Design of Nonlinear Optimal Control System for Aircraft with Thrust Vector

For the forth generation fighter aircraft, with thrust vector is one of the key technique characters. In condition of High AOA (Angle of attack), the dynamic of aircraft has strong nonlinear characteristic, and the general effectors lose the maneuver efficiency or get poorly, most control energy will be produced by the thrust vector, so new type of control law must be found. This control law should not only overcome those problems but also satisfy requirements of the forth generation aircraft. Nonlinear optimal control theory has merit on solving those problems. In this paper linearization method at Sampling Point and Receding Horizon Optimal (RHO) Control is brought forward. This control system can solve problem of a class of affine nonlinear system. Simulation result shows that the system can solve those problems perfectly and accord with the requirements of the forth generation fighter aircraft.