This work is aimed at reproducing numerically a campaign of experimental tests performed for<br />the development of reinforced panels, typically found in aircraft fuselage. The bonded reinforcements can<br />significantly reduce the rate of fatigue crack growth and increase the residual strength of the skin. The<br />reinforcements are of two types: stringers and doublers. The former provides stiffening to the panel while the<br />latter controls the crack growth between the stringers. The purpose of the study is to validate a numerical<br />method of analysis that can predict the damage tolerance of these reinforced panels. Therefore, using a fracture<br />mechanics approach, several models (different by the geometry and the types of reinforcement constraints)<br />were simulated with the finite element solver ABAQUS. The model was created exploiting symmetries, while<br />the bonding between skin and stiffener was taken either rigid or flexible due to the presence of adhesive. The<br />possible rupture of the reinforcements was also considered. The stress intensity factor trend obtained<br />numerically as a function of crack growth was used to determine the fatigue crack growth rate, obtaining a good<br />approximation of the experimental crack propagation rate in the skin. Therefore, different solutions for<br />improving the damage tolerance of aircraft reinforced panels can be virtually tested in this way before<br />performing experiments.
Carta, F., & Pirondi, A. (2018). Damage tolerance analysis of aircraft reinforced panels. Frattura Ed Integrità StrutturaleFrattura Ed Integrità Strutturale, 5(16), 34–42. https://doi.org/10.3221/igf-esis.16.04