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International Journal of Aerospace Engineering
Volume 2019, Article ID 3684015, 27 pages
Research Article

Detailed Parametric Investigation and Optimization of a Composite Wing with High Aspect Ratio

College of Aerospace Science and Engineering, National University of Defense Technology, Changsha, 410073 Hunan, China

Correspondence should be addressed to Wei Huang; moc.361@1002niardalg

Received 10 March 2019; Revised 4 May 2019; Accepted 4 June 2019; Published 11 July 2019

Academic Editor: Antonio Viviani

Copyright © 2019 Yu-shan Meng et al. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.


The large deformation problem of the wing with high aspect ratio cannot be avoided due to the large bending moment and poor torsional stiffness. The wing design follows the following procedure; firstly, the design indexes of high aspect ratio wing are preliminarily formulated referring to some parameters of the Predator UAV. Then, the aerodynamic analysis of the wing is performed, and the stress cloud diagram is obtained. Next, the finite element model of the wing is designed, and the static analysis is conducted in the ANSYS ACP module, and the unreasonable component size is changed. An appropriate thickness which is 12 mm is selected as the final thickness of the wing. Then, the analysis of laying methods of skin structure is conducted. Finally, the composite structure is proved to reduce the maximum deformation and maximum stress effectively compared with the metal wing.