基于超稳定理论的导弹电动舵机自适应控制方法研究  

Adaptive control of missile electronic actuator based on hyper stability theory

作　　者：朱宇光[1] 曹彪[2] 汪浩[1] 

机构地区：[1]中国人民解放军92941部队 [2]海军航空工程学院基础实验部

出　　处：《机电工程》2012年第6期693-695,共3页Journal of Mechanical & Electrical Engineering

基　　金：国家自然科学基金资助项目(61174031)

摘　　要：舵机是导弹控制系统的执行装置,其性能直接影响导弹的作战能力。电动舵机在不同飞行条件下呈现出非线性特点,传统的PID控制方法不能满足其性能要求,针对这一问题提出了一种基于波波夫超稳定理论的自适应控制方法。首先根据电动舵机的工作原理,建立了舵机的状态描述方程,然后在此基础上设计了自适应控制器;最后利用Matlab/Simulink对舵机系统进行了仿真分析。仿真及研究结果显示:该自适应控制器可解决传统的PID控制方法在控制对象参数发生变化后控制效果变差的问题,并且能够克服舵机参数剧烈变化的影响,使舵机系统具有较好的稳定性和快速响应性。Actuator is an important equipment of missile control system, and its performance can affect the battle capability of missile. Aiming that the missile＇s nonlinear characteristic in different flying environment, the traditional PID controller can＇t afford the needed performance, an adaptive control method based on hyper stability was proposed to solve the problem. According to electronic actuator＇s principle, its state model was constructed and adaptive controller was designed. Analysis of actuator system was completed using Matlab/ Simulink. The simulation results indicate that the adaptive controller can solve the problem of bad effect of traditional PID control method and can conquer the difficulty caused by the actuator＇s parameter fierce change, and actuator is able to follow the command quickly and stably.

关 键 词：导弹舵机 PID控制 自适应控制 

分 类 号：TP765.4[自动化与计算机技术—检测技术与自动化装置] TH39[自动化与计算机技术—控制科学与工程]