org.orekit.propagation.analytical

Class FieldKeplerianPropagator<T extends CalculusFieldElement<T>>

java.lang.Object

org.orekit.propagation.FieldAbstractPropagator<T>

org.orekit.propagation.analytical.FieldAbstractAnalyticalPropagator<T>

org.orekit.propagation.analytical.FieldKeplerianPropagator<T>

All Implemented Interfaces:

FieldPropagator<T>, FieldPVCoordinatesProvider<T>

public class FieldKeplerianPropagator<T extends CalculusFieldElement<T>>
extends FieldAbstractAnalyticalPropagator<T>

Simple Keplerian orbit propagator.

Author:

Guylaine Prat

See Also:

FieldOrbit

Field Summary

Fields inherited from interface org.orekit.propagation.FieldPropagator

DEFAULT_MASS

Constructor Summary

Constructors

Constructor and Description
FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit) Build a propagator from orbit only.
FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit, AttitudeProvider attitudeProv) Build a propagator from orbit and attitude provider.
FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit, AttitudeProvider attitudeProv, T mu) Build a propagator from orbit, attitude provider and central attraction coefficient μ.
FieldKeplerianPropagator(FieldOrbit<T> initialOrbit, AttitudeProvider attitudeProv, T mu, T mass) Build propagator from orbit, attitude provider, central attraction coefficient μ and mass.
FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit, T mu) Build a propagator from orbit and central attraction coefficient μ.

Method Summary

Modifier and Type	Method and Description
protected T	getMass(FieldAbsoluteDate<T> date) Get the mass.
protected List<ParameterDriver>	getParametersDrivers() Get the parameters driver for propagation model.
protected FieldOrbit<T>	propagateOrbit(FieldAbsoluteDate<T> date, T[] parameters) Extrapolate an orbit up to a specific target date.
void	resetInitialState(FieldSpacecraftState<T> state) Reset the propagator initial state.
protected void	resetIntermediateState(FieldSpacecraftState<T> state, boolean forward) Reset an intermediate state.

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

acceptStep, addEventDetector, basicPropagate, clearEventsDetectors, getEphemerisGenerator, getEventsDetectors, getParameters, getPvProvider, propagate

Methods inherited from class org.orekit.propagation.FieldAbstractPropagator

addAdditionalStateProvider, getAdditionalStateProviders, getAttitudeProvider, getField, getFrame, getInitialState, getManagedAdditionalStates, getMultiplexer, getPVCoordinates, getStartDate, initializePropagation, isAdditionalStateManaged, propagate, setAttitudeProvider, setStartDate, 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.FieldPropagator

clearStepHandlers, setStepHandler, setStepHandler

Constructor Detail

FieldKeplerianPropagator

public FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit)

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:

initialFieldOrbit - initial orbit

See Also:

FieldKeplerianPropagator(FieldOrbit, AttitudeProvider)

FieldKeplerianPropagator

public FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit,
                                T mu)

Build a propagator from orbit and central attraction coefficient μ.

Mass and attitude provider are set to unspecified non-null arbitrary values.

Parameters:

initialFieldOrbit - initial orbit

mu - central attraction coefficient (m³/s²)

See Also:

FieldKeplerianPropagator(FieldOrbit, AttitudeProvider, CalculusFieldElement)

FieldKeplerianPropagator

public FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit,
                                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:

initialFieldOrbit - initial orbit

attitudeProv - attitude provider

FieldKeplerianPropagator

public FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit,
                                AttitudeProvider attitudeProv,
                                T mu)

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

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

Parameters:

initialFieldOrbit - initial orbit

attitudeProv - attitude provider

mu - central attraction coefficient (m³/s²)

FieldKeplerianPropagator

public FieldKeplerianPropagator(FieldOrbit<T> initialOrbit,
                                AttitudeProvider attitudeProv,
                                T mu,
                                T 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(FieldSpacecraftState<T> state)

Reset the propagator initial state.

Specified by:

resetInitialState in interface FieldPropagator<T extends CalculusFieldElement<T>>

Overrides:

resetInitialState in class FieldAbstractPropagator<T extends CalculusFieldElement<T>>

Parameters:

state - new initial state to consider

resetIntermediateState

protected void resetIntermediateState(FieldSpacecraftState<T> state,
                                      boolean forward)

Reset an intermediate state.

Specified by:

resetIntermediateState in class FieldAbstractAnalyticalPropagator<T extends CalculusFieldElement<T>>

Parameters:

state - new intermediate state to consider

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

propagateOrbit

protected FieldOrbit<T> propagateOrbit(FieldAbsoluteDate<T> date,
                                       T[] parameters)

Extrapolate an orbit up to a specific target date.

Specified by:

propagateOrbit in class FieldAbstractAnalyticalPropagator<T extends CalculusFieldElement<T>>

Parameters:

date - target date for the orbit

parameters - model parameters

Returns:

extrapolated parameters

getMass

protected T getMass(FieldAbsoluteDate<T> date)

Get the mass.

Specified by:

getMass in class FieldAbstractAnalyticalPropagator<T extends CalculusFieldElement<T>>

Parameters:

date - target date for the orbit

Returns:

mass mass

getParametersDrivers

protected List<ParameterDriver> getParametersDrivers()

Get the parameters driver for propagation model.

Specified by:

getParametersDrivers in class FieldAbstractAnalyticalPropagator<T extends CalculusFieldElement<T>>

Returns:

drivers for propagation model