留言板

尊敬的读者、作者、审稿人, 关于本刊的投稿、审稿、编辑和出版的任何问题, 您可以本页添加留言。我们将尽快给您答复。谢谢您的支持!

姓名
邮箱
手机号码
标题
留言内容
验证码

高超声速风洞子母弹大迎角抛壳投放试验

蒋增辉 宋威 陈农 贾区耀

蒋增辉, 宋威, 陈农, 等. 高超声速风洞子母弹大迎角抛壳投放试验[J]. 实验流体力学, 2016, 30(5): 42-48. doi: 10.11729/syltlx20160020
引用本文: 蒋增辉, 宋威, 陈农, 等. 高超声速风洞子母弹大迎角抛壳投放试验[J]. 实验流体力学, 2016, 30(5): 42-48. doi: 10.11729/syltlx20160020
Jiang Zenghui, Song Wei, Chen Nong, et al. Hypersonic wind tunnel drop-model test on cover ejection from cargo projectile at large angle of attack[J]. Journal of Experiments in Fluid Mechanics, 2016, 30(5): 42-48. doi: 10.11729/syltlx20160020
Citation: Jiang Zenghui, Song Wei, Chen Nong, et al. Hypersonic wind tunnel drop-model test on cover ejection from cargo projectile at large angle of attack[J]. Journal of Experiments in Fluid Mechanics, 2016, 30(5): 42-48. doi: 10.11729/syltlx20160020

高超声速风洞子母弹大迎角抛壳投放试验

doi: 10.11729/syltlx20160020
详细信息
    通讯作者:

    蒋增辉(1980-), 男, 内蒙古赤峰人, 高级工程师。研究方向:非定常空气动力学, 超空泡流体力学。通信地址:北京市7201信箱16分箱(100074)。E-mail:jzhhit@163.com

  • 中图分类号: V211.7;V212.1

Hypersonic wind tunnel drop-model test on cover ejection from cargo projectile at large angle of attack

  • 摘要: 在高超声速风洞中开展了投放模型试验,对在高超声速(Ma=5)及母弹处于大迎角(25°)状态下,子母弹壳片抛射过程的分离特性进行了研究,观察到了壳片从母弹的分离过程,对处于母弹迎风面壳片和处于母弹背风面壳片的运动轨迹,以及x向、y向位移和总位移随时间的变化规律进行了分析和对比。研究发现,迎风面和背风面壳片运动轨迹截然不同,但壳片的运动轨迹发展根据其运动特点均可分为2个阶段。迎风面和背风面壳片x方向的位移运动均可明显地分为位移缓慢变化和位移迅速增大2个阶段,而y向位移均无明显的阶段变化,但迎风面壳片y向运动速度总体上大于背风面壳片。迎风面和背风面壳片的总位移曲线也可明显地分为总位移较缓慢变化(总速度较为恒定)和迅速变化2个阶段。
  • 图  1  母弹模型示意图

    Figure  1.  Cargo projectile model figuration

    图  2  壳片模型示意图

    Figure  2.  Cover model figuration

    图  3  壳片分离前母弹模型上头激波状态

    Figure  3.  The shock on cargo projectile model before cover separation

    图  4  壳片分离试验典型状态图片序列

    Figure  4.  Typical sequence of cover separation state in wind tunnel

    图  5  壳片分离过程运动轨迹曲线

    Figure  5.  Covers separation trajectory

    图  6  壳片分离过程x向位移-时间曲线

    Figure  6.  Displacement-time curves in x-direction of covers separation

    图  7  壳片分离过程y向位移-时间曲线

    Figure  7.  Displacement-time curves in y-direction of covers separation

    图  8  壳片分离过程总位移-时间曲线

    Figure  8.  Total displacement-time curves of covers separation

  • [1] 杨启仁.子母弹飞行动力学[M].北京:国防工业出版社, 1999:1-16.

    Yang Q R. Flight dynamics of cargo projectile[M]. Beijing:National Defense Industry Press, 1999:1-16.
    [2] 王巍, 刘君, 郭正.子母弹抛壳过程非定常流动的数值模拟[J].空气动力学学报, 2006, 24(3):285-288. http://www.cnki.com.cn/Article/CJFDTOTAL-KQDX200603002.htm

    Wang W, Liu J, Gou Z. Numerical simulation of release the cover from cargo projectile[J]. Acta Aerodynamica Sinica, 2006, 24(3):285-288. http://www.cnki.com.cn/Article/CJFDTOTAL-KQDX200603002.htm
    [3] 柳森, 张鲁民.再入弹抛壳气动特性研究[J].空气动力学学报, 1993, 11(1):16-21. http://www.cnki.com.cn/Article/CJFDTOTAL-KQDX199301002.htm

    Liu S, Zhang L M. Numerical investigation of flow over shrapel/shell discarding configuration[J]. Acta Aerodynamica Sinica, 1993, 11(1):16-21. http://www.cnki.com.cn/Article/CJFDTOTAL-KQDX199301002.htm
    [4] 梁京春.导弹抛壳问题的分析[J].气动实验与测量控制, 1989, 3(3):81-87. http://www.cnki.com.cn/Article/CJFDTOTAL-LTLC198903012.htm

    Liang J C. Analysis on sabot-discard from missiles[J]. Aerodynamic Experiment and Measurement & Control, 1989, 3(3):81-87. http://www.cnki.com.cn/Article/CJFDTOTAL-LTLC198903012.htm
    [5] 龙尧松, 涂正光, 李亨鹤, 等.高超音速导弹壳片分离的CFD计算研究[C].第十二届全国计算流体力学会议, 2004, 3:386-390.

    Long Y S, Tu Z G, Li H H, et al. Research on shell separation of hypersonic missile by CFD method[C]. The Twelfth National Conference on Computational Fluid Dynamics, 2004, 3:386-390.
    [6] 龙尧松, 涂正光.导弹壳片分离的计算与试验研究[C].首届全国航空航天领域中的力学问题学术研讨会, 2004:124-127.

    Long Y S, Tu Z G. Simulation and experimental research on shell separation of missiles[C]. The First National Conference on Mechanics Problems in Aeronautics and Space Field, 2004:124-127.
    [7] 杨永健, 张来平, 高树椿, 等.多体干扰气动特性数值模拟方法研究[C].第十一届全国计算流体力学会议, 2002:325-330.

    Yang Y J, Zhang L P, Gao S C, et al. Research on numerical method of multi-body interference aerodynamic characteristic[C]. The Eleventh National Conference on Computational Fluid Dynamics, 2002:325-330.
    [8] 黄蓓, 王浩, 王帅, 等.薄片状体沉降过程中的多体干扰流场特性[J].弹道学报, 2012, 24(1):41-46. http://www.cnki.com.cn/Article/CJFDTOTAL-DDXB201201010.htm

    Huang B, Wang H, Wang S, et al. Flow field characteristics of multi-plates interference in descent[J]. Journal of Ballistics, 2012, 24(1):41-46. http://www.cnki.com.cn/Article/CJFDTOTAL-DDXB201201010.htm
    [9] 王巍.有相对运动的多体分离过程非定常数值算法研究及实验验证[D].长沙:国防科学技术大学, 2008.

    Wang W. Numerical simulation technique research and experiment verification for unsteady multi-body flowfield involving relative movement[D]. Changsha:National University of Defense Technology, 2008.
    [10] 马家驩, 唐宗衡, 张小平, 等.抛壳方案的模型自由飞试验[R].中国科学院力学研究所报告, 1983.

    Ma J H, Tang Z H, Zhang X P, et al. Wind tunnel free-flight test on shell separation[R]. IMCAS Report, 1983.
    [11] 李周复.风洞特种试验技术[M].北京:航空工业出版社, 2010:88-161.Li

    Z F. Wind tunnel special tests technique[M]. Beijing:Aviation Industry Press, 2010:88-161.
    [12] 陈少松, 丁则胜.旋转子母弹后抛撒风洞试验研究[J].流体力学实验与测量, 2004, 18(2):43-46. http://www.cnki.com.cn/Article/CJFDTOTAL-LTLC200402010.htm

    Chen S S, Ding Z S. The wind tunnel experiment techniques of backward dispersion of turning shrapnel[J]. Experiments and Measurements in Fluid Mechanics, 2004, 18(2):43-46. http://www.cnki.com.cn/Article/CJFDTOTAL-LTLC200402010.htm
    [13] 孙新利, 蔡星会, 王少龙, 等.子母弹静态开舱抛射实验[J].兵工学报, 2002, 23(2):258-260. http://www.cnki.com.cn/Article/CJFDTOTAL-BIGO200202028.htm

    Sun X L, Cai X H, Wang S L, et al. Projectile tests from a bomb dispenser[J]. Acta Armamentarii, 2002, 23(2):258-260. http://www.cnki.com.cn/Article/CJFDTOTAL-BIGO200202028.htm
    [14] 程仁全, 于夕民. NH-1风洞外挂物高速投放实验技术[R].南京航空航天大学科技报告, 1984, NHJB-85-2359.

    Cheng R Q, Yu X M. Experimental technique about dropping test of external stores in the NH-1 high speed wind tunnel[R]. Nanjing University of Aeronautics & Astronautics Report, NHJB-85-2359, 1984.
    [15] 张竹坡.高速风洞自由投放实验[R].中国空气动力研究与发展中心科技报告, 1983.

    Zhang Z P. Dropping test in the high speed wind tunnel[R]. China Aerodynamics Research and Development Centre Report, 1983.
    [16] Hinson W F. Transonic and supersonic ejection release characteristics of six dynamically scaled external-store shapes from an 0.086-scale model of a current fighter airplane[R]. Langley Research Center, NASA-TM-X-12865N26632, 1959.
    [17] Black R L. High-speed store separation-correlation between wind-tunnel and flight-test data[J]. Journal of Aircraft, 1969, 6(1):42-45. doi: 10.2514/3.43999
    [18] Clark R L. Evaluation of F-111 weapon bay aero-acoustic and weapon separation improvement techniques[R]. Air Force Flight Dynamics Lab, AFFDL-TR-79-3003(ADA070253), 1979.
    [19] Allee E G. Store separation testing techniques at the Arnold Engineering Development Center:Volume IV:description of dynamic drop store separation testing[R]. Arnold Engineering Development Center, AEDC-TR-79-1(ADA087490), 1980.
    [20] Arterbury R L, Morgret C H, Keen K S. An analytic investigation of accuracy requirements for onboard instrumentation and film data for dynamically scaled wind tunnel drop models[R]. Arnold Engineering Development Center, AEDC-TR-96-7(ADA322893), 1997.
    [21] Shalaev V I, Fedorov A V. Dynamics of slender bodies separating from rectangular cavities[C]. AIAA-2001-2996.
    [22] Schwartz D R, Bower W W, Kibens V. Active flow control for high-speed weapon release from a bay[R]. Air Force Research Lab Air Vehicles Directorate Wright-Patterson AFB, OH, RTO-MP-AVT-108-30(ADA468798), 2004.
    [23] Johnson R A, Stanek M J, Grove J E. Store separation trajectory deviations due to unsteady weapons bay aerodynamics[C]. AIAA-2008-188.
    [24] Paul M C. Experimental measurements of store separation using dry ice models in a subsonic flow[R]. Air Force Institute of Technology, AFIT/GAE/ENY/11-M23(ADA540224), 2011.
    [25] Flora T J, Reeder M F, Lofthouse A, et al. Dynamic store release of ice models from a cavity into Mach 2.9 flow[J]. Journal of Aircraft, 2014, 51(6):1927-1941.
    [26] Holden M S, Harvey J, MacLean M, et al. Development and application of a new ground test capability to conduct full-scale shroud and stage separation studies at duplicated flight conditions[C]. AIAA-2005-696.
    [27] Holden M S, Smolinski G J, Mundy E, et al. Experimental studies for hypersonic vehicle design and code validation of unsteady flow characteristics associated with free flight shroud and stage seperation and mode switching[C]. AIAA-2008-642.
    [28] Henicke B, Yechout T. Aerodynamic investigation of NASA Crew Exploration Vehicle Forward Bay Cover separation characteristics[C]. AIAA-2010-191.
    [29] Montes D R, West T J, Yechout T R. Investigation of Orion Crew Exploration Vehicle Forward Bay Cover separation characteristics[C]. AIAA-2011-1308.
  • 加载中
图(8)
计量
  • 文章访问数:  294
  • HTML全文浏览量:  151
  • PDF下载量:  13
  • 被引次数: 0
出版历程
  • 收稿日期:  2016-01-22
  • 修回日期:  2016-05-27
  • 刊出日期:  2016-10-25

目录

    /

    返回文章
    返回

    重要公告

    www.syltlx.com是《实验流体力学》期刊唯一官方网站,其他皆为仿冒。请注意识别。

    《实验流体力学》期刊不收取任何费用。如有组织或个人以我刊名义向作者、读者收取费用,皆为假冒。

    相关真实信息均印刷于《实验流体力学》纸刊。如有任何疑问,请先行致电编辑部咨询并确认,以避免损失。编辑部电话0816-2463376,2463374,2463373。

    请广大读者、作者相互转告,广为宣传!

    感谢大家对《实验流体力学》的支持与厚爱,欢迎继续关注我刊!


    《实验流体力学》编辑部

    2021年8月13日