液体火箭发动机试验测量系统的关键环节改进及应用  

Improvement and Application of Key Link of Liquid Rocket Engine Test Measurement System

作　　者：李秋霞 李斌[1] 吕守国 Li Qiu-xia;Li Bin;Lv Shou-guo(Beijing Institute of Aerospace Experiment Technology,Beijing 100074,China)

机构地区：[1]北京航天试验技术研究所,北京100074

出　　处：《科学与信息化》2022年第16期107-110,114,共5页Technology and Information

摘　　要：本文以液体火箭发动机试验测量系统紧急恢复改造过程中的关键环节作为研究对象,主要包括压力传感器供电电源冗余方法、紧急关机测试工作可靠性、数据采集设备复记功能、用电设备220V集中供电模式。通过对国内某试验台测量系统中的关键环节进行模式改进和功能提升,提高了液体火箭发动机试验测量系统的工作效率和可靠性。This article takes the key links in the process of emergency recovery and reconstruction of the liquid rocket engine test and measurement system as the research object,mainly including the redundancy method of the pressure sensor power supply,the reliability of the emergency shutdown test,the repeat function of the data acquisition equipment,the 220 V concentration of the equipment power supply mode.The working efficiency and reliability of the liquid rocket engine test and measurement system have been improved by improving the mode and function of the key links in the measurement system of a Chinese test bench.

关 键 词：发动机试验 测量系统 恢复改造 可靠性提升 

分 类 号：V43[航空宇航科学与技术—航空宇航推进理论与工程]