Class TLEPartialDerivativesEquations


  • @Deprecated
    public class TLEPartialDerivativesEquations
    extends Object
    Deprecated.
    Set of additional equations computing the partial derivatives of the state (orbit) with respect to initial state.

    This set of equations are automatically added to an analytical propagator in order to compute partial derivatives of the orbit along with the orbit itself. This is useful for example in orbit determination applications.

    The partial derivatives with respect to initial state are dimension 6 (orbit only).

    Since:
    11.0
    Author:
    Bryan Cazabonne, Thomas Paulet
    • Constructor Detail

      • TLEPartialDerivativesEquations

        public TLEPartialDerivativesEquations​(String name,
                                              TLEPropagator propagator)
        Deprecated.
        Simple constructor.

        Instance regrouping equations to compute derivatives.

        Parameters:
        name - name of the partial derivatives equations
        propagator - the propagator that will handle the orbit propagation
    • Method Detail

      • getName

        public String getName()
        Deprecated.
        Get the name of the additional state.
        Returns:
        name of the additional state
      • 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).

        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