ObservatoryRegion>Heliosphere.NearEarth</ObservatoryRegion>
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/ISEE2.xml
@@ -0,0 +1,32 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/ISEE2</ResourceID>
+    <ResourceHeader>
+      <ResourceName>ISEE 2</ResourceName>
+      <AlternateName>1977-102B</AlternateName>
+      <AlternateName>International Sun-Earth Explorer-B</AlternateName>
+      <AlternateName>ISEE-B</AlternateName>
+      <ReleaseDate>2010-10-01T20:06:06Z</ReleaseDate>
+      <Description>The Explorer-class daughter spacecraft, International Sun-Earth Explorer 2, was part of the mother/daughter/heliocentric mission (ISEE 1, ISEE 2, ISEE 3). The purposes of the mission were: (1) to investigate solar-terrestrial relationships at the outermost boundaries of the Earth's magnetosphere, (2) to examine in detail the structure of the solar wind near the Earth and the shock wave that forms the interface between the solar wind and the Earth's magnetosphere, (3) to investigate motions of and mechanisms operating in the plasma sheets, and (4) to continue the investigation of cosmic rays and solar flare effects in the interplanetary region near 1 AU. The three spacecraft carried a number of complementary instruments for making measurements of plasmas, energetic particles, waves, and fields. The mission thus extended the investigations of previous IMP spacecraft. The mother/daughter portion of the mission consisted of two spacecraft (ISEE 1 and ISEE 2) with station-keeping capability in the same highly eccentric geocentric orbit with an apogee of 23 Earth radii. During the course of the mission, the ISEE 1 and ISEE 2 orbit parameters underwent short-term and long-term variations due to solar and lunar perturbations. These two spacecraft maintained a small separation distance, and made simultaneous coordinated measurements to permit separation of spatial from temporal irregularities in the near-Earth solar wind, the bow shock, and inside the magnetosphere. By maneuvering ISEE 2, the inter-spacecraft separation as measured near the Earth's bow shock was allowed to vary between 10 km and 5000 km; its value is accurately known as a function of time and orbital position. The spacecraft were spin stabilized, with the spin vectors maintained nominally within 1 degree of perpendicular to the ecliptic plane, pointing north. The spin rates were nominally 19.75 rpm for ISEE 1 and 19.8 rpm for ISEE 2, so that there was a slow differential rotation between the two spacecraft. The ISEE 2 body-mounted solar array supplied approximately 112 watts at launch. The ISEE 2 data rate was 2048 bps most of the time and 8192 bps during one orbit out of every five (with some exceptions). Both ISEE 1 and ISEE 2 re-entered the Earth's atmosphere during orbit 1518 on September 26, 1987. Seventeen of 21 on-board experiments were operational at the end. For instrument descriptions written by the investigators, see IEEE Trans. on Geosci. Electron., v. GE-16, no. 3, July 1978.</Description>
+      <Contact>
+        <PersonID>spase://SMWG/Person/Keith.W.Ogilvie</PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>
+      <Contact>
+        <PersonID>spase://SMWG/Person/Alastair.C.Durney</PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>
+      <InformationURL>
+        <Name>NSSDC's Master Catalog</Name>
+        <URL>http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1977-102B</URL>
+        <Description>Information about the ISEE 2 mission</Description>
+      </InformationURL>
+    </ResourceHeader>
+    <ObservatoryGroupID>spase://CDPP/Observatory/AMDA/ISEE</ObservatoryGroupID>
+    <Location>
+      <ObservatoryRegion>Heliosphere.NearEarth</ObservatoryRegion>
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/Indices.xml
@@ -0,0 +1,20 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/Indices</ResourceID>
+    <ResourceHeader>
+      <ResourceName>Indices</ResourceName>
+      <AlternateName></AlternateName>
+      <ReleaseDate>2010-09-27T18:45:12Z</ReleaseDate>
+      <Description></Description>
+      <Contact>     
+        <PersonID> </PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>      
+    </ResourceHeader>
+    <Location> 
+      <ObservatoryRegion>Earth</ObservatoryRegion>      
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/Interball-Tail.xml
@@ -0,0 +1,24 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/Interball-Tail</ResourceID>
+    <ResourceHeader>
+      <ResourceName>Interball Tail</ResourceName>
+      <ReleaseDate>2010-09-27T18:40:58Z</ReleaseDate>
+      <Description>The Interball Project is a multi-national effort that consists of four spacecraft: two main spacecraft of the Prognoz series, made in Russia, each with a small subsatellite made in Czechoslovakia. The main objective is to study the physical mechanisms responsible for the transmission of solar wind energy to the magnetosphere, its storage there, and subsequent dissipation in the tail and auroral regions of the magnetosphere, ionosphere, and atmosphere during magnetospheric substorms. One pair of spacecraft, Tail Probe and its subsatellite S2-X (X for the first letter of the Russian word for ``Tail''), will be launched into the magnetospheric tail. The second pair, Auroral Probe and S2-A (A for ``Auroral''), will have an orbit that crosses the auroral oval to observe the acceleration of auroral particles and the flow of electric currents that connect the magnetospheric tail with the conducting ionosphere.</Description>
+      <Contact>
+        <PersonID>spase://SMWG/Person/Jan.Merka</PersonID>
+        <Role>MetadataContact</Role>
+      </Contact>
+    </ResourceHeader>
+    <ObservatoryGroupID>spase://CDPP/Observatory/AMDA/Interball</ObservatoryGroupID>
+    <Location>
+      <ObservatoryRegion>Heliosphere.NearEarth</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosheath</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosphere</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosphere.Main</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosphere.Polar</ObservatoryRegion>
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/Interball.xml
@@ -0,0 +1,24 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/Interball</ResourceID>
+    <ResourceHeader>
+      <ResourceName>Interball</ResourceName>
+      <ReleaseDate>2010-09-27T18:40:58Z</ReleaseDate>
+      <Description>The Interball Project is a multi-national effort that consists of four spacecraft: two main spacecraft of the Prognoz series, made in Russia, each with a small subsatellite made in Czechoslovakia. The main objective is to study the physical mechanisms responsible for the transmission of solar wind energy to the magnetosphere, its storage there, and subsequent dissipation in the tail and auroral regions of the magnetosphere, ionosphere, and atmosphere during magnetospheric substorms. One pair of spacecraft, Tail Probe and its subsatellite S2-X (X for the first letter of the Russian word for ``Tail''), will be launched into the magnetospheric tail. The second pair, Auroral Probe and S2-A (A for ``Auroral''), will have an orbit that crosses the auroral oval to observe the acceleration of auroral particles and the flow of electric currents that connect the magnetospheric tail with the conducting ionosphere.</Description>
+      <Contact>
+        <PersonID>spase://SMWG/Person/Jan.Merka</PersonID>
+        <Role>MetadataContact</Role>
+      </Contact>
+    </ResourceHeader>
+    <Location> 
+      <ObservatoryRegion>Earth.Magnetosphere</ObservatoryRegion>
+      <ObservatoryRegion>Heliosphere.NearEarth</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosheath</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosphere</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosphere.Main</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosphere.Polar</ObservatoryRegion>
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/Juice.xml
@@ -0,0 +1,20 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/Juice</ResourceID>
+    <ResourceHeader>
+      <ResourceName>Juice</ResourceName>
+      <AlternateName></AlternateName>
+      <ReleaseDate>2010-09-27T18:45:12Z</ReleaseDate>
+      <Description></Description>
+      <Contact>     
+        <PersonID> </PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>      
+    </ResourceHeader>
+    <Location> 
+      <ObservatoryRegion>Jupiter</ObservatoryRegion>      
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/Juno.xml
@@ -0,0 +1,20 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/Juno</ResourceID>
+    <ResourceHeader>
+      <ResourceName>Juno</ResourceName>
+      <AlternateName></AlternateName>
+      <ReleaseDate>2010-09-27T18:45:12Z</ReleaseDate>
+      <Description></Description>
+      <Contact>     
+        <PersonID> </PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>      
+    </ResourceHeader>
+    <Location> 
+      <ObservatoryRegion>Jupiter</ObservatoryRegion>      
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/MAVEN.xml
@@ -0,0 +1,20 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/MAVEN</ResourceID>
+    <ResourceHeader>
+      <ResourceName>MAVEN</ResourceName>
+      <AlternateName>Mars Atmosphere and Volatile Evolution Mission</AlternateName>
+      <ReleaseDate>2010-09-27T18:45:12Z</ReleaseDate>
+      <Description></Description>
+      <Contact>     
+        <PersonID> </PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>      
+    </ResourceHeader>
+    <Location> 
+      <ObservatoryRegion>Mars</ObservatoryRegion>
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/MESSENGER.xml
@@ -0,0 +1,33 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/MESSENGER</ResourceID>
+    <ResourceHeader>
+      <ResourceName>MESSENGER</ResourceName>
+      <ReleaseDate>2012-02-09T21:20:38Z</ReleaseDate>
+      <Description>The Mercury Surface, Space Environment, Geochemistry 
+and Ranging (MESSENGER) mission, launched on 2004-08-03, was mainly
+designed to study the characteristics and environment of Mercury from 
+orbit.  After an Earth flyby July-August, 2005, Venus flybys October-
+November, 2006, and May-June, 2007, and Mercury flybys December 2007 - 
+January 2008, September-October, 2008, and September-October, 2009, 
+MESSENGER entered Mercury orbit 2011-03-04.  Much data of interest to
+the heliospheric community was obtained during the cruise phases
+between planetary encounters from a magnetometer and an energetic 
+particle and plasma spectrometer.</Description>
+      <Contact>
+        <PersonID>spase://SMWG/Person/Ralph.L.McNutt.Jr</PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>
+      <InformationURL>
+        <Name>NSSDC Master Catalog</Name>
+        <URL>http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=2004-030A</URL>
+      </InformationURL>
+    </ResourceHeader>
+    <Location>
+      <ObservatoryRegion>Heliosphere.Inner</ObservatoryRegion>
+      <ObservatoryRegion>Mercury</ObservatoryRegion>
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/MEX.xml
@@ -0,0 +1,20 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/MEX</ResourceID>
+    <ResourceHeader>
+      <ResourceName>MEX</ResourceName>
+      <AlternateName>Mars-Express</AlternateName>
+      <ReleaseDate>2010-09-27T18:45:12Z</ReleaseDate>
+      <Description></Description>
+      <Contact>     
+        <PersonID> </PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>      
+    </ResourceHeader>
+    <Location> 
+      <ObservatoryRegion>Mars</ObservatoryRegion>      
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/MGS.xml
@@ -0,0 +1,42 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/MGS</ResourceID>
+    <ResourceHeader>
+      <ResourceName>MGS</ResourceName>      
+      <AlternateName>Mars Global Surveyor</AlternateName>
+      <AlternateName>1996-062A</AlternateName>
+      <ReleaseDate>2010-08-05T18:19:17Z</ReleaseDate>
+      <Description>The Mars Global Surveyor (MGS) orbited Mars over a seven year period and collected data on the surface morphology, topography, composition, gravity, atmospheric dynamics, and magnetic field. This data is used to investigate the surface processes, geology, distribution of material, internal properties, evolution of the magnetic field, and the weather and climate of Mars.
+      
+Spacecraft and Subsystems
+
+The spacecraft itself is a rectangular box approximately 1.17 x 1.17 x 1.7 meters in size, made up of two parts, the equipment module and the propulsion module. All instruments except the magnetometer are stored on the nadir equipment deck, on one of the 1.17 x 1.17 meter surfaces. This is the top of the equipment module, which is 0.735 m high. The main thruster and propulsion tanks are on the opposite side from the instruments, on the propulsion module, which is approximately 1 meter high. Two solar panels, each 3.5 x 1.9 m in size, extend out from opposite sides of the craft. A 1.5 meter diameter parabolic high gain dish antenna is mounted on an adjacent side, and attached to a 2 meter boom, which is extended for mapping operations so the antenna is held away from the body of the spacecraft.
+
+The spacecraft is three-axis stabilized with no scan platform. The main 596 N thruster used hydrazine and N2O4 propellant. Control is through 12 4.45 N hydrazine thrusters, mounted in four groups of three (two aft facing and one roll control thruster). The initial propellant load was 216.5 kg of hydrazine and 144 kg of N2O4. Four solar array panels (2 GaAs, 2 SI) provided 980 W of power to the spacecraft. Energy was stored in two 20 Amp-hr nickel hydrogen batteries, and supplied at 28 V DC. Temperature control was primarily passive with multilayer insulation, thermal radiators, and louvers, augmented by electrical heaters. Communications was achieved via the deep space network using the high gain antenna and two low gain antennas, one mounted on the high gain antenna and one on the equipment module. Uplink was in the X-band, downlink in the X and Ka bands. Minimum downlink rate was 21.33 kbps, 2 kbps engineering data downlink, and 10 bps emergency downlink.
+
+The instruments on the nadir equipment deck consist of a camera, thermal emission spectrometer, laser altimeter, and a radio transmission relay. A magnetometer/electron reflectometer sensor is attached to the end of each solar array, and an ultra-stable oscillator is used for tracking and gravity determination. An 8086 processor is used for the payload data subsystem, and 1750A processors for the standard controls processor and the engineering data formatter. Data is stored on four 0.75 Gb solid state recorders.
+
+Mission Profile
+
+After launch on a Delta 7925 (a Delta II Lite launch vehicle with nine strap-on solid-rocket boosters and a Star 48 (PAM-D) third stage) and a 10 month cruise phase, the Mars Global Surveyor was inserted into an elliptical capture orbit at 01:17 UT 12 September 1997. Over the next four months, it was intended that aerobraking maneuvers and thrusters would be used to lower the orbit to the final circular mapping orbit. However, one of the solar panels failed to latch properly when it was deployed and subsequently showed unexpected motion and moved past its fully deployed position when aerobraking began (thought to be due to the fracture of a damper arm and subsequent structural damage). A new aerobraking schedule was employed, which involved slower aerobraking putting less pressure on the solar panels through April 1998, at which time an 11.6 hour science phasing orbit with a 171 km periapsis was achieved and aerobraking was halted. After a 5 month hiatus, aerobraking was resumed on 23 September 1998. Science observations were made periodically during these maneuvers.
+
+After aerobraking ended in February 1999, MGS was in a 118 minute circular polar science mapping orbit with an index altitude of 378 km. The orbit is sun-synchronous (2 a.m./2 p.m.) and maps over the 2 p.m. crossing from south to north (instead of north to south as originally planned). The orbit has a 7 day near-repeat cycle so Mars will be mapped in 26 day cycles. Science mapping began in mid-March 1999, which was summer in the northern hemisphere on Mars. The primary mission lasted one martian year (687 Earth days) through January, 2001. An extended mission took place until April 2002, further extensions were added until contact with the spacecraft was lost on 2 November 2006.</Description>
+      <Contact>
+        <!-- Arden Albee -->
+        <PersonID>spase://SMWG/Person/Arden.L.Albee</PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>
+      <InformationURL>
+        <Name>NSSDC's Master Catalog</Name>
+        <URL>http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1996-062A</URL>
+        <Description>Information about the Mars Global Surveyor mission</Description>
+      </InformationURL>
+    </ResourceHeader>
+    <Location>
+      <ObservatoryRegion>Mars</ObservatoryRegion>
+      <ObservatoryRegion>Heliosphere.Outer</ObservatoryRegion>
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/Magion-4.xml
@@ -0,0 +1,44 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/Magion-4</ResourceID>
+    <ResourceHeader>
+      <ResourceName>Magion-4</ResourceName>
+      <AlternateName>1995-039F</AlternateName>
+      <AlternateName>S2-X</AlternateName>
+      <AlternateName>Tail Subsatellite S2-X</AlternateName>
+      <AlternateName>Interball S2-X</AlternateName>
+      <ReleaseDate>2010-09-27T18:41:14Z</ReleaseDate>
+      <Description>The Interball Project is a multi-national effort that consists of four spacecraft: two main spacecraft of the Prognoz series, made in Russia, each with a small subsatellite made in Czechoslovakia. The main objective is to study the physical mechanisms responsible for the transmission of solar wind energy to the magnetosphere, its storage there, and subsequent dissipation in the tail and auroral regions of the magnetosphere, ionosphere, and atmosphere during magnetospheric substorms. A ground-based support group will provide coordinated and simultaneous ground-based data of many types, including observations from auroral and polar cap regions. Interball is an IACG-related mission. Key physical parameters will be generated, and will be available for exchange with other projects. Campaigns for intercomparison with the Wind and Geotail spacecraft are expected. One pair of spacecraft, Tail Probe and its subsatellite S2-X (X for the first letter of the Russian word for ``Tail''), will be launched into the magnetospheric tail. The second pair, Auroral Probe and S2-A (A for ``Auroral''), will have an orbit that crosses the auroral oval to observe the acceleration of auroral particles and the flow of electric currents that connect the magnetospheric tail with the conducting ionosphere. To study the equilibrium tail structure, during about half of each year the Tail Probe pair will cross the main parts of the magnetotail every four days. The Tail Probe, with approximately 30 earth radii apogee, will cross the noon-midnight plane on December 1, so the measurements in the magnetotail will cover the period from October 1995 to February 1996. The Auroral Probe pair will support the Tail Probe pair with auroral region measurements.
+
+Each main spacecraft has more than twenty scientific instruments. The spacecraft is cylindrical, with spin axis toward the sun (within 10 degrees), and with spin period of ~120 s. The electric and magnetic field sensors are on booms connected to the ends of the solar panels.
+
+The subsatellites are small, each with about ten scientific instruments. The spin axis will be directed within 10 degrees of the sun, with a spin period of ~120 s, as with the main spacecraft. The subsatellites also carry gas-jet thrusters for limited control of the orbit. Separation distance will range from hundreds of kilometers to several tens of thousands of kilometers for the Tail Probe pair. Separation distance will range from hundreds of meters to hundreds of kilometers for the Auroral Probe pair. The Tail Probe has two telemetry systems, at up to 32 Kbps in real-time, with a memory mode capacity of 30 Mb in the RTK telemetry system and 120 Mb in the SSNI system. The Auroral Probe has similar capability plus the additional real-time-only STO system, capable of 40 Kbps. Each subsatellite has only the STO real-time telemetry system. For S2-X the rate can be varied from 2--40 kbps.
+
+The Tail Probe has an adapting alert mode while in the memory mode, allowing time resolutions that are the same as in the real-time mode. The aim is to have the highest time resolution available at the thin borders of magnetospheric regions or the sharp borders of some features. In the alert mode (triggered by an on-board computer monitoring plasma and field parameters), the bit rate is increased for plasma, field, and wave measurements. The duration of these alert periods is about 10 minutes, and there can be 5--6 of them during one orbit.</Description>
+      <Contact>
+        <PersonID>spase://SMWG/Person/Jan.Merka</PersonID>
+        <Role>MetadataContact</Role>
+      </Contact>
+      <InformationURL>
+        <Name>Magion-4 Spacecraft (IKI page)</Name>
+        <URL>http://www.iki.rssi.ru/interball/magion.html</URL>
+        <Description>Magion-4 spacecraft description at the Russian Space Research Institute (IKI)</Description>
+      </InformationURL>
+      <InformationURL>
+        <Name>NSSDC's Master Catalog</Name>
+        <URL>http://nssdc.gsfc.nasa.gov/nmc/masterCatalog.do?sc=1995-039F</URL>
+        <Description>Information about the Interball S2-X mission</Description>
+      </InformationURL>
+    </ResourceHeader>
+    <ObservatoryGroupID>spase://CDPP/Observatory/AMDA/Interball-Tail</ObservatoryGroupID>
+    <Location>
+      <ObservatoryRegion>Heliosphere.NearEarth</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosheath</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosphere</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosphere.Main</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosphere.Polar</ObservatoryRegion>
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/MarsExpress.xml
@@ -0,0 +1,33 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/MarsExpress</ResourceID>
+    <ResourceHeader>
+      <ResourceName>Mars Express</ResourceName>
+      <ReleaseDate>2012-06-13T00:00:00Z</ReleaseDate>
+      <Description>ESA's Mars Express mission was launched 02-June-2003 
+and arrived at Mars in December, 2003.  A lander, Beagle 2, was deployed
+on 19-Dec-2003, but communication was lost prior to any science data
+capture.  The main spacecraft went into a polar orbit on 25-Dec-2003, with
+apogee and perigee altitudes of 11,634 km and 279 km (3.4 and 0.08 Martian
+radii).  The scientific objectives of the 3-axis-stabilized Mars Express 
+Orbiter are to obtain global high-resolution photo-geology (10 m resolution), 
+mineralogical mapping (100 m resolution) and mapping of the atmospheric 
+composition, study the subsurface structure, the global atmospheric 
+circulation, and the interaction between the atmosphere and the subsurface, 
+and the atmosphere and the interplanetary medium.</Description>
+      <Contact>
+        <PersonID>spase://SMWG/Person/Rudolf.J.Schmidt</PersonID>
+        <Role>GeneralContact</Role>
+      </Contact>
+      <InformationURL>
+        <Name>ESA Mars Express web page</Name>
+        <URL>http://www.esa.int/SPECIALS/Mars_Express/index.html</URL>
+      </InformationURL>
+    </ResourceHeader>
+    <Location>
+      <ObservatoryRegion>Mars</ObservatoryRegion>
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/OMNI.xml
@@ -0,0 +1,50 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/OMNI</ResourceID>
+    <ResourceHeader>
+      <ResourceName>OMNI</ResourceName>
+      <ReleaseDate>2011-08-18T15:57:51Z</ReleaseDate>
+      <Description>The OMNI observatory is a virtual observatory representing the collection of spacecraft used in the creation of the OMNI datasets.  
+            The observatories used within the OMNI datasets are ACE, Wind, IMP8, Geotail, GOES and various other spacecraft. For any given time period 
+            OMNI uses a selection criteria to select the "best" available data to be used.  Thus, a data record may consist of data from multiple
+            observatories.  Without looking at each data record it is not possible to tell which observatories contributed. As result, the OMNI 
+            observatories is used as a proxy for the set of possible contributing observatories. Complete details on the instruments and the 
+            selection criteria are available at the Information URLs listed below.</Description>
+      <Contact>
+        <PersonID>spase://SMWG/Person/Joseph.H.King</PersonID>
+        <Role>Scientist</Role>
+      </Contact>
+      <InformationURL>
+        <Name>Overview of High Resolution OMNI</Name>
+        <URL>http://omniweb.gsfc.nasa.gov/html/HROdocum.html</URL>
+        <Description>Description of the instruments and processing techniques used in the creation of high resolution OMNI</Description>
+      </InformationURL>
+      <InformationURL>
+        <Name>Overview of Low Resolution OMNI</Name>
+        <URL>http://omniweb.gsfc.nasa.gov/html/ow_data.html</URL>
+        <Description>Description of the instruments and processing techniques used in the creation of low resolution OMNI</Description>
+      </InformationURL>
+      <Association>
+        <AssociationID>spase://SMWG/Observatory/ACE</AssociationID>
+        <AssociationType>PartOf</AssociationType>
+      </Association>
+      <Association>
+        <AssociationID>spase://SMWG/Observatory/Wind</AssociationID>
+        <AssociationType>PartOf</AssociationType>
+      </Association>
+      <Association>
+        <AssociationID>spase://SMWG/Observatory/IMP8</AssociationID>
+        <AssociationType>PartOf</AssociationType>
+      </Association>
+      <Association>
+        <AssociationID>spase://SMWG/Observatory/Geotail</AssociationID>
+        <AssociationType>PartOf</AssociationType>
+      </Association>
+    </ResourceHeader>
+    <Location>
+      <ObservatoryRegion>Heliosphere.NearEarth</ObservatoryRegion>
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/POLAR.xml
@@ -0,0 +1,36 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/POLAR</ResourceID>
+    <ResourceHeader>
+      <ResourceName>Polar</ResourceName>
+      <AlternateName>Polar Plasma Laboratory</AlternateName>
+      <AlternateName>GGS/Polar</AlternateName>
+      <AlternateName>ISTP/Polar</AlternateName>
+      <ReleaseDate>2010-08-05T18:19:11Z</ReleaseDate>
+      <Description>POLAR is one of four spacecraft in the Global Geospace Science (GGS) program. These are among the six spacecraft in the International Solar Terrestrial Physics (ISTP) program. POLAR provides multi-wavelength imaging of the aurora, measuring plasma entry into the polar magnetosphere and geomagnetic tail, the flow of plasmas to and from the ionosphere, and the deposition of particle energy in the ionosphere and upper atmosphere. POLAR has on-board propulsion systems and a design lifetime of three to five years, with redundant subsystems. POLAR is cylindrical, approximately 2.8 m in diameter by 1.25 m high (plus 1.25 m for its two despun platforms), with body-mounted solar cells, weighs 1250 kg and uses 333 W of power. The spin rate is 10 rpm around an axis approximately normal to the orbital plane. It has long wire spin-plane antennas, inertial booms, and spin-plane appendages to support sensors. 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>
+      <Contact>
+        <!-- John Sigwarth -->
+        <PersonID>spase://SMWG/Person/John.B.Sigwarth</PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>
+      <InformationURL>
+        <Name>NASA Polar Project</Name>
+        <URL>http://pwg.gsfc.nasa.gov/polar/</URL>
+        <Description>Web site of NASA Polar Mission, including overview, data products, FTP to the data, publications, educational outreach, orbits, instrument descriptions, contacts, news archive, and ISTP archive.</Description>
+      </InformationURL>
+      <InformationURL>
+        <Name>NSSDC's Master Catalog</Name>
+        <URL>http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1996-013A</URL>
+        <Description>Information about the Polar mission</Description>
+      </InformationURL>
+      <PriorID>spase://vspo/observatory/67</PriorID>
+    </ResourceHeader>
+    <Location>
+      <ObservatoryRegion>Earth.Magnetosphere</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosphere.Polar</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosphere.RadiationBelt</ObservatoryRegion>
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/Pioneer.xml
@@ -0,0 +1,25 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/Pioneer</ResourceID>
+    <ResourceHeader>
+      <ResourceName>Pioneer</ResourceName>
+      <AlternateName>NASA</AlternateName>
+      <ReleaseDate>2010-09-25T03:09:48Z</ReleaseDate>
+      <Description> </Description>
+      <Contact>
+        <PersonID>spase://SMWG/Person/Palmer.Dyal</PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>
+      <InformationURL>
+        <Name>NSSDC's Master Catalog</Name>
+        <URL>http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1972-012A</URL>
+        <Description>Information about the Pioneer 10 mission</Description>
+      </InformationURL>
+    </ResourceHeader>
+    <Location>
+      <ObservatoryRegion>Heliosphere.NearEarth</ObservatoryRegion>
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/Pioneer10.xml
@@ -0,0 +1,43 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/Pioneer10</ResourceID>
+    <ResourceHeader>
+      <ResourceName>Pioneer 10</ResourceName>
+      <AlternateName>1972-012A</AlternateName>
+      <AlternateName>Pioneer-F</AlternateName>
+      <ReleaseDate>2010-09-25T03:09:48Z</ReleaseDate>
+      <Description>This mission was the first to be sent to the outer solar system and the first to investigate the planet Jupiter, after which it followed an escape trajectory from the solar system. The spacecraft achieved its closest approach to Jupiter on December 3, 1973, when it reached approximately 2.8 Jovian radii (about 200,000 km). As of Jan. 1, 1997 Pioneer 10 was at about 67 AU from the Sun near the ecliptic plane and heading outward from the Sun at 2.6 AU/year and downstream through the heliomagnetosphere towards the tail region and interstellar space. This solar system escape direction is unique because the Voyager 1 and 2 spacecraft (and the now terminated Pioneer 11 spacecraft mission) are heading in the opposite direction towards the nose of the heliosphere in the upstream direction relative to the inflowing interstellar gas. The spacecraft is heading generally towards the red star Aldebaran, which forms the eye of Taurus (The Bull). The journey over a distance of 68 light years to Aldebaran will require about two million years to complete. Routine tracking and project data processing operatations were terminated on March 31, 1997 for budget reasons. Occasional tracking continued later under support of the Lunar Prospector project at NASA Ames Research Center with retrieval of energetic particle and radio science data. The last successful data acquisitions through NASA's Deep Space Network (DSN) occurred on March 3, 2002, the 30th anniversary of Pioneer 10's launch date, and on April 27, 2002. The spacecraft signal was last detected on Jan. 23, 2003 after an uplink was transmitted to turn off the last operational experiment, the Geiger Tube Telescope (GTT), but lock-on to the sub-carrier signal for data downlink was not achieved. No signal at all was detected during a final attempt on Feb. 6-7, 2003. Pioneer Project staff at NASA Ames then concluded that the spacecraft power level had fallen below that needed to power the onboard transmitter, so no further attempts would be made.
+
+The history of the Pioneer 10 tracking status is available from the web site of the former Pioneer Project at the following location:
+
+http://spaceprojects.arc.nasa.gov/Space_Projects/pioneer/PNhome.html
+
+Fifteen experiments were carried to study the interplanetary and planetary magnetic fields; solar wind parameters; cosmic rays; transition region of the heliosphere; neutral hydrogen abundance; distribution, size, mass, flux, and velocity of dust particles; Jovian aurorae; Jovian radio waves; atmosphere of Jupiter and some of its satellites, particularly Io; and to photograph Jupiter and its satellites. Instruments carried for these experiments were magnetometer, plasma analyzer, charged particle detector, ionizing detector, non-imaging telescopes with overlapping fields of view to detect sunlight reflected from passing meteoroids, sealed pressurized cells of argon and nitrogen gas for measuring the penetration of meteoroids, UV photometer, IR radiometer, and an imaging photopolarimeter, which produced photographs and measured polarization. Further scientific information was obtained from the tracking and occultation data.
+
+The spacecraft body was mounted behind a 2.74-m-diameter parabolic dish antenna that was 46 cm deep. The spacecraft structure was a 36-cm-deep flat equipment compartment, the top and bottom being regular hexagons. Its sides were 71 cm long. One side joined a smaller compartment that carried the scientific experiments. The high-gain antenna feed was situated on three struts, which projected forward about 1.2 m. This feed was topped with a medium-gain antenna. A low-gain omnidirectional antenna extended about 0.76 m behind the equipment compartment and was mounted below the high-gain antenna. Power for the spacecraft was obtained by four SNAP-19 radioisotope thermonuclear generators (RTG), which were held about 3 m from the center of the spacecraft by two three-rod trusses 120 deg apart. A third boom extended 6.6 m from the experiment compartment to hold the magnetometer away from the spacecraft. The four RTG's generated about 155 W at launch and decayed to approximately 140 W by the time the spacecraft reached Jupiter, 21 months after launch. There were three reference sensors: a star sensor for Canopus which failed shortly after Jupiter encounter and two sun sensors. Attitude position could be calculated from the reference directions to the earth and the sun, with the known direction to Canopus as a backup. Three pairs of rocket thrusters provided spin-rate control and changed the velocity of the spacecraft, the spin period near the end of the mission being 14.1 seconds. These thrusters could be pulsed or fired steadily by command. The spacecraft was temperature-controlled between minus 23 deg C and plus 38 deg C. A plaque was mounted on the spacecraft body with drawings depicting a man, a woman, and the location of the sun and the earth in our galaxy.
+
+Communications were maintained via (1) the omnidirectional and medium-gain antennas which operated together while connected to one receiver and (2) the high-gain antenna which was connected to another receiver. These receivers could be interchanged by command to provide some redundancy. Two radio transmitters, coupled to two traveling-wave tube amplifiers, produced 8 W at 2292 MHz each. Uplink was accomplished at 2110 MHz, while data transmission downlink was at 2292 MHz. The data were received by NASA's Deep Space Network (DSN) at bit rates up to 2048 bps enroute to Jupiter and at 16 bps near end of the mission.
+
+Space experiments mostly continued to operate for planetary or interplanetary measurements until failure or until insufficient spacecraft power from the RTG's was available for operation of all instruments, such that some were turned off permanently and others were cycled on and off in accordance with a power sharing plan implemented in September 1989. The Asteroid/Meteroid Detector failed in December 1973, followed by the Helium Vector Magnetometer (HVM) in November 1975 and the Infrared Radiometer in January 1974. The Meteroid Detector was turned off in October 1980 due to inactive sensors at low temperatures. The spacecraft sun sensors became inoperative in May 1986, and the Imaging Photopolarimeter (IPP) instrument was used to obtain roll phase and spin period information until being turned off in October 1993 to conserve power. The Trapped Radiation Detector (TRD) and Plasma Analyzer (PA) were respectively turned off in November 1993 and September 1995 for the same reason. As of January 1996 the final power cycling plan included part-time operations of the Charged Particle Instrument (CPI), the Cosmic Ray Telescope (CRT), the Geiger Tube Telescope (GTT), and the Ultraviolet Photometer (UV). As of August 2000, only the GTT instrument was still returning data.
+
+Various other spacecraft subsystems also either failed or were turned off for power or other reasons, and an account of these may be of interest for engineering design of long duration deep space missions. The primary antenna feed offset bellows failed sometime in 1976 but a redundant unit was available for use thereafter. The Program Storage and Execution (PSE) subsystem was turned off in September 1989 for power conservation, after which spacecraft maneuvers were performed by ground command sequences. A receiver problem in mid-1992 prevented uplink to the high gain antenna, after which uplink commands could only be sent with 70-meter DSN antennas which also supported the 16 bps downlink. The Backup Line Heater experienced a sticking thermostat operation in March 1993 for 30 days but the problem did not reoccur. Undervoltage Protection Logic was turned off in December 1993 to prevent loss of critical spacecraft systems in the event of a transient undervoltage condition. Duration and Steering Logic (DSL) was turned off in February 1995 to conserve power, after which it was turned on again only for spacecraft maneuvers. RTG power levels are low enough that the spacecraft occasionally relies in part on battery power (accumulated during inactive periods) to run experiments and other systems.
+
+The total mission cost for Pioneer 10 through the 1997 end of official science operations was about 350 million in FY 2001 U.S. dollars. This included about 200 million dollars for pre-launch design and development, and another 150 million for launch, telemetry tracking, mission operations and data analysis. These estimates were provided by the former Pioneer Project at NASA Ames Research Center.</Description>
+      <Contact>
+        <PersonID>spase://SMWG/Person/Palmer.Dyal</PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>
+      <InformationURL>
+        <Name>NSSDC's Master Catalog</Name>
+        <URL>http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1972-012A</URL>
+        <Description>Information about the Pioneer 10 mission</Description>
+      </InformationURL>
+    </ResourceHeader>
+    <ObservatoryGroupID>spase://CDPP/Observatory/AMDA/Pioneer</ObservatoryGroupID>
+    <Location>
+      <ObservatoryRegion>Heliosphere.NearEarth</ObservatoryRegion>
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/Pioneer11.xml
@@ -0,0 +1,37 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/Pioneer11</ResourceID>
+    <ResourceHeader>
+      <ResourceName>Pioneer 11</ResourceName>
+      <AlternateName>1973-019A</AlternateName>
+      <AlternateName>Pioneer-G</AlternateName>
+      <ReleaseDate>2010-09-25T03:09:48Z</ReleaseDate>
+      <Description>Pioneer 11 was the second mission to investigate Jupiter and the outer solar system and the first to explore the planet Saturn and its main rings. Pioneer 11, like Pioneer 10, used Jupiter's gravitational field to alter its trajectory radically. It passed close to Saturn and then it followed an escape trajectory from the solar system.
+
+The spacecraft was 2.9 m long and contained a 2.74-m diameter high-gain antenna of aluminum honeycomb sandwich material whose feed was topped with a medium-gain antenna. A low-gain, omnidirectional antenna was mounted below the high-gain dish. The spacecraft contained two nuclear electric-power generators, which generated 144 W at Jupiter, but decreased to 100 W at Saturn. There were three reference sensors: a star (Canopus) sensor, and two sun sensors. Attitude position could be calculated from the reference direction to the earth and the sun, with the known direction to Canopus as backup. Pioneer 11's star sensor gain and threshold settings were modified, based on experience gained from the settings used on Pioneer 10. Three pairs of rocket thrusters provided spin-axis control (maintained at 4.8 rpm) and change of the spacecraft velocity. The thrusters could be either fired steadily or pulsed, by command.
+
+Communications were maintained via the omnidirectional and medium-gain antennas, which operated together, connected to one receiver, while the high-gain antenna was connected to the other receiver. The receivers could be interchanged by command. Two radio transmitters, coupled to two traveling-wave tube amplifiers, produced 8 W power each in S-band. Communication uplink (earth to spacecraft) operated at 2110 MHz, and downlink (spacecraft to earth) at 2292 MHz. At Jupiter's distance, round-trip communication time took 92 min. Data were received at the Deep Space Network (DSN). The spacecraft was temperature-controlled to between -23 and +38 deg C (-10 to +100 deg F). An additional experiment, a low-sensitivity fluxgate magnetometer, was added to the Pioneer 11 payload.
+
+Instruments studied the interplanetary and planetary magnetic fields; solar wind properties; cosmic rays; transition region of the heliosphere; neutral hydrogen abundance; distribution, size, mass, flux, and velocity of dust particles; Jovian aurorae; Jovian radio waves; the atmospheres of planets and satellites; and the surfaces of Jupiter, Saturn, and some of their satellites. Instruments carried for these experiments were magnetometer, plasma analyzer (for solar wind), charged-particle detector, ionizing detector, non-imaging telescopes with overlapping fields of view to detect sunlight reflected from passing meteoroids, sealed pressurized cells of argon and nitrogen gas for measuring penetration of meteoroids, UV photometer, IR radiometer, and an imaging photopolarimeter, which produced photographs and measured the polarization. Further scientific information was obtained from celestial mechanics and occultation phenomena.
+
+This spacecraft, like Pioneer 10, contains a plaque that has a drawing depicting man, woman, and the location of the sun and earth in the galaxy.
+
+During its closest approach, December 4, 1974, Pioneer 11 passed to within 34,000 km of Jupiter's cloud tops. It passed by Saturn on September 1, 1979, at a distance of 21,000 km from Saturn's cloud tops. The spacecraft has operated on a backup transmitter since launch. Instrument power sharing began in February 1985 due to declining RTG power output. Science operations and daily telemetry ceased on September 30, 1995 when the RTG power level was insufficient to operate any experiments. As of the end of 1995 the spacecraft was located at 44.7 AU from the Sun at a nearly asymptotic latitude of 17.4 degrees above the solar equatorial plane and was heading outward at 2.5 AU/year.</Description>
+      <Contact>
+        <PersonID>spase://SMWG/Person/Palmer.Dyal</PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>
+      <InformationURL>
+        <Name>NSSDC's Master Catalog</Name>
+        <URL>http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1973-019A</URL>
+        <Description>Information about the Pioneer 11 mission</Description>
+      </InformationURL>
+    </ResourceHeader>
+    <ObservatoryGroupID>spase://CDPP/Observatory/AMDA/Pioneer</ObservatoryGroupID>
+    <Location>
+      <ObservatoryRegion>Heliosphere.NearEarth</ObservatoryRegion>
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/PioneerVenusOrbiter.xml
@@ -0,0 +1,31 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/PioneerVenusOrbiter</ResourceID>
+    <ResourceHeader>
+      <ResourceName>Pioneer Venus Orbiter</ResourceName>
+      <AlternateName>1978-051A</AlternateName>
+      <AlternateName>Pioneer Venus 1</AlternateName>
+      <AlternateName>PVO</AlternateName>
+      <AlternateName>Pioneer 12</AlternateName>
+      <AlternateName>Pioneer Venus 1978 Orbiter</AlternateName>
+      <ReleaseDate>2010-09-25T03:09:48Z</ReleaseDate>
+      <Description>The Pioneer Venus Orbiter was the first of a two-spacecraft orbiter-probe combination designed to conduct a comprehensive investigation of the atmosphere of Venus. The spacecraft was a solar-powered cylinder about 250 cm in diameter with its spin axis spin-stabilized perpendicular to the ecliptic plane. A high-gain antenna was mechanically despun to remain focused on the earth. The instruments were mounted on a shelf within the spacecraft except for a magnetometer mounted at the end of a boom to ensure against magnetic interference from the spacecraft. Pioneer Venus Orbiter measured the detailed structure of the upper atmosphere and ionosphere of Venus, investigated the interaction of the solar wind with the ionosphere and the magnetic field in the vicinity of Venus, determined the characteristics of the atmosphere and surface of Venus on a planetary scale, determined the planet's gravitational field harmonics from perturbations of the spacecraft orbit, and detected gamma-ray bursts. UV observations of comets have also been made. From Venus orbit insertion on December 4, 1978 to July 1980 periapsis was held between 142 and 253 km to facilitate radar and ionospheric measurements. Thereafter, the periapsis was allowed to rise (to 2290 km at maximum) and then fall, to conserve fuel. In 1991 the Radar Mapper was reactivated to investigate previously inaccessible southern portions of the planet. In May 1992 Pioneer Venus began the final phase of its mission, in which the periapsis was held between 150 and 250 km until the fuel ran out and atmospheric entry destroyed the spacecraft the following August. The orbiter cost $125 million to build and operate for the first 10 years. For further details see Colin, L. and Hunten, D. M., Space Science Reviews 20, 451, 1977.</Description>
+      <Contact>
+        <PersonID>spase://SMWG/Person/Lawrence.Colin</PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>
+      <InformationURL>
+        <Name>NSSDC's Master Catalog</Name>
+        <URL>http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1978-051A</URL>
+        <Description>Information about the Pioneer Venus Orbiter mission</Description>
+      </InformationURL>
+    </ResourceHeader>
+    <ObservatoryGroupID>spase://CDPP/Observatory/AMDA/Pioneer</ObservatoryGroupID>
+    <Location>
+      <ObservatoryRegion>Venus</ObservatoryRegion>
+      <ObservatoryRegion>Heliosphere.Inner</ObservatoryRegion>
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/Rosetta.xml
@@ -0,0 +1,20 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/Rosetta</ResourceID>
+    <ResourceHeader>
+      <ResourceName>Rosetta</ResourceName>
+      <AlternateName>ESA mission to the comet Churjumov-Gerasimenko</AlternateName>
+      <ReleaseDate>2010-09-27T18:45:12Z</ReleaseDate>
+      <Description></Description>
+      <Contact>     
+        <PersonID> </PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>      
+    </ResourceHeader>
+    <Location> 
+      <ObservatoryRegion>Comet</ObservatoryRegion>      
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/STEREO-A.xml
@@ -0,0 +1,35 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/STEREO-A</ResourceID>
+    <ResourceHeader>
+      <ResourceName>STEREO A</ResourceName>
+      <AlternateName>STEREO Ahead</AlternateName>
+      <AlternateName>STEREO East</AlternateName>
+      <AlternateName>Solar Terrestrial Relations Observatory A</AlternateName>
+      <ReleaseDate>2010-09-25T03:09:48Z</ReleaseDate>
+      <Description>The Solar-Terrestrial Relations Observatory (STEREO) mission includes two spacecraft respectively lagging (STEREO A) and leading (STEREO B) the Earth in heliocentric orbit around the Sun for remote 3-D imaging and radio observations of coronal mass ejections (CMEs). These events are responsible for large solar energetic particle events in interplanetary space and are the primary cause of major geomagnetic storms at Earth. The two spacecraft are launched to drift slowly away from the Earth in opposite directions at about 10 degrees per year for the lagging spacecraft and 20 degrees per year for the leading one. Optimal longitudinal separation of about sixty degrees is achieved after two years. Afterwards the separation gradually increases beyond the design lifetime of two years with the possibility of extended mission observations at larger angles. Science instruments selected for STEREO include the Sun Earth Connection Coronal and Heliospheric Investigation (SECCHI) for extreme ultraviolet (EUV), white-light coronographic, and heliospheric imaging, the STEREO/WAVES (SWAVES) interplanetary radio burst tracker, the In situ Measurements of Particles and CME Transients (IMPACT) investigation for in-situ sampling the 3-D distribution and plasma characteristics of solar energetic particles and the interplanetary magnetic field, and the PLAsma and SupraThermal Ion and Composition (PLASTIC) experiment to measure elemental and charge composition of ambient and CME plasma ions. STEREO data recorded and stored onboard each spacecraft will be downlinked through the NASA Deep Space Network on a daily schedule. Real-time space weather data will be continuously transmitted through a separate beacon system to NASA and non-NASA receiving stations.</Description>
+      <Contact>
+        <!-- Mike Kaiser -->
+        <PersonID>spase://SMWG/Person/Michael.L.Kaiser</PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>
+      <InformationURL>
+        <Name>STEREO Project Page</Name>
+        <URL>http://stereo.gsfc.nasa.gov/</URL>
+        <Description>Project home page</Description>
+      </InformationURL>
+      <InformationURL>
+        <Name>NSSDC's Master Catalog</Name>
+        <URL>http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=2006-047A</URL>
+        <Description>Information about the STEREO A mission</Description>
+      </InformationURL>
+      <PriorID>spase://vspo/observatory/139</PriorID>
+    </ResourceHeader>
+    <ObservatoryGroupID>spase://CDPP/Observatory/AMDA/STEREO</ObservatoryGroupID>
+    <Location>
+      <ObservatoryRegion>Heliosphere.Remote1AU</ObservatoryRegion>
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/STEREO-B.xml
@@ -0,0 +1,35 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/STEREO-B</ResourceID>
+    <ResourceHeader>
+      <ResourceName>STEREO B</ResourceName>
+      <AlternateName>STEREO Behind</AlternateName>
+      <AlternateName>STEREO West</AlternateName>
+      <AlternateName>Solar Terrestrial Relations Observatory B</AlternateName>
+      <ReleaseDate>2010-09-25T03:09:48Z</ReleaseDate>
+      <Description>The Solar-Terrestrial Relations Observatory (STEREO) mission includes two spacecraft respectively lagging (STEREO A) and leading (STEREO B) the Earth in heliocentric orbit around the Sun for remote 3-D imaging and radio observations of coronal mass ejections (CMEs). These events are responsible for large solar energetic particle events in interplanetary space and are the primary cause of major geomagnetic storms at Earth. The two spacecraft are launched to drift slowly away from the Earth in opposite directions at about 10 degrees per year for the lagging spacecraft and 20 degrees per year for the leading one. Optimal longitudinal separation of about sixty degrees is achieved after two years. Afterwards the separation gradually increases beyond the design lifetime of two years with the possibility of extended mission observations at larger angles. Science instruments selected for STEREO include the Sun Earth Connection Coronal and Heliospheric Investigation (SECCHI) for extreme ultraviolet (EUV), white-light coronographic, and heliospheric imaging, the STEREO/WAVES (SWAVES) interplanetary radio burst tracker, the In situ Measurements of Particles and CME Transients (IMPACT) investigation for in-situ sampling the 3-D distribution and plasma characteristics of solar energetic particles and the interplanetary magnetic field, and the PLAsma and SupraThermal Ion and Composition (PLASTIC) experiment to measure elemental and charge composition of ambient and CME plasma ions. STEREO data recorded and stored onboard each spacecraft will be downlinked through the NASA Deep Space Network on a daily schedule. Real-time space weather data will be continuously transmitted through a separate beacon system to NASA and non-NASA receiving stations.</Description>
+      <Contact>
+        <!-- Mike Kaiser -->
+        <PersonID>spase://SMWG/Person/Michael.L.Kaiser</PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>
+      <InformationURL>
+        <Name>STEREO Project Page</Name>
+        <URL>http://stereo.gsfc.nasa.gov/</URL>
+        <Description>Project home page</Description>
+      </InformationURL>
+      <InformationURL>
+        <Name>NSSDC's Master Catalog</Name>
+        <URL>http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=2006-047B</URL>
+        <Description>Information about the STEREO B mission</Description>
+      </InformationURL>
+      <PriorID>spase://vspo/observatory/140</PriorID>
+    </ResourceHeader>
+    <ObservatoryGroupID>spase://CDPP/Observatory/AMDA/STEREO</ObservatoryGroupID>
+    <Location>
+      <ObservatoryRegion>Heliosphere.Remote1AU</ObservatoryRegion>
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/STEREO.xml
@@ -0,0 +1,26 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/STEREO</ResourceID>
+    <ResourceHeader>
+      <ResourceName>STEREO</ResourceName>
+      <AlternateName>Solar Terrestrial Relations Observatory; NASA</AlternateName>
+      <ReleaseDate>2010-09-25T03:09:48Z</ReleaseDate>
+      <Description>The Solar-Terrestrial Relations Observatory (STEREO) mission includes two spacecraft respectively lagging (STEREO A) and leading (STEREO B) the Earth in heliocentric orbit around the Sun for remote 3-D imaging and radio observations of coronal mass ejections (CMEs). These events are responsible for large solar energetic particle events in interplanetary space and are the primary cause of major geomagnetic storms at Earth. The two spacecraft are launched to drift slowly away from the Earth in opposite directions at about 10 degrees per year for the lagging spacecraft and 20 degrees per year for the leading one. Optimal longitudinal separation of about sixty degrees is achieved after two years. Afterwards the separation gradually increases beyond the design lifetime of two years with the possibility of extended mission observations at larger angles. Science instruments selected for STEREO include the Sun Earth Connection Coronal and Heliospheric Investigation (SECCHI) for extreme ultraviolet (EUV), white-light coronographic, and heliospheric imaging, the STEREO/WAVES (SWAVES) interplanetary radio burst tracker, the In situ Measurements of Particles and CME Transients (IMPACT) investigation for in-situ sampling the 3-D distribution and plasma characteristics of solar energetic particles and the interplanetary magnetic field, and the PLAsma and SupraThermal Ion and Composition (PLASTIC) experiment to measure elemental and charge composition of ambient and CME plasma ions. STEREO data recorded and stored onboard each spacecraft will be downlinked through the NASA Deep Space Network on a daily schedule. Real-time space weather data will be continuously transmitted through a separate beacon system to NASA and non-NASA receiving stations.</Description>
+      <Contact>
+        <!-- Mike Kaiser -->
+        <PersonID>spase://SMWG/Person/Michael.L.Kaiser</PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>
+      <InformationURL>
+        <Name>STEREO Project Page</Name>
+        <URL>http://stereo.gsfc.nasa.gov/</URL>
+        <Description>Project home page</Description>
+      </InformationURL>      
+    </ResourceHeader>
+    <Location>
+      <ObservatoryRegion>Heliosphere.Remote1AU</ObservatoryRegion>
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/Solar_Orbiter.xml
@@ -0,0 +1,20 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/Solar_Orbiter</ResourceID>
+    <ResourceHeader>
+      <ResourceName>Solar Orbiter</ResourceName>
+      <AlternateName></AlternateName>
+      <ReleaseDate>2010-09-27T18:45:12Z</ReleaseDate>
+      <Description></Description>
+      <Contact>     
+        <PersonID> </PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>      
+    </ResourceHeader>
+    <Location> 
+      <ObservatoryRegion>Heliosphere.Inner</ObservatoryRegion>      
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/Solar_Probe_Plus.xml
@@ -0,0 +1,20 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/Solar_Probe_Plus</ResourceID>
+    <ResourceHeader>
+      <ResourceName>Solar Probe Plus</ResourceName>
+      <AlternateName></AlternateName>
+      <ReleaseDate>2010-09-27T18:45:12Z</ReleaseDate>
+      <Description></Description>
+      <Contact>     
+        <PersonID> </PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>      
+    </ResourceHeader>
+    <Location> 
+      <ObservatoryRegion>Heliosphere.Inner</ObservatoryRegion>      
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/THEMIS.xml
@@ -0,0 +1,36 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/THEMIS</ResourceID>
+    <ResourceHeader>
+      <ResourceName>THEMIS</ResourceName>
+      <AlternateName>Time History of Events and Macroscale Interactions during Substorms; NASA Magnetospheric Mission</AlternateName>
+      <ReleaseDate>2010-09-24T21:35:00Z</ReleaseDate>
+      <Description></Description>
+      <Acknowledgement>National Aeronautics and Space Administration/United States</Acknowledgement>
+      <Contact>
+        <!-- Vassilis Angelopoulos -->
+        <PersonID>spase://SMWG/Person/Vassilis.Angelopoulos</PersonID>
+        <Role>PrincipalInvestigator</Role>
+      </Contact>
+      <Contact>
+        <!-- David Sibeck -->
+        <PersonID>spase://SMWG/Person/David.G.Sibeck</PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>
+      <InformationURL>
+        <Name>Time History of Events and Macroscale Interactions during Substorms (THEMIS) mission </Name>
+        <URL>http://themis.ssl.berkeley.edu/index.shtml</URL>
+        <Description>THEMIS Mission Homepage</Description>
+      </InformationURL>     
+    </ResourceHeader>
+    <Location> 
+      <ObservatoryRegion>Earth.Magnetosphere</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosphere.Magnetotail</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosphere.Main</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosheath</ObservatoryRegion>
+      <ObservatoryRegion>Heliosphere.NearEarth</ObservatoryRegion>
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/THEMIS/A.xml
@@ -0,0 +1,50 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/THEMIS/A</ResourceID>
+    <ResourceHeader>
+      <ResourceName>THEMIS-A</ResourceName>
+      <AlternateName>Explorer 85</AlternateName>
+      <AlternateName>2007-004A</AlternateName>
+      <AlternateName>MIDEX/THEMIS</AlternateName>
+      <AlternateName>THEMIS-P5</AlternateName>
+      <AlternateName>30580</AlternateName>
+      <ReleaseDate>2010-09-24T21:35:00Z</ReleaseDate>
+      <Description>The Time History of Events and Macroscale Interactions during Substorms (THEMIS) mission is a five-satellite Explorer mission whose primary objective is to understand the onset and macroscale evolution of magnetospheric substorms. Most importantly, THEMIS will find out which magnetotail process is responsible for substorm onset: (a) a local disruption of the plasma sheet current; or, (b) that current's interaction with the rapid influx of plasma emanating from lobe flux annihilation at ~25Re. Three inner probes at ~10Re will monitor current disruption onset, while two outer probes, at 20 and 30Re respectively, will remotely monitor plasma acceleration due to lobe flux dissipation. The five small satellites were launched together on a Delta II rocket and they carry identical sets of instruments including an electric field instrument (EFI), a flux gate magnetometer (FGM), a search coil magnetometer (SCM), a electro-static analyzer, and solid state telescopes (SST). The mission consists of several phases. In the first phase, the spacecraft will all orbit as a tight cluster in the same orbital plane with apogee at 15.4 Earth radii (RE). In the second phase, also called the Dawn Phase, the satellites will be placed in their orbits and during this time their apogees will be on the dawn side of the magnetosphere. During the third phase (also known as the Tail Science Phase) the apogees will be in the magnetotail. The fourth phase is called the Dusk Phase or Radiation Belt Science Phase, with all apogees on the dusk side. In the fifth and final phase, the apogees will shift to the sunward side (Dayside Science Phase).
+
+All five satellites will have similar perigee altitudes (1.16-1.5 Re) but varying apogee altitudes (P1: ~30 RE, P2: ~20 RE, P3 &amp; P4: ~12 RE, P5: ~10RE) with corresponding orbital periods of ~4, 2, and 1 days, respectively. This results in multi-point magnetic conjunctions. Every four days the satellites will line up along the Earth's magnetic tail with magnetic foot points in the North American sector, allowing the tracking of disturbances through different geospace regions from tail to ground.
+
+The satellite data will be combined with observations of the aurora from a network of 20 ground observatories (all sky imagers, magnetometers) across the North American continent. In addition to its primary goal, THEMIS will answer critical questions in radiation belt physics and solar wind - magnetosphere energy coupling. THEMIS is complementary to MMS in terms of the temporal and spatial scales of the phenomena observed by these two constellation missions. THEMIS's focus is macroscale, whereas MMS will observe micro/meso scale features. </Description>
+      <Acknowledgement>National Aeronautics and Space Administration/United States</Acknowledgement>
+      <Contact>
+        <!-- Vassilis Angelopoulos -->
+        <PersonID>spase://SMWG/Person/Vassilis.Angelopoulos</PersonID>
+        <Role>PrincipalInvestigator</Role>
+      </Contact>
+      <Contact>
+        <!-- David Sibeck -->
+        <PersonID>spase://SMWG/Person/David.G.Sibeck</PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>
+      <InformationURL>
+        <Name>Time History of Events and Macroscale Interactions during Substorms (THEMIS) mission </Name>
+        <URL>http://themis.ssl.berkeley.edu/index.shtml</URL>
+        <Description>THEMIS Mission Homepage</Description>
+      </InformationURL>
+      <InformationURL>
+        <Name>Information on Time History of Events and Macroscale Interactions during Substorms (THEMIS) mission </Name>
+        <URL>http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=2007-004A</URL>
+        <Description>NSSDC Master Catalog information on the THEMIS Mission</Description>
+      </InformationURL>
+      <PriorID>spase://SMWG/Observatory/THEMIS-A</PriorID>
+    </ResourceHeader>
+    <ObservatoryGroupID>spase://CDPP/Observatory/AMDA/THEMIS</ObservatoryGroupID>
+    <Location>
+      <ObservatoryRegion>Heliosphere.NearEarth</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosphere.Magnetotail</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosphere.Main</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosheath</ObservatoryRegion>
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/THEMIS/B.xml
@@ -0,0 +1,52 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/THEMIS/B</ResourceID>
+    <ResourceHeader>
+      <ResourceName>THEMIS-B</ResourceName>
+      <AlternateName>Explorer 86</AlternateName>
+      <AlternateName>2007-004B</AlternateName>
+      <AlternateName>MIDEX/THEMIS</AlternateName>
+      <AlternateName>THEMIS-P1</AlternateName>
+      <AlternateName>ARTEMIS-P1</AlternateName>
+      <AlternateName>30581</AlternateName>
+      <ReleaseDate>2011-02-23T22:23:40Z</ReleaseDate>
+      <Description>The Time History of Events and Macroscale Interactions during Substorms (THEMIS) mission is a five-satellite Explorer mission whose primary objective is to understand the onset and macroscale evolution of magnetospheric substorms. Most importantly, THEMIS will find out which magnetotail process is responsible for substorm onset: (a) a local disruption of the plasma sheet current; or, (b) that current's interaction with the rapid influx of plasma emanating from lobe flux annihilation at ~25Re. Three inner probes at ~10Re will monitor current disruption onset, while two outer probes, at 20 and 30Re respectively, will remotely monitor plasma acceleration due to lobe flux dissipation. The five small satellites were launched together on a Delta II rocket and they carry identical sets of instruments including an electric field instrument (EFI), a flux gate magnetometer (FGM), a search coil magnetometer (SCM), a electro-static analyzer, and solid state telescopes (SST). The mission consists of several phases. In the first phase, the spacecraft will all orbit as a tight cluster in the same orbital plane with apogee at 15.4 Earth radii (RE). In the second phase, also called the Dawn Phase, the satellites will be placed in their orbits and during this time their apogees will be on the dawn side of the magnetosphere. During the third phase (also known as the Tail Science Phase) the apogees will be in the magnetotail. The fourth phase is called the Dusk Phase or Radiation Belt Science Phase, with all apogees on the dusk side. In the fifth and final phase, the apogees will shift to the sunward side (Dayside Science Phase).
+
+All five satellites will have similar perigee altitudes (1.16-1.5 Re) but varying apogee altitudes (P1: ~30 RE, P2: ~20 RE, P3 &amp; P4: ~12 RE, P5: ~10RE) with corresponding orbital periods of ~4, 2, and 1 days, respectively. This results in multi-point magnetic conjunctions. Every four days the satellites will line up along the Earth's magnetic tail with magnetic foot points in the North American sector, allowing the tracking of disturbances through different geospace regions from tail to ground.
+
+The satellite data will be combined with observations of the aurora from a network of 20 ground observatories (all sky imagers, magnetometers) across the North American continent. In addition to its primary goal, THEMIS will answer critical questions in radiation belt physics and solar wind - magnetosphere energy coupling. THEMIS is complementary to MMS in terms of the temporal and spatial scales of the phenomena observed by these two constellation missions. THEMIS's focus is macroscale, whereas MMS will observe micro/meso scale features. </Description>
+      <Acknowledgement>National Aeronautics and Space Administration/United States</Acknowledgement>
+      <Contact>
+        <!-- Vassilis Angelopoulos -->
+        <PersonID>spase://SMWG/Person/Vassilis.Angelopoulos</PersonID>
+        <Role>PrincipalInvestigator</Role>
+      </Contact>
+      <Contact>
+        <!-- David Sibeck -->
+        <PersonID>spase://SMWG/Person/David.G.Sibeck</PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>
+      <InformationURL>
+        <Name>Time History of Events and Macroscale Interactions during Substorms (THEMIS) mission </Name>
+        <URL>http://themis.ssl.berkeley.edu/index.shtml</URL>
+        <Description>THEMIS Mission Homepage</Description>
+      </InformationURL>
+      <InformationURL>
+        <Name>Information on Time History of Events and Macroscale Interactions during Substorms (THEMIS) mission </Name>
+        <URL>http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=2007-004B</URL>
+        <Description>NSSDC Master Catalog information on the THEMIS Mission</Description>
+      </InformationURL>
+      <PriorID>spase://SMWG/Observatory/THEMIS-B</PriorID>
+    </ResourceHeader>
+    <ObservatoryGroupID>spase://CDPP/Observatory/AMDA/THEMIS</ObservatoryGroupID>
+    <ObservatoryGroupID>spase://SMWG/Observatory/ARTEMIS</ObservatoryGroupID>
+    <Location>
+      <ObservatoryRegion>Heliosphere.NearEarth</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosphere.Magnetotail</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosphere.Main</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosheath</ObservatoryRegion>
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/THEMIS/C.xml
@@ -0,0 +1,52 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/THEMIS/C</ResourceID>
+    <ResourceHeader>
+      <ResourceName>THEMIS-C</ResourceName>
+      <AlternateName>Explorer 87</AlternateName>
+      <AlternateName>2007-004C</AlternateName>
+      <AlternateName>MIDEX/THEMIS</AlternateName>
+      <AlternateName>THEMIS-P2</AlternateName>
+      <AlternateName>ARTEMIS-P2</AlternateName>
+      <AlternateName>30582</AlternateName>
+      <ReleaseDate>2011-02-23T22:23:15Z</ReleaseDate>
+      <Description>The Time History of Events and Macroscale Interactions during Substorms (THEMIS) mission is a five-satellite Explorer mission whose primary objective is to understand the onset and macroscale evolution of magnetospheric substorms. Most importantly, THEMIS will find out which magnetotail process is responsible for substorm onset: (a) a local disruption of the plasma sheet current; or, (b) that current's interaction with the rapid influx of plasma emanating from lobe flux annihilation at ~25Re. Three inner probes at ~10Re will monitor current disruption onset, while two outer probes, at 20 and 30Re respectively, will remotely monitor plasma acceleration due to lobe flux dissipation. The five small satellites were launched together on a Delta II rocket and they carry identical sets of instruments including an electric field instrument (EFI), a flux gate magnetometer (FGM), a search coil magnetometer (SCM), a electro-static analyzer, and solid state telescopes (SST). The mission consists of several phases. In the first phase, the spacecraft will all orbit as a tight cluster in the same orbital plane with apogee at 15.4 Earth radii (RE). In the second phase, also called the Dawn Phase, the satellites will be placed in their orbits and during this time their apogees will be on the dawn side of the magnetosphere. During the third phase (also known as the Tail Science Phase) the apogees will be in the magnetotail. The fourth phase is called the Dusk Phase or Radiation Belt Science Phase, with all apogees on the dusk side. In the fifth and final phase, the apogees will shift to the sunward side (Dayside Science Phase).
+
+All five satellites will have similar perigee altitudes (1.16-1.5 Re) but varying apogee altitudes (P1: ~30 RE, P2: ~20 RE, P3 &amp; P4: ~12 RE, P5: ~10RE) with corresponding orbital periods of ~4, 2, and 1 days, respectively. This results in multi-point magnetic conjunctions. Every four days the satellites will line up along the Earth's magnetic tail with magnetic foot points in the North American sector, allowing the tracking of disturbances through different geospace regions from tail to ground.
+
+The satellite data will be combined with observations of the aurora from a network of 20 ground observatories (all sky imagers, magnetometers) across the North American continent. In addition to its primary goal, THEMIS will answer critical questions in radiation belt physics and solar wind - magnetosphere energy coupling. THEMIS is complementary to MMS in terms of the temporal and spatial scales of the phenomena observed by these two constellation missions. THEMIS's focus is macroscale, whereas MMS will observe micro/meso scale features. </Description>
+      <Acknowledgement>National Aeronautics and Space Administration/United States</Acknowledgement>
+      <Contact>
+        <!-- Vassilis Angelopoulos -->
+        <PersonID>spase://SMWG/Person/Vassilis.Angelopoulos</PersonID>
+        <Role>PrincipalInvestigator</Role>
+      </Contact>
+      <Contact>
+        <!-- David Sibeck -->
+        <PersonID>spase://SMWG/Person/David.G.Sibeck</PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>
+      <InformationURL>
+        <Name>Time History of Events and Macroscale Interactions during Substorms (THEMIS) mission </Name>
+        <URL>http://themis.ssl.berkeley.edu/index.shtml</URL>
+        <Description>THEMIS Mission Homepage</Description>
+      </InformationURL>
+      <InformationURL>
+        <Name>Information on Time History of Events and Macroscale Interactions during Substorms (THEMIS) mission </Name>
+        <URL>http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=2007-004C</URL>
+        <Description>NSSDC Master Catalog information on the THEMIS Mission</Description>
+      </InformationURL>
+      <PriorID>spase://SMWG/Observatory/THEMIS-C</PriorID>
+    </ResourceHeader>
+    <ObservatoryGroupID>spase://CDPP/Observatory/AMDA/THEMIS</ObservatoryGroupID>
+    <ObservatoryGroupID>spase://SMWG/Observatory/ARTEMIS</ObservatoryGroupID>
+    <Location>
+      <ObservatoryRegion>Heliosphere.NearEarth</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosphere.Magnetotail</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosphere.Main</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosheath</ObservatoryRegion>
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/THEMIS/D.xml
@@ -0,0 +1,50 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/THEMIS/D</ResourceID>
+    <ResourceHeader>
+      <ResourceName>THEMIS-D</ResourceName>
+      <AlternateName>Explorer 88</AlternateName>
+      <AlternateName>2007-004D</AlternateName>
+      <AlternateName>MIDEX/THEMIS</AlternateName>
+      <AlternateName>THEMIS-P3</AlternateName>
+      <AlternateName>30797</AlternateName>
+      <ReleaseDate>2010-09-24T21:35:00Z</ReleaseDate>
+      <Description>The Time History of Events and Macroscale Interactions during Substorms (THEMIS) mission is a five-satellite Explorer mission whose primary objective is to understand the onset and macroscale evolution of magnetospheric substorms. Most importantly, THEMIS will find out which magnetotail process is responsible for substorm onset: (a) a local disruption of the plasma sheet current; or, (b) that current's interaction with the rapid influx of plasma emanating from lobe flux annihilation at ~25Re. Three inner probes at ~10Re will monitor current disruption onset, while two outer probes, at 20 and 30Re respectively, will remotely monitor plasma acceleration due to lobe flux dissipation. The five small satellites were launched together on a Delta II rocket and they carry identical sets of instruments including an electric field instrument (EFI), a flux gate magnetometer (FGM), a search coil magnetometer (SCM), a electro-static analyzer, and solid state telescopes (SST). The mission consists of several phases. In the first phase, the spacecraft will all orbit as a tight cluster in the same orbital plane with apogee at 15.4 Earth radii (RE). In the second phase, also called the Dawn Phase, the satellites will be placed in their orbits and during this time their apogees will be on the dawn side of the magnetosphere. During the third phase (also known as the Tail Science Phase) the apogees will be in the magnetotail. The fourth phase is called the Dusk Phase or Radiation Belt Science Phase, with all apogees on the dusk side. In the fifth and final phase, the apogees will shift to the sunward side (Dayside Science Phase).
+
+All five satellites will have similar perigee altitudes (1.16-1.5 Re) but varying apogee altitudes (P1: ~30 RE, P2: ~20 RE, P3 &amp; P4: ~12 RE, P5: ~10RE) with corresponding orbital periods of ~4, 2, and 1 days, respectively. This results in multi-point magnetic conjunctions. Every four days the satellites will line up along the Earth's magnetic tail with magnetic foot points in the North American sector, allowing the tracking of disturbances through different geospace regions from tail to ground.
+
+The satellite data will be combined with observations of the aurora from a network of 20 ground observatories (all sky imagers, magnetometers) across the North American continent. In addition to its primary goal, THEMIS will answer critical questions in radiation belt physics and solar wind - magnetosphere energy coupling. THEMIS is complementary to MMS in terms of the temporal and spatial scales of the phenomena observed by these two constellation missions. THEMIS's focus is macroscale, whereas MMS will observe micro/meso scale features. </Description>
+      <Acknowledgement>National Aeronautics and Space Administration/United States</Acknowledgement>
+      <Contact>
+        <!-- Vassilis Angelopoulos -->
+        <PersonID>spase://SMWG/Person/Vassilis.Angelopoulos</PersonID>
+        <Role>PrincipalInvestigator</Role>
+      </Contact>
+      <Contact>
+        <!-- David Sibeck -->
+        <PersonID>spase://SMWG/Person/David.G.Sibeck</PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>
+      <InformationURL>
+        <Name>Time History of Events and Macroscale Interactions during Substorms (THEMIS) mission </Name>
+        <URL>http://themis.ssl.berkeley.edu/index.shtml</URL>
+        <Description>THEMIS Mission Homepage</Description>
+      </InformationURL>
+      <InformationURL>
+        <Name>Information on Time History of Events and Macroscale Interactions during Substorms (THEMIS) mission </Name>
+        <URL>http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=2007-004D</URL>
+        <Description>NSSDC Master Catalog information on the THEMIS Mission</Description>
+      </InformationURL>
+      <PriorID>spase://SMWG/Observatory/THEMIS-D</PriorID>
+    </ResourceHeader>
+    <ObservatoryGroupID>spase://CDPP/Observatory/AMDA/THEMIS</ObservatoryGroupID>
+    <Location>
+      <ObservatoryRegion>Heliosphere.NearEarth</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosphere.Magnetotail</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosphere.Main</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosheath</ObservatoryRegion>
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/THEMIS/E.xml
@@ -0,0 +1,50 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/THEMIS/E</ResourceID>
+    <ResourceHeader>
+      <ResourceName>THEMIS-E</ResourceName>
+      <AlternateName>Explorer 89</AlternateName>
+      <AlternateName>2007-004E</AlternateName>
+      <AlternateName>MIDEX/THEMIS</AlternateName>
+      <AlternateName>THEMIS-P4</AlternateName>
+      <AlternateName>30798</AlternateName>
+      <ReleaseDate>2010-09-24T21:35:00Z</ReleaseDate>
+      <Description>The Time History of Events and Macroscale Interactions during Substorms (THEMIS) mission is a five-satellite Explorer mission whose primary objective is to understand the onset and macroscale evolution of magnetospheric substorms. Most importantly, THEMIS will find out which magnetotail process is responsible for substorm onset: (a) a local disruption of the plasma sheet current; or, (b) that current's interaction with the rapid influx of plasma emanating from lobe flux annihilation at ~25Re. Three inner probes at ~10Re will monitor current disruption onset, while two outer probes, at 20 and 30Re respectively, will remotely monitor plasma acceleration due to lobe flux dissipation. The five small satellites were launched together on a Delta II rocket and they carry identical sets of instruments including an electric field instrument (EFI), a flux gate magnetometer (FGM), a search coil magnetometer (SCM), a electro-static analyzer, and solid state telescopes (SST). The mission consists of several phases. In the first phase, the spacecraft will all orbit as a tight cluster in the same orbital plane with apogee at 15.4 Earth radii (RE). In the second phase, also called the Dawn Phase, the satellites will be placed in their orbits and during this time their apogees will be on the dawn side of the magnetosphere. During the third phase (also known as the Tail Science Phase) the apogees will be in the magnetotail. The fourth phase is called the Dusk Phase or Radiation Belt Science Phase, with all apogees on the dusk side. In the fifth and final phase, the apogees will shift to the sunward side (Dayside Science Phase).
+
+All five satellites will have similar perigee altitudes (1.16-1.5 Re) but varying apogee altitudes (P1: ~30 RE, P2: ~20 RE, P3 &amp; P4: ~12 RE, P5: ~10RE) with corresponding orbital periods of ~4, 2, and 1 days, respectively. This results in multi-point magnetic conjunctions. Every four days the satellites will line up along the Earth's magnetic tail with magnetic foot points in the North American sector, allowing the tracking of disturbances through different geospace regions from tail to ground.
+
+The satellite data will be combined with observations of the aurora from a network of 20 ground observatories (all sky imagers, magnetometers) across the North American continent. In addition to its primary goal, THEMIS will answer critical questions in radiation belt physics and solar wind - magnetosphere energy coupling. THEMIS is complementary to MMS in terms of the temporal and spatial scales of the phenomena observed by these two constellation missions. THEMIS's focus is macroscale, whereas MMS will observe micro/meso scale features. </Description>
+      <Acknowledgement>National Aeronautics and Space Administration/United States</Acknowledgement>
+      <Contact>
+        <!-- Vassilis Angelopoulos -->
+        <PersonID>spase://SMWG/Person/Vassilis.Angelopoulos</PersonID>
+        <Role>PrincipalInvestigator</Role>
+      </Contact>
+      <Contact>
+        <!-- David Sibeck -->
+        <PersonID>spase://SMWG/Person/David.G.Sibeck</PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>
+      <InformationURL>
+        <Name>Time History of Events and Macroscale Interactions during Substorms (THEMIS) mission </Name>
+        <URL>http://themis.ssl.berkeley.edu/index.shtml</URL>
+        <Description>THEMIS Mission Homepage</Description>
+      </InformationURL>
+      <InformationURL>
+        <Name>Information on Time History of Events and Macroscale Interactions during Substorms (THEMIS) mission </Name>
+        <URL>http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=2007-004E</URL>
+        <Description>NSSDC Master Catalog information on the THEMIS Mission</Description>
+      </InformationURL>
+      <PriorID>spase://SMWG/Observatory/THEMIS-E</PriorID>
+    </ResourceHeader>
+    <ObservatoryGroupID>spase://CDPP/Observatory/AMDA/THEMIS</ObservatoryGroupID>
+    <Location>
+      <ObservatoryRegion>Heliosphere.NearEarth</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosphere.Magnetotail</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosphere.Main</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosheath</ObservatoryRegion>
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/Ulysses.xml
@@ -0,0 +1,34 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/Ulysses</ResourceID>
+    <ResourceHeader>
+      <ResourceName>Ulysses</ResourceName>
+      <AlternateName>1990-090B</AlternateName>
+      <AlternateName>Solar Polar</AlternateName>
+      <AlternateName>International Solar Polar Mission</AlternateName>
+      <AlternateName>ULY</AlternateName>
+      <ReleaseDate>2010-08-05T18:19:18Z</ReleaseDate>
+      <Description>The primary objectives of Ulysses, formerly the International Solar Polar Mission (ISPM), are to investigate, as a function of solar latitude, the properties of the solar wind and the interplanetary magnetic field, of galactic cosmic rays and neutral interstellar gas, and to study energetic particle composition and acceleration. The 55 kg payload includes two magnetometers, two solar wind plasma instruments, a unified radio/plasma wave instrument, three energetic charged particle instruments, an interstellar neutral gas sensor, a solar X-ray/cosmic gamma-ray burst detector, and a cosmic dust sensor. The communications systems is also used to study the solar corona and to search for gravitational waves. Secondary objectives included interplanetary and planetary physics investigations during the initial Earth-Jupiter phase and investigations in the Jovian magnetosphere. The spacecraft used a Jupiter swingby in Feb. 1992 to transfer to a heliospheric orbit with high heliocentric inclination, and will pass over the rotational south pole of the sun in mid-1994 at 2 AU, and over the north pole in mid-1995. A second solar orbit will take Ulysses again over the south and north poles in years 2000 and 2001, respectively. The spacecraft is powered by a single radio-isotope generator. It is spin stabilized at a rate of 5 rpm and its high-gain antenna points continuously to the earth. A nutation anomaly after launch was controlled by CONSCAN. The original mission planned for two spacecraft, one built by ESA and the other by NASA. NASA cancelled its spacecraft in 1981.</Description>
+      <Contact>
+        <PersonID>spase://SMWG/Person/Edward.J.Smith</PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>
+      <Contact>
+        <PersonID>spase://SMWG/Person/Richard.G.Marsden</PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>
+      <InformationURL>
+        <Name>Ulysses website at JPL</Name>
+        <URL>http://ulysses.jpl.nasa.gov/index.html</URL>
+        <Description>JPL's primary website for the Ulysses mission.  Links to all of the experiment subpages exist here.</Description>
+      </InformationURL>
+    </ResourceHeader>
+    <Location>
+      <ObservatoryRegion>Heliosphere.Inner</ObservatoryRegion>
+      <ObservatoryRegion>Heliosphere.NearEarth</ObservatoryRegion>
+      <ObservatoryRegion>Heliosphere.Outer</ObservatoryRegion>
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/VEX.xml
@@ -0,0 +1,20 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/VEX</ResourceID>
+    <ResourceHeader>
+      <ResourceName>VEX</ResourceName>
+      <AlternateName>Venus-Express</AlternateName>
+      <ReleaseDate>2010-09-27T18:45:12Z</ReleaseDate>
+      <Description></Description>
+      <Contact>     
+        <PersonID> </PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>      
+    </ResourceHeader>
+    <Location> 
+      <ObservatoryRegion>Venus</ObservatoryRegion>      
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/Voyager.xml
@@ -0,0 +1,29 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/Voyager</ResourceID>
+    <ResourceHeader>
+      <ResourceName>Voyager</ResourceName>
+      <AlternateName>1977-084A</AlternateName>
+      <AlternateName>Mariner Jupiter/Saturn</AlternateName>
+      <ReleaseDate>2010-09-25T03:09:48Z</ReleaseDate>
+      <Description>The twin Voyager 1 and 2 spacecraft continue exploring where nothing 
+	      from Earth has flown before. In the 25th year after their 1977 launches, 
+	      they each are much farther away from Earth and the Sun than Pluto is and approaching ... </Description>
+      <Contact>
+        <PersonID>spase://SMWG/Person/Edward.C.Stone.Jr</PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>
+      <InformationURL>
+        <Name>NSSDC's Master Catalog</Name>
+        <URL>http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1977-084A</URL>
+        <Description>Information about the Voyage mission</Description>
+      </InformationURL>
+    </ResourceHeader>
+    <ObservatoryGroupID>spase://CDPP/Observatory/AMDA/Voyager</ObservatoryGroupID>
+    <Location>  
+	 <ObservatoryRegion>Heliosphere.Outer</ObservatoryRegion>      
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/Voyager1.xml
@@ -0,0 +1,60 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/Voyager1</ResourceID>
+    <ResourceHeader>
+      <ResourceName>Voyager 1</ResourceName>
+      <AlternateName>1977-084A</AlternateName>
+      <AlternateName>Mariner Jupiter/Saturn A</AlternateName>
+      <ReleaseDate>2010-09-25T03:09:48Z</ReleaseDate>
+      <Description>Voyager 1 was one of a pair of spacecraft launched to explore the planets of the outer solar system and the interplanetary environment. Each Voyager had as its major objectives at each planet to: (1) investigate the circulation, dynamics, structure, and composition of the planet's atmosphere; (2) characterize the morphology, geology, and physical state of the satellites of the planet; (3) provide improved values for the mass, size, and shape of the planet, its satellites, and any rings; and, (4) determine the magnetic field structure and characterize the composition and distribution of energetic trapped particles and plasma therein.
+
+Spacecraft and Subsystems
+
+Each Voyager consisted of a decahedral bus, 47 cm in height and 1.78 m across from flat to flat. A 3.66 m diameter parabolic high-gain antenna was mounted on top of the bus. The major portion of the science instruments were mounted on a science boom extending out some 2.5 m from the spacecraft. At the end of the science boom was a steerable scan platform on which were mounted the imaging and spectroscopic remote sensing instruments. Also mounted at various distances along the science boom were the plasma and charged particle detectors. The magnetometers were located along a separate boom extending 13 m on the side opposite the science boom. A third boom, extending down and away from the science instruments, held the spacecraft's radioisotope thermoelectric generators (RTGs). Two 10 m whip antennas (used for the plasma wave and planetary radio astronomy investigations) also extended from the spacecraft, each perpendicular to the other. The spacecraft was three-axis spin stabilized to enable long integration times and selective viewing for the instruments mounted on the scan platform.
+
+Power was provided to the spacecraft systems and instruments through the use of three radioisotope thermoelectric generators. The RTGs were assembled in tandem on a deployable boom hinged on an outrigger arrangement of struts attached to the basic structure. Each RTG unit, contained in a beryllium outer case, was 40.6 cm in diameter, 50.8 cm in length, and weighed 39 kg. The RTGs used a radioactive source (Plutonium-238 in the form of plutonium oxide, or PuO2, in this case) which, as it decayed, gave off heat. A bi-metallic thermoelectric device was used to convert the heat to electric power for the spacecraft. The total output of RTGs slowly decreases with time as the radioactive material is expended. Therefore, although the initial output of the RTGs on Voyager was approximately 470 W of 30 V DC power at launch, it had fallen off to approximately 335 W by the beginning of 1997 (about 19.5 years post-launch). As power continues to decrease, power loads on the spacecraft must also decrease. Current estimates (1998) are that increasingly limited instrument operations can be carried out at least until 2020.
+
+Communications were provided through the high-gain antenna with a low-gain antenna for backup. The high-gain antenna supported both X-band and S-band downlink telemetry. Voyager was the first spacecraft to utilize X-band as the primary telemetry link frequency. Data could be stored for later transmission to Earth through the use of an on-board digital tape recorder.
+
+Voyager, because of its distance from Earth and the resulting time-lag for commanding, was designed to operate in a highly-autonomous manner. In order to do this and carry out the complex sequences of spacecraft motions and instrument operations, three interconnected on-board computers were utilized. The Computer Command Subsystem (CCS) was responsible for storing commanding for the other two computers and issuing the commands at set times. The Attitude and Articulation Control Subsystem (AACS) was responsible for controlling spacecraft attitude and motions of the scan platform. The Flight Data Subsystem (FDS) controlled the instruments, including changes in configuration (state) or telemetry rates. All three computers had redundant components to ensure continued operations. The AACS included redundant star trackers and Sun sensors as well.
+
+Message in a Bottle
+
+Each Voyager has mounted to one of the sides of the bus a 12-inch gold-plated copper disk. The disk has recorded on it sounds and images of Earth designed to portray the diversity of life and culture on the planet. Each disk is encased in a protective aluminum jacket along with a cartridge and a needle. Instructions explaining from where the spacecraft originated and how to play the disk are engraved onto the jacket. Electroplated onto a 2 cm area on the cover is also an ultra-pure source of uranium-238 (with a radioactivity of about 0.26 nanocuries and a half-life of 4.51 billion years), allowing the determination of the elapsed time since launch by measuring the amount of daughter elements to remaining U238. The 115 images on the disk were encoded in analog form. The sound selections (including greetings in 55 languages, 35 sounds, natural and man-made, and portions of 27 musical pieces) are designed for playback at 1000 rpm. The Voyagers were not the first spacecraft designed with such messages to the future. Pioneers 10 and 11, LAGEOS, and the Apollo landers also included plaques with a similar intent, though not quite so ambitious.
+
+Mission Profile
+
+Originally planned as a Grand Tour of the outer planets, including dual launches to Jupiter, Saturn, and Pluto in 1976-77 and dual launches to Jupiter, Uranus, and Neptune in 1979, budgetary constraints caused a dramatic rescoping of the project to two spacecraft, each of which would go to only Jupiter and Saturn. The new mission was called Mariner Jupiter/Saturn, or MJS. It was subsequently renamed Voyager about six months prior to launch. The rescoped mission was estimated to cost $250 million (through the end of Saturn operations), only a third of what the Grand Tour design would have cost.
+
+Originally scheduled to launch twelve days after Voyager 2, Voyager 1's launch was delayed twice to prevent the occurrence of problems which Voyager 2 experienced after launch. Voyager 1's launch finally happened on 05 Sept. 1977 and was termed "flawless and accurate".
+
+Although launched sixteen days after Voyager 2, Voyager 1's trajectory was the quicker one to Jupiter. On 15 Dec. 1977, while both spacecraft were in the asteroid belt, Voyager 1 surpassed Voyager 2's distance from the Sun. Voyager 1 then proceeded to Jupiter (making its closest approach on 05 March 1979) and Saturn (with closest approach on 12 Nov. 1980). Both prior to and after planetary encounters observations were made of the interplanetary medium. Some 18,000 images of Jupiter and its satellites were taken by Voyager 1. In addition, roughly 16,000 images of Saturn, its rings and satellites were obtained.
+
+After its encounter with Saturn, Voyager 1 remained relatively quiescent, continuing to make in situ observations of the interplanetary environment and UV observations of stars. After nearly nine years of dormancy, Voyager 1's cameras were once again turned on to take a series of pictures. On 14 Feb. 1990, Voyager 1 looked back from whence it came and took the first "family portrait" of the solar system, a mosaic of 60 frames of the Sun and six of the planets (Venus, Earth, Jupiter, Saturn, Uranus, and Neptune) as seen from "outside" the solar system. After this final look back, the cameras on Voyager 1 were once again turned off.
+
+All of the experiments, save the photopolarimeter (which failed to operate), have produced useful data.
+
+Onward and Outward
+
+Rechristened the Voyager Interstellar Mission (VIM) by NASA in 1989 (after Voyager 2's Neptune encounter), Voyager 1 continues operations, taking measurements of the interplanetary magnetic field, plasma, and charged particle environment while searching for the heliopause (the distance at which the solar wind becomes subsumed by the more general interstellar wind). Through the end of the Neptune phase of the Voyager project, a total of $875 million had been expended for the construction, launch, and operations of both Voyager spacecraft. An additional $30 million was allocated for the first two years of VIM.
+
+Voyager 1 is speeding away from the Sun at a velocity of about 3.50 AU/year toward a point in the sky of RA= 262 degrees, Dec=+12 degrees (35.55 degrees ecliptic latitude, 260.78 degrees ecliptic longitude). Late on 17 February 1998, Voyager 1 became the most distant man-made object from the Sun, surpassing the distance of Pioneer 10.</Description>
+      <Contact>
+        <PersonID>spase://SMWG/Person/Edward.C.Stone.Jr</PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>
+      <InformationURL>
+        <Name>NSSDC's Master Catalog</Name>
+        <URL>http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1977-084A</URL>
+        <Description>Information about the Voyager 1 mission</Description>
+      </InformationURL>
+    </ResourceHeader>
+    <ObservatoryGroupID>spase://CDPP/Observatory/AMDA/Voyager</ObservatoryGroupID>
+    <Location>
+      <ObservatoryRegion>Heliosphere.NearEarth</ObservatoryRegion>
+      <ObservatoryRegion>Heliosphere.Outer</ObservatoryRegion>
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/Voyager2.xml
@@ -0,0 +1,64 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/Voyager2</ResourceID>
+    <ResourceHeader>
+      <ResourceName>Voyager 2</ResourceName>
+      <AlternateName>1977-076A</AlternateName>
+      <AlternateName>Mariner Jupiter/Saturn B</AlternateName>
+      <ReleaseDate>2010-09-25T03:09:48Z</ReleaseDate>
+      <Description>Voyager 2 was one of a pair of spacecraft launched to explore the planets of the outer solar system and the interplanetary environment. Each Voyager had as its major objectives at each planet to: (1) investigate the circulation, dynamics, structure, and composition of the planet's atmosphere; (2) characterize the morphology, geology, and physical state of the satellites of the planet; (3) provide improved values for the mass, size, and shape of the planet, its satellites, and any rings; and, (4) determine the magnetic field structure and characterize the composition and distribution of energetic trapped particles and plasma therein.
+
+Spacecraft and Subsystems
+
+Each Voyager consisted of a decahedral bus, 47 cm in height and 1.78 m across from flat to flat. A 3.66 m diameter parabolic high-gain antenna was mounted on top of the bus. The major portion of the science instruments were mounted on a science boom extending out some 2.5 m from the spacecraft. At the end of the science boom was a steerable scan platform on which were mounted the imaging and spectroscopic remote sensing instruments. Also mounted at various distances along the science boom were the plasma and charged particle detectors. The magnetometers were located along a separate boom extending 13 m on the side opposite the science boom. A third boom, extending down and away from the science instruments, held the spacecraft's radioisotope thermoelectric generators (RTGs). Two 10 m whip antennas (used for the plasma wave and planetary radio astronomy investigations) also extended from the spacecraft, each perpendicular to the other. The spacecraft was three-axis spin stabilized to enable long integration times and selective viewing for the instruments mounted on the scan platform.
+
+Power was provided to the spacecraft systems and instruments through the use of three radioisotope thermoelectric generators. The RTGs were assembled in tandem on a deployable boom hinged on an outrigger arrangement of struts attached to the basic structure. Each RTG unit, contained in a beryllium outer case, was 40.6 cm in diameter, 50.8 cm in length, and weighed 39 kg. The RTGs used a radioactive source (Plutonium-238 in the form of plutonium oxide, or PuO2, in this case) which, as it decayed, gave off heat. A bi-metallic thermoelectric device was used to convert the heat to electric power for the spacecraft. The total output of RTGs slowly decreases with time as the radioactive material is expended. Therefore, although the initial output of the RTGs on Voyager was approximately 470 W of 30 V DC power at launch, it had fallen off to approximately 335 W by the beginning of 1997 (about 19.5 years post-launch). As power continues to decrease, power loads on the spacecraft must also decrease. Current estimates (1998) are that increasingly limited instrument operations can be carried out at least until 2020.
+
+Communications were provided through the high-gain antenna with a low-gain antenna for backup. The high-gain antenna supported both X-band and S-band downlink telemetry. Voyager was the first spacecraft to utilize X-band as the primary telemetry link frequency. Data could be stored for later transmission to Earth through the use of an on-board digital tape recorder.
+
+Voyager, because of its distance from Earth and the resulting time-lag for commanding, was designed to operate in a highly-autonomous manner. In order to do this and carry out the complex sequences of spacecraft motions and instrument operations, three interconnected on-board computers were utilized. The Computer Command Subsystem (CCS) was responsible for storing commanding for the other two computers and issuing the commands at set times. The Attitude and Articulation Control Subsystem (AACS) was responsible for controlling spacecraft attitude and motions of the scan platform. The Flight Data Subsystem (FDS) controlled the instruments, including changes in configuration (state) or telemetry rates. All three computers had redundant components to ensure continued operations. The AACS included redundant star trackers and Sun sensors as well.
+
+Message in a Bottle
+
+Each Voyager has mounted to one of the sides of the bus a 12-inch gold-plated copper disk. The disk has recorded on it sounds and images of Earth designed to portray the diversity of life and culture on the planet. Each disk is encased in a protective aluminum jacket along with a cartridge and a needle. Instructions explaining from where the spacecraft originated and how to play the disk are engraved onto the jacket. Electroplated onto a 2 cm area on the cover is also an ultra-pure source of uranium-238 (with a radioactivity of about 0.26 nanocuries and a half-life of 4.51 billion years), allowing the determination of the elapsed time since launch by measuring the amount of daughter elements to remaining U238. The 115 images on the disk were encoded in analog form. The sound selections (including greetings in 55 languages, 35 sounds, natural and man-made, and portions of 27 musical pieces) are designed for playback at 1000 rpm. The Voyagers were not the first spacecraft designed with such messages to the future. Pioneers 10 and 11, LAGEOS, and the Apollo landers also included plaques with a similar intent, though not quite so ambitious.
+
+Mission Profile
+
+Originally planned as a Grand Tour of the outer planets, including dual launches to Jupiter, Saturn, and Pluto in 1976-77 and dual launches to Jupiter, Uranus, and Neptune in 1979, budgetary constraints caused a dramatic rescoping of the project to two spacecraft, each of which would go to only Jupiter and Saturn. The new mission was called Mariner Jupiter/Saturn, or MJS. It was subsequently renamed Voyager about six months prior to launch. The rescoped mission was estimated to cost $250 million (through the end of Saturn operations), only a third of what the Grand Tour design would have cost.
+
+Voyager 2 was the first of the two spacecraft to be launched, with liftoff occurring 20 Aug. 1977. What was at first an auspicious launch, however, proved to be the beginning of a number of problems. The primary cause of the initial problems were attributed to commanding by the AACS, including difficulty in determining the full deployment of the science boom. These problems resulted in a delay of four days in the launch of Voyager 1 to ensure they wouldn't occur for it.
+
+Although launched sixteen days after Voyager 2, Voyager 1's trajectory was the quicker one to Jupiter. On 15 Dec. 1977, while both spacecraft were in the asteroid belt, Voyager 1 surpassed Voyager 2's distance from the Sun.
+
+Several months after launch, in April 1978, Voyager 2's primary radio receiver failed, automatically kicking in the backup receiver which proved to be faulty. Attempts to recover the use of the primary receiver failed and the backup receiver was used for the remainder of the mission. Although use of the backup receiver made communication with the spacecraft more difficult, engineers were able to find workarounds.
+
+Voyager 2 proceeded with its primary mission and flew by Jupiter (closest approach on 09 July 1979) and Saturn (05 Aug. 1981). During these flybys, Voyager 2 obtained images roughly equal in number to Voyager 1 (18,000 at Jupiter, 16,000 at Saturn).
+
+Voyager 2's launch date had preserved one part of the original Grand Tour design, i.e. the possibility of an extended mission to Uranus and Neptune. Despite the difficulties encountered, scientists and engineers had been able to make Voyager enormously successful. As a result, approval was granted to extend the mission, first to Uranus, then to Neptune and later to continue observations well past Neptune. Voyager 2 made successful flybys of Uranus (24 Jan. 1986) and Neptune (25 Aug. 1989). Because of the additional distance of these two planets, adaptations had to made to accomodate the lower light levels and decreased communications. Voyager 2 was successfully able to obtain about 8,000 images of Uranus and its satellites. Additional improvements in the on-board software and use of image compression techniques allowed about 10,000 images of Neptune and its satellites to be taken.
+
+All of the experiments on Voyager 2 have produced useful data.
+
+Onward and Outward
+
+Rechristened the Voyager Interstellar Mission (VIM) by NASA in 1989 after its encounter with Neptune, Voyager 2 continues operations, taking measurements of the interplanetary magnetic field, plasma, and charged particle environment while searching for the heliopause (the distance at which the solar wind becomes subsumed by the more general interstellar wind). Through the end of the Neptune phase of the Voyager project, a total of $875 million had been expended for the construction, launch, and operations of both Voyager spacecraft. An additional $30 million was allocated for the first two years of VIM.
+
+Voyager 2 is speeding away from the Sun at a velocity of about 3.13 AU/year toward a point in the sky of RA=338 degrees, Dec=-62 degrees (-47.46 degrees ecliptic latitude, 310.89 degrees ecliptic longitude).</Description>
+      <Contact>
+        <PersonID>spase://SMWG/Person/Edward.C.Stone.Jr</PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>
+      <InformationURL>
+        <Name>NSSDC's Master Catalog</Name>
+        <URL>http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1977-076A</URL>
+        <Description>Information about the Voyager 2 mission</Description>
+      </InformationURL>
+    </ResourceHeader>
+    <ObservatoryGroupID>spase://CDPP/Observatory/AMDA/Voyager</ObservatoryGroupID>
+    <Location>
+      <ObservatoryRegion>Heliosphere.NearEarth</ObservatoryRegion>
+      <ObservatoryRegion>Heliosphere.Outer</ObservatoryRegion>
+    </Location>
+  </Observatory>
+</Spase>
+++ a/Observatory/AMDA/Wind.xml
@@ -0,0 +1,27 @@
+<?xml version="1.0" encoding="UTF-8"?>
+<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_6.xsd">
+  <Version>2.2.6</Version>
+  <Observatory>
+    <ResourceID>spase://CDPP/Observatory/AMDA/Wind</ResourceID>
+    <ResourceHeader>
+      <ResourceName>Wind</ResourceName>
+      <AlternateName>NASA Mission</AlternateName>     
+      <ReleaseDate>2010-09-27T18:45:12Z</ReleaseDate>
+      <Description>Wind studies the solar wind and its impact on the near-Earth environment. 
+        This mission is part of SMD's Heliophysics Research program.</Description>
+      <Contact>      
+        <PersonID></PersonID>
+        <Role>ProjectScientist</Role>
+      </Contact>
+      <InformationURL>
+        <Name></Name>
+        <URL></URL>
+      </InformationURL>     
+    </ResourceHeader>    
+    <Location>
+      <ObservatoryRegion>Heliosphere.NearEarth</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosheath</ObservatoryRegion>
+      <ObservatoryRegion>Earth.Magnetosphere</ObservatoryRegion>
+    </Location>
+  </Observatory>
+</Spase>