氢氧谐振点火器多室同步点火研究

俞南嘉; 张国舟; 宋雅娜; 程圣清

氢氧谐振点火器多室同步点火研究

1.
北京航空航天大学宇航学院, 北京 100083
2. 北京航天动力研究所, 北京 100074

详细信息

作者简介:
俞南嘉(1974-),男,浙江镇海人,博士后, ynj@buaa.edu.cn.

中图分类号: V 431
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- 文章访问数: 2904
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- 被引次数: 0
出版历程
- 收稿日期: 2004-01-13
- 网络出版日期: 2005-06-30

Research on synchronistic multi-ignitions of hydrogen-oxygen resonance ignitor

1.
School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
2. Beijing Aerospace Propulsion Institute, Beijing 100074, China

摘要

摘要: 将气动谐振点火技术应用于塞式喷管发动机多推力室的多次同步点火,研制了新型的氢氧谐振点火器. 通过对点火器的点火响应时间、点火延迟时间、多次点火的重复性以及点火器寿命等方面进行试验研究,验证了新研制的点火器具有起动快、点火延迟时间短、多次点火重复性好、寿命长等特点.采用2个点火器联试的方式进行了5次同步点火试验,研究了连接管路对同步性的影响,并提出了进一步缩短同步性时差的方法,结果表明氢氧谐振点火器完全可以满足塞式喷管发动机多推力室同步点火的要求.
- 谐振 /
- 点火 /
- 同步 /
- 液体推进剂 /
- 火箭发动机
Abstract: New hydrogen-oxygen resonance igniter is designed to use in synchronistic multi-ignition for aerospike nozzle engine. Ignition start time, delay time, repetition of multi-ignition and lifetime of igniter are tested. It can be found from performance tests that the new hydrogen-oxygen resonance igniter with quick starting, short time delay for ignition, good repetition and long life time. Two igniters are used in every synchronistic ignition tests. The pipeline’s influence to synchronization is analyzed. Two ways are put forward for shorten the time difference of synchronistic. It can be concluded from total 5 times synchronistic ignition tests that the new hydrogen-oxygen resonance igniter can satisfy the requirements of synchronistic multi-ignition for aerospike nozzle engine and other liquid propellant rocket engines which need synchronistic multi-ignition.
- resonance /
- ignition /
- synchronization /
- liquid propellants /
- rocket engine

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参考文献(1)

[1] Daniel A H, Don A H. Advanced reusable engines for SSTO . AIAA 91-2181, 1991 [2] Venkatasubramanyam G, James A M. Continuing propulsion evaluations for SSTO . AIAA 94-3158, 1994 [3] Rachuk Dr V, Orlov Dr V, Plis A, et al. The RD-0120 has great potential for low cost reusable engines and for tri-propellant SSTO validations . E-51124 [4] 俞南嘉,宋雅娜,张国舟,等. 氢氧点火器多管同步点火方案论证报告 . 中国国防科学技术报告, 2003 Yu Nanjia, Song Yana, Zhang Guozhou, et al. Expound and prove report of simultaneous multi-ignition project of hydrogen-oxygen igniter . Chinese Defense Science and Technology Report, 2003(in Chinese) [5] 童晓艳,马彬,张国舟. 塞式喷管发动机点火方案的研究[J]. 宇航学报,2001,22(4):62~66 Tong Xiaoyan, Ma Bin, Zhang Guozhou. Investigation on the ignition methods of aerospike nozzle engine [J]. Journal of Astronautics, 2001, 22(4):62~66 (in Chinese) [6] 童晓艳. 气动谐振加热机理及液体火箭发动机多室多次点火技术研究 . 北京:北京航空航天大学宇航学院, 2001 Tong Xiaoyan. Investigation on gas dynamic resonance heating mechanisms and rocket engine multi-thruster repeated ignition technology . Beijing:School of Astronautics, Beijing University of Aeronautics and Astronautics, 2001 (in Chinese) [7] 童晓艳,张国舟,马彬,等. 多推力室的气动谐振点火器研究[J]. 推进技术,2002,23(5):402~405 Tong Xiaoyan, Zhang Guozhou, Ma Bin, et al. Research on gas dynamic resonance igniters of multi-thruster [J]. Journal of Propulsion Technology, 2002, 23(5):402~405 (in Chinese)

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