液体火箭发动机泵动态特性水力试验研究  

Hydraulic test research on dynamic characteristics of oxygen pump of liquid rocket engine

作　　者：杜大华[1] 黄金平[1] 邢理想[1] 徐浩海[1] 

机构地区：[1]西安航天动力研究所,陕西西安710100

出　　处：《火箭推进》2013年第3期50-57,共8页Journal of Rocket Propulsion

基　　金：国家863项目(2006AA705311)

摘　　要：为了获取新一代大型运载火箭POGO稳定性分析及液体火箭发动机动力学研究等所必需的发动机泵动力学传递函数,进行了以常温水为试验介质、全尺寸降转速液氧/煤油补燃循环发动机氧泵的动态特性水力试验,对试验原理、试验模拟准则、隔离贮箱设计、激励系统设计、控制和测量分析系统设计、试验内容及数据分析方法等进行了深入探讨。通过试验成功地识别出泵的POGO动特性参数及参数的规律特点,为其他水力试验和真实介质试验储备经验。In order to obtain the essential dynamic transfer function of the engine pump which is necessary for POGO stability analysis of the new generation large launch vehicle and dynamics research of the liquid rocket engine,a hydraulic test for the dynamic characteristics of a full-scale LOX/kerosene staged combustion cycle engine pump with speed drop-down was conducted,in which normal temperature water is taken as the test medium.The hydraulic test theory,simulation criterion,isolation tank design,exciting system design,control and measurement analysis system design,test details and data analysis method are thoroughly discussed in this paper.The POGO dynamic characteristics parameters and their disciplinarian laws of the oxygen pump were successfully identified through the test,which would be helpful to other hydraulic test and the real medium test.

关 键 词：水力试验 泵 液氧 煤油补燃循环发动机 POGO 

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]