摘要
中国民用航空局颁布的《航空发动机适航规定》(CCAR-33R2),其中33.28条款对发动机控制系统做出了系统需容忍“单点故障”的规定。然而,传感器失效在所难免,而限制保护是发动机控制系统的重要组成部分。为保障控制系统安全可靠的运行,提高局方在传感器失效状态下对控制系统适航审查的能力,掌握传感器失效下限制保护的影响,进而为适航审定提供一定技术支持。在传感器失效下,探究了航空发动机限制保护控制系统的影响。利用MATLAB/Simulink平台搭建涡轮温度控制系统,以电流信号表征传感器故障,并针对高压涡轮出口温度(T 48)的控制,设计了温度限制保护装置,并设定温度限制进行仿真分析。结果表明:过渡过程中,温度限制保护的两次切换可有效解决系统超调过大的现象,而传感器失效和改变参数的限制值均会对限制保护的切换时刻造成超前或滞后等影响,而对限制时间造成缩短或延长的影响。
The Civil Aviation Administration of China has issued The Aviation Engine Airworthiness Regulation(CCAR-33R2),of which the aero-engine control system of the 33.28 clause has required that the system needs to tolerate single point failure.However,sensor failure is inevitable,and limit protection is an important part of the engine control system.The research aims to ensure safe and reliable operation of the control system,and to improve the CAAC s ability for airworthiness certification of the control system under the sensor failure,as well as to know well the influence of the limit protection under the sensor failure,and to provide technical support for the airworthiness certification.The turbine temperature control system was built on MATLAB/Simulink platform and the current signal was used to characterize as sensor failure.Then,a device of temperature limit protection was designed for the control of total temperature at high-pressure turbine outlet(T 48),and the temperature limit was set for simulation analysis.The result shows that twice switching of limit protection can effectively solve the phenomenon that is excessive overshoot of the system during the transition state.Sensor failures and changing of the limit parameters will cause leading or lagging on the switching moment of limit protection.Meanwhile,limit time will cause to some impacts such as short or extend.
作者
朱日兴
朱兆优
ZHU Ri-xing;ZHU Zhao-you(School of Airworthiness,Civil Aviation University of China,Tianjin 300300,China;Key Laboratory of Civil Aircraft Airworthiness Technology,Civil Aviation University of China,Tianjin 300300,China;School of Mechanical and Electric Engineering,East China University of Technology,Nanchang 3300133,China)
出处
《科学技术与工程》
北大核心
2021年第12期5144-5150,共7页
Science Technology and Engineering
基金
大飞机重大专项。
关键词
高压涡轮出口温度
发动机控制
限制保护
单点故障
超调
影响
total temperature at high-pressure turbine outlet
aero-engine control
limit protection
single point failure
overshoot
impact
