涵道共轴多旋翼无人机设计研究

Research on the Design of a Ducted Coxial Rotor UAV

多旋翼无人机凭借其较高的稳定性及操纵性,应用领域越来越广泛,但在广泛的应用中,也暴露出一些问题,螺旋桨无法改变桨距,使得其气动效率低于直升机旋翼,又加上多个螺旋桨相距较近,会产生较为严重的气动干扰,进一步降低了它的气动效率。本文设计了一种涵道共轴多旋翼无人机系统,通过固定涡系理论,验证了其可行性,与当前的多旋翼无人机相比,具有一定的气动优势,可进一步进行相关研究。

Multi rotor UAV has been used more and more widely due to its high stability and maneuverability.However,some problems have also been exposed in the extensive application.The propeller cannot change the pitch,which makes its aerodynamic efficiency lower than that of the helicopter rotor.In addition,multiple propellers are close to each other,which will produce more serious aerodynamic interference,further reducing its aerodynamic efficiency.In this paper,a ducted coaxial multi rotor UAV system is designed,and its feasibility is verified by the fixed vortex system theory.Compared with the current multi rotor UAV,it has certain aerodynamic advantages,which can be further studied.