fr.cnes.sirius.patrius.propagation

Class PVCoordinatesPropagator

java.lang.Object

fr.cnes.sirius.patrius.propagation.AbstractPropagator

fr.cnes.sirius.patrius.propagation.PVCoordinatesPropagator

All Implemented Interfaces:

PVCoordinatesProvider, Propagator, SpacecraftStateProvider, Serializable

public class PVCoordinatesPropagator
extends AbstractPropagator

This class is an analytical propagator which propagates states from the input PV, Attitude, and additional state provider.

It can handle events and all functionalities from extended AbstractPropagator class.

The resetInitialState action will do nothing on this propagator but is authorized to reset possible included attitude laws for instance.

Since:

3.1

Version:

$Id$

Author:

chabaudp

See Also:

Serialized Form

Concurrency :

not thread-safe

Concurrency comment :

extends the AbstractPropagator class

Field Summary

Fields inherited from class fr.cnes.sirius.patrius.propagation.AbstractPropagator

MASS

Fields inherited from interface fr.cnes.sirius.patrius.propagation.Propagator

EPHEMERIS_GENERATION_MODE, MASTER_MODE, SLAVE_MODE

Constructor Summary

Constructors

Constructor and Description
PVCoordinatesPropagator(PVCoordinatesProvider pvCoordProvider, AbsoluteDate initDate, double mu, Frame frame) Creates an instance of PVCoordinatePropagator without attitude and additional state providers
PVCoordinatesPropagator(PVCoordinatesProvider pvCoordProvider, AbsoluteDate initDate, double mu, Frame frame, AttitudeProvider attProviderForces, AttitudeProvider attProviderEvents, List<AdditionalStateProvider> additionalStateProviders) Creates an instance of PVCoordinatePropagator with PV, attitude for forces, attitude for events, and additional state providers given by the user.

Method Summary

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

Methods inherited from class fr.cnes.sirius.patrius.propagation.AbstractPropagator

acceptStep, addAdditionalStateProvider, addAdditionalStateProvider, addEventDetector, basicPropagate, clearEventsDetectors, getAttitudeProvider, getAttitudeProviderEvents, getAttitudeProviderForces, getEventsDetectors, getFrame, getGeneratedEphemeris, getInitialState, getMode, getPVCoordinates, getPvProvider, getSpacecraftState, manageStateFrame, propagate, propagate, resetInitialState, setAttitudeProvider, setAttitudeProviderEvents, setAttitudeProviderForces, setEphemerisMode, setMasterMode, setMasterMode, setOrbitFrame, setSlaveMode, setStartDate

Methods inherited from class java.lang.Object

clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait

Methods inherited from interface fr.cnes.sirius.patrius.propagation.Propagator

getNativeFrame

Constructor Detail

PVCoordinatesPropagator

public PVCoordinatesPropagator(PVCoordinatesProvider pvCoordProvider,
                               AbsoluteDate initDate,
                               double mu,
                               Frame frame)
                        throws PatriusException

Creates an instance of PVCoordinatePropagator without attitude and additional state providers

Parameters:

pvCoordProvider - The position velocity coordinate provider used to propagate position velocity

initDate - reference date

mu - used for internal orbit parameter to convert orbital parameters type

frame - used to express the pv coordinates

Throws:

PatriusException - when a problem occurs in setting initial state

IllegalArgumentException - if frame is not pseudo inertial

PVCoordinatesPropagator

public PVCoordinatesPropagator(PVCoordinatesProvider pvCoordProvider,
                               AbsoluteDate initDate,
                               double mu,
                               Frame frame,
                               AttitudeProvider attProviderForces,
                               AttitudeProvider attProviderEvents,
                               List<AdditionalStateProvider> additionalStateProviders)
                        throws PatriusException

Creates an instance of PVCoordinatePropagator with PV, attitude for forces, attitude for events, and additional state providers given by the user.

Parameters:

pvCoordProvider - The position velocity coordinate provider used to propagate position velocity

initDate - reference date

mu - used for internal orbit parameter to convert orbital parameters type

frame - used to express the pv coordinates

attProviderForces - The attitude provider used to compute forces. Can be null.

attProviderEvents - The attitude provider used to compute events. Can be null.

additionalStateProviders - The additional state providers used to propagate additional states. Can be null.

Throws:

PatriusException - when a problem occurs in setting initial state

IllegalArgumentException - if frame is not pseudo inertial

Method Detail

propagateOrbit

protected Orbit propagateOrbit(AbsoluteDate date)
                        throws PropagationException

Extrapolate an orbit up to a specific target date.

Specified by:

propagateOrbit in class AbstractPropagator

Parameters:

date - target date for the orbit

Returns:

extrapolated parameters

Throws:

PropagationException - if some parameters are out of bounds