 | Kamal, K. |
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 | Sizing Procedures for a Fibre Reinforced Plastic Box
Author : Kamal, K.
Source : Defence Science Journal ; Vol:42(4) ; 1992 ; pp 265-272
Subject : 678 Composite Materials
Keywords : Carbon fibre composites;Torsion;FRP box
Abstract : A fibre-reinforced plastic (FRP) box is an important class of structural component employed as the bending, torsion, or bending-torsion load bearing member in the modern light- weight structures. This paper presents various steps involved in the design of such a box beginning with preliminary analysis and optimization to the final sizing. The box made up of carbon fibre composite is a typical numerical example of such FRP construction. Numerical results obtained from the static stress analysis, the panel buckling analysis and the structural optimization as used for this sizing exercise, are presented. It is believed that the complete procedure of analysis using finite element method and then sizing of any FRP box in a comprehensive way, is reported for the first time. |
| | A continuum Solution to the Problems of Composite Laminate Analysis
Author : Kamal, K. ;Durvasula, S.
Source : Defence Science Journal ; Vol:41(1) ; 1991 ; pp 69-77
Subject : 678 Composite Materials
Keywords : Composite laminates ;Antisymmetric
Abstract : In this paper, a method of solution and some numerical results of free vibration and buckling of composite laminates are presented. All the edges of the laminates are assumed as simply supported. Ritz's method of solution is used with deflection surface expressed in terms of double series in Chebyshev polynomials satisfying the simply supported laminate boundary conditions. The numerical results obtained using the present analysis for isotropic as well as orthotropic plate cases, are compared with the available results. A detailed investigation on ht unnatural frequencies and mode shapes of fourlayered, simply supported composite laminates made up of graphite FRP is then undertaken. Numerical results for the first few frequencies and the critical buckling values of symmetric and antisymmetric laminates so obtained, are presented here. |
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