1种弹用发动机控制系统高空转速超调控制技术应用研究  

Research of Speed Overshoot Control Technology in High Altitude for Missile Engine Control Systems

作　　者：仇小杰 林星辰 王全胜 胡文霏 王琴 QIU Xiao-jie;LIN Xing-chen;WANG Quan-sheng;HU Wen-fei;WANG Qin(AECC Aero Engine Control System Institute,Wu＇ Xi Jiangsu,214063,China;Office of PLA Air Force Representative,Yang Zhou Jiangsu,225000,China)

机构地区：[1]中国航发控制系统研究所,江苏无锡214063 [2]中国人民解放军空军驻扬州地区军事代表室,江苏扬州225000

出　　处：《航空发动机》2018年第3期31-35,共5页Aeroengine

基　　金：国防重点科研项目资助

摘　　要：为解决弹用发动机控制系统缺少发动机进口参数测量,无法实时对PI控制参数进行相似原理修正,从而导致地面点控制参数在高空不适用,产生发动机高空转速超调这一问题,基于压气机出口总压P_3重构发动机进口总压P_1对PI控制参数进行修正,设计了1种发动机进口参数测量不全条件下弹用发动机转速高空超调控制的方法。通过全数字仿真、半物理模拟试验、高空模拟试验及高空飞行试验验证该方法的有效性。In order to solve engine speed overshoot problem caused by controller parameter on the ground unsuitable for altitude tests,which is result from similarity principle can＇t be carried to PI controller parameter in real time because of lacking for missile engine control systems. A method of speed overshoot control for missile engine under lacking of engine inlet parameter measurement was designed. P_1 is constructed based on P_3 and PI controller parameter is corrected. Through full digital simulation, semi-physical simulation test, and altitude simulation test and altitude flyight test, its availability was proved.

关 键 词：PI控制 相似原理 转速超调 参数修正 航空发动机 

分 类 号：V233.7[航空宇航科学与技术—航空宇航推进理论与工程]