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java.lang.Object org.orekit.parameter.Parameterizable org.orekit.parameter.JacobiansParameterizable org.orekit.forces.radiation.SolarRadiationPressure
public class SolarRadiationPressure
Solar radiation pressure force model.
The implementation of this class enables the computation of partial derivatives with respect to absorption, specular reflection or diffusion reflection coefficients.
Field Summary | |
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static String |
REFERENCE_FLUX
Normalized reference flux. |
Constructor Summary | |
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SolarRadiationPressure(double dRef,
double pRef,
PVCoordinatesProvider sun,
double equatorialRadius,
RadiationSensitive spacecraft)
Complete constructor. |
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SolarRadiationPressure(double dRef,
double pRef,
PVCoordinatesProvider sun,
double equatorialRadius,
RadiationSensitive spacecraft,
boolean computePD)
Complete constructor. |
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SolarRadiationPressure(Parameter refFlux,
PVCoordinatesProvider sun,
double equatorialRadius,
RadiationSensitive spacecraft)
Complete constructor. |
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SolarRadiationPressure(Parameter refFlux,
PVCoordinatesProvider sun,
double equatorialRadius,
RadiationSensitive spacecraft,
boolean computePD)
Complete constructor. |
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SolarRadiationPressure(PVCoordinatesProvider sun,
double equatorialRadius,
RadiationSensitive spacecraft)
Simple constructor with default reference values. |
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SolarRadiationPressure(PVCoordinatesProvider sun,
double equatorialRadius,
RadiationSensitive spacecraft,
boolean computePD)
Simple constructor with default reference values. |
Method Summary | |
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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. |
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. |
EventDetector[] |
getEventsDetectors()
Get the discrete events related to the model. |
double |
getLightningRatio(Vector3D position,
Frame frame,
AbsoluteDate date)
Get the lightning ratio ([0-1]). |
Methods inherited from class org.orekit.parameter.JacobiansParameterizable |
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addJacobiansParameter, addJacobiansParameter, addJacobiansParameter, supportsJacobianParameter |
Methods inherited from class org.orekit.parameter.Parameterizable |
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addParameter, getParameters, supportsParameter |
Methods inherited from class java.lang.Object |
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clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait |
Methods inherited from interface org.orekit.parameter.IParameterizable |
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getParameters, supportsParameter |
Field Detail |
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public static final String REFERENCE_FLUX
Constructor Detail |
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public SolarRadiationPressure(PVCoordinatesProvider sun, double equatorialRadius, RadiationSensitive spacecraft)
When this constructor is used, the reference values are:
sun
- Sun modelequatorialRadius
- spherical shape model (for umbra/penumbra computation)spacecraft
- the object physical and geometrical informationpublic SolarRadiationPressure(PVCoordinatesProvider sun, double equatorialRadius, RadiationSensitive spacecraft, boolean computePD)
When this constructor is used, the reference values are:
sun
- Sun modelequatorialRadius
- spherical shape model (for umbra/penumbra computation)spacecraft
- the object physical and geometrical informationcomputePD
- true if partial derivatives wrt position have to be computedpublic SolarRadiationPressure(double dRef, double pRef, PVCoordinatesProvider sun, double equatorialRadius, RadiationSensitive 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.
dRef
- reference distance for the solar radiation pressure (m)pRef
- reference solar radiation pressure at dRef (N/m2)sun
- Sun modelequatorialRadius
- spherical shape model (for umbra/penumbra computation)spacecraft
- the object physical and geometrical informationpublic SolarRadiationPressure(double dRef, double pRef, PVCoordinatesProvider sun, double equatorialRadius, RadiationSensitive spacecraft, boolean computePD)
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.
dRef
- reference distance for the solar radiation pressure (m)pRef
- reference solar radiation pressure at dRef (N/m2)sun
- Sun modelequatorialRadius
- spherical shape model (for umbra/penumbra computation)spacecraft
- the object physical and geometrical informationcomputePD
- true if partial derivatives wrt position have to be computedpublic SolarRadiationPressure(Parameter refFlux, PVCoordinatesProvider sun, double equatorialRadius, RadiationSensitive spacecraft)
refFlux
- parameter representing the reference flux normalized for a 1m distance (N)sun
- Sun modelequatorialRadius
- spherical shape model (for umbra/penumbra computation)spacecraft
- the object physical and geometrical informationpublic SolarRadiationPressure(Parameter refFlux, PVCoordinatesProvider sun, double equatorialRadius, RadiationSensitive spacecraft, boolean computePD)
refFlux
- parameter representing the reference flux normalized for a 1m distance (N)sun
- Sun modelequatorialRadius
- spherical shape model (for umbra/penumbra computation)spacecraft
- the object physical and geometrical informationcomputePD
- true if partial derivatives wrt position have to be computedMethod Detail |
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public Vector3D computeAcceleration(SpacecraftState s) throws OrekitException
computeAcceleration
in interface ForceModel
s
- current state information: date, kinematics, attitude
SpacecraftState frame
OrekitException
- if some specific error occurspublic void addContribution(SpacecraftState s, TimeDerivativesEquations adder) throws OrekitException
addContribution
in interface ForceModel
s
- current state information: date, kinematics, attitudeadder
- object where the contribution should be added
OrekitException
- if some specific error occurspublic double getLightningRatio(Vector3D position, Frame frame, AbsoluteDate date) throws OrekitException
position
- the satellite's position in the selected frame.frame
- in which is defined the positiondate
- the date
OrekitException
- if an error occurspublic EventDetector[] getEventsDetectors()
getEventsDetectors
in interface ForceModel
public void addDAccDState(SpacecraftState s, double[][] dAccdPos, double[][] dAccdVel) throws OrekitException
addDAccDState
in interface IJacobiansParameterizable
s
- spacecraft statedAccdPos
- acceleration derivatives with respect to positiondAccdVel
- acceleration derivatives with respect to velocity
OrekitException
- if derivatives cannot be computedpublic void addDAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam) throws OrekitException
addDAccDParam
in interface IJacobiansParameterizable
s
- spacecraft stateparam
- the parameter with respect to which derivatives are requireddAccdParam
- acceleration derivatives with respect to specified parameters
OrekitException
- if derivatives cannot be computedpublic boolean computeGradientPosition()
computeGradientPosition
in interface GradientModel
public boolean computeGradientVelocity()
computeGradientVelocity
in interface GradientModel
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