Volume 34 Issue 11
Nov.  2019
Turn off MathJax
Article Contents
Article Navigation >  Journal of Aerospace Power  > 2019  >  34(11): 2331-2338
ZHANG Cheng, XIA Zhixun, MA Chao. Numerical simulation of flow field of concentric canister launcher based on k-ω SST turbulence model[J]. Journal of Aerospace Power, 2019, 34(11): 2331-2338. doi: 10.13224/j.cnki.jasp.2019.11.004
Citation: ZHANG Cheng, XIA Zhixun, MA Chao. Numerical simulation of flow field of concentric canister launcher based on k-ω SST turbulence model[J]. Journal of Aerospace Power, 2019, 34(11): 2331-2338. doi: 10.13224/j.cnki.jasp.2019.11.004
shu

Numerical simulation of flow field of concentric canister launcher based on k-ω SST turbulence model

doi: 10.13224/j.cnki.jasp.2019.11.004
  • 1.

    School of Space Science and Engineering,National University of Defense Technology,Changsha 410073,China

  • 2.

    China Academy of Launch Vehicle Technology,China Aerospace Science and Technology Corporation,Beijing 100076,China

  • 3.

    College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China

  • Received Date: 2019-03-31
  • Publish Date: 2019-11-28
    Abstract
  • The flow field of the concentric canister launcher and structural optimization was simulated numerically based on the axisymmetric Navier-Stokes(N-S)equation, the k-ω shear stress transfer (SST) turbulence model and the dynamic mesh update method named zone moving and dynamic laying. With reference to the initial scheme of the concentric canister launcher, the dynamic flow field of the launching process was studied. On this basis, the parameterization of the convergence angle of the convergent section of the inner cylinder and the expansion angle of the expansion section of the cylinder was studied. The results showed that the convergent section of the inner cylinder made the gas discharge guide smoother, the thermal environment inside the cylinder was improved, and the inner cylinder convergence section played a certain role of anti-spray. The larger convergence angle brought about the better thermal environment at the bottom of the cylinder. The expansion section of the nozzle had a significant change to the dynamic flow field during the launch process. When the convergence angle was 15 degrees and the expansion angle was 20 degrees, the thermal environment of the missile was the best from the start to the complete exit.

     

    • FullText(HTML)
  • loading
    • References(18)
  • [1]
    边金尧,徐松林,钱海鹰.同心发射筒研究现状［J］.舰船科学技术,2012,34(11):3-7.BIAN Jinyao,XU Songlin,QIAN Haiying.Research progress of concentric launching canister［J］.Ship Science and Technology,2012,34(11):3-7.(in Chinese)
    [2]
    苗佩云,袁曾凤.筒内复杂流场三维数值模拟［J］.弹箭与制导学报,2004,24(1):71-72.MIAO Peiyun,YUAN Zengfeng.Three-dimensional simulation for complicated flow of a canister［J］.Journal of Projectiles,Rockets,Missiles and Guidance,2004,24(1):71-72.(in Chinese)
    [3]
    张程,金玲,张木,等.一种异型同心筒发射装置的排导性能仿真研究［J］.航空动力学报,2019,34(1):248-256.ZHANG Cheng,JING Ling,ZHANG Mu,et al.Numerical simulation on the drainage performance of a special shaped concentric cylinder launcher［J］.Journal of Aeraspace Power,2019,34(1):248-256.(in Chinese)
    [4]
    王泉水,张剑钊.战斧导弹厚壁式同心筒发射装置的机械设计分析［J］.舰载武器,2000(1):1-10.WANG Quanshui,ZHANG Jianwei.Mechanical design analysis of thick axe concentric canister launcher of Tomahawk missile［J］.Shipborne Weapons,2000(1):1-10.(in Chinese)
    [5]
    熊永亮,郜冶,李燕良.同心筒发射中旁泄流影响的数值研究［J］.弹箭与制导学报,2007,27(4):194-197.XIONG Yongliang,GAO Ye,LI Yanliang.Numerical investigate the influence of the side releasing flow on the concentric canister launch［J］.Journal of Projectiles,Rockets,Missiles and Guidance,2007,27(4):194-197.(in Chinese)
    [6]
    郑榆淇,傅德彬,王新星,等.异形截面同心筒燃气流动特性数值研究［J］.固体火箭技术,2016,39(5):729-734.ZHENG Yuqi,FU Debin,WANG Xinxing,et al.Numerical investigation of exhaust flows for missile launching in an irregular section concentric canister launcher［J］.Journal of Solid Rocket Technology,2016,39(5):729-734.(in Chinese)
    [7]
    蔺翠郎,毕世华.同心发射筒内燃气流温度场的数值模拟［J］.弹箭与制导学报,2007,27(5):160-162.LIN Cuilang,BI Shihua.Numerical simulation of the combustion-gas temperature field in concentric canister launcher［J］.Journal of Projectiles,Rockets,Missiles and Guidance,2007,27(5):160-162.(in Chinese)
    [8]
    姜毅,郝继光,刘群.同心筒垂直发射装置排导燃气流的改进［J］.北京理工大学学报,2007,27(2):95-98.JIANG Yi,HAO Jiguang,LIU Qun.Improvement measures of exhausting the jet in the concentric certicalLaunching equipment［J］.Transactions of Beijing Institute of Technology,2007,27(2):95-98.(in Chinese)
    [9]
    马艳丽,姜毅,王伟臣,等.同心筒发射过程燃气射流冲击效应研究［J］.固体火箭技术,2011,34(2):140-145.MA Yanli,JIANG Yi,WANG Weicheng,et al.Study on impact effect of combustion gas jet during concentric canister launching process［J］.Journal of Solid Rocket Technology,2011,34(2):140-145.(in Chinese)
    [10]
    MENTER F R.Two-equation eddy-viscosity turbulence models for engineering applications［J］.AIAA Journal,1994,32(8):1598-1605.
    [11]
    刘安成,王亚盟,郝春生.SST k-ω模型用于冲击射流冷却的可靠性［J］.南昌航空大学学报(自然科学版),2009,23(4):32-36.LIU Ancheng,WANG Yameng,HAO Chunsheng.In vestigation of SST k-ω reliability in impinging jet cooling［J］.Journal of Nanchang HangkongUniversity(Natural Sciences),2009,23(4):32-36.(in Chinese)
    [12]
    KOLAR J,DVORAK V.Verification of k-ω SST turbulence model for supersonic internal flows［J］.World Academy of Science,Engineering and Technology,2011,81:262-266.
    [13]
    唐洪,乐贵高,王辉,等.同心筒垂直发射装置底部导流分析［J］.机械制造与自动化,2014,43(1):14-16.TANG Hong,LE Guigao,WANG Hui,et al.Research on jet exhaust at bottom of concentric launch canister［J］.Machine Building and Automation,2014,43(1):14-16.(in Chinese)
    [14]
    姜毅,郝继光,傅德彬,等.新型“引射同心筒”垂直发射装置理论及试验研究［J］.宇航学报,2008,29(1):236-241.JIANG Yi,HAO Jiguang,FU Debin,et al.Theoretical and experimental research on a new type of “ejection concentric tube” vertical launcher［J］.Journal of Astronautics,2008,29(1):236-241.(in Chinese)
    [15]
    邵立武,姜毅,马艳丽,等.新型舰载同心筒发射过程流场研究［J］.导弹与航天运载技术,2011(4):54-58.SHAO Liwu,JIANG Yi,MA Yanli,et al.Launching process of the new type shipborne concentric canister launcher［J］.Missiles and Space Vehicles,2011(4):54-58.(in Chinese)
    [16]
    郝继光,姜毅,韩书永,等.一种新的动网格更新技术及其应用［J］.弹道学报,2007,19(2):88-92.HAO Jiguang,JIANG Yi,HAN Shuyong,et al.A new dynamic mesh update method and its Applications［J］.Journal of Ballistics,2007,19(2):88-92.(in Chinese)
    [17]
    HANXIN Z,LIN F.NND schemes and numerical simulation of axial symmetric free jet flows［J］.Acta Mechanica Sinica,1990,6(3):193-203.
    [18]
    苗瑞生,居贤铭.火箭气体动力学［M］.北京:国防工业出版社,1985.
    • 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(3452.0KB)
    XML

    Article Metrics

    Article views (937) PDF downloads(678) 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