| 大过载下固体火箭发动机工作过程仿真的数学模型 |
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| 引用本文： | 郭颜红,梁晓庚,陈斌. 大过载下固体火箭发动机工作过程仿真的数学模型[J]. 航空兵器, 2008, 16(1): 21-25 |
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| 作者姓名： | 郭颜红 梁晓庚 陈斌 |
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| 作者单位： | 中国空空导弹研究院,河南,洛阳,471009 |
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| 摘 要： | 研究了Euler-Lagrangian两相方法模拟导弹大过载条件下固体火箭发动机三维两相内流场的动态过程的数学模型和计算方法，给出了所采用的过载作用下推进剂燃烧特性和有限速率化学反应模型，采用插值算法快速获取燃烧产物的平衡成分和输运参数，使用八叉树覆盖算法描述非平行层推移燃面的瞬时边界。
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| 关 键 词： | 固体火箭发动机 两相流场 长尾喷管 数值模拟 过载 |
| 文章编号： | 1673-5048（2008）01-0021-05 |
| 收稿时间： | 2007-07-13 |
| 修稿时间： | 2007-07-13 |
Working Process Simulation of Solid Rocket Motor with High Acceleration Load |
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| GUO Yan-hong,LIANG Xiao-geng,CHEN Bin. Working Process Simulation of Solid Rocket Motor with High Acceleration Load[J]. Aero Weaponry, 2008, 16(1): 21-25 |
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| Authors: | GUO Yan-hong LIANG Xiao-geng CHEN Bin |
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| Abstract: | An Euler-Lagrangian two-phase approach is adopted to simulate the 3D two-phase internal flow field in a solid rocket motor with long-tail nozzle. Burning dynamic process of character and finite chemical reaction model of the propellant under high acceleration load are given, and the equilibrium composition and transport parameters of combustion products are quickly achieved by using interpolation algorithm. The instantaneous boundary of non-parallel moving burning surface of propellant is described by Octree Cover Algorithm. |
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| Keywords: | solid rocket motor two-phase flow field long-tail nozzle numerical simulation acceleration load |
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