Survival Backstory: You can read it here. It's the ship of another mechanic, who Ill touch on more later in another entry. For the FE analysis MSC Nastran/Patran softwares have been used.I didn't make the iceberg, so some things might not be 100% accurate.Here's the original post: The SurfaceĢnd Crashed Ship: As the name implies, there's another ship, on a separate island, close to the top left border of the map. Also the effect of different radius ratios (lug geometry) on the number of cycles to failure is studied. Further, fatigue crack growth life for the cracked lug subjected to constant amplitude cyclic loading was estimated using the Walker’s crack growth model. Both analytical and numerical methods have been used for obtaining the stress intensity factor. Stress intensity factor for the pin loaded lug with through-the-thickness emanating from the lug hole has been determined. Initially stress concentration effects in the loaded lug were determined by applying analytical and numerical methods. The pin is assumed to be fit in the lughole with zero clearance and no frictional restraint. The pin is assumed to have a larger stiffness than the lug. To appraise the safety level of lugs under working conditions, fatigue crack growth and residual life data are required.In the present work, a computational model for estimating the residual fatigue life of attachment lugs has been proposed. Because of this reason the wing-fuselage lug joints are considered as most fracture critical components in the aircraft structure. At the pin and lug interface, the combination of high stress concentration and fretting could potentially lead to crack initiation and then crack propagation under cyclic loading. During service, the lug type joints are subjected to fatigue loading and complete load transfer takes place through the pin. Lug joints are special type of pin joints, which are widely used for joining various parts of an aircraft, especially for joining wings to fuselage.
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