涡轴发动机分布式控制系统架构设计  

Design of Turboshaft Engine Distributed Control System Architecture

作　　者：陈义峰[1] 郭迎清[1] 李睿超[1] 郭腊梅 韩同辉 CHEN Yi-feng;GUO Ying-qing;LI Rui-chao;GUO La-mei;HAN Tong-hui(School of Power and Energy,Northwestern Polytechnical University,Xi′an 710129,China;Aviation Powerplant Research Institute,AVIC,Zhuzhou 412002,China)

机构地区：[1]西北工业大学动力与能源学院,陕西西安710129 [2]航空工业航空动力机械研究所,湖南株洲412002

出　　处：《航空计算技术》2019年第5期21-26,共6页Aeronautical Computing Technique

摘　　要：针对民用涡轴发动机,以当前高温电子元件技术的成熟度为主要依据,提出了适合当前涡轴发动机分布式控制系统的架构为数据集中器与智能节点混合的部分分布式系统架构。针对某型涡轴发动机进行了分布式控制系统架构方案的详细设计,将系统划分为1个FADEC(Full Authority Digital Engine Control)节点,2个智能处理器节点和2个数据集中器节点,并重点确定了各节点的功能划分及信号传输。为了提高控制系统的模块化程度,基于IEEE 1451标准对分布式系统中的智能节点(包括智能传感器、智能处理器和数据集中器)进行了设计。For civil turboshaft engine,a partially distributed control system architecture with data concentrators and smart processor nodes is proposed based on the high-temperature electric components maturity.Then,a distributed turboshaft engine control system scheme is designed.During the design,the system is divided into five parts,1 FADEC(Full Authority Digital Engine Control),2 smart processor nodes and 2 data concentrators;and function division and information transmission are described,respectively.Lastly,in order to improve system′s modularity,all smart nodes(including smart sensors,actuators and data concentrators)used in the distributed control system are designed based on IEEE 1451 standards.

关 键 词：涡轴发动机 分布式控制系统架构 高温电子元件成熟度 系统方案设计 智能节点设计 

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]