Author, Subjects, Keywords

Cited Author

 
 
   » By Author or Editor
 » Browse Author by Alphabet
 » By Journal
 » By Subjects
 » Malaysian Journals
 » By Type
 » By Year
 » By Latest Additions
 
 
   » By Author
 » Top 20 Authors
 » Top 20 Article
 » Top Journal Cited
 » Top Article Cited
 » Journal Citation Statistics
 » Usage Since Sept 2007


 
 
 

Login | Create Account

Modelling of fiber metal laminate (fml) composite using the residual stiffness and strength model

Abdullah S., and Fahruddin A., and Syarif J., and Omar M.Z., (2009) Modelling of fiber metal laminate (fml) composite using the residual stiffness and strength model. International Journal of Mechanical and Materials Engineering, 4 (2). pp. 186-190. ISSN 1823-0334

[img]
Preview
PDF (Full Text) - Requires a PDF viewer such as GSview, Xpdf or Adobe Acrobat Reader
144Kb

Official URL: http://ejum.fsktm.um.edu.my/ArticleInformation.aspx?ArticleID=783

Affiliations

Universiti Kebangsaan Malaysia, Faculty of Engineering and Built Environment, Dept. of Mechanical and Materials Engineering
Universiti Kebangsaan Malaysia, Faculty of Engineering and Built Environment, Dept. of Mechanical and Materials Engineering
Universiti Kebangsaan Malaysia, Faculty of Engineering and Built Environment, Dept. of Mechanical and Materials Engineering
Universiti Kebangsaan Malaysia, Faculty of Engineering and Built Environment, Dept. of Mechanical and Materials Engineeringt

Abstract

The fatigue behavior of FML composite is so diverse and complex that present knowledge is far from complete. Two commonly used approaches to model fatigue damage are residual stiffness and the residual strength approach. In this paper, residual stiffness and the residual strength model is simulated. The model approach is in way: the damage growth rate-a measure for stiffness loss- is expressed by two separate terms representing the initiation and propagation phase of damage respectively. The model is capable of simulating the three stages of stiffness degradation: initial decline, gradual reduction, and final failure, as well as the stress redistribution due to the loss of stiffness in the damaged zones. The experiment also was carried out in this study.

Item Type:Journal
Keywords:FML, Fatigue, Residual stiffness and the residual strength model, Composite
Subjects:T Technology, Engineering
ID Code:10305

Alderliesten, R.C., 2005, Fatigue Crack Propagation and Delamination Growth in Glare, Delft University Press

Alderliesten, R.C.,2007, Analytical prediction model for fatigue crack propagation and delamination growth in Glare, p. 628-646.

Botelho, E.C., Pandini, L.C.,2005, Hygrothermal effect on damping behavior of metal/glass fiber/epoxy hybrid composite, p. 190-198.

Paepegem, V. , Degrieck, L.C., 2002, A new coupled approach of residual stiffnessand strength for fatigue of fiber reinforced composite, p. 747-762.

Schijve, J., 2003, Fatigue of structure and materials in the 20th century and the state of the art, p. 679-702.

Shim, D.J., Alderliesten, R.C., 2003, Fatigue crack growth prediction in Glare hybrid laminates, p. 1759-1767.

Sinke, J, 2003, Manufacturing of GLARE parts and structures, p.293–305.

Theodore, P., Vassilopoulos, A., 2004, Life prediction methodology for GFRP laminates under spectrum loading, p. 657–666.

Van Paepegem, W., Degrieck, J., 2002, Effects of load sequence and block loading on the fatigue response of fiber–reinforced compositesp. 19-35.

Vlot, A, Vogelesang, L.B., 1999, Towards application of fiber metal lamination in large aircraft p. 558-570 .

Vlot, A., Gunnink, J.W., 2001, Fibremetal Laminates: An Introduction, Kluwer Academic Publishers

Repository Staff Only: item control page
 
 
 
 
 
 
© Copyright 2007 MyAIS Faculty of Computer Science and Information Technology, University of Malaya – All Rights Reserved. Malaysian Abstracting and Indexing System is powered by EPrints 3 which is developed by the School of Electronics and Computer Science at the University of Southampton. More information and software credits.