Input file generation method and device and electronic equipment thereof

Abstract

The invention provides an input file generation method and device and electronic equipment thereof, and relates to the technical field of simulation. The input file comprises an execution control section, a working condition control section and a data section; the method comprises the following steps: acquiring flutter calculation parameters input by a user; the flutter calculation parameters comprise an input file name, an execution control parameter, a working condition control parameter and a data parameter; establishing an initial file based on the input file name; calling a preset execution control section template, filling the execution control parameters, and generating the execution control section in the initial file; calling a preset working condition control section template, filling the working condition control parameters, and generating a working condition control section in the initial file; and calling a preset data segment template, filling the preset data segment template with the data parameters, and generating the data segments in the initial file to obtain the input file, so that the accuracy of the obtained input file can be improved.

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 of 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, etc. The input files can usually reach hundreds of lines. Some simulation software does not have a pre-processing interface and cannot provide graphical guidance to users. In addition, precise syntax and format must be followed when writing input files. Therefore, the input files of simulation software without a pre-processing interface are generally written manually by professional technicians. When the content of the input file is relatively large, especially when part of the content in the input file needs to repeatedly query tables, pre-established models, etc., 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 device thereof.

[0004] The present invention provides a method for generating an input file, wherein the input file comprises: an execution control section, a working condition control section and a data section; the method comprises: Obtaining vibration calculation parameters input by a 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; Call the preset execution control segment template and fill in the execution control parameters, and 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, and generate the working condition control segment in the initial file; call the preset data segment template and fill in the data parameters, and generate the data segment in the initial file to obtain the input file.

[0005] According to an input file generation method 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; 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; Acquire the finite element nodes and their numbers of the lifting surface based on the aerodynamic grid node coordinates and a preset finite element model, and store the finite element node numbers of the lifting surface; Calling the preset data segment template and filling in the data parameters, specifically 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.

[0006] 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; Calculating the aerodynamic grid node coordinates of the lifting surface based on the lifting surface data parameters specifically includes: Based on the root chord vertex coordinates, the root chord length and the number of aerodynamic grids in the chord direction, the aerodynamic grid node coordinates on the root chord are obtained; 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 on the tip chord are obtained; 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.

[0007] 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; 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 including: The coordinates of the end point of the root chord are obtained based on the coordinates of the root chord vertex and the length of the root chord, and a plurality of root chord equally divided points are obtained on the line between the root chord vertex and the end point of the root chord 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 end point of the root chord 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 of the tip chord equally divided points.

[0008] 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: Based on the spanwise number of the aerodynamic grid, a plurality of internal equally divided points are obtained on the line between the aerodynamic grid nodes on the root chord and the corresponding aerodynamic grid nodes on the tip chord; 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.

[0009] According to an input file generation method provided by the present invention, the execution control parameter is a modal calculation result file name; Acquiring the finite element nodes and their numbers of the lifting surface based on the aerodynamic grid node coordinates and the preset finite element model specifically includes: Acquiring a modal calculation result database file based on the modal calculation result file name; Obtaining the finite element nodes of the preset finite element model according to the modal calculation result database file, selecting the finite element nodes closest to each of the aerodynamic mesh node coordinates from the finite element nodes based on the aerodynamic mesh node coordinates and obtaining the numbers; The finite element nodes and their numbers of the lifting surface are obtained based on the selected finite element nodes and their numbers.

[0010] 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: 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.

[0011] The present invention also provides an input file generating device, wherein the input file comprises: an execution control section, a working condition control section and a data section; the device comprises: A parameter acquisition module, used to acquire the 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, used to create an initial file based on the input file name; An input file generation module is used to call a preset execution control segment template and fill in the execution control parameters, so as to generate the execution control segment in the initial file; call a preset operating condition control segment template and fill in the operating condition control parameters, so as to generate the operating condition control segment in the initial file; call a preset data segment template and fill in the data parameters, so as to generate the data segment in the initial file, so as to obtain the input file.

[0012] 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 of the input file generation methods described above is implemented.

[0013] The present invention also provides a non-transitory computer-readable storage medium on which a computer program is stored. When the computer program is executed by a processor, the input file generation method described in any one of the above is implemented.

[0014] 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 obtain the input file based on the initial file in combination with the vibration calculation parameters input by the user, which can improve the accuracy of the obtained input file. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to more clearly illustrate the technical solutions in the present invention or the prior art, the following briefly introduces 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 creative work.

[0016] Figure 1 It is a flow chart of the input file generating method provided by the present invention.

[0017] Figure 2 It is one of the schematic diagrams of the input file of the input file generating method provided by the present invention.

[0018] Figure 3 This is the second schematic diagram of the input file of the input file generating method provided by the present invention.

[0019] Figure 4 This is the third schematic diagram of the input file of the input file generating method provided by the present invention.

[0020] Figure 5 This is the fourth schematic diagram of the input file of the input file generating method provided by the present invention.

[0021] Figure 6 This is the fifth schematic diagram of the input file of the input file generating method provided by the present invention.

[0022] Figure 7 This is the sixth schematic diagram of the input file of the input file generating method provided by the present invention.

[0023] Figure 8 This is the seventh schematic diagram of the input file of the input file generating method provided by the present invention.

[0024] Fig. 9 This is the eighth schematic diagram of the input file of the input file generating method provided by the present invention.

[0025] Fig.10 This is the ninth schematic diagram of the input file of the input file generating method provided by the present invention.

[0026] Fig.11 This is the tenth schematic diagram of the input file of the input file generating method provided by the present invention.

[0027] Fig.12 This is the eleventh schematic diagram of the input file of the input file generating method provided by the present invention.

[0028] Fig.13 This is the twelfth schematic diagram of the input file of the input file generating method provided by the present invention.

[0029] Fig.14 This is the thirteenth schematic diagram of the input file of the input file generating method provided by the present invention.

[0030] Fig.15 This is the fourteenth schematic diagram of the input file of the input file generating method provided by the present invention.

[0031] Fig.16 This is the fifteenth schematic diagram of the input file of the input file generating method provided by the present invention.

[0032] Fig.17 It is a structural schematic diagram of the input file generating device provided by the present invention.

[0033] Fig.18 It is a structural schematic diagram of the electronic device provided by the present invention. DETAILED DESCRIPTION

[0034] In order to make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be clearly and completely described below in conjunction with the drawings of the present invention. Obviously, the described embodiments are 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 creative work are within the scope of protection of the present invention.

[0035] Combine the following Figure 1-Figure 18 The invention describes an input file generating method, device and electronic device thereof.

[0036] Figure 1 It is a flow chart of the input file generation method provided by the present invention, wherein the input file comprises: an execution control section, a working condition control section and a data section.

[0037] The input file is the input file of the simulation software. The simulation software can perform flutter calculation based on the input file, or the input file can provide the necessary information and parameters for the simulation software to perform flutter calculation. The input file can be a text file or a JSON file. The text file can be a text file with the suffix .inp.

[0038] The execution control section generally indicates how the simulation software reads and processes the modal calculation results to perform flutter calculations. For example, the execution control section may specify how the simulation software reads the modal calculation result file, sets the initial conditions for the simulation, etc. The modal calculation result file is a result file generated after the modal calculation of the finite element model, including modal calculation results such as natural frequency and modal shape.

[0039] In order 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 program that generates the modal calculation result file.

[0040] The operating condition control section generally indicates the operating conditions and analysis parameters used by the simulation software for flutter calculations, and the data section generally indicates the specific data used by the simulation software for flutter calculations.

[0041] like Figure 1 As shown, the method includes: Step 101, obtaining the flutter calculation parameters input by the user; the flutter calculation parameters include input file name, execution control parameters, working condition control parameters and data parameters.

[0042] Exemplarily, a parameter input window may pop up to the user on the display interface, the parameter input window may include a parameter input template, and the user may input the vibration calculation parameters in the parameter input window based on the parameter input template.

[0043] Step 102: Create an initial file based on the input file name.

[0044] The input file name refers to the file name of the input file. The initial file is a container for storing the flutter calculation parameters, specific data and analysis parameters used for flutter calculation. The analysis parameters are parameters that guide the simulation software to process the flutter calculation parameters and specific data, etc. For example, parameters that specify the analysis type, boundary condition parameters, etc.

[0045] 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.

[0046] Step 103, call the preset execution control segment template and fill in the execution control parameters, 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, generate the working condition control segment in the initial file; call the preset data segment template and fill in the data parameters, generate the data segment in the initial file, and obtain the input file.

[0047] The preset execution control segment template includes necessary structures, 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 refers to the specific execution control parameters filled in. Exemplarily, 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", and the preset execution control segment template after assignment is written into the initial file through the preset function to generate the execution control segment.

[0048] The composition, application and technical effects of the preset operating condition control segment template and the preset data segment template are basically the same as the composition, application and technical effects of the preset execution control segment template, and will not be repeated here.

[0049] It can be understood that the necessary structure, elements and filling information in the preset execution control segment template, the necessary structure, elements and filling information in the preset operating condition control segment template, and the necessary structure, elements and filling information in the preset data segment template are generally different. The specific necessary structure, necessary elements and filling information can be determined by professionals and pre-compiled into corresponding templates, and the present invention does not further limit this.

[0050] 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, and obtains the input file based on the initial file in combination with the flutter calculation parameters input by the user, thereby improving the accuracy of the obtained input file.

[0051] 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.

[0052] Based on the above embodiment, the data parameters include card parameters and lifting surface data parameters; the input file is used to perform flutter calculation on the lifting surface.

[0053] The card is the basic unit of the data segment. The data segment includes multiple cards, such as 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.

[0054] The card includes a card name and card data, and the card data can be one line or multiple lines. Each line of card data can include multiple card data, and in some embodiments, each card data does not exceed a preset character length, for example, each card data does not exceed 8 characters.

[0055] The preset data segment template includes multiple card templates. The card data of a card includes a card template and card filling data. The card filling data is the specific card parameters filled in. For example, the card name of the AEROZ card is AEROZ. The card template of the AEROZ card includes "FMMUNIT: N / , FMLUNIT: M, REFC: modal_pattern". The card parameters for input can be assigned to the variable modal_pattern to fill the card parameters into the card template to obtain "FMMUNIT: N / , FMLUNIT: M, REFC: card parameters". Only part of the AEROZ card data is shown in this embodiment, which does not represent the complete AEROZ card data. The assigned card template can be written into the initial file through the preset function to generate part of the AEROZ card data in the data segment.

[0056] The input file is used to transfer to the simulation software for flutter calculation. The flutter calculation results are used to evaluate the dynamic stability and structural safety of the lifting surface under high-speed flight conditions. When the simulation software performs flutter calculations, it is generally necessary 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, the modal calculation of the lifting surface is first performed, 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 position where the aerodynamic force is applied on the lifting surface and obtaining the dynamic characteristics of the structure.

[0057] The SET1 card in the data segment includes the finite element node number. At present, when adding the finite element node number to the SET1 card in the data segment, the technician generally uses the mouse to click the finite element model to query the finite element node number, and writes the finite element node number one by one into the input file, which takes a lot of time. In addition, when there are many finite element node numbers, the probability of errors in the finite element node numbers added to the input file is very high.

[0058] 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: Calculating aerodynamic grid node coordinates of the lifting surface based on the lifting surface data parameters; Acquire the finite element nodes and their numbers of the lifting surface based on the aerodynamic grid node coordinates and a preset finite element model, and store the finite element node numbers of the lifting surface; Calling the preset data segment template and filling in the data parameters, specifically 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.

[0059] A lifting surface is a surface used to generate lift, such as the wing of an airplane.

[0060] The lifting surface data parameters are the parameters that describe the structural characteristics of the lifting surface. The aerodynamic grid nodes are the intersections of the aerodynamic grids in the lifting surface. The aerodynamic grids divide the lifting surface into multiple small areas for the convenience of aerodynamic analysis. The aerodynamic grid nodes can approximate the position where the aerodynamic force is applied on the lifting surface.

[0061] Exemplarily, after the aerodynamic grid node coordinates of the lifting surface are calculated, each aerodynamic grid node coordinate can be transferred to the coordinate system of the finite element node according to the preset conversion matrix, and then the distance between the aerodynamic grid node and the finite element node is obtained according to the aerodynamic grid node coordinates and the finite element node coordinates in the preset finite element model, so as to obtain the finite element node closest to each aerodynamic grid node and its number, and save the finite element node number of the lifting surface to the variable nodesID, which 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 numbers are filled into the card template, and the assigned card template is written into the card in the generated data segment in the initial file.

[0062] In this embodiment, the aerodynamic grid node coordinates of the lifting surface are calculated using the lift 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 input file obtained.

[0063] 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. The root chord vertex coordinates and tip chord vertex coordinates of the lift 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 lift surface, the z-axis points upward, and the y-axis is determined by the right-hand system. Among them, the chord direction of the lift surface points to the direction of the airflow, and the upward direction refers to the direction of the pilot's head. The lift surface must be located in the +y space of the aerodynamic coordinate system, or in other words, the lift surface must be located in the positive direction of the y-axis of the aerodynamic coordinate system, that is, on the right hand side of the pilot.

[0064] 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-wise direction, the y-axis is the span-wise direction, the number of aerodynamic grids in the span-wise direction is 4, and the number of aerodynamic grids in the chord-wise direction is 4.

[0065] In one embodiment, calculating the aerodynamic grid node coordinates of the lifting surface based on the lifting surface data parameters specifically includes: Based on the root chord vertex coordinates, the root chord length and the number of aerodynamic grids in the chord direction, the aerodynamic grid node coordinates on the root chord are obtained; 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 on the tip chord are obtained; 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.

[0066] The aerodynamic mesh nodes inside the lifting surface include all aerodynamic mesh nodes except the aerodynamic mesh nodes on the root chord and the aerodynamic mesh nodes on the tip chord on the lifting surface. For example, the aerodynamic mesh nodes on the line between the root chord vertex and the tip chord vertex belong to the aerodynamic mesh nodes inside the lifting surface.

[0067] Exemplarily, 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 portion of the lift surface can be obtained based on the aerodynamic grid nodes on the root chord closest to the root chord apex, the aerodynamic grid nodes on the tip chord closest to the tip chord apex, and the spanwise number of aerodynamic grids, and so on until the aerodynamic grid node coordinates inside all of the lift surfaces are obtained.

[0068] 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.

[0069] Based on any of the above embodiments, 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 specifically includes: The coordinates of the end point of the root chord are obtained based on the coordinates of the root chord vertex and the length of the root chord, and a plurality of root chord equally divided points are obtained on the line between the root chord vertex and the end point of the root chord 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 end point of the root chord 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 of the tip chord equally divided points.

[0070] For example, the x-axis of the aerodynamic coordinate system can be parallel to the root chord direction (chord direction) of the lift surface, the root chord vertex coordinates are (4.37, 0.113, 0.113), and the root chord length is 0.759m, so the root chord end point coordinates are (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 grids 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: The x-axis of the aerodynamic coordinate system can be parallel to the tip chord direction (chord 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 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 grids in the chord direction is 30, and there will be 31 aerodynamic grid nodes on the tip chord. The coordinate x of the nth point starting from the vertex is: 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: Based on the spanwise number of the aerodynamic grid, a plurality of internal equally divided points are obtained on the line between the aerodynamic grid nodes on the root chord and the corresponding aerodynamic grid nodes on the tip chord; 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.

[0071] Exemplarily, a corresponding number of internal equally divided points may 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 grids.

[0072] 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 of 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 of n=2, and its coordinates are (4.4707, 0.3253, 0.3253). 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 The remaining internal equal division points can be obtained by repeating the above steps of obtaining the internal equal division points.

[0073] Based on any of the above embodiments, the execution control parameter is a modal calculation result file name.

[0074] 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.

[0075] 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.

[0076] Exemplarily, the modal calculation result file name input 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 filling in the execution control parameters, the file extension .unv is set in the position corresponding to the modal calculation result file name in the preset execution control section template, and the file Job-symm-fix and the file extension .unv are combined to use the file Job-symm-fix.unv. When the finite element nodes and their numbers of the lift surface are obtained based on the aerodynamic grid node coordinates and the preset finite element model, the file Job-symm-fix.odb can also be used by the preset template or splicing processing, etc., through the file name Job-symm-fix and the file extension .odb.

[0077] 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, thereby 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 obtained.

[0078] Acquiring the finite element nodes and their numbers of the lifting surface based on the aerodynamic grid node coordinates and the preset finite element model specifically includes: Acquiring a modal calculation result database file based on the modal calculation result file name; Obtaining the finite element nodes of the preset finite element model according to the modal calculation result database file, selecting the finite element nodes closest to each of the aerodynamic mesh node coordinates from the finite element nodes based on the aerodynamic mesh node coordinates and obtaining the numbers; The finite element nodes and their numbers of the lifting surface are obtained based on the selected finite element nodes and their numbers.

[0079] 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, connection elements, etc. of the finite element nodes.

[0080] 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.

[0081] 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 according to 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.

[0082] 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: 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.

[0083] Exemplarily, the modal calculation result database file may be stored in advance in the working directory of the finite element software Abaqus, and the finite element software Abaqus may 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.

[0084] The getClosest function can be called through the ASI (Abaqus Scripting Interface) of the finite element software Abaqus to obtain the finite element nodes of the preset finite element model.

[0085] 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, or the finite element node closest to each aerodynamic mesh node coordinate in the list may be obtained in the file Job-symm-fix.odb according to the list.

[0086] In order to specifically illustrate the function of the input file generation method provided by this embodiment, a specific example is provided below.

[0087] 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; Based on the input file name "Zaero", an empty text file named Zaero.inp is created in the working directory as an initial file and opened in write mode; like Figure 4As shown, the preset execution control segment template is called and the modal calculation result file name "Job-symm-fix" is filled in to generate the execution control segment in the Zeero.inp file; like Figure 5 As shown, calling a preset operating condition control section template and filling in the operating condition control parameter, generating the operating condition control section in the initial file; the operating condition control parameter may be a Mach number; The coordinates of the end point of the root chord are obtained based on the coordinates of the root chord vertex and the length of the root chord, and a plurality of root chord equally divided points are obtained on the line between the root chord vertex and the end point of the root chord 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 end point of the root chord 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, 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; Based on the spanwise number of the aerodynamic grid, a plurality of internal equally divided points are obtained 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 coordinates of each of the internal equally divided points, the coordinates of the aerodynamic grid nodes inside the lifting surface are obtained; Acquiring a modal calculation result database file based on the modal calculation result file name; Importing the modal calculation result database file into the finite element software; calling the 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 of the aerodynamic grid node coordinates from the finite element nodes based on the aerodynamic grid node coordinates and obtaining the number; Obtaining the finite element nodes and their numbers of the lifting surface based on the selected finite element nodes and their numbers; like Figure 6 As 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 may be called to generate the CORD2R card content of the data segment in the Zeroro.inp file. 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; like Figure 8As shown, the card parameters may include the number of lifting surface aerodynamic grids in span direction 30, the number of lifting surface aerodynamic grids in chord direction 30, the coordinates of the lifting surface root chord vertex (4.37, 0.113, 0.113), the lifting surface root chord length 0.759, the coordinates of the lifting surface tip chord vertex (4.4507, 0.3253, 0.3253), and the lifting surface tip chord length 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; like Fig. 9 As shown, the preset data segment template can be called to generate the PLTAERO card content of the data segment in the Zeroro.inp file; Fig.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; Fig.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; like Fig.12 As shown, the finite element node number of the lift 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 Zeero.inp file; wherein the finite element node numbers in the SET1 card do not need to be sorted; like Fig.13 As shown, according to 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; like Fig.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; like Fig.15 As shown, the preset data segment template can be called according to the atmospheric density of 1.225 kilograms per cubic meter to generate the FLUTTER and FIXMDEN card contents of the data segment in the Zero.inp file; like Fig.16 As shown, the preset data segment template can be called according to the modal order (1, 3) used for 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; The input file can be obtained according to the execution control section, the working condition control section and the data section.

[0088] 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 referred to each other.

[0089] Fig.17 is a schematic diagram of the structure of the input file generating device provided by the present invention, wherein the input file comprises: an execution control section, a working condition control section and a data section; Fig.17 As shown, the device comprises: The parameter acquisition module 1701 is used to acquire the 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 1702, used to create an initial file based on the input file name; 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.

[0090] 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; The input file generating device further comprises a finite element node number obtaining module, which is used for: Calculating aerodynamic grid node coordinates of the lifting surface based on the lifting surface data parameters; Acquire the finite element nodes and their numbers of the lifting surface based on the aerodynamic grid node coordinates and a preset finite element model, and store the finite element node numbers of the lifting surface; The input file generation module 1703 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.

[0091] 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; 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; An edge aerodynamic grid node coordinate acquisition unit is used 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 to 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; 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.

[0092] Based on any of the above embodiments, the edge aerodynamic grid node coordinate acquisition unit is specifically used for: The coordinates of the end point of the root chord are obtained based on the coordinates of the root chord vertex and the length of the root chord, and a plurality of root chord equally divided points are obtained on the line between the root chord vertex and the end point of the root chord 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 end point of the root chord 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 of the tip chord equally divided points.

[0093] Based on any of the above embodiments, the internal aerodynamic grid node coordinate acquisition unit is specifically used for: Based on the spanwise number of the aerodynamic grid, a plurality of internal equally divided points are obtained on the line between the aerodynamic grid nodes on the root chord and the corresponding aerodynamic grid nodes on the tip chord; 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.

[0094] Based on any of the above embodiments, the execution control parameter is a modal calculation result file name; Finite element node number acquisition module, specifically used for: Acquiring a modal calculation result database file based on the modal calculation result file name; Obtaining the finite element nodes of the preset finite element model according to the modal calculation result database file, selecting the finite element nodes closest to each of the aerodynamic mesh node coordinates from the finite element nodes based on the aerodynamic mesh node coordinates and obtaining the numbers; The finite element nodes and their numbers of the lifting surface are obtained based on the selected finite element nodes and their numbers.

[0095] Based on any of the above embodiments, the finite element node number acquisition module is specifically used for: 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.

[0096] Fig.18 An example of a structural diagram of an electronic device is shown in FIG. Fig.18 As shown, the electronic device may include: a processor 1810, a communication interface 1820, a memory 1830 and a communication bus 1840, wherein the processor 1810, the communication interface 1820 and the memory 1830 communicate with each other through the communication bus 1840. The processor 1810 may call the logic instructions in the memory 1830 to execute the input file generation method, wherein the input file includes: an execution control segment, a working 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 the input file name, the execution control parameters, the working condition control parameters and the 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 working condition control segment template and filling in the working condition control parameters, generating the working 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.

[0097] In addition, the logic instructions in the above-mentioned memory 1830 can be implemented in the form of a software functional unit and can be stored in a computer-readable storage medium when it is sold or used as an independent product. Based on such an understanding, the technical solution of the present invention, in essence, or the part that contributes to the prior art or the part of the technical solution, can be embodied in the form of a software product, and the computer software product is stored in a storage medium, including a number of instructions for a computer device (which can be a personal computer, a server, or a network device, etc.) to perform all or part of the steps of the method described in each embodiment of the present invention. The aforementioned storage medium includes: U disk, mobile hard disk, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access Memory), disk or optical disk, etc. Various media that can store program codes.

[0098] 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, 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, and 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, and generating the operating condition control segment in the initial file; calling a preset data segment template and filling in the data parameters, and generating the data segment in the initial file to obtain the input file.

[0099] On the other hand, the present invention also provides a non-transitory computer-readable storage medium having a computer program stored thereon. When the computer program is executed by a processor, it is implemented to execute 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. 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.

[0100] The device embodiments described above are merely illustrative, wherein the units described as separate components may or may not be physically separated, and the components displayed as units may or may not be physical units, that is, they may be located in one place, or they may be distributed on multiple network units. Some or all of the modules may be selected according to actual needs to achieve the purpose of the scheme of this embodiment. Ordinary technicians in this field can understand and implement it without paying creative labor.

[0101] Through the description of the above implementation methods, those skilled in the art can clearly understand that each implementation method can be implemented by means of software plus a necessary general hardware platform, and of course, can also be implemented by hardware. Based on this understanding, the above technical solution is essentially or the part that contributes to the prior art can be embodied in the form of a software product, and the computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, a disk, an optical disk, etc., including a number of instructions for a computer device (which can be a personal computer, a server, or a network device, etc.) to execute the methods described in each embodiment or some parts of the embodiments.

[0102] 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 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 a 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; Call the preset execution control segment template and fill in the execution control parameters, and 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, and generate the working condition control segment in the initial file; call the preset data segment template and fill in the data parameters, and generate the data segment in the initial file to obtain the input file.

2. The input file generation method according to claim 1, characterized in that: 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; Acquire the finite element nodes and their numbers of the lifting surface based on the aerodynamic grid node coordinates and a preset finite element model, and store the finite element node numbers of the lifting surface; Calling the preset data segment template and filling in the data parameters, specifically 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.

3. The input file generation method according to claim 2, 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: Based on the root chord vertex coordinates, the root chord length and the number of aerodynamic grids in the chord direction, the aerodynamic grid node coordinates on the root chord are obtained; 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 on the tip chord are obtained; 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.

4. The input file generation method according to claim 3, characterized in that: The method further comprises: obtaining the coordinates of the aerodynamic grid nodes on the root chord based on the coordinates of the root chord vertex, the length of the root chord and the number of the aerodynamic grids in the chord direction; and obtaining the coordinates of the aerodynamic grid nodes on the tip chord based on the coordinates of the tip chord vertex, the length of the tip chord and the number of the aerodynamic grids in the chord direction. The coordinates of the end point of the root chord are obtained based on the coordinates of the root chord vertex and the length of the root chord, and a plurality of root chord equally divided points are obtained on the line between the root chord vertex and the end point of the root chord 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 end point of the root chord 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 of the tip chord equally divided points.

5. The input file generation method according to claim 3, characterized in that: 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 including: Acquire a plurality of internal equally divided points on the line between the aerodynamic grid nodes on the root chord and the corresponding aerodynamic grid nodes 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.

6. The input file generation method according to claim 2, characterized in that: The execution control parameter is the modal calculation result file name; Acquiring the finite element nodes and their numbers of the lifting surface based on the aerodynamic grid node coordinates and the preset finite element model specifically includes: Acquiring a modal calculation result database file based on the modal calculation result file name; Obtaining the finite element nodes of the preset finite element model according to the modal calculation result database file, selecting the finite element nodes closest to each of the aerodynamic mesh node coordinates from the finite element nodes based on the aerodynamic mesh node coordinates and obtaining the numbers; The finite element nodes and their numbers of the lifting surface are obtained based on the selected finite element nodes and their numbers.

7. The input file generation method according to claim 6, characterized in that: Acquiring 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.

8. 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, used to acquire the 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, used to create an initial file based on the input file name; An input file generation module is used to call a preset execution control segment template and fill in the execution control parameters, so as to generate the execution control segment in the initial file; call a preset operating condition control segment template and fill in the operating condition control parameters, so as to generate the operating condition control segment in the initial file; call a preset data segment template and fill in the data parameters, so as to generate the data segment in the initial file, so as to obtain the input file.

9. 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 7 is implemented.

10. 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 7 is implemented.

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