摘要
文中研究了固体火箭冲压发动机推力调节和进气道喘振保护的切换控制。首先建立了燃气流量调节系统和发动机的动态模型,并分析了燃气流量及进气道出口压力的负调响应特性。然后建立了固体火箭冲压发动机多回路切换控制系统,最后通过仿真分析了推力调节和进气道喘振保护回路的切换过程及控制器积分限幅对切换过程的影响。研究表明固体火箭冲压发动机多回路闭环切换控制的引入,有利于兼顾发动机性能充分发挥和工作安全性的矛盾。
In this article,switching control of ramjet was investigated. Firstly,dynamic mathematical models and characteristics of gas regulating system and ramjet were established and analyzed. Then,the switching control system of ramjet system was discussed. Lastly,the switching process of thrust regulation loop and inlet buzz protection loop was simulated,and the influences of integral limitations of controllers were analyzed. The results show that the multi-loop switching control for ramject can balance engine performance with work safety.
出处
《弹箭与制导学报》
CSCD
北大核心
2015年第4期93-96,100,共5页
Journal of Projectiles,Rockets,Missiles and Guidance
