Research on finite element nodal load application method for civil aircraft wing structures

Abstract

Finite element simulation is a crucial tool for strength analysis of civil aircraft wing structures, imposing stringent requirements on accurate nodal load application. Wing surface loads are typically provided as spatial curved surface pressure distributions (CP) at aerodynamic grid points, which cannot be directly applied to finite element elements in the form of pressure for rapid internal force simulation analysis. This paper presents an efficient load processing methodology and workflow. First, the CP distribution over the wing surface is integrated to obtain small-block point loads, which are then corrected to be consistent with the total station loads. Subsequently, following the “multi-point arrangement” principle, the spatial small-block point loads are distributed to finite element nodes (considering various compound deflection states of the wing structure during flight), generating a nodal load array. This array is then applied to the finite element model for internal force analysis and subsequent strength evaluation. The analysis results have been validated through static tests.