Package 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:

Propagator, PVCoordinatesProvider

public class KeplerianPropagator
extends AbstractAnalyticalPropagator

Simple Keplerian orbit propagator.

Author:

Guylaine Prat

See Also:

Orbit

Field Summary

Fields inherited from interface org.orekit.propagation.Propagator

DEFAULT_MASS

Constructor Summary

Constructors

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

Method Summary

Modifier and Type	Method	Description
protected AbstractMatricesHarvester	createHarvester(String stmName, RealMatrix initialStm, DoubleArrayDictionary initialJacobianColumns)	Create the harvester suitable for propagator.
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, getEphemerisGenerator, getEventsDetectors, getJacobiansColumnsNames, getPvProvider, propagate

Methods inherited from class org.orekit.propagation.AbstractPropagator

addAdditionalStateProvider, getAdditionalStateProviders, getAttitudeProvider, getFrame, getHarvester, getInitialState, getManagedAdditionalStates, getMultiplexer, getPVCoordinates, getStartDate, initializeAdditionalStates, initializePropagation, isAdditionalStateManaged, propagate, setAttitudeProvider, setStartDate, setupMatricesComputation, stateChanged, updateAdditionalStates, updateUnmanagedStates

Methods inherited from class java.lang.Object

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

Methods inherited from interface org.orekit.propagation.Propagator

clearStepHandlers, setStepHandler, setStepHandler

Methods inherited from interface org.orekit.utils.PVCoordinatesProvider

getPosition

Constructor Detail

KeplerianPropagator

public KeplerianPropagator(Orbit initialOrbit)

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

See Also:

KeplerianPropagator(Orbit, AttitudeProvider)

KeplerianPropagator

public KeplerianPropagator(Orbit initialOrbit,
                           double mu)

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)

See Also:

KeplerianPropagator(Orbit, AttitudeProvider, double)

KeplerianPropagator

public KeplerianPropagator(Orbit initialOrbit,
                           AttitudeProvider attitudeProv)

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

KeplerianPropagator

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

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)

KeplerianPropagator

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

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)

Method Detail

resetInitialState

public void resetInitialState(SpacecraftState state)

Reset the propagator initial state.

Specified by:

resetInitialState in interface Propagator

Overrides:

resetInitialState in class AbstractPropagator

Parameters:

state - new initial state to consider

resetIntermediateState

protected void resetIntermediateState(SpacecraftState state,
                                      boolean forward)

Reset an intermediate state.

Specified by:

resetIntermediateState in class AbstractAnalyticalPropagator

Parameters:

state - new intermediate state to consider

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

propagateOrbit

protected Orbit propagateOrbit(AbsoluteDate date)

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

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

createHarvester

protected AbstractMatricesHarvester createHarvester(String stmName,
                                                    RealMatrix initialStm,
                                                    DoubleArrayDictionary initialJacobianColumns)

Create the harvester suitable for propagator.

Overrides:

createHarvester in class AbstractPropagator

Parameters:

stmName - State Transition Matrix state name

initialStm - initial State Transition Matrix ∂Y/∂Y₀, if null (which is the most frequent case), assumed to be 6x6 identity

initialJacobianColumns - initial columns of the Jacobians matrix with respect to parameters, if null or if some selected parameters are missing from the dictionary, the corresponding initial column is assumed to be 0

Returns:

harvester to retrieve computed matrices during and after propagation