A method for quickly updating and outputting overall finite element model information of box segments

Abstract

The present invention relates to the field of computer-aided engineering technology, specifically a method for rapidly updating and outputting overall finite element model information of a box segment. The method comprises the following steps: S1: constructing a material database, a ply database, a cross-section information database, and a specification database; S2: filling out an Excel spreadsheet in a format required by a program based on underlying data to provide input parameters required for model updating; S3: performing secondary development in HyperMesh, based on GFEM characteristics, obtaining structural elements and their information, storing them in memory, and outputting the information to an Excel spreadsheet via Excel development; S4: creating a property update template based on GFEM characteristics and the output model information file, obtaining element physical parameters via Excel development, and performing secondary development in HyperMesh. By developing a format that can output structural element information of upper and lower wing surfaces, front and rear beams, etc. according to actual structural forms, the method greatly improves GFEM model processing efficiency, particularly for large wide-body wings and tailplanes, and can significantly improve work efficiency.

Description

Technical Field

[0001] The present invention relates to the technical field of computer-aided engineering, in particular to a method for rapidly updating and outputting overall finite element model information of a box segment. Background Art

[0002] In the aviation industry, aircraft design is a highly complex and iterative process. To improve design efficiency and accuracy, finite element analysis (FEA) has become a core tool for aircraft structural design and verification. Especially in the early design phase, engineers often use the Global Finite Element Model (GFEM) for simulation, analysis, and verification. GFEM significantly improves computational efficiency by reducing the number of model elements, providing important support for design optimization and performance evaluation. However, the application of GFEM also faces numerous challenges. Due to the complexity of aircraft structures, especially large components such as wide-body wings and tailplanes, their GFEM models often contain tens of thousands of structural elements. Each structural element often requires independent property definitions, including material parameters, layup information, cross-sectional properties, and offset data. Traditional methods rely heavily on manual verification and updating of these properties, requiring engineers to modify the properties of each element one by one. This is not only time-consuming and labor-intensive, but also prone to errors. For example, manually updating a GFEM model of a wing containing tens of thousands of elements can take days, severely impacting the efficiency of design iterations. In the prior art, checking or updating the attributes of GFEM information involves many operations, especially for wide-body aircraft with a large number of structural units. Checking or updating them requires a large number of interactive operations and 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 segment to solve the above-mentioned technical problems. Summary of the Invention

[0004] The present invention aims to provide a method for rapidly updating and outputting overall finite element model information of a box segment. The present invention develops a method for outputting structural unit information of upper and lower wing surfaces, front and rear beams, etc. in the style of actual structural form, including structural unit ID, structural unit attributes, materials, layups, offsets, as well as one-dimensional unit type, cross-sectional area, modulus, length, moment of inertia, and other information. The method also supports outputting parameter information of all metal and composite materials in the model, greatly facilitating user review and inspection. Furthermore, based on the output information, parameters can be quickly specified for each structural unit. Based on the user-specified parameter information, the method can create or update the attributes of the structural unit. For shell units, the updated content includes structural unit attributes, materials, layups, and offsets. For one-dimensional units, the updated content includes unit type, cross-sectional area, equivalent material parameters, length, moment of inertia, and other information. This method greatly improves the efficiency of GFEM model processing, especially for large wide-body wings and tails, and can greatly improve work efficiency.

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

[0006] The present invention provides a method for quickly updating and outputting overall finite element model information of a box segment, comprising the following steps:

[0007] S1: Build material database, ply database, cross-section information database and specification database;

[0008] S2: Based on the underlying data, fill in the Excel table in the format required by the program and provide the input parameters required for model update;

[0009] S3: Secondary development in HyperMesh, based on the characteristics of GFEM, obtains structural elements and their information and stores them in memory, and develops through Excel to output the information to Excel tables;

[0010] S4: Based on the characteristics of GFEM and the output model information file, create a property update template, obtain the unit physical parameters through Excel development, and perform secondary development in HyperMesh.

[0011] The material database in S1 includes engineering constants of metals and composite materials, the ply database includes detailed ply layup sequences for different numbers of plies at different ply ratios, the section information library includes section information of various sizes under different section forms, and the specification library includes modeling specifications and simulation analysis specifications.

[0012] The engineering constants of the metal 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, and each type of cross-section contains cross-sectional parameters with different size information.

[0013] The Excel table in S2 is provided with a material parameter filling area, a structure ply parameter filling area, a unit offset parameter filling area and a cross-section parameter filling area, and each area has a clear data format and unit requirements.

[0014] The specific process of outputting the overall finite element model information of the wing box segment in S3 is as follows:

[0015] S3.1: Define the output direction of the structure: This provides an interactive interface through which users can specify two nodes on the model in sequence to determine the output direction. This operation can be performed twice to define the two output directions respectively.

[0016] S3.2: Specify structural reference elements: Provides an interactive interface for users to select the positioning elements to be output. For the wing surface, these are mainly ribs, front and rear beams, and long strings. For the rib web, these are mainly transverse and longitudinal reinforcements.

[0017] S3.3: The program can group and sort the selected positioning reference elements according to the defined direction and create a corresponding unit set;

[0018] S3.4: Provides an interface where the user selects the two-dimensional or one-dimensional structural unit to be output according to the actual structural form. The program automatically determines the intersection of each selected structural unit and the reference positioning unit, obtains the set number of the positioning reference unit that intersects with it, and takes the minimum value of the two-directional numbers to form a two-dimensional array as the output number of the structural unit;

[0019] S3.5: After obtaining all the numbers, the two-dimensional array of numbers is matched with the rows and columns of the Excel table, and then output, and the actual physical space position mapping table of the structural unit is obtained;

[0020] S3.6: Based on the mapping table, corresponding information of the structural unit is obtained, and also output according to the mapping relationship.

[0021] The corresponding information of the structural unit includes material, thickness, ply, length and width dimensional information.

[0022] The specific process of updating the overall finite element model information of the wing box segment in S4 is as follows:

[0023] S4.1: Read the structural unit information input table, obtain the metal and composite material engineering constant information in the table, and create materials;

[0024] S4.2: Parse the one-dimensional structural unit information table to obtain the finite element model unit ID corresponding to each structural unit;

[0025] S4.3: Obtain the cross-sectional form of a one-dimensional structural unit and obtain the cross-sectional parameters from the corresponding cross-sectional form table. For example, for a T-stringer, obtain the web height, flange width, web layup information, and flange layup information of the T-stringer. Then, find the corresponding layup and single-layer material parameters in the layup library and material library, and calculate the equivalent material parameters of the cross-sectional form based on the classical composite laminate theory. Furthermore, the web and flange thickness can be obtained based on the layup information, thereby calculating the cross-sectional moment of inertia and area information.

[0026] S4.4: Create cross-sectional properties based on the calculated cross-sectional information and match them with the structural elements to complete the attribute assignment of the one-dimensional element;

[0027] S4.5: Synthesize and analyze the two-dimensional structural unit parameter information to obtain the structural unit ply information, offset and other information;

[0028] S4.6: Create two-dimensional attributes and match them with structural units to complete the two-dimensional unit attribute assignment.

[0029] The cross-section equivalent material parameters include equivalent elastic modulus, equivalent Poisson's ratio, and equivalent thermal expansion coefficient.

[0030] The equivalent material parameters are calculated in S4.3, and the specific formula is as follows:

[0031] The specific formula for the stiffness component of a single layer of material is:

[0032] ,

[0033] Where, is the elastic modulus in the fiber direction and transverse direction; are the main direction Poisson’s ratio and the transverse Poisson’s ratio, is the shear modulus; is the stiffness matrix component of the single layer material;

[0034] Equivalent engineering constants of laminates:

[0035] ,

[0036] Where h is the total thickness; is the equivalent elastic modulus; is Poisson's ratio; is the shear modulus, is the in-plane tensile stiffness of the laminate along the fiber direction; is the in-plane tension-shear coupling stiffness of the laminate; is the in-plane tensile stiffness of the laminate in the transverse direction.

[0037] The specific formula for calculating the cross-sectional inertia moment and area information is:

[0038] M-type cross-sectional area:

[0039] ,

[0040] Center axis position:

[0041] ,

[0042] Total moment of inertia of the section:

[0043]

[0044] T-type cross-sectional area:

[0045]

[0046] Center axis position:

[0047]

[0048] Total moment of inertia of the section:

[0049]

[0050] Cross-sectional area of ​​the I-type:

[0051]

[0052] Center axis position:

[0053]

[0054]

[0055] Total moment of inertia of the section:

[0056]

[0057] Z-section area:

[0058]

[0059] Center axis position:

[0060]

[0061] Total moment of inertia of the section:

[0062]

[0063] J-type cross-sectional area:

[0064]

[0065] Center axis position:

[0066]

[0067] Total moment of inertia of the section:

[0068]

[0069] C-type cross-sectional area:

[0070]

[0071] Center axis position:

[0072]

[0073] Total moment of inertia of the section:

[0074]

[0075] L-shaped cross-sectional area:

[0076]

[0077] Center axis position:

[0078]

[0079] Total moment of inertia of the section:

[0080]

[0081]

[0082] Rectangular cross-sectional area:

[0083]

[0084] Center axis position:

[0085]

[0086] Total moment of inertia of the section:

[0087] .

[0088] Compared with the prior art, the present invention has the following beneficial effects:

[0089] The present invention develops a method for outputting structural unit information of upper and lower wing surfaces, front and rear beams, etc. in a style according to the actual structural form, including structural unit ID, structural unit attributes, materials, layups, offsets, as well as one-dimensional unit type, cross-sectional area, modulus, length, moment of inertia, etc. The method also supports outputting parameter information of all metal and composite materials in the model, which greatly facilitates users to view and inspect the information. Based on the output information, parameters can be quickly specified for each structural unit. According to the user-specified parameter information, the method can create or update the attributes of the structural unit. For shell units, the updated content includes structural unit attributes, materials, layups, offsets; 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 wide-body wings and tails, and can greatly improve work efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0090] Figure 1 This is an overall architecture diagram of a method for quickly updating and outputting overall finite element model information of a box segment according to the present invention.

[0091] Figure 2 This is a system implementation diagram of a method for quickly updating and outputting overall finite element model information of a box segment according to the present invention.

[0092] Figure 3 The present invention provides a flow chart of outputting the overall finite element model information of a wing box section in a method for rapidly updating and outputting the overall finite element model information of the box section.

[0093] Figure 4 The present invention provides a flow chart for updating the overall finite element model information of a wing box section in a method for rapidly updating and outputting the overall finite element model information of the box section.

[0094] Figure 5 This is a parameter calculation diagram of an M-type long stringer in a method for quickly updating and outputting overall finite element model information of a box segment according to the present invention.

[0095] Figure 6 This is a T-type long stringer parameter calculation diagram in a method for quickly updating and outputting overall finite element model information of a box segment according to the present invention.

[0096] Figure 7 This is a calculation diagram of I-section parameters in a method for quickly updating and outputting overall finite element model information of a box segment according to the present invention.

[0097] Figure 8 This is a calculation diagram of Z-section parameters in a method for quickly updating and outputting overall finite element model information of a box segment according to the present invention.

[0098] Figure 9This is a J-section parameter calculation diagram in a method for quickly updating and outputting overall finite element model information of a box segment according to the present invention.

[0099] Figure 10 This is a C-section parameter calculation diagram in a method for quickly updating and outputting overall finite element model information of a box segment according to the present invention.

[0100] Figure 11 This is a calculation diagram of L-section parameters in a method for quickly updating and outputting overall finite element model information of a box segment according to the present invention.

[0101] Figure 12 This is a rectangular section parameter calculation diagram in a method for quickly updating and outputting overall finite element model information of a box segment according to the present invention. DETAILED DESCRIPTION

[0102] The following will be combined with the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making any creative efforts shall fall within the scope of protection of the present invention.

[0103] Example:

[0104] like Figures 1-12 As shown, this embodiment provides a method for quickly updating and outputting overall finite element model information of a box segment, comprising the following steps:

[0105] S1: Build material database, ply database, cross-section information database and specification database;

[0106] S2: Based on the underlying data, fill in the Excel table in the format required by the program and provide the input parameters required for model update;

[0107] S3: Secondary development in HyperMesh, based on the characteristics of GFEM, obtains structural elements and their information and stores them in memory, and develops through Excel to output the information to Excel tables;

[0108] S4: Based on the characteristics of GFEM and the output model information file, create a property update template, obtain the unit physical parameters through Excel development, and perform secondary development in HyperMesh.

[0109] The material database in S1 includes engineering constants of metals and composite materials, the ply database includes detailed ply layup sequences for different numbers of plies at different ply ratios, the cross-sectional information library includes cross-sectional information of various sizes under different cross-sectional forms, and the specification library includes modeling specifications and simulation analysis specifications.

[0110] Engineering constants for metals and composite materials include elastic modulus, Poisson's ratio, shear modulus, and thermal expansion coefficient. Different cross-sections include T, Z, J, hat, and I-sections. Each type of cross-section contains cross-sectional parameters with different dimensional information.

[0111] The Excel spreadsheet in S2 has areas for filling in material parameters, structural ply parameters, unit offset parameters, and cross-section parameters. Each area has clear data formats and unit requirements.

[0112] The specific process of outputting the overall finite element model information of the wing box in S3 is as follows:

[0113] S3.1: Define the output direction of the structure: This provides an interactive interface through which users can specify two nodes on the model in sequence to determine the output direction. This operation can be performed twice to define the two output directions respectively.

[0114] S3.2: Specify structural reference elements: Provides an interactive interface for users to select the positioning elements to be output. For the wing surface, these are mainly ribs, front and rear beams, and long strings. For the rib web, these are mainly transverse and longitudinal reinforcements.

[0115] S3.3: The program can group and sort the selected positioning reference elements according to the defined direction and create a corresponding unit set;

[0116] S3.4: Provides an interface where the user selects the two-dimensional or one-dimensional structural unit to be output according to the actual structural form. The program automatically determines the intersection of each selected structural unit and the reference positioning unit, obtains the set number of the positioning reference unit that intersects with it, and takes the minimum value of the two-directional numbers to form a two-dimensional array as the output number of the structural unit;

[0117] S3.5: After obtaining all the numbers, the two-dimensional array of numbers is matched with the rows and columns of the Excel table, and then output, and the actual physical space position mapping table of the structural unit is obtained;

[0118] S3.6: Based on the mapping table, corresponding information of the structural unit is obtained, and also output according to the mapping relationship.

[0119] The corresponding information of the structural unit includes material, thickness, ply, length and width.

[0120] The specific process of updating the overall finite element model information of the wing box section in S4 is as follows:

[0121] S4.1: Read the structural unit information input table, obtain the metal and composite material engineering constant information in the table, and create materials;

[0122] S4.2: Parse the one-dimensional structural unit information table to obtain the finite element model unit ID corresponding to each structural unit;

[0123] S4.3: Obtain the cross-sectional form of a one-dimensional structural unit and obtain the cross-sectional parameters from the corresponding cross-sectional form table. For example, for a T-stringer, obtain the web height, flange width, web layup information, and flange layup information of the T-stringer. Then, find the corresponding layup and single-layer material parameters in the layup library and material library, and calculate the equivalent material parameters of the cross-sectional form based on the classical composite laminate theory. Furthermore, the web and flange thickness can be obtained based on the layup information, thereby calculating the cross-sectional moment of inertia and area information.

[0124] S4.4: Create cross-sectional properties based on the calculated cross-sectional information and match them with the structural elements to complete the attribute assignment of the one-dimensional element;

[0125] S4.5: Synthesize and analyze the two-dimensional structural unit parameter information to obtain the structural unit ply information, offset and other information;

[0126] S4.6: Create two-dimensional attributes and match them with structural units to complete the two-dimensional unit attribute assignment.

[0127] The cross-section equivalent material parameters include equivalent elastic modulus, equivalent Poisson's ratio, and equivalent thermal expansion coefficient.

[0128] The equivalent material parameters are calculated in S4.3. The specific formula is as follows:

[0129] The specific formula for the stiffness component of a single layer of material is:

[0130]

[0131] Where, is the elastic modulus in the fiber direction and transverse direction; are the main direction Poisson’s ratio and the transverse Poisson’s ratio, is the shear modulus; is the stiffness matrix component of the single layer material;

[0132] Equivalent engineering constants of laminates:

[0133]

[0134] Where h is the total thickness; is the equivalent elastic modulus; is Poisson's ratio; is the shear modulus, is the in-plane tensile stiffness of the laminate along the fiber direction; is the in-plane tension-shear coupling stiffness of the laminate; is the in-plane tensile stiffness of the laminate in the transverse direction.

[0135] The specific formula for calculating the cross-sectional inertia moment and area information is:

[0136] M-type cross-sectional area:

[0137]

[0138] Center axis position:

[0139]

[0140] Total moment of inertia of the section:

[0141]

[0142]

[0143] T-type cross-sectional area:

[0144]

[0145] Center axis position:

[0146]

[0147] Total moment of inertia of the section:

[0148]

[0149] Cross-sectional area of ​​the I-type:

[0150]

[0151] Center axis position:

[0152]

[0153] Total moment of inertia of the section:

[0154]

[0155] Z-section area:

[0156]

[0157] Center axis position:

[0158]

[0159] Total moment of inertia of the section:

[0160]

[0161] J-type cross-sectional area:

[0162]

[0163] Center axis position:

[0164]

[0165] Total moment of inertia of the section:

[0166]

[0167] C-type cross-sectional area:

[0168]

[0169] Center axis position:

[0170]

[0171] Total moment of inertia of the section:

[0172]

[0173] L-shaped cross-sectional area:

[0174]

[0175] Center axis position:

[0176]

[0177] Total moment of inertia of the section:

[0178]

[0179] Rectangular cross-sectional area:

[0180]

[0181] Center axis position:

[0182]

[0183] Total moment of inertia of the section:

[0184]

[0185] .

[0186] like Figures 1-12As shown, this embodiment provides a method for rapidly updating and outputting overall finite element model information for a box segment. The specific method is as follows: First, S1: construct a material database, a ply database, a cross-section information database, and a specification database. The material database in S1 includes engineering constants for metals and composite materials, including elastic modulus, Poisson's ratio, shear modulus, and thermal expansion coefficient. The ply database includes detailed layup sequences for various ply ratios. For example, a layup file with a layup angle of 0° / ±45° / 90° of 631 contains 12 to 100 plies, and the 0° / ±45° / 90° ratio for each number of plies is approximately 6 / 3 / 1. The cross-section information database includes cross-section information of various sizes for different cross-section types, including T, Z, J, hat, and I-section sections. Each cross-section type contains cross-section parameters with different dimensional information. The specification database includes modeling specifications and simulation analysis specifications to ensure that the updated model information meets requirements. S2: Based on the underlying data, fill in the Excel table in the format required by the program and provide the input parameters required for model update; the Excel table in S2 has material parameter filling area, structural ply parameter filling area, unit offset parameter filling area and section parameter filling area, and each area has clear data format and unit requirements. S3: Secondary development in HyperMesh, based on the characteristics of GFEM, obtains structural units and their information and stores them in memory, and outputs the information to the Excel table through Excel development; 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, through which the user can specify two nodes on the model in turn to determine the output direction. The operation can be performed twice to define the two output directions respectively; S3.2: Specify structural reference elements: Provide an interactive interface, which is mainly used for users to select the positioning elements for output. For the wing surface, it is mainly ribs, front and rear beams, and long spar. For the rib web, it is mainly transverse and longitudinal reinforcement; S3.3: The program can output the overall finite element model information of the wing box section according to the defined direction S3.4: Provides an interface for users to select the two-dimensional or one-dimensional structural units that need to be output according to the actual structural form. The program automatically determines the intersection of each selected structural unit and the reference positioning unit, obtains the positioning reference unit set number that intersects with it, and takes the minimum value of the two-directional numbers to form a two-dimensional array as the output number of the structural unit. S3.5: After obtaining all the numbers, the two-dimensional array of numbers is matched with the rows and columns of the Excel table, and then output, and you can get the actual physical space position mapping table of the structural unit. S3.6: Based on the mapping table, obtain the corresponding information of the structural unit and output it according to the mapping relationship. The corresponding information of the structural unit includes material, thickness, ply, length and width.S4: Based on the characteristics of GFEM and the output model information file, a property update template is created. The physical parameters of the elements are obtained through Excel development and secondary development is performed in HyperMesh. 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 metal and composite engineering constant information in the table, and create materials; S4.2: Parse the one-dimensional structural element information table to obtain the corresponding finite element model element ID for each structural element; S4.3: Obtain the cross-sectional form of the one-dimensional structural element and obtain the cross-sectional parameters from the corresponding cross-sectional form table. For example, for a T-type stringer, obtain the web height, flange width, web layup information, and flange layup information for the T-type stringer. Then, find the corresponding layup and single-layer material parameters in the layup library and material library, and calculate the cross-sectional equivalent material parameters based on the classical composite laminate theory. The cross-sectional equivalent material parameters include the equivalent elastic modulus, equivalent Poisson's ratio, and equivalent thermal expansion coefficient. The specific formula for calculating the equivalent material parameters is as follows:

[0187] The specific formula for the stiffness component of a single layer of material is:

[0188]

[0189] Where, is the elastic modulus in the fiber direction and transverse direction; are the main direction Poisson’s ratio and the transverse Poisson’s ratio, is the shear modulus; is the stiffness matrix component of the single layer material;

[0190] Equivalent engineering constants of laminates:

[0191]

[0192] Where h is the total thickness; is the equivalent elastic modulus; is Poisson's ratio; is the shear modulus, is the in-plane tensile stiffness of the laminate along the fiber direction; is the in-plane tension-shear coupling stiffness of the laminate; is the in-plane tensile stiffness of the laminate in the transverse direction.

[0193] The web and flange thickness can be obtained based on the layup information, thereby calculating the cross-sectional inertia moment and area information. The specific formula for calculating the cross-sectional inertia moment and area information is:

[0194] M-type long stringer parameter calculation: Figure 5 shown

[0195] M-type cross-sectional area:

[0196]

[0197] Center axis position:

[0198]

[0199] Total moment of inertia of the section:

[0200]

[0201] Calculation of T-type long stringer parameters: Figure 6 shown

[0202] T-type cross-sectional area:

[0203]

[0204] Center axis position:

[0205]

[0206] Total moment of inertia of the section:

[0207]

[0208] Calculation of I-section parameters: Figure 7 shown

[0209] Cross-sectional area of ​​the I-type:

[0210]

[0211] Center axis position:

[0212]

[0213] Total moment of inertia of the section:

[0214]

[0215] Z-section parameter calculation: Figure 8 shown

[0216] Z-section area:

[0217]

[0218] Center axis position:

[0219]

[0220] Total moment of inertia of the section:

[0221]

[0222] J-section parameter calculation: Figure 9 shown

[0223] J-type cross-sectional area:

[0224]

[0225] Center axis position:

[0226]

[0227] Total moment of inertia of the section:

[0228]

[0229] C-section parameter calculation: Figure 10 shown

[0230] C-type cross-sectional area:

[0231]

[0232] Center axis position:

[0233]

[0234] Total moment of inertia of the section:

[0235]

[0236] L-section parameter calculation: Figure 11 shown

[0237] L-shaped cross-sectional area:

[0238]

[0239] Center axis position:

[0240]

[0241] Total moment of inertia of the section:

[0242]

[0243] Rectangular section parameter calculation: Figure 12 shown

[0244] Rectangular cross-sectional area:

[0245]

[0246] Center axis position:

[0247]

[0248] Total moment of inertia of the section:

[0249] .

[0250] S4.4: Create section properties based on the calculated section information and match them with the structural units to complete the attribute assignment of the one-dimensional unit; S4.5: Simultaneously analyze the parameter information of the two-dimensional structural unit to obtain the structural unit ply information, offset and other information; S4.6: Create two-dimensional properties and match them with the structural unit to complete the attribute assignment of the two-dimensional unit.

[0251] Throughout this specification, references to terms such as "one embodiment," "example," or "specific example" indicate that the specific features, structures, materials, or characteristics described in conjunction with that embodiment or example are included in at least one embodiment or example of the present invention. In this specification, schematic representations of these terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

[0252] The preferred embodiments of the present invention disclosed above are intended only to help illustrate the present invention. These preferred embodiments do not exhaustively describe all details, nor do they limit the present invention to the specific embodiments described. Obviously, many modifications and variations are possible based on the content of this specification. These embodiments are selected and described in detail in this specification to better explain the principles and practical applications of the present invention, thereby enabling those skilled in the art to better understand and utilize the present invention. The present invention is limited only by the claims and their full scope and equivalents.

Claims

1. A method for rapidly updating and outputting overall finite element model information of a box segment, characterized in that: The following steps are involved: S1: Build material database, ply database, cross-section information database and specification database; S2: Based on the underlying data, fill in the Excel table in the format required by the program and provide the input parameters required for model update; S3: Secondary development was performed in HyperMesh. Based on the characteristics of GFEM, the structural elements and their information were obtained and stored in the memory. The overall finite element model information of the wing box section was output to an Excel spreadsheet through Excel development. S4: Based on the characteristics of GFEM and the output model information file, a property update template is created, the unit physical parameters are obtained through Excel development, and the overall finite element model information of the wing box section is updated through secondary development in HyperMesh; The specific process of outputting the overall finite element model information of the wing box in S3 is as follows: S3.1: Define the output direction of the structure: This provides an interactive interface through which users can specify two nodes on the model in sequence to determine the output direction. This operation can be performed twice to define the two output directions respectively. S3.2: Specify structural reference elements: Provides an interactive interface for users to select the positioning elements to be output. For the wing surface, these are mainly ribs, front and rear beams, and long strings. For the rib web, these are 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 a corresponding unit set; S3.4: Provides an interface where the user selects the two-dimensional or one-dimensional structural unit to be output according to the actual structural form. The program automatically determines the intersection of each selected structural unit and the reference positioning unit, obtains the set number of the positioning reference unit that intersects with it, and takes the minimum value of the two-directional numbers to form a two-dimensional array as the output number of the structural unit; S3.5: After obtaining all the numbers, the two-dimensional array of numbers is matched with the rows and columns of the Excel table, and then output to obtain the actual physical space position mapping table of the structural units; S3.6: Based on the mapping table, obtain corresponding information of the structural unit and output it according to the mapping relationship; The corresponding information of the structural unit includes material, thickness, ply, 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 unit information input table, obtain the metal and composite material engineering constant information in the table, and create materials; S4.2: Parse the one-dimensional structural unit information table to obtain the finite element model unit ID corresponding to each structural unit; S4.3: Obtain the cross-sectional form of a one-dimensional structural unit and obtain the cross-sectional parameters from the corresponding cross-sectional form table. For example, for a T-stringer, obtain the web height, flange width, web layup information, and flange layup information of the T-stringer. Then, find the corresponding layup and single-layer material parameters in the layup library and material library, and calculate the equivalent material parameters of the cross-sectional form based on the classical composite laminate theory. Furthermore, the web and flange thickness can be obtained based on the layup information, thereby calculating the cross-sectional moment of inertia and area information. S4.4: Create cross-sectional properties based on the calculated cross-sectional information and match them with the structural elements to complete the attribute assignment of the one-dimensional element; S4.5: Synthesize and analyze the two-dimensional structural unit parameter information to obtain the structural unit ply information and offset information; S4.6: Create two-dimensional attributes and match them with structural units to complete the two-dimensional unit attribute assignment.

2. The method for rapidly updating and outputting the overall finite element model information of a box segment according to claim 1, characterized in that: The material database in S1 includes engineering constants of metals and composite materials, the ply database includes detailed ply layup sequences for different numbers of plies at different ply ratios, the section information library includes section information of various sizes under different section forms, and the specification library includes modeling specifications and simulation analysis specifications.

3. The method for rapidly 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 metal 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, and each type of cross-section contains cross-sectional parameters with different size information.

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

5. The method for rapidly 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 thermal expansion coefficient.

6. The method for rapidly updating and outputting the overall finite element model information of a box segment according to claim 1, characterized in that: The equivalent material parameters are calculated in S4.3, and the specific formula is as follows: The specific formula for the stiffness component of a single layer of material is: ， Where, 、 is the elastic modulus in the fiber direction and transverse direction; are the main direction Poisson’s ratio and the transverse Poisson’s ratio, is the shear modulus; is the stiffness matrix component of the single layer material; Equivalent engineering constants of laminates: ， Where h is the total thickness; is the equivalent elastic modulus; is Poisson's ratio; is the shear modulus; is the in-plane tensile stiffness of the laminate along the fiber direction; is the in-plane tension-shear coupling stiffness of the laminate; is the in-plane tensile stiffness of the laminate in the transverse direction.

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