Method and device for generating aerodynamic model of aircraft and storage medium

Abstract

The invention discloses an aircraft aerodynamic model generation method and device and a storage medium. In the scheme, path information of a target folder is acquired; each sub-folder in the target folder comprises a plurality of interpolation table data files, and the interpolation table data files comprise variable information of a plurality of flight state variables corresponding to the aircraft and pneumatic data corresponding to each flight state variable; traversing the target folder based on the path information, sequentially obtaining variable information and pneumatic data corresponding to each interpolation table data file in each sub-folder, and creating an interpolation table module corresponding to the interpolation table data file based on the variable information and pneumatic data corresponding to each interpolation table data file; and creating a virtual subsystem according to each interpolation table module corresponding to each sub-folder, and generating a pneumatic model according to the virtual subsystem corresponding to each sub-folder. According to the technical scheme, the aerodynamic model of the aircraft is generated in an automatic mode, and the generation efficiency of the aerodynamic model is improved.

Description

Technical Field

[0001] The present application relates to the technical field of aerodynamics, and in particular to a method, device and storage medium for generating an aerodynamic model of an aircraft. Background Art

[0002] In the field of aeronautical engineering technology, the aerodynamic data of aircraft (such as lift, drag, lateral force, etc.) is crucial for evaluating the flight performance of aircraft. Aerodynamic data not only affects the design and optimization of aircraft, but also plays a key role in the development and verification of flight control systems.

[0003] At present, the existing technology usually uses an aircraft aerodynamic model to fit the aerodynamic coefficients of the aircraft under different flight conditions to evaluate the flight performance of the aircraft. However, the above-mentioned aircraft aerodynamic model often needs to be manually constructed, for example, by manually querying the aerodynamic data required to build the aerodynamic model, and manually creating the functional modules (such as input modules, interpolation table modules, etc.) that constitute the aerodynamic model to build the aerodynamic model. This not only increases the risk of introducing human errors, but also leads to the problem of low efficiency in generating the aerodynamic model due to the cumbersome manual modeling process. Summary of the invention

[0004] Based on the above problems, the present application provides a method, device and storage medium for generating an aircraft aerodynamic model, the purpose of which is to generate an aircraft aerodynamic model in an automated manner and improve the efficiency of generating the aerodynamic model.

[0005] The embodiments of the present application disclose the following technical solutions:

[0006] In a first aspect of the present application, a method for generating an aerodynamic model of an aircraft is provided, the method being applied to GCKontrol software, the method comprising:

[0007] Obtain path information of a target folder; the target folder includes multiple subfolders, each subfolder includes multiple interpolation table data files, the interpolation table data files in each subfolder correspond to the same type of rudder effect, the interpolation table data files include variable information of multiple flight state variables corresponding to the aircraft, and aerodynamic data corresponding to each flight state variable, and the variable information includes the number of variables and variable names;

[0008] Traversing the target folder based on the path information, obtaining the variable information and aerodynamic data corresponding to each interpolation table data file in each subfolder in turn, and creating an interpolation table module corresponding to the interpolation table data file based on the variable information and aerodynamic data corresponding to each interpolation table data file; the interpolation table module is used to fit the aerodynamic coefficients matching the input variables of the aerodynamic model based on the aerodynamic data;

[0009] A virtual subsystem is created according to each interpolation table module corresponding to each subfolder, and an aerodynamic model is generated according to the virtual subsystem corresponding to each subfolder; the aerodynamic model is used to fit the aerodynamic coefficients of the aircraft under different flight conditions.

[0010] In an optional implementation, the target folder is traversed based on the path information, the variable information and pneumatic data of each interpolation table data file in each subfolder are obtained in turn, and based on the variable information and pneumatic data corresponding to each interpolation table data file, an interpolation table module corresponding to the interpolation table data file is created, including:

[0011] Traverse the target folder based on the path information and obtain the directory information of the target folder;

[0012] Based on the directory information, each subfolder in the target folder and each interpolation table data file in the subfolder are traversed in turn to obtain variable information and pneumatic data corresponding to each interpolation table data file;

[0013] Based on the variable information and pneumatic data corresponding to each interpolation table data file, an interpolation table module corresponding to each interpolation table data file is created respectively.

[0014] In an optional implementation, before obtaining the path information of the target folder, the method further includes:

[0015] An input module and a Mux module are created based on the preset flight state variables; the Mux module is used to combine multiple input variables received by the input module into a single output signal;

[0016] Create connections between the input module and the Mux module.

[0017] In an optional implementation, a virtual subsystem is created according to each interpolation table module corresponding to the subfolder, including:

[0018] Based on the variable information of each interpolation table data file in the subfolder, a Demux module corresponding to the subfolder is created; the Demux module is used to decompose the output signal output by the Mux module into multiple input variables, and route the input variables to the matching interpolation table module;

[0019] Establish connections between the Demux modules and Mux modules corresponding to each subfolder;

[0020] Create output modules corresponding to each interpolation table module;

[0021] Establish connections between each interpolation table module and the Demux module, and establish connections between each interpolation table module and the corresponding output module;

[0022] The connected Demux modules, interpolation table modules and output modules are encapsulated as a virtual subsystem.

[0023] In an optional implementation, the aerodynamic model is generated according to the virtual subsystems corresponding to the subfolders, including:

[0024] Generate an aerodynamic model based on the connected input modules and Mux modules, as well as the virtual subsystems corresponding to each subfolder.

[0025] In a second aspect of the present application, a device for generating an aircraft aerodynamic model is provided, characterized in that the device is applied to GCKontrol software and comprises:

[0026] An acquisition module is used to acquire path information of a target folder; the target folder includes multiple subfolders, each subfolder includes multiple interpolation table data files, the interpolation table data files in each subfolder correspond to the same type of rudder effect, the interpolation table data files include variable information of multiple flight state variables corresponding to the aircraft, and aerodynamic data corresponding to each flight state variable, and the variable information includes the number of variables and variable names;

[0027] A creation module is used to traverse the target folder based on the path information, obtain the variable information and aerodynamic data corresponding to each interpolation table data file in each subfolder in turn, and create an interpolation table module corresponding to the interpolation table data file based on the variable information and aerodynamic data corresponding to each interpolation table data file; the interpolation table module is used to fit the aerodynamic coefficients matching the input variables of the aerodynamic model based on the aerodynamic data;

[0028] The model generation module is used to create a virtual subsystem based on the interpolation table modules corresponding to the subfolders, and to generate an aerodynamic model based on the virtual subsystems corresponding to the subfolders; the aerodynamic model is used to fit the aerodynamic coefficients of the aircraft under different flight conditions.

[0029] Optionally, creating a module includes:

[0030] A first acquisition unit, configured to traverse a target folder based on the path information to acquire directory information of the target folder;

[0031] A second acquisition unit, based on the directory information, sequentially traverses each subfolder in the target folder and each interpolation table data file in the subfolder to acquire variable information and pneumatic data corresponding to each interpolation table data file;

[0032] The first creation unit is used to create interpolation table modules corresponding to each interpolation table data file based on variable information and pneumatic data corresponding to each interpolation table data file.

[0033] Optionally, the model generation module includes:

[0034] The second creation unit is used to create a Demux module corresponding to the subfolder based on the variable information of each interpolation table data file in the subfolder; the Demux module is used to decompose the output signal output by the Mux module into multiple input variables, and route the input variables to the matching interpolation table module;

[0035] The first connection unit is used to establish a connection between the Demux module and the Mux module corresponding to each sub-folder;

[0036] A third creation unit is used to create output modules corresponding to each interpolation table module;

[0037] A second connection unit is used to establish a connection between each interpolation table module and the Demux module, and to establish a connection between each interpolation table module and the corresponding output module;

[0038] The encapsulation unit is used to encapsulate the connected Demux modules, various interpolation table modules and output modules into a virtual subsystem.

[0039] In a third aspect of the present application, a computer-readable storage medium is provided, in which a computer program is stored. When the computer program is executed by a processor, the above-mentioned method for generating an aerodynamic model of an aircraft is implemented.

[0040] In a fourth aspect of the present application, a processor is provided for running a computer program, and when the computer program is running, the above-mentioned method for generating an aerodynamic model of an aircraft is executed.

[0041] Compared with the prior art, this application has the following beneficial effects:

[0042] In the technical solution of the present application, firstly, the path information of the target folder is obtained; then, the target folder is traversed based on the path information, and the variable information and aerodynamic data corresponding to each interpolation table data file in each subfolder are obtained in turn, and based on the variable information and aerodynamic data corresponding to each interpolation table data file, an interpolation table module corresponding to the interpolation table data file is created, wherein the interpolation table module is used to fit the aerodynamic coefficients matching the input variables of the aerodynamic model based on the aerodynamic data; the variable information includes the number of variables and the variable name; finally, a virtual subsystem is created according to each interpolation table module corresponding to the subfolder, and an aerodynamic model is generated according to the virtual subsystem corresponding to each subfolder, wherein the aerodynamic model is used to fit the aerodynamic coefficients of the aircraft under different flight state conditions.

[0043] Through the technical solution of the present application, the target folder can be traversed based on the path information of the target folder, and the variable information of multiple flight state variables corresponding to the aircraft in each interpolation table data file in each subfolder and the aerodynamic data corresponding to each flight state variable can be automatically obtained, and the interpolation table module corresponding to the interpolation table data file can be created, without manually querying the aerodynamic data or manually creating the interpolation table module, which reduces the time-consuming manual query and input of aerodynamic data and manual creation of the interpolation table module, and improves the efficiency of creating the interpolation table module; since the interpolation table data files in each subfolder correspond to the same type of rudder effect, the virtual subsystem corresponding to the subfolder can be automatically created through each interpolation table module corresponding to the subfolder, and the aerodynamic model can be automatically generated according to the virtual subsystem corresponding to each subfolder, without manually creating the functional modules constituting the aerodynamic model, thereby realizing the generation of the aircraft aerodynamic model in an automated manner, and improving the generation efficiency of the aerodynamic model. In addition, through the technical solution of the present application, the risk of introducing human errors is reduced, and the accuracy and reliability of the generated aircraft aerodynamic model are improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0044] In order to more clearly illustrate the embodiments of the present application 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, 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 creative labor.

[0045] Figure 1 A flow chart of a method for generating an aircraft aerodynamic model provided in an embodiment of the present application;

[0046] Figure 2 A flowchart of another method for generating an aircraft aerodynamic model provided in an embodiment of the present application;

[0047] Figure 3 A schematic diagram of the structure of a pneumatic model provided in an embodiment of the present application;

[0048] Figure 4 A flowchart of a process of creating a virtual subsystem provided in an embodiment of the present application;

[0049] Figure 5 A schematic diagram of the structure of a device for generating an aerodynamic model of an aircraft provided in an embodiment of the present application. DETAILED DESCRIPTION

[0050] As described above, current aircraft aerodynamic models often need to be constructed manually, for example, by manually querying the aerodynamic data required to build the aerodynamic model, and manually creating functional modules that constitute the aerodynamic model (such as input modules, interpolation table modules, etc.). This not only increases the risk of introducing human errors, but also leads to low efficiency in generating aerodynamic models due to the cumbersome manual modeling process.

[0051] After research, the inventor proposed a method for generating an aircraft aerodynamic model. The method can realize the automatic modeling function of the aerodynamic model through Python code. Through GCControl software and Python API interface, the target folder can be traversed based on the path information of the target folder, and the variable information of multiple flight state variables corresponding to the aircraft in each interpolation table data file in each subfolder and the aerodynamic data corresponding to each flight state variable can be automatically obtained, and an interpolation table module corresponding to the interpolation table data file can be created. There is no need to manually query the aerodynamic data or manually create the interpolation table module, which reduces the time consumption of manually querying and inputting aerodynamic data and manually creating the interpolation table module, and improves the efficiency of creating the interpolation table module. Since the interpolation table data files in each subfolder correspond to the same type of rudder effect, the virtual subsystem corresponding to the subfolder can be automatically created through the interpolation table modules corresponding to the subfolder, and the aerodynamic model can be automatically generated according to the virtual subsystem corresponding to each subfolder, and there is no need to manually create the functional modules constituting the aerodynamic model, thereby realizing the generation of the aircraft aerodynamic model in an automated manner and improving the generation efficiency of the aerodynamic model. In addition, the technical solution of the present application reduces the risk of introducing human errors and improves the accuracy and reliability of the generated aircraft aerodynamic model.

[0052] 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 are within the scope of protection of this application.

[0053] Method Embodiment

[0054] An embodiment of the present application provides an embodiment of a method for generating an aerodynamic model of an aircraft. It should be noted that the steps shown in the flowchart of the accompanying drawings can be executed in a computer system such as a set of computer executable instructions, and although a logical order is shown in the flowchart, in some cases, the steps shown or described can be executed in an order different from that shown here.

[0055] See also Figure 1 , which is a flow chart of a method for generating an aircraft aerodynamic model provided by an embodiment of the present application. The method is applied to GCKontrol software, which is a graphical modeling and simulation tool that can realize system design and simulation, has rich control system modeling elements, supports control system modeling and simulation, linear and nonlinear system modeling and simulation, can automatically generate efficient and high-quality C code, supports FMU export, real-time simulation, automated testing and verification. Through GCKontrol software and pythonAPI interface, the automated modeling function of the aerodynamic model can be realized based on python code.

[0056] like Figure 1 As shown, the method comprises the following steps:

[0057] Step S101, obtaining the path information of the target folder.

[0058] In step S101, the target folder includes multiple subfolders, each subfolder includes multiple interpolation table data files, the interpolation table data files in each subfolder correspond to the same type of rudder effect, the interpolation table data files include variable information of multiple flight state variables corresponding to the aircraft, and aerodynamic data corresponding to each flight state variable, and the variable information includes the number of variables and variable names.

[0059] In this embodiment, the interpolation table data file includes interpolation table data composed of a large amount of aerodynamic data collected through experimental tests (such as wind tunnel tests and flight tests), wherein the flight state variables included in the interpolation table data file can be parameters corresponding to the aircraft, such as the angle of attack, sideslip angle, altitude, Mach number, elevator, left wing rudder, right wing rudder and aileron, which are used to evaluate the flight state and performance of the aircraft; the aerodynamic data corresponding to each flight state variable can be any one of parameters such as the lift coefficient cl, the drag coefficient cd, the side force coefficient cy, the pitch moment coefficient cm, the yaw moment coefficient cn, etc.

[0060] For example, each subfolder includes multiple interpolation table data files, which may be cl.csv and cy.csv respectively, wherein cl.csv may include four flight state variables, namely angle of attack, sideslip angle, altitude, and Mach number, as well as the vector length and vector breakpoints corresponding to the angle of attack, the vector length and vector breakpoints corresponding to the sideslip angle, the vector length and vector breakpoints corresponding to the altitude, the vector length and vector breakpoints corresponding to the Mach number, and the lift coefficients corresponding to the angle of attack, the sideslip angle, the altitude, and the Mach number respectively; cy.csv may include four flight state variables, namely angle of attack, sideslip angle, altitude, and Mach number, as well as the vector length and vector breakpoints corresponding to the angle of attack, the vector length and vector breakpoints corresponding to the sideslip angle, the vector length and vector breakpoints corresponding to the altitude, the vector length and vector breakpoints corresponding to the Mach number, and the side force coefficients corresponding to the angle of attack, the sideslip angle, the altitude, and the Mach number respectively.

[0061] In this embodiment, the interpolation table data files in each subfolder correspond to the same type of rudder effect. For example, the rudder effect corresponding to all the interpolation table data files in subfolder 1 is the elevator rudder effect, the rudder effect corresponding to all the interpolation table data files in subfolder 2 is the aileron rudder effect, and the rudder effect corresponding to all the interpolation table data files in subfolder 3 is the rudder effect.

[0062] It should be noted that by placing interpolation table data files with the same type of rudder effect in the same subfolder, it is possible to quickly and accurately read interpolation table data files with the same type of rudder effect, thereby reducing the time-consuming task of searching for interpolation table data files with the same type of rudder effect one by one from a large number of interpolation table data files, thereby providing data preparation for the automatic generation of an aerodynamic model to improve the generation efficiency of the aerodynamic model.

[0063] In order to improve the generation efficiency of the aerodynamic model, in this embodiment, before obtaining the path information of the target folder, the GCKontrol software can create an input module and a Mux module based on preset flight state variables, wherein the Mux module is used to merge multiple input variables received by the input module into a single output signal; and then establish a connection between the input module and the Mux module.

[0064] In this embodiment, the preset flight state variables are input variables of the pre-set aerodynamic model, and the preset flight state variables include but are not limited to the parameters corresponding to the aircraft such as the angle of attack, sideslip angle, altitude, Mach number, elevator, left rudder, right rudder and aileron used to evaluate the flight state and performance of the aircraft, which can be selected according to actual needs, so no specific limitation is made here. Figure 2As shown, the GCKontrol software can automatically create an input module of the aerodynamic model based on preset flight state variables, as well as a Mux module for merging multiple input variables received by the input module into a single output signal, and establish a connection between the input module and the Mux module. There is no need to manually create the input module and the Mux module, nor is there a need to manually establish a connection between the input module and the Mux module, thereby reducing the risk of introducing human errors and reducing the time spent on manually creating the input module and the Mux module and manually connecting the wires, thereby improving the efficiency of aerodynamic model generation, as well as the accuracy and reliability of the generated aircraft aerodynamic model.

[0065] Optionally, after creating the Mux module, the GCKontrol software can automatically update the parameters of the Mux module based on the names of the preset flight state variables. For example, the initial parameters of the Mux module are in1, in2, in3 and in4. After updating, the parameters of the Mux module are: in1 is updated to the angle of attack, in2 is updated to the sideslip angle, in3 is updated to the altitude, and in4 is updated to the Mach number.

[0066] Step S102, traverse the target folder based on the path information, obtain variable information corresponding to each interpolation table data file in each subfolder in turn, and create an interpolation table module corresponding to the interpolation table data file based on each interpolation table data file and the variable information corresponding to the interpolation table data file.

[0067] In step S102, the interpolation table module is used to fit aerodynamic coefficients that match the input variables of the aerodynamic model based on the interpolation table data file.

[0068] In order to improve the generation efficiency of the pneumatic model and avoid the problem of low generation efficiency of the pneumatic model due to manual query of pneumatic data and creation of interpolation table modules, in this embodiment, the GCKontrol software can traverse the target folder based on the path information, and automatically obtain the variable information corresponding to each interpolation table data file in each subfolder in turn, and automatically create an interpolation table module corresponding to the interpolation table data file based on each interpolation table data file and the variable information corresponding to the interpolation table data file. There is no need to manually query the pneumatic data or manually create the interpolation table module, thereby reducing the time spent on manually querying and inputting pneumatic data and manually creating the interpolation table module.

[0069] Specifically, the GCKontrol software can traverse the target folder based on the path information to obtain the directory information of the target folder; then, based on the directory information, it can traverse each subfolder in the target folder and each interpolation table data file in the subfolder in turn to obtain the variable information and pneumatic data corresponding to each interpolation table data file; finally, based on the variable information and pneumatic data corresponding to each interpolation table data file, it can create interpolation table modules corresponding to each interpolation table data file.

[0070] In this embodiment, if Figure 2 As shown, the GCKontrol software can traverse the target folder based on the path information, obtain the directory information of the target folder, and determine whether the currently accessed data is a subfolder through the directory information, so as to traverse the subfolders in the target folder and the interpolation table data files in the subfolder in turn; specifically, if the currently accessed data is a subfolder, continue to traverse the target folder, and if the currently accessed data is an interpolation table data file in a subfolder, traverse the interpolation table data file in the subfolder to obtain the variable information and pneumatic data corresponding to the interpolation table data file; finally, the GCKontrol software can create interpolation table modules corresponding to each interpolation table data file based on the variable information and pneumatic data corresponding to each interpolation table data file. For example, the subfolder includes interpolation table data files such as cl.csv, cd.csv, cm.csv and cy.csv. The GCKontrol software can create an interpolation table module corresponding to cl.csv, an interpolation table module corresponding to cd.csv, an interpolation table module corresponding to cm.csv and an interpolation table module corresponding to cy.csv based on the variable information and pneumatic data in cl.csv, cd.csv, cm.csv and cy.csv respectively.

[0071] Optionally, after creating an interpolation table module corresponding to the interpolation table data file, the variable name corresponding to the interpolation table data file can be set as the interpolation table module input parameter, and the type of aerodynamic data (such as lift coefficient, drag coefficient, etc.) can be set as the interpolation table module output parameter.

[0072] It should be noted that, by automatically traversing each subfolder in the target folder and each interpolation table data file in the subfolder based on the directory information, the variable information and aerodynamic data corresponding to each interpolation table data file are obtained, and the interpolation table modules corresponding to each interpolation table data file are automatically created based on the variable information and the aerodynamic data. There is no need to manually query the aerodynamic data or manually create the interpolation table module, which reduces the time spent on manually querying and inputting aerodynamic data and manually creating the interpolation table module, reduces the risk of introducing human errors, and thus improves the generation efficiency of the aerodynamic model as well as the accuracy and reliability of the generated aircraft aerodynamic model.

[0073] Step S103, creating a virtual subsystem according to each interpolation table module corresponding to the subfolder, and generating an aerodynamic model according to the virtual subsystem corresponding to each subfolder.

[0074] In step S103, the aerodynamic model is used to fit the aerodynamic coefficients of the aircraft under different flight conditions.

[0075] In order to improve the efficiency of generating the aerodynamic model, in this embodiment, the GCKontrol software can automatically create the interpolation table modules corresponding to the subfolders. Figure 3 The virtual subsystem shown in the figure is automatically generated based on the virtual subsystems corresponding to each subfolder, the input modules and the Mux modules after wiring. Figure 3 The aerodynamic model shown in . Figure 3 The pneumatic model shown includes an input module, a Mux module, a virtual subsystem 1 and a virtual subsystem 2, wherein the virtual subsystem 1 and the virtual subsystem 2 respectively include a Demux module, a plurality of interpolation table modules and a corresponding output module. The connection relationship between the modules can be shown as follows: Figure 3 shown.

[0076] Specifically, see Figure 4 , Figure 4 A flowchart of a process of creating a virtual subsystem provided in an embodiment of the present application, the process includes the following steps:

[0077] Step S401: based on the variable information of each interpolation table data file in the subfolder, create a Demux module corresponding to the subfolder.

[0078] In step S401, the Demux module is used to decompose the output signal output by the Mux module into multiple input variables, and route the input variables to the matching interpolation table module.

[0079] In this embodiment, each subfolder corresponds to a Demux module. For example, the rudder effect corresponding to all interpolation table data files in subfolder 1 is the elevator rudder effect, and the variable information of each interpolation table data file: the number of variables is 4, and the variable names are angle of attack, sideslip angle, altitude, and Mach number. The GCKontrol software can create a Demux module of 4-dimensional variables corresponding to subfolder 1.

[0080] Step S402: Establish connections between the Demux modules and the Mux modules corresponding to each sub-folder.

[0081] Step S403: Create output modules corresponding to each interpolation table module.

[0082] Step S404: Establish a connection between each interpolation table module and the Demux module, and establish a connection between each interpolation table module and the corresponding output module.

[0083] Step S405: encapsulate the connected Demux module, each interpolation table module and the output module into a virtual subsystem.

[0084] In this embodiment, the GCKontrol software can automatically create Demux modules corresponding to subfolders and output modules corresponding to each interpolation table module based on the variable information of each interpolation table data file, and automatically establish connections between the Demux modules and Mux modules corresponding to each subfolder, establish connections between each interpolation table module and the Demux module, and establish connections between each interpolation table module and the corresponding output modules. There is no need to manually create the functional modules that constitute the aerodynamic model, nor to manually establish connections between the modules, which reduces the time consumption of manual operations and reduces the risk of introducing human errors, thereby improving the generation efficiency of the aerodynamic model and the accuracy and reliability of the generated aircraft aerodynamic model.

[0085] Furthermore, if Figure 2 As shown, the GCKontrol software can determine whether to generate a pneumatic model based on the virtual subsystems corresponding to each subfolder by judging whether there are unvisited subfolders in the target folder; if there are no unvisited subfolders in the target folder, the GCKontrol software can automatically generate a pneumatic model based on the virtual subsystems corresponding to each subfolder, the connected input modules and the Mux modules. If there are unvisited subfolders in the target folder, the interpolation table data files in the unvisited subfolders will continue to be traversed until there are no unvisited subfolders in the target folder.

[0086] Through the method for generating an aircraft aerodynamic model provided by the embodiment of the present application, it is realized to traverse the target folder based on the path information of the target folder, automatically obtain the variable information of multiple flight state variables corresponding to the aircraft in each interpolation table data file in each subfolder, and the aerodynamic data corresponding to each flight state variable, and create an interpolation table module corresponding to the interpolation table data file, without manually querying the aerodynamic data, and without manually creating the interpolation table module, reducing the time-consuming of manually querying and inputting aerodynamic data and manually creating the interpolation table module, and improving the efficiency of creating the interpolation table module; since the interpolation table data files in each subfolder correspond to the same type of rudder effect, through each interpolation table module corresponding to the subfolder, the virtual subsystem corresponding to the subfolder can be automatically created, and the aerodynamic model is automatically generated according to the virtual subsystem corresponding to each subfolder, without manually creating the functional modules constituting the aerodynamic model, thereby realizing the generation of the aircraft aerodynamic model in an automated manner, and improving the generation efficiency of the aerodynamic model. In addition, through the method for generating an aircraft aerodynamic model provided by the embodiment of the present application, the risk of introducing human errors is reduced, and the accuracy and reliability of the generated aircraft aerodynamic model are improved.

[0087] Device Embodiment

[0088] The embodiment of the present application provides a device for generating an aerodynamic model of an aircraft, wherein: Figure 5 A schematic diagram of a device for generating an aerodynamic model of an aircraft provided in an embodiment of the present application is shown in FIG. Figure 5 As shown, the device includes: an acquisition module 11, a creation module 12 and a model generation module 13. Figure 5 You can see the connection relationship between several modules.

[0089] The acquisition module 11 is used to acquire the path information of the target folder; the target folder includes multiple subfolders, each subfolder includes multiple interpolation table data files, the interpolation table data files in each subfolder correspond to the same type of rudder effect, the interpolation table data files include variable information of multiple flight state variables corresponding to the aircraft, and aerodynamic data corresponding to each flight state variable, and the variable information includes the number of variables and variable names;

[0090] A creation module 12 is used to traverse the target folder based on the path information, sequentially obtain the variable information and aerodynamic data corresponding to each interpolation table data file in each subfolder, and create an interpolation table module corresponding to the interpolation table data file based on the variable information and aerodynamic data corresponding to each interpolation table data file; the interpolation table module is used to fit the aerodynamic coefficients matching the input variables of the aerodynamic model based on the aerodynamic data;

[0091] The model generation module 13 is used to create a virtual subsystem according to each interpolation table module corresponding to the subfolder, and to generate an aerodynamic model according to the virtual subsystem corresponding to each subfolder; the aerodynamic model is used to fit the aerodynamic coefficients of the aircraft under different flight conditions.

[0092] Optionally, the creation module includes: a first acquisition unit, a second acquisition unit and a first creation unit.

[0093] The first acquisition unit is used to traverse the target folder based on the path information to acquire the directory information of the target folder;

[0094] A second acquisition unit, based on the directory information, sequentially traverses each subfolder in the target folder and each interpolation table data file in the subfolder to acquire variable information and pneumatic data corresponding to each interpolation table data file;

[0095] The first creation unit is used to create interpolation table modules corresponding to each interpolation table data file based on variable information and pneumatic data corresponding to each interpolation table data file.

[0096] Optionally, the model generation module includes: a second creation unit, a first connection unit, a third creation unit, a second connection unit and an encapsulation unit.

[0097] The second creation unit is used to create a Demux module corresponding to the subfolder based on the variable information of each interpolation table data file in the subfolder; the Demux module is used to decompose the output signal output by the Mux module into multiple input variables, and route the input variables to the matching interpolation table module;

[0098] The first connection unit is used to establish a connection between the Demux module and the Mux module corresponding to each sub-folder;

[0099] A third creation unit is used to create output modules corresponding to each interpolation table module;

[0100] A second connection unit is used to establish a connection between each interpolation table module and the Demux module, and to establish a connection between each interpolation table module and the corresponding output module;

[0101] The encapsulation unit is used to encapsulate the connected Demux modules, various interpolation table modules and output modules into a virtual subsystem.

[0102] Optionally, the device for generating the aircraft aerodynamic model further comprises:

[0103] The fourth creation unit is used to create an input module and a Mux module based on a preset flight state variable before obtaining the path information of the target folder; the Mux module is used to merge multiple input variables received by the input module into a single output signal;

[0104] The third connection unit is used to establish a connection between the input module and the Mux module.

[0105] Optionally, the model generation module further includes: a model generation unit, which is used to generate an aerodynamic model based on the connected input module and Mux module, and the virtual subsystems corresponding to each subfolder.

[0106] Storage Medium Embodiments

[0107] The embodiment of the present application provides a computer-readable storage medium, on which a program is stored, wherein when the program is executed by a processor, some or all of the steps in the method for generating an aircraft aerodynamic model described in the aforementioned method embodiment of the present application are implemented. The storage medium can be a U disk, a mobile hard disk, a read-only memory (ROM), a random access memory (RAM), a magnetic disk or an optical disk, and other media that can store program codes.

[0108] Processor Embodiments

[0109] An embodiment of the present application provides a processor for running a program, wherein when the program is running, some or all of the steps in the method for generating an aircraft aerodynamic model introduced in the aforementioned method embodiment are executed.

[0110] It should be noted that each embodiment in this specification is described in a progressive manner, and the same or similar parts between the embodiments can be referred to each other, and each embodiment focuses on the differences from other embodiments. In particular, for the device embodiment, since it is basically similar to the method embodiment, the description is relatively simple, and the relevant parts can be referred to the partial description of the method embodiment. The device embodiment described above is merely schematic, in which the unit described as a separate component may or may not be physically separated, and the component prompted as a unit may or may not be a physical unit, that is, it may be located in one place, or it may be distributed on multiple network units. Some or all of the modules can be selected according to actual needs to achieve the purpose of the scheme of this embodiment. Ordinary technicians in this field can understand and implement it without paying creative work.

[0111] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application should be based on the protection scope of the claims.

Claims

1. A method for generating an aircraft aerodynamic model, characterized in that: Applied to GCKontrol software, the method comprises: Acquire path information of a target folder; the target folder includes multiple subfolders, each of the subfolders includes multiple interpolation table data files, the interpolation table data files in each subfolder correspond to the same type of rudder effect, the interpolation table data files include variable information of multiple flight state variables corresponding to the aircraft, and aerodynamic data corresponding to each flight state variable, the variable information includes the number of variables and variable names; Traversing the target folder based on the path information, sequentially acquiring the variable information and the aerodynamic data corresponding to each of the interpolation table data files in each of the subfolders, and creating an interpolation table module corresponding to the interpolation table data file based on the variable information and the aerodynamic data corresponding to each of the interpolation table data files; the interpolation table module is used to fit the aerodynamic coefficients that match the input variables of the aerodynamic model based on the aerodynamic data; A virtual subsystem is created according to each of the interpolation table modules corresponding to the subfolders, and the aerodynamic model is generated according to the virtual subsystems corresponding to each of the subfolders; the aerodynamic model is used to fit the aerodynamic coefficients of the aircraft under different flight conditions.

2. The method according to claim 1, characterized in that The traversing the target folder based on the path information, sequentially acquiring the variable information and the pneumatic data corresponding to each of the interpolation table data files in each of the subfolders, and creating an interpolation table module corresponding to the interpolation table data file based on the variable information and the pneumatic data corresponding to each of the interpolation table data files, includes: Traversing the target folder based on the path information to obtain directory information of the target folder; Based on the directory information, traverse each of the subfolders in the target folder and each of the interpolation table data files in the subfolder in turn to obtain variable information and the pneumatic data corresponding to each of the interpolation table data files; Based on the variable information corresponding to each of the interpolation table data files and the pneumatic data, interpolation table modules corresponding to each of the interpolation table data files are created respectively.

3. The method according to claim 2, characterized in that Before obtaining the path information of the target folder, the method further includes: An input module and a Mux module are created based on preset flight state variables; the Mux module is used to merge the multiple input variables received by the input module into a single output signal; Establish a connection between the input module and the Mux module.

4. The method according to claim 3, characterized in that The step of creating a virtual subsystem according to each of the interpolation table modules corresponding to the subfolders includes: Based on the variable information of each of the interpolation table data files in the subfolder, a Demux module corresponding to the subfolder is created; the Demux module is used to decompose the output signal output by the Mux module into a plurality of the input variables, and route the input variables to a matching interpolation table module; Establishing a connection between the Demux module corresponding to each of the sub-folders and the Mux module; Creating output modules corresponding to each of the interpolation table modules; Establishing a connection between each of the interpolation table modules and the Demux module, and establishing a connection between each of the interpolation table modules and the corresponding output module; The connected Demux module, each of the interpolation table modules and the output module are encapsulated as the virtual subsystem.

5. The method according to claim 4, characterized in that Generating the aerodynamic model according to the virtual subsystems corresponding to the subfolders includes: The aerodynamic model is generated based on the connected input module and the Mux module, and the virtual subsystems corresponding to the subfolders.

6. A device for generating an aerodynamic model of an aircraft, characterized in that: Applied to GCKontrol software, the device comprises: an acquisition module, used for acquiring path information of a target folder; the target folder includes a plurality of subfolders, each of the subfolders includes a plurality of interpolation table data files, the interpolation table data files in each subfolder correspond to the same type of rudder effect, the interpolation table data files include variable information of a plurality of flight state variables corresponding to the aircraft, and aerodynamic data corresponding to each flight state variable, the variable information includes the number of variables and variable names; A creation module, used for traversing the target folder based on the path information, sequentially acquiring the variable information and the aerodynamic data corresponding to each of the interpolation table data files in each of the subfolders, and creating an interpolation table module corresponding to the interpolation table data file based on the variable information and the aerodynamic data corresponding to each of the interpolation table data files; the interpolation table module is used for fitting aerodynamic coefficients that match the input variables of the aerodynamic model based on the aerodynamic data; A model generation module is used to create a virtual subsystem based on each of the interpolation table modules corresponding to the subfolders, and to generate the aerodynamic model based on the virtual subsystems corresponding to each of the subfolders; the aerodynamic model is used to fit the aerodynamic coefficients of the aircraft under different flight conditions.

7. The device according to claim 6, characterized in that The creation module includes: A first acquisition unit, configured to traverse a target folder based on the path information to acquire directory information of the target folder; A second acquisition unit, based on the directory information, sequentially traverses each of the subfolders in the target folder and each of the interpolation table data files in the subfolder to acquire variable information and the pneumatic data corresponding to each of the interpolation table data files; The first creation unit is used to create interpolation table modules corresponding to each of the interpolation table data files based on the variable information corresponding to each of the interpolation table data files and the pneumatic data.

8. The device according to claim 7, characterized in that The model generation module includes: A second creation unit is used to create a Demux module corresponding to the subfolder based on the variable information of each of the interpolation table data files in the subfolder; the Demux module is used to decompose the output signal output by the Mux module into a plurality of the input variables, and route the input variables to a matching interpolation table module; A first connection unit, used for establishing a connection between the Demux module corresponding to each of the sub-folders and the Mux module; A third creation unit, used to create output modules corresponding to each of the interpolation table modules; A second connection unit, used to establish a connection between each of the interpolation table modules and the Demux module, and to establish a connection between each of the interpolation table modules and a corresponding output module; The encapsulation unit is used to encapsulate the connected Demux module, each of the interpolation table modules and the output module into the virtual subsystem.

9. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores a computer program, and when the computer program is executed by a processor, the method for generating an aircraft aerodynamic model according to any one of claims 1 to 5 is implemented.

10. A processor, characterized in that: Used to run a computer program, which, when running, executes the method for generating an aircraft aerodynamic model according to any one of claims 1 to 5.

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