Optimization of the design ingenerating of composite plates under compression with analytic and experimental study

Abstract
The aerospace structural components are inevitably subjected to high compression loads, which lead at most of times to the instability problems, by mean of buckling phenomenon. Thus, their buckling response studies must be given by renewed attention because of the intrinsic property obtained by a large number of parameters as well as the mechanical properties and geometrical one. The interaction/between non linearity of the material and of the geometry can lead in most of the times at a failure of the structure under compressive loads. In this survey we are dealing with the analytic resolution of the problem of plate bifurcation in submissive composites to a loading of simple or combined compression. In a first objective we go tried to give an evaluation of the critical bifurcation load of the considered plates. For sake of siniplicity this survey is restrained to the case of the simply supported- four edge plates. In a second objective, an experimental study is used to validate the analytic one. We have analyzed the effect of variation in aspect ratio with a monotonic loading path, and the Bifurcation Load Factor, labeled is studied Laminated plates of 200 mm width are used for this purpose under uni-axial compression. The comparative study of analytic and experimental results show a good agreement in many cases and a number of concluding remarks was obtained.