fr.cnes.sirius.patrius.propagation
Class PVCoordinatePropagator

java.lang.Object
  org.orekit.propagation.AbstractPropagator
      fr.cnes.sirius.patrius.propagation.PVCoordinatePropagator

All Implemented Interfaces:

Serializable, Propagator, PVCoordinatesProvider

public class PVCoordinatePropagator
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.

Warning: Events detector with EventDetector.Action.RESET_STATE should not be used with this propagator fed with a "precomputed" PV coordinate provider (such as an ephemeris or an orbit object). In particular, impulse maneuvers cannot be used. Otherwise propagation will fail. This is due to the fact that the provided PV coordinate provider is not valid any more after the EventDetector.Action.RESET_STATE action.

Since:

3.1

Version:

$Id: PVCoordinatePropagator.java 17585 2017-05-10 13:27:59Z bignon $

Author:

chabaudp

See Also:

Serialized Form

Concurrency :

not thread-safe

Concurrency comment :

extends the AbstractPropagator class

Field Summary

Fields inherited from class org.orekit.propagation.AbstractPropagator

MASS

Fields inherited from interface org.orekit.propagation.Propagator

EPHEMERIS_GENERATION_MODE, MASTER_MODE, SLAVE_MODE

Constructor Summary

PVCoordinatePropagator(PVCoordinatesProvider pvCoordProvider, AbsoluteDate initDate, double mu, Frame frame)
Creates an instance of PVCoordinatePropagator without attitude and additional state providers

PVCoordinatePropagator(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

protected Orbit

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

Methods inherited from class org.orekit.propagation.AbstractPropagator

acceptStep, addAdditionalStateProvider, addAdditionalStateProvider, addEventDetector, basicPropagate, clearEventsDetectors, getAttitudeProvider, getAttitudeProviderEvents, getAttitudeProviderForces, getEventsDetectors, getFrame, getGeneratedEphemeris, getInitialState, getMode, getPVCoordinates, getPvProvider, 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

Constructor Detail

PVCoordinatePropagator

public PVCoordinatePropagator(PVCoordinatesProvider pvCoordProvider,
                              AbsoluteDate initDate,
                              double mu,
                              Frame frame)
                       throws OrekitException

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:

OrekitException - when a problem occurs in setting initial state

IllegalArgumentException - if frame is not pseudo inertial

PVCoordinatePropagator

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

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:

OrekitException - 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