Research On The Structure And Aerodynamic Characteristics Of A VTOL Fixed-wing Aerial Robot

VTOL fixed-wing aerial robot can achieve vertical take-off and landing in a complex environment,with the ability of hovering in the air and fast fly,and the application prospect in both military and civilian fields is very broad.Therefore,it is very important to research this kind of aerial robot.This paper is based on the domestic and international researches,design the structure of a VTOL fixed-wing aerial robot,research and optimize its aerodynamic characteristics.Firstly,we determine the airfoil and the form of main structure layout through the analysis of typical airfoil and structural layout.Secondly,preliminarily design the structural layout of a VTOL fixed-wing aerial robot,including blended wing body,winglets,landing gear and vector tilting power device.Thirdly,we use FLUENT to make a simulation analysis of the of wing model,use Control variables method to research the influence on the aerodynamic characteristics,such as wing twist angle,wing knife,winglet,etc.and optimize the structure of the wing.Finally,we analyze the aerodynamic characteristics of the aircraft.In addition,we applied sliding mesh method to study the effect of the propeller slipstream on the aerodynamic characteristics of the aircraft.At the same time,use CFD and CSD coupling method to research the static aeroelastics of aircraft,explore the influence of the elastic deformation of the aerodynamic characteristics.Comprehensive studies have shown that after optimizing its wing the lift coefficient is improved,the drag coefficient is reduced and the rolling stability is increased.Propeller slipstream improves the lift characteristics of the aircraft,but it also increases the resistance.Elastic deformation makes the lift coefficient decrease,the drag coefficient increase and the aerodynamic characteristics of the whole decline,but the degree of deformation will not lead to structural damage,on the whole,the aerodynamic characteristics perform well after optimization,which meets the design requirement properly.The maximum deformation displacement and stress distribution can be used to guide the whole internal structure of the re-optimization and the selection of new materials,to reduce the elastic deformation,and to further improve the aerodynamic performance of the aircraft.