Uses of Class
org.orekit.attitudes.Attitude

Packages that use Attitude

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.files.ccsds.ndm.adm.apm	This package contains class managing CCSDS Attitude Parameter Message.
org.orekit.forces.maneuvers.propulsion	This package provides propulsion models intended to be used with class Maneuver.
org.orekit.propagation	Propagation

Uses of Attitude in org.orekit.attitudes

Methods in org.orekit.attitudes that return Attitude

Modifier and Type	Method and Description
Attitude	AttitudeBuilder.build(Frame frame, PVCoordinatesProvider pvProv, TimeStampedAngularCoordinates rawAttitude) Build a filtered attitude.
Attitude	FixedFrameBuilder.build(Frame frame, PVCoordinatesProvider pvProv, TimeStampedAngularCoordinates rawAttitude) Build a filtered attitude.
Attitude	TorqueFree.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	TabulatedLofOffset.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	CelestialBodyPointed.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	YawSteering.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	LofOffset.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	FrameAlignedProvider.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	FixedRate.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	TabulatedProvider.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	AggregateBoundedAttitudeProvider.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	AttitudeProvider.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	AttitudesSequence.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	YawCompensation.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	LofOffsetPointing.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	SpinStabilized.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	GroundPointing.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	YawSteering.getBaseState(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the base system state at given date, without compensation.
Attitude	YawCompensation.getBaseState(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the base system state at given date, without compensation.
Attitude	TorqueFree.getInitialAttitude() Get the initial attitude.
Attitude	FixedRate.getReferenceAttitude() Get the reference attitude.
protected Attitude	AttitudeInterpolator.interpolate(AbstractTimeInterpolator.InterpolationData interpolationData) Interpolate instance from given interpolation data.
Attitude	Attitude.shiftedBy(double dt) Get a time-shifted attitude.
Attitude	FieldAttitude.toAttitude() Converts to an Attitude instance.
Attitude	Attitude.withReferenceFrame(Frame newReferenceFrame) Get a similar attitude with a specific reference frame.

Constructors in org.orekit.attitudes with parameters of type Attitude

Constructor and Description
FieldAttitude(org.hipparchus.Field<T> field, Attitude attitude) Builds an instance for a regular Attitude.
FixedRate(Attitude referenceAttitude) Creates a new instance.
TorqueFree(Attitude initialAttitude, Inertia inertia) Simple constructor.

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

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

Modifier and Type	Method and Description
Attitude	AttitudeEndpoints.build(Frame frame, PVCoordinatesProvider pvProv, TimeStampedAngularCoordinates rawAttitude) Build a filtered attitude.

Uses of Attitude in org.orekit.files.ccsds.ndm.adm.apm

Methods in org.orekit.files.ccsds.ndm.adm.apm that return Attitude

Modifier and Type	Method and Description
Attitude	Apm.getAttitude(Frame frame, PVCoordinatesProvider pvProvider) Get the attitude.
Attitude	ApmData.getAttitude(Frame frame, PVCoordinatesProvider pvProvider) Get the attitude.

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

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

Modifier and Type	Method and Description
Attitude	ThrustDirectionAndAttitudeProvider.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
protected Attitude	ThrustDirectionAndAttitudeProvider.getAttitudeFromFrame(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude for DIRECTION_IN_FRAME or DIRECTION_IN_LOF types.

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

Modifier and Type	Method and Description
default org.hipparchus.geometry.euclidean.threed.Vector3D	ThrustPropulsionModel.getAcceleration(SpacecraftState s, Attitude maneuverAttitude, double[] parameters) Get the acceleration of the spacecraft during maneuver and in maneuver frame.
org.hipparchus.geometry.euclidean.threed.Vector3D	PropulsionModel.getAcceleration(SpacecraftState s, Attitude maneuverAttitude, double[] parameters) Get the acceleration of the spacecraft during maneuver and in maneuver frame.

Uses of Attitude in org.orekit.propagation

Methods in org.orekit.propagation that return Attitude

Modifier and Type	Method and Description
Attitude	SpacecraftState.getAttitude() Get the attitude.

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

Modifier and Type	Method and Description
Optional<TimeInterpolator<Attitude>>	SpacecraftStateInterpolator.getAttitudeInterpolator() Get attitude interpolator.

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

Constructor and Description
SpacecraftState(AbsolutePVCoordinates absPva, Attitude attitude) Build a spacecraft state from position-velocity-acceleration and attitude.
SpacecraftState(AbsolutePVCoordinates absPva, Attitude attitude, double mass) Build a spacecraft state from position-velocity-acceleration, attitude and mass.
SpacecraftState(AbsolutePVCoordinates absPva, Attitude attitude, DoubleArrayDictionary additional) Build a spacecraft state from position-velocity-acceleration, attitude and additional states.
SpacecraftState(AbsolutePVCoordinates absPva, Attitude attitude, double mass, DoubleArrayDictionary additional) Build a spacecraft state from position-velocity-acceleration, attitude, mass and additional states.
SpacecraftState(AbsolutePVCoordinates absPva, Attitude attitude, double mass, DoubleArrayDictionary additional, DoubleArrayDictionary additionalDot) Build a spacecraft state from position-velocity-acceleration, attitude, mass and additional states and derivatives.
SpacecraftState(Orbit orbit, Attitude attitude) Build a spacecraft state from orbit and attitude.
SpacecraftState(Orbit orbit, Attitude attitude, double mass) Build a spacecraft state from orbit, attitude and mass.
SpacecraftState(Orbit orbit, Attitude attitude, DoubleArrayDictionary additional) Build a spacecraft state from orbit, attitude and additional states.
SpacecraftState(Orbit orbit, Attitude attitude, double mass, DoubleArrayDictionary additional) Build a spacecraft state from orbit, attitude, mass and additional states.
SpacecraftState(Orbit orbit, Attitude attitude, double mass, DoubleArrayDictionary additional, DoubleArrayDictionary additionalDot) Build a spacecraft state from orbit, attitude, mass, additional states and derivatives.

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

Constructor and Description
SpacecraftStateInterpolator(Frame outputFrame, TimeInterpolator<Orbit> orbitInterpolator, TimeInterpolator<AbsolutePVCoordinates> absPVAInterpolator, TimeInterpolator<TimeStampedDouble> massInterpolator, TimeInterpolator<Attitude> attitudeInterpolator, TimeInterpolator<TimeStampedDouble> additionalStateInterpolator) Constructor with: Default number of interpolation points of DEFAULT_INTERPOLATION_POINTS Default extrapolation threshold of DEFAULT_EXTRAPOLATION_THRESHOLD_SEC s
SpacecraftStateInterpolator(int interpolationPoints, double extrapolationThreshold, Frame outputFrame, TimeInterpolator<Orbit> orbitInterpolator, TimeInterpolator<AbsolutePVCoordinates> absPVAInterpolator, TimeInterpolator<TimeStampedDouble> massInterpolator, TimeInterpolator<Attitude> attitudeInterpolator, TimeInterpolator<TimeStampedDouble> additionalStateInterpolator) Constructor.