Free Vibrations of Aircraft Wings Modeled as Thin-walled Composite Beam

This paper presents an analytical study of an aircraft wing modeled as thin-walled composite beam. For a reliable prediction of wing free vibration behavior, a number of important non-classical effects such as restrained warping and transverse shear are considered. The solution methodology is based on Extended Galerkin’s Method. Free vibration results are obtained for a thin-walled single-call composite beam. The predictions by present method are compared with other analytical as well as numerical results in the open literature.

کلیدواژه ها:

Thin-walled ، composite beams ، Free Vibration