CN117274537A - Grid generation method, device, terminal equipment and medium based on boundary problem - Google Patents
Grid generation method, device, terminal equipment and medium based on boundary problem Download PDFInfo
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- 239000002344 surface layer Substances 0.000 claims abstract description 65
- 238000004364 calculation method Methods 0.000 claims abstract description 48
- 238000012545 processing Methods 0.000 claims abstract description 28
- 238000004088 simulation Methods 0.000 claims abstract description 28
- 238000004422 calculation algorithm Methods 0.000 claims abstract description 25
- 230000003044 adaptive effect Effects 0.000 claims description 52
- 230000008859 change Effects 0.000 claims description 11
- 238000004590 computer program Methods 0.000 claims description 9
- 230000007704 transition Effects 0.000 claims description 6
- 238000011069 regeneration method Methods 0.000 abstract description 4
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06T—IMAGE DATA PROCESSING OR GENERATION, IN GENERAL
- G06T17/00—Three dimensional [3D] modelling, e.g. data description of 3D objects
- G06T17/20—Finite element generation, e.g. wire-frame surface description, tesselation
- G06T17/205—Re-meshing
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
- G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
- G06F30/28—Design optimisation, verification or simulation using fluid dynamics, e.g. using Navier-Stokes equations or computational fluid dynamics [CFD]
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2111/00—Details relating to CAD techniques
- G06F2111/10—Numerical modelling
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- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2113/00—Details relating to the application field
- G06F2113/08—Fluids
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2113/00—Details relating to the application field
- G06F2113/28—Fuselage, exterior or interior
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
Abstract
The application discloses a grid generation method, a device, terminal equipment and a medium based on boundary problems, wherein a background Cartesian grid is determined according to preset grid generation parameters; determining a near-wall boundary layer grid of the aircraft according to the aircraft model; determining a self-adaptive Cartesian grid corresponding to the near-wall surface layer grid according to the near-wall surface layer grid; according to the self-adaptive Cartesian grid and the boundary layer grid, performing grid processing by adopting an overlapping algorithm or a contribution unit method to obtain a processed grid; based on a flow control equation, performing simulation calculation on the processed grid to obtain initial flow field information; according to the initial flow field information, the boundary motion of the aircraft is grid-adjusted, so that the method has the advantages of higher automation degree and less manual intervention compared with the traditional method, the grid does not need to be repeatedly regenerated, the calculation cost is lower compared with that of the regeneration method, and the boundary can be rapidly processed.
Description
Technical Field
The application belongs to the technical field of hydrodynamics, and particularly relates to a grid generation method, device, terminal equipment and medium based on boundary problems.
Background
Compared with a wind tunnel test method, the method for predicting the dynamic stability parameters of the aircraft by means of computational fluid dynamics (ComputationalFluidDynamics, CFD) has the unique advantages of short relative period, low cost and convenient parameter setting, and has become an important means for developing the aircraft.
For the problem of movement of an aircraft, as a movement boundary exists, challenges are brought to high-quality grid efficient generation during CFD simulation, and the traditional common methods mainly comprise a grid deformation method and a body-attached movement grid technology, such as a nested grid technology, a Cartesian grid method and the like, wherein the grid deformation method has poor applicability to large-amplitude movement; however, the traditional body-attached motion grid technology still generally needs to manually generate body-attached grids around a moving object, so that the degree of automation is not high; although the cartesian grid can realize automation, a grid regeneration mode is generally adopted to capture the motion boundary, and when the appearance is complex and the grid scale is large, the calculation cost of grid regeneration is high. For complex shapes such as aircraft, how to deal with the boundary of the aircraft is a current urgent issue.
Disclosure of Invention
The invention aims to provide a grid generation method, a device, terminal equipment and a medium based on boundary problems, so as to solve the defects in the prior art.
In a first aspect, an embodiment of the present invention provides a method for generating a grid based on a boundary problem, where the method includes:
determining a background Cartesian grid according to preset grid generation parameters;
determining a near-wall boundary layer grid of the aircraft according to the aircraft model;
determining a self-adaptive Cartesian grid corresponding to the near-wall surface layer grid according to the near-wall surface layer grid;
according to the self-adaptive Cartesian grid and the boundary layer grid, performing grid processing by adopting an overlapping algorithm or a contribution unit method to obtain a processed grid; based on a flow control equation, performing simulation calculation on the processed grid to obtain initial flow field information;
and according to the initial flow field information, carrying out grid adjustment on the boundary motion of the aircraft.
Optionally, the determining the near-wall boundary layer grid of the aircraft according to the aircraft model includes:
generating a surface discrete grid with an aircraft model according to the aircraft model;
Generating a near-wall surface layer grid by adopting a surface layer grid generation algorithm according to the surface discrete grid;
and acquiring an upper top surface discrete grid of the near-wall surface layer grid according to the near-wall surface layer grid.
Optionally, the determining, according to the near-wall surface layer grid, an adaptive cartesian grid corresponding to the near-wall surface layer grid includes:
acquiring adaptive Cartesian grid generation parameters, wherein the adaptive Cartesian grid generation parameters at least comprise a maximum encryption layer number, a curvature encryption threshold value and a transition layer number;
and taking the upper top surface discrete grid of the near-wall surface layer grid as an adaptive boundary, and generating an adaptive Cartesian grid corresponding to the upper top surface discrete grid according to the adaptive Cartesian grid generation parameters.
Optionally, the determining the background cartesian grid according to the preset grid generation parameter includes:
generating a background Cartesian grid according to preset grid generation parameters, wherein the preset grid generation parameters at least comprise: an initial mesh size, the number of meshes in each coordinate direction, and a calculated domain size.
Optionally, the grid processing is performed by adopting an overlapping algorithm or a contribution unit method according to the adaptive cartesian grid and the boundary layer grid, so as to obtain a processed grid, which includes:
Constructing a space bounding box by taking a lattice center of a background Cartesian grid as a center according to the space characteristic size of the background Cartesian grid;
searching structural grid nodes in the space bounding box according to the space bounding box;
calculating a first distance from the structural grid node to the background Cartesian grid core according to the number of the structural grid nodes;
determining the processed grid according to the structural grid nodes, the required number of contribution units and the first distance;
or (b)
Determining an overlapped grid boundary according to the adaptive Cartesian grid;
determining the logic position of the adaptive Cartesian grid intersection unit where the structural grid node is positioned according to the overlapped grid boundary;
the intersecting unit is taken as a center, and a neighbor unit corresponding to the intersecting unit is determined according to the full-thread tree data format of the self-adaptive Cartesian grid;
sequentially calculating a second distance between the center of the intersecting unit and the structural grid node according to the number of the neighbor units;
and determining the processed grid according to the second distance, the number of neighbor units and the required number of contribution units. Optionally, based on the flow control equation, performing simulation calculation on the processed grid to obtain initial flow field information, including:
Based on the background Cartesian grid and the incoming flow parameters, the Navier-Stokes equation or the Euler equation is solved, the computer hydrodynamic numerical calculation is carried out, and the initial flow field information at the current moment is obtained after convergence.
Optionally, the grid adjustment for boundary motion of the aircraft according to the initial flow field information includes:
adjusting the grid of the boundary layer according to the motion parameters, and obtaining the change information of the grid position of the top surface on the boundary layer;
adjusting an external Cartesian grid according to the change information of the grid position of the top surface on the boundary layer;
and performing flow field calculation on the updated Cartesian grid.
In a second aspect, an embodiment of the present invention provides a grid generating device based on a boundary problem, where the device includes:
the first determining module is used for determining a background Cartesian grid according to preset grid generation parameters;
the second determining module is used for determining a near-wall boundary layer grid of the aircraft according to the aircraft model;
the third determining module is used for determining an adaptive Cartesian grid corresponding to the near-wall surface layer grid according to the near-wall surface layer grid;
the processing module is used for carrying out grid processing by adopting an overlapping algorithm or a contribution unit method according to the self-adaptive Cartesian grid and the boundary layer grid to obtain a processed grid;
The calculation module is used for carrying out simulation calculation on the processed grid based on a flow control equation to obtain initial flow field information;
and the adjusting module is used for carrying out grid adjustment on the boundary motion of the aircraft according to the initial flow field information.
Optionally, the second determining module is configured to:
generating a surface discrete grid with an aircraft model according to the aircraft model;
generating a near-wall surface layer grid by adopting a surface layer grid generation algorithm according to the surface discrete grid;
and acquiring an upper top surface discrete grid of the near-wall surface layer grid according to the near-wall surface layer grid.
Optionally, the third determining module is configured to:
acquiring adaptive Cartesian grid generation parameters, wherein the adaptive Cartesian grid generation parameters at least comprise a maximum encryption layer number, a curvature encryption threshold value and a transition layer number;
and taking the upper top surface discrete grid of the near-wall surface layer grid as an adaptive boundary, and generating an adaptive Cartesian grid corresponding to the upper top surface discrete grid according to the adaptive Cartesian grid generation parameters.
Optionally, the first determining module is configured to:
the determining the background Cartesian grid according to the preset grid generation parameters comprises the following steps:
Generating a background Cartesian grid according to preset grid generation parameters, wherein the preset grid generation parameters at least comprise: an initial mesh size, the number of meshes in each coordinate direction, and a calculated domain size.
Optionally, the processing module is configured to:
constructing a space bounding box by taking a lattice center of a background Cartesian grid as a center according to the space characteristic size of the background Cartesian grid;
searching structural grid nodes in the space bounding box according to the space bounding box;
calculating a first distance from the structural grid node to the background Cartesian grid core according to the number of the structural grid nodes;
determining the processed grid according to the structural grid nodes, the required number of contribution units and the first distance;
or (b)
Determining an overlapped grid boundary according to the adaptive Cartesian grid;
determining the logic position of the adaptive Cartesian grid intersection unit where the structural grid node is positioned according to the overlapped grid boundary;
the intersecting unit is taken as a center, and a neighbor unit corresponding to the intersecting unit is determined according to the full-thread tree data format of the self-adaptive Cartesian grid;
sequentially calculating a second distance between the center of the intersecting unit and the structural grid node according to the number of the neighbor units;
And determining the processed grid according to the second distance, the number of neighbor units and the required number of contribution units.
Optionally, the computing module is configured to:
based on the background Cartesian grid and the incoming flow parameters, the Navier-Stokes equation or the Euler equation is solved, the computer hydrodynamic numerical calculation is carried out, and the initial flow field information at the current moment is obtained after convergence.
Optionally, the adjusting module is configured to:
adjusting the grid of the boundary layer according to the motion parameters, and obtaining the change information of the grid position of the top surface on the boundary layer;
adjusting an external Cartesian grid according to the change information of the grid position of the top surface on the boundary layer;
and performing flow field calculation on the updated Cartesian grid.
In a third aspect, an embodiment of the present invention provides a terminal device, including: at least one processor and memory;
the memory stores a computer program; the at least one processor executes the computer program stored by the memory to implement the boundary problem-based grid generation method provided in the first aspect.
In a fourth aspect, an embodiment of the present invention provides a computer-readable storage medium having stored therein a computer program that, when executed, implements the boundary problem-based grid generation method provided in the first aspect.
The embodiment of the invention has the following advantages:
the grid generation method, the device, the terminal equipment and the medium based on the boundary problem, provided by the embodiment of the invention, determine the background Cartesian grid according to preset grid generation parameters; determining a near-wall boundary layer grid of the aircraft according to the aircraft model; determining a self-adaptive Cartesian grid corresponding to the near-wall surface layer grid according to the near-wall surface layer grid; according to the self-adaptive Cartesian grid and the boundary layer grid, performing grid processing by adopting an overlapping algorithm or a contribution unit method to obtain a processed grid; based on a flow control equation, performing simulation calculation on the processed grid to obtain initial flow field information; according to the initial flow field information, grid adjustment is carried out on boundary motion of an aircraft, the embodiment of the application is realized through an automatic generation technology of boundary layer grids and a self-adaptive Cartesian grid technology, the boundary layer adopts a body-attached structural grid, a background adopts the self-adaptive Cartesian grid, and an interface between the boundary layer grid and the self-adaptive Cartesian grid is processed through an overlapping technology, so that full-field automatic grid generation and simulation calculation are realized.
Drawings
In order to more clearly illustrate the embodiments or prior art solutions of the present application, the drawings that are required for the description of the embodiments or prior art will be briefly described below, it being apparent that the drawings in the following description are only some of the embodiments described in the present application, and that other drawings may be obtained according to these drawings without inventive faculty for a person skilled in the art.
FIG. 1 is a flowchart of a grid generation method based on a boundary problem according to an embodiment of the present application;
FIG. 2 is a flowchart of yet another grid generation method based on boundary problems according to an embodiment of the present application;
FIG. 3 is a schematic diagram of an overlay grid and a Cartesian grid in accordance with an embodiment of the present application;
FIG. 4 is a schematic diagram of an adaptive Cartesian grid according to an embodiment of the present application;
FIG. 5 is a schematic diagram of a surrounding contribution unit of a Cartesian grid according to an embodiment of the present application;
FIG. 6 is a schematic diagram of a contribution unit around an additional layer grid in an embodiment of the present application
FIG. 7 is a block diagram of an embodiment of a boundary problem-based mesh generation apparatus of the present invention;
fig. 8 is a schematic structural view of a terminal device of the present invention.
Detailed Description
For the purposes, technical solutions and advantages of the present application, the technical solutions of the present application will be clearly and completely described below with reference to specific embodiments and corresponding drawings. It will be apparent that the described embodiments are only some, but not all, of the embodiments of the present application. All other embodiments, which can be made by one of ordinary skill in the art without undue burden from the present disclosure, are within the scope of the present disclosure.
Noun interpretation:
computational fluid dynamics: the method is also called CFD, and mainly solves a fluid control equation by means of a computer and a numerical method to obtain physical parameters of a flow field and dynamics characteristics of a study object. Compared with the physical test, the method has the unique advantages of low cost, short period, convenient parameter setting and the like.
And (3) an auxiliary surface layer: adhesive films proximate to the surface of the object, which typically need to be considered in CFD calculations, require higher mesh quality and a specific mesh distribution (typically denser than the outside, generated at a certain ratio along the object plane normal) for simulation.
An embodiment of the invention provides a grid generation method based on boundary problems, which is used for processing the boundary problems of an aircraft. The execution subject of the present embodiment is a grid generating apparatus based on a boundary problem, and is provided on a terminal device, for example, the terminal device includes at least a computer terminal or the like.
Referring to fig. 1, there is shown a flowchart of steps of an embodiment of a grid generation method based on a boundary problem of the present invention, which may specifically include the steps of:
s101, determining a background Cartesian grid according to preset grid generation parameters;
specifically, the terminal device imports an aircraft model, and generates a background cartesian grid according to preset grid generation parameters, wherein the cartesian grid: the grid surface or side is parallel to the coordinate plane or coordinate axis, is generally rectangular grid in two-dimensional condition, is hexahedral grid in three-dimensional condition, can be directly generated without considering the shape of the object plane, is generally intersected with the object plane of the geometric model, and has the advantages of automatic generation, convenient self-adaption and higher grid quality.
The background cartesian grid is a uniform grid.
S102, determining a near-wall surface layer grid of the aircraft according to the aircraft model;
s103, determining a self-adaptive Cartesian grid corresponding to the near-wall surface layer grid according to the near-wall surface layer grid;
specifically, the terminal equipment is led into an aircraft model to generate surface discrete grids, an accessory surface layer grid automatic generation technology is adopted according to the surface discrete grids to generate near-wall accessory surface layer grids, and an adaptive Cartesian grid, namely an adaptive Cartesian grid, is generated aiming at the outer boundary of the accessory surface layer.
S104, performing grid processing by adopting an overlapping algorithm or a contribution unit method according to the self-adaptive Cartesian grid and the boundary layer grid to obtain a processed grid;
specifically, after the background cartesian grid and the adaptive cartesian grid are obtained, the terminal device processes the overlapping area of the adaptive cartesian grid and the background cartesian grid, namely processes and transmits data by adopting an overlapping technology and a contribution unit method aiming at the adaptive cartesian grid and the boundary layer grid.
S105, based on a flow control equation, performing simulation calculation on the processed grid to obtain initial flow field information;
s106, grid adjustment is carried out on boundary movement of the aircraft according to the initial flow field information.
The embodiment of the application provides an automatic grid generation and simulation technology corresponding to the movement problem of an aircraft, and provides an automatic generation method from a boundary layer grid to a space grid, and a technical method for automatic processing and calculation between the two grids, which can reduce more manual intervention problems compared with the traditional body-attached movement grid technology; compared with the grid regeneration method, the method can reduce the calculation cost and improve the calculation efficiency.
According to the grid generation method based on the boundary problem, which is provided by the embodiment of the invention, the background Cartesian grid is determined according to the preset grid generation parameters; determining a near-wall boundary layer grid of the aircraft according to the aircraft model; determining a self-adaptive Cartesian grid corresponding to the near-wall surface layer grid according to the near-wall surface layer grid; according to the self-adaptive Cartesian grid and the boundary layer grid, performing grid processing by adopting an overlapping algorithm or a contribution unit method to obtain a processed grid; based on a flow control equation, performing simulation calculation on the processed grid to obtain initial flow field information; according to the initial flow field information, grid adjustment is carried out on boundary motion of an aircraft, the embodiment of the application is realized through an automatic generation technology of boundary layer grids and a self-adaptive Cartesian grid technology, the boundary layer adopts a body-attached structural grid, a background adopts the self-adaptive Cartesian grid, and an interface between the boundary layer grid and the self-adaptive Cartesian grid is processed through an overlapping technology, so that full-field automatic grid generation and simulation calculation are realized.
The invention further provides a grid generating method based on the boundary problem, which is provided by the embodiment.
Optionally, determining a near-wall boundary layer grid of the aircraft from the aircraft model includes:
generating a surface discrete grid with the aircraft model according to the aircraft model;
generating a near-wall surface layer grid by adopting a surface layer grid generation algorithm according to the surface discrete grid;
and acquiring the upper top surface discrete grid of the near-wall surface layer grid according to the near-wall surface layer grid.
Optionally, determining an adaptive cartesian grid corresponding to the near-wall boundary layer grid according to the near-wall boundary layer grid, including:
acquiring adaptive Cartesian grid generation parameters, wherein the adaptive Cartesian grid generation parameters at least comprise a maximum encryption layer number, a curvature encryption threshold value and a transition layer number;
and taking the upper top surface discrete grid of the near-wall surface layer grid as a self-adaptive boundary, and generating the self-adaptive Cartesian grid corresponding to the upper top surface discrete grid according to the self-adaptive Cartesian grid generation parameters.
The aerodynamic parameters at least comprise one or more of incoming flow speed, density, pressure and attack angle, and the aircraft motion parameters at least comprise: one or more of initial angle of attack, amplitude, reduced frequency, centroid position.
Optionally, determining the background cartesian grid according to the preset grid generation parameters includes:
generating a background Cartesian grid according to preset grid generation parameters, wherein the preset grid generation parameters at least comprise: an initial mesh size, the number of meshes in each coordinate direction, and a calculated domain size.
Optionally, according to the adaptive cartesian grid and the boundary layer grid, performing grid processing by adopting an overlapping algorithm or a contribution unit method to obtain a processed grid, including:
constructing a space bounding box by taking a lattice center of a background Cartesian grid as a center according to the space characteristic size of the background Cartesian grid;
searching structural grid nodes in the space bounding box according to the space bounding box;
calculating a first distance from the structural grid node to a background Cartesian grid core according to the number of the structural grid nodes;
determining a processed grid according to the structural grid nodes, the required number of the contribution units and the first distance;
or (b)
Determining an overlapped grid boundary according to the adaptive Cartesian grid;
determining the logic position of the adaptive Cartesian grid intersection unit where the structural grid node is positioned according to the overlapped grid boundary;
the intersecting unit is taken as a center, and a neighbor unit corresponding to the intersecting unit is determined according to the full-thread tree data format of the self-adaptive Cartesian grid;
Sequentially calculating a second distance between the center of the intersecting unit and the structural grid node according to the number of the neighbor units;
and determining the processed grid according to the second distance, the number of neighbor units and the required number of contribution units. Optionally, based on a flow control equation, performing simulation calculation on the processed grid to obtain initial flow field information, including:
based on the background Cartesian grid and the incoming flow parameters, the Navier-Stokes equation or the Euler equation is solved, the computer hydrodynamic numerical calculation is carried out, and the initial flow field information at the current moment is obtained after convergence.
Optionally, grid adjustment is performed on boundary motion of the aircraft according to the initial flow field information, including:
adjusting the grid of the boundary layer according to the motion parameters, and obtaining the change information of the grid position of the top surface on the boundary layer;
adjusting the external Cartesian grid according to the change information of the grid position of the top surface on the auxiliary surface layer;
and performing flow field calculation on the updated Cartesian grid.
Fig. 2 is a flowchart of still another grid generating method based on a boundary problem according to an embodiment of the present application, as shown in fig. 2, the grid generating method based on the boundary problem includes:
step 101, importing an aircraft model to generate a surface discrete grid;
Step 102, setting parameters related to the pneumatic and the movement of the aircraft:
(1) Setting aerodynamic parameters (incoming flow speed, density, pressure intensity, attack angle, etc.)
(2) Setting aircraft motion parameters (initial angle of attack, amplitude, reduced frequency, centroid position, etc.)
Step 103, generating a near-wall surface layer grid: a near-wall boundary layer mesh is generated for the imported aircraft model.
(a) Generating a near-wall surface layer grid by adopting an automatic surface layer grid generation technology based on the model surface grid, as shown in fig. 3;
(b) And extracting the upper surface discrete grids of the boundary layer grids.
Step 104, background cartesian grid generation: a uniform cartesian grid is generated within the computational domain.
(a) An adaptive cartesian grid generation parameter (e.g., initial grid size or number of grids per coordinate direction, calculated domain size, etc.) is set.
(b) A uniform cartesian grid is generated from the above parameters, as shown in fig. 3.
Step 105, adaptive cartesian grid generation: an adaptive Cartesian grid is generated for the boundary layer outer boundary.
(a) Setting adaptive Cartesian grid generation parameters (such as maximum encryption layer number, curvature encryption threshold value, transition layer number, etc.).
(b) The discrete grid extracted according to 103 (b) is used as an adaptive boundary to generate an adaptive cartesian grid for the top surface on the boundary layer grid according to the parameters described above, as shown in fig. 4.
Step 106, processing an overlapping area of the near-wall grid and the background grid: and processing and data transfer are carried out by adopting an overlapping technology and a contribution unit method aiming at the interface of the boundary layer grid and the background grid.
(a) The cartesian grid contribution unit searching method is shown in fig. 5, wherein squares in fig. 5 represent target units, and circles represent contribution units. Constructing a bounding box with a proper space size by taking a lattice center of a target Cartesian lattice as a center and taking a space characteristic size of the Cartesian lattice as a reference; searching the structural grid nodes contained in the bounding box by taking the space coordinates as the measurement scale; and counting the number of the structural grid nodes in the bounding box, and calculating the distance between the structural grid nodes and the target Cartesian grid center. If the grid node number meets the number required by the contribution units, selecting the grid nodes of the required structure according to the distance parameters; if the grid node number is less than the number required by the contribution units, continuing to expand the bounding box range until the number of the selectable contribution units meets the condition; and taking the selected structural grid nodes in the bounding box as contribution units, and combining corresponding interpolation algorithms to obtain Cartesian grid flow parameters.
(b) The structural grid contribution unit search method is shown in fig. 6. According to the overlapped grid boundary determined by the near-wall body-attached grid, the logic position of the Cartesian grid intersection unit where the structural grid node is located can be obtained; the intersecting units are taken as the center, and neighbor units of the intersecting units of the Cartesian grid can be conveniently and rapidly determined according to the full-thread tree data format of the Cartesian grid; and counting the number of neighbor units, and sequentially calculating the distance between the grid core and the grid core of the target structure. If the number of the neighbor units meets the number required by the contribution units, selecting a required Cartesian unit according to the distance parameter; if the number of neighbor units is less than the number required by the contribution units, continuing to enlarge the number of neighbor layers of the Cartesian grid until the number of selectable contribution units meets the condition; and taking the selected Cartesian grid and the neighbor units thereof as contribution units, and combining a corresponding interpolation algorithm to obtain the flow parameters of the overlapped boundary nodes of the body-attached structural grid.
Step 107, flow field calculation: based on the flow control equation, simulation calculation is performed on the grid processed in step 106, and an initial flow field is obtained.
(a) Based on the space discrete grid and incoming flow parameters (incoming flow speed, density, pressure, attack angle and the like), CFD numerical calculation is carried out by solving a Navier-Stokes equation or an Euler equation, and a steady flow field state at the current moment is obtained after convergence.
Step 108, generating and calculating a motion grid: grid automatic adjustment and calculation are performed for boundary motion.
(a) Adjusting the boundary layer grid (the boundary layer grid moves along with the body) according to the motion parameters, and extracting the position change of the top surface grid on the boundary layer in real time;
(b) The external Cartesian grid is adaptively adjusted and updated according to the top surface position on the boundary layer;
(c) Carrying out updating pushing calculation of a flow field on the updated grid;
(d) Judging whether the set time step number is reached or whether the aerodynamic force is converged or not, if so, ending; if not, repeating 108 (a) - (d).
Step 109, outputting a result: and outputting the calculated data and ending.
It should be noted that, for simplicity of description, the method embodiments are shown as a series of acts, but it should be understood by those skilled in the art that the embodiments are not limited by the order of acts, as some steps may occur in other orders or concurrently in accordance with the embodiments. Further, those skilled in the art will appreciate that the embodiments described in the specification are presently preferred embodiments, and that the acts are not necessarily required by the embodiments of the invention.
According to the grid generation method based on the boundary problem, which is provided by the embodiment of the invention, the background Cartesian grid is determined according to the preset grid generation parameters; determining a near-wall boundary layer grid of the aircraft according to the aircraft model; determining a self-adaptive Cartesian grid corresponding to the near-wall surface layer grid according to the near-wall surface layer grid; according to the self-adaptive Cartesian grid and the boundary layer grid, performing grid processing by adopting an overlapping algorithm or a contribution unit method to obtain a processed grid; based on a flow control equation, performing simulation calculation on the processed grid to obtain initial flow field information; according to the initial flow field information, grid adjustment is carried out on boundary motion of an aircraft, the embodiment of the application is realized through an automatic generation technology of boundary layer grids and a self-adaptive Cartesian grid technology, the boundary layer adopts a body-attached structural grid, a background adopts the self-adaptive Cartesian grid, and an interface between the boundary layer grid and the self-adaptive Cartesian grid is processed through an overlapping technology, so that full-field automatic grid generation and simulation calculation are realized.
Another embodiment of the present invention provides a boundary problem-based mesh generation apparatus for executing the boundary problem-based mesh generation method provided in the foregoing embodiment.
Referring to fig. 7, there is shown a block diagram of an embodiment of a grid generating apparatus based on boundary problem according to the present invention, which may specifically include the following modules: a first determination module 701, a second determination module 702, a third determination module 703, a processing module 704, a calculation module 705, and an adjustment module 706, wherein:
the first determining module 701 is configured to determine a background cartesian grid according to a preset grid generation parameter;
the second determining module 702 is configured to determine a near-wall boundary layer grid of the aircraft according to the aircraft model;
the third determining module 703 is configured to determine an adaptive cartesian grid corresponding to the near-wall surface layer grid according to the near-wall surface layer grid;
the processing module 704 is configured to perform grid processing according to the adaptive cartesian grid and the boundary layer grid by adopting an overlapping algorithm or a contribution unit method, so as to obtain a processed grid;
the calculation module 705 is configured to perform simulation calculation on the processed grid based on a flow control equation, so as to obtain initial flow field information;
The adjustment module 706 is configured to perform grid adjustment on boundary motion of the aircraft according to the initial flow field information.
According to the grid generating device based on the boundary problem, the background Cartesian grid is determined according to the preset grid generating parameters; determining a near-wall boundary layer grid of the aircraft according to the aircraft model; determining a self-adaptive Cartesian grid corresponding to the near-wall surface layer grid according to the near-wall surface layer grid; according to the self-adaptive Cartesian grid and the boundary layer grid, performing grid processing by adopting an overlapping algorithm or a contribution unit method to obtain a processed grid; based on a flow control equation, performing simulation calculation on the processed grid to obtain initial flow field information; according to the initial flow field information, grid adjustment is carried out on boundary motion of an aircraft, the embodiment of the application is realized through an automatic generation technology of boundary layer grids and a self-adaptive Cartesian grid technology, the boundary layer adopts a body-attached structural grid, a background adopts the self-adaptive Cartesian grid, and an interface between the boundary layer grid and the self-adaptive Cartesian grid is processed through an overlapping technology, so that full-field automatic grid generation and simulation calculation are realized.
A further embodiment of the present invention further provides a grid generating device based on boundary problem provided in the above embodiment.
Optionally, the second determining module is configured to:
generating a surface discrete grid with the aircraft model according to the aircraft model;
generating a near-wall surface layer grid by adopting a surface layer grid generation algorithm according to the surface discrete grid;
and acquiring the upper top surface discrete grid of the near-wall surface layer grid according to the near-wall surface layer grid.
Optionally, the third determining module is configured to:
acquiring adaptive Cartesian grid generation parameters, wherein the adaptive Cartesian grid generation parameters at least comprise a maximum encryption layer number, a curvature encryption threshold value and a transition layer number;
and taking the upper top surface discrete grid of the near-wall surface layer grid as a self-adaptive boundary, and generating the self-adaptive Cartesian grid corresponding to the upper top surface discrete grid according to the self-adaptive Cartesian grid generation parameters.
Optionally, the first determining module is configured to:
determining a background Cartesian grid according to preset grid generation parameters, including:
generating a background Cartesian grid according to preset grid generation parameters, wherein the preset grid generation parameters at least comprise: an initial mesh size, the number of meshes in each coordinate direction, and a calculated domain size.
Optionally, the processing module is configured to:
constructing a space bounding box by taking a lattice center of a background Cartesian grid as a center according to the space characteristic size of the background Cartesian grid;
searching structural grid nodes in the space bounding box according to the space bounding box;
calculating a first distance from the structural grid node to a background Cartesian grid core according to the number of the structural grid nodes;
determining a processed grid according to the structural grid nodes, the required number of the contribution units and the first distance;
or (b)
Determining an overlapped grid boundary according to the adaptive Cartesian grid;
determining the logic position of the adaptive Cartesian grid intersection unit where the structural grid node is positioned according to the overlapped grid boundary;
the intersecting unit is taken as a center, and a neighbor unit corresponding to the intersecting unit is determined according to the full-thread tree data format of the self-adaptive Cartesian grid;
sequentially calculating a second distance between the center of the intersecting unit and the structural grid node according to the number of the neighbor units;
and determining the processed grid according to the second distance, the number of neighbor units and the required number of contribution units.
Optionally, the computing module is configured to:
based on the background Cartesian grid and the incoming flow parameters, the Navier-Stokes equation or the Euler equation is solved, the computer hydrodynamic numerical calculation is carried out, and the initial flow field information at the current moment is obtained after convergence.
Optionally, the adjusting module is configured to:
adjusting the grid of the boundary layer according to the motion parameters, and obtaining the change information of the grid position of the top surface on the boundary layer;
adjusting the external Cartesian grid according to the change information of the grid position of the top surface on the auxiliary surface layer;
and performing flow field calculation on the updated Cartesian grid.
For the device embodiments, since they are substantially similar to the method embodiments, the description is relatively simple, and reference is made to the description of the method embodiments for relevant points.
According to the grid generating device based on the boundary problem, the background Cartesian grid is determined according to the preset grid generating parameters; determining a near-wall boundary layer grid of the aircraft according to the aircraft model; determining a self-adaptive Cartesian grid corresponding to the near-wall surface layer grid according to the near-wall surface layer grid; according to the self-adaptive Cartesian grid and the boundary layer grid, performing grid processing by adopting an overlapping algorithm or a contribution unit method to obtain a processed grid; based on a flow control equation, performing simulation calculation on the processed grid to obtain initial flow field information; according to the initial flow field information, grid adjustment is carried out on boundary motion of an aircraft, the embodiment of the application is realized through an automatic generation technology of boundary layer grids and a self-adaptive Cartesian grid technology, the boundary layer adopts a body-attached structural grid, a background adopts the self-adaptive Cartesian grid, and an interface between the boundary layer grid and the self-adaptive Cartesian grid is processed through an overlapping technology, so that full-field automatic grid generation and simulation calculation are realized.
Still another embodiment of the present invention provides a terminal device, configured to perform the boundary problem-based mesh generation method provided in the foregoing embodiment.
Fig. 8 is a schematic structural view of a terminal device of the present invention, as shown in fig. 8, the terminal device comprising: at least one processor 801 and memory 802;
the memory stores a computer program; the at least one processor executes the computer program stored in the memory to implement the boundary problem-based grid generation method provided by the above embodiments.
The terminal equipment provided by the embodiment determines a background Cartesian grid through generating parameters according to a preset grid; determining a near-wall boundary layer grid of the aircraft according to the aircraft model; determining a self-adaptive Cartesian grid corresponding to the near-wall surface layer grid according to the near-wall surface layer grid; according to the self-adaptive Cartesian grid and the boundary layer grid, performing grid processing by adopting an overlapping algorithm or a contribution unit method to obtain a processed grid; based on a flow control equation, performing simulation calculation on the processed grid to obtain initial flow field information; according to the initial flow field information, grid adjustment is carried out on boundary motion of an aircraft, the embodiment of the application is realized through an automatic generation technology of boundary layer grids and a self-adaptive Cartesian grid technology, the boundary layer adopts a body-attached structural grid, a background adopts the self-adaptive Cartesian grid, and an interface between the boundary layer grid and the self-adaptive Cartesian grid is processed through an overlapping technology, so that full-field automatic grid generation and simulation calculation are realized.
Yet another embodiment of the present application provides a computer readable storage medium having a computer program stored therein, which when executed implements the boundary problem-based grid generating method provided in any of the above embodiments.
According to the computer-readable storage medium of the present embodiment, a background Cartesian grid is determined by generating parameters according to a preset grid; determining a near-wall boundary layer grid of the aircraft according to the aircraft model; determining a self-adaptive Cartesian grid corresponding to the near-wall surface layer grid according to the near-wall surface layer grid; according to the self-adaptive Cartesian grid and the boundary layer grid, performing grid processing by adopting an overlapping algorithm or a contribution unit method to obtain a processed grid; based on a flow control equation, performing simulation calculation on the processed grid to obtain initial flow field information; according to the initial flow field information, grid adjustment is carried out on boundary motion of an aircraft, the embodiment of the application is realized through an automatic generation technology of boundary layer grids and a self-adaptive Cartesian grid technology, the boundary layer adopts a body-attached structural grid, a background adopts the self-adaptive Cartesian grid, and an interface between the boundary layer grid and the self-adaptive Cartesian grid is processed through an overlapping technology, so that full-field automatic grid generation and simulation calculation are realized.
It should be noted that the foregoing detailed description is exemplary and is intended to provide further explanation of the invention. Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments in accordance with the present application. As used herein, the singular is intended to include the plural unless the context clearly indicates otherwise. Furthermore, it will be further understood that the terms "comprises" and/or "comprising," when used in this specification, specify the presence of stated features, steps, operations, devices, components, and/or groups thereof.
It should be noted that the terms "first," "second," and the like in the description and claims of the present application and the above figures are used for distinguishing between similar objects and not necessarily for describing a particular sequential or chronological order. It is to be understood that the terms so used are interchangeable under appropriate circumstances such that the embodiments of the application described herein are capable of operation in sequences other than those illustrated or otherwise described herein.
Furthermore, the terms "comprise" and "have," as well as any variations thereof, are intended to cover a non-exclusive inclusion. For example, a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those elements but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.
Spatially relative terms, such as "above … …," "above … …," "upper surface at … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial location relative to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "above" or "over" other devices or structures would then be oriented "below" or "beneath" the other devices or structures. Thus, the exemplary term "above … …" may include both orientations of "above … …" and "below … …". The device may also be positioned in other different ways, such as rotated 90 degrees or at other orientations, and the spatially relative descriptors used herein interpreted accordingly.
In the above detailed description, reference is made to the accompanying drawings, which form a part hereof. In the drawings, like numerals typically identify like components unless context indicates otherwise. The illustrated embodiments described in the detailed description, drawings, and claims are not meant to be limiting. Other embodiments may be utilized, and other changes may be made, without departing from the spirit or scope of the subject matter presented herein.
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A method for generating a grid based on a boundary problem, the method comprising:
determining a background Cartesian grid according to preset grid generation parameters;
determining a near-wall boundary layer grid of the aircraft according to the aircraft model;
determining a self-adaptive Cartesian grid corresponding to the near-wall surface layer grid according to the near-wall surface layer grid;
According to the self-adaptive Cartesian grid and the boundary layer grid, performing grid processing by adopting an overlapping algorithm or a contribution unit method to obtain a processed grid;
based on a flow control equation, performing simulation calculation on the processed grid to obtain initial flow field information;
and according to the initial flow field information, carrying out grid adjustment on the boundary motion of the aircraft.
2. The method of claim 1, wherein determining a near-wall attachment layer grid of an aircraft from an aircraft model comprises:
generating a surface discrete grid with an aircraft model according to the aircraft model;
generating a near-wall surface layer grid by adopting a surface layer grid generation algorithm according to the surface discrete grid;
and acquiring an upper top surface discrete grid of the near-wall surface layer grid according to the near-wall surface layer grid.
3. The method of claim 2, wherein the determining an adaptive cartesian grid corresponding to the near-wall boundary layer grid from the near-wall boundary layer grid comprises:
acquiring adaptive Cartesian grid generation parameters, wherein the adaptive Cartesian grid generation parameters at least comprise a maximum encryption layer number, a curvature encryption threshold value and a transition layer number;
And taking the upper top surface discrete grid of the near-wall surface layer grid as an adaptive boundary, and generating an adaptive Cartesian grid corresponding to the upper top surface discrete grid according to the adaptive Cartesian grid generation parameters.
4. The method of claim 1, wherein determining a background cartesian grid from preset grid generation parameters comprises:
generating a background Cartesian grid according to preset grid generation parameters, wherein the preset grid generation parameters at least comprise: an initial mesh size, the number of meshes in each coordinate direction, and a calculated domain size.
5. The method of claim 4, wherein the performing grid processing according to the adaptive cartesian grid and the boundary layer grid by using an overlap algorithm or a contribution unit method to obtain a processed grid comprises:
constructing a space bounding box by taking a lattice center of a background Cartesian grid as a center according to the space characteristic size of the background Cartesian grid;
searching structural grid nodes in the space bounding box according to the space bounding box;
calculating a first distance from the structural grid node to the background Cartesian grid core according to the number of the structural grid nodes;
Determining the processed grid according to the structural grid nodes, the required number of contribution units and the first distance;
or according to the adaptive Cartesian grid and the boundary layer grid, performing grid processing by adopting an overlapping algorithm or a contribution unit method to obtain a processed grid, including:
determining an overlapped grid boundary according to the adaptive Cartesian grid;
determining the logic position of the adaptive Cartesian grid intersection unit where the structural grid node is positioned according to the overlapped grid boundary;
the intersecting unit is taken as a center, and a neighbor unit corresponding to the intersecting unit is determined according to the full-thread tree data format of the self-adaptive Cartesian grid;
sequentially calculating a second distance between the center of the intersecting unit and the structural grid node according to the number of the neighbor units;
and determining the processed grid according to the second distance, the number of neighbor units and the required number of contribution units.
6. The method of claim 1, wherein performing a simulation calculation on the processed mesh based on a flow control equation to obtain initial flow field information comprises:
based on the background Cartesian grid and the incoming flow parameters, the Navier-Stokes equation or the Euler equation is solved, the computer hydrodynamic numerical calculation is carried out, and the initial flow field information at the current moment is obtained after convergence.
7. The method of claim 1, wherein said mesh adjusting boundary motion of the aircraft based on said initial flow field information comprises:
adjusting the grid of the boundary layer according to the motion parameters, and obtaining the change information of the grid position of the top surface on the boundary layer;
adjusting an external Cartesian grid according to the change information of the grid position of the top surface on the boundary layer;
and performing flow field calculation on the updated Cartesian grid.
8. A boundary problem-based mesh generation apparatus, the apparatus comprising:
the first determining module is used for determining a background Cartesian grid according to preset grid generation parameters;
the second determining module is used for determining a near-wall boundary layer grid of the aircraft according to the aircraft model;
the third determining module is used for determining an adaptive Cartesian grid corresponding to the near-wall surface layer grid according to the near-wall surface layer grid;
the processing module is used for carrying out grid processing by adopting an overlapping algorithm or a contribution unit method according to the self-adaptive Cartesian grid and the boundary layer grid to obtain a processed grid; based on a flow control equation, performing simulation calculation on the processed grid to obtain initial flow field information;
And the adjusting module is used for carrying out grid adjustment on the boundary motion of the aircraft according to the initial flow field information.
9. A terminal device, comprising: at least one processor and memory;
the memory stores a computer program; the at least one processor executing the computer program stored by the memory to implement the boundary problem-based grid generation method of any one of claims 1-7.
10. A computer readable storage medium, characterized in that the computer readable storage medium has stored therein a computer program which, when executed, implements the boundary problem based grid generation method of any of claims 1-7.
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