直接力/气动力拦截弹复合逻辑与复合控制系统设计

Blended Logic and Control System Design for an Interception Missile with Lateral Thrust and Aerodynamic Combination

以大气层内拦截弹直接侧向力和气动力的复合控制系统为研究对象,首先设计了轨控复合控制逻辑,然后建立了复合控制模型,并将复合系统分解为直接侧向力子系统和气动力子系统,用经典控制理论设计了气动力子系统,用模糊控制理论设计了直接力子系统。仿真结果表明:所设计的复合控制逻辑合理;基于模糊逻辑的直接力子系统可有效避免点燃发动机数量过多而需要反向点火情况的发生;与气动力系统相比,复合控制系统性能有较大提高。

The blended control system for an interception missile with lateral thrust and aerodynamic com- bination is studied in this paper. At first, the blended control logics for diverting control missile are designed. And then, the blended control model is established. Further more the blended system is divided into the lateral thrust subsystem and the aerodynamic subsystem. Here, the aerodynamic subsystem is designed in classical control theory, while the lateral thrust subsystem is designed in fuzzy control theory. The simulation results show that the blended logic is appropriate for the blended system. And the lateral subsystem based on fuzzy logic can effectively avoid the situation that the firing number of lateral thrust is so large that it need fire reverse jet thrusts. Compared with aerodynamic subsystem, the performance of the blended system is improved greatly.