Structural strength analysis of unmanned aircraft body based on finite element method

This paper introduces the general process and specific methods of using finite element analysis to analyze the structural strength of unmanned aerial vehicle (UAV) fuselage structure, and according to the loading situation of UAV in air flight, it carries out static analysis and modal analysis on the wing structure of UAV, and obtains the stress-strain cloud diagrams of the structural components of the wing, which provides a basis for the optimization of structural analysis and has certain reference value for the use of the finite element method to carry out strength analysis and optimization of the fuselage structure of the UAV. It has certain reference value for the strength analysis and optimization of UAV fuselage structure using finite element method.