The invention discloses a ducted multi-rotor unmanned aerial vehicle (UAV) and relates to the technical field of UAVs. The invention aims to solve the problems of low mechanical efficiency, large operating noise and complicated manipulation of the UAVs in the prior art. The ducted multi-rotor UAV comprises a hemispherical cargo compartment and a hemispherical power equipment compartment which aredistributed vertically and a dish airfoil surface arranged around the hemispherical cargo compartment and the hemispherical power equipment compartment, wherein a plurality of vertically arranged propeller ducted holes are evenly distributed along the circumferential direction of the dish airfoil surface; a corresponding ducted fan propeller is arranged in each propeller ducted hole; a landing gear is arranged under the hemispherical power equipment compartment; thrust turbofans are fixed to the landing gear; one end of each propeller blade of the corresponding ducted fan propeller is seamlessly fixed to a corresponding propeller blade hub and the other end of each propeller blade is seamlessly fixed to a corresponding propeller reinforcing ring; the inner sides of turbofan blades of the thrust turbofans are seamlessly connected to the outer side walls of blade hubs; the outer sides of the turbofan blades of the thrust turbofans are seamlessly connected to the inner side walls of ducted shells; and each turbofan blade spirally extends from one end to the other end along the axial direction of the corresponding blade hub.