Effect of Cavity on Scramjet Combustion Characteristics of Boron-containing Solid Rocket

doi:10.12382/bgxb.2021.0280

Abstract

Abstract: Cavity is often used to enhance the mixing of air and gas in scramjet，and improve the flame stability and combustion efficiency. The characteristics of flow field in supersonic combustor depend on the structure and distribution of cavity. In order to optimize the cavity structure and its distribution，and improve the combustion performance of secondary combustion chamber in solid rocket scramjet，the effects of cavity length-to-depth ratio and rear tilt angle on the combustion characteristics of boron-containing solid rocket scramjet were studied by numerical method. The calculation results show that, when the cavity length is constant and the length-to-depth ratios of cavity are 5，3.75，3，2.5，2.14，1.85，1.67，respectively, the length-to-depth ratio of cavity is 1.85，and the combustion efficiency and specific impulse of boron particles are the highest. When the length-to-depth ratio of cavity is 1.85，and the rear tilt angle of cavity is changed from 90° to 175°， the combustion efficiency of boron particles increases with the increase in the tilt angle. When the rear tilt angle is 175°，the combustion efficiency of boron particles is the highest，but the total pressure recovery coefficient and specific impulse are the smallest. And the specific impulse is the highest when the rear tilt angle is 165°.

Key words: boron-containingsolidrocket, cavity, scramjet, combustioncharacteristic

CLC Number:

V236

LING Jiang， XU Yihua， SUN Haijun， LIU Weigen， FENG Xiping. Effect of Cavity on Scramjet Combustion Characteristics of Boron-containing Solid Rocket[J]. Acta Armamentarii, 2022, 43(5): 1054-1062.

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第43卷第5期2022 年5月
兵工学报ACTA ARMAMENTARII
Vol.43No.5May2022

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