The aim of this work is to investigate the repair performance of aircraft structures modeled by 2024-T3 aluminum plate with inclined central cracks under biaxial complex loading.The mixed-mode stress intensity factor (SIF) is greatly affected by biaxial loading.The goal is to reduce the (SIF) level near the crack after repairing, and determine the best orientation of patch fibers regarding the complex load.The results of the study show that the fiber orientation should conform to the patch sequence for better fixation efficiency.
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