Method and device for determining finite element point load distribution in aircraft wing

Abstract

The invention provides a method and a device for determining finite element point load distribution in an aircraft wing. The method comprises the steps that all pneumatic points and finite element points contained in the aircraft wing to be calculated are determined; all the pneumatic points are grouped, and loads of all the pneumatic points are calculated according to coordinates, load coefficients and velocity pressure corresponding to all the pneumatic points; the finite element points are divided into finite element units; whether a projection of each pneumatic point is in one finite element unit is determined; if yes, the loads of the pneumatic points are distributed to all the finite element points on the finite element units where the projections of the pneumatic points are located; if not, front-beam finite element points and back-beam finite element points of the pneumatic points are selected according to rib stances of the finite element points in the aircraft wing, and quadrilateral finite element units are sequentially constructed according to the order of the stances and the selected finite element points; and the loads of the pneumatic points are distributed to all the finite element points in the constructed finite element units. Through the load distribution method, the accuracy of a calculation result is high.

Description

technical field [0001] The invention relates to the technical field of calculation of finite element point loads on aircraft wings, in particular to a method and a device for determining the distribution of finite element point loads on an aircraft wing surface. Background technique [0002] The loads that the aircraft wing structure needs to bear include aerodynamic loads, inertial loads and concentrated force loads. When performing finite element calculations, it is necessary to map aerodynamic loads, inertial loads, and concentrated force loads to finite element points. The mapping results must satisfy that the total load and total moment are equal, and the position of the center of pressure remains unchanged. Since the mapping method is a numerical method, there is a problem of distribution accuracy, and the distributed load needs to be trimmed and shared. Different solution methods will have different results. Therefore, the authenticity of the load distribution on the ...

AI Technical Summary

Problems solved by technology

[0005] The conditions that the three-point row scheme needs to meet are too harsh. For some aerodynamic points, the nearest three finite element points are found, but they do not fall into the triangular area formed by them. The allocation cannot be handled, and the rationality of the allocation cannot be guaranteed.

It can be seen that the existing finite element point load distribution scheme on the aircraft wing cannot guarantee the rationality of the distribution, that is, the accuracy of the load distribution is poor

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