Structural Design And Optimization Of Flapping-wing's Wing

Micro flapping-wing aerial vehicle (FMAV) is the outcome of the application of the new materials and technologies, and quickly become a hot subject studied both at home and abroad because it has wide prospect in the military and civil field. But there are a great deal of key tochnology issues in overall to design,aerodynamic theory,resource of power, transmission and control system during studies.Synthesizing the current research situation both at home and abroad and developing research to the design of transmission of FMAV in this paper. It aims at structural design of flapping-wing's wing. The main content of the paper as follows.First, made use of the picture that the high speed photographs to gain to study the flight process and the mechanics analysis of the birds and insect, also inquiry into the rush toward of living creature wing flight mechanism, Analyzed to flapping-wing principle of MAV on this foundation. Carry on the mechanics analysis to the plane wing in coordinate system in order to build up for the plane wing structure model and excellent turn to provide the theories foundation.This text commences from two projects of model which are the computer really imitate and Actual model, counteracting the actual model on trial to verify to imitate the true model possibility. Imitate the true model can replace the actual model to get the trial data after pass the verification.Because of using of the model frequently, for reducing the devotion and lifting the high-efficiency, adopting PCL to carry on parameter's turn to set up the mold to the plane wing model, dividing the line the mesh automatically, establishing the material and load automatically. Finally, for easing the weight of the plane wing to carry on the plane wing structure excellent turn. The establishment of design variable and design experiment with equal design table, thus building up response surface, getting the weight, stress, displacement respond to the relation level to the different factor. Response surface of the weight is the target. Response surfaces of the stress and displacement are the restriction. Making use of inheritance arithmetic to carry on optimization, find out plane wing parameters, when restriction of light weight is satisfied.