Fracture Analysis Of Fuselage And Wing Joint

Abstract

The main aim of this thesis is to investigate the fatigue crack and growth by fracture analysis in an aircraft fuselage and wing joint by determining the stress intensity factors, deformation and compared with alloy and composite materials. The materials considered are Al 6061, E- glass fiber, aramid fiber, technetium. 3D modeling will be done in Creo and fracture analysis will be done in Ansys 14.5.