|Table of Contents|

Dynamic supply characteristics of N2O self-pressurization tank(PDF)

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

Issue:
2018年03期
Page:
43-48
Research Field:
推进剂
Publishing date:

Info

Title:
Dynamic supply characteristics of N2O self-pressurization tank
Author(s):
CHEN Pengfei1;  ZHAO Xiaohui2;  HONG Liu1;  ZHOU Lixin1
1. Science and Technology on Liquid Propulsion Rocket Engine Laboratory, Xi'an 710100, China; 2. Xi'an Aerospace Propulsion Institute,Xi'an 710100, China
Keywords:
N2O self-pressurization tank;  dynamic characteristic;  mathematical model;  simulating calculation
PACS:
V434.23-34
DOI:
-
Abstract:
A mathematical model of N2O self-pressurization tank was built to study the dynamic supply process, and the calculated tank pressure was in good agreement with the experimental results. For the dynamic operating characteristics of self-pressurization tank supplying the liquid medium, the simulation was carried out. The results show that the supply of the liquid propellant is more favorable than that of the gaseous propellant for maintaining the tank pressure and flow rate steadily under the same mass flow rate. Due to the influence of the evaporation endothermic reaction, the tank pressure usually decreases during the supply process. Heating the tank is beneficial to slow down the rate of pressure drop, but there are problems such as the delayed pressure response and the decreased heat exchange area. In addition, it is difficult to obtain a steady dynamic supply pressure.

References:

[1] 贺芳,方涛,李亚裕,等. 新型绿色推进剂研究进展[J].火炸药学报, 2006, 29(4): 54-57.
[2] TILIAKOS N, TYLL J S, HERDY R, et al. Development and testing of a nitrous oxide / propane rocket engine: AIAA 2001-3258 [R].USA: AIAA, 2001.
[3] 宋长青,徐万武,张家奇,等. 氧化亚氮推进技术研究进展[J].火箭推进, 2014, 40(2): 7-15.
SONG Changqing, XU Wanwu, ZHANG Jiaqi, et al. Research progress of nitrous oxide propulsion technology [J].Journal of rocket propulsion, 2014, 40(2): 7-15.(in Chinese)
[4] WHITMORE S A. Engineering model for self-pressurizing saturated-N2O-propellant feed systems [J].Journal of propulsion and power, 2010, 26(4): 706-714.
[5] ZILLIAC G, KARABEYOGLU M A. Modeling of propellant tank pressurization: AIAA-2005-3549 [R].USA: AIAA, 2005.
[6] CASALINO L, PASTRONE D. Optimal design of hybrid rocket motors for microgravity platform [J].Journal of propulsion and power, 2008, 24(3): 491-498.
[7] CASALINO L, PASTRONE D. Optimal design of hybrid rockets with self-pressurizing oxidizer: AIAA 2006-4501 [R].USA: AIAA, 2006.
[8] ZIMMERMAN J E, CANTWELL B J, ZILLIAC G G. Parametric visualization study of self-pressurizing propellant tank dynamics: AIAA 2015-3829 [R].USA: AIAA, 2015.
[9] HAAG G S. Alternative geometry hybrid rockets for spacecraft orbit transfer [D].Guildford, UK: University of Surrey, 2001.
[10] 禹天福,贾月. 一氧化二氮催化分解的研究与应用[J].化学推进剂与高分子材料, 2006, 4(2): 6-10.
[11] 孙威,方杰,蔡国飙. N2O单组元微推进系统贮箱自增压特性[J].北京航空航天大学学报, 2009, 35(11): 1910-1913.
[12] CAI Guobiao, SUN Wei, FANG Jie, et al. Desing and performance characterization of a sub-Newton N2O monopropellant thruster [J].Aerospace science and technology, 2012, 23(1): 439-451.
[13] 陈则韶. 高等工程热力学[M].北京:高等教育出版社, 2008.
[14] 赵红玲,王凤坤. 气液物性估算手册[M].陈圣坤等,译. 北京:化学工业出版社, 2005.
[15] 杨世铭, 陶文铨. 传热学[M].4版. 北京:高等教育出版社, 2006.
[16] 龚亮. 一氧化二氮单组元发动机系统方案设计及仿真研究[D].长沙:国防科技大学, 2013.

Memo

Memo:
-
Last Update: 2018-06-30