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对复合材料开口补强层合板进行压缩试验研究.对复合材料开口非补强和开口补强层合板建立有限元模型,采用三维8节点厚壳单元(S8R),分别利用非线性分析和线性分析方法对复合材料的应力-应变响应进行模拟.通过试验数据与数值结果对比发现,几何非线性分析方法较线弹性分析方法能更好地符合试验结果.通过编制材料子程序(UMAT)来预测材料的损伤萌生和扩展,预测的应力-应变响应、损伤扩展、失效强度基本与试验结果一致.

参考文献

[1] O' Neill G S. Asymmetric Reinforcements of a Quasiisotropic Graphite Epoxy Plate Containing a Circular Hole [R]. ADA119625MF, 1985.
[2] Pickett D H, Sillivan P. Analysis of Symmetric Reinforcement of Quasi-isotropic Graphite/Epoxy Plates with a Circular Cutout under Uniaxial Tension Loading [R]. ADA139998MF, 1988.
[3] 程乐锦,薛明德,胡宁.基于三维有限元法的层合圆柱壳应力分析[J].复合材料学报,2003,20(2):88-93.Cheng Lejin, Xue Mingde, Hu Ning. Stress analysis of the laminated cylindrical shells based on the 3D FEM [J]. Acta Materiae Compositae Sinica, 2003, 20(2) : 88-93.
[4] 罗小东,寇长河,于卫东.复合材料层合结构开口的非对称补强研究[J].航空学报,1994,15(12):1478-1481.Luo Xiaodong, Kou Changhe, Yu Weidong. Asymmetric submerged reinforcement of composite laminates containing a circular hole [J]. Acta Aeronautica et Astronautica Sinica ,1994, 15(12): 1478-1481.
[5] 寇长河,汪彤,郦正能,杨旭.复合材料层合板开口补强研究[J].北京航空航天大学学报,1997,23(4):477-481.Kou Changhe, Wang Tong, Li Zhengneng, Yang Xu. Reinforcement research of composite laminates containing a circular hole [J]. Journal of Beijing University of Aeronautics and Astronautics, 1997, 23(4): 477-481.
[6] Eiblmeier J, Loughlan J. The buckling response of carbon fiber composite panels with reinforced cut-outs[J]. Composite Structures, 1995, 32: 97-113.
[7] Mahdi S, Kinloch A J, Matthews F L, Crisfield M A. The mechanical performance of repaired stiffened panels Ⅰ:Experimental characterization [J]. Composites, 2002, 33:343-354.
[8] Mahdi S, Kinloch A J, Crisfield M A. The mechanical performance of repaired stiffened panels Ⅱ: Finite element modeling[J]. Composites, 2002, 33:355-366.
[9] Marie laure Dano, Guy Gendron, Andre Picard. Stress and failure analysis of mechanically fastened joints in composite laminates [J]. Composite Structures, 2000, 50: 287-296.
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