Version:2.4.0
NumericalData
ResourceID
spase://CNES/NumericalData/CDPP-Archive/Interball-Auroral/Ephemeris-Auroral/INT_AUR_ATTITUDE
ResourceHeader
ResourceName
INT_AUR : Attitude Data
DOI
https://doi.org/10.24400/802406/zjkg-4kq6
ReleaseDate
2022-04-27 18:07:14Z
Description
This data set contains the attitude quaternions of Interball-Auroral allowing the conversion of any vector from the satellite body-build frame to GEI-1950 frame.
Contacts
AccessInformation
RepositoryID
Availability
Online
AccessURL
Name
REGARDS
URL
Description
Access via CNES Data Archive for CDPP
Format
Binary
InstrumentIDs
MeasurementType
Ephemeris
TemporalDescription
TimeSpan
StartDate
1996-09-11 00:00:00Z
StopDate
1998-07-27 00:00:00Z
Parameter #1
Name
INT_AUR Q0 Attitude quaternion SC to GEI transformation
Description
INT_AUR 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
Parameter #2
Name
INT_AUR Q1 Attitude quaternion SC to GEI transformation
Description
INT_AUR 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
Parameter #3
Name
INT_AUR Q2 Attitude quaternion SC to GEI transformation
Description
INT_AUR 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
Parameter #4
Name
INT_AUR Q3 Attitude quaternion SC to GEI transformation
Description
INT_AUR 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
Parameter #5
Name
INT_AUR Right ascension of the spin axis in GEI coordinate system
Description
INT_AUR 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
Parameter #6
Name
INT_AUR Declination of the spin axis in GEI coordinate system
Description
INT_AUR 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
Parameter #7
Name
INT_AUR Right ascension of the spin axis in GSE coordinate system
Description
INT_AUR 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
Parameter #8
Name
INT_AUR Declination of the spin axis in GSE coordinate system
Description
INT_AUR 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