An efficient method of analysis for stress intensity was studied in this paper through the anisotropic elasticity solution using complex potentials on the stringer bonded composite panel with impact damage including notch-like edge crack. The finite element analysis of stiffened panel was also performed to be compared with its results.
ABSTRACT:The prediction and analysis procedure of fatigue damage crack growth life for a stiffener bonded composite laminate panel including center hole and edge notch damage, was studied. It was performed on the basis of fatigue damage growth test results on a laminated skin panel specimens and the analysis results of stress intensity factor for the stiffener bonded composite panel. According to the comparison between experimental test and prediction results of fatigue damage growth life, it was concluded that the residual strength and damage tolerance assessment can be carried out along to the edge notch crack growth.
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