Method, device and equipment for optimizing static strength of outer wing box section made of composite material

Abstract

The invention discloses a method, a device and equipment for optimizing the static strength of a composite material outer wing box section. The method comprises the following steps: performing static calculation on a finite element model of the composite material outer wing box section to obtain an internal force solution; independently carrying out static strength parameter optimization on the structure of the composite material outer wing box section by adopting a dichotomy according to the internal force solution to obtain optimized parameters; carrying out attribute updating on the finite element model according to the optimization parameters to obtain an updated finite element model; when it is determined that the weight of the updated finite element model meets the requirement, static strength checking and parameter adjustment are conducted on the updated finite element model, and an optimization result is obtained. The internal force distribution of the composite material outer wing box section structure is calculated based on the finite element model, static strength parameter optimization is independently carried out on the skin and the stringer based on an internal force solution so as to realize optimal decoupling of the skin and the stringer, structural parameters which meet the strength requirement and are the lightest in structural weight are obtained, and therefore the efficiency of static strength optimization of the composite material outer wing box section is improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aircraft technology, in particular to a composite outer wing box section static strength optimization method, device and equipment. BACKGROUND

[0002] The static strength optimization of the composite outer wing box section of a civil aircraft is based on the input of aerodynamic shape, load and structural arrangement, etc., to determine the size parameters, layering ratio and corresponding structural weight with the highest structural efficiency under the constraints of static strength, stability and process, etc., by adjusting the size parameters and layering ratio of structures such as skin, stringer, spar and rib, etc.

[0003] The current design variables and design constraints of the composite outer wing box section of a civil aircraft are numerous, and the load conditions are complex. Since the skin and the stringer belong to the same component, the skin and the stringer are usually adjusted simultaneously during the static strength optimization. However, it is not easy to converge when adjusting the parameters of the skin and the stringer simultaneously, thereby affecting the efficiency of the static strength optimization. SUMMARY

[0004] The present application provides a composite outer wing box section static strength optimization method to improve the efficiency of the static strength optimization of the composite outer wing box section.

[0005] According to a first aspect of the present application, a composite outer wing box section static strength optimization method is provided, comprising: performing static force calculation on a finite element model of a composite outer wing box section to obtain an internal force solution;

[0006] According to the internal force solution, a static strength parameter optimization is performed on the structure of the composite outer wing box section separately by using a dichotomy method to obtain optimization parameters, wherein the structure includes a skin, a stringer, a spar and a rib;

[0007] According to the optimization parameters, attribute updating is performed on the finite element model to obtain an updated finite element model;

[0008] When it is determined that the weight of the updated finite element model meets the requirements, static strength checking and parameter adjustment are performed on the updated finite element model to obtain an optimization result.

[0009] According to another aspect of the present application, a composite outer wing box section static strength optimization device is provided, comprising: a static force calculation module configured to perform static force calculation on a finite element model of a composite outer wing box section to obtain an internal force solution;

[0010] A static strength parameter optimization module is configured to perform static strength parameter optimization on the structure of the composite outer wing box section separately according to the internal force solution by using a dichotomy method to obtain optimization parameters, wherein the structure includes a skin, a stringer, a spar and a rib;

[0011] a finite element model attribute updating module configured to perform attribute updating on the finite element model according to the optimization parameters to obtain an updated finite element model;

[0012] a static strength checking module configured to perform static strength checking and parameter adjustment on the updated finite element model when it is determined that the weight of the updated finite element model meets the requirements.

[0013] According to another aspect of the present application, an electronic device is provided, which comprises:

[0014] at least one processor; and

[0015] a memory in communication with the at least one processor; wherein

[0016] the memory stores a computer program executable by the at least one processor, and the computer program is executed by the at least one processor to enable the at least one processor to perform the method according to any one of the embodiments of the present application.

[0017] According to another aspect of the present application, a computer readable storage medium is provided, which stores computer instructions for enabling a processor to perform the method according to any one of the embodiments of the present application when executed.

[0018] The technical solution of the embodiments of the present application is based on finite element model to calculate the internal force distribution of the composite outer wing box section structure, and based on the internal force solution to separately perform static strength parameter optimization on the skin and the longeron to realize the optimization decoupling of the skin and the longeron, to obtain the structural parameters with the lightest structure weight meeting the strength requirements, thereby improving the static strength optimization efficiency of the composite outer wing box section.

[0019] It should be understood that the content described in this part is not intended to identify the key or important features of the embodiments of the present application, nor to limit the scope of the present application. Other features of the present application will become apparent from the following description. BRIEF DESCRIPTION OF DRAWINGS

[0020] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings needed in the embodiment description will be briefly introduced as follows. Obviously, the drawings in the following description are only some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative labor.

[0021] Figure 1 is a flow chart of a composite outer wing box section static strength optimization method according to the first embodiment of the present application;

[0022] Figure 2 is a structural schematic diagram of a finite element model of a composite outer wing box segment provided according to an embodiment of the present application;

[0023] Figure 3 is a flow chart of a method for static strength optimization of a composite outer wing box segment provided according to a second embodiment of the present application;

[0024] Figure 4 is a schematic diagram of the principle of dichotomy provided according to the second embodiment of the present application;

[0025] Figure 5 is a flow chart of a method for static strength optimization of a composite outer wing box segment provided according to a third embodiment of the present application;

[0026] Figure 6 is a structural schematic diagram of a device for static strength optimization of a composite outer wing box segment provided according to a fourth embodiment of the present application;

[0027] Figure 7 is a structural schematic diagram of an electronic device provided according to a fifth embodiment of the present application. DETAILED DESCRIPTION

[0028] In order to make the technical personnel in the art better understand the present application, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, not all. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor should be within the scope of protection of the present application.

[0029] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, and do not necessarily describe a specific order or sequence. It should be understood that the data thus used can be interchanged under appropriate circumstances, so that the embodiments of the present application described herein can be implemented in an order other than those illustrated or described herein. In addition, the terms "include" and "have" and any variations thereof are intended to cover non-exclusive inclusion, for example, a process, method, system, product or device including a series of steps or units does not necessarily limit to those steps or units clearly listed, but can include other steps or units not clearly listed or inherent to these processes, methods, products or devices.

[0030] Embodiment one

[0031] Figure 1 A flow chart of a method for static strength optimization of a composite outer wing box segment is provided for the first embodiment of the present application, as shown in Figure 1 the method comprises:

[0032] Step S101 : performing static calculation on the finite element model of the composite material outer wing box section to obtain an internal force solution.

[0033] Optionally, before performing static calculation on the finite element model of the composite material outer wing box section to obtain the internal force solution, the method further includes: establishing a finite element model of the composite material outer wing box section; and setting material properties, unit section properties, constraints, and boundary conditions for the finite element model.

[0034] Specifically, in this embodiment, a natural grid finite element model is established for the composite material outer wing box structure, such as Figure 2 The figure shows the structure of the established finite element model of the composite outer wing box section. After the model is established, the material properties, unit section properties, constraints, and boundary conditions will be set for the finite element model. Material properties include elastic modulus, Poisson's ratio, density, and allowable value; unit section properties include ply angle, ply thickness, material selection, and one-dimensional unit section parameters; and constraints include the design space of optimization variables, strength analysis method, Poisson's ratio, stiffness ratio, and process constraints. The design space includes thickness variation range, ply ratio variation range, dimensional parameter variation range, etc. This embodiment is only an example and does not limit the specific content of the finite element model settings. Users can set them according to actual needs.

[0035] Optionally, after performing static calculation on the finite element model of the composite material outer wing box section to obtain the internal force solution, it also includes: extracting internal forces from the internal force solution, wherein the internal forces include skin unit loads, long stringer unit loads, beam web unit loads, beam flange unit loads, rib web unit loads and rib flange unit loads.

[0036] In the embodiment, after the finite element model corresponding to the composite outer wing box section is established, the internal force solution is obtained by static calculation of the finite element model. In the static calculation, the load is applied to the finite element model to simulate the external force of the model in the actual working condition. In addition, the static equilibrium equation matched with the finite element model is determined in advance in the embodiment. Therefore, the displacement field of the model is obtained by solving the corresponding linear equation set. In the solving process, the computer software automatically performs iterative calculation until the balance condition is met, so that the internal force solution is obtained according to the solving result. After the internal force solution is obtained in the embodiment, the internal force extraction is performed, specifically, the skin element load, the stringer element load, the beam web element load, the beam flange element load, the rib web element load and the rib flange element load are extracted. The extracted internal force is used for subsequent optimization of the structure parameters. Of course, the extracted internal force is only used as an example in the embodiment and is not limited to the extracted internal force. The element load of different structures refers to the external force or acting force borne by the element of different structures in the finite element analysis. For example, the skin element is a kind of finite element model used for simulating the thin shell structure and is commonly used in the fields of aerospace and automobile manufacturing. It can simulate the mechanical behavior of the material under complex load. The skin element load refers to the external force or acting force borne by the skin element. The skin element load is only used as an example in the embodiment. The principle of the element load of other structures is basically the same as that of the skin element load. The embodiment will not be described in detail.

[0037] In step S102, the structure of the composite outer wing box section is individually optimized according to the internal force solution by using the dichotomy method to obtain the optimized parameters.

[0038] Optionally, the structure of the composite outer wing box section is individually optimized according to the internal force solution by using the dichotomy method to obtain the optimized parameters, including: the beam web of the composite outer wing box section is optimized according to the beam web element load by using the dichotomy method to obtain the beam web optimized parameters, wherein the beam web optimized parameters include the minimum beam web thickness and the beam web layering ratio corresponding to the minimum beam web thickness; the skin of the composite outer wing box section is optimized according to the skin element load by using the dichotomy method to obtain the skin optimized parameters, wherein the skin optimized parameters include the minimum skin thickness and the skin layering ratio corresponding to the minimum skin thickness; the stringer of the composite outer wing box section is optimized according to the stringer element load by using the dichotomy method to obtain the stringer optimized parameters, wherein the stringer optimized parameters include the minimum stringer cross-sectional size and the stringer layering ratio corresponding to the minimum stringer cross-sectional size, and the stringer cross-sectional size includes the web thickness and the web height.

[0039] Optionally, after obtaining the beam web optimization parameters by using dichotomy to perform static strength parameter optimization on the beam web of the composite outer wing box section according to the beam web unit load, the method further comprises: performing static strength parameter optimization on the beam stringer of the composite outer wing box section according to the beam stringer unit load and the beam web optimization parameters, and obtaining beam stringer optimization parameters.

[0040] Optionally, the method of obtaining the beam web optimization parameters by using dichotomy to perform static strength parameter optimization on the beam web of the composite outer wing box section according to the beam web unit load comprises: obtaining beam web parameter variables, wherein the beam web parameter variables comprise beam web layering proportion upper and lower limits, beam web thickness upper and lower limits, and a beam web initial thickness; performing static strength checking according to the beam web unit load and the beam web parameter variables to obtain minimum margins corresponding to each failure mode, wherein the failure modes comprise tension, compression, shear, composite strain, uniaxial compression stability, biaxial compression stability, shear stability, and compression-shear composite stability; adjusting the beam web initial thickness at each beam web layering proportion by using dichotomy according to the minimum margins, to obtain beam web thicknesses corresponding to each beam web layering proportion; comparing the beam web thicknesses corresponding to each beam web layering proportion to obtain a minimum beam web thickness, and taking the minimum beam web thickness and the beam web layering proportion corresponding to the minimum beam web thickness as the beam web optimization parameters.

[0041] Optionally, the method of obtaining the skin optimization parameters by using dichotomy to perform static strength parameter optimization on the skin of the composite outer wing box section according to the skin unit load comprises: obtaining skin parameter variables, wherein the skin parameter variables comprise skin layering proportion upper and lower limits, skin thickness upper and lower limits, and a skin initial thickness; performing static strength checking according to the skin unit load and the skin parameter variables to obtain minimum margins corresponding to each failure mode; adjusting the skin initial thickness at each skin layering proportion by using dichotomy according to the minimum margins, to obtain skin thicknesses corresponding to each skin layering proportion; comparing the skin thicknesses corresponding to each skin layering proportion to obtain a minimum skin thickness, and taking the minimum skin thickness and the skin layering proportion corresponding to the minimum skin thickness as the skin optimization parameters.

[0042] Optionally, the stringer optimization parameters of the composite outer wing box section are obtained by static strength parameter optimization of the stringer using dichotomy according to stringer unit load, including: obtaining stringer parameter variables, wherein the stringer parameter variables include stringer layer proportion upper and lower limits, stringer initial cross-sectional dimensions, wherein the initial cross-sectional dimensions include stringer initial web thickness and stringer initial web height; performing stringer web local stability checking according to the stringer unit load and the stringer parameter variables to obtain a first margin; adjusting the stringer initial web thickness under each stringer layer proportion using dichotomy according to the first margin to obtain stringer adjusted web thicknesses corresponding to each stringer layer proportion; performing stringer strain and combined section column strength checking according to the stringer unit load and the stringer parameter variables based on the stringer adjusted web thicknesses corresponding to each stringer layer proportion to obtain a second margin; adjusting the stringer initial web height and the stringer adjusted web thicknesses under each stringer layer proportion using dichotomy according to the second margin to obtain stringer cross-sectional dimensions corresponding to each stringer layer proportion; comparing the stringer cross-sectional dimensions corresponding to each stringer layer proportion to obtain minimum stringer cross-sectional dimensions, and taking the minimum stringer cross-sectional dimensions and the stringer layer proportion corresponding to the minimum stringer cross-sectional dimensions as the stringer optimization parameters.

[0043] Specifically, the composite outer wing box section includes beam webs, stringers, spars and ribs, wherein the spar includes beam webs and beam edge strips, and in this embodiment, the beam webs, stringers and spars are respectively optimized based on the extracted internal forces. In addition, the parameter optimization of the ribs based on the extracted internal forces is also involved in this embodiment, but since the improvement of the ribs follows the existing parameter optimization method of the ribs and there is no corresponding improvement, it is not the focus of this application, so it will not be described in this embodiment. The beam web optimization parameters obtained through the above optimization process include the minimum beam web thickness and the beam web layup ratio corresponding to the minimum beam web thickness; the skin optimization parameters include the minimum skin thickness and the skin layup ratio corresponding to the minimum skin thickness; and the stringer optimization parameters include the minimum stringer cross-sectional size and the stringer layup ratio corresponding to the minimum stringer cross-sectional size. Among them, the parameter optimization principles of the beam web and the skin are the same, only the thickness adjustment is involved, while the parameter optimization of the stringer involves the adjustment of the stringer web thickness and the stringer web height, and the stringer web thickness and the stringer web height are decoupled. In this embodiment, the skin and the stringer in the same structure are split, and since the distance between the skin and the centroid of the box section profile is farther, the structural efficiency is greater than that of the stringer, therefore, the strategy of optimizing the skin first and then the stringer is adopted to decouple the parameter optimization of the skin and the stringer, and by defining the stringer optimization strategy, the parameter optimization of the stringer web height and the web thickness is decoupled, the optimization convergence speed is improved, and the bisection method is involved in the parameter optimization of the beam web, the skin and the stringer. The bisection method is used to obtain the structural parameters with the lightest structure weight that meet the strength requirements, thereby speeding up the optimization process of the optimization variables.

[0044] In step S103, the attribute of the finite element model is updated according to the optimization parameters to obtain an updated finite element model.

[0045] In this embodiment, after the static strength parameter optimization of each structure is performed, the optimization parameters of each structure are exported, and the exported optimization parameters are used to update the attributes of the finite element model. Specifically, the unit thickness and the layup ratio are adjusted according to the optimization parameters, thereby effectively reducing the weight of the updated finite element model.

[0046] It should be noted that after the updated finite element model is obtained, the weight of the finite element model before updating is compared.

[0047] In step S104, when it is determined that the weight of the updated finite element model meets the requirements, the static strength of the updated finite element model is checked and the parameters are adjusted to obtain the optimization result.

[0048] Optionally, when it is determined that the weight of the updated finite element model meets the requirements, then the static strength checking and parameter adjustment are performed on the updated finite element model, including: obtaining the weight of the historical finite element model of the adjacent iteration optimization, calculating the weight difference between the weight of the historical finite element model and the weight of the updated finite element model; when it is determined that the weight difference is less than a preset threshold, then the static strength checking and parameter adjustment are performed on the updated finite element model to obtain the optimization result.

[0049] Specifically, in actual application, multiple iteration optimization processes are usually involved, so after the updated finite element model corresponding to the current iteration number is obtained, the weight of the updated finite element model is calculated, and the weight of the historical finite element model of the adjacent iteration optimization is also obtained, the weight difference between the weight of the historical finite element model and the weight of the updated finite element model is calculated, and whether convergence is judged according to the obtained weight difference. When judging whether to converge, the weight difference is compared with a preset threshold, for example, 1%, when the weight difference is less than or equal to 1%, the optimization is ended, and if the weight difference is greater than 1%, the above static strength parameter optimization process is repeated until the weight difference is less than or equal to 1%.

[0050] When it is determined that the weight of the updated finite element model meets the requirements, the last round of static force calculation and strength checking is performed on the updated finite element model to obtain the strength margin corresponding to each structure, and the strength margin less than 0 is improved to be greater than or equal to 0, and the specific improvement amplitude can be determined with reference to the related properties of the finite element model. In the embodiment, the specific value of the improvement amplitude is not limited, as long as it can be improved to be greater than or equal to 0, it is within the protection scope of the application.

[0051] In the embodiment of the application, the internal force distribution of the composite outer wing box section structure is calculated based on the finite element model, and the skin and the longeron are separately optimized for static strength parameters based on the internal force solution to realize the optimization decoupling of the skin and the longeron, so that the structure parameters meeting the strength requirements and having the lightest weight are obtained, thereby improving the efficiency of the static strength optimization of the composite outer wing box section.

[0052] Embodiment two

[0053] Figure 3 The flowchart of the static strength optimization method of the composite outer wing box section provided in the embodiment two of the application is based on the above-mentioned embodiment, and the skin optimization parameter obtained by the static strength parameter optimization of the skin of the composite outer wing box section by using the dichotomy method according to the skin unit load in the above-mentioned embodiment is specifically described, as shown in the figure, the method comprises the following steps. Figure 3

[0054] In step S201, the skin parameter variable is obtained.

[0055] ​Specifically, in the present embodiment, when the skin is subjected to static strength parameter optimization, the skin parameter variables need to be obtained in advance, and the skin parameter variables include skin layer ratio upper and lower limits, skin thickness upper and lower limits, and skin initial thickness. The skin layer ratio refers to the proportion of different fiber directions in the total number of layers in the composite laminate, for example, 0 degrees, ±45 degrees, or 90 degrees. The fiber layer in different directions determines the mechanical properties of the material under no load, for example, 0-degree layer mainly bears longitudinal load, ±45-degree layer mainly resists shear force, and reasonable design of layer ratio can improve the tensile strength, compressive strength, impact resistance, and fatigue resistance of the material. In aircraft design, the selection of skin layer ratio needs to be optimized according to the load characteristics. Therefore, in the present embodiment, the layer ratio upper and lower limits can be pre-configured, and the skin layer ratio is traversed within the range to obtain the skin thickness corresponding to each skin layer ratio, and the skin layer ratio meeting the requirements is selected from the skin thickness according to the requirements. In addition, for the skin, the optimization variable corresponding to the skin is the skin thickness A, so the present embodiment obtains the skin initial thickness, the upper limit of the skin thickness A_U, and the lower limit of the skin thickness A_L. Subsequently, the skin static strength parameter optimization is performed based on the above-obtained skin parameter variables and the skin unit load obtained by internal force extraction.

[0056] In step S202, the minimum margin corresponding to each failure mode is obtained by static strength checking according to the skin unit load and the skin parameter variables.

[0057] In the present embodiment, the skin unit load and the skin parameter variables are used as input to check the static strength of the skin. When checking the static strength of the skin, the margins corresponding to each failure mode, such as tension, compression, shear, composite strain, uniaxial pressure stability, biaxial pressure stability, shear stability, and compression-shear composite stability, are calculated respectively, and the minimum margin MS is obtained by comparing the margins corresponding to each failure mode. The margin of the skin failure mode refers to the difference between the maximum strain that the skin can withstand under certain load conditions and the actual working strain in aircraft structure design. Therefore, the margin is an important indicator of structural safety, and the larger the margin, the higher the safety of the skin structure.

[0058] In one specific implementation, the following formula (1) can be used to calculate the margin:

[0059] Margin = (Allowable Strain - Actual Strain) / Allowable Strain (1)

[0060] Wherein, the allowable strain depends on the characteristics of the material, such as yield strength or ultimate strength, which can be obtained from the skin parameter variables, and the actual strain can be obtained from the skin element load. Of course, the above formula is only used as an example in the present embodiment, and the specific way of calculating the margin is not limited. For example, when the above formula (1) is used to calculate the margin corresponding to each failure mode, the margin is respectively: 0.5 for tension, 0.18 for compression, 0.22 for shear, 0.1 for complex strain, 2.0 for uniaxial pressure stability, 0.8 for biaxial pressure stability, 0.4 for shear stability, and 0.22 for compression-shear complex stability. Therefore, 0.1 corresponding to the complex strain failure mode is taken as the minimum margin. Of course, the minimum margin corresponding to each failure mode is only used as an example in the present embodiment, and is not limited.

[0061] In step S203, the initial thickness of the skin is adjusted according to the minimum margin using the bisection method under each skin layer ratio to obtain the skin thickness corresponding to each skin layer ratio.

[0062] In the present embodiment, after the minimum margin is determined, the skin thickness is adjusted using the bisection method under each skin layer ratio, as shown in Figure 4 The principle of the bisection method is shown in the schematic diagram. For the skin structure, the initial thickness A of the skin, the upper limit A_U of the skin thickness, and the lower limit A_L of the skin thickness are input. The strength is checked based on the initial thickness of the skin. If the margin MS is less than 0, the value A of the current variable is set as the lower limit of the optimization variable, and then the value of the optimization variable is increased to adjust the optimization variable to 1 / 2 of the sum of the value A of the current variable and the upper limit A_U of the current variable. If the margin is greater than 0, the value A of the current variable is set as the upper limit of the optimization variable, and then the value of the optimization variable is decreased to adjust the optimization variable to 1 / 2 of the sum of the value of the current variable and the lower limit A_L of the current variable. The parameter adjustment and strength checking are repeated iteratively until the adjustment value of the optimization variable is less than or equal to 0.01 mm, and the optimization result is output.

[0063] In step S204, the skin thickness corresponding to each skin layer ratio is compared to obtain the minimum skin thickness, and the minimum skin thickness and the skin layer ratio corresponding to the minimum skin thickness are taken as the skin optimization parameters.

[0064] In the embodiment, different thicknesses corresponding to different lay-up ratios are obtained by traversing the lay-up ratios, and the purpose of optimization is to adjust the weight of the composite outer wing box section to be the lightest, and the smaller the thickness, the lighter the weight, so the minimum skin thickness in each lay-up ratio is obtained, for example, the minimum skin thickness is determined to be 5mm, and the skin [0° / ±45° / 90°] lay-up ratio corresponding to the minimum skin thickness is [50 / 40 / 10], and the minimum skin thickness and the skin lay-up ratio corresponding to the minimum skin thickness obtained above are taken as the skin optimization parameters.

[0065] It should be noted that in the embodiment, the static strength parameter optimization of the web and the skin only involves the adjustment of the thickness, and the difference between the two is only that the input parameters are different. For the web, the input is the obtained web parameter variable and the web unit load, and the optimization process is basically the same as that of the skin. Therefore, in the embodiment, only the static strength parameter optimization process of the skin is described, and the optimization process of the web is not described in detail.

[0066] In the embodiment, the internal force distribution of the composite outer wing box section structure is calculated based on the finite element model, and the skin and the stringer are separately optimized based on the internal force solution to realize the optimization decoupling of the skin and the stringer, obtain the structure parameters with the lightest weight that meet the strength requirement, and thus improve the efficiency of the static strength optimization of the composite outer wing box section.

[0067] Embodiment Three

[0068] Figure 5 The embodiment three of the application provides a flowchart of a composite outer wing box section static strength optimization method, and the embodiment is based on the above-mentioned embodiment and specifically describes the static strength parameter optimization of the stringer of the composite outer wing box section based on the stringer unit load by using the dichotomy method to obtain the stringer optimization parameter, as shown in the figure, the method comprises the steps of: Figure 5

[0069] In step S301, the stringer parameter variable is obtained.

[0070] ​Specifically, in the static strength parameter optimization of the longeron in the embodiment, the longeron parameter variables need to be obtained in advance, wherein the longeron parameter variables include upper and lower limits of the longeron layer proportion, initial cross-sectional dimensions of the longeron, wherein the initial cross-sectional dimensions include initial web thickness and initial web height of the longeron, and the longeron layer proportion refers to the layer direction and proportion distribution of the longeron in the composite material structure of the composite material outer wing box section, which is a key parameter in the design of the composite material and directly affects the strength, stiffness and stability of the structure. Therefore, in the embodiment, the upper and lower limits of the layer proportion can be configured in advance, and the longeron layer proportion is traversed within the range to obtain the longeron thickness corresponding to each longeron layer proportion, and the longeron layer proportion meeting the requirements is selected from the longeron thickness according to the requirements. In addition, for the longeron, the optimization variable corresponding to the longeron is the web thickness B1 and the web height B2 of the longeron. Therefore, in the embodiment, the initial web thickness and the initial web height of the longeron, and the upper and lower limits of the longeron layer proportion are obtained, and then the static strength parameter optimization of the longeron is performed based on the obtained longeron parameter variables and the longeron unit load obtained by the inner body extraction.

[0071] In step S302, the first margin is obtained by checking the local stability of the web of the longeron according to the longeron unit load and the longeron parameter variables.

[0072] In the embodiment, the longeron unit load and the longeron parameter variables are used as input to check the local stability of the web of the longeron, and when the local stability of the web of the longeron is checked, the margin corresponding to the local stability failure mode is calculated, that is, the first margin MS1. The first margin in the local stability failure mode of the longeron is calculated according to the local stability analysis method of the longeron, and measures the difference between the maximum stress that the longeron can withstand under a specific load condition and the actual working stress. Therefore, the margin is an important indicator for measuring the safety of the structure, and the larger the margin, the higher the safety of the longeron structure.

[0073] In step S303, the initial web thickness of the longeron is adjusted under each longeron layer proportion by using the bisection method according to the first margin, and the adjusted web thickness of the longeron corresponding to each longeron layer proportion is obtained.

[0074] In the embodiment, when it is determined that the first margin is equal to 0, the subsequent strain and combined columnar lightness check of the longeron is directly performed, otherwise the initial web thickness of the longeron is adjusted under each longeron layer proportion by using the bisection method according to the first margin. The variable adjustment principle of the bisection method has been described in detail in the adjustment of the skin thickness, and will not be described again in the embodiment. The web thickness of the longeron is optimized until the local stability meets the margin control requirement, that is, the adjustment amount of the web thickness is less than or equal to 0.01 mm, which means that the margin control requirement is met, and then the local stability check is exited.

[0075] Step 304, based on the long string layer proportion corresponding to the long string adjustment web thickness, the long string strain and the combined section column strength checking are carried out according to the long string unit load and the long string parameter variable to obtain the second margin.

[0076] Among them, in the embodiment, after completing the long string bottom web local stability checking and obtaining the long string adjustment web thickness corresponding to each long string layer proportion, the second margin MS2 will be obtained when the long string strain and the combined section column strength checking are carried out. The obtaining method of the second margin is basically the same as the above-mentioned first margin, only the corresponding failure mode of the checking is different, therefore, the embodiment will not be described again.

[0077] Step S305, according to the second margin, the long string initial web height and the long string adjustment web thickness are adjusted under each long string layer proportion by using the dichotomy method to obtain the long string section size corresponding to each long string layer proportion.

[0078] Among them, when checking the long string strain and the long string skin combined column strength, the long string web height is first optimized under each long string layer proportion by using the dichotomy method according to the second margin. If the long string web height reaches the upper limit and the long string strain and the long string skin combined column strength still do not meet the margin control requirements, then the long string web thickness is optimized, until the margins of the long string local stability, the long string strain and the long string skin combined column strength all meet the margin control requirements, the long string web thickness and the long string web height corresponding to the current layer proportion are obtained, and finally the long string section size corresponding to different layer proportions is obtained through layer proportion iteration.

[0079] Step S306, the long string section size corresponding to each long string layer proportion is compared to obtain the minimum long string section size, and the minimum long string section size and the long string layer proportion corresponding to the minimum long string section size are taken as the long string optimization parameters.

[0080] Among them, after obtaining the long string section size corresponding to each long string layer proportion in the embodiment, since the purpose of optimization in the embodiment is to adjust the weight of the composite outer wing box section to be the lightest, and the smaller the thickness is, the lighter the weight is, therefore the minimum long string section size in each layer proportion is obtained. For example, it is determined that the minimum long string section is: the long string web thickness is 10mm, the height is 75mm, and the layer proportion corresponding to the minimum long string section size is [50 / 40 / 10] is obtained, then the minimum long string section size and the long string layer proportion corresponding to the minimum long string section size are taken as the long string optimization parameters.

[0081] Example four

[0082] Figure 6 The structure schematic diagram of a composite outer wing box section static strength optimization device provided by the embodiment four of the application is shown in the figure.Figure 6 The device comprises a static force calculation module 410, a static strength parameter optimization module 420, a finite element model attribute updating module 430, and a static strength checking module 440.

[0083] The static force calculation module 410 is configured to perform static force calculation on the finite element model of the composite outer wing box section to obtain an internal force solution.

[0084] The static strength parameter optimization module 420 is configured to perform static strength parameter optimization on the structure of the composite outer wing box section according to the internal force solution by using a dichotomy method to obtain optimization parameters, wherein the structure comprises a skin, a stringer, a spar, and a rib, and the spar comprises a web plate and a flange strip.

[0085] The finite element model attribute updating module 430 is configured to perform attribute updating on the finite element model according to the optimization parameters to obtain an updated finite element model.

[0086] The static strength checking module 440 is configured to perform static strength checking and parameter adjustment on the updated finite element model when it is determined that the weight of the updated finite element model meets the requirements, to obtain an optimization result.

[0087] Optionally, the device further comprises a finite element model establishing module configured to establish a finite element model of the composite outer wing box section.

[0088] The finite element model is set with material attributes, unit section attributes, constraint conditions, and boundary conditions.

[0089] Optionally, the device further comprises an internal force extraction module configured to extract internal forces from the internal force solution, wherein the internal forces comprise skin unit loads, stringer unit loads, web plate unit loads, flange strip unit loads, rib web plate unit loads, and rib flange strip unit loads.

[0090] Optionally, the static strength parameter optimization module comprises:

[0091] The web plate parameter optimization unit is configured to perform static strength parameter optimization on the web plate of the composite outer wing box section according to the web plate unit loads by using a dichotomy method to obtain web plate optimization parameters, wherein the web plate optimization parameters comprise a minimum web plate thickness and a web plate layup ratio corresponding to the minimum web plate thickness.

[0092] The skin parameter optimization unit is configured to perform static strength parameter optimization on the skin of the composite outer wing box section according to the skin unit loads by using a dichotomy method to obtain skin optimization parameters, wherein the skin optimization parameters comprise a minimum skin thickness and a skin layup ratio corresponding to the minimum skin thickness.

[0093] The longeron parameter optimization unit is configured to obtain longeron optimization parameters by using dichotomy to perform static strength parameter optimization on the longeron of the composite outer wing box section according to longeron unit load, wherein the longeron optimization parameters include a minimum longeron section size and a longeron layup ratio corresponding to the minimum longeron section size, and the longeron section size includes a web thickness and a web height.

[0094] Optionally, the static strength parameter optimization module further includes a beam flange strip parameter optimization unit configured to obtain beam flange strip optimization parameters by performing static strength parameter optimization on the beam flange strip of the composite outer wing box section according to beam flange strip unit load and the beam web optimization parameters.

[0095] Optionally, the beam web parameter optimization unit is configured to obtain beam web parameter variables, wherein the beam web parameter variables include beam web layup ratio upper and lower limits, beam web thickness upper and lower limits, and a beam web initial thickness.

[0096] The minimum margin corresponding to each failure mode is obtained by performing static strength checking according to the beam web unit load and the beam web parameter variables, wherein the failure modes include tension, compression, shear, combined strain, uniaxial compression stability, biaxial compression stability, shear stability, and compression-shear combined stability.

[0097] The beam web initial thickness is adjusted at each beam web layup ratio by using dichotomy according to the minimum margin, to obtain a beam web thickness corresponding to each beam web layup ratio.

[0098] The beam web thickness corresponding to each beam web layup ratio is compared to obtain a minimum beam web thickness, and the minimum beam web thickness and the beam web layup ratio corresponding to the minimum beam web thickness are taken as the beam web optimization parameters.

[0099] Optionally, the skin parameter optimization unit is configured to obtain skin parameter variables, wherein the skin parameter variables include skin layup ratio upper and lower limits, skin thickness upper and lower limits, and a skin initial thickness.

[0100] The minimum margin corresponding to each failure mode is obtained by performing static strength checking according to the skin unit load and the skin parameter variables.

[0101] The skin initial thickness is adjusted at each skin layup ratio by using dichotomy according to the minimum margin, to obtain a skin thickness corresponding to each skin layup ratio.

[0102] The skin thickness corresponding to each skin layup ratio is compared to obtain a minimum skin thickness, and the minimum skin thickness and the skin layup ratio corresponding to the minimum skin thickness are taken as the skin optimization parameters.

[0103] Optionally, the longeron parameter optimization unit is configured to obtain longeron parameter variables, wherein the longeron parameter variables include longeron layup proportion upper and lower limits and longeron initial cross-sectional dimensions, wherein the initial cross-sectional dimensions include longeron initial web thickness and longeron initial web height.

[0104] The longeron web local stability check is performed according to the longeron unit load and the longeron parameter variables to obtain a first margin.

[0105] The longeron initial web thickness is adjusted at each longeron layup proportion by using a dichotomy method according to the first margin, to obtain longeron adjusted web thicknesses corresponding to the respective longeron layup proportions.

[0106] The longeron strain and combined section column strength check is performed according to the longeron unit load and the longeron parameter variables based on the longeron adjusted web thicknesses corresponding to the respective longeron layup proportions, to obtain a second margin.

[0107] The longeron initial web height and the longeron adjusted web thickness are adjusted at each longeron layup proportion by using a dichotomy method according to the second margin, to obtain longeron cross-sectional dimensions corresponding to the respective longeron layup proportions.

[0108] The longeron cross-sectional dimensions corresponding to the respective longeron layup proportions are compared to obtain a minimum longeron cross-sectional dimension, and the minimum longeron cross-sectional dimension and a longeron layup proportion corresponding to the minimum longeron cross-sectional dimension are taken as longeron optimization parameters.

[0109] Optionally, the static strength check module is configured to obtain a weight of a historical finite element model of adjacent iteration optimization, and calculate a weight difference between the weight of the historical finite element model and a weight of an updated finite element model.

[0110] When it is determined that the weight difference is less than a preset threshold, the static strength check and parameter adjustment are performed on the updated finite element model to obtain an optimization result.

[0111] The composite outer wing box section static strength optimization device provided in the embodiments of the present application can perform the composite outer wing box section static strength optimization method provided in any of the embodiments of the present application, and has the corresponding function modules and beneficial effects of the execution method.

[0112] Embodiment five

[0113] Figure 7A structural diagram of an electronic device 10 that can be used to implement embodiments of the present application is shown. The electronic device is intended to represent various forms of digital computers, such as laptops, desktops, tablets, personal digital assistants, servers, blade servers, mainframes, and other appropriate computers. The electronic device can also represent various forms of mobile devices, such as personal digital assistants, cellular telephones, smartphones, wearable devices (e.g., headsets, glasses, watches, etc.), and other similar computing devices. The components shown here, their connections and relationships, and their functions, are meant to be examples only, and are not meant to limit implementations of the present application described and / or claimed in this document.

[0114] As Figure 7 As shown, the electronic device 10 includes at least one processor 11, and memory, such as read-only memory (ROM) 12, random access memory (RAM) 13, etc., that is communicatively coupled with the at least one processor 11, where the memory stores computer programs that are executable by the at least one processor 11, and the processor 11 can perform various appropriate actions and processes according to the computer programs stored in the read-only memory (ROM) 12 or loaded into the random access memory (RAM) 13 from the storage unit 18. In the RAM 13, various programs and data required for the operation of the electronic device 10 can also be stored. The processor 11, the ROM 12, and the RAM 13 are connected to each other through a bus 14. An input / output (I / O) interface 15 is also connected to the bus 14.

[0115] Various components in the electronic device 10 are connected to the I / O interface 15, including an input unit 16, such as a keyboard, a mouse, etc., an output unit 17, such as various types of displays, speakers, etc., a storage unit 18, such as a magnetic disk, an optical disk, etc., and a communication unit 19, such as a network card, a modem, a wireless communication transceiver, etc. The communication unit 19 allows the electronic device 10 to exchange information / data with other devices through a computer network, such as the Internet, and / or various telecommunication networks.

[0116] The processor 11 can be various general and / or special purpose processing components with processing and computing capabilities. Some examples of the processor 11 include, but are not limited to, a central processing unit (CPU), a graphics processing unit (GPU), various specialized artificial intelligence (AI) computing chips, various processors running machine learning model algorithms, a digital signal processor (DSP), and any appropriate processor, controller, microcontroller, etc. The processor 11 performs various methods and processes described above, such as the composite outer wing box segment static strength optimization method.

[0117] In some embodiments, the composite outer wing box segment static strength optimization method can be implemented as a computer program tangibly embodied in a computer readable storage medium, e.g., storage unit 18. In some embodiments, parts or all of the computer program can be loaded and / or installed onto electronic device 10 via, e.g., ROM 12 and / or communication unit 19. When the computer program is loaded onto RAM 13 and executed by processor 11, one or more steps of the composite outer wing box segment static strength optimization method described above can be performed. Alternatively, in other embodiments, processor 11 can be configured to perform the composite outer wing box segment static strength optimization method by way of other means (e.g., by way of firmware).

[0118] Various implementations of the systems and techniques described above can be realized in digital electronic circuitry, integrated circuitry, a field programmable gate array (FPGA), an application specific integrated circuit (ASIC), a system on a chip (SOC), a programmable logic device (PLD), a computer hardware, firmware, software, and / or combinations thereof. These various implementations can include implementation in one or more computer programs that are executable and / or interpretable on a programmable system including at least one programmable processor, which can be special or general purpose, coupled to receive data and instructions from, and to transmit data and instructions to, a storage system, at least one input device, and at least one output device.

[0119] Computer programs used to implement the processes of the application can be written in any combination of one or more programming languages. These computer programs can be provided to a processor of a general purpose computer, special purpose computer, or other programmable data processing apparatus to produce a machine, such that the computer program, when executed by the processor of the machine, implements the functions / acts specified in the flowcharts and / or block diagrams. The computer program can be executed entirely on a machine, partially on a machine, partially on a machine as a stand-alone software package, partially on a machine and partially on a remote machine or entirely on a remote machine or server.

[0120] In the context of the present application, a computer-readable storage medium can be a tangible medium that can contain or store a computer program for use by or in connection with an instruction execution system, apparatus, or device. A computer-readable storage medium can include, but is not limited to, an electronic, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any suitable combination of the foregoing. Alternatively, a computer-readable storage medium can be a machine-readable signal medium. More specific examples of a machine-readable storage medium will include one or more lines of a program of instructions in a transitory signal, a portable computer diskette, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or Flash memory), an optical fiber, a portable compact disc read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the foregoing.

[0121] To provide for interaction with a user, the systems and techniques described here can be implemented on an electronic device having a display device (e.g., a CRT (cathode ray tube) or LCD (liquid crystal display) monitor) for displaying information to the user and a keyboard and a pointing device (e.g., a mouse or a trackball) by which the user can provide input to the electronic device. Other kinds of devices can be used to provide for interaction with a user as well; for example, feedback provided to the user can be any form of sensory feedback (e.g., visual feedback, auditory feedback, or tactile feedback); and input from the user can be received in any form, including acoustic, speech, or tactile input.

[0122] The systems and techniques described here can be implemented in a computing system that includes a back end component (e.g., as a data server), or that includes a middleware component (e.g., an application server), or that includes a front end component (e.g., a user computer having a graphical user interface or a Web browser through which a user can interact with an implementation of the systems and techniques described here), or any combination of such back end, middleware, or front end components. The components of the system can be interconnected by any form or medium of digital data communication (e.g., a communication network). Examples of communication networks include a local area network (LAN), a wide area network (WAN), a blockchain network, and the Internet.

[0123] The computing system can include clients and servers. A client and server are generally remote from each other and typically interact through a communication network. The relationship of client and server arises by virtue of computer programs running on the respective computers and having a client-server relationship to each other. The server can be a cloud server, also known as a cloud computing server or cloud host, which is a host product in the cloud computing service system, to solve the defects of large management difficulty and weak business scalability in traditional physical host and VPS service.

[0124] It should be understood that the various forms of flow shown above can be used to reorder, add or delete steps. For example, each step described in the present application can be executed in parallel, sequentially or in a different order, as long as the desired results of the technical solutions of the present application can be achieved, which is not limited herein.

[0125] The above detailed description does not constitute a limitation on the scope of protection of the present application. Those skilled in the art should understand that various modifications, combinations, sub-combinations and substitutions can be made according to design requirements and other factors. Any modifications, equivalent replacements and improvements made within the spirit and principles of the present application shall be included in the scope of protection of the present application.

Claims

1. A method for optimizing the static strength of a composite material outer wing box section, characterized in that: include: Perform static calculations on the finite element model of the composite outer wing box section to obtain the internal force solution; According to the internal force solution, a bisection method is used to separately optimize the static strength parameters of the structure of the composite material outer wing box section to obtain optimized parameters, wherein the structure includes a skin, a long stringer, a wing spar and a wing rib, wherein the wing spar includes a spar web and a spar cap; updating the attributes of the finite element model according to the optimization parameters to obtain an updated finite element model; When it is determined that the weight of the updated finite element model meets the requirements, static strength verification and parameter adjustment are performed on the updated finite element model to obtain an optimization result.

2. The method according to claim 1, characterized in that Before performing static calculation on the finite element model of the composite material outer wing box section to obtain the internal force solution, the method further includes: Establishing a finite element model of the composite material outer wing box section; The material properties, unit section properties, constraint conditions and boundary conditions of the finite element model are set.

3. The method according to claim 1, characterized in that After performing static calculation on the finite element model of the composite material outer wing box section to obtain the internal force solution, the method further includes: Internal force extraction is performed on the internal force solution, wherein the internal force includes skin unit load, stringer unit load, beam web unit load, beam cap unit load, rib web unit load and rib cap unit load.

4. The method according to claim 3, characterized in that The step of optimizing the static strength parameters of the composite material outer wing box section structure using a bisection method based on the internal force solution to obtain optimized parameters includes: Optimizing the static strength parameters of the beam web of the composite outer wing box section using a bisection method according to the beam web unit load to obtain beam web optimization parameters, wherein the beam web optimization parameters include a minimum beam web thickness and a beam web ply ratio corresponding to the minimum beam web thickness; Optimizing the static strength parameters of the skin of the composite material outer wing box section using a dichotomy method according to the skin unit load to obtain skin optimization parameters, wherein the skin optimization parameters include a minimum skin thickness and a skin ply ratio corresponding to the minimum skin thickness; According to the stringer unit load, a bisection method is used to optimize the static strength parameters of the stringer of the composite material outer wing box section to obtain stringer optimization parameters, wherein the stringer optimization parameters include a minimum stringer cross-sectional size and a stringer ply ratio corresponding to the minimum stringer cross-sectional size, wherein the stringer cross-sectional size includes a web thickness and a web height.

5. The method according to claim 4, characterized in that After optimizing the static strength parameters of the beam web of the composite material outer wing box section using a dichotomy method according to the beam web unit load to obtain the beam web optimization parameters, the method further includes: The static strength parameters of the beam cap of the composite material outer wing box section are optimized according to the beam cap unit load and the beam web optimization parameters to obtain the beam cap optimization parameters.

6. The method according to claim 4, characterized in that The step of optimizing the static strength parameters of the beam web of the composite material outer wing box section using a dichotomy method according to the beam web unit load to obtain beam web optimization parameters includes: Obtaining beam web parameter variables, wherein the beam web parameter variables include upper and lower limits of beam web ply ratio, upper and lower limits of beam web thickness, and initial thickness of the beam web; Performing static strength verification based on the beam web unit load and the beam web parameter variables to obtain the minimum margin corresponding to each failure mode, wherein the failure modes include tension, compression, shear, combined strain, uniaxial compressive stability, biaxial compressive stability, shear stability, and combined compression-shear stability; Adjusting the initial thickness of the beam web at each beam web ply ratio using a dichotomy method according to the minimum margin to obtain the beam web thickness corresponding to each beam web ply ratio; The beam web thicknesses corresponding to the beam web ply ratios are compared to obtain the minimum beam web thickness, and the minimum beam web thickness and the beam web ply ratio corresponding to the minimum beam web thickness are used as the beam web optimization parameters.

7. The method according to claim 4, characterized in that The step of optimizing the static strength parameters of the composite material outer wing box section skin using a dichotomy method according to the skin unit load to obtain skin optimization parameters includes: Obtaining skin parameter variables, wherein the skin parameter variables include upper and lower limits of skin ply ratio, upper and lower limits of skin thickness, and initial skin thickness; Performing static strength verification according to the skin unit load and the skin parameter variables to obtain the minimum margin corresponding to each failure mode; Adjusting the initial skin thickness at each skin ply ratio using a dichotomy method according to the minimum margin to obtain the skin thickness corresponding to each skin ply ratio; The skin thicknesses corresponding to the various skin ply ratios are compared to obtain a minimum skin thickness, and the minimum skin thickness and the skin ply ratio corresponding to the minimum skin thickness are used as the skin optimization parameters.

8. The method according to claim 4, characterized in that The step of optimizing the static strength parameters of the truss of the composite material outer wing box section using a dichotomy method according to the truss unit load to obtain optimized truss parameters includes: Obtaining stringer parameter variables, wherein the stringer parameter variables include upper and lower limits of the stringer ply ratio and initial stringer cross-sectional dimensions, wherein the initial cross-sectional dimensions include initial stringer web thickness and initial stringer web height; Performing a local stability check of the web of the girder according to the girder unit load and the girder parameter variable to obtain a first margin; Adjusting the initial web thickness of the stringer at each stringer ply ratio using a dichotomy method according to the first margin to obtain an adjusted web thickness of the stringer corresponding to each stringer ply ratio; adjusting the web thickness of the girder corresponding to the ply ratio of each girder, and performing girder strain and combined section column strength verification according to the girder unit load and the girder parameter variable to obtain a second margin; Adjusting the initial web height of the stringer and the adjusted web thickness of the stringer at each stringer ply ratio using a dichotomy method according to the second margin to obtain a stringer cross-sectional size corresponding to each stringer ply ratio; The stringer cross-sectional dimensions corresponding to the respective stringer ply ratios are compared to obtain a minimum stringer cross-sectional dimension, and the minimum stringer cross-sectional dimension and the stringer ply ratio corresponding to the minimum stringer cross-sectional dimension are used as the stringer optimization parameters.

9. The method according to claim 1, characterized in that When it is determined that the weight of the updated finite element model meets the requirements, static strength verification and parameter adjustment are performed on the updated finite element model, including: Obtaining the weight of a historical finite element model of adjacent iterative optimizations, and calculating a weight difference between the weight of the historical finite element model and the weight of the updated finite element model; When it is determined that the weight difference is less than a preset threshold, static strength verification and parameter adjustment are performed on the updated finite element model to obtain an optimization result.

10. A device for optimizing the static strength of a composite material outer wing box section, characterized in that: include: Static calculation module, used to perform static calculation on the finite element model of the composite outer wing box section to obtain the internal force solution; a static strength parameter optimization module, configured to perform static strength parameter optimization on the structure of the composite material outer wing box section using a bisection method according to the internal force solution to obtain optimized parameters, wherein the structure includes a skin, a stringer, a wing spar, and a wing rib; A finite element model attribute updating module, configured to update the attributes of the finite element model according to the optimization parameters to obtain an updated finite element model; The static strength checking module is used to perform static strength checking and parameter adjustment on the updated finite element model when it is determined that the weight of the updated finite element model meets the requirements.

11. An electronic device, characterized in that: The electronic device comprises: at least one processor; and a memory communicatively connected to the at least one processor; wherein, The memory stores a computer program executable by the at least one processor, and the computer program is executed by the at least one processor to enable the at least one processor to perform the method according to any one of claims 1 to 9.

12. A computer-readable storage medium, characterized in that The computer-readable storage medium stores computer instructions, and the computer instructions are used to enable a processor to implement the method according to any one of claims 1 to 9 when executed.

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