Abstract
A substantial amount of parametric analysis and testing is carried out in the design and construction process for a large transport aircraft to achieve an optimal structure. One of the damage tolerance design objectives of any large transport aircraft is a two bay crack arrest in a circumferential direction. In this crack arrest ability, the longeron static strength plays a dominant role. Thus, a parametric analysis of the efficiency of the longeron on the residual strength of a two-bay circumferential crack have been carried out in this study. One of the critical load cases that the fuselage has to effectively tolerate is internal pressurization. In the fatigue life estimation for the fuselage, the compression and decompression cycles are generally used as an input. Pressurization load cases are considered for the study in the present work. Analytical method is used to calculate the circumferential crack arrest capability in the stiffened panel by considering longitudinal stresses. The stress intensity factor (SIF) values obtained using finite element analysis (FEA) agree with the SIF values obtained by theoretical method.
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