缝合复材层板损伤后压缩强度的数值计算方法  

CALCULATION RESEARCH ON THE RESIDUAL COMPRESSIVE STRENGTH OF STITCHED COMPOSITE LAMINATES AFTER IMPACT DAMAGE

作　　者：陈涛[1] 许希武[1] 毛春见[1] 

机构地区：[1]南京航空航天大学机械结构力学及控制国家重点实验室,南京210016

出　　处：《机械强度》2017年第5期1126-1131,共6页Journal of Mechanical Strength

基　　金：国家自然科学基金项目(11272146);江苏高校优势学科建设工程项目资助~~

摘　　要：缝合复合材料在复合材料的厚度方向加入了缝线,不仅提高了层板的层间强度,抑制了分层的扩展,而且提高了受冲击后的压缩强度。采用开口等效法来模拟层板的初始损伤,用三维实体单元模拟层板,空间三维杆单元模拟缝线的增强作用,采用三维Hashin判据作为压缩时层板渐近损伤的失效判据,模拟缝合复合材料层板受冲击损伤后的压缩过程;得到层板的剩余压缩强度,与试验结果吻合较好。Stitched composite material not only suppresses delamination expansion, but also improves inter-laminar toughness and compressive characteristics after impact by introducing stitch in the thickness direction. Equivalent hole method simulates the initial damage of stitched plate. The finite element analysis method with damage evolution process based on threedimensional Hashin criterion with 3D solid element modelling laminates,3D bar element modelling stitch simulated the stitched composite laminates damage evolution effectively. The calculation results were in good agreement with the experimental data.

关 键 词：复合材料 缝合层板 冲击损伤 剩余压缩强度 

分 类 号：V214.8[航空宇航科学与技术—航空宇航推进理论与工程]