fr.cnes.sirius.patrius.attitudes

Interface AttitudeProvider

All Superinterfaces:

Serializable

All Known Subinterfaces:

AttitudeLaw, AttitudeLawModifier, AttitudeLeg, AttitudeProfile, Slew

All Known Implementing Classes:

AbstractAngularVelocitiesAttitudeProfile, AbstractAttitudeLaw, AbstractAttitudeProfile, AbstractGroundPointing, AbstractGroundPointingWrapper, AeroAttitudeLaw, AngularVelocitiesHarmonicProfile, AngularVelocitiesPolynomialProfile, AngularVelocitiesPolynomialProfileLeg, AngularVelocitiesPolynomialSlew, AttitudeLawLeg, AttitudeLegLaw, AttitudeProfilesSequence, AttitudesSequence, BodyCenterGroundPointing, BodyCenterPointing, CelestialBodyPointed, ComposedAttitudeLaw, ConstantAttitudeLaw, ConstantSpinSlew, FixedRate, IsisSunAndPseudoSpinPointing, IsisSunPointing, LofOffset, LofOffsetPointing, NadirPointing, QuaternionDatePolynomialProfile, QuaternionHarmonicProfile, QuaternionPolynomialProfile, RelativeTabulatedAttitudeLaw, RelativeTabulatedAttitudeLeg, SpinStabilized, StrictAttitudeLegsSequence, SunPointing, TabulatedAttitude, TabulatedSlew, TargetGroundPointing, TargetPointing, TwoDirectionAttitudeLaw, YawCompensation, YawSteering

public interface AttitudeProvider
extends Serializable

This interface represents an attitude provider model set.

An attitude provider provides a way to compute an Attitude from an date and position-velocity local provider.

Author:

Véronique Pommier-Maurussane

Method Summary

Modifier and Type	Method and Description
default Vector3D	computeSpinByFD(PVCoordinatesProvider pvProv, Frame frame, AbsoluteDate date, double computationStep) Compute the rotation rate vector at a given date by finite differences (using 2nd order centered finite differences).
default Vector3D	computeSpinDerivativeByFD(PVCoordinatesProvider pvProv, Frame frame, AbsoluteDate date, double computationStep) Compute the rotation acceleration vector at a given date by finite differences (using 2nd order centered finite differences).
default Attitude	getAttitude(Orbit orbit) Compute the attitude corresponding to an orbital state.
Attitude	getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
void	setSpinDerivativesComputation(boolean computeSpinDerivatives) Method to activate spin derivative computation.

Method Detail

getAttitude

Attitude getAttitude(PVCoordinatesProvider pvProv,
                     AbsoluteDate date,
                     Frame frame)
              throws PatriusException

Compute the attitude corresponding to an orbital state.

Parameters:

pvProv - local position-velocity provider around current date

date - current date

frame - reference frame from which attitude is computed

Returns:

attitude on the specified date and position-velocity state

Throws:

PatriusException - if attitude cannot be computed for provided date

getAttitude

default Attitude getAttitude(Orbit orbit)
                      throws PatriusException

Compute the attitude corresponding to an orbital state.

Parameters:

orbit - current orbit

Returns:

attitude on the current orbit

Throws:

PatriusException - if attitude cannot be computed

setSpinDerivativesComputation

void setSpinDerivativesComputation(boolean computeSpinDerivatives)

Method to activate spin derivative computation.

Parameters:

computeSpinDerivatives - true if spin derivatives should be computed

computeSpinByFD

default Vector3D computeSpinByFD(PVCoordinatesProvider pvProv,
                                 Frame frame,
                                 AbsoluteDate date,
                                 double computationStep)
                          throws PatriusException

Compute the rotation rate vector at a given date by finite differences (using 2nd order centered finite differences).

Warning: this method calls getAttitude(PVCoordinatesProvider, AbsoluteDate, Frame) hence it should not be called by this method.

Parameters:

pvProv - PV Coordinates Provider.

frame - Frame of expression of the attitude. The rotation rate will then be relative to this frame.

date - Date at which the rotation rate vector is desired.

computationStep - Computation step used for the finite differences (in seconds).

Returns:

The rotation rate vector of the satellite with respect to the specified frame, expressed in satellite frame.

Throws:

PatriusException - When the attitude cannot be computed

computeSpinDerivativeByFD

default Vector3D computeSpinDerivativeByFD(PVCoordinatesProvider pvProv,
                                           Frame frame,
                                           AbsoluteDate date,
                                           double computationStep)
                                    throws PatriusException

Compute the rotation acceleration vector at a given date by finite differences (using 2nd order centered finite differences).

Warning: this method calls getAttitude(PVCoordinatesProvider, AbsoluteDate, Frame) hence it should not be called by this method.

Parameters:

pvProv - PV Coordinates Provider.

frame - Frame of expression of the attitude. The rotation acceleration will then be relative to this frame.

date - Date at which the rotation acceleration vector is desired.

computationStep - Computation step used for the finite differences (in seconds).

Returns:

The rotation acceleration vector of the satellite with respect to the specified frame, expressed in satellite frame.

Throws:

PatriusException - When the attitude cannot be computed