org.orekit.forces.radiation

Class SolarRadiationPressure

java.lang.Object

org.apache.commons.math3.ode.AbstractParameterizable

org.orekit.forces.radiation.SolarRadiationPressure

All Implemented Interfaces:

Parameterizable, ParameterizedODE, ForceModel

public class SolarRadiationPressure
extends AbstractParameterizable
implements ForceModel

Solar radiation pressure force model.

Author:

Fabien Maussion, Édouard Delente, Véronique Pommier-Maurussane, Pascal Parraud

Constructor Summary

Constructors

Constructor and Description
SolarRadiationPressure(double dRef, double pRef, PVCoordinatesProvider sun, double equatorialRadius, RadiationSensitive spacecraft) Complete constructor.
SolarRadiationPressure(PVCoordinatesProvider sun, double equatorialRadius, RadiationSensitive spacecraft) Simple constructor with default reference values.

Method Summary

Methods

Modifier and Type	Method and Description
FieldVector3D<DerivativeStructure>	accelerationDerivatives(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldVector3D<DerivativeStructure> velocity, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass) Compute acceleration derivatives with respect to state parameters.
FieldVector3D<DerivativeStructure>	accelerationDerivatives(SpacecraftState s, String paramName) Compute acceleration derivatives with respect to additional parameters.
void	addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.
EventDetector[]	getEventsDetectors() Get the discrete events related to the model.
double	getLightningRatio(Vector3D position, Frame frame, AbsoluteDate date) Get the lightning ratio ([0-1]).
double	getParameter(String name)
void	setParameter(String name, double value)

Methods inherited from class org.apache.commons.math3.ode.AbstractParameterizable

complainIfNotSupported, getParametersNames, isSupported

Methods inherited from class java.lang.Object

clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait

Methods inherited from interface org.apache.commons.math3.ode.Parameterizable

getParametersNames, isSupported

Constructor Detail

SolarRadiationPressure

public SolarRadiationPressure(PVCoordinatesProvider sun,
                      double equatorialRadius,
                      RadiationSensitive spacecraft)

Simple constructor with default reference values.

When this constructor is used, the reference values are:

• d_ref = 149597870000.0 m
• p_ref = 4.56 10^-6 N/m²

Parameters:

sun - Sun model

equatorialRadius - spherical shape model (for umbra/penumbra computation)

spacecraft - the object physical and geometrical information

SolarRadiationPressure

public SolarRadiationPressure(double dRef,
                      double pRef,
                      PVCoordinatesProvider sun,
                      double equatorialRadius,
                      RadiationSensitive spacecraft)

Complete constructor.

Note that reference solar radiation pressure pRef in N/m² is linked to solar flux SF in W/m² using formula pRef = SF/c where c is the speed of light (299792458 m/s). So at 1UA a 1367 W/m² solar flux is a 4.56 10^-6 N/m² solar radiation pressure.

Parameters:

dRef - reference distance for the solar radiation pressure (m)

pRef - reference solar radiation pressure at dRef (N/m²)

sun - Sun model

equatorialRadius - spherical shape model (for umbra/penumbra computation)

spacecraft - the object physical and geometrical information

Method Detail

addContribution

public void addContribution(SpacecraftState s,
                   TimeDerivativesEquations adder)
                     throws OrekitException

Compute the contribution of the force model to the perturbing acceleration.

Specified by:

addContribution in interface ForceModel

Parameters:

s - current state information: date, kinematics, attitude

adder - object where the contribution should be added

Throws:

OrekitException - if some specific error occurs

getLightningRatio

public double getLightningRatio(Vector3D position,
                       Frame frame,
                       AbsoluteDate date)
                         throws OrekitException

Get the lightning ratio ([0-1]).

Parameters:

position - the satellite's position in the selected frame.

frame - in which is defined the position

date - the date

Returns:

lightning ratio

Throws:

OrekitException - if the trajectory is inside the Earth

getEventsDetectors

public EventDetector[] getEventsDetectors()

Get the discrete events related to the model.

Specified by:

getEventsDetectors in interface ForceModel

Returns:

array of events detectors or null if the model is not related to any discrete events

accelerationDerivatives

public FieldVector3D<DerivativeStructure> accelerationDerivatives(AbsoluteDate date,
                                                         Frame frame,
                                                         FieldVector3D<DerivativeStructure> position,
                                                         FieldVector3D<DerivativeStructure> velocity,
                                                         FieldRotation<DerivativeStructure> rotation,
                                                         DerivativeStructure mass)
                                                           throws OrekitException

Compute acceleration derivatives with respect to state parameters.

The derivatives should be computed with respect to position, velocity and optionnaly mass. The input parameters already take into account the free parameters (6 or 7 depending on derivation with respect to mass being considered or not) and order (always 1). Free parameters at indices 0, 1 and 2 correspond to derivatives with respect to position. Free parameters at indices 3, 4 and 5 correspond to derivatives with respect to velocity. Free parameter at index 6 (if present) corresponds to to derivatives with respect to mass.

Specified by:

accelerationDerivatives in interface ForceModel

Parameters:

date - current date

frame - inertial reference frame for state (both orbit and attitude)

position - position of spacecraft in reference frame

velocity - velocity of spacecraft in reference frame

rotation - orientation (attitude) of the spacecraft with respect to reference frame

mass - spacecraft mass

Returns:

acceleration with all derivatives specified by the input parameters own derivatives

Throws:

OrekitException - if derivatives cannot be computed

accelerationDerivatives

public FieldVector3D<DerivativeStructure> accelerationDerivatives(SpacecraftState s,
                                                         String paramName)
                                                           throws OrekitException

Compute acceleration derivatives with respect to additional parameters.

Specified by:

accelerationDerivatives in interface ForceModel

Parameters:

s - spacecraft state

paramName - name of the parameter with respect to which derivatives are required

Returns:

acceleration with all derivatives specified by the input parameters own derivatives

Throws:

OrekitException - if derivatives cannot be computed

getParameter

public double getParameter(String name)
                    throws IllegalArgumentException

Specified by:

getParameter in interface ParameterizedODE

Throws:

IllegalArgumentException

setParameter

public void setParameter(String name,
                double value)
                  throws IllegalArgumentException

Specified by:

setParameter in interface ParameterizedODE

Throws:

IllegalArgumentException