Class PythonPropulsionModel
- java.lang.Object
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- org.orekit.forces.maneuvers.propulsion.PythonPropulsionModel
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- All Implemented Interfaces:
PropulsionModel
,EventDetectorsProvider
,ParameterDriversProvider
public class PythonPropulsionModel extends Object implements PropulsionModel
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Field Summary
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Fields inherited from interface org.orekit.propagation.events.EventDetectorsProvider
DATATION_ACCURACY
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Constructor Summary
Constructors Constructor Description PythonPropulsionModel()
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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 object<T extends CalculusFieldElement<T>>
FieldVector3D<T>getAcceleration(FieldSpacecraftState<T> s, FieldAttitude<T> maneuverAttitude, T[] parameters)
Get the acceleration of the spacecraft during maneuver and in maneuver frame.Vector3D
getAcceleration(SpacecraftState s, Attitude maneuverAttitude, double[] parameters)
Get the acceleration of the spacecraft during maneuver and in maneuver frame.Control3DVectorCostType
getControl3DVectorCostType()
Get the control vector's cost type.<T extends CalculusFieldElement<T>>
TgetMassDerivatives(FieldSpacecraftState<T> s, T[] parameters)
Get the mass derivative (i.e.double
getMassDerivatives(SpacecraftState s, double[] parameters)
Get the mass derivative (i.e.String
getName()
Get the maneuver name.List<ParameterDriver>
getParametersDrivers()
Get the drivers for parameters.void
init(SpacecraftState initialState, AbsoluteDate target)
Initialization method.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 java.lang.Object
clone, equals, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait
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Methods inherited from interface org.orekit.propagation.events.EventDetectorsProvider
getEventDetectors, getFieldEventDetectors
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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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Methods inherited from interface org.orekit.forces.maneuvers.propulsion.PropulsionModel
getEventDetectors, getFieldEventDetectors, init
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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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init
public void init(SpacecraftState initialState, AbsoluteDate target)
Initialization method. Called in when Maneuver.init(...) is called (from ForceModel.init(...))- Specified by:
init
in interfacePropulsionModel
- Parameters:
initialState
- initial spacecraft state (at the start of propagation).target
- date of propagation. Not equal toinitialState.getDate()
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getAcceleration
public Vector3D getAcceleration(SpacecraftState s, Attitude maneuverAttitude, double[] parameters)
Get the acceleration of the spacecraft during maneuver and in maneuver frame.- Specified by:
getAcceleration
in interfacePropulsionModel
- Parameters:
s
- current spacecraft statemaneuverAttitude
- current attitude in maneuverparameters
- propulsion model parameters- Returns:
- acceleration
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getAcceleration
public <T extends CalculusFieldElement<T>> FieldVector3D<T> getAcceleration(FieldSpacecraftState<T> s, FieldAttitude<T> maneuverAttitude, T[] parameters)
Get the acceleration of the spacecraft during maneuver and in maneuver frame.- Specified by:
getAcceleration
in interfacePropulsionModel
- Type Parameters:
T
- extends CalculusFieldElement<T>- Parameters:
s
- current spacecraft statemaneuverAttitude
- current attitude in maneuverparameters
- propulsion model parameters- Returns:
- acceleration
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getMassDerivatives
public double getMassDerivatives(SpacecraftState s, double[] parameters)
Get the mass derivative (i.e. flow rate in kg/s) during maneuver.- Specified by:
getMassDerivatives
in interfacePropulsionModel
- Parameters:
s
- current spacecraft stateparameters
- propulsion model parameters- Returns:
- mass derivative in kg/s
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getMassDerivatives
public <T extends CalculusFieldElement<T>> T getMassDerivatives(FieldSpacecraftState<T> s, T[] parameters)
Get the mass derivative (i.e. flow rate in kg/s) during maneuver.- Specified by:
getMassDerivatives
in interfacePropulsionModel
- Type Parameters:
T
- extends CalculusFieldElement<T>- Parameters:
s
- current spacecraft stateparameters
- propulsion model parameters- Returns:
- mass derivative in kg/s
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getParametersDrivers
public List<ParameterDriver> getParametersDrivers()
Get the drivers for parameters.- Specified by:
getParametersDrivers
in interfaceParameterDriversProvider
- Returns:
- drivers for parameters
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getName
public String getName()
Get the maneuver name.- Specified by:
getName
in interfacePropulsionModel
- Returns:
- the maneuver name
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getControl3DVectorCostType
public Control3DVectorCostType getControl3DVectorCostType()
Get the control vector's cost type.- Specified by:
getControl3DVectorCostType
in interfacePropulsionModel
- Returns:
- control cost type
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