Uses of Class
org.orekit.attitudes.Attitude
Packages that use Attitude
Package
Description
This package provides classes to represent simple attitudes.
This package contains class managing CCSDS Attitude Data Message.
This package contains class managing CCSDS Attitude Parameter Message.
This package provides propulsion models intended to be used with class
Maneuver. Propagation
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Uses of Attitude in org.orekit.attitudes
Methods in org.orekit.attitudes that return AttitudeModifier and TypeMethodDescriptionAttitudeBuilder.build(Frame frame, PVCoordinatesProvider pvProv, TimeStampedAngularCoordinates rawAttitude) Build a filtered attitude.FixedFrameBuilder.build(Frame frame, PVCoordinatesProvider pvProv, TimeStampedAngularCoordinates rawAttitude) Build a filtered attitude.AggregateBoundedAttitudeProvider.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.AlignedAndConstrained.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.AttitudeProvider.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.default AttitudeAttitudeProviderModifier.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.CelestialBodyPointed.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.FixedRate.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.FrameAlignedProvider.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.GroundPointing.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.LofOffset.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.LofOffsetPointing.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.SpinStabilized.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.TabulatedLofOffset.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.TabulatedProvider.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.TorqueFree.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.YawCompensation.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.YawSteering.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.GroundPointingAttitudeModifier.getBaseState(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the base system state at given date, without modifications.TorqueFree.getInitialAttitude()Get the initial attitude.FixedRate.getReferenceAttitude()Get the reference attitude.protected AttitudeAttitudeInterpolator.interpolate(AbstractTimeInterpolator<Attitude>.InterpolationData interpolationData) Interpolate instance from given interpolation data.Attitude.shiftedBy(double dt) Get a time-shifted attitude.Attitude.shiftedBy(TimeOffset dt) Get a time-shifted attitude.FieldAttitude.toAttitude()Converts to an Attitude instance.Attitude.withReferenceFrame(Frame newReferenceFrame) Get a similar attitude with a specific reference frame.Constructors in org.orekit.attitudes with parameters of type AttitudeModifierConstructorDescriptionFieldAttitude(Field<T> field, Attitude attitude) Builds an instance for a regularAttitude.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 AttitudeModifier and TypeMethodDescriptionAttitudeEndpoints.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 AttitudeModifier and TypeMethodDescriptionApm.getAttitude(Frame frame, PVCoordinatesProvider pvProvider) Get the 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 with parameters of type AttitudeModifier and TypeMethodDescriptionPropulsionModel.getAcceleration(SpacecraftState s, Attitude maneuverAttitude, double[] parameters) Get the acceleration of the spacecraft during maneuver and in maneuver frame.default Vector3DThrustPropulsionModel.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 AttitudeMethods in org.orekit.propagation that return types with arguments of type AttitudeModifier and TypeMethodDescriptionSpacecraftStateInterpolator.getAttitudeInterpolator()Get attitude interpolator.Methods in org.orekit.propagation with parameters of type AttitudeModifier and TypeMethodDescriptionSpacecraftState.withAttitude(Attitude newAttitude) Create a new instance with input attitude.Constructors in org.orekit.propagation with parameters of type AttitudeModifierConstructorDescriptionSpacecraftState(Orbit orbit, Attitude attitude) Build a spacecraft state from orbit and attitude.SpacecraftState(Orbit orbit, Attitude attitude, double mass, DataDictionary additional, DoubleArrayDictionary additionalDot) Build a spacecraft state from orbit, attitude, mass, additional states and derivatives.SpacecraftState(AbsolutePVCoordinates absPva, Attitude attitude) Build a spacecraft state from position-velocity-acceleration and attitude.SpacecraftState(AbsolutePVCoordinates absPva, Attitude attitude, double mass, DataDictionary additional, DoubleArrayDictionary additionalDot) Build a spacecraft state from position-velocity-acceleration, attitude, mass and additional states and derivatives.