سال انتشار: ۱۳۸۸

محل انتشار: هشتمین همایش انجمن هوافضای ایران

تعداد صفحات: ۴

نویسنده(ها):

P. Khaneh Masjedi – Graduate Student, Department of Aerospace Engineering and Center of Excellence in Computational Aerospace Engineering, Amirkabir University of Technology, Tehran, Iran
H.R. Ovesy – Associate Professor, Department of Aerospace Engineering and Center of Excellence in Computational Aerospace Engineering, Amirkabir University of Technology, Tehran, Iran (corresponding author)

چکیده:

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.