Research On The Key Technology Of Bionic Flapping Wing Aircraft

The bionic flapping-wing aircraft is a kind of micro aircraft,it acquires the ability to fly by imitating the flapping wing of a flying creature in nature.It has the advantages of small size,light weight,good flexibility,easy to carry and so on.There is considerable potential for development in both military and civilian fields.Therefore,the bionic flapping wing aircraft is one of the hot spots in the field of domestic and foreign aviation in recent years.This paper reviews the historical background and development of bionic flapping wing aircraft.The basic characteristics,application prospects and scientific research value of bionic flapping wing aircraft are discussed in more detail.The key problem of studying Bionic Flapping Wing vehicle is put forward,and the research direction and contents are clarified.First,the design of the prototype is the basis for the analysis of the bionic flapping wing aircraft.This paper is based on the research data of bionics,the overall structure of flapping wing aircraft prototype is designed in detail,and the fuselage size,drive deceleration system and flapping wing structure are designed respectively.Then the kinematic simulation analysis of the mechanism is carried out by MATLAB software.The simulation results show that the mechanism meets the initial set of motion parameters.The reasonableness of the design of the flapping wing mechanism is verified.Secondly,starting from the study of the flight mechanism of natural flying organisms,a coordinate system for the bionic flapping wing aircraft is set up during flight,and deduced the transformation relationship between them.The aerodynamic analysis of the prototype model is carried out.The aerodynamic forces and moments of flapping wing aircraft during horizontal flight are calculated,and derived the kinematics and dynamics equations of the whole aircraft,and established the dynamic model of the whole machine.The MATLAB tool is used to simulate the model and verify the feasibility of the prototype’s flight.Finally,an attitude control system of flapping wing aircraft made up of MEMS components is designed for the prototype.Selecting each module and designing the control circuit.In order to improve the observation accuracy of flying attitude of flapping-wing aircraft,in this paper,we propose a method of integrating the observation data of gyroscope and accelerometer based on kalman filter,which can be used to compensate the externalacceleration.Through experiment and simulation analysis,it is proved that the proposed kalman filter algorithm can greatly reduce the measurement deviation and can reduce the noise interference and improve the accuracy of attitude measurement.On the one hand this article enriches the connotation of the multi-degree-of-freedom flapping mechanism and provides a reference for follow-up flapping aircraft research.On the other hand,an attitude calculation method with higher observation accuracy is proposed,which paves the way for improving the control system of flapping wing aircraft.