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

Class AeroCoeffByMach

java.lang.Object

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

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

All Implemented Interfaces:

AerodynamicCoefficient, IParamDiffFunction, IParameterizable, IParameterizableFunction, Serializable

public class AeroCoeffByMach
extends AbstractAeroCoeff1D

Aerodynamic coefficient function of the spacecraft Mach number. 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
AeroCoeffByMach(double[] xVariables, double[] yVariables, Atmosphere atmosphereIn) Constructor.

Method Summary

Modifier and Type	Method and Description
protected double	computeXVariable(SpacecraftState state) Computes the x variable from the spacecraft state.
AerodynamicCoefficientType	getType() Returns type of aerodynamic coefficient.
static double	machFromSpacecraftState(SpacecraftState state, Atmosphere atmosphere) Computes the Mach number from the spacecraft state and an atmosphere model.

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

AeroCoeffByMach

public AeroCoeffByMach(double[] xVariables,
                       double[] yVariables,
                       Atmosphere atmosphereIn)

Constructor.

Parameters:

xVariables - array of x variables (Mach number)

yVariables - array of y variables (aerodynamic coefficient)

atmosphereIn - atmosphere model

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.

machFromSpacecraftState

public static double machFromSpacecraftState(SpacecraftState state,
                                             Atmosphere atmosphere)
                                      throws PatriusException

Computes the Mach number from the spacecraft state and an atmosphere model.

Parameters:

state - the spacecraft state

atmosphere - the atmosphere model

Returns:

the mach number

Throws:

PatriusException - thrown if conversion to ITRF failed

getType

public AerodynamicCoefficientType getType()

Returns type of aerodynamic coefficient.

Returns:

type of aerodynamic coefficient