Package org.orekit.forces.radiation

Class IsotropicRadiationClassicalConvention

java.lang.Object
org.orekit.forces.radiation.IsotropicRadiationClassicalConvention
All Implemented Interfaces:
RadiationSensitive
public class IsotropicRadiationClassicalConvention extends Object implements RadiationSensitive
This class represents the features of a simplified spacecraft.

This model uses the classical thermo-optical coefficients Ca for absorption, Cs for specular reflection and Cd 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.

Since:
7.1
Author:
Luc Maisonobe
See Also:

  • Constructor Details

    • IsotropicRadiationClassicalConvention

      public IsotropicRadiationClassicalConvention(double crossSection, double ca, double cs)
      Simple constructor.
      Parameters:
      crossSection - Surface (m²)
      ca - absorption coefficient Ca between 0.0 an 1.0
      cs - specular reflection coefficient Cs between 0.0 an 1.0

  • Method Details

    • getRadiationParametersDrivers

      public List<ParameterDriver> getRadiationParametersDrivers()
      Get the drivers for supported parameters.
      Specified by:
      getRadiationParametersDrivers in interface RadiationSensitive
      Returns:
      parameters drivers

    • radiationPressureAcceleration

      public Vector3D radiationPressureAcceleration(SpacecraftState state, Vector3D flux, double[] parameters)
      Compute the acceleration due to radiation pressure.
      Specified by:
      radiationPressureAcceleration in interface RadiationSensitive
      Parameters:
      state - current state
      flux - radiation flux in the same inertial frame as spacecraft orbit
      parameters - values of the force model parameters
      Returns:
      spacecraft acceleration in the same inertial frame as spacecraft orbit (m/s²)

    • radiationPressureAcceleration

      public <T extends CalculusFieldElement<T>> FieldVector3D<T> radiationPressureAcceleration(FieldSpacecraftState<T> state, FieldVector3D<T> flux, T[] parameters)
      Compute the acceleration due to radiation pressure.
      Specified by:
      radiationPressureAcceleration in interface RadiationSensitive
      Type Parameters:
      T - extends CalculusFieldElement
      Parameters:
      state - current state
      flux - radiation flux in the same inertial frame as spacecraft orbit
      parameters - values of the force model parameters
      Returns:
      spacecraft acceleration in the same inertial frame as spacecraft orbit (m/s²)