基于自适应模糊滑模退步控制的直接力/气动力复合控制导弹自动驾驶仪设计

Reaction-jet and Aerodynamics Compound Control Missile Autopilot Design Based on Adaptive Fuzzy Sliding Mode Control via Backstepping

针对直接力/气动力复合控制导弹所具有的强耦合非线性特性,提出了一种基于自适应模糊滑模退步控制的自动驾驶仪设计方法。该方法利用自适应模糊系统所具有的万能逼近特性,对大迎角飞行过程中导弹动力学方程中存在的非线性函数进行逼近,并利用变结构控制所具有对干扰的强鲁棒性,构造误差系统滑模面,克服了逼近误差和外界干扰对控制系统的影响,实现了对大机动指令的精确跟踪。仿真结果表明,所设计的自动驾驶仪对过载指令有良好的跟踪效果,对模型不确定性和外界干扰具有鲁棒性。

Aim at nonlinearity and strong couple of reaction-jet and aerodynamics compound control missile, a missile autopilot design method based on adaptive fuzzy sliding mode control （AFSMC） via backstepping is proposed. The universal approximation ability of adaptive fuzzy system is used to approximate the nonlinear function in missile dynamics equations during the flight at high angle of attack. And because the sliding mode control is robust to external disturbance strongly, the sliding mode surface of the error system is constructed, and thus the effects of approximation error and external disturbance is overcome so that the missile can track the maneuvering overload command with high precision. Simulation results show that the missile autopilot design method proposed not only can track command with higher precision than traditional method, but also is robust to model uncertainty and external disturbance strongly.