fr.cnes.sirius.patrius.assembly.models

Class AeroModel

java.lang.Object

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

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

All Implemented Interfaces:

DragSensitive, IParameterizable, JacobianParametersProvider, Serializable

public final class AeroModel
extends Parameterizable
implements DragSensitive

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

Since:

1.2

Version:

$Id$

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

Constructors

Constructor and Description
AeroModel(Assembly inAssembly) Aero model (the acceleration is computed from all the sub parts of the vehicle) default constructor.
AeroModel(Assembly inAssembly, Atmosphere inAtmosphere, OneAxisEllipsoid inGeodPos) Aero model (the acceleration is computed from all the sub parts of the vehicle) with default step for finite differences computation.
AeroModel(Assembly inAssembly, Atmosphere inAtmosphere, OneAxisEllipsoid earthShapeIn, double altStep) Aero model (the acceleration is computed from all the sub parts of the vehicle) with an Atmosphere model and a OneAxisEllipsoid for acceleration partial derivatives computation with respect to state by finite differences(including density partial derivatives).

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.
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, Frame mainPartFrame) Method to compute the force for the part model (cylinder, parallelepiped, sphere).
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

AeroModel

public AeroModel(Assembly inAssembly,
                 Atmosphere inAtmosphere,
                 OneAxisEllipsoid earthShapeIn,
                 double altStep)

Aero model (the acceleration is computed from all the sub parts of the vehicle) with an Atmosphere model and a OneAxisEllipsoid for acceleration partial derivatives computation with respect to state by finite differences(including density partial derivatives).

Parameters:

inAssembly - The considered vehicle

inAtmosphere - the atmospheric model

earthShapeIn - the spacecraft geodetic position model

altStep - atmospheric density derivatives altitude finite differences computation

AeroModel

public AeroModel(Assembly inAssembly,
                 Atmosphere inAtmosphere,
                 OneAxisEllipsoid inGeodPos)

Aero model (the acceleration is computed from all the sub parts of the vehicle) with default step for finite differences computation.

Parameters:

inAssembly - The considered vehicle

inAtmosphere - the atmospheric model

inGeodPos - the spacecraft geodetic position model

AeroModel

public AeroModel(Assembly inAssembly)

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

Warning: This constructor should not be used if partial derivatives have to be computed.

Parameters:

inAssembly - The considered vehicle

Method Detail

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.

Returns:

the acceleration applied on the assembly.

Throws:

PatriusException - when an error occurs.

forceOnFacet

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

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:

PatriusException - orekit frame exception

forceOnSphere

protected static Vector3D forceOnSphere(SpacecraftState state,
                                        IPart part,
                                        double density,
                                        Vector3D relativeVelocity,
                                        Frame mainPartFrame)
                                 throws PatriusException

Method to compute the force for the part model (cylinder, parallelepiped, sphere).

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.

mainPartFrame - mainPartFrame

Returns:

the force applied on the facet.

Throws:

PatriusException - if no attitude is defined

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 - 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:

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

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.