Fatigue Analysis of Fuselage & Wing Joint

Fatigue is progressive failure mechanism and material degradation initiates with the first cycle. Thedegradation/damage accumulation progresses until a finite crack is nucleated, then the crack propagates untilthe failure process culminates in a complete failure of the structures. The total life from first cycle to thecomplete failure can be divided into three stages: Initial life interval, Life interval, Final Life interval. Thefatigue damage is mainly based on two designs: FAIL-SAFE and SAFE-LIFE. The objective is to design aFail-Safe Structural component. In this project we have designed a Wing-Bracket interaction which was notyet designed by any of the industry. And we have estimated the fatigue life of our Wing-Bracket attachmentmodel. Here we compared the fatigue life of our model with three materials such as Maraging Steel, Titaniumand Structural A36 steel. Among this three we have proved that Maraging steel gives more fatigue lifecompared to other two materials. For estimating the fatigue life we have made some hand calculations.Finally we have represented the fatigue life with the help of Goodman Curve. The Structural Component isdesigned and analysed using CATIA and ANSYS Softwares. In analysis the maximum stress at which thecomponent undergoes degradation/damage is calculated for different End Conditions (loadings and stresses),which determines the fatigue life of the component.