Abstract
This paper describes the effort to apply a semi-numerical formulation to the buckling analysis of laminated C-section column. The presented analysis is confined to the elastic buckling of axially end compressed laminated C-section column. In this method, the laminated C-section is treated as a system of three connected laminated composite panels. Assembled stiffness matrices are then integrated from the individual composite panel's stiffness. Eventually, an eigen-value problem is formed for buckling solutions. Since the theoretical formulation is seminumerical, the method can be employed to other arbitrary cross-sectional geometries of laminated columns.
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