International Journal of Advanced and Applied Sciences
Int. j. adv. appl. sci.
EISSN: 2313-3724
Print ISSN: 2313-626X
Volume 4, Issue 6 (June 2017), Pages: 43-49
Title: Numerical modeling of defective hybrid composite plates
Author(s): Belkacem Achour 1, *, Djamel Ouinas 2, Mabrouk Touahmia 1, Mustapha Boukendakdji 1
Affiliation(s):
1Department of Civil Engineering, College of Engineering, University of Hail, Hail, Saudi Arabia
2Department of Mechanical Engineering, Université Abdelhamid Ibn Badis de Mostaganem, Mostaganem, Algeria
https://doi.org/10.21833/ijaas.2017.06.006
Abstract:
It is known that the optimization of the positioning of reinforcements within a composite material is likely to increase significantly the performance of a structure. Accordingly, buckling is the most critical failure mode for notched and non-stiffened plates under axial compressive stress. In this study, the buckling response of laminated plates made of hybrid composite materials with and without elliptical notches is analyzed using finite element methods. The plates are made of carbon/epoxy/aluminum and arranged in following ordered manner [Al/ (θ/-θ) /Al]. The resistance to buckling of the hybrid plates under uniaxial compression is examined according to fiber orientations, the orientation of the notch and finally the thickness of the aluminum layer in the composite material. The results showed that when the fibers are at the amplification of the critical load of buckling in the hybrid notchless plate is of the order of 59% and 27.66% for a thickness of the aluminum layer tAl= 0.2mm and 0.127mm respectively. The elliptical notch oriented at 0° reduces the maximum load four times more than when oriented at 90o .
© 2017 The Authors. Published by IASE.
This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/).
Keywords: Elliptical notch, Buckling, Hybrid composites, Finite element analysis
Article History: Received 11 February 2017, Received in revised form 11 April 2017, Accepted 2 May 2017
Digital Object Identifier:
https://doi.org/10.21833/ijaas.2017.06.006
Citation:
Achour B, Ouinas D, Touahmia M, and Boukendakdji M (2017). Numerical modeling of defective hybrid composite plates. International Journal of Advanced and Applied Sciences, 4(6): 43-49
http://www.science-gate.com/IJAAS/V4I6/Achour.html
References:
Baba B O (2007). Buckling behavior of laminated composite plates. Journal of Reinforced Plastic Composites, 26(16): 1637–1655. https://doi.org/10.1177/0731684407079515 |
||||
Baba BO and Baltaci A (2007). Buckling characteristics of symmetrically and anti-symmetrically laminated composite plates with central cutout. Applied Composite Materials, 14(4): 265-276. https://doi.org/10.1007/s10443-007-9045-z |
||||
Hamani N, Ouinas D, Benderdouche N, and Sahnoun M (2012). Buckling analyses of the antisymetrical composite laminate plate with a crack from circular notch. Advanced Materials Research, 365: 56-61. https://doi.org/10.4028/www.scientific.net/AMR.365.56 |
||||
Hu HT and Lin BH (1995). Buckling optimization of symmetrically laminated rectangular plates with various geometry and end conditions. Composite Science and Technology, 55(3): 277–285. https://doi.org/10.1016/0266-3538(95)00105-0 |
||||
Komur MA, Sen F, Atas A, and Arslan N (2010). Buckling analysis of laminated composite plates with an elliptical/circular cutout using FEM. Advances in Engineering Software, 41(2): 161–164. https://doi.org/10.1016/j.advengsoft.2009.09.005 |
||||
Kweon JH, Jung JW, Kim TH, Choi JH, and Kim DH (2006). Failure of carbon composite-toaluminum joints with combined mechanical fastening and adhesive bonding. Composite Structures, 75(1): 192–198. https://doi.org/10.1016/j.compstruct.2006.04.013 |
||||
Mroz A (2011). Stability analysis of a plane, rectangular, boron-epoxy laminated plate basing on strength properties determined by different methods. Mechanics and Mechanical Engineering, 15(2): 161-181. | ||||
Nemeth MP (1988). Buckling behavior of compression-loaded symmetrically laminated angle-ply plates with holes. The American Institute of Aeronautics and Astronautics Journal, 26(3): 330–336. https://doi.org/10.2514/3.9893 |
||||
Ouinas D and Achour B (2013). Buckling analysis of laminated composite plates [(θ/− θ)] containing an elliptical notch. Composites Part B: Engineering, 55: 575-579. https://doi.org/10.1016/j.compositesb.2013.07.011 |
||||
Reddy PR and Harish T (2014). Buckling analysis of orthotropic laminated composite plate with rectangular Cut-Outs by using FEA. Journal of Emerging Technologies in Computational and Applied Sciences, 10(1): 75-81. | ||||
Rhodes MD, Mikulas MM, and McGowan PE (1984). Effects of orthotropy and width on the compression strength of graphite–epoxy panels with holes. AIAA Journal, 22(9): 1283–1292. https://doi.org/10.2514/3.8774 |