積層パラメータによる対称積層板のパネルフラッタ設計

抄録

The present paper examines the optimal laminate configuration to maximize the flutter boundary for simply-supported symmetrically laminated plates with bending-twisting coupling. The Rayleigh-Ritz method is used to solve the natural vibration, and modal analysis using several lowest natural modes is applied to obtain the supersonic panel flutter boundary. First, the flutter characteristics are clarified with use of lamination parameters. Next, the optimal laminate configuration to maximize the flutter boundary is obtained using mathematical programming method where the lamination parameters are adopted as intermediate design variables.