[1]王 坚,陈 雄,许进升,等.一种软隔层双脉冲固体火箭发动机点火冲击仿真分析[J].南京理工大学学报(自然科学版),2019,43(06):778-783.[doi:10.14177/j.cnki.32-1397n.2019.43.06.016]
 Wang Jian,Chen Xiong,Xu Jinsheng,et al.Simulation of ignition impact for soft interlayerdual-pulse solid rocket motor[J].Journal of Nanjing University of Science and Technology,2019,43(06):778-783.[doi:10.14177/j.cnki.32-1397n.2019.43.06.016]
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一种软隔层双脉冲固体火箭发动机点火冲击仿真分析()
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《南京理工大学学报》(自然科学版)[ISSN:1005-9830/CN:32-1397/N]

卷:
43卷
期数:
2019年06期
页码:
778-783
栏目:
出版日期:
2019-12-31

文章信息/Info

Title:
Simulation of ignition impact for soft interlayerdual-pulse solid rocket motor
文章编号:
1005-9830(2019)06-0778-06
作者:
王 坚1陈 雄1许进升1李宏文2
1.南京理工大学 机械工程学院,江苏 南京 210094; 2.晋西工业集团有限责任公司,山西 太原 030027
Author(s):
Wang Jian1Chen Xiong1Xu Jinsheng1Li Hongwen2
1.School of Mechanical Engineering,Nanjing University of Science and Technology,Nanjing 210094,China; 2.Jinxi Industries Group Co.,Ltd.,Taiyuan 030027,China
关键词:
软隔层 双脉冲发动机 固体火箭发动机 点火 冲击 燃烧室 流固耦合 推进剂
Keywords:
soft interlayers dual-pulse motors solid rocket motors ignition impulse combustion chamber fluid-solid coupling propellant
分类号:
V435
DOI:
10.14177/j.cnki.32-1397n.2019.43.06.016
摘要:
为实现对双脉冲固体火箭发动机Ⅱ脉冲点火冲击过程中燃烧室全域的数值计算,搭建了1种流固耦合求解器。该求解器基于ANSYS Workbench平台,使用用户自定义函数(UDF)功能进行了推进剂点火、燃烧和加质等模型的建立以及边界条件的定义。结合动网格技术,实现了对采用隔层式隔离装置的Ⅱ脉冲燃烧室的全域数值计算。计算结果表明,Ⅱ脉冲点火冲击过程呈现典型的大变形域流动特性,同时,流场中压强、温度等属性受到推进剂燃烧、加质和隔层形变的影响作用明显; 固体区域中,隔层的各形变阶段可以明显区分,推进剂直角处应力集中现象显著。
Abstract:
A fluid-solid coupling solver is built to calculate the whole combustion chamber of a dual-pulse solid rocket motor duing second pulse ignition impulse. The solver is built on ANSYS Workbench platform. The models of propellant ignition,combustion and mass source addition are established and boundary conditions are defined by using User Define Function(UDF). Combining with the dynamic grid technology,the global numerical calculation of the second pulse combustor with an interlayer separator is realized. The calculation results show that the second pulse ignition shock process presents the typical flow characteristics in large deformation region,and the pressure and temperature properties in the flow field are obviously affected by combustion,mass source addition of the propellant and the deformation of the barrier; in the solid region,the deformation stages of the interlayer can be clearly distinguished,and the stress concentration occurs at the right angle of the propellant.

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备注/Memo

备注/Memo:
收稿日期:2018-08-28 修回日期:2018-12-08
作者简介:王坚(1992-),男,硕士生,主要研究方向:固体火箭发动机,E-mail:40997890@qq.com。
引文格式:王坚,陈雄,许进升,等. 一种软隔层双脉冲固体火箭发动机点火冲击仿真分析[J]. 南京理工大学学报,2019,43(6):778-783.
投稿网址:http://zrxuebao.njust.edu.cn
更新日期/Last Update: 2019-12-31