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Efficient nested grid host unit searching method in aircraft dynamic flow field analysis

A search method and aircraft technology, applied in the field of efficient nested grid host cell search, can solve problems such as unbalanced tree structure, reduced search host cell efficiency, and increased depth, so as to improve efficiency, reduce intersection judgment tasks, and reduce small depth effect

Active Publication Date: 2022-03-01
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Description
  • Claims
  • Application Information

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Problems solved by technology

But when dealing with large-scale grids, the tree structure of ADT will be extremely unbalanced, and the depth of the tree will increase sharply, seriously reducing the efficiency of searching for host units

Method used

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  • Efficient nested grid host unit searching method in aircraft dynamic flow field analysis
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  • Efficient nested grid host unit searching method in aircraft dynamic flow field analysis

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Embodiment Construction

[0043] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0044] The present invention discloses a highly efficient nested grid host unit search method in the dynamic flow field analysis of aircraft, such as figure 1 As shown, the following steps S10-S100 are included:

[0045] S10. Based on the geometric model of the engineering object, generate N sets of nested fluid calculation grids. The fluid calculation grids can be of any type, such as tetrahedron, hexahedron, polyhedron, and the like.

[0046] S20. Calculat...

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Abstract

The invention provides an efficient nested grid host unit searching method in dynamic flow field analysis of an aircraft, which comprises the following steps of: creating more than one sub-ADT tree of a series for grid units in a given area, and registering storage addresses of the sub-ADT trees to a register book in an array form; firstly, grid points to be checked are freeze-framed on sub-ADT corresponding to a specific local area according to coordinate positions of the grid points to be checked, then corresponding host units of the grid points to be checked are searched in a conventional ADT mode, and therefore multiple sets of mutually-nested grids are assembled, and aircraft dynamic motion flow field analysis is carried out. According to the method, the depth of each sub ADT is greatly reduced, so that each sub ADT tree structure has better balance, meanwhile, the to-be-searched point is quickly positioned to a very small local area, the area range searched by the host unit is reduced, the search time is effectively reduced, and the numerical simulation time of the dynamic motion process of the aircraft is shortened.

Description

technical field [0001] The invention relates to the technical field of fluid mechanics, in particular to an efficient nested grid host unit search method in the dynamic flow field analysis of an aircraft. Background technique [0002] With the rapid development of computer technology in recent years, Computational Fluid Dynamics (CFD) has developed vigorously. CFD technology has become a basic key technology for hydrodynamic and aerodynamic analysis, and has been widely verified in the fields of aerospace, marine vehicles, etc. with application. However, many practical engineering problems will involve the analysis of geometric deformation or multi-body relative motion of aircraft dynamic motion flow field, such as flaperon deflection, landing gear retraction, weapon separation, etc. Dynamic grid technology is calculated by CFD unsteady flow field an important job. With the movement of the boundary, the computational mesh of the flow field at each time step needs to be upd...

Claims

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Application Information

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IPC IPC(8): G06T17/00G06T17/20G06F30/23G06F30/28G06F111/10G06F113/08
CPCG06T17/005G06T17/20G06F30/23G06F30/28G06F2111/10G06F2113/08Y02T90/00
Inventor 肖天航支豪林邓双厚
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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