Design of Missile Attitude Constraint Control under New Disturbance Observation Compensation

An output information-based constrained control method with disturbance compensation is proposed for missiles subjected to attitude constraints. Firstly, the attitude model of missile is transferred to the matched representation, and a novel observer based on output and its integral information is presented to precisely estimate the unknown state and disturbances simultaneously in finite time. Then, the constrained attitude control method is designed using the backstepping approach and second-order filter technique. As consequence, the bounded stability of the closed-loop system is achieved and the constraints will not be violated. Finally, the numerical simulations for the missile attitude system verify the effectiveness of the proposed method.