Uses of Class
org.orekit.parameter.Parameter

Packages that use Parameter

fr.cnes.sirius.patrius.assembly.models
fr.cnes.sirius.patrius.assembly.models.cook
fr.cnes.sirius.patrius.assembly.properties
fr.cnes.sirius.patrius.forces
fr.cnes.sirius.patrius.forces.radiation
fr.cnes.sirius.patrius.stela.forces.drag
fr.cnes.sirius.patrius.wrenches
org.orekit.forces.drag
org.orekit.forces.gravity
org.orekit.forces.gravity.tides
org.orekit.forces.gravity.variations
org.orekit.forces.maneuvers	This package provides models of simple maneuvers.
org.orekit.forces.radiation
org.orekit.forces.relativistic
org.orekit.parameter
org.orekit.propagation.numerical

Uses of Parameter in fr.cnes.sirius.patrius.assembly.models

Methods in fr.cnes.sirius.patrius.assembly.models that return types with arguments of type Parameter

ArrayList<Parameter>	DragLiftModel.getJacobianParameters()
ArrayList<Parameter>	DirectRadiativeModel.getJacobianParameters() Get the list of all jacobian parameters supported.
ArrayList<Parameter>	GlobalAeroModel.getJacobianParameters() Get the list of all jacobian parameters supported.
ArrayList<Parameter>	AeroModel.getJacobianParameters() Get the list of all jacobian parameters supported.
ArrayList<Parameter>	RediffusedRadiativeModel.getJacobianParameters() Get the list of all jacobian parameters supported.

Methods in fr.cnes.sirius.patrius.assembly.models with parameters of type Parameter

void	RediffusedRadiativeModel.addDAccDParamRediffusedRadiativePressure(SpacecraftState s, Parameter param, double[] dAccdParam)
void	DragLiftModel.addDDragAccDParam(SpacecraftState s, Parameter param, double density, Vector3D relativeVelocity, double[] dAccdParam) Compute acceleration derivatives with respect to ballistic coefficient.
void	GlobalAeroModel.addDDragAccDParam(SpacecraftState s, Parameter param, double density, Vector3D relativeVelocity, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters (the ballistic coefficient).
void	AeroModel.addDDragAccDParam(SpacecraftState s, Parameter param, double density, Vector3D relativeVelocity, double[] dAccdParam) Compute acceleration derivatives with respect to ballistic coefficient.
void	DirectRadiativeModel.addDSRPAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam, Vector3D satSunVector) Compute acceleration derivatives with respect to additional parameters.

Constructors in fr.cnes.sirius.patrius.assembly.models with parameters of type Parameter

DirectRadiativeModel(Assembly inAssembly, Parameter inK0Albedo)
Radiative model (the acceleration is computed from all the sub parts of the vehicle).

RediffusedRadiativeModel(boolean inAlbedo, boolean inIr, Parameter inK0Albedo, Parameter inK0Ir, Assembly inAssembly)
Rediffused radiative model (the acceleration is computed from all the sub parts of the vehicle).

Uses of Parameter in fr.cnes.sirius.patrius.assembly.models.cook

Methods in fr.cnes.sirius.patrius.assembly.models.cook that return types with arguments of type Parameter

ArrayList<Parameter>	CtCookModel.getParameters() Get the supported parameters.
ArrayList<Parameter>	CnCookModel.getParameters() Get the supported parameters.

Methods in fr.cnes.sirius.patrius.assembly.models.cook with parameters of type Parameter

double	CtCookModel.derivativeValue(Parameter p, SpacecraftState state) Compute the derivative value with respect to the input parameter.
double	CnCookModel.derivativeValue(Parameter p, SpacecraftState state) Compute the derivative value with respect to the input parameter.
boolean	CtCookModel.isDifferentiableBy(Parameter p) Tell if the function is differentiable by the given parameter.
boolean	CnCookModel.isDifferentiableBy(Parameter p) Tell if the function is differentiable by the given parameter.
boolean	CtCookModel.supportsParameter(Parameter param) Check if a parameter is supported.
boolean	CnCookModel.supportsParameter(Parameter param) Check if a parameter is supported.

Uses of Parameter in fr.cnes.sirius.patrius.assembly.properties

Methods in fr.cnes.sirius.patrius.assembly.properties that return Parameter

Parameter	RadiativeIRProperty.getAbsorptionCoef() Get the parameter representing the absorption coefficient of the part.
Parameter	RadiativeProperty.getAbsorptionRatio() Get the parameter representing the ratio of light absorbed: Ka = α.
Parameter	RadiativeIRProperty.getDiffuseReflectionCoef() Get the parameter representing the diffuse reflection coefficient of the part.
Parameter	RadiativeProperty.getDiffuseReflectionRatio() Get the parameter representing the ratio of light subjected to diffuse reflectance : Kd = (1 - α) (1 - τ).
Parameter	RadiativeIRProperty.getSpecularReflectionCoef() Get the parameter representing the specular reflection coefficient of the part.
Parameter	RadiativeProperty.getSpecularReflectionRatio() Get the parameter representing the ratio of light subjected to specular reflectance : Ks = (1 - α) τ.

Methods in fr.cnes.sirius.patrius.assembly.properties with parameters of type Parameter

double

AeroSphereProperty.getDragForceDerivativeValue(Parameter parameter, SpacecraftState s) Get the drag force coefficient derivative value with respect to the given parameter.

Constructors in fr.cnes.sirius.patrius.assembly.properties with parameters of type Parameter

AeroFacetProperty(Facet inFacet, Parameter normalCoef, Parameter tangentialCoef)
Constructor of this property using Parameter.

AeroSphereProperty(double inSphereRadius, double inAtmScaleHeight, Parameter dragCoef)
This constructor shall be used for defining the drag coef using Parameter

AeroSphereProperty(double inSphereRadius, Parameter dragCoef)
Constructor of this propertydefining the drag coef using Parameter without the atmospheric height scale.

AeroSphereProperty(Parameter inSphereArea, double dragCoef)
Constructor of this property giving the drag coef without the atmospheric height scale.

MassProperty(Parameter inMass)
Constructor of this property using a Parameter.

RadiativeIRProperty(Parameter absorptionCoef, Parameter specularCoef, Parameter diffuseCoef)
Constructor of this property using Parameter.

RadiativeProperty(Parameter ka, Parameter ks, Parameter kd)
Constructor of this property using Parameter.

RadiativeSphereProperty(Parameter inSphereArea)
Constructor with area.

Uses of Parameter in fr.cnes.sirius.patrius.forces

Methods in fr.cnes.sirius.patrius.forces with parameters of type Parameter

void	EmpiricalForce.addDAccDParam(SpacecraftState state, Parameter param, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters.

Constructors in fr.cnes.sirius.patrius.forces with parameters of type Parameter

EmpiricalForce(int harmonicFactor, Vector3D vectorS, Parameter ax, Parameter ay, Parameter az, Parameter bx, Parameter by, Parameter bz, Parameter cx, Parameter cy, Parameter cz, Frame coeffsFrame)
Simple constructor for an empiric force using Parameter for A; B and C coef with a given frame.

EmpiricalForce(int harmonicFactor, Vector3D vectorS, Parameter ax, Parameter ay, Parameter az, Parameter bx, Parameter by, Parameter bz, Parameter cx, Parameter cy, Parameter cz, LOFType coeffsFrameLOFType)
Simple constructor for an empiric force using Parameter for A; B and C coef with a given LOF frame.

Uses of Parameter in fr.cnes.sirius.patrius.forces.radiation

Methods in fr.cnes.sirius.patrius.forces.radiation with parameters of type Parameter

void	PatriusSolarRadiationPressure.addDAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam)

Constructors in fr.cnes.sirius.patrius.forces.radiation with parameters of type Parameter

PatriusSolarRadiationPressure(Parameter referenceFlux, PVCoordinatesProvider sunBody, GeometricBodyShape shape, RadiationSensitive spacecraftModel)
Complete constructor using Parameter.

PatriusSolarRadiationPressure(Parameter referenceFlux, PVCoordinatesProvider sunBody, GeometricBodyShape shape, RadiationSensitive spacecraftModel, boolean computePD)
Complete constructor using Parameter.

Uses of Parameter in fr.cnes.sirius.patrius.stela.forces.drag

Methods in fr.cnes.sirius.patrius.stela.forces.drag that return types with arguments of type Parameter

ArrayList<Parameter>

StelaAeroModel.getJacobianParameters() Get the list of all jacobian parameters supported.

Methods in fr.cnes.sirius.patrius.stela.forces.drag with parameters of type Parameter

void	StelaAeroModel.addDDragAccDParam(SpacecraftState s, Parameter param, double density, Vector3D relativeVelocity, double[] dAccdParam)

Uses of Parameter in fr.cnes.sirius.patrius.wrenches

Constructors in fr.cnes.sirius.patrius.wrenches with parameters of type Parameter

SolarRadiationWrench(Parameter distance, Parameter pressure, Parameter sunRadius, PVCoordinatesProvider sunBody, GeometricBodyShape shape, RadiationWrenchSensitive spacecraftModel)
Complete constructor using Parameter.

Uses of Parameter in org.orekit.forces.drag

Methods in org.orekit.forces.drag with parameters of type Parameter

void	DragForce.addDAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters.
void	DragSensitive.addDDragAccDParam(SpacecraftState s, Parameter param, double density, Vector3D relativeVelocity, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters (the ballistic coefficient).

Constructors in org.orekit.forces.drag with parameters of type Parameter

DragForce(Parameter k, Atmosphere atmosphere, DragSensitive spacecraft)
Constructor with multiplicative factor k.

DragForce(Parameter k, Atmosphere atmosphere, DragSensitive spacecraft, boolean computePDPos, boolean computePDVel)
Constructor with multiplicative factor k.

Uses of Parameter in org.orekit.forces.gravity

Methods in org.orekit.forces.gravity with parameters of type Parameter

void	BalminoAttractionModel.addDAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters.
void	ThirdBodyAttraction.addDAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters.
void	CunninghamAttractionModel.addDAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters.
void	NewtonianAttraction.addDAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters.

Constructors in org.orekit.forces.gravity with parameters of type Parameter

BalminoAttractionModel(Frame frame, Parameter ae, Parameter mu, double[][] Ccoefs, double[][] Scoefs)
Create an instance of a normalized gravity computation model using normalized coefficients.

BalminoAttractionModel(Frame frame, Parameter ae, Parameter mu, double[][] Ccoefs, double[][] Scoefs, int degreePD, int orderPD)
Create an instance of a normalized gravity computation model using normalized coefficients.

CunninghamAttractionModel(Frame centralBodyFrame, Parameter equatorialRadius, Parameter mu, double[][] C, double[][] S)
Creates a new instance using Parameter.

CunninghamAttractionModel(Frame centralBodyFrame, Parameter equatorialRadius, Parameter mu, double[][] C, double[][] S, int degreePD, int orderPD)
Creates a new instance using Parameter.

DrozinerAttractionModel(Frame centralBodyFrame, Parameter equatorialRadius, Parameter mu, double[][] C, double[][] S)
Creates a new instance using Parameter.

DrozinerAttractionModel(Frame centralBodyFrame, Parameter equatorialRadius, Parameter mu, double[][] C, double[][] S, boolean computePDPos, boolean computePDVel)
Creates a new instance using Parameter.

NewtonianAttraction(Parameter mu)
Simple constructor using Parameter.

NewtonianAttraction(Parameter mu, boolean computePD)
Simple constructor using Parameter.

Uses of Parameter in org.orekit.forces.gravity.tides

Fields in org.orekit.forces.gravity.tides declared as Parameter

protected Parameter	AbstractTides.paramAe Equatorial radius parameter.
protected Parameter	AbstractTides.paramMu Central attraction coefficient parameter.

Methods in org.orekit.forces.gravity.tides with parameters of type Parameter

void	AbstractTides.addDAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters.

Constructors in org.orekit.forces.gravity.tides with parameters of type Parameter

AbstractTides(Frame centralBodyFrame, Parameter equatorialRadius, Parameter mu, int degree, int order)
Build a new instance using Parameter.

AbstractTides(Frame centralBodyFrame, Parameter equatorialRadius, Parameter mu, int degree, int order, int degreePD, int orderPD)
Build a new instance using Parameter.

OceanTides(Frame centralBodyFrame, Parameter equatorialRadius, Parameter mu, Parameter density, int degree, int order, boolean withAdmittance, IOceanTidesDataProvider tidesData)
Constructor using Parameter.

OceanTides(Frame centralBodyFrame, Parameter equatorialRadius, Parameter mu, Parameter density, int degree, int order, int degreePD, int orderPD, boolean withAdmittance, IOceanTidesDataProvider tidesData)
Constructor using Parameter.

TerrestrialTides(Frame centralBodyFrame, Parameter equatorialRadius, Parameter mu)
Creates a new instance.

TerrestrialTides(Frame centralBodyFrame, Parameter equatorialRadius, Parameter mu, boolean computePD)
Creates a new instance.

TerrestrialTides(Frame centralBodyFrame, Parameter equatorialRadius, Parameter mu, List<CelestialBody> bodies, boolean thirdBodyAttDegree3, boolean frequencyCorr, boolean ellipticityCorr, ITerrestrialTidesDataProvider terrestrialData)
Creates a new instance using Parameter.

TerrestrialTides(Frame centralBodyFrame, Parameter equatorialRadius, Parameter mu, List<CelestialBody> bodies, boolean thirdBodyAttDegree3, boolean frequencyCorr, boolean ellipticityCorr, ITerrestrialTidesDataProvider terrestrialData, boolean computePD)
Creates a new instance using Parameter.

Uses of Parameter in org.orekit.forces.gravity.variations

Methods in org.orekit.forces.gravity.variations with parameters of type Parameter

void	VariablePotentialAttractionModel.addDAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters.

Uses of Parameter in org.orekit.forces.maneuvers

Methods in org.orekit.forces.maneuvers with parameters of type Parameter

void	ConstantThrustManeuver.addDAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters.
void	ConstantThrustError.addDAccDParam(SpacecraftState state, Parameter param, double[] dAccdParam)
void	VariableThrustManeuver.addDAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters.

Constructors in org.orekit.forces.maneuvers with parameters of type Parameter

ConstantThrustError(AbsoluteDate date, double duration, Frame frame, Parameter cx, Parameter cy, Parameter cz)
Create a constant thrust error model whose x, y and z components are constant functions:
fx = cx
fy = cy
fz = cz

ConstantThrustError(AbsoluteDate date, double duration, Frame frame, Parameter ax, Parameter bx, Parameter ay, Parameter by, Parameter az, Parameter bz, AbsoluteDate date0)
Create a constant thrust error model whose x, y and z components are linear functions:
fx = ax*t + bx
fy = ay*t + by
fz = az*t + bz

ConstantThrustError(AbsoluteDate date, double duration, LOFType lofType, Parameter cx, Parameter cy, Parameter cz)
Create a constant thrust error model whose x, y and z components are constant functions:
fx = cx
fy = cy
fz = cz

ConstantThrustError(AbsoluteDate date, double duration, LOFType lofType, Parameter ax, Parameter bx, Parameter ay, Parameter by, Parameter az, Parameter bz, AbsoluteDate date0)
Create a constant thrust error model whose x, y and z components are linear functions:
fx = ax*t + bx
fy = ay*t + by
fz = az*t + bz

ConstantThrustError(AbsoluteDate date, double duration, Parameter cx, Parameter cy, Parameter cz)
Create a constant thrust error model whose x, y and z components are constant functions:
fx = cx
fy = cy
fz = cz

ConstantThrustError(AbsoluteDate date, double duration, Parameter ax, Parameter bx, Parameter ay, Parameter by, Parameter az, Parameter bz, AbsoluteDate date0)
Create a constant thrust error model whose x, y and z components are linear functions:
fx = ax*t + bx
fy = ay*t + by
fz = az*t + bz

ConstantThrustError(EventDetector startEventDetector, EventDetector stopEventDetector, Frame frame, Parameter cx, Parameter cy, Parameter cz)
Create a constant thrust error model whose x, y and z components are constant functions:
fx = cx
fy = cy
fz = cz

ConstantThrustError(EventDetector startEventDetector, EventDetector stopEventDetector, LOFType lofType, Parameter cx, Parameter cy, Parameter cz)
Create a constant thrust error model whose x, y and z components are constant functions:
fx = cx
fy = cy
fz = cz

ConstantThrustError(EventDetector startEventDetector, EventDetector stopEventDetector, Parameter cx, Parameter cy, Parameter cz)
Create a constant thrust error model whose x, y and z components are constant functions:
fx = cx
fy = cy
fz = cz

ConstantThrustManeuver(AbsoluteDate date, double duration, Parameter thrust, Parameter flowRate, Vector3D direction, MassProvider massProvider, String partName)
Constructor for a constant direction in satellite frame and constant thrust using Parameter.

ConstantThrustManeuver(AbsoluteDate date, double duration, Parameter thrust, Parameter flowRate, Vector3D direction, MassProvider massProvider, String partName, Frame frame)
Constructor for a constant direction in provided frame and constant thrust using Parameter.

ConstantThrustManeuver(AbsoluteDate date, double duration, Parameter thrust, Parameter flowRate, Vector3D direction, MassProvider massProvider, String partName, LOFType lofType)
Constructor for a constant direction in provided local orbital frame and constant thrust using Parameter with a local orbital frame defined by its type.

Uses of Parameter in org.orekit.forces.radiation

Methods in org.orekit.forces.radiation with parameters of type Parameter

void	RediffusedRadiationPressure.addDAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters.
void	SolarRadiationPressure.addDAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters.
void	RediffusedRadiationSensitive.addDAccDParamRediffusedRadiativePressure(SpacecraftState s, Parameter param, double[] dAccdParam) Compute acceleration derivatives.
void	RadiationSensitive.addDSRPAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam, Vector3D satSunVector) Compute acceleration derivatives with respect to additional parameters.

Constructors in org.orekit.forces.radiation with parameters of type Parameter

SolarRadiationPressure(Parameter refFlux, PVCoordinatesProvider sun, double equatorialRadius, RadiationSensitive spacecraft)
Complete constructor.

SolarRadiationPressure(Parameter refFlux, PVCoordinatesProvider sun, double equatorialRadius, RadiationSensitive spacecraft, boolean computePD)
Complete constructor.

Uses of Parameter in org.orekit.forces.relativistic

Methods in org.orekit.forces.relativistic with parameters of type Parameter

void	SchwarzschildRelativisticEffect.addDAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters.
void	LenseThirringRelativisticEffect.addDAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters.
void	CoriolisRelativisticEffect.addDAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters.

Uses of Parameter in org.orekit.parameter

Methods in org.orekit.parameter that return types with arguments of type Parameter

ArrayList<Parameter>	PiecewiseFunction.getParameters() Get the supported parameters.
ArrayList<Parameter>	IParameterizable.getParameters() Get the supported parameters.
ArrayList<Parameter>	Parameterizable.getParameters() Get the supported parameters.
ArrayList<Parameter>	ConstantFunction.getParameters() Get the supported parameters.
ArrayList<Parameter>	LinearFunction.getParameters() Get the supported parameters.

Methods in org.orekit.parameter with parameters of type Parameter

void	IJacobiansParameterizable.addDAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters.
protected void	JacobiansParameterizable.addJacobiansParameter(Parameter... params) Add a parameters in the jacobians parameters list.
protected void	JacobiansParameterizable.addJacobiansParameter(Parameter param) Add a new parameter in the jacobians parameters list.
protected void	Parameterizable.addParameter(Parameter param) Add a new parameter in the lit, only if it does not exist.
double	PiecewiseFunction.derivativeValue(Parameter p, SpacecraftState s) Compute the derivative value with respect to the input parameter.
double	IParamDiffFunction.derivativeValue(Parameter p, SpacecraftState s) Compute the derivative value with respect to the input parameter.
double	ConstantFunction.derivativeValue(Parameter p, SpacecraftState state) Compute the derivative value with respect to the input parameter.
double	LinearFunction.derivativeValue(Parameter p, SpacecraftState state) Compute the derivative value with respect to the input parameter.
boolean	IParamDiffFunction.isDifferentiableBy(Parameter p) Tell if the function is differentiable by the given parameter.
boolean	ParamDiffFunction.isDifferentiableBy(Parameter p) Tell if the function is differentiable by the given parameter.
boolean	IJacobiansParameterizable.supportsJacobianParameter(Parameter param) Check if a jacobian parameter is supported.
boolean	JacobiansParameterizable.supportsJacobianParameter(Parameter param) Check if a jacobian parameter is supported.
boolean	ParamDiffFunction.supportsParameter(Parameter p) Check if a parameter is supported.
boolean	IParameterizable.supportsParameter(Parameter param) Check if a parameter is supported.
boolean	Parameterizable.supportsParameter(Parameter param) Check if a parameter is supported.

Method parameters in org.orekit.parameter with type arguments of type Parameter

protected void

JacobiansParameterizable.addJacobiansParameter(ArrayList<Parameter> params) Add a list of parameters in the jacobians parameters list.

Constructors in org.orekit.parameter with parameters of type Parameter

ConstantFunction(Parameter param)
Simple constructor with a given Parameter.

JacobiansParameterizable(Parameter... params)
Simple constructor.

LinearFunction(AbsoluteDate t0, Parameter slope, Parameter zeroValue)
Simple constructor of a linear function a * (t - t0) + b using input Parameter and initial date.

Parameterizable(Parameter... params)
Simple constructor.

Constructor parameters in org.orekit.parameter with type arguments of type Parameter

JacobiansParameterizable(ArrayList<Parameter> paramList)
Simple constructor.

Parameterizable(ArrayList<Parameter> paramList)
Simple constructor.

Uses of Parameter in org.orekit.propagation.numerical

Methods in org.orekit.propagation.numerical that return types with arguments of type Parameter

List<Parameter>	PartialDerivativesEquations.getAvailableParameters() Get the names of the available parameters in the propagator.
ArrayList<Parameter>	JacobianParametersProvider.getJacobianParameters() Get the list of all jacobian parameters supported.
List<Parameter>	JacobiansMapper.getParametersList() Get parameters list.

Methods in org.orekit.propagation.numerical with parameters of type Parameter

double[]	JacobiansMapper.getParametersJacobian(Parameter parameter, SpacecraftState state) Get the Jacobian with respect to provided parameter parameter.
void	JacobiansMapper.getParametersJacobian(Parameter parameter, SpacecraftState state, double[] dYdP) Get the Jacobian with respect to provided parameter parameter.
void	PartialDerivativesEquations.selectParamAndStep(Parameter parameter, double hP) Select the parameters to consider for Jacobian processing.
void	PartialDerivativesEquations.selectParameters(Parameter... parameters) Select the parameters to consider for Jacobian processing.
SpacecraftState	PartialDerivativesEquations.setInitialJacobians(SpacecraftState s, Parameter parameter, double[] dY1dP) Set the initial value of the Jacobian with respect to state.