Class PythonFieldAbstractAnalyticalPropagator<T extends CalculusFieldElement<T>>
- java.lang.Object
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- org.orekit.propagation.FieldAbstractPropagator<T>
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- org.orekit.propagation.analytical.FieldAbstractAnalyticalPropagator<T>
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- org.orekit.propagation.analytical.PythonFieldAbstractAnalyticalPropagator<T>
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- All Implemented Interfaces:
FieldPropagator<T>
,FieldPVCoordinatesProvider<T>
,ParameterDriversProvider
public class PythonFieldAbstractAnalyticalPropagator<T extends CalculusFieldElement<T>> extends FieldAbstractAnalyticalPropagator<T>
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Field Summary
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Fields inherited from interface org.orekit.propagation.FieldPropagator
DEFAULT_MASS
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Constructor Summary
Constructors Constructor Description PythonFieldAbstractAnalyticalPropagator(Field<T> field, AttitudeProvider attitudeProvider)
Build a new instance.
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Method Summary
All Methods Instance Methods Concrete Methods Modifier and Type Method Description void
finalize()
Part of JCC Python interface to objectT
getMass(FieldAbsoluteDate<T> date)
Get the mass.List<ParameterDriver>
getParametersDrivers()
Get the parameters driver for propagation model.FieldOrbit<T>
propagateOrbit(FieldAbsoluteDate<T> date, T[] parameters)
Extrapolate an orbit up to a specific target date.void
pythonDecRef()
Part of JCC Python interface to objectlong
pythonExtension()
Part of JCC Python interface to objectvoid
pythonExtension(long pythonObject)
Part of JCC Python interface to objectvoid
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, getPvProvider, propagate
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Methods inherited from class org.orekit.propagation.FieldAbstractPropagator
addAdditionalStateProvider, getAdditionalStateProviders, getAttitudeProvider, getField, getFrame, getInitialState, getManagedAdditionalStates, getMultiplexer, getPVCoordinates, getStartDate, initializeAdditionalStates, initializePropagation, isAdditionalStateManaged, propagate, resetInitialState, setAttitudeProvider, setStartDate, stateChanged, updateAdditionalStates, updateUnmanagedStates
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Methods inherited from class java.lang.Object
clone, equals, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait
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Methods inherited from interface org.orekit.propagation.FieldPropagator
clearStepHandlers, setStepHandler, setStepHandler
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Methods inherited from interface org.orekit.utils.FieldPVCoordinatesProvider
getPosition
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Methods inherited from interface org.orekit.utils.ParameterDriversProvider
getNbParametersDriversValue, getParameterDriver, getParameters, getParameters, getParameters, getParameters, getParametersAllValues, getParametersAllValues, isSupported
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Constructor Detail
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PythonFieldAbstractAnalyticalPropagator
public PythonFieldAbstractAnalyticalPropagator(Field<T> field, AttitudeProvider attitudeProvider)
Build a new instance.- Parameters:
field
- field used as defaultattitudeProvider
- provider for attitude computation
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Method Detail
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pythonExtension
public void pythonExtension(long pythonObject)
Part of JCC Python interface to object
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pythonExtension
public long pythonExtension()
Part of JCC Python interface to object
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finalize
public void finalize() throws Throwable
Part of JCC Python interface to object
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pythonDecRef
public void pythonDecRef()
Part of JCC Python interface to object
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getMass
public T getMass(FieldAbsoluteDate<T> date)
Get the mass.- Specified by:
getMass
in classFieldAbstractAnalyticalPropagator<T extends CalculusFieldElement<T>>
- Parameters:
date
- target date for the orbit- Returns:
- mass mass
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resetIntermediateState
public void resetIntermediateState(FieldSpacecraftState<T> state, boolean forward)
Reset an intermediate state.- Specified by:
resetIntermediateState
in classFieldAbstractAnalyticalPropagator<T extends CalculusFieldElement<T>>
- Parameters:
state
- new intermediate state to considerforward
- if true, the intermediate state is valid for
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propagateOrbit
public FieldOrbit<T> propagateOrbit(FieldAbsoluteDate<T> date, T[] parameters)
Extrapolate an orbit up to a specific target date.- Specified by:
propagateOrbit
in classFieldAbstractAnalyticalPropagator<T extends CalculusFieldElement<T>>
- Parameters:
date
- target date for the orbitparameters
- model parameters- Returns:
- extrapolated parameters
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getParametersDrivers
public List<ParameterDriver> getParametersDrivers()
Get the parameters driver for propagation model.- Returns:
- drivers for propagation model
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