Six-Wheel Trolley Type Landing Gear Ground Slip-Run Load Analysis Considering Fuselage Flexibility

Abstract

This paper investigates the effect of fuselage flexibility on the landing gear ground skidding load in the landing gear load design of a large unmanned aerial vehicle (UAV). Since the traditional load design method often assumes that the aircraft fuselage is a rigid body, the influence of fuselage flexibility is neglected. In this paper, on the basis of applying the basic principles of dynamics, a six-wheeled trolley landing gear and the whole aircraft dynamics model are established; the fuselage is flexibly processed, and the influence of the fuselage flexibility on the landing gear ground loads is analysed. The results show that after considering the fuselage flexibility, the acceleration at the centre of gravity of the fuselage decreased by 35%, and the vertical load of the main landing gear decreased by 7.4%. This indicates that the flexible fuselage deformation absorbs energy and helps to attenuate the fuselage vibration. Therefore, in the design process of UAV landing gear, the maximum value of work absorbed by the buffer system composed of flexible fuselage and landing gear system should be the design goal.