fr.cnes.sirius.patrius.propagation.analytical

Class KeplerianPropagator

java.lang.Object

fr.cnes.sirius.patrius.propagation.AbstractPropagator

fr.cnes.sirius.patrius.propagation.analytical.KeplerianPropagator

All Implemented Interfaces:

PVCoordinatesProvider, Propagator, Serializable

public class KeplerianPropagator
extends AbstractPropagator

Simple keplerian orbit propagator.

Author:

Guylaine Prat

See Also:

Orbit, Serialized Form

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
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.

Method Summary

Modifier and Type	Method and Description
protected void	manageStateFrame() Manage the state frame : the orbit to propagate is converted in the propagation frame.
protected Orbit	propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.
void	resetInitialState(SpacecraftState state) Reset the propagator initial state.

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, propagate, propagate, 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

KeplerianPropagator

public KeplerianPropagator(Orbit initialOrbit)
                    throws PropagationException

Build a propagator from orbit only.

The central attraction coefficient μ is set to the same value used for the initial orbit definition. Mass and attitude provider are set to null values.

Parameters:

initialOrbit - initial orbit

Throws:

PropagationException - if initial attitude cannot be computed

KeplerianPropagator

public KeplerianPropagator(Orbit initialOrbit,
                           double mu)
                    throws PropagationException

Build a propagator from orbit and central attraction coefficient μ.

Mass and attitude provider are set to null values.

Parameters:

initialOrbit - initial orbit

mu - central attraction coefficient (m^3/s^2)

Throws:

PropagationException - if initial attitude cannot be computed

KeplerianPropagator

public KeplerianPropagator(Orbit initialOrbit,
                           AttitudeProvider attitudeProv)
                    throws PropagationException

Build a propagator from orbit and a single attitude provider.

The central attraction coefficient μ is set to the same value used for the initial orbit definition. Mass is set to null value.

Parameters:

initialOrbit - initial orbit

attitudeProv - attitude provider

Throws:

PropagationException - if initial attitude cannot be computed

KeplerianPropagator

public KeplerianPropagator(Orbit initialOrbit,
                           AttitudeProvider attitudeProvForces,
                           AttitudeProvider attitudeProvEvents)
                    throws PropagationException

Build a propagator from orbit and attitude provider for forces and event computation.

The central attraction coefficient μ is set to the same value used for the initial orbit definition. Mass is set to null value.

Parameters:

initialOrbit - initial orbit

attitudeProvForces - attitude provider for forces computation

attitudeProvEvents - attitude provider for events computation

Throws:

PropagationException - if initial attitude cannot be computed

KeplerianPropagator

public KeplerianPropagator(Orbit initialOrbit,
                           AttitudeProvider attitudeProv,
                           double mu)
                    throws PropagationException

Build a propagator from orbit, a single attitude provider and central attraction coefficient μ.

Mass is set to null value.

Parameters:

initialOrbit - initial orbit

attitudeProv - attitude provider

mu - central attraction coefficient (m^3/s^2)

Throws:

PropagationException - if initial attitude cannot be computed

KeplerianPropagator

public KeplerianPropagator(Orbit initialOrbit,
                           AttitudeProvider attitudeProvForces,
                           AttitudeProvider attitudeProvEvents,
                           double mu)
                    throws PropagationException

Build a propagator from orbit, attitude provider for forces and events computation and central attraction coefficient μ.

Mass is set to null value.

Parameters:

initialOrbit - initial orbit

attitudeProvForces - attitude provider for forces computation

attitudeProvEvents - attitude provider for events computation

mu - central attraction coefficient (m^3/s^2)

Throws:

PropagationException - if initial attitude cannot be computed

KeplerianPropagator

public KeplerianPropagator(Orbit initialOrbit,
                           AttitudeProvider attitudeProv,
                           double mu,
                           MassProvider massProvider)
                    throws PropagationException

Build propagator from orbit, attitude provider, central attraction coefficient μ and mass.

Parameters:

initialOrbit - initial orbit

attitudeProv - attitude provider

mu - central attraction coefficient (m^3/s^2)

massProvider - spacecraft mass (kg)

Throws:

PropagationException - if initial attitude cannot be computed

KeplerianPropagator

public KeplerianPropagator(Orbit initialOrbit,
                           AttitudeProvider attitudeProvForces,
                           AttitudeProvider attitudeProvEvents,
                           double mu,
                           MassProvider massProvider)
                    throws PropagationException

Build propagator from orbit, attitude provider, central attraction coefficient μ and mass.

Parameters:

initialOrbit - initial orbit

attitudeProvForces - attitude provider for forces computation

attitudeProvEvents - attitude provider for events computation

mu - central attraction coefficient (m^3/s^2)

massProvider - spacecraft mass (kg)

Throws:

PropagationException - if initial attitude cannot be computed

Method Detail

resetInitialState

public void resetInitialState(SpacecraftState state)
                       throws PropagationException

Reset the propagator initial state.

Specified by:

resetInitialState in interface Propagator

Overrides:

resetInitialState in class AbstractPropagator

Parameters:

state - new initial state to consider

Throws:

PropagationException - if initial state cannot be reset

manageStateFrame

protected void manageStateFrame()
                         throws PatriusException

Manage the state frame : the orbit to propagate is converted in the propagation frame.

Overrides:

manageStateFrame in class AbstractPropagator

Throws:

PatriusException - if the frame of the initial state is not inertial or pseudo-inertial

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