Uses of Class
org.orekit.propagation.FieldSpacecraftState

Packages that use FieldSpacecraftState

Package	Description
org.orekit.control.indirect.adjoint	This package provides routines to model the adjoint dynamics as in the Pontryagin Maximum Principle, as used in indirect control.
org.orekit.control.indirect.shooting	This package provides routines to solve indirect optimal control within the frame of orbital mechanics, using shooting methods.
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.empirical	This package provides empirical 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.maneuvers.trigger	This package provides maneuver triggers' 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.analytical.intelsat	This package provides classes to propagate Intelsat's 11 elements.
org.orekit.propagation.analytical.tle	This package provides classes to read and extrapolate tle's.
org.orekit.propagation.analytical.tle.generation	This package provides classes related to TLE generation.
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).
org.orekit.utils	This package provides useful objects.

Uses of FieldSpacecraftState in org.orekit.control.indirect.adjoint

Methods in org.orekit.control.indirect.adjoint with parameters of type FieldSpacecraftState

Modifier and Type	Method	Description
FieldCombinedDerivatives<T>	FieldCartesianAdjointDerivativesProvider.combinedDerivatives(FieldSpacecraftState<T> state)	Compute the derivatives related to the additional state (and optionally main state increments).
T	FieldCartesianAdjointDerivativesProvider.evaluateHamiltonian(FieldSpacecraftState<T> state)	Evaluate the Hamiltonian from Pontryagin's Maximum Principle.
void	FieldCartesianAdjointDerivativesProvider.init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target)	Initialize the generator at the start of propagation.

Uses of FieldSpacecraftState in org.orekit.control.indirect.shooting

Methods in org.orekit.control.indirect.shooting that return FieldSpacecraftState

Modifier and Type	Method	Description
protected FieldSpacecraftState<Gradient>	AbstractFixedBoundaryCartesianSingleShooting.createFieldStateWithMassAndAdjoint(double initialMass, double[] initialAdjoint)	Create initial state with input mass and adjoint vector.

Methods in org.orekit.control.indirect.shooting with parameters of type FieldSpacecraftState

Modifier and Type	Method	Description
protected FieldNumericalPropagator<Gradient>	AbstractFixedBoundaryCartesianSingleShooting.buildFieldPropagator(FieldSpacecraftState<Gradient> initialState)	Create Gradient numerical propagator.
protected FieldNumericalPropagator<Gradient>	AbstractIndirectShooting.buildFieldPropagator(FieldSpacecraftState<Gradient> initialState)	Create Gradient numerical propagator.
protected abstract double[]	AbstractFixedBoundaryCartesianSingleShooting.updateAdjoint(double[] originalInitialAdjoint, FieldSpacecraftState<Gradient> fieldTerminalState)	Update initial adjoint vector.
protected double[]	NewtonFixedBoundaryCartesianSingleShooting.updateAdjoint(double[] originalInitialAdjoint, FieldSpacecraftState<Gradient> fieldTerminalState)	Update initial adjoint vector.

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

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

Modifier and Type	Method	Description
Gradient	ParametricModelEffectGradient.evaluate(GroundStation station, FieldSpacecraftState<Gradient> state, Gradient[] parameters)	Evaluate the parametric model effect.
protected <T extends CalculusFieldElement<T>> T	BaseRangeIonosphericDelayModifier.rangeErrorIonosphericModel(GroundStation station, FieldSpacecraftState<T> state, T[] parameters)	Compute the measurement error due to Ionosphere.
<T extends CalculusFieldElement<T>> T	BaseRangeTroposphericDelayModifier.rangeErrorTroposphericModel(GroundStation station, FieldSpacecraftState<T> state, T[] parameters)	Compute the measurement error due to Troposphere.
protected <T extends CalculusFieldElement<T>> T	BaseRangeRateIonosphericDelayModifier.rangeRateErrorIonosphericModel(GroundStation station, FieldSpacecraftState<T> state, T[] parameters)	Compute the measurement error due to Ionosphere.
protected <T extends CalculusFieldElement<T>> T	RangeRateIonosphericDelayModifier.rangeRateErrorIonosphericModel(GroundStation station, FieldSpacecraftState<T> state, T[] parameters)	Compute the measurement error due to Ionosphere.
<T extends CalculusFieldElement<T>> T	BaseRangeRateTroposphericDelayModifier.rangeRateErrorTroposphericModel(GroundStation station, FieldSpacecraftState<T> state, T[] parameters)	Compute the measurement error due to Troposphere.
<T extends CalculusFieldElement<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 CalculusFieldElement<T>> FieldVector3D<T>	ForceModel.acceleration(FieldSpacecraftState<T> s, T[] parameters)	Compute acceleration.
default <T extends CalculusFieldElement<T>> void	ForceModel.addContribution(FieldSpacecraftState<T> s, FieldTimeDerivativesEquations<T> adder)	Compute the contribution of the force model to the perturbing acceleration.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	BoxAndSolarArraySpacecraft.dragAcceleration(FieldSpacecraftState<T> state, T density, FieldVector3D<T> relativeVelocity, T[] parameters)	Compute the acceleration due to drag.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	FixedPanel.getNormal(FieldSpacecraftState<T> state)	Get panel normal in spacecraft frame.
abstract <T extends CalculusFieldElement<T>> FieldVector3D<T>	Panel.getNormal(FieldSpacecraftState<T> state)	Get panel normal in spacecraft frame.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	PointingPanel.getNormal(FieldSpacecraftState<T> state)	Get panel normal in spacecraft frame.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	SlewingPanel.getNormal(FieldSpacecraftState<T> state)	Get panel normal in spacecraft frame.
default <T extends CalculusFieldElement<T>> void	ForceModel.init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target)	Initialize the force model at the start of propagation.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	BoxAndSolarArraySpacecraft.radiationPressureAcceleration(FieldSpacecraftState<T> state, FieldVector3D<T> flux, T[] parameters)	Compute the acceleration due to radiation pressure.

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 CalculusFieldElement<T>> FieldVector3D<T>	DragForce.acceleration(FieldSpacecraftState<T> s, T[] parameters)	Compute acceleration.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	TimeSpanDragForce.acceleration(FieldSpacecraftState<T> s, T[] parameters)	Deprecated. Compute acceleration.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	DragSensitive.dragAcceleration(FieldSpacecraftState<T> state, T density, FieldVector3D<T> relativeVelocity, T[] parameters)	Compute the acceleration due to drag.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	IsotropicDrag.dragAcceleration(FieldSpacecraftState<T> state, T density, FieldVector3D<T> relativeVelocity, T[] parameters)	Compute the acceleration due to drag.
protected <T extends CalculusFieldElement<T>> T	AbstractDragForceModel.getFieldDensity(FieldSpacecraftState<T> s)	Evaluate the Field density.
protected <T extends CalculusFieldElement<T>> boolean	AbstractDragForceModel.isDSStateDerivative(FieldSpacecraftState<T> state)	Check if a field state corresponds to derivatives with respect to state.
protected <T extends CalculusFieldElement<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.empirical

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

Modifier and Type	Method	Description
<T extends CalculusFieldElement<T>> FieldVector3D<T>	ParametricAcceleration.acceleration(FieldSpacecraftState<T> state, T[] parameters)	Compute acceleration.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	TimeSpanParametricAcceleration.acceleration(FieldSpacecraftState<T> state, T[] parameters)	Compute acceleration.
<T extends CalculusFieldElement<T>> T	AccelerationModel.signedAmplitude(FieldSpacecraftState<T> state, T[] parameters)	Compute the signed amplitude of the acceleration.
<T extends CalculusFieldElement<T>> T	HarmonicAccelerationModel.signedAmplitude(FieldSpacecraftState<T> state, T[] parameters)	Compute the signed amplitude of the acceleration.
<T extends CalculusFieldElement<T>> T	PolynomialAccelerationModel.signedAmplitude(FieldSpacecraftState<T> state, T[] parameters)	Compute the signed amplitude of the 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 CalculusFieldElement<T>> FieldVector3D<T>	DeSitterRelativity.acceleration(FieldSpacecraftState<T> s, T[] parameters)	Compute acceleration.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	HolmesFeatherstoneAttractionModel.acceleration(FieldSpacecraftState<T> s, T[] parameters)	Compute acceleration.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	J2OnlyPerturbation.acceleration(FieldSpacecraftState<T> state, T[] parameters)	Compute acceleration.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	LenseThirringRelativity.acceleration(FieldSpacecraftState<T> s, T[] parameters)	Compute acceleration.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	NewtonianAttraction.acceleration(FieldSpacecraftState<T> s, T[] parameters)	Compute acceleration.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	OceanTides.acceleration(FieldSpacecraftState<T> s, T[] parameters)	Compute acceleration.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	Relativity.acceleration(FieldSpacecraftState<T> s, T[] parameters)	Compute acceleration.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	SingleBodyAbsoluteAttraction.acceleration(FieldSpacecraftState<T> s, T[] parameters)	Compute acceleration.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	SingleBodyRelativeAttraction.acceleration(FieldSpacecraftState<T> s, T[] parameters)	Compute acceleration.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	SolidTides.acceleration(FieldSpacecraftState<T> s, T[] parameters)	Compute acceleration.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	ThirdBodyAttraction.acceleration(FieldSpacecraftState<T> s, T[] parameters)	Compute acceleration.
<T extends CalculusFieldElement<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	Description
<T extends CalculusFieldElement<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	Description
<T extends CalculusFieldElement<T>> FieldVector3D<T>	Maneuver.acceleration(FieldSpacecraftState<T> s, T[] parameters)
<T extends CalculusFieldElement<T>> void	Maneuver.addContribution(FieldSpacecraftState<T> s, FieldTimeDerivativesEquations<T> adder)	Compute the contribution of the force model to the perturbing acceleration.
T	FieldImpulseManeuver.g(FieldSpacecraftState<T> fieldSpacecraftState)	Compute the value of the switching function.
void	FieldImpulseManeuver.init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t)	Initialize event handler at the start of a propagation.
<T extends CalculusFieldElement<T>> void	Maneuver.init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target)	Initialize the force model at the start of propagation.
<T extends CalculusFieldElement<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	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.
<T extends CalculusFieldElement<T>> T	AbstractConstantThrustPropulsionModel.getFlowRate(FieldSpacecraftState<T> s, T[] parameters)	Get the flow rate (kg/s).
<T extends CalculusFieldElement<T>> T	ProfileThrustPropulsionModel.getFlowRate(FieldSpacecraftState<T> s, T[] parameters)	Get the flow rate (kg/s).
<T extends CalculusFieldElement<T>> T	ThrustPropulsionModel.getFlowRate(FieldSpacecraftState<T> s, T[] parameters)	Get the flow rate (kg/s).
<T extends CalculusFieldElement<T>> T	PropulsionModel.getMassDerivatives(FieldSpacecraftState<T> s, T[] parameters)	Get the mass derivative (i.e.
default <T extends CalculusFieldElement<T>> T	ThrustPropulsionModel.getMassDerivatives(FieldSpacecraftState<T> s, T[] parameters)	Get the mass derivative (i.e.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	AbstractConstantThrustPropulsionModel.getThrustVector(FieldSpacecraftState<T> s, T[] parameters)	Get the thrust vector in spacecraft frame (N).
<T extends CalculusFieldElement<T>> FieldVector3D<T>	ProfileThrustPropulsionModel.getThrustVector(FieldSpacecraftState<T> s, T[] parameters)	Get the thrust vector in spacecraft frame (N).
<T extends CalculusFieldElement<T>> FieldVector3D<T>	ThrustPropulsionModel.getThrustVector(FieldSpacecraftState<T> s, T[] parameters)	Get the thrust vector in spacecraft frame (N).
default <T extends CalculusFieldElement<T>> void	PropulsionModel.init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target)	Initialization method.

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

Methods in org.orekit.forces.maneuvers.trigger that return FieldSpacecraftState

Modifier and Type	Method	Description
protected <T extends CalculusFieldElement<T>> FieldSpacecraftState<T>	AbstractManeuverTriggers.applyResetters(FieldSpacecraftState<T> state)	Apply resetters.
FieldSpacecraftState<T>	FieldManeuverTriggersResetter.resetState(FieldSpacecraftState<T> state)	Reset state as a maneuver triggers.

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

Modifier and Type	Method	Description
protected <T extends CalculusFieldElement<T>> FieldSpacecraftState<T>	AbstractManeuverTriggers.applyResetters(FieldSpacecraftState<T> state)	Apply resetters.
<T extends CalculusFieldElement<T>> void	AbstractManeuverTriggers.init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target)	Initialization method called at propagation start.
default void	FieldManeuverTriggersResetter.init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target)	Initialization method called at propagation start.
<D extends CalculusFieldElement<D>> void	IntervalEventTrigger.init(FieldSpacecraftState<D> initialState, FieldAbsoluteDate<D> target)	Initialization method called at propagation start.
default <T extends CalculusFieldElement<T>> void	ManeuverTriggers.init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target)	Initialization method called at propagation start.
protected <T extends CalculusFieldElement<T>> void	AbstractManeuverTriggers.initializeResetters(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target)	Initialize resetters.
void	FieldManeuverTriggersResetter.maneuverTriggered(FieldSpacecraftState<T> state, boolean start)	Observe a maneuver trigger.
protected <T extends CalculusFieldElement<T>> void	AbstractManeuverTriggers.notifyResetters(FieldSpacecraftState<T> state, boolean start)	Notify resetters.
FieldSpacecraftState<T>	FieldManeuverTriggersResetter.resetState(FieldSpacecraftState<T> state)	Reset state as a maneuver triggers.

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 CalculusFieldElement<T>> FieldVector3D<T>	ECOM2.acceleration(FieldSpacecraftState<T> s, T[] parameters)	Compute acceleration.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	KnockeRediffusedForceModel.acceleration(FieldSpacecraftState<T> s, T[] parameters)	Compute acceleration.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	RadiationPressureModel.acceleration(FieldSpacecraftState<T> s, T[] parameters)	Compute acceleration.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	SolarRadiationPressure.acceleration(FieldSpacecraftState<T> s, T[] parameters)	Compute acceleration.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	KnockeRediffusedForceModel.computeElementaryFlux(FieldSpacecraftState<T> state, FieldVector3D<T> elementCenter, FieldVector3D<T> sunPosition, OneAxisEllipsoid earth, T elementArea)	Compute elementary rediffused flux on satellite.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	AbstractLightFluxModel.getLightFluxVector(FieldSpacecraftState<T> state)	Get the light flux vector in the state's frame.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	LightFluxModel.getLightFluxVector(FieldSpacecraftState<T> state)	Get the light flux vector in the state's frame.
<T extends CalculusFieldElement<T>> T	AbstractLightFluxModel.getLightingRatio(FieldSpacecraftState<T> state)	Get the lighting ratio ([0-1]).
<T extends CalculusFieldElement<T>> T	SolarRadiationPressure.getLightingRatio(FieldSpacecraftState<T> state)	Get the lighting ratio ([0-1]).
<T extends CalculusFieldElement<T>> void	ConicallyShadowedLightFluxModel.init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> targetDate)	Perform initialization steps before starting propagation.
default <T extends CalculusFieldElement<T>> void	LightFluxModel.init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> targetDate)	Perform initialization steps before starting propagation.
<T extends CalculusFieldElement<T>> void	RadiationPressureModel.init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target)	Initialize the force model at the start of propagation.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	IsotropicRadiationClassicalConvention.radiationPressureAcceleration(FieldSpacecraftState<T> state, FieldVector3D<T> flux, T[] parameters)	Compute the acceleration due to radiation pressure.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	IsotropicRadiationCNES95Convention.radiationPressureAcceleration(FieldSpacecraftState<T> state, FieldVector3D<T> flux, T[] parameters)	Compute the acceleration due to radiation pressure.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	IsotropicRadiationSingleCoefficient.radiationPressureAcceleration(FieldSpacecraftState<T> state, FieldVector3D<T> flux, T[] parameters)	Compute the acceleration due to radiation pressure.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	RadiationSensitive.radiationPressureAcceleration(FieldSpacecraftState<T> state, FieldVector3D<T> flux, T[] parameters)	Compute the acceleration due to radiation pressure.

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	Description
<T extends CalculusFieldElement<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 CalculusFieldElement<T>> T	GlobalIonosphereMapModel.pathDelay(FieldSpacecraftState<T> state, TopocentricFrame baseFrame, double frequency, T[] parameters)
<T extends CalculusFieldElement<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 CalculusFieldElement<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 CalculusFieldElement<T>> T	NeQuickModel.pathDelay(FieldSpacecraftState<T> state, TopocentricFrame baseFrame, double frequency, T[] parameters)
<T extends CalculusFieldElement<T>> T	SsrVtecIonosphericModel.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.

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>	FieldSpacecraftState.addAdditionalStateDerivative(String name, T... value)	Add an additional state derivative.
abstract FieldSpacecraftState<T>	FieldAbstractStateModifier.change(FieldSpacecraftState<T> state)	Change main state.
FieldSpacecraftState<T>	FieldAbstractPropagator.getInitialState()	Get the propagator initial state.
FieldSpacecraftState<T>	FieldPropagator.getInitialState()	Get the propagator initial state.
protected FieldSpacecraftState<KK>	FieldSpacecraftStateInterpolator.interpolate(AbstractFieldTimeInterpolator.InterpolationData interpolationData)	Interpolate instance from given interpolation data.
FieldSpacecraftState<KK>	FieldSpacecraftStateInterpolator.interpolate(FieldAbsoluteDate<KK> interpolationDate, Collection<FieldSpacecraftState<KK>> 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.
FieldSpacecraftState<T>	FieldAbstractStateModifier.update(FieldSpacecraftState<T> state)	Update a state.
default FieldSpacecraftState<T>	FieldAdditionalStateProvider.update(FieldSpacecraftState<T> state)	Update a state.
protected FieldSpacecraftState<T>	FieldAbstractPropagator.updateAdditionalStates(FieldSpacecraftState<T> original)	Update state by adding all additional states.
protected FieldSpacecraftState<T>	FieldAbstractPropagator.updateUnmanagedStates(FieldSpacecraftState<T> original)	Update state by adding unmanaged states.

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

Modifier and Type	Method	Description
abstract FieldSpacecraftState<T>	FieldAbstractStateModifier.change(FieldSpacecraftState<T> state)	Change main state.
void	FieldSpacecraftState.ensureCompatibleAdditionalStates(FieldSpacecraftState<T> state)	Check if two instances have the same set of additional states available.
T[]	FieldAbstractStateModifier.getAdditionalState(FieldSpacecraftState<T> state)	Get the additional state.
T[]	FieldAdditionalStateProvider.getAdditionalState(FieldSpacecraftState<T> state)	Get the additional state.
default void	FieldAdditionalStateProvider.init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target)	Initialize the additional state provider at the start of propagation.
void	FieldAbstractPropagator.resetInitialState(FieldSpacecraftState<T> state)	Reset the propagator initial state.
void	FieldPropagator.resetInitialState(FieldSpacecraftState<T> state)	Reset the propagator initial state.
protected void	FieldAbstractPropagator.stateChanged(FieldSpacecraftState<T> state)	Notify about a state change.
FieldSpacecraftState<T>	FieldAbstractStateModifier.update(FieldSpacecraftState<T> state)	Update a state.
default FieldSpacecraftState<T>	FieldAdditionalStateProvider.update(FieldSpacecraftState<T> state)	Update a state.
protected FieldSpacecraftState<T>	FieldAbstractPropagator.updateAdditionalStates(FieldSpacecraftState<T> original)	Update state by adding all additional states.
protected FieldSpacecraftState<T>	FieldAbstractPropagator.updateUnmanagedStates(FieldSpacecraftState<T> original)	Update state by adding unmanaged states.
default boolean	FieldAdditionalStateProvider.yields(FieldSpacecraftState<T> state)	Check if this provider should yield so another provider has an opportunity to add missing parts.

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

Modifier and Type	Method	Description
FieldSpacecraftState<KK>	FieldSpacecraftStateInterpolator.interpolate(FieldAbsoluteDate<KK> interpolationDate, Collection<FieldSpacecraftState<KK>> 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)	Accept a step, triggering events and step handlers.
protected FieldSpacecraftState<T>	FieldAbstractAnalyticalPropagator.basicPropagate(FieldAbsoluteDate<T> date)	Propagate an orbit without any fancy features.
FieldSpacecraftState<Gradient>	AbstractAnalyticalGradientConverter.getState()	Get the state with the number of parameters consistent with the propagation model.
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
abstract FieldAbstractAnalyticalPropagator<Gradient>	AbstractAnalyticalGradientConverter.getPropagator(FieldSpacecraftState<Gradient> state, Gradient[] parameters)	Get the converted analytical orbit propagator.
void	FieldBrouwerLyddanePropagator.resetInitialState(FieldSpacecraftState<T> state)	Reset the propagator initial state.
void	FieldBrouwerLyddanePropagator.resetInitialState(FieldSpacecraftState<T> state, PropagationType stateType)	Reset the propagator initial state.
void	FieldBrouwerLyddanePropagator.resetInitialState(FieldSpacecraftState<T> state, PropagationType stateType, double epsilon, int maxIterations)	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.
void	FieldEcksteinHechlerPropagator.resetInitialState(FieldSpacecraftState<T> state, PropagationType stateType, double epsilon, int maxIterations)	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	FieldBrouwerLyddanePropagator.resetIntermediateState(FieldSpacecraftState<T> state, boolean forward)	Reset an intermediate state.
protected void	FieldBrouwerLyddanePropagator.resetIntermediateState(FieldSpacecraftState<T> state, boolean forward, double epsilon, int maxIterations)	Reset an intermediate state.
protected void	FieldEcksteinHechlerPropagator.resetIntermediateState(FieldSpacecraftState<T> state, boolean forward)	Reset an intermediate state.
protected void	FieldEcksteinHechlerPropagator.resetIntermediateState(FieldSpacecraftState<T> state, boolean forward, double epsilon, int maxIterations)	Reset an intermediate state.
protected void	FieldKeplerianPropagator.resetIntermediateState(FieldSpacecraftState<T> state, boolean forward)	Reset an intermediate state.

Uses of FieldSpacecraftState in org.orekit.propagation.analytical.intelsat

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

Modifier and Type	Method	Description
void	FieldIntelsatElevenElementsPropagator.resetInitialState(FieldSpacecraftState<T> state)	Reset the propagator initial state.
protected void	FieldIntelsatElevenElementsPropagator.resetIntermediateState(FieldSpacecraftState<T> state, boolean forward)	Reset an intermediate state.

Uses of FieldSpacecraftState in org.orekit.propagation.analytical.tle

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

Modifier and Type	Method	Description
void	FieldTLEPropagator.resetInitialState(FieldSpacecraftState<T> state)	Reset the propagator initial state.
protected void	FieldTLEPropagator.resetIntermediateState(FieldSpacecraftState<T> state, boolean forward)	Reset an intermediate state.
static <T extends CalculusFieldElement<T>> FieldTLE<T>	FieldTLE.stateToTLE(FieldSpacecraftState<T> state, FieldTLE<T> templateTLE, TleGenerationAlgorithm generationAlgorithm)	Convert Spacecraft State into TLE.

Uses of FieldSpacecraftState in org.orekit.propagation.analytical.tle.generation

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

Modifier and Type	Method	Description
<T extends CalculusFieldElement<T>> FieldTLE<T>	FixedPointTleGenerationAlgorithm.generate(FieldSpacecraftState<T> state, FieldTLE<T> templateTLE)	Generate a TLE from a given spacecraft state and a template TLE.
<T extends CalculusFieldElement<T>> FieldTLE<T>	LeastSquaresTleGenerationAlgorithm.generate(FieldSpacecraftState<T> state, FieldTLE<T> templateTLE)	Generate a TLE from a given spacecraft state and a template TLE.
<T extends CalculusFieldElement<T>> FieldTLE<T>	TleGenerationAlgorithm.generate(FieldSpacecraftState<T> state, FieldTLE<T> templateTLE)	Generate a TLE from a given spacecraft state and a template TLE.

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.

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

Modifier and Type	Method	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	Description
static <T extends CalculusFieldElement<T>> T	FieldBetaAngleDetector.calculateBetaAngle(FieldSpacecraftState<T> state, FieldPVCoordinatesProvider<T> celestialBodyProvider)	Calculate the beta angle between the orbit plane and the celestial body.
static <T extends CalculusFieldElement<T>> T	FieldBetaAngleDetector.calculateBetaAngle(FieldSpacecraftState<T> state, FieldPVCoordinatesProvider<T> celestialBodyProvider, Frame frame)	Calculate the beta angle between the orbit plane and the celestial body.
FieldPVCoordinates<T>	FieldExtremumApproachDetector.computeDeltaPV(FieldSpacecraftState<T> s)	Deprecated. The output type of this method shall be modified in the future to improve code efficiency (though it will still give access to the relative position and velocity)
double	FieldAdaptableInterval.currentInterval(FieldSpacecraftState<T> state)	Get the current value of maximal time interval between events handler checks.
FieldEventState.EventOccurrence<T>	FieldEventState.doEvent(FieldSpacecraftState<T> state)	Notify the user's listener of the event.
boolean	FieldEnablingPredicate.eventIsEnabled(FieldSpacecraftState<T> state, FieldEventDetector<T> detector, T g)	Compute an event enabling function of state.
void	FieldAdapterDetector.finish(FieldSpacecraftState<T> state)	This method finalizes the event detector's job.
default void	FieldEventDetector.finish(FieldSpacecraftState<T> state)	This method finalizes the event detector's job.
void	FieldEventState.finish(FieldSpacecraftState<T> state)	This method finalizes the event detector's job.
T	FieldAdapterDetector.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	FieldBetaAngleDetector.g(FieldSpacecraftState<T> s)	Compute the value of the switching function.
T	FieldBooleanDetector.g(FieldSpacecraftState<T> s)
T	FieldCylindricalShadowEclipseDetector.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	FieldElevationExtremumDetector.g(FieldSpacecraftState<T> s)	Compute the value of the detection function.
T	FieldEventDetector.g(FieldSpacecraftState<T> s)	Compute the value of the switching function.
T	FieldEventEnablingPredicateFilter.g(FieldSpacecraftState<T> s)	Compute the value of the switching function.
T	FieldEventSlopeFilter.g(FieldSpacecraftState<T> s)	Compute the value of the switching function.
T	FieldExtremumApproachDetector.g(FieldSpacecraftState<T> s)	The g is positive when the primary object is getting further away from the secondary object and is negative when it is getting closer to it.
T	FieldFunctionalDetector.g(FieldSpacecraftState<T> s)
T	FieldLatitudeCrossingDetector.g(FieldSpacecraftState<T> s)	Compute the value of the detection function.
T	FieldLatitudeRangeCrossingDetector.g(FieldSpacecraftState<T> s)	Compute the value of the detection function.
T	FieldLongitudeCrossingDetector.g(FieldSpacecraftState<T> s)	Compute the value of the detection function.
T	FieldLongitudeRangeCrossingDetector.g(FieldSpacecraftState<T> s)	Compute the value of the detection function.
T	FieldNegateDetector.g(FieldSpacecraftState<T> s)
T	FieldNodeDetector.g(FieldSpacecraftState<T> s)	Compute the value of the switching function.
T	FieldParameterDrivenDateIntervalDetector.g(FieldSpacecraftState<T> s)	Compute the value of the switching function.
T	FieldRelativeDistanceDetector.g(FieldSpacecraftState<T> s)	The g is positive when the relative distance is larger or equal than the threshold, non-positive otherwise.
T	FieldElevationExtremumDetector.getElevation(FieldSpacecraftState<T> s)	Get the elevation value.
void	FieldAbstractDetector.init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t)	Initialize event handler at the start of a propagation.
void	FieldAdapterDetector.init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t)	Initialize event handler at the start of a propagation.
void	FieldBooleanDetector.init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t)
default void	FieldEventDetector.init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t)	Initialize event handler at the start of a propagation.
void	FieldEventEnablingPredicateFilter.init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t)	Initialize event handler at the start of a propagation.
void	FieldEventSlopeFilter.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.
void	FieldLongitudeCrossingDetector.init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t)	Initialize event handler at the start of a propagation.
void	FieldNegateDetector.init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t)
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	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.

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

Constructor	Description
FieldFunctionalDetector(FieldAdaptableInterval<T> maxCheck, T threshold, int maxIter, FieldEventHandler<T> handler, Function<FieldSpacecraftState<T>,T> function)	Private constructor.

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

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

Modifier and Type	Method	Description
FieldSpacecraftState<T>	FieldRecordAndContinue.Event.getState()	Get the spacecraft's state at the event.
default FieldSpacecraftState<T>	FieldEventHandler.resetState(FieldEventDetector<T> detector, FieldSpacecraftState<T> oldState)	Reset the state prior to continue propagation.
FieldSpacecraftState<T>	FieldRecallLastOccurrence.resetState(FieldEventDetector<T> 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
Action	FieldContinueOnEvent.eventOccurred(FieldSpacecraftState<T> s, FieldEventDetector<T> detector, boolean increasing)	Specific implementation of the eventOccurred interface.
Action	FieldEventHandler.eventOccurred(FieldSpacecraftState<T> s, FieldEventDetector<T> detector, boolean increasing)	Handle an event.
Action	FieldRecallLastOccurrence.eventOccurred(FieldSpacecraftState<T> s, FieldEventDetector<T> detector, boolean increasing)	Handle an event.
Action	FieldRecordAndContinue.eventOccurred(FieldSpacecraftState<T> s, FieldEventDetector<T> detector, boolean increasing)
Action	FieldResetDerivativesOnEvent.eventOccurred(FieldSpacecraftState<T> s, FieldEventDetector<T> detector, boolean increasing)	Specific implementation of the eventOccurred interface.
Action	FieldStopOnDecreasing.eventOccurred(FieldSpacecraftState<T> s, FieldEventDetector<T> detector, boolean increasing)	Handle a detection event and choose what to do next.
Action	FieldStopOnEvent.eventOccurred(FieldSpacecraftState<T> s, FieldEventDetector<T> detector, boolean increasing)	Specific implementation of the eventOccurred interface.
Action	FieldStopOnIncreasing.eventOccurred(FieldSpacecraftState<T> s, FieldEventDetector<T> detector, boolean increasing)	Handle a detection event and choose what to do next.
default void	FieldEventHandler.finish(FieldSpacecraftState<T> finalState, FieldEventDetector<T> detector)	This method finalize event handler at the end of a propagation.
void	FieldRecallLastOccurrence.finish(FieldSpacecraftState<T> finalState, FieldEventDetector<T> detector)	This method finalize event handler at the end of a propagation.
default void	FieldEventHandler.init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target, FieldEventDetector<T> detector)	Initialize event handler at the start of a propagation.
void	FieldRecallLastOccurrence.init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target, FieldEventDetector<T> detector)	Initialize event handler at the start of a propagation.
default FieldSpacecraftState<T>	FieldEventHandler.resetState(FieldEventDetector<T> detector, FieldSpacecraftState<T> oldState)	Reset the state prior to continue propagation.
FieldSpacecraftState<T>	FieldRecallLastOccurrence.resetState(FieldEventDetector<T> 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 static FieldSpacecraftState<Gradient>	AbstractGradientConverter.buildBasicGradientSpacecraftState(SpacecraftState state, int freeStateParameters, AttitudeProvider provider)	Process a state into a Gradient version without force model parameter.
protected FieldSpacecraftState<T>	FieldAbstractIntegratedPropagator.getInitialIntegrationState()	Get the initial state for integration.
FieldSpacecraftState<T>	FieldIntegratedEphemeris.getInitialState()	Get the propagator initial state.
FieldSpacecraftState<Gradient>	AbstractGradientConverter.getState(ParameterDriversProvider parametricModel)	Get the state with the number of parameters consistent with parametric model.
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.
FieldSpacecraftState<T>	FieldAbstractIntegratedPropagator.propagate(FieldAbsoluteDate<T> tStart, FieldAbsoluteDate<T> tEnd)	Propagate from a start date towards a target date.
protected FieldSpacecraftState<T>	FieldIntegratedEphemeris.updateAdditionalStates(FieldSpacecraftState<T> original)	Update state by adding all additional states.

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.
FieldCombinedDerivatives<T>	FieldAdditionalDerivativesProvider.combinedDerivatives(FieldSpacecraftState<T> s)	Compute the derivatives related to the additional state (and optionally main state increments).
T[]	FieldAbstractIntegratedPropagator.MainStateEquations.computeDerivatives(FieldSpacecraftState<T> state)	Compute differential equations for main state.
Gradient[]	AbstractGradientConverter.getParameters(FieldSpacecraftState<Gradient> state, ParameterDriversProvider parametricModel)	Get the parametric model parameters, return gradient values for each span of each driver (several gradient values for each parameter).
Gradient[]	AbstractGradientConverter.getParametersAtStateDate(FieldSpacecraftState<Gradient> state, ParameterDriversProvider parametricModel)	Get the parametric model parameters, return gradient values at state date for each driver (only 1 gradient value for each parameter).
void	FieldAbstractIntegratedPropagator.MainStateEquations.init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target)	Initialize the equations at the start of propagation.
default void	FieldAdditionalDerivativesProvider.init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target)	Initialize the generator at the start of propagation.
protected void	AbstractGradientConverter.initStates(FieldSpacecraftState<Gradient> zeroParametersState)	Initialize first state with 0 parameters.
abstract void	FieldStateMapper.mapStateToArray(FieldSpacecraftState<T> state, T[] y, T[] yDot)	Map a spacecraft state to raw double components.
void	FieldAbstractIntegratedPropagator.resetInitialState(FieldSpacecraftState<T> state, PropagationType stateType)	Reset initial state with a given propagation type.
void	FieldIntegratedEphemeris.resetInitialState(FieldSpacecraftState<T> state)	Reset the propagator initial state.
protected void	FieldIntegratedEphemeris.resetIntermediateState(FieldSpacecraftState<T> state, boolean forward)	Reset an intermediate state.
protected FieldSpacecraftState<T>	FieldIntegratedEphemeris.updateAdditionalStates(FieldSpacecraftState<T> original)	Update state by adding all additional states.
default boolean	FieldAdditionalDerivativesProvider.yields(FieldSpacecraftState<T> state)	Check if this provider should yield so another provider has an opportunity to add missing parts.

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.numerical.cr3bp

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

Modifier and Type	Method	Description
<T extends CalculusFieldElement<T>> FieldVector3D<T>	CR3BPForceModel.acceleration(FieldSpacecraftState<T> s, T[] parameters)	Compute acceleration.
<T extends CalculusFieldElement<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	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
default void	FieldOrekitFixedStepHandler.finish(FieldSpacecraftState<T> finalState)	Finalize propagation.
default void	FieldOrekitStepHandler.finish(FieldSpacecraftState<T> finalState)	Finalize propagation.
void	FieldOrekitStepNormalizer.finish(FieldSpacecraftState<T> finalState)	Finalize propagation.
void	FieldStepHandlerMultiplexer.finish(FieldSpacecraftState<T> finalState)	Finalize propagation.
void	FieldOrekitFixedStepHandler.handleStep(FieldSpacecraftState<T> currentState)	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.
default 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	FieldStepHandlerMultiplexer.init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t)	Initialize step handler at the start of a propagation.
FieldOrekitStepInterpolator<T>	FieldOrekitStepInterpolator.restrictStep(FieldSpacecraftState<T> newPreviousState, FieldSpacecraftState<T> newCurrentState)	Create a new restricted version of the instance.

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

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

Modifier and Type	Method	Description
static <T extends CalculusFieldElement<T>> FieldSpacecraftState<T>	FieldDSSTPropagator.computeMeanState(FieldSpacecraftState<T> osculating, AttitudeProvider attitudeProvider, Collection<DSSTForceModel> forceModel)	Conversion from osculating to mean orbit.
static <T extends CalculusFieldElement<T>> FieldSpacecraftState<T>	FieldDSSTPropagator.computeMeanState(FieldSpacecraftState<T> osculating, AttitudeProvider attitudeProvider, Collection<DSSTForceModel> forceModel, double epsilon, int maxIterations)	Conversion from osculating to mean orbit.
static <T extends CalculusFieldElement<T>> 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	Description
protected void	FieldDSSTPropagator.beforeIntegration(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> tEnd)	Method called just before integration.
static <T extends CalculusFieldElement<T>> FieldSpacecraftState<T>	FieldDSSTPropagator.computeMeanState(FieldSpacecraftState<T> osculating, AttitudeProvider attitudeProvider, Collection<DSSTForceModel> forceModel)	Conversion from osculating to mean orbit.
static <T extends CalculusFieldElement<T>> FieldSpacecraftState<T>	FieldDSSTPropagator.computeMeanState(FieldSpacecraftState<T> osculating, AttitudeProvider attitudeProvider, Collection<DSSTForceModel> forceModel, double epsilon, int maxIterations)	Conversion from osculating to mean orbit.
static <T extends CalculusFieldElement<T>> 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.resetInitialState(FieldSpacecraftState<T> state, PropagationType stateType)	Reset initial state with a given propagation type.
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	Description
AbstractGaussianContribution.FieldSlot<T>	AbstractGaussianContribution.FieldGaussianShortPeriodicCoefficients.createSlot(FieldSpacecraftState<T>... meanStates)	Get the slot valid for some date.
protected abstract <T extends CalculusFieldElement<T>> T[]	AbstractGaussianContribution.getLLimits(FieldSpacecraftState<T> state, FieldAuxiliaryElements<T> auxiliaryElements)	Compute the limits in L, the true longitude, for integration.
protected <T extends CalculusFieldElement<T>> T[]	DSSTAtmosphericDrag.getLLimits(FieldSpacecraftState<T> state, FieldAuxiliaryElements<T> auxiliaryElements)	Compute the limits in L, the true longitude, for integration.
protected <T extends CalculusFieldElement<T>> T[]	DSSTSolarRadiationPressure.getLLimits(FieldSpacecraftState<T> state, FieldAuxiliaryElements<T> auxiliaryElements)	Compute the limits in L, the true longitude, for integration.
protected <T extends CalculusFieldElement<T>> T[]	AbstractGaussianContribution.getMeanElementRate(FieldSpacecraftState<T> state, AbstractGaussianContribution.GaussQuadrature gauss, T low, T high, FieldAbstractGaussianContributionContext<T> context, T[] parameters)	Computes the mean equinoctial elements rates dai / dt.
<T extends CalculusFieldElement<T>> T[]	AbstractGaussianContribution.getMeanElementRate(FieldSpacecraftState<T> state, FieldAuxiliaryElements<T> auxiliaryElements, T[] parameters)	Computes the mean equinoctial elements rates dai / dt.
<T extends CalculusFieldElement<T>> T[]	DSSTForceModel.getMeanElementRate(FieldSpacecraftState<T> state, FieldAuxiliaryElements<T> auxiliaryElements, T[] parameters)	Computes the mean equinoctial elements rates dai / dt.
<T extends CalculusFieldElement<T>> T[]	DSSTJ2SquaredClosedForm.getMeanElementRate(FieldSpacecraftState<T> state, FieldAuxiliaryElements<T> auxiliaryElements, T[] parameters)	Computes the mean equinoctial elements rates dai / dt.
<T extends CalculusFieldElement<T>> T[]	DSSTNewtonianAttraction.getMeanElementRate(FieldSpacecraftState<T> state, FieldAuxiliaryElements<T> auxiliaryElements, T[] parameters)	Computes the mean equinoctial elements rates dai / dt.
<T extends CalculusFieldElement<T>> T[]	DSSTTesseral.getMeanElementRate(FieldSpacecraftState<T> spacecraftState, FieldAuxiliaryElements<T> auxiliaryElements, T[] parameters)	Computes the mean equinoctial elements rates dai / dt.
<T extends CalculusFieldElement<T>> T[]	DSSTThirdBody.getMeanElementRate(FieldSpacecraftState<T> currentState, FieldAuxiliaryElements<T> auxiliaryElements, T[] parameters)	Computes the mean equinoctial elements rates dai / dt.
<T extends CalculusFieldElement<T>> T[]	DSSTZonal.getMeanElementRate(FieldSpacecraftState<T> spacecraftState, FieldAuxiliaryElements<T> auxiliaryElements, T[] parameters)	Computes the mean equinoctial elements rates dai / dt.
<T extends CalculusFieldElement<T>> void	AbstractGaussianContribution.init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target)	Initialize the force model at the start of propagation.
default <T extends CalculusFieldElement<T>> void	DSSTForceModel.init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target)	Initialize the force model at the start of propagation.
<T extends CalculusFieldElement<T>> void	AbstractGaussianContribution.updateShortPeriodTerms(T[] parameters, FieldSpacecraftState<T>... meanStates)	Update the short period terms.
<T extends CalculusFieldElement<T>> void	DSSTForceModel.updateShortPeriodTerms(T[] parameters, FieldSpacecraftState<T>... meanStates)	Update the short period terms.
<T extends CalculusFieldElement<T>> void	DSSTJ2SquaredClosedForm.updateShortPeriodTerms(T[] parameters, FieldSpacecraftState<T>... meanStates)	Update the short period terms.
<T extends CalculusFieldElement<T>> void	DSSTNewtonianAttraction.updateShortPeriodTerms(T[] parameters, FieldSpacecraftState<T>... meanStates)	Update the short period terms.
<T extends CalculusFieldElement<T>> void	DSSTTesseral.updateShortPeriodTerms(T[] parameters, FieldSpacecraftState<T>... meanStates)	Update the short period terms.
<T extends CalculusFieldElement<T>> void	DSSTThirdBody.updateShortPeriodTerms(T[] parameters, FieldSpacecraftState<T>... meanStates)	Update the short period terms.
<T extends CalculusFieldElement<T>> void	DSSTZonal.updateShortPeriodTerms(T[] parameters, FieldSpacecraftState<T>... meanStates)	Update the short period terms.
default <T extends CalculusFieldElement<T>> void	J2SquaredModel.updateShortPeriodTerms(T[] parameters, FieldSpacecraftState<T>... meanStates)	Update the J2-squared short period terms.

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

Constructor	Description
FieldIntegrableFunction(FieldSpacecraftState<T> state, boolean meanMode, int j, T[] parameters, Field<T> field)	Build a new instance with a new field.

Uses of FieldSpacecraftState in org.orekit.utils

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

Modifier and Type	Method	Description
<T extends CalculusFieldElement<T>> OccultationEngine.FieldOccultationAngles<T>	OccultationEngine.angles(FieldSpacecraftState<T> state)	Compute the occultation angles as seen from a spacecraft.