Attitude data and configuration. More...

Inheritance diagram for EECFI::Attitude:

Public Member Functions
	Attitude ()
	Default constructor.
	Attitude (const Attitude &other)
	Attitude (const TimeCorrelation &timeId, const SatNomTransId &satNomTrId, const SatTransId &satTrId, const InstrTransId &instTrId)
	Constructor with satellite frame ids.
virtual	~Attitude () EXCEPT
	Class destructor.
void	setTransformations (const TimeCorrelation &timeId, const SatNomTransId &satNomTrId, const SatTransId &satTrId, const InstrTransId &instTrId)
	Set the transformations in the attitutde Id..
void	compute (const ModelId &modelId, const StateVector &stateVector, long targetFrame)
void	userSet (const ModelId &modelId, const StateVector &stateVector, long targetFrame, const double matrix[3][3], const double matrixRate[3][3], const double matrixRateRate[3][3], const double offset[3])
	Assign user-defined attitude frame.
AttRec	getAttitudeData (long dataType, long sourceRefType, long sourceRef) const
	Compute quaternions/angles equivalent to the transformation from sourceRef to the attitude target frame.
AttitudeData	getData () const
	Get attitude id data.
void	setData (const AttitudeData &attitudeData)
	Set attitude id data.
Coord	changeFrame (const SatId &satId, const ModelId &modelId, long modeFlag, long frameFlagIn, long frameIdIn, long frameFlagOut, long frameIdOut, const StateVector &satStateVec, const Coord &statVecIn)
	Change the input vector/direction from a coordinate system to another ( including attitude frames ).
Attitude &	operator= (const Attitude &other)
SatId	satId () const
	Return satellite id.
Protected Member Functions
void	eraseObject ()
	Erase object and free memory.

Detailed Description

Attitude data and configuration.

Constructor & Destructor Documentation

EECFI::Attitude::Attitude ( )

Default constructor.

References EECFI::CfiId::status(), and EECFI::CfiClass::throwWarn.

EECFI::Attitude::Attitude ( const Attitude & other )

Copy constructor

Parameters:

other

The Attitude to copy from

EECFI::Attitude::Attitude	(	const TimeCorrelation &	timeId,
		const SatNomTransId &	satNomTrId,
		const SatTransId &	satTrId,
		const InstrTransId &	instTrId
	)

Constructor with satellite frame ids.

Parameters:

	timeId	Time correlations.
	satNomTrId	Satellite nominal attitude.
	satTrId	Satellite attitude.
	instTrId	Instrument attitude.

References setTransformations(), and EECFI::CfiClass::throwWarn.

EECFI::Attitude::~Attitude ( ) [virtual]

Class destructor.

References eraseObject().

Member Function Documentation

Coord EECFI::Attitude::changeFrame	(	const SatId &	satId,
		const ModelId &	modelId,
		long	modeFlag,
		long	frameFlagIn,
		long	frameIdIn,
		long	frameFlagOut,
		long	frameIdOut,
		const StateVector &	satStateVec,
		const Coord &	stateVec
	)

Change the input vector/direction from a coordinate system to another ( including attitude frames ).

This method changes the coordinate or attitude frame of a location or direction by keeping the location or direction in inertial space identical. Both all coordinate frames and all attitude frames are supported. When changing the frame for a location, the difference in origin of the frames is taken into account. While when changing the frame for a direction, the target is assumed to be at infinity.

Parameters:

	satId	Satellite id.
	modelId	Model id.
	modeFlag	Selection of location or direction calculus (ModeFlagPointingEnum).
	frameFlagIn	Selection of coordinate or Attitude frame on input (FrameFlagEnum).
	frameIdIn	Coordinate frame id or attitude frame id on input (AttFrEnum or CsRlEnum).
	frameFlagOut	Selection of coordinate or Attitude frame on output (FrameFlagEnum).
	frameIdOut	Coordinate frame id or attitude frame id on output (AttFrEnum or CsRlEnum).
	satStateVec	State vector with time, time reference, position, velocity and acceleration of satellite (Earth fixed CS).
	stateVec	Coordinates to be transformed in input frame (deriv indicates if pos, pos and vel or pos, vel and acc is to be calculated).

Returns:: Tranformed coordinates in ouput frame.

References EECFI::Coord::acc, EECFI::StateVector::coord, EECFI::Coord::cs, EECFI::Coord::deriv, EECFI::SatId::getSatellite(), EECFI::Coord::pos, EECFI::Time::ref, EECFI::CfiClass::throwWarn, EECFI::Time::time, EECFI::StateVector::time, and EECFI::Coord::vel.

void EECFI::Attitude::compute	(	const ModelId &	modelId,
		const StateVector &	stateVector,
		long	targetFrame
	)

Compute attitude matrix.

Note: it can be internally applied a correction to computations in order to compensate for the travel time of light from the Sun to the Earth and the satellites orbiting it. To activate this compensation, the Sun model in xl_model_id must be initialized with the enum XL_MODEL_SUN_TRAVEL_TIME using the function xl_model_init (see [LIBSUM]).

This method calculates the Attitude Frame for a given S/C state vector.

Parameters:

	modelId	Model Id.
	stateVector	State vector which contains time reference, time, position, velocity and acceleration needed for computation. Coordinates must be in Earth Fixed reference frame.
	targetFrame	Attitude frame (AttFrEnum).

References EECFI::Coord::acc, EECFI::CfiError::addMsg(), EECFI::StateVector::coord, EECFI::Coord::cs, EECFI::Coord::pos, EECFI::Time::ref, EECFI::CfiClass::throwWarn, EECFI::Time::time, EECFI::StateVector::time, and EECFI::Coord::vel.

void EECFI::Attitude::eraseObject ( ) [protected]

Erase object and free memory.

References EECFI::CfiError::addMsg(), EECFI::CfiId::status(), and EECFI::CfiClass::throwWarn.

Referenced by operator=(), and ~Attitude().

AttRec EECFI::Attitude::getAttitudeData	(	long	dataType,
		long	sourceRefType,
		long	sourceRef
	)			const

Compute quaternions/angles equivalent to the transformation from sourceRef to the attitude target frame.

This method computes the quaternions or Euler angles that returns the transformation between the sourceRef frame and the target frame defined in the attitude object

Parameters:

	dataType	requested data type: quaternions or angles
	sourceRefType	Source reference frame type: external or satellite
	sourceRef	Source reference frame

Returns:: Attitude record with the time and quaternions or angles.

References EECFI::CfiClass::throwWarn.

AttitudeData EECFI::Attitude::getData ( ) const

Get attitude id data.

Returns:: Attitude data.

References EECFI::Coord::acc, EECFI::CfiError::addMsg(), EECFI::CsTra::ambFlag, EECFI::AttitudeData::attitudeEF, EECFI::AzElDefinition::az0Axis, EECFI::AzElDefinition::az90Axis, EECFI::CsTra::azelDef, EECFI::CsTra::azelFlag, EECFI::StateVector::coord, EECFI::Coord::cs, EECFI::CsTra::deriv, EECFI::Coord::deriv, EECFI::AzElDefinition::el90Axis, EECFI::Time::format, EECFI::CsTra::m, EECFI::CsTra::m2d, EECFI::CsTra::md, EECFI::AttitudeData::model, EECFI::AttitudeData::offset, EECFI::Coord::pos, EECFI::Time::ref, EECFI::CsTra::reff, EECFI::CsTra::refi, EECFI::AttitudeData::satMat, EECFI::AttitudeData::satVector, EECFI::AttitudeData::sourceFrame, EECFI::AttitudeData::targetFrame, EECFI::CfiClass::throwWarn, EECFI::Time::time, EECFI::StateVector::time, EECFI::CsTra::v, EECFI::CsTra::v2d, EECFI::CsTra::vd, and EECFI::Coord::vel.

Attitude & EECFI::Attitude::operator= ( const Attitude & other )

Copy assignment operator.

Parameters:

other

The Attitude to copy/assign from

References EECFI::CfiError::addMsg(), eraseObject(), and EECFI::CfiClass::throwWarn.

SatId EECFI::Attitude::satId ( ) const

Return satellite id.

Returns:: Satellite id.

void EECFI::Attitude::setData ( const AttitudeData & attData )

Set attitude id data.

Parameters:

attData

Attitude data.

References EECFI::Coord::acc, EECFI::CfiError::addMsg(), EECFI::CsTra::ambFlag, EECFI::AttitudeData::attitudeEF, EECFI::AzElDefinition::az0Axis, EECFI::AzElDefinition::az90Axis, EECFI::CsTra::azelDef, EECFI::CsTra::azelFlag, EECFI::StateVector::coord, EECFI::Coord::cs, EECFI::CsTra::deriv, EECFI::Coord::deriv, EECFI::AzElDefinition::el90Axis, EECFI::CsTra::m, EECFI::CsTra::m2d, EECFI::CsTra::md, EECFI::AttitudeData::model, EECFI::AttitudeData::offset, EECFI::Coord::pos, EECFI::Time::ref, EECFI::CsTra::reff, EECFI::CsTra::refi, EECFI::AttitudeData::satMat, EECFI::AttitudeData::satVector, EECFI::AttitudeData::sourceFrame, EECFI::AttitudeData::targetFrame, EECFI::CfiClass::throwWarn, EECFI::Time::time, EECFI::StateVector::time, EECFI::CsTra::v, EECFI::CsTra::v2d, EECFI::CsTra::vd, and EECFI::Coord::vel.

void EECFI::Attitude::setTransformations	(	const TimeCorrelation &	timeId,
		const SatNomTransId &	satNomTrId,
		const SatTransId &	satTrId,
		const InstrTransId &	instTrId
	)

Set the transformations in the attitutde Id..

Parameters:

	timeId	Time correlations.
	satNomTrId	Satellite nominal attitude.
	satTrId	Satellite attitude.
	instTrId	Instrument attitude.

Referenced by Attitude().

void EECFI::Attitude::userSet	(	const ModelId &	modelId,
		const StateVector &	stateVector,
		long	targetFrame,
		const double	matrix[3][3],
		const double	matrixRate[3][3],
		const double	matrixRateRate[3][3],
		const double	offset[3]
	)

Assign user-defined attitude frame.

Parameters:

	modelId	Model Id.
	stateVector	State vector with time, time reference, position, velocity and acceleration needed for computation.
	targetFrame	Attitude frame ID (AttFrEnum).
	matrix	Matrix represeting the transformation from ToD to targetFrame.
	matrixRate	Matrix represeting the transformation rate from ToD to targetFrame.
	matrixRateRate	Matrix represeting the transformation rate rate from ToD to targetFrame.
	offset	Offset in the reference frame origin.

References EECFI::Coord::acc, EECFI::StateVector::coord, EECFI::Coord::pos, EECFI::Time::ref, EECFI::CfiClass::throwWarn, EECFI::Time::time, EECFI::StateVector::time, and EECFI::Coord::vel.

Generated on Mon Dec 11 2023 13:28:30 for by

1.7.1

EECFI::Attitude Class Reference

Public Member Functions

Protected Member Functions

Detailed Description

Constructor & Destructor Documentation

Member Function Documentation