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Structural optimization of a composite wing
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Date
2006
Author
Sökmen, Özlem
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In this study, the structural optimization of a cruise missile wing is accomplished for the aerodynamic loads for four different flight conditions. The flight conditions correspond to the corner points of the V-n diagram. The structural analysis and optimization is performed using the ANSYS finite element program. In order to construct the flight envelope and to find the pressure distribution in each flight condition, FASTRAN Computational Fluid Dynamics program is used. The structural optimization is performed for two different wing configurations. In the first wing configuration all the structural members are made up of aluminum material. In the second wing configuration, the skin panels are all composite material and the other members are made up of aluminum material. The minimum weight design which satisfies the strength and buckling constraints are found for both wings after the optimization analyses.
Subject Keywords
Aeronautics.
,
Aeronautical Engineering.
URI
http://etd.lib.metu.edu.tr/upload/2/12607715/index.pdf
https://hdl.handle.net/11511/16123
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Graduate School of Natural and Applied Sciences, Thesis
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Ö. Sökmen, “Structural optimization of a composite wing,” M.S. - Master of Science, Middle East Technical University, 2006.
