Uses of Class
org.orekit.propagation.SpacecraftState

Packages that use SpacecraftState

fr.cnes.sirius.patrius.assembly
fr.cnes.sirius.patrius.assembly.models
fr.cnes.sirius.patrius.assembly.models.cook
fr.cnes.sirius.patrius.assembly.properties
fr.cnes.sirius.patrius.events
fr.cnes.sirius.patrius.events.multi
fr.cnes.sirius.patrius.events.sensor
fr.cnes.sirius.patrius.forces
fr.cnes.sirius.patrius.forces.radiation
fr.cnes.sirius.patrius.propagation
fr.cnes.sirius.patrius.propagation.events.multi
fr.cnes.sirius.patrius.propagation.numerical.multi
fr.cnes.sirius.patrius.propagation.precomputed.multi
fr.cnes.sirius.patrius.propagation.sampling.multi
fr.cnes.sirius.patrius.stela
fr.cnes.sirius.patrius.stela.forces.drag
fr.cnes.sirius.patrius.stela.propagation
fr.cnes.sirius.patrius.wrenches
fr.cnes.sirius.validate.files
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
org.orekit.forces.gravity.tides
org.orekit.forces.gravity.variations
org.orekit.forces.maneuvers	This package provides models of simple maneuvers.
org.orekit.forces.radiation
org.orekit.forces.relativistic
org.orekit.parameter
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.events	This package provides interfaces and classes dealing with events occurring during propagation.
org.orekit.propagation.events.multi
org.orekit.propagation.numerical
org.orekit.propagation.precomputed
org.orekit.propagation.sampling	This package provides interfaces and classes dealing with step handling during propagation.
org.orekit.utils	This package provides useful objects.
org.orekit.wrenches

Uses of SpacecraftState in fr.cnes.sirius.patrius.assembly

Methods in fr.cnes.sirius.patrius.assembly with parameters of type SpacecraftState

void	Assembly.initMainPartFrame(SpacecraftState state) Initialize the main part's frame using a SpacecraftState as an input argument.
void	AssemblyBuilder.initMainPartFrame(SpacecraftState state) Sets up the main frame of the assembly from a "SpacecraftState" object.
void	Assembly.updateMainPartFrame(SpacecraftState state) Updates the main part frame's transformation to its parent frame using a Transform as an input argument.

Uses of SpacecraftState in fr.cnes.sirius.patrius.assembly.models

Methods in fr.cnes.sirius.patrius.assembly.models with parameters of type SpacecraftState

void	RediffusedRadiativeModel.addDAccDParamRediffusedRadiativePressure(SpacecraftState s, Parameter param, double[] dAccdParam)
void	RediffusedRadiativeModel.addDAccDStateRediffusedRadiativePressure(SpacecraftState s, double[][] dAccdPos, double[][] dAccdVel)
void	DragLiftModel.addDDragAccDParam(SpacecraftState s, Parameter param, double density, Vector3D relativeVelocity, double[] dAccdParam) Compute acceleration derivatives with respect to ballistic coefficient.
void	GlobalAeroModel.addDDragAccDParam(SpacecraftState s, Parameter param, double density, Vector3D relativeVelocity, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters (the ballistic coefficient).
void	AeroModel.addDDragAccDParam(SpacecraftState s, Parameter param, double density, Vector3D relativeVelocity, double[] dAccdParam) Compute acceleration derivatives with respect to ballistic coefficient.
void	DragLiftModel.addDDragAccDState(SpacecraftState s, double[][] dAccdPos, double[][] dAccdVel, double density, Vector3D acceleration, Vector3D relativeVelocity, boolean computeGradientPosition, boolean computeGradientVelocity) Compute acceleration derivatives with respect to state parameters (position and velocity).
void	GlobalAeroModel.addDDragAccDState(SpacecraftState s, double[][] dAccdPos, double[][] dAccdVel, double density, Vector3D acceleration, Vector3D relativeVelocity, boolean computeGradientPosition, boolean computeGradientVelocity) Compute acceleration derivatives with respect to state parameters (position and velocity).
void	AeroModel.addDDragAccDState(SpacecraftState s, double[][] dAccdPos, double[][] dAccdVel, double density, Vector3D acceleration, Vector3D relativeVelocity, boolean computeGradientPosition, boolean computeGradientVelocity) Compute acceleration derivatives with respect to state parameters (position and velocity).
void	DirectRadiativeModel.addDSRPAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam, Vector3D satSunVector) Compute acceleration derivatives with respect to additional parameters.
void	DirectRadiativeModel.addDSRPAccDState(SpacecraftState s, double[][] dAccdPos, double[][] dAccdVel, Vector3D satSunVector) Compute acceleration derivatives with respect to state parameters.
Vector3D	DragLiftModel.dragAcceleration(SpacecraftState state, double density, Vector3D relativeVelocity) Method to compute the aero acceleration, based on the assembly.
Vector3D	GlobalAeroModel.dragAcceleration(SpacecraftState state, double density, Vector3D relativeVelocity) Method to compute the aero acceleration, based on the assembly.
Vector3D	AeroModel.dragAcceleration(SpacecraftState state, double density, Vector3D relativeVelocity) Method to compute the aero acceleration, based on the assembly.
Wrench	AeroWrenchModel.dragWrench(SpacecraftState state, double density, Vector3D relativeVelocity)
Wrench	AeroWrenchModel.dragWrench(SpacecraftState state, double density, Vector3D relativeVelocity, Vector3D origin, Frame frame) Compute the torque due to radiation pressire.
protected static Vector3D	AeroModel.forceOnFacet(SpacecraftState state, IPart part, Assembly assembly, double density, Vector3D relativeVelocity) Method to compute the force for a plane model.
protected static Vector3D	DirectRadiativeModel.forceOnFacet(SpacecraftState state, IPart part, Vector3D flux) Method to compute the force for a plane model.
protected static Vector3D	AeroModel.forceOnSphere(SpacecraftState state, IPart part, double density, Vector3D relativeVelocity) Method to compute the force for a sphere model.
double	InertiaSimpleModel.getTotalMass(SpacecraftState state) Return the mass of the spacecraft following the order.
double	InertiaComputedModel.getTotalMass(SpacecraftState state) Return the mass of the spacecraft following the order.
double	MassModel.getTotalMass(SpacecraftState state) Return the mass of the spacecraft following the order.
Vector3D	DirectRadiativeModel.radiationPressureAcceleration(SpacecraftState state, Vector3D flux) Method to compute the radiation pressure acceleration, based on the assembly.
Wrench	DirectRadiativeWrenchModel.radiationWrench(SpacecraftState state, Vector3D flux) Compute the torque due to radiation pressire.
Wrench	DirectRadiativeWrenchModel.radiationWrench(SpacecraftState state, Vector3D flux, Vector3D origin, Frame frame) Compute the torque due to radiation pressire.
Vector3D	RediffusedRadiativeModel.rediffusedRadiationPressureAcceleration(SpacecraftState state, ElementaryFlux flux) Method to compute the rediffused radiation pressure acceleration, based on the assembly.

Uses of SpacecraftState in fr.cnes.sirius.patrius.assembly.models.cook

Methods in fr.cnes.sirius.patrius.assembly.models.cook with parameters of type SpacecraftState

double	CtCookModel.derivativeValue(Parameter p, SpacecraftState state) Compute the derivative value with respect to the input parameter.
double	CnCookModel.derivativeValue(Parameter p, SpacecraftState state) Compute the derivative value with respect to the input parameter.
double	AlphaConstant.getAlpha(SpacecraftState state) Return alpha (energy accomodation coefficient) value.
double	AlphaCookModel.getAlpha(SpacecraftState state) Return alpha (energy accomodation coefficient) value.
double	AlphaProvider.getAlpha(SpacecraftState state) Return alpha (energy accomodation coefficient) value.
double	ConstantWallGasTemperature.getWallGasTemperature(SpacecraftState state, Vector3D relativeVelocity, double theta) Compute wall gas temperature.
double	CookWallGasTemperature.getWallGasTemperature(SpacecraftState state, Vector3D relativeVelocity, double theta) Compute wall gas temperature.
double	WallGasTemperatureProvider.getWallGasTemperature(SpacecraftState state, Vector3D relativeVelocity, double theta) Compute wall gas temperature.
double	GinsWallGasTemperature.getWallGasTemperature(SpacecraftState state, Vector3D relativeVelocity, double theta) Compute wall gas temperature.
double	CtCookModel.value(SpacecraftState state) Getting the value of the function.
double	CnCookModel.value(SpacecraftState state) Getting the value of the function.

Uses of SpacecraftState in fr.cnes.sirius.patrius.assembly.properties

Methods in fr.cnes.sirius.patrius.assembly.properties with parameters of type SpacecraftState

void	MassEquation.computeDerivatives(SpacecraftState s, TimeDerivativesEquations adder) Compute the derivatives related to the additional state parameters.
double	AeroSphereProperty.getDragForceDerivativeValue(Parameter parameter, SpacecraftState s) Get the drag force coefficient derivative value with respect to the given parameter.

Uses of SpacecraftState in fr.cnes.sirius.patrius.events

Methods in fr.cnes.sirius.patrius.events that return SpacecraftState

SpacecraftState	CodedEventsLogger.LoggedCodedEvent.getState() Gets the SpacecraftState that caused the coded event.
SpacecraftState	GenericCodingEventDetector.resetState(SpacecraftState oldState)

Methods in fr.cnes.sirius.patrius.events with parameters of type SpacecraftState

CodedEvent	CodingEventDetector.buildCodedEvent(SpacecraftState s, boolean increasing) Build a CodedEvent instance appropriate for the provided SpacecraftState.
CodedEvent	GenericCodingEventDetector.buildCodedEvent(SpacecraftState s, boolean increasing)
CodedEvent	CodingEventDetector.buildDelayedCodedEvent(SpacecraftState s, boolean increasing) Build a delayed CodedEvent instance appropriate for the provided SpacecraftState.
CodedEvent	GenericCodingEventDetector.buildDelayedCodedEvent(SpacecraftState s, boolean increasing)
CodedEvent	CodingEventDetector.buildOccurrenceCodedEvent(SpacecraftState s, boolean increasing) Build a CodedEvent instance appropriate for the provided SpacecraftState.
CodedEvent	GenericCodingEventDetector.buildOccurrenceCodedEvent(SpacecraftState s, boolean increasing)
Map<CodingEventDetector,PhenomenaList>	CodedEventsLogger.buildPhenomenaListMap(AbsoluteDateInterval definitionInterval, SpacecraftState duringState) Builds a map of PhenomenaList, one list per CodingEventDetector instance.
EventDetector.Action	EarthZoneDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) Handle the event and choose what to do next.
EventDetector.Action	CombinedPhenomenaDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) Handle an event and choose what to do next.
EventDetector.Action	GenericCodingEventDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward)
EventDetector.Action	CentralBodyMaskCircularFOVDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) Handle a target in field of view outside eclipse reaching event and choose what to do next.
double	EarthZoneDetector.g(SpacecraftState s) Compute the value of the switching function.
double	CombinedPhenomenaDetector.g(SpacecraftState s) Compute the value of the switching function for a combination (AND or OR) of two phenomena. After computing the switching function of each detector and, if necessary, changing its sign to apply a general convention (g>0 if the phenomenon associated to an event is active), it returns one between the two g functions, according to the boolean operator.
double	GenericCodingEventDetector.g(SpacecraftState s)
double	CentralBodyMaskCircularFOVDetector.g(SpacecraftState s) The switching function is the minimum value between the eclipse detector g function and the circularFOVDetector
void	EarthZoneDetector.init(SpacecraftState s0, AbsoluteDate t)
void	CombinedPhenomenaDetector.init(SpacecraftState s0, AbsoluteDate t)
void	GenericCodingEventDetector.init(SpacecraftState s0, AbsoluteDate t)
boolean	GenericCodingEventDetector.isStateActive(SpacecraftState state) Tells if the event state is "active" for the given input.
SpacecraftState	GenericCodingEventDetector.resetState(SpacecraftState oldState)

Uses of SpacecraftState in fr.cnes.sirius.patrius.events.multi

Methods in fr.cnes.sirius.patrius.events.multi that return types with arguments of type SpacecraftState

Map<String,SpacecraftState>	MultiCodedEventsLogger.MultiLoggedCodedEvent.getStates() Gets the map of SpacecraftState that caused the coded event.
Map<String,SpacecraftState>	MultiEventsLogger.MultiLoggedEvent.getStates() Get the triggering states.
Map<String,SpacecraftState>	MultiGenericCodingEventDetector.resetStates(Map<String,SpacecraftState> oldStates)

Method parameters in fr.cnes.sirius.patrius.events.multi with type arguments of type SpacecraftState

CodedEvent	MultiGenericCodingEventDetector.buildCodedEvent(Map<String,SpacecraftState> states, boolean increasing)
CodedEvent	MultiCodingEventDetector.buildCodedEvent(Map<String,SpacecraftState> s, boolean increasing) Build a CodedEvent instance appropriate for the provided map of SpacecraftState.
CodedEvent	MultiGenericCodingEventDetector.buildDelayedCodedEvent(Map<String,SpacecraftState> states, boolean increasing)
CodedEvent	MultiCodingEventDetector.buildDelayedCodedEvent(Map<String,SpacecraftState> s, boolean increasing) Build a delayed CodedEvent instance appropriate for the provided map of SpacecraftState.
CodedEvent	MultiGenericCodingEventDetector.buildOccurrenceCodedEvent(Map<String,SpacecraftState> states, boolean increasing)
CodedEvent	MultiCodingEventDetector.buildOccurrenceCodedEvent(Map<String,SpacecraftState> s, boolean increasing) Build a CodedEvent instance appropriate for the provided map of SpacecraftState.
Map<MultiCodingEventDetector,PhenomenaList>	MultiCodedEventsLogger.buildPhenomenaListMap(AbsoluteDateInterval definitionInterval, Map<String,SpacecraftState> duringState) Builds a map of PhenomenaList, one list per MultiCodingEventDetector instance.
EventDetector.Action	MultiGenericCodingEventDetector.eventOccurred(Map<String,SpacecraftState> s, boolean increasing, boolean forward)
double	MultiGenericCodingEventDetector.g(Map<String,SpacecraftState> s)
void	MultiGenericCodingEventDetector.init(Map<String,SpacecraftState> s0, AbsoluteDate t)
boolean	MultiGenericCodingEventDetector.isStateActive(Map<String,SpacecraftState> states) Tells if the multi event state is "active" for the given input.
Map<String,SpacecraftState>	MultiGenericCodingEventDetector.resetStates(Map<String,SpacecraftState> oldStates)

Uses of SpacecraftState in fr.cnes.sirius.patrius.events.sensor

Methods in fr.cnes.sirius.patrius.events.sensor that return types with arguments of type SpacecraftState

Map<String,SpacecraftState>

SatToSatMutualVisibilityDetector.resetStates(Map<String,SpacecraftState> oldStates)

Methods in fr.cnes.sirius.patrius.events.sensor with parameters of type SpacecraftState

EventDetector.Action	SatToSatMutualVisibilityDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward)
EventDetector.Action	MaskingDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) Handle "masking" event and choose what to do next.
EventDetector.Action	ExtremaSightAxisDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) Handle an event and choose what to do next.
EventDetector.Action	SensorVisibilityDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward)
EventDetector.Action	VisibilityFromStationDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) Handle "visibility from station" event and choose what to do next.
EventDetector.Action	TargetInFieldOfViewDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward)
EventDetector.Action	RFVisibilityDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward)
EventDetector.Action	StationToSatMutualVisibilityDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward)
EventDetector.Action	SensorInhibitionDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward)
double	SatToSatMutualVisibilityDetector.g(SpacecraftState s)
double	MaskingDetector.g(SpacecraftState s) Compute the value of the switching function.
double	ExtremaSightAxisDetector.g(SpacecraftState s) The switching function is specific case of the extrema three bodies angle detector.
double	SensorVisibilityDetector.g(SpacecraftState s)
double	VisibilityFromStationDetector.g(SpacecraftState s) Compute the value of the switching function.
double	TargetInFieldOfViewDetector.g(SpacecraftState s)
double	RFVisibilityDetector.g(SpacecraftState s) Compute the value of the switching function.
double	StationToSatMutualVisibilityDetector.g(SpacecraftState s)
double	SensorInhibitionDetector.g(SpacecraftState s)
protected Vector3D	AbstractDetectorWithTropoCorrection.getCorrectedVector(SpacecraftState s) Compute the apparent vector from the station to the spacecraft with tropospheric effects.
void	SatToSatMutualVisibilityDetector.init(SpacecraftState s0, AbsoluteDate t)
void	MaskingDetector.init(SpacecraftState s0, AbsoluteDate t) Initialize event handler at the start of a propagation.
void	ExtremaSightAxisDetector.init(SpacecraftState s0, AbsoluteDate t)
void	SensorVisibilityDetector.init(SpacecraftState s0, AbsoluteDate t)
void	VisibilityFromStationDetector.init(SpacecraftState s0, AbsoluteDate t) Initialize event handler at the start of a propagation.
void	TargetInFieldOfViewDetector.init(SpacecraftState s0, AbsoluteDate t)
void	StationToSatMutualVisibilityDetector.init(SpacecraftState s0, AbsoluteDate t)
void	SensorInhibitionDetector.init(SpacecraftState s0, AbsoluteDate t)

Method parameters in fr.cnes.sirius.patrius.events.sensor with type arguments of type SpacecraftState

EventDetector.Action	SatToSatMutualVisibilityDetector.eventOccurred(Map<String,SpacecraftState> s, boolean increasing, boolean forward)
double	SatToSatMutualVisibilityDetector.g(Map<String,SpacecraftState> s)
void	SatToSatMutualVisibilityDetector.init(Map<String,SpacecraftState> s0, AbsoluteDate t)
Map<String,SpacecraftState>	SatToSatMutualVisibilityDetector.resetStates(Map<String,SpacecraftState> oldStates)

Uses of SpacecraftState in fr.cnes.sirius.patrius.forces

Methods in fr.cnes.sirius.patrius.forces with parameters of type SpacecraftState

void	EmpiricalForce.addContribution(SpacecraftState state, TimeDerivativesEquations adder)
void	EmpiricalForce.addDAccDParam(SpacecraftState state, Parameter param, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters.
void	EmpiricalForce.addDAccDState(SpacecraftState state, double[][] dAccdPos, double[][] dAccdVel)
Vector3D	EmpiricalForce.computeAcceleration(PVCoordinates pv, LocalOrbitalFrame localFrameValidation, Vector3D vectorS, Frame frame, SpacecraftState state) Method to compute the acceleration.
Vector3D	EmpiricalForce.computeAcceleration(SpacecraftState state)

Uses of SpacecraftState in fr.cnes.sirius.patrius.forces.radiation

Methods in fr.cnes.sirius.patrius.forces.radiation with parameters of type SpacecraftState

void	PatriusSolarRadiationPressure.addContribution(SpacecraftState s, TimeDerivativesEquations adder)
void	PatriusSolarRadiationPressure.addDAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam)
void	PatriusSolarRadiationPressure.addDAccDState(SpacecraftState s, double[][] dAccdPos, double[][] dAccdVel)
Vector3D	PatriusSolarRadiationPressure.computeAcceleration(SpacecraftState s)

Uses of SpacecraftState in fr.cnes.sirius.patrius.propagation

Methods in fr.cnes.sirius.patrius.propagation that return types with arguments of type SpacecraftState

Map<String,SpacecraftState>	MultiPropagator.getInitialStates() Get the propagator initial states.
Map<String,SpacecraftState>	MultiPropagator.propagate(AbsoluteDate target) Propagate towards a target date.
Map<String,SpacecraftState>	MultiPropagator.propagate(AbsoluteDate start, AbsoluteDate target) Propagate from a start date towards a target date.

Methods in fr.cnes.sirius.patrius.propagation with parameters of type SpacecraftState

void	MultiPropagator.addInitialState(SpacecraftState initialState, String satId) Add a new spacecraft state to be propagated.

Uses of SpacecraftState in fr.cnes.sirius.patrius.propagation.events.multi

Methods in fr.cnes.sirius.patrius.propagation.events.multi that return types with arguments of type SpacecraftState

Map<String,SpacecraftState>	OneSatEventDetectorWrapper.resetStates(Map<String,SpacecraftState> oldStates)
Map<String,SpacecraftState>	MultiAbstractDetector.resetStates(Map<String,SpacecraftState> oldStates)

Method parameters in fr.cnes.sirius.patrius.propagation.events.multi with type arguments of type SpacecraftState

EventDetector.Action	OneSatEventDetectorWrapper.eventOccurred(Map<String,SpacecraftState> s, boolean increasing, boolean forward)
abstract EventDetector.Action	MultiAbstractDetector.eventOccurred(Map<String,SpacecraftState> s, boolean increasing, boolean forward)
double	OneSatEventDetectorWrapper.g(Map<String,SpacecraftState> s)
abstract double	MultiAbstractDetector.g(Map<String,SpacecraftState> s)
void	OneSatEventDetectorWrapper.init(Map<String,SpacecraftState> s0, AbsoluteDate t)
void	MultiAbstractDetector.init(Map<String,SpacecraftState> s0, AbsoluteDate t)
Map<String,SpacecraftState>	OneSatEventDetectorWrapper.resetStates(Map<String,SpacecraftState> oldStates)
Map<String,SpacecraftState>	MultiAbstractDetector.resetStates(Map<String,SpacecraftState> oldStates)

Uses of SpacecraftState in fr.cnes.sirius.patrius.propagation.numerical.multi

Methods in fr.cnes.sirius.patrius.propagation.numerical.multi that return SpacecraftState

SpacecraftState

MultiStateVectorInfo.mapArrayToState(double[] y, AbsoluteDate currentDate, OrbitType orbitType, PositionAngle angleType, AttitudeProvider attProviderForces, AttitudeProvider attProviderEvents, double mu, Frame integrationFrame, String satId) Extract a given SpacecraftState from the state vector.

Methods in fr.cnes.sirius.patrius.propagation.numerical.multi that return types with arguments of type SpacecraftState

Map<String,SpacecraftState>	MultiNumericalPropagator.getInitialStates()
Map<String,SpacecraftState>	MultiStateVectorInfo.mapArrayToStates(double[] y, AbsoluteDate currentDate, OrbitType orbitType, PositionAngle angleType, Map<String,AttitudeProvider> attProvidersForces, Map<String,AttitudeProvider> attProvidersEvents, Map<String,Double> mu, Map<String,Frame> integrationFrame) Convert state vector into a Map of SpacecraftState
Map<String,SpacecraftState>	MultiNumericalPropagator.propagate(AbsoluteDate target)
Map<String,SpacecraftState>	MultiNumericalPropagator.propagate(AbsoluteDate start, AbsoluteDate target)

Methods in fr.cnes.sirius.patrius.propagation.numerical.multi with parameters of type SpacecraftState

void	MultiNumericalPropagator.addInitialState(SpacecraftState initialState, String satId)

Method parameters in fr.cnes.sirius.patrius.propagation.numerical.multi with type arguments of type SpacecraftState

void	MultiStateVectorInfo.mapStatesToArray(Map<String,SpacecraftState> s, OrbitType orbitType, PositionAngle angleType, double[] y) Convert a map of SpacecraftState into a state vector.

Constructor parameters in fr.cnes.sirius.patrius.propagation.numerical.multi with type arguments of type SpacecraftState

MultiStateVectorInfo(Map<String,SpacecraftState> s)
Build a MultiSatStateVectorInfo instance using the spacecraft states' map.

Uses of SpacecraftState in fr.cnes.sirius.patrius.propagation.precomputed.multi

Methods in fr.cnes.sirius.patrius.propagation.precomputed.multi that return SpacecraftState

protected SpacecraftState	MultiIntegratedEphemeris.basicPropagate(AbsoluteDate date) Propagate an orbit without any fancy features.
SpacecraftState	MultiIntegratedEphemeris.getInitialState() Get the propagator initial state.

Methods in fr.cnes.sirius.patrius.propagation.precomputed.multi with parameters of type SpacecraftState

void	MultiIntegratedEphemeris.resetInitialState(SpacecraftState state) Reset the propagator initial state.

Uses of SpacecraftState in fr.cnes.sirius.patrius.propagation.sampling.multi

Methods in fr.cnes.sirius.patrius.propagation.sampling.multi that return types with arguments of type SpacecraftState

Map<String,SpacecraftState>	MultiOrekitStepInterpolator.getInterpolatedStates() Get all the interpolated states.
Map<String,SpacecraftState>	MultiAdaptedStepHandler.getInterpolatedStates() Get all the interpolated states.

Method parameters in fr.cnes.sirius.patrius.propagation.sampling.multi with type arguments of type SpacecraftState

void	MultiOrekitFixedStepHandler.handleStep(Map<String,SpacecraftState> currentStates, boolean isLast) Handle the current step.
void	MultiOrekitStepNormalizer.init(Map<String,SpacecraftState> s0, AbsoluteDate t) Initialize step handler at the start of a propagation.
void	MultiOrekitStepHandler.init(Map<String,SpacecraftState> s0, AbsoluteDate t) Initialize step handler at the start of a propagation.
void	MultiOrekitFixedStepHandler.init(Map<String,SpacecraftState> s0, AbsoluteDate t) Initialize step handler at the start of a propagation.

Uses of SpacecraftState in fr.cnes.sirius.patrius.stela

Methods in fr.cnes.sirius.patrius.stela with parameters of type SpacecraftState

EventDetector.Action	PerigeeAltitudeDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) Handle an altitude event and choose what to do next.
double	PerigeeAltitudeDetector.g(SpacecraftState s) Compute the value of the switching function.

Uses of SpacecraftState in fr.cnes.sirius.patrius.stela.forces.drag

Methods in fr.cnes.sirius.patrius.stela.forces.drag with parameters of type SpacecraftState

void	StelaAeroModel.addDDragAccDParam(SpacecraftState s, Parameter param, double density, Vector3D relativeVelocity, double[] dAccdParam)
void	StelaAeroModel.addDDragAccDState(SpacecraftState s, double[][] dAccdPos, double[][] dAccdVel, double density, Vector3D acceleration, Vector3D relativeVelocity, boolean computeGradientPosition, boolean computeGradientVelocity)
Vector3D	StelaAeroModel.dragAcceleration(SpacecraftState state, double density, Vector3D relativeVelocity) Return the drag acceleration in the CIRF frame.

Uses of SpacecraftState in fr.cnes.sirius.patrius.stela.propagation

Methods in fr.cnes.sirius.patrius.stela.propagation that return SpacecraftState

protected SpacecraftState	StelaAbstractPropagator.acceptStep(AbsoluteDate target, double epsilon) Accept a step, triggering events and step handlers.
SpacecraftState	StelaPartialDerivativesEquations.addInitialAdditionalState(SpacecraftState state)
SpacecraftState	StelaAdditionalEquations.addInitialAdditionalState(SpacecraftState state)
protected SpacecraftState	StelaAbstractPropagator.basicPropagate(AbsoluteDate date) Propagate a SpacecraftState without any fancy features.
SpacecraftState	StelaAbstractPropagator.getInitialState() Get the propagator initial state.
SpacecraftState	StelaBasicInterpolator.getInitialState()
SpacecraftState	StelaBasicInterpolator.getInterpolatedState() Get the interpolated state.
SpacecraftState	StelaAbstractPropagator.goAhead(double stepSize, double dt, AbsoluteDate target) go one step ahead
SpacecraftState	StelaAbstractPropagator.propagate(AbsoluteDate target) Propagate towards a target date.
SpacecraftState	StelaAbstractPropagator.propagate(AbsoluteDate start, AbsoluteDate target) Propagate from a start date towards a target date.
SpacecraftState	StelaGTOPropagator.propagate(AbsoluteDate start, AbsoluteDate target)
protected abstract SpacecraftState	StelaAbstractPropagator.propagateSpacecraftState(AbsoluteDate date) Extrapolate a spacecraftState up to a specific target date.
protected SpacecraftState	StelaGTOPropagator.propagateSpacecraftState(AbsoluteDate date)
SpacecraftState	StelaAbstractPropagator.propagationManagement(SpacecraftState state, double stepSize, double dt, AbsoluteDate target) Manages the current step, method to override when user wants to deal with exceptions during the propagation.
SpacecraftState	StelaGTOPropagator.propagationManagement(SpacecraftState state, double stepSize, double dt, AbsoluteDate target)

Methods in fr.cnes.sirius.patrius.stela.propagation with parameters of type SpacecraftState

SpacecraftState	StelaPartialDerivativesEquations.addInitialAdditionalState(SpacecraftState state)
SpacecraftState	StelaAdditionalEquations.addInitialAdditionalState(SpacecraftState state)
void	ForcesStepHandler.init(SpacecraftState s0, AbsoluteDate t)
SpacecraftState	StelaAbstractPropagator.propagationManagement(SpacecraftState state, double stepSize, double dt, AbsoluteDate target) Manages the current step, method to override when user wants to deal with exceptions during the propagation.
SpacecraftState	StelaGTOPropagator.propagationManagement(SpacecraftState state, double stepSize, double dt, AbsoluteDate target)
void	StelaAbstractPropagator.resetInitialState(SpacecraftState state) Reset the propagator initial state.
void	StelaGTOPropagator.setInitialState(SpacecraftState initialState, double massIn, boolean isOsculatingIn) Set the initial state.
void	StelaBasicInterpolator.storeSC(SpacecraftState initialStateIn, SpacecraftState targetState) Store the current dates and spacecraft states.

Uses of SpacecraftState in fr.cnes.sirius.patrius.wrenches

Methods in fr.cnes.sirius.patrius.wrenches with parameters of type SpacecraftState

Vector3D	SolarRadiationWrench.computeTorque(SpacecraftState s) Compute the resulting torque at the mass centre of the spacecraft in the frame of the main part.
Vector3D	GravitationalAttractionWrench.computeTorque(SpacecraftState s) Compute the resulting torque at the mass centre of the spacecraft in the frame of the main part.
Vector3D	DragWrench.computeTorque(SpacecraftState s) Compute the resulting torque at the mass centre of the spacecraft in the frame of the main part.
Vector3D	GenericWrenchModel.computeTorque(SpacecraftState s) Compute the resulting torque at the mass centre of the spacecraft in the frame of the main part.
Vector3D	MagneticWrench.computeTorque(SpacecraftState s) Compute the resulting torque at the mass centre of the spacecraft in the frame of the main part.
Vector3D	SolarRadiationWrench.computeTorque(SpacecraftState s, Vector3D origin, Frame frame) Compute the resulting wrench.
Vector3D	GravitationalAttractionWrench.computeTorque(SpacecraftState s, Vector3D origin, Frame frame) Compute the resulting wrench.
Vector3D	DragWrench.computeTorque(SpacecraftState s, Vector3D origin, Frame frame) Compute the resulting wrench.
Vector3D	GenericWrenchModel.computeTorque(SpacecraftState s, Vector3D origin, Frame frame) Compute the resulting wrench.
Vector3D	MagneticWrench.computeTorque(SpacecraftState s, Vector3D origin, Frame frame) Compute the resulting wrench.
Wrench	SolarRadiationWrench.computeWrench(SpacecraftState s) Compute the resulting wrench at the mass centre of the spacecraft in the frame of the main part.
Wrench	GravitationalAttractionWrench.computeWrench(SpacecraftState s) Compute the resulting wrench at the mass centre of the spacecraft in the frame of the main part.
Wrench	DragWrench.computeWrench(SpacecraftState s) Compute the resulting wrench at the mass centre of the spacecraft in the frame of the main part.
Wrench	GenericWrenchModel.computeWrench(SpacecraftState s) Compute the resulting wrench at the mass centre of the spacecraft in the frame of the main part.
Wrench	MagneticWrench.computeWrench(SpacecraftState s) Compute the resulting wrench at the mass centre of the spacecraft in the frame of the main part.
Wrench	SolarRadiationWrench.computeWrench(SpacecraftState s, Vector3D origin, Frame frame) Compute the resulting wrench.
Wrench	GravitationalAttractionWrench.computeWrench(SpacecraftState s, Vector3D origin, Frame frame) Compute the resulting wrench.
Wrench	DragWrench.computeWrench(SpacecraftState s, Vector3D origin, Frame frame) Compute the resulting wrench.
Wrench	GenericWrenchModel.computeWrench(SpacecraftState s, Vector3D origin, Frame frame) Compute the resulting wrench.
Wrench	MagneticWrench.computeWrench(SpacecraftState s, Vector3D origin, Frame frame) Compute the resulting wrench.
Wrench	DragWrenchSensitive.dragWrench(SpacecraftState state, double density, Vector3D relativeVelocity) Compute the torque due to radiation pressire.
Wrench	DragWrenchSensitive.dragWrench(SpacecraftState state, double density, Vector3D relativeVelocity, Vector3D origin, Frame frame) Compute the torque due to radiation pressire.
Wrench	RadiationWrenchSensitive.radiationWrench(SpacecraftState state, Vector3D flux) Compute the torque due to radiation pressire.
Wrench	RadiationWrenchSensitive.radiationWrench(SpacecraftState state, Vector3D flux, Vector3D origin, Frame frame) Compute the torque due to radiation pressire.

Uses of SpacecraftState in fr.cnes.sirius.validate.files

Method parameters in fr.cnes.sirius.validate.files with type arguments of type SpacecraftState

static void

ResultsFileWriter.writeResultsToVTS(String thematic, String useCase, String orbitComment, String attitudeComment, List<SpacecraftState> results) Method to write the attitudes and positions files used by VTS visualization tool.

Uses of SpacecraftState in org.orekit.forces

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

void	ForceModel.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.
Vector3D	ForceModel.computeAcceleration(SpacecraftState s) Compute the acceleration due to the force.

Uses of SpacecraftState in org.orekit.forces.drag

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

void	DragForce.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the drag to the perturbing acceleration.
void	DragForce.addDAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters.
void	DragForce.addDAccDState(SpacecraftState s, double[][] dAccdPos, double[][] dAccdVel) Compute acceleration derivatives with respect to state parameters.
void	DragSensitive.addDDragAccDParam(SpacecraftState s, Parameter param, double density, Vector3D relativeVelocity, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters (the ballistic coefficient).
void	DragSensitive.addDDragAccDState(SpacecraftState s, double[][] dAccdPos, double[][] dAccdVel, double density, Vector3D acceleration, Vector3D relativeVelocity, boolean computeGradientPosition, boolean computeGradientVelocity) Compute acceleration derivatives with respect to state parameters (position and velocity).
Vector3D	DragForce.computeAcceleration(SpacecraftState s) Compute the acceleration due to the force.
Vector3D	DragSensitive.dragAcceleration(SpacecraftState state, double density, Vector3D relativeVelocity) Compute the acceleration due to drag and the lift.

Uses of SpacecraftState in org.orekit.forces.gravity

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

void	BalminoAttractionModel.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	ThirdBodyAttraction.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	NewtonianAttraction.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.
void	BalminoAttractionModel.addDAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters.
void	ThirdBodyAttraction.addDAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters.
void	CunninghamAttractionModel.addDAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters.
void	NewtonianAttraction.addDAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters.
void	BalminoAttractionModel.addDAccDState(SpacecraftState s, double[][] dAccdPos, double[][] dAccdVel) Compute acceleration derivatives with respect to state parameters.
void	ThirdBodyAttraction.addDAccDState(SpacecraftState s, double[][] dAccdPos, double[][] dAccdVel) Compute acceleration derivatives with respect to state parameters.
void	CunninghamAttractionModel.addDAccDState(SpacecraftState s, double[][] dAccdPos, double[][] dAccdVel) Compute acceleration derivatives with respect to state parameters.
void	NewtonianAttraction.addDAccDState(SpacecraftState s, double[][] dAccdPos, double[][] dAccdVel) Compute acceleration derivatives with respect to state parameters.
Vector3D	BalminoAttractionModel.computeAcceleration(SpacecraftState s) Compute the acceleration due to the force.
Vector3D	DrozinerAttractionModel.computeAcceleration(SpacecraftState s) Compute the acceleration due to the force.
Vector3D	ThirdBodyAttraction.computeAcceleration(SpacecraftState s) Compute the acceleration due to the force.
Vector3D	CunninghamAttractionModel.computeAcceleration(SpacecraftState s) Compute the acceleration due to the force.
Vector3D	NewtonianAttraction.computeAcceleration(SpacecraftState s) Compute the acceleration due to the force.

Uses of SpacecraftState in org.orekit.forces.gravity.tides

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

void	AbstractTides.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.
void	AbstractTides.addDAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters.
void	AbstractTides.addDAccDState(SpacecraftState s, double[][] dAccdPos, double[][] dAccdVel) Compute acceleration derivatives with respect to state parameters.
Vector3D	AbstractTides.computeAcceleration(SpacecraftState s) Compute the acceleration due to the force.

Uses of SpacecraftState in org.orekit.forces.gravity.variations

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

void	VariablePotentialAttractionModel.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.
void	VariablePotentialAttractionModel.addDAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters.
void	VariablePotentialAttractionModel.addDAccDState(SpacecraftState s, double[][] dAccdPos, double[][] dAccdVel)
Vector3D	VariablePotentialAttractionModel.computeAcceleration(SpacecraftState s) Compute the acceleration due to the force.

Uses of SpacecraftState in org.orekit.forces.maneuvers

Methods in org.orekit.forces.maneuvers that return SpacecraftState

SpacecraftState	SmallManeuverAnalyticalModel.apply(SpacecraftState state1) Compute the effect of the maneuver on a spacecraft state.
SpacecraftState	ImpulseManeuver.resetState(SpacecraftState oldState) Reset the state (including additional states) prior to continue propagation.

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

void	ConstantThrustManeuver.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.
void	ConstantThrustError.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the constant thrust error model to the perturbing acceleration.
void	VariableThrustManeuver.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.
void	ConstantThrustManeuver.addDAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters.
void	ConstantThrustError.addDAccDParam(SpacecraftState state, Parameter param, double[] dAccdParam)
void	VariableThrustManeuver.addDAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters.
void	ConstantThrustManeuver.addDAccDState(SpacecraftState s, double[][] dAccdPos, double[][] dAccdVel) Compute acceleration derivatives with respect to state parameters.
void	ConstantThrustError.addDAccDState(SpacecraftState state, double[][] dAccdPos, double[][] dAccdVel)
void	VariableThrustManeuver.addDAccDState(SpacecraftState s, double[][] dAccdPos, double[][] dAccdVel) Compute acceleration derivatives with respect to state parameters.
SpacecraftState	SmallManeuverAnalyticalModel.apply(SpacecraftState state1) Compute the effect of the maneuver on a spacecraft state.
Vector3D	ConstantThrustManeuver.computeAcceleration(SpacecraftState s) Compute the acceleration due to the force.
Vector3D	ConstantThrustError.computeAcceleration(SpacecraftState s) Compute the acceleration due to the force.
Vector3D	VariableThrustManeuver.computeAcceleration(SpacecraftState s)
EventDetector.Action	ImpulseManeuver.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) Handle an event and choose what to do next.
double	ImpulseManeuver.g(SpacecraftState s) Compute the value of the switching function.
Vector3D	VariableThrustManeuver.getDirection(SpacecraftState s) Get the thrust direction.
double	VariableThrustManeuver.getFlowRate(SpacecraftState s) Get the flow rate.
double	VariableThrustManeuver.getISP(SpacecraftState s) Get the specific impulse.
double	VariableThrustManeuver.getThrust(SpacecraftState s) Get the thrust.
void	ImpulseManeuver.init(SpacecraftState s0, AbsoluteDate t) Initialize event handler at the start of a propagation.
SpacecraftState	ImpulseManeuver.resetState(SpacecraftState oldState) Reset the state (including additional states) prior to continue propagation.

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

SmallManeuverAnalyticalModel(SpacecraftState state0, Frame frame, Vector3D dV, double isp, String partName)
Build a maneuver defined in user-specified frame.

SmallManeuverAnalyticalModel(SpacecraftState state0, Vector3D dV, double isp, String partName)
Build a maneuver defined in spacecraft frame.

Constructor parameters in org.orekit.forces.maneuvers with type arguments of type SpacecraftState

VariableThrustManeuver(AbsoluteDate date, double duration, IDependentVariable<SpacecraftState> variableThrust, IDependentVariable<SpacecraftState> variableIsp, IDependentVectorVariable<SpacecraftState> variableDirection, MassProvider massModel, String partName)
Constructor for a variable direction in spacecraft frame, thrust and ISP.

VariableThrustManeuver(AbsoluteDate date, double duration, IDependentVariable<SpacecraftState> variableThrust, IDependentVariable<SpacecraftState> variableIsp, IDependentVectorVariable<SpacecraftState> variableDirection, MassProvider massModel, String partName)
Constructor for a variable direction in spacecraft frame, thrust and ISP.

VariableThrustManeuver(AbsoluteDate date, double duration, IDependentVariable<SpacecraftState> variableThrust, IDependentVariable<SpacecraftState> variableIsp, IDependentVectorVariable<SpacecraftState> variableDirection, MassProvider massModel, String partName)
Constructor for a variable direction in spacecraft frame, thrust and ISP.

VariableThrustManeuver(AbsoluteDate date, double duration, IDependentVariable<SpacecraftState> variableThrust, IDependentVariable<SpacecraftState> variableIsp, IDependentVectorVariable<SpacecraftState> variableDirection, MassProvider massModel, String partName, Frame refFrame)
Constructor for a variable direction in provided frame, thrust and ISP.

VariableThrustManeuver(AbsoluteDate date, double duration, IDependentVariable<SpacecraftState> variableThrust, IDependentVariable<SpacecraftState> variableIsp, IDependentVectorVariable<SpacecraftState> variableDirection, MassProvider massModel, String partName, Frame refFrame)
Constructor for a variable direction in provided frame, thrust and ISP.

VariableThrustManeuver(AbsoluteDate date, double duration, IDependentVariable<SpacecraftState> variableThrust, IDependentVariable<SpacecraftState> variableIsp, IDependentVectorVariable<SpacecraftState> variableDirection, MassProvider massModel, String partName, Frame refFrame)
Constructor for a variable direction in provided frame, thrust and ISP.

VariableThrustManeuver(AbsoluteDate date, double duration, IDependentVariable<SpacecraftState> variableThrust, IDependentVariable<SpacecraftState> variableIsp, IDependentVectorVariable<SpacecraftState> variableDirection, MassProvider massModel, String partName, LOFType lofTyp)
Constructor for a variable direction in provided local orbital frame, thrust and ISP expressed in a LocalOrbitalFrame.

VariableThrustManeuver(AbsoluteDate date, double duration, IDependentVariable<SpacecraftState> variableThrust, IDependentVariable<SpacecraftState> variableIsp, IDependentVectorVariable<SpacecraftState> variableDirection, MassProvider massModel, String partName, LOFType lofTyp)
Constructor for a variable direction in provided local orbital frame, thrust and ISP expressed in a LocalOrbitalFrame.

VariableThrustManeuver(AbsoluteDate date, double duration, IDependentVariable<SpacecraftState> variableThrust, IDependentVariable<SpacecraftState> variableIsp, IDependentVectorVariable<SpacecraftState> variableDirection, MassProvider massModel, String partName, LOFType lofTyp)
Constructor for a variable direction in provided local orbital frame, thrust and ISP expressed in a LocalOrbitalFrame.

VariableThrustManeuver(EventDetector startEventDetector, EventDetector stopEventDetector, IDependentVariable<SpacecraftState> variableThrust, IDependentVariable<SpacecraftState> variableIsp, IDependentVectorVariable<SpacecraftState> variableDirection, MassProvider massModel, String partName)
Constructor for a variable direction in spacecraft frame, thrust and ISP.

VariableThrustManeuver(EventDetector startEventDetector, EventDetector stopEventDetector, IDependentVariable<SpacecraftState> variableThrust, IDependentVariable<SpacecraftState> variableIsp, IDependentVectorVariable<SpacecraftState> variableDirection, MassProvider massModel, String partName)
Constructor for a variable direction in spacecraft frame, thrust and ISP.

VariableThrustManeuver(EventDetector startEventDetector, EventDetector stopEventDetector, IDependentVariable<SpacecraftState> variableThrust, IDependentVariable<SpacecraftState> variableIsp, IDependentVectorVariable<SpacecraftState> variableDirection, MassProvider massModel, String partName)
Constructor for a variable direction in spacecraft frame, thrust and ISP.

VariableThrustManeuver(EventDetector startEventDetector, EventDetector stopEventDetector, IDependentVariable<SpacecraftState> variableThrust, IDependentVariable<SpacecraftState> variableIsp, IDependentVectorVariable<SpacecraftState> variableDirection, MassProvider massModel, String partName, Frame refFrame)
Constructor for a variable direction in provided frame, thrust and ISP.

VariableThrustManeuver(EventDetector startEventDetector, EventDetector stopEventDetector, IDependentVariable<SpacecraftState> variableThrust, IDependentVariable<SpacecraftState> variableIsp, IDependentVectorVariable<SpacecraftState> variableDirection, MassProvider massModel, String partName, Frame refFrame)
Constructor for a variable direction in provided frame, thrust and ISP.

VariableThrustManeuver(EventDetector startEventDetector, EventDetector stopEventDetector, IDependentVariable<SpacecraftState> variableThrust, IDependentVariable<SpacecraftState> variableIsp, IDependentVectorVariable<SpacecraftState> variableDirection, MassProvider massModel, String partName, Frame refFrame)
Constructor for a variable direction in provided frame, thrust and ISP.

VariableThrustManeuver(EventDetector startEventDetector, EventDetector stopEventDetector, IDependentVariable<SpacecraftState> variableThrust, IDependentVariable<SpacecraftState> variableIsp, IDependentVectorVariable<SpacecraftState> variableDirection, MassProvider massModel, String partName, LOFType lofTyp)
Constructor for a variable direction in provided local orbital frame, thrust and ISP expressed in a LocalOrbitalFrame.

VariableThrustManeuver(EventDetector startEventDetector, EventDetector stopEventDetector, IDependentVariable<SpacecraftState> variableThrust, IDependentVariable<SpacecraftState> variableIsp, IDependentVectorVariable<SpacecraftState> variableDirection, MassProvider massModel, String partName, LOFType lofTyp)
Constructor for a variable direction in provided local orbital frame, thrust and ISP expressed in a LocalOrbitalFrame.

VariableThrustManeuver(EventDetector startEventDetector, EventDetector stopEventDetector, IDependentVariable<SpacecraftState> variableThrust, IDependentVariable<SpacecraftState> variableIsp, IDependentVectorVariable<SpacecraftState> variableDirection, MassProvider massModel, String partName, LOFType lofTyp)
Constructor for a variable direction in provided local orbital frame, thrust and ISP expressed in a LocalOrbitalFrame.

Uses of SpacecraftState in org.orekit.forces.radiation

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

void	RediffusedRadiationPressure.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.
void	SolarRadiationPressure.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.
void	RediffusedRadiationPressure.addDAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters.
void	SolarRadiationPressure.addDAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters.
void	RediffusedRadiationSensitive.addDAccDParamRediffusedRadiativePressure(SpacecraftState s, Parameter param, double[] dAccdParam) Compute acceleration derivatives.
void	RediffusedRadiationPressure.addDAccDState(SpacecraftState s, double[][] dAccdPos, double[][] dAccdVel) Compute acceleration derivatives with respect to state parameters.
void	SolarRadiationPressure.addDAccDState(SpacecraftState s, double[][] dAccdPos, double[][] dAccdVel) Compute acceleration derivatives with respect to state parameters.
void	RediffusedRadiationSensitive.addDAccDStateRediffusedRadiativePressure(SpacecraftState s, double[][] dAccdPos, double[][] dAccdVel) Compute acceleration derivatives.
void	RadiationSensitive.addDSRPAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam, Vector3D satSunVector) Compute acceleration derivatives with respect to additional parameters.
void	RadiationSensitive.addDSRPAccDState(SpacecraftState s, double[][] dAccdPos, double[][] dAccdVel, Vector3D satSunVector) Compute acceleration derivatives with respect to state parameters.
Vector3D	RediffusedRadiationPressure.computeAcceleration(SpacecraftState s) Compute the acceleration due to the force.
Vector3D	SolarRadiationPressure.computeAcceleration(SpacecraftState s) Compute the acceleration due to the force.
Vector3D	RadiationSensitive.radiationPressureAcceleration(SpacecraftState state, Vector3D flux) Compute the acceleration due to radiation pressure.
Vector3D	RediffusedRadiationSensitive.rediffusedRadiationPressureAcceleration(SpacecraftState state, ElementaryFlux flux) rediffused radiative pressure acceleration

Uses of SpacecraftState in org.orekit.forces.relativistic

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

void	SchwarzschildRelativisticEffect.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.
void	LenseThirringRelativisticEffect.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.
void	CoriolisRelativisticEffect.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.
void	SchwarzschildRelativisticEffect.addDAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters.
void	LenseThirringRelativisticEffect.addDAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters.
void	CoriolisRelativisticEffect.addDAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters.
void	SchwarzschildRelativisticEffect.addDAccDState(SpacecraftState s, double[][] dAccdPos, double[][] dAccdVel) Compute acceleration derivatives with respect to state parameters.
void	LenseThirringRelativisticEffect.addDAccDState(SpacecraftState s, double[][] dAccdPos, double[][] dAccdVel) Compute acceleration derivatives with respect to state parameters.
void	CoriolisRelativisticEffect.addDAccDState(SpacecraftState s, double[][] dAccdPos, double[][] dAccdVel) Compute acceleration derivatives with respect to state parameters.
Vector3D	SchwarzschildRelativisticEffect.computeAcceleration(SpacecraftState s) Compute the acceleration due to the force.
Vector3D	LenseThirringRelativisticEffect.computeAcceleration(SpacecraftState s) Compute the acceleration due to the force.
Vector3D	CoriolisRelativisticEffect.computeAcceleration(SpacecraftState s) Compute the acceleration due to the force.

Uses of SpacecraftState in org.orekit.parameter

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

void	IJacobiansParameterizable.addDAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters.
void	IJacobiansParameterizable.addDAccDState(SpacecraftState s, double[][] dAccdPos, double[][] dAccdVel) Compute acceleration derivatives with respect to state parameters.
double	PiecewiseFunction.derivativeValue(Parameter p, SpacecraftState s) Compute the derivative value with respect to the input parameter.
double	IParamDiffFunction.derivativeValue(Parameter p, SpacecraftState s) Compute the derivative value with respect to the input parameter.
double	ConstantFunction.derivativeValue(Parameter p, SpacecraftState state) Compute the derivative value with respect to the input parameter.
double	LinearFunction.derivativeValue(Parameter p, SpacecraftState state) Compute the derivative value with respect to the input parameter.
double	IParameterizableFunction.value(SpacecraftState state) Getting the value of the function.
double	PiecewiseFunction.value(SpacecraftState s) Getting the value of the function.
double	ConstantFunction.value(SpacecraftState s) Getting the value of the function.
double	LinearFunction.value(SpacecraftState s) Getting the value of the function.

Uses of SpacecraftState in org.orekit.propagation

Methods in org.orekit.propagation that return SpacecraftState

protected SpacecraftState	AbstractPropagator.acceptStep(AbsoluteDate target, double epsilon) Accept a step, triggering events and step handlers.
SpacecraftState	SpacecraftState.addAdditionalState(String name, double[] state) Add an additional state to the additional states map.
SpacecraftState	SpacecraftState.addAttitude(Attitude newAttitude, AttitudeEquation.AttitudeType type) Add attitude to the additional states map.
SpacecraftState	SpacecraftState.addAttitudeToAdditionalStates(AttitudeEquation.AttitudeType attitudeType) Add attitude to the additional states map.
SpacecraftState	SpacecraftState.addMassProvider(MassProvider massProvider) Add the values of mass parts from MassProvider to additional states map.
protected SpacecraftState	AbstractPropagator.basicPropagate(AbsoluteDate date) Propagate an orbit without any fancy features.
SpacecraftState	OsculatingToMeanElementsConverter.convert() Convert an osculating orbit into a mean orbit, in DSST sense.
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	AnalyticalIntegratedEphemeris.propagate(AbsoluteDate target) Propagate towards a target date.
SpacecraftState	Propagator.propagate(AbsoluteDate target) Propagate towards a target date.
SpacecraftState	AbstractPropagator.propagate(AbsoluteDate target) Propagate towards a target date.
SpacecraftState	AnalyticalIntegratedEphemeris.propagate(AbsoluteDate start, AbsoluteDate target) Propagate from a start date towards a target date.
SpacecraftState	Propagator.propagate(AbsoluteDate start, AbsoluteDate target) Propagate from a start date towards a target date.
SpacecraftState	AbstractPropagator.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	SpacecraftState.updateMass(String partName, double newMass) Update the mass of the given part.
SpacecraftState	SpacecraftState.updateOrbit(Orbit newOrbit) Update the orbit.

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

double	MassProvider.getTotalMass(SpacecraftState state) Return the mass of the spacecraft following the order.
double	SimpleMassModel.getTotalMass(SpacecraftState state) Return the mass of the spacecraft following the order.
void	Propagator.resetInitialState(SpacecraftState state) Reset the propagator initial state.
void	AbstractPropagator.resetInitialState(SpacecraftState state) Reset the propagator initial state.

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

SpacecraftState

SpacecraftState.interpolate(AbsoluteDate date, Collection<SpacecraftState> sample) Get an interpolated instance.

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

OsculatingToMeanElementsConverter(SpacecraftState state, int satelliteRevolution, Propagator propagator)
Constructor.

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

AnalyticalIntegratedEphemeris(List<AbsoluteDate> initialDates, List<AbsoluteDate> finalDates, List<SpacecraftState> initialStates, AbstractPropagator propagator, AttitudeProvider attForcesProvider, AttitudeProvider attEventsProvider, boolean isForward)
Constructor.

Uses of SpacecraftState in org.orekit.propagation.analytical

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

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.
SpacecraftState	AdapterPropagator.getInitialState() Get the propagator initial state.

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

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	AnalyticalEphemerisModeHandler.init(SpacecraftState s0, AbsoluteDate t) Initialize step handler at the start of a propagation.
void	AdapterPropagator.resetInitialState(SpacecraftState state) Reset the propagator initial state.
void	EcksteinHechlerPropagator.resetInitialState(SpacecraftState state) Reset the propagator initial state.
void	AbstractLyddanePropagator.resetInitialState(SpacecraftState state) Reset the propagator initial state.
void	KeplerianPropagator.resetInitialState(SpacecraftState state) Reset the propagator initial state.
void	J2SecularPropagator.resetInitialState(SpacecraftState state) Reset the propagator initial state.

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

J2DifferentialEffect(SpacecraftState original, AdapterPropagator.DifferentialEffect directEffect, boolean applyBefore, double referenceRadius, double mu, double j2)
Simple constructor.

J2DifferentialEffect(SpacecraftState original, AdapterPropagator.DifferentialEffect directEffect, boolean applyBefore, PotentialCoefficientsProvider gravityField)
Simple constructor.

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

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

TLE	AbstractTLEFitter.toTLE(List<SpacecraftState> states, double positionTolerance, boolean positionOnly, boolean withBStar) Find the TLE elements that minimize the mean square error for a sample of states.

Uses of SpacecraftState in org.orekit.propagation.events

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

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 (including additional states) prior to continue propagation.
SpacecraftState	EventDetector.resetState(SpacecraftState oldState) Reset the state (including additional states) prior to continue propagation.
SpacecraftState	NthOccurrenceDetector.resetState(SpacecraftState oldState) Reset the state (including additional states) prior to continue propagation.
SpacecraftState	NullMassPartDetector.resetState(SpacecraftState oldState) Reset the state (including additional states) prior to continue propagation.

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

Map<String,SpacecraftState>	ThreeBodiesAngleDetector.resetStates(Map<String,SpacecraftState> oldStates)
Map<String,SpacecraftState>	ExtremaThreeBodiesAngleDetector.resetStates(Map<String,SpacecraftState> oldStates)

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

boolean	EventState.evaluateStep(SpacecraftState state) Evaluate the impact of the proposed step on the event handler.
EventDetector.Action	ThreeBodiesAngleDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) Handle an angle event and choose what to do next.
EventDetector.Action	ExtremaDistanceDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) Handle an extrema distance event and choose what to do next.
abstract EventDetector.Action	AbstractDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) Handle an event and choose what to do next.
EventDetector.Action	EventDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) Handle an event and choose what to do next.
EventDetector.Action	NodeDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) Handle a node crossing event and choose what to do next.
EventDetector.Action	NthOccurrenceDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) Handle an event and choose what to do next.
EventDetector.Action	LatitudeDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) Handle a latitude reaching event and choose what to do next.
EventDetector.Action	DistanceDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) Handle a distance event and choose what to do next.
EventDetector.Action	DihedralFieldOfViewDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) Handle an fov event and choose what to do next.
EventDetector.Action	AltitudeDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) Handle an altitude event and choose what to do next.
EventDetector.Action	ApsideDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) Handle an apside crossing event and choose what to do next.
EventDetector.Action	EventShifter.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) Handle an event and choose what to do next.
EventDetector.Action	ExtremaThreeBodiesAngleDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) Handle a min or max angle event and choose what to do next.
EventDetector.Action	CircularFieldOfViewDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) Handle an fov event and choose what to do next.
EventDetector.Action	BetaAngleDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) Handles a beta angle event and chooses what to do next.
EventDetector.Action	EclipseDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) Handle an eclipse event and choose what to do next.
EventDetector.Action	LocalTimeDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) Handle a local time event and choose what to do next.
EventDetector.Action	NadirSolarIncidenceDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) Handle a solar incidence event and choose what to do next.
EventDetector.Action	ElevationDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) Handle an elevation event and choose what to do next.
EventDetector.Action	DateDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) Handle a date event and choose what to do next.
EventDetector.Action	ExtremaLatitudeDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) Handle an extrema latitude event and choose what to do next.
EventDetector.Action	GroundMaskElevationDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) Handle an azimuth-elevation event and choose what to do next.
EventDetector.Action	AOLDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) Handle an AOL event and choose what to do next.
EventDetector.Action	AlignmentDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) Handle an alignment event and choose what to do next.
EventDetector.Action	ExtremaElevationDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) Handle an extrema distance event and choose what to do next.
EventDetector.Action	NullMassDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) If the global mass of the satellite becomes negative, the propagation is stopped.
EventDetector.Action	SolarTimeDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) Handle a solar time event and choose what to do next.
EventDetector.Action	ExtremaLongitudeDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) Handle an extrema distance event and choose what to do next.
EventDetector.Action	LongitudeDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) Handle a longitude reaching event and choose what to do next.
EventDetector.Action	ApparentElevationDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) Handle an apparent elevation event and choose what to do next.
EventDetector.Action	NullMassPartDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) If the mass of the element becomes negative, a reset_state is performed.
EventDetector.Action	AnomalyDetector.eventOccurred(SpacecraftState s, boolean increasing, boolean forward) Handle an anomaly event and choose what to do next.
double	ThreeBodiesAngleDetector.g(SpacecraftState s) Compute the value of the switching function.
double	ExtremaDistanceDetector.g(SpacecraftState s)
abstract double	AbstractDetector.g(SpacecraftState s) Compute the value of the switching function.
double	EventDetector.g(SpacecraftState s) Compute the value of the switching function.
double	NodeDetector.g(SpacecraftState s) Compute the value of the switching function.
double	NthOccurrenceDetector.g(SpacecraftState s) Compute the value of the switching function.
double	LatitudeDetector.g(SpacecraftState s)
double	DistanceDetector.g(SpacecraftState s)
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	ApsideDetector.g(SpacecraftState s) Compute the value of the switching function.
double	EventShifter.g(SpacecraftState s) Compute the value of the switching function.
double	ExtremaThreeBodiesAngleDetector.g(SpacecraftState s)
double	CircularFieldOfViewDetector.g(SpacecraftState s) Compute the value of the switching function.
double	BetaAngleDetector.g(SpacecraftState s)
double	EclipseDetector.g(SpacecraftState s) Compute the value of the switching function.
double	LocalTimeDetector.g(SpacecraftState s)
double	NadirSolarIncidenceDetector.g(SpacecraftState s)
double	ElevationDetector.g(SpacecraftState s) Compute the value of the switching function.
double	DateDetector.g(SpacecraftState s) Compute the value of the switching function.
double	ExtremaLatitudeDetector.g(SpacecraftState s)
double	GroundMaskElevationDetector.g(SpacecraftState s) Compute the value of the switching function.
double	AOLDetector.g(SpacecraftState s)
double	AlignmentDetector.g(SpacecraftState s) Compute the value of the switching function.
double	ExtremaElevationDetector.g(SpacecraftState s)
double	NullMassDetector.g(SpacecraftState s) Compute the value of the switching function.
double	SolarTimeDetector.g(SpacecraftState s)
double	ExtremaLongitudeDetector.g(SpacecraftState s)
double	LongitudeDetector.g(SpacecraftState s)
double	ApparentElevationDetector.g(SpacecraftState s) Compute the value of the switching function.
double	NullMassPartDetector.g(SpacecraftState s) Compute the value of the switching function.
double	AnomalyDetector.g(SpacecraftState s)
void	ThreeBodiesAngleDetector.init(SpacecraftState s0, AbsoluteDate t)
void	ExtremaDistanceDetector.init(SpacecraftState s0, AbsoluteDate t)
void	AbstractDetector.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	NthOccurrenceDetector.init(SpacecraftState s0, AbsoluteDate t) Initialize event handler at the start of a propagation.
void	LatitudeDetector.init(SpacecraftState s0, AbsoluteDate t)
void	DistanceDetector.init(SpacecraftState s0, AbsoluteDate t)
void	EventShifter.init(SpacecraftState s0, AbsoluteDate t) Initialize event handler at the start of a propagation.
void	ExtremaThreeBodiesAngleDetector.init(SpacecraftState s0, AbsoluteDate t)
void	BetaAngleDetector.init(SpacecraftState s0, AbsoluteDate t)
void	LocalTimeDetector.init(SpacecraftState s0, AbsoluteDate t)
void	NadirSolarIncidenceDetector.init(SpacecraftState s0, AbsoluteDate t)
void	ExtremaLatitudeDetector.init(SpacecraftState s0, AbsoluteDate t)
void	AOLDetector.init(SpacecraftState s0, AbsoluteDate t)
void	ExtremaElevationDetector.init(SpacecraftState s0, AbsoluteDate t)
void	SolarTimeDetector.init(SpacecraftState s0, AbsoluteDate t)
void	ExtremaLongitudeDetector.init(SpacecraftState s0, AbsoluteDate t)
void	LongitudeDetector.init(SpacecraftState s0, AbsoluteDate t)
void	AnomalyDetector.init(SpacecraftState s0, AbsoluteDate t)
void	EventState.reinitializeBegin(SpacecraftState state0) 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 (including additional states) prior to continue propagation.
SpacecraftState	EventDetector.resetState(SpacecraftState oldState) Reset the state (including additional states) prior to continue propagation.
SpacecraftState	NthOccurrenceDetector.resetState(SpacecraftState oldState) Reset the state (including additional states) prior to continue propagation.
SpacecraftState	NullMassPartDetector.resetState(SpacecraftState oldState) Reset the state (including additional states) prior to continue propagation.
void	EventState.stepAccepted(SpacecraftState state) Acknowledge the fact the step has been accepted by the propagator.
void	EventState.storeState(SpacecraftState state0) Reinitialize event state with provided time and state.

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

EventDetector.Action	ThreeBodiesAngleDetector.eventOccurred(Map<String,SpacecraftState> s, boolean increasing, boolean forward)
EventDetector.Action	ExtremaThreeBodiesAngleDetector.eventOccurred(Map<String,SpacecraftState> s, boolean increasing, boolean forward)
double	ThreeBodiesAngleDetector.g(Map<String,SpacecraftState> s)
double	ExtremaThreeBodiesAngleDetector.g(Map<String,SpacecraftState> s)
void	ThreeBodiesAngleDetector.init(Map<String,SpacecraftState> s0, AbsoluteDate t)
void	ExtremaThreeBodiesAngleDetector.init(Map<String,SpacecraftState> s0, AbsoluteDate t)
Map<String,SpacecraftState>	ThreeBodiesAngleDetector.resetStates(Map<String,SpacecraftState> oldStates)
Map<String,SpacecraftState>	ExtremaThreeBodiesAngleDetector.resetStates(Map<String,SpacecraftState> oldStates)

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

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

Map<String,SpacecraftState>

MultiEventDetector.resetStates(Map<String,SpacecraftState> oldStates) Reset the states (including additional states) prior to continue propagation.

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

EventDetector.Action	MultiEventDetector.eventOccurred(Map<String,SpacecraftState> s, boolean increasing, boolean forward) Handle an event and choose what to do next.
double	MultiEventDetector.g(Map<String,SpacecraftState> s) Compute the value of the switching function.
void	MultiEventDetector.init(Map<String,SpacecraftState> s0, AbsoluteDate t) Initialize event handler at the start of a propagation.
Map<String,SpacecraftState>	MultiEventDetector.resetStates(Map<String,SpacecraftState> oldStates) Reset the states (including additional states) prior to continue propagation.

Uses of SpacecraftState in org.orekit.propagation.numerical

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

SpacecraftState	NumericalPropagator.getInitialState() Get the propagator initial state.
SpacecraftState	NumericalPropagator.propagate(AbsoluteDate target) Propagate towards a target date.
SpacecraftState	NumericalPropagator.propagate(AbsoluteDate tStart, AbsoluteDate tEnd) Propagate from a start date towards a target date.
SpacecraftState	PartialDerivativesEquations.setInitialJacobians(SpacecraftState s, double[][] dY1dY0) Set the initial value of the Jacobian with respect to 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 paramDimension) Set the initial value of the Jacobian with respect to state and parameter.
SpacecraftState	PartialDerivativesEquations.setInitialJacobians(SpacecraftState s, Parameter parameter, double[] dY1dP) Set the initial value of the Jacobian with respect to state.

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

void	PartialDerivativesEquations.computeDerivatives(SpacecraftState s, TimeDerivativesEquations adder) Compute the derivatives related to the additional state parameters.
void	AdditionalEquations.computeDerivatives(SpacecraftState s, TimeDerivativesEquations adder) Compute the derivatives related to the additional state parameters.
double[]	JacobiansMapper.getParametersJacobian(Parameter parameter, SpacecraftState state) Get the Jacobian with respect to provided parameter parameter.
void	JacobiansMapper.getParametersJacobian(Parameter parameter, SpacecraftState state, double[] dYdP) Get the Jacobian with respect to provided parameter parameter.
double[][]	JacobiansMapper.getParametersJacobian(SpacecraftState state) Get the Jacobian with respect to parameters.
void	JacobiansMapper.getParametersJacobian(SpacecraftState state, double[][] dYdP) Get the Jacobian with respect to parameters.
double[][]	JacobiansMapper.getStateJacobian(SpacecraftState state) Get the Jacobian with respect to state.
void	JacobiansMapper.getStateJacobian(SpacecraftState state, double[][] dYdY0) Get the Jacobian with respect to state.
void	NumericalPropagator.resetInitialState(SpacecraftState state) Reset the propagator initial state.
SpacecraftState	PartialDerivativesEquations.setInitialJacobians(SpacecraftState s, double[][] dY1dY0) Set the initial value of the Jacobian with respect to 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 paramDimension) Set the initial value of the Jacobian with respect to state and parameter.
SpacecraftState	PartialDerivativesEquations.setInitialJacobians(SpacecraftState s, Parameter parameter, double[] dY1dP) Set the initial value of the Jacobian with respect to state.
void	NumericalPropagator.setInitialState(SpacecraftState initialState) Set the initial state.

Uses of SpacecraftState in org.orekit.propagation.precomputed

Fields in org.orekit.propagation.precomputed declared as SpacecraftState

protected SpacecraftState[]

AbstractEphemeris.stateTab The SpacecraftStates array, chronologically sorted.

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

protected SpacecraftState	IntegratedEphemeris.basicPropagate(AbsoluteDate date) Propagate an orbit without any fancy features.
SpacecraftState	Ephemeris.basicPropagate(AbsoluteDate date)
protected SpacecraftState	AbstractEphemeris.basicPropagate(AbsoluteDate date)
protected SpacecraftState	AbstractEphemeris.checkBounds(double date) Returns spacecraftstate on bounds if duration is on bounds.
static SpacecraftState[]	AbstractEphemeris.generateSpacecraftState(PVCoordinatesProvider pvProv, AttitudeProvider attProvForces, AttitudeProvider attProvEvents, double step, AbsoluteDateInterval ptsInterval, Frame frame, double mu) Creates a spacecraft array with constant step size.
SpacecraftState	IntegratedEphemeris.getInitialState() Get the propagator initial state.
SpacecraftState	Ephemeris.getInitialState() Get the propagator initial state.
SpacecraftState	AbstractEphemeris.getInitialState() Get the propagator initial state.
protected SpacecraftState	LagrangeEphemeris.getInterpolatedSpacecraftState(AbsoluteDate date) Deprecated. Get the interpolated spacecraft state.
protected SpacecraftState	HermiteEphemeris.getInterpolatedSpacecraftState(AbsoluteDate date) Deprecated. Get the interpolated spacecraft state.
protected abstract SpacecraftState	AbstractEphemeris.getInterpolatedSpacecraftState(AbsoluteDate date) Get the interpolated spacecraft state.

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

protected Attitude[]	AbstractEphemeris.attitudesInterpolation(SpacecraftState[] tab, int order, int i0, AbsoluteDate date) This method is called only if attitudes are supported.
protected double[]	AbstractEphemeris.convertTab(SpacecraftState[] tab, int order) Convert the SpacecraftState[] into a double[] which represents the duration from the first state date.
protected int	AbstractEphemeris.indexValidity(SpacecraftState[] tab, int index) Checks if interpolation is valid : meaning if 0<= index +1 -interpOrder/2 or index + interpOrder/2 <= maximalIndex
protected AbsoluteDateInterval	AbstractEphemeris.intervalValidity(SpacecraftState[] tab) Corrects the min and max dates with the constraint of the number of interpolations points required.
void	IntegratedEphemeris.resetInitialState(SpacecraftState state) Reset the propagator initial state.
void	Ephemeris.resetInitialState(SpacecraftState state) Try (and fail) to reset the initial state.
void	AbstractEphemeris.resetInitialState(SpacecraftState state) Reset the propagator initial state.

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

AbstractEphemeris(SpacecraftState[] tab)
Simple constructor of class AbstractEphemeris, with interpolation order equal to 2.

AbstractEphemeris(SpacecraftState[] tab, int order)
Simple constructor of class AbstractEphemeris with defined interpolation order.

AbstractEphemeris(SpacecraftState[] tab, int order, ISearchIndex algo)
Constructor of class AbstractEphemeris where a search index algorithm is passed on the constructor.

AbstractEphemeris(SpacecraftState[] tab, ISearchIndex algo)
Constructor of class AbstractEphemeris where a search index algorithm is passed on the constructor and the order is by default equal to 2.

HermiteEphemeris(SpacecraftState[] tab)
Deprecated. Constructor of class HermiteEphemeris, used by other constructors of this class.

HermiteEphemeris(SpacecraftState[] tab, ISearchIndex algo)
Deprecated. Constructor of class HermiteEphemeris, where a search index algorithm is passed on the constructor.

HermiteEphemeris(SpacecraftState[] tabStates, Vector3D[] tabAcc)
Deprecated. Constructor of class HermiteEphemeris, where a search index algorithm is passed on the constructor.

HermiteEphemeris(SpacecraftState[] tab, Vector3D[] tabAcc, ISearchIndex algo)
Deprecated. Constructor of class HermiteEphemeris, where a search index algorithm is passed on the constructor.

LagrangeEphemeris(SpacecraftState[] tabulatedStates)
Deprecated. Constructor for a 8th order Lagrange interpolator.

LagrangeEphemeris(SpacecraftState[] tab, int order)
Deprecated. Constructor of class LagrangeEphemeris, used by other constructors of this class.

LagrangeEphemeris(SpacecraftState[] tab, int order, ISearchIndex algo)
Deprecated. Constructor of class LagrangeEphemeris, where a search index algorithm is passed on the constructor.

LagrangeEphemeris(SpacecraftState[] tab, ISearchIndex algo)
Deprecated. Constructor for a 8th order Lagrange interpolator, where a search index algorithm is passed on the constructor.

Constructor parameters in org.orekit.propagation.precomputed with type arguments of type SpacecraftState

Ephemeris(List<SpacecraftState> states, int interpolationPoints)
Constructor with tabulated states.

Uses of SpacecraftState in org.orekit.propagation.sampling

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

SpacecraftState	BasicStepInterpolator.getInterpolatedState() Get the interpolated state.
SpacecraftState	OrekitStepInterpolator.getInterpolatedState() Get the interpolated state.
SpacecraftState	AdaptedStepHandler.getInterpolatedState() Get the interpolated state.

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

void	OrekitFixedStepHandler.handleStep(SpacecraftState currentState, boolean isLast) Handle the current step.
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.
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.

Uses of SpacecraftState in org.orekit.utils

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

AbstractBoundedPVProvider(SpacecraftState[] tabState, ISearchIndex algo)
Creates an instance of AbstractBoundedPVProvider from a SpacecraftState table

EphemerisPvHermite(SpacecraftState[] tabState, Vector3D[] tabAcc, ISearchIndex algo)
Creates an instance of EphemerisPvHermite from a SpacecraftState table

EphemerisPvLagrange(SpacecraftState[] tabState, int order, ISearchIndex algo)
Creates an instance of EphemerisPvLagrange from a spacecraftstate list

Uses of SpacecraftState in org.orekit.wrenches

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

Vector3D	WrenchModel.computeTorque(SpacecraftState s) Compute the resulting torque at the mass centre of the spacecraft in the frame of the main part.
Vector3D	WrenchModel.computeTorque(SpacecraftState s, Vector3D origin, Frame frame) Compute the resulting wrench.
Wrench	WrenchModel.computeWrench(SpacecraftState s) Compute the resulting wrench at the mass centre of the spacecraft in the frame of the main part.
Wrench	WrenchModel.computeWrench(SpacecraftState s, Vector3D origin, Frame frame) Compute the resulting wrench.