Uses of Class
org.orekit.propagation.SpacecraftState

Packages that use SpacecraftState

Package	Description
org.orekit.attitudes	This package provides classes to represent simple attitudes.
org.orekit.control.indirect.adjoint	This package provides routines to model the adjoint dynamics as in the Pontryagin Maximum Principle, as used in indirect control.
org.orekit.control.indirect.shooting	This package provides routines to solve indirect optimal control within the frame of orbital mechanics, using shooting methods.
org.orekit.estimation.measurements	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 that return SpacecraftState

Modifier and Type	Method	Description
SpacecraftState	AttitudesSequence.Switch.resetState(EventDetector detector, SpacecraftState oldState)	Reset the state prior to continue propagation.

Methods in org.orekit.attitudes with parameters of type SpacecraftState

Modifier and Type	Method	Description
Action	AttitudesSequence.Switch.eventOccurred(SpacecraftState s, EventDetector detector, boolean increasing)	Handle an event.
double	AttitudesSequence.Switch.g(SpacecraftState s)	Compute the value of the switching function.
void	AttitudesSequence.Switch.init(SpacecraftState s0, AbsoluteDate t)	Initialize event handler at the start of a propagation.
SpacecraftState	AttitudesSequence.Switch.resetState(EventDetector detector, SpacecraftState oldState)	Reset the state prior to continue propagation.
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.control.indirect.adjoint

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

Modifier and Type	Method	Description
CombinedDerivatives	CartesianAdjointDerivativesProvider.combinedDerivatives(SpacecraftState state)	Compute the derivatives related to the additional state (and optionally main state increments).
double	CartesianAdjointDerivativesProvider.evaluateHamiltonian(SpacecraftState state)	Evaluate the Hamiltonian from Pontryagin's Maximum Principle.
void	CartesianAdjointDerivativesProvider.init(SpacecraftState initialState, AbsoluteDate target)	Initialize the generator at the start of propagation.

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

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

Modifier and Type	Method	Description
protected SpacecraftState	AbstractFixedBoundaryCartesianSingleShooting.createStateWithMassAndAdjoint(double initialMass, double[] initialAdjoint)	Create initial state with input mass and adjoint vector.
SpacecraftState	ShootingBoundaryOutput.getInitialState()	Getter for the initial state.
SpacecraftState	ShootingBoundaryOutput.getTerminalState()	Getter for the terminal state.

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

Modifier and Type	Method	Description
protected NumericalPropagator	AbstractFixedBoundaryCartesianSingleShooting.buildPropagator(SpacecraftState initialState)	Create numerical propagator.
protected NumericalPropagator	AbstractIndirectShooting.buildPropagator(SpacecraftState initialState)	Create numerical propagator.

Constructors in org.orekit.control.indirect.shooting with parameters of type SpacecraftState

Constructor	Description
ShootingBoundaryOutput(boolean converged, int iterationCount, SpacecraftState initialState, ShootingPropagationSettings shootingPropagationSettings, SpacecraftState terminalState)	Constructor.

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	AbstractLightFluxModel.getLightingRatio(SpacecraftState state)	Get the lighting ratio ([0-1]).
double	SolarRadiationPressure.getLightingRatio(SpacecraftState state)	Get the lighting ratio ([0-1]).
void	ConicallyShadowedLightFluxModel.init(SpacecraftState initialState, AbsoluteDate targetDate)	Perform initialization steps before starting propagation.
default void	LightFluxModel.init(SpacecraftState initialState, AbsoluteDate targetDate)	Perform initialization steps before starting propagation.
void	RadiationPressureModel.init(SpacecraftState initialState, AbsoluteDate target)	Initialize the force model at the start of propagation.
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.
void	AdapterDetector.finish(SpacecraftState state)	This method finalizes the event detector's job.
default void	EventDetector.finish(SpacecraftState state)	This method finalizes the event detector's job.
void	EventState.finish(SpacecraftState state)	This method finalizes the event detector's job.
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	ResetDerivativesOnEvent.eventOccurred(SpacecraftState s, EventDetector detector, boolean increasing)	Specific implementation of the eventOccurred interface.
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.finish(SpacecraftState finalState, EventDetector detector)	This method finalizes the event handler's job.
void	EventMultipleHandler.finish(SpacecraftState finalState, EventDetector detector)
void	RecallLastOccurrence.finish(SpacecraftState finalState, EventDetector detector)	This method finalizes the event handler's job.
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 dai / dt.
double[]	AbstractGaussianContribution.getMeanElementRate(SpacecraftState state, AuxiliaryElements auxiliaryElements, double[] parameters)	Computes the mean equinoctial elements rates dai / dt.
double[]	DSSTForceModel.getMeanElementRate(SpacecraftState state, AuxiliaryElements auxiliaryElements, double[] parameters)	Computes the mean equinoctial elements rates dai / dt.
double[]	DSSTJ2SquaredClosedForm.getMeanElementRate(SpacecraftState state, AuxiliaryElements auxiliaryElements, double[] parameters)	Computes the mean equinoctial elements rates dai / dt.
double[]	DSSTNewtonianAttraction.getMeanElementRate(SpacecraftState state, AuxiliaryElements auxiliaryElements, double[] parameters)	Computes the mean equinoctial elements rates dai / dt.
double[]	DSSTTesseral.getMeanElementRate(SpacecraftState spacecraftState, AuxiliaryElements auxiliaryElements, double[] parameters)	Computes the mean equinoctial elements rates dai / dt.
double[]	DSSTThirdBody.getMeanElementRate(SpacecraftState currentState, AuxiliaryElements auxiliaryElements, double[] parameters)	Computes the mean equinoctial elements rates dai / dt.
double[]	DSSTZonal.getMeanElementRate(SpacecraftState spacecraftState, AuxiliaryElements auxiliaryElements, double[] parameters)	Computes the mean equinoctial elements rates dai / 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.
default void	J2SquaredModel.updateShortPeriodTerms(double[] parameters, SpacecraftState... meanStates)	Update the J2-squared 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.