org.orekit.propagation.analytical

Class FieldKeplerianPropagator<T extends org.hipparchus.RealFieldElement<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 org.hipparchus.RealFieldElement<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_LAW, DEFAULT_MASS, EPHEMERIS_GENERATION_MODE, MASTER_MODE, SLAVE_MODE

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, double mu) Build a propagator from orbit, attitude provider and central attraction coefficient μ.
FieldKeplerianPropagator(FieldOrbit<T> initialOrbit, AttitudeProvider attitudeProv, double mu, T mass) Build propagator from orbit, attitude provider, central attraction coefficient μ and mass.
FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit, double 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 FieldOrbit<T>	propagateOrbit(FieldAbsoluteDate<T> date) 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, getEventsDetectors, getGeneratedEphemeris, getPvProvider, propagate

Methods inherited from class org.orekit.propagation.FieldAbstractPropagator

addAdditionalStateProvider, getAdditionalStateProviders, getAttitudeProvider, getField, 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

FieldKeplerianPropagator

public FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit)
                         throws OrekitException

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

Throws:

OrekitException - if initial attitude cannot be computed

FieldKeplerianPropagator

public FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit,
                                double mu)
                         throws OrekitException

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)

Throws:

OrekitException - if initial attitude cannot be computed

FieldKeplerianPropagator

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

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

Throws:

OrekitException - if initial attitude cannot be computed

FieldKeplerianPropagator

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

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)

Throws:

OrekitException - if initial attitude cannot be computed

FieldKeplerianPropagator

public FieldKeplerianPropagator(FieldOrbit<T> initialOrbit,
                                AttitudeProvider attitudeProv,
                                double mu,
                                T mass)
                         throws OrekitException

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:

OrekitException - if initial attitude cannot be computed

Method Detail

resetInitialState

public void resetInitialState(FieldSpacecraftState<T> state)
                       throws OrekitException

Reset the propagator initial state.

Specified by:

resetInitialState in interface FieldPropagator<T extends org.hipparchus.RealFieldElement<T>>

Overrides:

resetInitialState in class FieldAbstractPropagator<T extends org.hipparchus.RealFieldElement<T>>

Parameters:

state - new initial state to consider

Throws:

OrekitException - if initial state cannot be reset

resetIntermediateState

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

Reset an intermediate state.

Specified by:

resetIntermediateState in class FieldAbstractAnalyticalPropagator<T extends org.hipparchus.RealFieldElement<T>>

Parameters:

state - new intermediate state to consider

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

Throws:

OrekitException - if initial state cannot be reset

propagateOrbit

protected FieldOrbit<T> propagateOrbit(FieldAbsoluteDate<T> date)
                                throws OrekitException

Extrapolate an orbit up to a specific target date.

Specified by:

propagateOrbit in class FieldAbstractAnalyticalPropagator<T extends org.hipparchus.RealFieldElement<T>>

Parameters:

date - target date for the orbit

Returns:

extrapolated parameters

Throws:

OrekitException - if some parameters are out of bounds

getMass

protected T getMass(FieldAbsoluteDate<T> date)

Get the mass.

Specified by:

getMass in class FieldAbstractAnalyticalPropagator<T extends org.hipparchus.RealFieldElement<T>>

Parameters:

date - target date for the orbit

Returns:

mass mass