fr.cnes.sirius.patrius.assembly.models

Class AeroWrenchModel

java.lang.Object

fr.cnes.sirius.patrius.assembly.models.AeroWrenchModel

All Implemented Interfaces:

DragWrenchSensitive

public class AeroWrenchModel
extends Object
implements DragWrenchSensitive

This class represents a DragWrenchSensitive assembly model.

Since:

2.1

Version:

$Id $

Author:

Rami Houdroge

Concurrency :

not thread-safe

Concurrency comment :

class uses internal mutable attributes and frames

Constructor Summary

Constructors

Constructor and Description
AeroWrenchModel(Assembly inAssembly) Radiative model (the acceleration is computed from all the sub parts of the vehicle).

Method Summary

Modifier and Type	Method and Description
Wrench	dragWrench(SpacecraftState state, double density, Vector3D relativeVelocity) Compute the torque due to radiation pressire.
Wrench	dragWrench(SpacecraftState state, double density, Vector3D relativeVelocity, Vector3D origin, Frame frame) Compute the torque due to radiation pressire.

Methods inherited from class java.lang.Object

clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait

Constructor Detail

AeroWrenchModel

public AeroWrenchModel(Assembly inAssembly)

Radiative model (the acceleration is computed from all the sub parts of the vehicle).

Parameters:

inAssembly - The considered vehicle.

Method Detail

dragWrench

public Wrench dragWrench(SpacecraftState state,
                         double density,
                         Vector3D relativeVelocity)
                  throws PatriusException

Compute the torque due to radiation pressire.

The computation includes all spacecraft specific characteristics like shape, area and coefficients.

Specified by:

dragWrench in interface DragWrenchSensitive

Parameters:

state - current state information: date, kinematics, attitude

density - atmospheric density at spacecraft position

relativeVelocity - relative velocity of atmosphere with respect to spacecraft, in the same inertial frame as spacecraft orbit

Returns:

spacecraft torque expressed at the mass center in the frame of the main part of the assembly (accounts for attitude)

Throws:

PatriusException - if torque cannot be computed

dragWrench

public Wrench dragWrench(SpacecraftState state,
                         double density,
                         Vector3D relativeVelocity,
                         Vector3D origin,
                         Frame frame)
                  throws PatriusException

Compute the torque due to radiation pressire.

The computation includes all spacecraft specific characteristics like shape, area and coefficients.

Specified by:

dragWrench in interface DragWrenchSensitive

Parameters:

state - current state information: date, kinematics, attitude

density - atmospheric density at spacecraft position

relativeVelocity - relative velocity of atmosphere with respect to spacecraft, in the same inertial frame as spacecraft orbit

origin - point in which to express torque

frame - the reference frame

Returns:

spacecraft torque expressed at origin in frame

Throws:

PatriusException - if torque cannot be computed