航天推进技术研究院主办
Study on the multi-start system of turbopump-fed rocket engine with storable propellants[J].Journal of Rocket Propulsion,2010,36(03):15-18.
可贮存推进剂泵压式液体火箭发动机多次起动系统研究
- Title:
- Study on the multi-start system of turbopump-fed rocket engine with storable propellants
- 文章编号:
- (2010)03-0015-04
- 分类号:
- V434
- 文献标志码:
- A
- 摘要:
- 在推力超过一定量级、任务时间较长的情况下,泵压式发动机比挤压式发动机具有明显的技术优势。从国内外上面级及重型空间飞行器推进系统的发展需求来看,均要求其主发动机具有多次起动工作的能力。针对采用可贮存推进剂的泵压式液体发动机多次起动需求,对几种可选的多次起动系统方案进行了比较分析,介绍了起动箱式起动系统的研究情况。
- Abstract:
- For high level thrust requirement and long duration mission, the turbopump-fed rocket engine has more advantages than that of the pressure-fed rocket engine. To meet the need of the development of propulsion system for upper stage and heavy space vehicle, the engine should have the capability of multi-start. This paper aimed at the need for the multi-start capability of the storable propellant turbopump-fed rocket engine. Several different designs of the multi-start system were analyzed and efforts on the start-tank system development were described.
参考文献/References:
[1]刘国球. 液体火箭发动机原理[M].北京: 宇航出版社, 1993. [2] 休泽尔D K. 液体火箭发动机现代工程设计[M]. 朱宁昌译. 北京: 宇航出版社, 2004. [3]颜庆津. 数值分析[M]. 北京: 北京航空航天大学出版社, 1992. [4]江宏俊. 液体力学[M]. 西安: 高等教育出版社, 1985.
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备注/Memo
收稿日期:2010-02-13;修回日期:2010-04-07。
作者简介: 张涛(1971—),男,高级工程师,研究领域为液体火箭发动机总体设计技术。