含孔复合材料点阵夹层结构数值计算方法及其影响因素

发布时间：2018-01-18 04:07

本文关键词：含孔复合材料点阵夹层结构数值计算方法及其影响因素　出处：《复合材料学报》2017年01期 　论文类型：期刊论文

【摘要】：针对含孔复合材料点阵夹层结构在面内压缩载荷作用下的失效模式及其影响因素问题,通过实验对含孔复合材料点阵夹层结构失效模式进行了研究;基于3D Hashin准则和Chang-Chang刚度退化准则建立了含孔复合材料点阵夹层结构有限元渐进损伤失效分析模型,并将计算结果与实验结果进行了对比;基于有限元分析方法探讨了开孔形状、开孔率以及开孔位置对其极限承载力的影响。结果表明:当点阵夹层结构面板厚度较大时,含孔复合材料点阵夹层结构的主要失效模式为面板W'溃;通过对比有限元计算结果和实验结果,极限承载力的最大误差约为12%,失效位置与实验结果一致;当点阵夹层结构的对称面与载荷方向平行且孔的中心在对称面上时,面内压缩强度与开孔位置无关,主要受到开孔形状和开孔率的影响;当点阵夹层结构对称面与载荷方向垂直且孔的中心在对称面上时,边距大于一个胞元,面内压缩强度基本不变,边距小于一个胞元,面内压缩强度下降。
[Abstract]:Aiming at the failure mode of porous composite lattice sandwich structure under in-plane compression and its influencing factors, the failure mode of porous composite lattice sandwich structure was studied by experiments. Based on 3D Hashin criterion and Chang-Chang stiffness degradation criterion, a finite element progressive failure analysis model of composite lattice sandwich structures with holes is established. The calculated results are compared with the experimental results. Based on the finite element analysis method, the effects of hole shape, opening ratio and hole location on the ultimate bearing capacity are discussed. The results show that: when the thickness of lattice sandwich structure panel is large. The main failure mode of porous composite lattice sandwich structure is panel W'collapse. By comparing the finite element calculation results with the experimental results, the maximum error of the ultimate bearing capacity is about 12 percent, and the failure position is consistent with the experimental results. When the symmetrical plane of the lattice sandwich structure is parallel to the load direction and the center of the hole is on the symmetric plane, the in-plane compression strength is independent of the opening position and is mainly affected by the opening shape and the opening rate. When the symmetrical plane of the lattice sandwich structure is perpendicular to the load direction and the center of the hole is on the symmetric surface, the edge distance is larger than one cell, the in-plane compression strength is almost unchanged, the edge distance is less than one cell, and the in-plane compression strength decreases.
【作者单位】：南京工业大学机械与动力工程学院;
【基金】：国家自然科学基金青年基金(11402132)
【分类号】：TB33
【正文快照】： 现代工业与国防装备向着高承载、高机动性、多功能的方向发展,要求结构具有质量轻、承载能力大以及功能集成性好的特点。作为典型的集轻质、高承载、多功能为一体的结构材料,夹层结构[1-2]受到航空航天飞行器和船舶结构研究者们的青睐[3-5]。随着研究的深入,出现了更低密度、

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