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 and 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>	YawCompensation.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>	AttitudeProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the attitude corresponding to an orbital state.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	InertialProvider.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>	AttitudesSequence.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>	SpinStabilized.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>	TabulatedLofOffset.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>	AggregateBoundedAttitudeProvider.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>	CelestialBodyPointed.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the attitude corresponding to an orbital state.
<T extends CalculusFieldElement<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 CalculusFieldElement<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.files.ccsds.ndm.adm

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

Modifier and Type	Method and Description
<T extends CalculusFieldElement<T>> FieldAttitude<T>	AttitudeEndoints.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 that return FieldAttitude

Modifier and Type	Method and Description
<T extends CalculusFieldElement<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 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.
<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.

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.
FieldSpacecraftState(FieldAbsolutePVCoordinates<T> absPva, FieldAttitude<T> attitude, FieldArrayDictionary<T> additional) Build a spacecraft state from orbit and attitude.
FieldSpacecraftState(FieldAbsolutePVCoordinates<T> absPva, FieldAttitude<T> attitude, Map<String,T[]> additional) Deprecated. as of 11.1, replaced by FieldSpacecraftState.FieldSpacecraftState(FieldAbsolutePVCoordinates, FieldAttitude, FieldArrayDictionary)
FieldSpacecraftState(FieldAbsolutePVCoordinates<T> absPva, FieldAttitude<T> attitude, T mass) Build a spacecraft state from orbit, attitude and mass.
FieldSpacecraftState(FieldAbsolutePVCoordinates<T> absPva, FieldAttitude<T> attitude, T mass, FieldArrayDictionary<T> additional) Build a spacecraft state from orbit, attitude and mass.
FieldSpacecraftState(FieldAbsolutePVCoordinates<T> absPva, FieldAttitude<T> attitude, T mass, FieldArrayDictionary<T> additional, FieldArrayDictionary<T> additionalDot) Build a spacecraft state from orbit, attitude and mass.
FieldSpacecraftState(FieldAbsolutePVCoordinates<T> absPva, FieldAttitude<T> attitude, T mass, Map<String,T[]> additional) Deprecated. as of 11.1, replaced by FieldSpacecraftState.FieldSpacecraftState(FieldAbsolutePVCoordinates, FieldAttitude, CalculusFieldElement, FieldArrayDictionary)
FieldSpacecraftState(FieldOrbit<T> orbit, FieldAttitude<T> attitude) Build a spacecraft state from orbit and attitude.
FieldSpacecraftState(FieldOrbit<T> orbit, FieldAttitude<T> attitude, FieldArrayDictionary<T> additional) Build a spacecraft state from orbit attitude and additional states.
FieldSpacecraftState(FieldOrbit<T> orbit, FieldAttitude<T> attitude, Map<String,T[]> additional) Deprecated. as of 11.1, replaced by FieldSpacecraftState.FieldSpacecraftState(FieldOrbit, FieldAttitude, FieldArrayDictionary)
FieldSpacecraftState(FieldOrbit<T> orbit, FieldAttitude<T> attitude, T mass) Build a spacecraft state from orbit, attitude and mass.
FieldSpacecraftState(FieldOrbit<T> orbit, FieldAttitude<T> attitude, T mass, FieldArrayDictionary<T> additional) Build a spacecraft state from orbit, attitude, mass and additional states.
FieldSpacecraftState(FieldOrbit<T> orbit, FieldAttitude<T> attitude, T mass, FieldArrayDictionary<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, Map<String,T[]> additional) Deprecated. as of 11.1, replaced by FieldSpacecraftState.FieldSpacecraftState(FieldOrbit, FieldAttitude, CalculusFieldElement, FieldArrayDictionary)