Uses of Class
org.orekit.attitudes.Attitude
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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 classManeuver
.org.orekit.propagation Propagation -
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Uses of Attitude in org.orekit.attitudes
Methods in org.orekit.attitudes that return Attitude Modifier and Type Method 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
AggregateBoundedAttitudeProvider. getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute the attitude corresponding to an orbital state.Attitude
AlignedAndConstrained. 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
CelestialBodyPointed. 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
FrameAlignedProvider. 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
LofOffset. 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
TabulatedLofOffset. 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
TorqueFree. 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
YawSteering. getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute the attitude corresponding to an orbital state.Attitude
GroundPointingAttitudeModifier. getBaseState(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute the base system state at given date, without modifications.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 Description FieldAttitude(Field<T> field, Attitude attitude)
Builds an instance for a regularAttitude
.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 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 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 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 Description Vector3D
PropulsionModel. getAcceleration(SpacecraftState s, Attitude maneuverAttitude, double[] parameters)
Get the acceleration of the spacecraft during maneuver and in maneuver frame.default Vector3D
ThrustPropulsionModel. 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 Description Attitude
SpacecraftState. getAttitude()
Get the attitude.Methods in org.orekit.propagation that return types with arguments of type Attitude Modifier and Type Method Description Optional<TimeInterpolator<Attitude>>
SpacecraftStateInterpolator. getAttitudeInterpolator()
Get attitude interpolator.Constructors in org.orekit.propagation with parameters of type Attitude Constructor Description 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, 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.SpacecraftState(Orbit orbit, Attitude attitude, DoubleArrayDictionary additional)
Build a spacecraft state from orbit, attitude and additional states.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, 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(AbsolutePVCoordinates absPva, Attitude attitude, DoubleArrayDictionary additional)
Build a spacecraft state from position-velocity-acceleration, attitude and additional states.
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