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脱粘尺寸对复合材料单加筋板压缩性能的影响

冀赵杰 关志东 黎增山 薛斌

冀赵杰, 关志东, 黎增山, 等 . 脱粘尺寸对复合材料单加筋板压缩性能的影响[J]. 北京航空航天大学学报, 2016, 42(10): 2169-2179. doi: 10.13700/j.bh.1001-5965.2015.0603
引用本文: 冀赵杰, 关志东, 黎增山, 等 . 脱粘尺寸对复合材料单加筋板压缩性能的影响[J]. 北京航空航天大学学报, 2016, 42(10): 2169-2179. doi: 10.13700/j.bh.1001-5965.2015.0603
JI Zhaojie, GUAN Zhidong, LI Zengshan, et al. Effects of debond size on compressional behavior of single-stiffened composite panels[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(10): 2169-2179. doi: 10.13700/j.bh.1001-5965.2015.0603(in Chinese)
Citation: JI Zhaojie, GUAN Zhidong, LI Zengshan, et al. Effects of debond size on compressional behavior of single-stiffened composite panels[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(10): 2169-2179. doi: 10.13700/j.bh.1001-5965.2015.0603(in Chinese)

脱粘尺寸对复合材料单加筋板压缩性能的影响

doi: 10.13700/j.bh.1001-5965.2015.0603
详细信息
    作者简介:

    冀赵杰,男,博士研究生。主要研究方向:复合材料损伤容限设计。E-mail:jizhaojie@buaa.edu.cn;关志东,男,博士,教授。主要研究方向:复合材料结构设计、复合材料力学。Tel.:010-82338873,E-mail:D5062010@163.com

    通讯作者:

    关志东,Tel.:010-82338873,E-mail:D5062010@163.com

  • 中图分类号: V257;TB330.1

Effects of debond size on compressional behavior of single-stiffened composite panels

  • 摘要: 为确定脱粘缺陷尺寸对轴压载荷下复合材料单加筋板屈曲和后屈曲特性的影响,对4组含不同尺寸脱粘缺陷的工型加筋板进行了试验和数值模拟研究。试验中通过应变测量和超声C扫描等技术手段对试验件的屈曲及后屈曲过程中的变形和缺陷扩展情况进行了监测。基于ABAQUS软件建立了有限元分析(FEA)模型,采用LaRC03准则对复合材料层内损伤进行判定,采用胶层单元对界面脱粘损伤进行模拟,以几何扰动的形式引入失稳波形,利用FEA模型对试验件的屈曲和后屈曲过程进行了模拟。模拟结果与试验结果吻合较好,根据研究结果对试验件的失效过程和脱粘缺陷扩展机理进行了分析与探讨。研究表明,预制脱粘缺陷尺寸大小对试验件屈曲和后屈曲特性影响较大,对最终破坏模式影响不大。脱粘尺寸的增大会导致试验件承载能力的大幅降低,在复合材料加筋结构损伤容限设计中需要着重考虑。

     

  • [1] STEVENS K A,RICCI R,DAVIES G A O.Buckling and postbuckling of composite structures[J].Composites,1995,26(3):189-199.
    [2] FALZON B G,STEVENS K A,DAVIES G A O.Postbuckling behaviour of a blade-stiffened composite panel loaded in uniaxial compression[J].Composites Part A:Applied Science and Manufacturing,2000,31(5):459-468.
    [3] ORIFICI A C,SHAH S A,HERSZBERG I,et al.Failure analysis in postbuckled composite T-sections[J].Composite Structures,2008,86(1-3):146-153.
    [4] 孔斌,叶强,陈普会,等.复合材料整体加筋板轴压后屈曲的传载机制[J].复合材料学报,2010,27(5):142-149.KONG B,YE Q,CHEN P H,et al.Post-buckling load transfer mechanisms of an integrated composite panel under uniaxial compression[J].Acta Materiae Compositae Sinica,2010,27(5):142-149(in Chinese).
    [5] KONG C W,LI I C,KIM C G,et al.Postbuckling and failure of stiffened composite panels under axial compression[J].Composite Structures,1998,42(1):13-21.
    [6] ZHU S,YAN J,CHEN Z,et al.Effect of the stiffener stiffness on the buckling and post-buckling behavior of stiffened composite panels-Experimental investigation[J].Composite Structures,2015,120:334-345.
    [7] 邵青,何宇廷,张腾,等.侧边边界条件对复合材料加筋板轴压载荷下屈曲和后屈曲性能的影响[J].复合材料学报,2014,31(3):741-748.SHAO Q,HE Y T,ZHANG T,et al.Influence of side boundary condition on buckling and post-buckling performance of composite stiffiened panels under axial compression load[J].Acta Materiae Compositae Sinica,2014,31(3):741-748(in Chinese).
    [8] 王菲菲,崔德刚,熊强,等.复合材料加筋板后屈曲承载能力工程分析方法[J].北京航空航天大学学报,2013,39(4):494-497.WANG F F,CUI D G,XIONG Q,et al.Engineering analysis of post-buckling loading capability for composite stiffened panels[J].Journal of Beijing University of Aeronautics and Astronautics,2013,39(4):494-497(in Chinese).
    [9] ORIFICI A C,THOMSON R S,DEGENHARDT R,et al.An analysis tool for design and certification of postbuckling composite aerospace structures[J].International Journal of Structural Stability & Dynamics,2010,10(3):669-683.
    [10] BISAGNI C,VESCOVINI R,DÁVILA C G,et al.Assessment of the damage tolerance of postbuckled hat-stiffened panels using single-stringer specimens:AIAA-2010-2696[R].Reston:AIAA,2010.
    [11] 徐荣章,关志东,刘璐,等.屈曲模态对含缺陷复材加筋板后屈曲的影响[J].北京航空航天大学学报,2014,40(9):1299-1304.XU R Z,GUAN Z D,LIU L,et al.Effect of buckling mode on performance of post-buckled composite stringer-stiffened panels with debond[J].Journal of Beijing University of Aeronautics and Astronautics,2014,40(9):1299-1304(in Chinese).
    [12] LAURIN F,CARRERE N,MAIRE J F.Laminated composite structures subjected to compressive loading:A material and structural buckling analysis[J].Composite Structures,2007,80(2):172-182.
    [13] GREENHALGH E,MEEKS C,CLARKE A,et al.The effect of defects on the performance of post-buckled CFRP stringer-stiffened panels[J].Composites Part A:Applied Science and Manufacturing,2003,34(7):623-633.
    [14] ORIFICI A C,ALBERDI I O Z,THOMSON R S,et al.Compression and post-buckling damage growth and collapse analysis of flat composite stiffened panels[J].Composites Science and Technology,2008,68(15-16):3150-3160.
    [15] YAP J W H,THOMSON R S,SCOTT M L,et al.Influence of post-buckling behavior of composite stiffened panels on the damage criticality[J].Composite Structures,2004,66(1-4):197-206.
    [16] VESCOVINI R,DÁVILA C G,BISAGNI C.Failure analysis of composite multi-stringer panels using simplified models[J].Composites Part B:Engineering,2013,45(1):939-951.
    [17] 周睿,关志东,黎增山,等.长桁-翼肋连接对复合材料单加筋板压缩性能的影响[J].复合材料学报,2015,32(2):491-500.ZHOU R,GUAN Z D,LI Z S,et al.Effects of connector between stringer and rib on compressional behavior of single-stiffened composite panels[J].Acta Materiae Compositae Sinica,2015,32(2):491-500(in Chinese).
    [18] DÁVILA C G,CAMANHO P P.Failure criteria for FRP laminates in plane stress:NASA/TM-2003-212663[R].Hampton:NASA,Langley Research Center,2003.
    [19] LAŠ V,ZEMŠÍK R,KROUPA T,et al.Failure prediction of composite materials[J].Bulletin of Applied Mechanics,2008,4(14):81-87.
    [20] BENZEGGAGH M L,KENANE M.Measurement of mixed-mode delamination fracture toughness of unidirectional glass/expoxy composites with mixed-mode bending apparatus[J].Composites Science and Technology,1996,56(4):439-449.
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出版历程
  • 收稿日期:  2015-09-15
  • 刊出日期:  2016-10-20

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