The Design Research Of Micro Flapping Wing Rotor's Actuation Mechanism And Wing Structure Optimization

With the advanced characteristics of small dimension,light weight,high aerodynamic efficiency and maneuverability,bio-inspired Micro Air Vehicle(MAV)can complete special mission in small space or complex environment where the traditional fixed-wing air vehicle hardly enter.MAV in general has become research hotspot in vehicle design aero as it can be used widely both in military and civil field.This thesis focus on the design and optimization of a new concept of MAV,a bioinspired Flapping Wing Rotor(FWR).First the research was conducted for optimal design of angular magnification of flapping mechanism in particular for piezoelectric actuation schemes.Secondly on the basis of analyzing the aerodynamic characteristic of the Flapping Wing Rotor,the flapping wing structure of the wing is designed by using topology optimization method.The main contents of this thesis are followed by:Investigation is conducted to study the state-of-art of research and the development trend and research status of MAV at home and abroad,and the research hotspot and key technology of Flapping Wing Rotor are analyzed to support the flowing research.The basic theory of topology optimization method is summarized.The modeling methods and optimization process of SIMP method and ICM method are analyzed including numerical instabilities,such as checkerboards,mesh dependencies and the efficient solution.Actual schemes suitable for Flapping Wing Rotor are studied,Angular magnification of flapping mechanism in particular for piezoelectric actual schemes is designed and optimized to meet the demand of FWR,and the design scheme is verified by dynamic simulation.The aerodynamic characteristic of FWR under a given motion state is analyzed based on panel method.The interpolation scheme of topology method and duplicate sensitivity filtering method are part of the investigation,the optimization model of the wing is formulated based on SIMP method,which refers to the minimal compliance and subjects to structural volume,and the initial material distribution of wing structure is obtained.Based on ICM topology method,the local model numerical instability problem is studied,the optimization model of minimum wing structure weight subjected to frequency and displacement constraints is established to obtain an optimal structure layout for the flapping in terms of material distribution of wing.