Composite material outer wing box section beam model rigidity correction method, device, equipment and medium

Abstract

The embodiment of the invention discloses a rigidity correction method, device and equipment for a composite material outer wing box section beam model and a medium. The method comprises the steps that a beam model and a GFEM model of an outer wing box section are obtained, the load of the beam model is an aerodynamic load, and the load of the GFEM model is a node load; performing node rigid connection on the beam model and the GFEM model to obtain a combined model; and carrying out rigidity difference calibration on the outer wing box section based on the combined model, the aerodynamic load and the node load. On the basis, the beam model and the GFEM model are combined, and then the rigidity of the beam model is calibrated according to the deformation difference of the beam model under different load working conditions, so that the effectiveness and accuracy of structural optimization and aeroelastic design iteration of the composite outer wing box section are ensured.

Description

Technical Field

[0001] This application relates to the field of stiffness design of composite material outer wing box segments, and particularly to methods, devices, equipment and media for stiffness correction of composite material outer wing box segment beam models. Background Technology

[0002] The design of composite material wings for civil aircraft typically involves multiple disciplines, including overall design, load-bearing capacity, aeroelasticity, structural strength, and manufacturing and assembly. Each discipline involves numerous design variables and constraints, and these disciplines are interconnected. Therefore, the design of composite material wings is an iterative process of gradual optimization.

[0003] For structural strength, the Global Finite Element Model (GFEM) is usually used for design, while for aeroelasticity, the wing is usually simplified into a beam model for design.

[0004] However, when structural optimization and aeroelastic iteration are performed based on the two models respectively, the results of both models involve the stiffness of the outer wing box section. The two stiffness results may have large errors, which cannot ensure the effectiveness and accuracy of the composite outer wing box section structural optimization and aeroelastic design iteration. Summary of the Invention

[0005] This application provides a method, apparatus, equipment, and medium for stiffness correction of a composite material outer wing box segment beam model, to ensure the effectiveness and accuracy of composite material outer wing box segment structural optimization and aeroelastic design iteration.

[0006] In a first aspect, embodiments of this application provide a method for correcting the stiffness of a composite material outer wing box segment beam model, the method comprising:

[0007] Obtain the beam model and GFEM model of the outer wing box segment. The loads on the beam model are aerodynamic loads, and the loads on the GFEM model are nodal loads.

[0008] By rigidly connecting the beam model and the GFEM model at the nodes, a combined model is obtained;

[0009] Stiffness difference calibration of the outer wing box segment beam model was performed based on the combined model, aerodynamic loads, and nodal loads.

[0010] Secondly, embodiments of this application provide a stiffness correction device for a composite material outer wing box segment beam model, comprising:

[0011] The acquisition module is used to acquire the beam model and GFEM model of the outer wing box segment. The loads on the beam model are aerodynamic loads, and the loads on the GFEM model are nodal loads.

[0012] The connection module is used to rigidly connect the beam model and the GFEM model at nodes to obtain a combined model.

[0013] The difference calibration module is used to perform stiffness difference calibration on the outer wing box beam model based on the combined model, aerodynamic loads, and nodal loads.

[0014] Thirdly, this application also provides a stiffness correction device for a composite material outer wing box segment beam model, the stiffness correction device for the composite material outer wing box segment beam model includes:

[0015] One or more processors;

[0016] Storage device for storing one or more programs.

[0017] When one or more programs are executed by one or more processors, the one or more processors implement the stiffness correction method for composite material outer wing box segment beam models as provided in any embodiment of this application.

[0018] Fourthly, embodiments of this application also provide a computer-readable storage medium storing a computer program thereon, characterized in that, when the program is executed by a processor, it implements the composite material outer wing box segment beam model stiffness correction method as provided in any embodiment of this application.

[0019] The technical solution of this application embodiment involves obtaining a beam model and a GFEM model of the outer wing box segment. The loads on the beam model are aerodynamic loads, and the loads on the GFEM model are nodal loads. The beam model and the GFEM model are rigidly connected at the nodes to obtain a combined model. Based on the combined model, aerodynamic loads, and nodal loads, the stiffness difference of the outer wing box segment beam model is calibrated. Therefore, by combining the beam model and the GFEM model and then calibrating their stiffness differences under different load conditions, the effectiveness and accuracy of the composite outer wing box segment structural optimization and aeroelastic design iteration are ensured. Attached Figure Description

[0020] Figure 1 This is a flowchart illustrating the stiffness correction method for the composite material outer wing box segment beam model provided in Embodiment 1 of this application;

[0021] Figure 2 This is a schematic diagram of the stiffness correction device for the composite material outer wing box segment beam model provided in Embodiment 2 of this application;

[0022] Figure 3 This is a structural schematic diagram of a composite material outer wing box segment beam model stiffness correction device provided in Embodiment 4 of this application. Detailed Implementation

[0023] The present application will now be described in further detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the application and not intended to limit it. Furthermore, it should be noted that, for ease of description, the accompanying drawings show only the parts relevant to the present application, not the entire structure.

[0024] Example 1

[0025] Figure 1 This is a flowchart illustrating the stiffness correction method for the composite material outer wing box segment beam model provided in Embodiment 1 of this application, as shown below. Figure 1 As shown, the method for correcting the stiffness of the composite material outer wing box segment beam model provided in this embodiment can be implemented based on a composite material outer wing box segment beam model stiffness correction device equipped with a video acquisition terminal, and can specifically include the following steps:

[0026] Step 101: Obtain the beam model and GFEM model of the outer wing box segment. The loads on the beam model are aerodynamic loads, and the loads on the GFEM model are nodal loads.

[0027] In this step, the beam model and the GFEM model are positioned differently in the structural analysis. The beam model focuses on global simplified analysis, while the GFEM model focuses on accurate simulation of complex details.

[0028] Among them, the beam model simplifies the structure to one-dimensional beam elements, focusing only on the overall stiffness and mass characteristics of the wing and ignoring the internal details of the cross section; while the GFEM model simulates the mechanical properties of the main structure such as wing panels, spars and ribs through plate elements, shell elements, rod elements and beam elements.

[0029] In this step, the beam model and the GFEM model are subjected to load conditions separately. The load on the beam model is an aerodynamic load, which is applied to the beam model through RBAR elements. The load on the GFEM model is a nodal load, which is applied to the nodes of the GFEM model elements.

[0030] Step 102: Connect the beam model and the GFEM model with rigid nodes to obtain the combined model.

[0031] In this step, for any node of the beam model, the node of the beam model is rigidly connected to the node of the corresponding GFEM model with the same cross section; a fixed boundary condition is applied to the root of the model after rigid connection to obtain the combined model.

[0032] When rigidly connecting nodes, the RBE2 element can be used to achieve this. The RBE2 element is used to rigidly connect each node of the beam model to the nodes of the GFEM model around the same section, thus completing the assembly of the two models.

[0033] Furthermore, the core of applying fixed supports to the root boundary condition is to restrict all degrees of freedom at the root, simulating a rigid connection between the structure and the fuselage. This ensures effective load transfer and avoids rigid body motion, serving as the fundamental boundary setting for structural analysis such as wing box sections. Methods for applying fixed supports can be found in relevant technologies and will not be elaborated upon here.

[0034] Step 103: Based on the combined model, aerodynamic loads, and nodal loads, perform stiffness difference calibration on the outer wing box segment beam model.

[0035] In this step, the stiffness difference of the outer wing box segment under aerodynamic load and nodal load can be based on the combined model; then, the stiffness of the outer wing box segment is calibrated according to the stiffness difference; the beam model is updated based on the calibrated stiffness, and the steps of nodal rigid connection and stiffness difference calibration are performed until the stiffness difference meets the preset stop iteration condition.

[0036] It should be noted that the rigid connection step is the aforementioned step 102, and the stiffness difference calibration step is this step 103.

[0037] When determining stiffness differences, the first deformation data of the beam model under aerodynamic load and the second deformation data under nodal load can be determined based on the combined model; then, based on the combined model, the third deformation data of the GFEM model under aerodynamic load and the fourth deformation data under nodal load can be determined.

[0038] Finally, the stiffness difference is determined based on the first, second, third, and fourth deformation data. The stiffness difference includes torsional stiffness difference and vertical bending stiffness difference; the first deformation data includes the first deflection and first torsion angle under aerodynamic loads on the beam model; the second deformation data includes the second deflection and second torsion angle under nodal loads on the beam model; the third deformation data includes the third deflection and third torsion angle under aerodynamic loads on the GFEM model; and the fourth deformation data includes the fourth deflection and fourth torsion angle under nodal loads on the GFEM model.

[0039] When determining the first deformation data of the beam model under aerodynamic load, only the GFEM model nodes in the combined model can be retained for GFEM model load condition loading. The GFEM model elements do not participate in the calculation. Then, the static solution is submitted to calculate the deformation data of the beam model under two load conditions (aerodynamic load condition and nodal load condition), namely the first deformation data and the second deformation data.

[0040] To avoid the difference in deformation data extraction methods affecting the actual stiffness comparison, two RBAR elements rigidly connected to the BEAM element of the beam model can be selected at the wingtip end face. The vector between the two elements can be calculated, and the projection of this vector in the downflow method can be calculated. The angle between the projections before and after deformation is the torsion angle. The vertical displacement of the leading edge point at each rib station before and after deformation can be extracted as deflection, which is used as deformation data.

[0041] In a specific example, the torsional angle of the beam model under the beam model loading condition is: The torsional angle of the beam model under the GFEM model load condition is: The torsional angle of the GFEM model under the beam model load condition is: The torsional angle under the load condition of the GFEM model is .

[0042] In addition, the deflection of the beam model under the beam model load condition is The deflection under the load condition of the GFEM model is The deflection of the GFEM model under the beam model load condition is: The deflection under the load condition of the GFEM model is .

[0043] It should be noted that stiffness difference includes torsional stiffness difference and vertical bending stiffness difference. Therefore, when determining stiffness difference, torsional stiffness difference can be determined based on the first torsion angle, the second torsion angle, the third torsion angle, and the fourth torsion angle; vertical bending stiffness difference can be determined based on the first deflection, the second deflection, the third deflection, and the fourth deflection.

[0044] In a specific example, the difference in vertical bending stiffness is: The difference in torsional stiffness is .

[0045] Correspondingly, when performing stiffness calibration, the torsional stiffness of the outer wing box segment can be calibrated based on the difference in torsional stiffness and the first preset threshold; the vertical bending stiffness of the outer wing box segment beam model can be calibrated based on the difference in vertical bending stiffness and the second preset threshold.

[0046] The first preset threshold can be 3%, and the second preset threshold can also be 3%.

[0047] In a specific example, if Then, the vertical bending stiffness correction ratio is uniformly increased to each beam element of the beam model, and the vertical bending stiffness of the beam element becomes: ;like If so, the vertical bending stiffness of the beam model is not corrected.

[0048] like Then, the torsional stiffness correction ratio is uniformly increased to each beam element of the beam model, and the torsional stiffness of the beam element becomes: ;like If so, the torsional stiffness of the beam model is not corrected.

[0049] It should be noted that the aforementioned preset stopping iteration condition is that the difference in torsional stiffness is less than a first preset threshold, and the difference in vertical bending stiffness is less than a second preset threshold, that is, and .

[0050] In this embodiment, a beam model and a GFEM model of the outer wing box segment are obtained. The loads on the beam model are aerodynamic loads, and the loads on the GFEM model are nodal loads. The beam model and the GFEM model are rigidly connected at the nodes to obtain a combined model. Based on the combined model, aerodynamic loads, and nodal loads, the stiffness difference of the outer wing box segment beam model is calibrated. Therefore, by combining the beam model and the GFEM model and then calibrating their stiffness differences under different load conditions, the effectiveness and accuracy of the composite outer wing box segment structural optimization and aeroelastic design iteration are ensured.

[0051] Example 2

[0052] Figure 2 This is a structural schematic diagram of a composite material outer wing box segment beam model stiffness correction device provided in Embodiment 2 of this application. The composite material outer wing box segment beam model stiffness correction device provided in this embodiment can execute the composite material outer wing box segment beam model stiffness correction method provided in any embodiment of this application, and possesses the corresponding functional modules and beneficial effects of the method. This device can be implemented using software and / or hardware, such as... Figure 2 As shown, the device includes:

[0053] The acquisition module 201 is used to acquire the beam model and GFEM model of the outer wing box segment. The load of the beam model is aerodynamic load, and the load of the GFEM model is nodal load.

[0054] Connection module 202 is used to rigidly connect the beam model and the GFEM model at nodes to obtain a combined model;

[0055] The difference calibration module 203 is used to perform stiffness difference calibration on the outer wing box beam model based on the combined model, aerodynamic loads, and nodal loads.

[0056] Furthermore, the connection module is specifically used for:

[0057] For any node of the beam model, rigidly connect the node of the beam model to the node of the corresponding GFEM model with the same cross section.

[0058] By applying fixed boundary conditions to the root of the rigidly connected model, a combined model is obtained.

[0059] Furthermore, the difference calibration module is specifically used for:

[0060] Based on the stiffness difference between the outer wing box segment beam model and the GFEM model under aerodynamic and nodal loads using the combined model;

[0061] Stiffness calibration of the outer wing box section is performed based on stiffness differences;

[0062] The beam model and GFEM model are updated based on the calibrated stiffness, and the steps of node rigid connection and stiffness difference calibration are performed until the stiffness difference meets the preset stop iteration condition.

[0063] Furthermore, the difference calibration module is specifically used for:

[0064] Based on the combined model, the first deformation data of the beam model under aerodynamic load and the second deformation data under nodal load are determined.

[0065] Based on the combined model, the third deformation data of the GFEM model under aerodynamic load and the fourth deformation data under nodal load were determined.

[0066] The stiffness difference is determined based on the first deformation data, the second deformation data, the third deformation data, and the fourth deformation data.

[0067] Furthermore, the stiffness differences include torsional stiffness differences and vertical bending stiffness differences; the first deformation data includes the first deflection and the first torsion angle under aerodynamic load on the beam model, the second deformation data includes the second deflection and the second torsion angle under nodal load on the beam model, the third deformation data includes the third deflection and the third torsion angle under aerodynamic load on the GFEM model, and the fourth deformation data includes the fourth deflection and the fourth torsion angle under nodal load on the GFEM model.

[0068] The difference calibration module is specifically used for:

[0069] The torsional stiffness difference is determined based on the first torsion angle, the second torsion angle, the third torsion angle, and the fourth torsion angle;

[0070] The difference in vertical bending stiffness is determined based on the first deflection, the second deflection, the third deflection, and the fourth deflection.

[0071] Furthermore, stiffness differences include torsional stiffness differences and vertical bending stiffness differences;

[0072] The difference calibration module is specifically used for:

[0073] The torsional stiffness of the outer wing box section is calibrated based on the difference in torsional stiffness and a first preset threshold.

[0074] The vertical bending stiffness of the outer wing box segment is calibrated based on the difference in vertical bending stiffness and a second preset threshold.

[0075] Furthermore, the preset stopping iteration condition is that the difference in torsional stiffness is less than a first preset threshold, and the difference in vertical bending stiffness is less than a second preset threshold.

[0076] Example 3

[0077] Figure 3 This is a structural schematic diagram of a composite material outer wing box segment beam model stiffness correction device provided in Embodiment 4 of this application, as shown below. Figure 3 As shown, the composite material outer wing box segment beam model stiffness correction device further includes a processor 310, a memory 320, an input device 330, and an output device 340; the number of processors 310 in the composite material outer wing box segment beam model stiffness correction device can be one or more. Figure 3 Taking a processor 310 as an example; the processor 310, memory 320, input device 330, and output device 340 in the composite material outer wing box segment beam model stiffness correction device can be connected via a bus or other means. Figure 3 Taking the example of a connection between China and Israel via a bus.

[0078] The memory 320, as a computer-readable storage medium, can be used to store software programs, computer-executable programs, and modules, such as the program instructions / modules corresponding to the composite material outer wing box segment beam model stiffness correction method in this embodiment of the invention. The processor 310 executes the various functional applications and data processing of the composite material outer wing box segment beam model stiffness correction device by running the software programs, instructions, and modules stored in the memory 320, thereby realizing the aforementioned composite material outer wing box segment beam model stiffness correction method.

[0079] Obtain the beam model and GFEM model of the outer wing box segment. The loads on the beam model are aerodynamic loads, and the loads on the GFEM model are nodal loads.

[0080] By rigidly connecting the beam model and the GFEM model at the nodes, a combined model is obtained;

[0081] Stiffness difference calibration of the outer wing box segment beam model was performed based on the combined model, aerodynamic loads, and nodal loads.

[0082] Furthermore, the beam model and the GFEM model are rigidly connected at the nodes to obtain a combined model, including:

[0083] For any node of the beam model, rigidly connect the node of the beam model to the node of the corresponding GFEM model with the same cross section.

[0084] By applying fixed boundary conditions to the root of the rigidly connected model, a combined model is obtained.

[0085] Furthermore, stiffness difference calibration of the outer wing box segment is performed based on the combined model, aerodynamic loads, and nodal loads, including:

[0086] Based on the stiffness difference between the outer wing box segment beam model and the GFEM model under aerodynamic and nodal loads using the combined model;

[0087] Stiffness calibration was performed on the outer wing box segment beam model based on stiffness differences;

[0088] The beam model is updated based on the calibrated stiffness, and the steps of node rigid connection and stiffness difference calibration are performed until the stiffness difference meets the preset stop iteration condition.

[0089] Furthermore, based on the stiffness differences between the outer wing box segment beam model and the GFEM model under aerodynamic and nodal loads, the results include:

[0090] Based on the combined model, the first deformation data of the beam model under aerodynamic load and the second deformation data under nodal load are determined.

[0091] Based on the combined model, the third deformation data of the GFEM model under aerodynamic load and the fourth deformation data under nodal load were determined.

[0092] The stiffness difference is determined based on the first deformation data, the second deformation data, the third deformation data, and the fourth deformation data.

[0093] Furthermore, the stiffness differences include torsional stiffness differences and vertical bending stiffness differences; the first deformation data includes the first deflection and the first torsion angle under aerodynamic load on the beam model, the second deformation data includes the second deflection and the second torsion angle under nodal load on the beam model, the third deformation data includes the third deflection and the third torsion angle under aerodynamic load on the GFEM model, and the fourth deformation data includes the fourth deflection and the fourth torsion angle under nodal load on the GFEM model.

[0094] The stiffness difference is determined based on the first deformation data, the second deformation data, the third deformation data, and the fourth deformation data, including:

[0095] The torsional stiffness difference is determined based on the first torsion angle, the second torsion angle, the third torsion angle, and the fourth torsion angle;

[0096] The difference in vertical bending stiffness is determined based on the first deflection, the second deflection, the third deflection, and the fourth deflection.

[0097] Furthermore, stiffness differences include torsional stiffness differences and vertical bending stiffness differences;

[0098] Stiffness calibration of the outer wing box section is performed based on stiffness differences, including:

[0099] The torsional stiffness of the outer wing box section is calibrated based on the difference in torsional stiffness and a first preset threshold.

[0100] The vertical bending stiffness of the outer wing box segment is calibrated based on the difference in vertical bending stiffness and a second preset threshold.

[0101] Furthermore, the preset stopping iteration condition is that the difference in torsional stiffness is less than a first preset threshold, and the difference in vertical bending stiffness is less than a second preset threshold.

[0102] The memory 320 may primarily include a program storage area and a data storage area. The program storage area may store the operating system and at least one application program required for a given function; the data storage area may store data created based on terminal usage. Furthermore, the memory 320 may include high-speed random access memory and non-volatile memory, such as at least one disk storage device, flash memory, or other non-volatile solid-state storage device. In some instances, the memory 320 may further include memory remotely located relative to the processor 310, which can be connected via a network to a composite material outer wing box segment beam model stiffness correction device. Examples of such networks include, but are not limited to, the Internet, intranets, local area networks, mobile communication networks, and combinations thereof.

[0103] Example 4

[0104] Embodiment 4 of this application also provides a storage medium containing computer-executable instructions. When executed by a computer processor, the computer-executable instructions are used to perform a method for correcting the stiffness of a composite material outer wing box segment beam model. The method includes:

[0105] Obtain the beam model and GFEM model of the outer wing box segment. The loads on the beam model are aerodynamic loads, and the loads on the GFEM model are nodal loads.

[0106] By rigidly connecting the beam model and the GFEM model at the nodes, a combined model is obtained;

[0107] Stiffness difference calibration of the outer wing box segment beam model was performed based on the combined model, aerodynamic loads, and nodal loads.

[0108] Furthermore, the beam model and the GFEM model are rigidly connected at the nodes to obtain a combined model, including:

[0109] For any node of the beam model, rigidly connect the node of the beam model to the node of the corresponding GFEM model with the same cross section.

[0110] By applying fixed boundary conditions to the root of the rigidly connected model, a combined model is obtained.

[0111] Furthermore, stiffness difference calibration of the outer wing box segment is performed based on the combined model, aerodynamic loads, and nodal loads, including:

[0112] Based on the stiffness difference between the outer wing box segment beam model and the GFEM model under aerodynamic and nodal loads using the combined model;

[0113] Stiffness calibration was performed on the outer wing box segment beam model based on stiffness differences;

[0114] The beam model is updated based on the calibrated stiffness, and the steps of node rigid connection and stiffness difference calibration are performed until the stiffness difference meets the preset stop iteration condition.

[0115] Furthermore, based on the stiffness differences between the outer wing box segment beam model and the GFEM model under aerodynamic and nodal loads, the results include:

[0116] Based on the combined model, the first deformation data of the beam model under aerodynamic load and the second deformation data under nodal load are determined.

[0117] Based on the combined model, the third deformation data of the GFEM model under aerodynamic load and the fourth deformation data under nodal load were determined.

[0118] The stiffness difference is determined based on the first deformation data, the second deformation data, the third deformation data, and the fourth deformation data.

[0119] Furthermore, the stiffness differences include torsional stiffness differences and vertical bending stiffness differences; the first deformation data includes the first deflection and the first torsion angle under aerodynamic load on the beam model, the second deformation data includes the second deflection and the second torsion angle under nodal load on the beam model, the third deformation data includes the third deflection and the third torsion angle under aerodynamic load on the GFEM model, and the fourth deformation data includes the fourth deflection and the fourth torsion angle under nodal load on the GFEM model.

[0120] The stiffness difference is determined based on the first deformation data, the second deformation data, the third deformation data, and the fourth deformation data, including:

[0121] The torsional stiffness difference is determined based on the first torsion angle, the second torsion angle, the third torsion angle, and the fourth torsion angle;

[0122] The difference in vertical bending stiffness is determined based on the first deflection, the second deflection, the third deflection, and the fourth deflection.

[0123] Furthermore, stiffness differences include torsional stiffness differences and vertical bending stiffness differences;

[0124] Stiffness calibration of the outer wing box section is performed based on stiffness differences, including:

[0125] The torsional stiffness of the outer wing box section is calibrated based on the difference in torsional stiffness and a first preset threshold.

[0126] The vertical bending stiffness of the outer wing box segment is calibrated based on the difference in vertical bending stiffness and a second preset threshold.

[0127] Furthermore, the preset stopping iteration condition is that the difference in torsional stiffness is less than a first preset threshold, and the difference in vertical bending stiffness is less than a second preset threshold.

[0128] Of course, the computer-executable instructions provided in the embodiments of this application are not limited to the above-described method operations, but can also execute related operations in the composite material outer wing box segment beam model stiffness correction method provided in any embodiment of this application.

[0129] Based on the above description of the implementation methods, those skilled in the art can clearly understand that this application can be implemented using software and necessary general-purpose hardware, and of course, it can also be implemented using hardware, but in many cases the former is a better implementation method. Based on this understanding, the technical solution of this application, in essence, or the part that contributes to the prior art, can be embodied in the form of a software product. This computer software product can be stored in a computer-readable storage medium, such as a computer floppy disk, read-only memory (ROM), random access memory (RAM), flash memory, hard disk, or optical disk, etc., including several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute the methods of the various embodiments of this application.

[0130] It is worth noting that in the embodiments of the search device described above, the various units and modules included are only divided according to functional logic, but are not limited to the above division, as long as the corresponding functions can be achieved; in addition, the specific names of each functional unit are only for easy differentiation and are not used to limit the scope of protection of this application.

[0131] Note that the above description is merely a preferred embodiment and the technical principles employed in this application. Those skilled in the art will understand that this application is not limited to the specific embodiments described herein, and various obvious changes, readjustments, and substitutions can be made without departing from the scope of protection of this application. Therefore, although this application has been described in detail through the above embodiments, this application is not limited to the above embodiments. Many other equivalent embodiments may be included without departing from the concept of this application, and the scope of this application is determined by the scope of the appended claims.

Claims

1. A method for stiffness correction of a composite material outer wing box segment beam model, characterized in that, The method includes: Obtain the beam model and GFEM model of the outer wing box segment. The loads on the beam model are aerodynamic loads, and the loads on the GFEM model are nodal loads. The beam model and the GFEM model are rigidly connected at nodes to obtain a combined model; The stiffness difference of the outer wing box segment beam model is calibrated based on the combined model, the aerodynamic load, and the nodal load.

2. The method according to claim 1, characterized in that, The step of rigidly connecting the beam model and the GFEM model at the nodes to obtain a combined model includes: For any node of the beam model, the node of the beam model is rigidly connected to the node of the corresponding GFEM model with the same cross section. By applying fixed boundary conditions to the root of the rigidly connected model, a combined model is obtained.

3. The method according to claim 1, characterized in that, The stiffness difference calibration of the outer wing box segment based on the combined model, the aerodynamic loads, and the nodal loads includes: Based on the combined model under the aerodynamic load and the nodal load, the stiffness difference between the outer wing box segment beam model and the GFEM model; The stiffness of the outer wing box segment beam model is calibrated based on the stiffness difference. The beam model is updated based on the calibrated stiffness, and the steps of node rigid connection and stiffness difference calibration are performed until the stiffness difference meets the preset stop iteration condition.

4. The method according to claim 3, characterized in that, The stiffness difference between the outer wing box segment beam model and the GFEM model under the aerodynamic load and the nodal load, based on the combined model, includes: Based on the combined model, the first deformation data of the beam model under aerodynamic load and the second deformation data under the nodal load are determined; Based on the combined model, the third deformation data of the GFEM model under aerodynamic load and the fourth deformation data under the nodal load are determined. The stiffness difference is determined based on the first deformation data, the second deformation data, the third deformation data, and the fourth deformation data.

5. The method according to claim 4, characterized in that, The stiffness difference includes torsional stiffness difference and vertical bending stiffness difference; the first deformation data includes the first deflection and the first torsion angle under aerodynamic load on the beam model, the second deformation data includes the second deflection and the second torsion angle under nodal load on the beam model, the third deformation data includes the third deflection and the third torsion angle under aerodynamic load on the GFEM model, and the fourth deformation data includes the fourth deflection and the fourth torsion angle under nodal load on the GFEM model. Determining the stiffness difference based on the first deformation data, the second deformation data, the third deformation data, and the fourth deformation data includes: The torsional stiffness difference is determined based on the first torsion angle, the second torsion angle, the third torsion angle, and the fourth torsion angle; The difference in vertical bending stiffness is determined based on the first deflection, the second deflection, the third deflection, and the fourth deflection.

6. The method according to claim 3, characterized in that, The stiffness difference includes torsional stiffness difference and vertical bending stiffness difference; The stiffness calibration of the outer wing box segment based on the stiffness difference includes: The torsional stiffness of the outer wing box segment is calibrated based on the torsional stiffness difference and a first preset threshold. The vertical bending stiffness of the outer wing box segment is calibrated based on the vertical bending stiffness difference and the second preset threshold.

7. The method according to claim 6, characterized in that, The preset stop iteration condition is that the difference in torsional stiffness is less than a first preset threshold, and the difference in vertical bending stiffness is less than a second preset threshold.

8. A stiffness correction device for a composite material outer wing box segment beam model, characterized in that, include: The acquisition module is used to acquire the beam model and GFEM model of the outer wing box segment. The load of the beam model is an aerodynamic load, and the load of the GFEM model is a nodal load. A connection module is used to rigidly connect the beam model and the GFEM model at nodes to obtain a combined model; The stiffness calibration module is used to perform stiffness calibration on the outer wing box segment beam model based on the combined model, the aerodynamic load, and the nodal load.

9. A device for correcting the stiffness of a composite material outer wing box segment beam, characterized in that, include: One or more processors; Storage device for storing one or more programs. When the one or more programs are executed by the one or more processors, the one or more processors implement the composite material outer wing box segment beam model stiffness correction method as described in any one of claims 1-7.

10. A computer-readable storage medium having a computer program stored thereon, characterized in that, When executed by the processor, the program implements the stiffness correction method for the composite material outer wing box segment beam model as described in any of claims 1-7.

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