|Table of Contents|

Analysison saturation process of liquid hydrogen with heat leakage in closed container(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2018年03期
Page:
49-53
Research Field:
推进剂
Publishing date:

Info

Title:
Analysison saturation process of liquid hydrogen with heat leakage in closed container
Author(s):
LIANG Huaixi1 Han Zhanxiu1 LI Qing2
1. Beijing Institute of Aerospace Testing Technology, Beijing 100074,China; 2. China Ordnance Industrial Standardization Research Institute Beijing 100089,China
Keywords:
hydrogen-oxygen rocket engine closed container liquid hydrogen saturation process analysis
PACS:
V434.3-34
DOI:
-
Abstract:
The state variation of the saturation process for the liquid hydrogen in a closed container is presented according to the practical problem in the tests of a hydrogen-oxygen rocket engine and its components. The analysis results of this problem can be used for the safety assessment of the test process. In this paper, the mass and energy conservation equations are used to establish a mathematic model for the saturated condition of hydrogen medium in the closed container. The saturation process is qualitatively analyzed according to the mathematical analysis results of the model, and the conception of critical filling rate is proposed creatively. It is found that the saturation state process can be divided into different processes of complete vaporization, complete liquidation and intermediate saturation equilibrium. Combined with a typical engineering case of liquid hydrogen test, the state parameters of the saturation process are calculated by means of the mathematic model. The calculated results are in good agreement with the qualitative analysis. The rule of the saturation process of liquid hydrogen in the closed container is summarized.It is indicated that the liquid hydrogen can be completely vaporized when the filling rate of liquid hydrogen is low, and the liquid hydrogen can be fully expanded when the filling rate is high. In addition, the liquid hydrogen will expand and completely fill the test duct when the filling rate of test duct is 90%, which is easy to cause an overpressure damage risk.

References:

[1] 王竹溪. 热力学[M]. 北京:北京大学出版社.2003.
[2] 陈国邦,包锐,黄永华. 低温工程技术数据卷[M]. 北京:化学工业出版社. 2005.
[3] 弗罗斯特W. 低温传热学[M]. 陈叔平,陈玉生译. 北京:科学出版社. 1982:228-237.
[4] 徐烈,赵兰萍,李兆慈,等.低温容器无损贮存中的最佳充满率[J].低温工程,1999(4):126-131.
[5] 荣顺,高鲁嘉,徐芳.低温容器无损贮存规律[J].北京:低温工程,1999(4):132-135.
[6] 穆鹏刚,童飞,蒲光荣,等.温度对贮箱增压系统的影响分析[J]. 火箭推进, 2015,41(4):74-78.
MU Penggang, TONG Fei, PU Guangrong, et al. Influence of temperature on tank pressurization system [J]. Journal of rocket propulsion, 2015, 41(4): 74-78.
[7] 范瑞祥, 田玉蓉, 黄兵. 新一代运载火箭增压技术研究[J].火箭推进, 2012,38(4): 9-16.
FANRuixiang, TIAN Yurong, HUANG Bing. Study on pressurization technology of the new generation launch vehicle [J]. Journal of rocket propulsion, 2012, 38(4): 9-16.
[8] 陈春富, 李茂, 王树光.液氧贮箱增压过程研究[J].火箭推进, 2013,39(4): 80-84.
CHEN Chunfu, LI Mao, WANG Shunguang. Numerical study on pressurization process of liquid oxygen tank [J]. Journal of rocket propulsion, 2013, 39(4): 80-84.
[9] ZILLIAC G, Karabeyoglu M A. Modeling of propellant tank pressurization: AIAA2005-3549 [R].USA: AIAA,2005.
[10] LI Zhaoci, XU Lie, SUN Heng, et al. Investigation on performances of non-loss storage for cryogenic liquefied gas [J]. Cryogenics, 2004, 44(5): 357-362.
[11] FADDOUL J M, MCLNTYRE S D. The NASA cryogenic fluid management technology program plan: NASA-TM 1999-105256 [R]. USA: NASA, 1999.
[12] AHUJA Vineet, HOSANGADI Ashvin, MATTICK Stephen, et al. Computational analyses of pressurization in cryo genic tanks: AIAA-2008-4752 [R]. USA: AIAA, 2008.

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Last Update: 2018-06-30