基于Timoshenko-Mindlin假设及Hamiton原理，建立了一般纤维叠层圆柱厚壳在参数激励下的大线性振动方程；应用多摸态近似和增量谐波平衡法求解丁叠层圆柱厚壳的非线性动力稳定性问题。横向剪切变形、端部支承条件等因素的影响被讨论。

Non-linaear vibrations of generally larminateed circualr cylindrical shells are examined using the Timoshenko-Mindlin kinematic hypotheis and an extensin of te Donnell-type shell theory. The effects of transverse shear deformatoion. Rotatory inertia and geometricaly initial imperfection are included in te analysis. A soultion for non-linear free vibratins of these cylindrical shell is fromulated using a mulotimode apprjoach. The boudary condition for the varying rotational end stiffness in the cirrumferentail direcito is staisfied by replacement of the and bending moments by an equivalent lateral pressure ncar the shell ands. The Galerkin procedure furnishes an infinite postbukling behavior of the shell is trated as a specialcase. Numerical results in non-linear vibration. and postbuckling of cylindraical lamnates are presented grasphically for different parameters and comparedd with available data.

Based on Timosheko-Mindlin kinematic hypotheses and Hamilton's principle a system of equations of motion is derived for geometrically nonlinear behavior of generally lamineted cylindrical thick panels of geometric initial imperfections. The variation of rotational stiffness is assumed to be identical along opposite edges. A solution for nonlinear vibratin of these panels is formulated by use of a muliti-mode approach. The boundary condilion for the varying rotational siiffness is satisfied by replacemnent of the edge bending moments by an equivalent lateral pressure near the paneldeges as in a previous work. The Galerkin procedure furnishes an infunite set of equations for time-dependent coefficients which is solved by the method of harmonic balance. Int the post-buckling case the set of time equations reduces to algebraic equations. Numericall results in nonlinear vibratio and post-buckling are presesnted gruphically for different parameters and compared with avalible data.

A dynamic non-linear theory for generally laminated shallow clidrical shallow eylindrical panels is developed with the aid of Hamilton's principle. The effects of transverse shear deformatin. Rotatory inertia and geometrically initial imperfectin are included in the analysis. A multi-mode solution is formulated for non-linear free vibratin of an anti-symmetric angle-ply cylindrical lamminate with its edges elastically restained against roataion. The resulting equoations for time functions are solved by the mehod of harmonic balance. The postbuckling behavior of the panel is treated as a special case. Numerical results in non-linear vibration and posbuckling are presented for different values of the amplitude of iaitial imperfection. side-to-thickness ratio rotaional edge stiffiness,aspect ratio, orientation angle,number of layrs and material properies. Present results are compared with available data.

This paper deals with the static large deflpetion and the large amplitude free flexural ibration of a symmetrically laminated orthotropic eliiptical plted with a simply equations of the plated in terms of the deflection and two inplane displacemets is presented by use of a modified Galerkin procedure. Two inplance equations of equilibrium and the associted inplance bonndary eonditions are satified axaotly. Numerical Comatations are performed for stsatic and dynamic responses of homogenceous and symmetric cross-plyelliptical plates with different axes rations, numbers of layers and high-modulus material properties. In the static and dynamic linear caasea, preent reaults are compared with avaliable data.