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Volume 41 Issue 6
Jun.  2015
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Journal of Beijing University of Aeronautics and Astronautics  > 2015  >  41(6): 1066-1072.
ZHOU Rui, GUAN Zhidong, LI Xing, et al. Progressive damage analysis of open-hole composite laminates under compression load[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(6): 1066-1072. doi: 10.13700/j.bh.1001-5965.2014.0395(in Chinese)
Citation: ZHOU Rui, GUAN Zhidong, LI Xing, et al. Progressive damage analysis of open-hole composite laminates under compression load[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(6): 1066-1072. doi: 10.13700/j.bh.1001-5965.2014.0395(in Chinese)
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Progressive damage analysis of open-hole composite laminates under compression load

doi: 10.13700/j.bh.1001-5965.2014.0395
  • 1.

    School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

  • 2. Department of Strength Analysis, Beijing Aeronautical Science & Technology Research Institute, Commercial Aircraft Corporation of China Ltd, Beijing 102211, China

  • Received Date: 02 Jul 2014
  • Publish Date: 20 Jun 2015
    Abstract
  • Firstly, compressional experiments were conducted on open-hole composite laminates. The progressive damage during the loading process and the final damage mode of the specimen were detected with a digital microscope, scanning electron miroscope and an X-scan equipment. Damage initiation and delamination between layups of 45° and 90° were observed during the experiments. Secondly, the failure modes of composite laminates are divided into intra-laminar failure and inter-laminar failure. A multiscale model based on the micro-mechanics of failure MMF3 theory and the interface cohesive element method for the damage analysis of open-hole compression laminates was developed. At last, the initiation and propagation of the damage and the failure modes of the laminates were predicted with the model. Numerical results such as the damage initiation position of fiber and matrix, the delamination propagation process and the final failure modes are in good agreement with experimental results, which indicates that the model is applicable to analysis of progressive damage of open-hole composite laminates under compression load.

     

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    • References(15)
  • [1]
    杜善义, 关志东.我国大型客机先进复合材料技术应对策略思考[J].复合材料学报, 2008, 25(1):1-10. Du S Y, Guan Z D.Strategic considerations for development of advanced composite technology for large commercial aircraft in China[J].Acta Materiae Compositae Sinica, 2008, 25(1):1-10(in Chinese).
    [2]
    Suemasu H, Takahashi H, Ishikawa T.On failure mechanisms of composite laminates with an open hole subjected to compressive load[J].Composites Science and Technology, 2006, 66(5):634-641.
    [3]
    Berbinau P, Scoutis C, Guz I A.Compressive failure of 0°unidirectional carbon-fibre-reinforced plastic(CFRP)laminates by fibre microbuckling[J].Composites Science and Technology, 1999, 59(9):1451-1455.
    [4]
    Soutis C.Damage tolerance of open-hole CFRP laminates loaded in compression[J].Composite Engineering, 1994, 4(3):317-327.
    [5]
    Soutis C, Curtisb P T.A method for predicting the fracture toughness of CFRP laminates failing by fiber microbuckling[J].Composites Part A:Applied Science and Manufacturing, 2000, 31(7):733-740.
    [6]
    Lee J, Soutis C.Thickness effect on the compressive strength of T800/924C carbon fibre-epoxy laminates[J].Composites, 2006, 36(2):213-227.
    [7]
    关志东, 黎增山, 刘德博, 等.复合材料层板开孔压缩损伤分析[J].复合材料学报, 2012, 29(3):167-172. Guan Z D, Li Z S, Liu D B, et al.Damage analysis of open-hole compression laminates[J].Acta Materiae Compositae Sinica, 2012, 29(3):167-172(in Chinese).
    [8]
    Lee H K, Kim B R.Numerical characterization of compressive response and damage evolution in laminated plates containing a cutout[J].Composites Science and Technology, 2007, 67(11):2221-2230.
    [9]
    American Society for Testing and Materials International.ASTM D6484/D6484M-09 Standard test method for open-hole compressive strength of polymer matrix composite laminates[S].West Conshohocken:ASTM International, 2009.
    [10]
    Wisnom M R, Hallett S R.The role of delamination in strength, failure mechanism and hole size effect in open hole tensile tests on quasi-isotropic laminates[J].Composites Part A:Applied Science and Manufacturing, 2009, 40(4):335-342.
    [11]
    Tsai S W.Strength & life of composites[M].Stanford:Stanford University, 2008:6-29-6-51.
    [12]
    Sun X S, Tan V B C, Tay T E.Micromechanics-based progressive failure analysis of fibre-reinforced composites with non-iterative element-failure method[J].Computers & Structures, 2011, 89(11):1103-1116.
    [13]
    Anon.ABAQUS user's manual[CP/CD].Version 6.10.Pawtucket:Hibbitt Karlsson and Sorensen, 2010.
    [14]
    Benzeggagh M L, Kenane M.Measurement of mixed-mode delamination fracture toughness of unidirectional glass/epoxy composites with mixed-mode bending apparatus[J].Composites Science and Technology, 1996, 56(4):439-449.
    [15]
    Turon A, Davila C G, Camanho P P, et al.An engineering solution for mesh size effects in the simulation of delamination using cohesive zone models[J].Engineering Fracture Mechanics, 2007, 74(10):1665-1682.
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