高空舱进气环境压力模拟新型自抗扰控制  

New active disturbance rejection control for high-altitude cabin intake environmental pressure simulation system

作　　者：李婉如 张和洪 王鹏[1] 翟超 张松 但志宏 王信 LI Wanru;ZHANG Hehong;WANG Peng;ZHAI Chao;ZHANG Song;DAN Zhihong;WANG Xin(School of Mathematics and Statistics,Fuzhou University,Fuzhou 350108,China;College of Computer Science and Big Data,Fuzhou University,Fuzhou 350108,China;School of Automation,China University of Geosciences,Wuhan 430079,China;AECC Sichuan Gas Turbine Establishment,Mianyang 621703,China)

机构地区：[1]福州大学数学与统计学院,福建福州350108 [2]福州大学计算机与大数据学院,福建福州350108 [3]中国地质大学自动化学院,湖北武汉430079 [4]中国航发四川燃气涡轮研究院,四川绵阳621703

出　　处：《推进技术》2024年第8期246-256,共11页Journal of Propulsion Technology

基　　金：福建省自然科学基金重点项目(2021J02008);国家自然科学基金(62003088);基础加强重点项目(JWKT-2001-2022-0002)。

摘　　要：高空舱进气环境压力模拟控制系统在发动机开展过渡态试验中存在强气流扰动及大量随机噪声干扰,为此,提出新型非线性状态误差反馈函数xal及在结构上引入总扰动状态变量反馈环节来设计扩张状态观测器算法(记作xal-ESO),并以此提出基于xal-ESO的高空舱进气环境压力模拟新型自抗扰控制方法。借助数值仿真对比所提出的xal-ESO与常见ESO在状态与总扰动方面的估计能力,结果表明xal-ESO能有效抑制系统输出噪声并取得较好的估计品质。基于系统核心设备模型搭建高空舱进气环境压力模拟仿真平台并进行工程试验,对比了基于xal-ESO的自抗扰控制与当前工程中使用的线性自抗扰控制的进气环境压力控制效果,试验结果显示线性自抗扰控制方法受噪声影响明显,而所提出的新型自抗扰控制方法在发动机过渡态试验中跟踪进气压力时超调量降低了58.70%,稳态误差降低了95.71%,表明该方法能够有效提升高空舱进气环境压力模拟效果,提升发动机过渡态性能评价的准确性。During the transition state tests of aero-engines,there exist strong airflow disturbances and large output noise in the high-altitude cabin intake environmental pressure simulation system.As a result,a new extended state observer algorithm(denoted as xal-ESO)is proposed by jointly designing a nonlinear state error feedback function(denoted as xal)and adopting the feedback loop with total disturbance state as a part of the structure of ESO.In addition,a new active disturbance rejection control(ADRC)scheme via the proposed xal-ESO for simulating the intake pressure of high-altitude cabin is presented.Numerical simulations are carried out to compare the estimation capability including the system states and total disturbances among xal-ESO and other commonly-used ESOs.The results show that xal-ESO can effectively suppress noise and achieve better estima⁃tion quality.By construction of models of the core equipments and process,a high-altitude cabin simulation plat⁃form is built to simulate the transition state test of an aero-engine.The simulations compare the control perfor⁃mance of xal-ESO-ADRC with the linear active disturbance rejection control(LADRC)that currently used in en⁃gineering for intake environmental pressure control.The test results show that the performance of the LADRC is significantly degraded when unavoidable noise is taken into account while xal-ESO-ADRC reduced the overshoot by about 58.70%when tracking the intake pressure in the transition state test and the steady state error was re⁃duced by about 95.71%.This indicates xal-ESO-ADRC can effectively improve the simulation effect of the in⁃take environmental pressure simulation control system and improve the accuracy of engine’s transition state test.

关 键 词：高空舱 压力模拟 过渡态试验 非线性状态误差反馈 扩张状态观测器 自抗扰控制 

分 类 号：V217[航空宇航科学与技术—航空宇航推进理论与工程]