飞行环境模拟腔积分型[μ]综合控制

推进技术 ›› 2018, Vol. 39 ›› Issue (3): 660-666.

飞行环境模拟腔积分型[μ]综合控制

张松¹,朱美印^2,3,但志宏¹,裴希同¹,王信¹,王曦^2,3

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

发布日期:2021-08-15
作者简介:张松，男，博士，研究领域为高空台设备控制系统。E-mail: 657890168@qq.com 通讯作者:朱美印，男，博士生，研究领域为航空发动机控制、高空台数字仿真平台研究以及鲁棒控制等。

Integral Type[μ]Synthesis Control of Flight Environment Simulation Volume

China Gas Turbine Establishment，Mianyang 621703，China,School of Energy and Power Engineering，Beihang University，Beijing 100191，China; Collaborative Innovation Center of Advanced Aero-Engine，Beijing 100191，China,China Gas Turbine Establishment，Mianyang 621703，China,China Gas Turbine Establishment，Mianyang 621703，China,China Gas Turbine Establishment，Mianyang 621703，China and School of Energy and Power Engineering，Beihang University，Beijing 100191，China; Collaborative Innovation Center of Advanced Aero-Engine，Beijing 100191，China

Published:2021-08-15

摘要/Abstract

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。

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

Abstract: 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 1K and the relative error of pressure simulation of FESV is less 3%.

Key words: Altitude ground test facilities；Flight environment simulation volume；Temperature and pressure double variable control；Synthesis control；Iterative algorithm

张松,朱美印,但志宏,裴希同,王信,王曦. 飞行环境模拟腔积分型[μ]综合控制[J]. 推进技术, 2018, 39(3): 660-666.

ZHANG Song¹,ZHU Mei-yin^2,3,DAN Zhi-hong¹,PEI Xi-tong¹,WANG Xin¹,WANG Xi^2,3. Integral Type[μ]Synthesis Control of Flight Environment Simulation Volume[J]. Journal of Propulsion Technology, 2018, 39(3): 660-666.

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