Comparison of fatigue crack growth of riveted and bonded aircraft lap joints made of Aluminium alloy 2024-T3 substrates _ A numerical study

6th International Conference on Fracture Fatigue and Wear

Pitta, S.^1 ; Rojas, J.I.^1 ; Crespo, D.^2

Dept. of Physics, Division of Aerospace Engineering, C/Esteve Terradas 5, Castelldefels

08660, Spain^1

Dept. of Physics, C/Esteve Terradas 5, Castelldefels

08860, Spain^2

关键词: Adhesive bonding;    Aircraft lap joints;    Bonded joint;    Bonded repairs;    Crack length;    Fracture analysis;    IS maintenance;    Lower stress;   

Others  :  https://iopscience.iop.org/article/10.1088/1742-6596/843/1/012035/pdf
DOI  :  10.1088/1742-6596/843/1/012035

来源: IOP

【 摘 要 】

Aircraft lap joints play an important role in minimizing the operational cost of airlines. Hence, airlines pay more attention to these technologies to improve efficiency. Namely, a major time consuming and costly process is maintenance of aircraft between the flights, for instance, to detect early formation of cracks, monitoring crack growth, and fixing the corresponding parts with joints, if necessary. This work is focused on the study of repairs of cracked aluminium alloy (AA) 2024-T3 plates to regain their original strength; particularly, cracked AA 2024-T3 substrate plates repaired with doublers of AA 2024-T3 with two configurations (riveted and with adhesive bonding) are analysed. The fatigue life of the substrate plates with cracks of 1, 2, 5, 10 and 12.7mm is computed using Fracture Analysis 3D (FRANC3D) tool. The stress intensity factors for the repaired AA 2024-T3 plates are computed for different crack lengths and compared using commercial FEA tool ABAQUS. The results for the bonded repairs showed significantly lower stress intensity factors compared with the riveted repairs. This improves the overall fatigue life of the bonded joint.