基于单元法的三维装药通用燃面计算  

Generalized Burning Surface Calculation of Three Dimensional Propellant Based on Element Method

作　　者：熊文波[1] 刘宇[1] 任军学[1] 张晓光[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《航空学报》2009年第7期1176-1180,共5页Acta Aeronautica et Astronautica Sinica

基　　金：国家"863"计划(2007AA702311)

摘　　要：提出了一种应用于三维装药的通用燃面计算方法——单元法。该方法认为装药由有限个体积微元组成,而燃面由有限个面积微元组成。在任一时刻,装药的燃烧可以看成是燃面上的面积微元沿其法向推进,而体积微元距离燃面的最近距离可以判定该体积微元在燃烧过程中是否燃尽,发动机装药的燃面通过对相邻肉厚的体积微分获得。采用该计算方法不仅避免了大量的数学公式推导,也避免了内型面标准几何体的复杂定义。燃面计算结果表明,其计算精度足以满足一般工程计算的需要。由于该方法方便快速,且能应用于任何三维装药的燃面计算,所以具有较好的应用前景。An element method to compute the burning surface of a three-dimensional propellant is proposed in this article. It is assumed that the propellant consists of a finite volume of elements and the burning surface consists of a finite area of elements. The propellant burning is considered to be the finite area of elements sho- ving in the normal direction, and then whether a volume of elements is burning out depends on the minimum distance between the volume of elements and the burning surface. The burning surface of the propellant is computed by its volume differential. This burning surface calculation method not only avoids stack math for- mulation derivation and calculation, but also avoids complex definition of standard geometry entities. The cal- culation results show that they can satisfy the precision requirements in actual engineering calculation. Because of its convenience and its ability for generalization to any three-dimensional propellants, this method has good prospects for actual application.

关 键 词：固体火箭发动机 装药 燃面计算 单元法 最短距离 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]