Parametric modeling method, system, equipment and medium for civil aircraft finite element model

Abstract

The invention relates to a parametric modeling method, system and device for a civil aircraft finite element model and a medium. The method comprises the following steps of S1, performing mesh generation on an original model to generate a natural mesh model; performing fine granularity decomposition on the complete original model into grid units reflecting the main bearing force construction of the aircraft structure; s2, multi-scene synchronous rendering and interaction analysis are carried out; and restoring the grid unit into a three-dimensional finite element model at a Web end, providing a planar finite element model in a two-dimensional scene, and synchronously constructing a self-defined cloud database at a server end. According to the method, the model data is analyzed, normatively updated and shared by constructing the cloud database, and a three-dimensional scene and two-dimensional scene visualization combined linkage model operation mode is provided for engineering designers to intuitively and accurately complete parametric modeling and analysis of the finite element model.

Description

Technical Field

[0001] The present invention relates to the field of aviation, and in particular to a parametric modeling method, system, equipment and medium for a finite element model of a civil aircraft. Background Art

[0002] As the complexity of civil aircraft structures increases, the corresponding parametric models also become more complex, which not only increases the difficulty of modeling, but also requires designers to spend more time and energy to adjust parameters for finite element analysis. There are often multiple complex correlations between various parameters. Improper handling will lead to a reduction in the space for design optimization and limit the ability of engineering designers to find the optimal solution.

[0003] At present, most engineers use manual parametric modeling methods, which require manual reference to various information to update model data. When errors occur in the manual process, it is necessary to find the errors based on the results and feedback to the upstream after the strength calculation and analysis process is completed. This process consumes a lot of time and manpower. When rendering the model, it is difficult to accurately locate elements when using a three-dimensional view to modify data, and it is more difficult to perform batch operations on model units than in a two-dimensional scene.

[0004] Of course, some existing parametric modeling methods are also developed based on Excel and VB, but the code readability is poor, it is difficult to upgrade or modify functions, and it is not easy to maintain when the code is wrong; and it is necessary to manually generate a two-dimensional view of the model in Excel, which consumes more manpower costs. In addition, the profiles, plies and material data of each aircraft model are scattered in different Excel tables of a single machine. The operation process is complicated and cumbersome, and engineers are prone to errors when modifying and manually synchronizing data. It can be seen that the existing parametric modeling technology has deficiencies in data information integration, and it is difficult to achieve true collaborative design. In addition, this method only displays the model in two dimensions, which is poorly understandable.

[0005] Existing parametric modeling technology also has deficiencies in flexibility and reusability. Due to the high degree of specificity of the model, the reuse rate of models between different projects is low. When design requirements change, engineering designers often need to rebuild the model instead of simply adjusting the existing model, which results in high design costs. Summary of the invention

[0006] In view of the above-mentioned defects of the prior art, a first aspect of the present invention provides a parametric modeling method for a civil aircraft finite element model, which comprises the following steps:

[0007] Step S1: meshing the original model to generate a natural mesh model; fine-grained decomposition of the complete original model into mesh units reflecting the main bearing force of the aircraft structure, each mesh unit corresponding to a different component of the original model, and each mesh unit containing attribute information of the corresponding part;

[0008] Step S2: synchronous rendering and interactive analysis of multiple scenes; restoring the grid unit to a three-dimensional finite element model on the Web side, providing a plane finite element model in a two-dimensional scene, and synchronously building a custom cloud database on the server side; the attribute information of each grid unit is stored in the cloud database, and the cloud database includes a profile library, a ply library, and a material library.

[0009] In the parametric modeling method of the civil aircraft finite element model as described above, optionally, the step S1 includes the following steps:

[0010] Step S1.1: importing the original model into finite element pre-processing software Hypermesh;

[0011] Step S1.2: meshing the original model to create a natural mesh model required for finite element analysis;

[0012] Step S1.3: exporting the natural mesh model into a BDF file in Nastran BDF format; the BDF file includes a plurality of BDF cards, each of the BDF cards corresponds to each of the mesh units.

[0013] In the parametric modeling method of the finite element model of a civil aircraft as described above, optionally, in the step S1.2, the digital model of the aircraft structure skeleton is used as the basis for the meshing.

[0014] In the parametric modeling method of the civil aircraft finite element model as described above, optionally, step S2 includes the following steps:

[0015] Step S2.1: importing the natural grid model on the Web end;

[0016] Step S2.2: converting the natural mesh model into the three-dimensional finite element model by using finite element analysis software and a three-dimensional visualization component;

[0017] Step S2.3: Reduce the dimension of the three-dimensional finite element model to form a two-dimensional finite element model through a two-dimensional visualization component and provide a linkage synchronization operation mechanism, so that the user's operation on the finite element model in any view can be reflected in real time on another view.

[0018] In the parametric modeling method of the civil aircraft finite element model as described above, optionally, the cloud database is inserted into the finite element analysis software as a basic service. In step S2, all operations performed by the user on the model data of the three-dimensional finite element model will be synchronously updated in real time to the cloud database for user query and analysis.

[0019] In the parametric modeling method of the civil aircraft finite element model as described above, optionally, the finite element analysis software is PyNastran, and the finite element analysis of the three-dimensional finite element model is performed by running the built-in solver of the finite element analysis software and combining the attribute information in the cloud database.

[0020] In the parametric modeling method of the civil aircraft finite element model as described above, optionally, the cloud database is a NoSQL database MongoDB; the profile library includes profile cross-section information required to construct the three-dimensional finite element model, the layup library includes composite material layups and metal shell element property information required to construct the three-dimensional finite element model, and the material library includes composite material and metal material information required to construct the three-dimensional finite element model.

[0021] In order to achieve the above-mentioned purpose, the second aspect of the present invention provides a parametric modeling system for civil aircraft finite element models. The front end of the parametric modeling system uses Vue.js to build a user interface, create components, routes, and state management; the server uses Python to develop database interaction and API interfaces; the database uses MongoDB to create collections and indexes. It includes:

[0022] A model building module, the model building module includes a natural mesh model module and a finite element model module; the natural mesh model module has a built-in finite element pre-processing software Hypermesh; the finite element model module has a built-in data processing engine;

[0023] A rendering interaction module, wherein the rendering module has built-in three-dimensional visualization components and two-dimensional visualization components;

[0024] Cloud database; the cloud database includes a profile library, a layer library, and a material library.

[0025] In order to achieve the above-mentioned purpose, the third aspect of the present invention provides a computer device, including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein when the processor runs the program, the steps of the parametric modeling method of the civil aircraft finite element model as described in any one of the first aspects above are implemented.

[0026] In order to achieve the above-mentioned purpose, the fourth aspect of the present invention provides a computer-readable medium, wherein the computer-readable storage medium stores computer-executable instructions or computer programs, and when the computer-executable instructions or computer programs are processed and executed, the parametric modeling method of the civil aircraft finite element model as described in any one of the first aspects above is implemented.

[0027] The parametric modeling method of a civil aircraft finite element model provided by the present invention realizes the analysis, standardized update and sharing of model data by constructing a cloud database, and provides a method of combining three-dimensional scene and two-dimensional scene visualization with a linkage operation model so that engineering designers can intuitively and accurately complete the parametric modeling and analysis of the finite element model.

[0028] The concept, specific structure and technical effects of the present invention will be further described below in conjunction with the accompanying drawings to fully understand the purpose, characteristics and effects of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 It is a schematic flow chart of a parametric modeling method of a civil aircraft finite element model of the present invention;

[0030] Figure 2 yes Figure 1 A detailed flow chart of the parametric modeling method for the finite element model of the civil aircraft;

[0031] Figure 3 It is a structural schematic diagram of a parametric modeling system of a civil aircraft finite element model of the present invention. DETAILED DESCRIPTION

[0032] In order to make the technical means, creative features, objectives and effects of the invention easier to understand, the invention is further described below with reference to specific diagrams. However, the invention is not limited to the following implementation cases.

[0033] It should be noted that the structures, proportions, sizes, etc. illustrated in the drawings in this specification are only used to match the contents disclosed in the specification so as to facilitate understanding and reading by persons familiar with this technology. They are not used to limit the conditions under which the present invention can be implemented, and therefore have no substantive technical significance. Any structural modification, change in proportion or adjustment of size, without affecting the effects and purposes that can be achieved by the present invention, should still fall within the scope of the technical contents disclosed by the present invention.

[0034] Terms such as “comprise” and “include” indicate that in addition to the components directly and explicitly stated in the specification and claims, the technical solution of the present invention does not exclude the situation where it has other components that are not directly or explicitly stated.

[0035] It should also be noted that the terms "upper", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present disclosure and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present disclosure.

[0036] In addition, the term "and / or" in this article is only a description of the association relationship of the associated objects, indicating that there can be three relationships. For example, A and / or B can represent: A exists alone, A and B exist at the same time, and B exists alone. In addition, the character " / " in this article generally indicates that the associated objects before and after are in an "or" relationship.

[0037] Parametric modeling is the process of creating and editing models by introducing parameters. When engineers add new parameters, all objects in the model are automatically created and changed, and the characteristics and relationships of each element in the model are determined.

[0038] from Figure 1 and Figure 2 It can be seen that the parametric modeling of the civil aircraft finite element model of the present invention may include the following steps:

[0039] Step S1: Meshing the locally imported original model to generate a natural mesh model.

[0040] Step S2: Simultaneous rendering of multiple scenes to construct a finite element model and interactive analysis, and output an updated finite element model.

[0041] A model is a description of a three-dimensional object using a strictly defined language or data structure, which can include information such as geometry, viewpoint, and texture.

[0042] In step S1, the complete original model of the civil aircraft is finely decomposed to form grid units that reflect the main load-bearing structure of the aircraft structure. Each grid unit corresponds to a different component of the civil aircraft in the original model, and records the attribute information of the corresponding part to prepare for subsequent finite element analysis. The natural grid model can generate a grid that fits the geometric shape closely, so as to facilitate accurate geometric analysis or as a pre-step for finite element analysis. Through further processing and analysis, it can be converted into a finite element model suitable for numerical analysis.

[0043] Finite element analysis (FEA) is a process that predicts the deflection and other stress effects of a structure. In finite element analysis, a continuous complete physical structure such as the civil aircraft of the present invention is divided into many grid units for the convenience of numerical calculation and analysis. A grid unit refers to a model of the actual structure formed by disassembling a complete 3D civil aircraft original model into multiple small parts or small components. These small parts or small components can be substructures. Each model grid unit has a series of specific attribute information corresponding to different parts of the model, such as geometric shape, material properties (such as elastic modulus, Poisson's ratio, etc.), boundary conditions, load conditions, etc., which can accurately reflect the characteristic attributes of a specific part of the model and interact with each other in the entire modeling process of simulating physical phenomena (such as stress, strain, temperature distribution, displacement, etc.). Engineering designers can process and update data on the selected model grid units during the parametric modeling process to adjust the parameters of different parts of the model and improve the model in an individualized manner.

[0044] In an optional embodiment, step S1 may specifically include the following steps:

[0045] Step S1.1: Import the original model into the finite element pre-processing software Hypermesh.

[0046] Step S1.2: Mesh the original model to create a natural mesh model required for finite element analysis.

[0047] Specifically, the meshing of the natural mesh model generates meshes according to the natural features of the geometric shape (such as curves and surfaces), which conform to the authenticity of the geometric shape and can better capture the geometric features. In this step, the engineering designer can use the digital model of the aircraft structure skeleton (the fuselage is based on frames and long stringers, and the wing surface is based on ribs and long stringers) as the basis for the meshing.

[0048] Step S1.3: Export the natural mesh model to a BDF (Bulk Data Format) file in Nastran BDF format.

[0049] The BDF file includes multiple BDF cards, each BDF card corresponds to a grid unit of each model, that is, the information of each model grid unit is stored and managed through the BDF card, and the BDF card serves as the information carrier of each model grid unit.

[0050] The natural grid model here refers to a three-dimensional model composed of multiple grid units used in computer-aided design (CAD) or engineering analysis. BDF file is a file format for storing finite element analysis data, which can be used in finite element analysis software Nastran. A BDF file is composed of multiple BDF cards in a certain order and format. Since each BDF card records the various different parts of the finite element model and its attribute information, the BDF file composed of multiple BDF cards can organize these BDF cards together to form a complete finite element model data file, fully describe each part of the aircraft, and construct a finite element model. In this embodiment, the attribute information included in the BDF card includes but is not limited to the structural unit type, geometric shape, material properties, ply material and quantity, boundary conditions, three-dimensional coordinate node position, etc. of the aircraft parts.

[0051] In the present invention, the BDF card is used to import, parse, update and output the data of the finite element model. Through the BDF card, the mesh unit of the model can be read, parsed, converted, updated and output by the BDF processing engine to ensure the data accuracy and consistency of the mesh unit of the model. In an optional embodiment, the BDF processing engine can be the finite element analysis software PyNastran.

[0052] In step S2, the mesh unit of the model is restored to a three-dimensional finite element model on the Web side, and a plane finite element model is provided in a two-dimensional scene, and a custom cloud database is synchronously built on the server side for integrating various types of data information, real-time synchronous data update, analysis and sharing. It should also be noted here that in this step, the cloud database is inserted into the finite element analysis software as a basic service, and all operations performed by the user on the model data of the three-dimensional finite element model will be synchronously updated in real time to the cloud database for user query and analysis.

[0053] In an optional embodiment, the cloud database is specifically a NoSQL database (non-relational database) MongoDB. The cloud database may specifically include a profile library, a layer library, and a material library. The profile library may include profile section information (such as trapezoidal steel, I-beam, etc.) required for building a three-dimensional finite element model, the layer library may include composite material layers (such as skins, partitions, etc.) and metal shell element attribute information required for building a three-dimensional finite element model, and the material library may include composite material and metal material information required for building a three-dimensional finite element model.

[0054] The three-dimensional finite element model uses discretization to convert continuous media into discrete problems that can be solved by numerical methods.

[0055] In an optional embodiment, step S2 may specifically include the following steps:

[0056] Step S2.1: Import the above natural mesh model on the Web.

[0057] In an optional embodiment, the natural mesh model BDF file (including model data) imported from the Web side can be parsed on the server side by the finite element analysis software PyNastran.

[0058] Step S2.2: The natural mesh model is converted into a three-dimensional finite element model by using finite element analysis software and a three-dimensional visualization component.

[0059] In an optional embodiment, the finite element analysis software is PyNastran, which is used to identify and parse the information in the BDF file, such as nodes, units, material properties, boundary conditions and loads in the natural mesh model, so as to obtain the complete data of the model, restore the details of each part of the model according to the data of each BDF card, and can be visualized, updated (if subsequent engineering personnel modify the parameters) and synchronized to form a three-dimensional finite element model.

[0060] In this process, for the analysis of aircraft structure, engineering designers will calculate the aerodynamic influence of the model, stress analysis of composite laminates, etc. Specifically, users can set the required analysis type on the web interface, such as static analysis, modal analysis, transient analysis, thermal analysis, etc., and perform finite element analysis on the three-dimensional finite element model by running the built-in solver of the finite element analysis software and combining the attribute information from the BDF file in the cloud database. From the server side, the finite element analysis of the grid cells in the natural grid model is to calculate the data in the BDF card through the solver to obtain the finite element analysis results.

[0061] In an optional embodiment, the solver may use the following formula to perform finite element analysis on the BDF card data corresponding to the grid unit of the selected natural grid model, taking the response of the calculation model in static analysis as an example:

[0062] Stress formula: σ=E·∈, where σ is stress, E is elastic modulus, and ∈ is strain.

[0063] Strain formula: Where ΔL is the change in length and L0 is the original length.

[0064] Displacement formula: In dynamic analysis, displacement can be obtained by integrating velocity and acceleration.

[0065] In other optional embodiments, finite element analysis may include structural analysis, thermal analysis, fatigue analysis, composite material analysis, fluid-structure coupling analysis, and multi-physics field analysis. Specifically, structural analysis may include the above-mentioned static analysis and dynamic analysis. Static analysis may analyze the response of the model structure under static loads (such as gravity, aerodynamic force, etc.), including displacement, stress, strain, etc. Dynamic analysis may analyze the response of the model structure under dynamic loads (such as vibration, impact, etc.), including natural frequency, vibration mode, dynamic stress, etc. Thermal analysis may include steady-state thermal analysis and transient thermal analysis. Steady-state thermal analysis may analyze the temperature distribution and thermal stress of the model structure under stable thermal loads. Transient thermal analysis may analyze the temperature distribution and thermal stress of the model structure under time-varying thermal loads. Fatigue analysis may analyze the fatigue life of the model structure under cyclic loads and predict fatigue damage and crack propagation of the model structure. Fluid-structure coupling analysis may analyze the interaction between fluid and structure, such as aeroelastic analysis, flutter analysis, etc. Multi-physics field analysis involves complex problems of multiple physical fields, such as thermal-structure coupling analysis, electromagnetic-structure coupling analysis, etc. Composite material analysis can analyze the strength, stiffness and stability of composite material structures, taking into account the anisotropic properties of composite materials. Through finite element analysis, engineering designers can comprehensively evaluate the structural performance of aircraft and optimize the model structure, such as topology optimization, shape optimization and size optimization, to reduce structural weight and improve performance.

[0066] Users can decide whether to continue to modify related parameters based on the results of finite element analysis, including viewing displacement cloud maps and stress cloud maps. For example, engineers can use the results of finite element analysis to determine whether the material of a part is suitable, whether it is too thin to withstand pressure during flight, etc., and thus decide whether to modify the model parameters. If modification is required, continue finite element analysis after modifying the response parameters to continuously improve the model.

[0067] Step S2.3: Reduce the dimension of the three-dimensional finite element model to form a two-dimensional finite element model through the two-dimensional visualization component and provide a linkage synchronization operation mechanism, so that the user's operation on the finite element model in any view can be reflected in real time on another view.

[0068] Since it is difficult to operate a three-dimensional finite element model in a three-dimensional scene, whether the engineering designers need to locate parts to modify parameters or select components in batches, they need to rotate or disassemble the model. The present invention provides a two-dimensional view through a two-dimensional visualization component, which can more intuitively display the internal structure and details of the model and improve the comprehensibility of the model. The operation under the two-dimensional view will be simpler and more intuitive than the three-dimensional view, so as to reduce the difficulties of the user in the operation process, reduce errors caused by viewing angles and operational complexity in the three-dimensional view, and improve operational efficiency and accuracy. It should be noted here that the two-dimensional view can display the entire plane model or the plane model view of the selected parts or components. In a two-dimensional scene, due to the low dimensionality, engineering designers can quickly locate the parts they want to select.

[0069] When a part of a part is arbitrarily selected in a three-dimensional scene or a two-dimensional scene, it will be correspondingly highlighted in the two-dimensional scene or the three-dimensional scene. The linked synchronous operation mechanism ensures that the user's operation on any view can be reflected in the other view in real time, avoiding the problem of data asynchrony and improving the accuracy and consistency of the operation. The user can switch freely between three-dimensional and two-dimensional views and select the most appropriate operation view as needed, thereby enhancing the interactivity between the user and the model. The present invention can improve the efficiency and accuracy of finite element model operations through this two-dimensional and three-dimensional linked visualization method, allowing users to analyze and modify models more intuitively and conveniently.

[0070] From the server side, selecting a part (corresponding to the grid unit of the natural grid model) is equivalent to selecting a BDF card. The modification of the model parameters will be synchronously updated to the BDF card after calculation by the cross-sectional centroid, area, moment of inertia calculation formula of the profile and the equivalent modulus calculation formula of the ply. The updated BDF file is finally output as the updated three-dimensional finite element model. This is the entire process of parametric modeling of the finite element model. As for how to deal with the finite element model later, it will be arranged according to the business needs of different downstream organizations, such as aircraft manufacturing based on the finite element model.

[0071] In order to achieve the above purpose, the present invention also provides a parametric modeling system for civil aircraft finite element models. The system adopts an end-to-end architecture, and the front end uses Vue.js to build a user interface, create components, routes, and state management; the server uses Python to develop database interaction and API interfaces; the database uses MongoDB to create collections and indexes, realizing an efficient, easy-to-use, and scalable Web-based parametric modeling system for civil aircraft finite element models.

[0072] Specifically, in an optional embodiment, Vue.js is used to create reusable UI components, such as model display components (displaying three-dimensional and two-dimensional views of natural grid models), parameter editing components, data query components, etc. These components can be independently developed and maintained, which improves the reusability and maintainability of the model. Further, Vue Router is used to manage page routing, and routing rules for different pages are defined, such as model display pages, parameter setting pages, etc. Through routing management, users can switch between different functional pages. Vuex is used for state management to centrally manage all state data in the application, such as model data, parameter data, etc. Through state management, data sharing and communication between components can be achieved. In this embodiment, the server side uses Python to write services, interacts with the MongoDB database, and implements the addition, deletion, modification, and query operations of model data. Specifically, third-party libraries such as pymongo can be used to simplify database operations. In this process, Python is used to develop RESTful API interfaces, which are provided to the front-end call. These API interfaces can include operations such as obtaining model data, updating model data parameters, and querying databases. The database uses MongoDB to create collections and indexes. Different collections are created in MongoDB to store model data, profile library data, paving material library data, material library data, etc. Furthermore, each collection can contain multiple documents, each of which represents a data record. In order to improve the efficiency of data query, you can create an index in MongoDB. For example, you can create an index on a field of model data to quickly query and filter data.

[0073] In order to achieve the above purpose, Figure 3 As shown, the parametric modeling system of the civil aircraft finite element model of the present invention may specifically include a model building module, a rendering interaction module and a cloud database. Specifically, the model building module may include a natural mesh model module and a finite element model module. The natural mesh model module has built-in finite element pre-processing software Hypermesh. The finite element model module has a built-in data processing engine to import, parse, convert and export data of the BDF file of the natural mesh model. The rendering module has built-in three-dimensional visualization components and two-dimensional visualization components. The cloud database may include a profile library, a ply library, and a material library.

[0074] In order to achieve the above-mentioned purpose, the present invention also provides a computer device, including a memory, a processor and a computer program stored in the memory and executable on the processor. When the processor runs the program, the steps of the parametric modeling method of the civil aircraft finite element model as described in any of the aforementioned embodiments can be implemented.

[0075] The processor and the memory may be provided separately or integrated together, for example, integrated into a system on chip (SOC) of a terminal device.

[0076] In order to achieve the above-mentioned purpose, the present invention also provides a computer-readable storage medium, which stores computer-executable instructions or computer programs. When the computer-executable instructions or computer programs are processed and executed, the parametric modeling method of the civil aircraft finite element model as described above is implemented.

[0077] The computer-readable storage medium is, for example, a memory. The memory may be a volatile memory or a nonvolatile memory, or the memory may include both a volatile memory and a nonvolatile memory. Among them, the nonvolatile memory may be a read-only memory (ROM), a programmable read-only memory (PROM), an erasable programmable read-only memory (EPROM), an electrically erasable programmable read-only memory (EEPROM), or a flash memory. The volatile memory may be a random access memory (RAM), which is used as an external cache. By way of example and not limitation, many forms of RAM are available, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double data rate synchronous dynamic random access memory (DDR SDRAM), enhanced synchronous dynamic random access memory (ESDRAM), synchronous link dynamic random access memory (SLDRAM), and direct rambus RAM (DR RAM).

[0078] If the integrated units in the above embodiments are implemented in the form of software functional units and sold or used as independent products, they can be stored in the above computer-readable storage medium. Based on such understanding, the technical solution of the present invention, or the part that contributes to the prior art, or all or part of the technical solution can be embodied in the form of a software product, which is stored in a storage medium and includes several instructions for enabling one or more computer devices (which can be personal computers, servers or network devices, etc.) to perform all or part of the steps of the methods described in various embodiments of the present invention.

[0079] The preferred specific embodiments of the present invention are described in detail above. It should be understood that ordinary technicians in the field can make many modifications and changes based on the concept of the present invention without creative work. Therefore, all technical solutions that can be obtained by technicians in the technical field based on the concept of the present invention through logical analysis, reasoning or limited experiments on the basis of the prior art should be within the scope of protection determined by the claims.

Claims

1. A parametric modeling method for a civil aircraft finite element model, characterized in that: The steps include: Step S1: meshing the original model to generate a natural mesh model; fine-grained decomposition of the complete original model into mesh units reflecting the main bearing force of the aircraft structure, each mesh unit corresponding to a different component of the original model, and each mesh unit containing attribute information of the corresponding part; Step S2: multi-scene synchronous rendering and interactive analysis; The grid unit is restored to a three-dimensional finite element model on the Web side, a plane finite element model is provided in a two-dimensional scene, and a customized cloud database is synchronously constructed on the server side; the attribute information of each grid unit is stored in the cloud database, and the cloud database includes a profile library, a ply library, and a material library.

2. The parametric modeling method of a civil aircraft finite element model according to claim 1, characterized in that: The step S1 comprises the following steps: Step S1.1: importing the original model into finite element pre-processing software Hypermesh; Step S1.2: meshing the original model to create a natural mesh model required for finite element analysis; Step S1.3: exporting the natural mesh model into a BDF file in Nastran BDF format; the BDF file includes a plurality of BDF cards, each of the BDF cards corresponds to each of the mesh units.

3. The parametric modeling method of a civil aircraft finite element model according to claim 2, characterized in that: In the step S1.2, the digital model of the aircraft structure skeleton is used as the basis for the mesh division.

4. The parametric modeling method of a civil aircraft finite element model according to claim 1, characterized in that: The step S2 comprises the following steps: Step S2.1: importing the natural grid model on the Web end; Step S2.2: converting the natural mesh model into the three-dimensional finite element model by using finite element analysis software and a three-dimensional visualization component; Step S2.3: Reduce the dimension of the three-dimensional finite element model to form a two-dimensional finite element model through a two-dimensional visualization component and provide a linkage synchronization operation mechanism, so that the user's operation on the finite element model in any view can be reflected in real time on another view.

5. The parametric modeling method of a civil aircraft finite element model according to claim 4, characterized in that: The cloud database is inserted into the finite element analysis software as a basic service. In step S2, all operations performed by the user on the model data of the three-dimensional finite element model will be synchronized and updated in real time to the cloud database for user query and analysis.

6. The parametric modeling method of a civil aircraft finite element model according to claim 4, characterized in that: The finite element analysis software is PyNastran, and the finite element analysis is performed on the three-dimensional finite element model by running the built-in solver of the finite element analysis software and combining the attribute information in the cloud database.

7. The parametric modeling method of a civil aircraft finite element model according to claim 1, characterized in that: The cloud database is a NoSQL database MongoDB; the profile library includes profile section information required for building the three-dimensional finite element model, the ply library includes composite material plies and metal shell element property information required for building the three-dimensional finite element model, and the material library includes composite material and metal material information required for building the three-dimensional finite element model.

8. A parametric modeling system for a civil aircraft finite element model, characterized in that: The front end of the parametric modeling system uses Vue.js to build the user interface, create components, routes, and state management; The server side uses Python to develop database interaction and API interface; The database uses MongoDB to create collections and indexes; including: A model building module, the model building module includes a natural mesh model module and a finite element model module; the natural mesh model module has a built-in finite element pre-processing software Hypermesh; the finite element model module has a built-in data processing engine; A rendering interaction module, wherein the rendering module has built-in three-dimensional visualization components and two-dimensional visualization components; Cloud database; the cloud database includes a profile library, a layer library, and a material library.

9. A computer device comprising a memory, a processor and a computer program stored in the memory and executable on the processor, characterized in that: When the processor runs the program, the steps of the parametric modeling method of the civil aircraft finite element model as described in any one of claims 1-7 are implemented.

10. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores computer-executable instructions or a computer program, and when the computer-executable instructions or the computer program are processed and executed, the parametric modeling method of the civil aircraft finite element model as described in any one of claims 1 to 7 is implemented.

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