fr.cnes.sirius.patrius.assembly.models
Class AeroModel

java.lang.Object
  org.orekit.parameter.Parameterizable
      fr.cnes.sirius.patrius.assembly.models.AeroModel

All Implemented Interfaces:

Serializable, DragSensitive, IParameterizable, JacobianParametersProvider

public final class AeroModel
extends Parameterizable
implements DragSensitive

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

Since:

1.2

Version:

$Id: AeroModel.java 16763 2016-10-10 09:31:17Z bignon $

Author:

cardosop

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

AeroModel(Assembly inAssembly)
Aero model (the acceleration is computed from all the sub parts of the vehicle).

Method Summary

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.
protected static Vector3D	forceOnFacet(SpacecraftState state, IPart part, Assembly assembly, double density, Vector3D relativeVelocity) Method to compute the force for a plane model.
protected static Vector3D	forceOnSphere(SpacecraftState state, IPart part, double density, Vector3D relativeVelocity) Method to compute the force for a sphere model.
ArrayList<Parameter>	getJacobianParameters() Get the list of all jacobian parameters supported.

Methods inherited from class org.orekit.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

AeroModel

public AeroModel(Assembly inAssembly)

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

Parameters:

inAssembly - The considered vehicle.

Method Detail

dragAcceleration

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

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.

Returns:

the acceleration applied on the assembly.

Throws:

OrekitException - when an error occurs.

forceOnFacet

protected static Vector3D forceOnFacet(SpacecraftState state,
                                       IPart part,
                                       Assembly assembly,
                                       double density,
                                       Vector3D relativeVelocity)
                                throws OrekitException

Method to compute the force for a plane model.

Parameters:

state - the current state of the spacecraft.

part - the current part of the assembly.

assembly - the assembly.

density - the atmosphere density.

relativeVelocity - the spacecraft velocity relative to the atmosphere.

Returns:

the force applied on the facet.

Throws:

OrekitException - orekit frame exception

forceOnSphere

protected static Vector3D forceOnSphere(SpacecraftState state,
                                        IPart part,
                                        double density,
                                        Vector3D relativeVelocity)
                                 throws OrekitException

Method to compute the force for a sphere model.

Parameters:

state - the current state of the spacecraft.

part - the current part of the assembly.

density - the atmosphere density.

relativeVelocity - the spacecraft velocity relative to the atmosphere.

Returns:

the force applied on the facet.

Throws:

OrekitException - if no attitude is defined

addDDragAccDParam

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

Compute acceleration derivatives with respect to ballistic coefficient.

Specified by:

addDDragAccDParam in interface DragSensitive

Parameters:

s - the 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:

OrekitException - 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 OrekitException

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 - the spacecraft velocity relative to the atmosphere

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:

OrekitException - if derivatives cannot be computed

getJacobianParameters

public ArrayList<Parameter> getJacobianParameters()

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.