Method for acquiring electric field distribution of large-sized complex aircraft by using fast boundary element method

Abstract

The invention relates to a method for acquiring the electric field distribution of a large-sized complex aircraft by using a fast boundary element method, which is technically characterized by solving the problem of the fast computation and analysis of a large-sized electrostatic field of the aircraft in the field of aircraft design by adopting the boundary element method. The method comprises the following steps of: dividing a medium interface into smooth curved surfaces with parametric equations by adopting a Nessler discretization method, and projecting integral points to the medium interface to form boundary integral points through the parametric equations; and constructing a wavelet transform matrix on the basis of the multiscale grouping of the integral points, and carrying out matrix compression, computation and storage on a boundary element coefficient matrix. The invention overcomes the shortages of complex computation, large computation amount and low precision of the coefficient matrix in the traditional wavelet boundary element method and effectively reduces the internal storage occupying amount and the computation time of boundary element analysis, thereby solving theproblems of a large-scale project with millions of freedom degrees; and in addition, the invention can be applied to the electric field computation and analysis of the large-sized complex aircraft inan aerospace field and electric field analysis in other project fields.

Description

technical field [0001] The invention relates to a method for obtaining the electric field distribution of a large-scale complex aircraft by using a fast boundary element method, belongs to the field of aircraft design, and specifically belongs to a rapid analysis and design method for a large-scale electromagnetic field of an aircraft. Background technique [0002] In the field of aerospace, the charging and discharging phenomenon of the aircraft structure will interfere with the communication and navigation of the aircraft, and even cause serious consequences such as damage to the aircraft structure. Therefore, the calculation and analysis of the charging and discharging process of the aircraft structure is a problem that must be considered in the design of the aircraft. The core is to determine the electrostatic field of the aircraft by solving the Laplace equation. This problem has the characteristics of complex solution area and large solution scale. [0003] There are ...

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Problems solved by technology

[0007] However, the existing boundary element method based on wavelet compression (hereinafter referred to as "wavelet boundary element method") adopts collocation method and Galerkin (Galerkin) method as discretization methods, and there are three main problems: ① need to calculate the single weight Or double surface integrals, singular integral processing is complex, and the coefficient matrix calculation is relatively large; ②Limited by boundary subdivision and shape function approximation methods, it is difficult to obtain high-precision results; ③The surfaces of aircraft, spacecraft, etc. are usually composed of a large number of smooth Composed of surface patches, the division of units will artificially destroy the continuity of the boundary, so the calculation efficiency of the collocation method and the Galerkin method is low

The existing wavelet boundary element method based on collocation method and Galerkin method has the disadvantages of complex calculation method of coefficient matrix, large amount of calculation, accuracy limited by element division, and low calculation efficiency for complex aircraft electric field

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