一种小型弹用发动机空中起动环境模拟试验主动抗扰控制方法  

An active disturbance rejection control method for air starting environment simulation test of small missile engine

作　　者：王信 钟华贵 但志宏 罗载奇 郭强 WANG Xin;ZHONG Hua-gui;DAN Zhi-hong;LUO Zai-qi;GUO qiang(AECC Sichuan Gas Turbine Establishment,Mianyang 621000,China;Science and Technology on Altitude Simulation Laboratory,Mianyang 621000,China)

机构地区：[1]中国航发四川燃气涡轮研究院,四川绵阳621000 [2]高空模拟技术重点实验室,四川绵阳621000

出　　处：《燃气涡轮试验与研究》2021年第3期32-36,5,共6页Gas Turbine Experiment and Research

基　　金：四川省科技计划资助项目(2019YJ0292)。

摘　　要：针对高空模拟试车台(简称高空台)弹用发动机起动环境模拟试验具有起动时间极短、流量变化率大等特点,采用常规控制方法难以实现快速、准确模拟空中飞行环境的技术难题,引入自抗扰控制思想,提出一种适用于高空台非线性不确定复杂系统的主动抗扰控制方法。仿真验证表明,采用该主动抗扰控制方法,试验舱进气、排气压力最大偏差≯0.3 kPa,进入稳态时间较短且无超调,能有效抑制弹用发动机起动对试验舱进气、排气压力的干扰。本研究对于高空台弹用发动机及其他型号发动机试验控制技术的发展具有重要借鉴意义。The starting environment simulation test of missile engine on high altitude facility has very short start-up time and large flow variation,so it is difficult to realize fast and accurate simulation of air flight en⁃vironment by conventional control method.An active disturbance rejection control method for complex non⁃linear uncertain system on high altitude facility was proposed by introducing active disturbance rejection control method.Using the active disturbance rejection control method,the maximum deviation of inlet and exhaust pressure of test chamber is not more than 0.3 kPa,the steady-state time is short and there is no overshoot.It can effectively restrain the interference of missile engine starting on the inlet and exhaust pres⁃sure of test chamber.It provides important reference for development of test control technology of missile en⁃gine and other types of engines on high altitude facility.

关 键 词：航空发动机 空中起动 主动抗扰控制 起动环境模拟 高空模拟试车台 

分 类 号：V217[航空宇航科学与技术—航空宇航推进理论与工程] TP272[自动化与计算机技术—检测技术与自动化装置]