Study On Structure Design And Aerodynamic Characteristics Of Flapping Wing System Of Aircraft Learn From The Allomyrina Dichotoma

Micro flapping wing aircraft is a novel aircraft learn from the movement mode of flying insects in nature.It has the advantages of small size,light weight,good concealability and low power consumption.It can carry certain mission loads for slow autonomous flight,adapt to complex working environment,and has broad application prospects in military and civilian fields.Based on Xflow software,this paper analyzed the aerodynamic characteristics of different motion modes of the aircraft learn from the Allomyrina dichotoma as the bionic object.The kinematic and dynamic simulation analysis was carried out and the vibration problem of flexible wing was studied.The specific research contents are as follows:The motion design of the flapping wing system of aircraft learn from the Allomyrina dichotoma was carried out by referring to the motion mode of the Allomyrina dichotoma.The high lift aerodynamic mechanism of flying insects was analyzed,and the computational fluid dynamics method of insect flight simulation was analyzed.The vibration theory of flexible wings was introduced,and the equivalent model of simplified flexible wings was created.The wing of the flapping wing aircraft learn from the Allomyrina dichotomat was designed.Xflow software was used to analyze the aerodynamic performance of different wing chord sections and wing surface shapes,and a suitable wing model was determined.Different motion modes,such as fuselage Angle,flutter amplitude,incoming flow velocity,flutter frequency,torsion amplitude and whether there was active torsional motion,were compared and analyzed to explore the aerodynamic characteristics of the flapping wing aircraft learn from the Allomyrina dichotomat.The flapping wing system which can realize the coupling motion of flapping and torsional motion was designed.By referring to the flight motion parameters of the bionic object,it was simplified as the target flapping and torsional motion function,and the structural parameters of the flapping and torsional bar were optimized to approximate the target flapping and torsional motion function.ADAMS software was used to simulate the kinematics and dynamics of the flapping and torsional mechanism,to determine that the structure movement can achieve the design objectives,to determine the force at each hinge,to provide reference for the structure strength design.According to the flexible wing vibration analysis method,the flexible wing was simplified and the Hamilton principle was used to establish the flexible wing dynamics model.To solve the high order partial differential equation,and the MATLAB software was used to calculate the vibration results of different motion modes and materials.Based on the boundary control method,the vibration control of flexible wing subjected to distributed disturbance was designed.