Add to ORKGNonlinear equations of motion of symmetrically laminated anisotropic plates are derived accounting for von Karman strains. The effect of transverse shear is included in the formulation and the rotatory inertia effect is ignored. Using a single-mode Galerkin procedure the nonlinear modal equation is obtained. Direct equivalent linearization is employed. The response of acoustic excitation on moderately thick composite panels is studied. Further, the effects of transverse shear on large deflection vibration of laminates under random excitation are studied. Mean-square deflection and mean-square inplane stresses are obtained for some symmetric graphite-epoxy laminates. Using equilibrium equations and the continuity requirements, the mean-squar...
In stochastic structural dynamics, the majority of analyses have dealt with linear structures under ...
The objectives of the project were to investigate numerical methodology for the determination of nar...
Composite panels in aircraft structures are exposed to fluctuating sound pressure originating mostly...
Lightweight aircraft structures exposed to a high intensity noise environment can fatigue prematurel...
A time-domain study of the random response of a laminated plate subjected to combined acoustic and t...
The primary effort of this research project has been focused on the development of analytical method...
A time-domain study of the random response of a laminated plate subjected to combined acoustic and t...
A time-domain study of the random response of a laminated plate subjected to combined acoustic and t...
A time-domain study of the random response of a laminated plate subjected to combined acoustic and t...
The panel structures of flight vehicles at supersonic or hypersonic speeds are subjected to combined...
Within this research project, the following topics were studied: (1) foundation of the refined theor...
In stochastic structural dynamics, the majority of analyses have dealt with linear structures under ...
In stochastic structural dynamics, the majority of analyses have dealt with linear structures under ...
The nonlinear random response of composite plates to the simultaneously applied, combined acoustic/t...
The nonlinear random response of composite plates to the simultaneously applied, combined acoustic/t...
In stochastic structural dynamics, the majority of analyses have dealt with linear structures under ...
The objectives of the project were to investigate numerical methodology for the determination of nar...
Composite panels in aircraft structures are exposed to fluctuating sound pressure originating mostly...
Lightweight aircraft structures exposed to a high intensity noise environment can fatigue prematurel...
A time-domain study of the random response of a laminated plate subjected to combined acoustic and t...
The primary effort of this research project has been focused on the development of analytical method...
A time-domain study of the random response of a laminated plate subjected to combined acoustic and t...
A time-domain study of the random response of a laminated plate subjected to combined acoustic and t...
A time-domain study of the random response of a laminated plate subjected to combined acoustic and t...
The panel structures of flight vehicles at supersonic or hypersonic speeds are subjected to combined...
Within this research project, the following topics were studied: (1) foundation of the refined theor...
In stochastic structural dynamics, the majority of analyses have dealt with linear structures under ...
In stochastic structural dynamics, the majority of analyses have dealt with linear structures under ...
The nonlinear random response of composite plates to the simultaneously applied, combined acoustic/t...
The nonlinear random response of composite plates to the simultaneously applied, combined acoustic/t...
In stochastic structural dynamics, the majority of analyses have dealt with linear structures under ...
The objectives of the project were to investigate numerical methodology for the determination of nar...
Composite panels in aircraft structures are exposed to fluctuating sound pressure originating mostly...