Abstract
An approach is proposed to determine the global Optimum solutions for the maximum critical buckling loads of symmetrically laminated composite plates. In the approach the buckling loads are calculated for all possible combinations of the fiber orientation angles with small increments in the outer layers but relatively rough increments in the inner layers. The best twenty solutions and global distribution of the buckling loads are presented to limit the range of search for the next step. This process is repeated until the fiber orientation angle, in the inner-most layer is determined. Numerical examples show the effectiveness of the approach for 8-layer laminated plates.
