Numerical Simulation Research And Platform Design Of Flapping Wing Aircraft

Flapping wing flight is the result of natural selection and has great potential in the application of micro-small aircraft.This paper aims to construct a virtual prototype platform of a universal flapping-wing aircraft.The virtual prototype platform is a virtual environment for analyzing and simulating aircraft performance,and it plays an important role in the development of aircraft.It plays an important role in the aircraft development process:shorten the development cycle of flapping-wing aircraft,and optimize the dynamics and aerodynamic performance of the flapping wing aircraft,Preliminary verification of the effectiveness of the aircraft control algorithm.Based on the above requirements,the work done in this article includes:Based on a high-efficiency flapping-wing aircraft driving mechanism designed in the early stage of the laboratory-a single driving source with a wing flapping and torsion structure,a virtual prototype model was built in ADAMS,which was used as an example of a general virtual prototype platform for simulation analysis;establishment;The communication between Python software and ADAMS software is used to send control instructions,including:basic operating parameter setting,flapping-wing aircraft motion parameter setting,flapping-wing aircraft motion information acquisition and other instruction operations;based on ADAMS spline function,implementation The aerodynamic forces of the wing and tail of the virtual prototype are loaded in real time to simulate the movement of the prototype in the flow fieldBased on the wing motion data of the virtual prototype in ADAMS,the motion mode modeling was completed,including:wing torsion angle,flap angle and flap motion;two wing aerodynamic calculation models were established,one was based on the UAM model,and It takes a long time to accurately calculate the aerodynamic force of the prototype during its motion.The other is based on Theodorsen and Garrick theory to quickly calculate the aerodynamic force of the prototype;the tail aerodynamic force calculation model and the inertial force calculation model are established,which is a vortex structure.The analysis of evolution and aerodynamic changes laid the theoretical foundation.The structure evolution of the leading edge vortex and trailing edge vortex on the wing surface of the flapping-wing aircraft is analyzed in the stationary and flying states.In the static state,the vortices are distributed disorderly on the upper and lower surfaces of the wing,while in the flying state,the vortices are distributed in order and regularity on the upper and lower surfaces of the wing.Fly for multiple cycles at a fixed speed,observe the evolution of the vortex structure,showing periodic characteristics,and the distance between two adjacent shedding vortices is the same.In the same cycle,the vortex structure evolution and corresponding aerodynamic changes in the static state and flight state of the same part of the aircraft are analyzed.The aerodynamic force and the vortex distribution show consistency.At the same time,the aerodynamic changes and the vortex structure evolution are compared.(9 meters per second,10 Hz),when the aircraft is stationary,the average lift applied to the wings is-0.969 Newtons,when the aircraft is stationary,the thrust applied to the wings is 0.2501 Newtons,and the average lift applied to the wings during flight is 4.3842 Newtons.The thrust received is 1.893 Newtons,and the aerodynamic force exhibited in the flight state is significantly greater than the aerodynamic force in the stationary state,and the vortex evolves faster when the aircraft is flying.Based on the problem that the aircraft is affected by periodic inertial forces during the flight,which disturbs the aircraft's normal attitude and makes the aircraft unable to perform stable control,the aircraft attitude disturbance rate method is designed to be applied to the virtual prototype platform,laying a foundation for the realization of the prototype closed-loop simulation basis.Based on the motion signal capture system and the airborne inertial measurement unit,the pitch attitude data is obtained for verification.The results show that the method designed in this paper can effectively filter the attitude disturbance caused by the periodic inertial force.