Multiscale aircraft fuselage fatigue analysis by the dual boundary element method

This paper focuses on the multiscale fatigue life analysis of an aircraft fuselage panel in order to investigate the damage tolerance performance. The two-dimensional multiscale analyses were carried out under different levels of external loads and based on linear elastic fracture mechanics. For this, a micro model consisting of a square plate with a central circular hole and two cracks, from pre-established initial damages and subjected to uniaxial tension, was modelled using the computer program BemCracker2D an academic computational package for crack growth analysis based on the dual boundary element method (DBEM). The objective is to compute the number of fatigue cycles for each load increment and relate them to their respective compliance in local micro elements. Then, the results were treated statistically with Monte Carlo simulation to ensure the integrity of the fuselage and, therefore, avoiding reaching a Limit State during the design lifespan. The main advantages of using the DBEM formulation implemented in BemCracker2D are easy pre- and post-processing, simplicity of meshing and satisfactory accuracy.