Package org.orekit.propagation.integration

Class FieldIntegratedEphemeris<T extends CalculusFieldElement<T>>

java.lang.Object

org.orekit.propagation.FieldAbstractPropagator<T>

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

org.orekit.propagation.integration.FieldIntegratedEphemeris<T>

Type Parameters:

T - type of the field elements

All Implemented Interfaces:

FieldBoundedPropagator<T>, FieldPropagator<T>, FieldPVCoordinatesProvider<T>, ParameterDriversProvider

public class FieldIntegratedEphemeris<T extends CalculusFieldElement<T>>
extends FieldAbstractAnalyticalPropagator<T>
implements FieldBoundedPropagator<T>

This class stores sequentially generated orbital parameters for later retrieval.

Instances of this class are built automatically when the getEphemerisGenerator method has been called. They are created when propagation is over. Random access to any intermediate state of the orbit throughout the propagation range is possible afterwards through this object.

A typical use case is for numerically integrated orbits, which can be used by algorithms that need to wander around according to their own algorithm without cumbersome tight links with the integrator.

As this class implements the Propagator interface, it can itself be used in batch mode to build another instance of the same type. This is however not recommended since it would be a waste of resources.

Note that this class stores all intermediate states along with interpolation models, so it may be memory intensive.

Author:

Mathieu Roméro, Luc Maisonobe, Véronique Pommier-Maurussane

See Also:

NumericalPropagator

Field Summary

Fields inherited from interface org.orekit.propagation.FieldPropagator

DEFAULT_MASS

Constructor Summary

Constructors

Constructor	Description
FieldIntegratedEphemeris(FieldAbsoluteDate<T> startDate, FieldAbsoluteDate<T> minDate, FieldAbsoluteDate<T> maxDate, FieldStateMapper<T> mapper, AttitudeProvider attitudeProvider, PropagationType type, FieldDenseOutputModel<T> model, FieldArrayDictionary<T> unmanaged, List<FieldAdditionalStateProvider<T>> providers, String[] equations, int[] dimensions)	Creates a new instance of IntegratedEphemeris.

Method Summary

Modifier and Type	Method	Description
protected FieldSpacecraftState<T>	basicPropagate(FieldAbsoluteDate<T> date)	Propagate an orbit without any fancy features.
Frame	getFrame()	Get the frame in which the orbit is propagated.
FieldSpacecraftState<T>	getInitialState()	Get the propagator initial state.
protected T	getMass(FieldAbsoluteDate<T> date)	Get the mass.
FieldAbsoluteDate<T>	getMaxDate()	Get the last date of the range.
FieldAbsoluteDate<T>	getMinDate()	Get the first date of the range.
List<ParameterDriver>	getParametersDrivers()	Get the drivers for parameters.
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.
protected FieldSpacecraftState<T>	updateAdditionalStates(FieldSpacecraftState<T> original)	Update state by adding all additional states.

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

acceptStep, addEventDetector, clearEventsDetectors, getEphemerisGenerator, getEventDetectors, getPvProvider, propagate

Methods inherited from class org.orekit.propagation.FieldAbstractPropagator

addAdditionalStateProvider, getAdditionalStateProviders, getAttitudeProvider, getField, getManagedAdditionalStates, getMultiplexer, getStartDate, initializeAdditionalStates, initializePropagation, isAdditionalStateManaged, propagate, setAttitudeProvider, setStartDate, stateChanged, 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

addAdditionalStateProvider, addEventDetector, clearEventsDetectors, clearStepHandlers, getAdditionalStateProviders, getAttitudeProvider, getEphemerisGenerator, getEventDetectors, getManagedAdditionalStates, getMultiplexer, getPosition, getPVCoordinates, isAdditionalStateManaged, propagate, propagate, setAttitudeProvider, setStepHandler, setStepHandler

Methods inherited from interface org.orekit.utils.ParameterDriversProvider

getNbParametersDriversValue, getParameterDriver, getParameters, getParameters, getParameters, getParameters, getParametersAllValues, getParametersAllValues, isSupported

Constructor Detail

FieldIntegratedEphemeris

public FieldIntegratedEphemeris(FieldAbsoluteDate<T> startDate,
                                FieldAbsoluteDate<T> minDate,
                                FieldAbsoluteDate<T> maxDate,
                                FieldStateMapper<T> mapper,
                                AttitudeProvider attitudeProvider,
                                PropagationType type,
                                FieldDenseOutputModel<T> model,
                                FieldArrayDictionary<T> unmanaged,
                                List<FieldAdditionalStateProvider<T>> providers,
                                String[] equations,
                                int[] dimensions)

Creates a new instance of IntegratedEphemeris.

Parameters:

startDate - Start date of the integration (can be minDate or maxDate)

minDate - first date of the range

maxDate - last date of the range

mapper - mapper between raw double components and spacecraft state

attitudeProvider - attitude provider

type - type of orbit to output (mean or osculating)

model - underlying raw mathematical model

unmanaged - unmanaged additional states that must be simply copied

providers - generators for pre-integrated states

equations - names of additional equations

dimensions - dimensions of additional equations

Since:

13.0

Method Detail

basicPropagate

protected FieldSpacecraftState<T> basicPropagate(FieldAbsoluteDate<T> date)

Propagate an orbit without any fancy features.

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

Overrides:

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

Parameters:

date - target date for propagation

Returns:

state at specified date

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

getMinDate

public FieldAbsoluteDate<T> getMinDate()

Get the first date of the range.

Specified by:

getMinDate in interface FieldBoundedPropagator<T extends CalculusFieldElement<T>>

Returns:

the first date of the range

getMaxDate

public FieldAbsoluteDate<T> getMaxDate()

Get the last date of the range.

Specified by:

getMaxDate in interface FieldBoundedPropagator<T extends CalculusFieldElement<T>>

Returns:

the last date of the range

getFrame

public Frame getFrame()

Description copied from class: FieldAbstractPropagator

Get the frame in which the orbit is propagated.

The propagation frame is the definition frame of the initial state, so this method should be called after this state has been set, otherwise it may return null.

Specified by:

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

Overrides:

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

Returns:

frame in which the orbit is propagated

See Also:

FieldPropagator.resetInitialState(FieldSpacecraftState)

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

getInitialState

public FieldSpacecraftState<T> getInitialState()

Get the propagator initial state.

Specified by:

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

Overrides:

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

Returns:

initial state

updateAdditionalStates

protected FieldSpacecraftState<T> updateAdditionalStates(FieldSpacecraftState<T> original)

Update state by adding all additional states.

Overrides:

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

Parameters:

original - original state

Returns:

updated state, with all additional states included

See Also:

FieldAbstractPropagator.addAdditionalStateProvider(FieldAdditionalStateProvider)

getParametersDrivers

public List<ParameterDriver> getParametersDrivers()

Get the drivers for parameters.

Specified by:

getParametersDrivers in interface ParameterDriversProvider

Returns:

drivers for parameters