Author : Ashish A. Desai 1
Date of Publication :7th February 2017
Abstract: The composite thin-walled beams like I-beams are extensively used as chief structural elements. Composite load carrying structures like aircraft wings, skin, tail planes have solid stiffeners for efficient load bearing abilities. This paper is intended to provide tools that ensure better designing options for composite laminates of I -beam. In this Paper an analytical method & FEM approach calculating bending stiffness, bending stress, bending strain of flange and web laminates. The results show the stacking sequence and fiber angle orientation strongly affects strength of composite I-beam
Reference :
-
- P.F. Liu, L.J. Xing, J.Y. Zheng “Failure analysis of carbon fiber/epoxy composite cylindrical laminates using explicit finite element method” Composites: Part B 56 (2014) 54–61
- M.A. Badie, E. Mahdi , A.M.S. Hamouda, “An investigation into hybrid carbon /glass fiber reinforced epoxy composite automotive drive shaft”, Materials and Design 32 (2011), pp 1485– 1500
- G. Zhou, J. Hood, “ Design, manufacture and evaluation of laminated carbon/epoxy I-beams in bending”, Composites: Part A 37 (2006) 506–517
- K.D. Potter , R. Davies , “Heavily loaded bonded composite structure: design, manufacture and test of `I' beam specimens”, Composite Structures 51 (2001) 389-399
- W. S. Chan and K.A. Syed, “Determination of Centroid and Shear Center Locations of Composite Box Beams” the University of Texas at Arlington, Texas, USA