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Please use this identifier to cite or link to this item: http://hdl.handle.net/123456789/1540

Title: Bending-Torsion Decoupling In Eigen Mode Of Subsonic and Supersonic Composite Monocoque Aircraft wing
Authors: Muluken, Masresha
Advisors: Dr.A.Ramman
Copyright: 2007
Date Added: 21-Oct-2008
Publisher: Addis Ababa University
Abstract: The 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.
Description: A thesis submitted to the School of Graduate Studies of Addis Ababa University in partial fulfillment of the requirements for the Degree of Masters of Science in Mechanical Engineering (Applied Mechanics Stream)
URI: http://hdl.handle.net/123456789/1540
Appears in:Thesis - Mechanical Engineering

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