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SETSCI - Volume 4 (6) (2019)
ISAS WINTER-2019 (ENS) - 4th International Symposium on Innovative Approaches in Engineering and Natural Sciences, Samsun, Turkey, Nov 22, 2019

Rib Spacing Optimization of a Generic UAV Wing to Increase the Aeroelastic Endurance
Tolga Vergün1, Ceyhun Tola2*
1University of Turkish Aeronautical Association, Ankara, Turkey
2University of Turkish Aeronautical Association, Ankara, Turkey
* Corresponding author: ctola@thk.edu.tr
Published Date: 2019-12-22   |   Page (s): 108-111   |    268     7
https://doi.org/10.36287/setsci.4.6.032

ABSTRACT Design and usage of Unmanned Aerial Vehicles (UAV) especially for military purposes has been rapidly increasing in recent years due to their capability to endure long flight durations without needing a crew and due to their low cost compared with the conventional military aircrafts. In order to increase range and flight time endurance of a UAV, aspect ratio of the wing should be increased. This increment leads to aeroelastic problems such as flutter if the cruise velocity is high enough. On the other hand, the flutter velocity of the wing is strictly depending on the ratios of first body bending and torsional frequency values. In order to shift the flutter velocity to higher values, ratio of the torsional frequency to the first body bending frequency of the wing should be increased. Therefore, within the content of this research it is aimed to optimize the wing rib spacing of a generic UAV to maximize the wing frequency ratio. Parametric wing model will be constructed and modal analysis will be performed in Abaqus finite element commercial software environment with the assistance of a Python script and optimization process will be carried by Mode Frontier optimization software. Finally, the optimum rib spacing will be determined for the wing structure.
KEYWORDS Wing, Rib Spacing, Optimization, Flutter, Modal Analysis, Abaqus, Mode Frontier
REFERENCES [1] D. H. Hodges and G. A. Pierce, Introduction to Structural Dynamics and Aeroelasticity, Cambridge University Press, 2002.
[2] S. Guo, D. Li, and Y. Liu, “Multi-objective optimization of a composite wing subject to strength and aeroelastic constraints,” Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, vol. 226, pp. 1095–1106, July. 2011.
[3] W. Zhiqiang, Z. Bocheng,, D. Ziliang, and Y. Chao, “Aeroelastic two-level optimization for preliminary design of wing structures considering robust constraints,” Chinese Journal of Aeronautics, vol. 27, no. 2, pp. 259–265, Nov. 2013.
[4] M. Hasan, “Multidisciplinary Design and Optimization of a Composite Wing Box,” Ph.D. thesis, Middle East Technical University, Ankara, Turkey, Sept. 2003.
[5] C. Tola, and M. Nikbay, “Investigation of the Effect of Thickness, Taper Ratio and Aspect Ratio on Fin Flutter Velocity of a Model Rocket using Response Surface Method,” 7th International Conference on Recent Advances in Space Technologies (RAST), Istanbul, Turkey, June 2015.
[6] Matweb Material Property Data, Aluminum 2024-T351 (2019). [Online]. Available: http://www.matweb.com.


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