Nonlinear response of laminated cylindrical panels

摘要

The geometric nonlinear responses of laminated composite cylindrical panels subjected to (i)axial compression and (ii) central concentrated load are investigated in this work. The parameters considered are: number of layers, symmetric/antisymmetric laminate constructions, cross-ply/angle-ply fibre orientation, boundary concentrated load are investigated in this work. The parameters considered are; number of layers, symmetric/antisymmetric laminate constructions, cross-ply/angle-ply fibre orientation, boundary conditions and central angle of panel. An eight- node degenerated layered shell element with an efficient explicit throuhg-thickness integration scheme is employed. It has been observed that the cylindrical panels under axial compression exhibit stable post-buckling paths and the number of layers in the laminate for a given total thickness has considerable influence on the load-deflection behaviour.