Analysis and Research on Wing-Fuselage Connection Design of Small Combined UAV

Abstract

In this paper, the analysis and research is conducted on a wing-fuselage connection part using a small combined unmanned aerial vehicle (UAV). The work is based on the characteristics of flexible disassembly in order to be easy to carry and transport for the combined type unmanned aerial vehicle (UAV). The combined wing-fuselage structure is designed with the structure design theory. Analyzing each project from the internal stress and strain situation, mass attributes and other aspects based on result from FEM sofware. With the comprehensive comparisons of the characteristics of each project in the consideration of satisfying the strength and stiffness criteria it provides a reference for the design of the combined type UAV wing-fuselage connecting structure.