Uses of Class
fr.cnes.sirius.patrius.utils.exception.PropagationException

Packages that use PropagationException

Package	Description
fr.cnes.sirius.patrius.forces.maneuvers
fr.cnes.sirius.patrius.propagation
fr.cnes.sirius.patrius.propagation.analytical
fr.cnes.sirius.patrius.propagation.analytical.tle
fr.cnes.sirius.patrius.propagation.analytical.twod
fr.cnes.sirius.patrius.propagation.numerical
fr.cnes.sirius.patrius.propagation.numerical.multi
fr.cnes.sirius.patrius.propagation.precomputed
fr.cnes.sirius.patrius.propagation.precomputed.multi
fr.cnes.sirius.patrius.propagation.sampling
fr.cnes.sirius.patrius.propagation.sampling.multi
fr.cnes.sirius.patrius.stela.propagation
fr.cnes.sirius.patrius.utils.exception

Uses of PropagationException in fr.cnes.sirius.patrius.forces.maneuvers

Methods in fr.cnes.sirius.patrius.forces.maneuvers that throw PropagationException

Modifier and Type	Method and Description
void	ContinuousThrustManeuver.handleStep(PatriusStepInterpolator interpolator, boolean isLast) Handle the current step.

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

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

Modifier and Type	Method and Description
protected SpacecraftState	AbstractPropagator.basicPropagate(AbsoluteDate date) Propagate an orbit without any fancy features.
double[]	AdditionalStateProvider.getAdditionalState(AbsoluteDate date) Get the additional state.
SpacecraftState	AbstractPropagator.propagate(AbsoluteDate target) Propagate towards a target date.
SpacecraftState	Propagator.propagate(AbsoluteDate target) Propagate towards a target date.
SpacecraftState	AnalyticalIntegratedEphemeris.propagate(AbsoluteDate target) Propagate towards a target date.
Map<String,SpacecraftState>	MultiPropagator.propagate(AbsoluteDate target) Propagate towards a target date.
SpacecraftState	AbstractPropagator.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	AnalyticalIntegratedEphemeris.propagate(AbsoluteDate start, AbsoluteDate target) Propagate from a start date towards a target date.
Map<String,SpacecraftState>	MultiPropagator.propagate(AbsoluteDate start, AbsoluteDate target) Propagate from a start date towards a target date.
protected abstract Orbit	AbstractPropagator.propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.
protected Orbit	AnalyticalIntegratedEphemeris.propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.
protected Orbit	PVCoordinatesPropagator.propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.
void	AbstractPropagator.resetInitialState(SpacecraftState state) Reset the propagator initial state.
void	Propagator.resetInitialState(SpacecraftState state) Reset the propagator initial state.

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

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

Modifier and Type	Method and Description
protected SpacecraftState	AdapterPropagator.basicPropagate(AbsoluteDate date) Propagate an orbit without any fancy features.
void	AnalyticalEphemerisModeHandler.handleStep(PatriusStepInterpolator interpolator, boolean isLast) Handle the current step.
Orbit	EcksteinHechlerPropagator.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	KeplerianPropagator.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	AdapterPropagator.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	EcksteinHechlerPropagator.resetInitialState(SpacecraftState state) Reset the propagator initial state.
void	J2SecularPropagator.resetInitialState(SpacecraftState state) Reset the propagator initial state.
void	KeplerianPropagator.resetInitialState(SpacecraftState state) Reset the propagator initial state.
void	AbstractLyddanePropagator.resetInitialState(SpacecraftState state) Reset the propagator initial state.
void	AdapterPropagator.resetInitialState(SpacecraftState state) Reset the propagator initial state.

Constructors in fr.cnes.sirius.patrius.propagation.analytical that throw PropagationException

Constructor and Description
EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitudeProvForces, AttitudeProvider attitudeProvEvents, double referenceRadiusIn, double muIn, Frame frame, double c20In, double c30In, double c40In, double c50In, double c60In, MassProvider massProvider, ParametersType paramsType) Build a propagator from orbit, attitude provider, mass and potential.
EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitudeProvForces, AttitudeProvider attitudeProvEvents, double referenceRadiusIn, double muIn, Frame frame, double c20In, double c30In, double c40In, double c50In, double c60In, ParametersType paramsType) Build a propagator from orbit, attitude provider for forces and events computation and potential.
EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double referenceRadiusIn, double muIn, Frame frame, double c20In, double c30In, double c40In, double c50In, double c60In, MassProvider massProvider, ParametersType paramsType) Build a propagator from orbit, attitude provider, mass and potential.
EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double referenceRadiusIn, double muIn, Frame frame, double c20In, double c30In, double c40In, double c50In, double c60In, ParametersType paramsType) Build a propagator from orbit, attitude provider and potential.
EcksteinHechlerPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, Frame frame, double c20In, double c30In, double c40In, double c50In, double c60In, MassProvider massProvider, ParametersType paramsType) Build a propagator from orbit, mass and potential.
EcksteinHechlerPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, Frame frame, double c20In, double c30In, double c40In, double c50In, double c60In, 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 fr.cnes.sirius.patrius.propagation.analytical.tle

Methods in fr.cnes.sirius.patrius.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.

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

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

Modifier and Type	Method and Description
protected Orbit	Analytical2DPropagator.propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.

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

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

Modifier and Type	Method and Description
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 fr.cnes.sirius.patrius.propagation.numerical.multi

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

Modifier and Type	Method and Description
Map<String,SpacecraftState>	MultiNumericalPropagator.propagate(AbsoluteDate target) Propagate towards a target date.
Map<String,SpacecraftState>	MultiNumericalPropagator.propagate(AbsoluteDate start, AbsoluteDate target) Propagate from a start date towards a target date.

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

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

Modifier and Type	Method and Description
protected SpacecraftState	IntegratedEphemeris.basicPropagate(AbsoluteDate date) Propagate an orbit without any fancy features.
SpacecraftState	Ephemeris.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.
void	IntegratedEphemeris.resetInitialState(SpacecraftState state) Reset the propagator initial state.
void	Ephemeris.resetInitialState(SpacecraftState state) Try (and fail) to reset the initial state.

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

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

Modifier and Type	Method and Description
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

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

Modifier and Type	Method and Description
void	PatriusStepNormalizer.handleStep(PatriusStepInterpolator interpolator, boolean isLast) Handle the last accepted step.
void	PatriusStepHandler.handleStep(PatriusStepInterpolator interpolator, boolean isLast) Handle the current step.
void	PatriusStepHandlerMultiplexer.handleStep(PatriusStepInterpolator interpolator, boolean isLast) Handle the current step.
void	PatriusFixedStepHandler.handleStep(SpacecraftState currentState, boolean isLast) Handle the current step.
void	BasicStepInterpolator.setInterpolatedDate(AbsoluteDate date) Set the interpolated date.
void	PatriusStepInterpolator.setInterpolatedDate(AbsoluteDate date) Set the interpolated date.
void	BasicStepInterpolator.storeDate(AbsoluteDate date) Store the current step date.

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

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

Modifier and Type	Method and Description
void	MultiPatriusFixedStepHandler.handleStep(Map<String,SpacecraftState> currentStates, boolean isLast) Handle the current step.
void	MultiPatriusStepHandler.handleStep(MultiPatriusStepInterpolator interpolator, boolean isLast) Handle the current step.
void	MultiPatriusStepNormalizer.handleStep(MultiPatriusStepInterpolator interpolator, boolean isLast) Handle the last accepted step.
void	MultiPatriusStepInterpolator.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

Modifier and Type	Method and Description
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) Get the mass.
protected SpacecraftState	StelaAbstractPropagator.goAhead(double stepSize, double dt, AbsoluteDate target) go one step ahead
void	ForcesStepHandler.handleStep(PatriusStepInterpolator interpolator, boolean isLast) Handle the current step.
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) Propagate from a start date towards a target date.
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 fr.cnes.sirius.patrius.utils.exception

Methods in fr.cnes.sirius.patrius.utils.exception 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(PatriusException oe) Recover a PropagationException, possibly embedded in a PatriusException.