Uses of Class
org.orekit.propagation.FieldSpacecraftState

Packages that use FieldSpacecraftState

Package	Description
org.orekit.estimation.measurements.modifiers	This package provides measurement modifier.
org.orekit.forces	This package provides the interface for force models that will be used by the NumericalPropagator, as well as some classical spacecraft models for surface forces (spherical, box and solar array ...).
org.orekit.forces.drag	This package provides all drag-related forces.
org.orekit.forces.gravity	This package provides all gravity-related forces.
org.orekit.forces.inertia	This package provides inertial force model.
org.orekit.forces.maneuvers	This package provides models of simple maneuvers.
org.orekit.forces.maneuvers.propulsion	This package provides propulsion models intended to be used with class Maneuver.
org.orekit.forces.radiation	This package provides all radiation pressure related forces.
org.orekit.models.earth.ionosphere	This package provides models that simulate the impact of the ionosphere.
org.orekit.propagation	Propagation
org.orekit.propagation.analytical	Top level package for analytical propagators.
org.orekit.propagation.events	This package provides interfaces and classes dealing with events occurring during propagation.
org.orekit.propagation.events.handlers	This package provides an interface and classes dealing with events occurrence only.
org.orekit.propagation.integration	Utilities for integration-based propagators (both numerical and semi-analytical).
org.orekit.propagation.numerical	Top level package for numerical propagators.
org.orekit.propagation.numerical.cr3bp	Top level package for CR3BP Models used with a numerical propagator.
org.orekit.propagation.sampling	This package provides interfaces and classes dealing with step handling during propagation.
org.orekit.propagation.semianalytical.dsst	This package provides an implementation of the Draper Semi-analytical Satellite Theory (DSST).
org.orekit.propagation.semianalytical.dsst.forces	This package provides force models for Draper Semi-analytical Satellite Theory (DSST).

Uses of FieldSpacecraftState in org.orekit.estimation.measurements.modifiers

Methods in org.orekit.estimation.measurements.modifiers that return FieldSpacecraftState

Modifier and Type	Method and Description
FieldSpacecraftState<Gradient>	TroposphericGradientConverter.getState(DiscreteTroposphericModel tropoModel) Get the state with the number of parameters consistent with tropospheric model.
FieldSpacecraftState<DerivativeStructure>	TroposphericDSConverter.getState(DiscreteTroposphericModel tropoModel) Deprecated. Get the state with the number of parameters consistent with tropospheric model.
FieldSpacecraftState<DerivativeStructure>	IonosphericDSConverter.getState(IonosphericModel ionoModel) Deprecated. Get the state with the number of parameters consistent with ionospheric model.
FieldSpacecraftState<Gradient>	IonosphericGradientConverter.getState(IonosphericModel ionoModel) Get the state with the number of parameters consistent with ionospheric model.

Methods in org.orekit.estimation.measurements.modifiers with parameters of type FieldSpacecraftState

Modifier and Type	Method and Description
DerivativeStructure[]	TroposphericDSConverter.getParameters(FieldSpacecraftState<DerivativeStructure> state, DiscreteTroposphericModel tropoModel) Deprecated. Get the tropospheric model parameters.
DerivativeStructure[]	IonosphericDSConverter.getParameters(FieldSpacecraftState<DerivativeStructure> state, IonosphericModel ionoModel) Deprecated. Get the ionospheric model parameters.
Gradient[]	TroposphericGradientConverter.getParameters(FieldSpacecraftState<Gradient> state, DiscreteTroposphericModel tropoModel) Get the tropospheric model parameters.
Gradient[]	IonosphericGradientConverter.getParameters(FieldSpacecraftState<Gradient> state, IonosphericModel ionoModel) Get the ionospheric model parameters.
<T extends RealFieldElement<T>> T	RangeRateTroposphericDelayModifier.rangeRateErrorTroposphericModel(GroundStation station, FieldSpacecraftState<T> state, T[] parameters) Compute the measurement error due to Troposphere.

Uses of FieldSpacecraftState in org.orekit.forces

Methods in org.orekit.forces with parameters of type FieldSpacecraftState

Modifier and Type	Method and Description
<T extends RealFieldElement<T>> FieldVector3D<T>	ForceModel.acceleration(FieldSpacecraftState<T> s, T[] parameters) Compute acceleration.
<T extends RealFieldElement<T>> FieldVector3D<T>	AbstractParametricAcceleration.acceleration(FieldSpacecraftState<T> state, T[] parameters) Compute acceleration.
default <T extends RealFieldElement<T>> void	ForceModel.addContribution(FieldSpacecraftState<T> s, FieldTimeDerivativesEquations<T> adder) Compute the contribution of the force model to the perturbing acceleration.
protected <T extends RealFieldElement<T>> T	HarmonicParametricAcceleration.signedAmplitude(FieldSpacecraftState<T> state, T[] parameters) Compute the signed amplitude of the acceleration.
protected abstract <T extends RealFieldElement<T>> T	AbstractParametricAcceleration.signedAmplitude(FieldSpacecraftState<T> state, T[] parameters) Compute the signed amplitude of the acceleration.
protected <T extends RealFieldElement<T>> T	PolynomialParametricAcceleration.signedAmplitude(FieldSpacecraftState<T> state, T[] parameters) Compute the signed amplitude of the acceleration.

Uses of FieldSpacecraftState in org.orekit.forces.drag

Methods in org.orekit.forces.drag with parameters of type FieldSpacecraftState

Modifier and Type	Method and Description
<T extends RealFieldElement<T>> FieldVector3D<T>	TimeSpanDragForce.acceleration(FieldSpacecraftState<T> s, T[] parameters) Compute acceleration.
<T extends RealFieldElement<T>> FieldVector3D<T>	DragForce.acceleration(FieldSpacecraftState<T> s, T[] parameters) Compute acceleration.
protected <T extends RealFieldElement<T>> boolean	AbstractDragForceModel.isDSStateDerivative(FieldSpacecraftState<T> state) Check if a field state corresponds to derivatives with respect to state.
protected <T extends RealFieldElement<T>> boolean	AbstractDragForceModel.isGradientStateDerivative(FieldSpacecraftState<T> state) Check if a field state corresponds to derivatives with respect to state.

Uses of FieldSpacecraftState in org.orekit.forces.gravity

Methods in org.orekit.forces.gravity with parameters of type FieldSpacecraftState

Modifier and Type	Method and Description
<T extends RealFieldElement<T>> FieldVector3D<T>	HolmesFeatherstoneAttractionModel.acceleration(FieldSpacecraftState<T> s, T[] parameters) Compute acceleration.
<T extends RealFieldElement<T>> FieldVector3D<T>	SingleBodyRelativeAttraction.acceleration(FieldSpacecraftState<T> s, T[] parameters) Compute acceleration.
<T extends RealFieldElement<T>> FieldVector3D<T>	Relativity.acceleration(FieldSpacecraftState<T> s, T[] parameters) Compute acceleration.
<T extends RealFieldElement<T>> FieldVector3D<T>	ThirdBodyAttraction.acceleration(FieldSpacecraftState<T> s, T[] parameters) Compute acceleration.
<T extends RealFieldElement<T>> FieldVector3D<T>	NewtonianAttraction.acceleration(FieldSpacecraftState<T> s, T[] parameters) Compute acceleration.
<T extends RealFieldElement<T>> FieldVector3D<T>	SingleBodyAbsoluteAttraction.acceleration(FieldSpacecraftState<T> s, T[] parameters) Compute acceleration.
<T extends RealFieldElement<T>> FieldVector3D<T>	OceanTides.acceleration(FieldSpacecraftState<T> s, T[] parameters) Compute acceleration.
<T extends RealFieldElement<T>> FieldVector3D<T>	SolidTides.acceleration(FieldSpacecraftState<T> s, T[] parameters) Compute acceleration.
<T extends RealFieldElement<T>> void	NewtonianAttraction.addContribution(FieldSpacecraftState<T> s, FieldTimeDerivativesEquations<T> adder) Compute the contribution of the force model to the perturbing acceleration.

Uses of FieldSpacecraftState in org.orekit.forces.inertia

Methods in org.orekit.forces.inertia with parameters of type FieldSpacecraftState

Modifier and Type	Method and Description
<T extends RealFieldElement<T>> FieldVector3D<T>	InertialForces.acceleration(FieldSpacecraftState<T> s, T[] parameters) Compute acceleration.

Uses of FieldSpacecraftState in org.orekit.forces.maneuvers

Methods in org.orekit.forces.maneuvers with parameters of type FieldSpacecraftState

Modifier and Type	Method and Description
<T extends RealFieldElement<T>> FieldVector3D<T>	Maneuver.acceleration(FieldSpacecraftState<T> s, T[] parameters)
<T extends RealFieldElement<T>> void	Maneuver.addContribution(FieldSpacecraftState<T> s, FieldTimeDerivativesEquations<T> adder) Compute the contribution of the force model to the perturbing acceleration.
<T extends RealFieldElement<T>> boolean	ConstantThrustManeuver.isFiring(FieldSpacecraftState<T> s) Check if maneuvering is on.

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

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

Modifier and Type	Method and Description
default <T extends RealFieldElement<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 RealFieldElement<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 RealFieldElement<T>> T	ThrustPropulsionModel.getFlowRate(FieldSpacecraftState<T> s, T[] parameters) Get the flow rate (kg/s).
<T extends RealFieldElement<T>> T	AbstractConstantThrustPropulsionModel.getFlowRate(FieldSpacecraftState<T> s, T[] parameters) Get the flow rate (kg/s).
default <T extends RealFieldElement<T>> T	ThrustPropulsionModel.getMassDerivatives(FieldSpacecraftState<T> s, T[] parameters) Get the mass derivative (i.e.
<T extends RealFieldElement<T>> T	PropulsionModel.getMassDerivatives(FieldSpacecraftState<T> s, T[] parameters) Get the mass derivative (i.e.
<T extends RealFieldElement<T>> FieldVector3D<T>	ThrustPropulsionModel.getThrustVector(FieldSpacecraftState<T> s, T[] parameters) Get the thrust vector in spacecraft frame (N).
<T extends RealFieldElement<T>> FieldVector3D<T>	AbstractConstantThrustPropulsionModel.getThrustVector(FieldSpacecraftState<T> s, T[] parameters) Get the thrust vector in spacecraft frame (N).

Uses of FieldSpacecraftState in org.orekit.forces.radiation

Methods in org.orekit.forces.radiation with parameters of type FieldSpacecraftState

Modifier and Type	Method and Description
<T extends RealFieldElement<T>> FieldVector3D<T>	ECOM2.acceleration(FieldSpacecraftState<T> s, T[] parameters) Compute acceleration.
<T extends RealFieldElement<T>> FieldVector3D<T>	SolarRadiationPressure.acceleration(FieldSpacecraftState<T> s, T[] parameters) Compute acceleration.

Uses of FieldSpacecraftState in org.orekit.models.earth.ionosphere

Methods in org.orekit.models.earth.ionosphere with parameters of type FieldSpacecraftState

Modifier and Type	Method and Description
<T extends RealFieldElement<T>> T	EstimatedIonosphericModel.pathDelay(FieldSpacecraftState<T> state, TopocentricFrame baseFrame, double frequency, T[] parameters) Calculates the ionospheric path delay for the signal path from a ground station to a satellite.
<T extends RealFieldElement<T>> T	IonosphericModel.pathDelay(FieldSpacecraftState<T> state, TopocentricFrame baseFrame, double frequency, T[] parameters) Calculates the ionospheric path delay for the signal path from a ground station to a satellite.
<T extends RealFieldElement<T>> T	GlobalIonosphereMapModel.pathDelay(FieldSpacecraftState<T> state, TopocentricFrame baseFrame, double frequency, T[] parameters)
<T extends RealFieldElement<T>> T	KlobucharIonoModel.pathDelay(FieldSpacecraftState<T> state, TopocentricFrame baseFrame, double frequency, T[] parameters) Calculates the ionospheric path delay for the signal path from a ground station to a satellite.
<T extends RealFieldElement<T>> T	NeQuickModel.pathDelay(FieldSpacecraftState<T> state, TopocentricFrame baseFrame, double frequency, T[] parameters)

Uses of FieldSpacecraftState in org.orekit.propagation

Methods in org.orekit.propagation that return FieldSpacecraftState

Modifier and Type	Method and Description
FieldSpacecraftState<T>	FieldSpacecraftState.addAdditionalState(String name, T... value) Add an additional state.
FieldSpacecraftState<T>	FieldPropagator.getInitialState() Get the propagator initial state.
FieldSpacecraftState<T>	FieldAbstractPropagator.getInitialState() Get the propagator initial state.
FieldSpacecraftState<T>	FieldSpacecraftState.interpolate(FieldAbsoluteDate<T> date, Stream<FieldSpacecraftState<T>> sample) Get an interpolated instance.
FieldSpacecraftState<T>	FieldPropagator.propagate(FieldAbsoluteDate<T> target) Propagate towards a target date.
FieldSpacecraftState<T>	FieldAbstractPropagator.propagate(FieldAbsoluteDate<T> target) Propagate towards a target date.
FieldSpacecraftState<T>	FieldPropagator.propagate(FieldAbsoluteDate<T> start, FieldAbsoluteDate<T> target) Propagate from a start date towards a target date.
FieldSpacecraftState<T>	FieldSpacecraftState.shiftedBy(double dt) Get a time-shifted state.
FieldSpacecraftState<T>	FieldSpacecraftState.shiftedBy(T dt) Get a time-shifted state.
protected FieldSpacecraftState<T>	FieldAbstractPropagator.updateAdditionalStates(FieldSpacecraftState<T> original) Update state by adding all additional states.

Methods in org.orekit.propagation with parameters of type FieldSpacecraftState

Modifier and Type	Method and Description
void	FieldSpacecraftState.ensureCompatibleAdditionalStates(FieldSpacecraftState<T> state) Check if two instances have the same set of additional states available.
T[]	FieldAdditionalStateProvider.getAdditionalState(FieldSpacecraftState<T> state) Get the additional state.
void	FieldPropagator.resetInitialState(FieldSpacecraftState<T> state) Reset the propagator initial state.
void	FieldAbstractPropagator.resetInitialState(FieldSpacecraftState<T> state) Reset the propagator initial state.
protected void	FieldAbstractPropagator.stateChanged(FieldSpacecraftState<T> state) Notify about a state change.
protected FieldSpacecraftState<T>	FieldAbstractPropagator.updateAdditionalStates(FieldSpacecraftState<T> original) Update state by adding all additional states.

Method parameters in org.orekit.propagation with type arguments of type FieldSpacecraftState

Modifier and Type	Method and Description
FieldSpacecraftState<T>	FieldSpacecraftState.interpolate(FieldAbsoluteDate<T> date, Stream<FieldSpacecraftState<T>> sample) Get an interpolated instance.

Uses of FieldSpacecraftState in org.orekit.propagation.analytical

Methods in org.orekit.propagation.analytical that return FieldSpacecraftState

Modifier and Type	Method and Description
protected FieldSpacecraftState<T>	FieldAbstractAnalyticalPropagator.acceptStep(org.orekit.propagation.analytical.FieldAbstractAnalyticalPropagator.FieldBasicStepInterpolator interpolator, FieldAbsoluteDate<T> target, double epsilon) Accept a step, triggering events and step handlers.
protected FieldSpacecraftState<T>	FieldAbstractAnalyticalPropagator.basicPropagate(FieldAbsoluteDate<T> date) Propagate an orbit without any fancy features.
FieldSpacecraftState<T>	FieldAbstractAnalyticalPropagator.propagate(FieldAbsoluteDate<T> start, FieldAbsoluteDate<T> target) Propagate from a start date towards a target date.

Methods in org.orekit.propagation.analytical with parameters of type FieldSpacecraftState

Modifier and Type	Method and Description
void	FieldKeplerianPropagator.resetInitialState(FieldSpacecraftState<T> state) Reset the propagator initial state.
void	FieldEcksteinHechlerPropagator.resetInitialState(FieldSpacecraftState<T> state) Reset the propagator initial state.
void	FieldEcksteinHechlerPropagator.resetInitialState(FieldSpacecraftState<T> state, PropagationType stateType) Reset the propagator initial state.
protected void	FieldKeplerianPropagator.resetIntermediateState(FieldSpacecraftState<T> state, boolean forward) Reset an intermediate state.
protected abstract void	FieldAbstractAnalyticalPropagator.resetIntermediateState(FieldSpacecraftState<T> state, boolean forward) Reset an intermediate state.
protected void	FieldEcksteinHechlerPropagator.resetIntermediateState(FieldSpacecraftState<T> state, boolean forward) Reset an intermediate state.

Uses of FieldSpacecraftState in org.orekit.propagation.events

Methods in org.orekit.propagation.events that return FieldSpacecraftState

Modifier and Type	Method and Description
FieldSpacecraftState<T>	FieldEventState.EventOccurrence.getNewState() Get the new state for a reset action.
FieldSpacecraftState<T>	FieldEventsLogger.FieldLoggedEvent.getState() Get the triggering state.
FieldSpacecraftState<T>	FieldAbstractDetector.resetState(FieldSpacecraftState<T> oldState) Reset the state prior to continue propagation.
default FieldSpacecraftState<T>	FieldEventDetector.resetState(FieldSpacecraftState<T> oldState) Reset the state prior to continue propagation.

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

Modifier and Type	Method and Description
Function<FieldSpacecraftState<T>,T>	FieldFunctionalDetector.getFunction() Get the switching function.

Methods in org.orekit.propagation.events with parameters of type FieldSpacecraftState

Modifier and Type	Method and Description
FieldEventState.EventOccurrence<T>	FieldEventState.doEvent(FieldSpacecraftState<T> state) Notify the user's listener of the event.
Action	FieldAbstractDetector.eventOccurred(FieldSpacecraftState<T> s, boolean increasing) Handle the event.
Action	FieldEventDetector.eventOccurred(FieldSpacecraftState<T> s, boolean increasing) Handle the event.
T	FieldEclipseDetector.g(FieldSpacecraftState<T> s) Compute the value of the switching function.
T	FieldNodeDetector.g(FieldSpacecraftState<T> s) Compute the value of the switching function.
T	FieldElevationDetector.g(FieldSpacecraftState<T> s) Compute the value of the switching function.
T	FieldLatitudeCrossingDetector.g(FieldSpacecraftState<T> s) Compute the value of the detection function.
abstract T	FieldAbstractDetector.g(FieldSpacecraftState<T> s) Compute the value of the switching function.
T	FieldDateDetector.g(FieldSpacecraftState<T> s) Compute the value of the switching function.
T	FieldFunctionalDetector.g(FieldSpacecraftState<T> s)
T	FieldAltitudeDetector.g(FieldSpacecraftState<T> s) Compute the value of the switching function.
T	FieldEventDetector.g(FieldSpacecraftState<T> s) Compute the value of the switching function.
T	FieldApsideDetector.g(FieldSpacecraftState<T> s) Compute the value of the switching function.
void	FieldEventState.init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t) Initialize event handler at the start of a propagation.
void	FieldAbstractDetector.init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t) Initialize event handler at the start of a propagation.
default void	FieldEventDetector.init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t) Initialize event handler at the start of a propagation.
FieldSpacecraftState<T>	FieldAbstractDetector.resetState(FieldSpacecraftState<T> oldState) Reset the state prior to continue propagation.
default FieldSpacecraftState<T>	FieldEventDetector.resetState(FieldSpacecraftState<T> oldState) Reset the state prior to continue propagation.
boolean	FieldEventState.tryAdvance(FieldSpacecraftState<T> state, FieldOrekitStepInterpolator<T> interpolator) Try to accept the current history up to the given time.

Method parameters in org.orekit.propagation.events with type arguments of type FieldSpacecraftState

Modifier and Type	Method and Description
FieldFunctionalDetector<T>	FieldFunctionalDetector.withFunction(Function<FieldSpacecraftState<T>,T> newGFunction) Create a new event detector with a new g function, keeping all other attributes the same.

Uses of FieldSpacecraftState in org.orekit.propagation.events.handlers

Methods in org.orekit.propagation.events.handlers that return FieldSpacecraftState

Modifier and Type	Method and Description
FieldSpacecraftState<F>	FieldRecordAndContinue.Event.getState() Get the spacecraft's state at the event.
default FieldSpacecraftState<T>	FieldEventHandler.resetState(KK detector, FieldSpacecraftState<T> oldState) Reset the state prior to continue propagation.
FieldSpacecraftState<E>	FieldRecordAndContinue.resetState(T detector, FieldSpacecraftState<E> oldState)

Methods in org.orekit.propagation.events.handlers with parameters of type FieldSpacecraftState

Modifier and Type	Method and Description
Action	FieldRecordAndContinue.eventOccurred(FieldSpacecraftState<E> s, T detector, boolean increasing)
Action	FieldStopOnDecreasing.eventOccurred(FieldSpacecraftState<T> s, KK detector, boolean increasing) Handle a detection event and choose what to do next.
Action	FieldStopOnEvent.eventOccurred(FieldSpacecraftState<T> s, KK detector, boolean increasing) Specific implementation of the eventOccurred interface.
Action	FieldContinueOnEvent.eventOccurred(FieldSpacecraftState<T> s, KK detector, boolean increasing) Specific implementation of the eventOccurred interface.
Action	FieldStopOnIncreasing.eventOccurred(FieldSpacecraftState<T> s, KK detector, boolean increasing) Handle a detection event and choose what to do next.
Action	FieldEventHandler.eventOccurred(FieldSpacecraftState<T> s, KK detector, boolean increasing) eventOccurred method mirrors the same interface method as in EventDetector and its subclasses, but with an additional parameter that allows the calling method to pass in an object from the detector which would have potential additional data to allow the implementing class to determine the correct return state.
default void	FieldEventHandler.init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target) Initialize event handler at the start of a propagation.
default FieldSpacecraftState<T>	FieldEventHandler.resetState(KK detector, FieldSpacecraftState<T> oldState) Reset the state prior to continue propagation.
FieldSpacecraftState<E>	FieldRecordAndContinue.resetState(T detector, FieldSpacecraftState<E> oldState)

Uses of FieldSpacecraftState in org.orekit.propagation.integration

Methods in org.orekit.propagation.integration that return FieldSpacecraftState

Modifier and Type	Method and Description
protected FieldSpacecraftState<T>	FieldIntegratedEphemeris.basicPropagate(FieldAbsoluteDate<T> date) Propagate an orbit without any fancy features.
protected FieldSpacecraftState<T>	FieldAbstractIntegratedPropagator.getInitialIntegrationState() Get the initial state for integration.
FieldSpacecraftState<T>	FieldIntegratedEphemeris.getInitialState() Get the propagator initial state.
abstract FieldSpacecraftState<T>	FieldStateMapper.mapArrayToState(FieldAbsoluteDate<T> date, T[] y, T[] yDot, PropagationType type) Map the raw double components to a spacecraft state.
FieldSpacecraftState<T>	FieldStateMapper.mapArrayToState(T t, T[] y, T[] yDot, PropagationType type) Map the raw double components to a spacecraft state.
FieldSpacecraftState<T>	FieldAbstractIntegratedPropagator.propagate(FieldAbsoluteDate<T> target) Propagate towards a target date.
protected FieldSpacecraftState<T>	FieldAbstractIntegratedPropagator.propagate(FieldAbsoluteDate<T> tEnd, boolean activateHandlers) Propagation with or without event detection.
FieldSpacecraftState<T>	FieldAbstractIntegratedPropagator.propagate(FieldAbsoluteDate<T> tStart, FieldAbsoluteDate<T> tEnd) Propagate from a start date towards a target date.

Methods in org.orekit.propagation.integration with parameters of type FieldSpacecraftState

Modifier and Type	Method and Description
protected void	FieldAbstractIntegratedPropagator.beforeIntegration(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> tEnd) Method called just before integration.
T[]	FieldAbstractIntegratedPropagator.MainStateEquations.computeDerivatives(FieldSpacecraftState<T> state) Compute differential equations for main state.
T[]	FieldAdditionalEquations.computeDerivatives(FieldSpacecraftState<T> s, T[] pDot) Compute the derivatives related to the additional state parameters.
void	FieldAbstractIntegratedPropagator.MainStateEquations.init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target) Initialize the equations at the start of propagation.
default void	FieldAdditionalEquations.init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target) Initialize the equations at the start of propagation.
abstract void	FieldStateMapper.mapStateToArray(FieldSpacecraftState<T> state, T[] y, T[] yDot) Map a spacecraft state to raw double components.
void	FieldIntegratedEphemeris.resetInitialState(FieldSpacecraftState<T> state) Reset the propagator initial state.
protected void	FieldIntegratedEphemeris.resetIntermediateState(FieldSpacecraftState<T> state, boolean forward) Reset an intermediate state.

Uses of FieldSpacecraftState in org.orekit.propagation.numerical

Methods in org.orekit.propagation.numerical with parameters of type FieldSpacecraftState

Modifier and Type	Method and Description
void	FieldNumericalPropagator.resetInitialState(FieldSpacecraftState<T> state) Reset the propagator initial state.
void	FieldNumericalPropagator.setInitialState(FieldSpacecraftState<T> initialState) Set the initial state.

Uses of FieldSpacecraftState in org.orekit.propagation.numerical.cr3bp

Methods in org.orekit.propagation.numerical.cr3bp with parameters of type FieldSpacecraftState

Modifier and Type	Method and Description
<T extends RealFieldElement<T>> FieldVector3D<T>	CR3BPForceModel.acceleration(FieldSpacecraftState<T> s, T[] parameters) Compute acceleration.
<T extends RealFieldElement<T>> FieldDerivativeStructure<T>	CR3BPForceModel.getPotential(FieldSpacecraftState<T> s) Calculate spacecraft potential.

Uses of FieldSpacecraftState in org.orekit.propagation.sampling

Methods in org.orekit.propagation.sampling that return FieldSpacecraftState

Modifier and Type	Method and Description
FieldSpacecraftState<T>	FieldOrekitStepInterpolator.getCurrentState() Get the state at previous grid point date.
FieldSpacecraftState<T>	FieldOrekitStepInterpolator.getInterpolatedState(FieldAbsoluteDate<T> date) Get the state at interpolated date.
FieldSpacecraftState<T>	FieldOrekitStepInterpolator.getPreviousState() Get the state at previous grid point date.

Methods in org.orekit.propagation.sampling with parameters of type FieldSpacecraftState

Modifier and Type	Method and Description
void	FieldOrekitFixedStepHandlerMultiplexer.handleStep(FieldSpacecraftState<T> currentState, boolean isLast) Handle the current step.
void	FieldOrekitFixedStepHandler.handleStep(FieldSpacecraftState<T> currentState, boolean isLast) Handle the current step.
void	FieldOrekitStepHandlerMultiplexer.init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t) Initialize step handler at the start of a propagation.
void	FieldOrekitStepHandler.init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t) Initialize step handler at the start of a propagation.
void	FieldOrekitStepNormalizer.init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t) Initialize step handler at the start of a propagation.
void	FieldOrekitFixedStepHandlerMultiplexer.init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t, T step) Initialize step handler at the start of a propagation.
default void	FieldOrekitFixedStepHandler.init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t, T step) Initialize step handler at the start of a propagation.

Uses of FieldSpacecraftState in org.orekit.propagation.semianalytical.dsst

Methods in org.orekit.propagation.semianalytical.dsst that return FieldSpacecraftState

Modifier and Type	Method and Description
FieldSpacecraftState<T>	FieldDSSTPropagator.computeMeanState(FieldSpacecraftState<T> osculating, AttitudeProvider attitudeProvider, Collection<DSSTForceModel> forceModel) Conversion from osculating to mean orbit.
FieldSpacecraftState<T>	FieldDSSTPropagator.computeMeanState(FieldSpacecraftState<T> osculating, AttitudeProvider attitudeProvider, Collection<DSSTForceModel> forceModel, double epsilon, int maxIterations) Conversion from osculating to mean orbit.
FieldSpacecraftState<T>	FieldDSSTPropagator.computeOsculatingState(FieldSpacecraftState<T> mean, AttitudeProvider attitudeProvider, Collection<DSSTForceModel> forces) Conversion from mean to osculating orbit.
protected FieldSpacecraftState<T>	FieldDSSTPropagator.getInitialIntegrationState() Get the initial state for integration.

Methods in org.orekit.propagation.semianalytical.dsst with parameters of type FieldSpacecraftState

Modifier and Type	Method and Description
protected void	FieldDSSTPropagator.beforeIntegration(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> tEnd) Method called just before integration.
FieldSpacecraftState<T>	FieldDSSTPropagator.computeMeanState(FieldSpacecraftState<T> osculating, AttitudeProvider attitudeProvider, Collection<DSSTForceModel> forceModel) Conversion from osculating to mean orbit.
FieldSpacecraftState<T>	FieldDSSTPropagator.computeMeanState(FieldSpacecraftState<T> osculating, AttitudeProvider attitudeProvider, Collection<DSSTForceModel> forceModel, double epsilon, int maxIterations) Conversion from osculating to mean orbit.
FieldSpacecraftState<T>	FieldDSSTPropagator.computeOsculatingState(FieldSpacecraftState<T> mean, AttitudeProvider attitudeProvider, Collection<DSSTForceModel> forces) Conversion from mean to osculating orbit.
void	FieldDSSTPropagator.resetInitialState(FieldSpacecraftState<T> state) Reset the initial state.
void	FieldDSSTPropagator.setInitialState(FieldSpacecraftState<T> initialState) Set the initial state with osculating orbital elements.
void	FieldDSSTPropagator.setInitialState(FieldSpacecraftState<T> initialState, PropagationType stateType) Set the initial state.

Uses of FieldSpacecraftState in org.orekit.propagation.semianalytical.dsst.forces

Methods in org.orekit.propagation.semianalytical.dsst.forces with parameters of type FieldSpacecraftState

Modifier and Type	Method and Description
protected abstract <T extends RealFieldElement<T>> T[]	AbstractGaussianContribution.getLLimits(FieldSpacecraftState<T> state, FieldAuxiliaryElements<T> auxiliaryElements) Compute the limits in L, the true longitude, for integration.
protected <T extends RealFieldElement<T>> T[]	DSSTAtmosphericDrag.getLLimits(FieldSpacecraftState<T> state, FieldAuxiliaryElements<T> auxiliaryElements) Compute the limits in L, the true longitude, for integration.
protected <T extends RealFieldElement<T>> T[]	DSSTSolarRadiationPressure.getLLimits(FieldSpacecraftState<T> state, FieldAuxiliaryElements<T> auxiliaryElements) Compute the limits in L, the true longitude, for integration.
<T extends RealFieldElement<T>> T[]	DSSTZonal.getMeanElementRate(FieldSpacecraftState<T> spacecraftState, FieldAuxiliaryElements<T> auxiliaryElements, T[] parameters) Computes the mean equinoctial elements rates dai / dt.
<T extends RealFieldElement<T>> T[]	AbstractGaussianContribution.getMeanElementRate(FieldSpacecraftState<T> state, FieldAuxiliaryElements<T> auxiliaryElements, T[] parameters) Computes the mean equinoctial elements rates dai / dt.
<T extends RealFieldElement<T>> T[]	DSSTNewtonianAttraction.getMeanElementRate(FieldSpacecraftState<T> state, FieldAuxiliaryElements<T> auxiliaryElements, T[] parameters) Computes the mean equinoctial elements rates dai / dt.
<T extends RealFieldElement<T>> T[]	DSSTForceModel.getMeanElementRate(FieldSpacecraftState<T> state, FieldAuxiliaryElements<T> auxiliaryElements, T[] parameters) Computes the mean equinoctial elements rates dai / dt.
<T extends RealFieldElement<T>> T[]	DSSTTesseral.getMeanElementRate(FieldSpacecraftState<T> spacecraftState, FieldAuxiliaryElements<T> auxiliaryElements, T[] parameters) Computes the mean equinoctial elements rates dai / dt.
<T extends RealFieldElement<T>> T[]	DSSTThirdBody.getMeanElementRate(FieldSpacecraftState<T> currentState, FieldAuxiliaryElements<T> auxiliaryElements, T[] parameters) Computes the mean equinoctial elements rates dai / dt.
<T extends RealFieldElement<T>> void	DSSTZonal.updateShortPeriodTerms(T[] parameters, FieldSpacecraftState<T>... meanStates) Update the short period terms.
<T extends RealFieldElement<T>> void	AbstractGaussianContribution.updateShortPeriodTerms(T[] parameters, FieldSpacecraftState<T>... meanStates) Update the short period terms.
<T extends RealFieldElement<T>> void	DSSTNewtonianAttraction.updateShortPeriodTerms(T[] parameters, FieldSpacecraftState<T>... meanStates) Update the short period terms.
<T extends RealFieldElement<T>> void	DSSTForceModel.updateShortPeriodTerms(T[] parameters, FieldSpacecraftState<T>... meanStates) Update the short period terms.
<T extends RealFieldElement<T>> void	DSSTTesseral.updateShortPeriodTerms(T[] parameters, FieldSpacecraftState<T>... meanStates) Update the short period terms.
<T extends RealFieldElement<T>> void	DSSTThirdBody.updateShortPeriodTerms(T[] parameters, FieldSpacecraftState<T>... meanStates) Update the short period terms.