Uses of Class
org.orekit.errors.PropagationException

Packages that use PropagationException

Package	Description
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.conversion	This package provides tools to convert a given propagator or a set of SpacecraftState into another propagator.
org.orekit.propagation.integration
org.orekit.propagation.numerical
org.orekit.propagation.sampling	This package provides interfaces and classes dealing with step handling during propagation.
org.orekit.propagation.semianalytical.dsst	This package provides an implementation of the Draper Semi-analytical Satellite Theory (DSST).

Uses of PropagationException in org.orekit.errors

Methods in org.orekit.errors that return PropagationException

Modifier and Type	Method and Description
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

Modifier and Type	Method and Description
double[]	AdditionalStateProvider.getAdditionalState(SpacecraftState state) Get the additional state.
SpacecraftState	Propagator.getInitialState() Get the propagator initial state.
SpacecraftState	AbstractPropagator.getInitialState() Get the propagator initial state.
SpacecraftState	Propagator.propagate(AbsoluteDate target) Propagate towards a target date.
SpacecraftState	AbstractPropagator.propagate(AbsoluteDate target) Propagate towards a target date.
SpacecraftState	Propagator.propagate(AbsoluteDate start, AbsoluteDate target) Propagate from a start date towards a target date.
void	Propagator.resetInitialState(SpacecraftState state) Reset the propagator initial state.
void	AbstractPropagator.resetInitialState(SpacecraftState state) Reset the propagator initial state.
protected SpacecraftState	AbstractPropagator.updateAdditionalStates(SpacecraftState original) Update state by adding all additional states.

Uses of PropagationException in org.orekit.propagation.analytical

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

Modifier and Type	Method and Description
protected SpacecraftState	AdapterPropagator.basicPropagate(AbsoluteDate date) Propagate an orbit without any fancy features.
protected SpacecraftState	AbstractAnalyticalPropagator.basicPropagate(AbsoluteDate date) Propagate an orbit without any fancy features.
SpacecraftState	Ephemeris.basicPropagate(AbsoluteDate date)
SpacecraftState	AdapterPropagator.getInitialState() Get the propagator initial state.
SpacecraftState	Ephemeris.getInitialState() Get the propagator initial state.
protected double	AdapterPropagator.getMass(AbsoluteDate date) Get the mass.
protected abstract double	AbstractAnalyticalPropagator.getMass(AbsoluteDate date) Get the mass.
protected double	Ephemeris.getMass(AbsoluteDate date) Get the mass.
SpacecraftState	AbstractAnalyticalPropagator.propagate(AbsoluteDate start, AbsoluteDate target) Propagate from a start date towards a target date.
protected Orbit	AdapterPropagator.propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.
CartesianOrbit	EcksteinHechlerPropagator.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.
protected abstract Orbit	AbstractAnalyticalPropagator.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.
void	AdapterPropagator.resetInitialState(SpacecraftState state) Reset the propagator initial state.
void	EcksteinHechlerPropagator.resetInitialState(SpacecraftState state) Reset the propagator initial state.
void	KeplerianPropagator.resetInitialState(SpacecraftState state) Reset the propagator initial state.
void	Ephemeris.resetInitialState(SpacecraftState state) Try (and fail) to reset the initial state.

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

Constructor and Description
EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double referenceRadius, double mu, double c20, double c30, double c40, double c50, double c60) Build a propagator from orbit, attitude provider and potential.
EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double mass, double referenceRadius, double mu, double c20, double c30, double c40, double c50, double c60) Build a propagator from orbit, attitude provider, mass and potential.
EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double mass, UnnormalizedSphericalHarmonicsProvider provider) Build a propagator from orbit, attitude provider, mass and potential provider.
EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, UnnormalizedSphericalHarmonicsProvider provider) Build a propagator from orbit, attitude provider and potential provider.
EcksteinHechlerPropagator(Orbit initialOrbit, double referenceRadius, double mu, double c20, double c30, double c40, double c50, double c60) Build a propagator from orbit and potential.
EcksteinHechlerPropagator(Orbit initialOrbit, double mass, double referenceRadius, double mu, double c20, double c30, double c40, double c50, double c60) Build a propagator from orbit, mass and potential.
EcksteinHechlerPropagator(Orbit initialOrbit, double mass, UnnormalizedSphericalHarmonicsProvider provider) Build a propagator from orbit, mass and potential provider.
EcksteinHechlerPropagator(Orbit initialOrbit, UnnormalizedSphericalHarmonicsProvider provider) Build a propagator from orbit and potential provider.
KeplerianPropagator(Orbit initialOrbit) Build a propagator from orbit only.
KeplerianPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv) Build a propagator from orbit and attitude provider.
KeplerianPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double mu) Build a propagator from orbit, attitude provider and central attraction coefficient μ.
KeplerianPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double mu, double mass) 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

Modifier and Type	Method and Description
protected Orbit	TLEPropagator.propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.
void	TLEPropagator.resetInitialState(SpacecraftState state) Reset the propagator initial state.

Uses of PropagationException in org.orekit.propagation.conversion

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

Modifier and Type	Method and Description
AbstractIntegrator	AdamsMoultonIntegratorBuilder.buildIntegrator(Orbit orbit) Build a first order integrator.
AbstractIntegrator	DormandPrince853IntegratorBuilder.buildIntegrator(Orbit orbit) Build a first order integrator.
AbstractIntegrator	DormandPrince54IntegratorBuilder.buildIntegrator(Orbit orbit) Build a first order integrator.
AbstractIntegrator	AdamsBashforthIntegratorBuilder.buildIntegrator(Orbit orbit) Build a first order integrator.
AbstractIntegrator	GraggBulirschStoerIntegratorBuilder.buildIntegrator(Orbit orbit) Build a first order integrator.
AbstractIntegrator	HighamHall54IntegratorBuilder.buildIntegrator(Orbit orbit) Build a first order integrator.
AbstractIntegrator	FirstOrderIntegratorBuilder.buildIntegrator(Orbit orbit) Build a first order integrator.

Uses of PropagationException in org.orekit.propagation.integration

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

Modifier and Type	Method and Description
protected SpacecraftState	IntegratedEphemeris.basicPropagate(AbsoluteDate date) Propagate an orbit without any fancy features.
SpacecraftState	IntegratedEphemeris.getInitialState() Get the propagator initial state.
protected double	IntegratedEphemeris.getMass(AbsoluteDate date) Get the mass.
SpacecraftState	AbstractIntegratedPropagator.propagate(AbsoluteDate target) Propagate towards a target date.
SpacecraftState	AbstractIntegratedPropagator.propagate(AbsoluteDate tStart, AbsoluteDate tEnd) Propagate from a start date towards a target date.
protected SpacecraftState	AbstractIntegratedPropagator.propagate(AbsoluteDate tEnd, boolean activateHandlers) Propagation with or without event detection.
protected Orbit	IntegratedEphemeris.propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.
void	IntegratedEphemeris.resetInitialState(SpacecraftState state) Reset the propagator initial state.

Uses of PropagationException in org.orekit.propagation.numerical

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

Modifier and Type	Method and Description
void	NumericalPropagator.resetInitialState(SpacecraftState state) Reset the propagator initial state.
void	NumericalPropagator.setInitialState(SpacecraftState initialState) Set the initial state.
static double[][]	NumericalPropagator.tolerances(double dP, Orbit orbit, OrbitType type) Estimate tolerance vectors for integrators.

Uses of PropagationException in org.orekit.propagation.sampling

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

Modifier and Type	Method and Description
void	OrekitStepHandlerMultiplexer.handleStep(OrekitStepInterpolator interpolator, boolean isLast) Handle the current step.
void	OrekitStepNormalizer.handleStep(OrekitStepInterpolator interpolator, boolean isLast) Handle the last accepted step.
void	OrekitStepHandler.handleStep(OrekitStepInterpolator interpolator, boolean isLast) Handle the current step.
void	OrekitFixedStepHandler.handleStep(SpacecraftState currentState, boolean isLast) Handle the current step.
void	OrekitStepHandlerMultiplexer.init(SpacecraftState s0, AbsoluteDate t) Initialize step handler at the start of a propagation.
void	OrekitStepNormalizer.init(SpacecraftState s0, AbsoluteDate t) Initialize step handler at the start of a propagation.
void	OrekitFixedStepHandler.init(SpacecraftState s0, AbsoluteDate t) Initialize step handler at the start of a propagation.
void	OrekitStepHandler.init(SpacecraftState s0, AbsoluteDate t) Initialize step handler at the start of a propagation.
void	OrekitStepInterpolator.setInterpolatedDate(AbsoluteDate date) Set the interpolated date.

Uses of PropagationException in org.orekit.propagation.semianalytical.dsst

Methods in org.orekit.propagation.semianalytical.dsst that throw PropagationException

Modifier and Type	Method and Description
void	DSSTPropagator.resetInitialState(SpacecraftState state) Reset the initial state.
void	DSSTPropagator.setInitialState(SpacecraftState initialState) Set the initial state with osculating orbital elements.
void	DSSTPropagator.setInitialState(SpacecraftState initialState, boolean isOsculating) Set the initial state.
static double[][]	DSSTPropagator.tolerances(double dP, Orbit orbit) Estimate tolerance vectors for an AdaptativeStepsizeIntegrator.