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http://dx.doi.org/10.3795/KSME-A.2004.28.4.394

Study on the Thermo-Mechanical Behaviors of Fiber Metal Laminates Using the Classical Lamination Theory  

Choi, Heung-Soap (대한항공, 한국항공기술연구원)
Roh, Hee-Seok (대한항공, 한국항공기술연구원)
Kang, Gil-Ho (한국항공대학교 항공재료공학과 대학원)
Ha, Min-Su (경기공업대학, 정밀계측과)
Publication Information
Transactions of the Korean Society of Mechanical Engineers A / v.28, no.4, 2004 , pp. 394-401 More about this Journal
Abstract
In this study the mechanical behaviors of fiber metal laminates(FMLs) such as ARALL, GLARE and CARE which are recently developed as new structural materials and known to have excellent fatigue resistant characteristics while with relatively low densities compared to the conventional aluminum materials, are considered through the classical lamination theory. The mechanical properties such as elastic moduli, thermal expansion coefficients and hygro-thermally induced residual stresses in the fiber metal laminates are obtained and compared each other. Also, carpet plots of effective elastic moduli, Poisson's ratio and the thermal expansion coefficient for GLARE FML are plotted.
Keywords
Classical Lamination Theory; Composites; Fiber Metal Laminate; GLARE;
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  • Reference
1 Vlot, A. and Gunnink, J. W., 2001, Fiber Metal Laminates An Introduction, Kluwer Academic Publishers
2 Vogelesang, L. B. and Vlot, A., 2000, 'Development of Fibre Metal Laminates for Advanced Aerospace Materials ,' Journal of Materials Precessing Technology, Vol. 103, pp. 1-5   DOI   ScienceOn
3 Vinson, J. R. and Chou, T. W., 1975, Composite Materials and Their Use in Structures, John & Sons
4 Staley, J. T. and Hunt, W. H. Jr., 1998, 'Needs of the Aircraft Industry for Aluminum Products,' 12th Annual NCMS Technical Conference, May 4-6, 1998, Orlando, Florida, USA
5 MIL-HDBK-17-2E,Polymer Matrix Composites, Vol.2: Materials Properties
6 MIL-HDBK-5H, Metallic Materials and Elements for Aerospace Vehicle Structures
7 Aluminum-Fiberglass Laminate Material, 2002, Boeing Material Specification, BMS 7-326H
8 Remmers, J. J. C. and de Borst, R., 2001, 'Delamination Buckling of Fiber-Metal Laminates,' Composite Science and Technology, Vol. 61, pp. 2207-2213   DOI   ScienceOn
9 Wittenberg,T. C., van Baten, T. J. and de Boer, A., 2001, 'Design of Fiber Metal Laminate Shear Panels for Ultra-High Capacity Aircraft,' Aircratf Design, Vol. 4, pp. 99-113   DOI   ScienceOn
10 Yeh, J. R., 1994, 'Fatigue crack growth in Fiber-Metal Laminates,' Int. J. of Solids Structures, Vol. 32, No. 14, pp. 2063-2075   DOI   ScienceOn
11 Aerospace Structures and Materials Status, Status Report 2002, National Aerospace Technology, NLR
12 Choi, H. S., Ahn, K. J., Nam, J. D. and Chun, H. J., 2000, 'Hygroscopic Aspects of Eposy/Carbon Fiber Composite Laminates in Aircraft Environments,' Composites Part A: Applied Science and Manufacturing, Vol. 32, pp. 709-720   DOI   ScienceOn
13 Asundi, A, Choi, A. Y. N., 1997, 'Fiber Metal Laminates: An Advanced Material for Future Aircraft,' Journal of Materials Processing Technology, Vol. 63, pp. 384-394   DOI   ScienceOn
14 European Space Agency, Structural Material Handbook
15 Daniel, I.M. and Ishai. O., 1994, 'Engineering Mechanics of Composite Materials, Oxfore University Press