Package org.orekit.forces.drag
Class PythonDragSensitive
- java.lang.Object
-
- org.orekit.forces.drag.PythonDragSensitive
-
- All Implemented Interfaces:
DragSensitive
public class PythonDragSensitive extends Object implements DragSensitive
-
-
Field Summary
-
Fields inherited from interface org.orekit.forces.drag.DragSensitive
DRAG_COEFFICIENT, LIFT_RATIO
-
-
Constructor Summary
Constructors Constructor Description PythonDragSensitive()
-
Method Summary
All Methods Instance Methods Concrete Methods Modifier and Type Method Description Vector3D
dragAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, double density, Vector3D relativeVelocity, double[] parameters)
Compute the acceleration due to drag.<T extends CalculusFieldElement<T>>
FieldVector3D<T>dragAcceleration(FieldAbsoluteDate<T> date, Frame frame, FieldVector3D<T> position, FieldRotation<T> rotation, T mass, T density, FieldVector3D<T> relativeVelocity, T[] parameters)
Compute the acceleration due to drag.<T extends CalculusFieldElement<T>>
FieldVector3D<T>dragAcceleration_FFFFTTFT(FieldAbsoluteDate<T> date, Frame frame, FieldVector3D<T> position, FieldRotation<T> rotation, T mass, T density, FieldVector3D<T> relativeVelocity, T[] parameters)
void
finalize()
Part of JCC Python interface to objectList<ParameterDriver>
getDragParametersDrivers()
Get the drivers for supported parameters.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
-
-
-
Method Detail
-
pythonExtension
public void pythonExtension(long pythonObject)
Part of JCC Python interface to object
-
pythonExtension
public long pythonExtension()
Part of JCC Python interface to object
-
finalize
public void finalize() throws Throwable
Part of JCC Python interface to object
-
pythonDecRef
public void pythonDecRef()
Part of JCC Python interface to object
-
getDragParametersDrivers
public List<ParameterDriver> getDragParametersDrivers()
Get the drivers for supported parameters. Extension point for Python.- Specified by:
getDragParametersDrivers
in interfaceDragSensitive
- Returns:
- parameters drivers
- Since:
- 8.0
-
dragAcceleration
public Vector3D dragAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, double density, Vector3D relativeVelocity, double[] parameters)
Compute the acceleration due to drag. Extension point for Python.The computation includes all spacecraft specific characteristics like shape, area and coefficients.
- Specified by:
dragAcceleration
in interfaceDragSensitive
- Parameters:
date
- current dateframe
- inertial reference frame for state (both orbit and attitude)position
- position of spacecraft in reference framerotation
- orientation (attitude) of the spacecraft with respect to reference framemass
- current massdensity
- atmospheric density at spacecraft positionrelativeVelocity
- relative velocity of atmosphere with respect to spacecraft, in the same inertial frame as spacecraft orbit (m/s)parameters
- values of the force model parameters- Returns:
- spacecraft acceleration in the same inertial frame as spacecraft orbit (m/s²)
-
dragAcceleration
public <T extends CalculusFieldElement<T>> FieldVector3D<T> dragAcceleration(FieldAbsoluteDate<T> date, Frame frame, FieldVector3D<T> position, FieldRotation<T> rotation, T mass, T density, FieldVector3D<T> relativeVelocity, T[] parameters)
Compute the acceleration due to drag. Connects to dragAcceleration_FFFFTTFT for Python extension.The computation includes all spacecraft specific characteristics like shape, area and coefficients.
- Specified by:
dragAcceleration
in interfaceDragSensitive
- Type Parameters:
T
- instance of a CalculusFieldElement- Parameters:
date
- current dateframe
- inertial reference frame for state (both orbit and attitude)position
- position of spacecraft in reference framerotation
- orientation (attitude) of the spacecraft with respect to reference framemass
- current massdensity
- atmospheric density at spacecraft positionrelativeVelocity
- relative velocity of atmosphere with respect to spacecraft, in the same inertial frame as spacecraft orbit (m/s)parameters
- values of the force model parameters- Returns:
- spacecraft acceleration in the same inertial frame as spacecraft orbit (m/s²)
- Since:
- 9.0
-
dragAcceleration_FFFFTTFT
public <T extends CalculusFieldElement<T>> FieldVector3D<T> dragAcceleration_FFFFTTFT(FieldAbsoluteDate<T> date, Frame frame, FieldVector3D<T> position, FieldRotation<T> rotation, T mass, T density, FieldVector3D<T> relativeVelocity, T[] parameters)
-
-