Showing papers by "M. Ganapathi published in 2018"
TL;DR: In this paper, the free vibration characteristics of variable stiffness laminated composite shells are numerically studied using a higher-order accurate theory, and it is inferred that the fiber orientation within the lamina changes continuously leading to spatial variation of stiffness of the resulting laminate.
32 citations
TL;DR: In this article, elastic stability analysis of curved nanobeams is investigated using the differential constitutive law consequent to Eringen's strain-driven integral model coupled with a higher-order shear deformation theory accounting for through thickness stretching effect.
31 citations
TL;DR: In this article, the effects of various structural and material parameters such as thickness ratio, beam length, rise of the curved beam, boundary conditions, and size-dependent or nonlocal parameter are brought out on the vibration behaviors of curved nanobeams.
30 citations
TL;DR: In this paper, the nonlinear free flexural vibration of thick curvilinear fiber composite laminates is investigated using a higher-order shear flexible eight-noded quadrilateral element.
Abstract: In the present work, the nonlinear free flexural vibration of thick curvilinear fiber composite laminates is investigated using a higher-order shear flexible eight-noded quadrilateral element devel...
27 citations
TL;DR: In this paper, the authors focus on the problem of parametrically excited doubly curved sandwich shells with carbon nanotubes reinforced composite (CNTRC) facesheets subjected to in-plane periodic load.
Abstract: This paper focuses on the problem of parametrically excited doubly curved sandwich shells with carbon nanotubes reinforced composite (CNTRC) facesheets subjected to in-plane periodic load. The panels consist of cylindrical and spherical shells modeled using QUAD-8 element which was developed using higher-order shear flexible theory. The formulation considers the secondary effects such as the influence of in-plane and rotary inertia terms, and the aerodynamic pressure when the panel is exposed to air flow. The governing equations developed are solved based on eigenvalue approach. The limits of the principal instability zone predicted here are graphically represented using excitation frequencies against the load amplitudes. The results of this study are tested against the available solutions in the literature. A detailed study considering various design parameters including structural theories on the dynamic instability boundaries and its associated origin of instability regions is conducted. These paramete...
8 citations