航天推进技术研究院主办
[1]徐鸿鹏,张志涛,唐斌运,等.发动机试验液氧贮箱放气系统动态特性研究[J].火箭推进,2018,44(05):71-76.
XU Hongpeng,ZHANG Zhitao,TANG Binyun,et al.Study on dynamic characteristics of gas-exhaust-system for liquid oxygen tank used for liquid rocket engine ground test[J].Journal of Rocket Propulsion,2018,44(05):71-76.
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XU Hongpeng,ZHANG Zhitao,TANG Binyun,et al.Study on dynamic characteristics of gas-exhaust-system for liquid oxygen tank used for liquid rocket engine ground test[J].Journal of Rocket Propulsion,2018,44(05):71-76.
发动机试验液氧贮箱放气系统动态特性研究
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
44
期数:
2018年05期
页码:
71-76
栏目:
测控与试验
出版日期:
2018-10-31
- Title:
- Study on dynamic characteristics of gas-exhaust-system for liquid oxygen tank used for liquid rocket engine ground test
- 文章编号:
- 1672-9374(2018)05-0071-06
- Keywords:
- liquid oxygen tank; gas-exhaust-system; dynamic characteristic; numerical simulation; tank pressure control
- 分类号:
- V434.3-34
- 文献标志码:
- A
- 摘要:
- 在液氧/煤油火箭发动机地面试验中,为得到液氧贮箱放气系统放气流量与放气阀门动作的响应特性,从而控制箱压的下降速率,验证液氧煤油发动机在低入口压力条件下的工作适应性,对液氧贮箱放气系统的动态特性进行了研究。建立了液氧贮箱二维计算模型,结合试验数据,对低温贮箱内气枕空间的非稳态换热过程进行研究,确定放出气体温度以及相应状态。应用CFD的动网格技术,建立二维计算模型,对放气系统阀门的开关动态特性与过流流量特性进行综合分析,获得了不同通径放气管路的放气流量与箱压的计算关联式,基于理想气体状态方程,完善了箱压计算理论模型。应用该模型量化分析箱压下降速率,为计算箱压控制的准确时间节点提供了操作参考。
- 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.
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相似文献/References:
[1]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(04):80.
CHEN Chun-fu,LI Mao,WANG Shu-guang.Numerical study on pressurization process of liquid oxygen tank[J].Journal of Rocket Propulsion,2013,39(05):80.
备注/Memo
收稿日期:2017-06-20
基金项目: 装发共用技术科研项目(51317040101)
作者简介: 徐鸿鹏(1988—),男,工程师,研究领域为液体火箭发动机试验技术
更新日期/Last Update:
1900-01-01