public class MultiPartialDerivativesEquations extends AbstractPartialDerivativesEquations
additional equations
computing the partial derivatives
of the state (orbit) with respect to initial state and force models parameters.
This set of equations are automatically added to a numerical propagator
in order to
compute partial derivatives of the orbit along with the orbit itself. This is useful for example in orbit
determination applications.
Constructor and Description |
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MultiPartialDerivativesEquations()
Empty constructor for
Externalizable use. |
MultiPartialDerivativesEquations(String nameIn,
MultiNumericalPropagator propagatorIn,
String satId)
Simple constructor.
|
Modifier and Type | Method and Description |
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protected List<ForceModel> |
getForceModels()
Returns the propagator force models.
|
protected Frame |
getFrame()
Returns the propagator frame.
|
protected OrbitType |
getOrbitType()
Returns the propagator orbit type.
|
protected PositionAngle |
getPositionAngle()
Returns the propagator position angle.
|
buildAdditionalState, clearSelectedParameters, computeDerivatives, computeSecondDerivatives, concatenate, contains, extractY, extractYDot, getAvailableParameters, getFirstOrderDimension, gethPos, getJacobiansProviders, getMapper, getName, getParamDim, getSecondOrderDimension, getSelectedParameters, isDirty, isInitialJacobians, readExternal, selectParamAndStep, selectParameters, selectParameters, setDirty, setHPos, setInitialJacobians, setInitialJacobians, setInitialJacobians, setInitialJacobians, setSteps, writeExternal
public MultiPartialDerivativesEquations()
Externalizable
use.public MultiPartialDerivativesEquations(String nameIn, MultiNumericalPropagator propagatorIn, String satId)
Upon construction, this set of equations is automatically added to the propagator by calling its
NumericalPropagator.addAdditionalEquations(AdditionalEquations)
method. So there is no need to call this
method explicitly for these equations.
nameIn
- name of the partial derivatives equationspropagatorIn
- the propagator that will handle the orbit propagationsatId
- satellite IDprotected List<ForceModel> getForceModels()
getForceModels
in class AbstractPartialDerivativesEquations
protected Frame getFrame()
getFrame
in class AbstractPartialDerivativesEquations
protected OrbitType getOrbitType()
getOrbitType
in class AbstractPartialDerivativesEquations
protected PositionAngle getPositionAngle()
getPositionAngle
in class AbstractPartialDerivativesEquations
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