Enhancing the Structural Integrity in Aircraft by using Mechanical Fasteners
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Abstract
This study investigates the stress concentration around holes in riveted lap joint of airplane structures, employing CAD software CATIA V5, for design and Ansys Workbench 19.2 for numerical analysis. The materials chosen for analysis are Aluminium Alloy 2024-T3 and structural steel. Analytical and numerical results are compared to assess the accuracy of the simulations. Initially, the CAD software is utilised to design the riveted lap joints. Fatigue life analysis of the lap joint with rivets is conducted to ascertain its durability under cyclic loading conditions.
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