Abstract
This paper presents the results of a theoretical study of the supersonic flutter of panels composed of advanced composite materials. Three different materials were selected for this study: boron-epoxy, graphite-epoxy and boron-aluminum. Primary emphasis is given to panels composed of a single layer or ply of material; however, in two instances, the stability behavior of these single layer panels is contrasted with the behavior of panels composed of several layers of material. The results presented show that the orientation of the ply material principal axes and the number of plies in the laminate have a pronounced effect on flutter. Effects of anisotropy are shown to disappear quickly as more layers of material are added. In one case, an irregularity in the stability curve is discussed as is convergence of the assumed mode solution.
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