Abstract: 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 result is shown that the robust performance with controller designed is acquired on different missile locus.

Key words: Turbojet engine;Aerodynamic model;Integrated system;Robust control

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。

关键词: 涡轮喷气发动机;气动模型;综合系统;鲁棒控制