弹用涡喷发动机鲁棒性能μ综合控制  

μ synthesis control with robust performance for missile turbojet engine

作　　者：王曦[1] 姚华 

机构地区：[1]北京航空航天大学动力系,北京100083 [2]中国航空动力控制系统研究所,江苏无锡214063

出　　处：《推进技术》2003年第3期236-239,共4页Journal of Propulsion Technology

基　　金：航空科学基金资助项目 (0 0C51 0 3 6)

摘　　要：针对某型弹用涡喷发动机,分析了具有乘性输入不确定性的被控对象中嵌入加权函数的μ鲁棒性能问题,由具有N Δ结构的μ综合框架,给出了控制系统获得鲁棒性能的D K迭代法,设计了弹用涡喷发动机鲁棒μ控制器。仿真结果表明设计的控制器在全飞行包线内不同的弹道上取得了鲁棒性能。Focus on a missile turbojet engine, the problem of μ robust performance defined in terms of weighted function for the plant with multiplicative input uncertainty was analyzed. In virtue of μ synthesis frame with N-Δ structure, the D-K iteration obtaining robust performance was given, and accordingly robust μ controller for missile turbojet engine was designed. Simulation results showed that the robust performance with controller designed is acquired on different missile locus.

关 键 词：涡轮喷气发动机 气动模型 综合系统 鲁棒控制 

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]