Class for storing the Satellite Nominal Attitude configuration parameters. More...

Inheritance diagram for EECFI.SatTransId:

Public Member Functions
	SatTransId ()
	Empty Class constructor.
void	close () throws CfiError
	Release all resources managed by this object.
native void	init (double[] angle) throws CfiError
	Initialise using angles.
native void	init (double[][] matrix) throws CfiError
	Initialise using matrix.
native void	init (long angleType, final Vector< Long > harmTypePitch, final Vector< Long > harmTypeRoll, final Vector< Long > harmTypeYaw, final Vector< Double > harmCoeffPitch, final Vector< Double > harmCoeffRoll, final Vector< Double > harmCoeffYaw) throws CfiError
	Initialise satellite orbital to satellite nominal attitude mispointing angles for a given satellite with harmonics.
native void	init (long inertialFrame, final Vector< AttRec > quaternions, double[][] matrix) throws CfiError
	Initialise using quaternions plus matrix.
native void	init (long inertialFrame, final Vector< AttRec > quaternions, double[] angles) throws CfiError
	Initialise using quaternions plus angles.
native void	init (final TimeCorrelation timeId, final Vector< String > files, String auxiliaryFile, long timeInitMode, long timeRef, double time0, double time1) throws CfiError
	Initialise satellite attitude angles for a given satellite reading values from the attitude files.
native MatrixModel	getMatrix () throws CfiError
	Get matrix parameters.
native void	setMatrix (final MatrixModel matrixModel) throws CfiError
	Change initialisation AOCS parameters from the object.
native AngleModel	getAngles () throws CfiError
	Get angles model.
native void	setAngles (final AngleModel angleModel) throws CfiError
	Change angles model.
native HarmonicModel	getHarmonic () throws CfiError
	Get harmonic parameters of object.
native void	setHarmonic (final HarmonicModel harmModel) throws CfiError
	Change harmonic parameters of the object.
native SatAttFileModel	getFile () throws CfiError
	Get file data of object.
native void	setFile (final SatAttFileModel fileModel) throws CfiError
	Change initialisation file data of the object.
native void	setAzElDefinition (final AzElDefinition azElDef) throws CfiError
	Set azimuth/elevation definition.
native QuatPlusMatrixModel	getQuatPlusMatrix () throws CfiError
	Get quaternions plus matrix model.
native void	setQuatPlusMatrix (final QuatPlusMatrixModel quatPlusMatrixModel) throws CfiError
	Change quaternions plus matrix model.
native QuatPlusAnglesModel	getQuatPlusAngles () throws CfiError
	Get quaternions plus angles model.
native void	setQuatPlusAngles (final QuatPlusAnglesModel quatPlusAnglesModel) throws CfiError
	Change quaternions plus angles model.
native SatId	satId ()
	Return satellite id.

Detailed Description

Class for storing the Satellite Nominal Attitude configuration parameters.

Constructor & Destructor Documentation

EECFI.SatTransId.SatTransId ( )

Empty Class constructor.

Member Function Documentation

void EECFI.SatTransId.close ( ) throws CfiError

Release all resources managed by this object.

IMPORTANT: The life time of the EOCFI Java objects must be explicitly managed by the program work flow. Failure to perform this release will lead to resource leakage and might have a significant impact in performance.

AngleModel EECFI.SatTransId::getAngles ( ) throws CfiError

Get angles model.

Returns:: Angle model data.

SatAttFileModel EECFI.SatTransId::getFile ( ) throws CfiError

Get file data of object.

Returns:: File model data.

HarmonicModel EECFI.SatTransId::getHarmonic ( ) throws CfiError

Get harmonic parameters of object.

Returns:: Harmonic model data.

MatrixModel EECFI.SatTransId::getMatrix ( ) throws CfiError

Get matrix parameters.

Returns:: Matrix model data.

QuatPlusAnglesModel EECFI.SatTransId::getQuatPlusAngles ( ) throws CfiError

Get quaternions plus angles model.

Returns:: Quaternion plus angles model data.

QuatPlusMatrixModel EECFI.SatTransId::getQuatPlusMatrix ( ) throws CfiError

Get quaternions plus matrix model.

Returns:: Quaternion plus matrix model data.

void EECFI.SatTransId::init	(	final TimeCorrelation	timeId,
		final Vector< String >	files,
		String	auxiliaryFile,
		long	timeInitMode,
		long	timeRef,
		double	time0,
		double	time1
	)			throws CfiError

Initialise satellite attitude angles for a given satellite reading values from the attitude files.

In order to read files, this method internally uses Data Handling functions.

Please refer to [D_H_SUM] for further details.

Parameters:

	timeId	Time correlations.
	files	Filenames of the reference data files. In case multiple files are used, the files should be time ordered. The supported Attitude File formats are the Generic Attitude File (described in [DAT_SUM]) and Star Tracker files. If multiple files are used, Generic Attitude Files and Star Tracker files cannot be given to the function as part of the same list. When using Star-Tracker files, the function assumes that all the input files belong to the same Star-Tracker. As a consequence of this assumption only the Star-Tracker identifier of the first file provided in the list is read. Note that the Star-Tracker identification number should be either 1, 2 or 3 (no internal check is performed).
	auxiliaryFile	Auxiliary file with StarTracker misalignment matrices.
	timeInitMode	Flag for selecting the time range of the initialisation (XPCFI_SEL_TIME/XPCFI_SEL_FILE).
	timeRef	Time reference (TimeRefPointingEnum).
	time0	Start of the time range [Decimal days (Processing format)].
	time1	Stop of the time range [Decimal days (Processing format)].

void EECFI.SatTransId::init ( double matrix[][] ) throws CfiError

Initialise using matrix.

Parameters:

matrix

Rotation matrix.

void EECFI.SatTransId::init	(	long	angleType,
		final Vector< Long >	harmTypePitch,
		final Vector< Long >	harmTypeRoll,
		final Vector< Long >	harmTypeYaw,
		final Vector< Double >	harmCoefPitch,
		final Vector< Double >	harmCoefRoll,
		final Vector< Double >	harmCoefYaw
	)			throws CfiError

Initialise satellite orbital to satellite nominal attitude mispointing angles for a given satellite with harmonics.

The Attitude.compute and Attitude.changeFrame functions will then compute the values as follows:

Parameters:

	angleType	Type of angle (given by PointingAngleTypeEnum).
	harmTypePitch	Type of coefficients: 0= for the bias parameter <0 for the sinus coefficients (-n means that corresponds to the sinus coefficient of order n) >0 for the cosinus coefficients (-n means that corresponds to the cosinus coefficient of order n) .
	harmTypeRoll	Type of coefficients (bias, sinus, cosinus, see documentation).
	harmTypeYaw	Type of coefficients (bias, sinus, cosinus, see documentation).
	harmCoefPitch	Bias, sinus and cosinus coefficients for the pitch angle.
	harmCoefRoll	Bias, sinus and cosinus coefficients for the roll angle.
	harmCoefYaw	Bias, sinus and cosinus coefficients for the yaw angle.

void EECFI.SatTransId::init ( double[] angle ) throws CfiError

Initialise using angles.

Parameters:

angle

Rotation angles.

[0]: Pitch mispointing angle (Satellite Nominal Attitude Frame) [deg]. Allowed range: If no better value, assume 0.0.
[1]: Roll mispointing angle (Satellite Nominal Attitude Frame) [deg]. Allowed range: If no better value, assume 0.0.
[2]: Yaw mispointing angle (Satellite Nominal Attitude Frame) [deg]. Allowed range: If no better value, assume 0.0.

.

void EECFI.SatTransId::init	(	long	inertialFrame,
		final Vector< AttRec >	quaternions,
		double	matrix[][]
	)			throws CfiError

Initialise using quaternions plus matrix.

Parameters:

	inertialFrame	Inertial frame (CoordinateSystemsEnum).
	quaternions	Quaternions that give the rotation from the inertial reference frame to the frame based on the satellite.
	matrix	Rotation matrix from the frame based on the satellite to the satellite frame.

void EECFI.SatTransId::init	(	long	inertialFrame,
		final Vector< AttRec >	quaternions,
		double[]	angles
	)			throws CfiError

Initialise using quaternions plus angles.

Parameters:

	inertialFrame	Inertial frame (CoordinateSystemsEnum).
	quaternions	Quaternions that give the rotation from the inertial reference frame to the frame based on the satellite.
	angles	Angles that define the rotation from the frame based on the satellite to the satellite frame.

native SatId EECFI.SatTransId.satId ( )

Return satellite id.

void EECFI.SatTransId::setAngles ( final AngleModel angleModel ) throws CfiError

Change angles model.

Parameters:

angleModel

Angle model data.

void EECFI.SatTransId::setAzElDefinition ( final AzElDefinition azElDef ) throws CfiError

Set azimuth/elevation definition.

Parameters:

azElDef

Definition of azimuth and elevation.

void EECFI.SatTransId::setFile ( final SatAttFileModel fileModel ) throws CfiError

Change initialisation file data of the object.

Parameters:

fileModel

File model data.

void EECFI.SatTransId::setHarmonic ( final HarmonicModel harmModel ) throws CfiError

Change harmonic parameters of the object.

Parameters:

harmModel

Harmonic model data.

void EECFI.SatTransId::setMatrix ( final MatrixModel matrixModel ) throws CfiError

Change initialisation AOCS parameters from the object.

Parameters:

matrixModel

Matrix model data.

void EECFI.SatTransId::setQuatPlusAngles ( final QuatPlusAnglesModel quatPlusAng ) throws CfiError

Change quaternions plus angles model.

Parameters:

quatPlusAng

Quaternion plus angles model data.

void EECFI.SatTransId::setQuatPlusMatrix ( final QuatPlusMatrixModel quatPlusMatrixModel ) throws CfiError

Change quaternions plus matrix model.

Parameters:

quatPlusMatrixModel

Quaternion plus matrix model data.

Generated on Mon Dec 11 2023 14:48:29 for by

1.7.1

EECFI.SatTransId Class Reference

Public Member Functions

Detailed Description

Constructor & Destructor Documentation

Member Function Documentation