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BUCKLING BEHAVIOR OF COMPOSITE LAMINATES (WITH AND WITHOUT CUTOUTS) SUBJECTED TO NONUNIFORM IN-PLANE LOADS

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Title BUCKLING BEHAVIOR OF COMPOSITE LAMINATES (WITH AND WITHOUT CUTOUTS) SUBJECTED TO NONUNIFORM IN-PLANE LOADS
 
Creator SONI, G
SINGH, R
MITRA, M
 
Subject Composite laminates with cutouts
critical buckling load
nonuniform in-plane load
POSTBUCKLING RESPONSE
RECTANGULAR-PLATES
HOLES
 
Description Critical buckling loads of composite laminates are usually calculated using analytical solutions based on the assumption of uniform in-plane loads, despite of the fact that real structures are often subjected to various nonuniform loads. The present work is focused on the buckling behavior of composite laminates, with and without cutouts, subjected to various nonuniform in-plane loads. The effect of the size of the cutouts, on the buckling behavior, has been studied using finite element method. Furthermore, parametric studies on the effects of plate aspect ratio, location of the cutout and the application of a nonuniform load combined with a shear load have also been studied. Higher buckling loads were observed in pure in-plane bending compared to uniformly/nonuniformly distributed loads. Consequently, it is important to consider nonuniformly distributed loading whenever applicable, to utilize complete strength of the composite laminate and to avoid premature failure of the composite laminate due to structural instability.
 
Publisher WORLD SCIENTIFIC PUBL CO PTE LTD
 
Date 2014-10-14T17:39:05Z
2014-10-14T17:39:05Z
2013
 
Type Article
 
Identifier INTERNATIONAL JOURNAL OF STRUCTURAL STABILITY AND DYNAMICS, 13(8)
0219-4554
1793-6764
http://dx.doi.org/10.1142/S0219455413500442
http://dspace.library.iitb.ac.in/jspui/handle/100/14589
 
Language en