Mechanical Characterization and Analysis of Perforated Fibre Metal Laminates
|International Journal of Engineering Trends and Technology (IJETT)||
|© 2014 by IJETT Journal|
|Year of Publication : 2014|
|Authors : Syed Mufeez Ahmed , C.Anil Kumar
Syed Mufeez Ahmed , C.Anil Kumar. "Mechanical Characterization and Analysis of Perforated Fibre Metal Laminates", International Journal of Engineering Trends and Technology (IJETT), V13(1),18-24 July 2014. ISSN:2231-5381. www.ijettjournal.org. published by seventh sense research group
Composite materials have been a subject of interest with various special types of advanced materials during the last decades. However increasing demand in aircraft industry for high-performance, lightweight structures have stimulated a strong trend towards the development of refined models for hybrid composites material known as Fibre Metal Laminates. Fibre Metal Laminates are hybrid composites built up from interlacing layers of thin metals and fibre reinforced adhesives. Metallic layers and fibre reinforced laminate can be bonded by mechanical technique and adhesive technique. Based on these approach adhesive technique with plain and perforated aluminium sheet is used to determine its effect as a Fibre Metal Laminate. Tests are conducted to determine the mechanical properties of the Fibre Metal Laminate and the results are tabulated. The test results are validated using ANSYS 12. The weight optimization of Fibre Metal Laminates with perforation is about 25% than that of without perforations.
 Fibre Metal Laminates - An Introduction edited by Ad Vlot, Jan Willem Gunnink, Delft University of Technology, Faculty of Aerospace Engineering Delft, The Netherlands.
 Vogelesang LB, Vlot A. Development of fibre metal laminates for advanced. J Mater Process Technol 2000;103: 1–5.
 Botelho EC, Silva RA, Pardini LC, Rezende MC. A review on the development and properties of continuous fibre/epoxy/aluminum hybrid composites for aircraft structures. Mater Res 2006;9(3):247–256.
 KAUFMAN, J. G., “Fracture Toughness of 7075-T6 and –T651 sheet, plate and multilayered adhesive-bonded panels,” Jounal of Basic Engineering, vol. 89.
 JOHNSON, W. S., “Damage tolerance evaluation of adhesively laminated titanium,” ASME Journal of Materials Science and Technology, vol. 105, no. 3, pp. 182 – 187, 1983.
 VOGELESANG, L. B., MARISSEN, R., AND SCHIJVE, J., “A new fatigue resistant material: Aramid reinforced aluminum laminate (ARALL),” in Proceedings of the 11th ICAF Symposium, 1981
 WU, G. AND YANG, J.-M., “The mechanical behavior of GLARE laminates for aircraft structures,” JOM, pp. 72 – 79, 2005.
 GUNNIK, J. W., VLOT, A., DE VRIES, T. J., AND VAN DER HOEVEN, W., “GLARE technology development 1997-2000,” Applied Composite Materials, vol. 9, pp. 201 – 219,2002
 G. Roebroeks, The Metal Volume Fraction approach, TD-R-OO-003, Structural Laminates Industries, Delft.. University of Technology, Delft, 2000.
 Schwartz, M. M., “Composite Materials Handbook”, McGraw Hill, 1988.
 Bader, M. G., “Hybrid effect”, Handbook of Polymer-fibre Composites, LongmanScientific Technical, pp. 225-230, 1994.
 Higgins, A. Adhesive Bonding in Aircraft Structures. International Journal of Adhesion & adhesives. 2000. 20:367-376.
 Vermeeren, C., Beumler, T., De Kanter, J, Van Der Jagt, O., & Out B. Glare Design Aspects and Philosophies. Applied Composite Materials. 2003. 10:257-276
ARALL (Aramid Reinforced Aluminium Laminate), Composite Materials, Fibre Metal Laminate (FML), GLARE (Glass Reinforced Aluminium Laminate), Hybrid Composites, Spliced laminates.