Damage tolerance of GLARE laminates subjected to high-velocity impact

被引：0
|
作者：
Chen Y. [1 ]
Liao G. [1 ]
Ren L. [1 ]
Liu X. [1 ]
机构：
[1] Key Laboratory of Advanced Manufacture Technology for Automobile Part, Vehicle Engineering Institute, Chongqing University of Technology, Chongqing
来源：
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2018年 / 39卷 / 07期
关键词：
Ballistic limit; Constraint effect; Failure pattern; GLAss fiber-REinforced aluminum (GLARE) laminates; Impact;
D O I：
10.7527/S1000-6893.2017.21733
中图分类号：
学科分类号：
摘要：
To investigate the damage tolerance of the GLAss fiber-REinforced aluminum (GLARE) laminates subjected to high-velocity impacts, the single and multiple impact performance of the GLARE laminates was studied by tests and numerical simulation. High-velocity impact tests were conducted on GLARE panels using a one-stage gas gun at different impact locations, i.e. middle point, edge point and corner point of the plate. The ballistic limit was thus obtained as well as the failure patterns, and the dynamic response was studied based on the numerical simulation. The results show that GLARE laminates absorb the impact energy mainly in the form of plastic deformation, metal cracking, debonding, and fiber breakage. The clamp constraint exerted great influences on the damage mechanism of the GLARE laminates subjected to impacts. The failure patterns in the GLARE laminates subjected to the impact load were distinctly affected by the constraint, i.e. denting and metal cracking, plugging characteristics etc. The ballistic limit velocity of the GLARE laminates impacted at the corner point of the plate was found to be much less than that impacted at the middle location of the plate. Compared with the middle and the edge points, the corner position of the plate subjected to multiple impacts was the most vulnerable to perforation. © 2018, Press of Chinese Journal of Aeronautics. All right reserved.
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共 23 条
  • [1] Vogelesang L.B., Vlot A., Development of fibre metal laminates for advanced aerospace structures, Journal of Materials Processing Technology, 103, 1, pp. 1-5, (2000)
  • [2] Meng W.Y., Xie L.Y., Liu J.Z., Et al., Contrast study on fatigue life performance of glass fiber reinforced Al-Li alloy laminates under unimodal overload, Acta Aeronautica et Astronautica Sinica, 37, 5, pp. 1536-1543, (2016)
  • [3] Lin X.H., Zhang T., Zhang X.B., Et al., Impact resistance of carbon fiber-reinforced aluminumlaminates, Explosion and Shock Waves, 33, 3, pp. 303-310, (2013)
  • [4] Hamed Z., Mohadeseh F., Giangiacomo M., Et al., Low velocity impact analysis of fiber metal laminates (FMLs) in thermal environments withvarious boundary conditions, Composite Structures, 149, 1, pp. 170-183, (2016)
  • [5] Ma Y.E., Hu H.W., Xiong X.F., Comparison of damage in FMLs, aluminum and composite panels subjected to low-velocity impact, Acta Aeronautica et Astronautica Sinica, 35, 7, pp. 1902-1911, (2014)
  • [6] Wan Y., Zhang J.F., Wang Z.Q., Et al., Low-velocity impact damage on glassfibre reinforced aluminum laminates: Experiments and finite element analysis, Journal of Harbin Engineering University, 36, 6, pp. 769-773, (2015)
  • [7] Hen Q., Guan Z.D., Li Z.S., Et al., Experimental investigation on impact performances of GLARE laminates, Chinese Journal of Aeronautics, 28, 6, pp. 1784-1792, (2015)
  • [8] Yu G.C., Wu L.Z., Ma L., Et al., Low velocity impact of carbon fiber aluminumlaminates, Composite Structures, 119, pp. 757-766, (2015)
  • [9] Tao J., Li H.G., Pan L., Et al., Review on research and development of fiber metal laminates, Journal of Nanjing University of Aeronautics & Astronautics, 47, 5, pp. 626-636, (2015)
  • [10] Hu Y.B., Li H.G., Tao J., Et al., The effects of temperature variation on mechanical behaviors ofpolyetheretherketone-based fiber metal laminates, Polymer Composites
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