| Earth Observation Mission CFI Software Pointing Software User Manual for JAVA |

Public Member Functions

# EECFI.Attitude Class Reference

Attitude data and configuration. More...

Inheritance diagram for EECFI.Attitude:

List of all members.

## Public Member Functions
| Attitude () throws CfiError
| Empty Class constructor.
| Attitude (final TimeCorrelation timeId, final SatNomTransId satNomTrId, final SatTransId satTrId, final InstrTransId instTrId) throws CfiError
| Constructor with satellite frame ids.
void | setTransformations (final TimeCorrelation timeId, final SatNomTransId satNomTrId, final SatTransId satTrId, final InstrTransId instTrId) throws CfiError
| Set the transformations in the attitutde Id.
native void | compute (final ModelId modelId, final StateVector stateVector, long targetFrame) throws CfiError
| Compute attitude matrix.
native void | userSet (final ModelId modelId, final StateVector stateVector, long targetFrame, final double[][] matrix, final double[][] matrixRate, final double[][] matrixRateRate, final double[] offset) throws CfiError
| Assign user-defined attitude frame.
native AttitudeData | getData () throws CfiError
| Get attitude id data.
native void | setData (final AttitudeData attitudeData) throws CfiError
| Set attitude id data.
native Coord | changeFrame (final SatId satId, final ModelId modelId, long modeFlag, long frameFlagIn, long frameIdIn, long frameFlagOut, long frameIdOut, final StateVector satStateVec, final Coord statVecIn) throws CfiError
| Change the input vector/direction from a coordinate system to another ( including attitude frames ).
native void | eq (final Attitude att)
| Copy operator. It overwrites the one in CfiId, since this one makes an independent copy.

## Detailed Description

Attitude data and configuration.

## Constructor & Destructor Documentation

EECFI.Attitude.Attitude | ( |  | ) | throws CfiError

Empty Class constructor.

EECFI.Attitude::Attitude | ( | final TimeCorrelation | timeId,
|  | final SatNomTransId | satNomTrId,
|  | final SatTransId | satTrId,
|  | final InstrTransId | instTrId |
| ) |  |  | throws CfiError

Constructor with satellite frame ids.

Parameters:

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

## Member Function Documentation

Coord EECFI.Attitude::changeFrame | ( | final SatId | satId,
|  | final ModelId | modelId,
|  | long | modeFlag,
|  | long | frameFlagIn,
|  | long | frameIdIn,
|  | long | frameFlagOut,
|  | long | frameIdOut,
|  | final StateVector | satStateVec,
|  | final Coord | statVecIn |
| ) |  |  | throws 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).
  | statVecIn | 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.

void EECFI.Attitude::compute | ( | final ModelId | modelId,
|  | final StateVector | stateVector,
|  | long | targetFrame |
| ) |  |  | throws 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).

Attitude void EECFI.Attitude::eq | ( | final Attitude | att | ) |

Copy operator. It overwrites the one in CfiId, since this one makes an independent copy.

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.

AttitudeData EECFI.Attitude::getData | ( |  | ) | throws CfiError

Get attitude id data.

Returns:
  Attitude data.

void EECFI.Attitude::setData | ( | final AttitudeData | attitudeData | ) | throws CfiError

Set attitude id data.

Parameters:

  | attitudeData | Attitude data.

void EECFI.Attitude::setTransformations | ( | final TimeCorrelation | timeId,
|  | final SatNomTransId | satNomTrId,
|  | final SatTransId | satTrId,
|  | final InstrTransId | instTrId |
| ) |  |  | throws 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 | ( | final ModelId | modelId,
|  | final StateVector | stateVector,
|  | long | targetFrame,
|  | final double | matrix[][],
|  | final double | matrixRate[][],
|  | final double | matrixRateRate[][],
|  | final double[] | offset |
| ) |  |  | throws 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.