Uses of Class
org.orekit.attitudes.FieldAttitude

Packages that use FieldAttitude

Package	Description
org.orekit.attitudes	This package provides classes to represent simple attitudes.
org.orekit.files.ccsds.ndm.adm	This package contains class managing CCSDS Attitude Data Message.
org.orekit.forces.maneuvers.propulsion	This package provides propulsion models intended to be used with class Maneuver.
org.orekit.propagation	Propagation

Uses of FieldAttitude in org.orekit.attitudes

Methods in org.orekit.attitudes that return FieldAttitude

Modifier and Type	Method	Description
<T extends CalculusFieldElement<T>> FieldAttitude<T>	AttitudeBuilder.build(Frame frame, FieldPVCoordinatesProvider<T> pvProv, TimeStampedFieldAngularCoordinates<T> rawAttitude)	Build a filtered attitude.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	FixedFrameBuilder.build(Frame frame, FieldPVCoordinatesProvider<T> pvProv, TimeStampedFieldAngularCoordinates<T> rawAttitude)	Build a filtered attitude.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	AggregateBoundedAttitudeProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the attitude corresponding to an orbital state.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	AlignedAndConstrained.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the attitude corresponding to an orbital state.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	AttitudeProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the attitude corresponding to an orbital state.
default <T extends CalculusFieldElement<T>> FieldAttitude<T>	AttitudeProviderModifier.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the attitude corresponding to an orbital state.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	CelestialBodyPointed.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the attitude corresponding to an orbital state.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	FixedRate.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the attitude corresponding to an orbital state.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	FrameAlignedProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the attitude corresponding to an orbital state.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	GroundPointing.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the attitude corresponding to an orbital state.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	LofOffset.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the attitude corresponding to an orbital state.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	LofOffsetPointing.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the attitude corresponding to an orbital state.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	SpinStabilized.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the attitude corresponding to an orbital state.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	TabulatedLofOffset.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the attitude corresponding to an orbital state.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	TabulatedProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the attitude corresponding to an orbital state.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	TorqueFree.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the attitude corresponding to an orbital state.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	YawCompensation.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the attitude corresponding to an orbital state.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	YawSteering.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the attitude corresponding to an orbital state.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	GroundPointingAttitudeModifier.getBaseState(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the base system state at given date, without modifications.
protected FieldAttitude<KK>	FieldAttitudeInterpolator.interpolate(AbstractFieldTimeInterpolator<FieldAttitude<KK>,KK>.InterpolationData interpolationData)	Interpolate instance from given interpolation data.
FieldAttitude<T>	FieldAttitude.shiftedBy(double dt)	Get a time-shifted attitude.
FieldAttitude<T>	FieldAttitude.shiftedBy(T dt)	Get a time-shifted attitude.
FieldAttitude<T>	FieldAttitude.withReferenceFrame(Frame newReferenceFrame)	Get a similar attitude with a specific reference frame.

Uses of FieldAttitude in org.orekit.files.ccsds.ndm.adm

Methods in org.orekit.files.ccsds.ndm.adm that return FieldAttitude

Modifier and Type	Method	Description
<T extends CalculusFieldElement<T>> FieldAttitude<T>	AttitudeEndpoints.build(Frame frame, FieldPVCoordinatesProvider<T> pvProv, TimeStampedFieldAngularCoordinates<T> rawAttitude)	Build a filtered attitude.

Uses of FieldAttitude in org.orekit.forces.maneuvers.propulsion

Methods in org.orekit.forces.maneuvers.propulsion with parameters of type FieldAttitude

Modifier and Type	Method	Description
<T extends CalculusFieldElement<T>> FieldVector3D<T>	PropulsionModel.getAcceleration(FieldSpacecraftState<T> s, FieldAttitude<T> maneuverAttitude, T[] parameters)	Get the acceleration of the spacecraft during maneuver and in maneuver frame.
default <T extends CalculusFieldElement<T>> FieldVector3D<T>	ThrustPropulsionModel.getAcceleration(FieldSpacecraftState<T> s, FieldAttitude<T> maneuverAttitude, T[] parameters)	Get the acceleration of the spacecraft during maneuver and in maneuver frame.

Uses of FieldAttitude in org.orekit.propagation

Methods in org.orekit.propagation that return FieldAttitude

Modifier and Type	Method	Description
FieldAttitude<T>	FieldSpacecraftState.getAttitude()	Get the attitude.

Methods in org.orekit.propagation that return types with arguments of type FieldAttitude

Modifier and Type	Method	Description
Optional<FieldTimeInterpolator<FieldAttitude<KK>,KK>>	FieldSpacecraftStateInterpolator.getAttitudeInterpolator()	Get attitude interpolator.

Methods in org.orekit.propagation with parameters of type FieldAttitude

Modifier and Type	Method	Description
FieldSpacecraftState<T>	FieldSpacecraftState.withAttitude(FieldAttitude<T> newAttitude)	Create a new instance with input attitude.

Constructors in org.orekit.propagation with parameters of type FieldAttitude

Modifier	Constructor	Description
	FieldSpacecraftState(FieldOrbit<T> orbit, FieldAttitude<T> attitude)	Build a spacecraft state from orbit and attitude.
	FieldSpacecraftState(FieldOrbit<T> orbit, FieldAttitude<T> attitude, T mass, FieldDataDictionary<T> additional, FieldArrayDictionary<T> additionalDot)	Build a spacecraft state from orbit, attitude, mass, additional states and derivatives.
	FieldSpacecraftState(FieldOrbit<T> orbit, FieldAttitude<T> attitude, T mass, T massRate, FieldDataDictionary<T> additional, FieldArrayDictionary<T> additionalDot)	Build a spacecraft state from orbit, attitude, mass, additional states and derivatives.
	FieldSpacecraftState(FieldAbsolutePVCoordinates<T> absPva, FieldAttitude<T> attitude)	Build a spacecraft state from absolute coordinates and attitude.
	FieldSpacecraftState(FieldAbsolutePVCoordinates<T> absPva, FieldAttitude<T> attitude, T mass, FieldDataDictionary<T> additional, FieldArrayDictionary<T> additionalDot)	Build a spacecraft state from absolute coordinates, attitude and mass.
	FieldSpacecraftState(FieldAbsolutePVCoordinates<T> absPva, FieldAttitude<T> attitude, T mass, T massRate, FieldDataDictionary<T> additional, FieldArrayDictionary<T> additionalDot)	Build a spacecraft state from absolute coordinates, attitude, mass and mass rate.