Design, Optimization, and Experimental Study of a Foldable Launcher for Small Fixed-Wing UAVs

This article presents a method to design and implement a foldable launcher for a small fixed-wing UAV. The launch process of the UAV was modeled, and the design parameters of the launcher were optimized using a solution process. A sinking height evaluation model based on flight dynamics simulation was also developed to improve the success rate and safety of UAV launch takeoff. By optimizing the relationship between the target takeoff weight range and the optimal launch elevation angle, the desired results can be achieved after launch. The minimum sinking height determines the optimal launch elevation angle for UAVs of different weights when launching. In terms of the workflow and mechanical structure design, the launcher has a remote control launch function and uses rubber bands as its launch power source. It weighs only 4.8 kg and can be carried and quickly deployed by a single person. It can enable a 1.8-kg fixed-wing UAV to obtain an initial breakaway airspeed of approximately 7 m/s. The effectiveness of the launcher design method and sinking height optimization method proposed in this article was verified through comprehensive field flight tests. The proposed method and related results improve the design process and experimental verification method of small fixed-wing UAV launchers.