Uses of Class
org.orekit.propagation.SpacecraftState

Packages that use SpacecraftState

Package	Description
org.orekit.files.ccsds	This package provides a parser for orbit data stored in CCSDS Orbit Data Message format.
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
org.orekit.forces.gravity	This package provides all gravity-related forces.
org.orekit.forces.maneuvers	This package provides models of simple maneuvers.
org.orekit.forces.radiation
org.orekit.propagation	This package provides tools to propagate orbital states with different methods.
org.orekit.propagation.analytical
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
org.orekit.propagation.numerical
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

Uses of SpacecraftState in org.orekit.files.ccsds

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

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

Uses of SpacecraftState in org.orekit.forces

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

Modifier and Type	Method and Description
FieldVector3D<DerivativeStructure>	ForceModel.accelerationDerivatives(SpacecraftState s, String paramName) Compute acceleration derivatives with respect to additional parameters.
void	ForceModel.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing 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
FieldVector3D<DerivativeStructure>	DragForce.accelerationDerivatives(SpacecraftState s, String paramName) Compute acceleration derivatives with respect to additional parameters.
void	DragForce.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the drag to the perturbing 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
FieldVector3D<DerivativeStructure>	SolidTides.accelerationDerivatives(SpacecraftState s, String paramName) Compute acceleration derivatives with respect to additional parameters.
FieldVector3D<DerivativeStructure>	CunninghamAttractionModel.accelerationDerivatives(SpacecraftState s, String paramName) Compute acceleration derivatives with respect to additional parameters.
FieldVector3D<DerivativeStructure>	Relativity.accelerationDerivatives(SpacecraftState s, String paramName)
FieldVector3D<DerivativeStructure>	ThirdBodyAttraction.accelerationDerivatives(SpacecraftState s, String paramName) Compute acceleration derivatives with respect to additional parameters.
FieldVector3D<DerivativeStructure>	OceanTides.accelerationDerivatives(SpacecraftState s, String paramName) Compute acceleration derivatives with respect to additional parameters.
FieldVector3D<DerivativeStructure>	DrozinerAttractionModel.accelerationDerivatives(SpacecraftState s, String paramName) Compute acceleration derivatives with respect to additional parameters.
FieldVector3D<DerivativeStructure>	HolmesFeatherstoneAttractionModel.accelerationDerivatives(SpacecraftState s, String paramName) Compute acceleration derivatives with respect to additional parameters.
FieldVector3D<DerivativeStructure>	NewtonianAttraction.accelerationDerivatives(SpacecraftState s, String paramName) Compute acceleration derivatives with respect to additional parameters.
void	SolidTides.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.
void	CunninghamAttractionModel.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.
void	Relativity.addContribution(SpacecraftState s, TimeDerivativesEquations adder)
void	ThirdBodyAttraction.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.
void	OceanTides.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.
void	DrozinerAttractionModel.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.
void	HolmesFeatherstoneAttractionModel.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing 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.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
FieldVector3D<DerivativeStructure>	ConstantThrustManeuver.accelerationDerivatives(SpacecraftState s, String paramName) Compute acceleration derivatives with respect to additional parameters.
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.

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
FieldVector3D<DerivativeStructure>	SolarRadiationPressure.accelerationDerivatives(SpacecraftState s, String paramName) Compute acceleration derivatives with respect to additional parameters.
void	SolarRadiationPressure.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.

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	Propagator.getInitialState() Get the propagator initial state.
SpacecraftState	AbstractPropagator.getInitialState() Get the propagator initial state.
SpacecraftState	SpacecraftState.interpolate(AbsoluteDate date, Collection<SpacecraftState> sample) Get an interpolated instance.
SpacecraftState	Propagator.propagate(AbsoluteDate target) Propagate towards a target date.
SpacecraftState	AbstractPropagator.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.
protected SpacecraftState	AbstractPropagator.updateAdditionalStates(SpacecraftState original) Update state by adding all additional states.

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	Propagator.resetInitialState(SpacecraftState state) Reset the propagator initial state.
void	AbstractPropagator.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, Collection<SpacecraftState> sample) Get an interpolated instance.

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(AbsoluteDate target, double epsilon) 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	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	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	AdapterPropagator.DifferentialEffect.apply(SpacecraftState original) Apply the effect to a spacecraft state.
SpacecraftState	J2DifferentialEffect.apply(SpacecraftState state1) Apply the effect to a spacecraft state.
void	AdapterPropagator.resetInitialState(SpacecraftState state) Reset the propagator initial state.
void	EcksteinHechlerPropagator.resetInitialState(SpacecraftState state) Reset the propagator initial state.
void	KeplerianPropagator.resetInitialState(SpacecraftState state) Reset the propagator initial state.
void	Ephemeris.resetInitialState(SpacecraftState state) Try (and fail) to reset the initial 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.

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.

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, Collection<String> freeParameters) Find the propagator that minimize the mean square error for a sample of states.
Propagator	PropagatorConverter.convert(List<SpacecraftState> states, boolean positionOnly, Collection<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) 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	EventsLogger.LoggedEvent.getState() Get the triggering state.
SpacecraftState	EventState.reset(SpacecraftState oldState) Let the event detector reset the state if it wants.
SpacecraftState	AbstractDetector.resetState(SpacecraftState oldState) Reset the state prior to continue propagation.
SpacecraftState	EventDetector.resetState(SpacecraftState oldState) Reset the state prior to continue propagation.

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

Modifier and Type	Method and Description
EventHandler.Action	AbstractDetector.eventOccurred(SpacecraftState s, boolean increasing) Handle the event.
EventHandler.Action	EventDetector.eventOccurred(SpacecraftState s, boolean increasing) Handle the event.
double	GeographicZoneDetector.g(SpacecraftState s) Compute the value of the detection function.
double	DateDetector.g(SpacecraftState s) Compute the value of the switching function.
double	ApsideDetector.g(SpacecraftState s) Compute the value of the switching function.
double	NodeDetector.g(SpacecraftState s) Compute the value of the switching function.
double	EventFilter.g(SpacecraftState s) Compute the value of the switching function.
double	EclipseDetector.g(SpacecraftState s) Compute the value of the switching function.
double	AlignmentDetector.g(SpacecraftState s) Compute the value of the switching function.
double	DihedralFieldOfViewDetector.g(SpacecraftState s) Compute the value of the switching function.
double	AltitudeDetector.g(SpacecraftState s) Compute the value of the switching function.
double	CircularFieldOfViewDetector.g(SpacecraftState s) Compute the value of the switching function.
abstract double	AbstractDetector.g(SpacecraftState s) Compute the value of the switching function.
double	ElevationDetector.g(SpacecraftState s) Compute the value of the switching function.
double	EventShifter.g(SpacecraftState s) Compute the value of the switching function.
double	EventDetector.g(SpacecraftState s) Compute the value of the switching function.
void	EventState.init(SpacecraftState s0, AbsoluteDate t) Initialize event handler at the start of a propagation.
void	EventFilter.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	EventShifter.init(SpacecraftState s0, AbsoluteDate t) Initialize event handler at the start of a propagation.
void	EventDetector.init(SpacecraftState s0, AbsoluteDate t) Initialize event handler at the start of a propagation.
void	EventState.reinitializeBegin(SpacecraftState state0, boolean isForward) Reinitialize the beginning of the step.
SpacecraftState	EventState.reset(SpacecraftState oldState) Let the event detector reset the state if it wants.
SpacecraftState	AbstractDetector.resetState(SpacecraftState oldState) Reset the state prior to continue propagation.
SpacecraftState	EventDetector.resetState(SpacecraftState oldState) Reset the state prior to continue propagation.
void	EventState.stepAccepted(SpacecraftState state) Acknowledge the fact the step has been accepted by the propagator.

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	StopOnIncreasing.resetState(T detector, SpacecraftState oldState) Reset the state prior to continue propagation.
SpacecraftState	ContinueOnEvent.resetState(T detector, SpacecraftState oldState) Reset the state prior to continue propagation.
SpacecraftState	EventHandler.resetState(T detector, SpacecraftState oldState) Reset the state prior to continue propagation.
SpacecraftState	StopOnDecreasing.resetState(T detector, SpacecraftState oldState) Reset the state prior to continue propagation.
SpacecraftState	StopOnEvent.resetState(T 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 and Description
EventHandler.Action	StopOnIncreasing.eventOccurred(SpacecraftState s, T detector, boolean increasing) Handle a detection event and choose what to do next.
EventHandler.Action	ContinueOnEvent.eventOccurred(SpacecraftState s, T detector, boolean increasing) Specific implementation of the eventOccurred interface.
EventHandler.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.
EventHandler.Action	StopOnDecreasing.eventOccurred(SpacecraftState s, T detector, boolean increasing) Handle a detection event and choose what to do next.
EventHandler.Action	StopOnEvent.eventOccurred(SpacecraftState s, T detector, boolean increasing) Specific implementation of the eventOccurred interface.
SpacecraftState	StopOnIncreasing.resetState(T detector, SpacecraftState oldState) Reset the state prior to continue propagation.
SpacecraftState	ContinueOnEvent.resetState(T detector, SpacecraftState oldState) Reset the state prior to continue propagation.
SpacecraftState	EventHandler.resetState(T detector, SpacecraftState oldState) Reset the state prior to continue propagation.
SpacecraftState	StopOnDecreasing.resetState(T detector, SpacecraftState oldState) Reset the state prior to continue propagation.
SpacecraftState	StopOnEvent.resetState(T 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 and Description
protected SpacecraftState	IntegratedEphemeris.basicPropagate(AbsoluteDate date) Propagate an orbit without any fancy features.
SpacecraftState	IntegratedEphemeris.getInitialState() Get the propagator initial state.
abstract SpacecraftState	StateMapper.mapArrayToState(double t, double[] y, boolean meanOnly) 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.
abstract void	StateMapper.mapStateToArray(SpacecraftState state, double[] y) Map a spacecraft state to raw double components.
void	IntegratedEphemeris.resetInitialState(SpacecraftState state) Reset the propagator initial state.

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 s1, double[][] dY1dY0, double[][] dY1dP) Set the initial value of the Jacobian with respect to state and parameter.
SpacecraftState	PartialDerivativesEquations.setInitialJacobians(SpacecraftState s0, int stateDimension, int paramDimension) 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
FieldVector3D<DerivativeStructure>	Jacobianizer.accelerationDerivatives(SpacecraftState s, String paramName) Compute acceleration and derivatives with respect to parameter.
double[]	PartialDerivativesEquations.computeDerivatives(SpacecraftState s, double[] pDot) Compute the derivatives related to the additional state parameters.
void	JacobiansMapper.getParametersJacobian(SpacecraftState state, double[][] dYdP) Get theJacobian with respect to parameters from a one-dimensional additional state array.
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 s1, double[][] dY1dY0, double[][] dY1dP) Set the initial value of the Jacobian with respect to state and parameter.
SpacecraftState	PartialDerivativesEquations.setInitialJacobians(SpacecraftState s0, int stateDimension, int paramDimension) Set the initial value of the Jacobian with respect to state and parameter.
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.getInterpolatedState() Get the interpolated state.

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.
void	OrekitStepHandlerMultiplexer.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	OrekitFixedStepHandler.init(SpacecraftState s0, AbsoluteDate t) Initialize step handler at the start of a propagation.
void	OrekitStepHandler.init(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 and Description
static SpacecraftState	DSSTPropagator.computeMeanState(SpacecraftState osculating, Collection<DSSTForceModel> forces) Conversion from osculating to mean, orbit.
static SpacecraftState	DSSTPropagator.computeOsculatingState(SpacecraftState mean, Collection<DSSTForceModel> forces) Conversion from mean to osculating orbit.

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.
static SpacecraftState	DSSTPropagator.computeMeanState(SpacecraftState osculating, Collection<DSSTForceModel> forces) Conversion from osculating to mean, orbit.
static SpacecraftState	DSSTPropagator.computeOsculatingState(SpacecraftState mean, Collection<DSSTForceModel> forces) Conversion from mean to osculating orbit.
void	DSSTPropagator.resetInitialState(SpacecraftState state) Reset the initial state.
void	DSSTPropagator.setInitialState(SpacecraftState initialState) Set the initial state with osculating orbital elements.
void	DSSTPropagator.setInitialState(SpacecraftState initialState, boolean isOsculating) Set the initial state.

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
void	AbstractGaussianContribution.computeShortPeriodicsCoefficients(SpacecraftState state) Compute the coefficients used for short periodic variations.
void	DSSTThirdBody.computeShortPeriodicsCoefficients(SpacecraftState state) Compute the coefficients used for short periodic variations.
void	DSSTCentralBody.computeShortPeriodicsCoefficients(SpacecraftState state) Compute the coefficients used for short periodic variations.
void	DSSTForceModel.computeShortPeriodicsCoefficients(SpacecraftState state) Compute the coefficients used for short periodic variations.
protected Vector3D	AbstractGaussianContribution.getAcceleration(SpacecraftState state) Compute the acceleration due to the non conservative perturbing force.
protected abstract double[]	AbstractGaussianContribution.getLLimits(SpacecraftState state) Compute the limits in L, the true longitude, for integration.
protected double[]	DSSTSolarRadiationPressure.getLLimits(SpacecraftState state) Compute the limits in L, the true longitude, for integration.
protected double[]	DSSTAtmosphericDrag.getLLimits(SpacecraftState state) Compute the limits in L, the true longitude, for integration.
double[]	AbstractGaussianContribution.getMeanElementRate(SpacecraftState state) Computes the mean equinoctial elements rates dai / dt.
double[]	DSSTThirdBody.getMeanElementRate(SpacecraftState currentState) Computes the mean equinoctial elements rates dai / dt.
double[]	DSSTCentralBody.getMeanElementRate(SpacecraftState spacecraftState) Computes the mean equinoctial elements rates dai / dt.
double[]	DSSTForceModel.getMeanElementRate(SpacecraftState state) Computes the mean equinoctial elements rates dai / dt.