An aircraft grid generation method, device and equipment based on conformal mapping and topological segmentation and a storage medium
By using conformal mapping and topology segmentation, and leveraging Ricci flow and topology segmentation algorithms to generate aircraft meshes, the problem of uneven mesh density in local regions is solved, improving generation efficiency and simulation accuracy, and enhancing the user experience.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
- Filing Date
- 2026-03-17
- Publication Date
- 2026-05-19
AI Technical Summary
Existing technologies struggle to generate uniformly high-quality meshes for aircraft based on conformal mapping, especially when dealing with extremely complex geometric or non-manifold topological models, where uneven mesh density in local areas affects simulation accuracy.
By employing conformal mapping and topological segmentation, the surface unstructured mesh is mapped to the parameter domain space through Ricci flow. The compression ratio is determined, contour lines are extracted, and discrete points are inserted using spatial partitioning and topological segmentation algorithms to perform one-dimensional boundary restoration and generate a high-quality mesh.
It improves the efficiency of aircraft mesh generation, enhances mesh quality and simulation accuracy, and improves user experience.
Smart Images
Figure CN121881918B_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of computational fluid dynamics, and in particular to a method, apparatus, device, and storage medium for generating aircraft meshes based on conformal mapping and topology segmentation. Background Technology
[0002] Currently, in the field of Computer-Aided Engineering (CAE), transforming complex 3D surfaces into high-quality computational meshes is the cornerstone of numerical simulation. Among these methods, parametric methods based on conformal mapping are considered ideal mathematical tools for generating high-quality meshes because they preserve angles and minimize local shape distortions. The standard procedure is as follows: conformally map the surface to a simple parameter domain, generate a regular mesh on the parameter domain, and then map it back to the 3D surface.
[0003] However, the conformal mapping's "conformal" property is a double-edged sword. It does not preserve area. For industrial models with complex geometry (such as slender branches, sharp concave areas, and high curvature variations), global conformal mapping often produces extreme area compression or stretching in local regions. A uniform mesh in the parameter domain, after being mapped back to a 3D surface, becomes abnormally sparse in these compressed regions and overly dense in stretched regions, leading to a sharp decrease in mesh element quality (such as the Jacobian condition number and interior angles), failing to meet the stringent mesh quality requirements of finite element analysis. This problem of local distortion destroying overall quality is the core bottleneck hindering the technology from moving from theory to engineering practice. In other words, when dealing with models with extremely high geometric complexity or non-manifold topology, existing technologies may struggle to generate uniformly high-quality parameterized results using simple global conformal mapping. While conformal mapping preserves angles, it can produce significant area distortion, causing a uniformly dense mesh in the parameter domain to become overly sparse in severely compressed regions and overly dense in stretched regions after being mapped back to a surface, thus affecting overall mesh quality and subsequent simulation accuracy.
[0004] As can be seen from the above, how to improve the efficiency of generating aircraft meshes in the process of generating aircraft meshes based on conformal mapping and topology segmentation is an urgent problem to be solved. Summary of the Invention
[0005] In view of this, the purpose of this invention is to provide a method, apparatus, device, and storage medium for generating aircraft meshes based on conformal mapping and topology partitioning, which can improve the efficiency of generating aircraft meshes during the process of generating aircraft meshes based on conformal mapping and topology partitioning. The specific solution is as follows:
[0006] In a first aspect, this application provides a method for generating aircraft meshes based on conformal mapping and topology segmentation, including:
[0007] The current surface unstructured mesh is generated based on the preset surface mesh generation parameters and the aircraft model file. The current surface unstructured mesh is conformally mapped to the parameter domain space using Ricci flow to obtain the current parameter domain planar mesh. Then, the current compression ratio between the current surface unstructured mesh and the current parameter domain planar mesh is determined.
[0008] Determine whether the current compression ratio is less than a first preset threshold. If it is less, extract the current contour line corresponding to a second preset threshold. The first preset threshold is less than the second preset threshold.
[0009] A preset spatial partitioning algorithm is used to determine the current triangular mesh corresponding to each discrete point in the current contour line in the current parameter domain plane mesh, so as to determine the current positional relationship between the current triangular mesh and the discrete point, including vertex distance and edge distance;
[0010] Using a preset topology segmentation algorithm and based on the current positional relationship, each discrete point is inserted into the current parameter domain planar grid to obtain the current inserted grid. A one-dimensional boundary recovery operation is then performed on the current inserted grid to obtain the current closed internal boundary. The current region is then determined based on the current closed internal boundary and the current parameter domain planar grid.
[0011] The current region is inversely mapped to the three-dimensional surface space to obtain a new current surface unstructured mesh, and then the process jumps back to the step of conformally mapping the current surface unstructured mesh to the parameter domain space using Ricci flow until the current compression ratio is greater than the first preset threshold, and the current parameter domain planar mesh is set as the target aircraft mesh.
[0012] Optionally, the step of generating a current unstructured surface mesh based on preset surface mesh generation parameters and an aircraft model file, conformally mapping the current unstructured surface mesh to the parameter domain space using Ricci flow to obtain a current parameter domain planar mesh, and then determining the current compression ratio between the current unstructured surface mesh and the current parameter domain planar mesh includes:
[0013] Obtain the model geometry file corresponding to the aircraft, and perform surface discretization processing on the model geometry file based on preset surface mesh generation parameters to generate the current surface unstructured mesh corresponding to the surface of the aircraft; wherein, the surface mesh generation parameters include global target size and curvature adaptive angle;
[0014] While keeping the local angular relationship unchanged, the current surface unstructured mesh is mapped to the parameter domain space using Ricci flow to obtain the corresponding current parameter domain planar mesh, and the first geometric metric of the current surface unstructured mesh and the second geometric metric of the current parameter domain planar mesh are used.
[0015] Based on the first geometric metric and the second geometric metric, metric change information is determined, and a compression ratio scalar field is determined in the parameter domain space to determine the current compression ratio based on the compression ratio scalar field and the metric change information; the current compression ratio is used to evaluate the conformal properties and geometric distortion of the parameter domain planar mesh.
[0016] Optionally, determining whether the current compression ratio is less than a first preset threshold, and if so, extracting the current contour line corresponding to a second preset threshold, includes:
[0017] Determine whether the current compression ratio is less than a first preset threshold. If the current compression ratio is less than the first preset threshold, determine a second preset threshold and extract the current contour line corresponding to the second preset threshold in the compression ratio scalar field. The second preset threshold is used to define a closed boundary that is less than the first preset threshold.
[0018] Each discrete point in the current contour line is stored as a discrete point sequence; the discrete point sequence is used to define the internal boundary located on the parameter domain plane grid; the region corresponding to the internal boundary is the region that satisfies the preset severe distortion condition.
[0019] Optionally, the step of using a preset spatial partitioning algorithm to determine the current triangular mesh corresponding to each discrete point in the current contour line within the current parameter domain planar mesh, and to determine the current positional relationship between the current triangular mesh and the discrete points, including vertex distance and edge distance, includes:
[0020] Using a preset spatial partitioning algorithm, each discrete point in the discrete point sequence is located in the parameter domain plane grid, and a triangular cell that satisfies the preset spatial position condition for each discrete point is set as the current triangular grid corresponding to the discrete point.
[0021] Determine the Euclidean distances between the three vertices of the current triangular mesh and the discrete point, and set the distance with the smallest value among the determined Euclidean distances as the minimum vertex distance;
[0022] Determine the perpendicular distances between the three sides of the current triangular mesh and the discrete points, and set the distance with the smallest value among the perpendicular distances as the minimum side distance;
[0023] The current positional relationship between the current triangular mesh and the discrete point is determined based on the minimum vertex distance and the minimum side distance.
[0024] Optionally, the step of using a preset topological segmentation algorithm and inserting each discrete point into the current parameter domain planar grid based on the current positional relationship to obtain the current inserted grid, and performing a one-dimensional boundary restoration operation on the current inserted grid to obtain the current closed internal boundary, so as to determine the current region based on the current closed internal boundary and the current parameter domain planar grid, includes:
[0025] The minimum vertex distance and minimum edge distance in the current position relationship are determined using a preset topology segmentation algorithm, and it is determined whether the minimum vertex distance is greater than a preset vertex distance threshold. If the minimum vertex distance is greater than the preset vertex distance threshold, it is determined whether the minimum edge distance is greater than a preset edge distance threshold.
[0026] If the minimum edge distance is greater than the preset edge distance threshold, then predict the minimum interior angle of several new triangles generated after inserting the discrete point into the current parameter domain plane grid, and determine whether the minimum interior angle is less than the preset angle threshold. If it is not less than the preset angle threshold, then set the discrete point as a new vertex and add it to the current parameter domain plane grid, delete the current triangle grid corresponding to the discrete point, and then create several new triangles based on the discrete point to update the topological adjacency relationship of the current parameter domain plane grid to obtain the current inserted grid.
[0027] A one-dimensional boundary recovery operation is performed on the currently inserted mesh to obtain the current closed internal boundary. Then, the current region is determined based on the current closed internal boundary and the current parameter domain planar mesh. The current closed internal boundary is the closed boundary that is topologically connected and closed by the discrete point sequence.
[0028] Optionally, the step of using a preset topology segmentation algorithm and inserting each discrete point into the current parameter domain plane grid based on the current positional relationship to obtain the currently inserted grid includes:
[0029] Determine whether the minimum vertex distance is less than the preset vertex distance threshold. If the minimum vertex distance is less than the preset vertex distance threshold, construct a first neighborhood triangle set based on each current triangle mesh corresponding to the discrete point, and determine the first minimum angle corresponding to each current triangle mesh in the first neighborhood triangle set.
[0030] The vertex corresponding to the minimum vertex distance is determined, and the coordinates of the vertex are updated to the coordinates of the discrete point to obtain the second neighborhood triangle set. Then, the second minimum angle corresponding to each current triangle grid in the second neighborhood triangle set is determined.
[0031] Determine the difference between the first minimum angle and the second minimum angle, and determine whether the difference is greater than a preset threshold. If the difference is not greater than the preset threshold, then determine the current inserted grid based on the second neighborhood triangle set.
[0032] If the difference is greater than the preset threshold, then the step of updating the coordinates corresponding to the vertex to the coordinates corresponding to the discrete point is prohibited.
[0033] Optionally, the step of using a preset topology segmentation algorithm and inserting each discrete point into the current parameter domain plane grid based on the current positional relationship to obtain the currently inserted grid includes:
[0034] Determine whether the minimum edge distance is less than a preset edge distance threshold. If the minimum edge distance is less than the preset edge distance threshold, determine whether the edge is an internal edge of the grid. If the edge is an internal edge of the grid, determine two associated triangular grids associated with the edge. If the edge is not an internal edge of the grid, determine one associated triangular grid associated with the edge.
[0035] Based on the coordinate position of the discrete point or the midpoint position of the edge, the edge is divided into a first edge to be processed and a second edge to be processed, and the associated triangular mesh is deleted. Then, a new triangular mesh corresponding to the edge is created to obtain the mesh to be updated. Based on the adjacency relationship of the meshes in the mesh to be updated, the mesh after the current insertion is obtained.
[0036] Secondly, this application provides an aircraft mesh generation device based on conformal mapping and topology segmentation, comprising:
[0037] The compression ratio determination module is used to generate the current surface unstructured mesh based on preset surface mesh generation parameters and aircraft model file, and to conformally map the current surface unstructured mesh to the parameter domain space using Ricci flow to obtain the current parameter domain planar mesh, and then determine the current compression ratio between the current surface unstructured mesh and the current parameter domain planar mesh.
[0038] The contour extraction module is used to determine whether the current compression ratio is less than a first preset threshold. If it is less, the current contour line corresponding to the second preset threshold is extracted. The first preset threshold is less than the second preset threshold.
[0039] The positional relationship determination module is used to determine the current triangular mesh corresponding to each discrete point in the current contour line in the current parameter domain plane mesh using a preset spatial partitioning algorithm, so as to determine the current positional relationship between the current triangular mesh and the discrete point, including vertex distance and edge distance.
[0040] The closed internal boundary determination module is used to insert each discrete point into the current parameter domain plane grid based on the current positional relationship using a preset topology segmentation algorithm to obtain the current inserted grid, and to perform a one-dimensional boundary recovery operation on the current inserted grid to obtain the current closed internal boundary, so as to determine the current region based on the current closed internal boundary and the current parameter domain plane grid.
[0041] The aircraft mesh generation module is used to inversely map the current region to a three-dimensional surface space to obtain a new current surface unstructured mesh, and then jump back to the step of conformally mapping the current surface unstructured mesh to the parameter domain space using Ricci flow, until the current compression ratio is greater than the first preset threshold, and set the current parameter domain planar mesh as the target aircraft mesh.
[0042] Thirdly, this application provides an electronic device, comprising:
[0043] Memory, used to store computer programs;
[0044] A processor is used to execute the computer program to implement the aforementioned method for generating aircraft meshes based on conformal mapping and topology segmentation.
[0045] Fourthly, this application provides a computer-readable storage medium for storing a computer program, wherein the computer program, when executed by a processor, implements the aforementioned method for generating aircraft meshes based on conformal mapping and topology segmentation.
[0046] As can be seen from the above, before generating the aircraft mesh based on conformal mapping and topological segmentation, this application needs to generate the current surface unstructured mesh based on preset surface mesh generation parameters and the aircraft model file, and then use Ricci flow to conformally map the current surface unstructured mesh to the parameter domain space to obtain the current parameter domain planar mesh. Next, the current compression ratio between the current surface unstructured mesh and the current parameter domain planar mesh is determined; it is then determined whether the current compression ratio is less than a first preset threshold. If it is less, the current contour lines corresponding to a second preset threshold are extracted; the first preset threshold is less than the second preset threshold; a preset spatial partitioning algorithm is used to determine the current triangular mesh corresponding to each discrete point in the current contour lines within the current parameter domain planar mesh, in order to ensure... Define the current positional relationship between the current triangular mesh and discrete points, including vertex distance and edge distance; use a preset topological segmentation algorithm and based on the current positional relationship to insert each discrete point into the current parameter domain planar mesh to obtain the current inserted mesh, and perform a one-dimensional boundary recovery operation on the current inserted mesh to obtain the current closed internal boundary, and determine the current region based on the current closed internal boundary and the current parameter domain planar mesh; inversely map the current region to the three-dimensional surface space to obtain a new current surface unstructured mesh, and jump back to the step of conformally mapping the current surface unstructured mesh to the parameter domain space using Ricci flow, until the current compression ratio is greater than the first preset threshold, and set the current parameter domain planar mesh as the target aircraft mesh.
[0047] Therefore, this application first needs to generate the current unstructured surface mesh based on preset surface mesh generation parameters and the aircraft model file, and then use Ricci flow to conformally map the current unstructured surface mesh to the parameter domain space to obtain the current parameter domain planar mesh. Next, it determines the current compression ratio between the current unstructured surface mesh and the current parameter domain planar mesh. Then, it determines whether the current compression ratio is less than a first preset threshold; if it is, it extracts the current contour lines corresponding to a second preset threshold. Finally, it uses a preset spatial partitioning algorithm to determine the current triangular mesh corresponding to each discrete point in the current parameter domain planar mesh and the current contour lines, thus determining the relationship between the current triangular mesh and the discrete points, including vertices. The algorithm first establishes the current positional relationship between distance and edge distance. Then, using a preset topology segmentation algorithm and based on the current positional relationship, each discrete point is inserted into the current parameter domain planar mesh to obtain the inserted mesh. A one-dimensional boundary restoration operation is then performed on the inserted mesh to obtain the current closed internal boundary. The current region is determined based on the current closed internal boundary and the current parameter domain planar mesh. Next, the current region is inversely mapped to the three-dimensional surface space to obtain a new current unstructured surface mesh. The process then jumps back to the step of conformally mapping the current unstructured surface mesh to the parameter domain space using Ricci flow, until the current compression ratio exceeds a first preset threshold. Finally, the current parameter domain planar mesh is set as the target aircraft mesh. This improves the efficiency of aircraft mesh generation during the conformal mapping and topology segmentation-based aircraft mesh generation process, thereby enhancing the user experience. Attached Figure Description
[0048] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.
[0049] Figure 1 This is a flowchart of an aircraft mesh generation method based on conformal mapping and topology segmentation disclosed in this application;
[0050] Figure 2 This is a schematic diagram of the structure of an aircraft mesh generation device based on conformal mapping and topology segmentation disclosed in this application;
[0051] Figure 3 This is a structural diagram of an electronic device disclosed in this application. Detailed Implementation
[0052] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.
[0053] Currently, when dealing with models with extremely high geometric complexity or non-manifold topology, simple global conformal mapping may struggle to generate uniformly high-quality parameterized results. While conformal mapping preserves the geometry, it can introduce significant area distortion. This results in a mesh that is too sparse in areas with severely compressed areas and too dense in areas with stretched areas after being mapped back to the surface, thus affecting the overall mesh quality and subsequent simulation accuracy. To address this, this application provides a method for generating aircraft meshes based on conformal mapping and topology segmentation, which can improve the efficiency of generating aircraft meshes in the process of generating aircraft meshes based on conformal mapping and topology segmentation.
[0054] See Figure 1 As shown in the figure, this invention discloses a method for generating aircraft meshes based on conformal mapping and topology segmentation, including:
[0055] Step S11: Generate the current surface unstructured mesh based on the preset surface mesh generation parameters and the aircraft model file, and use the Ricci flow to conformally map the current surface unstructured mesh to the parameter domain space to obtain the current parameter domain planar mesh. Then, determine the current compression ratio between the current surface unstructured mesh and the current parameter domain planar mesh.
[0056] In this embodiment, the present application requires reading the igs (Initial Graphics Exchange Specification) digital model information and generating an unstructured mesh based on the parameters. In one specific implementation, the present application first reads the CAD digital model igs file, then sets the surface mesh generation parameters (such as global target size, curvature adaptive angle, etc.) to generate the surface unstructured mesh M; subsequently, the conformal compression ratio is extracted: the mesh M is mapped to the parameter domain space using discrete Ricci flow conformal mapping to obtain the parameter domain plane N, and then the change in mesh metric before and after parameterization, dif, is calculated. Specifically, the step of generating a current surface unstructured mesh based on preset surface mesh generation parameters and an aircraft model file, and conformally mapping the current surface unstructured mesh to the parameter domain space using Ricci flow to obtain a current parameter domain planar mesh, and then determining the current compression ratio between the current surface unstructured mesh and the current parameter domain planar mesh, may include: obtaining a model geometry file corresponding to the aircraft, and performing surface discretization processing on the model geometry file based on preset surface mesh generation parameters to generate a current surface unstructured mesh corresponding to the surface of the aircraft; wherein, the surface mesh generation parameters include a global target size. With curvature adaptive angle; while maintaining the local angular relationship unchanged, the current surface unstructured mesh is mapped to the parameter domain space using Ricci flow to obtain the corresponding current parameter domain planar mesh, and based on the first geometric metric of the current surface unstructured mesh and the second geometric metric of the current parameter domain planar mesh; based on the first geometric metric and the second geometric metric, metric change information is determined, and a compression ratio scalar field is determined in the parameter domain space, so as to determine the current compression ratio based on the compression ratio scalar field and the metric change information; the current compression ratio is used to evaluate the conformal properties and geometric distortion degree of the parameter domain planar mesh.
[0057] Step S12: Determine whether the current compression ratio is less than the first preset threshold. If it is less, extract the current contour line corresponding to the second preset threshold. The first preset threshold is less than the second preset threshold.
[0058] In this embodiment, the present application embodiment needs to extract contour lines, that is, a continuous "compression ratio" scalar field is defined over the entire parameter domain based on the obtained current compression ratio. Furthermore, in order to locate extreme distortion regions, the present application embodiment extracts contour lines with specific thresholds in the parameter domain compression ratio field.
[0059] In one specific implementation, when the compression ratio is lower than At that time, this region was considered a "severely distorted region." Furthermore, to obtain a closed, stable boundary, the algorithm searches for a compression ratio from... Change to slightly higher This critical interval, to correspond to The contour lines are extracted. It is worth mentioning that the area inside the contour lines is the lesion area that needs to be "surgeonized". The contour lines are composed of a series of discrete points and are stored as Ei, which defines the "internal boundary" of subsequent segmentation.
[0060] Specifically, determining whether the current compression ratio is less than a first preset threshold, and if so, extracting the current contour line corresponding to a second preset threshold, may include: determining whether the current compression ratio is less than the first preset threshold; if the current compression ratio is less than the first preset threshold, determining the second preset threshold, and extracting the current contour line corresponding to the second preset threshold in the compression ratio scalar field; wherein, the second preset threshold is used to define a closed boundary less than the first preset threshold; storing each discrete point in the current contour line as a discrete point sequence; the discrete point sequence is used to define the internal boundary located on the parameter domain plane grid; the region corresponding to the internal boundary is a region that satisfies a preset severe distortion condition.
[0061] Step S13: Use a preset spatial partitioning algorithm to determine the current triangular mesh corresponding to each discrete point in the current contour line in the current parameter domain plane mesh, so as to determine the current positional relationship between the current triangular mesh and the discrete point, including vertex distance and edge distance.
[0062] In this embodiment, inserting discrete points in Ei into the target mesh N is the core step of topology manipulation. Specifically, based on the positional relationship between the discrete points and the mesh, three cases are handled: "inserting inside a triangle," "splitting mesh edges," and "moving to a mesh vertex," to ensure the integrity and distortion-free topological structure of the mesh after insertion. It is worth noting that before determining the insertion method, this embodiment first completes the position matching and distance calculation between the discrete points and the mesh, providing data for subsequent judgments.
[0063] In one specific implementation, this application embodiment traverses each discrete point (denoted as pt) in Ei, and then quickly locates the nearest grid triangle (denoted as tri) to pt using a spatial partitioning algorithm (such as KD tree), thereby avoiding the inefficiency caused by global traversal; then, vertex distance calculation is performed: calculate the Euclidean distance between the three vertices of tri (denoted as v1, v2, v3) and pt, and take the minimum value as minVDis; edge distance calculation: calculate the shortest distance (i.e., the perpendicular distance from a point to a line segment) between the three edges of tri (denoted as e1, e2, e3) and pt, and take the minimum value as minEDist, which is used to determine whether pt is close to the grid edge.
[0064] Specifically, determining the current triangular mesh corresponding to each discrete point in the current contour line within the current parameter domain planar mesh using a preset spatial partitioning algorithm, and determining the current positional relationship between the current triangular mesh and the discrete points, including vertex distance and edge distance, may include: using the preset spatial partitioning algorithm to locate triangular units that satisfy preset spatial position conditions for each discrete point in the discrete point sequence within the parameter domain planar mesh, and setting the triangular unit as the current triangular mesh corresponding to the discrete point; determining the Euclidean distances between the three vertices of the current triangular mesh and the discrete point, and setting the smallest value among the determined Euclidean distances as the minimum vertex distance; determining the perpendicular distances between the three sides of the current triangular mesh and the discrete point, and setting the smallest value among the perpendicular distances as the minimum edge distance; and determining the current positional relationship between the current triangular mesh and the discrete point based on the minimum vertex distance and the minimum edge distance.
[0065] Step S14: Using a preset topology segmentation algorithm and based on the current positional relationship, insert each discrete point into the current parameter domain plane grid to obtain the current inserted grid. Then, perform a one-dimensional boundary recovery operation on the current inserted grid to obtain the current closed internal boundary. Determine the current region based on the current closed internal boundary and the current parameter domain plane grid.
[0066] In this embodiment, the insertion of each discrete point into the current parameter domain plane grid is divided into the following three cases: Case 1: Insertion point into the interior of a triangle: When pt is neither close to the vertex of tri (minVDis is greater than the preset vertex distance threshold, such as 1 / 10 of the average side length of the grid) nor close to the edge of tri (minEDist is greater than the preset edge distance threshold, such as 1 / 20 of the average side length of the grid), pt is inserted into the interior of tri by default, forming three new sub-triangles. Subsequently, insertion judgment and operation are performed: First, in a specific implementation, the embodiment of this application needs to perform minimum angle verification: Before insertion, the minimum angle of the three new triangles (pt-v1-v2, pt-v2-v3, pt-v3-v1) formed after inserting pt needs to be predicted. If the minimum angle is less than 0.0001 degrees, it means that an extremely narrow, distorted triangle will be generated after insertion, and it is necessary to switch to the "split edge" or "shift point" mode; if the minimum angle is greater than or equal to 0.0001 degrees, perform the insertion operation: add the coordinate information of pt in N, delete the original triangle tri, create three new triangles and update the topological relationship of the mesh (such as the adjacent triangle index and the associated vertices of the edge).
[0067] Specifically, the step of using a preset topology segmentation algorithm and inserting each discrete point into the current parameter domain planar grid based on the current positional relationship to obtain the current inserted grid, and performing a one-dimensional boundary restoration operation on the current inserted grid to obtain the current closed internal boundary, and determining the current region based on the current closed internal boundary and the current parameter domain planar grid, may include: using a preset topology segmentation algorithm to determine the minimum vertex distance and minimum edge distance in the current positional relationship, and determining whether the minimum vertex distance is greater than a preset vertex distance threshold; if the minimum vertex distance is greater than the preset vertex distance threshold, then determining whether the minimum edge distance is greater than a preset edge distance threshold; if the minimum edge distance is greater than the preset edge distance threshold, then predicting that... The minimum interior angle of several new triangles generated after the discrete point is inserted into the current parameter domain plane grid is determined, and it is determined whether the minimum interior angle is less than a preset angle threshold. If it is not less than the threshold, the discrete point is set as a new vertex and added to the current parameter domain plane grid, and the current triangle grid corresponding to the discrete point is deleted. Then, several new triangles are created based on the discrete point to update the topological adjacency relationship of the current parameter domain plane grid, thus obtaining the current inserted grid. A one-dimensional boundary recovery operation is performed on the current inserted grid to obtain the current closed internal boundary. Then, the current region is determined based on the current closed internal boundary and the current parameter domain plane grid. The current closed internal boundary is the closed boundary that is topologically connected and closed by the discrete point sequence.
[0068] Case 2: Moving a point to a grid vertex: When When the distance is less than the preset vertex distance threshold, it indicates... distance A vertex (denoted as) (Very close, you can try) Point coordinates updated to The coordinates are determined to avoid increasing mesh complexity due to the addition of new vertices. Then, vertex relocation judgment and operation are performed: first, obtain... Neighborhood triangle set of a point (i.e., all containing) (Grid triangle of points); Calculate the set before moving points. The smallest angle of all triangles in the triangle is denoted as . ;Will Point coordinates updated to Then, recalculate the set. The smallest angle of all triangles in the triangle is denoted as . It is worth mentioning that, if and If the difference is greater than a preset threshold (e.g., 0.1 degrees), it indicates that the distortion of the triangle has worsened after the point shifting, so point shifting is not performed; if the difference is less than or equal to the threshold, point shifting is performed and the triangle is updated. Point coordinates and the topological relationships of related triangles.
[0069] Specifically, using a preset topology segmentation algorithm and based on the current positional relationship, inserting each discrete point into the current parameter domain planar grid to obtain the currently inserted grid may include: determining whether the minimum vertex distance is less than a preset vertex distance threshold; if the minimum vertex distance is less than the preset vertex distance threshold, constructing a first neighborhood triangle set based on each current triangle grid corresponding to the discrete point, and determining the first minimum angle corresponding to each current triangle grid in the first neighborhood triangle set; determining the vertex corresponding to the minimum vertex distance, and updating the coordinates of the vertex to the coordinates of the discrete point to obtain a second neighborhood triangle set, and then determining the second minimum angle corresponding to each current triangle grid in the second neighborhood triangle set; determining the difference between the first minimum angle and the second minimum angle, and determining whether the difference is greater than a preset threshold; if the difference is not greater than the preset threshold, determining the currently inserted grid based on the second neighborhood triangle set; if the difference is greater than the preset threshold, then prohibiting the step of updating the coordinates of the vertex to the coordinates of the discrete point.
[0070] Scenario 3: Mesh Edge Splitting: When minEDist is less than the preset edge distance threshold, it indicates that pt is extremely close to an edge (denoted as edge) of tri. The edge needs to be split into two segments, and pt is inserted as a new vertex into the edge. The splitting operation process is as follows: First, identify the associated triangles of the edge, that is, determine the associated triangles corresponding to the edge: if the edge is an internal edge of the mesh, associate two triangles (denoted as tri1 and tri2); if the edge is a mesh boundary edge, associate only one triangle (denoted as tri1). Then, add a new vertex at the midpoint of the edge (or the position corresponding to pt), splitting the original edge into two new edges; delete the original associated triangles (tri1 and tri2), create new triangles, and update the mesh adjacency relationship. Subsequently, perform boundary restoration: After completing the insertion / movement / splitting operations of all points, perform a one-dimensional boundary restoration operation, marking it as a complete and closed internal boundary on the topology.
[0071] Specifically, the step of using a preset topology segmentation algorithm and inserting each discrete point into the current parameter domain planar grid based on the current positional relationship to obtain the current inserted grid may include: determining whether the minimum edge distance is less than a preset edge distance threshold; if the minimum edge distance is less than the preset edge distance threshold, determining whether the edge is an internal edge of the grid; if the edge is an internal edge of the grid, determining two associated triangular grids associated with the edge; if the edge is not an internal edge of the grid, determining one associated triangular grid associated with the edge; segmenting the edge into a first edge to be processed and a second edge to be processed based on the coordinate position of the discrete point or the midpoint position of the edge, deleting the associated triangular grid, and then creating a new triangular grid corresponding to the edge to obtain the grid to be updated, and obtaining the current inserted grid based on the adjacency relationship of the grids in the grid to be updated.
[0072] Step S15: Inverse map the current region to the three-dimensional surface space to obtain a new current surface unstructured mesh, and jump back to the step of conformally mapping the current surface unstructured mesh to the parameter domain space using Ricci flow until the current compression ratio is greater than the first preset threshold, and set the current parameter domain planar mesh as the target aircraft mesh.
[0073] In this embodiment, the present application embodiment needs to include Perform face segmentation, that is, with The resulting boundary acts as a dividing line, dividing the original mesh surface into two regions: the interior... Region and outside The region, then, the region The data is inversely mapped to surface space, then conformally mapped again, and the compression ratio is calculated to generate contour lines. It's worth noting that if the compression ratio exceeds a limit, a new contour line is extracted. Perform point insertion and topology operations, and update the mesh and region partitioning. Repeat the above steps until the compression ratio accuracy is no less than [value missing]. This iterative loop ensures that no dimensional deviations exceed [a certain threshold] in the final generated mesh. This allows for greater geometric and dimensional accuracy in the region as a whole.
[0074] As can be seen from the above, the embodiments of this application first need to generate the current surface unstructured mesh based on preset surface mesh generation parameters and the aircraft model file, and then use Ricci flow to conformally map the current surface unstructured mesh to the parameter domain space to obtain the current parameter domain planar mesh. Then, the current compression ratio between the current surface unstructured mesh and the current parameter domain planar mesh is determined. Next, it is determined whether the current compression ratio is less than a first preset threshold. If it is less, the current contour lines corresponding to the second preset threshold are extracted. Then, a preset spatial partitioning algorithm is used to determine the current triangular mesh corresponding to each discrete point in the current parameter domain planar mesh and the current contour lines, so as to determine the relationship between the current triangular mesh and the discrete points, including the apex. The process begins by determining the current positional relationship between point distances and edge distances. Next, a preset topology segmentation algorithm is used to insert each discrete point into the current parameter domain planar mesh based on the current positional relationship, resulting in the inserted mesh. A one-dimensional boundary restoration operation is then performed on the inserted mesh to obtain the current closed internal boundary. This closed internal boundary and the current parameter domain planar mesh are used to determine the current region. Then, the current region is inversely mapped to a three-dimensional surface space to obtain a new current unstructured surface mesh. The process then jumps back to the step of conformally mapping the current unstructured surface mesh to the parameter domain space using Ricci flow, continuing until the current compression ratio exceeds a first preset threshold. Finally, the current parameter domain planar mesh is set as the target aircraft mesh. This improves the efficiency of aircraft mesh generation during the conformal mapping and topology segmentation process, thereby enhancing the user experience.
[0075] Accordingly, see Figure 2 As shown, this application also provides an aircraft mesh generation device based on conformal mapping and topology segmentation, comprising:
[0076] Compression ratio determination module 11 is used to generate a current surface unstructured mesh based on preset surface mesh generation parameters and aircraft model file, and to conformally map the current surface unstructured mesh to parameter domain space using Ricci flow to obtain a current parameter domain planar mesh, and then determine the current compression ratio between the current surface unstructured mesh and the current parameter domain planar mesh.
[0077] The contour extraction module 12 is used to determine whether the current compression ratio is less than a first preset threshold. If it is less, the current contour line corresponding to the second preset threshold is extracted. The first preset threshold is less than the second preset threshold.
[0078] The position relationship determination module 13 is used to determine the current triangular mesh corresponding to each discrete point in the current contour line in the current parameter domain plane mesh using a preset spatial partitioning algorithm, so as to determine the current position relationship between the current triangular mesh and the discrete point, including vertex distance and edge distance.
[0079] The closed internal boundary determination module 14 is used to insert each of the discrete points into the current parameter domain plane grid based on the current position relationship using a preset topology segmentation algorithm to obtain the current inserted grid, and to perform a one-dimensional boundary recovery operation on the current inserted grid to obtain the current closed internal boundary, so as to determine the current region based on the current closed internal boundary and the current parameter domain plane grid.
[0080] The aircraft mesh generation module 15 is used to inversely map the current region to a three-dimensional surface space to obtain a new current surface unstructured mesh, and then jump back to the step of conformally mapping the current surface unstructured mesh to the parameter domain space using Ricci flow, until the current compression ratio is greater than the first preset threshold, and set the current parameter domain planar mesh as the target aircraft mesh.
[0081] In some specific embodiments, the compression ratio determination module 11 may specifically include:
[0082] The model geometry file determination unit is used to acquire the model geometry file corresponding to the aircraft, and to perform surface discretization processing on the model geometry file based on preset surface mesh generation parameters to generate a current surface unstructured mesh corresponding to the surface of the aircraft; wherein, the surface mesh generation parameters include global target size and curvature adaptive angle;
[0083] The mesh mapping unit is used to map the current surface unstructured mesh to the parameter domain space using Ricci flow while keeping the local angular relationship unchanged, to obtain the corresponding current parameter domain planar mesh, and based on the first geometric metric of the current surface unstructured mesh and the second geometric metric of the current parameter domain planar mesh;
[0084] The metric change information determination unit is used to determine metric change information based on the first geometric metric and the second geometric metric, and to determine a compression ratio scalar field in the parameter domain space, so as to determine the current compression ratio based on the compression ratio scalar field and the metric change information; the current compression ratio is used to evaluate the conformal properties and geometric distortion of the parameter domain planar mesh.
[0085] In some specific embodiments, the contour line extraction module 12 may specifically include:
[0086] The current compression ratio determination unit is used to determine whether the current compression ratio is less than a first preset threshold. If the current compression ratio is less than the first preset threshold, a second preset threshold is determined, and the current contour line corresponding to the second preset threshold is extracted in the compression ratio scalar field. The second preset threshold is used to define a closed boundary that is less than the first preset threshold.
[0087] A discrete point sequence generation unit is used to store each discrete point in the current contour line as a discrete point sequence; the discrete point sequence is used to define the internal boundary located on the parameter domain plane grid; the region corresponding to the internal boundary is a region that satisfies a preset severe distortion condition.
[0088] In some specific embodiments, the positional relationship determination module 13 may specifically include:
[0089] A triangular unit positioning unit is used to locate each discrete point in the discrete point sequence in the parameter domain planar grid using a preset spatial partitioning algorithm and to set the triangular unit as the current triangular grid corresponding to the discrete point;
[0090] The Euclidean distance determination unit is used to determine the Euclidean distances between the three vertices of the current triangular mesh and the discrete points, and to set the distance with the smallest value among the Euclidean distance determination results as the minimum vertex distance;
[0091] A vertical distance determination unit is used to determine the vertical distances between the three sides of the current triangular mesh and the discrete points, and to set the minimum vertical distance among the vertical distances as the minimum side distance;
[0092] The current position relationship determination unit is used to determine the current position relationship between the current triangular mesh and the discrete point based on the minimum vertex distance and the minimum side distance.
[0093] In some specific embodiments, the closed internal boundary determination module 14 may specifically include:
[0094] The vertex distance determination unit is used to determine the minimum vertex distance and the minimum edge distance in the current position relationship using a preset topology segmentation algorithm, and to determine whether the minimum vertex distance is greater than a preset vertex distance threshold. If the minimum vertex distance is greater than the preset vertex distance threshold, then it is determined whether the minimum edge distance is greater than a preset edge distance threshold.
[0095] The minimum interior angle prediction unit is used to predict the minimum interior angle of several new triangles generated after inserting the discrete point into the current parameter domain plane grid if the minimum side distance is greater than the preset side distance threshold, and to determine whether the minimum interior angle is less than the preset angle threshold. If it is not less than the preset angle threshold, the discrete point is set as a new vertex and added to the current parameter domain plane grid, and the current triangle grid corresponding to the discrete point is deleted. Then, several new triangles are created based on the discrete point to update the topological adjacency relationship of the current parameter domain plane grid to obtain the current inserted grid.
[0096] The closed internal boundary determination sub-unit is used to perform a one-dimensional boundary recovery operation on the currently inserted mesh to obtain the current closed internal boundary. Then, the current region is determined based on the current closed internal boundary and the current parameter domain planar mesh. The current closed internal boundary is the closed boundary that is topologically connected and closed by the discrete point sequence.
[0097] In some specific embodiments, the closed internal boundary determination module 14 may specifically include:
[0098] The first neighborhood triangle set determination unit is used to determine whether the minimum vertex distance is less than the preset vertex distance threshold. If the minimum vertex distance is less than the preset vertex distance threshold, then a first neighborhood triangle set is constructed based on each current triangle grid corresponding to the discrete point, and the first minimum angle corresponding to each current triangle grid in the first neighborhood triangle set is determined.
[0099] The second neighborhood triangle set determination unit is used to determine the vertex corresponding to the minimum vertex distance, update the coordinates corresponding to the vertex to the coordinates corresponding to the discrete point, obtain the second neighborhood triangle set, and then determine the second minimum angle corresponding to each current triangle grid in the second neighborhood triangle set;
[0100] The difference generation unit is used to determine the difference between the first minimum angle and the second minimum angle, and to determine whether the difference is greater than a preset threshold. If the difference is not greater than the preset threshold, the current inserted grid is determined based on the second neighborhood triangle set.
[0101] The step-disable triggering unit is used to prevent the step of updating the coordinates corresponding to the vertex to the coordinates corresponding to the discrete point from being triggered if the difference is greater than the preset threshold.
[0102] In some specific embodiments, the closed internal boundary determination module 14 may specifically include:
[0103] An edge determination unit is used to determine whether the minimum edge distance is less than a preset edge distance threshold. If the minimum edge distance is less than the preset edge distance threshold, it determines whether the edge is an internal edge of the grid. If the edge is an internal edge of the grid, it determines two associated triangular grids associated with the edge. If the edge is not an internal edge of the grid, it determines one associated triangular grid associated with the edge.
[0104] The current insertion mesh determination unit is used to divide the edge into a first edge to be processed and a second edge to be processed based on the coordinate position of the discrete point or the midpoint position of the edge, delete the associated triangular mesh, and then create a new triangular mesh corresponding to the edge to obtain the mesh to be updated. Based on the adjacency relationship of the meshes in the mesh to be updated, the current insertion mesh is obtained.
[0105] Furthermore, embodiments of this application also disclose an electronic device, Figure 3 This is a structural diagram of an electronic device 20 according to an exemplary embodiment. The content of the diagram should not be construed as limiting the scope of this application. Specifically, the electronic device 20 may include: at least one processor 21, at least one memory 22, a power supply 23, a communication interface 24, an input / output interface 25, and a communication bus 26. The memory 22 stores a computer program, which is loaded and executed by the processor 21 to implement the relevant steps in the aircraft mesh generation method based on conformal mapping and topology segmentation disclosed in any of the foregoing embodiments. Furthermore, the electronic device 20 in this embodiment may specifically be an electronic computer.
[0106] In this embodiment, the power supply 23 is used to provide operating voltage for each hardware device on the electronic device 20; the communication interface 24 can create a data transmission channel between the electronic device 20 and external devices, and the communication protocol it follows can be any communication protocol applicable to the technical solution of this application, and is not specifically limited here; the input / output interface 25 is used to acquire external input data or output data to the outside world, and its specific interface type can be selected according to specific application needs, and is not specifically limited here.
[0107] In addition, the memory 22, as a carrier for resource storage, can be a read-only memory, random access memory, disk or optical disk, etc. The resources stored thereon can include operating system 221, computer program 222, etc., and the storage method can be temporary storage or permanent storage.
[0108] The operating system 221 is used to manage and control the various hardware devices on the electronic device 20 and the computer program 222, which may be Windows Server, Netware, Unix, Linux, etc. In addition to including a computer program capable of performing the aircraft mesh generation method based on conformal mapping and topology segmentation disclosed in any of the foregoing embodiments, the computer program 222 may further include computer programs capable of performing other specific tasks.
[0109] Furthermore, this application also discloses a computer-readable storage medium for storing a computer program; wherein, when the computer program is executed by a processor, it implements the aforementioned disclosed method for generating aircraft meshes based on conformal mapping and topology segmentation. Specific steps of this method can be found in the corresponding content disclosed in the foregoing embodiments, and will not be repeated here.
[0110] The various embodiments in this specification are described in a progressive manner, with each embodiment focusing on its differences from other embodiments. Similar or identical parts between embodiments can be referred to interchangeably. For the apparatus disclosed in the embodiments, since it corresponds to the method disclosed in the embodiments, the description is relatively simple; relevant parts can be referred to in the method section.
[0111] Those skilled in the art will further recognize that the units and algorithm steps of the various examples described in conjunction with the embodiments disclosed herein can be implemented in electronic hardware, computer software, or a combination of both. To clearly illustrate the interchangeability of hardware and software, the components and steps of the various examples have been generally described in terms of functionality in the foregoing description. Whether these functions are implemented in hardware or software depends on the specific application and design constraints of the technical solution. Those skilled in the art can use different methods to implement the described functions for each specific application, but such implementation should not be considered beyond the scope of this application.
[0112] The steps of the methods or algorithms described in conjunction with the embodiments disclosed herein can be implemented directly by hardware, a software module executed by a processor, or a combination of both. The software module can be located in random access memory (RAM), main memory, read-only memory (ROM), electrically programmable ROM, electrically erasable programmable ROM, registers, hard disk, removable disk, CD-ROM, or any other form of storage medium known in the art.
[0113] Finally, it should be noted that in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.
[0114] The technical solutions provided in this application have been described in detail above. Specific examples have been used to illustrate the principles and implementation methods of this application. The descriptions of the above embodiments are only for the purpose of helping to understand the methods and core ideas of this application. At the same time, for those skilled in the art, there will be changes in the specific implementation methods and application scope based on the ideas of this application. Therefore, the content of this specification should not be construed as a limitation of this application.
Claims
1. A method for generating aircraft meshes based on conformal mapping and topological segmentation, characterized in that, include: The current surface unstructured mesh is generated based on the preset surface mesh generation parameters and the aircraft model file. The current surface unstructured mesh is conformally mapped to the parameter domain space using Ricci flow to obtain the current parameter domain planar mesh. Then, the current compression ratio between the current surface unstructured mesh and the current parameter domain planar mesh is determined. Determine whether the current compression ratio is less than a first preset threshold. If it is less, extract the current contour line corresponding to the second preset threshold. The first preset threshold is less than the second preset threshold; A preset spatial partitioning algorithm is used to determine the current triangular mesh corresponding to each discrete point in the current contour line in the current parameter domain plane mesh, so as to determine the current positional relationship between the current triangular mesh and the discrete point, including vertex distance and edge distance; Using a preset topology segmentation algorithm and based on the current positional relationship, each discrete point is inserted into the current parameter domain planar grid to obtain the current inserted grid. A one-dimensional boundary recovery operation is then performed on the current inserted grid to obtain the current closed internal boundary. The current region is then determined based on the current closed internal boundary and the current parameter domain planar grid. The current region is inversely mapped to the three-dimensional surface space to obtain a new current surface unstructured mesh, and then the process jumps back to the step of conformally mapping the current surface unstructured mesh to the parameter domain space using Ricci flow until the current compression ratio is greater than the first preset threshold, and the current parameter domain planar mesh is set as the target aircraft mesh.
2. The aircraft mesh generation method based on conformal mapping and topology segmentation according to claim 1, characterized in that, The process involves generating a current unstructured surface mesh based on preset surface mesh generation parameters and an aircraft model file, conformally mapping the current unstructured surface mesh to the parameter domain space using Ricci flow to obtain a current parameter domain planar mesh, and then determining the current compression ratio between the current unstructured surface mesh and the current parameter domain planar mesh, including: Obtain the model geometry file corresponding to the aircraft, and perform surface discretization processing on the model geometry file based on preset surface mesh generation parameters to generate the current surface unstructured mesh corresponding to the surface of the aircraft; wherein, the surface mesh generation parameters include global target size and curvature adaptive angle; While keeping the local angular relationship unchanged, the current surface unstructured mesh is mapped to the parameter domain space using Ricci flow to obtain the corresponding current parameter domain planar mesh, and the first geometric metric of the current surface unstructured mesh and the second geometric metric of the current parameter domain planar mesh are used. Based on the first geometric metric and the second geometric metric, metric change information is determined, and a compression ratio scalar field is determined in the parameter domain space to determine the current compression ratio based on the compression ratio scalar field and the metric change information; the current compression ratio is used to evaluate the conformal properties and geometric distortion of the parameter domain planar mesh.
3. The aircraft mesh generation method based on conformal mapping and topology segmentation according to claim 2, characterized in that, The step of determining whether the current compression ratio is less than a first preset threshold, and if so, extracting the current contour line corresponding to a second preset threshold, includes: Determine whether the current compression ratio is less than a first preset threshold. If the current compression ratio is less than the first preset threshold, determine a second preset threshold and extract the current contour line corresponding to the second preset threshold in the compression ratio scalar field. The second preset threshold is used to define a closed boundary that is less than the first preset threshold. Each discrete point in the current contour line is stored as a discrete point sequence; the discrete point sequence is used to define the internal boundary located on the parameter domain plane grid; the region corresponding to the internal boundary is the region that satisfies the preset severe distortion condition.
4. The aircraft mesh generation method based on conformal mapping and topology segmentation according to claim 3, characterized in that, The step of determining the current triangular mesh corresponding to each discrete point in the current contour line within the current parameter domain planar mesh using a preset spatial partitioning algorithm, and determining the current positional relationship between the current triangular mesh and the discrete points, including vertex distance and edge distance, includes: Using a preset spatial partitioning algorithm, each discrete point in the discrete point sequence is located in the parameter domain plane grid, and a triangular cell that satisfies the preset spatial position condition for each discrete point is set as the current triangular grid corresponding to the discrete point. Determine the Euclidean distances between the three vertices of the current triangular mesh and the discrete point, and set the distance with the smallest value among the determined Euclidean distances as the minimum vertex distance; Determine the perpendicular distances between the three sides of the current triangular mesh and the discrete points, and set the distance with the smallest value among the perpendicular distances as the minimum side distance; The current positional relationship between the current triangular mesh and the discrete point is determined based on the minimum vertex distance and the minimum side distance.
5. The aircraft mesh generation method based on conformal mapping and topology segmentation according to claim 4, characterized in that, The process of inserting each discrete point into the current parameter domain planar grid using a preset topology segmentation algorithm and based on the current positional relationship to obtain the current inserted grid, and performing a one-dimensional boundary restoration operation on the current inserted grid to obtain the current closed internal boundary, and determining the current region based on the current closed internal boundary and the current parameter domain planar grid, includes: The minimum vertex distance and minimum edge distance in the current position relationship are determined using a preset topology segmentation algorithm, and it is determined whether the minimum vertex distance is greater than a preset vertex distance threshold. If the minimum vertex distance is greater than the preset vertex distance threshold, it is determined whether the minimum edge distance is greater than a preset edge distance threshold. If the minimum edge distance is greater than the preset edge distance threshold, then predict the minimum interior angle of several new triangles generated after inserting the discrete point into the current parameter domain plane grid, and determine whether the minimum interior angle is less than the preset angle threshold. If it is not less than the preset angle threshold, then set the discrete point as a new vertex and add it to the current parameter domain plane grid, delete the current triangle grid corresponding to the discrete point, and then create several new triangles based on the discrete point to update the topological adjacency relationship of the current parameter domain plane grid to obtain the current inserted grid. A one-dimensional boundary recovery operation is performed on the currently inserted mesh to obtain the current closed internal boundary. Then, the current region is determined based on the current closed internal boundary and the current parameter domain planar mesh. The current closed internal boundary is the closed boundary that is topologically connected and closed by the discrete point sequence.
6. The aircraft mesh generation method based on conformal mapping and topology segmentation according to claim 5, characterized in that, The step of inserting each discrete point into the current parameter domain planar grid using a preset topology segmentation algorithm and based on the current positional relationship to obtain the current inserted grid includes: Determine whether the minimum vertex distance is less than the preset vertex distance threshold. If the minimum vertex distance is less than the preset vertex distance threshold, construct a first neighborhood triangle set based on each current triangle mesh corresponding to the discrete point, and determine the first minimum angle corresponding to each current triangle mesh in the first neighborhood triangle set. The vertex corresponding to the minimum vertex distance is determined, and the coordinates of the vertex are updated to the coordinates of the discrete point to obtain the second neighborhood triangle set. Then, the second minimum angle corresponding to each current triangle grid in the second neighborhood triangle set is determined. Determine the difference between the first minimum angle and the second minimum angle, and determine whether the difference is greater than a preset threshold. If the difference is not greater than the preset threshold, then determine the current inserted grid based on the second neighborhood triangle set. If the difference is greater than the preset threshold, then the step of updating the coordinates corresponding to the vertex to the coordinates corresponding to the discrete point is prohibited.
7. The aircraft mesh generation method based on conformal mapping and topology segmentation according to claim 6, characterized in that, The step of inserting each discrete point into the current parameter domain planar grid using a preset topology segmentation algorithm and based on the current positional relationship to obtain the current inserted grid includes: Determine whether the minimum edge distance is less than a preset edge distance threshold. If the minimum edge distance is less than the preset edge distance threshold, determine whether the edge is an internal edge of the grid. If the edge is an internal edge of the grid, determine two associated triangular grids associated with the edge. If the edge is not an internal edge of the grid, determine one associated triangular grid associated with the edge. Based on the coordinate position of the discrete point or the midpoint position of the edge, the edge is divided into a first edge to be processed and a second edge to be processed, and the associated triangular mesh is deleted. Then, a new triangular mesh corresponding to the edge is created to obtain the mesh to be updated. Based on the adjacency relationship of the meshes in the mesh to be updated, the mesh after the current insertion is obtained.
8. An aircraft mesh generation device based on conformal mapping and topology segmentation, characterized in that, include: The compression ratio determination module is used to generate the current surface unstructured mesh based on preset surface mesh generation parameters and aircraft model file, and to conformally map the current surface unstructured mesh to the parameter domain space using Ricci flow to obtain the current parameter domain planar mesh, and then determine the current compression ratio between the current surface unstructured mesh and the current parameter domain planar mesh. The contour extraction module is used to determine whether the current compression ratio is less than a first preset threshold. If it is less, the current contour line corresponding to the second preset threshold is extracted. The first preset threshold is less than the second preset threshold; The positional relationship determination module is used to determine the current triangular mesh corresponding to each discrete point in the current contour line in the current parameter domain plane mesh using a preset spatial partitioning algorithm, so as to determine the current positional relationship between the current triangular mesh and the discrete point, including vertex distance and edge distance. The closed internal boundary determination module is used to insert each discrete point into the current parameter domain plane grid based on the current positional relationship using a preset topology segmentation algorithm to obtain the current inserted grid, and to perform a one-dimensional boundary recovery operation on the current inserted grid to obtain the current closed internal boundary, so as to determine the current region based on the current closed internal boundary and the current parameter domain plane grid. The aircraft mesh generation module is used to inversely map the current region to a three-dimensional surface space to obtain a new current surface unstructured mesh, and then jump back to the step of conformally mapping the current surface unstructured mesh to the parameter domain space using Ricci flow, until the current compression ratio is greater than the first preset threshold, and set the current parameter domain planar mesh as the target aircraft mesh.
9. An electronic device, characterized in that, include: Memory, used to store computer programs; A processor for executing the computer program to implement the aircraft mesh generation method based on conformal mapping and topology segmentation as described in any one of claims 1 to 7.
10. A computer-readable storage medium, characterized in that, Used to store a computer program, wherein the computer program, when executed by a processor, implements the aircraft mesh generation method based on conformal mapping and topology segmentation as described in any one of claims 1 to 7.