作者: Majid Khayat , Davood Poorveis , Shapour Moradi , Mona Hemmati
DOI: 10.12989/SEM.2016.58.1.059
关键词: Linear elasticity 、 Structural engineering 、 Stiffness matrix 、 Stiffness 、 Shell (structure) 、 Eigenvalues and eigenvectors 、 Buckling 、 Direct stiffness method 、 Materials science 、 Finite strip method
摘要: Laminated composite shells are commonly used in various engineering applications including aerospace and marine structures. In this paper, using semi-analytical finite strip method, the buckling behavior of laminated deep as well thick revolution under follower forces which remain normal to shell is investigated. The stiffness caused by pressure calculated for subjected external fibers shells. divided into several closed strips with alignment their nodal lines circumferential direction. governing equations derived based on first-order shear deformation theory accounts through thickness-shear flexibility. Displacements rotations middle surface approximated combining polynomial functions meridional direction truncated Fourier series an appropriate number harmonic terms load matrix variation loads will be each shell. Assembling these matrices results global may un-symmetric. Upon forming linear elastic called constitutive matrix, geometric required elements second step analysis eigenvalue problem provided. study, different parameter effects investigated geometry, material properties, boundary conditions. Afterwards, outcomes compared other researches. By considering article, it can concluded that deformation-dependent assumption entail decrease This characteristic studied examples.