DONG Jingang, JIN Jialin, LI Guangliang, QIN Yongming, MA Handong. Research on test technology of dynamic force measurement of rotating missile in wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2020, 34(4): 81-86. DOI: 10.11729/syltlx20190119
Citation: DONG Jingang, JIN Jialin, LI Guangliang, QIN Yongming, MA Handong. Research on test technology of dynamic force measurement of rotating missile in wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2020, 34(4): 81-86. DOI: 10.11729/syltlx20190119

Research on test technology of dynamic force measurement of rotating missile in wind tunnel

More Information
  • Received Date: September 17, 2019
  • Revised Date: November 18, 2019
  • The missile encounters complex aerodynamic problems during the rotating flight. The rotary motion causes unsteady aerodynamic characteristics. The conventional static force measurement wind tunnel test cannot meet the requirements of the dynamic aerodynamic characteristics research, and the dynamic aerodynamics of missile model needs to be measured in the wind tunnel, the rotational motion of missile model performs similar simulations. In the 1.2 m-level supersonic wind tunnel, the active control technology of the rotary motion of the long slender missile model and the dynamic aerodynamic measurement technology corresponding to the rotary motion are studied. The established test technique was verified by the wind tunnel test using a rotating missile model with a slenderness ratio of 20. The experimental results show that the micro-drive system and the integrated design of the rotating component and the missile model can stably control the rotational speed of the missile model with large slenderness ratio. The established wind tunnel dynamic force test technology can obtain the dynamical data of the missile model in rotating motion, and the test data was reproducible with good precision.
  • [1]
    王波兰, 李克勇, 杨永强.近程/末端防御旋转导弹发展及关键技术综述[J].上海航天, 2017, 34(s1):1-6. http://www.cnki.com.cn/Article/CJFDTotal-SHHT2017S1001.htm

    WANG B L, LI K Y, YANG Y Q. Review of development and key techniques of rolling airframe missiles[J]. Aerospace Shanghai, 2017, 34(s1):1-6. http://www.cnki.com.cn/Article/CJFDTotal-SHHT2017S1001.htm
    [2]
    李惠芝, 成楚之.旋转导弹的气动布局[J].战术导弹技术, 1989(3):4-10. http://www.cnki.com.cn/Article/CJFDTotal-ZSDD198903002.htm

    LI H Z, CHENG C Z. Aerodynamic layout of a rotating missile[J]. Tactical missile technology, 1989(3):4-10. http://www.cnki.com.cn/Article/CJFDTotal-ZSDD198903002.htm
    [3]
    杨安生.便携式红外寻的防空导弹——气动外形[J].上海航天, 1998(2):52-57. http://www.cnki.com.cn/Article/CJFDTotal-SHHT802.010.htm

    YANG A S. Portable infrared homing air-defense missile——aerodynamic configuration[J]. Aerospace Shanghai, 1998(2):52-57. http://www.cnki.com.cn/Article/CJFDTotal-SHHT802.010.htm
    [4]
    张宏俊, 吴强, 张铁兵.舰载末端防御导弹及其技术发展[J].上海航天, 2013, 30(5):1-6. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=shht201305001

    ZHANG H J, WU Q, ZHANG T B. Technology and development of ship-based terminal defense missile[J]. Aerospace Shanghai, 2013, 30(5):1-6. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=shht201305001
    [5]
    张平峰, 周志超.鸭式布局旋转导弹气动特性研究[J].上海航天, 2013, 30(3):45-49. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=shht201303010

    ZHANG P F, ZHOU Z C. Research on aerodynamics of canard rolling airframe missile[J]. Aerospace Shanghai, 2013, 30(3):45-49. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=shht201303010
    [6]
    WALTER R F. Free gyro imaging IR sensor in Rolling Airframe Missile application[R]. Raython Missile Systems, 1999.
    [7]
    任天荣, 马建敏.拉姆导弹总体构型设计分析[J].弹箭与制导学报, 2013, 33(3):25-32. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=djyzdxb201303007

    REN T R, MA J M. Analysis on preliminary layout design of RAM missile[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2013, 33(3):25-32. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=djyzdxb201303007
    [8]
    叶尧卿.便携式红外寻的防空弹道设计[M].北京:中国宇航出版社, 2006. http://www.cnki.com.cn/article/cjfdtotal-shht805.010.htm

    YE Y Q. Portable infrared homing air defense trajectory design[M]. Beijing:China Astronautic Publishing House, 2006. http://www.cnki.com.cn/article/cjfdtotal-shht805.010.htm
    [9]
    余奇华, 敬代勇.旋转尾翼鸭式布局导弹数值模拟[J].战术导弹技术, 2012(2):16-19. http://www.cqvip.com/QK/93603X/201202/41553090.html

    YU Q H, JING D Y. Numerical simulation of a canard missile with a spinning tail fin[J]. Tactical Missile Technology, 2012(2):16-19. http://www.cqvip.com/QK/93603X/201202/41553090.html
    [10]
    雷娟棉, 吴甲生, 郑志伟.弹箭旋转空气动力效应研究进展[C]//第十四届全国分离流、流动控制会议论文集. 2013.

    LEI J M, WU J S, ZHENG Z W. Research progress of spinning aerodynamic effects of rockets[C]//Proceedings of the 14th National Conference on Separation, Vortex and Flow Control. 2013.
    [11]
    SEGINER A. Magnus effects on spinning transonic missiles[R]. AIAA-83-2146, 1983.
    [12]
    SEGINER A. Magnus effects at high angles of attack and critical Reynolds numbers[R]. AIAA-83-2145, 1983.
    [13]
    SEGINER A, ROSENWASSER I. Magnus effects on spinning transonic finned missiles[J]. Journal of Spacecraft and Rockets, 1986, 23(1):31-38. DOI: 10.2514/3.25080
    [14]
    NYGAARD T A, MEAKIN R L. Aerodynamic analysis of a spinning missile with dithering canards[J]. Journal of Spacecraft and Rockets, 2004, 41(5):726-734. DOI: 10.2514/1.13075
    [15]
    BURKHALTER J E, HEISER M A. Linear aerodynamic analysis of a spinning missile with dithering canards[R]. AIAA-2002-2800, 2002.
    [16]
    SHENG C H, WANG X. Aerodynamic analysis of a spinning missile with dithering canards using a high order unstructured grid scheme[R]. AIAA-2009-1090, 2009.
    [17]
    BLADESE L, MARCUM D L, MITCHELL B. Simulation of spinning missile flow fields using U2NCLE[R]. AIAA-2002-2797, 2002.
    [18]
    HALL L H. Rolling airframe missile aerodynamic predictions using a chimera approach for dithering canards[R]. AIAA-2002-0405, 2002.
    [19]
    TISSERAND L E. Aerodynamics of a rolling airframe missile[R]. ADA111769, 1982.
    [20]
    GOLD R, BUSAN R. Design and implementation of a full-scale spinning missile model with active canard control[R]. AIAA-94-0721, 1994.
    [21]
    DILLEY A D, MCBRIDE R T, YUKI V A, et al. Dynamic wind tunnel test of an innovative rolling missile model[R]. AIAA-2008-4032, 2008.
    [22]
    吴甲生, 徐文熙. BS-7基本旋转模型magnus风洞试验(一)[J].兵工学报弹箭分册, 1987(4):15-21. http://www.cnki.com.cn/Article/CJFDTotal-DJZD198704002.htm
    [23]
    吴甲生, 徐文熙, 居贤铭.低阻增程弹风洞试验研究[J].北京理工大学学报, 1989(2):29-34. http://www.ixueshu.com/document/4eb12ee3a8f9232ffd84b0cc68808f88318947a18e7f9386.html

    WU J S, XU W X, JU X M.Wind tunnel experimental investigation of low extended range projectiles[J]. Transactions of Beijing Institute of Technology, 1989(2):29-34. http://www.ixueshu.com/document/4eb12ee3a8f9232ffd84b0cc68808f88318947a18e7f9386.html
    [24]
    吴甲生, 徐文熙.旋转弧翼身组合体空气动力特性实验研究[J].气动实验与测量控制, 1988, 2(1):41-50. http://www.cnki.com.cn/Article/CJFDTotal-LTLC198801005.htm

Catalog

    Article Metrics

    Article views (362) PDF downloads (32) Cited by()
    Related

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return
    x Close Forever Close