Evaluation of Crack Arrest Capability in the Stiffened Panel of a Transport Aircraft
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Abstract
The basic fuselage structure is developed primarily based on static strength and stability considerations. The static strength of the bulkhead plays a dominant role in its crack arrest capability. In this investigation, the strength of the rivets and skin in the presence of a longitudinal crack are studied to check the performance of the stiffened panel in arresting the two-bay crack. A finite element analysis approach was used to carry out the parametric study. A stiffened panel with multiple bays was considered for the analysis. The unstiffened fuselage expands uniformly in the radial and longitudinal directions. The fatigue cracks will initiate normally from the highest tensile stress locations. Also, cracks can get initiated due to discrete sources of damage, like tool marks on the surface or pebbles hitting the fuselage. The stress intensity factor (SIF) at different crack lengths was calculated. The panel was analysed with a central bulkhead in broken condition.
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