Fatigue Analysis of a Panel Consisting of Window Cutout and Frames in the Fuselage of a Transport Airframe

Abstract Aircraft structure is the symbolic representation of high performance where functional requirements demand light weight and, therefore, high operating stresses. An efficient structural component must have three primary attributes; namely, the ability to perform its intended function, adequate service life and the capability of being produced at reasonable cost. To ensure the safety of aircraft structures, life estimation analysis is essential. This paper focuses its attention on designing a fail-safe fuselage structure. The damage most frequently associated with the structural integrity of the fuselage are longitudinal cracks under high hoop stresses induced by cabin pressurization of the fuselage. The analysis of these types of cracks is complex, first due to the complex structural configuration (i.e. frames, skin Longerons and crack stopper straps) and secondly due to the influence of the curvature of the shell. Various analytical and empirical approaches have been used to study the fatigue life capability of the fuselage structure. In this paper, fatigue analysis of a panel consisting of window cut out and frames in the fuselage of a transport airframe are carried out through FEA method of analysing.