Design and analysis of inflatable wing of rapid deployment UAV

被引：0
作者：
Liao J. [1 ]
Wang N. [1 ]
Luo S. [1 ]
Li J. [1 ]
Chen Z. [1 ]
Ling L. [1 ]
机构：
[1] School of Aeronautics and Astronautics, Central South University, Changsha
来源：
Zhongnan Daxue Xuebao (Ziran Kexue Ban)/Journal of Central South University (Science and Technology) | 2022年 / 53卷 / 04期
关键词：
Aerodynamic load; Inflatable wing; Internal and external pressure difference; Optimization design; Skin stress; Unmanned aerial vehicle;
D O I：
10.11817/j.issn.1672-7207.2022.04.009
中图分类号：
学科分类号：
摘要：
In order to complete the design and analysis of the inflatable wing of rapid deployment unmanned aerial vehicle(UAV), considering the influence of airfoil overlap degree, skin mass and processing technology on the design of the inflatable wing, the inflatable wing was optimized. Based on the flexible membrane theory, the equivalent beam model of inflatable cantilever wing was established, and a method for calculating and analyzing the skin stress of inflatable wing was proposed. The skin stress distribution under different internal and external pressure differences and aerodynamic loads was analysised. The influence of the wing charging pressure difference on the critical aerodynamic load was analyzed. The results show that the tangential stress extreme value of skin appears in the middle and trailing edge air chamber of the wing, while the spanwise stress extreme value appears at the root of the upper and lower wing surface of the wing, which provides reference for the optimization design and strength design of the inflatable wing. ©2022, Central South University Press. All right reserved.
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页码：1241 / 1249
页数：8
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