Uses of Class
org.orekit.propagation.FieldSpacecraftState

Packages that use FieldSpacecraftState

Package	Description
org.orekit.estimation.measurements.modifiers
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.maneuvers	This package provides models of simple maneuvers.
org.orekit.forces.radiation	This package provides all radiation pressure related forces.
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.sampling	This package provides interfaces and classes dealing with step handling during propagation.

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

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

Modifier and Type	Method	Description
FieldSpacecraftState<org.hipparchus.analysis.differentiation.DerivativeStructure>	TroposphericDSConverter.getState(DiscreteTroposphericModel tropoModel)	Get the state with the number of parameters consistent with tropospheric model.

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

Modifier and Type	Method	Description
org.hipparchus.analysis.differentiation.DerivativeStructure[]	TroposphericDSConverter.getParameters(FieldSpacecraftState<org.hipparchus.analysis.differentiation.DerivativeStructure> state, DiscreteTroposphericModel tropoModel)	Get the tropospheric model parameters.
<T extends org.hipparchus.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	Description
<T extends org.hipparchus.RealFieldElement<T>> org.hipparchus.geometry.euclidean.threed.FieldVector3D<T>	AbstractParametricAcceleration.acceleration(FieldSpacecraftState<T> state, T[] parameters)	Compute acceleration.
<T extends org.hipparchus.RealFieldElement<T>> org.hipparchus.geometry.euclidean.threed.FieldVector3D<T>	ForceModel.acceleration(FieldSpacecraftState<T> s, T[] parameters)	Compute acceleration.
default <T extends org.hipparchus.RealFieldElement<T>> void	ForceModel.addContribution(FieldSpacecraftState<T> s, FieldTimeDerivativesEquations<T> adder)	Compute the contribution of the force model to the perturbing acceleration.
protected abstract <T extends org.hipparchus.RealFieldElement<T>> T	AbstractParametricAcceleration.signedAmplitude(FieldSpacecraftState<T> state, T[] parameters)	Compute the signed amplitude of the acceleration.
protected <T extends org.hipparchus.RealFieldElement<T>> T	HarmonicParametricAcceleration.signedAmplitude(FieldSpacecraftState<T> state, T[] parameters)	Compute the signed amplitude of the acceleration.
protected <T extends org.hipparchus.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	Description
<T extends org.hipparchus.RealFieldElement<T>> org.hipparchus.geometry.euclidean.threed.FieldVector3D<T>	DragForce.acceleration(FieldSpacecraftState<T> s, T[] parameters)	Compute acceleration.

Uses of FieldSpacecraftState in org.orekit.forces.gravity

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

Modifier and Type	Method	Description
<T extends org.hipparchus.RealFieldElement<T>> org.hipparchus.geometry.euclidean.threed.FieldVector3D<T>	HolmesFeatherstoneAttractionModel.acceleration(FieldSpacecraftState<T> s, T[] parameters)	Compute acceleration.
<T extends org.hipparchus.RealFieldElement<T>> org.hipparchus.geometry.euclidean.threed.FieldVector3D<T>	NewtonianAttraction.acceleration(FieldSpacecraftState<T> s, T[] parameters)	Compute acceleration.
<T extends org.hipparchus.RealFieldElement<T>> org.hipparchus.geometry.euclidean.threed.FieldVector3D<T>	OceanTides.acceleration(FieldSpacecraftState<T> s, T[] parameters)	Compute acceleration.
<T extends org.hipparchus.RealFieldElement<T>> org.hipparchus.geometry.euclidean.threed.FieldVector3D<T>	Relativity.acceleration(FieldSpacecraftState<T> s, T[] parameters)	Compute acceleration.
<T extends org.hipparchus.RealFieldElement<T>> org.hipparchus.geometry.euclidean.threed.FieldVector3D<T>	SolidTides.acceleration(FieldSpacecraftState<T> s, T[] parameters)	Compute acceleration.
<T extends org.hipparchus.RealFieldElement<T>> org.hipparchus.geometry.euclidean.threed.FieldVector3D<T>	ThirdBodyAttraction.acceleration(FieldSpacecraftState<T> s, T[] parameters)	Compute acceleration.
<T extends org.hipparchus.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.maneuvers

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

Modifier and Type	Method	Description
<T extends org.hipparchus.RealFieldElement<T>> org.hipparchus.geometry.euclidean.threed.FieldVector3D<T>	ConstantThrustManeuver.acceleration(FieldSpacecraftState<T> s, T[] parameters)	Compute acceleration.
<T extends org.hipparchus.RealFieldElement<T>> void	ConstantThrustManeuver.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.radiation

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

Modifier and Type	Method	Description
<T extends org.hipparchus.RealFieldElement<T>> org.hipparchus.geometry.euclidean.threed.FieldVector3D<T>	SolarRadiationPressure.acceleration(FieldSpacecraftState<T> s, T[] parameters)	Compute acceleration.

Uses of FieldSpacecraftState in org.orekit.propagation

Methods in org.orekit.propagation that return FieldSpacecraftState

Modifier and Type	Method	Description
FieldSpacecraftState<T>	FieldSpacecraftState.addAdditionalState(String name, T... value)	Add an additional state.
FieldSpacecraftState<T>	FieldAbstractPropagator.getInitialState()	Get the propagator initial state.
FieldSpacecraftState<T>	FieldPropagator.getInitialState()	Get the propagator initial state.
FieldSpacecraftState<T>	FieldSpacecraftState.interpolate(FieldAbsoluteDate<T> date, Stream<FieldSpacecraftState<T>> sample)	Get an interpolated instance.
FieldSpacecraftState<T>	FieldAbstractPropagator.propagate(FieldAbsoluteDate<T> target)	Propagate towards a target date.
FieldSpacecraftState<T>	FieldPropagator.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	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	FieldAbstractPropagator.resetInitialState(FieldSpacecraftState<T> state)	Reset the propagator initial state.
void	FieldPropagator.resetInitialState(FieldSpacecraftState<T> state)	Reset the propagator initial state.
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	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	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	Description
void	FieldEcksteinHechlerPropagator.resetInitialState(FieldSpacecraftState<T> state)	Reset the propagator initial state.
void	FieldKeplerianPropagator.resetInitialState(FieldSpacecraftState<T> state)	Reset the propagator initial 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.
protected void	FieldKeplerianPropagator.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	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 with parameters of type FieldSpacecraftState

Modifier and Type	Method	Description
FieldEventState.EventOccurrence<T>	FieldEventState.doEvent(FieldSpacecraftState<T> state)	Notify the user's listener of the event.
FieldEventHandler.Action	FieldAbstractDetector.eventOccurred(FieldSpacecraftState<T> s, boolean increasing)	Handle the event.
FieldEventHandler.Action	FieldEventDetector.eventOccurred(FieldSpacecraftState<T> s, boolean increasing)	Handle the event.
abstract T	FieldAbstractDetector.g(FieldSpacecraftState<T> s)	Compute the value of the switching function.
T	FieldAltitudeDetector.g(FieldSpacecraftState<T> s)	Compute the value of the switching function.
T	FieldApsideDetector.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	FieldEclipseDetector.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	FieldEventDetector.g(FieldSpacecraftState<T> s)	Compute the value of the switching function.
T	FieldNodeDetector.g(FieldSpacecraftState<T> s)	Compute the value of the switching function.
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.
void	FieldEventState.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.

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

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

Modifier and Type	Method	Description
default FieldSpacecraftState<T>	FieldEventHandler.resetState(KK detector, FieldSpacecraftState<T> oldState)	Reset the state prior to continue propagation.

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

Modifier and Type	Method	Description
FieldEventHandler.Action	FieldContinueOnEvent.eventOccurred(FieldSpacecraftState<T> s, KK detector, boolean increasing)	Specific implementation of the eventOccurred interface.
FieldEventHandler.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.
FieldEventHandler.Action	FieldStopOnDecreasing.eventOccurred(FieldSpacecraftState<T> s, KK detector, boolean increasing)	Handle a detection event and choose what to do next.
FieldEventHandler.Action	FieldStopOnEvent.eventOccurred(FieldSpacecraftState<T> s, KK detector, boolean increasing)	Specific implementation of the eventOccurred interface.
FieldEventHandler.Action	FieldStopOnIncreasing.eventOccurred(FieldSpacecraftState<T> s, KK detector, boolean increasing)	Handle a detection event and choose what to do next.
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.

Uses of FieldSpacecraftState in org.orekit.propagation.integration

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

Modifier and Type	Method	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, boolean meanOnly)	Map the raw double components to a spacecraft state.
FieldSpacecraftState<T>	FieldStateMapper.mapArrayToState(T t, T[] y, T[] yDot, boolean meanOnly)	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	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	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.sampling

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

Modifier and Type	Method	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	Description
void	FieldOrekitFixedStepHandler.handleStep(FieldSpacecraftState<T> currentState, boolean isLast)	Handle the current step.
default void	FieldOrekitFixedStepHandler.init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t, T step)	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	FieldOrekitStepHandlerMultiplexer.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.