Full-machine finite element automatic analysis method, system and equipment and storage medium

Abstract

The invention relates to a full-aircraft finite element automatic analysis method, system and device and a storage medium, and the method comprises the steps: carrying out the mesh generation of an aircraft model, adding material attributes, boundary conditions and loading nodes, and generating a mesh model file according to the aircraft model after mesh generation, the material attributes, the boundary conditions and the loading nodes; obtaining a working condition load file, reading a working condition load from the working condition load file, writing the working condition load into the grid model file, and generating a working condition calculation file; and submitting the working condition calculation file to finite element analysis calculation, outputting a calculation result file, and reading and outputting a reliability analysis report of the aircraft model according to the calculation result file, so that the finite element analysis efficiency is improved.

Description

Technical Field

[0001] The present application relates to the field of finite element analysis, and in particular to a method, system, computer equipment and storage medium for automatic finite element analysis of a whole machine. Background Art

[0002] With the rapid development of aircraft, they have been widely used in aerial photography, transportation, disaster relief and other fields, and the safety of aircraft is a criterion for evaluating the quality of aircraft. Finite element analysis uses mathematical approximation methods to simulate real physical systems, and uses simple and interactive elements to achieve the use of a finite number of unknown quantities to approximate the real system with infinite unknown quantities. Therefore, in order to better evaluate the safety of aircraft, finite element analysis for aircraft has begun to appear.

[0003] However, there are currently many load conditions for the finite element analysis of the entire aircraft. Each load condition requires pre-processing, submission of analysis and calculation, processing of finite element calculation results, and preparation of strength analysis reports. In addition, these processes rely on manual processing, resulting in a time-consuming calculation process and extremely low finite element analysis efficiency. Summary of the invention

[0004] Based on this, the present application provides a method, system, device and storage medium for automatic finite element analysis of the entire machine to improve the efficiency of finite element analysis.

[0005] On the one hand, a method for automatic finite element analysis of a whole machine is provided, the method comprising:

[0006] Meshing the aircraft model and adding material properties, boundary conditions and loading nodes, and generating a mesh model file according to the meshed aircraft model and the material properties, boundary conditions and loading nodes;

[0007] Obtaining a working condition load file and reading the working condition load from the working condition load file, so as to write the working condition load into the grid model file and generate a working condition calculation file;

[0008] The working condition calculation file is submitted to finite element analysis and calculation and a calculation result file is output, and a reliability analysis report of the aircraft model is read and output according to the calculation result file.

[0009] In one embodiment, the meshing of the aircraft model and adding material properties, boundary conditions and loading nodes, and generating a mesh model file according to the meshed aircraft model and the material properties, boundary conditions and loading nodes, include:

[0010] Meshing the aircraft model using Hypermesh software and adding material properties, boundary conditions and loading nodes to the meshed aircraft model using Hypermesh software;

[0011] The mesh model file is generated by Hypermesh software, and the mesh model file includes mesh information of the aircraft model after meshing, and material properties, boundary conditions and loading nodes corresponding to the aircraft model.

[0012] In one embodiment, the working condition load file includes a plurality of working condition load worksheets, each of which corresponds to a working condition load. Before obtaining the working condition load, the following steps are also included:

[0013] Determining several working loads of the aircraft model according to actual application scenarios of the aircraft model;

[0014] Each of the working condition loads is written into a corresponding working condition load work table to form the working condition load file and the working condition load file is stored in a preset path.

[0015] In one embodiment, the obtaining of the working condition load file and reading the working condition load from the working condition load file to write the working condition load into the grid model file and generate a working condition calculation file includes:

[0016] Obtaining the working condition load file from the preset path through Python software, and reading a plurality of working condition load worksheets from the working condition load file to obtain each working condition load;

[0017] The various working condition loads are written into the grid model file through Python software and the working condition calculation files corresponding to the various working condition loads are generated according to a preset format.

[0018] In one embodiment, each of the working condition loads corresponds to a working condition calculation file, and submitting the working condition calculation file to finite element analysis and outputting the calculation result file includes:

[0019] Selecting one of the working condition calculation files as a target calculation file, calling Optistruct software through Python software to perform finite element analysis calculation on the target calculation file, and monitoring the finite element analysis process of the target calculation file through Python software;

[0020] In response to obtaining a calculation end mark of the target calculation file, outputting a calculation result file of the target calculation file, and selecting a next working condition calculation file as the target calculation file to perform finite element analysis calculation;

[0021] Output the calculation result files corresponding to all working condition calculation files.

[0022] In one embodiment, the reading and outputting the reliability analysis report of the aircraft model according to the calculation result file includes:

[0023] Reading the calculation result file to obtain safety margin parameter information, and calculating a safety margin value according to the safety margin parameter information;

[0024] Calling the Hypermesh software through Python software to output a stress cloud map of the aircraft model, and outputting a reliability analysis report of the aircraft model through the Python software according to the safety margin value and the stress cloud map;

[0025] The reliability analysis report is sent to the mobile phone by calling the communication software on the computer through Python software.

[0026] In one embodiment, before meshing the aircraft model, the method further includes:

[0027] Selecting several typical working conditions, performing manual finite element analysis on the aircraft model under the typical working conditions and outputting manual analysis results;

[0028] Performing automatic finite element analysis based on Python software on the aircraft model under the typical working conditions and outputting automatic analysis results;

[0029] The manual analysis result is compared with the automatic analysis result, and in response to the error between the manual analysis result and the automatic analysis result being greater than or equal to a preset error threshold, the finite element automatic analysis method based on Python software is corrected until the error between the manual analysis result and the automatic analysis result is less than the preset error threshold.

[0030] On the other hand, a whole-machine finite element automatic analysis system is provided, the system comprising:

[0031] A mesh module is used to mesh the aircraft model and add material properties, boundary conditions and loading nodes, and generate a mesh model file according to the meshed aircraft model and the material properties, boundary conditions and loading nodes;

[0032] A working condition module, used for obtaining a working condition load file and reading the working condition load from the working condition load file, so as to write the working condition load into the grid model file and generate a working condition calculation file;

[0033] The report module is used to submit the working condition calculation file to finite element analysis calculation and output the calculation result file, read and output the reliability analysis report of the aircraft model according to the calculation result file.

[0034] In another aspect, a computer device is provided, 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 following steps are implemented:

[0035] Meshing the aircraft model and adding material properties, boundary conditions and loading nodes, and generating a mesh model file according to the meshed aircraft model and the material properties, boundary conditions and loading nodes;

[0036] Obtaining a working condition load file and reading the working condition load from the working condition load file, so as to write the working condition load into the grid model file and generate a working condition calculation file;

[0037] The working condition calculation file is submitted to finite element analysis and calculation and a calculation result file is output, and a reliability analysis report of the aircraft model is read and output according to the calculation result file.

[0038] On the other hand, a computer-readable storage medium is provided, wherein the computer-readable storage medium stores a program, and when the program is executed by a processor, the processor performs the following steps:

[0039] Meshing the aircraft model and adding material properties, boundary conditions and loading nodes, and generating a mesh model file according to the meshed aircraft model and the material properties, boundary conditions and loading nodes;

[0040] Obtaining a working condition load file and reading the working condition load from the working condition load file, so as to write the working condition load into the grid model file and generate a working condition calculation file;

[0041] The working condition calculation file is submitted to finite element analysis and calculation and a calculation result file is output, and a reliability analysis report of the aircraft model is read and output according to the calculation result file.

[0042] The above technical solution of the present application has the following advantages compared with the prior art:

[0043] The above-mentioned automatic finite element analysis method, system, computer equipment and storage medium for the whole aircraft realize the automatic analysis of the finite element of the whole aircraft. The existing manual finite element analysis takes 2-3 days to complete an operating condition analysis. With this method, one operating condition only takes about 2 hours, and no human supervision is required. The off-get off work and rest days can be fully utilized to achieve "people rest but the machine does not", which greatly speeds up the efficiency of finite element analysis. In addition, the analysis of all operating conditions can be realized without screening the operating conditions, thereby further improving the accuracy of the safety assessment of the aircraft, so that the finite element of the aircraft can cover more operating conditions. Furthermore, the method provided in the present application avoids the influence of errors that may be caused by manual calculations on the final analysis results; it can also specify a unified standard report template according to user needs, and generate a standardized safety report based on the template. BRIEF DESCRIPTION OF THE DRAWINGS

[0044] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0045] Figure 1 is a first method flow chart of the full-machine finite element automatic analysis method provided in an embodiment of the present application;

[0046] Figure 2 is a second method flow chart of the full-machine finite element automatic analysis method provided in an embodiment of the present application;

[0047] Figure 3 is a system structure diagram of the whole machine finite element automatic analysis system provided in an embodiment of the present application;

[0048] Figure 4 It is a device structure diagram of a computer device provided in an embodiment of the present application. DETAILED DESCRIPTION

[0049] In order to make the purpose, technical solution and advantages of the present application more clearly understood, the present application is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present application and are not used to limit the present application.

[0050] Embodiment 1

[0051] Reference Figure 1 As shown, Figure 1 A first method flow chart of the finite element automatic analysis method provided in an embodiment of the present application.

[0052] The method comprises the following steps:

[0053] S101, meshing the aircraft model and adding material properties, boundary conditions and loading nodes, and generating a mesh model file according to the meshed aircraft model and the material properties, boundary conditions and loading nodes;

[0054] The automatic finite element analysis method of the whole aircraft of the present application must first determine the target analysis object, that is, to model the aircraft through 3D modeling software and establish a finite element model of the whole aircraft. Specifically, after establishing the aircraft model, the aircraft model must first be meshed, and tetrahedral meshing or hexahedral meshing can be performed according to actual needs; then the material properties, boundary conditions and loading nodes of the aircraft model are edited; after the aircraft model is meshed and the material properties, boundary conditions and loading nodes of the aircraft model are edited, the meshed aircraft model and the corresponding material properties, boundary conditions and loading nodes can form a mesh model file (.fem file), which can be named structure.fem, for easy reference in subsequent finite element analysis steps.

[0055] S102, obtaining a working condition load file and reading the working condition load from the working condition load file, so as to write the working condition load into the grid model file and generate a working condition calculation file;

[0056] After the grid model file is generated, the working load can be set for the grid model file. Specifically, first obtain the working load file of the aircraft. The working load file stores the working load of the aircraft. The working load is the load that simulates the actual operating environment of the aircraft. After obtaining the working load file, read the working load file to obtain the working load, and then write the read working load into the grid model file to form a working calculation file. Therefore, the working calculation file includes the aircraft model, the grid information of the aircraft model, and the corresponding aircraft model's material properties, boundary conditions and loading nodes. After these parameters are configured, the working calculation file is formed.

[0057] S103, submitting the working condition calculation file to finite element analysis and outputting a calculation result file, reading and outputting a reliability analysis report of the aircraft model according to the calculation result file.

[0058] After the working condition calculation file is generated, it can be submitted to the corresponding finite element analysis software for calculation. After calculation, a calculation result file can be obtained. The calculation result file saves the calculation results under the corresponding working condition load. The reliability analysis report of the aircraft model can be obtained through the calculation result file.

[0059] The automatic finite element analysis method for the whole aircraft of the present application realizes the automatic analysis of the finite element of the whole aircraft. The existing manual finite element analysis takes 2-3 days to complete an operating condition analysis. With this method, one operating condition only takes about 2 hours, and no human supervision is required. The off-get off work and rest days can be fully utilized to achieve "people rest but the machine does not", which greatly speeds up the efficiency of finite element analysis. In addition, the analysis of all operating conditions can be realized without screening the operating conditions, thereby further improving the accuracy of the aircraft safety assessment and enabling the finite element of the aircraft to cover more operating conditions. Furthermore, the automatic finite element analysis method for the whole aircraft provided by the present application avoids the influence of errors that may be caused by manual calculations on the final analysis results.

[0060] In one embodiment, the meshing of the aircraft model and adding material properties, boundary conditions and loading nodes, and generating a mesh model file according to the meshed aircraft model and the material properties, boundary conditions and loading nodes, include:

[0061] Meshing the aircraft model using Hypermesh software and adding material properties, boundary conditions and loading nodes to the meshed aircraft model using Hypermesh software;

[0062] For the meshing of the aircraft model, this application uses Hypermesh software to complete it, that is, the aircraft model is meshed by Hypermesh software, and material properties, boundary conditions and loading nodes are added to the meshed aircraft model by Hypermesh software. Among them, when the meshing quality requirement is high, manual meshing can be selected when using Hypermesh software to mesh; when the meshing quality requirement is low, the Hypermesh software can be called by Python software to realize automatic meshing.

[0063] The mesh model file is generated by Hypermesh software, and the mesh model file includes mesh information of the aircraft model after meshing, and material properties, boundary conditions and loading nodes corresponding to the aircraft model.

[0064] After meshing the aircraft model with Hypermesh software and adding material properties, boundary conditions and loading nodes to the meshed aircraft model with Hypermesh software, a mesh model file is generated with Hypermesh software, that is, a .fem file is generated. The .fem file includes the mesh information of the meshed aircraft model and the material properties, boundary conditions and loading node information corresponding to the aircraft model.

[0065] In one embodiment, the working condition load file includes a plurality of working condition load worksheets, each of which corresponds to a working condition load. Before obtaining the working condition load, the following steps are also included:

[0066] Determining several working loads of the aircraft model according to actual application scenarios of the aircraft model;

[0067] Performing finite element analysis on the entire aircraft requires simulating the operating conditions of the aircraft in actual application scenarios. Therefore, performing finite element analysis on the entire aircraft first requires determining several operating loads of the aircraft model based on the actual application scenarios of the aircraft model, and then performing finite element analysis on the aircraft based on these operating loads to simulate the actual operating environment of the aircraft.

[0068] Each of the working condition loads is written into a corresponding working condition load work table to form the working condition load file and the working condition load file is stored in a preset path.

[0069] After determining several working loads of the aircraft model according to the actual application scenario of the aircraft model, these working loads can be written into the corresponding working load worksheets, and several working load worksheets form working load files, and then the working load files are stored in a preset path, and the working load files can be obtained from the preset path when needed. There are multiple working loads, and each working load is stored in a corresponding working load worksheet.

[0070] In one embodiment, the obtaining of the working condition load file and reading the working condition load from the working condition load file to configure the working condition load into the grid model file and generate a working condition calculation file includes:

[0071] Obtaining the working condition load file from the preset path through Python software, and reading a plurality of working condition load worksheets from the working condition load file to obtain each working condition load;

[0072] The whole-machine automatic finite element analysis method of the present application is implemented with the aid of Python software. After the mesh model file is generated, the preset path is obtained through the Python software, and then the working condition load file storing the working condition load is obtained from the preset path. Since the working condition load includes multiple working condition load worksheets, the corresponding working condition load can be obtained from each working condition load worksheet.

[0073] The subroutine name for obtaining the load case file and traversing the load case worksheet is get_subcase.py. The program code example is as follows:

[0074]

[0075]

[0076] The subroutine name for reading load conditions from the load condition worksheet is get_loads.py. The program code example is as follows:

[0077]

[0078]

[0079] The various working condition loads are written into the grid model file through Python software and the working condition calculation files corresponding to the various working condition loads are generated according to a preset format.

[0080] After obtaining the working condition load file through Python software, the corresponding working condition load is read from the working condition load worksheet through Python software, and then the working condition load is written into the mesh model file. Thus, a working condition calculation file (.fem file) is formed, which includes the mesh information of the aircraft model after meshing, the material properties corresponding to the aircraft model, boundary conditions and loading nodes, and the corresponding working condition loads.

[0081] The subroutine name for generating the working condition calculation file is text_create_2D.py, and the program code example is as follows:

[0082]

[0083]

[0084]

[0085] In one embodiment, each of the working condition loads corresponds to a working condition calculation file, and submitting the working condition calculation file to finite element analysis and outputting the calculation result file includes:

[0086] Selecting one of the working condition calculation files as a target calculation file, calling Optistruct software through Python software to perform finite element analysis calculation on the target calculation file, and monitoring the finite element analysis process of the target calculation file through Python software;

[0087] When performing finite element analysis of the entire machine, calculations need to be performed under various load conditions. One load condition corresponds to one calculation file. Therefore, the number of load conditions is consistent with the number of calculation files. When submitting finite element analysis calculations for the entire machine, first select one of the calculation files as the target calculation file (the target calculation file is the current calculation file that needs to be submitted for finite element calculation), and then use Python software to call Optistruct software to perform finite element analysis calculations on the target calculation file. That is, simulate mouse clicks and keyboard input to open the Optistruct software and submit the calculation to achieve automated calculations. Since there are multiple calculation files for working conditions, it is necessary to submit several calculation files for calculation to Optistruct software in turn. Therefore, when Optistruct software is calculating, the finite element analysis process of the target calculation file is monitored by Python software. When the current finite element analysis process ends, the next calculation file can be submitted.

[0088] The name of the subroutine that submits the working condition calculation file to the finite element analysis calculation is SubmitOpt.py. The program code example is as follows:

[0089] import pyautogui / / Import GUI interpreter

[0090] import time

[0091] defSubmitOpt():

[0092] oneLocation_solver=pyautogui.locateOnScreen('D:\\pics\\solver.png')

[0093] print(oneLocation_solver)

[0094] pyautogui.doubleClick(oneLocation_solver[0]+10,oneLocation_solver[1]+10,button='left') / / Simulate opening the Optistruct software in the processor

[0095] time.sleep(2)

[0096] oneLocation_open=pyautogui.locateOnScreen('D:\\pics\\open.png')

[0097] print(oneLocation_open)

[0098] pyautogui.doubleClick(oneLocation_open[0], oneLocation_open[1], button = 'left') / / Simulate opening the file import button in the Optistruct software

[0099] pyautogui.keyDown('shift')

[0100] time.sleep(1)

[0101] pyautogui.keyUp('shift')

[0102] pyautogui.typewrite('b8.fem',1)

[0103] pyautogui.typewrite(['enter'],1) / / Simulate the storage location of the calculation file entered on the keyboard

[0104] oneLocation_run=pyautogui.locateOnScreen('D:\\pics\\run.png')

[0105] print(oneLocation_run)

[0106] pyautogui.click(oneLocation_run[0],oneLocation_run[1],button='left')

[0107] / / Simulate clicking the Run button in the Optistruct software

[0108] In response to obtaining a calculation end mark of the target calculation file, outputting a calculation result file of the target calculation file, and selecting a next working condition calculation file as the target calculation file to perform finite element analysis calculation;

[0109] When the Optistruct software is calculating, the finite element analysis process of the target calculation file is monitored through Python software. Specifically, when any finite element analysis process ends, the calculation end flag is set for the working condition calculation file corresponding to the process. Therefore, when the calculation end flag exists in the target calculation file, it means that the target calculation file has been calculated. For example, when the .out log is collected and the word "Job completed" is monitored, the current window is closed, and the next working condition calculation file is automatically selected for submission, and the finite element analysis calculation is performed on the working condition calculation files in turn.

[0110] Output the calculation result files corresponding to all working condition calculation files.

[0111] After each working condition calculation file is calculated by calling Optistruct software through Python software, the corresponding calculation result file (.pch file) is output. The calculation result file stores parameters such as force flow, axial force, unit stress and material allowable value.

[0112] Use Python programming to extract and process the finite element analysis results and save them to Excel (calculation result file). The name of the subroutine is copy_pch_2D.py. The program code example is as follows:

[0113]

[0114]

[0115] mos_yy=sigma_tu_yy / sigma_yy

[0116] MOS_yy.append(mos_yy)

[0117] mos_xy=sigma_tu_xy / sigma_xy

[0118] MOS_xy.append(mos_xy)

[0119] min_mos_xx_value=min(MOS_xx)

[0120] min_mos_yy_value=min(MOS_yy)

[0121] min_mos_xy_value=min(MOS_xy)

[0122] min_mos_xx_index=MOS_xx.index(min_mos_xx_value)

[0123] min_mos_yy_index=MOS_yy.index(min_mos_yy_value)

[0124] min_mos_xy_index=MOS_xy.index(min_mos_xy_value)

[0125] print('The min min_mos_xx_value is',min_mos_xx_value,'at Node',Node[min_mos_xx_index])

[0126] print('The min min_mos_yy_value is',min_mos_yy_value,'at Node',Node[min_mos_yy_index])

[0127] print('The min min_mos_xy_value is',min_mos_xy_value,'at Node',Node[min_mos_xy_index])

[0128] writeexcel.save(file_new_list[x]+'.xls')

[0129] return min_mos_xx_value,min_mos_yy_value,min_mos_xy_value,\

[0130] min_mos_xx_index,min_mos_yy_index,min_mos_xy_index

[0131] In one embodiment, the reading and outputting the reliability analysis report of the aircraft model according to the calculation result file includes:

[0132] Reading the calculation result file to obtain safety margin parameter information, and calculating a safety margin value according to the safety margin parameter information;

[0133] Since the calculation result file stores parameters such as force flow, axial force, unit stress and material allowable value, after obtaining the calculation result file, the parameters such as force flow, axial force, unit stress and material allowable value can be read from the calculation result file. These parameters are safety margin parameter information. According to these parameters, the safety margin value (safety margin = allowable stress / working stress-1) can be obtained by calculation, so as to judge the reliability of the aircraft by the safety margin value.

[0134] The Hypermesh software is called by Python software to output a stress cloud map of the aircraft model, and a reliability analysis report of the aircraft model is output by the Python software according to the safety margin value and the stress cloud map.

[0135] Through secondary development of Hyperview software and the use of Python programming, mouse clicks and keyboard input are simulated. Therefore, after obtaining the calculation result file, the Hyperview software is called by Python software to generate the safety margin stress cloud map of each working condition load, and it is displayed through pictures, and the stress of the unit where the minimum safety margin is located, the most dangerous part of each section, and the most dangerous working condition can be highlighted separately. And using Python programming, the dangerous position, the most serious working condition, the safety margin value and other information of each section on the aircraft are written into Word and / or PPT to generate a reliability analysis report, realize automatic report production, and do not need manual editing, which improves the analysis efficiency. In addition, a unified standard report template can be specified according to user needs, and a standardized safety report can be generated according to the template, without spending too much effort on manual adjustment to meet the standard formatting requirements.

[0136] The name of the subroutine for generating a reliability analysis report is ExportContourToPPT (taking PPT report as an example). The program code example is as follows:

[0137] import pyautogui

[0138] import time

[0139] #Open the result file

[0140] time.sleep(2)

[0141] oneLocation_open_results=pyautogui.locateOnScreen('D:\\pics\\open_results.png')

[0142] print(oneLocation_open_results)

[0143] pyautogui.click(oneLocation_open_results[0], oneLocation_open_results[1], button='left')

[0144] # Switch to the stress contour map icon

[0145] time.sleep(10)

[0146] oneLocation_open_contour = pyautogui.locateOnScreen('D:\\pics\\open_contour.png')

[0147] print(oneLocation_open_contour)

[0148] pyautogui.click(oneLocation_open_contour[0] + 10, oneLocation_open_contour[1] + 10, button='left')

[0149] # Clear the stress contour map

[0150] time.sleep(3)

[0151] oneLocation_clear_contour = pyautogui.locateOnScreen('D:\\pics\\clear_contour.png')

[0152] print(oneLocation_clear_contour)

[0153] pyautogui.click(oneLocation_clear_contour[0] + 2, oneLocation_clear_contour[1] + 2, button='le ft')

[0154] # Open the stress contour map

[0155] time.sleep(3)

[0156] oneLocation_apply_contour = pyautogui.locateOnScreen('D:\\pics\\apply_contour.png')

[0157] print(oneLocation_apply_contour)

[0158] pyautogui.click(oneLocation_apply_contour[0]+2, oneLocation_apply_contour[1]+2, button='left')

[0159] # Export to PPT

[0160] time.sleep(5)

[0161] oneLocation_export_ppt = pyautogui.locateOnScreen('D:\\pics\\export_ppt.png')

[0162] print(oneLocation_export_ppt)

[0163] pyautogui.click(oneLocation_export_ppt[0]+2, oneLocation_export_ppt[1]+2, button='left')

[0164] # Publish the first page of PPT

[0165] time.sleep(3)

[0166] oneLocation_publish_ppt = pyautogui.locateOnScreen('D:\\pics\\publish_ppt.png')

[0167] print(oneLocation_publish_ppt)

[0168] pyautogui.click(oneLocation_publish_ppt[0]+2, oneLocation_publish_ppt[1]+2, button='left')

[0169] ## Minimize the PPT window

[0170] #time.sleep(5)

[0171] #oneLocation_min_ppt = pyautogui.locateOnScreen('D:\\pics\\min_ppt.png')

[0172] #print(oneLocation_min_ppt)

[0173] #pyautogui.click(oneLocation_min_ppt[0]+10,oneLocation_min_ppt[1]+10,button='left')

[0174] #Switch to Elements Step 1

[0175] time.sleep(3)

[0176] oneLocation_select_element_1 = pyautogui.locateOnScreen('D:\\pics\\select_element_1.png')

[0177] print(oneLocation_select_element_1)

[0178] pyautogui.click(oneLocation_select_element_1[0]+10,oneLocation_select_element_1[1]+10,button='left')

[0179] #Switch to Elements Step 2

[0180] time.sleep(3)

[0181] oneLocation_select_element_2 = pyautogui.locateOnScreen('D:\\pics\\select_element_2.png')

[0182] print(oneLocation_select_element_2)

[0183] pyautogui.click(oneLocation_select_element_2[0]+10,oneLocation_select_element_2[1]+10,button='left')

[0184] # Click on Element

[0185] time.sleep(3)

[0186] oneLocation_click_element = pyautogui.locateOnScreen('D:\\pics\\click_element.png')

[0187] print(oneLocation_click_element)

[0188] pyautogui.click(oneLocation_click_element[0]+2, oneLocation_click_element[1]+2, button='left')

[0189] # Select By ID

[0190] time.sleep(3)

[0191] oneLocation_by_id = pyautogui.locateOnScreen('D:\\pics\\by_id.png')

[0192] print(oneLocation_by_id)

[0193] pyautogui.click(oneLocation_by_id[0]+2, oneLocation_by_id[1]+2, button='left')

[0194] # Fill in the ID

[0195] time.sleep(3)

[0196] oneLocation_element_id_1 = pyautogui.locateOnScreen('D:\\pics\\element_id_1.png')

[0197] print(oneLocation_element_id_1)

[0198] pyautogui.click(oneLocation_element_id_1[0]+10,oneLocation_element_id_1[1]+10,button='left')

[0199] pyautogui.typewrite('20',1)

[0200] # Add unit

[0201] time.sleep(3)

[0202] oneLocation_add_element = pyautogui.locateOnScreen('D:\\pics\\add_element.png')

[0203] print(oneLocation_add_element)

[0204] pyautogui.click(oneLocation_add_element[0]+10,oneLocation_add_element[1]+10,button='left')

[0205] # Return

[0206] time.sleep(3)

[0207] oneLocation_return_element = pyautogui.locateOnScreen('D:\\pics\\return_element.png')

[0208] print(oneLocation_return_element)

[0209] pyautogui.click(oneLocation_return_element[0]+10,oneLocation_return_element[1]+10,button='left')

[0210] # Display the position of the unit with the minimum margin (highlighted)

[0211] time.sleep(3)

[0212] oneLocation_apply_contour = pyautogui.locateOnScreen('D:\\pics\\apply_contour.png')

[0213] print(oneLocation_apply_contour)

[0214] pyautogui.click(oneLocation_apply_contour[0]+2, oneLocation_apply_contour[1]+2, button='left')

[0215] # Export to PPT

[0216] time.sleep(5)

[0217] oneLocation_export_ppt = pyautogui.locateOnScreen('D:\\pics\\export_ppt.png')

[0218] print(oneLocation_export_ppt)

[0219] pyautogui.click(oneLocation_export_ppt[0]+2, oneLocation_export_ppt[1]+2, button='left')

[0220] # Publish the second page of the PPT

[0221] time.sleep(3)

[0222] oneLocation_publish_ppt = pyautogui.locateOnScreen('D:\\pics\\publish_ppt.png')

[0223] print(oneLocation_publish_ppt)

[0224] pyautogui.click(oneLocation_publish_ppt[0]+2, oneLocation_publish_ppt[1]+2, button='left')

[0225] # Switch to PPTX

[0226] time.sleep(3)

[0227] #oneLocation_ppt_icon=pyautogui.locateOnScreen('D:\\pics\\ppt_icon.png')

[0228] #print(oneLocation_ppt_icon)

[0229] #pyautogui.click(oneLocation_ppt_icon[0]+10,oneLocation_ppt_icon[1]+10,button='left')

[0230] pyautogui.click(200,400,duration=2)

[0231] #Save PPTX

[0232] time.sleep(5)

[0233] pyautogui.keyDown('ctrl')

[0234] pyautogui.press('s')

[0235] pyautogui.keyUp('ctrl')

[0236] time.sleep(5)

[0237] oneLocation_liulan=pyautogui.locateOnScreen('D:\\pics\\liulan.png')

[0238] print(oneLocation_liulan)

[0239] pyautogui.click(oneLocation_liulan[0]+10,oneLocation_liulan[1]+10,button='left')

[0240] The reliability analysis report is sent to the mobile phone by calling the communication software on the computer through Python software.

[0241] Once a reliability analysis report is generated, it can be sent to the staff's mobile phone. Specifically, the reliability analysis report is sent to the mobile phone by calling the communication software on the computer through Python software, which improves the convenience of use.

[0242] The subroutine name for sending the reliability analysis report to the mobile phone by calling the communication software on the computer through Python software is SendPPTByDD.py. The program code example is as follows:

[0243] import pyautogui

[0244] import time

[0245] defSendLogByDD():

[0246] oneLocation_dingding=pyautogui.locateOnScreen('D:\\pics\\dingding.png')

[0247] print(oneLocation_dingding)

[0248] pyautogui.doubleClick(oneLocation_dingding[0]+10,oneLocation_dingding[1]+10,button='le ft')

[0249] time.sleep(5)

[0250] oneLocation_sousuo=pyautogui.locateOnScreen('D:\\pics\\sousuo.png')

[0251] print(oneLocation_sousuo)

[0252] pyautogui.click(oneLocation_sousuo[0],oneLocation_sousuo[1],button='left')

[0253] time.sleep(2)

[0254] pyautogui.typewrite('wo',1)

[0255] pyautogui.keyDown('space')

[0256] time.sleep(1)

[0257] pyautogui.keyUp('space')

[0258] pyautogui.typewrite(['enter'],1)

[0259] time.sleep(1)

[0260] time.sleep(5)

[0261] pyautogui.moveTo(200,400,duration=2)

[0262] oneLocation_upload_1=pyautogui.locateOnScreen('D:\\pics\\upload_1.png')

[0263] print(oneLocation_upload_1)

[0264] pyautogui.click(oneLocation_upload_1[0],oneLocation_upload_1[1],button='left')

[0265] time.sleep(2)

[0266] oneLocation_upload_2=pyautogui.locateOnScreen('D:\\pics\\upload_2.png')

[0267] print(oneLocation_upload_2)

[0268] pyautogui.click(oneLocation_upload_2[0],oneLocation_upload_2[1],button='left')

[0269] time.sleep(2)

[0270] pyautogui.typewrite('b8.out',1)

[0271] pyautogui.typewrite(['enter'],1)

[0272] #Close the DingTalk dialog box

[0273] time.sleep(2)

[0274] oneLocation_close_dingding=pyautogui.locateOnScreen('D:\\pics\\close_dingding.png')

[0275] print(oneLocation_close_dingding)

[0276] pyautogui.click(oneLocation_close_dingding[0],oneLocation_close_dingding[1],button="left")

[0277] In addition, the main program implements the cyclic calling of the above subroutines and completes the operation of each working condition one by one. The name of the main program of the entire full-machine finite element automatic analysis method is main.py. The program is as follows:

[0278]

[0279]

[0280]

[0281] In one embodiment, before meshing the aircraft model, the method further includes:

[0282] Selecting several typical working conditions, performing manual finite element analysis on the aircraft model under the typical working conditions and outputting manual analysis results;

[0283] Before using the full-aircraft finite element automatic analysis method for the first time for finite element analysis, that is, before meshing the aircraft model for the first time, it is necessary to verify the effectiveness of this method. Specifically, several typical working conditions are selected according to the actual operation scenarios of the aircraft, and then the aircraft model is manually analyzed for finite elements under typical working conditions, and the manual analysis results are output.

[0284] Performing automatic finite element analysis based on Python software on the aircraft model under the typical working conditions and outputting automatic analysis results;

[0285] After determining the typical working conditions, the aircraft model is subjected to automatic finite element analysis based on Python software under typical working conditions, and the automatic analysis results are output to facilitate comparison between the manual analysis results and the automatic analysis results, thus verifying the effectiveness of the automatic finite element analysis method for the entire aircraft.

[0286] The manual analysis result is compared with the automatic analysis result, and in response to the error between the manual analysis result and the automatic analysis result being greater than or equal to a preset error threshold, the finite element automatic analysis method based on Python software is corrected until the error between the manual analysis result and the automatic analysis result is less than the preset error threshold.

[0287] After obtaining the manual analysis results and automatic analysis results under typical working conditions, compare the manual analysis results with the automatic analysis results. If the error between the manual analysis results and the automatic analysis results is less than the preset error threshold (the preset error threshold is set according to actual needs or experience values), it means that the result of the full-machine finite element automatic analysis method is within the allowable error and the result is reliable. The full-machine finite element automatic analysis method can be used directly for automatic analysis in the future. If the error between the manual analysis results and the automatic analysis results is greater than or equal to the preset error threshold, the finite element automatic analysis method based on Python software needs to be corrected until the error between the manual analysis results and the automatic analysis results is less than the preset error threshold and meets the accuracy requirements.

[0288] Embodiment 2

[0289] Reference Figure 2 As shown, Figure 2 The second method flow chart of the whole machine finite element automatic analysis method provided in the embodiment of the present application. Figure 2 In the method shown, Figure 1 For the same or similar contents in the method shown, please refer to Figure 1 The description in the method will not be repeated here.

[0290] S201, selecting several typical working conditions, performing manual finite element analysis on the aircraft model under the typical working conditions and outputting manual analysis results;

[0291] Before using the full-aircraft finite element automatic analysis method for the first time for finite element analysis, that is, before meshing the aircraft model for the first time, it is necessary to verify the effectiveness of this method. Specifically, several typical working conditions are selected according to the actual operation scenarios of the aircraft, and then the aircraft model is manually analyzed for finite elements under typical working conditions, and the manual analysis results are output.

[0292] S202, performing a finite element automatic analysis based on Python software on the aircraft model under the typical working condition and outputting the automatic analysis result;

[0293] After determining the typical working conditions, the aircraft model is subjected to automatic finite element analysis based on Python software under typical working conditions, and the automatic analysis results are output to facilitate comparison between the manual analysis results and the automatic analysis results, thus verifying the effectiveness of the automatic finite element analysis method for the entire aircraft.

[0294] S203, comparing the manual analysis result with the automatic analysis result, and in response to the error between the manual analysis result and the automatic analysis result being greater than or equal to a preset error threshold, modifying the Python software-based finite element automatic analysis method until the error between the manual analysis result and the automatic analysis result is less than the preset error threshold;

[0295] Compare the manual analysis results with the automatic analysis results. If the error between the manual analysis results and the automatic analysis results is less than the preset error threshold (the preset error threshold is set according to actual needs or experience), it means that the result of the full-machine finite element automatic analysis method is within the allowable error and the result is reliable. The full-machine finite element automatic analysis method can be used directly for automatic analysis in the future. If the error between the manual analysis results and the automatic analysis results is greater than or equal to the preset error threshold, the finite element automatic analysis method based on Python software needs to be corrected until the error between the manual analysis results and the automatic analysis results is less than the preset error threshold and meets the accuracy requirements.

[0296] S204, determining several working loads of the aircraft model according to actual application scenarios of the aircraft model;

[0297] Performing finite element analysis on the entire aircraft requires simulating the operating conditions of the aircraft in actual application scenarios. Therefore, performing finite element analysis on the entire aircraft first requires determining several operating loads of the aircraft model based on the actual application scenarios of the aircraft model, and then performing finite element analysis on the aircraft based on these operating loads to simulate the actual operating environment of the aircraft.

[0298] S205, writing each of the working condition loads into a corresponding working condition load work table and storing the working condition load file in a preset path;

[0299] After determining several working loads of the aircraft model according to the actual application scenario of the aircraft model, these working loads can be written into the corresponding working load worksheets, and several working load worksheets form working load files, and then the working load files are stored in a preset path, and the working load files can be obtained from the preset path when needed. There are multiple working loads, and each working load is stored in a corresponding working load worksheet.

[0300] S206, meshing the aircraft model using Hypermesh software and adding material properties, boundary conditions and loading nodes to the meshed aircraft model using Hypermesh software;

[0301] For the meshing of the aircraft model, the present application adopts Hypermesh software, that is, the aircraft model is meshed by Hypermesh software, and material properties, boundary conditions and loading nodes are added to the meshed aircraft model by Hypermesh software.

[0302] S207, generating the mesh model file by using Hypermesh software, wherein the mesh model file includes mesh information of the aircraft model after meshing and material properties, boundary conditions and loading nodes corresponding to the aircraft model;

[0303] After meshing the aircraft model with Hypermesh software and adding material properties, boundary conditions and loading nodes to the meshed aircraft model with Hypermesh software, a mesh model file is generated with Hypermesh software, that is, a .fem file is generated. The .fem file includes the mesh information of the meshed aircraft model and the material properties, boundary conditions and loading node information corresponding to the aircraft model.

[0304] S208, obtaining the working condition load file from the preset path through Python software, and reading a plurality of working condition load worksheets from the working condition load file to obtain each working condition load;

[0305] The whole-machine automatic finite element analysis method of the present application is implemented with the aid of Python software. After the mesh model file is generated, the preset path is obtained through the Python software, and then the working condition load file storing the working condition load is obtained from the preset path. Since the working condition load includes multiple working condition load worksheets, the corresponding working condition load can be obtained from each working condition load worksheet.

[0306] S209, writing each working condition load into the grid model file through Python software and generating a working condition calculation file corresponding to each working condition load according to a preset format;

[0307] After obtaining the working condition load file through Python software, the corresponding working condition load is read from the working condition load worksheet through Python software, and then the working condition load is written into the mesh model file. Thus, a working condition calculation file (.fem file) is formed, which includes the mesh information of the aircraft model after meshing, the material properties corresponding to the aircraft model, boundary conditions and loading nodes, and the corresponding working condition loads.

[0308] S210, selecting one of the working condition calculation files as a target calculation file, calling Optistruct software through Python software to perform finite element analysis calculation on the target calculation file, and monitoring the finite element analysis process of the target calculation file through Python software;

[0309] When performing finite element analysis of the entire machine, calculations need to be performed under various load conditions. One load condition corresponds to one calculation file. Therefore, the number of load conditions is consistent with the number of calculation files. When submitting finite element analysis calculations for the entire machine, first select one of the calculation files as the target calculation file (the target calculation file is the current calculation file that needs to be submitted for finite element calculation), and then use Python software to call Optistruct software to perform finite element analysis calculations on the target calculation file. That is, simulate mouse clicks and keyboard input to open the Optistruct software and submit the calculation to achieve automated calculations. Since there are multiple calculation files for working conditions, it is necessary to submit several calculation files for calculation to Optistruct software in turn. Therefore, when Optistruct software is calculating, the finite element analysis process of the target calculation file is monitored by Python software. When the current finite element analysis process ends, the next calculation file can be submitted.

[0310] S211, in response to obtaining a calculation end mark of the target calculation file, outputting a calculation result file of the target calculation file, and selecting a next working condition calculation file as the target calculation file to perform finite element analysis calculation;

[0311] When any finite element analysis process ends, a calculation end flag is set for the working condition calculation file corresponding to the process. Therefore, when a calculation end flag exists in the target calculation file, it means that the target calculation file has been calculated and the next working condition calculation file can be selected as the target calculation file to perform finite element analysis calculations, and finite element analysis calculations are performed on the working condition calculation files in turn.

[0312] S212, outputting the calculation result files corresponding to all the working condition calculation files;

[0313] After each working condition calculation file is calculated by calling Optistruct software through Python software, the corresponding calculation result file (.pch file) is output. The calculation result file stores parameters such as force flow, axial force, unit stress and material allowable value.

[0314] S213, reading the calculation result file to obtain safety margin parameter information, and calculating a safety margin value according to the safety margin parameter information;

[0315] Since the calculation result file stores parameters such as force flow, axial force, unit stress and material allowable value, after obtaining the calculation result file, parameters such as force flow, axial force, unit stress and material allowable value can be read from the calculation result file. These parameters are safety margin parameter information. Based on these parameters, the safety margin value can be calculated to judge the reliability of the aircraft through the safety margin value.

[0316] S214, calling the Hypermesh software through the Python software to output a stress cloud map of the aircraft model, and outputting a reliability analysis report of the aircraft model according to the safety margin value and the stress cloud map through the Python software.

[0317] Through secondary development of Hyperview software and Python programming, mouse clicks and keyboard input are simulated. Therefore, after obtaining the calculation result file, Hyperview software is called by Python software to generate the safety margin stress cloud map of each working condition load, and displayed through pictures, and the stress of the unit where the minimum safety margin is located, the most dangerous part of each section, and the most dangerous working condition can be highlighted separately. And using Python programming, the dangerous position, the most serious working condition, the safety margin value and other information of each section on the aircraft are written into Word and / or PPT to generate a reliability analysis report, realize automatic report production, and do not need manual editing, which improves the analysis efficiency.

[0318] S215, calling the communication software on the computer through the Python software to send the reliability analysis report to the mobile phone.

[0319] Once a reliability analysis report is generated, it can be sent to the staff's mobile phone. Specifically, the reliability analysis report is sent to the mobile phone by calling the communication software on the computer through Python software, which improves the convenience of use.

[0320] It should be understood that although Figure 1-2The steps in the flowchart are shown in sequence as indicated by the arrows, but these steps are not necessarily executed in the order indicated by the arrows. Unless otherwise specified in this document, there is no strict order restriction for the execution of these steps, and these steps can be executed in other orders. Moreover, Figure 1-2 At least part of the steps may include multiple sub-steps or multiple stages. These sub-steps or stages are not necessarily executed at the same time, but can be executed at different times. The execution order of these sub-steps or stages is not necessarily sequential, but can be executed in turn or alternately with other steps or at least part of the sub-steps or stages of other steps.

[0321] Embodiment 3

[0322] Reference Figure 3 As shown, Figure 3 This is a system structure diagram of the full-machine finite element automatic analysis system provided in an embodiment of the present application.

[0323] The whole machine finite element automatic analysis system of this embodiment includes:

[0324] A mesh module is used to mesh the aircraft model and add material properties, boundary conditions and loading nodes, and generate a mesh model file according to the meshed aircraft model and the material properties, boundary conditions and loading nodes;

[0325] A working condition module, used for obtaining a working condition load file and reading the working condition load from the working condition load file, so as to write the working condition load into the grid model file and generate a working condition calculation file;

[0326] The report module is used to submit the working condition calculation file to the finite element analysis calculation and output the calculation result file, read and output the reliability analysis report of the aircraft model according to the calculation result file.

[0327] For the specific definition of the whole machine finite element automatic analysis system, please refer to the definition of the method above, which will not be repeated here. Each module in the above-mentioned whole machine finite element automatic analysis system can be implemented in whole or in part by software, hardware and their combination. The above-mentioned modules can be embedded in or independent of the processor in the computer device in the form of hardware, or can be stored in the memory of the computer device in the form of software, so that the processor can call and execute the operations corresponding to the above modules.

[0328] Embodiment 4

[0329] This embodiment provides a computer device, including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor implements the steps of a method for automatic finite element analysis of a whole machine when executing the computer program.

[0330] The computer device may be a terminal, and its internal structure diagram may be as follows: Figure 4 As shown. The computer device includes a processor, a memory, a network interface, a display screen and an input device connected through a system bus. Among them, the processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system and a computer program. The internal memory provides an environment for the operation of the operating system and the computer program in the non-volatile storage medium. The network interface of the computer device is used to communicate with an external terminal through a network connection. When the computer program is executed by the processor, a full-machine finite element automatic analysis method is implemented. The display screen of the computer device can be a liquid crystal display screen or an electronic ink display screen, and the input device of the computer device can be a touch layer covering the display screen, or a button, trackball or touchpad set on the computer device housing, or an external keyboard, touchpad or mouse, etc.

[0331] Those skilled in the art should understand that Figure 4 The structure shown in the figure is only a block diagram of a part of the structure related to the solution of the present application, and does not constitute a limitation on the computer device to which the solution of the present application is applied. The specific computer device may include more or fewer components than those shown in the figure, or combine certain components, or have a different arrangement of components.

[0332] In one embodiment, a computer device is provided, including 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 following steps are implemented:

[0333] Meshing the aircraft model and adding material properties, boundary conditions and loading nodes, and generating a mesh model file according to the meshed aircraft model and the material properties, boundary conditions and loading nodes;

[0334] Obtaining a working condition load file and reading the working condition load from the working condition load file, so as to write the working condition load into the grid model file and generate a working condition calculation file;

[0335] The working condition calculation file is submitted to finite element analysis and calculation and a calculation result file is output, and a reliability analysis report of the aircraft model is read and output according to the calculation result file.

[0336] Embodiment 5

[0337] This embodiment provides a computer-readable storage medium, on which a computer program is stored. When the computer program is executed by a processor, the following steps are implemented:

[0338] Meshing the aircraft model and adding material properties, boundary conditions and loading nodes, and generating a mesh model file according to the meshed aircraft model and the material properties, boundary conditions and loading nodes;

[0339] Obtaining a working condition load file and reading the working condition load from the working condition load file, so as to write the working condition load into the grid model file and generate a working condition calculation file;

[0340] The working condition calculation file is submitted to finite element analysis and calculation and a calculation result file is output, and a reliability analysis report of the aircraft model is read and output according to the calculation result file.

[0341] Those skilled in the art can understand that all or part of the processes in the above-mentioned embodiment methods can be completed by instructing the relevant hardware through a computer program, and the computer program can be stored in a non-volatile computer-readable storage medium. When the computer program is executed, it can include the processes of the embodiments of the above-mentioned methods. Among them, any reference to memory, storage, database or other media used in the embodiments provided in this application can include non-volatile and / or volatile memory. Non-volatile memory can include read-only memory (ROM), programmable ROM (PROM), electrically programmable ROM (EPROM), electrically erasable programmable ROM (EEPROM) or flash memory. Volatile memory can include random access memory (RAM) or external cache memory. As an illustration and not limitation, RAM is available in many forms, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double data rate SDRAM (DDRSDRAM), enhanced SDRAM (ESDRAM), synchronous link (Synchlink) DRAM (SLDRAM), memory bus (Rambus) direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM).

[0342] The technical features of the above embodiments may be combined arbitrarily. To make the description concise, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0343] The above-mentioned embodiments only express several implementation methods of the present application, and the descriptions thereof are relatively specific and detailed, but they cannot be understood as limiting the scope of the invention patent. It should be pointed out that, for a person of ordinary skill in the art, several variations and improvements can be made without departing from the concept of the present application, and these all belong to the protection scope of the present application. Therefore, the protection scope of the patent of the present application shall be subject to the attached claims.

Claims

1. A method for automatic finite element analysis of the entire machine, characterized in that: The method comprises: Meshing the aircraft model and adding material properties, boundary conditions and loading nodes, and generating a mesh model file according to the meshed aircraft model and the material properties, boundary conditions and loading nodes; Obtaining a working condition load file and reading the working condition load from the working condition load file, so as to write the working condition load into the grid model file and generate a working condition calculation file; The working condition calculation file is submitted to finite element analysis and calculation and a calculation result file is output, and a reliability analysis report of the aircraft model is read and output according to the calculation result file.

2. The whole machine finite element automatic analysis method according to claim 1 is characterized in that: The meshing of the aircraft model and adding material properties, boundary conditions and loading nodes, and generating a mesh model file according to the meshed aircraft model and the material properties, boundary conditions and loading nodes, include: Meshing the aircraft model using Hypermesh software and adding material properties, boundary conditions and loading nodes to the meshed aircraft model using Hypermesh software; The mesh model file is generated by Hypermesh software, and the mesh model file includes mesh information of the aircraft model after meshing, and material properties, boundary conditions and loading nodes corresponding to the aircraft model.

3. The whole machine finite element automatic analysis method according to claim 1 is characterized in that: The working condition load file includes a plurality of working condition load worksheets, each of which corresponds to a working condition load. Before obtaining the working condition load, the following steps are also included: Determining several working loads of the aircraft model according to actual application scenarios of the aircraft model; Each of the working condition loads is written into a corresponding working condition load work table to form the working condition load file and the working condition load file is stored in a preset path.

4. The whole machine finite element automatic analysis method according to claim 3 is characterized in that: The obtaining of the working condition load file and reading the working condition load from the working condition load file, writing the working condition load into the grid model file and generating a working condition calculation file include: Obtaining the working condition load file from the preset path through Python software, and reading a plurality of working condition load worksheets from the working condition load file to obtain each working condition load; The various working condition loads are written into the grid model file through Python software and the working condition calculation files corresponding to the various working condition loads are generated according to a preset format.

5. The whole machine finite element automatic analysis method according to claim 1 is characterized in that: Each of the working condition loads corresponds to a working condition calculation file, and the working condition calculation file is submitted to the finite element analysis calculation and the calculation result file is output, including: Selecting one of the working condition calculation files as a target calculation file, calling Optistruct software through Python software to perform finite element analysis calculation on the target calculation file, and monitoring the finite element analysis process of the target calculation file through Python software; In response to obtaining a calculation end mark of the target calculation file, outputting a calculation result file of the target calculation file, and selecting a next working condition calculation file as the target calculation file to perform finite element analysis calculation; Output the calculation result files corresponding to all working condition calculation files.

6. The whole machine finite element automatic analysis method according to claim 1 is characterized in that: The step of reading and outputting the reliability analysis report of the aircraft model according to the calculation result file includes: Reading the calculation result file to obtain safety margin parameter information, and calculating a safety margin value according to the safety margin parameter information; Calling the Hypermesh software through Python software to output a stress cloud map of the aircraft model, and outputting a reliability analysis report of the aircraft model through the Python software according to the safety margin value and the stress cloud map; The reliability analysis report is sent to the mobile phone by calling the communication software on the computer through Python software.

7. The whole machine finite element automatic analysis method according to claim 1 is characterized in that: Before meshing the aircraft model, the method further includes: Selecting several typical working conditions, performing manual finite element analysis on the aircraft model under the typical working conditions and outputting manual analysis results; Performing automatic finite element analysis based on Python software on the aircraft model under the typical working conditions and outputting automatic analysis results; The manual analysis result is compared with the automatic analysis result, and in response to the error between the manual analysis result and the automatic analysis result being greater than or equal to a preset error threshold, the finite element automatic analysis method based on Python software is corrected until the error between the manual analysis result and the automatic analysis result is less than the preset error threshold.

8. A whole machine finite element automatic analysis system, characterized in that: The whole machine finite element automatic analysis system comprises: A mesh module is used to mesh the aircraft model and add material properties, boundary conditions and loading nodes, and generate a mesh model file according to the meshed aircraft model and the material properties, boundary conditions and loading nodes; A working condition module, used for obtaining a working condition load file and reading the working condition load from the working condition load file, so as to write the working condition load into the grid model file and generate a working condition calculation file; The report module is used to submit the working condition calculation file to finite element analysis calculation and output the calculation result file, read and output the reliability analysis report of the aircraft model according to the calculation result file.

9. A computer device comprising a memory, a processor and a computer program stored in the memory and executable on the processor, characterized in that: When the processor executes the computer program, the steps of the method according to any one of claims 1 to 7 are implemented.

10. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores a program, and when the program is executed by a processor, the processor is caused to execute the steps of the method according to any one of claims 1 to 7.

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