fr.cnes.sirius.patrius.assembly.models

Class DragLiftModel

java.lang.Object

fr.cnes.sirius.patrius.math.parameter.Parameterizable

fr.cnes.sirius.patrius.assembly.models.DragLiftModel

All Implemented Interfaces:

DragSensitive, IParameterizable, JacobianParametersProvider, Serializable

public final class DragLiftModel
extends Parameterizable
implements DragSensitive

Class that represents an drag and lift aero model, based on the vehicle.

Since:

3.0

Version:

$Id$

Author:

toussaintf

See Also:

Serialized Form

Concurrency :

not thread-safe

Concurrency comment :

The use of a frame (Assembly attribute) linked to the tree of frames in each of the parts makes this class not thread-safe.

Constructor Summary

Constructors

Constructor and Description
DragLiftModel(Assembly inAssembly) Aero drag and lift model (the acceleration is computed from all the sub parts of the vehicle).

Method Summary

Modifier and Type	Method and Description
void	addDDragAccDParam(SpacecraftState s, Parameter param, double density, Vector3D relativeVelocity, double[] dAccdParam) Compute acceleration derivatives with respect to ballistic coefficient.
void	addDDragAccDState(SpacecraftState s, double[][] dAccdPos, double[][] dAccdVel, double density, Vector3D acceleration, Vector3D relativeVelocity, boolean computeGradientPosition, boolean computeGradientVelocity) Compute acceleration derivatives with respect to state parameters (position and velocity).
Vector3D	dragAcceleration(SpacecraftState state, double density, Vector3D relativeVelocity) Method to compute the aero acceleration, based on the assembly.
ArrayList<Parameter>	getJacobianParameters() Get the list of all jacobian parameters supported.

Methods inherited from class fr.cnes.sirius.patrius.math.parameter.Parameterizable

addParameter, getParameters, supportsParameter

Methods inherited from class java.lang.Object

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

Constructor Detail

DragLiftModel

public DragLiftModel(Assembly inAssembly)

Aero drag and lift model (the acceleration is computed from all the sub parts of the vehicle).

Parameters:

inAssembly - The considered vehicle.

Method Detail

getJacobianParameters

public ArrayList<Parameter> getJacobianParameters()

Description copied from interface: JacobianParametersProvider

Get the list of all jacobian parameters supported.

Specified by:

getJacobianParameters in interface JacobianParametersProvider

Returns:

the list of additional parameters for which the jacobians can be computed.

dragAcceleration

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

Method to compute the aero acceleration, based on the assembly.

Specified by:

dragAcceleration in interface DragSensitive

Parameters:

state - the current state of the spacecraft.

density - the atmosphere density.

relativeVelocity - the spacecraft velocity relative to the atmosphere in the spacecraftstate reference frame.

Returns:

the acceleration applied on the assembly in the spacecraftstate frame.

Throws:

PatriusException - if acceleration cannot be computed.

addDDragAccDParam

public void addDDragAccDParam(SpacecraftState s,
                              Parameter param,
                              double density,
                              Vector3D relativeVelocity,
                              double[] dAccdParam)
                       throws PatriusException

Compute acceleration derivatives with respect to ballistic coefficient.

Specified by:

addDDragAccDParam in interface DragSensitive

Parameters:

s - SpacecraftState

param - name of parameter

density - the atmosphere density.

relativeVelocity - the spacecraft velocity relative to the atmosphere.

dAccdParam - acceleration derivatives with respect to ballistic coefficient.

Throws:

PatriusException - if derivatives cannot be computed

addDDragAccDState

public void addDDragAccDState(SpacecraftState s,
                              double[][] dAccdPos,
                              double[][] dAccdVel,
                              double density,
                              Vector3D acceleration,
                              Vector3D relativeVelocity,
                              boolean computeGradientPosition,
                              boolean computeGradientVelocity)
                       throws PatriusException

Compute acceleration derivatives with respect to state parameters (position and velocity).

Specified by:

addDDragAccDState in interface DragSensitive

Parameters:

s - spacecraft state

dAccdPos - acceleration derivatives with respect to position parameters

dAccdVel - acceleration derivatives with respect to velocity parameters

density - the atmospheric density value

acceleration - the spacecraft acceleration in the inertial frame

relativeVelocity - relative velocity of atmosphere with respect to spacecraft, in the same inertial frame as spacecraft orbit (m/s)

computeGradientPosition - true if partial derivatives with respect to position should be computed

computeGradientVelocity - true if partial derivatives with respect to position should be computed

Throws:

PatriusException - if derivatives cannot be computed