Research On The Design Of Ducted Blades Of A Rotorcraft

In recent years,single-person aircraft and flying vehicle have become a hot-spot in military and civilian research field at home and abroad.Single-person aircraft of various configurations have emerged,but these kinds of single-person aircraft hold some disadvantages,such as large size,difficult-to-control,and high cost.The aircraft with lift/thrust system of ducted rotor/fan has the characteristics of high aerodynamic efficiency,low rotor noise,high safety and compact structure,which achieves vertical takeoff and landing while showing good hovering performance.Therefore,this paper refers to several aircraft at home and abroad,and the advantages and disadvantages of various schemes are compared.A new type of electric single-person ducted aircraft according to the technical requirements is designed,and the overall layout of the aircraft is also carried out,which lays the foundations for aerodynamic and dynamic design of the lift system.Firstly,using the numerical simulation method established in this paper,the aerodynamic and flow field characteristics of the ducted single/double rotor and isolated single/double rotor are compared and analyzed,and the key design of the aerodynamic shape of the rotor blade with the ducted action is carried out.This paper is focused on the calculation and comparison of the influence of design parameters on the aerodynamic performance of the ducted rotor hovering state.Secondly,according to the analysis results of the aerodynamic performance of the above-mentioned lift system,the form and layout scheme of the lift system are determined,and the preliminary selection and overall layout design of the overall parameters of the new ducted aircraft are completed.Based on the overall layout,the preliminary parameters of the aerodynamic shape of the ducted rotor system are completed by the momentum-blade-element theory.Then,based on CATIA parametric modeling,CFD aerodynamic calculation model and optimization algorithm,the aerodynamic shape optimization integrated platform of the blade is established by arrogate model,and the CST airfoil parameterization method is completed based on the blade optimization results to carry out the optimization design of the blade airfoil.Finally,on the basis of the aerodynamic shape determination of the blade,the profile design,profile characteristics calculation,dynamics analysis and strength check of the composite blade are completed.