Ramman, A.(PhD)Masresha, Muluken2018-07-062023-11-182018-07-062023-11-182007-11http://etd.aau.edu.et/handle/12345678/6982The thesis deals with bending-torsion decoupling in eigen modes of monocoque laminated composite aircraft (subsonic and supersonic) wing using commercial software ANSYS. Theoretical background, mathematical formulation and finite element solution for a laminated composite shell structure are presented in this study. A monocoque aircraft wing is made of laminated composite with fiber angles in each ply aligned in different direction. Various airfoil thickness and ply angles were considered to study the effect of bending-torsion decoupling. Results obtained are presented and parametric studies are made to show the effect of airfoil thickness variation and ply orientation. The effect of location of shear center relative to the center of gravity is also studied and the results are presented.enApplied Mechanics StreamThesis