This work is aimed at reproducing numerically a campaign of experimental tests performed for
the development of reinforced panels, typically found in aircraft fuselage. The bonded reinforcements can
significantly reduce the rate of fatigue crack growth and increase the residual strength of the skin. The
reinforcements are of two types: stringers and doublers. The former provides stiffening to the panel while the
latter controls the crack growth between the stringers. The purpose of the study is to validate a numerical
method of analysis that can predict the damage tolerance of these reinforced panels. Therefore, using a fracture
mechanics approach, several models (different by the geometry and the types of reinforcement constraints)
were simulated with the finite element solver ABAQUS. The model was created exploiting symmetries, while
the bonding between skin and stiffener was taken either rigid or flexible due to the presence of adhesive. The
possible rupture of the reinforcements was also considered. The stress intensity factor trend obtained
numerically as a function of crack growth was used to determine the fatigue crack growth rate, obtaining a good
approximation of the experimental crack propagation rate in the skin. Therefore, different solutions for
improving the damage tolerance of aircraft reinforced panels can be virtually tested in this way before
performing experiments.