Design and analysis of retractable structure of new quadrotor landing gear

Abstract

Abstract With the development of equipment level, the requirements for the compact-ness and light-weight of UAV become more and more stringent. In order to solve the problems such as the weight and large volume of the landing gear of the existing four-rotor aircraft, this paper developed a new four-rotor unmanned helicopter landing gear retractable structure based on the existing landing gear. The release process and retractation of retractable structure of the new landing gear are described, and its motion form and attitude are introduced in detail. In this paper, the stress of high strength flexible rope during landing gear releasing and re-tracting is analyzed, and the mathematical model is established. Adams software is used to simulate and analyze the force state of the landing gear leg when the rope is pulling at a constant speed. The results of the dynamic simulation and mathematical model are consistent, that is, the maximum force when retracted to 90° is about 30N (for a single wing). Finally, the finite element simulation software Ansys Workbench was used to carry out strength checking and deformation analysis of the wing, and the rationality of the designed me-chanical structure was verified. The research results of this paper provide a certain basis for the development of landing gear of four-rotor unmanned helicopter.