Uses of Class org.orekit.propagation.SpacecraftState (OREKIT 12.1.3 API)

Packages that use SpacecraftState
Package	Description
org.orekit.attitudes	This package provides classes to represent simple attitudes.
org.orekit.estimation.measurements	The measurements package defines everything that is related to orbit determination measurements.
org.orekit.estimation.measurements.filtering	This package provides measurement pre-processing filters.
org.orekit.estimation.measurements.generation	This package provides Orbit Determination measurements generation.
org.orekit.estimation.measurements.gnss	This package provides methods to handle GNSS measurements.
org.orekit.estimation.measurements.modifiers	This package provides measurement modifier.
org.orekit.estimation.sequential	The sequential package provides an implementation of a Kalman Filter engine to perform an orbit determination.
org.orekit.files.ccsds.ndm.adm.aem	This package contains class managing CCSDS Attitude Ephemeris Message.
org.orekit.files.ccsds.ndm.odm.ocm	This package contains class managing CCSDS Orbit Comprehensive Message.
org.orekit.files.ccsds.ndm.odm.oem	This package contains class managing CCSDS Orbit Ephemeris Message.
org.orekit.files.ccsds.ndm.odm.omm	This package contains class managing CCSDS Orbit Mean-Elements Message.
org.orekit.files.ccsds.ndm.odm.opm	This package contains class managing CCSDS Orbit Parameter Message.
org.orekit.files.general	This package provides interfaces for orbit file representations and corresponding parsers.
org.orekit.files.ilrs	This package provides parsers for laser ranging data stored in CDR and CPF formats.
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.jacobians	Generators for columns of Jacobian matrices related to maneuver parameters.
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.orbits	This package provides classes to represent orbits.
org.orekit.propagation	Propagation
org.orekit.propagation.analytical	Top level package for analytical propagators.
org.orekit.propagation.analytical.gnss	This package provides classes to propagate GNSS orbits.
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.conversion	This package provides tools to convert a given propagator or a set of `SpacecraftState` into another propagator.
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 SpacecraftState in org.orekit.attitudes

Methods in org.orekit.attitudes with parameters of type SpacecraftState
Modifier and Type	Method	Description
`void`	AttitudesSequence.SwitchHandler.`switchOccurred(AttitudeProvider preceding, AttitudeProvider following, SpacecraftState state)`	Method called when attitude is switched from one law to another law.

Uses of SpacecraftState in org.orekit.estimation.measurements

Methods in org.orekit.estimation.measurements that return SpacecraftState
Modifier and Type	Method	Description
`SpacecraftState`	CommonParametersWithDerivatives.`getState()`	Get spacecraft state.
`SpacecraftState`	CommonParametersWithoutDerivatives.`getState()`	Get spacecraft state.
`SpacecraftState[]`	EstimatedMeasurementBase.`getStates()`	Get the states of the spacecrafts.
`SpacecraftState`	CommonParametersWithDerivatives.`getTransitState()`	Get transit state.
`SpacecraftState`	CommonParametersWithoutDerivatives.`getTransitState()`	Get transit state.

Methods in org.orekit.estimation.measurements with parameters of type SpacecraftState
Modifier and Type	Method	Description
`protected GroundReceiverCommonParametersWithDerivatives`	GroundReceiverMeasurement.`computeCommonParametersWithDerivatives(SpacecraftState state)`	Compute common estimation parameters.
`protected GroundReceiverCommonParametersWithoutDerivatives`	GroundReceiverMeasurement.`computeCommonParametersWithout(SpacecraftState state)`	Compute common estimation parameters.
`EstimatedMeasurement<T>`	AbstractMeasurement.`estimate(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value of the measurement, with derivatives.
`EstimatedMeasurement<T>`	ObservedMeasurement.`estimate(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value of the measurement, with derivatives.
`EstimatedMeasurementBase<T>`	AbstractMeasurement.`estimateWithoutDerivatives(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value of the measurement, without derivatives.
`EstimatedMeasurementBase<T>`	ObservedMeasurement.`estimateWithoutDerivatives(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value of the measurement, without derivatives.
`default EstimatedMeasurementBase<T>`	ObservedMeasurement.`estimateWithoutDerivatives(SpacecraftState[] states)`	Estimate the theoretical value of the measurement, without derivatives.
`static TimeStampedFieldPVCoordinates<Gradient>`	AbstractMeasurement.`getCoordinates(SpacecraftState state, int firstDerivative, int freeParameters)`	Get Cartesian coordinates as derivatives.
`protected abstract EstimatedMeasurement<T>`	AbstractMeasurement.`theoreticalEvaluation(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value.
`protected EstimatedMeasurement<AngularAzEl>`	AngularAzEl.`theoreticalEvaluation(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value.
`protected EstimatedMeasurement<AngularRaDec>`	AngularRaDec.`theoreticalEvaluation(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value.
`protected EstimatedMeasurement<BistaticRange>`	BistaticRange.`theoreticalEvaluation(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value.
`protected EstimatedMeasurement<BistaticRangeRate>`	BistaticRangeRate.`theoreticalEvaluation(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value.
`protected EstimatedMeasurement<FDOA>`	FDOA.`theoreticalEvaluation(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value.
`protected EstimatedMeasurement<InterSatellitesRange>`	InterSatellitesRange.`theoreticalEvaluation(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value.
`protected EstimatedMeasurement<MultiplexedMeasurement>`	MultiplexedMeasurement.`theoreticalEvaluation(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value.
`protected EstimatedMeasurement<Position>`	Position.`theoreticalEvaluation(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value.
`protected EstimatedMeasurement<PV>`	PV.`theoreticalEvaluation(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value.
`protected EstimatedMeasurement<Range>`	Range.`theoreticalEvaluation(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value.
`protected EstimatedMeasurement<RangeRate>`	RangeRate.`theoreticalEvaluation(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value.
`protected EstimatedMeasurement<TDOA>`	TDOA.`theoreticalEvaluation(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value.
`protected EstimatedMeasurement<TurnAroundRange>`	TurnAroundRange.`theoreticalEvaluation(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value.
`protected abstract EstimatedMeasurementBase<T>`	AbstractMeasurement.`theoreticalEvaluationWithoutDerivatives(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value without derivatives.
`protected EstimatedMeasurementBase<AngularAzEl>`	AngularAzEl.`theoreticalEvaluationWithoutDerivatives(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value without derivatives.
`protected EstimatedMeasurementBase<AngularRaDec>`	AngularRaDec.`theoreticalEvaluationWithoutDerivatives(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value without derivatives.
`protected EstimatedMeasurementBase<BistaticRange>`	BistaticRange.`theoreticalEvaluationWithoutDerivatives(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value without derivatives.
`protected EstimatedMeasurementBase<BistaticRangeRate>`	BistaticRangeRate.`theoreticalEvaluationWithoutDerivatives(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value without derivatives.
`protected EstimatedMeasurementBase<FDOA>`	FDOA.`theoreticalEvaluationWithoutDerivatives(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value without derivatives.
`protected EstimatedMeasurementBase<InterSatellitesRange>`	InterSatellitesRange.`theoreticalEvaluationWithoutDerivatives(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value without derivatives.
`protected EstimatedMeasurementBase<MultiplexedMeasurement>`	MultiplexedMeasurement.`theoreticalEvaluationWithoutDerivatives(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value without derivatives.
`protected EstimatedMeasurementBase<Position>`	Position.`theoreticalEvaluationWithoutDerivatives(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value without derivatives.
`protected EstimatedMeasurementBase<PV>`	PV.`theoreticalEvaluationWithoutDerivatives(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value without derivatives.
`protected EstimatedMeasurementBase<Range>`	Range.`theoreticalEvaluationWithoutDerivatives(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value without derivatives.
`protected EstimatedMeasurementBase<RangeRate>`	RangeRate.`theoreticalEvaluationWithoutDerivatives(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value without derivatives.
`protected EstimatedMeasurementBase<TDOA>`	TDOA.`theoreticalEvaluationWithoutDerivatives(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value without derivatives.
`protected EstimatedMeasurementBase<TurnAroundRange>`	TurnAroundRange.`theoreticalEvaluationWithoutDerivatives(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value without derivatives.

Constructors in org.orekit.estimation.measurements with parameters of type SpacecraftState
Constructor	Description
`CommonParametersWithDerivatives(SpacecraftState state, Map<String,Integer> indices, Gradient tauD, SpacecraftState transitState, TimeStampedFieldPVCoordinates<Gradient> transitPV)`	Simple constructor.
`CommonParametersWithoutDerivatives(SpacecraftState state, double tauD, SpacecraftState transitState, TimeStampedPVCoordinates transitPV)`	Simple constructor.
`EstimatedMeasurement(T observedMeasurement, int iteration, int count, SpacecraftState[] states, TimeStampedPVCoordinates[] participants)`	Simple constructor.
`EstimatedMeasurementBase(T observedMeasurement, int iteration, int count, SpacecraftState[] states, TimeStampedPVCoordinates[] participants)`	Simple constructor.
`GroundReceiverCommonParametersWithDerivatives(SpacecraftState state, Map<String,Integer> indices, FieldTransform<Gradient> offsetToInertialDownlink, TimeStampedFieldPVCoordinates<Gradient> stationDownlink, Gradient tauD, SpacecraftState transitState, TimeStampedFieldPVCoordinates<Gradient> transitPV)`	Simple constructor.
`GroundReceiverCommonParametersWithoutDerivatives(SpacecraftState state, Transform offsetToInertialDownlink, TimeStampedPVCoordinates stationDownlink, double tauD, SpacecraftState transitState, TimeStampedPVCoordinates transitPV)`	Simple constructor.

Uses of SpacecraftState in org.orekit.estimation.measurements.filtering

Methods in org.orekit.estimation.measurements.filtering with parameters of type SpacecraftState
Modifier and Type	Method	Description
`void`	ElevationFilter.`filter(ObservedMeasurement<T> measurement, SpacecraftState state)`	Apply a filter to an observed measurement.
`void`	MeasurementFilter.`filter(ObservedMeasurement<T> measurement, SpacecraftState state)`	Apply a filter to an observed measurement.
`void`	ResidualFilter.`filter(ObservedMeasurement<T> measurement, SpacecraftState state)`	Apply a filter to an observed measurement.

Uses of SpacecraftState in org.orekit.estimation.measurements.generation

Methods in org.orekit.estimation.measurements.generation with parameters of type SpacecraftState
Modifier and Type	Method	Description
`default T`	MeasurementBuilder.`build(AbsoluteDate date, SpacecraftState[] states)`	Generate a single measurement.

Uses of SpacecraftState in org.orekit.estimation.measurements.gnss

Methods in org.orekit.estimation.measurements.gnss with parameters of type SpacecraftState
Modifier and Type	Method	Description
`protected OnBoardCommonParametersWithDerivatives`	AbstractOnBoardMeasurement.`computeCommonParametersWith(SpacecraftState[] states, boolean clockOffsetAlreadyApplied)`	Compute common estimation parameters.
`protected OnBoardCommonParametersWithoutDerivatives`	AbstractOnBoardMeasurement.`computeCommonParametersWithout(SpacecraftState[] states, boolean clockOffsetAlreadyApplied)`	Compute common estimation parameters.
`protected PVCoordinatesProvider`	AbstractInterSatellitesMeasurement.`getRemotePV(SpacecraftState[] states)`	Get emitting satellite position/velocity provider.
`protected FieldPVCoordinatesProvider<Gradient>`	AbstractInterSatellitesMeasurement.`getRemotePV(SpacecraftState[] states, int freeParameters)`	Get emitting satellite position/velocity provider.
`protected abstract PVCoordinatesProvider`	AbstractOnBoardMeasurement.`getRemotePV(SpacecraftState[] states)`	Get emitting satellite position/velocity provider.
`protected abstract FieldPVCoordinatesProvider<Gradient>`	AbstractOnBoardMeasurement.`getRemotePV(SpacecraftState[] states, int freeParameters)`	Get emitting satellite position/velocity provider.
`protected PVCoordinatesProvider`	AbstractOneWayGNSSMeasurement.`getRemotePV(SpacecraftState[] states)`	Get emitting satellite position/velocity provider.
`protected FieldPVCoordinatesProvider<Gradient>`	AbstractOneWayGNSSMeasurement.`getRemotePV(SpacecraftState[] states, int freeParameters)`	Get emitting satellite position/velocity provider.
`protected EstimatedMeasurement<InterSatellitesOneWayRangeRate>`	InterSatellitesOneWayRangeRate.`theoreticalEvaluation(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value.
`protected EstimatedMeasurement<InterSatellitesPhase>`	InterSatellitesPhase.`theoreticalEvaluation(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value.
`protected EstimatedMeasurement<OneWayGNSSPhase>`	OneWayGNSSPhase.`theoreticalEvaluation(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value.
`protected EstimatedMeasurement<OneWayGNSSRange>`	OneWayGNSSRange.`theoreticalEvaluation(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value.
`protected EstimatedMeasurement<OneWayGNSSRangeRate>`	OneWayGNSSRangeRate.`theoreticalEvaluation(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value.
`protected EstimatedMeasurement<Phase>`	Phase.`theoreticalEvaluation(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value.
`protected EstimatedMeasurementBase<InterSatellitesOneWayRangeRate>`	InterSatellitesOneWayRangeRate.`theoreticalEvaluationWithoutDerivatives(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value without derivatives.
`protected EstimatedMeasurementBase<InterSatellitesPhase>`	InterSatellitesPhase.`theoreticalEvaluationWithoutDerivatives(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value without derivatives.
`protected EstimatedMeasurementBase<OneWayGNSSPhase>`	OneWayGNSSPhase.`theoreticalEvaluationWithoutDerivatives(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value without derivatives.
`protected EstimatedMeasurementBase<OneWayGNSSRange>`	OneWayGNSSRange.`theoreticalEvaluationWithoutDerivatives(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value without derivatives.
`protected EstimatedMeasurementBase<OneWayGNSSRangeRate>`	OneWayGNSSRangeRate.`theoreticalEvaluationWithoutDerivatives(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value without derivatives.
`protected EstimatedMeasurementBase<Phase>`	Phase.`theoreticalEvaluationWithoutDerivatives(int iteration, int evaluation, SpacecraftState[] states)`	Estimate the theoretical value without derivatives.

Constructors in org.orekit.estimation.measurements.gnss with parameters of type SpacecraftState
Constructor	Description
`OnBoardCommonParametersWithDerivatives(SpacecraftState localState, Map<String,Integer> indices, Gradient localOffset, Gradient localRate, Gradient remoteOffset, Gradient remoteRate, Gradient tauD, TimeStampedFieldPVCoordinates<Gradient> localPV, TimeStampedFieldPVCoordinates<Gradient> remotePV)`	Simple constructor.
`OnBoardCommonParametersWithoutDerivatives(SpacecraftState localState, double localOffset, double localRate, double remoteOffset, double remoteRate, double tauD, TimeStampedPVCoordinates localPV, TimeStampedPVCoordinates remotePV)`	Simple constructor.

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

Methods in org.orekit.estimation.measurements.modifiers with parameters of type SpacecraftState
Modifier and Type	Method	Description
`double`	ParametricModelEffect.`evaluate(GroundStation station, SpacecraftState state)`	Evaluate the parametric model effect.
`protected double`	BaseRangeIonosphericDelayModifier.`rangeErrorIonosphericModel(GroundStation station, SpacecraftState state)`	Compute the measurement error due to Ionosphere.
`double`	BaseRangeTroposphericDelayModifier.`rangeErrorTroposphericModel(GroundStation station, SpacecraftState state)`	Compute the measurement error due to Troposphere.
`protected double`	BaseRangeRateIonosphericDelayModifier.`rangeRateErrorIonosphericModel(GroundStation station, SpacecraftState state)`	Compute the measurement error due to Ionosphere.
`protected double`	RangeRateIonosphericDelayModifier.`rangeRateErrorIonosphericModel(GroundStation station, SpacecraftState state)`	Compute the measurement error due to Ionosphere.
`double`	BaseRangeRateTroposphericDelayModifier.`rangeRateErrorTroposphericModel(GroundStation station, SpacecraftState state)`	Compute the measurement error due to Troposphere.
`double`	RangeRateTroposphericDelayModifier.`rangeRateErrorTroposphericModel(GroundStation station, SpacecraftState state)`	Compute the measurement error due to Troposphere.

Constructors in org.orekit.estimation.measurements.modifiers with parameters of type SpacecraftState
Constructor	Description
`ModifierGradientConverter(SpacecraftState state, int freeStateParameters, AttitudeProvider provider)`	Simple constructor.

Uses of SpacecraftState in org.orekit.estimation.sequential

Methods in org.orekit.estimation.sequential that return SpacecraftState
Modifier and Type	Method	Description
`static SpacecraftState[]`	KalmanEstimatorUtil.`filterRelevant(ObservedMeasurement<?> observedMeasurement, SpacecraftState[] allStates)`	Filter relevant states for a measurement.
`SpacecraftState[]`	KalmanEstimation.`getCorrectedSpacecraftStates()`	Get the corrected spacecraft states.
`SpacecraftState[]`	SemiAnalyticalKalmanModel.`getCorrectedSpacecraftStates()`	Get the corrected spacecraft states.
`SpacecraftState[]`	SemiAnalyticalUnscentedKalmanModel.`getCorrectedSpacecraftStates()`	Get the corrected spacecraft states.
`SpacecraftState[]`	KalmanEstimation.`getPredictedSpacecraftStates()`	Get the predicted spacecraft states.
`SpacecraftState[]`	SemiAnalyticalKalmanModel.`getPredictedSpacecraftStates()`	Get the predicted spacecraft states.
`SpacecraftState[]`	SemiAnalyticalUnscentedKalmanModel.`getPredictedSpacecraftStates()`	Get the predicted spacecraft states.

Methods in org.orekit.estimation.sequential with parameters of type SpacecraftState
Modifier and Type	Method	Description
`static SpacecraftState[]`	KalmanEstimatorUtil.`filterRelevant(ObservedMeasurement<?> observedMeasurement, SpacecraftState[] allStates)`	Filter relevant states for a measurement.
`RealMatrix`	AbstractCovarianceMatrixProvider.`getInitialCovarianceMatrix(SpacecraftState initial)`	Get the initial covariance matrix.
`RealMatrix`	CovarianceMatrixProvider.`getInitialCovarianceMatrix(SpacecraftState initial)`	Get the initial covariance matrix.
`RealMatrix`	ConstantProcessNoise.`getProcessNoiseMatrix(SpacecraftState previous, SpacecraftState current)`	Get the process noise matrix between previous and current states.
`RealMatrix`	CovarianceMatrixProvider.`getProcessNoiseMatrix(SpacecraftState previous, SpacecraftState current)`	Get the process noise matrix between previous and current states.
`RealMatrix`	UnivariateProcessNoise.`getProcessNoiseMatrix(SpacecraftState previous, SpacecraftState current)`	Get the process noise matrix between previous and current states.
`void`	SemiAnalyticalMeasurementHandler.`init(SpacecraftState s0, AbsoluteDate t)`	Initialize step handler at the start of a propagation.
`void`	SemiAnalyticalKalmanModel.`initializeShortPeriodicTerms(SpacecraftState meanState)`	Initialize the short periodic terms for the Kalman Filter.
`void`	SemiAnalyticalProcess.`initializeShortPeriodicTerms(SpacecraftState meanState)`	Initialize the short periodic terms for the Kalman Filter.
`void`	SemiAnalyticalUnscentedKalmanModel.`initializeShortPeriodicTerms(SpacecraftState meanState)`	Initialize the short periodic terms for the Kalman Filter.
`void`	SemiAnalyticalKalmanModel.`updateNominalSpacecraftState(SpacecraftState nominal)`	Update the nominal spacecraft state.
`void`	SemiAnalyticalProcess.`updateNominalSpacecraftState(SpacecraftState nominal)`	Update the nominal spacecraft state.
`void`	SemiAnalyticalUnscentedKalmanModel.`updateNominalSpacecraftState(SpacecraftState nominal)`	Update the nominal spacecraft state.
`void`	SemiAnalyticalKalmanModel.`updateShortPeriods(SpacecraftState state)`	Update the DSST short periodic terms.
`void`	SemiAnalyticalProcess.`updateShortPeriods(SpacecraftState state)`	Update the DSST short periodic terms.
`void`	SemiAnalyticalUnscentedKalmanModel.`updateShortPeriods(SpacecraftState state)`	Update the DSST short periodic terms.

Uses of SpacecraftState in org.orekit.files.ccsds.ndm.adm.aem

Methods in org.orekit.files.ccsds.ndm.adm.aem with parameters of type SpacecraftState
Modifier and Type	Method	Description
`void`	StreamingAemWriter.SegmentWriter.`finish(SpacecraftState finalState)`	Finalize propagation.
`void`	StreamingAemWriter.SegmentWriter.`handleStep(SpacecraftState currentState)`	Handle the current step.
`void`	StreamingAemWriter.SegmentWriter.`init(SpacecraftState s0, AbsoluteDate t, double step)`	Initialize step handler at the start of a propagation.

Uses of SpacecraftState in org.orekit.files.ccsds.ndm.odm.ocm

Methods in org.orekit.files.ccsds.ndm.odm.ocm with parameters of type SpacecraftState
Modifier and Type	Method	Description
`void`	StreamingOcmWriter.BlockWriter.`finish(SpacecraftState finalState)`	Finalize propagation.
`void`	StreamingOcmWriter.BlockWriter.`handleStep(SpacecraftState currentState)`	Handle the current step.
`void`	StreamingOcmWriter.BlockWriter.`init(SpacecraftState s0, AbsoluteDate t, double step)`	Initialize step handler at the start of a propagation.

Uses of SpacecraftState in org.orekit.files.ccsds.ndm.odm.oem

Methods in org.orekit.files.ccsds.ndm.odm.oem with parameters of type SpacecraftState
Modifier and Type	Method	Description
`void`	StreamingOemWriter.SegmentWriter.`finish(SpacecraftState finalState)`	Finalize propagation.
`void`	StreamingOemWriter.SegmentWriter.`handleStep(SpacecraftState currentState)`	Handle the current step.
`void`	StreamingOemWriter.SegmentWriter.`init(SpacecraftState s0, AbsoluteDate t, double step)`	Initialize step handler at the start of a propagation.

Uses of SpacecraftState in org.orekit.files.ccsds.ndm.odm.omm

Methods in org.orekit.files.ccsds.ndm.odm.omm that return SpacecraftState
Modifier and Type	Method	Description
`SpacecraftState`	Omm.`generateSpacecraftState()`	Generate spacecraft state from the `CartesianOrbit` generated by generateCartesianOrbit.

Uses of SpacecraftState in org.orekit.files.ccsds.ndm.odm.opm

Methods in org.orekit.files.ccsds.ndm.odm.opm that return SpacecraftState
Modifier and Type	Method	Description
`SpacecraftState`	Opm.`generateSpacecraftState()`	Generate spacecraft state from the `CartesianOrbit` generated by generateCartesianOrbit.

Uses of SpacecraftState in org.orekit.files.general

Methods in org.orekit.files.general that return SpacecraftState
Modifier and Type	Method	Description
`SpacecraftState`	EphemerisSegmentPropagator.`getInitialState()`

Methods in org.orekit.files.general with parameters of type SpacecraftState
Modifier and Type	Method	Description
`void`	EphemerisSegmentPropagator.`resetInitialState(SpacecraftState state)`
`protected void`	EphemerisSegmentPropagator.`resetIntermediateState(SpacecraftState state, boolean forward)`

Method parameters in org.orekit.files.general with type arguments of type SpacecraftState
Modifier and Type	Method	Description
`OrekitAttitudeEphemerisFile.OrekitAttitudeEphemerisSegment`	OrekitAttitudeEphemerisFile.OrekitSatelliteAttitudeEphemeris.`addNewSegment(List<SpacecraftState> states, String interpolationMethod, int interpolationSamples, AngularDerivativesFilter availableDerivatives)`	Injects pre-computed satellite states into this attitude ephemeris file object, returning the generated `OrekitAttitudeEphemerisFile.OrekitAttitudeEphemerisSegment` that has been stored internally.
`OrekitEphemerisFile.OrekitEphemerisSegment`	OrekitEphemerisFile.OrekitSatelliteEphemeris.`addNewSegment(List<SpacecraftState> states)`	Injects pre-computed satellite states into this ephemeris file object, returning the generated `OrekitEphemerisFile.OrekitEphemerisSegment` that has been stored internally.
`OrekitEphemerisFile.OrekitEphemerisSegment`	OrekitEphemerisFile.OrekitSatelliteEphemeris.`addNewSegment(List<SpacecraftState> states, int interpolationSampleSize)`	Injects pre-computed satellite states into this ephemeris file object, returning the generated `OrekitEphemerisFile.OrekitEphemerisSegment` that has been stored internally.
`OrekitEphemerisFile.OrekitEphemerisSegment`	OrekitEphemerisFile.OrekitSatelliteEphemeris.`addNewSegment(List<SpacecraftState> states, CelestialBody body, int interpolationSampleSize)`	Injects pre-computed satellite states into this ephemeris file object, returning the generated `OrekitEphemerisFile.OrekitEphemerisSegment` that has been stored internally.
`OrekitEphemerisFile.OrekitEphemerisSegment`	OrekitEphemerisFile.OrekitSatelliteEphemeris.`addNewSegment(List<SpacecraftState> states, CelestialBody body, int interpolationSampleSize, TimeScale timeScale)`	Injects pre-computed satellite states into this ephemeris file object, returning the generated `OrekitEphemerisFile.OrekitEphemerisSegment` that has been stored internally.

Uses of SpacecraftState in org.orekit.files.ilrs

Methods in org.orekit.files.ilrs with parameters of type SpacecraftState
Modifier and Type	Method	Description
`void`	StreamingCpfWriter.Segment.`finish(SpacecraftState finalState)`	Finalize propagation.
`void`	StreamingCpfWriter.Segment.`handleStep(SpacecraftState currentState)`	Handle the current step.

Uses of SpacecraftState in org.orekit.forces

Methods in org.orekit.forces with parameters of type SpacecraftState
Modifier and Type	Method	Description
`Vector3D`	ForceModel.`acceleration(SpacecraftState s, double[] parameters)`	Compute acceleration.
`default void`	ForceModel.`addContribution(SpacecraftState s, TimeDerivativesEquations adder)`	Compute the contribution of the force model to the perturbing acceleration.
`Vector3D`	BoxAndSolarArraySpacecraft.`dragAcceleration(SpacecraftState state, double density, Vector3D relativeVelocity, double[] parameters)`	Compute the acceleration due to drag.
`Vector3D`	FixedPanel.`getNormal(SpacecraftState state)`	Get panel normal in spacecraft frame.
`abstract Vector3D`	Panel.`getNormal(SpacecraftState state)`	Get panel normal in spacecraft frame.
`Vector3D`	PointingPanel.`getNormal(SpacecraftState state)`	Get panel normal in spacecraft frame.
`Vector3D`	SlewingPanel.`getNormal(SpacecraftState state)`	Get panel normal in spacecraft frame.
`default void`	ForceModel.`init(SpacecraftState initialState, AbsoluteDate target)`	Initialize the force model at the start of propagation.
`Vector3D`	BoxAndSolarArraySpacecraft.`radiationPressureAcceleration(SpacecraftState state, Vector3D flux, double[] parameters)`	Compute the acceleration due to radiation pressure.

Uses of SpacecraftState in org.orekit.forces.drag

Methods in org.orekit.forces.drag with parameters of type SpacecraftState
Modifier and Type	Method	Description
`Vector3D`	DragForce.`acceleration(SpacecraftState s, double[] parameters)`	Compute acceleration.
`Vector3D`	TimeSpanDragForce.`acceleration(SpacecraftState s, double[] parameters)`	Deprecated. Compute acceleration.
`Vector3D`	DragSensitive.`dragAcceleration(SpacecraftState state, double density, Vector3D relativeVelocity, double[] parameters)`	Compute the acceleration due to drag.
`Vector3D`	IsotropicDrag.`dragAcceleration(SpacecraftState state, double density, Vector3D relativeVelocity, double[] parameters)`	Compute the acceleration due to drag.

Uses of SpacecraftState in org.orekit.forces.empirical

Methods in org.orekit.forces.empirical with parameters of type SpacecraftState
Modifier and Type	Method	Description
`Vector3D`	ParametricAcceleration.`acceleration(SpacecraftState state, double[] parameters)`	Compute acceleration.
`Vector3D`	TimeSpanParametricAcceleration.`acceleration(SpacecraftState state, double[] parameters)`	Compute acceleration.
`default void`	AccelerationModel.`init(SpacecraftState initialState, AbsoluteDate target)`	Initialize the acceleration model at the start of the propagation.
`void`	HarmonicAccelerationModel.`init(SpacecraftState initialState, AbsoluteDate target)`	Initialize the acceleration model at the start of the propagation.
`void`	ParametricAcceleration.`init(SpacecraftState initialState, AbsoluteDate target)`	Initialize the force model at the start of propagation.
`void`	PolynomialAccelerationModel.`init(SpacecraftState initialState, AbsoluteDate target)`	Initialize the acceleration model at the start of the propagation.
`void`	TimeSpanParametricAcceleration.`init(SpacecraftState initialState, AbsoluteDate target)`	Initialize the force model at the start of propagation.
`double`	AccelerationModel.`signedAmplitude(SpacecraftState state, double[] parameters)`	Compute the signed amplitude of the acceleration.
`double`	HarmonicAccelerationModel.`signedAmplitude(SpacecraftState state, double[] parameters)`	Compute the signed amplitude of the acceleration.
`double`	PolynomialAccelerationModel.`signedAmplitude(SpacecraftState state, double[] parameters)`	Compute the signed amplitude of the acceleration.

Uses of SpacecraftState in org.orekit.forces.gravity

Methods in org.orekit.forces.gravity with parameters of type SpacecraftState
Modifier and Type	Method	Description
`Vector3D`	DeSitterRelativity.`acceleration(SpacecraftState s, double[] parameters)`	Compute acceleration.
`Vector3D`	HolmesFeatherstoneAttractionModel.`acceleration(SpacecraftState s, double[] parameters)`	Compute acceleration.
`Vector3D`	J2OnlyPerturbation.`acceleration(SpacecraftState state, double[] parameters)`	Compute acceleration.
`Vector3D`	LenseThirringRelativity.`acceleration(SpacecraftState s, double[] parameters)`	Compute acceleration.
`Vector3D`	NewtonianAttraction.`acceleration(SpacecraftState s, double[] parameters)`	Compute acceleration.
`Vector3D`	OceanTides.`acceleration(SpacecraftState s, double[] parameters)`	Compute acceleration.
`Vector3D`	Relativity.`acceleration(SpacecraftState s, double[] parameters)`	Compute acceleration.
`Vector3D`	SingleBodyAbsoluteAttraction.`acceleration(SpacecraftState s, double[] parameters)`	Compute acceleration.
`Vector3D`	SingleBodyRelativeAttraction.`acceleration(SpacecraftState s, double[] parameters)`	Compute acceleration.
`Vector3D`	SolidTides.`acceleration(SpacecraftState s, double[] parameters)`	Compute acceleration.
`Vector3D`	ThirdBodyAttraction.`acceleration(SpacecraftState s, double[] parameters)`	Compute acceleration.
`void`	NewtonianAttraction.`addContribution(SpacecraftState s, TimeDerivativesEquations adder)`	Compute the contribution of the force model to the perturbing acceleration.
`double[]`	ThirdBodyAttractionEpoch.`getDerivativesToEpoch(SpacecraftState s, double[] parameters)`	Compute derivatives of the state w.r.t epoch.

Uses of SpacecraftState in org.orekit.forces.inertia

Methods in org.orekit.forces.inertia with parameters of type SpacecraftState
Modifier and Type	Method	Description
`Vector3D`	InertialForces.`acceleration(SpacecraftState s, double[] parameters)`	Compute acceleration.

Uses of SpacecraftState in org.orekit.forces.maneuvers

Methods in org.orekit.forces.maneuvers that return SpacecraftState
Modifier and Type	Method	Description
`SpacecraftState`	SmallManeuverAnalyticalModel.`apply(SpacecraftState state1)`	Compute the effect of the maneuver on a spacecraft state.

Methods in org.orekit.forces.maneuvers with parameters of type SpacecraftState
Modifier and Type	Method	Description
`Vector3D`	Maneuver.`acceleration(SpacecraftState s, double[] parameters)`
`void`	Maneuver.`addContribution(SpacecraftState s, TimeDerivativesEquations adder)`	Compute the contribution of the force model to the perturbing acceleration.
`SpacecraftState`	SmallManeuverAnalyticalModel.`apply(SpacecraftState state1)`	Compute the effect of the maneuver on a spacecraft state.
`double`	ImpulseManeuver.`g(SpacecraftState s)`	Compute the value of the switching function.
`void`	ImpulseManeuver.`init(SpacecraftState s0, AbsoluteDate t)`	Initialize event handler at the start of a propagation.
`void`	Maneuver.`init(SpacecraftState initialState, AbsoluteDate target)`	Initialize the force model at the start of propagation.
`boolean`	ConstantThrustManeuver.`isFiring(SpacecraftState s)`	Check if maneuvering is on.

Constructors in org.orekit.forces.maneuvers with parameters of type SpacecraftState
Constructor	Description
`SmallManeuverAnalyticalModel(SpacecraftState state0, Vector3D dV, double isp)`	Build a maneuver defined in spacecraft frame with default orbit type.
`SmallManeuverAnalyticalModel(SpacecraftState state0, Frame frame, Vector3D dV, double isp)`	Build a maneuver defined in user-specified frame.
`SmallManeuverAnalyticalModel(SpacecraftState state0, OrbitType orbitType, Vector3D dV, double isp)`	Build a maneuver defined in spacecraft frame.
`SmallManeuverAnalyticalModel(SpacecraftState state0, OrbitType orbitType, Frame frame, Vector3D dV, double isp)`	Build a maneuver defined in user-specified frame.

Uses of SpacecraftState in org.orekit.forces.maneuvers.jacobians

Methods in org.orekit.forces.maneuvers.jacobians that return SpacecraftState
Modifier and Type	Method	Description
`SpacecraftState`	TriggerDate.`resetState(SpacecraftState state)`	Reset state as a maneuver triggers.

Methods in org.orekit.forces.maneuvers.jacobians with parameters of type SpacecraftState
Modifier and Type	Method	Description
`CombinedDerivatives`	MassDepletionDelay.`combinedDerivatives(SpacecraftState state)`	Compute the derivatives related to the additional state (and optionally main state increments).
`double[]`	Duration.`getAdditionalState(SpacecraftState state)`	Get the additional state.
`double[]`	MedianDate.`getAdditionalState(SpacecraftState state)`	Get the additional state.
`double[]`	TriggerDate.`getAdditionalState(SpacecraftState state)`	Get the additional state.
`void`	MassDepletionDelay.`init(SpacecraftState initialState, AbsoluteDate target)`	Initialize the generator at the start of propagation.
`void`	TriggerDate.`init(SpacecraftState initialState, AbsoluteDate target)`	Initialize the additional state provider at the start of propagation.
`void`	TriggerDate.`maneuverTriggered(SpacecraftState state, boolean start)`	Observe a maneuver trigger.
`SpacecraftState`	TriggerDate.`resetState(SpacecraftState state)`	Reset state as a maneuver triggers.
`boolean`	Duration.`yields(SpacecraftState state)`	Check if this provider should yield so another provider has an opportunity to add missing parts.
`boolean`	MedianDate.`yields(SpacecraftState state)`	Check if this provider should yield so another provider has an opportunity to add missing parts.
`boolean`	TriggerDate.`yields(SpacecraftState state)`	Check if this provider should yield so another provider has an opportunity to add missing parts.

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

Methods in org.orekit.forces.maneuvers.propulsion with parameters of type SpacecraftState
Modifier and Type	Method	Description
`Vector3D`	PropulsionModel.`getAcceleration(SpacecraftState s, Attitude maneuverAttitude, double[] parameters)`	Get the acceleration of the spacecraft during maneuver and in maneuver frame.
`default Vector3D`	ThrustPropulsionModel.`getAcceleration(SpacecraftState s, Attitude maneuverAttitude, double[] parameters)`	Get the acceleration of the spacecraft during maneuver and in maneuver frame.
`default Vector3D`	ThrustPropulsionModel.`getDirection(SpacecraftState s)`	Get the thrust direction in spacecraft frame.
`double`	AbstractConstantThrustPropulsionModel.`getFlowRate(SpacecraftState s)`	Get the flow rate (kg/s).
`double`	AbstractConstantThrustPropulsionModel.`getFlowRate(SpacecraftState s, double[] parameters)`	Get the flow rate (kg/s).
`double`	ProfileThrustPropulsionModel.`getFlowRate(SpacecraftState s)`	Get the flow rate (kg/s).
`double`	ProfileThrustPropulsionModel.`getFlowRate(SpacecraftState s, double[] parameters)`	Get the flow rate (kg/s).
`double`	ThrustPropulsionModel.`getFlowRate(SpacecraftState s)`	Get the flow rate (kg/s).
`double`	ThrustPropulsionModel.`getFlowRate(SpacecraftState s, double[] parameters)`	Get the flow rate (kg/s).
`default double`	ThrustPropulsionModel.`getIsp(SpacecraftState s)`	Get the specific impulse (s).
`double`	PropulsionModel.`getMassDerivatives(SpacecraftState s, double[] parameters)`	Get the mass derivative (i.e.
`default double`	ThrustPropulsionModel.`getMassDerivatives(SpacecraftState s, double[] parameters)`	Get the mass derivative (i.e.
`Vector3D`	AbstractConstantThrustPropulsionModel.`getThrustVector(SpacecraftState s)`	Get the thrust vector in spacecraft frame (N).
`Vector3D`	AbstractConstantThrustPropulsionModel.`getThrustVector(SpacecraftState s, double[] parameters)`	Get the thrust vector in spacecraft frame (N).
`Vector3D`	ProfileThrustPropulsionModel.`getThrustVector(SpacecraftState s)`	Get the thrust vector in spacecraft frame (N).
`Vector3D`	ProfileThrustPropulsionModel.`getThrustVector(SpacecraftState s, double[] parameters)`	Get the thrust vector in spacecraft frame (N).
`Vector3D`	ThrustPropulsionModel.`getThrustVector(SpacecraftState s)`	Get the thrust vector in spacecraft frame (N).
`Vector3D`	ThrustPropulsionModel.`getThrustVector(SpacecraftState s, double[] parameters)`	Get the thrust vector in spacecraft frame (N).
`default void`	PropulsionModel.`init(SpacecraftState initialState, AbsoluteDate target)`	Initialization method.

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

Methods in org.orekit.forces.maneuvers.trigger that return SpacecraftState
Modifier and Type	Method	Description
`protected SpacecraftState`	AbstractManeuverTriggers.`applyResetters(SpacecraftState state)`	Apply resetters.
`SpacecraftState`	ManeuverTriggersResetter.`resetState(SpacecraftState state)`	Reset state as a maneuver triggers.

Methods in org.orekit.forces.maneuvers.trigger with parameters of type SpacecraftState
Modifier and Type	Method	Description
`protected SpacecraftState`	AbstractManeuverTriggers.`applyResetters(SpacecraftState state)`	Apply resetters.
`void`	AbstractManeuverTriggers.`init(SpacecraftState initialState, AbsoluteDate target)`	Initialization method called at propagation start.
`void`	IntervalEventTrigger.`init(SpacecraftState initialState, AbsoluteDate target)`	Initialization method called at propagation start.
`default void`	ManeuverTriggers.`init(SpacecraftState initialState, AbsoluteDate target)`	Initialization method called at propagation start.
`default void`	ManeuverTriggersResetter.`init(SpacecraftState initialState, AbsoluteDate target)`	Initialization method called at propagation start.
`void`	StartStopEventsTrigger.`init(SpacecraftState initialState, AbsoluteDate target)`	Initialization method called at propagation start.
`protected void`	AbstractManeuverTriggers.`initializeResetters(SpacecraftState initialState, AbsoluteDate target)`	Initialize resetters.
`protected abstract boolean`	AbstractManeuverTriggers.`isFiringOnInitialState(SpacecraftState initialState, boolean isForward)`	Method to check if the thruster is firing on initialization.
`protected boolean`	IntervalEventTrigger.`isFiringOnInitialState(SpacecraftState initialState, boolean isForward)`	Method to check if the thruster is firing on initialization.
`protected boolean`	StartStopEventsTrigger.`isFiringOnInitialState(SpacecraftState initialState, boolean isForward)`	Method to check if the thruster is firing on initialization.
`void`	ManeuverTriggersResetter.`maneuverTriggered(SpacecraftState state, boolean start)`	Observe a maneuver trigger.
`protected void`	AbstractManeuverTriggers.`notifyResetters(SpacecraftState state, boolean start)`	Notify resetters.
`SpacecraftState`	ManeuverTriggersResetter.`resetState(SpacecraftState state)`	Reset state as a maneuver triggers.

Uses of SpacecraftState in org.orekit.forces.radiation

Methods in org.orekit.forces.radiation with parameters of type SpacecraftState
Modifier and Type	Method	Description
`Vector3D`	ECOM2.`acceleration(SpacecraftState s, double[] parameters)`	Compute acceleration.
`Vector3D`	KnockeRediffusedForceModel.`acceleration(SpacecraftState s, double[] parameters)`	Compute acceleration.
`Vector3D`	RadiationPressureModel.`acceleration(SpacecraftState s, double[] parameters)`	Compute acceleration.
`Vector3D`	SolarRadiationPressure.`acceleration(SpacecraftState s, double[] parameters)`	Compute acceleration.
`Vector3D`	KnockeRediffusedForceModel.`computeElementaryFlux(SpacecraftState state, Vector3D elementCenter, Vector3D sunPosition, OneAxisEllipsoid earth, double elementArea)`	Compute elementary rediffused flux on satellite.
`Vector3D`	AbstractLightFluxModel.`getLightFluxVector(SpacecraftState state)`	Get the light flux vector in the state's frame.
`Vector3D`	LightFluxModel.`getLightFluxVector(SpacecraftState state)`	Get the light flux vector in the state's frame.
`double`	SolarRadiationPressure.`getLightingRatio(SpacecraftState state)`	Get the lighting ratio ([0-1]).
`Vector3D`	IsotropicRadiationClassicalConvention.`radiationPressureAcceleration(SpacecraftState state, Vector3D flux, double[] parameters)`	Compute the acceleration due to radiation pressure.
`Vector3D`	IsotropicRadiationCNES95Convention.`radiationPressureAcceleration(SpacecraftState state, Vector3D flux, double[] parameters)`	Compute the acceleration due to radiation pressure.
`Vector3D`	IsotropicRadiationSingleCoefficient.`radiationPressureAcceleration(SpacecraftState state, Vector3D flux, double[] parameters)`	Compute the acceleration due to radiation pressure.
`Vector3D`	RadiationSensitive.`radiationPressureAcceleration(SpacecraftState state, Vector3D flux, double[] parameters)`	Compute the acceleration due to radiation pressure.

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

Methods in org.orekit.models.earth.ionosphere with parameters of type SpacecraftState
Modifier and Type	Method	Description
`double`	EstimatedIonosphericModel.`pathDelay(SpacecraftState state, TopocentricFrame baseFrame, double frequency, double[] parameters)`	Calculates the ionospheric path delay for the signal path from a ground station to a satellite.
`double`	GlobalIonosphereMapModel.`pathDelay(SpacecraftState state, TopocentricFrame baseFrame, double frequency, double[] parameters)`
`double`	IonosphericModel.`pathDelay(SpacecraftState state, TopocentricFrame baseFrame, double frequency, double[] parameters)`	Calculates the ionospheric path delay for the signal path from a ground station to a satellite.
`double`	KlobucharIonoModel.`pathDelay(SpacecraftState state, TopocentricFrame baseFrame, double frequency, double[] parameters)`	Calculates the ionospheric path delay for the signal path from a ground station to a satellite.
`double`	NeQuickModel.`pathDelay(SpacecraftState state, TopocentricFrame baseFrame, double frequency, double[] parameters)`
`double`	SsrVtecIonosphericModel.`pathDelay(SpacecraftState state, TopocentricFrame baseFrame, double frequency, double[] parameters)`	Calculates the ionospheric path delay for the signal path from a ground station to a satellite.

Uses of SpacecraftState in org.orekit.orbits

Methods in org.orekit.orbits with parameters of type SpacecraftState
Modifier and Type	Method	Description
`PVCoordinates`	LibrationOrbit.`getManifolds(SpacecraftState s, boolean isStable)`	Return a manifold direction from one position on a libration Orbit.

Uses of SpacecraftState in org.orekit.propagation

Methods in org.orekit.propagation that return SpacecraftState
Modifier and Type	Method	Description
`SpacecraftState`	SpacecraftState.`addAdditionalState(String name, double... value)`	Add an additional state.
`SpacecraftState`	SpacecraftState.`addAdditionalStateDerivative(String name, double... value)`	Add an additional state derivative.
`abstract SpacecraftState`	AbstractStateModifier.`change(SpacecraftState state)`	Change main state.
`SpacecraftState`	AbstractPropagator.`getInitialState()`	Get the propagator initial state.
`SpacecraftState`	Propagator.`getInitialState()`	Get the propagator initial state.
`SpacecraftState`	SpacecraftStateInterpolator.`interpolate(AbsoluteDate interpolationDate, Collection<SpacecraftState> sample)`	Get an interpolated instance.
`protected SpacecraftState`	SpacecraftStateInterpolator.`interpolate(AbstractTimeInterpolator.InterpolationData interpolationData)`	Interpolate instance from given interpolation data.
`SpacecraftState`	AbstractPropagator.`propagate(AbsoluteDate target)`	Propagate towards a target date.
`SpacecraftState`	Propagator.`propagate(AbsoluteDate target)`	Propagate towards a target date.
`SpacecraftState`	Propagator.`propagate(AbsoluteDate start, AbsoluteDate target)`	Propagate from a start date towards a target date.
`SpacecraftState`	SpacecraftState.`shiftedBy(double dt)`	Get a time-shifted state.
`SpacecraftState`	FieldSpacecraftState.`toSpacecraftState()`	To convert a FieldSpacecraftState instance into a SpacecraftState instance.
`SpacecraftState`	AbstractStateModifier.`update(SpacecraftState state)`	Update a state.
`default SpacecraftState`	AdditionalStateProvider.`update(SpacecraftState state)`	Update a state.
`protected SpacecraftState`	AbstractPropagator.`updateAdditionalStates(SpacecraftState original)`	Update state by adding all additional states.
`protected SpacecraftState`	AbstractPropagator.`updateUnmanagedStates(SpacecraftState original)`	Update state by adding unmanaged states.

Methods in org.orekit.propagation that return types with arguments of type SpacecraftState
Modifier and Type	Method	Description
`List<SpacecraftState>`	PropagatorsParallelizer.`propagate(AbsoluteDate start, AbsoluteDate target)`	Propagate from a start date towards a target date.

Methods in org.orekit.propagation with parameters of type SpacecraftState
Modifier and Type	Method	Description
`abstract SpacecraftState`	AbstractStateModifier.`change(SpacecraftState state)`	Change main state.
`void`	SpacecraftState.`ensureCompatibleAdditionalStates(SpacecraftState state)`	Check if two instances have the same set of additional states available.
`double[]`	AbstractStateModifier.`getAdditionalState(SpacecraftState state)`	Get the additional state.
`double[]`	AdditionalStateProvider.`getAdditionalState(SpacecraftState state)`	Get the additional state.
`double[]`	StateCovarianceMatrixProvider.`getAdditionalState(SpacecraftState state)`	Get the additional state.
`protected double[][]`	AbstractMatricesHarvester.`getConversionJacobian(SpacecraftState state)`	Get the conversion Jacobian between state parameters and parameters used for derivatives.
`RealMatrix`	AbstractMatricesHarvester.`getParametersJacobian(SpacecraftState state)`	Get the Jacobian with respect to propagation parameters.
`RealMatrix`	MatricesHarvester.`getParametersJacobian(SpacecraftState state)`	Get the Jacobian with respect to propagation parameters.
`StateCovariance`	StateCovarianceMatrixProvider.`getStateCovariance(SpacecraftState state)`	Get the state covariance in the same frame/local orbital frame, orbit type and position angle as the initial covariance.
`StateCovariance`	StateCovarianceMatrixProvider.`getStateCovariance(SpacecraftState state, Frame frame)`	Get the state covariance expressed in a given frame.
`StateCovariance`	StateCovarianceMatrixProvider.`getStateCovariance(SpacecraftState state, OrbitType orbitType, PositionAngleType angleType)`	Get the state covariance expressed in a given orbit type.
`RealMatrix`	AbstractMatricesHarvester.`getStateTransitionMatrix(SpacecraftState state)`	Extract state transition matrix from state.
`RealMatrix`	MatricesHarvester.`getStateTransitionMatrix(SpacecraftState state)`	Extract state transition matrix from state.
`default void`	AdditionalStateProvider.`init(SpacecraftState initialState, AbsoluteDate target)`	Initialize the additional state provider at the start of propagation.
`void`	StateCovarianceMatrixProvider.`init(SpacecraftState initialState, AbsoluteDate target)`	Initialize the additional state provider at the start of propagation.
`void`	AbstractPropagator.`resetInitialState(SpacecraftState state)`	Reset the propagator initial state.
`void`	Propagator.`resetInitialState(SpacecraftState state)`	Reset the propagator initial state.
`void`	AbstractMatricesHarvester.`setReferenceState(SpacecraftState reference)`	Set up reference state.
`void`	MatricesHarvester.`setReferenceState(SpacecraftState reference)`	Set up reference state.
`protected void`	AbstractPropagator.`stateChanged(SpacecraftState state)`	Notify about a state change.
`SpacecraftState`	AbstractStateModifier.`update(SpacecraftState state)`	Update a state.
`default SpacecraftState`	AdditionalStateProvider.`update(SpacecraftState state)`	Update a state.
`protected SpacecraftState`	AbstractPropagator.`updateAdditionalStates(SpacecraftState original)`	Update state by adding all additional states.
`protected SpacecraftState`	AbstractPropagator.`updateUnmanagedStates(SpacecraftState original)`	Update state by adding unmanaged states.
`default boolean`	AdditionalStateProvider.`yields(SpacecraftState state)`	Check if this provider should yield so another provider has an opportunity to add missing parts.
`boolean`	StateCovarianceMatrixProvider.`yields(SpacecraftState 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 SpacecraftState
Modifier and Type	Method	Description
`static void`	SpacecraftStateInterpolator.`checkSampleAndInterpolatorConsistency(List<SpacecraftState> sample, boolean orbitInterpolatorIsPresent, boolean absPVInterpolatorIsPresent)`	Check that an interpolator exist for given sample state definition.
`static void`	SpacecraftStateInterpolator.`checkStatesDefinitionsConsistency(List<SpacecraftState> states)`	Check that all state are either orbit defined or based on absolute position-velocity-acceleration.
`SpacecraftState`	SpacecraftStateInterpolator.`interpolate(AbsoluteDate interpolationDate, Collection<SpacecraftState> sample)`	Get an interpolated instance.

Constructors in org.orekit.propagation with parameters of type SpacecraftState
Constructor	Description
`FieldSpacecraftState(Field<T> field, SpacecraftState state)`	Convert a `FieldSpacecraftState`.

Uses of SpacecraftState in org.orekit.propagation.analytical

Methods in org.orekit.propagation.analytical that return SpacecraftState
Modifier and Type	Method	Description
`protected SpacecraftState`	AbstractAnalyticalPropagator.`acceptStep(OrekitStepInterpolator interpolator, AbsoluteDate target)`	Accept a step, triggering events and step handlers.
`SpacecraftState`	AdapterPropagator.DifferentialEffect.`apply(SpacecraftState original)`	Apply the effect to a `spacecraft state`.
`SpacecraftState`	J2DifferentialEffect.`apply(SpacecraftState state1)`	Apply the effect to a `spacecraft state`.
`protected SpacecraftState`	AbstractAnalyticalPropagator.`basicPropagate(AbsoluteDate date)`	Propagate an orbit without any fancy features.
`protected SpacecraftState`	AdapterPropagator.`basicPropagate(AbsoluteDate date)`	Propagate an orbit without any fancy features.
`protected SpacecraftState`	AggregateBoundedPropagator.`basicPropagate(AbsoluteDate date)`
`SpacecraftState`	Ephemeris.`basicPropagate(AbsoluteDate date)`	Propagate an orbit without any fancy features.
`SpacecraftState`	AdapterPropagator.`getInitialState()`	Get the propagator initial state.
`SpacecraftState`	AggregateBoundedPropagator.`getInitialState()`
`SpacecraftState`	Ephemeris.`getInitialState()`	Get the propagator initial state.
`SpacecraftState`	AbstractAnalyticalPropagator.`propagate(AbsoluteDate start, AbsoluteDate target)`	Propagate from a start date towards a target date.

Methods in org.orekit.propagation.analytical that return types with arguments of type SpacecraftState
Modifier and Type	Method	Description
`TimeInterpolator<SpacecraftState>`	Ephemeris.`getStateInterpolator()`	Get state interpolator.

Methods in org.orekit.propagation.analytical with parameters of type SpacecraftState
Modifier and Type	Method	Description
`SpacecraftState`	AdapterPropagator.DifferentialEffect.`apply(SpacecraftState original)`	Apply the effect to a `spacecraft state`.
`SpacecraftState`	J2DifferentialEffect.`apply(SpacecraftState state1)`	Apply the effect to a `spacecraft state`.
`double[]`	AbstractAnalyticalMatricesHarvester.`getAdditionalState(SpacecraftState state)`	Get the additional state.
`RealMatrix`	AbstractAnalyticalMatricesHarvester.`getParametersJacobian(SpacecraftState state)`	Get the Jacobian with respect to propagation parameters.
`RealMatrix`	AbstractAnalyticalMatricesHarvester.`getStateTransitionMatrix(SpacecraftState state)`	Extract state transition matrix from state.
`void`	AdapterPropagator.`resetInitialState(SpacecraftState state)`	Reset the propagator initial state.
`void`	AggregateBoundedPropagator.`resetInitialState(SpacecraftState state)`
`void`	BrouwerLyddanePropagator.`resetInitialState(SpacecraftState state)`	Reset the propagator initial state.
`void`	BrouwerLyddanePropagator.`resetInitialState(SpacecraftState state, PropagationType stateType)`	Reset the propagator initial state.
`void`	BrouwerLyddanePropagator.`resetInitialState(SpacecraftState state, PropagationType stateType, double epsilon, int maxIterations)`	Reset the propagator initial state.
`void`	EcksteinHechlerPropagator.`resetInitialState(SpacecraftState state)`	Reset the propagator initial state.
`void`	EcksteinHechlerPropagator.`resetInitialState(SpacecraftState state, PropagationType stateType)`	Reset the propagator initial state.
`void`	EcksteinHechlerPropagator.`resetInitialState(SpacecraftState state, PropagationType stateType, double epsilon, int maxIterations)`	Reset the propagator initial state.
`void`	Ephemeris.`resetInitialState(SpacecraftState state)`	Try (and fail) to reset the initial state.
`void`	KeplerianPropagator.`resetInitialState(SpacecraftState state)`	Reset the propagator initial state.
`protected abstract void`	AbstractAnalyticalPropagator.`resetIntermediateState(SpacecraftState state, boolean forward)`	Reset an intermediate state.
`protected void`	AdapterPropagator.`resetIntermediateState(SpacecraftState state, boolean forward)`	Reset an intermediate state.
`protected void`	AggregateBoundedPropagator.`resetIntermediateState(SpacecraftState state, boolean forward)`
`protected void`	BrouwerLyddanePropagator.`resetIntermediateState(SpacecraftState state, boolean forward)`	Reset an intermediate state.
`protected void`	BrouwerLyddanePropagator.`resetIntermediateState(SpacecraftState state, boolean forward, double epsilon, int maxIterations)`	Reset an intermediate state.
`protected void`	EcksteinHechlerPropagator.`resetIntermediateState(SpacecraftState state, boolean forward)`	Reset an intermediate state.
`protected void`	EcksteinHechlerPropagator.`resetIntermediateState(SpacecraftState state, boolean forward, double epsilon, int maxIterations)`	Reset an intermediate state.
`protected void`	Ephemeris.`resetIntermediateState(SpacecraftState state, boolean forward)`	Reset an intermediate state.
`protected void`	KeplerianPropagator.`resetIntermediateState(SpacecraftState state, boolean forward)`	Reset an intermediate state.
`void`	AbstractAnalyticalMatricesHarvester.`setReferenceState(SpacecraftState reference)`	Set up reference state.

Method parameters in org.orekit.propagation.analytical with type arguments of type SpacecraftState
Modifier and Type	Method	Description
`static void`	Ephemeris.`checkInputConsistency(List<SpacecraftState> states, TimeInterpolator<SpacecraftState> stateInterpolator, List<StateCovariance> covariances, TimeInterpolator<TimeStampedPair<Orbit,StateCovariance>> covarianceInterpolator)`	Check input consistency between states, covariances and their associated interpolators.
`static void`	Ephemeris.`checkInputConsistency(List<SpacecraftState> states, TimeInterpolator<SpacecraftState> stateInterpolator, List<StateCovariance> covariances, TimeInterpolator<TimeStampedPair<Orbit,StateCovariance>> covarianceInterpolator)`	Check input consistency between states, covariances and their associated interpolators.
`static void`	Ephemeris.`checkStatesAndCovariancesConsistency(List<SpacecraftState> states, List<StateCovariance> covariances)`	Check that given states and covariances are consistent.

Constructors in org.orekit.propagation.analytical with parameters of type SpacecraftState
Constructor	Description
`J2DifferentialEffect(SpacecraftState original, AdapterPropagator.DifferentialEffect directEffect, boolean applyBefore, double referenceRadius, double mu, double j2)`	Simple constructor.
`J2DifferentialEffect(SpacecraftState original, AdapterPropagator.DifferentialEffect directEffect, boolean applyBefore, UnnormalizedSphericalHarmonicsProvider gravityField)`	Simple constructor.

Constructor parameters in org.orekit.propagation.analytical with type arguments of type SpacecraftState
Constructor	Description
`Ephemeris(List<SpacecraftState> states, int interpolationPoints)`	Legacy constructor with tabulated states and default Hermite interpolation.
`Ephemeris(List<SpacecraftState> states, TimeInterpolator<SpacecraftState> stateInterpolator)`	Constructor with tabulated states.
`Ephemeris(List<SpacecraftState> states, TimeInterpolator<SpacecraftState> stateInterpolator)`	Constructor with tabulated states.
`Ephemeris(List<SpacecraftState> states, TimeInterpolator<SpacecraftState> stateInterpolator, List<StateCovariance> covariances, TimeInterpolator<TimeStampedPair<Orbit,StateCovariance>> covarianceInterpolator)`	Constructor with tabulated states and associated covariances.
`Ephemeris(List<SpacecraftState> states, TimeInterpolator<SpacecraftState> stateInterpolator, List<StateCovariance> covariances, TimeInterpolator<TimeStampedPair<Orbit,StateCovariance>> covarianceInterpolator)`	Constructor with tabulated states and associated covariances.
`Ephemeris(List<SpacecraftState> states, TimeInterpolator<SpacecraftState> stateInterpolator, List<StateCovariance> covariances, TimeInterpolator<TimeStampedPair<Orbit,StateCovariance>> covarianceInterpolator, AttitudeProvider attitudeProvider)`	Constructor with tabulated states and associated covariances.
`Ephemeris(List<SpacecraftState> states, TimeInterpolator<SpacecraftState> stateInterpolator, List<StateCovariance> covariances, TimeInterpolator<TimeStampedPair<Orbit,StateCovariance>> covarianceInterpolator, AttitudeProvider attitudeProvider)`	Constructor with tabulated states and associated covariances.
`Ephemeris(List<SpacecraftState> states, TimeInterpolator<SpacecraftState> stateInterpolator, AttitudeProvider attitudeProvider)`	Constructor with tabulated states.
`Ephemeris(List<SpacecraftState> states, TimeInterpolator<SpacecraftState> stateInterpolator, AttitudeProvider attitudeProvider)`	Constructor with tabulated states.

Uses of SpacecraftState in org.orekit.propagation.analytical.gnss

Methods in org.orekit.propagation.analytical.gnss with parameters of type SpacecraftState
Modifier and Type	Method	Description
`double[]`	ClockCorrectionsProvider.`getAdditionalState(SpacecraftState state)`	Get the additional state.
`void`	GLONASSAnalyticalPropagator.`resetInitialState(SpacecraftState state)`	Reset the propagator initial state.
`void`	GNSSPropagator.`resetInitialState(SpacecraftState state)`	Reset the propagator initial state.
`void`	SBASPropagator.`resetInitialState(SpacecraftState state)`	Reset the propagator initial state.
`protected void`	GLONASSAnalyticalPropagator.`resetIntermediateState(SpacecraftState state, boolean forward)`	Reset an intermediate state.
`protected void`	GNSSPropagator.`resetIntermediateState(SpacecraftState state, boolean forward)`	Reset an intermediate state.
`protected void`	SBASPropagator.`resetIntermediateState(SpacecraftState state, boolean forward)`	Reset an intermediate state.

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

Methods in org.orekit.propagation.analytical.intelsat with parameters of type SpacecraftState
Modifier and Type	Method	Description
`void`	IntelsatElevenElementsPropagator.`resetInitialState(SpacecraftState state)`	Reset the propagator initial state.
`protected void`	IntelsatElevenElementsPropagator.`resetIntermediateState(SpacecraftState state, boolean forward)`	Reset an intermediate state.

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

Methods in org.orekit.propagation.analytical.tle with parameters of type SpacecraftState
Modifier and Type	Method	Description
`void`	TLEPropagator.`resetInitialState(SpacecraftState state)`	Reset the propagator initial state.
`protected void`	TLEPropagator.`resetIntermediateState(SpacecraftState state, boolean forward)`	Reset an intermediate state.
`static TLE`	TLE.`stateToTLE(SpacecraftState state, TLE templateTLE, TleGenerationAlgorithm generationAlgorithm)`	Convert Spacecraft State into TLE.

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

Methods in org.orekit.propagation.analytical.tle.generation with parameters of type SpacecraftState
Modifier and Type	Method	Description
`TLE`	FixedPointTleGenerationAlgorithm.`generate(SpacecraftState state, TLE templateTLE)`	Generate a TLE from a given spacecraft state and a template TLE.
`TLE`	LeastSquaresTleGenerationAlgorithm.`generate(SpacecraftState state, TLE templateTLE)`	Generate a TLE from a given spacecraft state and a template TLE.
`TLE`	TleGenerationAlgorithm.`generate(SpacecraftState state, TLE templateTLE)`	Generate a TLE from a given spacecraft state and a template TLE.

Uses of SpacecraftState in org.orekit.propagation.conversion

Methods in org.orekit.propagation.conversion that return SpacecraftState
Modifier and Type	Method	Description
`SpacecraftState`	OsculatingToMeanElementsConverter.`convert()`	Convert an osculating orbit into a mean orbit, in DSST sense.

Methods in org.orekit.propagation.conversion that return types with arguments of type SpacecraftState
Modifier and Type	Method	Description
`protected List<SpacecraftState>`	AbstractPropagatorConverter.`getSample()`	Get the states sample.

Method parameters in org.orekit.propagation.conversion with type arguments of type SpacecraftState
Modifier and Type	Method	Description
`Propagator`	AbstractPropagatorConverter.`convert(List<SpacecraftState> states, boolean positionOnly, String... freeParameters)`	Find the propagator that minimize the mean square error for a sample of `states`.
`Propagator`	AbstractPropagatorConverter.`convert(List<SpacecraftState> states, boolean positionOnly, List<String> freeParameters)`	Find the propagator that minimize the mean square error for a sample of `states`.
`Propagator`	PropagatorConverter.`convert(List<SpacecraftState> states, boolean positionOnly, String... freeParameters)`	Find the propagator that minimize the mean square error for a sample of `states`.
`Propagator`	PropagatorConverter.`convert(List<SpacecraftState> states, boolean positionOnly, List<String> freeParameters)`	Find the propagator that minimize the mean square error for a sample of `states`.

Constructors in org.orekit.propagation.conversion with parameters of type SpacecraftState
Constructor	Description
`OsculatingToMeanElementsConverter(SpacecraftState state, int satelliteRevolution, Propagator propagator, double positionScale)`	Constructor.

Constructor parameters in org.orekit.propagation.conversion with type arguments of type SpacecraftState
Constructor	Description
`EphemerisPropagatorBuilder(List<SpacecraftState> states, int interpolationPoints, double extrapolationThreshold, AttitudeProvider attitudeProvider)`	Constructor.
`EphemerisPropagatorBuilder(List<SpacecraftState> states, TimeInterpolator<SpacecraftState> stateInterpolator)`	Constructor using the default attitude provider.
`EphemerisPropagatorBuilder(List<SpacecraftState> states, TimeInterpolator<SpacecraftState> stateInterpolator)`	Constructor using the default attitude provider.
`EphemerisPropagatorBuilder(List<SpacecraftState> states, TimeInterpolator<SpacecraftState> stateInterpolator, List<StateCovariance> covariances, TimeInterpolator<TimeStampedPair<Orbit,StateCovariance>> covarianceInterpolator)`	Constructor with covariances and default attitude provider.
`EphemerisPropagatorBuilder(List<SpacecraftState> states, TimeInterpolator<SpacecraftState> stateInterpolator, List<StateCovariance> covariances, TimeInterpolator<TimeStampedPair<Orbit,StateCovariance>> covarianceInterpolator)`	Constructor with covariances and default attitude provider.
`EphemerisPropagatorBuilder(List<SpacecraftState> states, TimeInterpolator<SpacecraftState> stateInterpolator, List<StateCovariance> covariances, TimeInterpolator<TimeStampedPair<Orbit,StateCovariance>> covarianceInterpolator, AttitudeProvider attitudeProvider)`	Constructor.
`EphemerisPropagatorBuilder(List<SpacecraftState> states, TimeInterpolator<SpacecraftState> stateInterpolator, List<StateCovariance> covariances, TimeInterpolator<TimeStampedPair<Orbit,StateCovariance>> covarianceInterpolator, AttitudeProvider attitudeProvider)`	Constructor.
`EphemerisPropagatorBuilder(List<SpacecraftState> states, TimeInterpolator<SpacecraftState> stateInterpolator, AttitudeProvider attitudeProvider)`	Constructor.
`EphemerisPropagatorBuilder(List<SpacecraftState> states, TimeInterpolator<SpacecraftState> stateInterpolator, AttitudeProvider attitudeProvider)`	Constructor.

Uses of SpacecraftState in org.orekit.propagation.events

Methods in org.orekit.propagation.events that return SpacecraftState
Modifier and Type	Method	Description
`SpacecraftState`	EventState.EventOccurrence.`getNewState()`	Get the new state for a reset action.
`SpacecraftState`	EventsLogger.LoggedEvent.`getState()`	Get the triggering state.

Methods in org.orekit.propagation.events that return types with arguments of type SpacecraftState
Modifier and Type	Method	Description
`ToDoubleFunction<SpacecraftState>`	FunctionalDetector.`getFunction()`	Get the switching function.

Methods in org.orekit.propagation.events with parameters of type SpacecraftState
Modifier and Type	Method	Description
`static double`	BetaAngleDetector.`calculateBetaAngle(SpacecraftState state, PVCoordinatesProvider celestialBodyProvider)`	Calculate the beta angle between the orbit plane and the celestial body.
`static double`	BetaAngleDetector.`calculateBetaAngle(SpacecraftState state, PVCoordinatesProvider celestialBodyProvider, Frame frame)`	Calculate the beta angle between the orbit plane and the celestial body.
`PVCoordinates`	ExtremumApproachDetector.`computeDeltaPV(SpacecraftState 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`	AdaptableInterval.`currentInterval(SpacecraftState state)`	Get the current value of maximal time interval between events handler checks.
`EventState.EventOccurrence`	EventState.`doEvent(SpacecraftState state)`	Notify the user's listener of the event.
`boolean`	EnablingPredicate.`eventIsEnabled(SpacecraftState state, EventDetector detector, double g)`	Compute an event enabling function of state.
`abstract double`	AbstractDetector.`g(SpacecraftState s)`	Compute the value of the switching function.
`double`	AdapterDetector.`g(SpacecraftState s)`	Compute the value of the switching function.
`double`	AlignmentDetector.`g(SpacecraftState s)`	Compute the value of the switching function.
`double`	AltitudeDetector.`g(SpacecraftState s)`	Compute the value of the switching function.
`double`	AngularSeparationDetector.`g(SpacecraftState s)`	Compute the value of the switching function.
`double`	AngularSeparationFromSatelliteDetector.`g(SpacecraftState s)`	Compute the value of the switching function.
`double`	ApsideDetector.`g(SpacecraftState s)`	Compute the value of the switching function.
`double`	BetaAngleDetector.`g(SpacecraftState s)`	Compute the value of the switching function.
`double`	BooleanDetector.`g(SpacecraftState s)`
`double`	CylindricalShadowEclipseDetector.`g(SpacecraftState s)`	Compute the value of the switching function.
`double`	DateDetector.`g(SpacecraftState s)`	Compute the value of the switching function.
`double`	EclipseDetector.`g(SpacecraftState s)`	Compute the value of the switching function.
`double`	ElevationDetector.`g(SpacecraftState s)`	Compute the value of the switching function.
`double`	ElevationExtremumDetector.`g(SpacecraftState s)`	Compute the value of the detection function.
`double`	EventDetector.`g(SpacecraftState s)`	Compute the value of the switching function.
`double`	EventEnablingPredicateFilter.`g(SpacecraftState s)`	Compute the value of the switching function.
`double`	EventShifter.`g(SpacecraftState s)`	Compute the value of the switching function.
`double`	EventSlopeFilter.`g(SpacecraftState s)`	Compute the value of the switching function.
`double`	ExtremumApproachDetector.`g(SpacecraftState 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.
`double`	FieldOfViewDetector.`g(SpacecraftState s)`	Compute the value of the switching function.
`double`	FootprintOverlapDetector.`g(SpacecraftState s)`	Compute the value of the switching function.
`double`	FunctionalDetector.`g(SpacecraftState s)`
`double`	GeographicZoneDetector.`g(SpacecraftState s)`	Compute the value of the detection function.
`double`	GroundAtNightDetector.`g(SpacecraftState state)`	Compute the value of the switching function.
`double`	GroundFieldOfViewDetector.`g(SpacecraftState s)`	Compute the value of the switching function.
`double`	HaloXZPlaneCrossingDetector.`g(SpacecraftState s)`	Compute the value of the detection function.
`double`	InterSatDirectViewDetector.`g(SpacecraftState state)`	Compute the value of the switching function.
`double`	LatitudeCrossingDetector.`g(SpacecraftState s)`	Compute the value of the detection function.
`double`	LatitudeExtremumDetector.`g(SpacecraftState s)`	Compute the value of the detection function.
`double`	LatitudeRangeCrossingDetector.`g(SpacecraftState s)`	Compute the value of the detection function.
`double`	LongitudeCrossingDetector.`g(SpacecraftState s)`	Compute the value of the detection function.
`double`	LongitudeExtremumDetector.`g(SpacecraftState s)`	Compute the value of the detection function.
`double`	LongitudeRangeCrossingDetector.`g(SpacecraftState s)`	Compute the value of the detection function.
`double`	MagneticFieldDetector.`g(SpacecraftState s)`	Compute the value of the detection function.
`double`	NegateDetector.`g(SpacecraftState s)`
`double`	NodeDetector.`g(SpacecraftState s)`	Compute the value of the switching function.
`double`	ParameterDrivenDateIntervalDetector.`g(SpacecraftState s)`	Compute the value of the switching function.
`double`	PositionAngleDetector.`g(SpacecraftState s)`	Compute the value of the detection function.
`double`	RelativeDistanceDetector.`g(SpacecraftState s)`	The `g` is positive when the relative distance is larger or equal than the threshold, non-positive otherwise.
`double`	ElevationExtremumDetector.`getElevation(SpacecraftState s)`	Get the elevation value.
`void`	AbstractDetector.`init(SpacecraftState s0, AbsoluteDate t)`	Initialize event handler at the start of a propagation.
`void`	AdapterDetector.`init(SpacecraftState s0, AbsoluteDate t)`	Initialize event handler at the start of a propagation.
`void`	BooleanDetector.`init(SpacecraftState s0, AbsoluteDate t)`
`default void`	EventDetector.`init(SpacecraftState s0, AbsoluteDate t)`	Initialize event handler at the start of a propagation.
`void`	EventEnablingPredicateFilter.`init(SpacecraftState s0, AbsoluteDate t)`	Initialize event handler at the start of a propagation.
`void`	EventShifter.`init(SpacecraftState s0, AbsoluteDate t)`	Initialize event handler at the start of a propagation.
`void`	EventSlopeFilter.`init(SpacecraftState s0, AbsoluteDate t)`	Initialize event handler at the start of a propagation.
`void`	EventState.`init(SpacecraftState s0, AbsoluteDate t)`	Initialize event handler at the start of a propagation.
`void`	LongitudeCrossingDetector.`init(SpacecraftState s0, AbsoluteDate t)`	Initialize event handler at the start of a propagation.
`void`	MagneticFieldDetector.`init(SpacecraftState s0, AbsoluteDate t)`	Initialize event handler at the start of a propagation.
`void`	NegateDetector.`init(SpacecraftState s0, AbsoluteDate t)`
`void`	PositionAngleDetector.`init(SpacecraftState s0, AbsoluteDate t)`	Initialize event handler at the start of a propagation.
`boolean`	EventState.`tryAdvance(SpacecraftState state, OrekitStepInterpolator interpolator)`	Try to accept the current history up to the given time.

Method parameters in org.orekit.propagation.events with type arguments of type SpacecraftState
Modifier and Type	Method	Description
`FunctionalDetector`	FunctionalDetector.`withFunction(ToDoubleFunction<SpacecraftState> 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 SpacecraftState
Constructor	Description
`FunctionalDetector(AdaptableInterval maxCheck, double threshold, int maxIter, EventHandler handler, ToDoubleFunction<SpacecraftState> function)`	Private constructor.

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

Methods in org.orekit.propagation.events.handlers that return SpacecraftState
Modifier and Type	Method	Description
`SpacecraftState`	RecordAndContinue.Event.`getState()`	Get the spacecraft's state at the event.
`default SpacecraftState`	EventHandler.`resetState(EventDetector detector, SpacecraftState oldState)`	Reset the state prior to continue propagation.
`SpacecraftState`	EventMultipleHandler.`resetState(EventDetector detector, SpacecraftState oldState)`	Reset the state prior to continue propagation.
`SpacecraftState`	RecallLastOccurrence.`resetState(EventDetector detector, SpacecraftState oldState)`	Reset the state prior to continue propagation.

Methods in org.orekit.propagation.events.handlers with parameters of type SpacecraftState
Modifier and Type	Method	Description
`Action`	ContinueOnEvent.`eventOccurred(SpacecraftState s, EventDetector detector, boolean increasing)`	Specific implementation of the eventOccurred interface.
`Action`	EventHandler.`eventOccurred(SpacecraftState s, EventDetector detector, boolean increasing)`	Handle an event.
`Action`	EventMultipleHandler.`eventOccurred(SpacecraftState s, EventDetector detector, boolean increasing)`	Handle an event.
`Action`	RecallLastOccurrence.`eventOccurred(SpacecraftState s, EventDetector detector, boolean increasing)`	Handle an event.
`Action`	RecordAndContinue.`eventOccurred(SpacecraftState s, EventDetector detector, boolean increasing)`
`Action`	StopOnDecreasing.`eventOccurred(SpacecraftState s, EventDetector detector, boolean increasing)`	Handle a detection event and choose what to do next.
`Action`	StopOnEvent.`eventOccurred(SpacecraftState s, EventDetector detector, boolean increasing)`	Specific implementation of the eventOccurred interface.
`Action`	StopOnIncreasing.`eventOccurred(SpacecraftState s, EventDetector detector, boolean increasing)`	Handle a detection event and choose what to do next.
`default void`	EventHandler.`init(SpacecraftState initialState, AbsoluteDate target, EventDetector detector)`	Initialize event handler at the start of a propagation.
`void`	EventMultipleHandler.`init(SpacecraftState initialState, AbsoluteDate target, EventDetector detector)`	Initialize event handler at the start of a propagation.
`void`	RecallLastOccurrence.`init(SpacecraftState initialState, AbsoluteDate target, EventDetector detector)`	Initialize event handler at the start of a propagation.
`default SpacecraftState`	EventHandler.`resetState(EventDetector detector, SpacecraftState oldState)`	Reset the state prior to continue propagation.
`SpacecraftState`	EventMultipleHandler.`resetState(EventDetector detector, SpacecraftState oldState)`	Reset the state prior to continue propagation.
`SpacecraftState`	RecallLastOccurrence.`resetState(EventDetector detector, SpacecraftState oldState)`	Reset the state prior to continue propagation.

Uses of SpacecraftState in org.orekit.propagation.integration

Methods in org.orekit.propagation.integration that return SpacecraftState
Modifier and Type	Method	Description
`protected SpacecraftState`	IntegratedEphemeris.`basicPropagate(AbsoluteDate date)`	Propagate an orbit without any fancy features.
`protected SpacecraftState`	AbstractIntegratedPropagator.`getInitialIntegrationState()`	Get the initial state for integration.
`SpacecraftState`	IntegratedEphemeris.`getInitialState()`	Get the propagator initial state.
`SpacecraftState`	StateMapper.`mapArrayToState(double t, double[] y, double[] yDot, PropagationType type)`	Map the raw double components to a spacecraft state.
`abstract SpacecraftState`	StateMapper.`mapArrayToState(AbsoluteDate date, double[] y, double[] yDot, PropagationType type)`	Map the raw double components to a spacecraft state.
`SpacecraftState`	AbstractIntegratedPropagator.`propagate(AbsoluteDate target)`	Propagate towards a target date.
`SpacecraftState`	AbstractIntegratedPropagator.`propagate(AbsoluteDate tStart, AbsoluteDate tEnd)`	Propagate from a start date towards a target date.
`protected SpacecraftState`	IntegratedEphemeris.`updateAdditionalStates(SpacecraftState original)`	Update state by adding all additional states.

Methods in org.orekit.propagation.integration with parameters of type SpacecraftState
Modifier and Type	Method	Description
`protected void`	AbstractIntegratedPropagator.`beforeIntegration(SpacecraftState initialState, AbsoluteDate tEnd)`	Method called just before integration.
`protected static FieldSpacecraftState<Gradient>`	AbstractGradientConverter.`buildBasicGradientSpacecraftState(SpacecraftState state, int freeStateParameters, AttitudeProvider provider)`	Process a state into a Gradient version without force model parameter.
`CombinedDerivatives`	AdditionalDerivativesProvider.`combinedDerivatives(SpacecraftState s)`	Compute the derivatives related to the additional state (and optionally main state increments).
`double[]`	AbstractIntegratedPropagator.MainStateEquations.`computeDerivatives(SpacecraftState state)`	Compute differential equations for main state.
`default void`	AbstractIntegratedPropagator.MainStateEquations.`init(SpacecraftState initialState, AbsoluteDate target)`	Initialize the equations at the start of propagation.
`default void`	AdditionalDerivativesProvider.`init(SpacecraftState initialState, AbsoluteDate target)`	Initialize the generator at the start of propagation.
`abstract void`	StateMapper.`mapStateToArray(SpacecraftState state, double[] y, double[] yDot)`	Map a spacecraft state to raw double components.
`void`	AbstractIntegratedPropagator.`resetInitialState(SpacecraftState state, PropagationType stateType)`	Reset initial state with a given propagation type.
`void`	IntegratedEphemeris.`resetInitialState(SpacecraftState state)`	Reset the propagator initial state.
`protected void`	IntegratedEphemeris.`resetIntermediateState(SpacecraftState state, boolean forward)`	Reset an intermediate state.
`protected SpacecraftState`	IntegratedEphemeris.`updateAdditionalStates(SpacecraftState original)`	Update state by adding all additional states.
`default boolean`	AdditionalDerivativesProvider.`yields(SpacecraftState state)`	Check if this provider should yield so another provider has an opportunity to add missing parts.

Uses of SpacecraftState in org.orekit.propagation.numerical

Methods in org.orekit.propagation.numerical that return SpacecraftState
Modifier and Type	Method	Description
`SpacecraftState`	GLONASSNumericalPropagator.`propagate(AbsoluteDate date)`	Propagate towards a target date.
`SpacecraftState`	EpochDerivativesEquations.`setInitialJacobians(SpacecraftState s0)`	Set the initial value of the Jacobian with respect to state and parameter.
`SpacecraftState`	EpochDerivativesEquations.`setInitialJacobians(SpacecraftState s1, double[][] dY1dY0, double[][] dY1dP)`	Set the initial value of the Jacobian with respect to state and parameter.

Methods in org.orekit.propagation.numerical with parameters of type SpacecraftState
Modifier and Type	Method	Description
`protected void`	NumericalPropagator.`beforeIntegration(SpacecraftState initialState, AbsoluteDate tEnd)`	Method called just before integration.
`CombinedDerivatives`	EpochDerivativesEquations.`combinedDerivatives(SpacecraftState s)`	Compute the derivatives related to the additional state (and optionally main state increments).
`void`	NumericalPropagator.`resetInitialState(SpacecraftState state)`	Reset the propagator initial state.
`SpacecraftState`	EpochDerivativesEquations.`setInitialJacobians(SpacecraftState s0)`	Set the initial value of the Jacobian with respect to state and parameter.
`SpacecraftState`	EpochDerivativesEquations.`setInitialJacobians(SpacecraftState s1, double[][] dY1dY0, double[][] dY1dP)`	Set the initial value of the Jacobian with respect to state and parameter.
`void`	EpochDerivativesEquations.`setInitialJacobians(SpacecraftState state, double[][] dY1dY0, double[][] dY1dP, double[] p)`	Set the Jacobian with respect to state into a one-dimensional additional state array.
`void`	NumericalPropagator.`setInitialState(SpacecraftState initialState)`	Set the initial state.

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

Methods in org.orekit.propagation.numerical.cr3bp that return SpacecraftState
Modifier and Type	Method	Description
`protected SpacecraftState`	CR3BPMultipleShooter.`getAugmentedInitialState(int i)`	Compute the additional state from the additionalEquations.
`SpacecraftState`	STMEquations.`setInitialPhi(SpacecraftState s)`	Method adding the standard initial values of the additional state to the initial spacecraft state.

Methods in org.orekit.propagation.numerical.cr3bp with parameters of type SpacecraftState
Modifier and Type	Method	Description
`Vector3D`	CR3BPForceModel.`acceleration(SpacecraftState s, double[] parameters)`	Compute acceleration.
`CombinedDerivatives`	STMEquations.`combinedDerivatives(SpacecraftState s)`	Compute the derivatives related to the additional state (and optionally main state increments).
`DerivativeStructure`	CR3BPForceModel.`getPotential(SpacecraftState s)`	Calculate spacecraft potential.
`RealMatrix`	STMEquations.`getStateTransitionMatrix(SpacecraftState s)`	Method returning the State Transition Matrix.
`SpacecraftState`	STMEquations.`setInitialPhi(SpacecraftState s)`	Method adding the standard initial values of the additional state to the initial spacecraft state.

Method parameters in org.orekit.propagation.numerical.cr3bp with type arguments of type SpacecraftState
Modifier and Type	Method	Description
`protected double[]`	CR3BPMultipleShooter.`computeAdditionalConstraints(List<SpacecraftState> propagatedSP)`	Compute the additional constraints.
`protected double[][]`	CR3BPMultipleShooter.`computeAdditionalJacobianMatrix(List<SpacecraftState> propagatedSP)`	Compute a part of the Jacobian matrix from additional constraints.

Constructor parameters in org.orekit.propagation.numerical.cr3bp with type arguments of type SpacecraftState
Constructor	Description
`CR3BPMultipleShooter(List<SpacecraftState> initialGuessList, List<NumericalPropagator> propagatorList, List<STMEquations> stmEquations, double tolerance, int maxIter)`	Simple Constructor.

Uses of SpacecraftState in org.orekit.propagation.sampling

Methods in org.orekit.propagation.sampling that return SpacecraftState
Modifier and Type	Method	Description
`SpacecraftState`	OrekitStepInterpolator.`getCurrentState()`	Get the state at current grid point date.
`SpacecraftState`	OrekitStepInterpolator.`getInterpolatedState(AbsoluteDate date)`	Get the state at interpolated date.
`SpacecraftState`	OrekitStepInterpolator.`getPreviousState()`	Get the state at previous grid point date.

Methods in org.orekit.propagation.sampling with parameters of type SpacecraftState
Modifier and Type	Method	Description
`default void`	OrekitFixedStepHandler.`finish(SpacecraftState finalState)`	Finalize propagation.
`default void`	OrekitStepHandler.`finish(SpacecraftState finalState)`	Finalize propagation.
`void`	OrekitStepNormalizer.`finish(SpacecraftState finalState)`	Finalize propagation.
`void`	StepHandlerMultiplexer.`finish(SpacecraftState finalState)`	Finalize propagation.
`void`	OrekitFixedStepHandler.`handleStep(SpacecraftState currentState)`	Handle the current step.
`default void`	OrekitFixedStepHandler.`init(SpacecraftState s0, AbsoluteDate t, double step)`	Initialize step handler at the start of a propagation.
`default void`	OrekitStepHandler.`init(SpacecraftState s0, AbsoluteDate t)`	Initialize step handler at the start of a propagation.
`void`	OrekitStepNormalizer.`init(SpacecraftState s0, AbsoluteDate t)`	Initialize step handler at the start of a propagation.
`void`	StepHandlerMultiplexer.`init(SpacecraftState s0, AbsoluteDate t)`	Initialize step handler at the start of a propagation.
`OrekitStepInterpolator`	OrekitStepInterpolator.`restrictStep(SpacecraftState newPreviousState, SpacecraftState newCurrentState)`	Create a new restricted version of the instance.

Method parameters in org.orekit.propagation.sampling with type arguments of type SpacecraftState
Modifier and Type	Method	Description
`default void`	MultiSatFixedStepHandler.`finish(List<SpacecraftState> finalStates)`	Finalize propagation.
`default void`	MultiSatStepHandler.`finish(List<SpacecraftState> finalStates)`	Finalize propagation.
`void`	MultisatStepNormalizer.`finish(List<SpacecraftState> finalStates)`	Finalize propagation.
`void`	MultiSatFixedStepHandler.`handleStep(List<SpacecraftState> states)`	Handle the current step.
`default void`	MultiSatFixedStepHandler.`init(List<SpacecraftState> states0, AbsoluteDate t, double step)`	Initialize step handler at the start of a propagation.
`default void`	MultiSatStepHandler.`init(List<SpacecraftState> states0, AbsoluteDate t)`	Initialize step handler at the start of a propagation.
`void`	MultisatStepNormalizer.`init(List<SpacecraftState> s0, AbsoluteDate t)`	Initialize step handler at the start of a propagation.

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

Methods in org.orekit.propagation.semianalytical.dsst that return SpacecraftState
Modifier and Type	Method	Description
`static SpacecraftState`	DSSTPropagator.`computeMeanState(SpacecraftState osculating, AttitudeProvider attitudeProvider, Collection<DSSTForceModel> forceModels)`	Conversion from osculating to mean orbit.
`static SpacecraftState`	DSSTPropagator.`computeMeanState(SpacecraftState osculating, AttitudeProvider attitudeProvider, Collection<DSSTForceModel> forceModels, double epsilon, int maxIterations)`	Conversion from osculating to mean orbit.
`static SpacecraftState`	DSSTPropagator.`computeOsculatingState(SpacecraftState mean, AttitudeProvider attitudeProvider, Collection<DSSTForceModel> forces)`	Conversion from mean to osculating orbit.
`protected SpacecraftState`	DSSTPropagator.`getInitialIntegrationState()`	Get the initial state for integration.

Methods in org.orekit.propagation.semianalytical.dsst with parameters of type SpacecraftState
Modifier and Type	Method	Description
`protected void`	DSSTPropagator.`beforeIntegration(SpacecraftState initialState, AbsoluteDate tEnd)`	Method called just before integration.
`static SpacecraftState`	DSSTPropagator.`computeMeanState(SpacecraftState osculating, AttitudeProvider attitudeProvider, Collection<DSSTForceModel> forceModels)`	Conversion from osculating to mean orbit.
`static SpacecraftState`	DSSTPropagator.`computeMeanState(SpacecraftState osculating, AttitudeProvider attitudeProvider, Collection<DSSTForceModel> forceModels, double epsilon, int maxIterations)`	Conversion from osculating to mean orbit.
`static SpacecraftState`	DSSTPropagator.`computeOsculatingState(SpacecraftState mean, AttitudeProvider attitudeProvider, Collection<DSSTForceModel> forces)`	Conversion from mean to osculating orbit.
`RealMatrix`	DSSTHarvester.`getB2(SpacecraftState state)`	Get the Jacobian matrix B2 (B2 = ∂Y/∂Y₀).
`RealMatrix`	DSSTHarvester.`getB3(SpacecraftState state)`	Get the Jacobian matrix B3 (B3 = ∂Y/∂P).
`RealMatrix`	DSSTHarvester.`getParametersJacobian(SpacecraftState state)`	Get the Jacobian with respect to propagation parameters.
`double[]`	DSSTPropagator.`getShortPeriodTermsValue(SpacecraftState meanState)`	Get the short period terms value.
`RealMatrix`	DSSTHarvester.`getStateTransitionMatrix(SpacecraftState state)`	Extract state transition matrix from state.
`void`	DSSTHarvester.`initializeFieldShortPeriodTerms(SpacecraftState reference)`	Initialize the short periodic terms for the "field" elements.
`void`	DSSTHarvester.`initializeFieldShortPeriodTerms(SpacecraftState reference, PropagationType type)`	Initialize the short periodic terms for the "field" elements.
`void`	DSSTPropagator.`resetInitialState(SpacecraftState state)`	Reset the initial state.
`void`	DSSTPropagator.`resetInitialState(SpacecraftState state, PropagationType stateType)`	Reset initial state with a given propagation type.
`void`	DSSTPropagator.`setInitialState(SpacecraftState initialState)`	Set the initial state with osculating orbital elements.
`void`	DSSTPropagator.`setInitialState(SpacecraftState initialState, PropagationType stateType)`	Set the initial state.
`void`	DSSTHarvester.`setReferenceState(SpacecraftState reference)`	Set up reference state.
`void`	DSSTHarvester.`updateFieldShortPeriodTerms(SpacecraftState reference)`	Update the short periodic terms for the "field" elements.

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

Methods in org.orekit.propagation.semianalytical.dsst.forces with parameters of type SpacecraftState
Modifier and Type	Method	Description
`AbstractGaussianContribution.Slot`	AbstractGaussianContribution.GaussianShortPeriodicCoefficients.`createSlot(SpacecraftState... meanStates)`	Get the slot valid for some date.
`protected abstract double[]`	AbstractGaussianContribution.`getLLimits(SpacecraftState state, AuxiliaryElements auxiliaryElements)`	Compute the limits in L, the true longitude, for integration.
`protected double[]`	DSSTAtmosphericDrag.`getLLimits(SpacecraftState state, AuxiliaryElements auxiliaryElements)`	Compute the limits in L, the true longitude, for integration.
`protected double[]`	DSSTSolarRadiationPressure.`getLLimits(SpacecraftState state, AuxiliaryElements auxiliaryElements)`	Compute the limits in L, the true longitude, for integration.
`protected double[]`	AbstractGaussianContribution.`getMeanElementRate(SpacecraftState state, AbstractGaussianContribution.GaussQuadrature gauss, double low, double high, AbstractGaussianContributionContext context, double[] parameters)`	Computes the mean equinoctial elements rates da_i / dt.
`double[]`	AbstractGaussianContribution.`getMeanElementRate(SpacecraftState state, AuxiliaryElements auxiliaryElements, double[] parameters)`	Computes the mean equinoctial elements rates da_i / dt.
`double[]`	DSSTForceModel.`getMeanElementRate(SpacecraftState state, AuxiliaryElements auxiliaryElements, double[] parameters)`	Computes the mean equinoctial elements rates da_i / dt.
`double[]`	DSSTJ2SquaredClosedForm.`getMeanElementRate(SpacecraftState state, AuxiliaryElements auxiliaryElements, double[] parameters)`	Computes the mean equinoctial elements rates da_i / dt.
`double[]`	DSSTNewtonianAttraction.`getMeanElementRate(SpacecraftState state, AuxiliaryElements auxiliaryElements, double[] parameters)`	Computes the mean equinoctial elements rates da_i / dt.
`double[]`	DSSTTesseral.`getMeanElementRate(SpacecraftState spacecraftState, AuxiliaryElements auxiliaryElements, double[] parameters)`	Computes the mean equinoctial elements rates da_i / dt.
`double[]`	DSSTThirdBody.`getMeanElementRate(SpacecraftState currentState, AuxiliaryElements auxiliaryElements, double[] parameters)`	Computes the mean equinoctial elements rates da_i / dt.
`double[]`	DSSTZonal.`getMeanElementRate(SpacecraftState spacecraftState, AuxiliaryElements auxiliaryElements, double[] parameters)`	Computes the mean equinoctial elements rates da_i / dt.
`void`	AbstractGaussianContribution.`init(SpacecraftState initialState, AbsoluteDate target)`	Initialize the force model at the start of propagation.
`default void`	DSSTForceModel.`init(SpacecraftState initialState, AbsoluteDate target)`	Initialize the force model at the start of propagation.
`void`	AbstractGaussianContribution.`updateShortPeriodTerms(double[] parameters, SpacecraftState... meanStates)`	Update the short period terms.
`void`	DSSTForceModel.`updateShortPeriodTerms(double[] parameters, SpacecraftState... meanStates)`	Update the short period terms.
`void`	DSSTJ2SquaredClosedForm.`updateShortPeriodTerms(double[] parameters, SpacecraftState... meanStates)`	Update the short period terms.
`void`	DSSTNewtonianAttraction.`updateShortPeriodTerms(double[] parameters, SpacecraftState... meanStates)`	Update the short period terms.
`void`	DSSTTesseral.`updateShortPeriodTerms(double[] parameters, SpacecraftState... meanStates)`	Update the short period terms.
`void`	DSSTThirdBody.`updateShortPeriodTerms(double[] parameters, SpacecraftState... meanStates)`	Update the short period terms.
`void`	DSSTZonal.`updateShortPeriodTerms(double[] parameters, SpacecraftState... meanStates)`	Update the short period terms.

Uses of SpacecraftState in org.orekit.utils

Methods in org.orekit.utils that return SpacecraftState
Modifier and Type	Method	Description
`protected abstract SpacecraftState`	AbstractMultipleShooting.`getAugmentedInitialState(int i)`	Compute the additional state from the additionalEquations.
`protected SpacecraftState`	MultipleShooter.`getAugmentedInitialState(int i)`	Compute the additional state from the additionalEquations.
`protected SpacecraftState`	AbstractMultipleShooting.`getPatchPoint(int i)`	Get a patch point.

Methods in org.orekit.utils that return types with arguments of type SpacecraftState
Modifier and Type	Method	Description
`List<SpacecraftState>`	AbstractMultipleShooting.`compute()`	Return the list of corrected patch points.
`List<SpacecraftState>`	MultipleShooting.`compute()`	Return the list of corrected patch points.
`protected List<SpacecraftState>`	AbstractMultipleShooting.`getPatchedSpacecraftState()`	Get the list of patched spacecraft states.

Methods in org.orekit.utils with parameters of type SpacecraftState
Modifier and Type	Method	Description
`OccultationEngine.OccultationAngles`	OccultationEngine.`angles(SpacecraftState state)`	Compute the occultation angles as seen from a spacecraft.
`double[]`	StateFunction.`value(SpacecraftState state)`	Evaluate the function.
`double[][]`	StateJacobian.`value(SpacecraftState state)`	Evaluate the Jacobian of the function.

Method parameters in org.orekit.utils with type arguments of type SpacecraftState
Modifier and Type	Method	Description
`protected abstract double[]`	AbstractMultipleShooting.`computeAdditionalConstraints(List<SpacecraftState> propagatedSP)`	Compute the additional constraints.
`protected double[]`	MultipleShooter.`computeAdditionalConstraints(List<SpacecraftState> propagatedSP)`	Compute the additional constraints.
`protected abstract double[][]`	AbstractMultipleShooting.`computeAdditionalJacobianMatrix(List<SpacecraftState> propagatedSP)`	Compute a part of the Jacobian matrix from additional constraints.
`protected double[][]`	MultipleShooter.`computeAdditionalJacobianMatrix(List<SpacecraftState> propagatedSP)`	Compute a part of the Jacobian matrix from additional constraints.
`protected double[][]`	AbstractMultipleShooting.`computeEpochJacobianMatrix(List<SpacecraftState> propagatedSP)`	Compute a part of the Jacobian matrix with derivatives from epoch.

Constructor parameters in org.orekit.utils with type arguments of type SpacecraftState
Constructor	Description
`AbstractMultipleShooting(List<SpacecraftState> initialGuessList, List<NumericalPropagator> propagatorList, double tolerance, int maxIter, boolean isAutonomous, String additionalName)`	Simple Constructor.
`MultipleShooter(List<SpacecraftState> initialGuessList, List<NumericalPropagator> propagatorList, List<EpochDerivativesEquations> epochEquations, double tolerance, int maxIter)`	Simple Constructor.

Uses of Classorg.orekit.propagation.SpacecraftState

Uses of SpacecraftState in org.orekit.attitudes

Uses of SpacecraftState in org.orekit.estimation.measurements

Uses of SpacecraftState in org.orekit.estimation.measurements.filtering

Uses of SpacecraftState in org.orekit.estimation.measurements.generation

Uses of SpacecraftState in org.orekit.estimation.measurements.gnss

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

Uses of SpacecraftState in org.orekit.estimation.sequential

Uses of SpacecraftState in org.orekit.files.ccsds.ndm.adm.aem

Uses of SpacecraftState in org.orekit.files.ccsds.ndm.odm.ocm

Uses of SpacecraftState in org.orekit.files.ccsds.ndm.odm.oem

Uses of SpacecraftState in org.orekit.files.ccsds.ndm.odm.omm

Uses of SpacecraftState in org.orekit.files.ccsds.ndm.odm.opm

Uses of SpacecraftState in org.orekit.files.general

Uses of SpacecraftState in org.orekit.files.ilrs

Uses of SpacecraftState in org.orekit.forces

Uses of SpacecraftState in org.orekit.forces.drag

Uses of SpacecraftState in org.orekit.forces.empirical

Uses of SpacecraftState in org.orekit.forces.gravity

Uses of SpacecraftState in org.orekit.forces.inertia

Uses of SpacecraftState in org.orekit.forces.maneuvers

Uses of SpacecraftState in org.orekit.forces.maneuvers.jacobians

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

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

Uses of SpacecraftState in org.orekit.forces.radiation

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

Uses of SpacecraftState in org.orekit.orbits

Uses of SpacecraftState in org.orekit.propagation

Uses of SpacecraftState in org.orekit.propagation.analytical

Uses of SpacecraftState in org.orekit.propagation.analytical.gnss

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

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

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

Uses of SpacecraftState in org.orekit.propagation.conversion

Uses of SpacecraftState in org.orekit.propagation.events

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

Uses of SpacecraftState in org.orekit.propagation.integration

Uses of SpacecraftState in org.orekit.propagation.numerical

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

Uses of SpacecraftState in org.orekit.propagation.sampling

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

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

Uses of SpacecraftState in org.orekit.utils

Uses of Class
org.orekit.propagation.SpacecraftState