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Two-level composite wing structural optimization using response surfaces
Date
2000-10-01
Author
Liu, B
Haftka, RT
Akgun, MA
Metadata
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Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License
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A two-level optimization procedure for composite wing design subject to strength and buckling constraints is presented. At wing-level design, continuous optimization of ply thicknesses with orientations of 0 degrees, 90 degrees, and +/-45 degrees is performed to minimize weight. At panel level, the number of plies of each orientation (rounded to integers) and inplane loads are specified, and a permutation genetic algorithm is used to optimize the stacking sequence in order to maximize the buckling load. The process is started by performing a large number of panel genetic optimizations for a range of loads and numbers of plies of each orientation. Next, a cubic polynomial response surface is fitted to the optimum buckling load as a function of the loads and numbers of plies of each orientation. The resulting response surface is used for the wing-level optimization. Rounding and manual adjustment are used to obtain the final design. The procedure is demonstrated using an example of a simple wing box design.
Subject Keywords
Control and Systems Engineering
,
Software
,
Control and Optimization
,
Computer Graphics and Computer-Aided Design
,
Computer Science Applications
URI
https://hdl.handle.net/11511/67289
Journal
STRUCTURAL AND MULTIDISCIPLINARY OPTIMIZATION
DOI
https://doi.org/10.1007/s001580050140
Collections
Department of Aerospace Engineering, Article
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B. Liu, R. Haftka, and M. Akgun, “Two-level composite wing structural optimization using response surfaces,”
STRUCTURAL AND MULTIDISCIPLINARY OPTIMIZATION
, pp. 87–96, 2000, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/67289.