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《Journal of Solid Rocket Technology》 2010-02
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Numerical analysis on combustion process of simplified composite solid propellant based on BDP multi-flames model

YANG Yue-cheng,ZHOU Zhi-qing,ZHOU Wei,MA Chang-bing(201 Faculty,The Secondary Artillery Engineering Institute,Xi'an 710025,China)  
Composite solid propellant is a kind of typical energetic material with heterogeneous configuration in meso-scale.Due to its complexity of meso topology,it is necessary to establish simplified meso geometrical model and proper combustion model according to the characteristic of composite propellant so as to study the structure of combustion flame.This paper introduces the idea of heterogeneous "propellant unit",and then,applies multi-steps chemical reaction dynamics mechanism based on the BDP theoretic combustion model,finally,establishes 2-D meso combustion numerical model of AP/HTPB sandwich propellant.The effect on the variation of flame structure,burning surface geometry as well as burning rate with different ambient pressure and propellant stoichiometric(HTPB width) are discussed through computation and ananysis.The computational results conform with the report in some literatures,which proves validity of the model.Numerical simulation of the combustion process of sandwich propellant model is capable to capture meso-structure of combustion flames and offers the information of the combustion field in detail,which can be used to verify or improve theoretic combustion model,and then offers a meaningful numerical model and research technique,relying on which it is possible to study the macro combustion performance of heterogeneous propellant from meso scale.
【Fund】: 国家重大安全基础研究项目(973-61338)
【CateGory Index】: V512
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