Unmanned aerial vehicle component aerodynamic force extraction method, device, equipment and medium

Abstract

The invention provides an unmanned aerial vehicle component aerodynamic force extraction method, device and equipment and a medium, relates to the technical field of aircraft pneumatic calculation, and is used for solving the problem that the unmanned aerial vehicle component aerodynamic force extraction efficiency is low. The method comprises the following steps: acquiring numerical simulation results of the unmanned aerial vehicle under different control plane deflection angles and different flight states; the unmanned aerial vehicle comprises a plurality of parts; the numerical simulation result comprises surface pressure data of a plurality of components; according to a first type of parameter values input by a user, extracting first surface pressure data of a target part in the multiple parts from the numerical simulation calculation result; wherein the first type of parameter values comprise values of component characteristic parameters, and the component characteristic parameters are used for indicating the aerodynamic configuration of the target component; and performing interpolation integration on the first surface pressure data to obtain aerodynamic data of the target component. And through a parameterized universal extraction program, the participation threshold of professionals is effectively reduced, and the extraction efficiency of the aerodynamic force of the unmanned aerial vehicle component is improved.

Description

Technical Field

[0001] This application relates to the technical field of aircraft aerodynamic calculation, and provides a method, device, equipment and medium for extracting aerodynamic forces of UAV components. Background Technique

[0002] The flight load of a UAV is the basis for the structural design and strength check of the UAV. The accuracy of the flight load calculation directly determines the accuracy of the strength analysis and the reliability of the structural design. Precise flight load calculation is beneficial to reducing the structural design weight of the UAV and improving the economy of UAV use. And the aerodynamic force of the component is the original data for the flight load calculation and check. The quality of the original data processing is directly related to the reliability of the flight load calculation.

[0003] Currently, there is no general engineering calculation method for calculating the aerodynamic forces of UAV components. For UAVs with different aerodynamic configurations, a large amount of original data needs to be manually processed by staff each time of calculation, and the aerodynamic force calculation program needs to be written or changed. The data processing method is cumbersome, resulting in low extraction efficiency of component aerodynamic force data. Summary of the Invention

[0004] This application provides a method, device, equipment and medium for extracting aerodynamic forces of UAV components, which is used to solve the problem of low extraction efficiency of aerodynamic forces of UAV components.

[0005] In a first aspect, a method for extracting aerodynamic forces of UAV components is provided, including:

[0006] Obtaining numerical simulation results of the UAV at different rudder surface deflection angles and different flight states; the UAV includes multiple components; the numerical simulation results include surface pressure data of the multiple components;

[0007] According to the first type of parameter values input by the user, extracting first surface pressure data of a target component among the multiple components from the numerical simulation calculation results; wherein, the first type of parameter values includes the values of component characteristic parameters, and the component characteristic parameters are used to indicate the aerodynamic shape of the target component;

[0008] Performing interpolation integration on the first surface pressure data to obtain aerodynamic force data of the target component.

[0009] Optionally, the obtaining numerical simulation results of the UAV at different rudder surface deflection angles and different flight states includes:

[0010] Storing the numerical simulation results of the UAV at different rudder surface deflection angles and different flight states into a target folder;

[0011] According to the path of the target folder input by the user, obtaining the numerical simulation results from the target folder.

[0012] Optionally, extracting the first surface pressure data of the target component among the multiple components from the numerical simulation calculation results according to the first type of parameter values input by the user includes:

[0013] Generating an extraction file according to the first type of parameter values input by the user; the component characteristic parameters include the starting coordinate of the component, the ending coordinate of the component, the section spacing, the number of components, and the component serial number;

[0014] By running the extraction file, extracting the first surface pressure data of the target component among the multiple components from the numerical simulation calculation results.

[0015] Optionally, the first surface pressure data is the surface pressure data in the full-aircraft coordinate system; performing interpolation integration on the first surface pressure data to obtain the aerodynamic force data of the target component includes:

[0016] Establishing a local coordinate system of the target component according to the second type of parameter values input by the user; the second type of parameter values includes the value of the component angle parameter and the origin coordinate of the local coordinate system; the component angle parameter is used to indicate the relative angle of the target component in the full-aircraft coordinate system;

[0017] Performing coordinate transformation on the first surface pressure data to obtain the second surface pressure data in the local coordinate system of the target component;

[0018] Performing interpolation integration on the second surface pressure data to obtain the aerodynamic force data of the target component.

[0019] Optionally, performing coordinate transformation on the first surface pressure data to obtain the second surface pressure data in the local coordinate system of the target component includes:

[0020] Translating the origin of the full-aircraft coordinate system to the origin of the local coordinate system to obtain an intermediate coordinate system;

[0021] Performing translation on the first surface pressure data to obtain the third surface pressure data in the intermediate coordinate system;

[0022] The third surface pressure data is successively rotated by a first Euler angle about the Z-axis of the intermediate coordinate system, a second Euler angle about the Y-axis of the intermediate coordinate system, and a third Euler angle about the X-axis of the intermediate coordinate system to obtain the second surface pressure data in the local coordinate system of the target component; wherein, the first Euler angle is the relative angle between the Z-axis of the intermediate coordinate system and the Z-axis of the local coordinate system; the second Euler angle is the relative angle between the Y-axis of the intermediate coordinate system and the Y-axis of the local coordinate system; the third Euler angle is the relative angle between the X-axis of the intermediate coordinate system and the X-axis of the local coordinate system.

[0023] Optionally, the interpolating and integrating the second surface pressure data to obtain the aerodynamic force data of the target component includes:

[0024] Performing linear interpolation on the second surface pressure data within each section to obtain interpolation data;

[0025] Performing numerical integration on the interpolation data to obtain the aerodynamic force data of the target component.

[0026] Optionally, the component angle parameters include dihedral angle, installation angle, control surface deflection angle, and sweep angle.

[0027] In a second aspect, there is provided an aerodynamic force extraction device for an unmanned aerial vehicle component, including:

[0028] An acquisition module, configured to acquire numerical simulation results of the unmanned aerial vehicle under different control surface deflection angles and different flight states; the unmanned aerial vehicle includes a plurality of components; the numerical simulation results include surface pressure data of the plurality of components;

[0029] An extraction module, configured to extract first surface pressure data of a target component among the plurality of components from the numerical simulation calculation results according to a first type of parameter value input by a user; wherein, the first type of parameter value includes values of component characteristic parameters, and the component characteristic parameters are used to indicate the aerodynamic shape of the target component;

[0030] An obtaining module, configured to perform interpolating and integrating on the first surface pressure data to obtain the aerodynamic force data of the target component.

[0031] In a third aspect, the present application provides a computer device, which includes a memory and a processor, a computer program is stored in the memory, and the processor executes the computer program to implement the method for extracting the aerodynamic force of an unmanned aerial vehicle component described in the first aspect.

[0032] Fourthly, the present application provides a computer-readable storage medium, on which a computer program is stored, and a processor executes the computer program to implement the method for extracting aerodynamic forces of drone components described in the first aspect.

[0033] Compared with the prior art, the beneficial effects of the present application are as follows:

[0034] The present application provides a method for extracting aerodynamic forces of drone components, and the method includes: obtaining numerical simulation results of the drone under different rudder surface deflection angles and different flight states; the drone includes multiple components; the numerical simulation results include surface pressure data of multiple components; according to the first type of parameter values input by the user, extracting the first surface pressure data of the target component among multiple components from the numerical simulation calculation results; wherein, the first type of parameter values includes the values of component characteristic parameters, and the component characteristic parameters are used to indicate the aerodynamic shape of the target component; performing interpolation integration on the first surface pressure data to obtain the aerodynamic force data of the target component. Through a parameterized and general extraction program, the user only needs to input the key parameters of the target component of the drone, and then can quickly complete the batch extraction of the aerodynamic force data of the target component, effectively reducing the participation threshold of professionals and improving the extraction efficiency of the aerodynamic forces of drone components. Description of the Drawings

[0035] In order to more clearly illustrate the technical solutions in the embodiments of the present application or related technologies, the following will briefly introduce the drawings required for use in the description of the embodiments or related technologies. Obviously, the drawings in the following description are only the embodiments of the present application. For those of ordinary skill in the art, other drawings can also be obtained according to the provided drawings without creative efforts.

[0036] Figure 1 Schematic diagram of the computer device structure of the hardware operating environment related to the solution of the embodiment of the present application;

[0037] Figure 2 Schematic flowchart of a method for extracting aerodynamic forces of drone components provided by an embodiment of the present application;

[0038] Figure 3 Schematic diagram of a program interface provided by an embodiment of the present application;

[0039] Figure 4 Schematic diagram of another program interface provided by an embodiment of the present application;

[0040] Figure 5 Another schematic flowchart of the method for extracting aerodynamic forces of drone components provided by an embodiment of the present application;

[0041] Figure 6This is a schematic structural diagram of an aerodynamic force extraction device for a drone component provided by an embodiment of the present application.

[0042] Reference signs in the figure: 101 - processor, 102 - communication bus, 103 - network interface, 104 - user interface, 105 - memory. Detailed implementation manners

[0043] To make the objectives, technical solutions, and advantages of the present application clearer and more understandable, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all of the embodiments. Based on the embodiments of the present application, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the scope of protection of the present application. Without conflict, the embodiments in the present application and the features in the embodiments may be combined with each other arbitrarily. And although the logical order is shown in the flowchart, in some cases, the steps shown or described may be executed in a different order than here.

[0044] To improve the extraction efficiency of the aerodynamic force of drone components, an embodiment of the present application provides a method for extracting the aerodynamic force of drone components. First, the hardware operating environment related to the solution of the embodiment of the present application will be introduced below.

[0045] Please refer to Figure 1 , which is a schematic structural diagram of a computer device for the hardware operating environment related to the solution of the embodiment of the present application.

[0046] As Figure 1 shown, the computer device may include: a processor 101, such as a central processing unit (CPU), a communication bus 102, a user interface 104, a network interface 103, and a memory 105. Among them, the communication bus 102 is used to realize the connection and communication between these components. The user interface 104 may include a display screen (Display) and an input unit such as a keyboard (Keyboard). Optionally, the user interface 104 may further include a standard wired interface and a wireless interface. The network interface 103 may optionally include a standard wired interface and a wireless interface (such as a wireless fidelity (WI-FI) interface). The memory 105 may be a high-speed random access memory (Random Access Memory, RAM) or a stable non-volatile memory (Non-Volatile Memory, NVM), such as a disk memory. Optionally, the memory 105 may also be a storage device independent of the aforementioned processor 101.

[0047] Those skilled in the art can understand,Figure 1 The structure shown does not constitute a limitation on the computer device, and may include more or fewer components than shown, or combine certain components, or have a different component arrangement.

[0048] As Figure 1 shown, the memory 105, as a storage medium, may include an operating system, a network communication module, a user interface module, and an aerodynamic force extraction device for drone components.

[0049] In Figure 1 the computer device shown, the network interface 103 is mainly used for data communication with a network server; the user interface 104 is mainly used for data interaction with a user; the processor 101 and the memory 105 in the computer device of the present invention may be provided in the computer device, and the computer device calls the aerodynamic force extraction device for drone components stored in the memory 105 through the processor 101 and executes the aerodynamic force extraction method for drone components provided in the embodiments of the present application.

[0050] Based on the computer device of the foregoing embodiments, a method for extracting aerodynamic forces of drone components provided in the embodiments of the present application will be introduced below in conjunction with Figure 2 this.

[0051] S201. Obtain the numerical simulation results of the drone under different rudder surface deflection angles and different flight states.

[0052] In a specific implementation process, first, determine the geometric model of the drone, including the geometric parameters of the rudder surface. Then, determine the fluid inlet conditions (such as speed, aerodynamic parameters, etc.) for each flight state, and set different rudder surface deflection angles, including positive and negative deflection angle ranges. Next, configure the fluid dynamics solver, select appropriate numerical methods and boundary conditions to ensure that the movement of the fluid can be accurately simulated. Finally, run the fluid dynamics solver for numerical simulation for each combination (deflection angle and flight state) to obtain the numerical simulation results of the drone. Among them, the drone includes multiple components, such as a fuselage, a tail wing, a wing, etc.; the numerical simulation results include the serial number of each component and the surface pressure data of each component.

[0053] Furthermore, the numerical simulation results of drones with different aerodynamic configurations can be stored in a specified folder. Without the user inputting the folder path, the user can directly obtain the numerical simulation results of drones with all aerodynamic configurations from the specified folder according to the default folder path.

[0054] In order to improve the search efficiency, in a possible embodiment, the numerical simulation results of unmanned aerial vehicles (UAVs) with different aerodynamic configurations can be stored in different folders, and the numerical simulation results of the UAV at different control surface deflection angles and different flight states can be stored in the target folder; according to the path of the target folder input by the user, the numerical simulation results are obtained from the target folder.

[0055] In the embodiment of the present application, the numerical simulation results of a UAV with a certain aerodynamic configuration are stored in the target folder. When the user inputs the path of the target folder in the program interface, the numerical simulation results of the UAV with this aerodynamic configuration can be quickly found from the numerical simulation results of UAVs with different aerodynamic configurations.

[0056] S202. Extract the first surface pressure data of the target component from the numerical simulation calculation results according to the first type of parameter values input by the user.

[0057] In a possible embodiment, according to the first type of parameter values input by the user, an extraction file is generated; by running the extraction file, the first surface pressure data of the target component among multiple components is extracted from the numerical simulation calculation results.

[0058] In the specific implementation process, the user inputs the first type of parameter values in the first program interface to generate an extraction file, and then puts the numerical simulation results and the extraction file into the post-processing software to extract the first surface pressure data of the target component in the numerical simulation results.

[0059] Among them, the first type of parameter values includes the values of component characteristic parameters, the values of control batch extraction parameters, the number of components, and the component serial number. The component characteristic parameters include the starting coordinate of the component, the ending coordinate of the component, and the section spacing. The starting coordinate of the component refers to the coordinate of the starting point of the component along the section direction in the global coordinate system, and the ending coordinate of the component refers to the coordinate of the ending point of the component along the section direction in the global coordinate system. The component serial number refers to the serial number of the component to be intercepted. For example, 1 represents the fuselage, 2 represents the tail wing, 3 represents the wing, etc. The number of components refers to the total number of all components. For example, the number of fuselages is 1, and the number of wings is 2, etc. The control batch extraction parameters include the number of angle of attack cycles, the angle of attack interval cycle parameter, and the angle of attack starting value cycle parameter.

[0060] For example: y = ax + b, where y is the angle of attack, x is the current number of angle of attack cycles, a is the angle of attack interval cycle parameter, and b is the angle of attack starting value cycle parameter.

[0061] Please refer to Figure 3, which is a schematic diagram of a program interface provided by an embodiment of the present application. The blank rectangular box is an input box. In this program interface, first input the path, component start coordinates, component end coordinates, section spacing, number of components, component serial number, number of cycles, cycle parameter a, and cycle parameter b, and then click "Generate Macro" to generate an extraction file.

[0062] In the embodiment of the present application, input parameters can be adaptively determined according to components.

[0063] S203. Perform interpolation integration on the first surface pressure data to obtain the aerodynamic force data of the target component.

[0064] In a possible embodiment, the first surface pressure data extracted is the surface pressure data in the global coordinate system of the whole machine. The steps of S203 include:

[0065] Establish a local coordinate system of the target component according to the second type of parameter values input by the user; perform coordinate transformation on the first surface pressure data to obtain the second surface pressure data in the local coordinate system of the target component; perform interpolation integration on the second surface pressure data to obtain the aerodynamic force data of the target component.

[0066] In the specific implementation process, the second type of parameter values include the value of the component angle parameter, the origin coordinates of the local coordinate system, and the value of the component characteristic parameter. The component angle parameter is used to indicate the relative angle of the target component in the global coordinate system of the whole machine, including the dihedral angle, installation angle, control surface deflection angle, and sweep angle. The global coordinate system of the whole machine is usually a coordinate system established with the centroid of the aircraft as the origin. The component characteristic parameters include the component start coordinates, component end coordinates, and section spacing.

[0067] In a possible embodiment, the step of performing coordinate transformation on the first surface pressure data to obtain the second surface pressure data in the local coordinate system corresponding to the target component includes:

[0068] Translate the origin of the global coordinate system to the origin of the local coordinate system to obtain an intermediate coordinate system; translate the first surface pressure data to obtain the third surface pressure data in the intermediate coordinate system; rotate the third surface pressure data successively by the first Euler angle around the Z axis of the intermediate coordinate system, the second Euler angle around the Y axis of the intermediate coordinate system, and the third Euler angle around the X axis of the intermediate coordinate system to obtain the second surface pressure data in the local coordinate system corresponding to the target component. Among them, the first Euler angle is the relative angle between the Z axis of the intermediate coordinate system and the Z axis of the local coordinate system; the second Euler angle is the relative angle between the Y axis of the intermediate coordinate system and the Y axis of the local coordinate system; the third Euler angle is the relative angle between the X axis of the intermediate coordinate system and the X axis of the local coordinate system.

[0069] The specific transformation formula is as follows:

[0070]

[0071] Among them, (x1, y1, z1) are the third surface pressure data in the intermediate coordinate system, (x2, y2, z2) are the second surface pressure data in the local coordinate system, and L x L(ξ) is the transformation matrix about the X-axis, and L y L(η) is the transformation matrix about the Y-axis, and L z L(ζ) is the transformation matrix about the Z-axis.

[0072] The calculation formula of the transformation matrix about the X-axis is as follows:

[0073]

[0074] The calculation formula of the transformation matrix about the Y-axis is as follows:

[0075]

[0076] The calculation formula of the transformation matrix about the Z-axis is as follows:

[0077]

[0078] Among them, ξ is the third Euler angle of rotation about the X-axis, η is the second Euler angle of rotation about the Y-axis, and ζ is the first Euler angle of rotation about the Z-axis.

[0079] In the embodiments of the present application, converting the surface pressure data of the target component in the full-aircraft coordinate system to the local coordinate system of the target component can more accurately describe the pressure distribution on the surface of the component. By performing interpolation integration in the local coordinate system, the pressure change of the target component under the action of the fluid can be more accurately simulated, and more accurate aerodynamic data of the target component can be obtained.

[0080] In a possible embodiment, the steps of performing interpolation integration on the second surface pressure data to obtain the aerodynamic data of the target component include:

[0081] Performing linear interpolation on the second surface pressure data in each section to obtain interpolation data; performing numerical integration on the interpolation data to obtain the aerodynamic data of the target component.

[0082] In the specific implementation process, determine each section of the target component. According to the second surface pressure data, use three-dimensional interpolation methods, such as three-dimensional linear interpolation, three-dimensional spline interpolation, etc., to calculate the interpolation data in each section. Use numerical integration formulas for the interpolation data, such as the left rectangle quadrature formula, the right rectangle quadrature formula, the midpoint quadrature formula, etc., to obtain the aerodynamic data of the target component.

[0083] In the embodiments of the present application, pressure data can be smoothly estimated between each section through interpolation to obtain more continuous and accurate pressure distribution information, and the aerodynamic force data of the target component under the action of the fluid can be calculated more accurately through numerical integration.

[0084] Please refer to Figure 4 , which is another schematic diagram of the program interface provided by the embodiments of the present application. The blank rectangular box is the input box. Enter the data path (the path of the first surface pressure data), dihedral angle, installation angle, rudder surface deflection angle, sweep angle, origin coordinates of the local coordinate system, component start coordinates, component end coordinates, and section spacing in this program interface. Click "Import First Surface Pressure Data" to obtain the first surface pressure data extracted above. Click "Calculate Component Aerodynamic Force Data" to automatically perform coordinate transformation and interpolation integration on the first surface pressure data to obtain the component aerodynamic force data. Click "View Data" to view the component aerodynamic force data. Click "Output Data" to export the component aerodynamic force data in array format.

[0085] Please refer to Figure 5 , which is another schematic flowchart of the method for extracting the aerodynamic force of the unmanned aerial vehicle component provided by the embodiments of the present application. For component characteristic parameters such as component start coordinates, component end coordinates, and component serial numbers, programming is performed using the Matlab language to obtain an extraction file generator, that is, a general extraction program. The component surface pressure data can be automatically extracted through the extraction file generator. For the dihedral angle, installation angle, origin coordinates of the local coordinate system, etc., programming is performed using the Matlab language to obtain a component aerodynamic force automatic solver, that is, a general integration program. The component surface pressure data is automatically solved through the component aerodynamic force automatic solver to obtain the component aerodynamic force data, and the component aerodynamic force data is exported in array format.

[0086] In the embodiments of the present application, a general extraction program for numerical simulation results and a general integration program for component aerodynamic forces can be written using the Matlab language. The general extraction program can automatically batch extract the component surface pressure data, and the general integration program can perform coordinate transformation and interpolation integration on the component surface pressure data to obtain the component aerodynamic force data. The specific steps are as follows:

[0087] S1.1. For the characteristics of the component in the numerical simulation results, write a general extraction program with the characteristics as the input using Matlab.

[0088] S1.2. For the relative angle and relative origin of the component in the full aircraft coordinate system, write a program using Matlab to rotate and translate the position information of the component to the local coordinate system.

[0089] S1.3. Read in the component surface pressure data using the written Matlab program, rotate and translate it to the local coordinate system, and perform interpolation and integration.

[0090] S1.4. Loop through S1.2 and S1.3 until the interpolation and integration of the component aerodynamic forces for all flight states are completed. Finally, write a program using the Matlab language to export the component aerodynamic force data in array format.

[0091] Compared with the traditional manual component aerodynamic integration, the method for extracting the aerodynamic forces of the UAV components provided in the embodiments of the present application can reduce the aerodynamic integration period of a certain type of UAV components from 30 days to about 8 days. Specifically, it is reflected in that the extraction time of the component surface pressure data is reduced from 6 hours to 2 hours, the time for converting the position of the surface pressure data is reduced from 7 hours to 2 hours, and the working time for obtaining the aerodynamic force data through interpolation and integration is reduced from 11 hours to 3 hours.

[0092] In summary, the embodiments of the present application provide a method for extracting the aerodynamic forces of UAV components. Based on the numerical simulation results and the geometric shape and spatial position information of the target components, for the UAV components with complex configurations, the aerodynamic force data of the target components can be quickly and efficiently extracted from the numerical simulation results in batches, with strong versatility. Through the parameterized general extraction program and general integral calculation program, the participation threshold of professionals is effectively reduced, and the extraction efficiency of the aerodynamic forces of UAV components is improved.

[0093] Based on the same inventive concept, please refer to Figure 6 , the present application also provides a device for extracting the aerodynamic forces of UAV components, including:

[0094] An acquisition module, configured to acquire the numerical simulation results of the UAV under different rudder surface deflection angles and different flight states; the UAV includes multiple components; the numerical simulation results include the surface pressure data of multiple components;

[0095] An extraction module, configured to extract the first surface pressure data of the target component among multiple components from the numerical simulation calculation results according to the first type of parameter values input by the user; wherein, the first type of parameter values includes the values of the component characteristic parameters, and the component characteristic parameters are used to indicate the aerodynamic shape of the target component;

[0096] An obtaining module, configured to perform interpolation and integration on the first surface pressure data to obtain the aerodynamic force data of the target component.

[0097] Optionally, the acquisition module is specifically configured to:

[0098] Store the numerical simulation results of the UAV under different rudder surface deflection angles and different flight states in the target folder;

[0099] Obtain the numerical simulation results from the target folder according to the path of the target folder input by the user.

[0100] Optionally, the extraction module is specifically used for:

[0101] Generate an extraction file according to the first type of parameter values input by the user; the component feature parameters include the starting coordinates of the component, the ending coordinates of the component, the section spacing, the number of components, and the component serial number;

[0102] Extract the first surface pressure data of the target component among multiple components from the numerical simulation calculation results by running the extraction file.

[0103] Optionally, the first surface pressure data is the surface pressure data in the global coordinate system of the whole machine; the obtaining module is specifically used for:

[0104] Establish a local coordinate system of the target component according to the second type of parameter values input by the user; the second type of parameter values includes the value of the component angle parameter and the origin coordinates of the local coordinate system; the component angle parameter is used to indicate the relative angle of the target component in the global coordinate system of the whole machine;

[0105] Perform coordinate transformation on the first surface pressure data to obtain the second surface pressure data in the local coordinate system of the target component;

[0106] Perform interpolation integration on the second surface pressure data to obtain the aerodynamic force data of the target component.

[0107] Optionally, the obtaining module is specifically used for:

[0108] Translate the origin of the global coordinate system of the whole machine to the origin of the local coordinate system to obtain an intermediate coordinate system;

[0109] Translate the first surface pressure data to obtain the third surface pressure data in the intermediate coordinate system;

[0110] Rotate the third surface pressure data successively by the first Euler angle around the Z-axis of the intermediate coordinate system, by the second Euler angle around the Y-axis of the intermediate coordinate system, and by the third Euler angle around the X-axis of the intermediate coordinate system to obtain the second surface pressure data in the local coordinate system of the target component; where, the first Euler angle is the relative angle between the Z-axis of the intermediate coordinate system and the Z-axis of the local coordinate system; the second Euler angle is the relative angle between the Y-axis of the intermediate coordinate system and the Y-axis of the local coordinate system; the third Euler angle is the relative angle between the X-axis of the intermediate coordinate system and the X-axis of the local coordinate system.

[0111] Optionally, the obtaining module is specifically used for:

[0112] Perform linear interpolation on the second surface pressure data within each section to obtain interpolation data;

[0113] Numerically integrate the interpolated data to obtain the aerodynamic force data of the target component.

[0114] Optionally, the component angle parameters include dihedral angle, installation angle, rudder surface deflection angle, and sweep angle.

[0115] It should be noted that each module in the UAV component aerodynamic force extraction device in this embodiment corresponds one by one to each step in the UAV component aerodynamic force extraction method in the foregoing embodiment. Therefore, the specific implementation manner of this embodiment may refer to the implementation manner of the foregoing UAV component aerodynamic force extraction method, which will not be elaborated here.

[0116] Based on the same inventive concept, the present application also provides a computer device, which includes a processor, a memory, and a computer program stored in the memory. When the computer program is run by the processor, it implements the foregoing UAV component aerodynamic force extraction method.

[0117] Based on the same inventive concept, the present application also provides a computer storage medium, on which a computer program is stored. When the computer program is run by the processor, it implements the foregoing UAV component aerodynamic force extraction method.

[0118] In some embodiments, the computer-readable storage medium may be a memory such as FRAM, ROM, PROM, EPROM, EEPROM, flash memory, magnetic surface memory, optical disc, or CD-ROM; or it may be various devices including one or any combination of the above memories. The computer may be various computing devices including intelligent terminals and servers.

[0119] In some embodiments, the executable instructions may be in the form of a program, software, software module, script, or code, and may be written in any form of programming language (including compiled or interpreted languages, or declarative or procedural languages), and may be deployed in any form, including being deployed as an independent program or being deployed as a module, component, subroutine, or other unit suitable for use in a computing environment.

[0120] As an example, the executable instructions may or may not correspond to files in the file system, and may be stored as part of a file that stores other programs or data. For example, they may be stored in one or more scripts in a Hyper Text Markup Language (HTML) document, stored in a single file dedicated to the program under discussion, or stored in multiple cooperating files (for example, files that store one or more modules, subroutines, or code portions).

[0121] As an example, the executable instructions can be deployed to execute on one computing device, or on multiple computing devices located at one location, or on multiple computing devices distributed at multiple locations and interconnected by a communication network.

[0122] It should be noted that in this text, the term "including", "comprising" or any other variant thereof is intended to cover non-exclusive inclusion, such that a process, method, article or system including a series of elements not only includes those elements but also includes other elements not expressly listed, or also includes elements inherent to such process, method, article or system. Without further limitation, an element defined by the statement "including one..." does not exclude the existence of additional identical elements in the process, method, article or system including that element.

[0123] The serial numbers of the embodiments of the present application above are only for description and do not represent the superiority or inferiority of the embodiments.

[0124] Through the description of the above embodiments, those skilled in the art can clearly understand that the above embodiment methods can be implemented by means of software plus a necessary general hardware platform. Of course, they 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, in essence or the part that contributes to the prior art, can be embodied in the form of a software product. The computer software product is stored in a storage medium (such as a read-only memory / random access memory, magnetic disk, optical disc), and includes several instructions for causing a multimedia terminal device (which can be a mobile phone, a computer, a television receiver, or a network device, etc.) to execute the methods of the various embodiments of the present application.

[0125] The above are only the preferred embodiments of the present application, and do not limit the patent scope of the present application accordingly. Any equivalent structure or equivalent process transformation made by using the specification and drawings of the present application, or directly or indirectly applied in other related technical fields, shall be equally included in the patent protection scope of the present application.

Claims

1. A method for extracting aerodynamic force of a UAV component, characterized in that, Including: Obtaining numerical simulation results of an unmanned aerial vehicle (UAV) at different rudder surface deflection angles and different flight states; the UAV includes multiple components; the numerical simulation results include surface pressure data of the multiple components; Extracting first surface pressure data of a target component among the multiple components from the numerical simulation calculation results according to first type parameter values input by a user; wherein, the first type parameter values include values of component characteristic parameters, and the component characteristic parameters are used to indicate the aerodynamic shape of the target component; Performing interpolation integration on the first surface pressure data to obtain aerodynamic force data of the target component.

2. The method for extracting aerodynamic force of a drone component according to claim 1, wherein The obtaining of the numerical simulation results of the UAV at different rudder surface deflection angles and different flight states includes: Storing the numerical simulation results of the UAV at different rudder surface deflection angles and different flight states in a target folder; Obtaining the numerical simulation results from the target folder according to the path of the target folder input by the user.

3. The method for extracting aerodynamic force of a drone component according to claim 1, wherein, The extracting of the first surface pressure data of the target component among the multiple components from the numerical simulation calculation results according to the first type parameter values input by the user includes: Generating an extraction file according to the first type parameter values input by the user; the component characteristic parameters include component start coordinates, component end coordinates, section spacing, number of components, and component serial number; Extracting the first surface pressure data of the target component among the multiple components from the numerical simulation calculation results by running the extraction file.

4. The method for extracting aerodynamic force of a drone component according to claim 1, characterized in that The first surface pressure data is surface pressure data in the whole aircraft coordinate system; the performing of interpolation integration on the first surface pressure data to obtain the aerodynamic force data of the target component includes: Establishing a local coordinate system of the target component according to second type parameter values input by the user; the second type parameter values include values of component angle parameters and the origin coordinates of the local coordinate system; the component angle parameters are used to indicate the relative angle of the target component in the whole aircraft coordinate system; Performing coordinate transformation on the first surface pressure data to obtain second surface pressure data of the target component in the local coordinate system; Performing interpolation integration on the second surface pressure data to obtain the aerodynamic force data of the target component.

5. The method for extracting aerodynamic force of a drone component according to claim 4, wherein The performing of coordinate transformation on the first surface pressure data to obtain the second surface pressure data of the target component in the local coordinate system includes: Translating the origin of the whole aircraft coordinate system to the origin of the local coordinate system to obtain an intermediate coordinate system; Performing translation on the first surface pressure data to obtain third surface pressure data in the intermediate coordinate system; Rotate the third surface pressure data about the Z-axis of the intermediate coordinate system by a first Euler angle, about the Y-axis of the intermediate coordinate system by a second Euler angle, and about the X-axis of the intermediate coordinate system by a third Euler angle to obtain the second surface pressure data in the local coordinate system of the target component; wherein, the first Euler angle is the relative angle between the Z-axis of the intermediate coordinate system and the Z-axis of the local coordinate system; the second Euler angle is the relative angle between the Y-axis of the intermediate coordinate system and the Y-axis of the local coordinate system; the third Euler angle is the relative angle between the X-axis of the intermediate coordinate system and the X-axis of the local coordinate system.

6. The method for extracting aerodynamic force of a drone component according to claim 4, wherein Interpolating and integrating the second surface pressure data to obtain the aerodynamic force data of the target component includes: Performing linear interpolation on the second surface pressure data within each section to obtain interpolated data; Performing numerical integration on the interpolated data to obtain the aerodynamic force data of the target component.

7. The method for extracting aerodynamic force of a UAV component according to claim 4, wherein, The component angle parameters include dihedral angle, angle of incidence, control surface deflection angle, and sweep angle.

8. An aerodynamic force extraction device for a drone component, characterized in that Including: An acquisition module for acquiring the numerical simulation results of the unmanned aerial vehicle (UAV) under different control surface deflection angles and different flight states; the UAV includes a plurality of components; the numerical simulation results include the surface pressure data of the plurality of components; An extraction module for extracting the first surface pressure data of the target component among the plurality of components from the numerical simulation calculation results according to the first type of parameter values input by the user; wherein, the first type of parameter values includes the values of component characteristic parameters, and the component characteristic parameters are used to indicate the aerodynamic shape of the target component; An obtaining module for interpolating and integrating the first surface pressure data to obtain the aerodynamic force data of the target component.

9. A computer device, characterized in that, The computer device includes a memory and a processor, and a computer program is stored in the memory. The processor executes the computer program to implement the method for extracting the aerodynamic force of the UAV component according to any one of claims 1-7.

10. A computer-readable storage medium, characterized in that, A computer program is stored on the computer-readable storage medium, and the processor executes the computer program to implement the method for extracting the aerodynamic force of the UAV component according to any one of claims 1-7.

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