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 classManeuver
.org.orekit.propagation Propagation -
-
Uses of FieldAttitude in org.orekit.attitudes
Methods in org.orekit.attitudes that return FieldAttitude Modifier and Type Method 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>AggregateBoundedAttitudeProvider. 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>AttitudesSequence. 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>FixedRate. getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the attitude corresponding to an orbital state.<T extends CalculusFieldElement<T>>
FieldAttitude<T>FrameAlignedProvider. 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>LofOffset. 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>SpinStabilized. 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>TabulatedProvider. getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the attitude corresponding to an orbital state.<T extends CalculusFieldElement<T>>
FieldAttitude<T>TorqueFree. getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the attitude corresponding to an orbital state.<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>YawSteering. getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the attitude corresponding to an orbital state.<T extends CalculusFieldElement<T>>
FieldAttitude<T>GroundPointingAttitudeModifier. getBaseState(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the base system state at given date, without modifications.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 Description <T extends 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 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 Description <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.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. -
Uses of FieldAttitude in org.orekit.propagation
Methods in org.orekit.propagation that return FieldAttitude Modifier and Type Method 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 Description Optional<FieldTimeInterpolator<FieldAttitude<KK>,KK>>
FieldSpacecraftStateInterpolator. getAttitudeInterpolator()
Get attitude interpolator.Constructors in org.orekit.propagation with parameters of type FieldAttitude Constructor Description 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.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.
-