Experimental and simulation study on missile ejection gas impact load

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Journal of Vibration and Shock ›› 2020, Vol. 39 ›› Issue (11) : 109-115.

JIANG Xiaorui1, LI Zhuo1, QIAN Chengyuan2, HUANG Dahui1

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Abstract

A set of device is designed to simulate the built-in pressure process of launcher barrel, so that it can simulate the built-in pressure process of launcher barrel at different build-up speed and different final pressure, and then conduct ground cooling experiments on missile tail cover and other structures during missile ejection. Experiments were carried out on four different initial conditions, and numerical simulation was carried out on one case. The results show that by adjusting the initial pressure difference on both sides of the plunger and the initial pressure of the high-pressure cylinder, the simulation of different pressure build-up rates and different final pressures can be realized. During the process of pressure build-up, there are obvious eddies in the simulated launcher, the pressure in the middle part of the tail hood is greater, and the deformation time lags behind the boost time.

Key words

ejection;launcher / impact load / simulation experiment / numerical simulation

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JIANG Xiaorui1, LI Zhuo1, QIAN Chengyuan2, HUANG Dahui1. Experimental and simulation study on missile ejection gas impact load[J]. Journal of Vibration and Shock, 2020, 39(11): 109-115

References

[1]李广裕.战略导弹弹射技术的发展[J].国外导弹与航天运载器,1990(07):38-49.
Li Guang-yu.Development of Strategic Missile Ejection Technology[J].Missiles and Space Vehicles,1990(07):38-49.
[2]李显龙,瞿军,边晓阳,于志军.风载荷对舰载导弹出筒影响的仿真[J].兵工自动化,2018,37(08):6-10.
LI Xian-long, QU jun, BIAN Xiao-jun,et al.Simulation on the Impact of Wind Load on Shipboard Missile Ejection[J].Ordnance Industry Automation,2018,37(08):6-10.
[3]谭大成.弹射内弹道学[M].北京:北京理工大学出版社，2015: 2-3．
TAN Da-cheng. Interior ballistics of catapults[M].Bei Jing:Beijing University of Technology Press,2015: 2-3．
[4]SHAFQAT W，XIE K，LIU Y． Numerical simulation of multi-phase combustion flow in solid rocket motors with metalized propellant[J].Journal of Aerospace Power，2009，24( 7) : 1654-1660．
[5]袁曾凤.火箭导弹弹射内弹道学[M].北京: 北京工业学院出版社，1987: 112-132.
YUAN Zeng-feng. Missile ejection interior ballistics[M].Bei Jing:Beijing University of Technology Press,1987: 112-132.
[6]陈亚军. 导弹燃气弹射内弹道数值模拟与参数设计[D].安徽工业大学,2017.
CHEN Ya-jun.Numerical simulation and parameter design on missile Gas-ejection interior ballistic[D].Anhui University of Technology,2017
[7] Design and structural analysis of a coilgun for low acceleration of heavy loads. Wang, De-Man,Liu, Ping,Liu, Hai-Qiang,Cheng, Jian-Jun,Zhu, Ying-Min. IEEE Transactions on Magnetics, 1999.
[8]张艳芳. 弹射装置进气通道结构设计与仿真研究[D].中北大学,2017
ZHANG Yan-fang.Design and Simulation on intake channel structure of catapult device[D].North University of China,2017.
[9]姚琳,马大为,任杰,魏龙涛,李亚.无杆式气缸弹射装置内弹道仿真与优化设计[J].振动与冲击,2017,36(06):122-127.
YAO Lin ,MA Da-wei, REN Jie ,et al.Internal ballistics simulatin on and improving of rod-less cylinder cold launching device[J].Journal of Vibration andshock,2017,36(06):122-127.
[10]程洪杰,陈力,林睿.弹道导弹燃气弹射技术[J].弹箭与制导学报,2017,37(04):109-112.
Cheng Hong-jie, Chen Li, Lin Rui.Gas Ejection Technology of Ballistic Missile[J].Journal of Projectiles，Ｒockets，Missiles and Guidance,2017,37(04):109-112.
[11]程洪杰，陈力，赵媛，刘准. 环形隔板结构参数对燃气弹射压力冲击平滑效果影响[J]. 振动与冲击, 2018, 37(20): 193-199.
CHENG Hongjie,CHEN Li,ZHAO Yuan,LIU Zhun. Smoothing effect influence of annular baffle structural parameter on the pressure impact of gas-ejection. JOURNAL OF VIBRATION AND SHOCK, 2018, 37(20): 193-199.
[12]陈力,程洪杰,赵媛,刘准.导弹燃气弹射内弹道多目标优化设计[J].推进技术,2018,39(12):2651-2659.
CHEN Li,CHENG Hong-jie, ZHAO Yuan,et al.Multi-Objective Combination Optimization Design of Missile Gas-Ejection Internal Ballistic[J],Journal of Propulsion Technology,2018,39(12):2651-2659.
[13]张筱,刘宝龙,郑夏,邓鹏程,何冠杰.导弹井下冷弹射动力学仿真研究[J].导弹与航天运载技术,2018,4(04):81-86.
ZHANG Xiao,LIU Bao-long, ZHENG Xia,et al.Modeling and Dynamic Simulation Study on Missile Cold Ejection from Silo[J].Missiles and Space Vehicles,2018,4(04):81-86.
[14]程洪杰,陈力,赵媛,赵谢.基于导弹压力冲击平滑的燃气弹射装置环形腔结构参数次序优化[J].推进技术,2019,40(02):241-249.
Cheng Hong-jie, Chen Li, Zhao Yuan,et al.Ordinal Optimization of Ring Cavity Structure Parameters for Gas Ejection Device Based on Missile Pressure Impact Smoothness[J].Journal of Propulsion Technology,2019,40(02):241-249.