A method, device, equipment and medium for converting wing aerodynamic load and structural load

Abstract

The application provides a wing aerodynamic load and structural load conversion method, device, equipment and medium, comprising: obtaining a plurality of structural nodes of each aerodynamic node of a wing in a preset search range as associated structural nodes of the corresponding aerodynamic node, wherein each structural node is associated with a plurality of aerodynamic nodes; distributing the load of each aerodynamic node to the corresponding associated structural nodes with the minimum deformation energy between the aerodynamic nodes and the corresponding associated structural nodes as a constraint; obtaining the sum of the aerodynamic node loads distributed to each structural node as the total load of the corresponding structural node; and the application can effectively improve the accuracy of load conversion.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicles (UAVs), and more particularly to a method, apparatus, device, and medium for converting wing aerodynamic loads to structural loads. Background Technology

[0002] Aircraft design requires strength verification of the wing structure, with the primary input for this calculation being aerodynamic loads. Currently, simulation methods are used in both aerodynamic and structural strength calculations. However, aerodynamic and structural strength simulations are different methods, and their built-in numerical calculation methods are entirely different. Therefore, aerodynamic and structural strength simulation software have different mesh requirements; aerodynamic mesh nodes cannot be directly mapped to structural strength mesh nodes. Consequently, when using the loads output from aerodynamic calculations as input loads for structural strength calculations, a proper load conversion is necessary.

[0003] Existing load conversion methods are prone to having large loads on some structural nodes and zero loads on others, resulting in significant discrepancies with actual values. Summary of the Invention

[0004] In view of the problems existing in the prior art, the present invention proposes a method, device, equipment and medium for converting wing aerodynamic loads and structural loads, which mainly solves the problem that the existing load conversion simulation methods have large errors and poor accuracy compared with the actual loads.

[0005] To achieve the above and other objectives, the technical solution adopted by the present invention is as follows.

[0006] A method for converting aerodynamic loads to structural loads on an airfoil, comprising:

[0007] For each aerodynamic node of the wing, multiple structural nodes within a preset search range are obtained as associated structural nodes of the corresponding aerodynamic node, wherein each structural node is associated with multiple aerodynamic nodes;

[0008] The load of each aerodynamic node is distributed to the corresponding associated structural nodes with the constraint of minimizing the deformation energy between the aerodynamic node and each associated structural node.

[0009] The sum of the aerodynamic node loads assigned to each structural node is obtained as the total load of the corresponding structural node.

[0010] Optionally, the method further includes:

[0011] The wing is divided into an upper wing surface and a lower wing surface, and the aerodynamic nodes and structural nodes of the corresponding wing surfaces are marked.

[0012] Retrieve the associated structural nodes at the aerodynamic nodes on the upper and lower wing surfaces respectively;

[0013] After obtaining the total load of the structural nodes on each wing surface, the loads of the structural nodes on the upper and lower wing surfaces are combined to obtain the structural load of the entire wing.

[0014] Optionally, multiple structural nodes within a preset search range for each aerodynamic node of the wing are obtained as associated structural nodes of the corresponding aerodynamic node, including:

[0015] Obtain the distance between the current pneumatic node and each structural node, and designate the structural nodes whose distances are within the preset search range as the associated structural nodes of the current pneumatic node; wherein, the preset search range is a circular area centered on the pneumatic node with a preset length as the radius; the preset length is less than or equal to the minimum distance between pneumatic nodes and greater than the minimum distance between structural nodes.

[0016] Optionally, the loads of each aerodynamic node are distributed to the corresponding associated structural nodes with the constraint of minimizing the deformation energy between the aerodynamic node and the corresponding structural node, including:

[0017] The connection between the aerodynamic node and the corresponding associated structural node is used as an imaginary beam to obtain the corresponding deformation energy.

[0018] The loads of the aerodynamic nodes are distributed to the corresponding associated structural nodes using the Lagrange multiplier method, so that the deformation energy of the aerodynamic nodes is minimized.

[0019] Optionally, the wing is divided into an upper wing surface and a lower wing surface, and the aerodynamic and structural nodes of the corresponding wing surfaces are marked, including:

[0020] The wing is divided into the upper wing surface and the lower wing surface according to the wing chord line;

[0021] Mark the node number, node direction coordinates, and node load of the aerodynamic nodes of the corresponding airfoil;

[0022] Mark the node number and node direction coordinates of the structural nodes corresponding to the wing surface.

[0023] Optionally, distributing the load of each aerodynamic node to its corresponding associated structural nodes with the constraint of minimizing the deformation energy between the aerodynamic node and the corresponding structural node further includes:

[0024] If the distance between the pneumatic node and the corresponding associated structural node is less than a preset distance error, then the load of the pneumatic node is directly assigned to the associated structural node.

[0025] If the distance between the aerodynamic node and the corresponding associated structural node is greater than the preset distance error but less than the preset search range, then the load assigned to the aerodynamic node on the corresponding associated structural node is obtained according to the Lagrange multiplier method, so that the deformation energy is minimized.

[0026] Optionally, the loads of the aerodynamic nodes are distributed to the corresponding associated structural nodes according to the Lagrange multiplier method to minimize the deformation energy, including:

[0027] Based on the static equilibrium relationship of the airfoil, and taking the minimum variable performance as the constraint, a Lagrangian function is established to solve for the loads allocated to the associated structural nodes.

[0028] A device for converting aerodynamic loads to structural loads on an airfoil, comprising:

[0029] The associated node retrieval module is used to obtain multiple structural nodes of each aerodynamic node of the wing within a preset retrieval range as associated structural nodes of the corresponding aerodynamic node, wherein each structural node is associated with multiple aerodynamic nodes.

[0030] The load distribution module is used to distribute the load of each aerodynamic node to the corresponding associated structural nodes with the constraint of minimizing the deformation energy between the aerodynamic node and the corresponding associated structural nodes.

[0031] The structural load acquisition module is used to obtain the sum of the aerodynamic node loads assigned to each structural node as the total load of the corresponding structural node.

[0032] An apparatus comprising:

[0033] One or more processors; and

[0034] One or more machine-readable media storing instructions thereon, which, when executed by the one or more processors, cause the device to perform the method for converting wing aerodynamic loads to structural loads.

[0035] A machine-readable medium having instructions stored thereon that, when executed by one or more processors, cause a device to perform the method for converting wing aerodynamic loads to structural loads.

[0036] As described above, the present invention provides a method, apparatus, device, and medium for converting aerodynamic loads and structural loads on an airfoil, which has the following beneficial effects.

[0037] By acquiring multiple structural nodes within a preset search range for each aerodynamic node of the wing as associated structural nodes, each structural node is associated with multiple aerodynamic nodes. The load of each aerodynamic node is allocated to its corresponding associated structural nodes based on the constraint of minimizing the deformation energy between the aerodynamic node and its associated structural nodes. The sum of the aerodynamic node loads allocated to each structural node is then obtained as the total load of that structural node. Searching for structural nodes within a preset range avoids the problem of large local force distribution variations and inconsistencies with reality that can occur with existing three-point sorting methods that only search for three nearby structural nodes per aerodynamic node. Introducing deformation energy constraints improves the accuracy of load allocation, making the allocation results more consistent with mechanical principles and matching reality. Attached Figure Description

[0038] Figure 1 This is a flowchart illustrating the method for converting wing aerodynamic loads and structural loads in one embodiment of the present invention.

[0039] Figure 2 This is a block diagram of a wing aerodynamic load and structural load conversion device in one embodiment of the present invention.

[0040] Figure 3 This is a schematic diagram of the device in one embodiment of the present invention.

[0041] Figure 4 This is a schematic diagram of the device in another embodiment of the present invention.

[0042] Figure 5 This is a schematic diagram of load distribution using the three-point arrangement method in the prior art.

[0043] Figure 6 This is a schematic diagram illustrating the relationship between pneumatic nodes and structural nodes in one embodiment of the present invention.

[0044] Figure 7 This is a flowchart illustrating the method for converting wing aerodynamic loads and structural loads in another embodiment of the present invention. Detailed Implementation

[0045] The following specific examples illustrate the implementation of the present invention. Those skilled in the art can easily understand other advantages and effects of the present invention from the content disclosed in this specification. The present invention can also be implemented or applied through other different specific embodiments, and various details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of the present invention. It should be noted that, unless otherwise specified, the following embodiments and features described therein can be combined with each other.

[0046] It should be noted that the illustrations provided in the following embodiments are only schematic representations of the basic concept of the present invention. Therefore, the drawings only show the components related to the present invention and are not drawn according to the actual number, shape and size of the components in the actual implementation. In the actual implementation, the form, quantity and proportion of each component can be arbitrarily changed, and the layout of the components may also be more complex.

[0047] The inventor discovered through research that:

[0048] Existing technology: Three-point arrangement

[0049] The three-point distribution method allocates the load Pj on the aerodynamic node P to the structural nodes according to the principle of static equivalence, following the area principle. The sum of the loads allocated to each structural load on different aerodynamic nodes is the final load of that structure.

[0050] Please see Figure 5 Assuming the load on the aerodynamic node P is Pj, and nodes 1, 2, and 3 in the figure are structural nodes, fi is the load allocated to the structural node, and i = 1, 2, and 3, then fi = (Ai / A) * Pj. The sum of the loads allocated to node i from different aerodynamic nodes is the final load Fi.

[0051] Where Ai is the area corresponding to each structural node, A1 is the area of ​​△P23, A2 is the area of ​​△P13, A3 is the area of ​​△P12, and A is the area of ​​△123.

[0052] The shortcomings and deficiencies of the existing technology are as follows: It only considers static equilibrium, which can ensure that the pressure core remains unchanged, but does not consider deformation energy. Furthermore, it searches for three relatively close points on each aerodynamic node. When two adjacent aerodynamic nodes are far apart, but the corresponding structural nodes are relatively dense, some structural nodes will have a large load, while others will have a zero load. The local force distribution will vary greatly, and in many cases, the force distribution will not conform to the mechanical principles and will be detached from reality.

[0053] In addition, the wing thickness is relatively small. When the wing thickness is not considered, the projection surfaces of the upper and lower wing surfaces coincide. Therefore, when traversing around an aerodynamic node to search for surrounding structural nodes, sometimes the aerodynamic node of the upper wing surface will search for the structural node of the lower wing surface. This will result in the aerodynamic load of the upper wing surface being distributed to the structural load of the lower wing surface, causing incorrect load conversion.

[0054] Please see Figure 1 To address the problems existing in the prior art, this invention provides a method for converting aerodynamic loads and structural loads on an airfoil, comprising the following steps:

[0055] Step S01: Obtain multiple structural nodes of each aerodynamic node of the wing within a preset search range as associated structural nodes of the corresponding aerodynamic node, wherein each structural node is associated with multiple aerodynamic nodes.

[0056] Step S02: Distribute the load of each aerodynamic node to the corresponding associated structural nodes with the constraint of minimizing the deformation energy between the aerodynamic node and the corresponding associated structural nodes.

[0057] Step S03: Obtain the sum of the aerodynamic node loads assigned to each structural node as the total load of the corresponding structural node.

[0058] The method for converting wing aerodynamic loads and structural loads according to the present invention will be described in detail below with reference to specific embodiments.

[0059] Please see Figure 7 Using the wing chord line as the dividing point, the upper and lower wing surfaces are separated, and the aerodynamic and structural nodes of the upper and lower wing surfaces are labeled separately. When outputting aerodynamic data, the data for the upper and lower wing surfaces are output separately. Similarly, when outputting structural node data, the chord line is used as the dividing point, and the data for the upper and lower wing surfaces are output separately. During data conversion, the aerodynamic data of the upper wing surface corresponds to the structural data of the upper wing surface, and the converted data is the structural load data of the upper wing surface. The aerodynamic data of the lower wing surface corresponds to the structural data of the upper wing surface, and the converted data is the structural load data of the lower wing surface. Finally, the structural data of the upper and lower wing surfaces are merged into the overall wing structural load data.

[0060] Specifically, it includes the following steps:

[0061] 01) After the aerodynamic load calculation is completed, the upper wing surface data and the lower wing surface data are output respectively. The output data includes the aerodynamic node number, the node coordinates in three directions (X, Y, Z directions), and the loads in the three directions of the node.

[0062] 02) After the structural strength calculation mesh is generated, the upper and lower wing surface data are output respectively. The output data includes the structural node number and the three-directional coordinates of the structural node.

[0063] 03) Build a data reading interface and store the pneumatic output data in a two-dimensional array, such as... Figure 6 As shown, r is the preset search range radius, n is the total number of aerodynamic nodes, and m is the total number of structural nodes.

[0064] 04) For a pneumatic node, traverse and search the structural nodes. For each structural node, determine the distance between the structural node and the pneumatic node. When the distance is less than the error value e, assign all the loads on the pneumatic node to the structural node and mark the structural node as 0. Proceed to the search for the next node. When the distance is greater than the radius r, proceed to the search for the next structural node. When the distance is greater than e and less than r, increment the count of the pneumatic node by 1 and mark the structural node as 1. Calculate the matrix by superimposing the Lagrange multipliers.

[0065] 05) Determine if the traversal of the structural nodes has been completed. If it has, proceed to step 06; otherwise, repeat step 04.

[0066] 06) Call the matrix solver subroutine based on Gaussian elimination to calculate the Lagrange multipliers.

[0067] 07) Calculate the loads assigned to the current aerodynamic node by the Lagrange multipliers.

[0068] 08) Repeat steps 04) to 07) for all pneumatic nodes.

[0069] Output the upper and lower wing surface loads of the structural nodes separately, and combine them into the entire wing structure load.

[0070] The specific steps for distributing the load of the aerodynamic node to the structural nodes within its radius r by calculating the matrix using the Lagrange multiplier method include:

[0071] Suppose that aerodynamic node A searches for n structural nodes with a radius greater than e and less than r.

[0072] There is an imaginary beam between the aerodynamic node and the structural node, and the load P on aerodynamic A is... A The load assigned to the corresponding structural node is P. j The resulting deformation energy is

[0073]

[0074] Where EI is the bending stiffness of the hypothetical beam, Lj is the distance between the aerodynamic node and the structural node, and i = 1, 2, ..., n-1, n.

[0075] For aerodynamic node A, after distributing the aerodynamic load to n structural nodes, the resulting deformation energy is:

[0076]

[0077] Assuming the airfoil lies in the XZ plane, the static equilibrium relationships during the transformation process are as follows:

[0078]

[0079]

[0080]

[0081] To obtain the minimum deformation energy, a Lagrange function is established.

[0082]

[0083] in This represents the distance between the aerodynamic node and the structural node in the X direction. Let λ be the distance between the aerodynamic node and the structural node in the Z direction, and λ be the distance between them. x , λ z For Lagrange multipliers, to obtain F(λλ) x λ z To find the minimum value, differentiate both sides of the above equation to obtain...

[0084]

[0085] Substituting formula (5) into formula (3), we obtain the calculation matrix.

[0086]

[0087] The above conversion process can accurately obtain the structural load of the wing.

[0088] Please see Figure 2 This embodiment provides a device for converting wing aerodynamic loads to structural loads, used to execute the wing aerodynamic load to structural load conversion method described in the foregoing method embodiments. Since the technical principles of the device embodiment are similar to those of the foregoing method embodiments, the same technical details will not be repeated.

[0089] In one embodiment, the wing aerodynamic load to structural load conversion device includes:

[0090] The associated node retrieval module 10 is used to obtain multiple structural nodes of each aerodynamic node of the wing within a preset retrieval range as associated structural nodes of the corresponding aerodynamic node, wherein each structural node is associated with multiple aerodynamic nodes.

[0091] The load distribution module 11 is used to distribute the load of each aerodynamic node to the corresponding associated structural nodes with the constraint of minimizing the deformation energy between the aerodynamic node and the corresponding associated structural nodes.

[0092] The structural load acquisition module 12 is used to acquire the sum of the aerodynamic node loads allocated to each structural node as the total load of the corresponding structural node.

[0093] This application also provides an apparatus that may include: one or more processors; and one or more machine-readable media having instructions stored thereon, which, when executed by the one or more processors, cause the apparatus to perform... Figure 1 The method described herein. In practical applications, this device can be used as a terminal device, and the embodiments of this application do not limit the specific device.

[0094] This application also provides a non-volatile readable storage medium storing one or more modules (programs). When these modules are applied to a device, they enable the device to execute embodiments of this application. Figure 1 Instructions for the steps involved in the method of converting aerodynamic loads to structural loads on a mid-wing.

[0095] Figure 3 This is a schematic diagram of the hardware structure of a terminal device provided in an embodiment of this application. As shown in the figure, the terminal device may include: an input device 1100, a first processor 1101, an output device 1102, a first memory 1103, and at least one communication bus 1104. The communication bus 1104 is used to realize communication connections between components. The first memory 1103 may include a high-speed RAM memory, and may also include non-volatile memory (NVM), such as at least one disk storage device. The first memory 1103 can store various programs for performing various processing functions and implementing the method steps of this embodiment.

[0096] Optionally, the first processor 1101 may be implemented as a central processing unit (CPU), application-specific integrated circuit (ASIC), digital signal processor (DSP), digital signal processing device (DSPD), programmable logic device (PLD), field-programmable gate array (FPGA), controller, microcontroller, microprocessor or other electronic components. The processor 1101 is coupled to the input device 1100 and output device 1102 via wired or wireless connection.

[0097] Optionally, the input device 1100 may include a variety of input devices, such as a user interface, a device interface, a programmable software interface, a camera, and a sensor. Optionally, the device interface may be a wired interface for data transmission between devices, or a hardware insertion interface (e.g., USB interface, serial port) for data transmission between devices. Optionally, the user interface may be, for example, user-facing control buttons, a voice input device for receiving voice input, or a touch sensing device for receiving user touch input (e.g., a touchscreen, touchpad, etc.). Optionally, the programmable software interface may be, for example, an entry point for users to edit or modify programs, such as a chip input pin interface or input interface. The output device 1102 may include a display, speakers, and other output devices.

[0098] In this embodiment, the processor of the terminal device includes functions for executing the functions of each module of the voice recognition device in each device. The specific functions and technical effects can be referred to in the above embodiment, and will not be repeated here.

[0099] Figure 4 This is a schematic diagram of the hardware structure of a terminal device provided for another embodiment of this application. Figure 4 Yes Figure 3 This is a specific embodiment of the implementation process. As shown in the figure, the terminal device of this embodiment may include a second processor 1201 and a second memory 1202.

[0100] The second processor 1201 executes the computer program code stored in the second memory 1202 to implement the above embodiments. Figure 1 The method is described above.

[0101] The second memory 1202 is configured to store various types of data to support operation on the terminal device. Examples of this data include instructions for any application or method operating on the terminal device, such as messages, pictures, videos, etc. The second memory 1202 may include random access memory (RAM) and may also include non-volatile memory, such as at least one disk storage device.

[0102] Optionally, the first processor 1201 is disposed in the processing component 1200. The terminal device may further include: a communication component 1203, a power supply component 1204, a multimedia component 1205, an audio component 1206, an input / output interface 1207, and / or a sensor component 1208. The specific components included in the terminal device are determined according to actual needs, and this embodiment does not limit this.

[0103] Processing component 1200 typically controls the overall operation of the terminal device. Processing component 1200 may include one or more second processors 1201 to execute instructions to perform the above-described tasks. Figure 1 The method shown may include all or part of the steps. Furthermore, the processing component 1200 may include one or more modules to facilitate interaction between the processing component 1200 and other components. For example, the processing component 1200 may include a multimedia module to facilitate interaction between the multimedia component 1205 and the processing component 1200.

[0104] Power supply component 1204 provides power to various components of the terminal device. Power supply component 1204 may include a power management system, one or more power supplies, and other components associated with generating, managing, and distributing power to the terminal device.

[0105] Multimedia component 1205 includes a display screen that provides an output interface between a terminal device and a user. In some embodiments, the display screen may include a liquid crystal display (LCD) and a touch panel (TP). If the display screen includes a touch panel, the display screen may be implemented as a touchscreen to receive input signals from the user. The touch panel includes one or more touch sensors to sense touches, swipes, and gestures on the touch panel. The touch sensors may sense not only the boundaries of the touch or swipe action but also the duration and pressure associated with the touch or swipe operation.

[0106] Audio component 1206 is configured to output and / or input voice signals. For example, audio component 1206 includes a microphone (MIC) configured to receive external voice signals when the terminal device is in an operating mode, such as a voice recognition mode. The received voice signals may be further stored in a second memory 1202 or transmitted via communication component 1203. In some embodiments, audio component 1206 also includes a speaker for outputting voice signals.

[0107] Input / output interface 1207 provides an interface between processing component 1200 and peripheral interface modules, such as click wheels, buttons, etc. These buttons may include, but are not limited to, volume buttons, start buttons, and lock buttons.

[0108] Sensor assembly 1208 includes one or more sensors for providing status assessments of various aspects of the terminal device. For example, sensor assembly 1208 can detect the on / off state of the terminal device, the relative positioning of components, and the presence or absence of user contact with the terminal device. Sensor assembly 1208 may include a proximity sensor configured to detect the presence of nearby objects without any physical contact, including detecting the distance between the user and the terminal device. In some embodiments, sensor assembly 1208 may also include a camera, etc.

[0109] Communication component 1203 is configured to facilitate wired or wireless communication between the terminal device and other devices. The terminal device can access wireless networks based on communication standards, such as WiFi, 2G, or 3G, or combinations thereof. In one embodiment, the terminal device may include a SIM card slot for inserting a SIM card, enabling the terminal device to log in to a GPRS network and establish communication with a server via the Internet.

[0110] As can be seen from the above, in Figure 4 The communication component 1203, audio component 1206, input / output interface 1207, and sensor component 1208 involved in the embodiment can all be used as... Figure 3 The implementation method of the input device in the embodiment.

[0111] In summary, this invention provides a method, apparatus, device, and medium for converting aerodynamic loads and structural loads on an airfoil. Based on the principle of static equivalence, it adds a constraint of minimum deformation energy, ensuring that the deformation energy generated during the conversion process is minimized. This aligns with the principle that the minimum deformation energy is the optimal solution in structural strength simulation calculations. Furthermore, each aerodynamic node is not limited to corresponding to three structural nodes. For each aerodynamic node, structural nodes are searched within a radius of r, where r is less than or equal to the minimum distance between aerodynamic nodes. This avoids the phenomenon where some structural nodes have exceptionally large loads while others have zero loads. An error value e is also set to avoid the problem of computational singularities when structural and aerodynamic nodes coincide. Using a chord line as a boundary, the airfoil is divided into an upper and lower surface. Data is extracted separately for the upper and lower surfaces, and the converted structural loads of the upper and lower surfaces are combined into the overall airfoil structural load, avoiding erroneous surface conversion results and further improving the accuracy of load conversion. Therefore, this invention effectively overcomes the various shortcomings of existing technologies and has high industrial applicability.

[0112] The above embodiments are merely illustrative of the principles and effects of the present invention and are not intended to limit the invention. Any person skilled in the art can modify or alter the above embodiments without departing from the spirit and scope of the present invention. Therefore, all equivalent modifications or alterations made by those skilled in the art without departing from the spirit and technical concept disclosed in the present invention should still be covered by the claims of the present invention.

Claims

1. A method for converting aerodynamic loads and structural loads on an airfoil, characterized in that, include: For each aerodynamic node of the wing, multiple structural nodes within a preset search range are obtained as associated structural nodes of the corresponding aerodynamic node, wherein each structural node is associated with multiple aerodynamic nodes; The method of obtaining multiple structural nodes within a preset search range for each aerodynamic node of the wing as associated structural nodes includes: obtaining the distance between the current aerodynamic node and each structural node, and using the structural nodes whose distances are within the preset search range as associated structural nodes of the current aerodynamic node; wherein, the preset search range is a circular area centered on the aerodynamic node with a preset length as its radius; the preset length is less than or equal to the minimum distance between aerodynamic nodes and greater than the minimum distance between structural nodes; The load of each aerodynamic node is distributed to its corresponding associated structural nodes with the constraint of minimizing the deformation energy between the aerodynamic node and its corresponding structural nodes. This process includes: treating the line connecting the aerodynamic node and its corresponding associated structural node as an imaginary beam and obtaining the corresponding deformation energy; and obtaining the load distributed by the aerodynamic node to its corresponding associated structural node using the Lagrange multiplier method to minimize the deformation energy. The sum of the aerodynamic node loads assigned to each structural node is obtained as the total load of the corresponding structural node.

2. The method for converting wing aerodynamic loads and structural loads according to claim 1, characterized in that, Also includes: The wing is divided into an upper wing surface and a lower wing surface, and the aerodynamic nodes and structural nodes of the corresponding wing surfaces are marked. Retrieve the associated structural nodes at the aerodynamic nodes on the upper and lower wing surfaces respectively; After obtaining the total load of the structural nodes on each wing surface, the loads of the structural nodes on the upper and lower wing surfaces are combined to obtain the structural load of the entire wing.

3. The method for converting wing aerodynamic loads and structural loads according to claim 2, characterized in that, The wing is divided into an upper surface and a lower surface, and the aerodynamic and structural nodes of the corresponding surfaces are marked, including: The wing is divided into the upper wing surface and the lower wing surface according to the wing chord line; Mark the node number, node direction coordinates, and node load of the aerodynamic nodes of the corresponding airfoil; Mark the node number and node direction coordinates of the structural nodes corresponding to the wing surface.

4. The method for converting wing aerodynamic loads and structural loads according to claim 1, characterized in that, The load distribution from each aerodynamic node to its corresponding associated structural node is constrained by minimizing the deformation energy between the aerodynamic node and its corresponding structural node. This also includes: If the distance between the pneumatic node and the corresponding associated structural node is less than a preset distance error, then the load of the pneumatic node is directly assigned to the associated structural node. If the distance between the aerodynamic node and the corresponding associated structural node is greater than the preset distance error but less than the preset search range, then the load assigned to the corresponding associated structural node by the aerodynamic node is obtained according to the Lagrange multiplier method, so that the deformation energy is minimized.

5. The method for converting wing aerodynamic loads and structural loads according to claim 1, characterized in that, The loads of the aerodynamic nodes are distributed to the corresponding associated structural nodes using the Lagrange multiplier method to minimize the deformation energy, including: Based on the static equilibrium relationship of the airfoil, and taking the minimum variable performance as the constraint, a Lagrangian function is established to solve for the loads allocated to the associated structural nodes.

6. A method for converting aerodynamic loads and structural loads on an airfoil, characterized in that, include: The associated node retrieval module is used to obtain multiple structural nodes of each aerodynamic node of the wing within a preset retrieval range as associated structural nodes of the corresponding aerodynamic node, wherein each structural node is associated with multiple aerodynamic nodes. The method of obtaining multiple structural nodes within a preset search range for each aerodynamic node of the wing as associated structural nodes includes: obtaining the distance between the current aerodynamic node and each structural node, and using the structural nodes whose distances are within the preset search range as associated structural nodes of the current aerodynamic node; wherein, the preset search range is a circular area centered on the aerodynamic node with a preset length as its radius; the preset length is less than or equal to the minimum distance between aerodynamic nodes and greater than the minimum distance between structural nodes; The load distribution module is used to distribute the load of each aerodynamic node to its corresponding associated structural nodes with the constraint of minimizing the deformation energy between the aerodynamic node and its corresponding structural nodes. This includes: treating the line connecting the aerodynamic node and its corresponding associated structural node as an imaginary beam and obtaining the corresponding deformation energy; and obtaining the load distributed from the aerodynamic node to its corresponding associated structural node using the Lagrange multiplier method to minimize the deformation energy. The structural load acquisition module is used to obtain the sum of the aerodynamic node loads assigned to each structural node as the total load of the corresponding structural node.

7. A device, characterized in that, include: One or more processors; and One or more machine-readable media having instructions stored thereon, which, when executed by the one or more processors, cause the device to perform the method as described in any one of claims 1-5.

8. A machine-readable medium, characterized in that, It stores instructions that, when executed by one or more processors, cause the device to perform the method as described in any one of claims 1-5.

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