大攻角条件下制导弹滚转稳定控制方法

Eddy current asymmetry and transonic aerodynamic transition usually occure at a large angle-of-attack during the cross-domain flight process of guided missile, which may cause control instability and further increase miss distance. To solve the problems above, a missile roll channel dyanamics model is established, in which the strong nonlinearity of aerodynamic model, strong parameter uncertainty and strong external disturbance, and then an “observer + controller” composite control framework is proposed. This roll stabilization control framework contains a novel sliding mode disturbance observer and nonsingular terminal sliding mode. Based on this framework, a backstepping controller is proposed to compensate actuator dynamics. The stability and finite-time convergence properties of closed-loop system are verified through Lyapunov theory. Finally, the numerically simulated results demonstrate the superiority and universality of the proposed control method.