{
  "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_4_0.xsd",
    "Version": "2.4.0",
    "NumericalData": {
      "ResourceID": "spase://CNES/NumericalData/CDPP-Archive/Interball-Tail/Ephemeris-Tail/INT_TAIL_ATTITUDE",
      "ResourceHeader": {
        "ResourceName": "INT_TAIL : Attitude Data",
        "DOI": "https://doi.org/10.24400/802406/aj4b-9zjy",
        "ReleaseDate": "2022-04-27T18:07:14Z",
        "Description": "This data set contains the attitude quaternions of Interball-Tail allowing the conversion of any vector from the satellite body-build frame to GEI-1950 frame.",
        "Contact": {
          "PersonID": "spase://CNES/Person/CDPP-Archive/Elena.Ryazanova",
          "Role": "GeneralContact"
        }
      },
      "AccessInformation": {
        "RepositoryID": "spase://CNES/Repository/CDPP-Archive/REGARDS-CDPP",
        "Availability": "Online",
        "AccessURL": {
          "Name": "REGARDS",
          "URL": "https://regards.cnes.fr/user/cdpp/modules/1777?sp=DatasetName;q=DatasetName:INT_TAIL_ATTITUDE",
          "Description": "Access via CNES Data Archive for CDPP"
        },
        "Format": "Binary"
      },
      "InstrumentID": "spase://CNES/Instrument/CDPP-Archive/Interball-Tail/Ephemeris-Tail",
      "MeasurementType": "Ephemeris",
      "TemporalDescription": {
        "TimeSpan": {
          "StartDate": "1995-08-05T00:00:00Z",
          "StopDate": "2000-10-13T00:00:00Z"
        }
      },
      "Parameter": [
        {
          "Name": "INT_TAIL Q0 Attitude quaternion SC to GEI transformation",
          "Description": "INT_TAIL   Q0 = cos(ALPHA/2)  The attitude quaternion describes a transformation of a vector from spacecraft body coordinates into the GEI-1950 (Geocentric Equatorial Inertial) coordinate system. It represents a rotation of an ALPHA angle around an axis whose the unit vector coordinates are U, V, W.",
          "Support": {
            "Qualifier": "Scalar",
            "SupportQuantity": "Other"
          }
        },
        {
          "Name": "INT_TAIL Q1 Attitude quaternion SC to GEI transformation",
          "Description": "INT_TAIL   Q1=U*sin(ALPHA/2)  The attitude quaternion describes a transformation of a vector from spacecraft body coordinates into the GEI-1950 (Geocentric Equatorial Inertial) coordinate system. It represents a rotation of an ALPHA angle around an axis whose the unit vector coordinates are U, V, W.",
          "Support": {
            "Qualifier": "Scalar",
            "SupportQuantity": "Other"
          }
        },
        {
          "Name": "INT_TAIL Q2 Attitude quaternion SC to GEI transformation",
          "Description": "INT_TAIL   Q2 = V*sin(ALPHA/2) The attitude quaternion describes a transformation of a vector from spacecraft body coordinates into the GEI-1950 (Geocentric Equatorial Inertial) coordinate system. It represents a rotation of an ALPHA angle around an axis whose the unit vector coordinates are U, V, W.",
          "Support": {
            "Qualifier": "Scalar",
            "SupportQuantity": "Other"
          }
        },
        {
          "Name": "INT_TAIL Q3 Attitude quaternion SC to GEI transformation",
          "Description": "INT_TAIL   Q3 = W*sin(ALPHA/2)The attitude quaternion describes a transformation of a vector from spacecraft body coordinates into the GEI-1950 (Geocentric Equatorial Inertial) coordinate system. It represents a rotation of an ALPHA angle around an axis whose the unit vector coordinates are U, V, W.",
          "Support": {
            "Qualifier": "Scalar",
            "SupportQuantity": "Other"
          }
        },
        {
          "Name": "INT_TAIL  Right ascension  of the spin axis in GEI coordinate system",
          "Description": "INT_TAIL  Right ascension  of the spin axis in GEI (Geocentric Equatorial Inertial) coordinate system",
          "Units": "°",
          "UnitsConversion": "0.0174532925>rad",
          "CoordinateSystem": {
            "CoordinateRepresentation": "Spherical",
            "CoordinateSystemName": "GEI"
          },
          "Support": {
            "Qualifier": "Scalar",
            "SupportQuantity": "Other"
          }
        },
        {
          "Name": "INT_TAIL  Declination   of the spin axis in GEI coordinate system",
          "Description": "INT_TAIL Declination   of the spin axis in GEI (Geocentric Equatorial Inertial) coordinate system",
          "Units": "°",
          "UnitsConversion": "0.0174532925>rad",
          "CoordinateSystem": {
            "CoordinateRepresentation": "Spherical",
            "CoordinateSystemName": "GEI"
          },
          "Support": {
            "Qualifier": "Scalar",
            "SupportQuantity": "Other"
          }
        },
        {
          "Name": "INT_TAIL  Right ascension  of the spin axis in GSE coordinate system",
          "Description": "INT_TAIL  Right ascension  of the spin axis in GSE (Geocentric Equatorial Inertial) coordinate system",
          "Units": "°",
          "UnitsConversion": "0.0174532925>rad",
          "CoordinateSystem": {
            "CoordinateRepresentation": "Spherical",
            "CoordinateSystemName": "GSE"
          },
          "Support": {
            "Qualifier": "Scalar",
            "SupportQuantity": "Other"
          }
        },
        {
          "Name": "INT_TAIL  Declination   of the spin axis in GSE coordinate system",
          "Description": "INT_TAIL Declination   of the spin axis in GSE (Geocentric Equatorial Inertial) coordinate system",
          "Units": "°",
          "UnitsConversion": "0.0174532925>rad",
          "CoordinateSystem": {
            "CoordinateRepresentation": "Spherical",
            "CoordinateSystemName": "GSE"
          },
          "Support": {
            "Qualifier": "Scalar",
            "SupportQuantity": "Other"
          }
        }
      ]
    }
  }
}