fr.cnes.sirius.patrius.attitudes

Interface AttitudeLeg

All Superinterfaces:

AttitudeProvider, Leg, Serializable, TimeStamped

All Known Subinterfaces:

AttitudeProfile, Slew

All Known Implementing Classes:

AbstractAngularVelocitiesAttitudeProfile, AbstractAttitudeProfile, AngularVelocitiesHarmonicProfile, AngularVelocitiesPolynomialProfile, AngularVelocitiesPolynomialProfileLeg, AngularVelocitiesPolynomialSlew, AttitudeLawLeg, ConstantSpinSlew, QuaternionDatePolynomialProfile, QuaternionHarmonicProfile, QuaternionPolynomialProfile, RelativeTabulatedAttitudeLeg, TabulatedAttitude, TabulatedSlew

public interface AttitudeLeg
extends Leg, AttitudeProvider

Interface for all attitude legs: Leg and AttitudeProvider.

Since:

4.7

Author:

Julien Anxionnat (CNES — DSO/DV/MP)

See Also:

Leg, AttitudeProvider

Field Summary

Fields

Modifier and Type	Field and Description
static String	LEG_NATURE Default nature for attitude legs.

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).
AttitudeLeg	copy(AbsoluteDateInterval newInterval) Creates a new leg from this one.

Methods inherited from interface fr.cnes.sirius.patrius.utils.legs.Leg

contains, getDate, getEnd, getNature, getTimeInterval, toPrettyString

Methods inherited from interface fr.cnes.sirius.patrius.attitudes.AttitudeProvider

getAttitude, getAttitude, setSpinDerivativesComputation

Field Detail

LEG_NATURE

static final String LEG_NATURE

Default nature for attitude legs.

See Also:

Constant Field Values

Method Detail

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

Time interval boundaries are properly taken into account.

Specified by:

computeSpinByFD in interface AttitudeProvider

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

Time interval boundaries are properly taken into account.

Specified by:

computeSpinDerivativeByFD in interface AttitudeProvider

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

copy

AttitudeLeg copy(AbsoluteDateInterval newInterval)

Creates a new leg from this one.

Specified by:

copy in interface Leg

Parameters:

newInterval - The time interval of the leg to create

Returns:

A new Leg valid on provided interval