Numerical Simulation of Secondary Combustion Gas Field in Concentric Canister Launcher and Improvement Measures of Guider

doi:10.3969/j.issn.1000-1093.2014.01.009

Abstract

Abstract: To study the thermo-impact of jet flow secondary combustion, a three-order accurate MUSCL scheme is employed to solve 12-step reaction and 11 species chemical reactions of H₂/CO mixed combustion gas field in concentric canister launcher(CCL), and the zone moving and dynamically layering methods are adopted to simulate missile motion. Compared with free-jet flow experimental results, it is shown that the method is feasible. The jet field characteristic with chemical reactions and the temperature changes of missile body are analyzed. The results show that chemical reaction occures in mixing layer of gas and air out of cylinder and there is no reaction in CCL tube. Reflective shock is due to the mutual interference of gas out of cylinder, exhaust plume and missile tail. The axial temperature of reaction flow field is higher than those of frozen flow and single component flow. Guider can reduce missile body temperature and its height optimal value is near 1.5 times the clearances inside and outside cylinder. The research can provide theoretical significance for the optimization design of CCL structures.

Key words: fluid mechanics, concentric canister launcher, secondary combustion, dynamic mesh update method, guider

CLC Number:

TJ768

HU Xiao-lei, LE Gui-gao, MA Da-wei, ZHU Zhong-ling. Numerical Simulation of Secondary Combustion Gas Field in Concentric Canister Launcher and Improvement Measures of Guider[J]. Acta Armamentarii, 2014, 35(1): 62-69.

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