| 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 |
AeroCoeffConstant.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.
|
boolean |
AeroCoeffConstant.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 | Field and Description |
|---|---|
protected Parameter |
AbstractGravityModel.paramMu
Central attraction coefficient parameter.
|
| Modifier and Type | Method and Description |
|---|---|
Parameter |
AbstractBodyAttraction.getMultiplicativeFactorParameter()
Get the force multiplicative factor parameter
|
Parameter |
NewtonianGravityModel.getMuParameter()
Returns the gravitational coefficient as a parameter.
|
| Modifier and Type | Method and Description |
|---|---|
void |
AbstractBodyAttraction.addDAccDParam(SpacecraftState state,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters.
|
void |
AbstractBodyAttraction.addDAccDParam(Vector3D pos,
Frame frame,
AbsoluteDate date,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters.
|
| Constructor and Description |
|---|
AbstractBodyAttraction(GravityModel gravityModelIn,
boolean computePD,
Parameter k)
Simple constructor.
|
AbstractGravityModel(Parameter mu)
Constructor.
|
AbstractHarmonicGravityModel(Parameter mu)
Constructor.
|
BalminoGravityModel(Frame frame,
Parameter ae,
Parameter mu,
double[][] cCoefs,
double[][] sCoefs)
Create an instance of a normalized gravity computation model using normalized coefficients.
|
BalminoGravityModel(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.
|
BalminoGravityModel(Frame frame,
Parameter ae,
Parameter mu,
double[][] cCoefs,
double[][] sCoefs,
int degreePD,
int orderPD,
boolean centralTermContributionIn)
Create an instance of a normalized gravity computation model using normalized coefficients.
|
CunninghamGravityModel(Frame centralBodyFrame,
Parameter equatorialRadius,
Parameter mu,
double[][] cIn,
double[][] sIn)
Creates a new instance using
Parameter. |
CunninghamGravityModel(Frame centralBodyFrame,
Parameter equatorialRadius,
Parameter mu,
double[][] cIn,
double[][] sIn,
int degreePD,
int orderPD)
Creates a new instance using
Parameter. |
CunninghamGravityModel(Frame centralBodyFrame,
Parameter equatorialRadius,
Parameter mu,
double[][] cIn,
double[][] sIn,
int degreePD,
int orderPD,
boolean centralTermContributionIn)
Creates a new instance using
Parameter. |
DirectBodyAttraction(GravityModel gravityModelIn,
boolean computePD,
Parameter k)
Simple constructor.
|
DrozinerGravityModel(Frame centralBodyFrameIn,
Parameter equatorialRadius,
Parameter mu,
double[][] cCoefs,
double[][] sCoefs)
Creates a new instance using
Parameter. |
DrozinerGravityModel(Frame centralBodyFrameIn,
Parameter equatorialRadius,
Parameter mu,
double[][] cCoefs,
double[][] sCoefs,
boolean computePDPos,
boolean computePDVel)
Creates a new instance using
Parameter. |
DrozinerGravityModel(Frame centralBodyFrameIn,
Parameter equatorialRadius,
Parameter mu,
double[][] cCoefs,
double[][] sCoefs,
boolean computePDPos,
boolean computePDVel,
boolean centralTermContributionIn)
Creates a new instance using
Parameter. |
NewtonianGravityModel(Frame centralBodyFrame,
Parameter mu)
Simple constructor using
Parameter.Note that the body frame is used for translation only. |
NewtonianGravityModel(Frame centralBodyFrame,
Parameter mu,
boolean computePD)
Simple constructor using
Parameter.Note that the body frame is used for translation only. |
ThirdBodyAttraction(GravityModel gravityModelIn,
boolean computePD,
Parameter k)
Simple constructor.
|
| 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. |
PoleTides(Frame centralBodyFrame,
Parameter equatorialRadius,
Parameter mu,
boolean solidTidesFlag,
boolean oceanicTidesFlag)
Constructor.
|
PoleTides(Frame centralBodyFrame,
Parameter equatorialRadius,
Parameter mu,
boolean solidTidesFlag,
boolean oceanicTidesFlag,
boolean computePD)
Constructor.
|
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 |
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 |
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 |
| Modifier and Type | Method and Description |
|---|---|
Parameter |
RediffusedRadiationSensitive.getK0Albedo()
K0 albedo getter
|
Parameter |
RediffusedRadiationSensitive.getK0Ir()
K0 infrared getter
|
Parameter |
SolarRadiationPressure.getReferenceFlux()
Getter for the parameter representing the reference flux normalized for a 1m distance (N).
|
| Modifier and Type | Method and Description |
|---|---|
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.
|
| Constructor and Description |
|---|
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,
Frame 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.
|
| 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 | Field and Description |
|---|---|
protected Map<Parameter,Function<SpacecraftState,Double>> |
LinearCombinationFunction.functions
Map describing the functions.
|
| Modifier and Type | Method and Description |
|---|---|
Parameter |
Parameter.copy()
Performs a shallow copy of this parameter (the references to the field descriptors and the
mapped values are preserved).
|
| Modifier and Type | Method and Description |
|---|---|
static List<Parameter> |
ParameterUtils.buildOrbitalParameters(OrbitType orbitType,
PositionAngle positionAngle)
Builds the parameters associated with a given orbit type and position angle type, each one
representing one of the orbital coordinates.
|
static List<Parameter> |
ParameterUtils.extractParameters(Collection<Parameter> parameters,
FieldDescriptor<?> fieldDescriptor)
Extracts the parameters associated with a given field descriptor.
|
static <T> List<Parameter> |
ParameterUtils.extractParameters(Collection<Parameter> parameters,
FieldDescriptor<T> fieldDescriptor,
Predicate<T> fieldFilter)
Extracts the parameters associated with a given field descriptor if the mapped value matches
the specified predicate.
|
ArrayList<Parameter> |
IParameterizable.getParameters()
Get the supported parameters.
|
ArrayList<Parameter> |
Parameterizable.getParameters()
Get the supported parameters.
|
ArrayList<Parameter> |
NthOrderPolynomialFunction.getParameters()
Return the function N parameters in this following order : a0, a1, a2,
...
|
ArrayList<Parameter> |
LinearCombinationFunction.getParameters()
Get the supported parameters.
|
ArrayList<Parameter> |
LinearFunction.getParameters()
Return the function parameters in this following order: [a0, a1].
|
ArrayList<Parameter> |
ConstantFunction.getParameters()
Return the function parameter [a0] (also called [value]) stored in a list.
|
| Modifier and Type | Method and Description |
|---|---|
protected void |
Parameterizable.addAllParameters(Parameter... params)
Add the given parameters in the internal list.
|
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 the given parameter in the internal list.
|
double |
IntervalsFunction.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 |
LinearCombinationFunction.derivativeValue(Parameter p,
SpacecraftState s)
Compute the derivative value with respect to the input parameter.
|
boolean |
IntervalsFunction.isDifferentiableBy(Parameter p)
Tell if the function is differentiable by the given parameter.
|
boolean |
IParamDiffFunction.isDifferentiableBy(Parameter p)
Tell if the function is differentiable by the given parameter.
|
boolean |
LinearCombinationFunction.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 |
LinearCombinationFunction.supportsParameter(Parameter param)
Check if a parameter is supported.
|
| Modifier and Type | Method and Description |
|---|---|
protected void |
Parameterizable.addAllParameters(Collection<Parameter> params)
Add the given parameters in the internal list.
|
static <T> boolean |
ParameterUtils.addFieldIfAbsentToParameters(Collection<Parameter> parameters,
FieldDescriptor<T> fieldDescriptor,
T fieldValue)
Adds a given field descriptor to multiple parameters and maps it to the specified value
(existing values are overwritten when the field descriptor is already associated with a
parameter; parameter descriptors which are not currently mutable are ignored).
|
static <T> boolean |
ParameterUtils.addFieldToParameters(Collection<Parameter> parameters,
FieldDescriptor<T> fieldDescriptor,
T fieldValue)
Adds a given field descriptor to multiple parameters and maps it to the specified value
(existing values are overwritten when the field descriptor is already associated with a
parameter; parameter descriptors which are not currently mutable are ignored).
|
protected void |
JacobiansParameterizable.addJacobiansParameter(ArrayList<Parameter> params)
Add a list of parameters in the jacobians parameters list.
|
static String |
ParameterUtils.concatenateParameterNames(Collection<Parameter> parameters,
String nameSeparator,
String fieldSeparator,
boolean reverseOrder)
Concatenates the names of multiple parameters.
|
static List<ParameterDescriptor> |
ParameterUtils.extractParameterDescriptors(Collection<Parameter> parameters)
Extracts the parameter descriptors from all the provided parameters and returns them into a
new list.
|
static List<Parameter> |
ParameterUtils.extractParameters(Collection<Parameter> parameters,
FieldDescriptor<?> fieldDescriptor)
Extracts the parameters associated with a given field descriptor.
|
static <T> List<Parameter> |
ParameterUtils.extractParameters(Collection<Parameter> parameters,
FieldDescriptor<T> fieldDescriptor,
Predicate<T> fieldFilter)
Extracts the parameters associated with a given field descriptor if the mapped value matches
the specified predicate.
|
static void |
ParameterUtils.removeFieldFromParameters(Collection<Parameter> parameters,
FieldDescriptor<?> fieldDescriptor)
Removes a given field descriptor from multiple parameters.
|
| Constructor and Description |
|---|
ConstantFunction(Parameter param)
Constructor of a constant function f = a0 using the input parameter.
|
JacobiansParameterizable(Parameter... params)
Simple constructor.
|
LinearFunction(AbsoluteDate t0,
Parameter a0,
Parameter a1)
Constructor of a linear function: f = a0 + a1 * (t - t0) using the input a1 (slope)
and a0 (zeroValue) parameters and initial date.
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NthOrderPolynomialFunction(AbsoluteDate t0,
Parameter... params)
Constructor of a linear polynomial function of order N, defined such as:
f = a0 + a1 * (t - t0) + a2 * (t - t0)^2 + ..., with the first specified parameter
represents a0, the second represents a1, etc.
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Parameterizable(Parameter... params)
Simple constructor to add in the internal list the given parameters.
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| Constructor and Description |
|---|
JacobiansParameterizable(ArrayList<Parameter> paramList)
Simple constructor.
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LinearCombinationFunction(Map<Parameter,Function<SpacecraftState,Double>> functions)
Constructor to initialize the function.
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Parameterizable(ArrayList<Parameter> paramList)
Simple constructor to add in the internal list the parameters contained in the given list.
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| Modifier and Type | Method and Description |
|---|---|
Parameter |
ParameterConfiguration.getParameter()
Get parameter.
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| Modifier and Type | Method and Description |
|---|---|
List<Parameter> |
AbstractPartialDerivativesEquations.getAvailableParameters()
Get the names of the available parameters in the propagator.
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ArrayList<Parameter> |
JacobianParametersProvider.getJacobianParameters()
Get the list of all jacobian parameters supported.
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List<Parameter> |
JacobiansMapper.getParametersList()
Get parameters list.
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| Modifier and Type | Method and Description |
|---|---|
void |
Jacobianizer.addDAccDParam(SpacecraftState s,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters.
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boolean |
AbstractPartialDerivativesEquations.contains(Parameter parameter)
Check if the parameter is already in the selectedParameters list
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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 |
JacobiansMapper.getParametersJacobian(Parameter parameter,
SpacecraftState state,
double[] dYdP,
OrbitType orbitTypeIn,
PositionAngle angleTypeIn,
Frame frameIn)
Get the Jacobian with respect to provided parameter
parameter. |
double[] |
JacobiansMapper.getParametersJacobian(Parameter parameter,
SpacecraftState state,
OrbitType orbitTypeIn,
PositionAngle angleTypeIn,
Frame frameIn)
Get the Jacobian with respect to provided parameter
parameter. |
void |
AbstractPartialDerivativesEquations.selectParamAndStep(Parameter parameter,
double hP)
Select the parameters to consider for Jacobian processing.
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void |
AbstractPartialDerivativesEquations.selectParameters(Parameter... parameters)
Select the parameters to consider for Jacobian processing.
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SpacecraftState |
AbstractPartialDerivativesEquations.setInitialJacobians(SpacecraftState s,
Parameter parameter,
double[] dY1dP)
Set the initial value of the Jacobian with respect to state.
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| Modifier and Type | Method and Description |
|---|---|
void |
AbstractPartialDerivativesEquations.concatenate(List<Parameter> parameters)
Concatenate a list of parameters with the already existing selectedParameters list
Check that the parameter to add is not already on the list (to avoid problems with the step)
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void |
AbstractPartialDerivativesEquations.selectParameters(List<Parameter> parameters)
Select the parameters to consider for Jacobian processing.
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| Constructor and Description |
|---|
ParameterConfiguration(Parameter parameter,
double hPIn)
Parameter name and step pair constructor.
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| Constructor and Description |
|---|
JacobiansMapper(String nameIn,
List<Parameter> list,
OrbitType orbitTypeIn,
PositionAngle angleTypeIn,
Frame frame)
Simple constructor.
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| Modifier and Type | Method and Description |
|---|---|
ArrayList<Parameter> |
BentModel.getParameters()
Get the supported parameters.
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| Modifier and Type | Method and Description |
|---|---|
double |
BentModel.derivativeValue(Parameter p,
AbsoluteDate date,
Vector3D satellite,
Frame satFrame)
Compute the derivative value with respect to the input parameter.
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double |
IonosphericCorrection.derivativeValue(Parameter p,
AbsoluteDate date,
Vector3D satellite,
Frame satFrame)
Compute the derivative value with respect to the input parameter.
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boolean |
BentModel.isDifferentiableBy(Parameter p)
Tell if the function is differentiable by the given parameter.
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boolean |
IonosphericCorrection.isDifferentiableBy(Parameter p)
Tell if the function is differentiable by the given parameter.
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boolean |
BentModel.supportsParameter(Parameter param)
Check if a parameter is supported.
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| Modifier and Type | Method and Description |
|---|---|
ArrayList<Parameter> |
MariniMurrayModel.getParameters()
Get the supported parameters.
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ArrayList<Parameter> |
FixedDelayModel.getParameters()
Get the supported parameters.
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ArrayList<Parameter> |
SaastamoinenModel.getParameters()
Get the supported parameters.
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ArrayList<Parameter> |
AzoulayModel.getParameters()
Get the supported parameters.
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| Modifier and Type | Method and Description |
|---|---|
double |
MariniMurrayModel.derivativeValue(Parameter p,
double elevation)
Compute the derivative value with respect to the input parameter.
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double |
TroposphericCorrection.derivativeValue(Parameter p,
double elevation)
Compute the derivative value with respect to the input parameter.
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double |
FixedDelayModel.derivativeValue(Parameter p,
double elevation)
Compute the derivative value with respect to the input parameter.
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double |
SaastamoinenModel.derivativeValue(Parameter p,
double elevation)
Compute the derivative value with respect to the input parameter.
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double |
AzoulayModel.derivativeValue(Parameter p,
double elevation)
Compute the derivative value with respect to the input parameter.
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boolean |
MariniMurrayModel.isDifferentiableBy(Parameter p)
Tell if the function is differentiable by the given parameter.
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boolean |
TroposphericCorrection.isDifferentiableBy(Parameter p)
Tell if the function is differentiable by the given parameter.
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boolean |
FixedDelayModel.isDifferentiableBy(Parameter p)
Tell if the function is differentiable by the given parameter.
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boolean |
SaastamoinenModel.isDifferentiableBy(Parameter p)
Tell if the function is differentiable by the given parameter.
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boolean |
AzoulayModel.isDifferentiableBy(Parameter p)
Tell if the function is differentiable by the given parameter.
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boolean |
MariniMurrayModel.supportsParameter(Parameter param)
Check if a parameter is supported.
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boolean |
FixedDelayModel.supportsParameter(Parameter param)
Check if a parameter is supported.
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boolean |
SaastamoinenModel.supportsParameter(Parameter param)
Check if a parameter is supported.
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boolean |
AzoulayModel.supportsParameter(Parameter param)
Check if a parameter is supported.
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| Modifier and Type | Method and Description |
|---|---|
ArrayList<Parameter> |
StelaAeroModel.getJacobianParameters()
Get the list of all jacobian parameters supported.
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| 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).
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| Constructor and Description |
|---|
SolarRadiationWrench(Parameter distance,
Parameter pressure,
Parameter sunRadius,
PVCoordinatesProvider sunBody,
BodyShape shape,
RadiationWrenchSensitive spacecraftModel)
Complete constructor using
Parameter. |
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