Research On Technologies Of High-speed Ducted-rotor UAV Preliminary Design

Ducted rotor study has become a hot spot in recent years. Especially technologies of ductedrotor UAV are developing rapidly. However, most ducted rotor UAV of this kind flies in a lowspeed because of its special aerodynamic configuration. Based on analysis on technicalcharacteristics of various types of ducted rotor aircraft, this paper presents a high-speed ductedrotor unmanned aircraft concept. Preliminary design technology of high-speed ducted rotor UAVis researched in this thesis. It’s an UAV which is fixed with wings on the basis of ducted rotorUAV.Firstly, from the standpoint of preliminary design, research and analysis are made onaerodynamic characteristics of ducted single rotor and ducted coaxial rotor according to domesticand foreign research results in this thesis. Formulas are derived to calculate its aerodynamiccharacteristics, and its verification is carried out by test results. Secondly, based on researchesabove, the configuration and general parameters are chosen according to design requirements ofhigh-speed ducted rotor UAV, whose flight performance is calculated also. Then, flight dynamicsmodel of high-speed ducted rotor UAV is established based on trim calculation of regularsingle-rotor helicopter with tail rotor. Trim calculation and analysis are carried out for high-speedducted rotor UAV. Finally, some initiative design has been investigated which includes fuselageprofile, landing system, propulsion system and its control system, the whole structureconfiguration is arranged.Preliminary design scheme of ducted rotor unmanned aircraft is completed. Someconclusions of this paper have been applied to a ducted rotor unmanned aircraft. The results verifythe feasibility and rationality of the preliminary design scheme.