Uses of Class
org.orekit.errors.PropagationException

Packages that use PropagationException

fr.cnes.sirius.patrius.propagation
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.propagation
org.orekit.errors	This package provides classes to generate and handle exceptions.
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.analytical.twod
org.orekit.propagation.numerical
org.orekit.propagation.precomputed
org.orekit.propagation.sampling	This package provides interfaces and classes dealing with step handling during propagation.

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

Methods in fr.cnes.sirius.patrius.propagation that throw PropagationException

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.
protected Orbit	PVCoordinatePropagator.propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.

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

Methods in fr.cnes.sirius.patrius.propagation.numerical.multi that throw PropagationException

Map<String,SpacecraftState>	MultiNumericalPropagator.propagate(AbsoluteDate target)
Map<String,SpacecraftState>	MultiNumericalPropagator.propagate(AbsoluteDate start, AbsoluteDate target)

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

Methods in fr.cnes.sirius.patrius.propagation.precomputed.multi that throw PropagationException

protected SpacecraftState	MultiIntegratedEphemeris.basicPropagate(AbsoluteDate date) Propagate an orbit without any fancy features.
protected Orbit	MultiIntegratedEphemeris.propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.
void	MultiIntegratedEphemeris.resetInitialState(SpacecraftState state) Reset the propagator initial state.

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

Methods in fr.cnes.sirius.patrius.propagation.sampling.multi that throw PropagationException

void	MultiOrekitFixedStepHandler.handleStep(Map<String,SpacecraftState> currentStates, boolean isLast) Handle the current step.
void	MultiOrekitStepNormalizer.handleStep(MultiOrekitStepInterpolator interpolator, boolean isLast) Handle the last accepted step.
void	MultiOrekitStepHandler.handleStep(MultiOrekitStepInterpolator interpolator, boolean isLast) Handle the current step.
void	MultiOrekitStepInterpolator.setInterpolatedDate(AbsoluteDate date) Set the interpolated date.
void	MultiAdaptedStepHandler.setInterpolatedDate(AbsoluteDate date) Set the interpolated date.

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

Methods in fr.cnes.sirius.patrius.stela.propagation that throw PropagationException

protected SpacecraftState	StelaAbstractPropagator.basicPropagate(AbsoluteDate date) Propagate a SpacecraftState without any fancy features.
protected abstract double	StelaAbstractPropagator.getMass(AbsoluteDate date) Get the mass.
protected double	StelaGTOPropagator.getMass(AbsoluteDate date)
SpacecraftState	StelaAbstractPropagator.goAhead(double stepSize, double dt, AbsoluteDate target) go one step ahead
void	ForcesStepHandler.handleStep(OrekitStepInterpolator interpolator, boolean isLast)
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)
void	StelaAbstractPropagator.resetInitialState(SpacecraftState state) Reset the propagator initial state.
void	StelaBasicInterpolator.setInterpolatedDate(AbsoluteDate interpolatedDate) Set the interpolated date.
void	StelaBasicInterpolator.storeSC(SpacecraftState initialStateIn, SpacecraftState targetState) Store the current dates and spacecraft states.

Uses of PropagationException in org.orekit.errors

Methods in org.orekit.errors that return PropagationException

static PropagationException	PropagationException.unwrap(ExceptionContextProvider provider) Recover a PropagationException, possibly embedded in an ExceptionContextProvider.
static PropagationException	PropagationException.unwrap(OrekitException oe) Recover a PropagationException, possibly embedded in a OrekitException.

Uses of PropagationException in org.orekit.propagation

Methods in org.orekit.propagation that throw PropagationException

protected SpacecraftState	AbstractPropagator.basicPropagate(AbsoluteDate date) Propagate an orbit without any fancy features.
double[]	AdditionalStateProvider.getAdditionalState(AbsoluteDate date) Get the additional state.
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.
protected Orbit	AnalyticalIntegratedEphemeris.propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.
protected abstract Orbit	AbstractPropagator.propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.
void	Propagator.resetInitialState(SpacecraftState state) Reset the propagator initial state.
void	AbstractPropagator.resetInitialState(SpacecraftState state) Reset the propagator initial state.

Uses of PropagationException in org.orekit.propagation.analytical

Methods in org.orekit.propagation.analytical that throw PropagationException

protected SpacecraftState	AdapterPropagator.basicPropagate(AbsoluteDate date) Propagate an orbit without any fancy features.
void	AnalyticalEphemerisModeHandler.handleStep(OrekitStepInterpolator interpolator, boolean isLast) Handle the current step.
protected Orbit	AdapterPropagator.propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.
Orbit	EcksteinHechlerPropagator.propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.
Orbit	AbstractLyddanePropagator.propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.
protected Orbit	KeplerianPropagator.propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.
Orbit	J2SecularPropagator.propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.
protected Orbit	AbstractLyddanePropagator.propagateOrbit(AbsoluteDate date, Orbit secularOrbit, Frame outputFrame, AbstractLyddanePropagator.LyddaneParametersType returnType) Propagate orbit to provided date.
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 that throw PropagationException

EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitudeProvForces, AttitudeProvider attitudeProvEvents, double referenceRadius, double mu, Frame frame, double c20, double c30, double c40, double c50, double c60, MassProvider massProvider, ParametersType paramsType)
Build a propagator from orbit, attitude provider, mass and potential.

EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitudeProvForces, AttitudeProvider attitudeProvEvents, double referenceRadius, double mu, Frame frame, double c20, double c30, double c40, double c50, double c60, ParametersType paramsType)
Build a propagator from orbit, attitude provider for forces and events computation and potential.

EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double referenceRadius, double mu, Frame frame, double c20, double c30, double c40, double c50, double c60, MassProvider massProvider, ParametersType paramsType)
Build a propagator from orbit, attitude provider, mass and potential.

EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double referenceRadius, double mu, Frame frame, double c20, double c30, double c40, double c50, double c60, ParametersType paramsType)
Build a propagator from orbit, attitude provider and potential.

EcksteinHechlerPropagator(Orbit initialOrbit, double referenceRadius, double mu, Frame frame, double c20, double c30, double c40, double c50, double c60, MassProvider massProvider, ParametersType paramsType)
Build a propagator from orbit, mass and potential.

EcksteinHechlerPropagator(Orbit initialOrbit, double referenceRadius, double mu, Frame frame, double c20, double c30, double c40, double c50, double c60, ParametersType paramsType)
Build a propagator from orbit and potential.

KeplerianPropagator(Orbit initialOrbit)
Build a propagator from orbit only.

KeplerianPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv)
Build a propagator from orbit and a single attitude provider.

KeplerianPropagator(Orbit initialOrbit, AttitudeProvider attitudeProvForces, AttitudeProvider attitudeProvEvents)
Build a propagator from orbit and attitude provider for forces and event computation.

KeplerianPropagator(Orbit initialOrbit, AttitudeProvider attitudeProvForces, AttitudeProvider attitudeProvEvents, double mu)
Build a propagator from orbit, attitude provider for forces and events computation and central attraction coefficient μ.

KeplerianPropagator(Orbit initialOrbit, AttitudeProvider attitudeProvForces, AttitudeProvider attitudeProvEvents, double mu, MassProvider massProvider)
Build propagator from orbit, attitude provider, central attraction coefficient μ and mass.

KeplerianPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double mu)
Build a propagator from orbit, a single attitude provider and central attraction coefficient μ.

KeplerianPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double mu, MassProvider massProvider)
Build propagator from orbit, attitude provider, central attraction coefficient μ and mass.

KeplerianPropagator(Orbit initialOrbit, double mu)
Build a propagator from orbit and central attraction coefficient μ.

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

Methods in org.orekit.propagation.analytical.tle that throw PropagationException

protected Orbit

TLEPropagator.propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.

Uses of PropagationException in org.orekit.propagation.analytical.twod

Methods in org.orekit.propagation.analytical.twod that throw PropagationException

protected Orbit

Analytical2DPropagator.propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.

Uses of PropagationException in org.orekit.propagation.numerical

Methods in org.orekit.propagation.numerical that throw PropagationException

void	TimeDerivativesEquations.initDerivatives(double[] yDot, Orbit currentOrbit) Initialize all derivatives to zero.
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.

Uses of PropagationException in org.orekit.propagation.precomputed

Methods in org.orekit.propagation.precomputed that throw PropagationException

protected SpacecraftState	IntegratedEphemeris.basicPropagate(AbsoluteDate date) Propagate an orbit without any fancy features.
SpacecraftState	Ephemeris.basicPropagate(AbsoluteDate date)
protected SpacecraftState	AbstractEphemeris.basicPropagate(AbsoluteDate date)
SpacecraftState	Ephemeris.getInitialState() Get the propagator initial state.
protected Orbit	IntegratedEphemeris.propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.
protected Orbit	Ephemeris.propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.
protected Orbit	AbstractEphemeris.propagateOrbit(AbsoluteDate date)
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.

Uses of PropagationException in org.orekit.propagation.sampling

Methods in org.orekit.propagation.sampling that throw PropagationException

void	OrekitStepHandler.handleStep(OrekitStepInterpolator interpolator, boolean isLast) Handle the current step.
void	OrekitStepNormalizer.handleStep(OrekitStepInterpolator interpolator, boolean isLast) Handle the last accepted step.
void	OrekitStepHandlerMultiplexer.handleStep(OrekitStepInterpolator interpolator, boolean isLast) Handle the current step.
void	OrekitFixedStepHandler.handleStep(SpacecraftState currentState, boolean isLast) Handle the current step.
void	BasicStepInterpolator.setInterpolatedDate(AbsoluteDate date) Set the interpolated date.
void	OrekitStepInterpolator.setInterpolatedDate(AbsoluteDate date) Set the interpolated date.
void	BasicStepInterpolator.storeDate(AbsoluteDate date) Store the current step date.