基于多模式加速及反步滑模的航空发动机压气机压力模拟方法  

Aero-engine Compressor Pressure Simulation Method Based on Multi-mode Acceleration and Backstepping Sliding Mode

作　　者：林忠麟 王海涛 刘文超 甘锦裕 张天宏[2] 黄峰 LIN Zhonglin;WANG Haitao;LIU Wenchao;GAN Jinyu;ZHANG Tianhong;HUANG Feng(School of Mechanical Engineering and Automation,Fuzhou University,Fuzhou 350108,Fujian,China;College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,Jiangsu,China)

机构地区：[1]福州大学机械工程及自动化学院,福建福州350108 [2]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《兵工学报》2024年第6期1776-1786,共11页Acta Armamentarii

基　　金：福建省自然科学基金计划项目(2021J05113);2020年福建省中青年教师教育科研项目(科技类)(JAT200030);福州大学校人才基金项目(XRC-20051)。

摘　　要：在航空发动机硬件在环仿真试验中,压气机出口压力模拟是一个重要的环节。为模拟压气机失稳过程中的气流突变现象,需要设计一种高精度的压力模拟系统,通过该模拟系统生成真实压力信号为全权限数字发动机控制器提供准确的压力激励。根据开关阀特性提出多模式加速切换策略,设计加速驱动波形及生成方法,结合现场可编程门阵列模块精确输出加速波形,提高开关阀启闭速度;在传统三模式与五模式切换的基础上设计七模式切换方法,结合反步滑模控制方法提高控制精度并证明了控制系统的稳定性。研究结果表明:在稳态压力测试中最大平均超调量为1.25%,最大平均稳态误差为0.016 MPa;在随机阶跃响应试验与正弦跟踪试验中仅有低于0.02 MPa的平均误差;压力模拟方法可满足航空发动机硬件在环仿真试验的高精度压力模拟需求,低成本的实现精准模拟压力。In the aero-engine hardware-in-the-loop simulation test,the compressor outlet pressure simulation is an important part.In order to simulate the sudden change of airflow in the process of compressor destabilization,a high-precision pressure simulation system is designed,through which a real pressure signal is generated to provide an accurate pressure excitation for the full authority digital engine control.A multi-mode acceleration switching strategy is proposed according to the characteristics of the switching valve,and the acceleration drive waveform and generation method are designed to combine with the field-programmable gate array module to accurately output the acceleration waveform and improve the opening and closing speeds of switching valve.A seven-mode switching method is designed based on the traditional three-mode and five-mode switching methods.The backstepping sliding mode controller is combined with the seven-mode switching method to improve the control accuracy,and the stability of control system is proven.The test results show that the maximum average overshoot in the steady-state pressure test is 1.25%,and the maximum average steady-state error is 0.016 MPa.The average errors in the random step response and sinusoidal tracking tests are less than 0.02 MPa.The proposed pressure simulation method can meet the requirements for high-accuracy pressure simulation of aero-engine hardware-in-the-loop simulation tests and achieve the accurate pressure simulation at a low cost.

关 键 词：压气机 压力模拟 硬件在环仿真 开关阀 反步滑模控制 

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]