低温推进剂火箭喷泉效应及其抑制  

Geysering Effect of the Cryogenic Propellant Rocket and Restraint Research

作　　者：廖少英[1] 

机构地区：[1]上海航天技术研究院805所,上海201108

出　　处：《上海航天》2002年第3期29-34,共6页Aerospace Shanghai

摘　　要：针对低温推进剂火箭应用过程中出现的喷泉效应 ,在深入分析其产生机理的基础上 ,介绍了氦气注入、补充加注和循环回流三种相应的抑制方法。试验和应用结果表明 ,这三种方法可有效地实现系统平衡 ,抑制喷泉效应。In view of the geysering effect appeared in the operation of cryogenic propellant rocket, this paper discusses the geysering mechanism of the cryogenic propellant rocket, analyzes and researches the methods of restraint. Three appropriate restraint methods of the helium injection, repressuring injection and cycle reflowing are put forward. The test and application results show that these methods are effective in the balance and restraint of geysering effect.

关 键 词：低温推进剂火箭发动机 喷泉效应 抑制 氦气注入 补充加注 液体推进剂 

分 类 号：V434.13[航空宇航科学与技术—航空宇航推进理论与工程]