Method of information technology for calculating the nodal loads in stress strain state analysis of the transport category aircraft wing model

The article describes the method of the information technology for calculating nodal loads when analyzing the stress-strain state of a finite element model of a transport category aircraft wing. The proposed method makes it possible to calculate the values of nodal loads that simulate distributed aerodynamic loads acting on an aircraft wing, based on the integral values of forces and moments calculated for several cross sections of the wing. The use of the method makes it possible to use complex finite element models in the early stages of designing the wing of a transport category aircraft, which significantly improves the quality of design by increasing the accuracy of the analysis of stress distribution in the structure. It is shown that the used calculation algorithm ensures good convergence of load distribution diagrams with the original design diagrams.