Abstract
This paper presents a novel predictive sliding mode control for hypersonic vehicle by means of feedback linearization. First, the six degree-of-freedom rotational model of the hypersonic vehicle in three channels is presented and decoupled using feedback linearization control to facilitate the design of control system. Then, the sliding mode surface chosen as a combination of the tracking error and its higher order derivatives is predicted and incorporated into the quadratic performance index of the predictive control. The predictive sliding control law with an explicitly analytical form could be derived by minimizing the performance index which attenuates the undesirable chattering phenomenon due to the switching of sliding mode control law and avoids the large online computational issue of the predictive control. The stability of the designed control system could be demonstrated via Lyapunov stability theorem. Finally, simulation results demonstrate the effectiveness and robustness of the proposed attitude control scheme.
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