org.orekit.propagation.analytical
Class KeplerianPropagator

java.lang.Object
  org.orekit.propagation.AbstractPropagator
      org.orekit.propagation.analytical.KeplerianPropagator

All Implemented Interfaces:

java.io.Serializable, BasicPropagator, Propagator, PVCoordinatesProvider

public class KeplerianPropagator
extends AbstractPropagator

Simple keplerian orbit propagator.

Version:

$Revision:1665 $ $Date:2008-06-11 12:12:59 +0200 (mer., 11 juin 2008) $

Author:

Guylaine Prat

See Also:

Orbit, Serialized Form

Field Summary

Fields inherited from interface org.orekit.propagation.Propagator

EPHEMERIS_GENERATION_MODE, MASTER_MODE, SLAVE_MODE

Constructor Summary

KeplerianPropagator(Orbit initialOrbit)
Build a propagator from orbit only.

KeplerianPropagator(Orbit initialOrbit, AttitudeLaw attitudeLaw)
Build a propagator from orbit and attitude law.

KeplerianPropagator(Orbit initialOrbit, AttitudeLaw attitudeLaw, double mu)
Build a propagator from orbit, attitude law and central attraction coefficient μ.

KeplerianPropagator(Orbit initialOrbit, AttitudeLaw attitudeLaw, double mu, double mass)
Build propagator from orbit, attitude law, central attraction coefficient μ and mass.

KeplerianPropagator(Orbit initialOrbit, double mu)
Build a propagator from orbit and central attraction coefficient μ.

Method Summary

protected SpacecraftState	basicPropagate(AbsoluteDate date) Propagate an orbit without any fancy features.
SpacecraftState	getInitialState() Get the propagator initial state.
void	resetInitialState(SpacecraftState state) Reset the propagator initial state.

Methods inherited from class org.orekit.propagation.AbstractPropagator

addEndDateChecker, addEventDetector, clearEventsDetectors, getEventsDetectors, getGeneratedEphemeris, getMode, getPVCoordinates, propagate, setEphemerisMode, setMasterMode, setMasterMode, setSlaveMode

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 law 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 law are set to unspecified non-null arbitrary 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,
                           AttitudeLaw attitudeLaw)
                    throws PropagationException

Build a propagator from orbit and attitude law.

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

attitudeLaw - attitude law

Throws:

PropagationException - if initial attitude cannot be computed

KeplerianPropagator

public KeplerianPropagator(Orbit initialOrbit,
                           AttitudeLaw attitudeLaw,
                           double mu)
                    throws PropagationException

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

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

Parameters:

initialOrbit - initial orbit

attitudeLaw - attitude law

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

Throws:

PropagationException - if initial attitude cannot be computed

KeplerianPropagator

public KeplerianPropagator(Orbit initialOrbit,
                           AttitudeLaw attitudeLaw,
                           double mu,
                           double mass)
                    throws PropagationException

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

Parameters:

initialOrbit - initial orbit

attitudeLaw - attitude law

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

mass - spacecraft mass (kg)

Throws:

PropagationException - if initial attitude cannot be computed

Method Detail

getInitialState

public SpacecraftState getInitialState()

Get the propagator initial state.

Specified by:

getInitialState in interface Propagator

Specified by:

getInitialState in class AbstractPropagator

Returns:

initial state

basicPropagate

protected SpacecraftState basicPropagate(AbsoluteDate date)
                                  throws PropagationException

Propagate an orbit without any fancy features.

This method is similar in spirit to the AbstractPropagator.propagate(org.orekit.time.AbsoluteDate) method, except that it does not call any handler during propagation, nor any discrete events. It always stop exactly at the specified date.

Specified by:

basicPropagate in class AbstractPropagator

Parameters:

date - target date for propagation

Returns:

state at specified date

Throws:

PropagationException - if propagation cannot reach specified date

resetInitialState

public void resetInitialState(SpacecraftState state)
                       throws PropagationException

Reset the propagator initial state.

Parameters:

state - new initial state to consider

Throws:

PropagationException - if initial state cannot be reset