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Zhou Z.-Q.,The Institute of Survival Techniques and Performance Evaluation of Aerospacecraft | Liang W.,The Institute of Survival Techniques and Performance Evaluation of Aerospacecraft | Liu X.-M.,The Institute of Survival Techniques and Performance Evaluation of Aerospacecraft | Qi Z.-H.,The Institute of Survival Techniques and Performance Evaluation of Aerospacecraft | And 2 more authors.
Guti Huojian Jishu/Journal of Solid Rocket Technology | Year: 2013

Considering of the combustion characteristics of AP/HTPB composite solid propellant, a heat-flux coupled steady combustion numerical model of sandwich propellant based on complex gas kinetics was set up to study the flame structure and combustion characteristic of composite solid propellant. A complex gas kinetics composed of 49-species and 328-reactions was proposed to model flame, a one-step condensed total kinetics was used to determine initial gas species and heat release, an equivalent source term method and gas/solid heat-flux coupled condition was applied to represent gas phase mass-addition process of burning surface. The computational results show that, at lower pressure, total flame behaved as pre-mixed structure, as pressure increased, a high temperature diffusion flame zone was formed along AP/HTPB material surface, and the leading-edge flame became closer to burning surface, while flame blend point got farer. The computational burning rate pressure index was about 0.326~0.683, and the variation of burning rate with pressure, when binder width was about 100~176 μm, was consistent with experimental burning rate and computational burning rate of Knott's computational burning rate. Source

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