液体火箭发动机试验脉动压力测量技术研究  

Research on detection technology of fluctuating pressure in liquid rocket engine test

作　　者：陈海峰[1] 邝奇[1] 翟文化 姚羽佳 

机构地区：[1]西安航天动力试验技术研究所,陕西西安710100

出　　处：《火箭推进》2016年第5期104-109,共6页Journal of Rocket Propulsion

基　　金：国防科工局计量课题(JSJC2013203A001)

摘　　要：对常规液体火箭发动机的脉动压力测量特点、测量系统组成与测量方式以及发动机不稳性燃烧的关系和数据分析方法做了介绍,并在此基础上阐述了现有常规液体火箭发动机脉动压力测量工艺方法。通过对现有常规液体火箭发动机脉动压力测量参数引入,解决了常规液体火箭发动机在工作过程中以往无法对不稳定燃烧现象的监测及其有效评估问题。并为研究发动机工作状态和评价发动机工作性能提供了重要手段。The characteristics of fluctuating pressure detection, compositions of detecting system, detecting methods, instable combustion and data analyzing methods of the conventional liquid rocket engine are introduced in this paper. The detecting method currently used in the fluctuating pressure detection of the conventional liquid rocket engine is also described. The problem that the instable combustion during the work of the conventional liquid rocket engine could not be monitored and evaluated effectively in the past has been solved by importing the measurement parameters of fluctuating pressure of the available conventional liquid rocket engine, which is useful for research of engine working state and evaluation of engine working performance.

关 键 词：发动机试验 脉动压力测量 工艺方法 

分 类 号：V434-34[航空宇航科学与技术—航空宇航推进理论与工程]