Uses of Class
org.orekit.attitudes.FieldAttitude
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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.gnss.attitude This package provides classes related to navigation satellites attitude modeling.org.orekit.propagation Propagation -
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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>PythonAttitudeBuilder. build(Frame frame, FieldPVCoordinatesProvider<T> pvProv, TimeStampedFieldAngularCoordinates<T> rawAttitude)
<T extends CalculusFieldElement<T>>
FieldAttitude<T>PythonAttitudeBuilder. build_FFT(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>GroundPointing. getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the attitude corresponding to an orbital state.<T extends CalculusFieldElement<T>>
FieldAttitude<T>InertialProvider. 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>PythonAttitudeProvider. getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the attitude corresponding to an orbital state.<T extends CalculusFieldElement<T>>
FieldAttitude<T>PythonAttitudeProviderModifier. getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the attitude corresponding to an orbital state.<T extends CalculusFieldElement<T>>
FieldAttitude<T>PythonBoundedAttitudeProvider. 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>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>PythonAttitudeProvider. getAttitude_FFF(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the attitude corresponding to an orbital state.<T extends CalculusFieldElement<T>>
FieldAttitude<T>PythonAttitudeProviderModifier. getAttitude_FFF(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the attitude corresponding to an orbital state.<T extends CalculusFieldElement<T>>
FieldAttitude<T>PythonBoundedAttitudeProvider. getAttitude_FFF(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the attitude corresponding to an orbital state.<T extends CalculusFieldElement<T>>
FieldAttitude<T>YawCompensation. getBaseState(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the base system state at given date, without compensation.<T extends CalculusFieldElement<T>>
FieldAttitude<T>YawSteering. getBaseState(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the base system state at given date, without compensation.FieldAttitude<T>
FieldAttitude. interpolate(FieldAbsoluteDate<T> interpolationDate, Stream<FieldAttitude<T>> sample)
Get an interpolated instance.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.Method parameters in org.orekit.attitudes with type arguments of type FieldAttitude Modifier and Type Method Description FieldAttitude<T>
FieldAttitude. interpolate(FieldAbsoluteDate<T> interpolationDate, Stream<FieldAttitude<T>> sample)
Get an interpolated instance. -
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>AttitudeEndoints. 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.<T extends CalculusFieldElement<T>>
FieldVector3D<T>PythonPropulsionModel. 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.<T extends CalculusFieldElement<T>>
FieldVector3D<T>PythonPropulsionModel. getAcceleration_FFT(FieldSpacecraftState<T> s, FieldAttitude<T> maneuverAttitude, T[] parameters)
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Uses of FieldAttitude in org.orekit.gnss.attitude
Methods in org.orekit.gnss.attitude that return FieldAttitude Modifier and Type Method Description <T extends CalculusFieldElement<T>>
FieldAttitude<T>PythonGNSSAttitudeProvider. getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the attitude corresponding to an orbital state.<T extends CalculusFieldElement<T>>
FieldAttitude<T>PythonGNSSAttitudeProvider. getAttitude_FFF(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the attitude corresponding to an orbital state. -
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.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, Map<String,T[]> additional)
Deprecated.as of 11.1, replaced byFieldSpacecraftState(FieldOrbit, FieldAttitude, FieldArrayDictionary)
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, Map<String,T[]> additional)
Deprecated.as of 11.1, replaced byFieldSpacecraftState(FieldOrbit, FieldAttitude, CalculusFieldElement, FieldArrayDictionary)
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, Map<String,T[]> additional)
Deprecated.as of 11.1, replaced byFieldSpacecraftState(FieldAbsolutePVCoordinates, FieldAttitude, FieldArrayDictionary)
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, Map<String,T[]> additional)
Deprecated.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.
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