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Hybrid grid-based complex structure aerodynamic thermal environment analysis method and system

A hybrid mesh, complex structure technology, applied in instrumentation, geometric CAD, design optimization/simulation, etc., can solve difficulties and other problems, and achieve the effect of improving efficiency and shortening mesh generation time

Pending Publication Date: 2022-08-09
BEIJING LINJIN SPACE AIRCRAFT SYST ENG INST
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  • Description
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  • Application Information

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Problems solved by technology

Hybrid grids have better results in surface pressure capture. However, due to grid quality and algorithm limitations, it is still difficult to use hybrid grids to carry out aerothermal numerical simulations.

Method used

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  • Hybrid grid-based complex structure aerodynamic thermal environment analysis method and system
  • Hybrid grid-based complex structure aerodynamic thermal environment analysis method and system
  • Hybrid grid-based complex structure aerodynamic thermal environment analysis method and system

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Embodiment

[0079] A series of calorimetric tests were carried out in the LENS wind tunnel of Calspan University for the shape of the pointed biconical compression corner, and the test results were used as a standard database for code verification. This paper selects the state Run 28 times the test state Ma ∞ =9.59, Re ∞ =1.309×10 5 / m, T ∞ = 185.56K, T wall = 293.33K Numerical simulations based on structured grids and hybrid grids were carried out. The size parameters of the pointed biconical model are shown in the appendix figure 2 shown.

[0080] 1024 × 228 (233,000) grid cells are used in the structured grid computational domain. The hybrid mesh consists of a full prismatic mesh near the wall and an external field filled with tetrahedral elements, with a total of 117,600 mesh elements. Grid refinement is performed on the head, and the first-layer scale of the two sets of grids is 1×10 -6 m.

[0081] The surface dimensionless heat flow obtained using the two sets of meshes is...

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Abstract

The invention relates to a complex structure aerodynamic thermal environment analysis method and system based on hybrid grids, and the method comprises the steps: carrying out the geometric pretreatment of a to-be-calculated model and an external field before carrying out CFD numerical calculation; selecting a surface grid cell type, setting surface grid cell parameters, and performing geometric surface grid drawing; volume grid drawing is carried out to form a hybrid grid; based on the hybrid grid, performing aerodynamic thermal environment numerical simulation; grid optimization is carried out based on an aerodynamic thermal environment numerical simulation result; carrying out aerodynamic thermal environment numerical simulation again based on the optimized grid, judging whether a simulation result meets requirements or not, and if not, continuing to optimize the grid; and if yes, considering that a convergent aerodynamic thermal environment result has been obtained. The method is used for improving the efficiency of thermal environment numerical simulation.

Description

technical field [0001] The invention relates to a hybrid grid-based aerodynamic thermal environment analysis method and system for complex structures, and belongs to the field of aerospace aerodynamic thermal environment calculation. Background technique [0002] When the aircraft flies at a high speed of Ma>5, the surrounding air is strongly compressed to form high temperature air, which forms aerodynamic heating on the surface of the aircraft and brings pressure to the surface materials of the aircraft. Accurate and reliable assessment of hypersonic aerodynamic thermal environment is the key to thermal design. [0003] At present, the numerical calculation method based on computational fluid dynamics is an important way to evaluate the aerothermal environment. In engineering practice, computational fluid dynamics (CFD) numerical calculations are generally carried out based on structured docking grids to obtain surface-distributed thermal environment distribution. Accu...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/15G06F30/23G06F30/28G06T17/20G06F111/10G06F113/08
CPCG06F30/15G06F30/28G06F30/23G06T17/205G06F2111/10G06F2113/08Y02T90/00
Inventor 王迅程响刘波周禹檀妹静付斌曹占伟
Owner BEIJING LINJIN SPACE AIRCRAFT SYST ENG INST
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