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Load balancing method for dynamic computational domain in aircraft aerodynamic characteristic parallel simulation

A technology of load balancing and aerodynamic characteristics, applied in computing, computer parts, instruments, etc., can solve problems such as discount of acceleration effect

Active Publication Date: 2021-09-14
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Since the dynamic calculation domain keeps changing throughout the solution process, if the conventional static grid partition method is still used, the acceleration effect of the "disturbed region update method" may be greatly reduced due to the unbalanced load of parallel threads

Method used

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  • Load balancing method for dynamic computational domain in aircraft aerodynamic characteristic parallel simulation
  • Load balancing method for dynamic computational domain in aircraft aerodynamic characteristic parallel simulation
  • Load balancing method for dynamic computational domain in aircraft aerodynamic characteristic parallel simulation

Examples

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Effect test

Embodiment 1

[0141] The flow around a supersonic two-dimensional wedge with Mach number 2.5 is simulated with 4 threads. Fig. 3 has shown the effect of the load balancing technology of dynamic computing domain in the parallel simulation of the present invention in supersonic two-dimensional system wedge problem simulation; Among the figure η represents the ratio of the grid volume of convective dynamic domain and preset computing domain, N max Represents the total number of iterations required for solution convergence. During the entire solution process, the convective dynamic domain first increases from the far field of the wall surface, and then shrinks from upstream to downstream, and continues to change. From the grid division in the figure, it can be seen that the technology of the present invention firstly divides the grid into 4×1 linear division, as shown in Figure 3(a); then it develops into a zigzag division, as shown in Figure 3(b) and 3(c) Shown; in the change to hierarchica...

Embodiment 2

[0143] Simulate the supersonic flat plate laminar flow problem of Mach number 3.5 with 12 threads, Fig. 5 has shown the effect of the load balancing technology of dynamic computing domain in the parallel simulation of the present invention in the supersonic flat plate laminar flow problem simulation; Among the figure, η v Represents the ratio of the mesh volume of the viscous dynamic domain to the preset computational domain. The convective and viscous dynamic domains first increase from the wall to the far field, and then shrink from the far field to the wall. As can be seen from the grid division in the figure, the technology of the present invention firstly divides the grid into 12×1 linear division, such as Figure 5(a) and 5(b) shown; then developed into a zigzag split, such as Figure 5(c) , 5(d) and 5(e); the final reply is a 6×2 linear subdivision, as shown in Figure 5(f). It can be seen from the change curve of the number of grid sub-blocks and load ratio shown in...

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Abstract

The invention relates to a load balancing method for a dynamic computational domain in aircraft aerodynamic characteristic parallel simulation. The method comprises the following steps: inputting data; calculating a load ratio; judging whether the load is balanced; calculating an expected unit number and a unit number tolerance of the thread; selecting a mesh generation method; if a structure subdivision method is selected, carrying out structured subdivision on the grid subblocks, equally dividing the grid subblocks to threads, and outputting a result; if the cut and complement subdivision method is selected, combining the minimum grid blocks, circularly selecting the cut and complement thread pair, judging whether the grid blocks can be cut and complement, and cutting and complement the three steps until the load ratio is lower than a load balance threshold value or the number of moving units of the cut and complement thread pair is smaller than the unit number tolerance, and outputting a result. In order to solve the problem that dynamic load balance is required by a dynamic computational domain in parallelization of a disturbance area updating method, the method realizes load balance of the dynamic computational domain in aircraft aerodynamic characteristic parallel simulation by efficiently and dynamically adjusting a grid area required to be solved by each parallel thread (process).

Description

technical field [0001] The invention belongs to the technical field of computational fluid dynamics, and relates to a load balancing method of a dynamic calculation domain in parallel simulation of aircraft aerodynamic characteristics. Background technique [0002] The research and development of modern aircraft has generally adopted the method of numerical simulation of computational fluid dynamics to predict and verify the aerodynamic characteristics of the aircraft design scheme. A large number of calculations are required in the entire research and development process, and the number of meshes for simulating a real aircraft can often reach tens of millions or even Hundreds of millions. Therefore, continuously improving the calculation efficiency of aircraft aerodynamic simulation calculation has important engineering application value. [0003] In order to avoid invalid calculations in traditional numerical simulation methods, the invention patent ZL201810250654.8 provi...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/23G06F30/15G06K9/62G06F111/10
CPCG06F30/23G06F30/15G06F2111/10G06F18/241Y02T90/00
Inventor 蒋崇文胡姝瑶高振勋李椿萱
Owner BEIHANG UNIV
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