fr.cnes.sirius.patrius.assembly.models

Class GlobalAeroModel

java.lang.Object

fr.cnes.sirius.patrius.assembly.models.GlobalAeroModel

All Implemented Interfaces:

DragSensitive, JacobianParametersProvider, Serializable

public final class GlobalAeroModel
extends Object
implements DragSensitive

Global aero model for generic user-provided aero coefficients.

This model requires a AeroProperty. This property has to be applied to Main part only:

• If Main part does not have a AeroProperty, an exception is thrown.
• If other parts have AeroProperty, they are not taken into account.

Since:

3.3

Version:

$Id: GlobalAeroModel.java 18195 2017-10-13 11:49:12Z bignon $

Author:

Emmanuel Bignon

See Also:

Serialized Form

Concurrency :

not thread-safe

Constructor Summary

Constructors

Constructor and Description
GlobalAeroModel(Assembly assemblyIn, DragCoefficientProvider dragCoefficientProviderIn, ExtendedAtmosphere atmosphereIn) Constructor with default partial derivatives time step DEFAULT_STEP.
GlobalAeroModel(Assembly assemblyIn, DragCoefficientProvider dragCoefficientProviderIn, ExtendedAtmosphere atmosphereIn, double partialDerivativesStep) Constructor.

Method Summary

Methods

Modifier and Type	Method and Description
void	addDDragAccDParam(SpacecraftState s, Parameter param, double density, Vector3D relativeVelocity, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters (the 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 java.lang.Object

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

Constructor Detail

GlobalAeroModel

public GlobalAeroModel(Assembly assemblyIn,
               DragCoefficientProvider dragCoefficientProviderIn,
               ExtendedAtmosphere atmosphereIn,
               double partialDerivativesStep)

Constructor.

Parameters:

assemblyIn - assembly

dragCoefficientProviderIn - drag coefficient (x surface) provider

atmosphereIn - atmosphere

partialDerivativesStep - partial derivatives position step

GlobalAeroModel

public GlobalAeroModel(Assembly assemblyIn,
               DragCoefficientProvider dragCoefficientProviderIn,
               ExtendedAtmosphere atmosphereIn)

Constructor with default partial derivatives time step DEFAULT_STEP.

Parameters:

assemblyIn - assembly

dragCoefficientProviderIn - drag coefficient provider

atmosphereIn - atmosphere

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 - relative velocity of atmosphere with respect to spacecraft, in the same inertial frame as spacecraft orbit (m/s). WARNING : Remember that consequently, the spacecraft velocity is obtained as the opposite of relativeVelocity.

Returns:

the acceleration applied on the assembly.

Throws:

PatriusException - when an error occurs.

addDDragAccDParam

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

Compute acceleration derivatives with respect to additional parameters (the ballistic coefficient).

Specified by:

addDDragAccDParam in interface DragSensitive

Parameters:

s - spacecraft state

param - parameter

density - the atmospheric density value

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

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.