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.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 and Description
<T extends RealFieldElement<T>> FieldAttitude<T>	YawCompensation.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the attitude corresponding to an orbital state.
<T extends RealFieldElement<T>> FieldAttitude<T>	LofOffset.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the attitude corresponding to an orbital state.
<T extends RealFieldElement<T>> FieldAttitude<T>	AttitudeProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the attitude corresponding to an orbital state.
<T extends RealFieldElement<T>> FieldAttitude<T>	InertialProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the attitude corresponding to an orbital state.
<T extends RealFieldElement<T>> FieldAttitude<T>	FixedRate.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the attitude corresponding to an orbital state.
<T extends RealFieldElement<T>> FieldAttitude<T>	AttitudesSequence.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the attitude corresponding to an orbital state.
<T extends RealFieldElement<T>> FieldAttitude<T>	GroundPointing.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the attitude corresponding to an orbital state.
<T extends RealFieldElement<T>> FieldAttitude<T>	SpinStabilized.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the attitude corresponding to an orbital state.
<T extends RealFieldElement<T>> FieldAttitude<T>	LofOffsetPointing.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the attitude corresponding to an orbital state.
<T extends RealFieldElement<T>> FieldAttitude<T>	TabulatedLofOffset.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the attitude corresponding to an orbital state.
<T extends RealFieldElement<T>> FieldAttitude<T>	YawSteering.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the attitude corresponding to an orbital state.
<T extends RealFieldElement<T>> FieldAttitude<T>	TabulatedProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the attitude corresponding to an orbital state.
<T extends RealFieldElement<T>> FieldAttitude<T>	CelestialBodyPointed.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the attitude corresponding to an orbital state.
<T extends RealFieldElement<T>> FieldAttitude<T>	YawCompensation.getBaseState(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the base system state at given date, without compensation.
<T extends RealFieldElement<T>> FieldAttitude<T>	YawSteering.getBaseState(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the base system state at given date, without compensation.
FieldAttitude<T>	FieldAttitude.interpolate(FieldAbsoluteDate<T> interpolationDate, Stream<FieldAttitude<T>> sample) Get an interpolated instance.
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.

Method parameters in org.orekit.attitudes with type arguments of type FieldAttitude

Modifier and Type	Method and Description
FieldAttitude<T>	FieldAttitude.interpolate(FieldAbsoluteDate<T> interpolationDate, Stream<FieldAttitude<T>> sample) Get an interpolated instance.

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

Methods in org.orekit.forces.maneuvers.propulsion that return FieldAttitude

Modifier and Type	Method and Description
<T extends RealFieldElement<T>> FieldAttitude<T>	ThrustDirectionAndAttitudeProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the attitude corresponding to an orbital state.

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

Modifier and Type	Method and Description
default <T extends RealFieldElement<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.
<T extends RealFieldElement<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.

Uses of FieldAttitude in org.orekit.propagation

Methods in org.orekit.propagation that return FieldAttitude

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

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

Constructor and Description
FieldSpacecraftState(FieldAbsolutePVCoordinates<T> absPva, FieldAttitude<T> attitude) Build a spacecraft state from orbit and attitude provider.
FieldSpacecraftState(FieldAbsolutePVCoordinates<T> absPva, FieldAttitude<T> attitude, Map<String,T[]> additional) Build a spacecraft state from orbit and attitude provider.
FieldSpacecraftState(FieldAbsolutePVCoordinates<T> absPva, FieldAttitude<T> attitude, T mass) Build a spacecraft state from orbit, attitude provider and mass.
FieldSpacecraftState(FieldAbsolutePVCoordinates<T> absPva, FieldAttitude<T> attitude, T mass, Map<String,T[]> additional) Build a spacecraft state from orbit, attitude provider and mass.
FieldSpacecraftState(FieldOrbit<T> orbit, FieldAttitude<T> attitude) Build a spacecraft state from orbit and attitude provider.
FieldSpacecraftState(FieldOrbit<T> orbit, FieldAttitude<T> attitude, Map<String,T[]> additional) Build a spacecraft state from orbit and attitude provider.
FieldSpacecraftState(FieldOrbit<T> orbit, FieldAttitude<T> attitude, T mass) Build a spacecraft state from orbit, attitude provider and mass.
FieldSpacecraftState(FieldOrbit<T> orbit, FieldAttitude<T> attitude, T mass, Map<String,T[]> additional) Build a spacecraft state from orbit, attitude provider and mass.