ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Buckling of SSCC Composite Laminates Under In-plane Bending Load
Received date: 2013-08-26
Revised date: 2013-11-08
Online published: 2013-11-16
In order to provide a stability analysis method of composite airframe structures, this paper presents a numerical solution method for the buckling of SSCC composite laminates (laminates having two parallel edges simply supported and the remaining parallel edges clamped) based on the Levy form series and finite-difference method. First, the deflection function is transformed to a discrete form by the finite-difference method; then, the system of equations is supplemented by the boundary conditions; finally, the critical buckling load is obtained through solving a generalized eigenvalue problem. Numerical examples are utilized to verify the present method on both isotropic and composite plates. The comparison of the present method and a finite element method (FEM) is conducted as well. The result shows that the present method has high accuracy and provides a new way for the buckling analysis of composite plates.
YUAN Jianfeng , NI Zao , CHEN Baoxing . Buckling of SSCC Composite Laminates Under In-plane Bending Load[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014 , 35(4) : 1026 -1033 . DOI: 10.7527/S1000-6893.2013.0464
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