Aerodynamic characteristic data processing method and device, electronic device and storage medium

Abstract

The present application provides a method and device for processing aerodynamic characteristic data, an electronic device and a storage medium, wherein the method comprises: obtaining parameter variables contained in a current running script; batch reading parameter variables using a target programming algorithm; replacing the variable values ​​at corresponding positions in a preset script template with parameter variables to generate a target running script, wherein the preset script template is used to perform running operations on aerodynamic characteristic data, and the target running script is a script obtained after batch replacement of variable values ​​in the preset script template; using the target running script and target software to obtain processed aerodynamic characteristic data, wherein the target software is used to batch calculate the aerodynamic characteristic data for characterizing an aircraft contained in the target running script. Through the present application, the problem of manual adjustment existing in the related art, which leads to large manual workload, low work efficiency and easy errors, is solved.

Description

Technical Field

[0001] The present application relates to the field of aerospace, and in particular to a method and device for processing aerodynamic characteristic data, an electronic device and a storage medium. Background Art

[0002] Aerodynamic characteristics directly affect the handling stability, economy, carrying capacity, etc. of aircraft and rockets, and play an important role in aircraft development. With the development of computers and CFD (Computational Fluid Dynamics) technology, a large number of CFD calculations are often needed to support aerodynamic shape design, selection and optimization during model development. Since the calculation state changes with factors such as Mach number, flight altitude, angle of attack, sideslip angle, rudder angle, flaps, etc., a complete aerodynamic database often contains tens of thousands of sets of data.

[0003] Such a large number of working conditions not only brings a lot of workload to aerodynamic engineers, but also makes it difficult to avoid human errors in the process of repeated operations such as solution settings and result extraction. Model development often requires speed, especially downstream ballistics, attitude control and other disciplines require data input from aerodynamic professionals to carry out work. Therefore, improving the efficiency of aerodynamic professionals can often greatly speed up the progress of model development in the early stage.

[0004] In the related art, the calculation and data processing of aerodynamic performance are usually performed manually, resulting in a large workload, low work efficiency and prone to errors. Summary of the invention

[0005] The present application provides a method and device for processing aerodynamic characteristic data, an electronic device and a storage medium, so as to at least solve the problem in the related art that manual adjustment results in a large manual workload, low work efficiency and easy errors.

[0006] According to one aspect of an embodiment of the present application, a method for processing aerodynamic characteristic data is provided, the method comprising:

[0007] Get the parameter variables contained in the currently running script;

[0008] Using a target programming algorithm to batch read the parameter variables;

[0009] The parameter variable is used to replace the variable value at the corresponding position in the preset script template to generate a target operation script, wherein the preset script template is used to perform an operation on the aerodynamic characteristic data, and the target operation script is a script obtained after batch replacement of the variable values ​​in the preset script template;

[0010] The processed aerodynamic characteristic data are obtained by using the target operation script and the target software, wherein the target software is used to perform batch calculations on the aerodynamic characteristic data for characterizing the aircraft contained in the target operation script.

[0011] According to another aspect of the embodiment of the present application, there is also provided a device for processing aerodynamic characteristic data, the device comprising:

[0012] A first acquisition unit is used to acquire parameter variables contained in the currently running script;

[0013] A reading unit, used for batch reading the parameter variables using a target programming algorithm;

[0014] A replacement unit, used to replace the variable value at the corresponding position in the preset script template with the parameter variable, and generate a target operation script, wherein the preset script template is used to perform an operation on the aerodynamic characteristic data, and the target operation script is a script obtained after batch replacement of the variable values ​​in the preset script template;

[0015] The first obtaining unit is used to obtain the processed aerodynamic characteristic data using the target operation script and the target software, wherein the target software is used to perform batch calculations on the aerodynamic characteristic data for characterizing the aircraft contained in the target operation script.

[0016] Optionally, the first obtaining unit includes:

[0017] A module is used to input the target running script into the target software to obtain the output result file after calculation;

[0018] The extraction module is used to extract the processed aerodynamic characteristic data from the output result file.

[0019] Optionally, the device further comprises:

[0020] A second acquisition unit is used to acquire an output file after the target running script is input into the target software;

[0021] The second obtaining unit is used to use a string function to name the output file to which the computing condition noun belongs, and obtain a target output file corresponding to each computing condition noun;

[0022] The first determination unit is used to determine the data files after batch calculation based on each of the target output files, wherein the data files include the output result files after calculation and the convergence monitoring files after calculation.

[0023] Optionally, the reading unit includes:

[0024] A storage module, used for storing the parameter variables in a preset list;

[0025] A reading module is used to read the parameter variables in batches from the preset list using the target programming algorithm.

[0026] Optionally, the device further comprises:

[0027] A third acquisition unit is used for, after obtaining the processed aerodynamic characteristic data by using the target running script and the target software, batch acquiring the aerodynamic force values ​​and moment coefficients determined in multiple preset directions from the convergence monitoring file by using the target programming algorithm;

[0028] The second determining unit is used to determine the final convergence of the aerodynamic characteristic data according to the aerodynamic force value, the moment coefficient and the number of iterations.

[0029] Optionally, the second determining unit includes:

[0030] A first acquisition module is used to obtain a change curve of the aerodynamic force value and the moment coefficient along with the number of iterations;

[0031] A second acquisition module is used to acquire the aerodynamic force value and the maximum value of the moment coefficient corresponding to the preset range of the iteration number, the minimum value of the aerodynamic force value and the moment coefficient, and the current convergence value based on the change curve;

[0032] A determination module is used to determine the final convergence of the aerodynamic characteristic data based on the maximum value, the minimum value and the current convergence value.

[0033] Optionally, the calculation formula for determining the module is:

[0034]

[0035] Among them, Cx max is the maximum value, Cx min is the minimum value, Cx 收敛 is the current convergence value.

[0036] According to another aspect of the embodiments of the present application, there is also provided an electronic device, including a processor, a communication interface, a memory and a communication bus, wherein the processor, the communication interface and the memory communicate with each other via the communication bus; wherein the memory is used to store a computer program; and the processor is used to execute the method steps in any of the above embodiments by running the computer program stored in the memory.

[0037] According to another aspect of the embodiments of the present application, a computer-readable storage medium is provided, in which a computer program is stored, wherein the computer program is configured to execute the method steps in any of the above embodiments when executed.

[0038] In the embodiment of the present application, by obtaining the parameter variables contained in the current running script; using the target programming algorithm to batch read the parameter variables; replacing the variable values ​​at the corresponding positions in the preset script template with the parameter variables, a target running script is generated, wherein the preset script template is used to perform running operations on the aerodynamic characteristic data, and the target running script is a script obtained after batch replacing the variable values ​​in the preset script template; using the target running script and the target software, the processed aerodynamic characteristic data is obtained, wherein the target software is used to batch calculate the aerodynamic characteristic data for characterizing the aircraft contained in the target running script. Since the embodiment of the present application processes the aerodynamic characteristic data, the entire calculation setting, data extraction, analysis and batch processing process develops in the direction of standardization, process and automation, on the one hand, it greatly reduces the workload of aerodynamic engineers and increases work efficiency, and on the other hand, through standardization and process, it can avoid human operation errors and improve work quality, thereby solving the problem of manual adjustment existing in the related technology, resulting in large manual workload, low work efficiency and easy errors. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the invention and, together with the description, serve to explain the principles of the invention.

[0040] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, for ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative labor.

[0041] Figure 1 is a flow chart of an optional method for processing aerodynamic characteristic data according to an embodiment of the present application;

[0042] Figure 2 is a structural block diagram of an optional aerodynamic characteristic data processing device according to an embodiment of the present application;

[0043] Figure 3 It is a structural block diagram of an optional electronic device according to an embodiment of the present application. DETAILED DESCRIPTION

[0044] In order to enable those skilled in the art to better understand the solution of the present application, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work should fall within the scope of protection of the present application.

[0045] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the data used in this way can be interchangeable where appropriate, so that the embodiments of the present application described herein can be implemented in an order other than those illustrated or described herein. In addition, the terms "including" and "having" and any of their variations are intended to cover non-exclusive inclusions, for example, a process, method, system, product or device comprising a series of steps or units is not necessarily limited to those steps or units clearly listed, but may include other steps or units that are not clearly listed or inherent to these processes, methods, products or devices.

[0046] With the development of computers and CFD (Computational Fluid Dynamics) technology, in the process of model development, large-scale CFD calculations are often required to support aerodynamic shape design, selection and optimization. Since the calculation state varies with factors such as Ma, flight altitude, angle of attack, sideslip angle, rudder angle, flaps, etc., a complete aerodynamic database often contains tens of thousands of sets of data. Such a large number of working conditions not only brings a lot of workload to aerodynamic engineers, but also makes it difficult to avoid human errors in the process of performing a large number of repeated operations such as solution settings and result extraction. In order to solve the above problems, the embodiment of the present application proposes a method for processing aerodynamic characteristic data, which runs on a server, such as Figure 1 As shown, the method includes:

[0047] Step S101, obtaining parameter variables contained in the currently running script;

[0048] Step S102, batch reading parameter variables using a target programming algorithm;

[0049] Step S103, replacing the variable value at the corresponding position in the preset script template with the parameter variable to generate a target operation script, wherein the preset script template is used to perform an operation on the aerodynamic characteristic data, and the target operation script is a script obtained after batch replacement of the variable values ​​in the preset script template;

[0050] Step S104, using the target operation script and the target software to obtain processed aerodynamic characteristic data, wherein the target software is used to perform batch calculations on the aerodynamic characteristic data for characterizing the aircraft contained in the target operation script.

[0051] Optionally, the server of the embodiment of the present application can obtain a script template, and then record the script template, including the definition of boundary conditions, solution methods, monitoring data, output data, etc., and then obtain the parameter variables contained in the current running script, grid name, boundary conditions, reference length, torque reference point, etc., store these parameter variables in a preset list, such as an Excel table, and then use the target programming algorithm to batch read the parameter variables from the preset list. The target programming algorithm here is any programming method. Then for each calculation state, replace the corresponding variable value in the preset script template with the parameter variable read from the preset list (such as Excel), and then obtain the target running script. Use the loop command in programming to write out the batch settings in Excel at one time.

[0052] Using target software (such as CFD software), input the target operation script into the target software for batch calculation, obtain the calculated output result file, and use programming means to batch extract the processed aerodynamic characteristic data from the output result file (including component forces, moments, etc.), where the aerodynamic characteristic data includes aerodynamic characteristics such as aerodynamic force and moment coefficients, hinge moments, etc. of the entire arrow, the entire missile, and the entire aircraft. It should be noted that CFD software is used to perform batch calculations on the aerodynamic characteristic data used to characterize the aircraft contained in the target operation script.

[0053] In the embodiment of the present application, by obtaining the parameter variables contained in the current running script; using the target programming algorithm to batch read the parameter variables; replacing the variable values ​​at the corresponding positions in the preset script template with the parameter variables, a target running script is generated, wherein the preset script template is used to perform running operations on the aerodynamic characteristic data, and the target running script is a script obtained after batch replacing the variable values ​​in the preset script template; using the target running script and the target software, the processed aerodynamic characteristic data is obtained, wherein the target software is used to batch calculate the aerodynamic characteristic data for characterizing the aircraft contained in the target running script. Since the embodiment of the present application processes the aerodynamic characteristic data, the entire calculation setting, data extraction, analysis and batch processing process develops in the direction of standardization, process and automation, on the one hand, it greatly reduces the workload of aerodynamic engineers and increases work efficiency, and on the other hand, through standardization and process, it can avoid human operation errors and improve work quality, thereby solving the problem of manual adjustment existing in the related technology, resulting in large manual workload, low work efficiency and easy errors.

[0054] As an optional embodiment, after the target execution script is input into the target software, the method further includes:

[0055] Get the output file;

[0056] Use string functions to name the output files according to the calculation condition nouns to which they belong, and obtain the target output files corresponding to each calculation condition noun;

[0057] Based on each target output file, a data file after batch calculation is determined, wherein the data file includes an output result file after calculation and a convergence monitoring file after calculation.

[0058] Optionally, after batch processing using CFD software, an output file can be obtained. Then, the embodiment of the present application can name the output file using the grid name, altitude, Mach number, angle of attack, sideslip angle and other calculation condition nouns. Here, the relevant functions of string operations in the program can be used to distinguish file names. At this time, these files are called target output files. After that, based on the target output file, it is determined that a result file will be output after the calculation of each state is completed, as well as a convergence monitoring file after the calculation.

[0059] As an optional embodiment, after obtaining the processed aerodynamic characteristic data by using the target running script and the target software, the method further includes:

[0060] The target programming algorithm is used to batch obtain the aerodynamic force values ​​and moment coefficients determined in multiple preset directions from the convergence monitoring file;

[0061] The final convergence of the aerodynamic characteristic data is determined based on the aerodynamic force value, moment coefficient and number of iterations.

[0062] Optionally, when obtaining aerodynamic force values ​​and moment coefficients, the embodiments of the present application may collect values ​​from multiple preset directions, wherein the preset directions may be angle of attack, sideslip angle, rudder angle, etc. After obtaining aerodynamic force values ​​and moment coefficients, the final convergence of aerodynamic characteristic data is determined in combination with the number of iterations.

[0063] Among them, according to the aerodynamic force value, moment coefficient and iteration number, the final convergence of the aerodynamic characteristic data is determined as follows: the server first obtains the change curve of the aerodynamic force value and moment coefficient with the iteration number, and takes the axial force coefficient as an example to illustrate how to judge the convergence. First, the change of the axial force coefficient with the iteration number is plotted in batches to qualitatively judge the convergence.

[0064] Secondly, the program is used to find the maximum value of the aerodynamic force value and the moment coefficient, the minimum value of the aerodynamic force value and the moment coefficient, and the current convergence value on the change curve within the preset range of iterations (such as the last 10%). Based on the formula: The size of σ obtained is used to quantitatively judge the final convergence situation, where Cx in the formula max is the maximum value, Cx min is the minimum value, Cx 收敛 is the current convergence value.

[0065] In the embodiment of the present application, the convergence result obtained based on the above formula is the most effective, which can improve the efficiency of the pneumatic profession and greatly accelerate the model development progress in the early stage, while greatly improving work efficiency and quality.

[0066] It should be noted that, for the aforementioned method embodiments, for the sake of simplicity, they are all expressed as a series of action combinations, but those skilled in the art should be aware that the present application is not limited by the described order of actions, because according to the present application, certain steps can be performed in other orders or simultaneously. Secondly, those skilled in the art should also be aware that the embodiments described in the specification are all preferred embodiments, and the actions and modules involved are not necessarily required by the present application.

[0067] Through the description of the above implementation methods, those skilled in the art can clearly understand that the method according to the above embodiment can be implemented by means of software plus a necessary general hardware platform, and of course it can also be implemented by hardware, but in many cases the former is a better implementation method. Based on such an understanding, the technical solution of the present application, or the part that contributes to the prior art, can be embodied in the form of a software product, which is stored in a storage medium (such as ROM (Read-Only Memory) / RAM (Random Access Memory), a magnetic disk, or an optical disk), and includes a number of instructions for a terminal device (which can be a mobile phone, a computer, a server, or a network device, etc.) to execute the methods of each embodiment of the present application.

[0068] According to another aspect of the embodiments of the present application, there is also provided a device for processing aerodynamic characteristic data for implementing the above-mentioned method for processing aerodynamic characteristic data. Figure 2 is a structural block diagram of an optional aerodynamic characteristic data processing device according to an embodiment of the present application, such as Figure 2 As shown, the device may include:

[0069] A first acquisition unit 201 is used to acquire parameter variables contained in a currently running script;

[0070] A reading unit 202, used to read parameter variables in batches using a target programming algorithm;

[0071] A replacement unit 203 is used to replace the variable value at the corresponding position in the preset script template with the parameter variable to generate a target operation script, wherein the preset script template is used to perform an operation on the aerodynamic characteristic data, and the target operation script is a script obtained after batch replacement of the variable values ​​in the preset script template;

[0072] The first obtaining unit 204 is used to obtain processed aerodynamic characteristic data using the target operation script and the target software, wherein the target software is used to perform batch calculations on the aerodynamic characteristic data for characterizing the aircraft contained in the target operation script.

[0073] It should be noted that the first acquisition unit 201 in this embodiment can be used to execute the above step S101, the reading unit 202 in this embodiment can be used to execute the above step S102, the replacement unit 203 in this embodiment can be used to execute the above step S103, and the first obtaining unit 204 in this embodiment can be used to execute the above step S104.

[0074] Through the above modules, when processing aerodynamic characteristic data, the entire calculation setting, data extraction, analysis and batch processing process develops in the direction of standardization, process-based and automated. On the one hand, it greatly reduces the workload of pneumatic engineers and increases work efficiency. On the other hand, through standardization and process-based, it can avoid human operational errors and improve work quality, thereby solving the problem of manual adjustment existing in related technologies, resulting in large manual workload, low work efficiency and easy errors.

[0075] As an optional embodiment, the first obtaining unit includes:

[0076] Get module, used to input the target running script into the target software and get the output result file after calculation;

[0077] The extraction module is used to extract the processed aerodynamic characteristic data from the output result file.

[0078] As an optional embodiment, the device further includes:

[0079] A second acquisition unit is used to acquire an output file after inputting the target running script into the target software;

[0080] The second obtaining unit is used to name the output file by the calculation condition noun to which it belongs using the string function, and obtain the target output file corresponding to each calculation condition noun;

[0081] The first determination unit is used to determine the data files after batch calculation based on each target output file, wherein the data files include the output result files after calculation and the convergence monitoring files after calculation.

[0082] As an optional embodiment, the reading unit includes:

[0083] A storage module, used for storing parameter variables in a preset list;

[0084] The reading module is used to read parameter variables in batches from a preset list using a target programming algorithm.

[0085] As an optional embodiment, the device further includes:

[0086] A third acquisition unit is used to obtain the aerodynamic force values ​​and moment coefficients determined in multiple preset directions in batches from the convergence monitoring file using a target programming algorithm after obtaining the processed aerodynamic characteristic data using the target running script and the target software;

[0087] The second determining unit is used to determine the final convergence of the aerodynamic characteristic data according to the aerodynamic force value, the moment coefficient and the number of iterations.

[0088] As an optional embodiment, the second determining unit includes:

[0089] The first acquisition module is used to obtain the change curve of the aerodynamic force value and the moment coefficient with the number of iterations;

[0090] The second acquisition module is used to acquire the aerodynamic force value and the maximum value of the moment coefficient, the minimum value of the aerodynamic force value and the moment coefficient, and the current convergence value corresponding to the preset range of the iteration number based on the change curve;

[0091] The determination module is used to determine the final convergence of the aerodynamic characteristic data based on the maximum value, the minimum value and the current convergence value.

[0092] Optionally, the calculation formula for determining the module is:

[0093]

[0094] Among them, Cx max is the maximum value, Cx min is the minimum value, Cx 收敛 is the current convergence value.

[0095] According to another aspect of the embodiment of the present application, an electronic device for implementing the above-mentioned method for processing aerodynamic characteristic data is also provided. The electronic device may be a server, a terminal, or a combination thereof.

[0096] Figure 3 is a structural block diagram of an optional electronic device according to an embodiment of the present application, such as Figure 3As shown, it includes a processor 301, a communication interface 302, a memory 303 and a communication bus 304, wherein the processor 301, the communication interface 302 and the memory 303 communicate with each other through the communication bus 304, wherein,

[0097] Memory 303, used for storing computer programs;

[0098] The processor 301 is used to implement the following steps when executing the computer program stored in the memory 303:

[0099] Get the parameter variables contained in the currently running script;

[0100] Use target programming algorithms to batch read parameter variables;

[0101] The parameter variables are replaced with the variable values ​​at the corresponding positions in the preset script template to generate a target operation script, wherein the preset script template is used to perform operation operations on the aerodynamic characteristic data, and the target operation script is a script obtained after batch replacement of the variable values ​​in the preset script template;

[0102] The processed aerodynamic characteristic data are obtained by using the target operation script and the target software, wherein the target software is used to perform batch calculations on the aerodynamic characteristic data for characterizing the aircraft contained in the target operation script.

[0103] Optionally, in this embodiment, the communication bus may be a PCI (Peripheral Component Interconnect) bus or an EISA (Extended Industry Standard Architecture) bus. The communication bus may be divided into an address bus, a data bus, a control bus, etc. For ease of representation, Figure 3 Only one thick line is used in the diagram, but this does not mean that there is only one bus or only one type of bus.

[0104] The communication interface is used for communication between the above electronic device and other devices.

[0105] The memory may include RAM, or may include non-volatile memory, such as at least one disk memory. Optionally, the memory may also be at least one storage device located away from the aforementioned processor.

[0106] As an example, Figure 3As shown, the memory 303 may include, but is not limited to, the first acquisition unit 201, the reading unit 202, the replacement unit 203, and the first obtaining unit 204 in the aerodynamic characteristic data processing device. In addition, other module units in the aerodynamic characteristic data processing device may also be included but are not limited to, which will not be repeated in this example.

[0107] The above-mentioned processor can be a general-purpose processor, which can include but not be limited to: CPU (Central Processing Unit), NP (Network Processor), etc.; it can also be DSP (Digital Signal Processing), ASIC (Application Specific Integrated Circuit), FPGA (Field-Programmable Gate Array) or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components.

[0108] In addition, the electronic device mentioned above further comprises: a display for displaying the processing result of the aerodynamic characteristic data.

[0109] Optionally, the specific examples in this embodiment may refer to the examples described in the above embodiments, and this embodiment will not be described in detail here.

[0110] It can be understood by those skilled in the art that Figure 3 The structure shown is for illustration only. The device for implementing the above-mentioned method for processing aerodynamic characteristic data may be a terminal device, which may be a smart phone (such as an Android phone, an iOS phone, etc.), a tablet computer, a PDA, a mobile Internet device (Mobile Internet Devices, MID), a PAD, and other terminal devices. Figure 3 It does not limit the structure of the above electronic device. For example, the terminal device may also include Figure 3 More or fewer components (such as network interfaces, display devices, etc.) shown in, or having Figure 3 Different configurations shown.

[0111] A person of ordinary skill in the art can understand that all or part of the steps in the various methods of the above embodiments can be completed by instructing the hardware related to the terminal device through a program, and the program can be stored in a computer-readable storage medium, which can include: a flash drive, ROM, RAM, a magnetic disk or an optical disk, etc.

[0112] According to another aspect of the embodiment of the present application, a storage medium is also provided. Optionally, in this embodiment, the storage medium can be used to execute the program code of the method for processing aerodynamic characteristic data.

[0113] Optionally, in this embodiment, the storage medium may be located on at least one network device among a plurality of network devices in the network shown in the above embodiment.

[0114] Optionally, in this embodiment, the storage medium is configured to store program codes for executing the following steps:

[0115] Get the parameter variables contained in the currently running script;

[0116] Use target programming algorithms to batch read parameter variables;

[0117] The parameter variables are replaced with the variable values ​​at the corresponding positions in the preset script template to generate a target operation script, wherein the preset script template is used to perform operation operations on the aerodynamic characteristic data, and the target operation script is a script obtained after batch replacement of the variable values ​​in the preset script template;

[0118] The processed aerodynamic characteristic data are obtained by using the target operation script and the target software, wherein the target software is used to perform batch calculations on the aerodynamic characteristic data for characterizing the aircraft contained in the target operation script.

[0119] Optionally, the specific examples in this embodiment may refer to the examples described in the above embodiments, which will not be described in detail in this embodiment.

[0120] Optionally, in this embodiment, the storage medium may include, but is not limited to, various media that can store program codes, such as a USB flash drive, a ROM, a RAM, a mobile hard disk, a magnetic disk, or an optical disk.

[0121] According to another aspect of the embodiments of the present application, a computer program product or a computer program is also provided, which includes computer instructions, and the computer instructions are stored in a computer-readable storage medium; a processor of a computer device reads the computer instructions from the computer-readable storage medium, and the processor executes the computer instructions, so that the computer device executes the steps of the method for processing aerodynamic characteristic data in any of the above-mentioned embodiments.

[0122] The serial numbers of the above-mentioned embodiments of the present application are for description only and do not represent the advantages or disadvantages of the embodiments.

[0123] If the integrated units in the above embodiments are implemented in the form of software functional units and sold or used as independent products, they can be stored in the above computer-readable storage medium. Based on this understanding, the technical solution of the present application, or the part that contributes to the prior art, or all or part of the technical solution can be embodied in the form of a software product, which is stored in a storage medium and includes several instructions for enabling one or more computer devices (which can be personal computers, servers or network devices, etc.) to execute all or part of the steps of the method for processing aerodynamic characteristic data in each embodiment of the present application.

[0124] In the above embodiments of the present application, the description of each embodiment has its own emphasis. For parts that are not described in detail in a certain embodiment, please refer to the relevant description of other embodiments.

[0125] In the several embodiments provided in the present application, it should be understood that the disclosed client can be implemented in other ways. Among them, the device embodiments described above are only schematic, for example, the division of units is only a logical function division, and there may be other division methods in actual implementation, for example, multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed. Another point is that the mutual coupling or direct coupling or communication connection shown or discussed can be through some interfaces, indirect coupling or communication connection of units or modules, which can be electrical or other forms.

[0126] The units described as separate components may or may not be physically separated, and the components shown as units may or may not be physical units, that is, they may be located in one place or distributed on multiple network units. Some or all of the units may be selected according to actual needs to achieve the purpose of the solution provided in this embodiment.

[0127] In addition, each functional unit in each embodiment of the present application may be integrated into one processing unit, or each unit may exist physically separately, or two or more units may be integrated into one unit. The above-mentioned integrated unit may be implemented in the form of hardware or in the form of software functional units.

[0128] The above is only a preferred implementation of the present application. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principles of the present application. These improvements and modifications should also be regarded as the scope of protection of the present application.

Claims

1. A method for processing aerodynamic characteristic data, characterized in that: The method comprises: Get the parameter variables contained in the currently running script; Using a target programming algorithm to batch read the parameter variables; The parameter variable is used to replace the variable value at the corresponding position in the preset script template to generate a target operation script, wherein the preset script template is used to perform an operation on the aerodynamic characteristic data, and the target operation script is a script obtained after batch replacement of the variable values ​​in the preset script template; The target operation script and the target software are used to obtain the processed aerodynamic characteristic data, wherein the target software is used to perform batch calculations on the aerodynamic characteristic data for characterizing the aircraft contained in the target operation script, wherein the process of obtaining the processed aerodynamic characteristic data by using the target operation script and the target software includes: inputting the target operation script into the target software to obtain an output file; using a string function to name the output file according to the calculation condition noun to which it belongs, to obtain a target output file corresponding to each calculation condition noun; based on each target output file, determining a batch calculated data file, wherein the data file includes a calculated output result file and a calculated convergence monitoring file; extracting the processed aerodynamic characteristic data from the output result file; The target programming algorithm is used to batch-acquire the aerodynamic force values ​​and moment coefficients determined in multiple preset directions from the convergence monitoring file; The final convergence of the aerodynamic characteristic data is determined according to the aerodynamic force value, the moment coefficient and the number of iterations; wherein, the final convergence of the aerodynamic characteristic data is determined according to the aerodynamic force value, the moment coefficient and the number of iterations, including: obtaining a change curve of the aerodynamic force value and the moment coefficient along with the number of iterations; based on the change curve, obtaining the maximum values ​​of the aerodynamic force value and the moment coefficient corresponding to the preset range of the number of iterations, the minimum values ​​of the aerodynamic force value and the moment coefficient and the current convergence value; based on the maximum value, the minimum value and the current convergence value, the final convergence of the aerodynamic characteristic data is determined.

2. The method according to claim 1, characterized in that The batch reading of the parameter variables using the target programming algorithm comprises: Storing the parameter variables in a preset list; The parameter variables are read in batches from the preset list using the target programming algorithm.

3. The method according to claim 1, characterized in that The calculation formula for determining the final convergence of the aerodynamic characteristic data based on the maximum value, the minimum value and the current convergence value is: Among them, Cx max is the maximum value, Cx min is the minimum value, Cx 收敛 is the current convergence value.

4. A device for processing aerodynamic characteristic data, characterized in that: The device comprises: A first acquisition unit is used to acquire parameter variables contained in the currently running script; A reading unit, used for batch reading the parameter variables using a target programming algorithm; A replacement unit, used to replace the parameter variable with the variable value at the corresponding position in the preset script template, and generate a target operation script, wherein the preset script template is used to perform an operation on the aerodynamic characteristic data, and the target operation script is a script obtained after batch replacement of the variable values ​​in the preset script template; A first obtaining unit is used to obtain the processed aerodynamic characteristic data by using the target operation script and the target software, wherein the target software is used to perform batch calculations on the aerodynamic characteristic data for characterizing the aircraft contained in the target operation script; wherein the first obtaining unit includes: an obtaining module, used to input the target operation script into the target software; a second obtaining unit, used to obtain an output file after inputting the target operation script into the target software; a second obtaining unit, used to use a string function to name the output file according to the calculation condition noun to which it belongs, and obtain a target output file corresponding to each calculation condition noun; a first determining unit, used to determine a batch calculated data file based on each target output file, wherein the data file includes a calculated output result file and a calculated convergence monitoring file; an extraction module, used to extract the processed aerodynamic characteristic data from the output result file; A third acquisition unit is used for, after obtaining the processed aerodynamic characteristic data by using the target running script and the target software, batch acquiring the aerodynamic force values ​​and moment coefficients determined in multiple preset directions from the convergence monitoring file by using the target programming algorithm; A second determination unit is used to determine the final convergence of the aerodynamic characteristic data according to the aerodynamic force value, the moment coefficient and the number of iterations; wherein the second determination unit includes: a first acquisition module, used to obtain the change curve of the aerodynamic force value and the moment coefficient with the number of iterations; a second acquisition module, used to obtain the maximum value of the aerodynamic force value and the moment coefficient corresponding to the preset range of the iteration number, the minimum value of the aerodynamic force value and the moment coefficient and the current convergence value based on the change curve; a determination module, used to determine the final convergence of the aerodynamic characteristic data based on the maximum value, the minimum value and the current convergence value.

5. An electronic device comprising a processor, a communication interface, a memory and a communication bus, wherein: The processor, the communication interface and the memory communicate with each other via the communication bus, wherein: The memory is used to store computer programs; The processor is configured to execute the method steps described in any one of claims 1 to 3 by running the computer program stored in the memory.

6. A computer-readable storage medium, characterized in that: The storage medium stores a computer program, wherein the computer program implements the method steps described in any one of claims 1 to 3 when executed by a processor.

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