Structure correction method, device and equipment for composite material C-shaped beam and medium

Abstract

The embodiment of the invention discloses a structure correction method, device and equipment of a composite material C-shaped beam and a medium, which are applied to the field of composite materials, and the method comprises the following steps: obtaining a three-dimensional model and structure parameters of the composite material C-shaped beam; determining a web fiber direction reference line and an edge strip fiber direction reference line in the three-dimensional model according to the three-dimensional model; a deviation angle is determined according to the web fiber direction reference line and the edge strip fiber direction reference line, and the elastic modulus of the composite material C-shaped beam is determined according to the structural parameters of all the laying layers and the deviation angle; according to the elastic modulus, the strength margin of the composite material C-shaped beam is determined; if the strength margin does not meet the preset condition, the structural parameters, corresponding to the strength margin, of the composite material C-shaped beam are corrected according to the strength margin and the preset condition, and the structure of the composite material C-shaped beam is adjusted according to the corrected structural parameters. According to the technical scheme, the structural deviation of the composite material C-shaped beam can be corrected, and the safety of the composite material C-shaped beam is guaranteed.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of composite materials, and in particular to a composite C-beam structure correction method, device, equipment and medium. BACKGROUND

[0002] The hot diaphragm process is a technique for manufacturing composite parts, particularly suitable for the manufacture of complex-shaped parts in the field of aeronautics. This process achieves the desired shape by preforming a prepreg using a hot diaphragm.

[0003] The composite C-beam structure using the hot diaphragm process has a deviation between the actual fiber angle and the theoretically analyzed fiber angle during the forming process, which to some extent causes differences between the strength performance and safety margin obtained by theoretical analysis and the actual situation of the composite part.

[0004] The deviation between the fiber angle of the formed composite part and the design layup angle may affect the mechanical properties of the typical structure of the composite material, specifically in the following two cases: 1) the deviation of the fiber angle reduces the mechanical properties of the actual structure, which may cause the aircraft structure design not to follow the principle of conservatism, and in some cases where the structural safety margin is critical, it may pose a hidden danger to the safety of the aircraft; 2) the deviation of the fiber angle improves the mechanical properties of the actual structure, resulting in overly conservative design of the actual structure, which fails to fully utilize the designability of composite materials, leading to a heavier structure. At the same time, there is currently no accurate method to correct the deviation of the mechanical properties of the composite C-beam structure caused by the hot diaphragm process. SUMMARY

[0005] The present application provides a composite C-beam structure correction method, device, equipment and medium, the technical scheme provided by the present application can correct the mechanical properties of the composite C-beam structure and ensure the structural safety of the composite C-beam.

[0006] In a first aspect, the present application provides a composite C-beam structure correction method, comprising:

[0007] obtaining a three-dimensional model and structural parameters of a composite C-beam, wherein the composite C-beam is composed of multiple layers of plies, and the composite C-beam includes a web and a stringer;

[0008] determining a web fiber direction reference line and a stringer fiber direction reference line in the three-dimensional model according to the three-dimensional model;

[0009] determining a deviation angle according to the web fiber direction reference line and the stringer fiber direction reference line, and determining the elastic modulus of the composite C-beam according to the structural parameters of each ply and the deviation angle;

[0010] determine a strength margin of the composite C-beam according to the elastic modulus;

[0011] If the strength margin does not satisfy a preset condition, correct a structure parameter of the composite C-beam corresponding to the strength margin according to the strength margin and the preset condition, and adjust the structure of the composite C-beam according to the corrected structure parameter.

[0012] In a second aspect, an embodiment of the present application provides a structure correction device of a composite C-beam, including:

[0013] The obtaining module is configured to obtain a three-dimensional model and a structure parameter of the composite C-beam, wherein the composite C-beam is composed of multiple layers of plies, and the composite C-beam includes a web and a stringer;

[0014] The elastic modulus correction module is configured to determine a deviation angle according to the web fiber direction reference line and the stringer fiber direction reference line, and determine the elastic modulus of the composite C-beam according to the structure parameter of each ply and the deviation angle.

[0015] The strength margin correction module is configured to determine the strength margin of the composite C-beam according to the elastic modulus.

[0016] The structure parameter correction module is configured to correct the structure parameter of the composite C-beam corresponding to the strength margin according to the strength margin and the preset condition if the strength margin does not satisfy the preset condition, and adjust the structure of the composite C-beam according to the corrected structure parameter.

[0017] In a third aspect, an embodiment of the present application provides an electronic device, including:

[0018] at least one processor; and

[0019] a memory connected with the at least one processor; wherein

[0020] 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 execute the structure correction method of the composite C-beam according to any one of the embodiments of the present application.

[0021] In a fourth aspect, an embodiment of the present application provides a computer readable storage medium, which stores computer instructions for enabling a processor to execute the structure correction method of the composite C-beam according to any one of the embodiments of the present application.

[0022] The embodiment of the present application provides a composite C-shaped beam structure correction method, device, equipment and medium, the method comprises the following steps: obtaining a three-dimensional model and structure parameters of a composite C-shaped beam, wherein the composite C-shaped beam is composed of multiple layers of laminates, and the composite C-shaped beam comprises a web and a stringer; determining a web fiber direction reference line and a stringer fiber direction reference line in the three-dimensional model according to the three-dimensional model; determining a deviation angle according to the web fiber direction reference line and the stringer fiber direction reference line, and determining the elastic modulus of the composite C-shaped beam according to the structure parameters of each laminate and the deviation angle; determining the strength margin of the composite C-shaped beam according to the elastic modulus; if the strength margin does not meet a preset condition, correcting the structure parameters of the composite C-shaped beam corresponding to the strength margin according to the strength margin and the preset condition, and adjusting the structure of the composite C-shaped beam according to the corrected structure parameters. Specifically, by determining the web fiber direction reference line and the stringer fiber direction reference line, the deviation angle can be determined; then the elastic modulus of the composite C-shaped beam can be accurately determined according to the structure parameters and the deviation angle, and then the strength margin of the composite C-shaped beam can be determined according to the elastic modulus; and then the structure parameters of the composite C-shaped beam corresponding to the elastic modulus can be corrected according to the strength margin and the preset condition, so that the structural deviation of the composite C-shaped beam, such as the structural deviation caused by the fiber angle deviation due to the heat diaphragm process, can be accurately corrected, the accuracy of the mechanical property evaluation of the composite C-shaped beam is improved, and the safety of the composite C-shaped beam is ensured. BRIEF DESCRIPTION OF DRAWINGS

[0023] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the following will briefly introduce the drawings needed to be used in the embodiment description. Obviously, the drawings in the following description are only some embodiments of the present application, and other drawings can also be obtained by those skilled in the art without any creative effort.

[0024] Figure 1 A flowchart of a composite C-shaped beam structure correction method provided for the embodiment one of the present application;

[0025] Figure 2 A flowchart of a composite C-shaped beam structure correction method provided for the embodiment two of the present application;

[0026] Figure 3 A structure diagram of a composite C-shaped beam provided for the embodiment of the present application;

[0027] Figure 4 A schematic diagram of the coordinate relationship between the normal axis coordinate system and the offset axis coordinate system provided for the embodiment of the present application;

[0028] Figure 5A schematic diagram of the ply thickness provided for the embodiment of the present application is shown in FIG. 1.

[0029] Figure 6 A schematic diagram of the elastic modulus calculation process provided for the embodiment of the present application is shown in FIG. 2.

[0030] Figure 7 A schematic diagram of the composite C-beam structure modification provided for the embodiment of the present application is shown in FIG. 3.

[0031] Figure 8 A schematic diagram of the composite C-beam structure modification device provided for the third embodiment of the present application is shown in FIG. 4.

[0032] Figure 9 A schematic diagram of the electronic device provided for the fourth embodiment of the present application is shown in FIG. 5. DETAILED DESCRIPTION

[0033] In order to make the personnel in the technical field better understand the present application scheme, the technical scheme in the embodiment of the present application will be described clearly and completely below in combination with the drawings in the embodiment of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, not all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by the person skilled in the art without creative labor should belong to the scope of protection of the present application.

[0034] It should be noted that the terms "first", "second" and the like in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, and do not necessarily indicate 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 that 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 have to be limited 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.

[0035] It should be noted that in the technical scheme of the present disclosure, the collection, storage, use, processing, transmission, provision and disclosure of user personal information involved in the technical scheme comply with the relevant legal regulations and do not violate public order and good customs.

[0036] Embodiment one

[0037] Figure 1A flowchart of a structure modification method of a composite C-beam provided for an embodiment of the present application. The method can be applied to modify the structural deviation of a composite C-beam using a thermal diaphragm process, such as the structural deviation of a composite C-beam caused by the difference between the actual fiber angle and the preset fiber laying angle of the composite C-beam. The method can be executed by a structure modification device of a composite C-beam, which can be composed of software and hardware and configured in various computers or servers.

[0038] As shown in Figure 1 , comprising:

[0039] Step 110, obtaining a three-dimensional model and structure parameters of a composite C-beam, wherein the composite C-beam is composed of multiple layers of plies, and the composite C-beam includes a web and a stringer.

[0040] The composite C-beam can be laid and stacked by multiple layers of plies, and the cross section of the formed composite part is in the shape of "C", so it is called C-beam. The composite material can be composed of carbon fiber and resin material, which is not limited here. Further, the composite C-beam is composed of a web and a stringer.

[0041] The structure parameters can include overall structure parameters of the composite C-beam and local structure parameters of each ply. The overall structure parameters can represent the overall shape of the composite C-beam, including the length, width and height of the composite C-beam, and the shape of the composite C-beam. The local structure parameters can include the fiber laying angle of each ply, the ply thickness and the number of plies, etc. The fiber laying angles in different plies can be the same or different.

[0042] Specifically, the three-dimensional model of the composite C-beam can be generated by three-dimensional visualization processing of the composite C-beam based on the structure parameters of the composite C-beam.

[0043] Step 120, determining a web fiber direction reference line and a stringer fiber direction reference line in the three-dimensional model according to the three-dimensional model.

[0044] The web fiber direction reference line is a reference line determined on the web, and the stringer fiber direction reference line is a reference line determined on the stringer. The web fiber direction reference line and the stringer fiber direction reference line are used to provide a reference basis for the fiber angle of the composite C-beam, and further determine the fiber angle of the composite C-beam. The spatial coordinates corresponding to the three-dimensional model represent the coordinates of the pixel points in the three-dimensional diagram of the composite C-beam.

[0045] Specifically, the web fiber direction reference line and the edge strip fiber direction reference line can be determined according to the three-dimensional model of the composite C-beam, and then the specific deviation value of the fiber angle of the composite C-beam can be determined according to the web fiber direction reference line and the edge strip fiber direction reference line. Then, whether the composite C-beam needs to be corrected can be determined according to the elastic modulus determined according to the specific deviation value of the fiber angle.

[0046] Step 130, determining a deviation angle according to the web fiber direction reference line and the edge strip fiber direction reference line, and determining the elastic modulus of the composite C-beam according to the structure parameters of each ply and the deviation angle.

[0047] Specifically, the deviation angle is the deviation angle between the theoretical fiber angle and the actual fiber angle of the fiber. The deviation angle may change due to manufacturing errors, and the change of the deviation angle will affect the mechanical properties of the composite C-beam. The theoretical fiber angle can be the fiber laying angle of the ply of the composite C-beam.

[0048] Specifically, the elastic modulus is a characteristic parameter of the composite C-beam, which is used to describe the elastic properties of the composite C-beam, and is also used to determine whether the composite C-beam meets the preset condition. Further, the fiber angle in the ply of the composite C-beam will affect the elastic modulus of the composite C-beam, and then affect the mechanical properties of the composite C-beam.

[0049] Step 140, determining the strength margin of the composite C-beam according to the elastic modulus.

[0050] The strength margin refers to the difference between the maximum load that the composite C-beam structure can withstand and the actual working load during the design of the composite C-beam structure. It is usually used to evaluate the safety and reliability of the structure. Further, the calculation method of the strength margin is not limited here.

[0051] Step 150, if the strength margin does not meet the preset condition, then the structure parameters of the composite C-beam corresponding to the strength margin are corrected according to the strength margin and the preset condition, and the structure of the composite C-beam is adjusted according to the corrected structure parameters.

[0052] Specifically, the preset condition is used to determine whether the strength margin of the composite C-beam meets the expected safety index. If the preset condition is met, it means that the structure of the composite C-beam is stable and meets the safety index.

[0053] Optionally, the preset condition can be a structural safety margin condition. Further, the elastic modulus can be input into a structural strength checking tool, the internal force solution is imported and calculation is performed. If the structural safety margin calculated by the elastic modulus meets the requirement, the correction is ended, otherwise, the structural parameters of the composite C-beam corresponding to the elastic modulus can be corrected according to the elastic modulus and the preset condition. It should be noted that the present application does not limit the method of determining the structural safety margin according to the elastic modulus.

[0054] The embodiment of the present application provides a structural correction method of a composite C-beam, which comprises the following steps: obtaining a three-dimensional model and structural parameters of a composite C-beam, wherein the composite C-beam is composed of multiple layers of plies, and the composite C-beam comprises a web and a stringer; determining a web fiber direction reference line and a stringer fiber direction reference line in the three-dimensional model according to the three-dimensional model; determining a deviation angle according to the web fiber direction reference line and the stringer fiber direction reference line, and determining an elastic modulus of the composite C-beam according to the structural parameters of each ply and the deviation angle; determining a strength margin of the composite C-beam according to the elastic modulus; if the strength margin does not meet a preset condition, correcting the structural parameters of the composite C-beam corresponding to the strength margin according to the strength margin and the preset condition, and adjusting the structure of the composite C-beam according to the corrected structural parameters. Specifically, by determining the web fiber direction reference line and the stringer fiber direction reference line, the deviation angle can be determined, and then the elastic modulus of the composite C-beam can be accurately determined according to the deviation angle, and then the strength margin of the composite C-beam can be determined according to the elastic modulus, and then the structural parameters of the composite C-beam corresponding to the elastic modulus can be corrected according to the strength margin and the preset condition, so that the structural deviation of the composite C-beam, such as the structural deviation caused by the fiber angle deviation due to the thermal diaphragm process, can be accurately corrected, the mechanical properties of the composite C-beam are improved, and the safety of the composite C-beam is ensured. Further, by correcting the structure of the composite C-beam, the structural design potential of the composite C-beam can be improved, and the accuracy of the structural strength analysis of the composite C-beam can be improved.

[0055] Embodiment two

[0056] Figure 2 A flowchart of a structural correction method of a composite C-beam provided by the embodiment two of the present application is provided, and the embodiment is further limited to the way of determining the web fiber direction reference line and the stringer fiber direction reference line in the three-dimensional model of the composite C-beam based on the above-mentioned embodiments. The embodiment can be applied to the above-mentioned embodiments.

[0057] As Figure 2 shown, it comprises:

[0058] In step 201, a three-dimensional model and structural parameters of a composite C-beam are acquired, wherein the composite C-beam is composed of multiple layers of plies, and the composite C-beam includes a web and a stringer.

[0059] In step 202, a spatial coordinate of the web is determined according to a spatial coordinate corresponding to the three-dimensional model.

[0060] In step 203, a horizontal center line of the web is determined according to the spatial coordinate of the web.

[0061] In step 204, the horizontal center line is determined as a web fiber direction reference line.

[0062] Steps 202-204 are a determination manner of the web fiber direction reference line.

[0063] In step 205, a web coordinate plane in which the web is located is determined according to the spatial coordinate of the web.

[0064] In step 206, a stringer outer shape plane is determined according to a spatial coordinate of the stringer.

[0065] In step 207, a theoretical stringer fiber direction reference line is determined according to the web coordinate plane and the stringer outer shape plane.

[0066] In step 208, an actual stringer fiber direction reference line is determined according to the theoretical stringer fiber direction reference line and the web fiber direction reference line.

[0067] Specifically, steps 205-208 are a determination manner of the theoretical stringer fiber direction reference line and the actual stringer fiber direction reference line.

[0068] The web coordinate plane is a coordinate plane in which the web is located, and the stringer outer shape plane is an outer shape plane of the three-dimensional model in which the stringer is located.

[0069] Further, the fiber angle deviation, i.e., a deviation angle, can be determined through the theoretical stringer fiber direction reference line and the actual stringer fiber direction reference line.

[0070] Optionally, the determination manner of the theoretical stringer fiber direction reference line includes:

[0071] A spatial plane parallel to the web coordinate plane is determined as a candidate reference plane;

[0072] The candidate reference plane intersecting the stringer outer shape plane is determined as a target reference plane;

[0073] A candidate stringer fiber direction reference line generated by the intersection of the target reference plane and the stringer outer shape plane is determined;

[0074] The candidate stringer fiber direction reference line satisfying a preset position condition is determined as the theoretical stringer fiber direction reference line.

[0075] The preset position condition is used to represent the position of the preset fiber, and the center line of the wide edge of the edge strip can be determined as the position of the preset fiber length, for example.

[0076] Optionally, the determination method of the actual edge strip fiber direction reference line comprises:

[0077] At least one target point is obtained on the theoretical edge strip fiber direction reference line.

[0078] The surface length distance between the target point and the web fiber direction reference line is determined.

[0079] An actual edge strip fiber direction reference line is generated according to the surface length distance and the target point, wherein the surface distance between each point on the actual edge strip fiber direction reference line and the web fiber direction reference line is equal to the surface length distance.

[0080] Specifically, the target point is a sampling point for judging whether the fiber has an angle deviation on the theoretical edge strip fiber direction reference line, the actual edge strip fiber direction reference line can be generated through the target point, and the angle deviation of the fiber can be calculated, therefore, the calculation accuracy of the angle deviation increases with the increase of the number of target points, and the specific number is not limited. The surface length distance is the surface distance between the target point and the web fiber direction reference line, and is also the surface distance between each point on the actual edge strip fiber direction reference line and the web fiber direction reference line. For example, Figure 3 A structural diagram of a composite C-beam provided by the embodiment of the present application is shown, wherein 1 is a web, 2 is an edge strip, 3 is a web fiber direction reference line, 4 is a theoretical edge strip fiber direction reference line, 5 is an actual edge strip fiber direction reference line, 6 is a target point, and specifically, Figure 3 Three target points and corresponding actual edge strip fiber direction reference lines are shown in the figure, and the specific number of target points can be determined according to the required calculation accuracy, which is not limited here.

[0081] Further, by generating the actual edge strip fiber direction reference line and the theoretical edge strip fiber direction reference line, it can be determined whether the fiber has an angle deviation, and whether the structure of the composite C-beam needs to be corrected.

[0082] Specifically, the curved surface distance between the actual flange fiber direction reference line and the web fiber direction reference line is the actual fiber distance, the curved surface distance between the theoretical flange fiber direction reference line and the web fiber direction reference line is the theoretical fiber distance, if the actual flange fiber direction reference line and the theoretical flange fiber direction reference line do not overlap, it indicates that there may be a fiber angle deviation, and the structure of the composite C-shaped beam may have a safety problem, which needs to be corrected.

[0083] Step 209, determining the fiber laying angle, the thickness of the ply and the number of plies according to the structure parameters of the ply.

[0084] Since the composite C-shaped beam is made of multiple layers of fiber laying, the fiber laying angle and the thickness of the ply of different plies may be different. Therefore, the fiber laying angle, the thickness of the ply and the number of plies need to be determined according to the structure parameters of the ply.

[0085] Step 210, determining the included angle between the actual flange fiber direction reference line and the theoretical flange fiber direction reference line as the deviation angle.

[0086] Step 211, determining the elastic modulus of the composite C-shaped beam according to the fiber laying angle, the thickness of the ply, the number of plies and the deviation angle.

[0087] The fiber laying angle can be 90°, 0° and ±45°.

[0088] Optionally, the elastic modulus of the composite C-shaped beam can be determined by the following formula:

[0089] θ i '=θ i +Δθ(i=1,2,...,n)

[0090] Wherein, θ i ′ is the actual fiber angle of the i-th layer, θ i is the fiber laying angle of the i-th layer, Δθ is the fiber angle deviation, and n is the number of plies. It should be noted that the formula assumes that there is no interlayer slip during the thermal insulation process, i.e. the fiber angle deviation of the ply with fiber laying angle of 90° and ±45° is equal to 0° layer.

[0091]

[0092] Wherein, m and n are the directional cosines of the included angle between the arbitrary rectangular coordinate system x-y (offset axis coordinate system) and the 1-2 coordinate system (normal axis coordinate system), m=cosθ, n=sinθ, -90°≤θ≤90°; when calculating the formula, θ is the actual fiber angle, is the offset modulus coefficient, and T is the modulus conversion matrix.

[0093] Exemplary, Figure 4 The schematic diagram of the coordinate relationship of the normal axis coordinate system and the off-axis coordinate system provided by the embodiment of the present application, which comprises: 1-2 normal axis coordinate system, x-y off-axis coordinate system and coordinate system angle deviation.

[0094]

[0095] Wherein, N is the total number of layers, Z represents the thickness of the layer, and the above formula can be calculated is the off-weight modulus coefficient, A, B and D are shear stiffness matrix, tension-bending coupling stiffness matrix and bending-torsion coupling stiffness matrix respectively. Exemplary, Figure 5 The schematic diagram of the layer thickness provided by the embodiment of the present application, wherein Z represents the thickness of the layer group with different number of layers.

[0096]

[0097] Wherein, e is the total thickness of the composite laminate, A ij E is the element of different positions in the shear stiffness A matrix, x E y and G xy are the elastic modulus. Exemplary, Figure 6 The schematic diagram of the elastic modulus calculation process provided by the embodiment of the present application, specifically, the corresponding modulus conversion matrix and off-axis modulus coefficient can be determined through the angle deviation of the single-layer fiber plate, and then the stiffness calculation is carried out to obtain the tensile and shear stiffness matrix, and then the elastic modulus of the composite C-shaped beam is determined.

[0098] Step 212, determining the strength margin of the composite C-shaped beam according to the elastic modulus.

[0099] Step 213, if the strength margin does not meet the preset condition, the structure parameter of the composite C-shaped beam corresponding to the strength margin is modified according to the strength margin and the preset condition, and the structure of the composite C-shaped beam is adjusted according to the modified structure parameter.

[0100] Exemplary, Figure 7 The schematic diagram of the composite C-shaped beam structure modification provided by the embodiment of the present application, wherein the three-dimensional model of the composite C-shaped beam needs to be generated according to the part model, and then the fiber deviation angle is determined, and then the elastic modulus E x E y and G xy of the composite C-shaped beam are determined based on the classical laminate theory and the fiber deviation angle, and then E x E y and G xyThe elastic modulus can be input into a structural strength checking tool, the internal force solution is introduced and calculation is performed to determine the strength margin of the composite C-shaped beam. If the strength margin meets the requirement, the correction is ended, otherwise, the structural parameters of the composite C-shaped beam corresponding to the strength margin can be corrected according to the strength margin and preset conditions.

[0101] Embodiment three

[0102] Figure 8 A structural schematic diagram of a composite C-shaped beam structure correction device provided for embodiment three of the present application is shown in FIG. 3. As shown in the figure, the device comprises: Figure 8

[0103] The acquisition module 810 is configured to acquire a three-dimensional model and structural parameters of a composite C-shaped beam, wherein the composite C-shaped beam is composed of multiple layers of plies, and the composite C-shaped beam comprises a web and a stringer.

[0104] The reference line determination module 820 is configured to determine a web fiber direction reference line and a stringer fiber direction reference line in the three-dimensional model according to the three-dimensional model.

[0105] The elastic modulus correction module 830 is configured to determine a deviation angle according to the web fiber direction reference line and the stringer fiber direction reference line, and determine the elastic modulus of the composite C-shaped beam according to the structural parameters of each ply and the deviation angle.

[0106] The strength margin correction module 840 is configured to determine the strength margin of the composite C-shaped beam according to the elastic modulus.

[0107] ​The structure parameter correction module 850 is configured to correct the structure parameter of the composite C-beam corresponding to the strength margin according to the strength margin and a preset condition if the strength margin does not satisfy the preset condition, and adjust the structure of the composite C-beam according to the corrected structure parameter. The embodiment of the present application provides a structure correction device for a composite C-beam. The device is configured to obtain a three-dimensional model and a structure parameter of a composite C-beam, wherein the composite C-beam is composed of multiple layers of plies, and the composite C-beam includes a web and a stringer; determine a web fiber direction reference line and a stringer fiber direction reference line in the three-dimensional model according to the three-dimensional model; determine a deviation angle according to the web fiber direction reference line and the stringer fiber direction reference line, and determine an elastic modulus of the composite C-beam according to the structure parameter of each ply and the deviation angle; determine a strength margin of the composite C-beam according to the elastic modulus; correct the structure parameter of the composite C-beam corresponding to the strength margin according to the strength margin and a preset condition if the strength margin does not satisfy the preset condition, and adjust the structure of the composite C-beam according to the corrected structure parameter. Specifically, the deviation angle is determined by determining the web fiber direction reference line and the stringer fiber direction reference line, and then the elastic modulus of the composite C-beam can be accurately determined according to the deviation angle and the structure parameter, and then the strength margin of the composite C-beam can be determined according to the elastic modulus, and then the structure parameter of the composite C-beam corresponding to the elastic modulus can be corrected according to the strength margin and the preset condition, so that the structural deviation of the composite C-beam, such as the structural deviation caused by the fiber angle deviation due to the thermal diaphragm process, can be accurately corrected, the mechanical properties of the composite C-beam are improved, and the safety of the composite C-beam is ensured.

[0108] Optionally, the reference line determination module 820 includes a web fiber direction reference line determination sub-module, a stringer fiber direction reference line determination sub-module, and a theoretical stringer fiber direction reference line determination sub-module.

[0109] The web fiber direction reference line determination sub-module is configured to determine the spatial coordinates of the web according to the spatial coordinates corresponding to the three-dimensional model, determine the horizontal center line of the web according to the spatial coordinates of the web, and determine the horizontal center line as the web fiber direction reference line.

[0110] The stringer fiber direction reference line determination sub-module is configured to determine the web coordinate plane in which the web is located according to the spatial coordinates of the web.

[0111] The stringer fiber direction reference line determination sub-module is configured to determine the web coordinate plane in which the web is located according to the spatial coordinates of the web.

[0112] The theoretical stringer fiber direction reference line determination sub-module is configured to determine the theoretical stringer fiber direction reference line according to the web coordinate plane and the stringer outer shape surface.

[0113] The actual flange fiber direction reference line is determined according to the theoretical flange fiber direction reference line and the web fiber direction reference line.

[0114] The flange fiber direction reference line determination sub-module comprises a theoretical flange fiber direction reference line determination unit and an actual flange fiber direction reference line determination unit.

[0115] The theoretical flange fiber direction reference line determination unit is configured to determine a spatial plane parallel to the web coordinate plane as a candidate reference plane, determine the candidate reference plane intersecting the flange outer shape plane as a target reference plane, determine a candidate flange fiber direction reference line generated by the intersection of the target reference plane and the flange outer shape plane, and determine the candidate flange fiber direction reference line satisfying a preset position condition as the theoretical flange fiber direction reference line.

[0116] The actual flange fiber direction reference line determination unit is configured to obtain at least one target point on the theoretical flange fiber direction reference line, determine a curved surface length distance between the target point and the web fiber direction reference line, and generate an actual flange fiber direction reference line according to the curved surface length distance and the target point, wherein the curved surface distance between each point on the actual flange fiber direction reference line and the web fiber direction reference line is equal to the curved surface length distance.

[0117] Optionally, the elastic modulus determination module 830 comprises:

[0118] The parameter determination unit is configured to determine the fiber laying angle, the thickness of the ply, and the number of plies of the ply according to the structural parameters of the ply.

[0119] The deviation determination unit is configured to determine the included angle between the actual flange fiber direction reference line and the theoretical flange fiber direction reference line as a deviation angle.

[0120] The calculation unit is configured to determine the elastic modulus of the composite C-shaped beam according to the fiber laying angle, the thickness of the ply, the number of plies, and the deviation angle of the ply.

[0121] The composite C-shaped beam structure modification device provided in the embodiments of the present application can execute the composite C-shaped beam structure modification method provided in any of the embodiments of the present application, and has the corresponding function modules and beneficial effects of the execution method.

[0122] Embodiment Four

[0123] Figure 9A 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.

[0124] As shown in Figure 9 The electronic device 10 includes at least one processor 11, and a memory, such as a read-only memory (ROM) 12, a random access memory (RAM) 13, etc., communicatively connected to the at least one processor 11, where the memory stores computer programs executable by the at least one processor. 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.

[0125] 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.

[0126] 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 special-purpose 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 structural modification method of the composite C-beam.

[0127] In some embodiments, the method of structural modification of a composite C-beam 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 method of structural modification of a composite C-beam as described above can be performed. Alternatively, in other embodiments, processor 11 can be configured to perform the method of structural modification of a composite C-beam by way of other any suitable means (e.g., by way of firmware).

[0128] 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 complex programmable logic device (CPLD), 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.

[0129] Computer programs used to implement the methods of the present 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 and partially on a remote machine or entirely on a remote machine or server.

[0130] 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.

[0131] 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.

[0132] 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.

[0133] 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.

[0134] It should be understood that the various forms of flow shown above can be reordered, added to, or have steps deleted. For example, the steps described in the present application can be performed in parallel, in series, or in a different order, as long as the desired results of the technical solutions of the present application can be achieved, which are not limited herein.

[0135] The above detailed description does not constitute a limitation on the protection scope 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 protection scope of the present application.

Claims

1. A structural correction method for a composite material C-beam, characterized in that: include: Obtaining a three-dimensional model and structural parameters of a composite material C-shaped beam, wherein the composite material C-shaped beam is composed of multiple layers and includes a web and flanges; Determining, based on the three-dimensional model, a web fiber direction reference line and a flange fiber direction reference line in the three-dimensional model; Determining a deviation angle according to the web fiber direction reference line and the flange fiber direction reference line, and determining the elastic modulus of the composite C-beam according to the structural parameters of each ply and the deviation angle; Determining the strength margin of the composite material C-beam according to the elastic modulus; If the strength margin does not meet the preset conditions, the structural parameters of the composite material C-beam corresponding to the strength margin are corrected according to the strength margin and the preset conditions, and the structure of the composite material C-beam is adjusted according to the corrected structural parameters.

2. The method according to claim 1, characterized in that Determining a web fiber direction reference line in the three-dimensional model according to the three-dimensional model includes: Determining the spatial coordinates of the web according to the spatial coordinates corresponding to the three-dimensional model; determining a horizontal centerline of the web according to the spatial coordinates of the web; The horizontal center line is determined as the web fiber direction reference line.

3. The method according to claim 2, characterized in that The flange fiber direction reference line includes a theoretical flange fiber direction reference line and an actual flange fiber direction reference line. Determining the flange fiber direction reference line in the three-dimensional model according to the three-dimensional model includes: Determining the web coordinate plane where the web is located according to the spatial coordinates of the web; Determining the outer profile of the edge strip according to the spatial coordinates of the edge strip; Determine a theoretical flange fiber direction reference line based on the web coordinate plane and flange outer profile; The actual flange fiber direction reference line is determined according to the theoretical flange fiber direction reference line and the web fiber direction reference line.

4. The method according to claim 3, characterized in that The step of determining a theoretical flange fiber direction reference line based on the web coordinate plane and the flange outer profile includes: determining a spatial surface parallel to the web coordinate plane as a candidate reference surface; Determine a candidate reference surface intersecting with the outer surface of the edge strip as a target reference surface; Determine a candidate flange fiber direction reference line generated by the intersection of the target reference surface and the flange outer surface; The candidate flange fiber direction reference line that meets the preset position condition is determined as the theoretical flange fiber direction reference line.

5. The method according to claim 3, characterized in that The determining of the actual flange fiber direction reference line according to the theoretical flange fiber direction reference line and the web fiber direction reference line includes: Acquire at least one target point on the theoretical edge fiber direction reference line; Determining a curved surface length distance between the target point and the web fiber direction reference line; An actual flange fiber direction reference line is generated according to the curved surface length distance and the target point, wherein the curved surface distance between each point on the actual flange fiber direction reference line and the web fiber direction reference line is equal to the curved surface length distance.

6. The method according to claim 3, characterized in that Determining the deviation angle according to the web fiber direction reference line and the flange fiber direction reference line, and determining the elastic modulus of the composite material C-beam according to the structural parameters of each ply and the deviation angle, includes: Determine the fiber laying angle, layer thickness and number of layers based on the structural parameters of the layer; Determine the angle between the actual flange fiber direction reference line and the theoretical flange fiber direction reference line as the deviation angle; The elastic modulus of the composite material C-beam is determined according to the fiber laying angle, the ply thickness, the number of plies and the deviation angle of the ply.

7. A structural correction device for a composite material C-beam, characterized in that: include: an acquisition module, configured to acquire a three-dimensional model and structural parameters of a composite material C-shaped beam, wherein the composite material C-shaped beam is composed of multiple layers and includes a web and flanges; A reference line determination module, configured to determine, based on the three-dimensional model, a web fiber direction reference line and a flange fiber direction reference line in the three-dimensional model; an elastic modulus correction module, configured to determine a deviation angle based on the web fiber direction reference line and the flange fiber direction reference line, and determine the elastic modulus of the composite C-beam based on the structural parameters of each ply and the deviation angle; a strength margin correction module, configured to determine a strength margin of the composite material C-beam according to the elastic modulus; A structural parameter correction module is used to correct the structural parameters of the composite material C-beam corresponding to the strength margin according to the strength margin and the preset conditions if the strength margin does not meet the preset conditions, and adjust the structure of the composite material C-beam according to the corrected structural parameters.

8. 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. The computer program is executed by the at least one processor to enable the at least one processor to perform the structural correction method of the composite material C-beam according to any one of claims 1 to 6.

9. 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 structural correction method of the composite material C-beam according to any one of claims 1 to 6 when executed.

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