Interface AbstractIntegratedPropagator.MainStateEquations

  • Enclosing class:
    AbstractIntegratedPropagator

    public static interface AbstractIntegratedPropagator.MainStateEquations
    Differential equations for the main state (orbit, attitude and mass).
    • Method Detail

      • init

        default void init​(SpacecraftState initialState,
                          AbsoluteDate target)
        Initialize the equations at the start of propagation. This method will be called before any calls to computeDerivatives(SpacecraftState).

        The default implementation of this method does nothing.

        Parameters:
        initialState - initial state information at the start of propagation.
        target - date of propagation. Not equal to initialState.getDate().
      • computeDerivatives

        double[] computeDerivatives​(SpacecraftState state)
        Compute differential equations for main state.
        Parameters:
        state - current state
        Returns:
        derivatives of main state