| Modifier and Type | Method and Description |
|---|---|
Parameter |
RediffusedRadiativeModel.getK0Albedo()
K0 albedo getter
|
Parameter |
RediffusedRadiativeModel.getK0Ir()
K0 infrared getter
|
| Modifier and Type | Method and Description |
|---|---|
ArrayList<Parameter> |
GlobalAeroModel.getJacobianParameters()
Get the list of all jacobian parameters supported.
|
ArrayList<Parameter> |
DragLiftModel.getJacobianParameters()
Get the list of all jacobian parameters supported.
|
ArrayList<Parameter> |
RediffusedRadiativeModel.getJacobianParameters()
Get the list of all jacobian parameters supported.
|
ArrayList<Parameter> |
AeroModel.getJacobianParameters()
Get the list of all jacobian parameters supported.
|
ArrayList<Parameter> |
DirectRadiativeModel.getJacobianParameters()
Get the list of all jacobian parameters supported.
|
| Modifier and Type | Method and Description |
|---|---|
void |
RediffusedRadiativeModel.addDAccDParamRediffusedRadiativePressure(SpacecraftState s,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives.
|
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 |
DragLiftModel.addDDragAccDParam(SpacecraftState s,
Parameter param,
double density,
Vector3D relativeVelocity,
double[] dAccdParam)
Compute acceleration derivatives with respect to 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.
|
| Constructor and Description |
|---|
DirectRadiativeModel(Assembly inAssembly,
Parameter inK0)
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).
|
| Modifier and Type | Method and Description |
|---|---|
ArrayList<Parameter> |
AeroCoeffByAoAAndMach.getParameters()
Get the supported parameters.
|
ArrayList<Parameter> |
AbstractAeroCoeff1D.getParameters()
Get the supported parameters.
|
ArrayList<Parameter> |
AeroCoeffConstant.getParameters()
Get the supported parameters.
|
| Modifier and Type | Method and Description |
|---|---|
double |
AeroCoeffByAoAAndMach.derivativeValue(Parameter p,
SpacecraftState s)
Compute the derivative value with respect to the input parameter.
|
double |
AbstractAeroCoeff1D.derivativeValue(Parameter p,
SpacecraftState s)
Compute the derivative value with respect to the input parameter.
|
double |
AeroCoeffConstant.derivativeValue(Parameter p,
SpacecraftState s)
Compute the derivative value with respect to the input parameter.
|
boolean |
AeroCoeffByAoAAndMach.isDifferentiableBy(Parameter p)
Tell if the function is differentiable by the given parameter.
|
boolean |
AbstractAeroCoeff1D.isDifferentiableBy(Parameter p)
Tell if the function is differentiable by the given parameter.
|
boolean |
AeroCoeffByAoAAndMach.supportsParameter(Parameter param)
Check if a parameter is supported.
|
boolean |
AbstractAeroCoeff1D.supportsParameter(Parameter param)
Check if a parameter is supported.
|
| Constructor and Description |
|---|
AeroCoeffConstant(Parameter aeroCoeffIn)
Constructor.
|
| Modifier and Type | Method and Description |
|---|---|
ArrayList<Parameter> |
CtCookModel.getParameters()
Get the supported parameters.
|
ArrayList<Parameter> |
CnCookModel.getParameters()
Get the supported parameters.
|
| Modifier and Type | Method and Description |
|---|---|
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.
|
| Modifier and Type | Method and Description |
|---|---|
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. |
| Modifier and Type | Method and Description |
|---|---|
double |
AeroCrossSectionProperty.getDragForceDerivativeValue(Parameter parameter,
SpacecraftState s)
Get the drag force coefficient derivative value with respect to the given parameter.
|
| Constructor and Description |
|---|
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(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.
|
| Modifier and Type | Method and Description |
|---|---|
Parameter |
VehicleSurfaceModel.getMultiplicativeFactor()
Get the multiplicative factor applied to the reference surface as a parameter.
|
| Modifier and Type | Method and Description |
|---|---|
void |
EmpiricalForce.addDAccDParam(SpacecraftState state,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters.
|
| Constructor and Description |
|---|
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. |
| Modifier and Type | Method and Description |
|---|---|
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).
|
| Constructor and Description |
|---|
DragForce(Parameter kIn,
Atmosphere atmosphereIn,
DragSensitive spacecraftIn)
Constructor with multiplicative factor k.
|
DragForce(Parameter kIn,
Atmosphere atmosphereIn,
DragSensitive spacecraftIn,
boolean computePDPos,
boolean computePDVel)
Constructor with multiplicative factor k.
|
| Modifier and Type | Method and Description |
|---|---|
void |
BalminoAttractionModel.addDAccDParam(SpacecraftState state,
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 state,
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.
|
| Constructor and Description |
|---|
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[][] cIn,
double[][] sIn)
Creates a new instance using
Parameter. |
CunninghamAttractionModel(Frame centralBodyFrame,
Parameter equatorialRadius,
Parameter mu,
double[][] cIn,
double[][] sIn,
int degreePD,
int orderPD)
Creates a new instance using
Parameter. |
DrozinerAttractionModel(Frame centralBodyFrameIn,
Parameter equatorialRadius,
Parameter mu,
double[][] cCoefs,
double[][] sCoefs)
Creates a new instance using
Parameter. |
DrozinerAttractionModel(Frame centralBodyFrameIn,
Parameter equatorialRadius,
Parameter mu,
double[][] cCoefs,
double[][] sCoefs,
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. |
| Modifier and Type | Field and Description |
|---|---|
protected Parameter |
AbstractTides.paramAe
Equatorial radius parameter.
|
protected Parameter |
AbstractTides.paramMu
Central attraction coefficient parameter.
|
| Modifier and Type | Method and Description |
|---|---|
void |
AbstractTides.addDAccDParam(SpacecraftState s,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters.
|
| Constructor and Description |
|---|
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. |
| Modifier and Type | Method and Description |
|---|---|
void |
VariablePotentialAttractionModel.addDAccDParam(SpacecraftState s,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters.
|
| Modifier and Type | Method and Description |
|---|---|
void |
ConstantThrustError.addDAccDParam(SpacecraftState state,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters.
|
void |
ContinuousThrustManeuver.addDAccDParam(SpacecraftState s,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters.
|
| Constructor and Description |
|---|
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 Errors components are expressed in provided frame. |
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 Errors components are expressed in provided frame. |
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 Errors components are expressed in provided local orbital frame. |
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 Errors components are expressed in provided local orbital frame. |
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 Errors components are expressed in spacecraft frame. |
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 Errors components are expressed in spacecraft frame. |
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 Errors components are expressed in provided frame. |
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 Errors components are expressed in provided local orbital frame. |
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 Errors components are expressed in spacecraft frame. |
| Modifier and Type | Method and Description |
|---|---|
Parameter |
RediffusedRadiationSensitive.getK0Albedo()
K0 albedo getter
|
Parameter |
RediffusedRadiationSensitive.getK0Ir()
K0 infrared getter
|
Parameter |
SolarRadiationPressureEllipsoid.getReferenceFlux()
Get the normalized reference flux parameter
|
| Modifier and Type | Method and Description |
|---|---|
void |
SolarRadiationPressureCircular.addDAccDParam(SpacecraftState s,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters.
|
void |
RediffusedRadiationPressure.addDAccDParam(SpacecraftState s,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters.
|
void |
SolarRadiationPressureEllipsoid.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.
|
| Constructor and Description |
|---|
SolarRadiationPressureCircular(Parameter refFlux,
PVCoordinatesProvider sunIn,
double equatorialRadiusIn,
RadiationSensitive spacecraftIn)
Complete constructor.
|
SolarRadiationPressureCircular(Parameter refFlux,
PVCoordinatesProvider sunIn,
double equatorialRadiusIn,
RadiationSensitive spacecraftIn,
boolean computePD)
Complete constructor.
|
SolarRadiationPressureEllipsoid(Parameter referenceFlux,
PVCoordinatesProvider sunBody,
GeometricBodyShape shape,
RadiationSensitive spacecraftModel)
Complete constructor using
Parameter. |
SolarRadiationPressureEllipsoid(Parameter referenceFlux,
PVCoordinatesProvider sunBody,
GeometricBodyShape shape,
RadiationSensitive spacecraftModel,
boolean computePD)
Complete constructor using
Parameter. |
| Modifier and Type | Method and Description |
|---|---|
void |
CoriolisRelativisticEffect.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 |
SchwarzschildRelativisticEffect.addDAccDParam(SpacecraftState s,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters.
|
| Modifier and Type | Method and Description |
|---|---|
ArrayList<Parameter> |
IParameterizable.getParameters()
Get the supported parameters.
|
ArrayList<Parameter> |
Parameterizable.getParameters()
Get the supported parameters.
|
ArrayList<Parameter> |
LinearFunction.getParameters()
Get the supported parameters.
|
ArrayList<Parameter> |
PiecewiseFunction.getParameters()
Get the supported parameters.
|
ArrayList<Parameter> |
ConstantFunction.getParameters()
Get the supported parameters.
|
| Modifier and Type | Method and Description |
|---|---|
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 |
IParamDiffFunction.derivativeValue(Parameter p,
SpacecraftState s)
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.
|
double |
PiecewiseFunction.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.
|
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 |
IParameterizable.supportsParameter(Parameter param)
Check if a parameter is supported.
|
boolean |
Parameterizable.supportsParameter(Parameter param)
Check if a parameter is supported.
|
boolean |
ParamDiffFunction.supportsParameter(Parameter p)
Check if a parameter is supported.
|
| Modifier and Type | Method and Description |
|---|---|
protected void |
JacobiansParameterizable.addJacobiansParameter(ArrayList<Parameter> params)
Add a list of parameters in the jacobians parameters list.
|
| Constructor and Description |
|---|
ConstantFunction(Parameter param)
Simple constructor with a given
Parameter. |
JacobiansParameterizable(Parameter... params)
Simple constructor.
|
LinearFunction(AbsoluteDate t0,
Parameter slope,
Parameter zeroValue)
|
Parameterizable(Parameter... params)
Simple constructor.
|
| Constructor and Description |
|---|
JacobiansParameterizable(ArrayList<Parameter> paramList)
Simple constructor.
|
Parameterizable(ArrayList<Parameter> paramList)
Simple constructor.
|
| Modifier and Type | Method and Description |
|---|---|
Parameter |
ParameterConfiguration.getParameter()
Get parameter.
|
| Modifier and Type | Method and Description |
|---|---|
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.
|
| Modifier and Type | Method and Description |
|---|---|
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.
|
| Constructor and Description |
|---|
ParameterConfiguration(Parameter parameter,
double hPIn)
Parameter name and step pair constructor.
|
| Modifier and Type | Method and Description |
|---|---|
ArrayList<Parameter> |
StelaAeroModel.getJacobianParameters()
Get the list of all jacobian parameters supported.
|
| Modifier and Type | Method and Description |
|---|---|
void |
StelaAeroModel.addDDragAccDParam(SpacecraftState s,
Parameter param,
double density,
Vector3D relativeVelocity,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters (the ballistic coefficient).
|
| Constructor and Description |
|---|
SolarRadiationWrench(Parameter distance,
Parameter pressure,
Parameter sunRadius,
PVCoordinatesProvider sunBody,
GeometricBodyShape shape,
RadiationWrenchSensitive spacecraftModel)
Complete constructor using
Parameter. |
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