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.estimation.measurements	The measurements package defines everything that is related to orbit determination measurements.
org.orekit.estimation.measurements.generation	This package provides Orbit Determination measurements generation.
org.orekit.estimation.measurements.gnss
org.orekit.estimation.measurements.modifiers
org.orekit.estimation.sequential
org.orekit.files.ccsds	This package provides a parser for orbit data stored in CCSDS Orbit Data Message format.
org.orekit.files.general	This package provides interfaces for orbit file representations and corresponding parsers.
org.orekit.forces	This package provides the interface for force models that will be used by the NumericalPropagator, as well as some classical spacecraft models for surface forces (spherical, box and solar array ...).
org.orekit.forces.drag	This package provides all drag-related forces.
org.orekit.forces.gravity	This package provides all gravity-related forces.
org.orekit.forces.inertia
org.orekit.forces.maneuvers	This package provides models of simple maneuvers.
org.orekit.forces.radiation	This package provides all radiation pressure related forces.
org.orekit.models.earth.ionosphere	This package provides models that simulate the impact of the ionosphere.
org.orekit.propagation	Propagation
org.orekit.propagation.analytical	Top level package for analytical propagators.
org.orekit.propagation.analytical.gnss	This package provides classes to propagate GNSS orbits.
org.orekit.propagation.analytical.tle	This package provides classes to read and extrapolate tle's.
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.sampling	This package provides interfaces and classes dealing with step handling during propagation.
org.orekit.propagation.semianalytical.dsst	This package provides an implementation of the Draper Semi-analytical Satellite Theory (DSST).
org.orekit.propagation.semianalytical.dsst.forces	This package provides force models for Draper Semi-analytical Satellite Theory (DSST).
org.orekit.utils	This package provides useful objects.

Uses of SpacecraftState in org.orekit.attitudes

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

Modifier and Type	Method and Description
void	AttitudesSequence.SwitchHandler.switchOccurred(AttitudeProvider preceding, AttitudeProvider following, SpacecraftState state) Method called when attitude is switched from one law to another law.

Uses of SpacecraftState in org.orekit.estimation.measurements

Methods in org.orekit.estimation.measurements that return SpacecraftState

Modifier and Type	Method and Description
SpacecraftState[]	EstimatedMeasurement.getStates() Get the states of the spacecrafts.

Methods in org.orekit.estimation.measurements with parameters of type SpacecraftState

Modifier and Type	Method and Description
EstimatedMeasurement<T>	AbstractMeasurement.estimate(int iteration, int evaluation, SpacecraftState[] states) Estimate the theoretical value of the measurement.
EstimatedMeasurement<T>	ObservedMeasurement.estimate(int iteration, int evaluation, SpacecraftState[] states) Estimate the theoretical value of the measurement.
static TimeStampedFieldPVCoordinates<DerivativeStructure>	AbstractMeasurement.getCoordinates(SpacecraftState state, int firstDerivative, DSFactory factory) Get Cartesian coordinates as derivatives.
protected EstimatedMeasurement<PV>	PV.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 abstract EstimatedMeasurement<T>	AbstractMeasurement.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<Range>	Range.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 EstimatedMeasurement<RangeRate>	RangeRate.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<AngularAzEl>	AngularAzEl.theoreticalEvaluation(int iteration, int evaluation, SpacecraftState[] states) Estimate the theoretical value.

Constructors in org.orekit.estimation.measurements with parameters of type SpacecraftState

Constructor and Description
EstimatedMeasurement(T observedMeasurement, int iteration, int count, SpacecraftState[] states, TimeStampedPVCoordinates[] participants) Simple constructor.

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 and Description
TurnAroundRange	TurnAroundRangeBuilder.build(SpacecraftState[] states) Generate a single measurement.
Position	PositionBuilder.build(SpacecraftState[] states) Generate a single measurement.
PV	PVBuilder.build(SpacecraftState[] states) Generate a single measurement.
T	MeasurementBuilder.build(SpacecraftState[] states) Generate a single measurement.
Range	RangeBuilder.build(SpacecraftState[] states) Generate a single measurement.
InterSatellitesRange	InterSatellitesRangeBuilder.build(SpacecraftState[] states) Generate a single measurement.
AngularRaDec	AngularRaDecBuilder.build(SpacecraftState[] states) Generate a single measurement.
AngularAzEl	AngularAzElBuilder.build(SpacecraftState[] states) Generate a single measurement.
RangeRate	RangeRateBuilder.build(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 and Description
protected EstimatedMeasurement<Phase>	Phase.theoreticalEvaluation(int iteration, int evaluation, SpacecraftState[] states) Estimate the theoretical value.

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 and Description
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 and Description
IonosphericDSConverter(SpacecraftState state, int freeStateParameters, AttitudeProvider provider) Simple constructor.
TroposphericDSConverter(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 and Description
SpacecraftState[]	DSSTKalmanModel.getCorrectedSpacecraftStates() Get the corrected spacecraft states.
SpacecraftState[]	KalmanEstimation.getCorrectedSpacecraftStates() Get the corrected spacecraft states.
SpacecraftState[]	KalmanModel.getCorrectedSpacecraftStates() Get the corrected spacecraft states.
SpacecraftState[]	DSSTKalmanModel.getPredictedSpacecraftStates() Get the predicted spacecraft states.
SpacecraftState[]	KalmanEstimation.getPredictedSpacecraftStates() Get the predicted spacecraft states.
SpacecraftState[]	KalmanModel.getPredictedSpacecraftStates() Get the predicted spacecraft states.

Methods in org.orekit.estimation.sequential with parameters of type SpacecraftState

Modifier and Type	Method and Description
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	UnivariateProcessNoise.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.

Uses of SpacecraftState in org.orekit.files.ccsds

Methods in org.orekit.files.ccsds that return SpacecraftState

Modifier and Type	Method and Description
SpacecraftState	OPMFile.generateSpacecraftState() Generate spacecraft state from the CartesianOrbit generated by generateCartesianOrbit.
SpacecraftState	OMMFile.generateSpacecraftState() Generate spacecraft state from the KeplerianOrbit generated by generateKeplerianOrbit.

Methods in org.orekit.files.ccsds with parameters of type SpacecraftState

Modifier and Type	Method and Description
void	StreamingOemWriter.Segment.handleStep(SpacecraftState s, boolean isLast)
void	StreamingOemWriter.Segment.init(SpacecraftState s0, AbsoluteDate t, double step) Initialize step handler at the start of a propagation.

Uses of SpacecraftState in org.orekit.files.general

Method parameters in org.orekit.files.general with type arguments of type SpacecraftState

Modifier and Type	Method and Description
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, 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, int interpolationSampleSize) 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.forces

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

Modifier and Type	Method and Description
Vector3D	ForceModel.acceleration(SpacecraftState s, double[] parameters) Compute acceleration.
Vector3D	AbstractParametricAcceleration.acceleration(SpacecraftState state, double[] parameters) Compute acceleration.
default void	ForceModel.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.
void	HarmonicParametricAcceleration.init(SpacecraftState initialState, AbsoluteDate target) Initialize the force model at the start of propagation.
default void	ForceModel.init(SpacecraftState initialState, AbsoluteDate target) Initialize the force model at the start of propagation.
void	PolynomialParametricAcceleration.init(SpacecraftState initialState, AbsoluteDate target) Initialize the force model at the start of propagation.
protected double	HarmonicParametricAcceleration.signedAmplitude(SpacecraftState state, double[] parameters) Compute the signed amplitude of the acceleration.
protected abstract double	AbstractParametricAcceleration.signedAmplitude(SpacecraftState state, double[] parameters) Compute the signed amplitude of the acceleration.
protected double	PolynomialParametricAcceleration.signedAmplitude(SpacecraftState state, double[] parameters) Compute the signed amplitude of the acceleration.

Uses of SpacecraftState in org.orekit.forces.drag

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

Modifier and Type	Method and Description
Vector3D	DragForce.acceleration(SpacecraftState s, double[] parameters) Compute acceleration.

Uses of SpacecraftState in org.orekit.forces.gravity

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

Modifier and Type	Method and Description
Vector3D	NewtonianAttraction.acceleration(SpacecraftState s, double[] parameters) Compute acceleration.
Vector3D	Relativity.acceleration(SpacecraftState s, double[] parameters) Compute acceleration.
Vector3D	SingleBodyRelativeAttraction.acceleration(SpacecraftState s, double[] parameters) Compute acceleration.
Vector3D	SingleBodyAbsoluteAttraction.acceleration(SpacecraftState s, double[] parameters) Compute acceleration.
Vector3D	SolidTides.acceleration(SpacecraftState s, double[] parameters) Compute acceleration.
Vector3D	HolmesFeatherstoneAttractionModel.acceleration(SpacecraftState s, double[] parameters) Compute acceleration.
Vector3D	OceanTides.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.

Uses of SpacecraftState in org.orekit.forces.inertia

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

Modifier and Type	Method and 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 and 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 and Description
Vector3D	ConstantThrustManeuver.acceleration(SpacecraftState state, double[] parameters) Compute acceleration.
void	ConstantThrustManeuver.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	ConstantThrustManeuver.init(SpacecraftState s0, AbsoluteDate t) Initialize the force model at the start of propagation.

Constructors in org.orekit.forces.maneuvers with parameters of type SpacecraftState

Constructor and Description
SmallManeuverAnalyticalModel(SpacecraftState state0, Frame frame, Vector3D dV, double isp) Build a maneuver defined in user-specified frame.
SmallManeuverAnalyticalModel(SpacecraftState state0, Vector3D dV, double isp) Build a maneuver defined in spacecraft frame.

Uses of SpacecraftState in org.orekit.forces.radiation

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

Modifier and Type	Method and Description
Vector3D	SolarRadiationPressure.acceleration(SpacecraftState s, double[] parameters) Compute acceleration.

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 and Description
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	GlobalIonosphereMapModel.pathDelay(SpacecraftState state, TopocentricFrame baseFrame, double frequency, double[] parameters)

Uses of SpacecraftState in org.orekit.propagation

Methods in org.orekit.propagation that return SpacecraftState

Modifier and Type	Method and Description
SpacecraftState	SpacecraftState.addAdditionalState(String name, double... value) Add an additional state.
SpacecraftState	AbstractPropagator.getInitialState() Get the propagator initial state.
SpacecraftState	Propagator.getInitialState() Get the propagator initial state.
SpacecraftState	SpacecraftState.interpolate(AbsoluteDate date, Stream<SpacecraftState> sample) Get an interpolated instance.
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.
protected SpacecraftState	AbstractPropagator.updateAdditionalStates(SpacecraftState original) Update state by adding all additional states.

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

Modifier and Type	Method and 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 and Description
void	SpacecraftState.ensureCompatibleAdditionalStates(SpacecraftState state) Check if two instances have the same set of additional states available.
double[]	AdditionalStateProvider.getAdditionalState(SpacecraftState state) Get the additional state.
void	AbstractPropagator.resetInitialState(SpacecraftState state) Reset the propagator initial state.
void	Propagator.resetInitialState(SpacecraftState state) Reset the propagator initial state.
protected SpacecraftState	AbstractPropagator.updateAdditionalStates(SpacecraftState original) Update state by adding all additional states.

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

Modifier and Type	Method and Description
SpacecraftState	SpacecraftState.interpolate(AbsoluteDate date, Stream<SpacecraftState> sample) Get an interpolated instance.

Constructors in org.orekit.propagation with parameters of type SpacecraftState

Constructor and 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 and Description
protected SpacecraftState	AbstractAnalyticalPropagator.acceptStep(OrekitStepInterpolator interpolator, AbsoluteDate target, double epsilon) Accept a step, triggering events and step handlers.
SpacecraftState	J2DifferentialEffect.apply(SpacecraftState state1) Apply the effect to a spacecraft state.
SpacecraftState	AdapterPropagator.DifferentialEffect.apply(SpacecraftState original) Apply the effect to a spacecraft state.
protected SpacecraftState	AdapterPropagator.basicPropagate(AbsoluteDate date) Propagate an orbit without any fancy features.
protected SpacecraftState	AbstractAnalyticalPropagator.basicPropagate(AbsoluteDate date) Propagate an orbit without any fancy features.
SpacecraftState	Ephemeris.basicPropagate(AbsoluteDate date)
SpacecraftState	AggregateBoundedPropagator.getInitialState()
SpacecraftState	AdapterPropagator.getInitialState() Get the propagator initial state.
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 with parameters of type SpacecraftState

Modifier and Type	Method and Description
SpacecraftState	J2DifferentialEffect.apply(SpacecraftState state1) Apply the effect to a spacecraft state.
SpacecraftState	AdapterPropagator.DifferentialEffect.apply(SpacecraftState original) Apply the effect to a spacecraft state.
void	KeplerianPropagator.resetInitialState(SpacecraftState state) Reset the propagator initial state.
void	AggregateBoundedPropagator.resetInitialState(SpacecraftState state)
void	AdapterPropagator.resetInitialState(SpacecraftState state) Reset the propagator initial state.
void	EcksteinHechlerPropagator.resetInitialState(SpacecraftState state) Reset the propagator initial state.
void	Ephemeris.resetInitialState(SpacecraftState state) Try (and fail) to reset the initial state.
protected void	KeplerianPropagator.resetIntermediateState(SpacecraftState state, boolean forward) Reset an intermediate state.
protected void	AggregateBoundedPropagator.resetIntermediateState(SpacecraftState state, boolean forward)
protected void	AdapterPropagator.resetIntermediateState(SpacecraftState state, boolean forward) Reset an intermediate state.
protected void	EcksteinHechlerPropagator.resetIntermediateState(SpacecraftState state, boolean forward) Reset an intermediate state.
protected abstract void	AbstractAnalyticalPropagator.resetIntermediateState(SpacecraftState state, boolean forward) Reset an intermediate state.
protected void	Ephemeris.resetIntermediateState(SpacecraftState state, boolean forward) Reset an intermediate state.

Constructors in org.orekit.propagation.analytical with parameters of type SpacecraftState

Constructor and 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 and Description
Ephemeris(List<SpacecraftState> states, int interpolationPoints) Constructor with tabulated states.
Ephemeris(List<SpacecraftState> states, int interpolationPoints, double extrapolationThreshold) 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 and Description
double[]	ClockCorrectionsProvider.getAdditionalState(SpacecraftState state) Get the additional state.
void	GLONASSAnalyticalPropagator.resetInitialState(SpacecraftState state) Reset the propagator initial state.
void	AbstractGNSSPropagator.resetInitialState(SpacecraftState state) Reset the propagator initial state.
protected void	GLONASSAnalyticalPropagator.resetIntermediateState(SpacecraftState state, boolean forward) Reset an intermediate state.
protected void	AbstractGNSSPropagator.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 and Description
void	TLEPropagator.resetInitialState(SpacecraftState state) Reset the propagator initial state.
protected void	TLEPropagator.resetIntermediateState(SpacecraftState state, boolean forward) Reset an intermediate state.

Uses of SpacecraftState in org.orekit.propagation.conversion

Methods in org.orekit.propagation.conversion that return SpacecraftState

Modifier and Type	Method and 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 and 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 and Description
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, List<String> freeParameters) Find the propagator that minimize the mean square error for a sample of states.
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	PropagatorConverter.convert(List<SpacecraftState> states, boolean positionOnly, 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 and Description
OsculatingToMeanElementsConverter(SpacecraftState state, int satelliteRevolution, Propagator propagator, double positionScale) Constructor.

Uses of SpacecraftState in org.orekit.propagation.events

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

Modifier and Type	Method and Description
SpacecraftState	EventState.EventOccurrence.getNewState() Get the new state for a reset action.
SpacecraftState	EventsLogger.LoggedEvent.getState() Get the triggering state.
default SpacecraftState	EventDetector.resetState(SpacecraftState oldState) Reset the state prior to continue propagation.
SpacecraftState	AbstractDetector.resetState(SpacecraftState oldState) Reset the state prior to continue propagation.
SpacecraftState	AdapterDetector.resetState(SpacecraftState oldState) Reset the state prior to continue propagation.

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

Modifier and Type	Method and Description
ToDoubleFunction<SpacecraftState>	FunctionalDetector.getFunction() Get the switching function.

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

Modifier and Type	Method and Description
EventState.EventOccurrence	EventState.doEvent(SpacecraftState state) Notify the user's listener of the event.
boolean	EnablingPredicate.eventIsEnabled(SpacecraftState state, S eventDetector, double g) Compute an event enabling function of state.
Action	EventDetector.eventOccurred(SpacecraftState s, boolean increasing) Handle the event.
Action	AbstractDetector.eventOccurred(SpacecraftState s, boolean increasing) Handle the event.
Action	AdapterDetector.eventOccurred(SpacecraftState s, boolean increasing) Handle the event.
double	DateDetector.g(SpacecraftState s) Compute the value of the switching function.
double	GroundFieldOfViewDetector.g(SpacecraftState s) Compute the value of the switching function.
double	FootprintOverlapDetector.g(SpacecraftState s) Compute the value of the switching function.
double	EventDetector.g(SpacecraftState s) Compute the value of the switching function.
double	FieldOfViewDetector.g(SpacecraftState s) Compute the value of the switching function.
double	LatitudeExtremumDetector.g(SpacecraftState s) Compute the value of the detection function.
abstract double	AbstractDetector.g(SpacecraftState s) Compute the value of the switching function.
double	LongitudeCrossingDetector.g(SpacecraftState s) Compute the value of the detection function.
double	CircularFieldOfViewDetector.g(SpacecraftState s) Compute the value of the switching function.
double	InterSatDirectViewDetector.g(SpacecraftState state) Compute the value of the switching function.
double	MagneticFieldDetector.g(SpacecraftState s) Compute the value of the detection function.
double	LatitudeCrossingDetector.g(SpacecraftState s) Compute the value of the detection function.
double	NodeDetector.g(SpacecraftState s) Compute the value of the switching function.
double	GroundAtNightDetector.g(SpacecraftState state) Compute the value of the switching function.
double	EventShifter.g(SpacecraftState s) Compute the value of the switching function.
double	EventEnablingPredicateFilter.g(SpacecraftState s) Compute the value of the switching function.
double	FunctionalDetector.g(SpacecraftState s)
double	ElevationExtremumDetector.g(SpacecraftState s) Compute the value of the detection function.
double	BooleanDetector.g(SpacecraftState s)
double	EventSlopeFilter.g(SpacecraftState s) Compute the value of the switching function.
double	NegateDetector.g(SpacecraftState s)
double	AngularSeparationDetector.g(SpacecraftState s) Compute the value of the switching function.
double	ApsideDetector.g(SpacecraftState s) Compute the value of the switching function.
double	LongitudeExtremumDetector.g(SpacecraftState s) Compute the value of the detection function.
double	GeographicZoneDetector.g(SpacecraftState s) Compute the value of the detection function.
double	AltitudeDetector.g(SpacecraftState s) Compute the value of the switching function.
double	AdapterDetector.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	AlignmentDetector.g(SpacecraftState s) Compute the value of the switching function.
double	PositionAngleDetector.g(SpacecraftState s) Compute the value of the detection function.
double	ElevationExtremumDetector.getElevation(SpacecraftState s) Get the elevation value.
default void	EventDetector.init(SpacecraftState s0, AbsoluteDate t) Initialize event handler at the start of a propagation.
void	AbstractDetector.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	EventShifter.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	BooleanDetector.init(SpacecraftState s0, AbsoluteDate t)
void	EventSlopeFilter.init(SpacecraftState s0, AbsoluteDate t) Initialize event handler at the start of a propagation.
void	NegateDetector.init(SpacecraftState s0, AbsoluteDate t)
void	EventState.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	PositionAngleDetector.init(SpacecraftState s0, AbsoluteDate t) Initialize event handler at the start of a propagation.
default SpacecraftState	EventDetector.resetState(SpacecraftState oldState) Reset the state prior to continue propagation.
SpacecraftState	AbstractDetector.resetState(SpacecraftState oldState) Reset the state prior to continue propagation.
SpacecraftState	AdapterDetector.resetState(SpacecraftState oldState) Reset the state prior to continue 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 and Description
FunctionalDetector	FunctionalDetector.withFunction(ToDoubleFunction<SpacecraftState> newGFunction) Create a new event detector with a new g function, keeping all other attributes the same.

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

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

Modifier and Type	Method and Description
SpacecraftState	RecordAndContinue.Event.getState() Get the spacecraft's state at the event.
default SpacecraftState	EventHandler.resetState(T detector, SpacecraftState oldState) Reset the state prior to continue propagation.
SpacecraftState	RecordAndContinue.resetState(T detector, SpacecraftState oldState)

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

Modifier and Type	Method and Description
Action	EventHandler.eventOccurred(SpacecraftState s, T detector, boolean increasing) eventOccurred method mirrors the same interface method as in EventDetector and its subclasses, but with an additional parameter that allows the calling method to pass in an object from the detector which would have potential additional data to allow the implementing class to determine the correct return state.
Action	StopOnIncreasing.eventOccurred(SpacecraftState s, T detector, boolean increasing) Handle a detection event and choose what to do next.
Action	RecordAndContinue.eventOccurred(SpacecraftState s, T detector, boolean increasing)
Action	StopOnDecreasing.eventOccurred(SpacecraftState s, T detector, boolean increasing) Handle a detection event and choose what to do next.
Action	ContinueOnEvent.eventOccurred(SpacecraftState s, T detector, boolean increasing) Specific implementation of the eventOccurred interface.
Action	StopOnEvent.eventOccurred(SpacecraftState s, T detector, boolean increasing) Specific implementation of the eventOccurred interface.
default void	EventHandler.init(SpacecraftState initialState, AbsoluteDate target) Initialize event handler at the start of a propagation.
default SpacecraftState	EventHandler.resetState(T detector, SpacecraftState oldState) Reset the state prior to continue propagation.
SpacecraftState	RecordAndContinue.resetState(T detector, SpacecraftState oldState)

Uses of SpacecraftState in org.orekit.propagation.integration

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

Modifier and Type	Method and 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.
abstract SpacecraftState	StateMapper.mapArrayToState(AbsoluteDate date, double[] y, double[] yDot, PropagationType type) Map the raw double components to a spacecraft state.
SpacecraftState	StateMapper.mapArrayToState(double t, 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	AbstractIntegratedPropagator.propagate(AbsoluteDate tEnd, boolean activateHandlers) Propagation with or without event detection.

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

Modifier and Type	Method and Description
protected void	AbstractIntegratedPropagator.beforeIntegration(SpacecraftState initialState, AbsoluteDate tEnd) Method called just before integration.
double[]	AbstractIntegratedPropagator.MainStateEquations.computeDerivatives(SpacecraftState state) Compute differential equations for main state.
double[]	AdditionalEquations.computeDerivatives(SpacecraftState s, double[] pDot) Compute the derivatives related to the additional state parameters.
protected abstract double[][]	AbstractJacobiansMapper.getConversionJacobian(SpacecraftState state) Get the conversion Jacobian between state parameters and parameters used for derivatives.
abstract void	AbstractJacobiansMapper.getParametersJacobian(SpacecraftState state, double[][] dYdP) Get the Jacobian with respect to parameters from a one-dimensional additional state array.
abstract void	AbstractJacobiansMapper.getStateJacobian(SpacecraftState state, double[][] dYdY0) Get the Jacobian with respect to state from a one-dimensional additional state array.
default void	AbstractIntegratedPropagator.MainStateEquations.init(SpacecraftState initialState, AbsoluteDate target) Initialize the equations at the start of propagation.
default void	AdditionalEquations.init(SpacecraftState initialState, AbsoluteDate target) Initialize the equations at the start of propagation.
abstract void	StateMapper.mapStateToArray(SpacecraftState state, double[] y, double[] yDot) Map a spacecraft state to raw double components.
void	IntegratedEphemeris.resetInitialState(SpacecraftState state) Reset the propagator initial state.
protected void	IntegratedEphemeris.resetIntermediateState(SpacecraftState state, boolean forward) Reset an intermediate state.
abstract void	AbstractJacobiansMapper.setInitialJacobians(SpacecraftState state, double[][] dY1dY0, double[][] dY1dP, double[] p) Set the Jacobian with respect to state into a one-dimensional additional state array.

Uses of SpacecraftState in org.orekit.propagation.numerical

Methods in org.orekit.propagation.numerical that return SpacecraftState

Modifier and Type	Method and Description
SpacecraftState	PartialDerivativesEquations.setInitialJacobians(SpacecraftState s0) Set the initial value of the Jacobian with respect to state and parameter.
SpacecraftState	PartialDerivativesEquations.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 and Description
protected void	NumericalPropagator.beforeIntegration(SpacecraftState initialState, AbsoluteDate tEnd) Method called just before integration.
double[]	PartialDerivativesEquations.computeDerivatives(SpacecraftState s, double[] pDot) Compute the derivatives related to the additional state parameters.
protected double[][]	JacobiansMapper.getConversionJacobian(SpacecraftState state) Get the conversion Jacobian between state parameters and parameters used for derivatives.
void	JacobiansMapper.getParametersJacobian(SpacecraftState state, double[][] dYdP) Get the Jacobian with respect to parameters from a one-dimensional additional state array.
PVCoordinates	GLONASSNumericalPropagator.getPVInPZ90(SpacecraftState state) This method transforms the PV coordinates obtained after the numerical integration in the ECEF PZ-90.
void	JacobiansMapper.getStateJacobian(SpacecraftState state, double[][] dYdY0) Get the Jacobian with respect to state from a one-dimensional additional state array.
void	NumericalPropagator.resetInitialState(SpacecraftState state) Reset the propagator initial state.
SpacecraftState	PartialDerivativesEquations.setInitialJacobians(SpacecraftState s0) Set the initial value of the Jacobian with respect to state and parameter.
SpacecraftState	PartialDerivativesEquations.setInitialJacobians(SpacecraftState s1, double[][] dY1dY0, double[][] dY1dP) Set the initial value of the Jacobian with respect to state and parameter.
void	JacobiansMapper.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.sampling

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

Modifier and Type	Method and 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 and Description
void	OrekitFixedStepHandler.handleStep(SpacecraftState currentState, boolean isLast) Handle the current step.
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	OrekitStepHandlerMultiplexer.init(SpacecraftState s0, AbsoluteDate t) Initialize step handler at the start of a propagation.
default void	OrekitFixedStepHandler.init(SpacecraftState s0, AbsoluteDate t, double step) 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 and Description
default void	MultiSatStepHandler.init(List<SpacecraftState> states0, 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 and Description
static SpacecraftState	DSSTPropagator.computeMeanState(SpacecraftState osculating, AttitudeProvider attitudeProvider, Collection<DSSTForceModel> forceModels) 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.
SpacecraftState	DSSTPartialDerivativesEquations.setInitialJacobians(SpacecraftState s0) Set the initial value of the Jacobian with respect to state and parameter.
SpacecraftState	DSSTPartialDerivativesEquations.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.semianalytical.dsst with parameters of type SpacecraftState

Modifier and Type	Method and Description
protected void	DSSTPropagator.beforeIntegration(SpacecraftState initialState, AbsoluteDate tEnd) Method called just before integration.
double[]	DSSTPartialDerivativesEquations.computeDerivatives(SpacecraftState s, double[] pDot) Compute the derivatives related to the additional state parameters.
static SpacecraftState	DSSTPropagator.computeMeanState(SpacecraftState osculating, AttitudeProvider attitudeProvider, Collection<DSSTForceModel> forceModels) Conversion from osculating to mean orbit.
static SpacecraftState	DSSTPropagator.computeOsculatingState(SpacecraftState mean, AttitudeProvider attitudeProvider, Collection<DSSTForceModel> forces) Conversion from mean to osculating orbit.
protected double[][]	DSSTJacobiansMapper.getConversionJacobian(SpacecraftState state) Get the conversion Jacobian between state parameters and parameters used for derivatives.
void	DSSTJacobiansMapper.getParametersJacobian(SpacecraftState state, double[][] dYdP) Get the Jacobian with respect to parameters from a one-dimensional additional state array.
void	DSSTJacobiansMapper.getStateJacobian(SpacecraftState state, double[][] dYdY0) Get the Jacobian with respect to state from a one-dimensional additional state array.
void	DSSTPropagator.resetInitialState(SpacecraftState state) Reset the initial state.
SpacecraftState	DSSTPartialDerivativesEquations.setInitialJacobians(SpacecraftState s0) Set the initial value of the Jacobian with respect to state and parameter.
SpacecraftState	DSSTPartialDerivativesEquations.setInitialJacobians(SpacecraftState s1, double[][] dY1dY0, double[][] dY1dP) Set the initial value of the Jacobian with respect to state and parameter.
void	DSSTJacobiansMapper.setInitialJacobians(SpacecraftState state, double[][] dY1dY0, double[][] dY1dP, double[] p) Set the Jacobian with respect to state into a one-dimensional additional state array.
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	DSSTJacobiansMapper.setShortPeriodJacobians(SpacecraftState s) Compute the derivatives of the short period terms related to the additional state parameters.

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 and Description
protected abstract double[]	AbstractGaussianContribution.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[]	DSSTAtmosphericDrag.getLLimits(SpacecraftState state, AuxiliaryElements auxiliaryElements) Compute the limits in L, the true longitude, for integration.
double[]	AbstractGaussianContribution.getMeanElementRate(SpacecraftState state, 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[]	DSSTTesseral.getMeanElementRate(SpacecraftState spacecraftState, 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[]	DSSTZonal.getMeanElementRate(SpacecraftState spacecraftState, 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.
void	AbstractGaussianContribution.updateShortPeriodTerms(double[] parameters, SpacecraftState... meanStates) Update the short period terms.
void	DSSTThirdBody.updateShortPeriodTerms(double[] parameters, SpacecraftState... meanStates) Update the short period terms.
void	DSSTTesseral.updateShortPeriodTerms(double[] parameters, SpacecraftState... meanStates) Update the short period terms.
void	DSSTNewtonianAttraction.updateShortPeriodTerms(double[] parameters, SpacecraftState... meanStates) Update the short period terms.
void	DSSTZonal.updateShortPeriodTerms(double[] parameters, SpacecraftState... meanStates) Update the short period terms.
void	DSSTForceModel.updateShortPeriodTerms(double[] parameters, SpacecraftState... meanStates) Update the short period terms.

Uses of SpacecraftState in org.orekit.utils

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

Modifier and Type	Method and Description
double[][]	StateJacobian.value(SpacecraftState state) Evaluate the Jacobian of the function.
double[]	StateFunction.value(SpacecraftState state) Evaluate the function.