分布式电推进无人机动力-气动特性和失速特性快速评估方法

A distributed electric propulsion (DEP) aircraft can achieve its ultra-short takeoff and landing distance by utilizing the coupling effect of distributed propellers and wing surface to increase lift. By utilizing the slipstream generated by distributed propellers, the UAV in the case study is able to maintain controllable flight at a 30 degree angle of attack, thus achieving the ultra-short take-off and landing distance. At the present conceptual design stage, the rapid evaluation method for distributed propulsion and aerodynamic characteristics and stall characteristics is not available. This article proposes a VLM-ADT (Vortex Lattice Method- Actuator Disk Theory)method based on high-fidelity and two-dimensional airfoil data correction to achieve the rapid evaluation of the distributed propulsion and aerodynamic characteristics and stall characteristics of a DEP UAV. Numerical results show that the method proposed in this paper can effectively calculate the distributed propulsion and aerodynamic characteristics of the DEP UAV and predict its stall characteristics, with the calculation time being within seconds. The method considers both calculation speed and accuracy for the configuration design and aerodynamic characteristic evaluation of a DEP aircraft in its conceptual design stage.