航空发动机主燃油执行机构容错控制  

Fault-tolerant Control for Main Fuel Actuator of Aeroengine

作　　者：王松 高亚辉 高峰 段绍栋 王建锋 WANG Song;GAO Ya-hui;GAO Feng;DUAN Shao-dong;WANG Jian-feng(AECC Aero Engine Control System Institute,Wuxi Jiangsu 214063)

机构地区：[1]中国航发控制系统研究所,江苏无锡214063

出　　处：《航空发动机》2023年第1期134-138,共5页Aeroengine

基　　金：航空动力基础研究项目资助。

摘　　要：为了在主燃油计量活门位移传感器出现故障时仍能实现航空发动机全包线范围内的转速自适应控制,根据航空发动机转速自适应控制原理提出了一种基于零极点配置原理的容错控制方法,根据高压转子转速控制计划与实测转速之间的误差对主燃油控制电液伺服阀电流进行闭环运算,并运用零极点配置原理将控制参数与转速自适应控制相融合,参数在全包线范围内随发动机状态变化进行自适应调整,通过半物理模拟试验对该容错控制方法进行了验证。结果表明:该容错控制方法能够在全包线范围内保证数字电子控制系统稳定工作,并具有较好的稳态和动态性能,发动机高压转子转速稳态波动量在±0.15%以内,超调量和下降量分别在0.63%和0.61%以下,而且容错控制方法实施方便、自适应性强,对提高航空发动机数字电子控制系统的工作可靠性具有重要作用。In order to realize the adaptive speed control within the full envelope of the aeroengine when the displacement sensor of the main fuel metering valve fails,a fault-tolerant control method based on pole-zero configuration was proposed according to the aeroengine adaptive speed control principle.According to the error between the high pressure rotor speed control plan and the measured speed,the main fuel control electro-hydraulic servo valve current was calculated in the closed loop control system.The pole-zero configuration principle was used to integrate the control parameters with the speed adaptive control,and the parameters were adaptively adjusted with the engine state change in the full envelope.The semi-physical simulation test was conducted to verify the fault-tolerant control method.The results show that the fault-tolerant control method can ensure the stable operation of the digital electronic control system in the full envelope,and exhibits good steady-state and dynamic performance.The steady state error of the high-pressure rotor speed is within±0.15%,the overshoot and undershoot are below 0.63%and 0.61%respectively.The fault-tolerant control method is easy to implement and strong in adaptability.It plays an important role in improving the reliability of aeroengine digital electronic control system.

关 键 词：数字电子控制系统 零极点配置 容错控制 转速自适应控制 航空发动机 

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]