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不同工艺成型复合材料加筋板轴压破坏机理分析

徐荣章 关志东 王仁宇 蒋思远

徐荣章, 关志东, 王仁宇, 等 . 不同工艺成型复合材料加筋板轴压破坏机理分析[J]. 北京航空航天大学学报, 2016, 42(5): 1032-1038. doi: 10.13700/j.bh.1001-5965.2015.0335
引用本文: 徐荣章, 关志东, 王仁宇, 等 . 不同工艺成型复合材料加筋板轴压破坏机理分析[J]. 北京航空航天大学学报, 2016, 42(5): 1032-1038. doi: 10.13700/j.bh.1001-5965.2015.0335
XU Rongzhang, GUAN Zhidong, WANG Renyu, et al. Failure mechanism analysis of different types of manufacture for composite stiffened panels under axial compression load[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(5): 1032-1038. doi: 10.13700/j.bh.1001-5965.2015.0335(in Chinese)
Citation: XU Rongzhang, GUAN Zhidong, WANG Renyu, et al. Failure mechanism analysis of different types of manufacture for composite stiffened panels under axial compression load[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(5): 1032-1038. doi: 10.13700/j.bh.1001-5965.2015.0335(in Chinese)

不同工艺成型复合材料加筋板轴压破坏机理分析

doi: 10.13700/j.bh.1001-5965.2015.0335
详细信息
    作者简介:

    徐荣章 男,硕士研究生。主要研究方向:复合材料结构设计。Tel.:010-82338873 E-mail:buaa_xrz@163.com;关志东 男,博士,教授,博士生导师。主要研究方向:飞机结构设计,复合材料力学和损伤容限。Tel.:010-82338873 E-mail:D5062010@126.com

    通讯作者:

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

  • 中图分类号: V257;TB330.1

Failure mechanism analysis of different types of manufacture for composite stiffened panels under axial compression load

  • 摘要: 对受到边界约束的不同工艺成型复合材料加筋板进行了轴压试验和数值模拟,研究二次胶接和共固化工艺成型加筋板轴向压缩破坏机理。轴压试验中,通过应变计实时监测试验件局部屈曲,及时记录试验件初始声响载荷,通过断面观测分析结构破坏机理。基于ABAQUS软件建立有限元模型模拟结构后屈曲损伤渐进直至破坏过程。计算结果和试验结果相吻合,研究表明工艺对结构稳定性及承载能力没有显著影响,而加筋板构型影响较大。聚甲基丙烯酰亚胺(Polymethacrylimide,PMI)泡沫不影响结构失稳载荷及破坏载荷,但能延缓结构初始损伤的发生。二次胶接成型加筋板界面临近破坏才出现损伤,而共固化成型加筋板界面损伤出现较早且扩展缓慢,表现出更好的损伤阻抗特性。

     

  • [1] 杜善义,关志东.我国大型客机先进复合材料应对策略思考[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] JEROME P.Advanced materials and technology for A380 struc-ture[J].FAST Magazine,2003,32:3-8.
    [3] NICHOLLS D J,GALLAGHER J P.Determination of GIC in angle-ply composites using a cantilever beam test method[J].Journal of Reinforced Plastics and Composites,1983,2(1):2-17.
    [4] CHAI H.The characterization of mode I delamination failure in nonwoven,multidirectional laminates[J].Composites,1984,15:277-290.
    [5] LANZI L.A numerical and experimental investigation on composite stiffened panels into post-buckling[J].Thin-Walled Structures,2004,42(12):1645-1664.
    [6] OH S H,KIM K S,KIM C G.An efficient postbuckling analysis technique for composite stiffened curved panels[J].Composite Structures,2006,74(3):361-369.
    [7] FALZON B G,STEVENS K A,DAVIES G 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.
    [8] ORIFICI A C,SHAH S A,HERSZBERG I,et al Failure analysis in postbuckled composite t-sections[J].Compsite Structures,2008,86(1-3):146-153.
    [9] 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).
    [10] 孔斌,陈普会,陈炎.复合材料整体加筋板轴压后屈曲失效评估方法[J].复合材料学报,2014,31(3):765-771. KONG B,CHEN P H,CHEN Y.Post-buckling failure evaluation method of integrated composite panels under uniaxial compression[J].Acta Materiae Compositae Sinica,2014,31(3):765-771(in Chinese).
    [11] 陈绍杰.复合材料技术与大型飞机[J].航空学报,2008,29(3):605-610. CHEN S J.Composite technology and large aircraft[J].Acta Aeronautica et Astroautica Sinica,2008,29(3):605-610(in Chinese).
    [12] FALZON B G,STEVEN G P.Buckling mode transition in hat-stiffened composite panels loaded in uniaxial compression[J].Composite Structures,1997,37(2):253-267.
    [13] FALZON B G.The behaviour of damage tolerant hat-stiffened composite panels loaded in uniaxial compression[J].Composites Part A:Applied Science and Manufacturing,2001,32(9):1255-1262.
    [14] MO Y M,GE D Y,ZHOU J F.Experiment and analysis of hat-stringer-stiffened composite curved panels under axial compression[J].Composite Structures,2015,123:150-160.
    [15] KIM G H,CHOI J H,KWEON J H.Manufacture and performance evaluation of the composite hat-stiffened panel[J].Composite Structures,2010,92(9):2276-2284.
    [16] ZHU S H,YAN J Y,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.
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出版历程
  • 收稿日期:  2015-05-25
  • 网络出版日期:  2016-05-20

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