Structural Design Of A Wing And Rotor Wing Variable Angle Vehicle

In order to make up for the shortcomings of helicopters and fixed-wing aircraft,many scientists have dreamed of inventing a new type of aircraft that can both take off and land vertically and cruise at high speed.After three years of exploration and practice,three main technical approaches have been formed: composite,rotor/wing conversion and tilt rotor/wing,and tilt rotor aircraft have advantages such as high forward speed and flexible maneuverability.It is widely used,but its rotor-washing airflow has a greater impact on the wing.It reduces the efficiency of helicopter helicopter mode.The impact of rotor-downwashing of a winged aircraft rotor on the wing is small,but its maneuverability is poor and the safety factor is poor.Lower.Combining the advantages of four-rotorcraft and fixed-wing aircraft,this paper designs a wing-and-rotor-connected variable-angle aircraft.The new aircraft has vertical take-off and landing,high-speed cruising,flexible maneuverability,high safety factor,and helicopters.The advantages of high efficiency of the model,the specific design is as follows:Firstly,the design objectives of the design aircraft are presented through the research and analysis of four-rotorcrafts,fixed-wing aircrafts,compound aircrafts,rotor/wing conversion vehicles,and tilt rotor/wing aircrafts.On the basis of meeting the overall objectives,this paper proposes different configurations and tilting plans for the aircraft designed in this paper.Through analysis and comparison,the aircraft configuration plan and tilting plan are determined,and the aerodynamic layout and fixed wing of the aircraft four-rotor model are determined.The overall design of the model fuselage/wings and the overall structure of the wing are preliminary designed.Second,on the basis of the overall design of the wing-rotor-wing variable-angle aircraft,the main parameters of the four-rotor model of the aircraft are designed,including:take-off weight,power ratio,and motor propeller model;The parameters are designed to include: maximum lift coefficient,aspect ratio,root tip ratio,extension,wing area,wing airfoil,maximum lift/drag ratio,cruising speed,and fuselage slenderness ratio,fuselage length and width,etc..Then,the CATIA software is used to design the aircraft wing and tilting mechanism in detail,and the force analysis of the wing structure is performed.The ANSYS Workbench isused to analyze the static state of the wing structure of the aircraft in different states to verify that the wing structure meets the strength requirements.Finally,the numerical simulation of computational fluid dynamics(CFD)is used to analyze the aerodynamic performance of the wing-and-wing-wing variable-angle aircraft designed in this paper,which mainly includes: the lift of the rotor at different speeds;the rotor/airfoil in the quadrotor mode.Airframe aerodynamic interference;lift coefficient,drag coefficient,and pitching moment coefficient for different flight states in fixed wing mode.This paper verifies the rationality of the design of the wing-and-wing-connected variable-angle aircraft.