fr.cnes.sirius.patrius.forces.radiation

Class SolarRadiationPressure

java.lang.Object

fr.cnes.sirius.patrius.math.parameter.Parameterizable

fr.cnes.sirius.patrius.math.parameter.JacobiansParameterizable

fr.cnes.sirius.patrius.forces.radiation.SolarRadiationPressure

All Implemented Interfaces:

ForceModel, GradientModel, IJacobiansParameterizable, IParameterizable, Serializable

public class SolarRadiationPressure
extends JacobiansParameterizable
implements ForceModel, GradientModel

Solar radiation pressure force model considering spherical/circular or non-spherical (ellipsoid) occulting bodies.

The implementation of this class enables the computation of partial derivatives with respect to absorption, specular reflection or diffusion reflection coefficients.

Eclipses computation can be deactivated by using setEclipsesComputation(boolean). By default, eclipses are taken into account.

This class allows to consider any occulting body (Earth, Moon, etc.).
In case of multiple occulting bodies, the assumption is made that only one body occults the spacecraft at a time.

Light speed is currently never taken into account.

Since:

1.2

Version:

$Id: PatriusSolarRadiationPressure.java 18114 2017-10-04 09:32:13Z bignon $

Author:

Rami Houdroge, Thibaut Bonit

See Also:

Serialized Form

Concurrency :

not thread-safe

Concurrency comment :

fields use Frames

Field Summary

Fields

Modifier and Type	Field and Description
static String	REFERENCE_FLUX Normalized reference flux.

Constructor Summary

Constructors

Constructor and Description
SolarRadiationPressure(double dRef, double pRef, PVCoordinatesProvider sunBody, double sunRadiusIn, BodyShape occultingBody, Assembly assembly, double multiplicativeFactorIn) Creates a new instance.
SolarRadiationPressure(double dRef, double pRef, PVCoordinatesProvider sunBody, double sunRadiusIn, BodyShape occultingBody, RadiationSensitive spacecraftModel) Complete constructor.
SolarRadiationPressure(double dRef, double pRef, PVCoordinatesProvider sunBody, double sunRadiusIn, BodyShape occultingBody, RadiationSensitive spacecraftModel, boolean computePD) Complete constructor.
SolarRadiationPressure(double dRef, double pRef, PVCoordinatesProvider sun, double sunRadiusIn, double occultingBodyRadius, CelestialBodyFrame occultingBodyFrame, RadiationSensitive spacecraft, boolean computePD) Complete constructor.
SolarRadiationPressure(double dRef, double pRef, PVCoordinatesProvider sun, double sunRadiusIn, double occultingBodyRadius, RadiationSensitive spacecraft) Complete constructor.
SolarRadiationPressure(double dRef, double pRef, PVCoordinatesProvider sun, double sunRadiusIn, double occultingBodyRadius, RadiationSensitive spacecraft, boolean computePD) Complete constructor.
SolarRadiationPressure(Parameter referenceFlux, PVCoordinatesProvider sunBody, BodyShape occultingBody, RadiationSensitive spacecraftModel) Complete constructor using Parameter.
SolarRadiationPressure(Parameter referenceFlux, PVCoordinatesProvider sunBody, double sunRadiusIn, BodyShape occultingBody, RadiationSensitive spacecraftModel, boolean computePD) Complete constructor using Parameter.
SolarRadiationPressure(Parameter refFluxParam, PVCoordinatesProvider sun, double sunRadiusIn, double occultingBodyRadius, CelestialBodyFrame occultingBodyFrame, RadiationSensitive spacecraft, boolean computePD) Complete constructor.
SolarRadiationPressure(Parameter refFluxParam, PVCoordinatesProvider sun, double occultingBodyRadius, RadiationSensitive spacecraft) Complete constructor.
SolarRadiationPressure(Parameter refFluxParam, PVCoordinatesProvider sun, double occultingBodyRadius, RadiationSensitive spacecraft, boolean computePD) Complete constructor.
SolarRadiationPressure(PVCoordinatesProvider sunBody, BodyShape occultingBody, RadiationSensitive spacecraftModel) Simple constructor with default reference values.
SolarRadiationPressure(PVCoordinatesProvider sunBody, BodyShape occultingBody, RadiationSensitive spacecraftModel, boolean computePD) Simple constructor with default reference values.
SolarRadiationPressure(PVCoordinatesProvider sun, double occultingBodyRadius, CelestialBodyFrame occultingBodyFrame, RadiationSensitive spacecraft, boolean computePD) Simple constructor with default reference values.
SolarRadiationPressure(PVCoordinatesProvider sun, double occultingBodyRadius, RadiationSensitive spacecraft) Simple constructor with default reference values.
SolarRadiationPressure(PVCoordinatesProvider sun, double occultingBodyRadius, RadiationSensitive spacecraft, boolean computePD) Simple constructor with default reference values.
SolarRadiationPressure(SolarRadiationPressure otherInstance, Assembly assembly) Creates a new instance from the data in another one but with a different assembly.

Method Summary

Modifier and Type	Method and Description
void	addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.
void	addDAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters.
void	addDAccDState(SpacecraftState s, double[][] dAccdPos, double[][] dAccdVel) Compute acceleration derivatives with respect to state parameters.
void	addOccultingBody(BodyShape body) Add an occulting body.
void	checkData(AbsoluteDate start, AbsoluteDate end) This methods throws an exception if the user did not provide all the required data to perform model call on provided range [start; end].
Vector3D	computeAcceleration(SpacecraftState s) Compute the acceleration due to the force.
boolean	computeGradientPosition() This method returns true if the acceleration partial derivatives with respect to position have to be computed.
boolean	computeGradientVelocity() This method returns true if the acceleration partial derivatives with respect to velocity have to be computed.
static double	convertRadiativePressureToFlux(double dRef, double pRef) Get the solar flux (SF) from the solar radiation pressure: SF = pRef * dRef2
double	getEpsilonSignalPropagation() Getter for the epsilon for signal propagation when signal propagation is taken into account.
EventDetector[]	getEventsDetectors() Get the discrete events related to the model.
Frame	getInertialFrame() Getter for the inertial frame used for signal propagation computation.
double	getLightingRatio(Vector3D satSunVector, BodyShape occultingBody, PVCoordinatesProvider pv, Frame frame, AbsoluteDate date) Get the lighting ratio ([0-1]) for provided occulting body.
int	getMaxIterSignalPropagation() Getter for the maximum number of iterations for signal propagation when signal propagation is taken into account.
double	getMultiplicativeFactor() Getter for the multiplicative factor.
List<BodyShape>	getOccultingBodies() Getter for the occulting bodies.
AbstractSignalPropagationDetector.PropagationDelayType	getPropagationDelayType() Getter for the propagation delay type.
Parameter	getReferenceFlux() Getter for the parameter representing the reference flux normalized for a 1m distance (N).
Vector3D	getSolarFlux(SpacecraftState s) Compute solar flux.
PVCoordinatesProvider	getSunBody() Getter for the Sun model used at construction.
boolean	isEclipseComputation() Returns flag indicating if eclipses should be taken into account.
void	setEclipsesComputation(boolean eclipsesComputationFlagIn) Setter for enabling/disabling eclipses computation.
void	setEpsilonSignalPropagation(double epsilon) Setter for the epsilon for signal propagation when signal propagation is taken into account. This epsilon (in s) directly reflect the accuracy of signal propagation (1s of accuracy = 3E8m of accuracy on distance between emitter and receiver)
void	setMaxIterSignalPropagation(int maxIterSignalPropagationIn) Setter for the maximum number of iterations for signal propagation when signal propagation is taken into account.
void	setPropagationDelayType(AbstractSignalPropagationDetector.PropagationDelayType propagationDelayTypeIn, Frame frameIn) Setter for the propagation delay computation type.

Methods inherited from class fr.cnes.sirius.patrius.math.parameter.JacobiansParameterizable

addJacobiansParameter, addJacobiansParameter, addJacobiansParameter, supportsJacobianParameter

Methods inherited from class fr.cnes.sirius.patrius.math.parameter.Parameterizable

addAllParameters, addAllParameters, addParameter, getParameters, supportsParameter

Methods inherited from class java.lang.Object

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

Methods inherited from interface fr.cnes.sirius.patrius.math.parameter.IParameterizable

getParameters, supportsParameter

Field Detail

REFERENCE_FLUX

public static final String REFERENCE_FLUX

Normalized reference flux.

See Also:

Constant Field Values

Constructor Detail

SolarRadiationPressure

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

Simple constructor with default reference values.

When this constructor is used, the reference values are:

• d_ref = Constants.SEIDELMANN_UA
• p_ref = Constants.CONST_SOL_N_M2

Note: this constructor defines a spherical/circular occulting body (see #buildOccultingBodies(double, Frame).
The lighting ratio and the events detectors computation will be optimized.

Parameters:

sun - Sun model

occultingBodyRadius - Occulting body radius

spacecraft - The physical and geometrical spacecraft representation

SolarRadiationPressure

public SolarRadiationPressure(PVCoordinatesProvider sun,
                              double occultingBodyRadius,
                              RadiationSensitive spacecraft,
                              boolean computePD)

Simple constructor with default reference values.

When this constructor is used, the reference values are:

• d_ref = Constants.SEIDELMANN_UA
• p_ref = Constants.CONST_SOL_N_M2

Note: this constructor defines a spherical/circular occulting body (see #buildOccultingBodies(double, Frame).
The lighting ratio and the events detectors computation will be optimized.

Parameters:

sun - Sun model

occultingBodyRadius - Occulting body radius

spacecraft - The physical and geometrical spacecraft representation

computePD - true if the partial derivatives wrt position have to be computed, false otherwise

SolarRadiationPressure

public SolarRadiationPressure(PVCoordinatesProvider sun,
                              double occultingBodyRadius,
                              CelestialBodyFrame occultingBodyFrame,
                              RadiationSensitive spacecraft,
                              boolean computePD)

Simple constructor with default reference values.

When this constructor is used, the reference values are:

• d_ref = Constants.SEIDELMANN_UA
• p_ref = Constants.CONST_SOL_N_M2

Note: this constructor defines a spherical/circular occulting body (see #buildOccultingBodies(double, Frame).
The lighting ratio and the events detectors computation will be optimized.

Parameters:

sun - Sun model

occultingBodyRadius - Occulting body radius

occultingBodyFrame - Occulting body-centered frame

spacecraft - The physical and geometrical spacecraft representation

computePD - true if the partial derivatives wrt position have to be computed, false otherwise

SolarRadiationPressure

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

Complete constructor.

Note that reference solar radiation pressure pRef in N/m² is linked to solar flux SF in W/m² using the method convertRadiativePressureToFlux(double, double).

Note: this constructor defines a spherical/circular occulting body (see #buildOccultingBodies(double, Frame).
The lighting ratio and the events detectors computation will be optimized.

Parameters:

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

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

sun - Sun model

sunRadiusIn - Sun radius

occultingBodyRadius - Occulting body radius

spacecraft - The physical and geometrical spacecraft representation

SolarRadiationPressure

public SolarRadiationPressure(double dRef,
                              double pRef,
                              PVCoordinatesProvider sun,
                              double sunRadiusIn,
                              double occultingBodyRadius,
                              RadiationSensitive spacecraft,
                              boolean computePD)

Complete constructor.

Note that reference solar radiation pressure pRef in N/m² is linked to solar flux SF in W/m² using the method convertRadiativePressureToFlux(double, double).

Note: this constructor defines a spherical/circular occulting body (see #buildOccultingBodies(double, Frame).
The lighting ratio and the events detectors computation will be optimized.

Parameters:

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

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

sun - Sun model

sunRadiusIn - Sun radius

occultingBodyRadius - Occulting body radius

spacecraft - The physical and geometrical spacecraft representation

computePD - true if the partial derivatives wrt position have to be computed, false otherwise

SolarRadiationPressure

public SolarRadiationPressure(double dRef,
                              double pRef,
                              PVCoordinatesProvider sun,
                              double sunRadiusIn,
                              double occultingBodyRadius,
                              CelestialBodyFrame occultingBodyFrame,
                              RadiationSensitive spacecraft,
                              boolean computePD)

Complete constructor.

Note that reference solar radiation pressure pRef in N/m² is linked to solar flux SF in W/m² using the method convertRadiativePressureToFlux(double, double).

Note: this constructor defines a spherical/circular occulting body (see #buildOccultingBodies(double, Frame).
The lighting ratio and the events detectors computation will be optimized.

Parameters:

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

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

sun - Sun model

sunRadiusIn - Sun radius

occultingBodyRadius - Occulting body radius

occultingBodyFrame - Occulting body-centered frame

spacecraft - The physical and geometrical spacecraft representation

computePD - true if the partial derivatives wrt position have to be computed, false otherwise

SolarRadiationPressure

public SolarRadiationPressure(Parameter refFluxParam,
                              PVCoordinatesProvider sun,
                              double occultingBodyRadius,
                              RadiationSensitive spacecraft)

Complete constructor.

Note: this constructor defines a spherical/circular occulting body (see #buildOccultingBodies(double, Frame).
The lighting ratio and the events detectors computation will be optimized.

Parameters:

refFluxParam - Normalized reference flux parameter for a 1m distance (N)

sun - Sun model

occultingBodyRadius - Occulting body radius

spacecraft - The physical and geometrical spacecraft representation

SolarRadiationPressure

public SolarRadiationPressure(Parameter refFluxParam,
                              PVCoordinatesProvider sun,
                              double occultingBodyRadius,
                              RadiationSensitive spacecraft,
                              boolean computePD)

Complete constructor.

Note: this constructor defines a spherical/circular occulting body (see #buildOccultingBodies(double, Frame).
The lighting ratio and the events detectors computation will be optimized.

Parameters:

refFluxParam - Normalized reference flux parameter for a 1m distance (N)

sun - Sun model

occultingBodyRadius - Occulting body radius

spacecraft - The physical and geometrical spacecraft representation

computePD - true if the partial derivatives wrt position have to be computed, false otherwise

SolarRadiationPressure

public SolarRadiationPressure(Parameter refFluxParam,
                              PVCoordinatesProvider sun,
                              double sunRadiusIn,
                              double occultingBodyRadius,
                              CelestialBodyFrame occultingBodyFrame,
                              RadiationSensitive spacecraft,
                              boolean computePD)

Complete constructor.

Note: this constructor defines a spherical/circular occulting body (see #buildOccultingBodies(double, Frame).
The lighting ratio and the events detectors computation will be optimized.

Parameters:

refFluxParam - Normalized reference flux parameter for a 1m distance (N)

sun - Sun model

sunRadiusIn - Sun radius

occultingBodyRadius - Occulting body radius

occultingBodyFrame - Occulting body-centered frame

spacecraft - The physical and geometrical spacecraft representation

computePD - true if the partial derivatives wrt position have to be computed, false otherwise

SolarRadiationPressure

public SolarRadiationPressure(PVCoordinatesProvider sunBody,
                              BodyShape occultingBody,
                              RadiationSensitive spacecraftModel)

Simple constructor with default reference values.

When this constructor is used, the reference values are:

• d_ref = Constants.SEIDELMANN_UA
• p_ref = Constants.CONST_SOL_N_M2

Parameters:

sunBody - Sun model

occultingBody - Occulting body model (for umbra/penumbra computation)

spacecraftModel - The physical and geometrical spacecraft representation

SolarRadiationPressure

public SolarRadiationPressure(PVCoordinatesProvider sunBody,
                              BodyShape occultingBody,
                              RadiationSensitive spacecraftModel,
                              boolean computePD)

Simple constructor with default reference values.

When this constructor is used, the reference values are:

• d_ref = Constants.SEIDELMANN_UA
• p_ref = Constants.CONST_SOL_N_M2

Parameters:

sunBody - Sun model

occultingBody - Occulting body model (for umbra/penumbra computation)

spacecraftModel - The physical and geometrical spacecraft representation

computePD - true if the partial derivatives wrt position have to be computed, false otherwise

SolarRadiationPressure

public SolarRadiationPressure(double dRef,
                              double pRef,
                              PVCoordinatesProvider sunBody,
                              double sunRadiusIn,
                              BodyShape occultingBody,
                              RadiationSensitive spacecraftModel)

Complete constructor.

Note that reference solar radiation pressure pRef in N/m² is linked to solar flux SF in W/m² using the method convertRadiativePressureToFlux(double, double).

Parameters:

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

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

sunBody - Sun model

sunRadiusIn - Sun radius

occultingBody - Occulting body model (for umbra/penumbra computation)

spacecraftModel - The physical and geometrical spacecraft representation

SolarRadiationPressure

public SolarRadiationPressure(double dRef,
                              double pRef,
                              PVCoordinatesProvider sunBody,
                              double sunRadiusIn,
                              BodyShape occultingBody,
                              RadiationSensitive spacecraftModel,
                              boolean computePD)

Complete constructor.

Note that reference solar radiation pressure pRef in N/m² is linked to solar flux SF in W/m² using the method convertRadiativePressureToFlux(double, double).

Parameters:

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

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

sunBody - Sun model

sunRadiusIn - Sun radius

occultingBody - Occulting body model (for umbra/penumbra computation)

spacecraftModel - The physical and geometrical spacecraft representation

computePD - true if the partial derivatives wrt position have to be computed, false otherwise

SolarRadiationPressure

public SolarRadiationPressure(Parameter referenceFlux,
                              PVCoordinatesProvider sunBody,
                              BodyShape occultingBody,
                              RadiationSensitive spacecraftModel)

Complete constructor using Parameter.

Parameters:

referenceFlux - The parameter representing the reference flux normalized for a 1m distance (N)

sunBody - Sun model

occultingBody - Occulting body model (for umbra/penumbra computation)

spacecraftModel - The physical and geometrical spacecraft representation

SolarRadiationPressure

public SolarRadiationPressure(Parameter referenceFlux,
                              PVCoordinatesProvider sunBody,
                              double sunRadiusIn,
                              BodyShape occultingBody,
                              RadiationSensitive spacecraftModel,
                              boolean computePD)

Complete constructor using Parameter.

Parameters:

referenceFlux - The parameter representing the reference flux normalized for a 1m distance (N)

sunBody - Sun model

sunRadiusIn - Sun radius

occultingBody - Occulting body model (for umbra/penumbra computation)

spacecraftModel - The physical and geometrical spacecraft representation

computePD - true if the partial derivatives wrt position have to be computed, false otherwise

SolarRadiationPressure

public SolarRadiationPressure(double dRef,
                              double pRef,
                              PVCoordinatesProvider sunBody,
                              double sunRadiusIn,
                              BodyShape occultingBody,
                              Assembly assembly,
                              double multiplicativeFactorIn)

Creates a new instance.

Parameters:

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

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

sunBody - Sun model

sunRadiusIn - Sun radius

occultingBody - Occulting body model (for umbra/penumbra computation)

assembly - Assembly with aerodynamic properties

multiplicativeFactorIn - Multiplicative factor

SolarRadiationPressure

public SolarRadiationPressure(SolarRadiationPressure otherInstance,
                              Assembly assembly)

Creates a new instance from the data in another one but with a different assembly.

Parameters:

otherInstance - The other instance

assembly - Assembly with aerodynamic properties

Method Detail

getSolarFlux

public Vector3D getSolarFlux(SpacecraftState s)
                      throws PatriusException

Compute solar flux.

Parameters:

s - Spacecraft state

Returns:

coefficient for acceleration computation

Throws:

PatriusException - thrown if Sun position cannot be retrieved

computeAcceleration

public Vector3D computeAcceleration(SpacecraftState s)
                             throws PatriusException

Compute the acceleration due to the force.

Specified by:

computeAcceleration in interface ForceModel

Parameters:

s - current state information: date, kinematics, attitude

Returns:

acceleration in the SpacecraftState frame

Throws:

PatriusException - if some specific error occurs

addContribution

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

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:

PatriusException - if some specific error occurs

getLightingRatio

public double getLightingRatio(Vector3D satSunVector,
                               BodyShape occultingBody,
                               PVCoordinatesProvider pv,
                               Frame frame,
                               AbsoluteDate date)
                        throws PatriusException

Get the lighting ratio ([0-1]) for provided occulting body.

Parameters:

satSunVector - Sat-Sun vector in spacecraft state frame

occultingBody - Occulting body

pv - Satellite's position-velocity

frame - Frame in which is defined the position

date - Date

Returns:

lighting ratio

Throws:

PatriusException - if an error occurs

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

addDAccDState

public void addDAccDState(SpacecraftState s,
                          double[][] dAccdPos,
                          double[][] dAccdVel)
                   throws PatriusException

Compute acceleration derivatives with respect to state parameters.

Specified by:

addDAccDState in interface IJacobiansParameterizable

Parameters:

s - spacecraft state

dAccdPos - acceleration derivatives with respect to position

dAccdVel - acceleration derivatives with respect to velocity

Throws:

PatriusException - if derivatives cannot be computed

addDAccDParam

public void addDAccDParam(SpacecraftState s,
                          Parameter param,
                          double[] dAccdParam)
                   throws PatriusException

Compute acceleration derivatives with respect to additional parameters.

Specified by:

addDAccDParam in interface IJacobiansParameterizable

Parameters:

s - spacecraft state

param - the parameter with respect to which derivatives are required

dAccdParam - acceleration derivatives with respect to specified parameters

Throws:

PatriusException - if derivatives cannot be computed

computeGradientPosition

public boolean computeGradientPosition()

This method returns true if the acceleration partial derivatives with respect to position have to be computed.

Specified by:

computeGradientPosition in interface GradientModel

Returns:

true if the derivatives have to be computed, false otherwise

computeGradientVelocity

public boolean computeGradientVelocity()

This method returns true if the acceleration partial derivatives with respect to velocity have to be computed.

Specified by:

computeGradientVelocity in interface GradientModel

Returns:

true if the derivatives have to be computed, false otherwise

getSunBody

public PVCoordinatesProvider getSunBody()

Getter for the Sun model used at construction.

Returns:

the Sun model.

getOccultingBodies

public List<BodyShape> getOccultingBodies()

Getter for the occulting bodies.

Returns:

the occulting bodies.

getMultiplicativeFactor

public double getMultiplicativeFactor()

Getter for the multiplicative factor.

Returns:

the multiplicative factor

getReferenceFlux

public Parameter getReferenceFlux()

Getter for the parameter representing the reference flux normalized for a 1m distance (N).

Returns:

the normlized reference flux parameter

checkData

public void checkData(AbsoluteDate start,
                      AbsoluteDate end)
               throws PatriusException

This methods throws an exception if the user did not provide all the required data to perform model call on provided range [start; end]. It is the responsibility of the model implementation to properly throw exceptions (for example DragForce will throw an exception if solar activity data is missing in the range [start, end]).

Specified by:

checkData in interface ForceModel

Parameters:

start - range start date

end - range end date

Throws:

PatriusException - thrown if some data is missing

setEclipsesComputation

public void setEclipsesComputation(boolean eclipsesComputationFlagIn)

Setter for enabling/disabling eclipses computation.

Parameters:

eclipsesComputationFlagIn - True if eclipses should be taken into account, false otherwise

isEclipseComputation

public boolean isEclipseComputation()

Returns flag indicating if eclipses should be taken into account.

Returns:

flag indicating if eclipses should be taken into account

addOccultingBody

public final void addOccultingBody(BodyShape body)

Add an occulting body.

Parameters:

body - Occulting body to add

convertRadiativePressureToFlux

public static double convertRadiativePressureToFlux(double dRef,
                                                    double pRef)

Get the solar flux (SF) from the solar radiation pressure: SF = pRef * dRef²

Parameters:

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

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

Returns:

the normalized reference flux.

getPropagationDelayType

public AbstractSignalPropagationDetector.PropagationDelayType getPropagationDelayType()

Getter for the propagation delay type.

Returns:

the propagation delay type

setPropagationDelayType

public void setPropagationDelayType(AbstractSignalPropagationDetector.PropagationDelayType propagationDelayTypeIn,
                                    Frame frameIn)

Setter for the propagation delay computation type. Warning: check Javadoc of detector to see if detector takes into account propagation time delay. if not, signals are always considered instantaneous. The provided frame is used to compute the signal propagation when delay is taken into account.

Parameters:

propagationDelayTypeIn - Propagation delay type used in events computation

frameIn - Frame to use for signal propagation with delay (may be null if propagation delay type is considered instantaneous). Warning: the usage of a pseudo inertial frame is tolerated, however it will lead to some inaccuracies due to the non-invariance of the frame with respect to time. For this reason, it is suggested to use the ICRF frame or a frame which is frozen with respect to the ICRF.

Throws:

IllegalArgumentException - if the provided frame is not pseudo inertial.

getInertialFrame

public Frame getInertialFrame()

Getter for the inertial frame used for signal propagation computation.

Returns:

the inertial frame

getEpsilonSignalPropagation

public double getEpsilonSignalPropagation()

Getter for the epsilon for signal propagation when signal propagation is taken into account.

Returns:

the epsilon for signal propagation when signal propagation is taken into account

setEpsilonSignalPropagation

public void setEpsilonSignalPropagation(double epsilon)

Setter for the epsilon for signal propagation when signal propagation is taken into account.
This epsilon (in s) directly reflect the accuracy of signal propagation (1s of accuracy = 3E8m of accuracy on distance between emitter and receiver)

Parameters:

epsilon - Epsilon for the signal propagation

getMaxIterSignalPropagation

public int getMaxIterSignalPropagation()

Getter for the maximum number of iterations for signal propagation when signal propagation is taken into account.

Returns:

the maximum number of iterations for signal propagation

setMaxIterSignalPropagation

public void setMaxIterSignalPropagation(int maxIterSignalPropagationIn)

Setter for the maximum number of iterations for signal propagation when signal propagation is taken into account.

Parameters:

maxIterSignalPropagationIn - Maximum number of iterations for signal propagation