Experimental Studies on GasOxygen/Alcohol MultiPipe Igniter
-
摘要: 多管同步点火是塞式喷管的一项关键技术,介绍了气氧酒精多管点火器的设计和试验情况.研究了推进剂的混合比、点火器的工作时间、燃气导管的材料和几何尺寸、点火器的冷却方式,以及补氧燃烧措施对多管点火性能的影响,同时对高空情况下的点火方法进行了初步探讨.最后确定了多管点火器的工作参数,实现了可靠的多管同步点火.
-
关键词:
- 点火 /
- 试验 /
- 液体推进剂火箭发动机 /
- 塞式喷管
Abstract: Multi-pipe synchronous ignition technique is one of the key techniques of aerospike engine. Design and experiments of a gas-oxygen/alcohol multi-pipe igniter were introduced. The key factors influencing multi-pipe ignition were studied, which include propellants mixture ratio, time of igniting, material and geometrical size of the pipe, methods used to cool the igniter, and oxygen supply combustion. In addition, ignition methods at high altitude were also investigated. On the above basis, parameters of the igniter were determined, multi-pipe synchronous ignition was realized.-
Key words:
- ignition /
- test /
- liquid rocket engines /
- aerospike nozzle
-
[1] Catchpole J E. X-33 testing the future[J]. Spaceflight,1999, 41:114~116 [2] Kumakama A, Onodera T, Yoshida A. A study of aerospike-nozzle engines. AIAA Paper 98-3526, 1998 [3] 刘国球,任汉芬,朱宁昌,等. 液体火箭发动机原理[M]. 北京:宇航出版社, 1993 Liu Guoqiu, Ren Hanfen, Zhu Ningchang,et al. Liquid rocket engine principle[M]. Beijing:Space Navigation Press,1993(in Chinese) [4] 李宜敏,张中钦,张远君. 固体火箭发动机原理[M]. 北京:北京航空航天大学出版社, 1991 Li Yimin, Zhang Zhongqin, Zhang Yuanjun. Solid rocket engine principle[M]. Beijing:Beijing University of Aeronautics and Astronautics Press,1991(in Chinese) [5] 郭霄峰,李耀华,蒋亦绶,等. 液体火箭发动机试验[M]. 北京:宇航出版社,1990 Guo Xiaofeng, Li Yaohua, Jiang Yishou,et al. Liquid rocket engine experiment[M]. Beijing:Space Navigation Press,1990(in Chinese) -
点击查看大图
计量
- 文章访问数: 2365
- HTML全文浏览量: 155
- PDF下载量: 768
- 被引次数: 0
下载:
