Attitude control of missile via Fliess expansion and model predictive control

This paper considers the attitude control of missile. We convert the problem into an output tracking one of nonlinear systems via control with finite admissible values. First, the Fliess functional expansion is used to describe the outputs. Then under piece-wise admissible value control and the quadratic criteria, the optimal control is obtained using model predictive control. The method developed is used to the attitude control of missile. Simulation results show the effectiveness of the proposed method.