|Table of Contents|

Study on dynamic characteristics of gas-exhaust-system for liquid oxygen tank used for liquid rocket engine ground test(PDF)

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

Issue:
2018年05期
Page:
71-76
Research Field:
测控与试验
Publishing date:

Info

Title:
Study on dynamic characteristics of gas-exhaust-system for liquid oxygen tank used for liquid rocket engine ground test
Author(s):
XU Hongpeng;  ZHANG Zhitao;  TANG Binyun;  LIU Tao;  DONG Hongbing
Xi'an Aerospace Propulsion Test Technology Institute, Xi'an 710100, China
Keywords:
liquid oxygen tank;  gas-exhaust-system;  dynamic characteristic;  numerical simulation;  tank pressure control
PACS:
V434.3-34
DOI:
-
Abstract:
The research on the dynamic characteristics of gas-exhaust-system was carried out for the ground test of the LOX/kerosene LRE to obtain the response characteristics of gas-exhaust flow and gas-exhaust valve of LOX tank, and verify the applicability of the LOX/kerosene LRE under a low inlet pressure condition, so as to control the pressure decreasing rate in the LOX tank.A 2-D calculation model for the LOX tank was established.In combination with test data, the unsteady heat transfering process of the ullage in the low-temperature tank was studied to define the temperature and state of the exhausted gas.The moving-grid approach of CFD was adopted to establish the 2D model, so that the dynamic and flow characteristics of the values were analyzed.Based on the ideal gas state equation, the calculating formulas of the gas flow and tank pressure were obtained while the tank pressure calculation model was refined.This model can be used to calculate the pressure decreasing rate in the tank, which can also provide a reference for calculation of the exact beginning time of the tank pressure control.

References:

[1] 程向华,厉彦忠,陈二锋,等.新型运载火箭射前预冷液氧贮箱热分层的数值研究[J].西安交通大学学报,2008,42(9):1133-1136.
[2] 程向华,厉彦忠,陈二峰.火箭液氧贮箱热分层现象数值模拟[J].低温工程,2008(2):10-13.
[3] 王磊,厉彦忠,李翠,等.液体火箭贮箱增压排液过程三种气枕模型的数值对比[J].航空动力学报,2011,26(9):1996-2001.
[4] 王赞社,顾兆林,冯诗愚,等.低温推进剂贮箱增压过程的传热传质数学模拟[J].低温工程,2007(6):29-37.
[5] 陈阳,高芳,张振鹏.低温推进剂贮箱增压系统分布参数数值仿真与贮箱的有限体积模型[J].航空动力学报,2008,23(2):323-328.
[6] 尚存存,耑锐,王文.液氧贮箱增压过程中气枕空间温度场的数值模拟[J].低温工程,2011(6):47-65.
[7] 王磊,厉彦忠,李翠,等.液体火箭贮箱增压排液过程温度场数值研究[J].航空动力学报,2011,26(8):1893-1899.
[8] 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):10-46.
FAN Ruixiang, TIAN Yurong, HUANG Bing.Study on pressurization of new generation launch vehicle [J].Journal of rocket propulsion, 2012,38(4): 10-46.
[9] 穆朋刚, 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.
[10] 王赞社, 顾兆林, 赵红轩, 王广飙.低温贮箱多路管道增压的一种模糊算法研究[J].火箭推进,2008,34(2):7-12.
WANG Zanshe, GU Zhaolin, ZHAO Hongxuan, et al.Research on fuzzy control algorithm of cryogenic propellant-tank pressurization [J].Journal of rocket propulsion, 2008,34(2): 7-12.
[11] 周振君,雷刚,王天祥,等.低温液氮贮箱静置增压及放气特性分析[J].低温技术,2015,43(12):9-12.

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