The Structural Analysis of Composite Wing by Using Numerical Technique

Abstract

The present work deals with the static and dynamic analysis of composite swept aircraft wings using an equivalent plate approach. The work's contribution is a new higher-order equivalent plate model which incorporates transverse shear deformation and satisfies the shear stress condition. The structural response of wings having different parameters is calculated and compared to that predicted by the several composite finite element method. The proposed method significantly improves the accuracy of thick wing results, and saves much of the computation time.