Volume 31 Issue 8
Aug.  2016
Turn off MathJax
Article Contents
Article Navigation >  Journal of Aerospace Power  > 2016  >  31(8): 1995-2001
CAI Hong-hua, NIE Wan-sheng, HOU Zhi-yong. Impact effect of liquid rocket motor exhaust plume on launching platform[J]. Journal of Aerospace Power, 2016, 31(8): 1995-2001. doi: 10.13224/j.cnki.jasp.2016.08.026
Citation: CAI Hong-hua, NIE Wan-sheng, HOU Zhi-yong. Impact effect of liquid rocket motor exhaust plume on launching platform[J]. Journal of Aerospace Power, 2016, 31(8): 1995-2001. doi: 10.13224/j.cnki.jasp.2016.08.026
shu

Impact effect of liquid rocket motor exhaust plume on launching platform

doi: 10.13224/j.cnki.jasp.2016.08.026

  • Department of Aerospace Equipment, The Academy of Equipment, Beijing 101416, China

  • Received Date: 2015-05-22
  • Publish Date: 2016-08-28
    Abstract
  • To study the impact effect of liquid rocket motor exhaust plume on launching platform, a mathematical calculation model of exhaust plume impact on launching platform for liquid rocket motor was built. For the impact effect of LOX (liquid oxygen)/ kerosene exhaust plume on the launching platform, the influences of the propellant flux and afterburning on the impact effect from the nozzle exit to the platform in two different cases of 3m and 5m were studied, the differences and the reasons for the differences were also analyzed. Results show that, with the increase of the propellant flux, the distance of shock wave expansion and compression of the free jet region and the area of the wall-jet region increased. Afterburning can not only change the structure of the free jet region and the stagnation zone, but also increase the temperature and the area of the wall-jet region. Afterburning and propellant flux influence the impact effect by generating influence on the structure of the exhaust plume, and the impact effect is related to the distance from the nozzle exit to launching platform.

     

    • FullText(HTML)
  • loading
    • References(18)
  • [1]
    聂万胜,杨军辉,何浩波,等.液体火箭发动机尾喷焰红外辐射特性[J].国防科学技术大学学报,2005,27(5):91-94. NIE Wansheng,YANG Junhui,HE Haobo,et al.The IR radiation characteristic of exhaust plume of the liquid rocket engine[J].Journal of Nation University of Defense Technology,2005,27(5):91-94.(in Chinese)
    [2]
    Greenwood T,Seymour D,Prozan R.Analysis of liquid rocket propellant engine exhaust plume[R].AIAA 70-0844,1970.
    [3]
    周帆,姜毅,郝继光.火箭发动机尾焰流场注水降温效果初探[J].推进技术,2012,33(2):249-252. ZHOU Fan,JIANG Yi,HAO Jiguang.Exploring on cooling effect of water injection on rocket motor exhaust[J].Journal of Propulsion Technology,2012,33(2):249-252.(in Chinese)
    [4]
    Mayer E,Prickett R.Rocket plume impingement heat transfer on plane surfaces[J].AIAA Journal,1987,24(4):291-295.
    [5]
    Ali A,Ahmed B,Syed B,et al.CFD analysis of supersonic jet impingement on axisymmetric deflector plate[R].Islamabad,Pakistan:9th International Bhurban Conference on Applied Science and Technology,2012.
    [6]
    Gonzalez D R,Wallman P,Sanford M,et al.Characterization of rocket plume fluid dynamic environment using numerical & experimental approaches[J].AIAA Journal,2013,50(3):527-539.
    [7]
    马艳丽,姜毅,郝继光,等.固体发动机燃气射流对发射平台冲击效应研究[J].固体火箭技术,2010,33(4):373-377. MA Yanli,JIANG Yi,HAO Jiguang,et al.Study on the impact effect of solid rocket motor exhaust plume to the launching platform[J].Journal of Solid Rocket Technology,2010,33(4):373-377.(in Chinese)
    [8]
    姜毅,傅德彬.固体火箭发动机尾喷焰复燃流场计算[J].宇航学报,2008,29(2):615-620. JIANG Yi,FU Debin.Numerical simulation for non equilibrium chemically reacting fluid field of the solid rocket motor exhaust plume[J].Journal of Astronautics,2008,29(2):615-620.(in Chinese)
    [9]
    张金容,靳爱国,汪亮.泵压式液体火箭发动机变推力方案选择[J].航空动力学报,2008,23(5):921-926. ZHANG Jinrong,JIN Aiguo,WANG Liang.Thrust regulation scheme selection for turbopumpfed rocket engine with variable thrust[J].Journal of Aerospace Power,2008,23(5):921-926.(in Chinese)
    [10]
    Sakakibara Y,Iwamoto J.Numerical study of oscillation mechanism in underexpanded jet impinging on plate[J].Journal of Fluids Engineering,1998,120(3):477-481.
    [11]
    何枫,谢峻石,姚朝晖.超声速欠膨胀冲击射流的数值模拟[J].推进技术,2002,23(2):96-99. HE Feng,XIE Junshi,YAO Zhaohui.Numerical simulation under-expanded supersonic impinging jet[J].Journal of Propulsion Technology,2002,23(2):96-99.(in Chinese)
    [12]
    Alvi F S,Ladd J A,Bower W W.Experimental and computational investigation of supersonic impinging jets[J].AIAA Journal,2002,40(4):599-605.
    [13]
    Ching Y L.Computation of tone noise from supersonic jet impinging on plates[R].AIAA-2005-418,2005.
    [14]
    Mayer E,Prickett R.Rocket plume impingement heat transfer on plane surfaces[R].AIAA 86-1321,1986.
    [15]
    刘尊洋,邵立,汪亚夫,等.复燃对固体火箭尾焰红外辐射特性的影响[J].光学学报,2013,33(6):0604001.1-0604001.8. LIU Zunyang,SHAO Li,WANG Yafu,et al.Influence on afterburning on infrared radiation of solid rocket exhaust plume[J].Acta Optica Sinca,2013,33(6):0604001.1-0604001.8.(in Chinese)
    [16]
    Devir A,Lessin A,Lev M,et al.Comparison of calculated and measured radiation from a rocket motor plume[R].AIAA-2001-0358,2001.
    [17]
    Mern J,Agarwal R.A study of numerical simulation of supersonic conical nozzle exhaust[R].AIAA-2013-3697,2013.
    [18]
    聂万胜,丰松江.液体火箭发动机燃烧动力学模型与数值计算[M].北京:国防工业出版社,2011.
    • Relative Articles
    • Supplements(0)
    • Cited By
  • 加载中

Catalog

    通讯作者: 陈斌, bchen63@163.com
    • 1. 

      沈阳化工大学材料科学与工程学院 沈阳 110142

    1. 本站搜索
    2. 百度学术搜索
    3. 万方数据库搜索
    4. CNKI搜索
    Get Citation
    PDF(1126.0KB)
    XML

    Article Metrics

    Article views (1017) PDF downloads(542) Cited by()
    Proportional views
    Related

    Copyright © 《Journal of Aerospace Power》 All Rights Reserved.

    Supported by: Beijing Renhe Information Technology Co., Ltd.  

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return