Abstract
As a new layout of micro air vehicle (MAV), the flapping rotary wing (FRW) has attracted lots of attentions in recent years. In this study, the structural design of FRW aircraft, consisting of driving device, transmission part, flapping rotary mechanism and wings, is investigated. Moreover, this paper discusses the manufacturing and assembly of the aircraft, including the materials and processing methods of each component. The design of FRW aircraft is verified via prototype tests and the influence of wingspan on lift is studied. The experimental results show that the design of the aircraft meets the requirements of endurance and frequency. It is expected this study may be helpful for guidance of structural design of MAV.
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