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Overlapped grid disturbance domain updating method for aircraft multi-body separation simulation

A technology of multi-body separation and update method, which is applied in the field of overlapping grid disturbance domain update of aircraft multi-body separation simulation, which can solve the problems of "outliers" affecting convergence and interpolation affecting accuracy, and achieves the effect of improving computational efficiency.

Active Publication Date: 2022-01-21
BEIHANG UNIV
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Problems solved by technology

[0005] Aiming at the three problems of "solitary point" affecting convergence, interpolation affecting accuracy, and grid assembly and interpolation efficiency steps in the process of simulating multi-body separation of aircraft in the existing overlapping grid method, the present invention proposes an overlapping method for multi-body separation simulation of aircraft Mesh Perturbation Domain Update Method

Method used

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  • Overlapped grid disturbance domain updating method for aircraft multi-body separation simulation
  • Overlapped grid disturbance domain updating method for aircraft multi-body separation simulation
  • Overlapped grid disturbance domain updating method for aircraft multi-body separation simulation

Examples

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Embodiment 1

[0184] Example 1: figure 2 A case where there are two corresponding units for one unit is illustrated. The coordinates of point A, point B, point C, point D, point 1, and point 2 in the figure x A , x B , x C , x D , x 1 , x 2 is a known quantity, step S3-2 is responsible for determining the coordinates of the remaining points, namely x a , x b , x d , x e , x f . It can be seen from the figure that there is the following geometric relationship between the points:

[0185] (12)

[0186] The reasonable position of the split point can be determined by using the Lagrange multiplier method.

Embodiment 2

[0187] Example 2: image 3 The corresponding situation of the grid cells in the overlapping region of large flow gradients is illustrated. In the figure, the coordinates of the 13 grid points marked with letters are known, and the grid points have the following geometric relationship:

[0188] (13)

[0189] In the formula, the subscript "1" represents the grid coordinates before moving, and "2" represents the grid coordinates after moving. The new coordinates of the grid cells in the large flow gradient overlapping area can be determined by using the Lagrange multiplier method.

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Abstract

The invention discloses an overlapped grid disturbance domain updating method for aircraft multi-body separation simulation. The method comprises the steps that a wall distance algorithm is simplified by employing an implicit assembly method based on the attribute characteristics of a wall distance marking unit, so that the grid assembly efficiency is improved; secondly, under the framework of a disturbance domain updating method, numerical simulation of the overlapped grids is realized, so that only units in a non-convergent disturbed region are subjected to interpolation operation, and the calculation amount of the interpolation operation of the overlapped grids is reduced; and thirdly, a novel overlapping grid information exchange method is established, and the mode that information is transmitted based on grid deformation and encryption in a large flow gradient area and information is transmitted based on flow gradient interpolation in a small flow gradient area is achieved, so that the accuracy of the overlapping area is improved, and the isolated point problem is avoided. According to the method, the calculation efficiency of numerical simulation of the multi-body separation problem of the aircraft can be remarkably improved, and the problems that the numerical precision is lost in a large-flow gradient grid overlapping region, and isolated points exist are solved.

Description

technical field [0001] The invention relates to the field of computational fluid dynamics, in particular to an update method of an overlapping grid disturbance domain for multi-body separation simulation of an aircraft. Background technique [0002] In the process of multi-body separation, there is a coupling interference effect among the multi-body aircraft that "the movement of the multi-body changes the aerodynamic characteristics, and the aerodynamic characteristics affect the trajectory of the multi-body motion". Therefore, accurately simulating the multi-body separation process of an aircraft is an essential part of designing an aircraft with multi-body separation problems, and is crucial to ensuring flight safety. [0003] Computational fluid dynamics numerical simulation is an important analysis method for the aerodynamic characteristics of multi-body separation process. However, the multi-body separation problem poses a great challenge to the generation of computat...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/15G06F30/28G06F30/23G06F111/10G06F113/08G06F119/14
CPCG06F30/15G06F30/28G06F30/23G06F2111/10G06F2113/08G06F2119/14
Inventor 蒋崇文胡姝瑶高振勋许晨豪李椿萱
Owner BEIHANG UNIV
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