复合材料帽型加筋壁板的失效机制分析与改进设计
发布时间：2019-03-06 14:41
【摘要】：为了准确预测复合材料帽型加筋壁板的后屈曲承载能力,针对压缩载荷下筋条端头斜削的复合材料帽型加筋壁板结构的失效机制及失效载荷进行了研究。首先利用物理试验,研究了端头斜削的复合材料帽型加筋壁板失效过程,然后构建了考虑蒙皮/缘条胶接界面以及复合材料层板失效的非线性损伤分析模型,详细地研究了损伤起始、扩展和失效的全过程。在此基础上,提出了包覆层对蒙皮/缘条界面进行增强的设计方案,并基于数值仿真和试验研究了包覆层对复合材料帽型壁板的破坏模式和承载能力的影响。数值分析和试验结果表明,包覆层设计能够明显提高结构的屈曲载荷和后屈曲承载能力,分析结果与试验值吻合良好,且预测的破坏模式也与试验结果一致。
[Abstract]:In order to accurately predict the post-buckling bearing capacity of composite cap-type stiffened panels, the failure mechanism and failure loads of composite cap-type stiffened panels subjected to compression loads were studied. In this paper, the failure process of composite cap stiffened panels with end slanting is studied by physical experiments, and then a nonlinear damage analysis model considering the failure of skin / edge bonding interface and composite laminate is constructed. The whole process of damage initiation, extension and failure is studied in detail. On the basis of this, a design scheme for strengthening the skin / edge interface by cladding is proposed. Based on numerical simulation and experiments, the influence of cladding layer on the failure mode and load-bearing capacity of composite cap-shaped panels is studied. The results of numerical analysis and test show that the buckling load and post-buckling bearing capacity of the structure can be obviously improved by the cladding design. The analytical results are in good agreement with the experimental values, and the predicted failure mode is also consistent with the experimental results.
【作者单位】： 西北工业大学航空学院;中国飞机强度研究所;
【基金】：民机专项科研(MJ-2015-F-027)
【分类号】：TB33
[Abstract]:In order to accurately predict the post-buckling bearing capacity of composite cap-type stiffened panels, the failure mechanism and failure loads of composite cap-type stiffened panels subjected to compression loads were studied. In this paper, the failure process of composite cap stiffened panels with end slanting is studied by physical experiments, and then a nonlinear damage analysis model considering the failure of skin / edge bonding interface and composite laminate is constructed. The whole process of damage initiation, extension and failure is studied in detail. On the basis of this, a design scheme for strengthening the skin / edge interface by cladding is proposed. Based on numerical simulation and experiments, the influence of cladding layer on the failure mode and load-bearing capacity of composite cap-shaped panels is studied. The results of numerical analysis and test show that the buckling load and post-buckling bearing capacity of the structure can be obviously improved by the cladding design. The analytical results are in good agreement with the experimental values, and the predicted failure mode is also consistent with the experimental results.
【作者单位】： 西北工业大学航空学院;中国飞机强度研究所;
【基金】：民机专项科研(MJ-2015-F-027)
【分类号】：TB33
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