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

Field Summary

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

a, A, B, C, co2AB, ecc, f, g, h, k, lm, mu, n, ooA, ooAB, ooBpo, ooMu, p, q, ton2a, w

Constructor Summary

Constructors

Constructor and Description
DSSTSolarRadiationPressure(double dRef, double pRef, double cr, double area, PVCoordinatesProvider sun, double equatorialRadius) Constructor with customizable reference values but spherical spacecraft.
DSSTSolarRadiationPressure(double cr, double area, PVCoordinatesProvider sun, double equatorialRadius) Simple constructor with default reference values and spherical spacecraft.
DSSTSolarRadiationPressure(double dRef, double pRef, PVCoordinatesProvider sun, double equatorialRadius, RadiationSensitive spacecraft) Complete constructor.
DSSTSolarRadiationPressure(PVCoordinatesProvider sun, double equatorialRadius, RadiationSensitive spacecraft) 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.
protected double[]	getLLimits(SpacecraftState state) Compute the limits in L, the true longitude, for integration.
RadiationSensitive	getSpacecraft() Get spacecraft shape.

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

getMeanElementRate, initialize, initializeStep, registerAttitudeProvider, updateShortPeriodTerms

Methods inherited from class java.lang.Object

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

Constructor Detail

DSSTSolarRadiationPressure

public DSSTSolarRadiationPressure(double cr,
                                  double area,
                                  PVCoordinatesProvider sun,
                                  double equatorialRadius)

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 sectionnal area of satellite

sun - Sun model

equatorialRadius - central body equatorial radius (for shadow computation)

DSSTSolarRadiationPressure

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

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

DSSTSolarRadiationPressure

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

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 sectionnal area of satellite

sun - Sun model

equatorialRadius - central body equatrial radius (for shadow computation)

DSSTSolarRadiationPressure

public DSSTSolarRadiationPressure(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 - central body equatrial radius (for shadow computation)

spacecraft - spacecraft model

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

getLLimits

protected double[] getLLimits(SpacecraftState state)
                       throws OrekitException

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

Specified by:

getLLimits in class AbstractGaussianContribution

Parameters:

state - current state information: date, kinematics, attitude

Returns:

the integration limits in L

Throws:

OrekitException - if some specific error occurs

getEquatorialRadius

public double getEquatorialRadius()

Get the central body equatorial radius.

Returns:

central body equatorial radius (m)