Class PythonAbstractConstantThrustPropulsionModel
- java.lang.Object
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- org.orekit.forces.maneuvers.propulsion.AbstractConstantThrustPropulsionModel
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- org.orekit.forces.maneuvers.propulsion.PythonAbstractConstantThrustPropulsionModel
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- All Implemented Interfaces:
PropulsionModel
,ThrustPropulsionModel
public class PythonAbstractConstantThrustPropulsionModel extends AbstractConstantThrustPropulsionModel implements ThrustPropulsionModel
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Constructor Summary
Constructors Constructor Description PythonAbstractConstantThrustPropulsionModel(double thrust, double isp, Vector3D direction, String name)
Generic constructor.
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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 objectdouble
getFlowRate()
Get the flow rate (kg/s).double
getFlowRate(double[] parameters)
Get the flow rate (kg/s).<T extends CalculusFieldElement<T>>
TgetFlowRate(T[] parameters)
Get the flow rate (kg/s).<T extends CalculusFieldElement<T>>
TgetFlowRate_T(T[] parameters)
Get the flow rate (kg/s).double
getInitialFlowrate()
Vector3D
getInitialThrustVector()
Vector3D
getThrustVector()
Get the thrust vector in spacecraft frame (N).Vector3D
getThrustVector(double[] parameters)
Get the thrust vector in spacecraft frame (N).<T extends CalculusFieldElement<T>>
FieldVector3D<T>getThrustVector(T[] parameters)
Get the thrust vector in spacecraft frame (N).<T extends CalculusFieldElement<T>>
FieldVector3D<T>getThrustVector_T(T[] parameters)
Get the thrust vector in spacecraft frame (N).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 org.orekit.forces.maneuvers.propulsion.AbstractConstantThrustPropulsionModel
getDirection, getFlowRate, getFlowRate, getFlowRate, getIsp, getName, getThrust, getThrustVector, getThrustVector, getThrustVector
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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.forces.maneuvers.propulsion.PropulsionModel
getName, getParametersDrivers, init
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Methods inherited from interface org.orekit.forces.maneuvers.propulsion.ThrustPropulsionModel
getAcceleration, getAcceleration, getDirection, getFlowRate, getFlowRate, getFlowRate, getIsp, getMassDerivatives, getMassDerivatives, getThrust, getThrustVector, getThrustVector, getThrustVector
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Constructor Detail
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PythonAbstractConstantThrustPropulsionModel
public PythonAbstractConstantThrustPropulsionModel(double thrust, double isp, Vector3D direction, String name)
Generic constructor.- Parameters:
thrust
- initial thrust value (N)isp
- initial isp value (s)direction
- initial thrust direction in S/C framename
- name of the maneuver
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Method Detail
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getInitialThrustVector
public Vector3D getInitialThrustVector()
- Overrides:
getInitialThrustVector
in classAbstractConstantThrustPropulsionModel
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getInitialFlowrate
public double getInitialFlowrate()
- Overrides:
getInitialFlowrate
in classAbstractConstantThrustPropulsionModel
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getThrustVector
public Vector3D getThrustVector()
Get the thrust vector in spacecraft frame (N). Here it does not depend on current S/C state.- Specified by:
getThrustVector
in classAbstractConstantThrustPropulsionModel
- Returns:
- thrust vector in spacecraft frame (N)
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getFlowRate
public double getFlowRate()
Get the flow rate (kg/s). Here it does not depend on current S/C.- Specified by:
getFlowRate
in classAbstractConstantThrustPropulsionModel
- Returns:
- flow rate (kg/s)
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getThrustVector
public Vector3D getThrustVector(double[] parameters)
Get the thrust vector in spacecraft frame (N). Here it does not depend on current S/C state.- Specified by:
getThrustVector
in classAbstractConstantThrustPropulsionModel
- Parameters:
parameters
- propulsion model parameters- Returns:
- thrust vector in spacecraft frame (N)
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getFlowRate
public double getFlowRate(double[] parameters)
Get the flow rate (kg/s). Here it does not depend on current S/C state.- Specified by:
getFlowRate
in classAbstractConstantThrustPropulsionModel
- Parameters:
parameters
- propulsion model parameters- Returns:
- flow rate (kg/s)
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getThrustVector
public <T extends CalculusFieldElement<T>> FieldVector3D<T> getThrustVector(T[] parameters)
Get the thrust vector in spacecraft frame (N). Here it does not depend on current S/C state.- Specified by:
getThrustVector
in classAbstractConstantThrustPropulsionModel
- Type Parameters:
T
- extends CalculusFieldElement<T>- Parameters:
parameters
- propulsion model parameters- Returns:
- thrust vector in spacecraft frame (N)
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getThrustVector_T
public <T extends CalculusFieldElement<T>> FieldVector3D<T> getThrustVector_T(T[] parameters)
Get the thrust vector in spacecraft frame (N). Here it does not depend on current S/C state.- Parameters:
parameters
- propulsion model parameters- Returns:
- thrust vector in spacecraft frame (N)
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getFlowRate
public <T extends CalculusFieldElement<T>> T getFlowRate(T[] parameters)
Get the flow rate (kg/s). Here it does not depend on current S/C state.- Specified by:
getFlowRate
in classAbstractConstantThrustPropulsionModel
- Type Parameters:
T
- extends CalculusFieldElement<T>- Parameters:
parameters
- propulsion model parameters- Returns:
- flow rate (kg/s)
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getFlowRate_T
public <T extends CalculusFieldElement<T>> T getFlowRate_T(T[] parameters)
Get the flow rate (kg/s). Here it does not depend on current S/C state.- Parameters:
parameters
- propulsion model parameters- Returns:
- flow rate (kg/s)
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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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