相对冲击位置和补片层数对胶接修理CFRP复合材料层合板抗冲击性能的影响
Effect of relative impact location and patch layer number on impact resistance of adhesive repaired CFRP composite laminates

本文针对碳纤维增强聚合物（CFRP）复合材料修补结构，基于连续损伤力学和粘结单元模型，在ABAQUS软件中对低速冲击载荷下不同冲击位置和补片层数的CFRP复合材料层合板内部和层间损伤进行了数值分析，并与试验结果进行了对比。选择相对冲击位置为0 mm、10 mm、20 mm、30 mm和40 mm时对应的五种修补结构，通过数值计算和试验，获得了修补结构在低速冲击过程中的冲击力、冲击能量等数据。在保持补片单层厚度不变的前提下，使补片层数从1层增加到5层，计算获得了修补结构的低速冲击响应。研究结果表明：冲头接触修补结构时会对补片造成较大的损伤，补片可以提高含孔损伤母板的抗冲击性能；冲击点离修补结构损伤孔越近，结构受冲击所产生的分层损伤越严重；增加补片的层数可以提高修补结构的抗冲击性能；通过对补片层数进行优化，得到优化层数为2，其对应的修补结构与无修补结构相比分层损伤面积减少了19.9%，较好地提升了母板的抗冲击性能。 In this paper, based on continuous damage mechanics and cohesive element model, the internal and interlaminar damage of carbon fiber reinforced polymer (CFRP) composite laminates with different impact locations and patch layers under low velocity impact load were numerically analyzed in ABAQUS, and the results were compared with the experimental results. Five kinds of repaired structures corresponding to the relative impact location of 0 mm, 10 mm, 20 mm, 30 mm and 40 mm were selected. The impact force and impact energy of the repaired structure during the low velocity impact were obtained from numerical and experimental approach. By keeping the monolayer thickness unchanged, the layer number of the used patches increased from 1 layer to 5 layers, and the low velocity impact response of repaired structures was obtained numerically and experimentally. The results show that when the impactor contacts repaired structures, it causes damage to the patch, but the patch definitely improves the impact resistance of the damaged parent laminates. When the impact point is closer to the damage hole of the repaired structure, the more serious the damage of the structure is caused by the impact. Moreover, the increase of the layer number within the patch design improves the impact resistance of the repaired structure. An optimum layer number is 2 obtained by optimizing the layer number, and the corresponding delamination area is reduced by 19.9% compared with damaged parent laminate without repair. 国家自然科学基金民航联合基金重点项目（U1333201）；国家博士后科学基金面上资助项目（2016M602256