[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]

Journal of Projectiles, Rockets, Missiles and Guidance >

2024 , Vol. 44 >Issue 2: 30 - 35

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2024.02.005

Numerical Study on Interaction Between Gas Jet and Supersonic Flow in Solid Rocket Motor

  • ZHANG Enhao ,
  • FAN Jianlong ,
  • ZHU Liang ,
  • DENG Heng
Expand
  • Xi’an Mordern Control Technology Research Institute,Xi’an 710065,Shaanxi, China

Received date: 2022-07-17

  Online published: 2024-12-28

Fold

Abstract

In order to obtain the interaction characteristics of supersonic flow and solid rocket motor (SRM) range stage gas jet, based on computational fluid dynamics (CFD), a high-precision numerical calculation scheme is used to simulate the interaction flow field of SRM gas jet and supersonic flow under different working conditions. The whole flow field can be roughly divided into the outer field, the recirculation zone and the plume zone. Under a certain nozzle drop pressure ratio, with the increase of altitude, the nozzle flow separation phenomenon gradually disappears, the jet wave nodes decrease, and the distance between the formation of the first incident shock wave and the nozzle outlet increases. On the other hand, the increase of altitude will cause the increase of the recirculation zone wall temperature rise. In addition, the actual working pressure is more than 30% lower than the static pressure due to the rapid expansion of supersonic inflow at the rear edge of the projectile.

Key words： solid rocket motor; gas jet; numerical simulation; supersonic speed; mixed refrigerants

Cite this article

ZHANG Enhao , FAN Jianlong , ZHU Liang , DENG Heng . Numerical Study on Interaction Between Gas Jet and Supersonic Flow in Solid Rocket Motor[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2024 , 44(2) : 30 -35 . DOI: 10.15892/j.cnki.djzdxb.2024.02.005

[an error occurred while processing this directive]

References

Publishing order | Descend order by publishing year | Descend order by cited within
[1]
李铮, 向红军, 张小英. 复合推进剂固体火箭发动机喷流流场数值模拟[J]. 固体火箭技术, 2014, 37(1): 37-42.

LI Z, XIANG H J, ZHANG X Y. Numerical simulation of composite solid propellant rocket motor exhaust plume[J]. Journal of Solid Rocket Technology, 2014, 37(1): 37-42.

[2]
于文浩, 相升海, 黄颗, 等. 飞行条件对导弹发动机尾焰流场的影响研究[J]. 战术导弹技术, 2016(4): 75-81.

YU W H, XIANG S H, HUANG K, et al. Research on influence of flying condition on tail flame flow field of missile motor[J]. Tactical Missile Technology, 2016(4): 75-81.

[3]
乔野, 聂万胜, 丰松江, 等. 液氢/液氧火箭发动机尾焰流场特性仿真研究[J]. 火箭推进, 2015, 41(5): 43-48.

QIAO Y, NIE W S, FENG S J, et al. Simulation research on fluid field characteristics of LH2/LOX rocket engine plume[J]. Journal of Rocket Propulsion, 2015, 41(5): 43-48.

[4]
张磊, 王浩, 阮文俊, 等. 超声速燃气射流流场特性的三维数值模拟[J]. 弹道学报, 2015, 27(2): 80-84.

ZHANG L, WANG H, RUAN W J, et al. Three-dimensional numerical simulation on flow characteristics of supersonic gas jet[J]. Journal of Ballistics, 2015, 27(2): 80-84.

[5]
张磊, 阮文俊, 王浩, 等. 固体火箭发动机燃气射流流场和声场数值计算[J]. 固体火箭技术, 2015(2): 198-202.

ZHANG L, RUAN W J, WANG H, et al. Numerical calculation of gas jet flow and acoustics fields for solid rocket motor[J]. Journal of Solid Rocket Technology, 2015(2): 198-202.

[6]
张磊. 大水深火箭发动机尾流场数值模拟[J]. 固体火箭技术, 2019, 42(2): 29-33.

ZHANG L. Numerical simulation of tail flow field for underwater solid rocket motor[J]. Journal of Solid Rocket Technology, 2019, 42(2): 29-33.

[7]
唐云龙. 深水条件下固体火箭发动机燃气射流与推力特性研究[D]. 北京: 北京理工大学, 2016.

TANG Y L. Research on gas gaseous jet flow structure and thrust characteristics of solid rocket motor working in deep water[D]. Beijing: Beijing Institute of Technology, 2016.

[8]
郭强, 施红辉, 王超, 等. 准二维水下超声速垂直过膨胀射流研究[J]. 实验流体力学, 2010, 24(3): 6-11.

GUO Q, SHI H H, WANG C, et al. Study on quasi-two-dimensional subsonic underwater vertical supersonic over-expanded jets[J]. Journal of Experiments in Fluid Mechanics, 2010, 24(3): 6-11.

[9]
卓长飞. 炮弹底部排气减阻机理研究[D]. 南京: 南京理工大学, 2015.

ZHUO C F. The research on mechanism of drag reduction by base bleed on projectile[D]. Nanjing: Nanjing University of Science and Technology, 2015.

[10]
郭则庆. 膛口流场动力学机理数值研究[D]. 南京: 南京理工大学, 2012.

GUO Z Q. Numerical investigations on the dynamics mechanism of muzzle flow[D]. Nanjing: Nanjing University of Science and Technology, 2012.

[11]
杨鸣, 谢雨彤, 王辉, 等. 火箭飞行速度与射流冲击作用关系研究[J]. 兵器装备工程学报, 2016, 37(3): 27-30.

YANG M, XIE Y T, WANG H, et al. Research on relationship between rockets flight velocity and jet impact effect[J]. Journal of Ordnance Equipment Engineering, 2016, 37(3): 27-30.

[12]
KUMAR A, DRUMMOND J P, MCCLINTON C R, et al. Research in hypersonic airbreathing propulsion at the NASA langlet research center: ISABE 2001-2007[R]. Washington: NASA, 2001.

[13]
HAYASHI K, ASO S. Effect of pressure ratio on aerodynamic heating reduction due to opposing Jet: AIAA 2003-4041[R]. Reston: AIAA, 2003.

Options
Outlines

/

〈 〉

[an error occurred while processing this directive]