A wing load conversion method, apparatus, device and medium

Abstract

The application provides a wing load conversion method, device, equipment and medium, comprising the following steps: acquiring aerodynamic loads of center nodes of each aerodynamic unit of a wing surface; dividing the wing surface into a plurality of rectangular blocks, each rectangular block comprising at least one aerodynamic unit grid and one structural unit grid at a corresponding position; and distributing the aerodynamic loads of the center nodes of each aerodynamic unit in each rectangular block to structural nodes in the same rectangular block to complete structural load conversion. The application has low calculation complexity and can effectively improve the accuracy of local structural strength analysis.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) applications, and more particularly to a method, apparatus, device, and medium for wing load conversion. 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 distribute the load on the central node of the aerodynamic unit to structural nodes at a distance, which has an adverse effect on the distribution of local structural loads. At the same time, it can lead to a large difference between the torque formed by the structural load and the actual situation. The conversion algorithm has high computational complexity and is prone to singularities, resulting in load conversion failure. 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 wing load conversion, which mainly solves the problems of insufficient conversion accuracy and high complexity of existing load conversion methods.

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

[0006] This application provides a wing load conversion method, including:

[0007] Obtain the aerodynamic loads at the center nodes of each aerodynamic element on the wing surface;

[0008] The wing surface is divided into multiple rectangular blocks, and each rectangular block includes at least one aerodynamic element grid and one structural element grid at a corresponding position;

[0009] The aerodynamic loads of the aerodynamic unit center nodes in each rectangular block are distributed to the structural nodes in the same rectangular block, thus completing the structural load conversion.

[0010] Optionally, the aerodynamic loads at the center nodes of each aerodynamic element on the wing surface are obtained, including:

[0011] The wing surface is divided into an upper wing surface and a lower wing surface by a chord line;

[0012] The aerodynamic unit information of the upper wing surface and the lower wing surface is obtained respectively, wherein the aerodynamic unit information includes: unit number, unit center node coordinates, unit pressure, and the projection of the unit grid area in each coordinate direction;

[0013] The load of the corresponding pneumatic unit center node is calculated based on the pneumatic unit information;

[0014] The upper and lower wing surfaces are divided into multiple rectangular blocks based on the aerodynamic unit information.

[0015] Optionally, the wing surface is divided into multiple rectangular blocks, including:

[0016] The size of the rectangular block is determined based on the size of the pneumatic unit grid and the size of the structural unit grid, wherein the size of the rectangular block is greater than or equal to the size of the pneumatic unit grid and the size of the structural unit grid;

[0017] The wing surface is divided into multiple rectangular blocks based on the coordinates of the center node of the aerodynamic unit and the size of the rectangular blocks.

[0018] Optionally, after dividing the wing surface into multiple rectangular blocks, the following steps are included:

[0019] Establish the mapping relationship between the center nodes of each pneumatic unit and the rectangular block based on the coordinates of the center nodes of each pneumatic unit;

[0020] Establish the mapping relationship between structural nodes and rectangular blocks based on the coordinates of each structural node;

[0021] The pneumatic unit center node and structural node contained in each rectangular block are determined based on the mapping relationship between the pneumatic unit center node and the rectangular block and the mapping relationship between the structural node and the rectangular block.

[0022] Optionally, the aerodynamic load of the central node of the aerodynamic unit in each rectangular block is distributed to the structural nodes in the same rectangular block, including:

[0023] Obtain the total aerodynamic load of the center nodes of all aerodynamic units in each rectangular block;

[0024] The total aerodynamic load is evenly distributed among the structural nodes located in the same rectangular block to obtain the load of the corresponding structural node.

[0025] Optionally, after dividing the wing surface into an upper wing surface and a lower wing surface with a chord line as the dividing line, it includes:

[0026] Obtain the loads of the structural nodes in each rectangular block on the upper and lower wing surfaces respectively;

[0027] After obtaining the structural node loads of each wing surface, the loads of the structural nodes of the upper and lower wing surfaces are combined to obtain the structural load of the entire wing.

[0028] Optionally, the total aerodynamic load of the center nodes of all aerodynamic units in each rectangular block is obtained, including:

[0029] The number of pneumatic unit center nodes in each rectangular block is determined based on the coordinates of the pneumatic unit center nodes.

[0030] Obtain the load components of the central node of each pneumatic unit in each rectangular block in the three coordinate axis directions;

[0031] The total aerodynamic load components of each aerodynamic unit center node in the three coordinate axes are determined based on the number of aerodynamic unit center nodes in each rectangular block.

[0032] The number of structural nodes in each rectangular block is determined based on the coordinates of the structural nodes, and the total aerodynamic load components of the aerodynamic unit center nodes in each rectangular block are evenly distributed to the corresponding coordinate axis directions of the structural nodes in the same rectangular block.

[0033] This application also provides a wing load conversion device, including:

[0034] The aerodynamic load acquisition module is used to acquire the aerodynamic loads at the center nodes of each aerodynamic unit on the wing surface.

[0035] A rectangular block planning module is used to divide the wing surface into multiple rectangular blocks, each of which includes at least one aerodynamic element grid and one structural element grid at a corresponding position.

[0036] The load conversion module is used to distribute the aerodynamic load of the aerodynamic unit center node in each rectangular block to the structural nodes in the same rectangular block, thus completing the structural load conversion.

[0037] An apparatus comprising:

[0038] One or more processors; and

[0039] One or more machine-readable media storing instructions thereon, which, when executed by the one or more processors, cause the device to perform the wing load conversion method.

[0040] A machine-readable medium having instructions stored thereon that, when executed by one or more processors, cause a device to perform the wing load conversion method described above.

[0041] As described above, this application provides a wing load conversion method, apparatus, device, and medium, which have the following beneficial effects.

[0042] This application obtains the aerodynamic loads of the center nodes of each aerodynamic unit on the wing surface; divides the wing surface into multiple rectangular blocks, each rectangular block including at least one aerodynamic unit mesh and one structural unit mesh at a corresponding position; and assigns the aerodynamic loads of the center nodes of the aerodynamic units in each rectangular block to the structural nodes within the same rectangular block, thus completing the structural load conversion. Dividing the wing surface into multiple rectangular blocks and performing load conversion on a rectangular block basis fully utilizes the condition that the aerodynamic and structural shapes are consistent, ensuring that each rectangular block contains both aerodynamic unit center nodes and structural nodes. This guarantees that each structural node can be assigned a corresponding load, avoiding the phenomenon where some structural nodes are assigned zero load while others are assigned large loads. The calculation is simple and the conversion accuracy is high. Attached Figure Description

[0043] Figure 1 This is a flowchart illustrating a wing load conversion method in one embodiment of this application.

[0044] Figure 2 This is a schematic diagram of a wing load conversion device in one embodiment of this application.

[0045] Figure 3 This is a schematic diagram of the device in one embodiment of this application.

[0046] Figure 4 This is a schematic diagram of the device in another embodiment of this application.

[0047] Figure 5 This is a schematic diagram of the rectangular block division of the wing in one embodiment of this application.

[0048] Figure 6 This is a flowchart illustrating the wing load conversion method in another embodiment of this application.

[0049] Figure 7 A schematic diagram of load distribution for the existing three-point arrangement method.

[0050] Figure 8 A schematic diagram of load distribution for the existing multi-point arrangement method. Detailed Implementation

[0051] 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.

[0052] 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.

[0053] Aircraft design requires strength analysis of the airframe structure. Aerodynamic loads are the primary input for this analysis, and it is necessary to rationally convert the loads on aerodynamic nodes to the loads on structural nodes required for the strength analysis. This load conversion process mainly involves two aspects: first, the search method for aerodynamic nodes to structural nodes; and second, the algorithm for converting aerodynamic node loads to structural node loads.

[0054] Existing technologies: Three-point arrangement, multi-point arrangement

[0055] 1) Three-point arrangement method

[0056] 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.

[0057] Please see Figure 7 Assume the load on the aerodynamic node P is Pj. Figure 5 Nodes 1, 2, and 3 are structural nodes, and fi is the load assigned to the structural node. If i = 1, 2, and 3, then fi = (Ai / A) * Pj. The final load Fi is the sum of the loads assigned to node i from different aerodynamic nodes.

[0058] 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.

[0059] 2) Multi-point arrangement method

[0060] Based on the principle of static equivalence, the constraint condition of minimum deformation energy is added, and it is not limited to three points. Please refer to [link / reference needed]. Figure 8 Assume that aerodynamic node A searches for n structural nodes with a radius of r, and there is a beam between the aerodynamic node and the structural node. The load P on aerodynamic node A is... A The load assigned to the corresponding structural node is P. j The resulting deformation energy is:

[0061]

[0062] EI is the bending stiffness of the hypothetical beam, Lj is the distance between the aerodynamic node and the structural node, i = 1, 2, ..., n-1, n.

[0063] For aerodynamic node A, after distributing the aerodynamic load to n structural nodes, the resulting deformation energy is:

[0064]

[0065] With static equilibrium as the constraint and the minimum strain energy U as the objective, the load Pj distributed from the aerodynamic node A to each structural node is solved using the Lagrange multiplier method. The final load on each structural node is obtained by adding the loads distributed from the different aerodynamic nodes.

[0066] Disadvantages and shortcomings of the three-point arrangement method: It searches for three structural nodes around a pneumatic node, but ignores the distance between the three structural nodes and the pneumatic node. When the distribution of structural nodes and pneumatic nodes differs greatly, the load on the pneumatic node will be distributed to structural nodes that are farther away, which will have an adverse effect on the distribution of local structural loads. At the same time, it will cause the torque formed by the structural load to differ greatly from the actual situation.

[0067] Disadvantages and limitations of the multi-point arrangement method: The multi-point arrangement method introduces the theory of deformation energy, aiming to improve load conversion accuracy by minimizing deformation energy during the conversion process. The node search method uses the aerodynamic node coordinates as the center and a radius of r for searching. However, searching in a circular shape on the structural mesh surface inevitably means that some structural nodes will not be found by any aerodynamic node, resulting in zero aerodynamic load assigned to these nodes and adversely affecting the local structural load distribution. Furthermore, when converting loads based on minimizing deformation energy, each aerodynamic node corresponds to a matrix to be solved. When there are many aerodynamic nodes, the calculation process becomes slower and the hardware requirements are higher. Occasionally, the matrix solution may fail, resulting in singularities and causing load conversion failure.

[0068] In view of the problems existing in the prior art, this application provides the following solutions, which will be described in detail below with reference to specific embodiments.

[0069] Please see Figure 1 This application provides a wing load conversion method, including the following steps:

[0070] Step S01: Obtain the aerodynamic loads at the center nodes of each aerodynamic unit on the wing surface;

[0071] Step S02: Divide the wing surface into multiple rectangular blocks, each rectangular block including at least one aerodynamic unit grid and one structural unit grid at the corresponding position;

[0072] Step S03: Distribute the aerodynamic load of the aerodynamic unit center node in each rectangular block to the structural node in the same rectangular block to complete the structural load conversion.

[0073] Since the aerodynamic shape and the structural shape are exactly the same, only the distribution of grid nodes is different, the condition that the aerodynamic shape and the structural shape are the same can be fully utilized to form the same rectangular block, and the load transfer can be performed on the central node of the aerodynamic unit and the structural node within the same rectangular block.

[0074] In one embodiment of this application, obtaining the aerodynamic loads at the center nodes of each aerodynamic element on the wing surface includes:

[0075] The wing surface is divided into an upper wing surface and a lower wing surface by a chord line;

[0076] The aerodynamic unit information of the upper wing surface and the lower wing surface is obtained respectively, wherein the aerodynamic unit information includes: unit number, unit center node coordinates, unit pressure, and the projection of the unit grid area in each coordinate direction;

[0077] The load of the corresponding pneumatic unit center node is calculated based on the pneumatic unit information;

[0078] The upper and lower wing surfaces are divided into multiple rectangular blocks based on the aerodynamic unit information.

[0079] Specifically, using the wing chord line as the dividing point, the upper and lower wing surfaces are separated, and the aerodynamic unit center nodes 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 structural load data of the overall wing.

[0080] Specifically, it includes the following steps:

[0081] After the aerodynamic load calculation is completed, the upper and lower wing surface data are output respectively. The output data includes the aerodynamic element center node number, the three-directional coordinates (X, Y, Z directions) of the aerodynamic element center node, the element pressure, and the projection of the element mesh area in the three coordinate directions.

[0082] 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.

[0083] A data reading interface was built, and the pneumatic output data was stored in an eight-dimensional array.

[0084] In one embodiment of this application, the wing surface is divided into multiple rectangular blocks, including:

[0085] The size of the rectangular block is determined based on the size of the pneumatic unit grid and the size of the structural unit grid, wherein the size of the rectangular block is greater than or equal to the size of the pneumatic unit grid and the size of the structural unit grid;

[0086] The wing surface is divided into multiple rectangular blocks based on the coordinates of the center node of the aerodynamic unit and the size of the rectangular blocks.

[0087] Specifically, the size of the rectangular blocks can be adjusted according to the aerodynamic mesh size and the structural mesh size to ensure that each rectangular block includes at least one aerodynamic element mesh and one structural element mesh. Each mesh contains at least 3-4 nodes, ensuring that each structural node is assigned its corresponding load and preventing singularities. In aerodynamic and structural finite element calculations, mesh sizes are generally small according to calculation requirements. While the rectangular size must be greater than or equal to the size of a single aerodynamic mesh and a single structural mesh, the rectangular size is also sufficiently small, resulting in sufficiently high accuracy for this conversion algorithm.

[0088] Please see Figure 5 Taking any airfoil as an example, the airfoil is divided into rectangular blocks. The size of each rectangular block is greater than or equal to the maximum of the size of the aerodynamic element mesh and the structural element mesh. This ensures that each rectangular block contains both the aerodynamic element center node and the structural node. Load transformation is performed on the aerodynamic element center nodes and structural nodes within the same rectangular block. This ensures that each structural node is assigned a corresponding load, avoiding the phenomenon where some structural nodes are assigned zero load while others are assigned a large load. This significantly improves the accuracy of local structural strength analysis in subsequent strength analyses.

[0089] In one embodiment of this application, after dividing the wing surface into multiple rectangular blocks, the following steps are included:

[0090] Establish the mapping relationship between the center nodes of each pneumatic unit and the rectangular block based on the coordinates of the center nodes of each pneumatic unit;

[0091] Establish the mapping relationship between structural nodes and rectangular blocks based on the coordinates of each structural node;

[0092] The pneumatic unit center node and structural node contained in each rectangular block are determined based on the mapping relationship between the pneumatic unit center node and the rectangular block and the mapping relationship between the structural node and the rectangular block.

[0093] Specifically, based on the coordinates of each rectangular block, when it is determined that the center node of the aerodynamic unit belongs to the current rectangular block, the rectangular block corresponding to the center node of the aerodynamic unit is marked, and a mapping relationship between the center node of the aerodynamic unit and the rectangular block is established. Similarly, based on the coordinates of the structural nodes, the rectangular blocks are traversed, and when it is determined that the structural node belongs to the current rectangular block, the rectangular block corresponding to the structural node is marked, and a mapping relationship between the structural node and the rectangular block is established. Based on these two sets of mapping relationships, the aerodynamic unit center nodes and structural nodes contained in each rectangular block can be determined.

[0094] In one embodiment of this application, the aerodynamic load of the central node of the aerodynamic unit in each rectangular block is distributed to the structural nodes located in the same rectangular block, including:

[0095] Obtain the total aerodynamic load of the center nodes of all aerodynamic units in each rectangular block;

[0096] The total aerodynamic load is evenly distributed among the structural nodes located in the same rectangular block to obtain the load of the corresponding structural node.

[0097] In one embodiment of this application, obtaining the total aerodynamic load of the center nodes of all aerodynamic units in each rectangular block includes:

[0098] The number of pneumatic unit center nodes in each rectangular block is determined based on the coordinates of the pneumatic unit center nodes.

[0099] Obtain the load components of the central node of each pneumatic unit in each rectangular block in the three coordinate axis directions;

[0100] The total aerodynamic load components of each aerodynamic unit center node in the three coordinate axes are determined based on the number of aerodynamic unit center nodes in each rectangular block.

[0101] The number of structural nodes in each rectangular block is determined based on the coordinates of the structural nodes, and the total aerodynamic load components of the aerodynamic unit center nodes in each rectangular block are evenly distributed to the corresponding coordinate axis directions of the structural nodes in the same rectangular block.

[0102] Specifically, within the same rectangular block, the loads at the center nodes of all aerodynamic units are summed. For a rectangular block, assuming there are m aerodynamic unit center nodes and n structural nodes, and the loads on each aerodynamic unit center node are Fxi, Fyi, and Fzi respectively, then the resultant force at the center nodes of the aerodynamic units is:

[0103]

[0104]

[0105]

[0106] For the structural nodes within the rectangular block, the load assigned to each node is:

[0107] fx = sumFx / n

[0108] fy = sumFy / n

[0109] fz = sumFz / n

[0110] The conversion algorithm shown in this invention can ensure that each structural node can be assigned a load, without the need to solve the matrix, the calculation process is simple, and the hardware requirements are low.

[0111] Please see Figure 6 In another embodiment of this application, the entire wing load conversion process can be described as follows:

[0112] 1) After the aerodynamic load calculation is completed, the upper and lower wing surface data are output respectively. The output data includes the aerodynamic element number, the coordinates of the aerodynamic element center node, the aerodynamic element pressure, and the projection of the aerodynamic element grid area in the three coordinate directions.

[0113] 2) Calculate the nodal loads in three directions at the center node of the aerodynamic unit.

[0114] 3) After the structural strength calculation mesh is generated, the upper and lower wing surface data are output respectively. The output data includes the node number and the three-directional coordinates of the node.

[0115] 4) Build a data reading interface and store the pneumatic output data and structural output data in a two-dimensional array respectively.

[0116] 5) Determine the size of the rectangular block based on the size of the aerodynamic unit mesh and the size of the structural unit mesh.

[0117] 6) Divide the wing surface into sections.

[0118] 7) Iterate through the block and sum the loads at the center node of the aerodynamic unit within the current block (sum the loads in the three directions separately).

[0119] 8) Within the current block, iterate through the structural nodes based on their coordinates. When a structural node belongs to the current block, mark it.

[0120] 9) Count the number of structural nodes in the same block, and distribute the load obtained in step 07) evenly to the structural nodes in the rectangular block.

[0121] 10) Repeat steps 07) to 09 for all blocks.

[0122] Please see Figure 2This 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.

[0123] In one embodiment, this application also provides a wing load conversion device, comprising: an aerodynamic load acquisition module 10, used to acquire the aerodynamic loads of the center nodes of each aerodynamic unit on the wing surface; a rectangular block planning module 11, used to divide the wing surface into multiple rectangular blocks, each rectangular block including at least one aerodynamic unit grid and one structural unit grid at a corresponding position; and a load conversion module 12, used to allocate the aerodynamic loads of the center nodes of the aerodynamic units in each rectangular block to the structural nodes in the same rectangular block, thereby completing the structural load conversion.

[0124] 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 this application embodiment does not limit the specific device.

[0125] 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 included in the wing load conversion method.

[0126] 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.

[0127] 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.

[0128] 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.

[0129] 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.

[0130] Figure 4 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.

[0131] 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.

[0132] 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.

[0133] 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.

[0134] 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-mentioned 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.

[0135] 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.

[0136] 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.

[0137] 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.

[0138] 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.

[0139] 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.

[0140] 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.

[0141] 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.

[0142] 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 wing loads, characterized in that, include: Obtain the aerodynamic loads at the center nodes of each aerodynamic element on the wing surface; Obtaining the aerodynamic loads at the center nodes of each aerodynamic element on the wing surface includes: dividing the wing surface into an upper wing surface and a lower wing surface using a chord line as the boundary; obtaining the aerodynamic element information for the upper wing surface and the lower wing surface respectively, wherein the aerodynamic element information includes: element number, coordinates of the element center node, element pressure, and projection of the element grid area in each coordinate direction; calculating the load at the corresponding aerodynamic element center node based on the aerodynamic element information; and dividing the upper wing surface and the lower wing surface into multiple rectangular blocks based on the aerodynamic element information. The wing surface is divided into multiple rectangular blocks, each rectangular block including at least one aerodynamic element grid and one structural element grid at a corresponding position; dividing the wing surface into multiple rectangular blocks includes: determining the size of the rectangular block according to the size of the aerodynamic element grid and the size of the structural element grid, wherein the size of the rectangular block is greater than or equal to the size of the aerodynamic element grid and the size of the structural element grid; dividing the wing surface into multiple rectangular blocks according to the size of the rectangular blocks; distributing the aerodynamic load of the aerodynamic element center node in each rectangular block to the structural node in the same rectangular block, including: obtaining the total aerodynamic load of all aerodynamic element center nodes in each rectangular block; distributing the total aerodynamic load evenly to each structural node in the same rectangular block to obtain the load of the corresponding structural node; The aerodynamic loads of the aerodynamic unit center nodes in each rectangular block are distributed to the structural nodes in the same rectangular block, thus completing the structural load conversion.

2. The wing load conversion method according to claim 1, characterized in that, After dividing the upper and lower wing surfaces into multiple rectangular blocks based on the aerodynamic unit information, the process includes: Establish the mapping relationship between the center nodes of each pneumatic unit and the rectangular blocks based on the coordinates of the center nodes of each pneumatic unit; Establish the mapping relationship between structural nodes and rectangular blocks based on the coordinates of each structural node; The pneumatic unit center node and structural node contained in each rectangular block are determined based on the mapping relationship between the pneumatic unit center node and the rectangular block and the mapping relationship between the structural node and the rectangular block.

3. The wing load conversion method according to claim 1, characterized in that, After dividing the wing surface into an upper wing surface and a lower wing surface with a chord line as the dividing line, it includes: Obtain the loads of the structural nodes in each rectangular block on the upper and lower wing surfaces respectively; After obtaining the structural node loads of each wing surface, the loads of the structural nodes of the upper and lower wing surfaces are combined to obtain the structural load of the entire wing.

4. The wing load conversion method according to claim 1, characterized in that, Obtain the total aerodynamic load on the center nodes of all aerodynamic units in each rectangular block, including: The number of pneumatic unit center nodes in each rectangular block is determined based on the coordinates of the pneumatic unit center nodes. Obtain the load components of the central node of each pneumatic unit in each rectangular block in the three coordinate axis directions; The total aerodynamic load components of each aerodynamic unit center node in the three coordinate axes are determined based on the number of aerodynamic unit center nodes in each rectangular block. The number of structural nodes in each rectangular block is determined based on the coordinates of the structural nodes, and the total aerodynamic load components of the aerodynamic unit center nodes in each rectangular block are evenly distributed to the corresponding coordinate axis directions of the structural nodes in the same rectangular block.

5. A wing load conversion device, characterized in that, include: The aerodynamic load acquisition module is used to acquire the aerodynamic loads at the center nodes of each aerodynamic unit on the wing surface. Obtaining the aerodynamic loads at the center nodes of each aerodynamic element on the wing surface includes: dividing the wing surface into an upper wing surface and a lower wing surface using a chord line as the boundary; obtaining the aerodynamic element information for the upper wing surface and the lower wing surface respectively, wherein the aerodynamic element information includes: element number, coordinates of the element center node, element pressure, and projection of the element grid area in each coordinate direction; calculating the load at the corresponding aerodynamic element center node based on the aerodynamic element information; and dividing the upper wing surface and the lower wing surface into multiple rectangular blocks based on the aerodynamic element information. A rectangular block planning module is used to divide the wing surface into multiple rectangular blocks, each rectangular block including at least one aerodynamic element grid and one structural element grid at a corresponding position; dividing the wing surface into multiple rectangular blocks includes: determining the size of the rectangular block according to the size of the aerodynamic element grid and the size of the structural element grid, wherein the size of the rectangular block is greater than or equal to the size of the aerodynamic element grid and the size of the structural element grid; dividing the wing surface into multiple rectangular blocks according to the size of the rectangular blocks; distributing the aerodynamic load of the aerodynamic element center node in each rectangular block to the structural node in the same rectangular block includes: obtaining the total aerodynamic load of all aerodynamic element center nodes in each rectangular block; distributing the total aerodynamic load evenly to each structural node in the same rectangular block to obtain the load of the corresponding structural node; The load conversion module is used to distribute the aerodynamic load of the aerodynamic unit center node in each rectangular block to the structural nodes in the same rectangular block, thus completing the structural load conversion.

6. 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 1-4.

7. 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 1-4.

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