PDF下载 分享
[1]孙迎霞,王 浩,陈 剑,等.液体推进剂的新型加注方法[J].火箭推进,2019,45(06):60-65.
　SUN Yingxia,WANG Hao,CHEN Jian,et al.A new injection method for liquid propellant[J].Journal of Rocket Propulsion,2019,45(06):60-65.
点击复制

液体推进剂的新型加注方法

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 45 期数: 2019年06期 页码: 60-65 栏目: 研究与技术 出版日期: 2019-12-25
Title:
A new injection method for liquid propellant
文章编号:
1672-9374(2019)06-0060-06
作者:
孙迎霞; 王 浩; 陈 剑; 赵 正
(上海空间推进研究所,上海 201112)
Author(s):
SUN Yingxia;  WANG Hao;  CHEN Jian;  ZHAO Zheng
(Shanghai Institute of Space Propulsion, Shanghai 201112, China)
关键词:
推进剂加注;  MON-1;  氦气;  析出;  新型加注方法
Keywords:
propellant injection;  MON-1;  helium;  separate out;  new injection method
分类号:
V511
文献标志码:
A
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。
Abstract:
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.

参考文献/References:

[1] 高思秘.液体推进剂[M].北京:宇航出版社, 1991.
[2] 任汉芬,刘国球,方照奎.液体火箭发动机原理[M].北京:中国宇航出版社, 1993.
[3] JOKELA K, FVALENCIA F B, KAELSCH I.Dynamic solubility of pressurized helium gas in liquid propellant in closed storage tanks:ESA SP-555 [Z].
[4] 李亚裕.液体推进剂[M].北京:中国宇航出版社, 2011.
[5] GOKCEN N A, CHANG E T.Estimation of solubilities of gases in liquid propellant mixtures by statistical thermodynamics[Z].Aerodynamics and Propulsion Research Laboratory, 1968.
[6] CHANG E T, GOKCEN N A, POSTON T M.Thermodynamic properties of gases in propellants solubility of He, N2, and ar in hydrazine, methylhydrazine, and unsymmetrical dimethylhydrazine[Z].Defense Technical Information Center, 1967.
[7] WHITMAN W G.The two-film theory of absorption[J].Chemistry and Metal Engineering, 1923, 29(1):147-157.
[8] HIGBIE R.The rate of absorption of a pure gas into a still liquid during short periods of exposure[J].Transactions of the American Institute of Chemical Engineers, 1935, 31(2):365-377
[9] PIEROTTI R A.The solubility of gases in liquids1[J].The Journal of Physical Chemistry, 1963, 67(9):1840-1845.
[10] 郭敬, 宋晶晶, 孔凡超.发动机推进剂增压输送系统建模仿真技术综述[J].火箭推进, 2015, 41(5):1-6.GUO J, SONG J J, KONG F C.Overview of modeling and simulation technology for propellant pressurization feed system of liquid rocket engine[J].Journal of Rocket Propulsion, 2015, 41(5):1-6.
[11] 李纯飞, 龙春伟, 董苑.某发动机并联贮箱排放均衡性研究[J].火箭推进, 2018, 44(3):76-80, 86.LI C F, LONG C W, DONG Y.Research on equalizing discharge of parallel tank for a liquid rocket engine[J].Journal of Rocket Propulsion, 2018, 44(3):76-80, 86.
[12] 赵万明, 罗维民.液体火箭发动机试验流量测量技术研究[J].火箭推进, 2017, 43(5):74-79.ZHAO W M, LUO W M.Research on flow-rate measurement technology for liquid rocket engine test[J].Journal of Rocket Propulsion, 2017, 43(5):74-79.
[13] 陈鹏飞, 赵晓慧, 洪流, 等.N2O自增压贮箱的动态供应特性[J].火箭推进, 2018, 44(3):43-48.CHEN P F, ZHAO X H, HONG L, et al.Dynamic supply characteristics of N2O self-pressurization tank[J].Journal of Rocket Propulsion, 2018, 44(3):43-48.
[14] 邹宇, 李平.自增压系统在轨姿控动力系统中的应用[J].火箭推进, 2010, 36(2):15-19.ZOU Y, LI P.Applications of self-pressurization in divert and attitude control system[J].Journal of Rocket Propulsion, 2010, 36(2):15-19.
[15] 李淑艳, 肖明杰, 李晓瑾, 等.新型活塞泵增压轨/姿控发动机系统方案研究[J].火箭推进, 2012, 38(1):12-16, 26.LIS Y, XIAO M J, LI X J, et al.Scheme study on divert and attitude control engines with piston pump pressurized system[J].Journal of Rocket Propulsion, 2012, 38(1):12-16, 26.

相似文献/References:

[1]李 乐.推进剂微重力加注稳定性仿真分析[J].火箭推进,2013,39(04):41.
　LI Le.Simulation and analysis of propellant refueling stability under low-gravity condition[J].Journal of Rocket Propulsion,2013,39(06):41.

备注/Memo

收稿日期:2018-10-30; 修回日期:2019-03-01基金项目:上海市科学技术委员会资助课题(17DZ2280800)作者简介:孙迎霞(1978—),女,硕士,高级工程师,研究领域为空间推进系统

更新日期/Last Update: 2019-12-20