液体火箭发动机爆震波点火技术初步研究

郭红杰; 梁国柱; 马彬; 张振鹏

液体火箭发动机爆震波点火技术初步研究

北京航空航天大学宇航学院, 北京 100083

基金项目: 国家高技术863计划资助项目(2002AA726021)

详细信息

作者简介:
郭红杰(1978-),男,河南安阳人,博士生, guohongjie@sa.buaa.edu.cn.

中图分类号: V 43411
计量
- 文章访问数: 2645
- HTML全文浏览量: 45
- PDF下载量: 896
- 被引次数: 0
出版历程
- 收稿日期: 2003-10-17
- 网络出版日期: 2005-04-30

Preliminary investigation on detonation wave ignition technique

School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

摘要

摘要: 对液体火箭发动机各种点火技术优缺点进行了对比分析,探讨了各种点火技术方案应用于未来先进推进系统的多管多次点火系统的可行性,讨论了各种点火技术应用方案的结构形式.对爆震波点火技术进行了初步研究,建立了气氢气氧爆震波点火的简化理论分析模型,对其在实际液氢液氧发动机中应用的具体方案进行了分析.分析结果表明,爆震波点火技术可以由低压混合气体产生高温高压的爆震产物,爆震波以高马赫数速度传播,迅速到达各点火位置.爆震波点火技术具备良好的同步性能和简单的结构方案形式,适用于液体火箭发动机多管多次同步点火.
- 火箭发动机 /
- 爆震 /
- 点火 /
- 点火系统
Abstract: The relative merits of several ignition techniques of liquid propellant rocket engine were analyzed. The feasibility of each ignition technique applicable to multi-chamber multi-run ignition system of future advanced propulsion system was discussed. The structural configurations of application scenarios of ignition techniques were considered. Preliminary investigation on detonation wave ignition technique was made and a simplified theoretically analytical model for the mixture of gaseous hydrogen and gaseous oxygen was established. The applicable schemes of the detonation wave ignition for liquid rocket engine were analyzed. The analysis results show that the detonation wave technique can product high pressure ratio and high temperature ratio by low pressure premix detonative gases. The detonation wave propagates with high mach number, and the detonation wave ignition source arrives each ignition place immediately. The detonation wave ignition technique has unique synchronic characteristic and simple structural configuration. It is suitable to multi-chamber multi-run synchronic ignition of liquid propellant rocket engine.
- rocket engines /
- detonation /
- ignition /
- ignition systems

HTML全文

参考文献(1)

[1] urawski R L, Green J M. Catalytic ignition of hydrogen and oxygen propellants . AIAA-88-3300,1988 [2] Fuller P N. Advanced ignition systems final report . NASA N71-35152, NASA-CR-119928,1971 [3] 森元. 氢氧火箭发动机及其低温技术[M]. 北京:国防工业出版社,1995 Zhu Senyuan. Hydrogen/oxygen rocket engine and low temperature technology[M]. Beijing:National Defense Industry Press,1995 (in Chinese) [4] mmich H, Caporicci M. Status of the FESTIP rocket propulsion technology programme . AIAA-97-3311,1997 [5] 国舟,童晓艳,梁国柱,等. 液体火箭发动机气动谐振点火技术的研究 . 宇航学报,2001,22(4):81~84 Zhang Guozhou, Tong Xiaoyan, Liang Guozhu, et al. Investigation on gas dynamic resonance ignition technology for liquid propellant rocket engine[J]. Journal of Astronautics, 2001, 22(4):81~84(in Chinese) [6] 国柱,马彬,张国舟,等. 气动谐振点火技术研究[J]. 推进技术,2001,22(4):286~289 Liang Guozhu, Ma Bin, Zhang Guozhou, et al. Investigation on gas dynamic resonance tube ignition method[J]. Journal of Propulsion Technology, 2001, 22(4):286~289 (in Chinese) [7] tabinsky L. Analytical and experimental study of resonance ignition tubes . NASA N74-17646,1973 [8] Bollinger L, Fong M, Edse R. Experimental measurements and theoretical analysis of detonation induction distances[J]. ARS Journal, 1961,31(5):588~595 [9] 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 resonace igniters of multi-thruster [J]. Journal of Propulsion Technology, 2002,23(5):402~405 (in Chinese) [10] 一白,刘宇,覃粒子,等. 气氧酒精多管点火器试验研究[J]. 北京航空航天大学学报,2003,29(1):54~58 Wang Yibai, Liu Yu, Qin Lizi, et al. Experimental studies on gas-oxygen/alcohol multi-pipe igniter[J]. Journal of Beijing University of Aeronautics and Astronautics, 2003,29(1):54~58 (in Chinese) [11] iou L C. Combustion-wave ignition for rocket engines . NASA 92-20043,1992 [12] Lockheed Martin. Allied Signal Aerospace, Rocketdyne. X-33 Phase II annual performance report . NASA-CR-205695,1997 [13] Walter S K. Research & technology 1998 . NASA TM-1999-208815, 1999 [14] 红杰,梁国柱,马彬,等. 爆震波点火技术基本特性实验[J]. 推进技术,2005,26(1):76~79 Guo Hongjie, Liang Guozhu, Ma Bin, et al. Preliminary experimental investigation on detonation wave ignition technique[J]. Journal of Propulsion Technology,2005, 26(1):76~79(in Chinese) [15] 红杰,梁国柱,马彬,等. 爆震波多管点火技术试验测试研究 . 见:第五届海内外华人航天科技研讨会 . 西安,2004 Guo Hongjie, Liang Guozhu, Ma Bin. et al. Experimental testing investigation on detonation wave ignition technique . In:The 5^th Global Chinese Symposium on Space Science and Technique . Xian, 2004(in Chinese) [16] enner S S,Williams F A. Detonation and two phase flow[M]. New York:Academic Press, 1962. 47~63

施引文献

资源附件(0)

访问统计