A post-processing method and system for topology optimization of lightweight aircraft component structures

Abstract

The present invention discloses a topology optimization post-processing method and system for lightweighting of aircraft component structures, which relates to the technical field of lightweighting of aircraft component structures. The method includes: constructing a structured model of a target aircraft component, and performing topology optimization processing on the structured model of the target aircraft component to obtain a topology optimization result of the target aircraft component; the topology optimization result of the target aircraft component includes a plurality of tetrahedral meshes; determining the sensitivity of each vertex in each of the tetrahedral meshes; comparing the sensitivity of each vertex in each of the tetrahedral meshes with the value of the isosurface to determine the marked voxel type of each of the tetrahedral meshes; and determining a post-processing mesh model corresponding to the structured model of the target aircraft component based on the voxels corresponding to each of the tetrahedral meshes. The present invention achieves the purpose of improving the work efficiency of lightweighting of aircraft component structures.

Description

Technical Field

[0001] The present invention relates to the technical field of lightweighting of aerospace component structures, and particularly to a post-processing method and system for topology optimization of aerospace component structure lightweighting. Background Art

[0002] With the increasing demand for material lightweighting in fields such as aerospace, topology optimization technology has played an increasingly important role in material weight reduction.

[0003] The existing post-processing method for topology optimization uses the Marching Cubes algorithm, but it requires that the computational grid must all be hexahedral grids, and it is very difficult to successfully perform hexahedral grid meshing for complex models. Therefore, tetrahedral grid meshing is generally used for complex model calculations. After the tetrahedral grid calculation is completed, the grid boundaries are very rough, so a large amount of manual re-modeling operations are still required, which reduces the work efficiency of aerospace component structure lightweighting. Summary of the Invention

[0004] The purpose of the present invention is to provide a post-processing method and system for topology optimization of aerospace component structure lightweighting, so as to achieve the purpose of improving the work efficiency of aerospace component structure lightweighting.

[0005] To achieve the above purpose, the present invention provides the following solutions:

[0006] A post-processing method for topology optimization of aerospace component structure lightweighting, comprising:

[0007] Construct a structured model of the target aerospace component, and perform topology optimization processing on the structured model of the target aerospace component to obtain a topology optimization result of the target aerospace component; the topology optimization result of the target aerospace component includes a plurality of tetrahedral grids;

[0008] Determine the sensitivity of each vertex in each of the tetrahedral networks;

[0009] Compare the sensitivity of each vertex in each tetrahedral grid with the value of the isosurface to determine the marked voxel type of each tetrahedral grid;

[0010] Based on the voxels corresponding to each tetrahedral grid, determine a post-processing grid model corresponding to the structured model of the target aerospace component.

[0011] Optionally, the performing topology optimization processing on the structured model of the target aerospace component to obtain a topology optimization result of the target aerospace component specifically includes:

[0012] Adopt a finite element method to perform tetrahedral meshing on the structured model of the target aerospace component to obtain a topology optimization result of the target aerospace component.

[0013] Optionally, determining the sensitivity of each vertex in each of the tetrahedral networks specifically includes:

[0014] Taking the compliance of the target aircraft part as the objective function, determining the sensitivity of each vertex in each of the tetrahedral networks.

[0015] Optionally, comparing the sensitivity of each vertex in each of the tetrahedral meshes with the value of the isosurface to determine the type of volume element marked for each of the tetrahedral meshes specifically includes:

[0016] Comparing the sensitivity of each vertex in each of the tetrahedral meshes with the value of the isosurface,

[0017] When the sensitivity of any vertex in the target tetrahedral mesh is not higher than the value of the isosurface, the target tetrahedral mesh is marked as an empty element;

[0018] When only one vertex in the target tetrahedral mesh has a sensitivity higher than the value of the isosurface, the target tetrahedral mesh is marked as a corner volume element;

[0019] When only two vertices in the target tetrahedral mesh have sensitivities higher than the value of the isosurface, the target tetrahedral mesh is marked as a triangular prism volume element;

[0020] When only three vertices in the target tetrahedral mesh have sensitivities higher than the value of the isosurface, the target tetrahedral mesh is marked as a frustum volume element;

[0021] When the sensitivities of all four vertices in the target tetrahedral mesh are higher than the value of the isosurface, the target tetrahedral mesh is marked as a tetrahedron volume element;

[0022] Wherein, the target tetrahedral mesh is any tetrahedral mesh.

[0023] Optionally, based on the volume element corresponding to each of the tetrahedral meshes, determining the post-processing mesh model corresponding to the structured model of the target aircraft part specifically includes:

[0024] Performing linear interpolation calculations based on the type of volume element marked for each tetrahedral mesh to obtain the volume element corresponding to each of the tetrahedral meshes, and then constructing a volume element cluster with overlapping faces;

[0025] Removing the overlapping faces in a volume element cluster with overlapping faces to determine the post-processing mesh model corresponding to the structured model of the target aircraft part.

[0026] A topology optimization post-processing system for aircraft part structure lightweighting, comprising:

[0027] The target aircraft part topology optimization result determination module is used to construct a structured model of the target aircraft part and perform topology optimization processing on the structured model of the target aircraft part to obtain the topology optimization result of the target aircraft part; the topology optimization result of the target aircraft part includes a plurality of tetrahedral meshes;

[0028] The sensitivity calculation module is used to determine the sensitivity of each vertex in each of the tetrahedral meshes;

[0029] The element type determination module is used to compare the sensitivity of each vertex in each of the tetrahedral meshes with the value of the isosurface to determine the marked element type of each of the tetrahedral meshes;

[0030] The post-processing mesh model determination module is used to determine the post-processing mesh model corresponding to the structured model of the target aircraft part based on the elements corresponding to each of the tetrahedral meshes.

[0031] Optionally, the target aircraft part topology optimization result determination module specifically includes:

[0032] The optimization unit is used to perform tetrahedral meshing on the structured model of the target aircraft part in a finite element manner to obtain the topology optimization result of the target aircraft part.

[0033] Optionally, the sensitivity calculation module specifically includes:

[0034] The calculation unit is used to use the compliance of the target aircraft part as the objective function to determine the sensitivity of each vertex in each of the tetrahedral meshes.

[0035] Optionally, the element type determination module specifically includes:

[0036] Compare the sensitivity of each vertex in each of the tetrahedral meshes with the value of the isosurface,

[0037] When the sensitivity of any vertex in the target tetrahedral mesh is not higher than the value of the isosurface, the target tetrahedral mesh is marked as an empty element;

[0038] When only one vertex in the target tetrahedral mesh has a sensitivity higher than the value of the isosurface, the target tetrahedral mesh is marked as a corner element;

[0039] When only two vertices in the target tetrahedral mesh have sensitivities higher than the value of the isosurface, the target tetrahedral mesh is marked as a triangular prism element;

[0040] When only three vertices in the target tetrahedral mesh have sensitivities higher than the value of the isosurface, the target tetrahedral mesh is marked as a frustum element;

[0041] When the sensitivities of the four vertices in the target tetrahedral mesh are all higher than the value of the isosurface, the target tetrahedral mesh is marked as a tetrahedral volume element;

[0042] Wherein, the target tetrahedral mesh is any tetrahedral mesh.

[0043] Optionally, the post-processing mesh model determination module specifically includes:

[0044] A volume element cluster construction unit, configured to perform linear interpolation calculation based on the volume element type marked for each tetrahedral mesh to obtain the volume element corresponding to each tetrahedral mesh, and further construct a volume element cluster with overlapping faces;

[0045] A post-processing mesh model determination unit, configured to remove the overlapping faces in a volume element cluster with overlapping faces, and determine the post-processing mesh model corresponding to the target aircraft part structured model.

[0046] According to the specific embodiments provided by the present invention, the following technical effects are disclosed:

[0047] The present invention first performs topology optimization processing on a complex target aircraft part structured model to obtain a plurality of tetrahedral meshes, then determines the sensitivity of each vertex in each tetrahedral network, compares the sensitivity of each vertex in each tetrahedral mesh with the value of the isosurface, determines the volume element type marked for each tetrahedral mesh, and finally determines the post-processing mesh model corresponding to the target aircraft part structured model based on the volume element corresponding to each tetrahedral mesh, realizing tetrahedral mesh division of the complex model, and making the mesh boundary smooth through the above post-processing method, avoiding the operation of manually re-modeling with a large amount of manpower, thereby improving the work efficiency of aircraft part structure lightweighting. Description of the Drawings

[0048] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for use in the embodiments. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0049] Figure 1 It is a schematic flow chart of a topology optimization post-processing method for aircraft part structure lightweighting according to the present invention;

[0050] Figure 2 It is a schematic diagram of an empty unit according to the present invention;

[0051] Figure 3 It is a schematic diagram of a corner volume element according to the present invention;

[0052] Figure 4Schematic diagram of the triangular prism element of the present invention;

[0053] Figure 5 Schematic diagram of the frustum element of the present invention;

[0054] Figure 6 Schematic diagram of the tetrahedron element of the present invention;

[0055] Figure 7 Schematic diagram of the linear interpolation principle of the present invention;

[0056] Figure 8 Schematic diagram of the tetrahedron cluster composed of the frustum element and the tetrahedron element of the present invention;

[0057] Figure 9 Schematic diagram of the inclusion grid formed by the elements with duplicate faces removed according to the present invention;

[0058] Figure 10 Object composed of the tetrahedron cluster according to the present invention;

[0059] Figure 11 Schematic diagram of the network model before tetrahedron-based topology optimization according to the present invention;

[0060] Figure 12 Schematic diagram of the network model after tetrahedron-based topology optimization according to the present invention;

[0061] Figure 13 Schematic diagram of the structure of the topology optimization post-processing system for lightweighting the structure of an aviation part according to the present invention. Specific implementation mode

[0062] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0063] To make the above objects, features, and advantages of the present invention more obvious and understandable, the present invention will be further described in detail below in conjunction with the accompanying drawings and specific implementation modes.

[0064] Embodiment 1

[0065] The embodiment of the present invention provides a topology optimization post-processing method for lightweighting the structure of an aviation part, which is used to solve the problem of low efficiency such as re-modeling in the existing topology optimization post-processing, and mainly includes: determining sensitivity data and tetrahedron clusters after topology optimization and setting appropriate isosurface values; generating a number of individual elements based on these data, and obtaining a smooth post-processing grid model after removing the duplicate faces of the elements.

[0066] As shown Figure 1 in the figure, the post - processing method for topology optimization of the lightweight structure of an aviation part provided by the embodiment of the present invention includes the following steps.

[0067] Step 101: Construct a structural model of the target aviation part, and perform topology optimization processing on the structural model of the target aviation part to obtain the topology optimization result of the target aviation part; the topology optimization result of the target aviation part includes a plurality of tetrahedral meshes, that is, a tetrahedral cluster; among them, the tetrahedral cluster means: the object is tetrahedrally meshed, and the object is composed of a number of tetrahedral meshes.

[0068] Specifically, this step includes: using the finite element method to perform tetrahedral meshing on the structural model of the target aviation part to obtain the topology optimization result of the target aviation part.

[0069] Step 102: Determine the sensitivity of each vertex in each of the tetrahedral networks.

[0070] The sensitivity refers to: after the topology optimization calculation is completed, the value of the sensitivity of each vertex of the tetrahedral mesh, and its value represents the change of the performance index related to the design variable.

[0071] Specifically, this step includes: taking the compliance of the target aviation part as the objective function to determine the sensitivity of each vertex in each of the tetrahedral networks.

[0072] Further explanation is as follows:

[0073] In finite element analysis, the equilibrium equation of the aviation part structure can be expressed as: Ku = f.

[0074] The expression of compliance is C = 1 / 2f T u.

[0075] Where, K - structural stiffness matrix; u - displacement vector; f - load vector; T - transpose.

[0076] In the embodiment of the present invention, the compliance is used as the objective function, and it is assumed that the design variable x changes continuously from 1 to x min Then the sensitivity of the objective function corresponding to the change of the design variable is:

[0077]

[0078] Step 103: Compare the sensitivity of each vertex in each of the tetrahedral meshes with the value of the isosurface to determine the type of volume element marked for each of the tetrahedral meshes.

[0079] The value of the appropriate isosurface refers to: based on the topology optimization result, extracting the sensitivity at the critical cell edges of the tetrahedral elements to be deleted as the value of the isosurface. Or a suitable threshold determined by methods such as reverse verification.

[0080] To more clearly illustrate how the embodiments of the present invention process the existing sensitivity and tetrahedrons into several voxels, the following introductions are made:

[0081] Based on the sensitivity levels of each vertex of the tetrahedral mesh (vertices with sensitivities higher than the value of the isosurface are represented by black dots), the basic form of this voxel can be divided into the following five types:

[0082] First, if there is no case where the sensitivity value of any vertex is not higher than the value of the isosurface ( Figure 2 ), it is an empty cell and does not form any figure.

[0083] Second, if there is only one vertex with a sensitivity value higher than the value of the isosurface ( Figure 3 ), a corner is formed.

[0084] Third, if there are two vertices with sensitivity values higher than the value of the isosurface ( Figure 4 ), a shape similar to a triangular prism is formed.

[0085] Fourth, if there are three vertices with sensitivity values higher than the value of the isosurface ( Figure 5 ), a frustum is formed.

[0086] Fifth, if the sensitivity values of all four vertices are higher than the value of the isosurface ( Figure 6 ), it is the tetrahedron itself.

[0087] Therefore, this step specifically includes: comparing the sensitivity of each vertex in each of the tetrahedral meshes with the value of the isosurface:

[0088] When the sensitivity of any vertex in the target tetrahedral mesh is not higher than the value of the isosurface, the target tetrahedral mesh is marked as an empty cell.

[0089] When only one vertex in the target tetrahedral mesh has a sensitivity higher than the value of the isosurface, the target tetrahedral mesh is marked as a corner voxel.

[0090] When only two vertices in the target tetrahedral mesh have sensitivities higher than the value of the isosurface, the target tetrahedral mesh is marked as a triangular prism voxel.

[0091] When only three vertices in the target tetrahedral mesh have sensitivities higher than the value of the isosurface, the target tetrahedral mesh is marked as a frustum voxel.

[0092] When the sensitivities of the four vertices in the target tetrahedral mesh are all higher than the value of the isosurface, the target tetrahedral mesh is marked as a tetrahedral volume element.

[0093] Among them, the target tetrahedral mesh is any tetrahedral mesh.

[0094] Step 104: Determine the post-processing mesh model corresponding to the target aircraft structural model based on the volume elements corresponding to each tetrahedral mesh.

[0095] This step specifically includes performing linear interpolation calculations based on the volume element types marked for each tetrahedral mesh to obtain the volume elements corresponding to each tetrahedral mesh, and then constructing a volume element cluster with duplicate faces; among them, when the tetrahedral mesh is marked as an empty element, it is directly removed.

[0096] Remove the duplicate faces in a volume element cluster with duplicate faces to determine the post-processing mesh model corresponding to the target aircraft structural model.

[0097] An example is: Each type of volume element can be linearly interpolated. Taking the basic volume element numbered 1 as an example, after interpolation, it is as shown in Figure 3 . The sensitivity value of the upper vertex is 0, the sensitivity value of the left vertex is 15, and the value of the set isosurface is 10. Therefore, a point A is inserted at two-thirds of the line between 0 and 15. Points B and C are obtained in this way, and then points A, B, C, and D are connected to form a new volume element ( Figure 7 gray area). Figure 7 gray area).

[0098] Taking a simple tetrahedral cluster as an example ( Figure 8 composed of three volume elements with basic volume element numbers 3, 4, and 4), according to the different sensitivity values of the vertices, set a suitable value for the isosurface and perform linear interpolation ( Figure 7 ), and substitute it into the tetrahedral cluster to obtain a volume element cluster with duplicate faces ( Figure 8 dark gray are the duplicate faces). Remove the duplicate faces of the volume element cluster ( Figure 8 ), and obtain a wrapped body mesh ( Figure 9 ).

[0099] Embodiment 2

[0100] A method for post-processing a topology optimization mesh based on tetrahedral meshing according to the present invention includes the following steps:

[0101] 1. Obtain the sensitivity data and tetrahedral cluster in the topology optimization result (such as Figure 10 ) and set a suitable value for the isosurface as an input condition.

[0102] 2. Combine the tetrahedron data and the sensitivity data of the tetrahedron vertices, and use 5 basic voxel types to process them into a number of voxels.

[0103] 3. After removing the duplicate faces of each voxel, a smoothed post-processing mesh model is obtained as the output model.

[0104] Figure 11 and Figure 12 is a model of one-eighth of an aircraft engine disk. Figure 11 is the mesh obtained without post-processing after the topological optimization of the tetrahedron meshing. The mesh boundary at the mesh deletion part is very rough with many spines. Figure 12 After being processed by this method, the obtained mesh is smoother and meets the mesh conditions for manufacturing such as 3D printing.

[0105] Example 3

[0106] As Figure 13 shown, the embodiment of the present invention provides a topological optimization post-processing system for the lightweight of an aviation part structure, including:

[0107] A target aviation part topological optimization result determination module 100, configured to construct a structured model of the target aviation part, and perform topological optimization processing on the structured model of the target aviation part to obtain a target aviation part topological optimization result; the target aviation part topological optimization result includes a plurality of tetrahedron meshes.

[0108] A sensitivity calculation module 200, configured to determine the sensitivity of each vertex in each of the tetrahedron networks.

[0109] A voxel type determination module 300, configured to compare the sensitivity of each vertex in each of the tetrahedron meshes with the value of the isosurface, and determine the voxel type marked for each of the tetrahedron meshes.

[0110] A post-processing mesh model determination module 400, configured to determine a post-processing mesh model corresponding to the structured model of the target aviation part based on the voxels corresponding to each of the tetrahedron meshes.

[0111] The target aviation part topological optimization result determination module 100 specifically includes:

[0112] An optimization unit, configured to perform tetrahedron meshing on the structured model of the target aviation part in a finite element manner to obtain a target aviation part topological optimization result.

[0113] The sensitivity calculation module 200 specifically includes:

[0114] A calculation unit, configured to use the compliance of the target aviation part as an objective function to determine the sensitivity of each vertex in each of the tetrahedron networks.

[0115] The voxel type determination module specifically includes:

[0116] Compare the sensitivity of each vertex in each of the tetrahedral meshes with the value of the isosurface.

[0117] When the sensitivity of any vertex in the target tetrahedral mesh is not higher than the value of the isosurface, the target tetrahedral mesh is marked as an empty cell;

[0118] When only one vertex in the target tetrahedral mesh has a sensitivity higher than the value of the isosurface, the target tetrahedral mesh is marked as a corner voxel;

[0119] When only two vertices in the target tetrahedral mesh have sensitivities higher than the value of the isosurface, the target tetrahedral mesh is marked as a triangular prism voxel;

[0120] When only three vertices in the target tetrahedral mesh have sensitivities higher than the value of the isosurface, the target tetrahedral mesh is marked as a frustum voxel;

[0121] When the sensitivities of all four vertices in the target tetrahedral mesh are higher than the value of the isosurface, the target tetrahedral mesh is marked as a tetrahedral voxel;

[0122] Wherein, the target tetrahedral mesh is any tetrahedral mesh.

[0123] The post - processing mesh model determination module 400 specifically includes:

[0124] A voxel cluster construction unit, configured to perform linear interpolation calculations based on the marked voxel types of each tetrahedral mesh to obtain the voxels corresponding to each tetrahedral mesh, and then construct a voxel cluster with overlapping faces.

[0125] A post - processing mesh model determination unit, configured to remove the overlapping faces in a voxel cluster with overlapping faces to determine the post - processing mesh model corresponding to the target aviation part structured model.

[0126] The various embodiments in this specification are described in a progressive manner. Each embodiment focuses on the differences from other embodiments. The same or similar parts among the various embodiments can be referred to each other. For the system disclosed in the embodiments, since it corresponds to the method disclosed in the embodiments, the description is relatively simple, and the relevant parts can be referred to the description in the method section.

[0127] In this article, specific examples are used to elaborate on the principles and implementation manners of the present invention. The description of the above embodiments is only used to help understand the method of the present invention and its core idea; at the same time, for those of ordinary skill in the art, according to the idea of the present invention, there will be changes in the specific implementation manners and application scopes. In summary, the content of this specification should not be construed as a limitation to the present invention.

Claims

1. A post - processing method for topology optimization of lightweight aircraft component structures, characterized in that, it includes: Construct a structured model of the target aircraft component, and perform topology optimization on the structured model of the target aircraft component to obtain the topology optimization result of the target aircraft component; The topology optimization result of the target aircraft component includes a plurality of tetrahedral meshes; Determine the sensitivity of each vertex in each of the tetrahedral meshes; Compare the sensitivity of each vertex in each tetrahedral mesh with the value of the isosurface to determine the type of volume element marked for each tetrahedral mesh. Specifically, it includes: Compare the sensitivity of each vertex in each tetrahedral mesh with the value of the isosurface, When the sensitivity of any vertex in the target tetrahedral mesh is not higher than the value of the isosurface, the target tetrahedral mesh is marked as an empty element; When only one vertex in the target tetrahedral mesh has a sensitivity higher than the value of the isosurface, the target tetrahedral mesh is marked as a corner volume element; When only two vertices in the target tetrahedral mesh have sensitivities higher than the value of the isosurface, the target tetrahedral mesh is marked as a triangular prism volume element; When only three vertices in the target tetrahedral mesh have sensitivities higher than the value of the isosurface, the target tetrahedral mesh is marked as a frustum volume element; When the sensitivities of all four vertices in the target tetrahedral mesh are higher than the value of the isosurface, the target tetrahedral mesh is marked as a tetrahedral volume element; wherein, the target tetrahedral mesh is any tetrahedral mesh; Based on the volume element corresponding to each tetrahedral mesh, determine the post - processing mesh model corresponding to the structured model of the target aircraft component.

2. The post - processing method for topology optimization of lightweight aircraft component structures according to claim 1, characterized in that, The performing topology optimization on the structured model of the target aircraft component to obtain the topology optimization result of the target aircraft component specifically includes: Using the finite element method, perform tetrahedral meshing on the structured model of the target aircraft component to obtain the topology optimization result of the target aircraft component.

3. The post - processing method for topology optimization of lightweight aircraft component structures according to claim 1, characterized in that, The determining the sensitivity of each vertex in each of the tetrahedral meshes specifically includes: Taking the compliance of the target aircraft component as the objective function, determine the sensitivity of each vertex in each of the tetrahedral meshes.

4. The post - processing method for topology optimization of lightweight aircraft component structures according to claim 1, characterized in that, The determining the post - processing mesh model corresponding to the structured model of the target aircraft component based on the volume element corresponding to each tetrahedral mesh specifically includes: Perform linear interpolation calculation based on the type of volume element marked for each tetrahedral mesh to obtain the volume element corresponding to each tetrahedral mesh, and then construct a volume element cluster with repeated faces; Remove the repeated faces in a volume element cluster with repeated faces to determine the post - processing mesh model corresponding to the structured model of the target aircraft component.

5. A post - processing system for topology optimization of lightweight aircraft component structures, characterized in that, it includes: The target aircraft component topology optimization result determination module is used to construct a structured model of the target aircraft component and perform topology optimization processing on the structured model of the target aircraft component to obtain the topology optimization result of the target aircraft component; The topology optimization result of the target aircraft component includes a plurality of tetrahedral meshes; The sensitivity calculation module is used to determine the sensitivity of each vertex in each of the tetrahedral meshes; The volume element type determination module is used to compare the sensitivity of each vertex in each tetrahedral mesh with the value of the isosurface to determine the marked volume element type of each tetrahedral mesh, specifically including: Comparing the sensitivity of each vertex in each tetrahedral mesh with the value of the isosurface; When the sensitivity of any vertex in the target tetrahedral mesh is not higher than the value of the isosurface, the target tetrahedral mesh is marked as an empty element; When only one vertex in the target tetrahedral mesh has a sensitivity higher than the value of the isosurface, the target tetrahedral mesh is marked as a corner volume element; When only two vertices in the target tetrahedral mesh have sensitivities higher than the value of the isosurface, the target tetrahedral mesh is marked as a triangular prism volume element; When only three vertices in the target tetrahedral mesh have sensitivities higher than the value of the isosurface, the target tetrahedral mesh is marked as a frustum volume element; When the sensitivities of all four vertices in the target tetrahedral mesh are higher than the value of the isosurface, the target tetrahedral mesh is marked as a tetrahedral volume element; Wherein, the target tetrahedral mesh is any tetrahedral mesh; The post-processing mesh model determination module is used to determine the post-processing mesh model corresponding to the structured model of the target aircraft component based on the volume element corresponding to each tetrahedral mesh.

6. The topology optimization post-processing system for aircraft component structure lightweighting according to claim 5, characterized in that, The target aircraft component topology optimization result determination module specifically includes: An optimization unit is used to perform tetrahedral meshing on the structured model of the target aircraft component in a finite element manner to obtain the topology optimization result of the target aircraft component.

7. The topology optimization post-processing system for aircraft component structure lightweighting according to claim 5, characterized in that, The sensitivity calculation module specifically includes: A calculation unit is used to take the compliance of the target aircraft component as the objective function to determine the sensitivity of each vertex in each of the tetrahedral meshes.

8. The topology optimization post-processing system for aircraft component structure lightweighting according to claim 5, characterized in that, The post-processing mesh model determination module specifically includes: A volume element cluster construction unit is used to perform linear interpolation calculation based on the marked volume element type of each tetrahedral mesh to obtain the volume element corresponding to each tetrahedral mesh, and then construct a volume element cluster with repeated faces; A post-processing mesh model determination unit is used to remove the repeated faces in a volume element cluster with repeated faces to determine the post-processing mesh model corresponding to the structured model of the target aircraft component.

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