In this study, effective theoretical and computational (the finite element method) procedures are introduced and used to characterize the dynamic behavior of beams and of cylindrical panels with circular cross-section; both structures have the single delamination between laminate layers.
This paper investigates the large amplitude vibration behavior of nanocomposite cylindrical panels resting on elastic foundations in thermal environments.
The results reveal that the nanotube volume fraction, foundation stiffness, and the panel curvature ratio have a significant effect on the thermal postbuckling behavior of CNTRC cylindrical panels.
This paper presents an investigation on the thermal postbuckling behavior of nanocomposite cylindrical panels resting on elastic foundations and subjected to a uniform temperature rise.
Numerical results reveal that the CNT volume fraction, temperature rise, foundation stiffness, and the panel geometric parameters have a significant effect on the buckling load and postbuckling behavior of CNTRC cylindrical panels.
The results reveal that the temperature dependency and temperature rise have a significant effect on the buckling load and postbuckling behavior of piezolaminated cylindrical panels, but they only have a very small effect on the imperfection sensitivity of the thin panels.
Zhao et al. (2003) studied the vibration behavior of composite cylindrical panels using the mesh-free approach.
The governing partial differential equations describing the buckling and postbuckling behavior of cylindrical sandwich panels are derived using the principle of minimum total potential energy.
The nonlinear dynamic buckling of cylindrical panel acted on by axial loading is considered.
Differential quadrature method is being utilized and natural frequencies of cylindrical panel are obtained.
