直接力/气动力复合控制导弹自适应模糊滑模控制

Adaptive fuzzy sliding mode control for reaction-jet and aerodynamics compound control missile

针对采用直接力/气动力复合控制导弹所具有的强耦合非线性等特性,提出了一种基于自适应模糊滑模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,对大攻角飞行过程中导弹动力学系统存在的非线性特性进行逼近,并利用变结构控制对外界干扰的强鲁棒性,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,所设计的控制方法对大过载指令有较好的跟踪效果,对模型不确定性和外界干扰也具有较好的鲁棒性.由于采用直接力/气动力复合控制,有效的减小了气动舵偏角,避免了气动舵的饱和.

A missile autopilot design method based on adaptive fuzzy sliding mode control （AFSMC） was proposed for reaction-jet and aerodynamics compound control missile with nonlinearity and strong coupling. The universal approximation ability of adaptive fuzzy system was used to approximate the nonlinear function in missile dynamics equation during the flight of high angle of attack. And because the sliding mode control was robustness to external disturbance strongly, the sliding mode surface of the error system was constructed to overcome the influence of approximation error and external disturbance so that the actual overload can track the maneuvering command with high precision. Simulation results show that the missile autopilot designed in this paper not only can track large overload command with higher precision than traditional methods, but also is robust to model uncertainty and external disturbance strongly. After employing the reaction-jet and aerodynamics compound control, the aerodynamic fin deflection is decreased greatly. Therefore, the aerodynamic fin deflection saturation is avoided.