Research Article

Optimal design of Vertical-Taking-Off-and-Landing UAV wing using multilevel approach

¹ National and High School of Electricity and Mechanic (ENSEM), Hassan II University, Casablanca, Morocco
² Research Foundation for Development and Innovation in Science and Engineering (FRDISI), Casablanca, Morocco
³ CNRS/UMR 5060, Université de Technologie de Belfort-Montbéliard, France, France
⁴ Centre Borelli, CMLA, ENS Cachan, CNRS, Université Paris-Saclay, 94235 Cachan, France
⁵ Institute of Industry Technology, Guangzhou & Chinese Academy of Sciences (IIT, GZ&CAS), Guangzhou, PR China
⁶ INRAE, Avignon University, UMR EMMAH, F-84000, Avignon, France

^* e-mail: yuehao20160719@gmail.com

Received: 31 October 2020
Accepted: 11 November 2020

Abstract

In order to overcome the propre disadvantages of FW(Fixed-Wing) and VTOL(Vertical-Taking-Off-and-Landing) UAV (Unmanned Aerial Vehicle) and extend its application, the hybrid drone is invested more in recent years by researchers and several classifications are developed on the part of dual system. In this article, an innovative hybrid UAV is raised and studied by introducing the canard configuration that is coupled with conventional delta wing as well as winglet structure. Profited by Computational Fluid Dynamics (CFD) and Response Surface Method (RSM), a multilevel optimization approach is practically presented and concerned in terms of cruise flight mode: adopted by an experienced-based distribution strategy, the total lift object is respectively assigned into the delta wing (90–95%) and canard wing(5–10%) which is applied into a two-step optimization: the first optimization problem is solved only with the parameters concerned with delta wing afterwards the second optimization is successively concluded to develop the canard configuration considering the optimized delta wing conception. Above all, the optimal conceptual design of the delta and canard wing is realized by achieving the lift goal with less drag performance in cruise mode.