Input file generation method, device and electronic device thereof

Abstract

The present invention provides an input file generation method, device, and electronic device thereof, relating to the field of simulation technology. The input file includes: an execution control segment, a working condition control segment, and a data segment; the method includes: obtaining flutter calculation parameters input by a user; the flutter calculation parameters include an input file name, execution control parameters, working condition control parameters, and data parameters; establishing an initial file based on the input file name; calling a preset execution control segment template and filling in the execution control parameters, thereby generating the execution control segment in the initial file; calling a preset working condition control segment template and filling in the working condition control parameters, thereby generating the working condition control segment in the initial file; calling a preset data segment template and filling in the data parameters, thereby generating the data segment in the initial file, thereby obtaining the input file, thereby improving the accuracy of the obtained input file.

Description

Technical Field

[0001] The present invention relates to the field of simulation technology, and in particular to an input file generation method, device and electronic equipment thereof. Background Art

[0002] The input files for simulation software generally need to describe various aspects of the simulation object, such as boundary conditions, initial conditions, loads, and the motion of the simulation object. Input files can often reach hundreds of lines. Some simulation software lacks a pre-processing interface and cannot provide graphical guidance to users. Furthermore, precise syntax and formatting must be followed when writing input files. Therefore, input files for simulation software without a pre-processing interface are generally written manually by professional technicians. When the input files contain a large amount of content, especially when part of the input file requires repeated querying of tables or pre-established models, the efficiency of generating the input file and the accuracy of the resulting input file are relatively low. Summary of the Invention

[0003] In view of the problems existing in the prior art, the present invention provides an input file generating method, device and electronic equipment thereof.

[0004] The present invention provides a method for generating an input file, wherein the input file includes: an execution control section, a working condition control section, and a data section; the method includes:

[0005] Obtaining vibration calculation parameters input by the user; the vibration calculation parameters include input file name, execution control parameters, working condition control parameters and data parameters;

[0006] Creating an initial file based on the input file name;

[0007] Call the preset execution control segment template and fill in the execution control parameters to generate the execution control segment in the initial file; call the preset working condition control segment template and fill in the working condition control parameters to generate the working condition control segment in the initial file; call the preset data segment template and fill in the data parameters to generate the data segment in the initial file to obtain the input file.

[0008] According to a method for generating an input file provided by the present invention, the data parameters include card parameters and lifting surface data parameters; the input file is used to perform flutter calculation on the lifting surface;

[0009] Before calling the preset data segment template and filling in the data parameters, the method further includes:

[0010] Calculating aerodynamic grid node coordinates of the lifting surface based on the lifting surface data parameters;

[0011] Obtaining finite element nodes and their numbers of the lifting surface based on the aerodynamic grid node coordinates and a preset finite element model, and storing the finite element node numbers of the lifting surface;

[0012] Call the preset data segment template and fill in the data parameters, including:

[0013] The preset data segment template is called and the card parameters and the finite element node number of the lifting surface are filled in.

[0014] According to an input file generation method provided by the present invention, the lifting surface data parameters include the spanwise number of aerodynamic grids, the chordwise number of aerodynamic grids, the root chord vertex coordinates, the root chord length, the tip chord vertex coordinates and the tip chord length;

[0015] Calculating the aerodynamic grid node coordinates of the lifting surface based on the lifting surface data parameters specifically includes:

[0016] Obtaining the aerodynamic grid node coordinates on the root chord based on the root chord vertex coordinates, the root chord length, and the number of aerodynamic grids in the chord direction; obtaining the aerodynamic grid node coordinates on the tip chord based on the tip chord vertex coordinates, the tip chord length, and the number of aerodynamic grids in the chord direction;

[0017] The aerodynamic grid node coordinates inside the lifting surface are obtained based on the aerodynamic grid node coordinates on the root chord, the corresponding aerodynamic grid node coordinates on the tip chord, and the spanwise number of the aerodynamic grids.

[0018] According to an input file generation method provided by the present invention, the aerodynamic grid node coordinates on the root chord are obtained based on the root chord vertex coordinates, the root chord length, and the number of aerodynamic grids in the chord direction; and the aerodynamic grid node coordinates on the tip chord are obtained based on the tip chord vertex coordinates, the tip chord length, and the number of aerodynamic grids in the chord direction, specifically comprising:

[0019] The coordinates of the root chord end point are obtained based on the coordinates of the root chord vertex and the root chord length; a plurality of root chord equally divided points are obtained on the line connecting the root chord vertex and the root chord end point based on the number of aerodynamic grid chord directions; and the coordinates of the aerodynamic grid nodes on the root chord are obtained through the coordinates of the root chord vertex, the coordinates of the root chord end point, and the coordinates of each of the root chord equally divided points.

[0020] The tip chord end point coordinates are obtained based on the tip chord apex coordinates and the tip chord length, and a plurality of tip chord equally divided points are obtained on the line between the tip chord apex and the tip chord end point based on the number of aerodynamic grid chord directions. The aerodynamic grid node coordinates on the tip chord are obtained through the tip chord apex coordinates, the tip chord end point coordinates and the coordinates of each tip chord equally divided point.

[0021] According to an input file generation method provided by the present invention, the aerodynamic grid node coordinates inside the lifting surface are obtained based on the aerodynamic grid node coordinates on the root chord, the corresponding aerodynamic grid node coordinates on the tip chord, and the spanwise number of the aerodynamic grids, specifically comprising:

[0022] Acquire a plurality of internal equally divided points on a line connecting an aerodynamic grid node on the root chord and a corresponding aerodynamic grid node on the tip chord based on the spanwise number of the aerodynamic grid;

[0023] The coordinates of the aerodynamic grid nodes inside the lifting surface are obtained based on the coordinates of each of the internal equally divided points.

[0024] According to an input file generation method provided by the present invention, the execution control parameter is a modal calculation result file name;

[0025] Obtaining the finite element nodes and their numbers of the lifting surface based on the aerodynamic grid node coordinates and a preset finite element model specifically includes:

[0026] Obtaining a modal calculation result database file based on the modal calculation result file name;

[0027] Obtaining finite element nodes of the preset finite element model according to the modal calculation result database file, selecting a finite element node closest to each aerodynamic grid node coordinate from the finite element nodes based on the aerodynamic grid node coordinates and obtaining a number;

[0028] The finite element nodes and their numbers of the lifting surface are obtained based on the selected finite element nodes and their numbers.

[0029] According to an input file generation method provided by the present invention, obtaining the finite element nodes of the preset finite element model according to the modal calculation result database file specifically includes:

[0030] Importing the modal calculation result database file into finite element software;

[0031] The finite element nodes of the preset finite element model are obtained by calling a setting function through the model data interface of the finite element software.

[0032] The present invention also provides an input file generating device, wherein the input file includes: an execution control section, a working condition control section and a data section; the device includes:

[0033] A parameter acquisition module is used to obtain vibration calculation parameters input by the user; the vibration calculation parameters include input file name, execution control parameters, working condition control parameters and data parameters;

[0034] An initial file creation module, configured to create an initial file based on the input file name;

[0035] An input file generation module is used to call a preset execution control segment template and fill in the execution control parameters to generate the execution control segment in the initial file; call a preset working condition control segment template and fill in the working condition control parameters to generate the working condition control segment in the initial file; call a preset data segment template and fill in the data parameters to generate the data segment in the initial file to obtain the input file.

[0036] The present invention also provides an electronic device, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein when the processor executes the computer program, any one of the above-described input file generation methods is implemented.

[0037] The present invention also provides a non-transitory computer-readable storage medium having a computer program stored thereon, which implements any of the above-mentioned input file generation methods when executed by a processor.

[0038] Compared with the user manually writing all the contents of the input file, the input file generation method, device and electronic device provided by the present invention, after establishing the initial file, obtain part of the content of the input file through a preset execution control segment template, a preset working condition control segment template and a preset data segment template, and combine the vibration calculation parameters input by the user to obtain the input file based on the initial file, which can improve the accuracy of the obtained input file. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] In order to more clearly illustrate the technical solutions in the present invention or the prior art, a brief introduction is given below to the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0040] Figure 1 It is a flow chart of the input file generating method provided by the present invention.

[0041] Figure 2 This is one of the schematic diagrams of the input file of the input file generation method provided by the present invention.

[0042] Figure 3 This is the second schematic diagram of the input file of the input file generation method provided by the present invention.

[0043] Figure 4 This is the third schematic diagram of the input file of the input file generation method provided by the present invention.

[0044] Figure 5This is the fourth schematic diagram of the input file of the input file generation method provided by the present invention.

[0045] Figure 6 This is the fifth schematic diagram of the input file of the input file generation method provided by the present invention.

[0046] Figure 7 This is the sixth schematic diagram of the input file of the input file generation method provided by the present invention.

[0047] Figure 8 This is the seventh schematic diagram of the input file of the input file generation method provided by the present invention.

[0048] Figure 9 This is the eighth schematic diagram of the input file of the input file generation method provided by the present invention.

[0049] Figure 10 This is the ninth schematic diagram of the input file of the input file generation method provided by the present invention.

[0050] Figure 11 This is the tenth schematic diagram of the input file of the input file generation method provided by the present invention.

[0051] Figure 12 This is the eleventh schematic diagram of the input file of the input file generation method provided by the present invention.

[0052] Figure 13 This is the twelfth schematic diagram of the input file of the input file generation method provided by the present invention.

[0053] Figure 14 This is the thirteenth schematic diagram of the input file of the input file generation method provided by the present invention.

[0054] Figure 15 This is the fourteenth schematic diagram of the input file of the input file generation method provided by the present invention.

[0055] Figure 16 This is the fifteenth schematic diagram of the input file of the input file generation method provided by the present invention.

[0056] Figure 17 It is a structural diagram of the input file generating device provided by the present invention.

[0057] Figure 18 It is a structural schematic diagram of the electronic device provided by the present invention. DETAILED DESCRIPTION

[0058] To make the objectives, technical solutions, and advantages of the present invention more clear, the technical solutions of the present invention will be clearly and completely described below in conjunction with the accompanying drawings. Obviously, the embodiments described are only some of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts shall fall within the scope of protection of the present invention.

[0059] The following combination Figures 1-18 The present invention describes an input file generating method, device and electronic device thereof.

[0060] Figure 1 The present invention provides a flow chart of the input file generation method, wherein the input file includes an execution control section, a working condition control section, and a data section.

[0061] Input files are used by the simulation software to perform flutter calculations. In other words, input files provide the necessary information and parameters for the simulation software to perform flutter calculations. Input files can be text files or JSON files. Text files can have a .inp extension.

[0062] The execution control section generally specifies how the simulation software reads and processes modal calculation results for flutter calculations. For example, the execution control section specifies how the simulation software reads modal calculation result files and sets initial simulation conditions. Modal calculation result files are generated after performing modal calculations on the finite element model and include modal calculation results such as natural frequencies and mode shapes.

[0063] To facilitate the simulation software to process the modal calculation result file, the execution control segment may also include background information of the modal calculation result file, such as the name of the application that generates the modal calculation result file.

[0064] The operating condition control section generally indicates the operating conditions and analysis parameters used by the simulation software for flutter calculation, and the data section generally indicates the specific data used by the simulation software for flutter calculation.

[0065] like Figure 1 As shown, the method includes:

[0066] Step 101: Obtain vibration calculation parameters input by a user; the vibration calculation parameters include an input file name, execution control parameters, working condition control parameters, and data parameters.

[0067] For example, a parameter input window may pop up to the user on the display interface. The parameter input window may include a parameter input template. The user may input the vibration calculation parameters in the parameter input window based on the parameter input template.

[0068] Step 102: Create an initial file based on the input file name.

[0069] The input file name is the file name of the input file. The initial file is a container for storing the flutter calculation parameters, detailed data, and analysis parameters used for the flutter calculation. Analysis parameters are parameters that guide the simulation software in processing the flutter calculation parameters and detailed data. Examples include parameters that specify the analysis type and boundary condition parameters.

[0070] Exemplarily, when the input file is a text file, after obtaining the input file name input by the user, a blank text file may be created, and the blank text file may be named using the input file name to create an initial file.

[0071] Step 103: Call the preset execution control segment template and fill in the execution control parameters to generate the execution control segment in the initial file; call the preset working condition control segment template and fill in the working condition control parameters to generate the working condition control segment in the initial file; call the preset data segment template and fill in the data parameters to generate the data segment in the initial file to obtain the input file.

[0072] The preset execution control segment template includes the necessary structure, elements and fill-in information, which can reduce the amount of writing tasks for the execution control segment and reduce the risk of missing important information or format errors. The fill-in information is the specific execution control parameters filled in. For example, the preset execution control segment template can be "$ASSIGN FEM = '{modal_result_file}',FORM = ABAQUS, BOUND = ASYM, PRINT = 0", and the execution control parameters entered by the user can be assigned to the variable modal_result_file to fill the execution control parameters into the preset execution control segment template, and obtain "$ASSIGN FEM ='execution control parameters', FORM = ABAQUS, BOUND = ASYM, PRINT = 0". The preset function is used to write the assigned preset execution control segment template into the initial file to generate the execution control segment.

[0073] The composition, application and technical effects of the preset working condition control segment template and the preset data segment template are basically the same as those of the preset execution control segment template, and will not be repeated here.

[0074] It can be understood that the necessary structure, elements and fill-in information in the preset execution control segment template, the necessary structure, elements and fill-in information in the preset working condition control segment template, and the necessary structure, elements and fill-in information in the preset data segment template are generally different. The specific necessary structure, necessary elements and fill-in information can be determined by professionals and pre-compiled into corresponding templates. The present invention does not further limit this.

[0075] Compared with the user manually writing all the contents of the input file, the input file generation method provided by the present invention, after establishing the initial file, obtains part of the content of the input file through a preset execution control segment template, a preset working condition control segment template, and a preset data segment template. Combined with the vibration calculation parameters input by the user, the input file is obtained on the basis of the initial file, which can improve the accuracy of the obtained input file.

[0076] At the same time, by obtaining part of the content of the input file through the preset execution control segment template, the preset working condition control segment template and the preset data segment template, the number of vibration calculation parameters input by the user can be reduced, thereby improving the efficiency of generating the input file.

[0077] Based on the above embodiment, the data parameters include card parameters and lifting surface data parameters; and the input file is used to perform flutter calculation on the lifting surface.

[0078] A card is the basic unit of a data segment, which includes multiple cards, such as the CORD2R card, AEROZ card, CAERO7 card, PLTAERO card, SPLINE1 card, PANLST3 card, SET1 card, MKAEROZ card, FLUTTER card, FIXMDEN card, PLTMODE card, and PLTFLUT card.

[0079] The card includes a card name and card data, which can be one line or multiple lines. Each line of card data can include multiple card data. In some embodiments, each card data does not exceed a preset character length, for example, each card data does not exceed 8 characters.

[0080] The preset data segment template includes multiple card templates. The card data for a card consists of a card template and card data, which are the specific card parameters to be entered. For example, the card name of an AEROZ card is AEROZ, and the card template for the AEROZ card includes "FMMUNIT:N / , FMLUNIT:M, REFC:modal_pattern." The card parameters used for input can be assigned to the variable modal_pattern to fill the card parameters into the card template, resulting in "FMMUNIT:N / , FMLUNIT:M, REFC:card_parameters." This embodiment only shows a portion of the AEROZ card data and does not represent the complete AEROZ card data. A preset function can be used to write the assigned card template into the initial file to generate the partial AEROZ card data in the data segment.

[0081] The input file is used to pass it to the simulation software for flutter calculations. The flutter calculation results are used to evaluate the dynamic stability and structural safety of the lifting surface under high-speed flight conditions. When performing flutter calculations, the simulation software generally needs to obtain the dynamic characteristics of the structure, and the modal analysis results of the finite element model can describe the dynamic characteristics of the structure. Therefore, before performing the flutter calculation of the lifting surface, a modal calculation is first performed on the lifting surface, and the results of the modal calculation are written into the input file. The results of the modal calculation include the finite element node numbers corresponding to the aerodynamic nodes of the lifting surface. The finite element node numbers can assist in identifying the location where the aerodynamic force is applied on the lifting surface and obtaining the dynamic characteristics of the structure.

[0082] The SET1 card in the data segment contains finite element node numbers. Currently, adding finite element node numbers to the SET1 card in the data segment typically requires a specialist technician to click on the finite element model to query the finite element node numbers and then write them one by one into the input file, which is very time-consuming. Furthermore, when there are many finite element node numbers, there is a high probability that the finite element node numbers added to the input file will be incorrect.

[0083] To solve the above technical problem, in one embodiment, before calling the preset data segment template and filling in the data parameters, the method further includes:

[0084] Calculating aerodynamic grid node coordinates of the lifting surface based on the lifting surface data parameters;

[0085] Obtaining finite element nodes and their numbers of the lifting surface based on the aerodynamic grid node coordinates and a preset finite element model, and storing the finite element node numbers of the lifting surface;

[0086] Call the preset data segment template and fill in the data parameters, including:

[0087] The preset data segment template is called and the card parameters and the finite element node number of the lifting surface are filled in.

[0088] A lifting surface is a surface used to generate lift, such as the wings of an airplane.

[0089] Lifting surface data parameters describe the structural characteristics of a lifting surface. Aerodynamic mesh nodes are the intersections of the aerodynamic mesh within the lifting surface. Aerodynamic meshes divide the lifting surface into multiple small regions for easier aerodynamic analysis. Aerodynamic mesh nodes approximate the locations where aerodynamic forces are applied on the lifting surface.

[0090] For example, after calculating the aerodynamic grid node coordinates of the lifting surface, each aerodynamic grid node coordinate can be transferred to the coordinate system of the finite element node according to the preset transformation matrix. Then, based on the aerodynamic grid node coordinates and the finite element node coordinates in the preset finite element model, the distance between the aerodynamic grid node and the finite element node is obtained, thereby obtaining the finite element node closest to each aerodynamic grid node and its number, and saving the finite element node number of the lifting surface to the variable nodesID. NodesID can be any sequence type. Then, the card template in the preset data segment template is called through the preset function, the corresponding card parameters or finite element node number are filled into the card template, and the assigned card template is written into the initial file to generate the card in the data segment.

[0091] In this embodiment, the aerodynamic grid node coordinates of the lifting surface are calculated using the lifting surface data parameters, and the corresponding finite element nodes in the preset finite element model are obtained through the aerodynamic grid node coordinates, and then the corresponding finite element node numbers are obtained. This can reduce the risk of omissions in methods such as clicking on the finite element model to query and obtain the finite element node numbers, improve the accuracy of the obtained finite element node numbers, and thus improve the accuracy of the obtained input file.

[0092] Based on any of the above embodiments, the lifting surface data parameters include the spanwise number of aerodynamic grids, the chordwise number of aerodynamic grids, the root chord vertex coordinates, the root chord length, the tip chord vertex coordinates, and the tip chord length.

[0093] The coordinates of the root chord vertex and tip chord vertex of a lifting surface can be determined based on the aerodynamic coordinate system. The x-axis of the aerodynamic coordinate system is parallel to the chord direction of the lifting surface, the z-axis points upward, and the y-axis is determined by the right-hand system. The chord direction of the lifting surface points in the direction of the airflow, and upward refers to the direction of the pilot's head. The lifting surface must be located in the +y space of the aerodynamic coordinate system, or in other words, it must be located in the positive direction of the y-axis of the aerodynamic coordinate system, that is, to the pilot's right hand.

[0094] The aerodynamic grid can be obtained by meshing the lifting surface plane model. The spanwise number of aerodynamic grids is the number of aerodynamic grids in the spanwise direction, and the chordwise number of aerodynamic grids is the number of aerodynamic grids in the chordwise direction. Figure 2 As shown, the x-axis is the chord direction, the y-axis is the span direction, the number of aerodynamic grids in the span direction is 4, and the number of aerodynamic grids in the chord direction is 4.

[0095] In one embodiment, calculating the aerodynamic grid node coordinates of the lifting surface based on the lifting surface data parameters specifically includes:

[0096] Obtaining the aerodynamic grid node coordinates on the root chord based on the root chord vertex coordinates, the root chord length, and the number of aerodynamic grids in the chord direction; obtaining the aerodynamic grid node coordinates on the tip chord based on the tip chord vertex coordinates, the tip chord length, and the number of aerodynamic grids in the chord direction;

[0097] The aerodynamic grid node coordinates inside the lifting surface are obtained based on the aerodynamic grid node coordinates on the root chord, the corresponding aerodynamic grid node coordinates on the tip chord, and the spanwise number of the aerodynamic grids.

[0098] Aerodynamic mesh nodes inside a lifting surface include all aerodynamic mesh nodes on the lifting surface except those on the root chord and tip chord. For example, the aerodynamic mesh nodes on the line connecting the root chord vertex and the tip chord vertex are considered aerodynamic mesh nodes inside the lifting surface.

[0099] For example, after obtaining the aerodynamic grid nodes on the root chord and the aerodynamic grid nodes on the tip chord, the aerodynamic grid node coordinates inside a part of the lifting surface can be obtained based on the aerodynamic grid nodes on the root chord closest to the root chord vertex, the aerodynamic grid nodes on the tip chord closest to the tip chord vertex, and the spanwise number of aerodynamic grids, and so on until the aerodynamic grid node coordinates inside all the lifting surfaces are obtained.

[0100] In this embodiment, by first obtaining the aerodynamic grid node coordinates on the root chord and the aerodynamic grid node coordinates on the tip chord, and then obtaining the aerodynamic grid node coordinates inside the lift surface through the aerodynamic grid node coordinates on the root chord, the corresponding aerodynamic grid node coordinates on the tip chord and the spanwise number of the aerodynamic grids, the orthogonality and area uniformity of the aerodynamic grid can be enhanced, the grid quality can be optimized, and the accuracy and convergence of the numerical analysis can be improved.

[0101] Based on any of the foregoing embodiments, obtaining the coordinates of the aerodynamic grid nodes on the root chord based on the root chord vertex coordinates, the root chord length, and the number of aerodynamic grids in the chord direction; and obtaining the coordinates of the aerodynamic grid nodes on the tip chord based on the tip chord vertex coordinates, the tip chord length, and the number of aerodynamic grids in the chord direction specifically includes:

[0102] The coordinates of the root chord end point are obtained based on the coordinates of the root chord vertex and the root chord length; a plurality of root chord equally divided points are obtained on the line connecting the root chord vertex and the root chord end point based on the number of aerodynamic grid chord directions; and the coordinates of the aerodynamic grid nodes on the root chord are obtained through the coordinates of the root chord vertex, the coordinates of the root chord end point, and the coordinates of each of the root chord equally divided points.

[0103] The tip chord end point coordinates are obtained based on the tip chord apex coordinates and the tip chord length, and a plurality of tip chord equally divided points are obtained on the line between the tip chord apex and the tip chord end point based on the number of aerodynamic grid chord directions. The aerodynamic grid node coordinates on the tip chord are obtained through the tip chord apex coordinates, the tip chord end point coordinates and the coordinates of each tip chord equally divided point.

[0104] For example, the x-axis of the aerodynamic coordinate system can be parallel to the root chord direction (chord-wise direction) of the lifting surface. The coordinates of the root chord vertex are (4.37, 0.113, 0.113), and the root chord length is 0.759m. From this, the coordinates of the root chord end point can be obtained as (5.129, 0.113, 0.113). When calculating the root chord dividing points, since the chord direction is parallel to the x-axis of the aerodynamic coordinate system, the y and z coordinates of the same chord remain unchanged, and only the x coordinate needs to be calculated. The number of aerodynamic grid nodes in the chord direction is 30, and there will be 31 aerodynamic grid nodes on the root chord. The coordinate x of the nth point starting from the vertex is:

[0105]

[0106] The x-axis of the aerodynamic coordinate system can be parallel to the tip chord direction (chordwise direction) of the lift surface. The coordinates of the tip chord vertex are (4.4507, 0.3253, 0.3253), and the tip chord length is 0.599. Therefore, the coordinates of the tip chord end point are (5.0497, 0.3253, 0.3253). When calculating the tip chord equalization points, since the chordwise direction is parallel to the x-axis of the aerodynamic coordinate system, the y and z coordinates of the same chord remain unchanged, and only the x coordinate needs to be calculated. The number of aerodynamic grid nodes in the chordwise direction is 30, and there will be 31 aerodynamic grid nodes on the tip chord. The x coordinate of the nth point starting from the vertex is:

[0107]

[0108] Based on any of the above embodiments, obtaining the aerodynamic grid node coordinates inside the lifting surface based on the aerodynamic grid node coordinates on the root chord, the corresponding aerodynamic grid node coordinates on the tip chord, and the spanwise number of the aerodynamic grids specifically includes:

[0109] Acquire a plurality of internal equally divided points on a line connecting an aerodynamic grid node on the root chord and a corresponding aerodynamic grid node on the tip chord based on the spanwise number of the aerodynamic grid;

[0110] The coordinates of the aerodynamic grid nodes inside the lifting surface are obtained based on the coordinates of each of the internal equally divided points.

[0111] For example, a corresponding number of internal equally divided points can be obtained on the line between the aerodynamic grid node on the root chord closest to the root chord vertex and the aerodynamic grid node on the tip chord closest to the tip chord vertex according to the spanwise number of the aerodynamic grid.

[0112] For example, the aerodynamic mesh node on the root chord closest to the root chord vertex is the aerodynamic mesh node on the root chord with n=2, and its coordinates are (4.3953, 0.113, 0.113). The aerodynamic mesh node on the tip chord closest to the tip chord vertex is the aerodynamic mesh node on the tip chord with n=2, and its coordinates are (4.4707, 0.3253, 0.3253).

[0113] The spanwise number of aerodynamic grids is 30. There will be 31 aerodynamic grid nodes on the line connecting the aerodynamic grid node on the root chord closest to the root chord vertex and the aerodynamic grid node on the tip chord closest to the tip chord vertex. The coordinates of the mth point starting from the root chord are

[0114]

[0115] Repeat the above steps of obtaining the internal equally divided points to obtain the remaining internal equally divided points.

[0116] Based on any of the above embodiments, the execution control parameter is the modal calculation result file name.

[0117] The file name includes a text name and a file extension. The file name input by the user may include the text name and the file extension, for example, the file name input by the user is ZAERO.inp; the file name input by the user may also include only the text name, for example, the file name input by the user is ZAERO.

[0118] It is understandable that no matter whether the file input by the user includes a file extension or not, a file name with the same text name and file extension points to the same file. In other words, two file names with the same text name but different file extensions point to different files.

[0119] For example, the modal calculation result file name entered by the user is Job-symm-fix, which only includes the text name and does not include the file extension. When calling the preset execution control section template and entering the execution control parameters, the file name Job-symm-fix and the file extension .unv are combined to create the file Job-symm-fix.unv. When obtaining the finite element nodes and their numbering of the lifting surface based on the aerodynamic mesh node coordinates and a preset finite element model, the file Job-symm-fix.odb can also be created using the preset template or splicing process, by using the file name Job-symm-fix and the file extension .odb.

[0120] In this way, by predetermining the file extensions of the modal calculation result file names at different locations, the user only needs to enter the text name of the modal calculation result file name, reducing the risk of filling in errors due to similarity between two modal calculation result file names and improving the accuracy of the input file.

[0121] Obtaining the finite element nodes and their numbers of the lifting surface based on the aerodynamic grid node coordinates and a preset finite element model specifically includes:

[0122] Obtaining a modal calculation result database file based on the modal calculation result file name;

[0123] Obtaining finite element nodes of the preset finite element model according to the modal calculation result database file, selecting a finite element node closest to each aerodynamic grid node coordinate from the finite element nodes based on the aerodynamic grid node coordinates and obtaining a number;

[0124] The finite element nodes and their numbers of the lifting surface are obtained based on the selected finite element nodes and their numbers.

[0125] The modal calculation result database file is a file that includes the modal analysis results and the modal analysis process. The modal analysis results include the frequency, vibration shape, modal mass, modal vector, etc. of each mode. The modal analysis process includes the number, position, and connection elements of the finite element nodes.

[0126] Exemplarily, the modal calculation result database file can be stored in a default path. As described above, the file name Job-symm-fix.odb can be obtained through the modal calculation result file name and the preset file extension, and the modal calculation result database file can be obtained through the file name Job-symm-fix.odb and the default path.

[0127] The modal calculation result database file provides detailed results of the modal calculation. In this embodiment, by obtaining the modal calculation result database file and obtaining the finite element nodes based on the reusable modal calculation result database file, the positions of the finite element nodes can be obtained more completely, thereby improving the accuracy of the input file obtained.

[0128] Based on any of the above embodiments, obtaining the finite element nodes of the preset finite element model according to the modal calculation result database file specifically includes:

[0129] Importing the modal calculation result database file into finite element software;

[0130] The finite element nodes of the preset finite element model are obtained by calling a setting function through the model data interface of the finite element software.

[0131] For example, the modal calculation result database file can be stored in advance in the working directory of the finite element software Abaqus. The finite element software Abaqus can obtain and import the file Job-symm-fix.odb in the working directory according to the modal calculation result file name Job-symm-fix input by the user.

[0132] The getClosest function can be called through the Abaqus Scripting Interface (ASI), an application programming interface between models and data, to obtain the finite element nodes of the preset finite element model.

[0133] In some embodiments, the aerodynamic mesh node coordinates may be stored in a list, and the getClosest function may be called by ASI of the finite element software Abaqus. Alternatively, the finite element node closest to each aerodynamic mesh node coordinate in the list may be obtained from the file Job-symm-fix.odb according to the list.

[0134] In order to specifically illustrate the function of the input file generation method provided by this embodiment, a specific example is provided below.

[0135] like Figure 3 As shown, a parameter input window (also referred to as a parameter input module) can be popped up in the software interface of the finite element software Abaqus to obtain the flutter calculation parameters input by the user; the flutter calculation parameters include an input file name, a modal calculation result file name, a working condition control parameter, a card parameter, the number of aerodynamic grids in the span direction, the number of aerodynamic grids in the chord direction, the root chord vertex coordinates, the root chord length, the tip chord vertex coordinates, and the tip chord length;

[0136] Based on the input file name "Zaero", an empty text file named Zaero.inp is created in the working directory as the initial file and opened in write mode;

[0137] like Figure 4 As shown, call the preset execution control segment template and fill in the modal calculation result file name "Job-symm-fix" to generate the execution control segment in the Zero.inp file;

[0138] like Figure 5 As shown, calling a preset working condition control section template and filling in the working condition control parameters, generating the working condition control section in the initial file; the working condition control parameters may be Mach number;

[0139] The coordinates of the root chord end point are obtained based on the coordinates of the root chord vertex and the root chord length; a plurality of root chord equally divided points are obtained on the line connecting the root chord vertex and the root chord end point based on the number of aerodynamic grid chord directions; and the coordinates of the aerodynamic grid nodes on the root chord are obtained through the coordinates of the root chord vertex, the coordinates of the root chord end point, and the coordinates of each of the root chord equally divided points.

[0140] The tip chord end point coordinates are obtained based on the tip chord apex coordinates and the tip chord length, a plurality of tip chord equally divided points are obtained on the line between the tip chord apex and the tip chord end point based on the number of aerodynamic grid chord directions, and the aerodynamic grid node coordinates on the tip chord are obtained through the tip chord apex coordinates, the tip chord end point coordinates and the coordinates of each of the tip chord equally divided points;

[0141] Acquire a plurality of internal equally divided points on the line between the aerodynamic grid node on the root chord and the corresponding aerodynamic grid node on the tip chord based on the spanwise number of the aerodynamic grid; and obtain the coordinates of the aerodynamic grid nodes inside the lifting surface based on the coordinates of each of the internal equally divided points;

[0142] Obtaining a modal calculation result database file based on the modal calculation result file name;

[0143] Importing the modal calculation result database file into finite element software; calling a setting function through the model data interface of the finite element software to obtain the finite element nodes of the preset finite element model; selecting the finite element node closest to each aerodynamic grid node coordinate from the finite element nodes based on the aerodynamic grid node coordinates and obtaining a number;

[0144] Obtaining the finite element nodes and their numbers of the lifting surface based on the selected finite element nodes and their numbers;

[0145] like Figure 6As shown, the card parameters may include the upward vector (0.0, 0.0, 100.0) in the modal calculation result database file and the backward vector (100.0, 0.0, 0.0) in the modal calculation result database file. The preset data segment template can be called to generate the CORD2R card content of the data segment in the Zero.inp file.

[0146] like Figure 7 As shown, the card parameters may include a reference span of the lifting surface of 0.6, a reference chord length of the lifting surface of 0.76, and a reference area of the lifting surface of 0.456, and the AEROZ card content of the data segment is generated in the Zero.inp file;

[0147] like Figure 8 As shown, the card parameters may include the number of lifting surface aerodynamic grids in the span direction of 30, the number of lifting surface aerodynamic grids in the chord direction of 30, the coordinates of the lifting surface root chord vertex (4.37, 0.113, 0.113), the lifting surface root chord length of 0.759, the coordinates of the lifting surface tip chord vertex (4.4507, 0.3253, 0.3253), and the lifting surface tip chord length of 0.599. The preset data segment template can be called to generate the CAERO7 card content of the data segment in the Zeero.inp file;

[0148] like Figure 9 As shown, the preset data segment template can be called to generate the PLTAERO card content of the data segment in the Zero.inp file; Figure 10 As shown, the preset data segment template can be called to generate the SPLINE1 card content of the data segment in the Zero.inp file; Figure 11 As shown, the preset data segment template can be called to generate the PANLST3 card content of the data segment in the Zero.inp file;

[0149] like Figure 12 As shown, the finite element node number of the lifting surface can be stored in the nodesID variable, and the preset data segment template is called based on the nodesID variable to generate the first SET1 card content of the data segment in the Zero.inp file; the finite element node numbers in the SET1 card do not need to be sorted;

[0150] like Figure 13 As shown, based on the Mach number of 5.0, the preset data segment template can be called to generate the MKAEROZ card content of the data segment in the Zero.inp file;

[0151] like Figure 14 As shown, the preset data segment template can be called according to the modal order (1, 3) used in the flutter calculation to generate the second SET1 card content of the data segment in the Zero.inp file;

[0152] like Figure 15 As shown, based on the atmospheric density of 1.225 kilograms per cubic meter, the preset data segment template can be called to generate the FLUTTER and FIXMDEN card contents of the data segment in the Zero.inp file;

[0153] like Figure 16 As shown, the preset data segment template can be called according to the modal order (1, 3) used in the flutter calculation to generate the PLTMODE and PLTFLUT card contents of the data segment in the Zero.inp file; so as to generate the data segment in the initial file;

[0154] The input file can be obtained according to the execution control section, the working condition control section, and the data section.

[0155] The input file generating device provided by the present invention is described below. The input file generating device described below and the input file generating method described above can be referenced to each other.

[0156] Figure 17 The present invention provides a schematic diagram of the structure of the input file generating device, the input file includes: an execution control section, a working condition control section and a data section; Figure 17 As shown, the device includes:

[0157] Parameter acquisition module 1701, used to obtain vibration calculation parameters input by the user; the vibration calculation parameters include input file name, execution control parameters, working condition control parameters and data parameters;

[0158] An initial file creation module 1702 is configured to create an initial file based on the input file name;

[0159] The input file generation module 1703 is used to call the preset execution control segment template and fill in the execution control parameters to generate the execution control segment in the initial file; call the preset working condition control segment template and fill in the working condition control parameters to generate the working condition control segment in the initial file; call the preset data segment template and fill in the data parameters to generate the data segment in the initial file to obtain the input file.

[0160] Based on any of the above embodiments, the data parameters include card parameters and lifting surface data parameters; the input file is used to perform flutter calculation on the lifting surface;

[0161] The input file generating device further includes a finite element node number obtaining module, which is used to:

[0162] Calculating aerodynamic grid node coordinates of the lifting surface based on the lifting surface data parameters;

[0163] Obtaining finite element nodes and their numbers of the lifting surface based on the aerodynamic grid node coordinates and a preset finite element model, and storing the finite element node numbers of the lifting surface;

[0164] The input file generation module 1703 is specifically used for:

[0165] The preset data segment template is called and the card parameters and the finite element node number of the lifting surface are filled in.

[0166] Based on any of the above embodiments, the lifting surface data parameters include the spanwise number of aerodynamic grids, the chordwise number of aerodynamic grids, the root chord vertex coordinates, the root chord length, the tip chord vertex coordinates, and the tip chord length;

[0167] The finite element node number acquisition module includes an edge aerodynamic grid node coordinate acquisition unit and an internal aerodynamic grid node coordinate acquisition unit;

[0168] an edge aerodynamic grid node coordinate acquisition unit, configured to obtain the aerodynamic grid node coordinates on the root chord based on the root chord vertex coordinates, the root chord length, and the number of aerodynamic grids in the chord direction; and obtain the aerodynamic grid node coordinates on the tip chord based on the tip chord vertex coordinates, the tip chord length, and the number of aerodynamic grids in the chord direction;

[0169] The internal aerodynamic grid node coordinate acquisition unit is used to obtain the aerodynamic grid node coordinates inside the lifting surface based on the aerodynamic grid node coordinates on the root chord, the corresponding aerodynamic grid node coordinates on the tip chord and the spanwise number of the aerodynamic grids.

[0170] Based on any of the above embodiments, the edge aerodynamic grid node coordinate acquisition unit is specifically used to:

[0171] The coordinates of the root chord end point are obtained based on the coordinates of the root chord vertex and the root chord length; a plurality of root chord equally divided points are obtained on the line connecting the root chord vertex and the root chord end point based on the number of aerodynamic grid chord directions; and the coordinates of the aerodynamic grid nodes on the root chord are obtained through the coordinates of the root chord vertex, the coordinates of the root chord end point, and the coordinates of each of the root chord equally divided points.

[0172] The tip chord end point coordinates are obtained based on the tip chord apex coordinates and the tip chord length, and a plurality of tip chord equally divided points are obtained on the line between the tip chord apex and the tip chord end point based on the number of aerodynamic grid chord directions. The aerodynamic grid node coordinates on the tip chord are obtained through the tip chord apex coordinates, the tip chord end point coordinates and the coordinates of each tip chord equally divided point.

[0173] Based on any of the above embodiments, the internal aerodynamic grid node coordinate acquisition unit is specifically used to:

[0174] Acquire a plurality of internal equally divided points on a line connecting an aerodynamic grid node on the root chord and a corresponding aerodynamic grid node on the tip chord based on the spanwise number of the aerodynamic grid;

[0175] The coordinates of the aerodynamic grid nodes inside the lifting surface are obtained based on the coordinates of each of the internal equally divided points.

[0176] Based on any of the above embodiments, the execution control parameter is a modal calculation result file name;

[0177] Finite element node number acquisition module, specifically used for:

[0178] Obtaining a modal calculation result database file based on the modal calculation result file name;

[0179] Obtaining finite element nodes of the preset finite element model according to the modal calculation result database file, selecting a finite element node closest to each aerodynamic grid node coordinate from the finite element nodes based on the aerodynamic grid node coordinates and obtaining a number;

[0180] The finite element nodes and their numbers of the lifting surface are obtained based on the selected finite element nodes and their numbers.

[0181] Based on any of the above embodiments, the finite element node number acquisition module is specifically used to:

[0182] Importing the modal calculation result database file into finite element software;

[0183] The finite element nodes of the preset finite element model are obtained by calling a setting function through the model data interface of the finite element software.

[0184] Figure 18 The following is a schematic diagram of the structure of an electronic device, such as Figure 18As shown, the electronic device may include: a processor 1810, a communications interface 1820, a memory 1830, and a communications bus 1840. The processor 1810, the communications interface 1820, and the memory 1830 communicate with each other via the communications bus 1840. The processor 1810 may invoke logic instructions in the memory 1830 to execute an input file generation method, wherein the input file includes: an execution control segment, an operating condition control segment, and a data segment. The method includes: obtaining user-input flutter calculation parameters; the flutter calculation parameters include an input file name, execution control parameters, operating condition control parameters, and data parameters; establishing an initial file based on the input file name; invoking a preset execution control segment template and entering the execution control parameters to generate the execution control segment in the initial file; invoking a preset operating condition control segment template and entering the operating condition control parameters to generate the operating condition control segment in the initial file; invoking a preset data segment template and entering the data parameters to generate the data segment in the initial file, thereby obtaining the input file.

[0185] Furthermore, the logic instructions in the aforementioned memory 1830 can be implemented as software functional units and, when sold or used as independent products, can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of the present invention, or the portion that contributes to the prior art, or a portion of the technical solution, can be embodied in the form of a software product. This computer software product, stored in a storage medium, includes instructions for enabling a computer device (which can be a personal computer, server, or network device, etc.) to perform all or part of the steps of the methods described in various embodiments of the present invention. The aforementioned storage medium includes various media capable of storing program code, such as a USB flash drive, a mobile hard drive, a read-only memory (ROM), a random access memory (RAM), a magnetic disk, or an optical disk.

[0186] On the other hand, the present invention also provides a computer program product, which includes a computer program, which can be stored on a non-transitory computer-readable storage medium. When the computer program is executed by a processor, the computer can execute the input file generation method provided by the above methods, wherein the input file includes: an execution control segment, an operating condition control segment and a data segment. The method includes: obtaining the flutter calculation parameters input by the user; the flutter calculation parameters include an input file name, execution control parameters, operating condition control parameters and data parameters; establishing an initial file based on the input file name; calling a preset execution control segment template and filling in the execution control parameters, generating the execution control segment in the initial file; calling a preset operating condition control segment template and filling in the operating condition control parameters, generating the operating condition control segment in the initial file; calling a preset data segment template and filling in the data parameters, generating the data segment in the initial file, and obtaining the input file.

[0187] On the other hand, the present invention also provides a non-transitory computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the input file generation method provided by the above-mentioned methods, wherein the input file includes: an execution control segment, an operating condition control segment and a data segment, and the method includes: obtaining the flutter calculation parameters input by the user; the flutter calculation parameters include an input file name, an execution control parameter, an operating condition control parameter and a data parameter; establishing an initial file based on the input file name; calling a preset execution control segment template and filling in the execution control parameters, generating the execution control segment in the initial file; calling a preset operating condition control segment template and filling in the operating condition control parameters, generating the operating condition control segment in the initial file; calling a preset data segment template and filling in the data parameters, generating the data segment in the initial file, and obtaining the input file.

[0188] The device embodiments described above are merely illustrative. The units described as separate components may or may not be physically separate, and the components shown as units may or may not be physical units, i.e., they may be located in one location or distributed across multiple network units. Some or all of the modules may be selected based on actual needs to achieve the objectives of the present embodiment. Persons of ordinary skill in the art will be able to understand and implement the present invention without inventive effort.

[0189] Through the above description of the embodiments, those skilled in the art will clearly understand that each embodiment can be implemented using software plus a necessary general-purpose hardware platform, or of course, hardware. Based on this understanding, the essence of the above technical solution, or the portion that contributes to the prior art, can be embodied in the form of a software product. This computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, a magnetic disk, or an optical disk, and includes a number of instructions for causing a computer device (such as a personal computer, server, or network device) to execute the methods described in each embodiment or certain portions of the embodiments.

[0190] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the various embodiments of the present invention.

Claims

1. A method for generating an input file, characterized in that: The input file includes: an execution control section, a working condition control section and a data section; the method includes: Obtaining vibration calculation parameters input by the user; the vibration calculation parameters include input file name, execution control parameters, working condition control parameters and data parameters; Creating an initial file based on the input file name; Calling a preset execution control segment template and filling in the execution control parameters to generate the execution control segment in the initial file; calling a preset working condition control segment template and filling in the working condition control parameters to generate the working condition control segment in the initial file; calling a preset data segment template and filling in the data parameters to generate the data segment in the initial file to obtain the input file; The data parameters include card parameters and lifting surface data parameters; the input file is used to perform flutter calculation on the lifting surface; Before calling the preset data segment template and filling in the data parameters, the method further includes: Calculating aerodynamic grid node coordinates of the lifting surface based on the lifting surface data parameters; Obtaining finite element nodes and their numbers of the lifting surface based on the aerodynamic grid node coordinates and a preset finite element model, and storing the finite element node numbers of the lifting surface; Call the preset data segment template and fill in the data parameters, including: The preset data segment template is called and the card parameters and the finite element node number of the lifting surface are filled in.

2. The input file generation method according to claim 1, characterized in that: The lifting surface data parameters include the spanwise number of aerodynamic grids, the chordwise number of aerodynamic grids, the root chord vertex coordinates, the root chord length, the tip chord vertex coordinates and the tip chord length; Calculating the aerodynamic grid node coordinates of the lifting surface based on the lifting surface data parameters specifically includes: Obtaining the aerodynamic grid node coordinates on the root chord based on the root chord vertex coordinates, the root chord length, and the number of aerodynamic grids in the chord direction; obtaining the aerodynamic grid node coordinates on the tip chord based on the tip chord vertex coordinates, the tip chord length, and the number of aerodynamic grids in the chord direction; The aerodynamic grid node coordinates inside the lifting surface are obtained based on the aerodynamic grid node coordinates on the root chord, the corresponding aerodynamic grid node coordinates on the tip chord, and the spanwise number of the aerodynamic grids.

3. The input file generation method according to claim 2, characterized in that: Obtaining the aerodynamic grid node coordinates on the root chord based on the root chord vertex coordinates, the root chord length, and the number of aerodynamic grids in the chord direction; and obtaining the aerodynamic grid node coordinates on the tip chord based on the tip chord vertex coordinates, the tip chord length, and the number of aerodynamic grids in the chord direction, specifically includes: The coordinates of the root chord end point are obtained based on the coordinates of the root chord vertex and the root chord length; a plurality of root chord equally divided points are obtained on the line connecting the root chord vertex and the root chord end point based on the number of aerodynamic grid chord directions; and the coordinates of the aerodynamic grid nodes on the root chord are obtained through the coordinates of the root chord vertex, the coordinates of the root chord end point, and the coordinates of each of the root chord equally divided points. The tip chord end point coordinates are obtained based on the tip chord apex coordinates and the tip chord length, and a plurality of tip chord equally divided points are obtained on the line between the tip chord apex and the tip chord end point based on the number of aerodynamic grid chord directions. The aerodynamic grid node coordinates on the tip chord are obtained through the tip chord apex coordinates, the tip chord end point coordinates and the coordinates of each tip chord equally divided point.

4. The input file generation method according to claim 2, characterized in that: Obtaining the aerodynamic grid node coordinates inside the lifting surface based on the aerodynamic grid node coordinates on the root chord, the corresponding aerodynamic grid node coordinates on the tip chord, and the spanwise number of the aerodynamic grids specifically includes: Acquire a plurality of internal equally divided points on a line connecting an aerodynamic grid node on the root chord and a corresponding aerodynamic grid node on the tip chord based on the spanwise number of the aerodynamic grid; The coordinates of the aerodynamic grid nodes inside the lifting surface are obtained based on the coordinates of each of the internal equally divided points.

5. The input file generation method according to claim 1, characterized in that: The execution control parameter is the modal calculation result file name; Obtaining the finite element nodes and their numbers of the lifting surface based on the aerodynamic grid node coordinates and a preset finite element model specifically includes: Obtaining a modal calculation result database file based on the modal calculation result file name; Obtaining finite element nodes of the preset finite element model according to the modal calculation result database file, selecting a finite element node closest to each aerodynamic grid node coordinate from the finite element nodes based on the aerodynamic grid node coordinates and obtaining a number; The finite element nodes and their numbers of the lifting surface are obtained based on the selected finite element nodes and their numbers.

6. The input file generation method according to claim 5, characterized in that: Obtaining the finite element nodes of the preset finite element model according to the modal calculation result database file specifically includes: Importing the modal calculation result database file into finite element software; The finite element nodes of the preset finite element model are obtained by calling a setting function through the model data interface of the finite element software.

7. An input file generating device, characterized in that: The input file includes: an execution control section, a working condition control section and a data section; the device includes: A parameter acquisition module is used to obtain vibration calculation parameters input by the user; the vibration calculation parameters include input file name, execution control parameters, working condition control parameters and data parameters; An initial file creation module, configured to create an initial file based on the input file name; An input file generation module is configured to call a preset execution control segment template and fill in the execution control parameters to generate the execution control segment in the initial file; call a preset working condition control segment template and fill in the working condition control parameters to generate the working condition control segment in the initial file; call a preset data segment template and fill in the data parameters to generate the data segment in the initial file to obtain the input file; The data parameters include card parameters and lifting surface data parameters; the input file is used to perform flutter calculation on the lifting surface; The input file generating device further includes a finite element node number obtaining module, which is used to: Calculating aerodynamic grid node coordinates of the lifting surface based on the lifting surface data parameters; Obtaining finite element nodes and their numbers of the lifting surface based on the aerodynamic grid node coordinates and a preset finite element model, and storing the finite element node numbers of the lifting surface; The input file generation module is specifically used for: The preset data segment template is called and the card parameters and the finite element node number of the lifting surface are filled in.

8. An electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein: When the processor executes the computer program, the input file generation method according to any one of claims 1 to 6 is implemented.

9. A non-transitory computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the input file generation method according to any one of claims 1 to 6 is implemented.

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