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Structural design and analysis of the mission adaptive wings of an unmanned aerial vehicle
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index.pdf
Date
2010
Author
Ünlüsoy, Levent
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In this study, the structural design and analysis of a wing having mission-adaptive control surfaces were conducted. The wing structure was designed in order to withstand a maximum aerodynamic loading of 5 g due to maneuver. The structural model of the wing was developed by using MSC/PATRAN package program and that structural model was analyzed by using MSC/NASTRAN package program. The designed wing was then manufactured by Turkish Aerospace Industries Inc. (TUSAŞ-TAI). The finite element analysis results were verified by conducting ground vibration tests on the manufactured wing. The comparative results were used to tune the finite element model and the results obtained showed that the modeling was very successful.
Subject Keywords
Aerospace engineering.
,
Finite Element Analysis.
URI
http://etd.lib.metu.edu.tr/upload/12611515/index.pdf
https://hdl.handle.net/11511/19160
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Graduate School of Natural and Applied Sciences, Thesis
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L. Ünlüsoy, “Structural design and analysis of the mission adaptive wings of an unmanned aerial vehicle,” M.S. - Master of Science, Middle East Technical University, 2010.
