Design of missile attitude controller based on backstepping method

A new approach of missile attitude controller using backstepping design method is proposed to improve the robustness of nonlinear system. In this approach, the backstepping design method is introduced from step 1 to step n in the design procedure firstly. The missile attitudes are taken as the control objects of systems by the proposed attitude controller, and according to the given reference signals of pitch angle, yaw angle and roll angle, the relative rudder deviation inputs are derived from backstepping controller. So the missile can fly along the trace in decided attitude angles. The angle of attack and sideslip angle can not be measured precisely in fact, the proposed controller is different from the previous backstepping designs which used angle of attack and sideslip angles as control subjects. Finally the numerical simulation results demonstrate the feasibility of the proposed controller.