飞行环境模拟腔积分型μ综合控制  

Integral Type μ Synthesis Control of Flight Environment Simulation Volume

作　　者：张松[1] 朱美印 但志宏[1] 裴希同 王信[1] 王曦[2,3] 

机构地区：[1]中国燃气涡轮研究院,四川绵阳621703 [2]北京航空航天大学能源与动力工程学院,北京100191 [3]先进航空发动机协同创新中心,北京100191

出　　处：《推进技术》2018年第3期660-666,共7页Journal of Propulsion Technology

摘　　要：针对高空台飞行环境模拟腔飞行环境温度、压力的双变量控制问题,采用系统不确定性建模的方法,建立了高空模拟腔、调节阀执行机构的增广被控对象模型,提出了一种高空模拟腔积分型μ综合控制的设计方法,为了确保控制器伺服性能,对温度、压力回路采用不同的性能加权函数,同时对控制器输出幅值进行分频成型加权函数设计,采用D-K迭代算法设计了μ综合控制器,以涡扇发动机的仿真试验为例对算法进行仿真验证。仿真结果表明,高空模拟腔温度仿真的最大偏差为1K,压力的相对误差在3%以内。Aiming at the temperature and pressure double variable control problem of altitude ground test facilities（AGTF）flight environment simulation volume（FESV）,the extended plant model of FESV and control valve actuator has been established with system uncertainty modeling method and an integral type μ synthesis control design method of FESV is proposed to solve the problem. In order to come true servo performance of temperature and pressure,two different performance weighting functions are used in temperature and pressure loop and the part frequency weighting shaping method is used for limiting control output. The μ synthesis controller has been designed with D-K iterative algorithm. Taking turbofan engine simulation test for instance to verify the algorithm,the simulation results show that the maximum deviation of temperature simulation of FESV is 1 K and the relative error of pressure simulation of FESV is less 3%.

关 键 词：高空台 高空模拟腔 温压双变量控制 综合控制 迭代算法 

分 类 号：V221.3[航空宇航科学与技术—飞行器设计] TB553[理学—物理]