Radial basis function mesh deformation method and airfoil design method based on virtual nodes

Through the radial basis function grid deformation method based on internal virtual control points, a high-quality deformation grid is generated, which solves the problem of grid deformation difficulties under large displacement in the prior art, and improves the efficiency of aircraft airfoil optimization.

CN115859472BActive Publication Date: 2025-08-12HANGZHOU DIANZI UNIV
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Patent Information

Application Number
CN202211649010.9
Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
Filing Date
2022-12-20
Publication Date
2025-08-12
Estimated Expiration
2042-12-20

AI Technical Summary

Technical Problem

The existing mesh deformation method based on radial basis functions is difficult to generate high-quality deformation grids, especially in large displacements, which leads to early stopping of deformation and affects numerical analysis.

Method used

The radial basis function grid deformation method based on internal virtual control points is adopted. By generating internal virtual nodes and interpolation of radial basis function, the boundary linear equilibrium equation is constructed, the displacement of internal nodes is calculated, and high-quality grid is generated.

Benefits of technology

It realizes the rapid generation of high-quality grids under large displacements, improves the degree of grid deformation, and shortens the time and computing resources required for aircraft airfoil optimization.

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Abstract

The present invention discloses a radial basis function mesh deformation method based on virtual nodes and an airfoil design method. Currently, generating a high-quality deformed mesh by a mesh deformation method is still an open problem. The present invention first obtains the distribution of internal virtual nodes based on the internal normal of the moving boundary point; then reduces the number of internal virtual nodes to obtain a small number of uniformly distributed internal virtual nodes; then obtains the displacement of each internal virtual point by interpolation of K adjacent boundary nodes; finally, uses the internal virtual nodes and the original boundary nodes to construct the linear equilibrium equation of the object surface, solves the coefficient matrix, and thus interpolates and calculates the displacement of the internal nodes to obtain the deformed mesh. The present invention effectively improves the quality of the deformed mesh and the degree of mesh deformation, and realizes the rapid generation of high-quality mesh units for the deformation of the aircraft airfoil section. This greatly reduces the time and computing power required for aircraft airfoil optimization.
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