Experimental investigation of combustion mode transitions on solid rocket scramjet combustor

Libei Zhao; Zhixun Xia; Likun MaBinbin ChenYunchao FengPengnian YangChaolong LiYifan Duan

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Experimental investigation of combustion mode transitions on solid rocket scramjet combustor

机译：Experimental investigation of combustion mode transitions on solid rocket scramjet combustor

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Based on the design configuration of a solid scramjet combustor, the direct-connect experimented investigation of combustion modes transition was carried out, simulating inflow conditions of Mach number 6.0 and flight altitude 25 km. It is the first experimental investigation using boron-based propellant as fuel to realize the transition between scram-mode and ram-mode, and to assess different operating modes of the combustor and their impacts on performance. In addition, the experimental pressure data are used to distinguish the combustion modes accurately. The experiment shows that, the structure of the shock train changes substantially during the mode transition. The combustion efficiency η, total pressure recovery coefficient S and the specific impulse of bench thrust Isp increase greatly when the combustion mode transforms from scram-mode to ram-mode. In addition, for inflow condition of Mach number 6.0 and flight altitude 25 km, the performance of the solid rocket scramjet combustor operating in ram-mode is better, and the isobaric combustion also occurs in the combustor.

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来源
《Aerospace science and technology》 |2022年第11期|107945.1-107945.11|共11页
作者
Libei Zhao; Zhixun Xia; Likun MaBinbin ChenYunchao FengPengnian YangChaolong LiYifan Duan;
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作者单位

College of Aerospace Science and Engineering, National University of Defense Technology, Changsha, 410073, China;

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收录信息美国《科学引文索引》(SCI);美国《工程索引》(EI);
原文格式 PDF
正文语种英语
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关键词
Solid rocket scramjet; Mode transition; Combustion mode recognition; Boron-based propellant; Dual-mode scramjet;

Experimental investigation of combustion mode transitions on solid rocket scramjet combustor

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