飞航导弹自动驾驶仪系统控制方案研究  

Analysis for Control Method in Autopilot System of Aerodynamics Missile

作　　者：马治明[1] 王雪梅[1] 易志虎[1] 

机构地区：[1]第二炮兵工程学院,陕西西安710025

出　　处：《计算机测量与控制》2009年第2期357-359,共3页Computer Measurement &Control

摘　　要：为了克服飞航导弹运动过程中的非线性、时变性和不确定性对自动驾驶仪系统性能的不良影响,进一步提高导弹的飞行质量,对自动驾驶仪系统及其采用的控制方案进行了研究;首先对系统的整体结构进行了分析,然后在介绍经典PID方案的基础上,分别采用模糊自调整PID方案和神经网络自适应PID方案设计了导弹姿态运动控制器,最后进行了仿真实验;仿真结果的对比展示了所设计控制器良好的品质,验证了将模糊控制和神经网络应用于飞航导弹自动控制中的可行性和有效性,为其它非线性控制理论与导弹传统控制相结合以进一步提高导弹控制系统的性能奠定了基础。To overcome the bad effect resulting from the nonlinearity, time--variability and uncertainty on autopilot system performance during the motion process of aerodynamics missile, and to further improve the flight quality of missile, the autopilot system and used control method are researched. Firstly the integrant structure of system is discussed; then based on introducing the traditional PID method, controllers for missile attitude motion are designed respectively using fuzzy self-- turning PID method and neural network self-- adaptive PID method; at last a simulation experiment is finished. By comparing the simulation results that the designed controllers have good qualities is showed, and the feasibility and validity of applying fuzzy control and neural network into automatic control of aerodynamics missile is confirmed, and the base that other nonlinear control theory can be combined with the traditional control for missile to further improve the per formance of missile control system is established.

关 键 词：飞航导弹 自动驾驶仪系统 控制方案 应用 

分 类 号：TJ765.23[兵器科学与技术—武器系统与运用工程]