Abstract
This study proposes an innovative methodology for integrating the Paris Law parameters, C and m, into the analysis, design, and maintenance of aircraft fuselages to enhance fatigue life predictions and structural integrity. The approach combines macro- and micro-scale analyses, leveraging the Boundary Element Method (BEM) to calculate internal stress fields, identify critical stress points, and guide crack propagation simulations at the micro-scale. These simulations utilize C and m to estimate remaining fatigue life under various operational scenarios. The methodology is implemented using a custom computational tool that integrates the BemLab GUI and BemCracker2D solver, automating stress evaluation, compliance calculations, and crack growth simulations. Case studies validate the approach, illustrating how variations in C and m affect fatigue life predictions and enable optimized material selection and inspection strategies. The first case examines a fuselage section under normal and shear loading, while the second includes additional stress components to evaluate their influence on damage tolerance. This methodology provides a practical alternative to traditional crack size-based evaluations by incorporating C and m into routine assessments. It enhances maintenance strategies, improves safety, reduces operational costs, and extends the service life of fuselage structures, presenting a significant advancement in aerospace engineering.
Published Version
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