org.orekit.propagation.analytical

Class KeplerianPropagator

java.lang.Object

org.orekit.propagation.AbstractPropagator

org.orekit.propagation.analytical.AbstractAnalyticalPropagator

org.orekit.propagation.analytical.KeplerianPropagator

All Implemented Interfaces:

Serializable, Propagator, PVCoordinatesProvider

public class KeplerianPropagator
extends AbstractAnalyticalPropagator
implements Serializable

Simple keplerian orbit propagator.

Author:

Guylaine Prat

See Also:

Orbit, Serialized Form

Field Summary

Fields inherited from interface org.orekit.propagation.Propagator

DEFAULT_LAW, DEFAULT_MASS, 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 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.

Method Summary

Methods

Modifier and Type	Method and Description
protected double	getMass(AbsoluteDate date) Get the mass.
protected Orbit	propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.
void	resetInitialState(SpacecraftState state) Reset the propagator initial state.
protected void	resetIntermediateState(SpacecraftState state, boolean forward) Reset an intermediate state.

Methods inherited from class org.orekit.propagation.analytical.AbstractAnalyticalPropagator

acceptStep, addEventDetector, basicPropagate, clearEventsDetectors, getEventsDetectors, getGeneratedEphemeris, getPvProvider, propagate

Methods inherited from class org.orekit.propagation.AbstractPropagator

addAdditionalStateProvider, getAdditionalStateProviders, getAttitudeProvider, getFixedStepSize, getFrame, getInitialState, getManagedAdditionalStates, getMode, getPVCoordinates, getStartDate, getStepHandler, isAdditionalStateManaged, propagate, setAttitudeProvider, setEphemerisMode, setMasterMode, setMasterMode, setSlaveMode, setStartDate, updateAdditionalStates

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 unspecified non-null arbitrary 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 unspecified non-null arbitrary values.

Parameters:

initialOrbit - initial orbit

mu - central attraction coefficient (m³/s²)

Throws:

PropagationException - if initial attitude cannot be computed

KeplerianPropagator

public KeplerianPropagator(Orbit initialOrbit,
                   AttitudeProvider attitudeProv)
                    throws PropagationException

Build a propagator from orbit and attitude provider.

The central attraction coefficient μ is set to the same value used for the initial orbit definition. Mass is set to an unspecified non-null arbitrary value.

Parameters:

initialOrbit - initial orbit

attitudeProv - attitude provider

Throws:

PropagationException - if initial attitude cannot be computed

KeplerianPropagator

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

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

Mass is set to an unspecified non-null arbitrary value.

Parameters:

initialOrbit - initial orbit

attitudeProv - attitude provider

mu - central attraction coefficient (m³/s²)

Throws:

PropagationException - if initial attitude cannot be computed

KeplerianPropagator

public KeplerianPropagator(Orbit initialOrbit,
                   AttitudeProvider attitudeProv,
                   double mu,
                   double mass)
                    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 (m³/s²)

mass - 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 AbstractAnalyticalPropagator

Parameters:

state - new initial state to consider

Throws:

PropagationException - if initial state cannot be reset

resetIntermediateState

protected void resetIntermediateState(SpacecraftState state,
                          boolean forward)
                               throws PropagationException

Reset an intermediate state.

Overrides:

resetIntermediateState in class AbstractAnalyticalPropagator

Parameters:

state - new intermediate state to consider

forward - if true, the intermediate state is valid for propagations after itself

Throws:

PropagationException - if initial state cannot be reset

propagateOrbit

protected Orbit propagateOrbit(AbsoluteDate date)
                        throws PropagationException

Extrapolate an orbit up to a specific target date.

Specified by:

propagateOrbit in class AbstractAnalyticalPropagator

Parameters:

date - target date for the orbit

Returns:

extrapolated parameters

Throws:

PropagationException - if some parameters are out of bounds

getMass

protected double getMass(AbsoluteDate date)

Get the mass.

Specified by:

getMass in class AbstractAnalyticalPropagator

Parameters:

date - target date for the orbit

Returns:

mass mass