氢氧火箭发动机试验低温流量校准系统设计  

Design of cryogenic flow gauging system for LH_2/LOX rocket engine test

作　　者：周磊[1] 陈锋[1] 王占林[1] 叶斌[1] 

机构地区：[1]北京航天试验技术研究所,北京100074

出　　处：《低温工程》2016年第2期60-65,共6页Cryogenics

基　　金：国防科工技术基础科研项目"液氢/液氧发动机试验低温流量现场校准技术研究"(JSJL2012203A006)资助

摘　　要：为了保证氢氧火箭发动机低温流量测量的准确性,需要研制低温流量校准系统。从对低温流量校准特点的分析入手,对比动态替代称重法的不同原理,优选适用于低温对象的低温流量校准系统方案,并对称重系统、储液容器、液路系统、气路系统和测控系统进行设计。研制的低温流量校准系统提供了低温真实介质校验能力,校准流量覆盖1—50 kg/s,校准流量计口径Ф30—80 mm,设计流量校准不确定度优于0.5%(k=2)。The cryogenic flow gauging system can guarantee the accuracy of the flow rate measurement for LH2/LOX rocket engine test. Starting with the specialties of cryogenic flow gauging process, different techniques of dynamic substitution were contrasted to make the preferential design decision. The details of weighting system, cryogenic tank, liquid and gas pipes, and measurement and control system were presen- ted. The developed cryogenic flow gauging system provides the capability of flow rate calibration for real cry- ogenic fluid, which covers the flow rate 1 - 50 kg/s, the caliber of flowmeter φ30 - 80 mm, gauging uncer- tainty less than 0.5 % （k = 2）.

关 键 词：流量校准 低温流体 动态替代称重 校准精度 

分 类 号：TB663[一般工业技术—制冷工程]