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|Title: ||Bending-Torsion Decoupling In Eigen Mode Of Subsonic and Supersonic Composite Monocoque Aircraft wing|
|Authors: ||Muluken, Masresha|
|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
(Applied Mechanics Stream)|
|Appears in:||Thesis - Mechanical Engineering|
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