java.lang.Object
- org.orekit.forces.radiation.IsotropicRadiationCNES95Convention

All Implemented Interfaces:

RadiationSensitive
```
public class IsotropicRadiationCNES95Convention
extends Object
implements RadiationSensitive
```
This class represents the features of a simplified spacecraft.
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.
Since:

7.1

Author:

Luc Maisonobe

See Also:

BoxAndSolarArraySpacecraft, IsotropicDrag, IsotropicRadiationClassicalConvention

Field Summary
- Fields inherited from interface org.orekit.forces.radiation.RadiationSensitive
  ABSORPTION_COEFFICIENT, REFLECTION_COEFFICIENT

Constructor Summary

Constructors
Constructor	Description
`IsotropicRadiationCNES95Convention(double crossSection, double alpha, double tau)`	Simple constructor.

Method Summary

All Methods Instance Methods Concrete Methods
Modifier and Type	Method	Description
`ParameterDriver[]`	`getRadiationParametersDrivers()`	Get the drivers for supported parameters.
`org.hipparchus.geometry.euclidean.threed.Vector3D`	`radiationPressureAcceleration(AbsoluteDate date, Frame frame, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Rotation rotation, double mass, org.hipparchus.geometry.euclidean.threed.Vector3D flux, double[] parameters)`	Compute the acceleration due to radiation pressure.
`org.hipparchus.geometry.euclidean.threed.FieldVector3D<org.hipparchus.analysis.differentiation.DerivativeStructure>`	`radiationPressureAcceleration(AbsoluteDate date, Frame frame, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Rotation rotation, double mass, org.hipparchus.geometry.euclidean.threed.Vector3D flux, double[] parameters, String paramName)`	Compute the acceleration due to radiation pressure, with parameters derivatives.
`<T extends org.hipparchus.RealFieldElement<T>> org.hipparchus.geometry.euclidean.threed.FieldVector3D<T>`	`radiationPressureAcceleration(FieldAbsoluteDate<T> date, Frame frame, org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> position, org.hipparchus.geometry.euclidean.threed.FieldRotation<T> rotation, T mass, org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> flux, T[] parameters)`	Compute the acceleration due to radiation pressure.

Methods inherited from class java.lang.Object
clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait

Constructor Detail
- IsotropicRadiationCNES95Convention
```
public IsotropicRadiationCNES95Convention(double crossSection,
                                          double alpha,
                                          double tau)
```
  Simple constructor.
  
  Parameters:
  
  crossSection - Surface (m²)
  
  alpha - absorption coefficient α between 0.0 an 1.0
  
  tau - specular reflection coefficient τ between 0.0 an 1.0

Method Detail

getRadiationParametersDrivers
```
public ParameterDriver[] getRadiationParametersDrivers()
```
Get the drivers for supported parameters.

Specified by:

getRadiationParametersDrivers in interface RadiationSensitive

Returns:

parameters drivers

radiationPressureAcceleration

public org.hipparchus.geometry.euclidean.threed.Vector3D radiationPressureAcceleration(AbsoluteDate date,
                                                                                       Frame frame,
                                                                                       org.hipparchus.geometry.euclidean.threed.Vector3D position,
                                                                                       org.hipparchus.geometry.euclidean.threed.Rotation rotation,
                                                                                       double mass,
                                                                                       org.hipparchus.geometry.euclidean.threed.Vector3D flux,
                                                                                       double[] parameters)

Compute the acceleration due to radiation pressure.

Specified by:: radiationPressureAcceleration in interface RadiationSensitive
Parameters:: date - current date; frame - inertial reference frame for state (both orbit and attitude); position - position of spacecraft in reference frame; rotation - orientation (attitude) of the spacecraft with respect to reference frame; mass - current mass; 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 org.hipparchus.RealFieldElement<T>> org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> radiationPressureAcceleration(FieldAbsoluteDate<T> date,
                                                                                                                                              Frame frame,
                                                                                                                                              org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> position,
                                                                                                                                              org.hipparchus.geometry.euclidean.threed.FieldRotation<T> rotation,
                                                                                                                                              T mass,
                                                                                                                                              org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> flux,
                                                                                                                                              T[] parameters)

Compute the acceleration due to radiation pressure.

Specified by:: radiationPressureAcceleration in interface RadiationSensitive
Type Parameters:: T - extends RealFieldElement
Parameters:: date - current date; frame - inertial reference frame for state (both orbit and attitude); position - position of spacecraft in reference frame; rotation - orientation (attitude) of the spacecraft with respect to reference frame; mass - current mass; 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 org.hipparchus.geometry.euclidean.threed.FieldVector3D<org.hipparchus.analysis.differentiation.DerivativeStructure> radiationPressureAcceleration(AbsoluteDate date,
                                                                                                                                                         Frame frame,
                                                                                                                                                         org.hipparchus.geometry.euclidean.threed.Vector3D position,
                                                                                                                                                         org.hipparchus.geometry.euclidean.threed.Rotation rotation,
                                                                                                                                                         double mass,
                                                                                                                                                         org.hipparchus.geometry.euclidean.threed.Vector3D flux,
                                                                                                                                                         double[] parameters,
                                                                                                                                                         String paramName)

Compute the acceleration due to radiation pressure, with parameters derivatives.

Specified by:: radiationPressureAcceleration in interface RadiationSensitive
Parameters:: date - current date; frame - inertial reference frame for state (both orbit and attitude); position - position of spacecraft in reference frame; rotation - orientation (attitude) of the spacecraft with respect to reference frame; mass - current mass; flux - radiation flux in the same inertial frame as spacecraft orbit; parameters - values of the force model parameters; paramName - name of the parameter with respect to which derivatives are required
Returns:: spacecraft acceleration in the same inertial frame as spacecraft orbit (m/s²)

Class IsotropicRadiationCNES95Convention

Field Summary

Fields inherited from interface org.orekit.forces.radiation.RadiationSensitive

Constructor Summary

Method Summary

Methods inherited from class java.lang.Object

Constructor Detail

IsotropicRadiationCNES95Convention

Method Detail

getRadiationParametersDrivers

radiationPressureAcceleration

radiationPressureAcceleration

radiationPressureAcceleration