某涡扇发动机分布式控制系统设计与总线性能  

Design of distributed control system and investigation on bus communication performance of a turbofan engine

作　　者：田飞龙[1] 郭迎清[1] 李睿超[1] 姜彩虹[2] 

机构地区：[1]西北工业大学动力与能源学院,西安710072 [2]中国航空工业集团公司沈阳发动机设计研究所,沈阳110015

出　　处：《航空动力学报》2015年第9期2278-2285,共8页Journal of Aerospace Power

基　　金：国家先进航空发动机技术研究计划

摘　　要：针对国内某型涡扇发动机,以该机目前采用的集中式FADEC为基础,依据地域分散原则,设计了一种发动机部分分布式控制系统结构,并对发动机控制系统中的传输信号进行了合理划分;对发动机采用分布式控制进行了总线通信需求分析;选择时间触发CAN总线作为发动机分布式控制系统通信总线,并进行了通信方案设计;利用TrueTime构建了分布式控制仿真系统,研究了网络时延、掉包对发动机性能的影响.研究表明:在250kbit/s和1Mbit/s带宽下,总线利用率分别为50%和12.34%,满足通信要求;250kbit/s带宽下所设计时间触发系统的网络诱导时延为12ms,高压转子转速上升时间延迟0.02s,而网络随机掉包使发动机响应明显变慢,设计时需要加以考虑.A partially distributed engine control system was designed based on the centralized FADEC（full authority digital engine control）of domestic turbofan engine by geographical distribution principle.A reasonable classification of various signals in the control system was presented.According to communication requirement assessment for distributed turbine engine control,Time-triggered CAN（controller area network）bus was determined as the engine area network and the communication strategy was designed.TrueTime was exploited to develop a distributed control system simulation.Impact of network delay and data dropout on the engine performance was studied.The results show that bus utilization is 50%at 250kbit/s and 12.34% at 1Mbit/s,which meets the communication requirement.The network-induced delay of the time-triggered system is 12 ms.It prolongs the rise time of high pressure rotor speed for 0.02 s.However,the engine response is significantly slower under the random packet dropout,which should be taken into account at the design phase.

关 键 词：涡扇发动机 分布式控制系统 数据集中器 总线通信 时延和掉包 

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]