Method for quickly updating and outputting box segment overall finite element model information

Abstract

The invention relates to the technical field of computer-aided engineering, in particular to a method for rapidly updating and outputting box segment overall finite element model information. Comprising the following steps: S1, constructing a material database, a paving layer database, a section information database and a specification database; s2, based on the bottom layer data, filling in an Excel table according to a format required by a program, and providing input parameters required by model updating; s3, carrying out secondary development in HyperMesh, obtaining a structural unit and information thereof based on GFEM characteristics, storing the structural unit and the information thereof in a memory, and outputting the information to an Excel table through Excel development; and S4, based on the GFEM characteristics and the output model information file, making an attribute updating template, obtaining unit physical parameters through Excel development, and performing secondary development in HyperMesh. According to the method, structural unit information of the upper wing surface, the lower wing surface, the front beam, the rear beam and the like can be output according to the style of an actual structural form, the GFEM model processing efficiency is greatly improved, especially for wide-body-level large wings and empennages, and the working efficiency can be greatly improved.

Description

Technical Field

[0001] The present invention relates to the field of computer-aided engineering technology, and particularly to a method for quickly updating and outputting the overall finite element model information of a box section. Background Art

[0002] In the aviation industry, aircraft design is a highly complex and frequently iterative process. To improve design efficiency and accuracy, finite element analysis (FEA) has become the core means for aircraft structural design and verification. Especially in the early design stage, engineers usually use the global finite element model (GFEM) for simulation analysis and checking. By simplifying the number of model units, GFEM significantly improves the calculation efficiency and provides important support for design optimization and performance evaluation. However, the application of GFEM also faces many challenges. Due to the complex structure of the aircraft, especially large components such as wide-body wings and tails, its GFEM model usually contains tens of thousands of structural units. Each structural unit often requires independent attribute definitions, including material parameters, ply information, section properties, and offset data, etc. In traditional methods, the inspection and update of these attributes mainly rely on manual operations. Engineers need to modify the attributes of each unit one by one, which is not only time-consuming and laborious but also error-prone. For example, manually updating a wing GFEM model with tens of thousands of units may take several days, seriously affecting the efficiency of design iteration. In the prior art, the attribute inspection or update of GFEM information involves many operations. Especially for wide-body aircraft with a large number of structural units, a large number of interactive operations are required for its inspection or update, which takes a lot of time.

[0003] Based on this, the present invention provides a method for quickly updating and outputting the overall finite element model information of a box section to solve the above-mentioned technical problems. Summary of the Invention

[0004] The object of the present invention is to provide a method for quickly updating and outputting the overall finite element model information of a box section. The present invention develops a method for outputting the structural unit information of the upper and lower wing surfaces, front and rear beams, etc. according to the actual structural form, including structural unit ID, structural unit attributes, materials, plies, offsets, and one-dimensional unit types, cross-sectional areas, moduli, lengths, moments of inertia, etc. It also supports outputting all metal and composite material parameter information in the model, which greatly facilitates users to view and check it. And based on the output information, parameters can be quickly specified for each structural unit. According to the parameter information specified by the user, this method can create or update the attributes of the structural unit. For shell elements, the updated content includes structural unit attributes, materials, plies, offsets. For one-dimensional units, the updated content includes unit types, cross-sectional areas, equivalent material parameters, lengths, moments of inertia, etc. This greatly improves the processing efficiency of the GFEM model, especially for large wings and tails of wide-body levels, and can greatly improve the work efficiency.

[0005] To achieve the above object, the present invention provides the following technical solutions: The present invention provides a method for quickly updating and outputting the overall finite element model information of a box section, including the following steps: S1: Construct a material database, a ply database, a cross-section information database, and a specification database; S2: Based on the underlying data, fill in the Excel table according to the format required by the program to provide the input parameters required for model update; S3: Secondary development in HyperMesh. Based on the characteristics of GFEM, obtain the structural units and their information and store them in memory, and through Excel development, output the information to an Excel table; S4: Based on the characteristics of GFEM and the output model information file, make an attribute update template, obtain the unit physical parameters through Excel development, and perform secondary development in HyperMesh.

[0006] In the S1, the material database includes the engineering constants of metals and composite materials. The ply database includes the detailed ply sequences of each number of plies under different ply ratios. The cross-section information database includes the cross-section information of each size under different cross-section forms. The specification database includes the modeling specifications and simulation analysis specifications.

[0007] The engineering constants of the metals and composite materials include elastic modulus, Poisson's ratio, shear modulus, and thermal expansion coefficient. The different cross-sections include T, Z, J, hat-shaped, and I-shaped cross-sections. Each type of cross-section contains cross-section parameters of different size information.

[0008] In the above S2, the Excel table is provided with a material parameter filling area, a structural ply parameter filling area, a unit offset parameter filling area, and a section parameter filling area, and each area has clear data format and unit requirements.

[0009] In the above S3, the specific process of outputting the overall finite element model information of the wing box section is as follows: S3.1: Define the structural output direction: Provide an interactive operation interface. Users can successively specify two nodes on the model through this interface to determine the output direction. Operating twice can respectively define the two output directions. S3.2: Specify the structural reference element: Provide an interactive interface, which is mainly used for users to select the positioning elements for output. For the wing surface, they are mainly ribs, front and rear beams, and stringers. For the rib webs, they are mainly transverse and longitudinal bars. S3.3: The program can group and sort the selected positioning reference elements according to the defined direction, and create the corresponding unit set. S3.4: Provide an interface. Users select the two-dimensional or one-dimensional structural elements that need to be output according to the actual structural form. The program automatically judges the intersection of each selected structural element and the reference positioning element, obtains the set number of the positioning reference element intersecting with it, and takes the minimum value combination of the two direction numbers as a two-dimensional array, which is used as the output number of this structural element. S3.5: After obtaining all the numbers, match the two-dimensional array of numbers with the rows and columns of the Excel table, and then output to obtain the actual physical space position mapping table of the structural elements. S3.6: Based on this mapping table, obtain the corresponding information of the structural elements and also output according to the mapping relationship.

[0010] The corresponding information of the above structural elements includes material, thickness, ply, and size information of length and width.

[0011] In the above S4, the specific process of updating the overall finite element model information of the wing box section is as follows: S4.1: Read the structural element information input table, obtain the engineering constant information of metals and composites in the table, and create materials. S4.2: Parse the one-dimensional structural element information table to obtain the finite element model unit ID corresponding to each structural element. S4.3: Obtain the cross-section form of the one-dimensional structural element, and obtain the cross-section parameters in the corresponding cross-section form table. For example, for a T-shaped stringer, obtain the web height, flange width, web ply information, and flange ply information of the T-shaped stringer. Then find the corresponding ply and single-layer material parameters in the ply library and material library, calculate the equivalent material parameters of the cross-section based on the classical laminated plate theory of composites, and be able to obtain the web and flange thicknesses based on the ply information, so as to calculate the cross-section moment of inertia and area information. S4.4: Create cross-section properties based on the calculated cross-section information and match them with the structural elements to complete the attribute assignment of one-dimensional elements; S4.5: Similarly analyze the parameter information of two-dimensional structural elements to obtain information such as the ply information and offset of the structural elements; S4.6: Create two-dimensional attributes and match them with the structural elements to complete the attribute assignment of two-dimensional elements.

[0012] The cross-section equivalent material parameters include equivalent elastic modulus, equivalent Poisson's ratio, and equivalent coefficient of thermal expansion.

[0013] In S4.3, the calculation of the equivalent material parameters is as follows: The specific formula for the stiffness components of a single-layer material is: , where, are the elastic moduli in the fiber direction and the transverse direction; are the principal direction Poisson's ratio and the transverse Poisson's ratio respectively, is the shear modulus; is the stiffness matrix component of the single-layer material; Equivalent engineering constants of the laminate: , where h is the total thickness; is the equivalent elastic modulus; is the Poisson's ratio; is the shear modulus, is the in-plane tensile stiffness of the laminate along the fiber direction; is the in-plane tensile-shear coupling stiffness of the laminate; is the in-plane tensile stiffness of the laminate in the transverse direction.

[0014] The specific formulas for calculating the cross-section moment of inertia and area information are: Cross-sectional area of M type: , Position of the central axis: , Total cross-section moment of inertia:

[0015] Cross-sectional area of T type:

[0016] Position of the central axis:

[0017] Total cross-section moment of inertia:

[0018] Cross-sectional area of I-shaped:

[0019] Position of central axis:

[0020]

[0021] Total moment of inertia of cross-section:

[0022] Cross-sectional area of Z-shaped:

[0023] Position of central axis:

[0024] Total moment of inertia of cross-section:

[0025] Cross-sectional area of J-shaped:

[0026] Position of central axis:

[0027] Total moment of inertia of cross-section:

[0028] Cross-sectional area of C-shaped:

[0029] Position of central axis:

[0030] Total moment of inertia of cross-section:

[0031] Cross-sectional area of L-shaped:

[0032] Position of central axis:

[0033] Total moment of inertia of cross-section:

[0034]

[0035] Cross-sectional area of rectangular:

[0036] Central axis position:

[0037] Total moment of inertia of cross-section: 。

[0038] Compared with the prior art, the beneficial effects of the present invention are as follows: The present invention develops the ability to output the structural unit information of the upper and lower wing surfaces, front and rear beams, etc. according to the actual structural form, including structural unit ID, structural unit attributes, materials, ply, offset, and one-dimensional unit type, cross-sectional area, modulus, length, moment of inertia, etc. It also supports outputting all metal and composite material parameter information in the model, which greatly facilitates the user to view and check it. And based on the output information, parameters can be quickly specified for each structural unit. According to the parameter information specified by the user, this method can create or update the attributes of the structural unit. For shell elements, the updated content includes structural unit attributes, materials, ply, offset. For one-dimensional units, the updated content includes unit type, cross-sectional area, equivalent material parameters, length, moment of inertia, etc., which greatly improves the processing efficiency of the GFEM model, especially for large wings and tails at the wide-body level, and can greatly improve the work efficiency. Description of the drawings

[0039] Figure 1 It is the overall architecture diagram of a method for quickly updating and outputting the overall finite element model information of a box section according to the present invention.

[0040] Figure 2 It is the system implementation diagram of a method for quickly updating and outputting the overall finite element model information of a box section according to the present invention.

[0041] Figure 3 It is the flowchart of outputting the overall finite element model information of the wing box section in a method for quickly updating and outputting the overall finite element model information of a box section according to the present invention.

[0042] Figure 4 It is the flowchart of updating the overall finite element model information of the wing box section in a method for quickly updating and outputting the overall finite element model information of a box section according to the present invention.

[0043] Figure 5 It is the calculation diagram of M-shaped stringer parameters in a method for quickly updating and outputting the overall finite element model information of a box section according to the present invention.

[0044] Figure 6 It is the calculation diagram of T-shaped stringer parameters in a method for quickly updating and outputting the overall finite element model information of a box section according to the present invention.

[0045] Figure 7 It is the calculation diagram of the I-shaped cross-section parameters in a method for quickly updating and outputting the overall finite element model information of a box segment according to the present invention.

[0046] Figure 8 It is the calculation diagram of the Z-shaped cross-section parameters in a method for quickly updating and outputting the overall finite element model information of a box segment according to the present invention.

[0047] Figure 9 It is the calculation diagram of the J-shaped cross-section parameters in a method for quickly updating and outputting the overall finite element model information of a box segment according to the present invention.

[0048] Figure 10 It is the calculation diagram of the C-shaped cross-section parameters in a method for quickly updating and outputting the overall finite element model information of a box segment according to the present invention.

[0049] Figure 11 It is the calculation diagram of the L-shaped cross-section parameters in a method for quickly updating and outputting the overall finite element model information of a box segment according to the present invention.

[0050] Figure 12 It is the calculation diagram of the rectangular cross-section parameters in a method for quickly updating and outputting the overall finite element model information of a box segment according to the present invention. Detailed implementation manners

[0051] Next, in combination with the embodiments of the present invention, the technical solutions in the embodiments of the present invention will be clearly and completely described. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without making creative efforts belong to the scope of protection of the present invention.

[0052] Embodiment: As Figures 1 - 12 shown, this embodiment provides a method for quickly updating and outputting the overall finite element model information of a box segment, including the following steps: S1: Construct a material database, a ply database, a cross-section information database, and a specification database; S2: Based on the underlying data, fill in the Excel table according to the format required by the program to provide the input parameters required for model updating; S3: Perform secondary development in HyperMesh. Based on the characteristics of GFEM, obtain the structural elements and their information and store them in memory, and through Excel development, output the information to the Excel table; S4: Based on the characteristics of GFEM and the output model information file, make an attribute update template, obtain the physical parameters of the elements through Excel development, and perform secondary development in HyperMesh.

[0053] The material database in S1 includes the engineering constants of metals and composite materials. The ply database includes the detailed ply sequences of each number of plies under different ply ratios. The cross-section information database includes the cross-section information of each size under different cross-section forms. The specification database includes the modeling specifications and simulation analysis specifications.

[0054] The engineering constants of metals and composite materials include elastic modulus, Poisson's ratio, shear modulus, and coefficient of thermal expansion. Different cross-sections include T, Z, J, hat-shaped, and I-shaped cross-sections. Each type of cross-section contains cross-section parameters with different size information.

[0055] The Excel table in S2 has a material parameter filling area, a structural ply parameter filling area, a unit offset parameter filling area, and a cross-section parameter filling area. Each area has clear data format and unit requirements.

[0056] The specific process for outputting the overall finite element model information of the wing box section in S3 is as follows: S3.1: Define the structural output direction: Provide an interactive operation interface. Users can sequentially specify two nodes on the model through this interface to determine the output direction. Operating twice can define the two output directions respectively. S3.2: Specify the structural reference element: Provide an interactive interface, mainly used for users to select the positioning element for output. For the wing surface, it is mainly ribs, front and rear beams, and stringers. For the rib webs, it is mainly transverse and longitudinal reinforcements. S3.3: The program can group and sort the selected positioning reference elements according to the defined direction and create the corresponding unit set. S3.4: Provide an interface. Users select the two-dimensional or one-dimensional structural elements that need to be output according to the actual structural form. The program automatically judges the intersection of each selected structural element and the reference positioning element, obtains the set number of the positioning reference element that intersects with it, and takes the minimum value of the two direction numbers to form a two-dimensional array as the output number of the structural element. S3.5: After obtaining all the numbers, match the two-dimensional array of numbers with the rows and columns of the Excel table, and then output to obtain the actual physical space position mapping table of the structural elements. S3.6: Based on this mapping table, obtain the corresponding information of the structural elements and also output according to the mapping relationship.

[0057] The corresponding information of the structural elements includes material, thickness, ply, and size information of length and width.

[0058] The specific process for updating the overall finite element model information of the wing box section in S4 is as follows: S4.1: Read the structural element information input table, obtain the engineering constant information of metals and composite materials in the table, and create materials. S4.2: Analyze the one-dimensional structural element information table to obtain the finite element model element ID corresponding to each structural element; S4.3: Obtain the cross-section form of the one-dimensional structural element, and obtain the cross-section parameters in the corresponding cross-section form table. For example, for a T-shaped stringer, obtain the web height, flange width, web ply information, and flange ply information of the T-shaped stringer. Then, find the corresponding ply and single-layer material parameters in the ply library and material library, and calculate the equivalent material parameters of the cross-section based on the classical laminated plate theory of composite materials. Also, be able to obtain the web and flange thicknesses based on the ply information, so as to calculate the cross-section moment of inertia and area information; S4.4: Create cross-section properties according to the calculated cross-section information and match them with the structural elements to complete the attribute assignment of the one-dimensional elements; S4.5: Similarly, analyze the two-dimensional structural element parameter information to obtain information such as the ply information and offset of the structural element; S4.6: Create two-dimensional attributes and match them with the structural elements to complete the attribute assignment of the two-dimensional elements.

[0059] The equivalent material parameters of the cross-section include equivalent elastic modulus, equivalent Poisson's ratio, and equivalent coefficient of thermal expansion.

[0060] When calculating the equivalent material parameters in S4.3, the specific formulas are as follows: The specific formula for the stiffness components of the single-layer material is:

[0061] In the formula, are the longitudinal and transverse elastic moduli; are the major Poisson's ratio and transverse Poisson's ratio respectively, is the shear modulus; are the stiffness matrix components of the single-layer material; Equivalent engineering constants of the laminated plate:

[0062] In the formula, h is the total thickness; is the equivalent elastic modulus; is the Poisson's ratio; is the shear modulus, is the in-plane tensile stiffness of the laminated plate along the fiber direction; is the in-plane tensile-shear coupling stiffness of the laminated plate; is the in-plane tensile stiffness of the laminated plate in the transverse direction.

[0063] The specific formulas for calculating the cross-section moment of inertia and area information are: Cross-sectional area of the M shape:

[0064] Position of the central axis:

[0065] Total moment of inertia of the cross-section:

[0066]

[0067] Cross-sectional area of T-shape:

[0068] Position of the central axis:

[0069] Total moment of inertia of the cross-section:

[0070] Cross-sectional area of I-shape:

[0071] Position of the central axis:

[0072] Total moment of inertia of the cross-section:

[0073] Cross-sectional area of Z-shape:

[0074] Position of the central axis:

[0075] Total moment of inertia of the cross-section:

[0076] Cross-sectional area of J-shape:

[0077] Position of the central axis:

[0078] Total moment of inertia of the cross-section:

[0079] Cross-sectional area of C-shape:

[0080] Position of the central axis:

[0081] Total moment of inertia of the cross-section:

[0082] L-shaped cross-sectional area:

[0083] Central axis position:

[0084] Total moment of inertia of the cross-section:

[0085] Rectangular cross-sectional area:

[0086] Central axis position:

[0087] Total moment of inertia of the cross-section:

[0088] 。

[0089] Such as Figures 1 - 12As shown, this embodiment provides a method for quickly updating and outputting the overall finite element model information of the box section. The specific method is as follows: First, S1: Construct a material database, a ply database, a section information database, and a specification database; the material database in S1 includes the engineering constants of metals and composite materials. The engineering constants of metals and composite materials include elastic modulus, Poisson's ratio, shear modulus, and coefficient of thermal expansion. The ply database includes the detailed ply sequences of each number of plies under different ply ratios. For example, a ply file with a ply angle of 0° / ±45° / 90° and a ratio of 631 contains 12 to 100 plies. In each number of plies, the ratio of 0° / ±45° / 90° is close to 6\3\1. The section information database includes the section information of each size under different section forms. Different sections include T, Z, J, hat-shaped, and I-shaped sections. Each type of section contains section parameters with different size information. The specification database includes modeling specifications and simulation analysis specifications to ensure that the model information meets the requirements after being updated. S2: Based on the underlying data, fill in the Excel table according to the format required by the program to provide the input parameters required for model updating; in S2, the Excel table is provided with a material parameter filling area, a structural ply parameter filling area, a unit offset parameter filling area, and a section parameter filling area. Each area has clear data format and unit requirements. S3: Secondary development in HyperMesh. Based on the characteristics of GFEM, obtain the structural elements and their information and store them in memory, and through Excel development, output the information to the Excel table; the specific process of outputting the overall finite element model information of the wing box section in S3 is as follows: S3.1: Define the structural output direction: Provide an interactive operation interface. Users can sequentially specify two nodes on the model through this interface to determine the output direction. Operating twice can define the two output directions respectively; S3.2: Specify the structural reference element: Provide an interactive interface, mainly used for users to select the positioning element for output. For the wing surface, it is mainly ribs, front and rear beams, and stringers. For the rib web, it is mainly transverse and longitudinal bars; S3.3: The program can group and sort the selected positioning reference elements according to the defined direction and create the corresponding unit set; S3.4: Provide an interface. Users select the two-dimensional or one-dimensional structural elements that need to be output according to the actual structural form. The program automatically judges the intersection of each selected structural element and the reference positioning unit, obtains the set number of the positioning reference unit that intersects with it, and takes the minimum value combination of the two direction numbers as a two-dimensional array as the output number of the structural element; S3.5: After obtaining all the numbers, match the two-dimensional array of numbers with the rows and columns of the Excel table, and then output to obtain the actual physical space position mapping table of the structural element; S3.6: Based on this mapping table, obtain the corresponding information of the structural element and also output it according to the mapping relationship. The corresponding information of the structural element includes material, thickness, ply, and size information of length and width.S4: Based on the characteristics of GFEM and the output model information file, create an attribute update template, obtain the physical parameters of the elements through Excel development, and perform secondary development in HyperMesh. The specific process of updating the overall finite element model information of the wing box section in S4 is as follows: S4.1: Read the input table of structural element information, obtain the engineering constant information of metals and composites in the table, and create materials; S4.2: Parse the one-dimensional structural element information table to obtain the finite element model element ID corresponding to each structural element; S4.3: Obtain the cross-sectional form of the one-dimensional structural element, and obtain the cross-sectional parameters in the corresponding cross-sectional form table. For example, for a T-shaped stringer, obtain the web height, flange width, web ply information, and flange ply information of the T-shaped stringer. Then, find the corresponding ply and single-layer material parameters in the ply library and material library, and calculate the equivalent material parameters of the cross-section based on the classical laminated plate theory of composites. The equivalent material parameters of the cross-section include equivalent elastic modulus, equivalent Poisson's ratio, and equivalent coefficient of thermal expansion. Calculate the equivalent material parameters, and the specific formulas are as follows: The specific formula for the stiffness components of the single-layer material is:

[0090] In the formula, are the longitudinal and transverse elastic moduli; are the principal-direction Poisson's ratio and transverse Poisson's ratio respectively, is the shear modulus; are the stiffness matrix components of the single-layer material; Equivalent engineering constants of the laminated plate:

[0091] In the formula, h is the total thickness; is the equivalent elastic modulus; is the Poisson's ratio; is the shear modulus, is the in-plane tensile stiffness of the laminated plate along the fiber direction; is the in-plane tensile-shear coupling stiffness of the laminated plate; is the in-plane tensile stiffness of the laminated plate in the transverse direction.

[0092] And the thickness of the web and flange can be obtained based on the ply information, so as to calculate the cross-sectional moment of inertia and area information; the specific formulas for calculating the cross-sectional moment of inertia and area information are: Calculation of M-shaped stringer parameters: As Figure 5 shown M-shaped cross-sectional area:

[0093] Position of the central axis:

[0094] Total cross-sectional moment of inertia:

[0095] Calculation of T-shaped stringer parameters: As Figure 6 shown T-shaped cross-sectional area:

[0096] Position of the central axis:

[0097] Total moment of inertia of the cross-section:

[0098] Calculation of I-shaped cross-section parameters: As Figure 7 shown I-shaped cross-sectional area:

[0099] Position of the central axis:

[0100] Total moment of inertia of the cross-section:

[0101] Calculation of Z-shaped cross-section parameters: As Figure 8 shown Z-shaped cross-sectional area:

[0102] Position of the central axis:

[0103] Total moment of inertia of the cross-section:

[0104] Calculation of J-shaped cross-section parameters: As Figure 9 shown J-shaped cross-sectional area:

[0105] Position of the central axis:

[0106] Total moment of inertia of the cross-section:

[0107] Calculation of C-shaped cross-section parameters: As Figure 10 shown C-shaped cross-sectional area:

[0108] Central axis position:

[0109] Total moment of inertia of cross-section:

[0110] Calculation of L-shaped cross-section parameters: As Figure 11 shown L-shaped cross-sectional area:

[0111] Central axis position:

[0112] Total moment of inertia of cross-section:

[0113] Calculation of rectangular cross-section parameters: As Figure 12 shown Rectangular cross-sectional area:

[0114] Central axis position:

[0115] Total moment of inertia of cross-section: .

[0116] S4.4: Create cross-section properties based on the calculated cross-section information and match them with the structural elements to complete the attribute assignment of one-dimensional elements; S4.5: Similarly analyze the parameter information of two-dimensional structural elements to obtain information such as the layup information and offset of the structural elements; S4.6: Create two-dimensional attributes and match them with the structural elements to complete the attribute assignment of two-dimensional elements.

[0117] In the description of this specification, the descriptions referring to terms such as "one embodiment", "example", "specific example", etc. mean that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described can be combined in a suitable manner in any one or more embodiments or examples.

[0118] The preferred embodiments of the present invention disclosed above are only used to help illustrate the present invention. The preferred embodiments do not describe all the details in detail, nor do they limit the invention to the specific embodiments described. Obviously, many modifications and variations can be made according to the content of this specification. These embodiments are selected and specifically described in this specification to better explain the principles and practical applications of the present invention, so that those skilled in the art can well understand and utilize the present invention. The present invention is only limited by the claims and their full scope and equivalents.

Claims

1. A method for quickly updating and outputting the overall finite element model information of a box segment, characterized in that It includes the following steps: S1: Construct a material database, a ply database, a section information database, and a specification database; S2: Based on the underlying data, fill in the Excel table in the format required by the program to provide the input parameters needed for model update; S3: Perform secondary development in HyperMesh. Based on the characteristics of GFEM, obtain the structural elements and their information and store them in memory, and through Excel development, output the information to an Excel table; S4: Based on the characteristics of GFEM and the output model information file, make an attribute update template, obtain the physical parameters of the elements through Excel development, and perform secondary development in HyperMesh; The specific process of outputting the overall finite element model information of the wing box section in S3 is as follows: S3.1: Define the structural output direction: Provide an interactive operation interface. Users can sequentially specify two nodes on the model through this interface to determine the output direction. Operating twice can define the two output directions respectively; S3.2: Specify the structural reference elements: Provide an interactive interface, which is mainly used for users to select the positioning elements for output. For the wing surface, they are mainly ribs, front and rear beams, and stringers. For the rib webs, they are mainly transverse and longitudinal bars; S3.3: The program can group and sort the selected positioning reference elements according to the defined direction and create the corresponding element set; S3.4: Provide an interface. Users select the two-dimensional or one-dimensional structural elements that need to be output according to the actual structural form. The program automatically judges the intersection of each selected structural element and the reference positioning element, obtains the set number of the positioning reference element intersecting with it, and takes the minimum value combination of the two direction numbers as a two-dimensional array, which is used as the output number of the structural element; S3.5: After obtaining all the numbers, match the two-dimensional array of numbers with the rows and columns of the Excel table, and then output to obtain the actual physical space position mapping table of the structural elements; S3.6: Based on this mapping table, obtain the corresponding information of the structural elements and also output according to the mapping relationship; The corresponding information of the structural elements includes material, thickness, ply, and size information of length and width; The specific process of updating the overall finite element model information of the wing box section in S4 is as follows: S4.1: Read the structural element information input table, obtain the engineering constant information of metals and composite materials in the table, and create materials; S4.2: Parse the one-dimensional structural element information table to obtain the finite element model element ID corresponding to each structural element; S4.3: Obtain the cross-section form of the one-dimensional structural element, and obtain the cross-section parameters in the corresponding cross-section form table. For example, for a T-shaped stringer, obtain the web height, flange width, web ply information, and flange ply information of the T-shaped stringer, and then find the corresponding ply and single-layer material parameters in the ply database and material database and calculate the equivalent material parameters of the cross-section based on the classical laminate theory of composite materials. And be able to obtain the web and flange thicknesses based on the ply information, so as to calculate the cross-section moment of inertia and area information; S4.4: Create cross-section attributes according to the calculated cross-section information and match them with the structural elements to complete the attribute assignment of the one-dimensional elements; S4.5: Similarly analyze the parameter information of the two-dimensional structural unit to obtain the ply information and offset information of the structural unit; S4.6: Create two-dimensional attributes and match them with the structural unit to complete the assignment of two-dimensional unit attributes.

2. A method for quickly updating and outputting the overall finite element model information of a box segment according to claim 1, characterized in that, In the above S1, the material database includes the engineering constants of metals and composite materials, the ply database includes the detailed ply sequences of each number of plies under different ply ratios, the cross-section information database includes the cross-section information of each size under different cross-section forms, and the specification database includes the modeling specifications and simulation analysis specifications.

3. A method for quickly updating and outputting the overall finite element model information of a box segment according to claim 2, characterized in that, The engineering constants of the metals and composite materials include elastic modulus, Poisson's ratio, shear modulus, and coefficient of thermal expansion. The different cross-sections include T, Z, J, hat-shaped, and I-shaped cross-sections, and each type of cross-section contains cross-section parameters with different size information.

4. A method for quickly updating and outputting the overall finite element model information of a box segment according to claim 3, characterized in that In the above S2, the Excel table is provided with a material parameter filling area, a structural ply parameter filling area, a unit offset parameter filling area, and a cross-section parameter filling area, and each area has clear data format and unit requirements.

5. A method for quickly updating and outputting the overall finite element model information of a box segment according to claim 4, characterized in that The cross-section equivalent material parameters include equivalent elastic modulus, equivalent Poisson's ratio, and equivalent coefficient of thermal expansion.

6. A method for quickly updating and outputting the overall finite element model information of a box segment according to claim 1, characterized in that In the above S4.3, calculate the equivalent material parameters, and the specific formula is as follows: The specific formula for the stiffness components of a single-layer material is: , In the formula, is the elastic modulus in the fiber direction and the transverse direction; are the principal direction Poisson's ratio and the transverse Poisson's ratio respectively, is the shear modulus; are the stiffness matrix components of the single-layer material; Equivalent engineering constants of the laminated plate: ， Where h is the total thickness; is the equivalent elastic modulus; is the Poisson's ratio; is the shear modulus; is the in-plane tensile stiffness of the laminate along the fiber direction; is the in-plane tensile-shear coupling stiffness of the laminate; is the in-plane tensile stiffness of the laminate in the transverse direction.

7. A method for quickly updating and outputting the overall finite element model information of a box segment according to claim 6, characterized in that The specific formulas for calculating the cross-section moment of inertia and area information are: Cross-sectional area of M-shaped: ， Position of the central axis: ， ， Total cross-section moment of inertia: ， Cross-sectional area of T-shaped: ， Position of the central axis: ， Total cross-section moment of inertia: ， ， Cross-sectional area of I-shaped: ， Position of the central axis: ， Total cross-section moment of inertia: ， Cross-sectional area of Z-shaped: ， Position of the central axis: ， Total cross-section moment of inertia: ， Cross-sectional area of J-shaped: ， Position of the central axis: ， Total cross-section moment of inertia: ， Cross-sectional area of C-shaped: ， Position of the central axis: ， Total cross-section moment of inertia: ， Cross-sectional area of L-shaped: ， Position of the central axis: ， Total cross-section moment of inertia: ， Cross-sectional area of rectangular: ， Position of the central axis: ， Total cross-section moment of inertia: 。

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