航天推进技术研究院主办
[1]郑大勇,陶瑞峰,张 玺,等.大推力氢氧发动机关键技术及解决途径[J].火箭推进,2014,40(02):22-27.
ZHENG Da-yong,TAO Rui-feng,ZHANG Xi,et al.Study on key technology for large thrust LOX/LH2 rocket engine[J].Journal of Rocket Propulsion,2014,40(02):22-27.
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ZHENG Da-yong,TAO Rui-feng,ZHANG Xi,et al.Study on key technology for large thrust LOX/LH2 rocket engine[J].Journal of Rocket Propulsion,2014,40(02):22-27.
大推力氢氧发动机关键技术及解决途径
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
40
期数:
2014年02期
页码:
22-27
栏目:
研究与设计
出版日期:
2014-04-28
- Title:
- Study on key technology for large thrust LOX/LH2 rocket engine
- 分类号:
- V434-34
- 文献标志码:
- A
- 摘要:
- 200吨级大推力氢氧发动机是重型运载火箭的基础，是航天强国的重要标志。与以往氢氧发动机相比，大推力氢氧发动机推力量级和结构参数均有大幅度提高，是目前世界上推力最大的高空发动机，发动机的设计、生产和试验技术跨度大、要求高，需要开展一系列的技术攻关工作。根据200吨级大推力氢氧发动机技术特点，介绍了发动机的总体技术方案，根据发动机技术特点和使用要求，梳理了一批制约发动机技术水平提高、系统方案优化和工程实施的关键技术，并提出了解决途径。
- Abstract:
- The large thrust LOX/LH2 rocket engine is the basis of the development of heavy-lift launch vehicle. In comparison with the previous LOX/LH2 engine, the thrust level and structure parameters of the large thrust LOX/LH2 engine have been enhanced substantially. It has the largest thrust level around the world. With the high requirements, engine's design, manufacture, and test require a series of hard work on key technology research. Based on the technology features of the large thrust LOX/LH2 engine, the overall technical scheme of the engine is introduced in this paper. According to the technical features and application requirements of the engine, a batch of key technologies that restrain the engine technology improvement, system optimization and project implementation are listed in the paper and the solutions are put forward.
参考文献/References:
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备注/Memo
收稿日期：2013-10-17；修回日期：2013-12-24 基金项目：中国航天科技集团公司支撑项目（2011JY06） 作者简介：郑大勇（1978—），男，高级工程师，研究领域为液体火箭发动机系统设计
更新日期/Last Update:
1900-01-01