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Overlapping Mesh Perturbation Domain Update Method for Multi-body Separation Simulation of Aircraft

A multi-body separation and update method technology, which is applied in the direction of instruments, CAD numerical modeling, geometric CAD, etc., can solve the problems of "solitary point" affecting convergence, interpolation affecting accuracy, etc., and achieve the effect of improving calculation efficiency

Active Publication Date: 2022-03-11
BEIHANG UNIV
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AI Technical Summary

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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  • Overlapping Mesh Perturbation Domain Update Method for Multi-body Separation Simulation of Aircraft
  • Overlapping Mesh Perturbation Domain Update Method for Multi-body Separation Simulation of Aircraft
  • Overlapping Mesh Perturbation Domain Update Method for Multi-body Separation Simulation of Aircraft

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 overlapping grid disturbance domain update method for multi-body separation simulation of an aircraft. First, the wall distance algorithm is simplified based on the characteristics of the wall distance marking unit attribute using the implicit assembly method, thereby improving the efficiency of grid assembly; secondly, Under the framework of the disturbance domain update method, the numerical simulation of the overlapping grid is realized, so that only the cells in the unconverged disturbed area are interpolated, thereby reducing the calculation amount of the overlapping grid interpolation operation; again, a new type of overlapping grid is established The information exchange method realizes the transmission of information based on grid deformation and encryption in the large flow gradient area, and the way of transmitting information based on flow gradient interpolation in the small flow gradient area, thereby improving the accuracy of the overlapping area and avoiding the "solitary point" problem. This method can significantly improve the computational efficiency of the numerical simulation of the aircraft multi-body separation problem, and solve the problems of numerical accuracy loss in the overlapping area of ​​the large flow gradient grid and the existence of "solitary points".

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 Patents(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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