International Journal of Aeronautical and Space Sciences

Abstract

In this paper, a computational approach based on a kinematic model for laminated composite I-section beam is presented. The flexural behavior of laminated composite I-beams is analyzed by using Classical Lamination Plate Theory (CLPT) and the First Order Shear Deformation Theory (FSDT). Based on these theories, a computer programme for analysis of laminated I-beam has been developed in MATLAB. The comparison of results obtained using both theories has been made. It is shown that the shear deformation has significant effect on the deflection of the beam. Furthermore, the laminated I-beam is also modeled using ABAQUS software package for numerical results using different value of load applied at mid-span of the beam. Results obtained using ABAQUS are compared with results obtained with self developed computer program in MATLAB. It is observed that there is good correlation between results obtained from ABAQUS and the computer program before local failure such as buckling of flanges and web occur. Finally, the effect of various parameters such as width-to- thickness ratio of flanges, depth-to-thickness of web, and span length-to-depth ratio of I-beam has been investigated. It is concluded that the effect of web depth-to-thickness ratio has little effect on the overall flexural response of I-beam while the width-to-thickness ratio of flanges has significant effect on the flexural response of composite I-beams