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Experimental investigation of combustion mode transitions on solid rocket scramjet combustor

Abstract

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 ?, total pressure recovery coefficient ? 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.

» Author: Libei Zhao, Zhixun Xia, Likun Ma, Binbin Chen, Yunchao Feng, Pengnian Yang, Chaolong Li, Yifan Duan

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