Interface FieldAbstractIntegratedPropagator.MainStateEquations<T extends org.hipparchus.RealFieldElement<T>>

  • Enclosing class:
    FieldAbstractIntegratedPropagator<T extends org.hipparchus.RealFieldElement<T>>

    public static interface FieldAbstractIntegratedPropagator.MainStateEquations<T extends org.hipparchus.RealFieldElement<T>>
    Differential equations for the main state (orbit, attitude and mass).
    • Method Detail

      • init

        void init​(FieldSpacecraftState<T> initialState,
                  FieldAbsoluteDate<T> target)
        Initialize the equations at the start of propagation. This method will be called before any calls to computeDerivatives(FieldSpacecraftState).

        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

        T[] computeDerivatives​(FieldSpacecraftState<T> state)
        Compute differential equations for main state.
        Parameters:
        state - current state
        Returns:
        derivatives of main state