Package 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:

EventDetectorsProvider, DSSTForceModel, ParameterDriversProvider

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

Nested Class Summary

Nested classes/interfaces inherited from class org.orekit.propagation.semianalytical.dsst.forces.AbstractGaussianContribution

AbstractGaussianContribution.FieldFourierCjSjCoefficients<T extends CalculusFieldElement<T>>, AbstractGaussianContribution.FieldGaussianShortPeriodicCoefficients<T extends CalculusFieldElement<T>>, AbstractGaussianContribution.FieldIntegrableFunction<T extends CalculusFieldElement<T>>, AbstractGaussianContribution.FieldSlot<T extends CalculusFieldElement<T>>, AbstractGaussianContribution.FieldUijVijCoefficients<T extends CalculusFieldElement<T>>, AbstractGaussianContribution.FourierCjSjCoefficients, AbstractGaussianContribution.GaussianShortPeriodicCoefficients, AbstractGaussianContribution.GaussQuadrature, AbstractGaussianContribution.IntegrableFunction, AbstractGaussianContribution.Slot, AbstractGaussianContribution.UijVijCoefficients

Field Summary

Fields inherited from interface org.orekit.propagation.events.EventDetectorsProvider

DATATION_ACCURACY

Constructor Summary

Constructors

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

Method Summary

Modifier and Type	Method	Description
double	getEquatorialRadius()	Get the central body equatorial radius.
protected <T extends CalculusFieldElement<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 List<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, getMeanElementRate, getMeanElementRate, getParametersDrivers, init, init, initializeShortPeriodTerms, initializeShortPeriodTerms, 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

extractParameters, extractParameters, getEventDetectors, getFieldEventDetectors

Methods inherited from interface org.orekit.propagation.events.EventDetectorsProvider

getDateDetector, getEventDetectors, getFieldDateDetector, getFieldEventDetectors

Methods inherited from interface org.orekit.utils.ParameterDriversProvider

getNbParametersDriversValue, getParameterDriver, getParameters, getParameters, getParameters, getParameters, getParametersAllValues, getParametersAllValues, isSupported

Constructor Detail

DSSTSolarRadiationPressure

public DSSTSolarRadiationPressure(double cr,
                                  double area,
                                  ExtendedPositionProvider sun,
                                  OneAxisEllipsoid centralBody,
                                  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

centralBody - central body (for shadow computation)

mu - central attraction coefficient

Since:

12.0

DSSTSolarRadiationPressure

public DSSTSolarRadiationPressure(ExtendedPositionProvider sun,
                                  OneAxisEllipsoid centralBody,
                                  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

centralBody - central body (for shadow computation)

spacecraft - spacecraft model

mu - central attraction coefficient

Since:

12.0

DSSTSolarRadiationPressure

public DSSTSolarRadiationPressure(double dRef,
                                  double pRef,
                                  double cr,
                                  double area,
                                  ExtendedPositionProvider sun,
                                  OneAxisEllipsoid centralBody,
                                  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

centralBody - central body (for shadow computation)

mu - central attraction coefficient

Since:

12.0

DSSTSolarRadiationPressure

public DSSTSolarRadiationPressure(double dRef,
                                  double pRef,
                                  ExtendedPositionProvider sun,
                                  OneAxisEllipsoid centralBody,
                                  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

centralBody - central body shape model (for umbra/penumbra computation)

spacecraft - spacecraft model

mu - central attraction coefficient

Since:

12.0

Method Detail

getSpacecraft

public RadiationSensitive getSpacecraft()

Get spacecraft shape.

Returns:

the spacecraft shape.

getParametersDriversWithoutMu

protected List<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 CalculusFieldElement<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)