Class PythonAbstractIntegratedPropagator
- java.lang.Object
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- org.orekit.propagation.AbstractPropagator
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- org.orekit.propagation.integration.AbstractIntegratedPropagator
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- org.orekit.propagation.integration.PythonAbstractIntegratedPropagator
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- All Implemented Interfaces:
Propagator
,PVCoordinatesProvider
public class PythonAbstractIntegratedPropagator extends AbstractIntegratedPropagator
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Nested Class Summary
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Nested classes/interfaces inherited from class org.orekit.propagation.integration.AbstractIntegratedPropagator
AbstractIntegratedPropagator.MainStateEquations
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Field Summary
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Fields inherited from interface org.orekit.propagation.Propagator
DEFAULT_MASS
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Constructor Summary
Constructors Constructor Description PythonAbstractIntegratedPropagator(ODEIntegrator integrator, PropagationType propagationType)
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Method Summary
All Methods Instance Methods Concrete Methods Modifier and Type Method Description StateMapper
createMapper(AbsoluteDate referenceDate, double mu, OrbitType orbitType, PositionAngleType positionAngleType, AttitudeProvider attitudeProvider, Frame frame)
Create a mapper between raw double components and spacecraft state.void
finalize()
Part of JCC Python interface to objectAbstractIntegratedPropagator.MainStateEquations
getMainStateEquations(ODEIntegrator integ)
Get the differential equations to integrate (for main state only).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 object-
Methods inherited from class org.orekit.propagation.integration.AbstractIntegratedPropagator
addAdditionalDerivativesProvider, addEventDetector, afterIntegration, beforeIntegration, clearEventsDetectors, getAdditionalDerivativesProviders, getBasicDimension, getCalls, getEphemerisGenerator, getEventsDetectors, getInitialIntegrationState, getIntegrator, getIntegratorName, getManagedAdditionalStates, getMu, getOrbitType, getPositionAngleType, getPropagationType, getResetAtEnd, initMapper, isAdditionalStateManaged, propagate, propagate, setAttitudeProvider, setMu, setOrbitType, setPositionAngleType, setResetAtEnd, setUpEventDetector, setUpStmAndJacobianGenerators, setUpUserEventDetectors
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Methods inherited from class org.orekit.propagation.AbstractPropagator
addAdditionalStateProvider, createHarvester, getAdditionalStateProviders, getAttitudeProvider, getFrame, getHarvester, getInitialState, getMultiplexer, getPVCoordinates, getStartDate, initializeAdditionalStates, initializePropagation, resetInitialState, setStartDate, setupMatricesComputation, 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.Propagator
clearStepHandlers, setStepHandler, setStepHandler
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Methods inherited from interface org.orekit.utils.PVCoordinatesProvider
getPosition
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Constructor Detail
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PythonAbstractIntegratedPropagator
public PythonAbstractIntegratedPropagator(ODEIntegrator integrator, PropagationType propagationType)
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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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createMapper
public StateMapper createMapper(AbsoluteDate referenceDate, double mu, OrbitType orbitType, PositionAngleType positionAngleType, AttitudeProvider attitudeProvider, Frame frame)
Create a mapper between raw double components and spacecraft state. /** Simple constructor.The position parameter type is meaningful only if
propagation orbit type
support it. As an example, it is not meaningful for propagation inCartesian
parameters.- Specified by:
createMapper
in classAbstractIntegratedPropagator
- Parameters:
referenceDate
- reference datemu
- central attraction coefficient (m³/s²)orbitType
- orbit type to use for mappingpositionAngleType
- angle type to use for propagationattitudeProvider
- attitude providerframe
- inertial frame- Returns:
- new mapper
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getMainStateEquations
public AbstractIntegratedPropagator.MainStateEquations getMainStateEquations(ODEIntegrator integ)
Get the differential equations to integrate (for main state only).- Specified by:
getMainStateEquations
in classAbstractIntegratedPropagator
- Parameters:
integ
- numerical integrator to use for propagation.- Returns:
- differential equations for main state
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