Integration of new conceptual design for VTOL UAV with multi-level optimization

Abstract

As the combination of FW(Fixed-Wing) and VTOL(Vertical-Taking-Off-and-Landing) UAV (Unmanned Aerial Vehicle), the hybrid drone is more accepted as its multipurpose application. With the aid of CFD method for test and RSM (Response Surface Methodology) for optimization, this article presents new concept of canard wings that were integrated to the fuselage of the UAV. It combines the conventional delta wing with winglet and the canard configuration. Based on the requirements and the limitations of the design, the lift was optimized and distributed respectively to the main wing (90-95%) and to the front wing (5-10%). Multi-level optimization approach using RSM was developed for the optimization. At the first level, we optimize the delta wing, then a second level is applied to evaluate the final design of the canard wing from the previous step. By comparison with the initial design, this concept provides enough lift with less drag in cruise model. Besides, the control surface of the canard wing in the front could replace the tail wing that was used for trimming and dynamic controls which turns the drone into a tailless vehicle which reduce also the weight of the UAV.