Earth Observation Mission CFI Software Pointing Software User Manual |
Attitude data and configuration. More...
Public Member Functions | |
Attitude () throw (CfiError) | |
Empty Class constructor. | |
Attitude (const TimeCorrelation &timeId, const SatNomTransId &satNomTrId, const SatTransId &satTrId, const InstrTransId &instTrId) throw (CfiError) | |
Constructor with satellite frame ids. | |
~Attitude () throw (CfiError) | |
Class destructor. | |
void | setTransformations (const TimeCorrelation &timeId, const SatNomTransId &satNomTrId, const SatTransId &satTrId, const InstrTransId &instTrId) throw (CfiError) |
Set the transformations in the attitutde Id.. | |
void | compute (const ModelId &modelId, const StateVector &stateVector, long targetFrame) throw (CfiError) |
Compute attitude matrix. | |
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]) throw (CfiError) |
Assign user-defined attitude frame. | |
AttitudeData | getData () const throw (CfiError) |
Get attitude id data. | |
void | setData (const AttitudeData &attitudeData) throw (CfiError) |
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) throw (CfiError) |
Change the input vector/direction from a coordinate system to another ( including attitude frames ). | |
Attitude const & | operator= (Attitude const &att) |
Operator =. | |
SatId | satId () const |
Return satellite id. | |
Protected Member Functions | |
GenericId * | getId () |
Get the id. |
Attitude data and configuration.
EECFI::Attitude::Attitude | ( | ) | throw (CfiError) |
Empty Class constructor.
References EECFI::CfiClass::throwWarn.
EECFI::Attitude::Attitude | ( | const TimeCorrelation & | timeId, | |
const SatNomTransId & | satNomTrId, | |||
const SatTransId & | satTrId, | |||
const InstrTransId & | instTrId | |||
) | throw (CfiError) |
Constructor with satellite frame ids.
timeId | Time correlations. | |
satNomTrId | Satellite nominal attitude. | |
satTrId | Satellite attitude. | |
instTrId | Instrument attitude. |
EECFI::Attitude::~Attitude | ( | ) | throw (CfiError) |
Class destructor.
References EECFI::CfiId::status(), and EECFI::CfiClass::throwWarn.
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 | |||
) | throw (CfiError) |
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.
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). |
References EECFI::Coord::acc, EECFI::Coord::cs, EECFI::Coord::deriv, EECFI::Coord::pos, and EECFI::Coord::vel.
void EECFI::Attitude::compute | ( | const ModelId & | modelId, | |
const StateVector & | stateVector, | |||
long | targetFrame | |||
) | throw (CfiError) |
AttitudeData EECFI::Attitude::getData | ( | ) | const throw (CfiError) |
Get attitude id 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.
GenericId * EECFI::Attitude::getId | ( | ) | [protected] |
Get the id.
Operator =.
att | Attitude object to be copied. |
References EECFI::CfiError::addMsg(), and EECFI::CfiClass::throwWarn.
SatId EECFI::Attitude::satId | ( | ) | const |
Return satellite id.
void EECFI::Attitude::setData | ( | const AttitudeData & | attData | ) | throw (CfiError) |
void EECFI::Attitude::setTransformations | ( | const TimeCorrelation & | timeId, | |
const SatNomTransId & | satNomTrId, | |||
const SatTransId & | satTrId, | |||
const InstrTransId & | instTrId | |||
) | throw (CfiError) |
Set the transformations in the attitutde Id..
timeId | Time correlations. | |
satNomTrId | Satellite nominal attitude. | |
satTrId | Satellite attitude. | |
instTrId | Instrument 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] | |||
) | throw (CfiError) |
Assign user-defined attitude frame.
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. |