Volume 15, Issue 3 (5-2015)                   Modares Mechanical Engineering 2015, 15(3): 1-8 | Back to browse issues page

XML Persian Abstract Print

Abstract:   (6247 Views)
Since aircrafts are subjected to aerodynamic and structural loads; one common defect in the aircraft fuselage and its wings is crack criterion. In most of the cases, the service life of defective parts can be increased by some sort of repairs. One of the most common types of repairs in this field is using composite patches and pasting them on damaged parts. These patches have significant advantages such as high strength, corrosion and moisture resistance, low weight and also excellent fatigue properties. In this study, base notched plates were fabricated by using of 2024 T4 aluminum alloy. Fiber metal laminate (FML) patches were made of carbon-epoxy and Phosphor – Bronze layers. These patches were attached to the base notched plate by using adhesive Arldit 2011. Specimens were subjected to tensile test and results of the tests were compared. The tested variables were chosen as lay-up, metal layer thickness and composite patch length. The results of current study indicate a dramatic increase in tensile strength of repaired parts by using these patches compared with the repaired notched parts without patches so that tensile strength is increased up to 82.4 % in the best sort of repair.
Full-Text [PDF 607 kb]   (5166 Downloads)    
Article Type: Research Article | Subject: Creep, Fatigue & Failure
Received: 2014/09/16 | Accepted: 2014/12/18 | Published: 2015/01/17

Rights and permissions
Creative Commons License This work is licensed under a Creative Commons Attribution-NonCommercial 4.0 International License.