航空发动机单管燃烧室试验器测控系统设计  

Design of Instrumentation System of Aeroengine Can Combustor Test

作　　者：张毫 王日先 熊进星 ZHANG Hao;WANG Ri-xian;XIONG Jin-xing(AECC Shenyang Engine Research Institute,Shenyang 110015,China)

机构地区：[1]中国航发沈阳发动机研究所,沈阳110015

出　　处：《航空发动机》2018年第3期86-90,共5页Aeroengine

基　　金：国防重点科研项目资助

摘　　要：为满足新型燃烧试验需求,针对航空发动机燃烧室试验中单管试验器的特点,提出并设计了1种基于以太网的分布式测控系统。详细阐述了该系统的总体设计方案,分别从软件和硬件两方面研究分析了该系统的详细设计过程,并对其进行了测量不确定度分析。目前该系统已经完成试验前调试,并已顺利完成了多项单管燃烧室燃烧试验任务。结果表明:该系统可靠性高、稳定性良好、通用性强,满足试验器测控需求,具有较高的工程应用价值。In order to meet the requirements of new combustion tests, a distributed measurement and control system which based on Ethernet technology was proposed and designed for the characteristic of can combustor tester in the test of aeroengine combustion chambers.The overall design scheme of the system are described in detail. The detailed design process of the system was researched and analyzed in hardware and software aspects, then the measurement uncertainty was analyzed. At present, the system has been Debugged and verified by tests before experiment, and has successfully completed multiple can combustor tasks. The result shows that the system has high reliability,stability, and strong versatility, and can satisfy the test and control requirements.

关 键 词：单管燃烧室 分布式测控系统 燃烧试验 航空发动机 

分 类 号：V211.72[航空宇航科学与技术—航空宇航推进理论与工程]