Methods, apparatus, equipment, and media for generating hexahedral dominant meshes for simulation of aircraft mechanical structural components.

Abstract

This application discloses a method, apparatus, device, and medium for generating hexahedral dominant meshes for simulating mechanical structural components of aircraft. It relates to the field of mesh generation technology, including: subdividing a quadrilateral dominant mesh to obtain a triangular mesh; adding the vertices of the surface triangular pieces of the tetrahedral mesh generated from the triangular mesh to a preset queue, and generating target points by traversing the frame of the first vertex in the queue in each direction; querying other position points within the target range, and determining hexahedral edge pairs based on the distance relationship between the target point and other position points; generating a lattice-like tetrahedral mesh based on the triangular mesh and the position field, and determining hexahedral element edges based on the hexahedral edge pairs and the lattice-like tetrahedral mesh; determining right-angled triangular faces based on the selected hexahedral element edges, determining tetrahedral combinations through the right-angled triangular faces, and merging the tetrahedral combinations to generate a hexahedral dominant mesh for simulating mechanical structural components of aircraft. This method rapidly generates high-percentage hexahedral meshes.

Description

Technical Field

[0001] This invention relates to the field of mesh generation technology, and in particular to a method, apparatus, equipment and medium for generating hexahedral dominant meshes for simulation of mechanical structural components of aircraft. Background Technology

[0002] In fields such as automotive, aerospace, and energy equipment, which rely on finite element analysis, hexahedral meshes have become a core requirement due to their high computational accuracy and excellent convergence. However, the automated generation of pure hexahedral meshes remains an unsolved technical challenge, especially for complex geometries (such as high-curvature surfaces, concave areas, and sharp edges). Traditional methods rely on manual interaction or predefined singular graphs, resulting in low generation efficiency and difficulty in adapting to large-scale engineering applications. To balance computational accuracy and generation efficiency, hexahedral dominant meshes are gradually becoming the preferred choice in industry. Currently, the technology for automatic generation of fully hexahedral meshes is not yet mature. The automatic generation of pure hexahedral meshes for complex shapes (such as high-curvature surfaces, concave areas, and sharp edges) is difficult and requires expert experience and manual interaction. While tetrahedral meshes can adapt to the discretization requirements of complex geometries, they have significant shortcomings in terms of mesh quantity and solution accuracy. Existing automatic generation of hexahedral dominant meshes cannot perfectly preserve the geometric features of the input and is not applicable in some specific scenarios (such as preserving surface constraints, multiple model contact surfaces sharing nodes, etc.), making it difficult to simultaneously meet the requirements of automatic generation, efficient computation, and high-quality output. Summary of the Invention

[0003] In view of this, the purpose of this invention is to provide a method, apparatus, device, and medium for generating hexahedral dominant meshes for simulating mechanical structural components of aircraft. This method can quickly generate effective hexahedral dominant meshes using only the required quadrilateral dominant surface mesh as input, exhibiting strong adaptability. The specific solution is as follows:

[0004] In a first aspect, this application discloses a method for generating hexahedral dominant meshes for simulating mechanical structural components of aircraft, including:

[0005] The quadrilateral elements corresponding to the quadrilateral-dominant mesh of the aircraft's mechanical structural components are divided into triangular elements by subdividing the diagonal to obtain a triangular mesh, and a tetrahedral mesh is generated based on the triangular mesh.

[0006] Each vertex of the surface triangle of the tetrahedral mesh is added to a preset queue. The frame of the vertex at the head of the preset queue is traversed in each direction to generate each target point corresponding to the target number of directions based on the quadrilateral dominant mesh.

[0007] Based on the spatial index structure, query other location points within the target range of the target point; determine the hexahedral edge point pairs constructed based on the vertex according to the distance relationship between the target point and the other location points; and determine the position field based on each vertex and each target point.

[0008] A tetrahedral mesh is generated using a tetrahedral mesh generation tool based on the triangular mesh and the position field. The edges of the hexahedral cells are determined based on the hexahedral edge point pairs and the lattice-shaped tetrahedral mesh.

[0009] The edges of the hexahedral units are filtered to determine the filtered hexahedral unit edges. Right-angled triangular faces are determined based on the filtered hexahedral unit edges, and tetrahedral pairs are determined through the right-angled triangular faces.

[0010] Based on all the tetrahedral pairs, a corresponding tetrahedral combination is determined. The tetrahedral combinations are merged based on the number of vertices of each tetrahedral combination to generate a corresponding hexahedral-dominant mesh, so as to simulate the mechanical structural components of the aircraft based on the hexahedral-dominant mesh.

[0011] Optionally, before determining the hexahedral edge pair constructed based on the vertex according to the distance relationship between the target point and the other location points, the method further includes:

[0012] The average side length of the quadrilateral-dominant mesh is determined as the target mesh size;

[0013] Determine the target product between the coordinates of the orientation component of the frame and the target mesh size;

[0014] The sum of the target product and the coordinates of the vertex is used to determine the coordinates of the target point.

[0015] Optionally, determining the hexahedral edge pair constructed based on the vertex according to the distance relationship between the target point and the other location points includes:

[0016] The target distance threshold is determined based on the product of the target grid size and the target value;

[0017] Based on the coordinates of the target point, determine the first location point among the other location points whose distance from the target point is less than the target distance threshold;

[0018] The position point that is closest to the target point among the first position points is determined as the second position point;

[0019] Mark the vertex and the second position point as a hexahedral edge pair, and jump back to the step of traversing the frame of the vertex at the head of the preset queue in each direction;

[0020] If the distance between the target point and the other location points is greater than the target distance threshold, the target point is embedded into the tetrahedral mesh by tetrahedral partitioning.

[0021] The target point is calculated using the centroid difference method, and the target point is stored at the tail of the preset queue.

[0022] The vertex and the target point are marked as the hexahedral edge-point pair.

[0023] Optionally, after storing the target point at the tail of the preset queue, the method further includes:

[0024] Determine whether the preset queue is empty;

[0025] If the preset queue is empty, the operation of generating a lattice-like tetrahedral mesh using a tetrahedral mesh generation tool based on the triangular mesh and the position field is triggered.

[0026] Otherwise, jump back to the step of traversing the frame of the vertex of the head of the preset queue in each direction until the preset queue is empty.

[0027] Optionally, determining the hexahedral cell edges based on the hexahedral edge point pairs and the lattice-like tetrahedral mesh includes:

[0028] Traverse the target mesh edges of the lattice-like tetrahedral mesh. If the two vertices of the target mesh edge are a pair of hexahedral edge points, then mark the corresponding target mesh edge as the hexahedral element edge, and mark all the mesh edges of the quadrilateral-dominant mesh as the hexahedral element edges.

[0029] Optionally, the step of filtering the edges of the hexahedral units to determine the filtered edges of the hexahedral units includes:

[0030] Traverse all triangular faces of the lattice-like tetrahedral mesh;

[0031] If all three sides of the triangular face are marked as edges of the hexahedral unit, then the marking of the longest edge among the three sides of the triangular face is removed to determine the filtered edges of the hexahedral unit.

[0032] Optionally, the step of determining right-angled triangular faces based on the edges of the selected hexahedral units, and determining tetrahedral pairs through the right-angled triangular faces, includes:

[0033] If two sides of the triangular face are the sides of the selected hexahedral unit, then the corresponding triangular face is determined as a right-angled triangular face;

[0034] Iterate through all unlabeled edges;

[0035] If two adjacent triangular faces of an unmarked edge are right-angled triangular faces, then the tetrahedrons corresponding to the two triangular faces are determined as a tetrahedron pair.

[0036] Optionally, the step of determining the corresponding tetrahedral combinations based on all the tetrahedral pairs, and merging the tetrahedral combinations based on the number of vertices of each tetrahedral combination to generate the corresponding hexahedral-dominant mesh includes:

[0037] An adjacency matrix is ​​constructed based on the information of the tetrahedral pairs, and the corresponding undirected graph is determined; wherein the nodes in the undirected graph are tetrahedrals and the edges are paired.

[0038] Determine the maximally connected subgraphs in the undirected graph, and determine the tetrahedral combination based on the maximally connected subgraphs;

[0039] Based on the number of vertices of each tetrahedral combination, the tetrahedral combinations are merged to generate a corresponding hexahedral-dominant mesh; wherein, if the number of vertices is a first quantity, the tetrahedral combinations are merged to generate a hexahedron; if the number of vertices is a second quantity, the tetrahedral combinations are merged to generate a triangular prism; if the number of vertices is a third quantity, the tetrahedral combinations are merged to generate a pyramid; otherwise, no merging is performed; wherein, the number of hexahedrons is greater than the number of triangular prisms, the number of pyramids, and the number of tetrahedrons.

[0040] Secondly, this application discloses a hexahedral dominant mesh generation device for simulating mechanical structural components of aircraft, comprising:

[0041] The tetrahedral mesh generation module is used to divide the quadrilateral units corresponding to the quadrilateral-dominant mesh of the aircraft mechanical structure into triangular units by dividing the diagonal to obtain a triangular mesh, and then generate a tetrahedral mesh based on the triangular mesh.

[0042] The target point generation module is used to add each vertex of the surface triangle of the tetrahedral mesh to a preset queue, traverse the frame of the vertex at the head of the preset queue in each direction, and generate each target point corresponding to the target number of directions based on the quadrilateral dominant mesh.

[0043] The hexahedral edge-point pair construction module is used to query other location points within the target range of the target point based on the spatial index structure, determine the hexahedral edge-point pairs constructed based on the vertex according to the distance relationship between the target point and the other location points, and determine the position field based on each vertex and each target point;

[0044] The hexahedral unit edge determination module is used to generate a lattice-like tetrahedral mesh based on the triangular mesh and the position field using a tetrahedral mesh generation tool, and to determine the hexahedral unit edges based on the hexahedral edge point pairs and the lattice-like tetrahedral mesh;

[0045] The tetrahedron pair determination module is used to filter the edges of the hexahedron units, determine the filtered hexahedron unit edges, determine right-angled triangle faces based on the filtered hexahedron unit edges, and determine tetrahedron pairs through the right-angled triangle faces;

[0046] The hexahedral dominant mesh generation module is used to determine the corresponding tetrahedral combinations based on all the tetrahedral pairs, merge the tetrahedral combinations based on the number of vertices of each tetrahedral combination, and generate the corresponding hexahedral dominant mesh, so as to simulate the mechanical structural components of the aircraft based on the hexahedral dominant mesh.

[0047] Thirdly, this application discloses an electronic device, comprising:

[0048] Memory, used to store computer programs;

[0049] A processor is used to execute computer programs to implement the hexahedral dominant mesh generation method for simulating mechanical structural components of aircraft, as described above.

[0050] Fourthly, this application discloses a computer-readable storage medium storing a computer program, which, when executed by a processor, implements the aforementioned method for generating hexahedral dominant meshes for simulating mechanical structural components of aircraft.

[0051] This invention first divides the quadrilateral elements corresponding to the quadrilateral-dominant mesh of the aircraft's mechanical structural components into triangular elements by dividing the diagonal, thus obtaining a triangular mesh. A tetrahedral mesh is then generated based on this triangular mesh. Each vertex of the surface triangular pieces of the tetrahedral mesh is added to a preset queue. The orientation of the frame of the vertex at the head of the preset queue is traversed to generate target points corresponding to a target number of orientations based on the quadrilateral-dominant mesh. Other location points within the target range of the target point are queried using a spatial index structure. Based on the distance relationship between the target point and the other location points, hexahedral edge pairs constructed based on the vertices are determined. Finally, based on each vertex and each target... The process involves: defining the position field; using a tetrahedral mesh generation tool to generate a lattice-like tetrahedral mesh based on the triangular mesh and the position field; determining hexahedral element edges based on the hexahedral edge pairs and the lattice-like tetrahedral mesh; filtering the hexahedral element edges to determine the filtered hexahedral element edges; determining right-angled triangular faces based on the filtered hexahedral element edges; and determining tetrahedral pairs based on the right-angled triangular faces; finally, determining corresponding tetrahedral combinations based on all the tetrahedral pairs; merging the tetrahedral combinations based on the number of vertices of each tetrahedral combination to generate a corresponding hexahedral-dominant mesh for simulating the mechanical structure of the aircraft. It is evident that this application marks hexahedral edge pairs when generating the position field and then filters out reasonable hexahedral edges to accurately identify potential hexahedral elements; then, it pairs tetrahedrals using triangles to quickly and intuitively obtain tetrahedral combinations of potential hexahedral elements. The system generates a position field guided by a frame field, and then uses the position field to generate tetrahedral meshes for merging. The final mesh is based on the orthogonality constraint of the frame field, ensuring the quality of the mesh elements. It can quickly find tetrahedral combinations of potential hexahedral elements, thereby rapidly generating hexahedral-dominant meshes. High-quality meshes can be generated efficiently and automatically without manual interaction. It has excellent robustness and can adapt to various complex shapes and application scenarios. Attached Figure Description

[0052] 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.

[0053] Figure 1 This application discloses a flowchart of a method for generating hexahedral dominant meshes for simulating mechanical structural components of aircraft.

[0054] Figure 2 This is a schematic diagram of a quadrilateral dominant grid disclosed in this application;

[0055] Figure 3 This is a schematic diagram of a position field disclosed in this application;

[0056] Figure 4 This is a schematic diagram of the edge of a hexahedral unit cell disclosed in this application;

[0057] Figure 5 This is a schematic diagram of a tetrahedral combination of a potential hexahedron and its surface triangle pairs disclosed in this application;

[0058] Figure 6 This is a schematic diagram illustrating the continuous pairing relationship of a triangle pair and its corresponding tetrahedral pair disclosed in this application;

[0059] Figure 7 This is a schematic diagram of a hexahedral dominant mesh disclosed in this application;

[0060] Figure 8 This is a schematic diagram of a cross-section of a hexahedral dominant mesh disclosed in this application;

[0061] Figure 9 This application discloses a flowchart of a specific method for generating hexahedral dominant meshes for simulating mechanical structural components of aircraft.

[0062] Figure 10 This is a schematic diagram of a hexahedral dominant mesh generation device for simulating mechanical structural components of aircraft disclosed in this application.

[0063] Figure 11 This is a structural diagram of an electronic device disclosed in this application. Detailed Implementation

[0064] 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.

[0065] Existing hexahedral dominant mesh generation techniques can be broadly categorized into four types. The first type is the octree-based method. Its main idea is to embed the target geometry into an axis-aligned bounding box, recursively subdivide the 3D space to generate an octree structure, with each leaf node corresponding to a cubic voxel, forming the initial mesh. An adaptive subdivision strategy is used to match local geometric features, and dangling nodes are further removed using either the primal or dual method. Finally, the mesh boundary is projected onto the target geometric surface to ensure geometric fidelity. However, this approach is prone to generating a large number of singular vertices, resulting in poor mesh quality. The second type is the frame field method. This method first pre-computes a smooth frame field aligned with the boundary on the geometric surface or in space. Integer mesh mappings are constructed using this field as a guide, and then integer isosurfaces are extracted to form a hexahedral mesh. Frame field optimization requires solving partial differential equations, resulting in high computational complexity, slow speed, and poor robustness. Furthermore, the frame field may retain unmeshable singularities, such as discontinuous direction vectors or singular vertices, leading to isosurface extraction failures. The third type is the multi-cube mapping method. This method first maps the target geometry to an orthogonal multi-cube structure, then determines the multi-cube topology by defining coordinate axis labels for surface elements. Based on the multi-cube topology, a parameterized mapping function is constructed to map the geometric surface nodes to the parameter space of the multi-cube structure. A regular hexahedral mesh is generated in the parameter space of the multi-cube structure, and then the parameter space mesh is converted to a hexahedral mesh in physical space using an inverse mapping function. This method has hyperparameter dependencies and is prone to mapping flip failure in complex geometric scenarios. Furthermore, non-axis-aligned features (such as spiral structures and freeform surfaces) can easily lead to element distortion during the mapping process. The fourth type is the tetrahedral combination method. Based on the tetrahedral mesh generated from the target geometry, adjacent tetrahedra are combined into hexahedral elements through local heuristic rules or global optimization strategies. This can quickly generate a high proportion of hexahedral meshes, but it is difficult to control the topology type of the mixed elements, easily resulting in incompatible mesh structures, and the aggregation process is prone to getting trapped in local optima. To address the aforementioned technical problems, this application discloses a method, apparatus, device, and medium for generating hexahedral dominant meshes for simulation of aircraft mechanical structural components. This method can quickly generate effective hexahedral dominant meshes using only the required quadrilateral dominant surface mesh as input, demonstrating strong adaptability.

[0066] See Figure 1 As shown, this invention discloses a method for generating hexahedral dominant meshes for simulating mechanical structural components of aircraft, comprising:

[0067] Step S11: Divide the quadrilateral elements corresponding to the quadrilateral-dominant mesh of the aircraft mechanical structure into triangular elements by dividing the diagonal to obtain a triangular mesh, and generate a tetrahedral mesh based on the triangular mesh.

[0068] In this embodiment, the import is first performed. Figure 2The quadrilateral-dominant mesh of the aircraft's mechanical structure is shown, and the average side length of the mesh edges is calculated as the target mesh size *r*. The quadrilateral elements are divided into triangular elements by subdividing the diagonals to obtain a triangular mesh. This triangular mesh is then input into Tetgen (a tetrahedral mesh generation tool) to generate a tetrahedral mesh. An arbitrary 3D frame field solution method is used to generate a spatial frame field, with a frame placed at each vertex of the tetrahedral mesh. In other words, in this application, the average side length of the quadrilateral-dominant mesh edges is determined as the target mesh size.

[0069] Step S12: Add each vertex of the surface triangle of the tetrahedral mesh to a preset queue, traverse the frame of the vertex at the head of the preset queue in each direction, and generate each target point corresponding to the target number of directions based on the quadrilateral dominant mesh.

[0070] In this embodiment, after generating the tetrahedral mesh, a position field is generated in conjunction with the frame field, and hexahedral edge point pairs are marked, with each pair representing an edge of a hexahedral cell. Specifically, a queue Q is created for generating position points by advancing the front edge, and surface vertices are added to Q; the frame of the vertex at the head of the preset queue is traversed in all directions. The vertex v at the head of the queue is taken, and the frame of v is traversed in its six directions, generating a new point u in each direction. The target product between the coordinates of the frame's directional components and the target mesh size is determined; the sum of the target product and the coordinates of the vertex is used to determine the coordinates of the target point (new point u). The position coordinates of u are calculated as follows:

[0071] ;

[0072] in, Let be the i-th directional component among the six directional components of the frame, and r be the target mesh size in the above steps.

[0073] Step S13: Based on the spatial index structure, query other location points within the target range of the target point, determine the hexahedral edge point pairs constructed based on the vertex according to the distance relationship between the target point and the other location points, and determine the position field based on each vertex and each target point.

[0074] In this embodiment, the location points near u are quickly queried using R-tree (bounding box tool), and the target distance threshold is determined based on the product between the target mesh size and the target value. Based on the coordinates of the target point, a first location point among the other location points whose distance to the target point is less than the target distance threshold is determined. The location point among the first location points closest to the target point is determined as the second location point. The vertex and the second location point are marked as a hexahedral edge pair, and the process jumps back to the step of traversing the frame of the vertex at the head of the preset queue in each direction. If the distance between the target point and the other location points is greater than the target distance threshold, the target point is embedded into the tetrahedral mesh using tetrahedral partitioning. The frame of the target point is calculated using the centroid difference method, and the target point is stored at the tail of the preset queue. The vertex and the target point are marked as the hexahedral edge pair. Specifically, if the distance to a nearby location point is less than r... If the value is 0.7, a collision is considered to have occurred. It is possible that the collision occurred with multiple points, and the point closest to u is selected from these points. , v and Marked as a pair of hexahedral edge points {v, The process abandons the generation of position point u and jumps to the step of "taking the first vertex v of the queue, traversing the six directions of v's frame, and generating a new point u in each direction"; if there is no collision point, u is embedded into a tetrahedral mesh through tetrahedral partitioning, the frame of u is calculated through barycentric interpolation, u is placed at the tail of the Q queue, and v and u are marked as a pair of hexahedral edge points {v, u}. The final position field visualization result is as follows. Figure 3 As shown.

[0075] In addition, after storing the target point at the tail of the preset queue, it is determined whether the preset queue is empty; if the preset queue is empty, the operation of generating a lattice-like tetrahedral mesh using a tetrahedral mesh generation tool based on the triangular mesh and the position field is triggered; otherwise, the process jumps back to the step of traversing the frame of the vertex at the head of the preset queue in each direction until the preset queue is empty.

[0076] Step S14: Use a tetrahedral mesh generation tool to generate a lattice-shaped tetrahedral mesh based on the triangular mesh and the position field, and determine the hexahedral cell edges based on the hexahedral edge point pairs and the lattice-shaped tetrahedral mesh.

[0077] In this embodiment, after determining the hexahedral edge pairs, potential hexahedral elements are extracted using these edge pairs. Specifically, the surface triangular mesh and position field are first input into Tetgen (a tetrahedral mesh generation tool) to generate a lattice-like tetrahedral mesh. The target mesh edges of the lattice-like tetrahedral mesh are traversed. If the two vertices of a target mesh edge are a pair of hexahedral edge points, the corresponding target mesh edge is marked as a hexahedral element edge, and all mesh edges of the quadrilateral-dominant mesh are also marked as hexahedral element edges.

[0078] Step S15: Filter the edges of the hexahedral units, determine the filtered hexahedral unit edges, determine right-angled triangular faces based on the filtered hexahedral unit edges, and determine tetrahedral pairs through the right-angled triangular faces.

[0079] In this embodiment of the invention, since a hexahedral unit consists of 12 edges and 6 quadrilateral faces, and each quadrilateral face consists of two triangles, a triangle can have at most two hexahedral unit edges (the other being the outer diagonal of the hexahedral unit). Therefore, redundant marked hexahedral unit edges should be processed. This application traverses all triangular faces of the lattice-like tetrahedral mesh; if all three edges of the triangular face are marked as hexahedral unit edges, the marking of the longest edge among the three edges of the triangular face is removed to determine the filtered hexahedral unit edges. Specifically, traversing all triangular faces of the mesh, if all three edges of a triangle are marked as hexahedral unit edges, the marking of the longest edge is removed (i.e., it becomes a regular mesh edge). At this time, all triangular faces have at most two hexahedral unit edges, and the visualization result of the hexahedral unit edges is as follows. Figure 4 As shown. In this way, when generating the position field, hexahedral edge pairs are marked, and then reasonable hexahedral edges are selected based on the property that "a triangle has at most two edges that are hexahedral edges" to accurately identify potential hexahedral elements.

[0080] In this embodiment, within a tetrahedral assembly that forms a hexahedron (referred to in this invention as a potential hexahedral unit), each quadrilateral on the surface of the hexahedron is composed of two triangles, and each triangle is adjacent to a tetrahedron. These two triangles are referred to as a triangle pair, and the adjacent tetrahedrons are referred to as a tetrahedral pair. Since triangles on different faces of a hexahedral unit may originate from the same tetrahedron, the tetrahedral pairing relationship is continuous. For example... Figure 5As shown, u0 and u1 are a pair, l0 and l1 are a pair, r0 and r1 are a pair, d0 and d1 are a pair, f0 and f1 are a pair, and b0 and b1 are a pair. u0 and l0 come from the same tetrahedron (called t1), u1, r0 and b1 come from the same tetrahedron (called t2), l1, f0 and d0 come from the same tetrahedron (called t3), r1 and d1 come from the same tetrahedron (called t4), and f1 and b0 come from two separate tetrahedrons (called t5 and t6). The tetrahedrons connected by the paired triangles are also paired. These 6 tetrahedrons (t1~t6) form a pairing combination, and these 6 tetrahedrons are exactly the tetrahedron combinations that make up the current hexahedral unit. Figure 6 This pairing relationship is illustrated, where each node represents a pair of triangles. Each triangle and its corresponding tetrahedron are connected by a solid line, and the two tetrahedrons connected by each triangle pair form a tetrahedron pair, connected by dashed lines. Through the continuity of the pairings described above, it can be seen that all the tetrahedrons below can be traversed in one go using dashed lines. Therefore, if a triangular face has exactly two edges that are hexahedral elements, this invention calls such a triangle a right-angled triangular face. By traversing all non-hexahedral element edges, any two adjacent triangular faces are paired into a triangle pair, and the tetrahedrons on the same side of the triangle pair are paired into tetrahedron pairs. All such tetrahedron pairs are found and represented by the tetrahedron's ID, such as {1,2} representing a tetrahedron pair. Specifically, if two sides of the triangular face are the edges of the selected hexahedral units, then the corresponding triangular face is determined as a right-angled triangular face; all unmarked edges are traversed; if two adjacent triangular faces of an unmarked edge are the right-angled triangular faces, then the tetrahedrons corresponding to the two triangular faces are determined as a tetrahedral pair.

[0081] Step S16: Determine the corresponding tetrahedral combinations based on all the tetrahedral pairs, merge the tetrahedral combinations based on the number of vertices of each tetrahedral combination, and generate the corresponding hexahedral-dominant mesh, so as to simulate the mechanical structure of the aircraft based on the hexahedral-dominant mesh.

[0082] In this embodiment, after determining the tetrahedrons, corresponding tetrahedron combinations can be determined. During this process, an adjacency matrix is ​​constructed based on the information of the tetrahedron pairs, and the corresponding undirected graph is determined; wherein nodes in the undirected graph are tetrahedrons and edges are paired; a maximal connected subgraph is determined in the undirected graph, and the tetrahedron combinations are determined based on the maximal connected subgraph. Specifically, an n-dimensional graph is constructed based on all tetrahedron pairs. An adjacency matrix M of n tetrahedra (numbered from 1 to n, a total of n tetrahedra) corresponds to an undirected graph G. Tetrahedral combinations can be found by identifying maximal connected subgraphs within G; each maximal connected subgraph corresponds to one tetrahedral combination. Since the method for finding maximal connected subgraphs is a fundamental algorithm in graph theory, it will not be elaborated upon in this invention.

[0083] Subsequently, the tetrahedral combinations are merged based on the number of vertices in each combination to generate a corresponding hexahedral-dominant mesh. Specifically, if the number of vertices is a first quantity, the tetrahedral combinations are merged to generate a hexahedron; if the number of vertices is a second quantity, the tetrahedral combinations are merged to generate a triangular prism; if the number of vertices is a third quantity, the tetrahedral combinations are merged to generate a pyramid; otherwise, no merging is performed. The number of hexahedrons is greater than the number of triangular prisms, pyramids, and tetrahedrons. Specifically, for each tetrahedral combination, it is merged into different polyhedral elements based on the number of vertices: 8 vertices correspond to a hexahedron, 6 vertices correspond to a triangular prism, 5 vertices correspond to a pyramid, and the remaining tetrahedral elements remain unchanged. Since this invention generates a position field aligned with the frame field, and tetrahedrons are generated through this position field, the final mesh elements obtained by merging tetrahedrons are mostly hexahedral elements. Thus, the hexahedral-dominant mesh generation is complete, as shown in the example below. Figure 7 As shown, the cross-sectional view is as follows Figure 8 As shown. Ultimately, the mechanical structural components of the aircraft can be simulated based on the hexahedral-dominated mesh.

[0084] As can be seen, this application marks hexahedral edge pairs when generating the position field, and then filters out reasonable hexahedral edges for accurate identification of potential hexahedral elements. Then, it uses triangles to pair tetrahedrons, quickly and intuitively obtaining tetrahedral combinations of potential hexahedral elements. The position field is generated by guiding the generation of the frame field, and then tetrahedral meshes are generated and merged using the position field. The final generated mesh is based on the orthogonality constraints of the frame field, ensuring the quality of the mesh elements and enabling the rapid identification of tetrahedral combinations of potential hexahedral elements, thus quickly generating a hexahedral-dominant mesh. It can efficiently and automatically generate high-quality meshes without manual interaction, exhibiting superior robustness and adaptability to various complex shapes and application scenarios.

[0085] Based on the previous embodiment, this application discloses a method for generating hexahedral dominant meshes for simulating mechanical structural components of aircraft. Next, in conjunction with... Figure 9 This paper provides a detailed explanation of the hexahedral dominant mesh generation method used for the simulation of mechanical structural components of aircraft.

[0086] First, input the quadrilateral dominant surface mesh, then divide the quadrilateral elements into triangular elements by dividing the diagonals to obtain a triangular mesh; input the triangular mesh into Tetgen (a tetrahedral mesh generation tool) to generate a tetrahedral mesh; and use an arbitrary 3D frame field solution method to generate a spatial frame field, with a frame placed on each vertex of the tetrahedral mesh.

[0087] Next, create a queue for generating position points using the leading edge propagation, adding surface vertices to the queue. Then, take the first vertex of the queue and traverse the six directions of the v frame, generating a new position point in each direction. Use an R-tree (bounding box tool) to quickly query the position points near the new position point; if the distance between the new position point and the nearby position point is less than r... If the value is 0.7, a collision is considered to have occurred, potentially involving multiple points. The point closest to the current vertex is selected, and this point and the current vertex are marked as a hexahedral edge pair. The generation of a new position point is abandoned, and the process jumps back to the vertex at the head of the queue, iterating through the six directions of v's frame. If no collision occurs, the new position point is embedded into a tetrahedral mesh using tetrahedral partitioning. The frame of the new position point is calculated using barycentric interpolation, and the new position point is added to the tail of the queue, marked as a hexahedral edge pair with the current vertex. Additionally, the queue is checked for emptiness. If the queue is not empty, the process jumps back to the vertex at the head of the queue, iterating through the six directions of v's frame. If the queue is empty, the subsequent operations continue.

[0088] Finally, the surface triangular mesh and the position field (all position points) are input into Tetgen (a tetrahedral mesh generation tool) to generate a lattice-like tetrahedral mesh. All edges of the mesh are traversed; if the two vertices of an edge are a pair of hexahedral edge points, the edge is marked as a hexahedral element edge, and all edges of the input quadrilateral-dominant mesh are also marked as hexahedral element edges. All triangular faces are traversed; if all three edges of a triangle are marked as hexahedral element edges, the longest edge is unmarked (i.e., becomes a regular mesh edge). At this point, all triangular faces have at most two hexahedral element edges. If a triangular face has exactly two hexahedral element edges, this invention calls such a triangle a right-angled triangular face. By traversing all non-hexahedral element edges, any two adjacent triangular faces are paired into a triangle pair, and the tetrahedrons on the same side of the triangle pair are paired into tetrahedral pairs. All such tetrahedral pairs are found to complete the tetrahedral pairing. An n-dimensional array is constructed based on all tetrahedral pairs. The adjacency matrix M of n corresponds to an undirected graph G. Tetrahedral combinations can be found by identifying maximal connected subgraphs within G; each maximal connected subgraph corresponds to one tetrahedral combination. For each tetrahedral combination, it is merged into different polyhedral elements based on the number of vertices: 8 vertices correspond to a hexahedron, 6 vertices to a triangular prism, 5 vertices to a pyramid, and the remaining tetrahedral elements are retained without merging. Since this invention generates a position field aligned with the frame field, and tetrahedrons are generated through this position field, the final merged tetrahedral mesh elements are mostly hexahedral elements. Thus, the hexahedral-dominant mesh generation is complete.

[0089] It should be noted that the final generated hexahedral dominant mesh can be used in fields that rely on finite element analysis, such as automotive, aerospace, and energy equipment, for corresponding simulations. For example, when simulating the mechanical structure of an aircraft, the effective hexahedral dominant mesh is generated based on the quadrilateral dominant surface mesh of the mechanical structure as input, and the simulation of the mechanical structure is finally performed using the hexahedral dominant mesh.

[0090] As can be seen, this application guides the generation of a position field through a frame field, then generates tetrahedral meshes from the position field and merges them. The final generated mesh is based on the orthogonality constraint of the frame field, ensuring the quality of the mesh elements. During the generation of the position field, hexahedral edge pairs are marked, and reasonable hexahedral edges are selected based on the property that "a triangle has at most two hexahedral edges" to accurately identify potential hexahedral elements. Triangles are used to pair tetrahedrons, quickly and intuitively obtaining tetrahedral combinations of potential hexahedral elements. An adjacency matrix of tetrahedral elements is constructed, and all tetrahedral combinations are found through a maximally connected subgraph, quickly identifying all tetrahedral combinations, which are then merged to obtain a hexahedral-dominant mesh. In this way, this application can find tetrahedral combinations of potential hexahedral elements more quickly, thus rapidly generating a hexahedral-dominant mesh. Furthermore, using the surface mesh as a hard constraint to generate the volume mesh perfectly preserves the characteristics.

[0091] See Figure 10 As shown, this embodiment of the invention discloses a hexahedral dominant mesh generation device for simulating mechanical structural components of aircraft, comprising:

[0092] The tetrahedral mesh generation module 11 is used to divide the quadrilateral units corresponding to the quadrilateral-dominant mesh of the aircraft mechanical structure into triangular units by dividing the diagonal to obtain a triangular mesh, and generate a tetrahedral mesh based on the triangular mesh.

[0093] The target point generation module 12 is used to add each vertex of the surface triangle of the tetrahedral mesh to a preset queue, traverse the frame of the vertex at the head of the preset queue in each direction, and generate each target point corresponding to the target number of directions based on the quadrilateral dominant mesh.

[0094] The hexahedral edge-point pair construction module 13 is used to query other position points within the target range of the target point based on the spatial index structure, determine the hexahedral edge-point pairs constructed based on the vertex according to the distance relationship between the target point and the other position points, and determine the position field based on each vertex and each target point;

[0095] The hexahedral unit edge determination module 14 is used to generate a lattice-shaped tetrahedral mesh based on the triangular mesh and the position field using a tetrahedral mesh generation tool, and to determine the hexahedral unit edges based on the hexahedral edge point pairs and the lattice-shaped tetrahedral mesh.

[0096] The tetrahedron pair determination module 15 is used to filter the edges of the hexahedron unit, determine the filtered hexahedron unit edges, determine right-angled triangle faces based on the filtered hexahedron unit edges, and determine tetrahedron pairs through the right-angled triangle faces;

[0097] The hexahedral dominant mesh generation module 16 is used to determine the corresponding tetrahedral combinations based on all the tetrahedral pairs, merge the tetrahedral combinations based on the number of vertices of each tetrahedral combination, and generate the corresponding hexahedral dominant mesh, so as to perform the simulation of the mechanical structure of the aircraft based on the hexahedral dominant mesh.

[0098] As can be seen, this application marks hexahedral edge pairs when generating the position field, and then filters out reasonable hexahedral edges for accurate identification of potential hexahedral elements. Then, it uses triangles to pair tetrahedrons, quickly and intuitively obtaining tetrahedral combinations of potential hexahedral elements. The position field is generated by guiding the generation of the frame field, and then tetrahedral meshes are generated and merged using the position field. The final generated mesh is based on the orthogonality constraints of the frame field, ensuring the quality of the mesh elements and enabling the rapid identification of tetrahedral combinations of potential hexahedral elements, thus quickly generating a hexahedral-dominant mesh. It can efficiently and automatically generate high-quality meshes without manual interaction, exhibiting superior robustness and adaptability to various complex shapes and application scenarios.

[0099] In some specific embodiments, the device can also be used to determine the average side length of the grid edges of the quadrilateral dominant grid as the target grid size; determine the target product between the coordinates of the orientation components of the frame and the target grid size; and determine the coordinates of the target point by summing the target product with the coordinates of the vertex.

[0100] In some specific embodiments, the device can also be used to determine a target distance threshold based on the product of the target mesh size and the target value; determine a first position point among the other position points whose distance to the target point is less than the target distance threshold based on the coordinates of the target point; determine the position point among the first position points that is closest to the target point as a second position point; mark the vertex and the second position point as a hexahedral edge pair, and jump back to the step of traversing the frame of the vertex at the head of the preset queue in each direction; if the distance between the target point and the other position points is greater than the target distance threshold, embed the target point into the tetrahedral mesh by tetrahedral partitioning; calculate the frame of the target point by the centroid difference method, store the target point at the tail of the preset queue; and mark the vertex and the target point as the hexahedral edge pair.

[0101] In some specific embodiments, the device can also be used to determine whether the preset queue is empty; if the preset queue is empty, the operation of generating a lattice-like tetrahedral mesh using a tetrahedral mesh generation tool based on the triangular mesh and the position field is triggered; otherwise, the step of traversing the frame of the vertex of the head of the preset queue is restarted until the preset queue is empty.

[0102] In some specific embodiments, the hexahedral cell edge determination module 14 can be used to traverse the target mesh edges of the lattice-like tetrahedral mesh. If the two vertices of the target mesh edge are a pair of hexahedral edge points, the corresponding target mesh edge is marked as the hexahedral cell edge, and all the mesh edges of the quadrilateral-dominant mesh are marked as the hexahedral cell edges.

[0103] In some specific embodiments, the tetrahedron pair determination module 15 can be used to traverse all triangular faces of the lattice-like tetrahedron mesh; if all three sides of the triangular face are marked as hexahedral unit edges, the marking of the longest side among the three sides of the triangular face is removed to determine the filtered hexahedral unit edges.

[0104] In some specific embodiments, the tetrahedron pair determination module 15 can be used to determine the corresponding triangular face as a right-angled triangular face if two sides of the triangular face are the edges of the filtered hexahedral units; traverse all unmarked edges; if two triangular faces adjacent to the unmarked edges are the right-angled triangular faces, then determine the tetrahedrons corresponding to the two triangular faces as a tetrahedron pair.

[0105] In some specific embodiments, the hexahedral dominant mesh generation module 16 can be used to construct an adjacency matrix based on the information of the tetrahedral pairs and determine the undirected graph corresponding to the adjacency matrix; wherein the nodes in the undirected graph are tetrahedrons and the edges are paired; determine the maximal connected subgraph in the undirected graph, and determine the tetrahedral combination based on the maximal connected subgraph; merge the tetrahedral combinations based on the number of vertices of each tetrahedral combination to generate the corresponding hexahedral dominant mesh; wherein, if the number of vertices is a first quantity, the tetrahedral combinations are merged to generate a hexahedron; if the number of vertices is a second quantity, the tetrahedral combinations are merged to generate a triangular prism; if the number of vertices is a third quantity, the tetrahedral combinations are merged to generate a pyramid; otherwise, no merging is performed; wherein, the number of hexahedrons is greater than the number of triangular prisms, the number of pyramids, and the number of tetrahedrons.

[0106] Furthermore, embodiments of this application also disclose an electronic device, Figure 11 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.

[0107] Figure 11 This is a schematic diagram of the structure of an electronic device 20 provided in an embodiment 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 hexahedral dominant mesh generation method for simulating aircraft mechanical structural components disclosed in any of the foregoing embodiments. Alternatively, the electronic device 20 in this embodiment may specifically be an electronic computer.

[0108] 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.

[0109] 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.

[0110] 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 hexahedral dominant mesh generation method for simulating aircraft mechanical structural components, which is executed by the electronic device 20 according to any of the foregoing embodiments, the computer program 222 may further include computer programs capable of performing other specific tasks.

[0111] 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 method for generating hexahedral dominant meshes for simulating aircraft mechanical structural components. Specific steps of this method can be found in the corresponding content disclosed in the foregoing embodiments, and will not be repeated here.

[0112] 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.

[0113] 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.

[0114] 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.

[0115] 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.

[0116] 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 hexahedral dominant meshes for simulating mechanical structural components of aircraft, characterized in that, include: The quadrilateral elements corresponding to the quadrilateral-dominant mesh of the aircraft's mechanical structural components are divided into triangular elements by subdividing the diagonal to obtain a triangular mesh, and a tetrahedral mesh is generated based on the triangular mesh. Each vertex of the surface triangle of the tetrahedral mesh is added to a preset queue. The frame of the vertex at the head of the preset queue is traversed in each direction to generate each target point corresponding to the target number of directions based on the quadrilateral dominant mesh. Based on the spatial index structure, query other location points within the target range of the target point, determine the hexahedral edge point pairs constructed based on the vertex according to the distance relationship between the target point and the other location points, and determine the position field based on each vertex and each target point; A tetrahedral mesh is generated using a tetrahedral mesh generation tool based on the triangular mesh and the position field. The edges of the hexahedral cells are determined based on the hexahedral edge point pairs and the lattice-shaped tetrahedral mesh. The edges of the hexahedral units are filtered to determine the filtered hexahedral unit edges. Right-angled triangular faces are determined based on the filtered hexahedral unit edges, and tetrahedral pairs are determined through the right-angled triangular faces. Based on all the tetrahedral pairs, the corresponding tetrahedral combinations are determined. The tetrahedral combinations are merged based on the number of vertices of each tetrahedral combination to generate a corresponding hexahedral-dominant mesh, so as to simulate the mechanical structural components of the aircraft based on the hexahedral-dominant mesh. Before determining the hexahedral edge pair constructed based on the vertex according to the distance relationship between the target point and the other position points, the method further includes: The average side length of the quadrilateral-dominant mesh is determined as the target mesh size; Determine the target product between the coordinates of the orientation component of the frame and the target mesh size; The sum of the target product and the coordinates of the vertex is used to determine the coordinates of the target point; The step of determining the hexahedral edge pair constructed based on the vertex according to the distance relationship between the target point and the other position points includes: The target distance threshold is determined based on the product of the target grid size and the target value; Based on the coordinates of the target point, determine the first location point among the other location points whose distance from the target point is less than the target distance threshold; The position point that is closest to the target point among the first position points is determined as the second position point; Mark the vertex and the second position point as a hexahedral edge pair, and jump back to the step of traversing the frame of the vertex at the head of the preset queue in each direction; If the distance between the target point and the other location points is greater than the target distance threshold, the target point is embedded into the tetrahedral mesh by tetrahedral partitioning. The target point is calculated using the centroid difference method, and the target point is stored at the tail of the preset queue. The vertex and the target point are marked as the hexahedral edge-point pair.

2. The method for generating a hexahedral dominant mesh for simulating mechanical structural components of an aircraft according to claim 1, characterized in that, After storing the target point to the tail of the preset queue, the method further includes: Determine whether the preset queue is empty; If the preset queue is empty, the operation of generating a lattice-like tetrahedral mesh using a tetrahedral mesh generation tool based on the triangular mesh and the position field is triggered. Otherwise, jump back to the step of traversing the frame of the vertex of the head of the preset queue in each direction until the preset queue is empty.

3. The method for generating a hexahedral dominant mesh for simulating mechanical structural components of an aircraft according to claim 1, characterized in that, The determination of hexahedral cell edges based on the hexahedral edge point pairs and the lattice-like tetrahedral mesh includes: Traverse the target mesh edges of the lattice-like tetrahedral mesh. If the two vertices of the target mesh edge are a pair of hexahedral edge points, then mark the corresponding target mesh edge as the hexahedral element edge, and mark all the mesh edges of the quadrilateral-dominant mesh as the hexahedral element edges.

4. The method for generating a hexahedral dominant mesh for simulating mechanical structural components of aircraft according to claim 1, characterized in that, The step of filtering the edges of the hexahedral cells to determine the filtered edges includes: Traverse all triangular faces of the lattice-like tetrahedral mesh; If all three sides of the triangular face are marked as edges of the hexahedral unit, then the marking of the longest edge among the three sides of the triangular face is removed to determine the filtered edges of the hexahedral unit.

5. The method for generating a hexahedral dominant mesh for simulating mechanical structural components of an aircraft according to claim 4, characterized in that, The step of determining right-angled triangular faces based on the edges of the selected hexahedral units, and determining tetrahedral pairs through the right-angled triangular faces, includes: If two sides of the triangular face are the sides of the selected hexahedral unit, then the corresponding triangular face is determined as a right-angled triangular face; Iterate through all unlabeled edges; If two adjacent triangular faces of an unmarked edge are right-angled triangular faces, then the tetrahedrons corresponding to the two triangular faces are determined as a tetrahedron pair.

6. The method for generating a hexahedral dominant mesh for simulating mechanical structural components of an aircraft according to any one of claims 1 to 5, characterized in that, The step of determining the corresponding tetrahedral combinations based on all the tetrahedral pairs, and merging the tetrahedral combinations based on the number of vertices in each tetrahedral combination to generate the corresponding hexahedral-dominant mesh includes: An adjacency matrix is ​​constructed based on the information of the tetrahedral pairs, and the corresponding undirected graph is determined; wherein the nodes in the undirected graph are tetrahedrals and the edges are paired. Determine the maximally connected subgraphs in the undirected graph, and determine the tetrahedral combination based on the maximally connected subgraphs; Based on the number of vertices of each tetrahedral combination, the tetrahedral combinations are merged to generate a corresponding hexahedral-dominant mesh; wherein, if the number of vertices is a first quantity, the tetrahedral combinations are merged to generate a hexahedron; if the number of vertices is a second quantity, the tetrahedral combinations are merged to generate a triangular prism; if the number of vertices is a third quantity, the tetrahedral combinations are merged to generate a pyramid; otherwise, no merging is performed; wherein, the number of hexahedrons is greater than the number of triangular prisms, the number of pyramids, and the number of tetrahedrons.

7. A hexahedral dominant mesh generation device for simulating mechanical structural components of aircraft, characterized in that, include: The tetrahedral mesh generation module is used to divide the quadrilateral units corresponding to the quadrilateral-dominant mesh of the aircraft mechanical structure into triangular units by dividing the diagonal to obtain a triangular mesh, and then generate a tetrahedral mesh based on the triangular mesh. The target point generation module is used to add each vertex of the surface triangle of the tetrahedral mesh to a preset queue, traverse the frame of the vertex at the head of the preset queue in each direction, and generate each target point corresponding to the target number of directions based on the quadrilateral dominant mesh. The hexahedral edge-point pair construction module is used to query other location points within the target range of the target point based on the spatial index structure, determine the hexahedral edge-point pairs constructed based on the vertex according to the distance relationship between the target point and the other location points, and determine the position field based on each vertex and each target point; The hexahedral unit edge determination module is used to generate a lattice-like tetrahedral mesh based on the triangular mesh and the position field using a tetrahedral mesh generation tool, and to determine the hexahedral unit edges based on the hexahedral edge point pairs and the lattice-like tetrahedral mesh; The tetrahedron pair determination module is used to filter the edges of the hexahedron units, determine the filtered hexahedron unit edges, determine right-angled triangle faces based on the filtered hexahedron unit edges, and determine tetrahedron pairs through the right-angled triangle faces; The hexahedral dominant mesh generation module is used to determine the corresponding tetrahedral combination based on all the tetrahedral pairs, merge the tetrahedral combinations based on the number of vertices of each tetrahedral combination, and generate the corresponding hexahedral dominant mesh, so as to simulate the mechanical structure of the aircraft based on the hexahedral dominant mesh. The device is further configured to determine the average side length of the grid edges of the quadrilateral-dominant grid as the target grid size; determine the target product between the coordinates of the orientation components of the frame and the target grid size; and determine the coordinates of the target point by summing the target product with the coordinates of the vertex. The hexahedral edge point pair construction module is used to determine the target distance threshold based on the product between the target mesh size and the target value. Based on the coordinates of the target point, determine the first location point among the other location points whose distance from the target point is less than the target distance threshold; The point closest to the target point among the first position points is determined as the second position point; the vertex and the second position point are marked as a hexahedral edge pair, and the process jumps back to the step of traversing the frame of the vertex at the head of the preset queue in each direction; if the distance between the target point and the other position points is greater than the target distance threshold, the target point is embedded into the tetrahedral mesh by tetrahedral partitioning. The frame of the target point is calculated using the centroid difference method, and the target point is stored at the tail of the preset queue; the vertex and the target point are marked as the hexahedral edge-point pair.

8. An electronic device, characterized in that, include: Memory, used to store computer programs; A processor for executing a computer program to implement the hexahedral dominant mesh generation method for simulation of aircraft mechanical structural components as described in any one of claims 1 to 6.

9. A computer-readable storage medium, characterized in that, A computer-readable storage medium stores a computer program that, when executed by a processor, implements the hexahedral dominant mesh generation method for simulation of aircraft mechanical structural components as described in any one of claims 1 to 6.

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