基于BDP多火焰模型的简化复合固体推进剂燃烧数值分析  

Numerical analysis on combustion process of simplified composite solid propellant based on BDP multi-flames model

作　　者：杨月诚[1] 周志清[1] 周伟[1] 马昌兵[1] 

机构地区：[1]第二炮兵工程学院201室,西安710025

出　　处：《固体火箭技术》2010年第2期185-190,共6页Journal of Solid Rocket Technology

基　　金：国家重大安全基础研究项目(973-61338)

摘　　要：复合固体推进剂是一种典型的具有细观异质结构的含能材料,其细观结构形态非常复杂,研究其燃烧火焰结构,首先需针对复合推进剂特点,建立简化的细观几何模型与合适的燃烧模型。文中引入异质"推进剂胞元"的思想,对复合推进剂细观结构进行简化,并应用基于BDP理论燃烧模型的多步化学反应动力学机制,建立AP/HTPB三明治推进剂2-D细观燃烧数值模型。计算分析考察了不同环境压强与推进剂计量数(HTPB宽度)对火焰结构、燃面几何型面及燃烧速率的影响。计算结果与相关文献研究结果相符,证明了该模型的有效性。三明治推进剂模型燃烧数值模拟可捕捉到推进剂燃烧火焰细观结构,并提供相关燃烧场详细信息,其结果可用于检验或改进各种理论燃烧模型,并为从细观层面预示异质推进剂宏观燃烧性能提供一种科学可行的数值模型与研究方法。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.

关 键 词：复合固体推进剂 推进剂胞元 三明治模型 燃烧 BDP多火焰模型 

分 类 号：V512[航空宇航科学与技术—航空宇航推进理论与工程]