[an error occurred while processing this directive] [an error occurred while processing this directive] [an error occurred while processing this directive]
[an error occurred while processing this directive]

弹箭与制导学报 >

2010 , Vol. 30 >Issue 5: 127 - 130

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2010.05.037

火箭技术

阶梯装药固体火箭发动机点火内流场特性研究

  • 孟亮飞 ,
  • 田发林 ,
  • 周长省
展开
  • 1 南京理工大学机械工程学院,南京 210094
    2 Anhui Dongfeng Machinery and Electronic Co. Ltd, Hefei 230022,China

孟亮飞(1986-),男,山西晋城人,硕士研究生,研究方向:火箭发动机与火箭总体设计。

收稿日期: 2009-12-21

  网络出版日期: 2025-05-28

收起

The Study on Ignition Interior Flow Field Characteristics of Ladder-shaped Propellant Solid Rocket Motor

  • MENG Liangfei ,
  • TIAN Falin ,
  • ZHOU Changsheng
Expand
  • 1 School of Mechanical Engineering, Nanjing University of Science and Technology, Nanjing 210094,China

Received date: 2009-12-21

  Online published: 2025-05-28

Fold

摘要

针对两节阶梯装药在火箭弹中的应用,对该类型固体火箭发动机点火內流场特性进行数值模拟。运用FLUENT软件进行二维轴对称非定常数值分析,通过UDF编程,采用表面单元格临界点火准则实现推进剂表面不同部位单元格的燃气加质,计算得到了前后燃烧室的不同部位压力分布及变化情况和点火器喷孔附近的激波传递情况。研究结果表明,该方法能够较好的预示点火内流场的特性,可以为阶梯装药发动机的点火性能研究和点火设计提供理论依据。

关键词： 阶梯装药; 点火内流场; 数值模拟; 表面单元格

本文引用格式

孟亮飞 , 田发林 , 周长省 . 阶梯装药固体火箭发动机点火内流场特性研究[J]. 弹箭与制导学报, 2010 , 30(5) : 127 -130 . DOI: 10.15892/j.cnki.djzdxb.2010.05.037

Abstract

According to the application of two step ladder-shaped propellant in solid rocket motor, a numerical simulation was made for the type of solid rocket motor ignition characteristics of interior flow field. The FLUENT software was used to make unsteady two-dimensional axisymmetric numerical simulation, through the UDF programming, the cell surface critical criteria were applied to achieve the surface cells in different parts of the gas increases quality respectively, pressure distribution and variation in different regions of chamber and shock wave transmission near the igniter nozzle were obtained. The result can predict the characteristics of ignition flow field, and provide basis for the ignition study and design of ladder-shaped propellant solid rocket motor.

Key words： ladder-shaped propellant; ignition flow field; numerical simulation; cell surface

[an error occurred while processing this directive]

参考文献

[1]
李海涛, 鲍福廷. 固体火箭发动机点火过程内弹道计算[J]. 弹箭与制导学报, 2008, 28(5): 152- 154.
[2]
L.d'Agostino. An ignition transient model for solid propellant rocket motors AIAA 2001-3449[R]. 2001.
[3]
陈军涛, 蹇泽群, 陈林泉. 固体火箭发动机点火瞬时内流场轴对称数值分析[J]. 固体火箭技术, 2004(27): 173- 176.
[4]
In Hyun Cho, Seung Wook Baek. A numerical simulation of axisymmetric solid rocket motor ignition transient with radiation effect[J]. Journal of Propulsion and Power, 1996, 16(4): 725- 728.
[5]
张端庆. 固体火箭推进剂[M]. 北京: 兵器工业出版社, 1991.
Options
文章导航

/

〈 〉

[an error occurred while processing this directive]