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[1]靳瑞斌,向红军.一种新的模拟固体火箭发动机射流铝颗粒燃烧的方法[J].火箭推进,2010,36(06):25-29.
　JIN Rui-bin,XIANG Hong-jun.New method of numerical simulation of combustion aluminium droplet in exhaust plume for SRM[J].Journal of Rocket Propulsion,2010,36(06):25-29.
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一种新的模拟固体火箭发动机射流铝颗粒燃烧的方法

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 36 期数: 2010年06期 页码: 25-29 栏目: 研究与设计 出版日期: 2010-12-15
Title:
New method of numerical simulation of combustion aluminium droplet in exhaust plume for SRM
文章编号:
1672-9374(2010)06-0025-05
作者:
靳瑞斌; 向红军
北京航空航天大学 宇航学院，北京 100083
Author(s):
JIN Rui-bin;  XIANG Hong-jun
School of Astronautics, Beijing Univ. of Aeronautics and Astronautics, Beijing 100083, China
关键词:
固体火箭发动机; 燃气射流; 铝颗粒; 燃烧
Keywords:
solid rocket motor;  exhaust plume;  aluminium particle;  combustion
分类号:
V435-34
文献标志码:
A
摘要:
在总结以往火箭射流数值模拟的基础上，采用多组分有限速率化学反应模型模拟气体在喷管后的复燃，并引入拉格朗日颗粒轨道模型来模拟由Al和Al2O3组成的混合颗粒。通过快速欧拉模型得到Al2O3烟尘的速度场，然后通过质量、动量、能量源项将气体相、颗粒相和烟尘相三者联立耦合计算来模拟铝颗粒的燃烧和燃烧产生的烟尘颗粒对整个射流结构的影响，为以后更准确地计算射流红外辐射特性提供了理论工具。
Abstract:
Multi-component chemical reaction models with finite rate are used to simulate the exhaust plume on the basis of summarization for the previous numerical simulation of the rocket jet. Lagrangian discrete phase model is used to simulate the particles composed of Al and Al2O3. The Al2O3 smoke velocity field is obtained with the fast Eulerian model. The gas phase, particulate phase, and smoke are coupled with source terms of mass, momentum and energy. The impact of aluminium particle combustion on the entire jet structure also can be simulated in order to accurately calculate the infrared radiation characteristics of the exhaust plume.

参考文献/References:

[1]洪滔, 秦承森. 铝颗粒激波点火机制初探[J]. 爆炸与冲击, 2003, 23 (4): 295-299. [2]杨丹. 固体火箭发动机气-固两相流的数值模拟[D]. 哈尔滨: 哈尔滨工程大学, 2006. [3]WIDENER J F, BECKSTEAD M W. Aluminium combustion modeling in solid propellant combustion products, AIAA, 1998－3824 [R]. USA: AIAA, 1998. [4]RODIONOV A V, PLASTININ Y A, DRAKES J A, et al. Modeling of multiphase alumina-loaded jet flow fields, AIAA1998-3462 [R]. USA: AIAA, 1998. [5]TROYES J, DUBOIS I, BORIE V, et al. Multi-phase reactive numerical simulations of a model solid rocket motor exhaust jet, AIAA 2006-4414 [R]. USA: AIAA, 2006. [6]LIFT R С, GRACE J R, WEBER M E. Bubbles, drops, and particles [M]. New York: Academic Press, 1978. [7]FERY J, BALACHANDAR S. A fast Eulerian method for disperse two-phase flow[J]. International Journal of Mul- tiphase Flow, 2001, 27: 1199-1226. [8]徐学文, 王连生, 牟俊林. 某固体火箭发动机点火启动过程三维流场一体化仿真[J]. 固体火箭技术, 2008, 31 (1): 8-14.

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备注/Memo

收稿日期：2010-10-20；修回日期：2010-11-08
基金项目： 国家航天技术支撑项目
作者简介： 靳瑞斌（1986—），男，硕士研究生，研究领域为固体火箭发动机工作过程仿

更新日期/Last Update: 1900-01-01