Cell-based lattice wing structure skin block geometry parameter optimization design method

Abstract

The application relates to a cell-based lattice wing structure skin block geometry parameter optimization design method, which extracts the suction pressure of the maximum suction position of a wing surface under various working conditions as the load boundary condition of the skin block under various working conditions, transforms the length, width and thickness of the skin block, calculates the maximum out-of-plane deformation deflection under various working conditions, further draws a relationship diagram of the maximum out-of-plane deformation deflection with the working condition change under different skin block length, width and thickness, analyzes the influence law among the three, determines the optimal skin block length, width and thickness range, so that the designed skin block can maintain a small out-of-plane deformation deflection under various working conditions and does not have a sudden change, is strong in theory, has high design efficiency, can guarantee that the skin block has a cooperative deformation capacity with the lattice cell, can keep the wing aerodynamic shape smooth and continuous, and will not have stability problems such as buckling and wrinkling when bearing the out-of-plane aerodynamic load.

Description

Technical Field

[0001] This application belongs to the field of design technology of lattice wing structure skin block, specifically involving a cell-based geometric parameter optimization design method for lattice wing structure skin block. Background Technology

[0002] In a cell-based lattice wing structure, each skin module has pre-drilled connection holes at its four vertices, which are then connected to the vertices of the four inner lattice cells via riveting or other fixing methods. Figure 1 As shown, it possesses excellent properties such as ultralight weight, high designability, and high specific stiffness / specific strength. It can simultaneously meet the requirements for lightweight, electrical insulation, radiation resistance, high and low temperature resistance, and deformation function. At the same time, its discrete and modular characteristics also provide potential opportunities for distributed intelligent control and drive, which is conducive to realizing any form of continuous smooth wing deformation.

[0003] In the cell-based lattice wing structure, the skin blocks are arranged in an overlapping manner to form the overall skin. Adjacent skin blocks are not connected and have no obvious gaps, allowing them to slide relative to each other. During the sliding process, the overlapping area of ​​the boundary ensures that there are no obvious gaps between the skin blocks, so that the overall skin exhibits "stretching" or "compression" along the spanwise and chordal directions of the wing. It has multi-directional deformation capabilities, which can meet the requirements of various deformation strategies such as variable camber, variable thickness, and wing torsion of the lattice wing structure.

[0004] The geometric parameter design of the skin module mainly includes the design of length, width and thickness. It should have the ability to deform in coordination with the lattice cell, maintain the smooth and continuous aerodynamic shape of the wing, and not have stability problems such as buckling and wrinkling when subjected to out-of-plane aerodynamic loads.

[0005] Currently, the design of geometric parameters for skin modules is mostly based on experience, lacks reliable theoretical support, is greatly influenced by subjectivity, has high uncertainty, and is difficult to obtain optimal results.

[0006] This application is made in view of the aforementioned technical deficiencies.

[0007] It should be noted that the above background information is only used to assist in understanding the inventive concept and technical solution of this application, and it does not necessarily belong to the prior art of this patent application. In the absence of clear evidence that the above information was disclosed on the filing date of this application, the above background information should not be used to evaluate the novelty and inventiveness of this application. Summary of the Invention

[0008] The purpose of this application is to provide a cell-based method for optimizing the geometric parameters of lattice wing structure skin blocks, in order to overcome or mitigate at least one of the known technical defects.

[0009] The technical solution of this application is:

[0010] A cell-based method for optimizing the geometric parameters of lattice wing structure skin modules includes:

[0011] Step 1: Calculate the pressure distribution on the airfoil under different operating conditions, and extract the suction pressure P0 at the location of maximum suction on the airfoil under each operating condition.

[0012] Step 2: Connect the four vertices of the skin block to the four lattice cell vertices, which is equivalent to a simply supported thin plate. Establish an equivalent model of the thin plate in elasticity. Distribute the suction pressure P0 at the location of the maximum suction force on the wing surface under various working conditions evenly on it. Change the length a, width b, and thickness h of the skin block, and calculate the maximum out-of-plane deformation deflection w under various working conditions:

[0013]

[0014]

[0015] in,

[0016] D represents the bending stiffness of the skin assembly material;

[0017] E is the elastic modulus of the skin assembly material;

[0018] v is the Poisson's ratio of the skin assembly;

[0019] Step 3: Draw a graph showing the relationship between the maximum out-of-plane deformation deflection w and the working conditions for different skin block lengths a, widths b, and thicknesses h. Determine the range of skin block lengths a, widths b, and thicknesses h to ensure that the skin block maintains a small out-of-plane deformation deflection under various working conditions without abrupt changes.

[0020] Optionally, in the above-mentioned cell-based lattice wing structure skin block geometric parameter optimization design method, in step one, the calculation of the wing surface pressure distribution under different working conditions is based on the establishment of a three-dimensional wing aerodynamic load analysis model by CFD and the calculation is performed.

[0021] Optionally, in the above-mentioned cell-based lattice wing structure skin block geometric parameter optimization design method, in step two, the skin block with four vertices connected to the four lattice cell vertices is equivalent to a four-sided simply supported thin plate, and an equivalent model of elastic mechanical thin plate is established based on Kirchhoff theory.

[0022] Optionally, in the above-mentioned cell-based lattice wing structure skin block geometric parameter optimization design method, in step two, the length a, width b, and thickness h of the skin block are transformed, and the maximum out-of-plane deformation deflection w under various working conditions is calculated. The step size for transforming the length a and width b of the skin block is 0.1, and the step size for transforming the thickness h is 0.01.

[0023] This application has at least the following beneficial technical effects:

[0024] This paper presents a cell-based method for optimizing the geometric parameters of skin modules for lattice wing structures. The method extracts the suction pressure at the location of maximum suction on the wing surface under various operating conditions, using it as the load boundary condition for the skin module. By varying the length, width, and thickness of the skin module, the maximum out-of-plane deflection under each condition is calculated. A graph showing the relationship between the maximum out-of-plane deflection and the operating conditions for different skin module lengths, widths, and thicknesses is then plotted. The influence of these three factors is analyzed to determine the optimal range for the skin module's length, width, and thickness. This method ensures that the designed skin module maintains a small out-of-plane deflection under various operating conditions without abrupt changes. It is theoretically sound, highly efficient, and guarantees that the skin module possesses the ability to deform in tandem with the lattice cells. It maintains a smooth and continuous aerodynamic shape of the wing and prevents buckling, wrinkling, or other stability issues when subjected to out-of-plane aerodynamic loads, thus ensuring the wing's aerodynamic performance. Attached Figure Description

[0025] Figure 1 This is a schematic diagram of a cell-based lattice wing structure and its partial design provided in an embodiment of this application;

[0026] Figure 2 This is a schematic diagram of establishing an equivalent model of an elastic thin plate by equating the skin assembly to a simply supported thin plate on four sides, as provided in the embodiments of this application.

[0027] Figure 3 This is a schematic diagram of the geometric parameter optimization design method for the skin block of a lattice wing structure based on cell unit provided in the embodiments of this application.

[0028] To better illustrate this embodiment, some parts in the accompanying drawings may be omitted, enlarged, or reduced, and do not represent the actual size of the product. Furthermore, the accompanying drawings are for illustrative purposes only and should not be construed as limiting this patent. Detailed Implementation

[0029] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings. Other related parts can be referred to the general design. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined with each other to obtain new embodiments.

[0030] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer," etc., used in this application description to indicate relative direction or positional relationship are used only to indicate relative orientation or positional relationship, and do not imply that the device or component must have a specific orientation, or be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly, and therefore should not be construed as a limitation on this application. The terms "first," "second," "third," and similar terms used in this application description are used only for descriptive purposes to distinguish different components, and should not be construed as indicating or implying relative importance. The terms "a," "one," or "the," etc., used in this application description should not be construed as an absolute limitation on quantity, but should be construed as indicating the existence of at least one. The terms "including," "comprising," etc., used in this application description mean that the element or object preceding the word covers the element or object listed after the word and its equivalents, without excluding other elements or objects.

[0031] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, terms such as “installation,” “connection,” and “linkage” used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; or it can be a connection within two components. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0032] The following is in conjunction with the appendix Figures 1 to 3 This application provides a more detailed explanation of the cell-based geometric parameter optimization design method for lattice wing structure skin modules.

[0033] Step 1: Establish a three-dimensional aerodynamic load analysis model of the wing based on CFD, calculate the pressure distribution on the wing surface under different operating conditions, extract the suction pressure P0 at the location of the maximum suction force on the wing surface under each operating condition, and use it as the load boundary condition of the skin block under each operating condition to calculate the maximum out-of-plane deformation deflection of the skin block.

[0034] Step 2: Connect the four vertices of the skin block to the four lattice cell vertices, which is equivalent to a simply supported thin plate. Based on Kirchhoff's theory, establish an equivalent model of the thin plate based on elasticity. Distribute the suction pressure P0 at the location of maximum suction force on the wing surface under various working conditions evenly on it. Develop a fast calculation program for the maximum out-of-plane deformation deflection of the skin block based on Matlab. By changing the length a, width b, and thickness h of the skin block, calculate the maximum out-of-plane deformation deflection w under various working conditions.

[0035]

[0036]

[0037] in,

[0038] D represents the bending stiffness of the skin assembly material;

[0039] E is the elastic modulus of the skin assembly material;

[0040] v is the Poisson's ratio of the skin assembly.

[0041] The step size for transforming the length a and width b of the skin block is 0.1, and the step size for transforming the thickness h is 0.01.

[0042] Step 3: Draw a graph showing the relationship between the maximum out-of-plane deformation deflection w and the working conditions for different skin block lengths a, widths b, and thicknesses h. This graph reflects the influence of different skin block geometric parameters and aerodynamic loads at different angles of attack on the local bulges of the skin block. Analyze the influence relationship among the three factors and determine the optimal range of skin block lengths a, widths b, and thicknesses h. Within this range, the skin block maintains a small out-of-plane deformation deflection under various working conditions without any abrupt changes.

[0043] The cell-based geometric parameter optimization design method for skin blocks of lattice wing structures disclosed in the above embodiments extracts the suction pressure at the location of maximum suction force on the wing surface under various working conditions, using it as the load boundary condition for the skin block under each working condition. By changing the length, width, and thickness of the skin block, the maximum out-of-plane deformation deflection under each working condition is calculated. Then, a graph showing the relationship between the maximum out-of-plane deformation deflection and the working condition under different skin block lengths, widths, and thicknesses is plotted. The influence law among the three factors is analyzed, and the optimal range of skin block length, width, and thickness is determined. This ensures that the designed skin block can maintain a small out-of-plane deformation deflection under various working conditions without abrupt changes. It has strong theoretical basis and high design efficiency, and can guarantee that the skin block has the ability to deform in tandem with the lattice cells. It can maintain the smooth and continuous aerodynamic shape of the wing and will not experience stability problems such as buckling or wrinkling when subjected to out-of-plane aerodynamic loads, thus ensuring the aerodynamic performance of the wing.

[0044] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.

Claims

1. A cell-based method for optimizing the geometric parameters of lattice wing structure skin modules, characterized in that, include: Step 1: Calculate the pressure distribution on the airfoil under different operating conditions, and extract the suction pressure at the location of maximum suction on the airfoil under each operating condition. ; Step 2: Connect the four vertices of the skin block to the four lattice cell vertices, which is equivalent to a simply supported thin plate. Establish an equivalent model of the thin plate in elasticity, and evenly distribute the suction pressure at the location of maximum suction force on the wing surface under various working conditions on it. By varying the length a, width b, and thickness h of the skin assembly, calculate the maximum out-of-plane deflection w under various working conditions: ； ； in, The bending stiffness of the skin assembly material; The elastic modulus of the skin assembly material; The Poisson's ratio of the skin assembly; Step 3: Draw a graph showing the relationship between the maximum out-of-plane deformation deflection w and the working conditions for different skin block lengths a, widths b, and thicknesses h. Determine the range of skin block lengths a, widths b, and thicknesses h to ensure that the skin block maintains a small out-of-plane deformation deflection under various working conditions without abrupt changes.

2. The method for optimizing the geometric parameters of lattice wing structure skin modules based on cell units according to claim 1, characterized in that, In step one, the calculation of the airfoil pressure distribution under different operating conditions is based on the establishment of a three-dimensional airfoil aerodynamic load analysis model by CFD.

3. The method for optimizing the geometric parameters of lattice wing structure skin modules based on cell units according to claim 1, characterized in that, In step two, the skin block with four vertices connected to the vertices of the four lattice cells is equivalent to a simply supported thin plate on four sides, and an equivalent model of the thin plate in elasticity is established, which is based on Kirchhoff's theory.

4. The method for optimizing the geometric parameters of lattice wing structure skin modules based on cell units according to claim 1, characterized in that, In step two, the length a, width b, and thickness h of the skin block are transformed, and the maximum out-of-plane deformation deflection w under each working condition is calculated. The step size for transforming the length a and width b of the skin block is 0.1, and the step size for transforming the thickness h is 0.01.

Images