public class IsotropicRadiationClassicalConvention extends Object implements RadiationSensitive
This model uses the classical thermo-optical coefficients Ca for absorption, Cs for specular reflection and Kd for diffuse reflection. The equation Ca + Cs + Cd = 1 always holds.
A less standard set of coefficients α = Ca for absorption and
τ = Cs/(1-Ca) for specular reflection is implemented in the sister
class IsotropicRadiationCNES95Convention.
BoxAndSolarArraySpacecraft,
IsotropicDrag,
IsotropicRadiationCNES95ConventionABSORPTION_COEFFICIENT, REFLECTION_COEFFICIENT| Constructor and Description |
|---|
IsotropicRadiationClassicalConvention(double crossSection,
double ca,
double cs)
Simple constructor.
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| Modifier and Type | Method and Description |
|---|---|
List<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.
|
<T extends CalculusFieldElement<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 IsotropicRadiationClassicalConvention(double crossSection,
double ca,
double cs)
crossSection - Surface (m²)ca - absorption coefficient Ca between 0.0 an 1.0cs - specular reflection coefficient Cs between 0.0 an 1.0public List<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 CalculusFieldElement<T>> FieldVector3D<T> radiationPressureAcceleration(FieldAbsoluteDate<T> date, Frame frame, FieldVector3D<T> position, FieldRotation<T> rotation, T mass, FieldVector3D<T> flux, T[] parameters)
radiationPressureAcceleration in interface RadiationSensitiveT - extends CalculusFieldElementdate - 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 parametersCopyright © 2002-2022 CS GROUP. All rights reserved.