DEIMOS
Earth Observation Mission CFI Software
Pointing Software User Manual		 ESA
Public Member Functions | Protected Member Functions

EECFI::Attitude Class Reference

Attitude data and configuration. More...

Inheritance diagram for EECFI::Attitude:
EECFI::CfiId EECFI::CfiClass

List of all members.

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.
long getCSEnum (long frame)
 Get C frame enum.

Detailed Description

Attitude data and configuration.

Constructor & Destructor Documentation

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.

Parameters:
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.

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 
) 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.

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::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)

Compute attitude matrix.

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.
targetFrame Attitude frame (AttFrEnum).
long EECFI::Attitude::getCSEnum ( long  csIn  )  [protected]

Get C frame enum.

Parameters:
csIn Wrapper reference system enum.
Returns:
Reference system C enum value.
AttitudeData EECFI::Attitude::getData (  )  const throw (CfiError)

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.

GenericId * EECFI::Attitude::getId (  )  [protected]

Get the id.

Returns:
Pointer to xo_orbit_id.
Attitude const & EECFI::Attitude::operator= ( Attitude const &  att  ) 

Operator =.

Parameters:
att Attitude object to be copied.
Returns:
Attitude object copy of the input object; the new object is completely independent from the input one.

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

SatId EECFI::Attitude::satId (  )  const

Return satellite id.

Returns:
Satellite id.
void EECFI::Attitude::setData ( const AttitudeData &  attData  )  throw (CfiError)

Set attitude id data.

Parameters:
attData Attitude data.

References EECFI::CfiError::addMsg().

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..

Parameters:
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.

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.
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