항공재료 리벳홀에 인접한 원공결함의 위치에 따른 응력집중계수의 변화와 균열발생거동
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The material deficiencies in the form of pre-existing defects can initiated cracks and fractures. The stress
distribution and fatigue crack initiation life of engineering materials may be associated with the size, the
shape and the relative location of defects contained in the component. The objective of this study is to
investigate the effect of arbitrarily located hole defect around the rivet hole of a wing section in monolithic
aluminum and Al/GFRP laminates under cyclic bending moment during a service load. The stress distribution
and the fatigue crack initiation behavior near a rivet hole of on the relationships between stress concentration
factor (Kt) and relative position of defects were considered. The test results indicated the features of different
stress field. Therefore, the stress concentration factor (Kt) and the fatigue crack initiation behavior was
illustrated different behavior according to each position of hole defect around the rivet hole in monolithic
aluminum and Al/GFRP laminates.