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| 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 |
PropulsiveProperty.getIspParam()
Getter for the isp as an Parameter object. |
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. |
Parameter |
PropulsiveProperty.getThrustParam()
Getter for the thrust force as an Parameter object. |
| Methods in fr.cnes.sirius.patrius.assembly.properties with parameters of type Parameter | |
|---|---|
double |
AeroCrossSectionProperty.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 | |
|---|---|
AeroCrossSectionProperty(CrossSectionProvider shape,
Parameter dragCoefFct)
Constructor of this property defining the drag coef as a IParamDiffFunction. |
|
AeroFacetProperty(Facet inFacet,
Parameter normalCoef,
Parameter tangentialCoef)
Constructor of this property using Parameter. |
|
AeroSphereProperty(double inSphereRadius,
Parameter dragCoef)
This constructor shall be used for defining the drag coef using Parameter |
|
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. |
|
PropulsiveProperty(String inName,
Parameter inThrust,
Parameter inIsp)
Constructor for the property with thrust and isp as 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 |
ConstantThrustManeuver.addDAccDParam(SpacecraftState s,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters. |
void |
EmpiricalForce.addDAccDParam(SpacecraftState state,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters. |
void |
VariableThrustManeuver.addDAccDParam(SpacecraftState s,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters. |
| Constructors in fr.cnes.sirius.patrius.forces with parameters of type Parameter | |
|---|---|
ConstantThrustManeuver(AbsoluteDate date,
double duration,
Parameter thrust,
Parameter flowRate,
Vector3D inDirection,
MassProvider massProvider,
String partNameIn)
Constructor for a constant direction in satellite frame and constant thrust using Parameter. |
|
ConstantThrustManeuver(AbsoluteDate date,
double duration,
Parameter thrust,
Parameter flowRate,
Vector3D inDirection,
MassProvider massProvider,
String partNameIn,
Frame frameIn)
Constructor for a constant dDirection in provided frame and constant thrust using Parameter. |
|
ConstantThrustManeuver(AbsoluteDate date,
double duration,
Parameter thrust,
Parameter flowRate,
Vector3D inDirection,
MassProvider massProvider,
String partNameIn,
LOFType lofTyp)
Constructor for a constant direction in provided local orbital frame and constant thrust using Parameter
with a local orbital frame defined by its type. |
|
ConstantThrustManeuver(AbsoluteDate date,
double duration,
PropulsiveProperty engine,
Parameter flowRate,
Vector3D inDirection,
MassProvider massProvider,
TankProperty tank)
Constructor for a constant direction in satellite frame and constant thrust using Parameter,
PropulsiveProperty and TankProperty. |
|
ConstantThrustManeuver(AbsoluteDate date,
double duration,
PropulsiveProperty engine,
Parameter flowRate,
Vector3D inDirection,
MassProvider massProvider,
TankProperty tank,
Frame frameIn)
Constructor for a constant direction in satellite frame and constant thrust using Parameter,
PropulsiveProperty and TankProperty. |
|
ConstantThrustManeuver(AbsoluteDate date,
double duration,
PropulsiveProperty engine,
Parameter flowRate,
Vector3D inDirection,
MassProvider massProvider,
TankProperty tank,
LOFType lofTyp)
Constructor for a constant direction in satellite frame and constant thrust using Parameter,
PropulsiveProperty and TankProperty. |
|
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 |
ConstantThrustError.addDAccDParam(SpacecraftState state,
Parameter param,
double[] dAccdParam)
|
| 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 |
|
| 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 Parameter | |
|---|---|
Parameter |
ParameterConfiguration.getParameter()
Get parameter. |
| 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 | |
|---|---|
void |
Jacobianizer.addDAccDParam(SpacecraftState s,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters. |
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. |
| Constructors in org.orekit.propagation.numerical with parameters of type Parameter | |
|---|---|
ParameterConfiguration(Parameter parameter,
double hP)
Parameter name and step pair constructor. |
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