Vibration of thermally buckled composite plates with initial deflections using triangular elements
Abstract
A consistent finite element formulation is presented for the analysis of thermal postbuckling and free vibration of thermally buckled thin, laminated composite plates subjected to large temperature change. The influence of moderately large initial imperfections in deflection on the thermal postbuckling deflection and the vibration characteristics of the buckled plate is also investigated. The finite element equations of motion are derived from the principle of virtual work. These equations can be mathematically separated into two sets and solved in sequence. The first set of equations yields the particular solution of static thermal postbuckling deflection, and the second set of equations gives the homogeneous solution of vibration characteristics on the buckled plate. The first set of static equations is solved by using NewtonRaphson iteration method. The tangent stiffness matrix in the final iteration is equal to the total stiffness matrix of the second set of dynamic equations. This feature saves tremendous computation time in comparing with using the conventional approach. The influence of lamination angle, temperature distribution, plate planform of arbitrary shape, and boundary support conditions on postbuckling and vibration behavior are investigated.
 Publication:

AIAA/ASME/ASCE/AHS/ASC 34th Structures, Structural Dynamics, and Materials Conference
 Pub Date:
 April 1993
 Bibcode:
 1993ssdm.conf..226Z
 Keywords:

 Composite Structures;
 Deflection;
 Finite Element Method;
 Free Vibration;
 Thermal Buckling;
 Thin Plates;
 Equations Of Motion;
 Laminates;
 Structural Vibration;
 Temperature Gradients;
 Vibration Effects;
 Structural Mechanics