[1]周 悦,郭着雨,陈四春,等.火箭导弹燃气射流冲击载荷实验研究[J].南京理工大学学报(自然科学版),2020,44(06):745-751.[doi:10.14177/j.cnki.32-1397n.2020.44.06.015]
 Zhou Yue,Guo Zhuoyu,Chen Sichun,et al.Experimental research of impact load of rocket and missile jet flow[J].Journal of Nanjing University of Science and Technology,2020,44(06):745-751.[doi:10.14177/j.cnki.32-1397n.2020.44.06.015]
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火箭导弹燃气射流冲击载荷实验研究()
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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:
44卷
期数:
2020年06期
页码:
745-751
栏目:
出版日期:
2020-12-31

文章信息/Info

Title:
Experimental research of impact load of rocket and missile jet flow
文章编号:
1005-9830(2020)06-0745-07
作者:
周 悦1郭着雨1陈四春2赵 鑫3莫宗来1李 军1
1.南京理工大学 机械工程学院,江苏 南京210094; 2.中国兵器工业集团江山重工研究院有限公司 南京研究院分公司,江苏 南京 210094; 3.中国船舶集团有限公司第七〇五研究所 第一研究部,陕西 西安 710077
Author(s):
Zhou Yue1Guo Zhuoyu1Chen Sichun2Zhao Xin3Mo Zonglai1Li Jun1
1.School of Mechanical Engineering,Nanjing University of Science and Technology,Nanjing 210094,China; 2.Nanjing Research Institute Branch,Jiangshan Heavy Industries Research Institute Co.,Ltd.,NORINCO Group,Nanjing 210094,China; 3.The 705th Research Institute,China StateShipbuilding Corporation Ltd.,Xi’an 710077,China
关键词:
火箭导弹 发射系统 燃气射流 冲击载荷 迎气面 测量前盖
Keywords:
rockets and missiles launching system jet flow impact load flow-facing surfaces front measuring covers
分类号:
TJ713
DOI:
10.14177/j.cnki.32-1397n.2020.44.06.015
摘要:
火箭导弹燃气射流对发射装置的冲击载荷是发射系统结构和刚强度设计的重要依据。为了获得这一冲击载荷,该文针对燃气射流对发射装置迎气面的冲击特征,建立了火箭导弹燃气射流压强测量系统,并采用该系统对某火箭燃气射流冲击载荷进行测量。根据箱式结构迎气面特点进行测量前盖测点布设,测得某火箭弹的燃气射流压强-时间曲线。结果表明,药温60 ℃、射角30°时,各测点的压强峰值均小于0.15 MPa,且均随火箭弹逐渐远离测点而衰减,冲击时长约为400 ms。其中发射管中心测点受到的冲击压强最大,距发射管中心越远的测点受到的压强越小,且峰值时刻滞后; 不同药温和射角时迎气面冲击压强的分布具有相似性。编程处理压强-时间曲线,得到不同发射状态下的压强-半径测量结果。通过对压强-半径进行迎气面面积分,得到了各发射状态下的燃气射流冲击载荷。该文方法还适于集束式定向器迎气面的压强测量。
Abstract:
The impact load of jet flow on rocket and missile launchers is the fundamental design basis for structure and rigidity of the launching system. Through analyzing the impact characteristics of jet flow against the flow-facing surface of the launching system,a measurement system of jet flow pressure based on the strain sensor is established in this paper. The measuring points are arranged on the front measuring cover of the lauching box according to the characteristics of the flow-facing surface of the box structure,and the pressure-time curves of the rocket is obtained experimentally. The experimental results show that the pressure peaks at each measuring point are all less than 0.15 MPa when the charge temperature is 60 ℃ and the firing angle is 30°,and they all decrease with the rocket moving away from the measuring points. The impact duration is about 400 ms. The measuring point in the center of the launch tube is subjected to the greatest impact pressure,and the further away from the center of the launch tube,the lower the pressure and the later the peak time. The pressure-time curves on the flow-facing surface are similar under different powder temperatures and launch angles. By programming the pressure-time curves,the pressure-radius measurement results under different launch states are obtained. The impact loads of jet flow under differemt launch states are calculated by integrating the pressure-radius into the flow field. The measurement system in this paper is also suitable for the pressure measurement of the flow-facing surface of cluster-type tubes.

参考文献/References:

[1] 李军. 火箭武器发射过程的燃气射流[M]. 北京:科学出版社,2018.
[2]Chiriac V A,Ortega A. A numerical study of the unsteady flow and heat transfer in a transitional confined slot jet impinging on an isothermal surface[J]. International Journal of Heat and Mass Transfer,2002,45(6):1237-1248.
[3]Angioletti M,Nino E,Ruocco G. CFD turbulent modelling of jet impingement and its validation by particle image velocimetry and mass transfer measurements[J]. International Journal of Thermal Sciences,2005,44(4):349-356.
[4]Narayanan V,Seyed Yagoobi J,Page R H. An experimental study of fluid mechanics and heat transfer in an impinging slot jet flow[J]. International Journal of Heat and Mass Transfer,2004,47(8-9):1827-1845.
[5]Sengupta A,Sarkar P P. Experimental measurement and numerical simulation of an impinging jet with application to thunderstorm microburst winds[J]. Journal of Wind Engineering & Industrial Aerodynamics,2008,96(3):345-365.
[6]Baydar E,Ozmen Y. An experimental investigation on flow structures of confined and unconfined impinging air jets[J]. Heat and Mass Transfer,2006,42(4):338-346.
[7]Gradeck M,Kouachi A,Dani A,et al. Experimental and numerical study of the hydraulic jump of an impinging jet on a moving surface[J]. Experimental Thermal & Fluid Science,2006,30(3):193-201.
[8]Baydar E,Ozmen Y. An experimental and numerical investigation on a confined impinging air jet at high Reynolds numbers[J]. Applied Thermal Engineering,2005,25(2-3):409-421.
[9]徐强,李开明,张福祥,等. 火箭发射箱内燃气流场的激光摩尔偏折显示[J]. 测试技术学报,1996,10(4):30-32.
Xu Qiang,Li Kaiming,Zhang Fuxiang,et al. Laser moire deflectometry displaying the internal exhausted flow field of launch tube[J]. Journal of Test and Measurement Technology,1996,10(4):30-32.
[10]徐强,张福祥,李开明. 燃气射流起始冲击波场形态的实验研究[J]. 实验力学,1999,14(4):98-101.
Xu Qiang,Zhang Fuxiang,Li Kaiming. An experimental study on the initial shockwave structure of exhaust flow field[J]. Journal of Experimental Mechanics,1999,14(4):98-101.
[11]姬晋卿,王浩. 点火具能量释放过程数值仿真分析[J]. 兵器装备工程学报,2018,39(10):63-68.
Ji Jinqing,Wang Hao. Numerical simulation analysis of the energy-released process for the ignition transient[J]. Journal of Ordnance Equipment Engineering,2018,39(10):63-68.
[12]刘晴. 火箭发射系统迎气面压强测量及振动特性分析[D]. 南京:南京理工大学机械工程学院,2015.
[13]陈四春,姜超,李军. 固体火箭燃气射流冲击载荷的数值与实验研究[J]. 南京理工大学学报,2015,39(6):698-703.
Chen Sichun,Jiang Chao,Li Jun. Numerical and experimental study on impact load of jet flow of solid rocket[J]. Journal of Nanjing University of Science and Technology,2015,39(6):698-703.
[14]邵彬,张国伟,韩文斌,等. 导引头对射流破甲威力的影响研究[J]. 兵器装备工程学报,2019,40(12):25-28.
Shao Bin,Zhang Guowei,Han Wenbin,et al. Influence of seeker on penetration power of jet[J]. Journal of Ordnance Equipment Engineering,2019,40(12):25-28.
[15]张俊,田中旭,高天宇,等. 固体火箭发动机尾流场数值模拟[J]. 弹箭与制导学报,2018,38(6):15-18.
Zhang Jun,Tian Zhongxu,Gao Tianyu,et al. Numerical simulation for wake flow field of solid rocket motor[J]. Journal of Projectiles,Rockets,Missiles and Guidance,2018,38(6):15-18.
[16]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 Lei,Wang Hao,Ruan Wenjun,et al. Three-dimensional numerical simulation on flow charac-teristics of supersonic gas jet[J]. Journal of Ballistics,2015,27(2):80-84.
[17]Zhang Ce,Zhao Xin,Mo Zonglai,et,al. A novel non-separation opening scheme of front cover for rocket launch canister[J]. Defence Technology,2019,15(6):905-911.

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备注/Memo

备注/Memo:
收稿日期:2020-09-30 修回日期:2020-10-10
作者简介:周悦(1995-),女,硕士,主要研究方向:发射动力学,E-mail:2821736615@qq.com; 通讯作者:李军(1965-),男,博士,教授,博士生导师,主要研究方向:兵器发射理论与技术,E-mail:lijunly@njust.edu.cn。
引文格式:周悦,郭着雨,陈四春,等. 火箭导弹燃气射流冲击载荷实验研究[J]. 南京理工大学学报,2020,44(6):745-751.
投稿网址:http://zrxuebao.njust.edu.cn
更新日期/Last Update: 2020-12-30