org.orekit.propagation.semianalytical.dsst.forces

Class DSSTSolarRadiationPressure

java.lang.Object

org.orekit.propagation.semianalytical.dsst.forces.AbstractGaussianContribution

org.orekit.propagation.semianalytical.dsst.forces.DSSTSolarRadiationPressure

All Implemented Interfaces:

DSSTForceModel

public class DSSTSolarRadiationPressure
extends AbstractGaussianContribution

Solar radiation pressure contribution to the DSSTPropagator.

The solar radiation pressure acceleration is computed through the acceleration model of SolarRadiationPressure.

Author:

Pascal Parraud

Constructor Summary

Constructors

Constructor and Description
DSSTSolarRadiationPressure(double dRef, double pRef, double cr, double area, ExtendedPVCoordinatesProvider sun, double equatorialRadius, double mu) Constructor with customizable reference values but spherical spacecraft.
DSSTSolarRadiationPressure(double cr, double area, ExtendedPVCoordinatesProvider sun, double equatorialRadius, double mu) Simple constructor with default reference values and spherical spacecraft.
DSSTSolarRadiationPressure(double dRef, double pRef, ExtendedPVCoordinatesProvider sun, double equatorialRadius, RadiationSensitive spacecraft, double mu) Complete constructor.
DSSTSolarRadiationPressure(ExtendedPVCoordinatesProvider sun, double equatorialRadius, RadiationSensitive spacecraft, double mu) Simple constructor with default reference values, but custom spacecraft.

Method Summary

Modifier and Type	Method and Description
double	getEquatorialRadius() Get the central body equatorial radius.
EventDetector[]	getEventsDetectors() Get the discrete events related to the model.
<T extends RealFieldElement<T>> FieldEventDetector<T>[]	getFieldEventsDetectors(Field<T> field) Get the discrete events related to the model.
protected <T extends RealFieldElement<T>> T[]	getLLimits(FieldSpacecraftState<T> state, FieldAuxiliaryElements<T> auxiliaryElements) Compute the limits in L, the true longitude, for integration.
protected double[]	getLLimits(SpacecraftState state, AuxiliaryElements auxiliaryElements) Compute the limits in L, the true longitude, for integration.
protected ParameterDriver[]	getParametersDriversWithoutMu() Get the drivers for force model parameters except the one for the central attraction coefficient.
RadiationSensitive	getSpacecraft() Get spacecraft shape.

Methods inherited from class org.orekit.propagation.semianalytical.dsst.forces.AbstractGaussianContribution

getMeanElementRate, getMeanElementRate, getParametersDrivers, initialize, initialize, registerAttitudeProvider, updateShortPeriodTerms, updateShortPeriodTerms

Methods inherited from class java.lang.Object

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

Methods inherited from interface org.orekit.propagation.semianalytical.dsst.forces.DSSTForceModel

getParameters, getParameters

Constructor Detail

DSSTSolarRadiationPressure

public DSSTSolarRadiationPressure(double cr,
                                  double area,
                                  ExtendedPVCoordinatesProvider sun,
                                  double equatorialRadius,
                                  double mu)

Simple constructor with default reference values and spherical spacecraft.

When this constructor is used, the reference values are:

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

The spacecraft has a spherical shape.

Parameters:

cr - satellite radiation pressure coefficient (assuming total specular reflection)

area - cross sectional area of satellite

sun - Sun model

equatorialRadius - central body equatorial radius (for shadow computation)

mu - central attraction coefficient

Since:

9.2

DSSTSolarRadiationPressure

public DSSTSolarRadiationPressure(ExtendedPVCoordinatesProvider sun,
                                  double equatorialRadius,
                                  RadiationSensitive spacecraft,
                                  double mu)

Simple constructor with default reference values, but custom spacecraft.

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 - central body equatorial radius (for shadow computation)

spacecraft - spacecraft model

mu - central attraction coefficient

Since:

9.2

DSSTSolarRadiationPressure

public DSSTSolarRadiationPressure(double dRef,
                                  double pRef,
                                  double cr,
                                  double area,
                                  ExtendedPVCoordinatesProvider sun,
                                  double equatorialRadius,
                                  double mu)

Constructor with customizable reference values but spherical spacecraft.

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)

cr - satellite radiation pressure coefficient (assuming total specular reflection)

area - cross sectional area of satellite

sun - Sun model

equatorialRadius - central body equatorial radius (for shadow computation)

mu - central attraction coefficient

Since:

9.2

DSSTSolarRadiationPressure

public DSSTSolarRadiationPressure(double dRef,
                                  double pRef,
                                  ExtendedPVCoordinatesProvider sun,
                                  double equatorialRadius,
                                  RadiationSensitive spacecraft,
                                  double mu)

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 - central body equatorial radius (for shadow computation)

spacecraft - spacecraft model

mu - central attraction coefficient

Since:

9.2

Method Detail

getSpacecraft

public RadiationSensitive getSpacecraft()

Get spacecraft shape.

Returns:

the spacecraft shape.

getEventsDetectors

public EventDetector[] getEventsDetectors()

Get the discrete events related to the model.

Returns:

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

getFieldEventsDetectors

public <T extends RealFieldElement<T>> FieldEventDetector<T>[] getFieldEventsDetectors(Field<T> field)

Get the discrete events related to the model.

Type Parameters:

T - type of the elements

Parameters:

field - field used by default

Returns:

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

getParametersDriversWithoutMu

protected ParameterDriver[] getParametersDriversWithoutMu()

Get the drivers for force model parameters except the one for the central attraction coefficient.

The driver for central attraction coefficient is automatically added at the last element of the ParameterDriver array into AbstractGaussianContribution.getParametersDrivers() method.

Specified by:

getParametersDriversWithoutMu in class AbstractGaussianContribution

Returns:

drivers for force model parameters

getLLimits

protected double[] getLLimits(SpacecraftState state,
                              AuxiliaryElements auxiliaryElements)

Compute the limits in L, the true longitude, for integration.

Specified by:

getLLimits in class AbstractGaussianContribution

Parameters:

state - current state information: date, kinematics, attitude

auxiliaryElements - auxiliary elements related to the current orbit

Returns:

the integration limits in L

getLLimits

protected <T extends RealFieldElement<T>> T[] getLLimits(FieldSpacecraftState<T> state,
                                                         FieldAuxiliaryElements<T> auxiliaryElements)

Compute the limits in L, the true longitude, for integration.

Specified by:

getLLimits in class AbstractGaussianContribution

Type Parameters:

T - type of the elements

Parameters:

state - current state information: date, kinematics, attitude

auxiliaryElements - auxiliary elements related to the current orbit

Returns:

the integration limits in L

getEquatorialRadius

public double getEquatorialRadius()

Get the central body equatorial radius.

Returns:

central body equatorial radius (m)