航天推进技术研究院主办
[1]李 程,刘站国,徐浩海.双推力室起动同步性研究[J].火箭推进,2014,40(04):16-21.
LI Cheng,LIU Zhan-guo,XU Hao-hai.Study on synchronous ignition of dual-thrust chamber engine[J].Journal of Rocket Propulsion,2014,40(04):16-21.
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LI Cheng,LIU Zhan-guo,XU Hao-hai.Study on synchronous ignition of dual-thrust chamber engine[J].Journal of Rocket Propulsion,2014,40(04):16-21.
双推力室起动同步性研究
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
40
期数:
2014年04期
页码:
16-21
栏目:
研究与设计
出版日期:
2014-08-28
- Title:
- Study on synchronous ignition of dual-thrust chamber engine
- 分类号:
- V434-34
- 文献标志码:
- A
- 摘要:
- 我国新一代大推力液氧/煤油补燃发动机采用双推力室方案，发动机起动时存在推力室点火不同步情况。以500 t级液氧/煤油补燃发动机为研究对象，针对起动时推力室点火不同步问题，对发动机推力室燃料路的控制方案进行了研究。建立了描述补燃循环发动机起动过程的数学模型，搭建了双推力室发动机起动仿真平台。通过对推力室燃料路两种控制方案的对比分析：指出了从降低发动机系统对双推力室不同步点火的敏感程度考虑，采用2个燃料节流阀分别控制各分支燃料路的方案较优；推力室燃料路采用一个燃料节流阀的控制方案时，推力室冷却套流阻偏差不宜大于1 MPa。
- Abstract:
- LOX/kerosene staged combustion cycle engine of 500 t thrust level is a new generation high thrust liquid propellant rocket engine with dual-thrust chamber system made in China. To eliminate the asynchronous ignition of the LOX/kerosene staged combustion cycle engine with dual-thrust chamber, a control scheme for fuel pathway is investigated in this paper. A mathematic model describing the start-up process and a start-up simulation platform of the rocket engine with dual-thrust chamber were established. Two control schemes for fuel pathway of the thruster were comparatively analyzed. The results show that a control scheme that two throttle valves are adopted respectively on corresponding branch lines is better for the purpose of reducing the sensitivity of asynchronous ignition of dual-thrust chamber engine. The deviation of the resistance between dual-thrust cooling jackets should be less than 1 MPa if only one throttle valve is used.
参考文献/References:
[1]谭永华. 中国重型运载火箭动力系统研究[J]. 火箭推进, 2011, 37(1): 1-6.
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备注/Memo
收稿日期：2014-03-31；修回日期：2014-07-04 基金项目：中国航天科技集团公司支撑项目（2012JY67） 作者简介：李程（1987—），男，硕士研究生，研究领域为液体火箭发动机系统仿真
更新日期/Last Update:
1900-01-01