Structural Modelling of Tapered Composite Aircraft Wings with Initial Angle of Attack using Thin-Walled Beam

얇은 벽 보를 이용한 초기 받음각이 있는 테이퍼형 복합재료 항공기 날개의 구조 모델링

A structural modelling for study on dynamic characteristics of tapered composite aircraft wings in the form of thin-walled beam is presented. The proposed structural model includes effects of transverse shear flexibility exhibited by the advanced composite materials and warping restraint characterizing elastic anisotropy and induced structural couplings. The complex effects of these factors could have a role in more efficient analysis on those structural models.