public class IsotropicRadiationCNES95Convention extends Object implements RadiationSensitive
This model uses the coefficients described in the collective book edited by CNES in 1995: Spaceflight Dynamics (part I), in section 5.2.2.1.3.1 (page 296 of the English edition). The absorption coefficient is called α and the specular reflection coefficient is called τ. A comment in section 5.2.2.1.3.2 of the same book reads:
Some authors prefer to express thermo-optical properties for surfaces using the following coefficients: Ka = α, Ks = (1-α)τ, Kd = (1-α)(1-τ)
Ka is the same absorption coefficient, and Ks is also called specular reflection coefficient, which leads to a confusion. In fact, as the Ka, Ks and Kd coefficients are the most frequently used ones (using the names Ca, Cs and Cd), when speaking about reflection coefficients, it is more often Cd that is considered rather than τ.
The classical set of coefficients Ca, Cs, and Cd are implemented in the
sister class IsotropicRadiationClassicalConvention, which should
probably be preferred to this legacy class.
BoxAndSolarArraySpacecraft,
IsotropicDrag,
IsotropicRadiationClassicalConventionABSORPTION_COEFFICIENT, REFLECTION_COEFFICIENT| Constructor and Description |
|---|
IsotropicRadiationCNES95Convention(double crossSection,
double alpha,
double tau)
Simple constructor.
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| Modifier and Type | Method and Description |
|---|---|
ParameterDriver[] |
getRadiationParametersDrivers()
Get the drivers for supported parameters.
|
Vector3D |
radiationPressureAcceleration(AbsoluteDate date,
Frame frame,
Vector3D position,
Rotation rotation,
double mass,
Vector3D flux,
double[] parameters)
Compute the acceleration due to radiation pressure.
|
FieldVector3D<DerivativeStructure> |
radiationPressureAcceleration(AbsoluteDate date,
Frame frame,
Vector3D position,
Rotation rotation,
double mass,
Vector3D flux,
double[] parameters,
String paramName)
Compute the acceleration due to radiation pressure, with parameters derivatives.
|
<T extends RealFieldElement<T>> |
radiationPressureAcceleration(FieldAbsoluteDate<T> date,
Frame frame,
FieldVector3D<T> position,
FieldRotation<T> rotation,
T mass,
FieldVector3D<T> flux,
T[] parameters)
Compute the acceleration due to radiation pressure.
|
public IsotropicRadiationCNES95Convention(double crossSection,
double alpha,
double tau)
crossSection - Surface (m²)alpha - absorption coefficient α between 0.0 an 1.0tau - specular reflection coefficient τ between 0.0 an 1.0public ParameterDriver[] getRadiationParametersDrivers()
getRadiationParametersDrivers in interface RadiationSensitivepublic Vector3D radiationPressureAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, Vector3D flux, double[] parameters)
radiationPressureAcceleration in interface RadiationSensitivedate - current dateframe - inertial reference frame for state (both orbit and attitude)position - position of spacecraft in reference framerotation - orientation (attitude) of the spacecraft with respect to reference framemass - current massflux - radiation flux in the same inertial frame as spacecraft orbitparameters - values of the force model parameterspublic <T extends RealFieldElement<T>> FieldVector3D<T> radiationPressureAcceleration(FieldAbsoluteDate<T> date, Frame frame, FieldVector3D<T> position, FieldRotation<T> rotation, T mass, FieldVector3D<T> flux, T[] parameters) throws OrekitException
radiationPressureAcceleration in interface RadiationSensitiveT - extends RealFieldElementdate - current dateframe - inertial reference frame for state (both orbit and attitude)position - position of spacecraft in reference framerotation - orientation (attitude) of the spacecraft with respect to reference framemass - current massflux - radiation flux in the same inertial frame as spacecraft orbitparameters - values of the force model parametersOrekitException - if acceleration cannot be computedpublic FieldVector3D<DerivativeStructure> radiationPressureAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, Vector3D flux, double[] parameters, String paramName) throws OrekitException
radiationPressureAcceleration in interface RadiationSensitivedate - current dateframe - inertial reference frame for state (both orbit and attitude)position - position of spacecraft in reference framerotation - orientation (attitude) of the spacecraft with respect to reference framemass - current massflux - radiation flux in the same inertial frame as spacecraft orbitparameters - values of the force model parametersparamName - name of the parameter with respect to which derivatives are requiredOrekitException - if acceleration cannot be computedCopyright © 2002-2017 CS Systèmes d'information. All rights reserved.