模糊控制在导弹瞬态气动热流试验中的研究  

Experimental Study on Fuzzy Control of Transient Aerodynamic Heat Flow of Missile

作　　者：吴大方[1] 高镇同[1] 王永海[1] 

机构地区：[1]北京航空航天大学飞行器设计与应用力学系

出　　处：《北京航空航天大学学报》2002年第6期682-684,共3页Journal of Beijing University of Aeronautics and Astronautics

基　　金：航空科学基金资助项目 (98I5 10 40 )

摘　　要：导弹与高速飞行器气动模拟试验瞬态热控过程的特点是变化复杂、瞬变、高度非线性、强耦合 ,很难或者根本无法建立控制的数学模型 .模糊控制具有鲁棒性好 ,对参数变化的适应性强 ,过渡过程时间短等常规控制方法所不能比拟的优点 .将模糊控制方法应用于导弹瞬态气动加热模拟控制系统 ,使该系统能够按照导弹高速飞行过程中弹体表面热流的瞬态连续变化对气动模拟加热过程实施快速的动态控制 .The characteristics of transient heating control process of aerodynamic simulation experiments are complicated, transient, high non linearity and strong coupling, which make it difficult or impossible to get a mathematical model. By using fuzzy control method,many good qualities (such as robust, high adaptability on changing parameters and short transition process time) can be obtained. Based on the fuzzy control method, a transient aerodynamic heating simulation control system for missiles was established. It was demonstrated that quick dynamic control of aerodynamic simulation heating process according to the transient and continual change of heat flow on the surface of a flying missile body can be completed by using this control system.

关 键 词：导弹 热流试验 模糊控制论 气动加热 动态响应 

分 类 号：TJ765.2[兵器科学与技术—武器系统与运用工程]