fr.cnes.sirius.patrius.assembly.models.aerocoeffs

Class AeroCoeffByAoA

java.lang.Object

fr.cnes.sirius.patrius.assembly.models.aerocoeffs.AbstractAeroCoeff1D

fr.cnes.sirius.patrius.assembly.models.aerocoeffs.AeroCoeffByAoA

All Implemented Interfaces:

AerodynamicCoefficient, IParamDiffFunction, IParameterizable, IParameterizableFunction, Serializable

public class AeroCoeffByAoA
extends AbstractAeroCoeff1D

Aerodynamic coefficient function of the spacecraft angle of attack. Aerodynamic coefficient is then retrieved by linear interpolation of an array.

Since:

4.1

Version:

$Id$

Author:

Marie Capot

See Also:

Serialized Form

Constructor Summary

Constructors

Constructor and Description
AeroCoeffByAoA(double[] xVariables, double[] yVariables, EllipsoidBodyShape earthShapeIn) Constructor.

Method Summary

Modifier and Type	Method and Description
static double	angleOfAttackFromSpacecraftState(SpacecraftState state, EllipsoidBodyShape earthShape) Computes the angle of attack from the spacecraft state and the Earth shape.
protected double	computeXVariable(SpacecraftState state) Computes the x variable from the spacecraft state.
AerodynamicCoefficientType	getType() Returns type of aerodynamic coefficient.

Methods inherited from class fr.cnes.sirius.patrius.assembly.models.aerocoeffs.AbstractAeroCoeff1D

derivativeValue, getFunction, getParameters, getXArray, getYArray, isDifferentiableBy, supportsParameter, toString, value

Methods inherited from class java.lang.Object

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

Constructor Detail

AeroCoeffByAoA

public AeroCoeffByAoA(double[] xVariables,
                      double[] yVariables,
                      EllipsoidBodyShape earthShapeIn)

Constructor.

Parameters:

xVariables - array of x variables (angle of attack (rad))

yVariables - array of y variables (aerodynamic coefficient)

earthShapeIn - Earth shape

Method Detail

computeXVariable

protected double computeXVariable(SpacecraftState state)
                           throws PatriusException

Computes the x variable from the spacecraft state.

Specified by:

computeXVariable in class AbstractAeroCoeff1D

Parameters:

state - the spacecraft state

Returns:

the x variable

Throws:

PatriusException - if there is a problem computing x from state.

angleOfAttackFromSpacecraftState

public static double angleOfAttackFromSpacecraftState(SpacecraftState state,
                                                      EllipsoidBodyShape earthShape)
                                               throws PatriusException

Computes the angle of attack from the spacecraft state and the Earth shape.

Parameters:

state - the spacecraft state

earthShape - the Earth shape

Returns:

the mach number

Throws:

PatriusException - if the transformation from state frame to body frame cannot be computed

getType

public AerodynamicCoefficientType getType()

Returns type of aerodynamic coefficient.

Returns:

type of aerodynamic coefficient