Fatigue Crack and Delamination Behavior in the Composite Material Containing n Saw-cut and Circular Hole (I) - Aramid Fiber Reinforced Metal Laminates -

소컷 및 원공 주위의 피로균열 형태변화와 층간분리거동 (I) - 아라미드섬유 강화 금속적층재의 경우 -

  • 송삼홍 (고려대학교 기계공학과) ;
  • 김철웅 (고려대학교 대학원 기계공학과)
  • Published : 2003.01.01


The aramid fiber reinforced metal laminates(AFRMLs) used for the wing part fair flight suffer the cyclic bending moment of variable amplitude during service. The fatigue crack propagation and delamination behavior in AFRMLs containing a saw-cut and circular hole was investigated using the average stress criterion(ASC) model. Mechanical tests were carried out using the cyclic bending moment of 4.9 N . m and delamination was observed by ultrasonic C-scan images. In case of AFRMLs containing a saw-cut fatigue crack propagated in aluminum matrix, inducing delamination. However, in case of AFRMLs containing a circular hole, delamination formed with two types under cyclic bending moment of 4.9 N . m. First, delamination formed along the fatigue crack in aluminum matrix. Second, delamination formed without any fatigue crack around the circular hole. Therefore, delamination was formed depending on the stress distribution near the circular hole.


Aramid Fiber Reinforced Metal Laminates;Cyclic Bending Moment;Saw-cut;Circular Hole;Average Stress Criterion;Delamination Zone;C-scan Image


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