液体推进剂的新型加注方法  

A new injection method for liquid propellant

作　　者：孙迎霞 王浩 陈剑 赵正 SUN Yingxia;WANG Hao;CHEN Jian;ZHAO Zheng(Shanghai Institute of Space Propulsion,Shanghai 201112,China)

机构地区：[1]上海空间推进研究所

出　　处：《火箭推进》2019年第6期60-65,共6页Journal of Rocket Propulsion

基　　金：上海市科学技术委员会资助课题(17DZ2280800)

摘　　要：常规液体双组元推进系统通常采用挤压加注方法,挤压介质一般为氦气,受氦气在液体推进剂特别是氧化剂中溶解特性的影响,加注过程中会出现氦气析出现象,这对加注过程本身以及推进系统后续使用均造成不可忽视的影响。为彻底解决该问题,对氦气在MON-1中的溶解特性进行了研究,模拟加注过程中的压力变化开展了氦气析出试验,在此基础上提出一种基于气动隔膜泵的加注方法,并完成加注约1 t推进剂、时长4 h情况下无氦气夹气的试验验证。为推进剂及相关模拟液的加注提供了一种新选择,试验表明该方法彻底解决了推进剂夹气问题,尤其适用于长时、大容量推进系统的推进剂加注。Helium is commonly used as the pressurized gas in the injection of the bi-propellant propulsion system.Helium gas can be dissolved in liquid propellant,especially in oxidizer.Helium dissolves in high-pressure period and separates out in low-pressure period in the process of propellant injection.That results in impact on the injection and work of spacecraft.Based on the research of helium exhalation in the process of NON-1 propellant injection,a new injection method based on pneumatic diaphragm pump was proposed and verified.1 t propellant was injected in 4 h without helium entrapment.A new approach was provided for propellant and modeling liquid,and it is proved that the method can be used to avoid Helium being dissolved in liquid propellant,especially for large amount and long time propellant injection.

关 键 词：推进剂加注 MON-1 氦气 析出 新型加注方法 

分 类 号：V511[航空宇航科学与技术—航空宇航推进理论与工程]