Class DSSTPartialDerivativesEquations

    • Constructor Detail

      • DSSTPartialDerivativesEquations

        public DSSTPartialDerivativesEquations​(String name,
                                               DSSTPropagator propagator,
                                               PropagationType propagationType)
        Deprecated.
        Simple constructor.

        Upon construction, this set of equations is automatically added to the propagator by calling its AbstractIntegratedPropagator.addAdditionalDerivativesProvider(AdditionalDerivativesProvider) method. So there is no need to call this method explicitly for these equations.

        Parameters:
        name - name of the partial derivatives equations
        propagator - the propagator that will handle the orbit propagation
        propagationType - type of the orbit used for the propagation (mean or osculating)
    • Method Detail

      • getName

        public String getName()
        Deprecated.
        Get the name of the additional derivatives (which will become state once integrated).
        Specified by:
        getName in interface AdditionalDerivativesProvider
        Specified by:
        getName in interface AdditionalEquations
        Returns:
        name of the additional state (names containing "orekit" with any case are reserved for the library internal use)
      • getDimension

        public int getDimension()
        Deprecated.
        Get the dimension of the generated derivative.
        Specified by:
        getDimension in interface AdditionalDerivativesProvider
        Returns:
        dimension of the generated
      • setInitialJacobians

        public SpacecraftState setInitialJacobians​(SpacecraftState s0)
        Deprecated.
        Set the initial value of the Jacobian with respect to state and parameter.

        This method is equivalent to call setInitialJacobians(SpacecraftState, double[][], double[][]) with dYdY0 set to the identity matrix and dYdP set to a zero matrix.

        The force models parameters for which partial derivatives are desired, must have been selected before this method is called, so proper matrices dimensions are used.

        Parameters:
        s0 - initial state
        Returns:
        state with initial Jacobians added
      • setInitialJacobians

        public SpacecraftState setInitialJacobians​(SpacecraftState s1,
                                                   double[][] dY1dY0,
                                                   double[][] dY1dP)
        Deprecated.
        Set the initial value of the Jacobian with respect to state and parameter.

        The returned state must be added to the propagator (it is not done automatically, as the user may need to add more states to it).

        The force models parameters for which partial derivatives are desired, must have been selected before this method is called, and the dY1dP matrix dimension must be consistent with the selection.

        Parameters:
        s1 - current state
        dY1dY0 - Jacobian of current state at time t₁ with respect to state at some previous time t₀ (must be 6x6)
        dY1dP - Jacobian of current state at time t₁ with respect to parameters (may be null if no parameters are selected)
        Returns:
        state with initial Jacobians added
      • computeDerivatives

        public double[] computeDerivatives​(SpacecraftState s,
                                           double[] pDot)
        Deprecated.
        Compute the derivatives related to the additional state parameters.

        When this method is called, the spacecraft state contains the main state (orbit, attitude and mass), all the states provided through the additional state providers registered to the propagator, and the additional state integrated using this equation. It does not contains any other states to be integrated alongside during the same propagation.

        Specified by:
        computeDerivatives in interface AdditionalEquations
        Parameters:
        s - current state information: date, kinematics, attitude, and additional state
        pDot - placeholder where the derivatives of the additional parameters should be put
        Returns:
        cumulative effect of the equations on the main state (may be null if equations do not change main state at all)
      • derivatives

        @Deprecated
        public double[] derivatives​(SpacecraftState state)
        Deprecated.
        Compute the derivatives related to the additional state parameters.
        Specified by:
        derivatives in interface AdditionalDerivativesProvider
        Parameters:
        state - current state information: date, kinematics, attitude, and additional states this equations depend on (according to the yield method)
        Returns:
        computed derivatives
      • combinedDerivatives

        public CombinedDerivatives combinedDerivatives​(SpacecraftState s)
        Deprecated.
        Compute the derivatives related to the additional state (and optionally main state increments).

        As of 11.2, there is a default implementation that calls the deprecated AdditionalDerivativesProvider.derivatives(SpacecraftState) method. This has been done for backward compatibility only and will be removed in 12.0.

        Specified by:
        combinedDerivatives in interface AdditionalDerivativesProvider
        Parameters:
        s - current state information: date, kinematics, attitude, and additional states this equations depend on (according to the yield method)
        Returns:
        computed combined derivatives, which may include some incremental coupling effect to add to main state derivatives