2.4.0 spase://CNES/NumericalData/CDPP-Archive/Interball-Tail/Ephemeris-Tail/INT_TAIL_ATTITUDE INT_TAIL : Attitude Data https://doi.org/10.24400/802406/aj4b-9zjy 2022-04-27T18:07:14Z 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. spase://CNES/Person/CDPP-Archive/Elena.Ryazanova GeneralContact spase://CNES/Repository/CDPP-Archive/REGARDS-CDPP Online REGARDS https://regards.cnes.fr/user/cdpp/modules/1777?sp=DatasetName;q=DatasetName:INT_TAIL_ATTITUDE Access via CNES Data Archive for CDPP Binary spase://CNES/Instrument/CDPP-Archive/Interball-Tail/Ephemeris-Tail Ephemeris 1995-08-05T00:00:00Z 2000-10-13T00:00:00Z INT_TAIL Q0 Attitude quaternion SC to GEI transformation 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. Scalar Other INT_TAIL Q1 Attitude quaternion SC to GEI transformation 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. Scalar Other INT_TAIL Q2 Attitude quaternion SC to GEI transformation 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. Scalar Other INT_TAIL Q3 Attitude quaternion SC to GEI transformation 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. Scalar Other INT_TAIL Right ascension of the spin axis in GEI coordinate system INT_TAIL Right ascension of the spin axis in GEI (Geocentric Equatorial Inertial) coordinate system ° 0.0174532925>rad Spherical GEI Scalar Other INT_TAIL Declination of the spin axis in GEI coordinate system INT_TAIL Declination of the spin axis in GEI (Geocentric Equatorial Inertial) coordinate system ° 0.0174532925>rad Spherical GEI Scalar Other INT_TAIL Right ascension of the spin axis in GSE coordinate system INT_TAIL Right ascension of the spin axis in GSE (Geocentric Equatorial Inertial) coordinate system ° 0.0174532925>rad Spherical GSE Scalar Other INT_TAIL Declination of the spin axis in GSE coordinate system INT_TAIL Declination of the spin axis in GSE (Geocentric Equatorial Inertial) coordinate system ° 0.0174532925>rad Spherical GSE Scalar Other