DYNAMIC STABILITY OF COMPOSITE LAMINATES UNDER NON-CONSERVATIVE FORCES

In this paper, the variation equation of the composite rectangular laminate plates subjected to uniformly distributed follower forces is deduced based on the variation principle of the quasi-natural frequency of the non-conservative system self-excited vibration. The basic equations of the finite element and the characteristic equations used to solve the critical loading and natural frequency are obtained. The critical loads are computed for composite rectangular plates bearing follower forces with various boundary conditions and different aspect ratios. It is concluded from the analysis that boundary conditions affect the dynamic stability and the buckling pattern of plates. The angle-ply directions of composite laminate plates have an influence on the buckling load.