Attitude data and configuration.
More...
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 |
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.
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). |
Copy operator. It overwrites the one in CfiId, since this one makes an independent copy.
- Parameters:
-
- Returns:
- Attitude object copy of the input object; the new object is completely independent from the input one.
Get attitude id data.
- Returns:
- Attitude data.
Set attitude id data.
- Parameters:
-
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. |
Generated on Mon Mar 31 2014 12:26:09 for by 1.7.1