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 org.hipparchus.CalculusFieldElement<T>> FieldAttitude<T>	AttitudeBuilder.build(Frame frame, FieldPVCoordinatesProvider<T> pvProv, TimeStampedFieldAngularCoordinates<T> rawAttitude) Build a filtered attitude.
<T extends org.hipparchus.CalculusFieldElement<T>> FieldAttitude<T>	FixedFrameBuilder.build(Frame frame, FieldPVCoordinatesProvider<T> pvProv, TimeStampedFieldAngularCoordinates<T> rawAttitude) Build a filtered attitude.
<T extends org.hipparchus.CalculusFieldElement<T>> FieldAttitude<T>	TorqueFree.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the attitude corresponding to an orbital state.
<T extends org.hipparchus.CalculusFieldElement<T>> FieldAttitude<T>	TabulatedLofOffset.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the attitude corresponding to an orbital state.
<T extends org.hipparchus.CalculusFieldElement<T>> FieldAttitude<T>	CelestialBodyPointed.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the attitude corresponding to an orbital state.
<T extends org.hipparchus.CalculusFieldElement<T>> FieldAttitude<T>	YawSteering.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the attitude corresponding to an orbital state.
<T extends org.hipparchus.CalculusFieldElement<T>> FieldAttitude<T>	LofOffset.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the attitude corresponding to an orbital state.
<T extends org.hipparchus.CalculusFieldElement<T>> FieldAttitude<T>	FrameAlignedProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the attitude corresponding to an orbital state.
<T extends org.hipparchus.CalculusFieldElement<T>> FieldAttitude<T>	FixedRate.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the attitude corresponding to an orbital state.
<T extends org.hipparchus.CalculusFieldElement<T>> FieldAttitude<T>	TabulatedProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the attitude corresponding to an orbital state.
<T extends org.hipparchus.CalculusFieldElement<T>> FieldAttitude<T>	AggregateBoundedAttitudeProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the attitude corresponding to an orbital state.
<T extends org.hipparchus.CalculusFieldElement<T>> FieldAttitude<T>	AttitudeProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the attitude corresponding to an orbital state.
<T extends org.hipparchus.CalculusFieldElement<T>> FieldAttitude<T>	AttitudesSequence.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the attitude corresponding to an orbital state.
<T extends org.hipparchus.CalculusFieldElement<T>> FieldAttitude<T>	YawCompensation.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the attitude corresponding to an orbital state.
<T extends org.hipparchus.CalculusFieldElement<T>> FieldAttitude<T>	LofOffsetPointing.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the attitude corresponding to an orbital state.
<T extends org.hipparchus.CalculusFieldElement<T>> FieldAttitude<T>	SpinStabilized.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the attitude corresponding to an orbital state.
<T extends org.hipparchus.CalculusFieldElement<T>> FieldAttitude<T>	GroundPointing.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the attitude corresponding to an orbital state.
<T extends org.hipparchus.CalculusFieldElement<T>> FieldAttitude<T>	YawSteering.getBaseState(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the base system state at given date, without compensation.
<T extends org.hipparchus.CalculusFieldElement<T>> FieldAttitude<T>	YawCompensation.getBaseState(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the base system state at given date, without compensation.
protected FieldAttitude<KK>	FieldAttitudeInterpolator.interpolate(AbstractFieldTimeInterpolator.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 and Description
<T extends org.hipparchus.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 that return FieldAttitude

Modifier and Type	Method and Description
<T extends org.hipparchus.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 org.hipparchus.CalculusFieldElement<T>> org.hipparchus.geometry.euclidean.threed.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 org.hipparchus.CalculusFieldElement<T>> org.hipparchus.geometry.euclidean.threed.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.

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

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

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, 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(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, 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.

Constructor parameters in org.orekit.propagation with type arguments of type FieldAttitude

Constructor and Description

FieldSpacecraftStateInterpolator(Frame outputFrame, FieldTimeInterpolator<FieldOrbit<KK>,KK> orbitInterpolator, FieldTimeInterpolator<FieldAbsolutePVCoordinates<KK>,KK> absPVAInterpolator, FieldTimeInterpolator<TimeStampedField<KK>,KK> massInterpolator, FieldTimeInterpolator<FieldAttitude<KK>,KK> attitudeInterpolator, FieldTimeInterpolator<TimeStampedField<KK>,KK> additionalStateInterpolator) Constructor.