Strength Analysis of Shock Strut of Aircraft Landing Gear Based on ANSYS

The aircraft gear is an essential load-bearing component when the aircraft is safely landed, which affects the landing safety of the entire aircraft. The finite element simulation technology is used to analyze the static strength of the aircraft’s landing gear. It is of great engineering significance to reduce the structural mass and improve the aircraft’s performance. Using ANSYS, a finite element analysis software, to accurately carry out the finite element simulation analysis of landing gear mechanics is an effective means to comprehensively evaluate the mechanical properties of the landing gear structure, which can systematically study the bearing capacity of the landing gear structure.This paper firstly introduces the actual geometric structure of the aircraft landing gear and defines its boundary conditions and loads, determines the analysis of the critical structure of the shock absorber strut, selects the static problem method as the modeling target; builds the landing gear based on SOLIDWORKS Geometric model. The model is simplified while ensuring authenticity; Solid187 is selected as the element type to develop finite element mesh, which provides the authenticity of the simulation, and Ti-6Al-4V is defined as the material property of the landing gear; The above analysis correctly sets the boundary conditions, load conditions and part contracts in the finite element model, solved using SPARSE as the solver.Through the observation of the result, it is found that the maximum deformation occurs at the connection between the inner and outer cylinders of the piston rod, and the fuselage is 730.83MPa. By comparing the strength of Ti-6Al-4V, the strength of the landing gear is safe under this working condition, and the simulation results can be used for subsequent results optimization and other processing.