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�������պ����ѧѧ�� 2005, Vol. 31 Issue (04) :375-380    DOI:
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Preliminary investigation on detonation wave ignition technique
Guo Hongjie, Liang Guozhu, Ma Bin, Zhang Zhenpen*
School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

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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.
Keywords�� rocket engines   detonation   ignition   ignition systems     
Received 2003-10-17;
Fund:

���Ҹ߼���863�ƻ�������Ŀ(2002AA726021)

About author: �����(1978-),��,���ϰ�����,��ʿ��, guohongjie@sa.buaa.edu.cn.
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�����, ������, ���, ������.Һ�������������𲨵���������о�[J]  �������պ����ѧѧ��, 2005,V31(04): 375-380
Guo Hongjie, Liang Guozhu, Ma Bin, Zhang Zhenpen.Preliminary investigation on detonation wave ignition technique[J]  JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2005,V31(04): 375-380
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http://bhxb.buaa.edu.cn//CN/     ��     http://bhxb.buaa.edu.cn//CN/Y2005/V31/I04/375
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