Due to their excellent fatigue characteristics and relatively low density, Fiber Metal Laminates (FML) are considered candidate fuselage materials in future generation Ultra-High Capacity Aircraft (UHCA). To exploit the postbuckling behavior, as is the practice in conventional aluminum alloy fuselage structures, an existing engineering design method for postbuckled shear panels was adapted for applications with FML materials. To verify the adapted design methodology, two stiffened FML shear panels were designed and tested until failure. The dimensions of the panels were taken representative for an UHCA fuselage structure. In addition, detailed Finite Element analyses were performed with STAGS to predict panel response during testing. The Finite Element results showed very good agreement with experimental data, giving confidence in replacing very costly actual panel tests with computer simulations. It was found that the test panel dimensions were outside the region where the current engineering design method for postbuckled panels is valid. To account for this phenomenon, an extension to the current design method is proposed.
Design of FML shear panels for ultra-high capacity aircraft
2000
14 Seiten, 11 Quellen
Conference paper
English
Design of fiber metal laminate shear panels for ultra-high capacity aircraft
Online Contents | 2001
|Design of an ultra-high capacity aircraft
AIAA | 1998
|Design of an Ultra-High Capacity Aircraft
British Library Conference Proceedings | 1998
|Design of an Ultra-High Capacity Aircraft
SAE Technical Papers | 1998
|Design of an Ultra-High Capacity Aircraft
British Library Conference Proceedings | 1993
|