Prediction of Ballistic Limit of Composite GFRP Sandwich Panels under Hypervelocity Impact

LI Siyu LI Xiaobin ZHAO Pengduo GAO Songlin

李思宇, 李晓彬, 赵鹏铎, 高松林. GFRP复合三明治板在高速弹体冲击下的弹道极限预测[J]. 高压物理学报, 2018, 32(1): 015101. doi: 10.11858/gywlxb.20170529
引用本文: 李思宇, 李晓彬, 赵鹏铎, 高松林. GFRP复合三明治板在高速弹体冲击下的弹道极限预测[J]. 高压物理学报, 2018, 32(1): 015101. doi: 10.11858/gywlxb.20170529
LI Siyu, LI Xiaobin, ZHAO Pengduo, GAO Songlin. Prediction of Ballistic Limit of Composite GFRP Sandwich Panels under Hypervelocity Impact[J]. Chinese Journal of High Pressure Physics, 2018, 32(1): 015101. doi: 10.11858/gywlxb.20170529
Citation: LI Siyu, LI Xiaobin, ZHAO Pengduo, GAO Songlin. Prediction of Ballistic Limit of Composite GFRP Sandwich Panels under Hypervelocity Impact[J]. Chinese Journal of High Pressure Physics, 2018, 32(1): 015101. doi: 10.11858/gywlxb.20170529

Prediction of Ballistic Limit of Composite GFRP Sandwich Panels under Hypervelocity Impact

doi: 10.11858/gywlxb.20170529
Funds: 

National Natural Science Foundation of China 11302259

More Information
    Author Bio:

    LI Siyu(1991—), male, master, major in structural safety and reliability.E-mail:lisiyufly@163.com

    Corresponding author: LI Xiaobin(1971—), male, doctor, professor, major in structural safety and reliability. E-mail:lxbmark@163.com
  • 摘要: 研究了玻璃纤维复合三明治板在圆柱形平头弹体打击下的预测弹道极限的理论预测方法。建立了玻璃纤维复合三明治板的三阶段侵彻模型,包括侵彻面板阶段、侵彻复合材料夹芯层阶段和侵彻内板阶段。基于高速弹体侵彻下靶板的局部变形假设建立了理论关系,将弹体侵彻复合材料夹心层时视为刚体处理,面板和背板的侵彻阶段考虑了弹体的墩粗效应和靶板的绝热剪切效应。基于能量平衡原理,推导了复合材料三明治板的弹道极限,并将理论计算结果与实验结果进行对比和分析,研究了不同侵彻速度、弹体质量和夹心层厚度对弹道极限的影响。结果表明,理论计算结果与实验结果具有较好的一致性。

     

  • Figure  1.  Schematic diagram of composite sandwich panels under impact of flat-nose cylindrical projectile

    Figure  2.  Three stages of perforation

    Figure  3.  Bai-Johnson thermal-plastic constitutive model

    Figure  4.  Penetration of the back skin

    Figure  5.  Experimental setup of the ballistic impact on sandwich panels

    Figure  6.  Plastic deformation of the front skin

    Figure  7.  Plastic deformation of GERP core

    Figure  8.  Plastic deformation of the back skin

    Figure  9.  Shape of projectile after perforation of back skin

    Figure  10.  Experimental data of sandwich composite panels with a 60 mm thick GFRP core under impact of flat-nosed cylindrical projectile

    Figure  11.  Ballistic limit changing with the GFRP core thickness under impact of a 40 g flat-nosed cylindrical projectile

    Figure  12.  Ballistic limit of composite GFRP sandwich panels with a 60 mm thick core changing with the mass of projectile

    Table  1.   Mechanical and geometrical properties of steel skins

    hf/mm hb/mm ρf/(kg·m-3) σu/MPa n γi
    6.2 10.6 7 850 779 0.586 1.4
    下载: 导出CSV

    Table  2.   Comparison of ballistic limit computed by theoretical model with experimental results

    Mass/g Core thickness/mm Exp. value/(m·s-1) Calc. value/(m·s-1) Error/%
    40 40 753.8 831.9 10.7
    30 60 1 422.9 1 402.9
    40 60 1 162.7 1 132.4 2.6
    50 60 974.1 958.1 1.6
    50 75 879.0 1 144.7
    下载: 导出CSV

    Table  3.   Energy absorption ratio of composite GFRP sandwich panels under impact of flat-nosed cylindrical projectile with ballistic limit velocity

    Mass/g Core thickness/mm (Efro/Eabs)/% (Ecor/Eabs)/% (Ebac/Eabs)/%
    40 40 2.9 90.7 6.4
    30 60 1.6 95.0 3.4
    40 60 1.4 95.7 2.9
    50 60 1.8 94.4 3.8
    50 75 1.2 96.1 2.7
    下载: 导出CSV
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出版历程
  • 收稿日期:  2017-01-12
  • 修回日期:  2017-03-27

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