航天推进技术研究院主办
[1]赵海龙,张成印,曹红娟,等.30 kN上面级液氧甲烷发动机方案[J].火箭推进,2021,47(01):13-20.
ZHAO Hailong,ZHANG Chengyin,CAO Hongjuan,et al.System scheme of a 30 kN upstage LOX/methane engine[J].Journal of Rocket Propulsion,2021,47(01):13-20.
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ZHAO Hailong,ZHANG Chengyin,CAO Hongjuan,et al.System scheme of a 30 kN upstage LOX/methane engine[J].Journal of Rocket Propulsion,2021,47(01):13-20.
30 kN上面级液氧甲烷发动机方案
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
47
期数:
2021年01期
页码:
13-20
栏目:
研究与设计
出版日期:
2021-02-28
- Title:
- System scheme of a 30 kN upstage LOX/methane engine
- 文章编号:
- 1672-9374(2021)01-0013-08
- Keywords:
- upstage; engine; LOX/methane; expander cycle
- 分类号:
- V434.2
- 文献标志码:
- A
- 摘要:
- 上面级是介于运载火箭与航天器之间的相对独立的一级,具备轨道转移能力,可将有效载荷精确送入预定轨道。上面级是提高火箭运载能力和提升任务适应性的有效途径,上面级发动机是实现该目标的关键。长期在轨的高性能上面级,要求主动力具备比冲高、空间可长期贮存和高可靠性等能力。针对此技术需求,对比分析了上面级发动机的系统方案; 设计了采用泵压膨胀循环、双涡轮泵串联的30 kN上面级发动机系统方案; 重点介绍了推力室、涡轮泵和发动机总装集成等关键组件的研究进展。研究表明:液氧甲烷推进剂非常适用于长期在轨上面级发动机; 闭式膨胀循环发动机系统是长期在轨上面级动力系统方案的首选; 推力室和涡轮泵等组件的研制结果,初步证明了发动机系统及组件方案的可行性; 发动机总装和演示试验方案设计工作,为深入开展发动机系统技术研究打下了良好基础。
- Abstract:
- The upstage is an relatively independent stage between the launch vehicle and the spacecraft, it has the ability of orbit transfer and can accurately send the payload into predetermined orbit. The upstage is an effective way to improve the carrying capacity and adaptability of rocket, and the upstage engine is the key to achieve this goal. The upstage with high performance and long-term on orbit needs the main engine with the capabilities on high specific impulse, long-term storage in space and high reliability. Based on those requirements, this paper compared and analyzed the system scheme of the upstage engine. It designed the system scheme of 30 kN engine of the upstage with expander cycle and double turbo-pump, also introduced the research progress of key technologies including the combustion chamber, turbo-pump and engine system integration.The results show that LOX/methane propellant is suitable for long-term on orbit upstage engine. The closed expander cycle engine system is the best choice for long-term on orbit upstage power system; the research results of combustion chamber, turbo-pump and other components have preliminarily proved the feasibility of design scheme of engine system and components. The design of engine prototype assembly and demonstrate scheme lays a good foundation for further research on engine system technology.
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相似文献/References:
[1]张爱文[],朱浩[],蔡国飙[],等.并联式固液上面级动力系统研究[J].火箭推进,2016,42(06):9.
ZHANG Aiwen[],ZHU Hao[],CAI Guobiao[],et al.Study on hybrid upper stage propulsion system with parallel structure[J].Journal of Rocket Propulsion,2016,42(01):9.
[2]程诚,曲波,林庆国.Morpheus液氧/甲烷一体化推进系统研究综述[J].火箭推进,2018,44(05):1.
CHENG Cheng,QU Bo,et al.Overview of integrated cryogenic propulsion system based on liquid oxygen/liquid methane for Morpheus[J].Journal of Rocket Propulsion,2018,44(01):1.
备注/Memo
收稿日期:2020-07-22
基金项目:装备预研航天科技联合基金(6141B061207)
作者简介:赵海龙(1977—),男,硕士,高级工程师,研究领域为液体火箭发动机系统。
更新日期/Last Update:
2021-02-20