Hole-drilling weight reduction method and apparatus for composite stiffened panel, and electronic device and storage medium

Abstract

Provided in the embodiments of the present disclosure are a hole-drilling weight reduction method and apparatus for a composite stiffened panel, and an electronic device and a storage medium. The method comprises: determining a target buckling load of a panel between any two target stringers in a constructed finite element model of a stiffened panel of a large composite thin-walled structure; determining the maximum deformation position of the stiffened panel in the finite element model of the stiffened panel, wherein the stiffened panel comprises the panel between the target stringers; providing holes with different preset diameters at the maximum deformation position and the center position of the stiffened panel, respectively, to obtain a plurality of first panels; determining a first buckling load of each first panel; acquiring, from each first buckling load, each second buckling load greater than or equal to the target buckling load; and acquiring, from each second buckling load, the first panel corresponding to the maximum buckling load, so as to perform hole drilling on the basis of a hole drilling mode of the first panel. The use of materials can be reduced, thereby reducing the weight of a large composite thin-walled structure.

Description

Composite stiffened panel opening weight reduction method and device, electronic equipment and storage medium

[0001] Cross-reference to Related Applications

[0002] The present disclosure claims priority to the Chinese patent application No. 202411231115.1, filed on September 3, 2024, and entitled "Composite Stiffened Panel Opening Weight Reduction Method and Device, Electronic Equipment and Storage Medium", the entire content of which is incorporated herein by reference. TECHNICAL FIELD

[0003] The present disclosure relates to the field of data processing, in particular to a composite stiffened panel opening weight reduction method and device, electronic equipment and storage medium. BACKGROUND

[0004] Large composite thin-walled structures are the main structure form in the fields of aerospace, rail transportation, etc. At present, the weight reduction of large composite thin-walled structures is achieved by reducing weight in the design process. For example, the weight reduction of large composite thin-walled structures is achieved by improving material allowable value and improving material utilization rate, etc. These methods have a certain degree of conservatism, so it is necessary to find a reasonable test method to determine the design value to achieve the purpose of de-conservatism and realize weight reduction. SUMMARY

[0005] The purpose of the present disclosure is to provide a composite stiffened panel opening weight reduction method and device, electronic equipment and storage medium, which can reduce the use of materials and thus achieve weight reduction.

[0006] To achieve the above purpose, the technical solutions adopted by the embodiments of the present application are as follows:

[0007] In a first aspect, the embodiments of the present application provide a composite stiffened panel opening weight reduction method, which comprises:

[0008] Determining the target buckling load of the panel between any two target stringers in the finite element model of the large composite thin-walled structure;

[0009] Determining the maximum deformation position of the stiffened panel in the finite element model of the stiffened panel, wherein the stiffened panel comprises the target panel between the target stringers;

[0010] Holes of different preset diameters are respectively formed in the maximum deformation position and the center position of the stiffened panel to obtain a plurality of first panels;

[0011] Determining the first buckling load of each first panel;

[0012] Obtaining each second buckling load greater than or equal to the target buckling load from each first buckling load;

[0013] obtaining a first wall panel corresponding to the maximum buckling load from the second buckling loads, and perforating the first wall panel based on a perforation mode of the first wall panel.

[0014] Optionally, the method further comprises:

[0015] determining a first diameter of a first hole corresponding to a maximum deformation position of the first wall panel corresponding to the maximum buckling load from the second buckling loads;

[0016] comparing the first diameter with a first preset diameter;

[0017] when the first diameter is greater than the first preset diameter, comparing the first diameter with a second preset diameter, wherein the first preset diameter is smaller than the second preset diameter;

[0018] when the first diameter is greater than the second preset diameter, performing a reinforcement treatment on the first hole.

[0019] Optionally, the method further comprises:

[0020] determining a second diameter of a second hole corresponding to a center position of the first wall panel corresponding to the maximum buckling load from the second buckling loads;

[0021] comparing the second diameter with a first preset diameter;

[0022] when the second diameter is greater than the first preset diameter, comparing the second diameter with a second preset diameter, wherein the first preset diameter is smaller than the second preset diameter;

[0023] when the second diameter is greater than the second preset diameter, performing a reinforcement treatment on the second hole.

[0024] Optionally, the step of determining the target buckling load of the wall panel between any two target stringers in the finite element model of the large composite thin-walled structure comprises:

[0025] determining a third buckling load of the wall panel between any two target stringers in the finite element model of the large composite thin-walled structure;

[0026] determining a fourth buckling load of the wall panel between any two target stringers in a four-side simply supported condition;

[0027] determining a fifth buckling load of the wall panel between any two target stringers in a four-side clamped condition;

[0028] calculating an average value of the fourth buckling load and the fifth buckling load;

[0029] calculating an absolute value of a difference between the third buckling load and the average value;

[0030] calculating a ratio of the absolute value and the third buckling load;

[0031] comparing the ratio with a preset value;

[0032] when the ratio is less than or equal to the preset value, taking the third buckling load as a target buckling load of a wallboard between any two target stringers in a finite element model of a stiffened wallboard of a large composite thin-walled structure.

[0033] Optionally, the step of determining the third buckling load of the wallboard between any two target stringers in the finite element model of the stiffened wallboard of the large composite thin-walled structure, comprises:

[0034] determining a mechanical property parameter of the finite element model of the stiffened wallboard of the large composite thin-walled structure;

[0035] determining an average strain of the wallboard between any two target stringers in the finite element model of the stiffened wallboard of the large composite thin-walled structure;

[0036] determining a thickness of any one of the wallboard between any two target stringers;

[0037] based on the mechanical property parameter, the average strain and the thickness, calculating the third buckling load of the wallboard between any two target stringers in the finite element model of the stiffened wallboard of the large composite thin-walled structure.

[0038] Optionally, the third buckling load satisfies the following formula: x = E * ε * t;

[0039] wherein N x is the third buckling load, E is the mechanical property parameter, ε is the average strain on the two target stringers, and t is the thickness.

[0040] Optionally, the fourth buckling load satisfies the following formula:

[0041] the fifth buckling load satisfies the following formula:

[0042] wherein D 11 is a bending stiffness coefficient of the wallboard between any two target stringers in the 11 direction, D 12 is a bending stiffness coefficient of the wallboard between any two target stringers in the 12 direction, D 22 is a bending stiffness coefficient of the wallboard between any two target stringers in the 22 direction, and D 66b is an outer spacing of the stringers of any of the target inter-stringer panels.

[0043] In a second aspect, the embodiments of the present application provide a composite stiffened panel opening weight-reducing device, the device comprising:

[0044] a determining module configured to determine a target buckling load of any two target inter-stringer panels in a finite element model of a large composite thin-walled structure;

[0045] an opening module configured to open holes with different preset diameters at the maximum deformation position and the center position of the stiffened panel, respectively, to obtain a plurality of first panels.

[0046] The determining module is further configured to determine a first buckling load of each of the first panels.

[0047] an obtaining module configured to obtain, from the first buckling loads, second buckling loads each of which is greater than or equal to the target buckling load, and obtain a first panel corresponding to a maximum buckling load from the second buckling loads, so as to open holes in the first panel.

[0048] In a third aspect, the embodiments of the present application provide an electronic device, which comprises a memory and a processor, the memory stores a computer program, and the processor implements the steps of the composite stiffened panel opening weight-reducing method when executing the computer program.

[0049] In a fourth aspect, the embodiments of the present application provide a computer readable storage medium, which stores a computer program, and the computer program is executed by a processor to implement the steps of the composite stiffened panel opening weight-reducing method.

[0050] The present application has the following beneficial effects:

[0051] The application determines the target buckling load of the wall plate between any two target stringers in the finite element model of the large composite thin-walled structure, determines the maximum deformation position of the stringer wall plate in the finite element model of the stringer wall plate, wherein the stringer wall plate includes the target wall plate between the target stringers, and different pre-set diameters are opened at the maximum deformation position and the center position of the stringer wall plate to obtain a plurality of first wall plates, the first buckling load of each first wall plate is determined, each second buckling load greater than or equal to the target buckling load is obtained from each first buckling load, the first wall plate corresponding to the maximum buckling load is obtained from each second buckling load, and the hole opening mode based on the first wall plate is used for hole opening, and when the hole opening diameter is less than a certain size, the buckling load is less affected, and local reinforcement can not be performed. This method can reduce the use of materials, thereby reducing the weight of the large composite thin-walled structure. BRIEF DESCRIPTION OF DRAWINGS

[0052] In order to more clearly illustrate the technical solutions of the embodiments of the present disclosure, the following will briefly introduce the drawings needed to be used in the embodiments. It should be understood that the following drawings only show some of the embodiments of the present disclosure, and therefore should not be regarded as a limitation on the scope. For those skilled in the art, other related drawings can also be obtained without creative labor on the basis of these drawings.

[0053] FIG. 1 is a block schematic diagram of an electronic device according to an embodiment of the present disclosure;

[0054] FIG. 2 is a flowchart of a composite stringer wall plate hole opening weight reduction method according to an embodiment of the present disclosure;

[0055] FIG. 3 is a schematic diagram of a strain load curve of a non-hole stringer wall plate under compression according to an embodiment of the present disclosure;

[0056] FIG. 4 is a schematic diagram of a strain load curve of a non-hole stringer wall plate under shear according to an embodiment of the present disclosure;

[0057] FIG. 5 is a schematic diagram of a strain load curve of a stringer wall plate with different hole diameters under compression according to an embodiment of the present disclosure;

[0058] FIG. 6 is a schematic diagram of a strain load curve of a stringer wall plate with different hole diameters under shear according to an embodiment of the present disclosure;

[0059] FIG. 7 is a flowchart of a composite stringer wall plate hole opening weight reduction method according to another embodiment of the present disclosure;

[0060] FIG. 8 is a flowchart of a composite stringer wall plate hole opening weight reduction method according to another embodiment of the present disclosure;

[0061] FIG. 9 is a schematic diagram of stringer spacing according to an embodiment of the present disclosure;

[0062] FIG. 10 is a structural block diagram of the opening weight-reducing device of the composite stiffened panel according to an embodiment of the present application. DETAILED DESCRIPTION

[0063] In order to make the objects, technical solutions and advantages of the embodiments of the present disclosure clearer, the technical solutions in the embodiments of the present disclosure will be described clearly and completely below with reference to the drawings in the embodiments of the present disclosure. Obviously, the described embodiments are only some but not all of the embodiments of the present disclosure. The components of the embodiments of the present disclosure described and shown in the drawings can be arranged and designed in various different configurations.

[0064] Therefore, the following detailed description of the embodiments of the present disclosure provided in the drawings is not intended to limit the scope of the claimed present disclosure, but only represents selected embodiments of the present disclosure. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in the present disclosure without creative labor are within the scope of protection of the present disclosure.

[0065] It should be noted that: similar reference numerals and letters represent similar items in the following drawings, and therefore, once an item is defined in one drawing, it does not need to be further defined and explained in subsequent drawings.

[0066] In the description of the present disclosure, it should be noted that if the terms "upper", "lower", "inner", "outer" and the like indicate the orientation or positional relationship shown in the drawings, or the orientation or positional relationship in which the product of the present disclosure is usually placed, which is only for the convenience of describing the present disclosure and simplifying the description, and does not indicate or imply that the indicated device or element must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present disclosure.

[0067] In addition, if the terms "first", "second" and the like appear, they are only configured to distinguish the description and cannot be understood as indicating or implying relative importance.

[0068] In the description of the present application, it should also be noted that unless otherwise explicitly specified and limited, the terms "arrangement", "installation", "connection", "connection" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium, or it can be the communication inside two elements. For those of ordinary skill in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0069] After a large number of researches, it is found that the current way to realize the weight reduction of large composite thin-walled structure is to reduce weight in the design process. For example, the weight reduction of large composite thin-walled structure is realized by improving the material allowable value and improving the material utilization rate. These methods have a certain conservatism, so it is necessary to find a reasonable test method to determine the design value to achieve the purpose of de-conservatism and realize the weight reduction.

[0070] In view of the above problems, the embodiment provides a composite stiffened panel hole weight reduction method and device, electronic equipment and storage medium, which can determine the target buckling load of the panel between any two target stringers in the finite element model of the stiffened panel of the large composite thin-walled structure constructed, determine the maximum deformation position of the stiffened panel in the finite element model of the stiffened panel, wherein the stiffened panel includes the target panel between the stringers, different preset diameters of holes are opened at the maximum deformation position and the center position of the stiffened panel respectively to obtain a plurality of first panels, the first buckling load of each first panel is determined, each second buckling load greater than or equal to the target buckling load is obtained from each first buckling load, the first panel corresponding to the maximum buckling load is obtained from each second buckling load, and the hole is opened based on the hole opening mode of the first panel. The use of materials can be reduced, and the weight of the large composite thin-walled structure can be reduced. The scheme provided in the embodiment is described in detail below.

[0071] The embodiment provides an electronic device. In a possible implementation manner, the electronic device can be a user terminal, for example, the electronic device can be, but is not limited to, a server, a smart phone, a personal computer (PC), a tablet computer, a personal digital assistant (PDA), a mobile Internet device (MID), and an image acquisition device, and the like.

[0072] Please refer to FIG. 1, which is a structural schematic diagram of an electronic device 100 provided by an embodiment of the present application. The electronic device 100 can further include more or fewer components than those shown in FIG. 1, or have a different configuration from that shown in FIG. 1. Each component shown in FIG. 1 can be realized by hardware, software, or a combination thereof.

[0073] The electronic device 100 includes a composite stiffened panel hole weight reduction device 110, a memory 120, and a processor 130.

[0074] The memory 120 and the processor 130 are electrically connected to each other directly or indirectly to realize data transmission or interaction. For example, the elements can be electrically connected to each other through one or more communication buses or signal lines. The composite stiffened panel opening weight reduction device 110 includes at least one software function module stored in the memory 120 in the form of software or firmware or solidified in the operating system (OS) of the electronic device 100. The processor 130 is configured to execute the executable modules stored in the memory 120, such as the software function modules and computer programs included in the composite stiffened panel opening weight reduction device 110.

[0075] The memory 120 can be, but is not limited to, a random access memory (RAM), a read-only memory (ROM), a programmable read-only memory (PROM), an erasable programmable read-only memory (EPROM), an electrically erasable programmable read-only memory (EEPROM), etc. The memory 120 is configured to store programs, and the processor 130 executes the programs after receiving an execution instruction.

[0076] Please refer to FIG. 2, which is a flow chart of a composite stiffened panel opening weight reduction method applied to the electronic device 100 of FIG. 1. The method including various steps will be described in detail below.

[0077] S201: Determine the target buckling load of the target inter-longeron panel in the finite element model of the large composite thin-walled structure.

[0078] S202: Determine the maximum deformation position of the stiffened panel in the finite element model of the stiffened panel.

[0079] The stiffened panel includes the target inter-longeron panel.

[0080] S203: Open holes with different preset diameters at the maximum deformation position and the center position of the stiffened panel, respectively, to obtain a plurality of first panels.

[0081] S204: Determine the first buckling load of each first panel.

[0082] S205: Obtain each second buckling load greater than or equal to the target buckling load from each first buckling load.

[0083] S206: Obtain the first wallboard corresponding to the maximum buckling load from each second buckling load, and perform hole opening based on the hole opening mode of the first wallboard.

[0084] It should be noted that the large composite thin-walled structure is the main structure form in the fields of aerospace, rail transportation, etc. Among them, the large composite thin-walled structure can be used as the main load-bearing component of an airplane, a car, a train, a ship, a high-speed rail, a subway, a drone, etc. The embodiments of the present application do not make specific limitations thereto.

[0085] In the CAE (Computer Aided Engineering) software, a stiffened wallboard finite element model of the large composite thin-walled structure is established, nonlinear analysis is performed under the compression load condition, and the buckling load of any two target stringer wallboards in the stiffened wallboard finite element model of the large composite thin-walled structure is extracted.

[0086] Based on the stiffened wallboard finite element model of the large composite thin-walled structure constructed in the CAE software, the maximum deformation position of the stiffened wallboard in the stiffened wallboard finite element model of the large composite thin-walled structure is determined, i.e., the position where the stiffened wallboard first buckles.

[0087] Holes with different preset diameters are respectively provided at the maximum deformation position and the center position of the stiffened wallboard. It should be noted that the different preset diameters can include 12mm, 24mm and 50mm.

[0088] Optionally, the maximum deformation position can be provided with a 12mm hole, a 24mm hole and a 50mm hole, and the center position of the stiffened wallboard can be provided with a 12mm hole, a 24mm hole and a 50mm hole.

[0089] The first buckling load of each first wallboard in the above six cases is calculated, each second buckling load greater than or equal to the target buckling load of any two target stringers in the stiffened wallboard finite element model of the large composite thin-walled structure is obtained from each first buckling load, and the first wallboard corresponding to the maximum buckling load is obtained from each second buckling load as the optimal hole opening wallboard.

[0090] There are various implementation manners for calculating the first buckling load of each first wallboard, and in one implementation manner:

[0091] The second buckling load is determined by the time calculation, and the specific formula is as follows: F = t * F0, F is the second buckling load, t is the time when the finite element is extracted, and F0 is the fixed load set in the compression and shear load case.

[0092] As shown in FIG. 3, it is a strain load curve of the non-hole stiffened wall panel in the compression condition, and the buckling load is the load corresponding to the sudden change of the two curves. FIG. 4 is a strain load curve of the non-hole stiffened wall panel in the shear condition. As shown in FIG. 5, it is a strain load curve of the stiffened wall panel with different hole diameters in the compression condition. As shown in FIG. 6, it is a strain load curve of the stiffened wall panel with different hole diameters in the shear condition.

[0093] Finally, based on the maximum deformation position of the first wall panel corresponding to the maximum buckling load and the hole mode of the middle position of the stiffened wall panel, the stiffened wall panel of the large composite thin-walled structure finite element model is holed, so that the use of materials can be reduced and the weight of the large composite thin-walled structure can be reduced on the basis of ensuring the stability of the large composite thin-walled structure.

[0094] In order to further increase the stability of the large composite thin-walled structure on the basis of holed stiffened wall panel, referring to FIG. 7, the following steps are included:

[0095] S301: determining a first diameter corresponding to a first hole of a maximum deformation position of a first wall panel corresponding to a maximum buckling load in each second buckling load.

[0096] S302: comparing the first diameter with a first preset diameter.

[0097] S303: comparing the first diameter with a second preset diameter when the first diameter is greater than the first preset diameter.

[0098] Wherein, the first preset diameter is smaller than the second preset diameter.

[0099] S304: strengthening the first hole when the first diameter is greater than the second preset diameter.

[0100] It should be noted that the first preset diameter can be set to 12mm, 13mm, 14mm. The second preset diameter can be set to 24mm, 25mm, 26mm, etc., and the embodiments of the present application do not make specific limitations.

[0101] In addition to the need to determine whether the first hole at the maximum deformation position needs to be reinforced to increase stability, the second hole at the center position of the stiffened wall panel also needs to be determined whether it needs to be reinforced. The specific way can be:

[0102] The second diameter corresponding to the second hole at the center position of the first wall panel corresponding to the maximum buckling load in each second buckling load is determined, and the second diameter is compared with the first preset diameter, and when the second diameter is greater than the first preset diameter, the second diameter is compared with the second preset diameter, wherein the first preset diameter is smaller than the second preset diameter, and when the second diameter is greater than the second preset diameter, the second hole is reinforced.

[0103] There are many ways to determine the target buckling load of the wall panel between any two target stringers in the finite element model of the large composite thin-walled structure in one implementation, as shown in FIG. 8, including the following steps:

[0104] S201-1: Determine the third buckling load of the wall panel between any two target stringers in the finite element model of the large composite thin-walled structure.

[0105] S201-2: Determine the fourth buckling load of the wall panel between any two target stringers under four-edge simply supported conditions.

[0106] S201-3: Determine the fifth buckling load of the wall panel between any two target stringers under four-edge clamped conditions.

[0107] S201-4: Calculate the average of the fourth buckling load and the fifth buckling load.

[0108] S201-5: Calculate the absolute value of the difference between the third buckling load and the average.

[0109] S201-6: Calculate the ratio of the absolute value to the third buckling load.

[0110] S201-7: Compare the ratio with a preset value.

[0111] S201-8: When the ratio is less than or equal to the preset value, the third buckling load is taken as the target buckling load of the wall panel between any two target stringers in the finite element model of the large composite thin-walled structure.

[0112] The third buckling load of the wall panel between any two target stringers in the finite element model of the large composite thin-walled structure can be calculated by the following method:

[0113] Determine the mechanical property parameters of the built large composite thin-walled structure's stiffened panel finite element model, determine the average strain of the panel between any two target stringers in the built large composite thin-walled structure's stiffened panel finite element model, determine the thickness of any one of the panels between any two target stringers, based on the mechanical property parameters, the average strain and the thickness, calculate the third buckling load of any two target stringers in the built large composite thin-walled structure's stiffened panel finite element model.

[0114] Optionally, in the CAE software, a finite element model of the stiffened panel of the large composite thin-walled structure is established, nonlinear analysis is carried out under compression load condition, the strain on any two target stringers is extracted, the stringer spacing diagram is shown in Figure 9, and the third buckling load is calculated by the following formula: x = E * ε * t

[0115] Wherein, N x is the third buckling load, E is the mechanical property parameter, ε is the average strain on the two target stringers, and t is the thickness.

[0116] The fourth buckling load of any two target stringers under four-edge simply supported condition is calculated by the following formula:

[0117] D 11 is the bending stiffness coefficient of any two target stringers 11 in the direction, D 12 is the bending stiffness coefficient of any two target stringers 12 in the direction, D 22 is the bending stiffness coefficient of any two target stringers 22 in the direction, and D 66 is the bending stiffness coefficient of any two target stringers 66 in the direction, and b is the outer spacing of the stringers of any target stringer.

[0118] The fifth buckling load of any two target stringers under four-edge fixed support condition is calculated by the following formula:

[0119] D 11 is the bending stiffness coefficient of any two target stringers 11 in the direction, D 12 is the bending stiffness coefficient of any two target stringers 12 in the direction, D 22 is the bending stiffness coefficient of any two target stringers 22 in the direction, and D 66 is the bending stiffness coefficient of any two target stringers 66 in the direction, and b is the outer spacing of the stringers of any target stringer.

[0120] Calculate the average of N1 and N2, calculate the absolute value of the difference between the average of N1 and N2 and the third buckling load, calculate the ratio of the absolute value to the third buckling load, compare the ratio with the preset value.

[0121] It should be noted that the preset value can be set to 0.1, 0.11, 0.12, 0.13, etc., and the embodiments of the present application do not make specific limitations.

[0122] When the ratio of the absolute value to the third buckling load is less than or equal to the preset value, the accuracy of the constructed large composite material thin-walled structure stiffened panel finite element model is within the error range, and the calculated third buckling load is taken as the target buckling load of the panel between any two target stringers in the constructed large composite material thin-walled structure stiffened panel finite element model.

[0123] Please refer to 10, the embodiments of the present application also provide a composite stiffened panel opening weight reduction device 110 applied to the electronic equipment 100 shown in FIG. 1, the composite stiffened panel opening weight reduction device 110 comprises:

[0124] The determination module 111 is configured to determine the target buckling load of the panel between any two target stringers in the constructed large composite material thin-walled structure stiffened panel finite element model; and determine the maximum deformation position of the stiffened panel in the stiffened panel finite element model, wherein the stiffened panel comprises the panel between the target stringers.

[0125] The opening module 112 is configured to open holes with different preset diameters at the maximum deformation position and the center position of the stiffened panel respectively, to obtain a plurality of first panels.

[0126] The determination module 111 is further configured to determine the first buckling load of each first panel.

[0127] The acquisition module 113 is configured to acquire each second buckling load greater than or equal to the target buckling load from each first buckling load; and acquire the first panel corresponding to the maximum buckling load from each second buckling load, so as to open holes based on the opening mode of the first panel.

[0128] The present application also provides an electronic equipment 100, which comprises a processor 130 and a memory 120. The memory 120 stores computer executable instructions, and the computer executable instructions are executed by the processor 130 to realize the composite stiffened panel opening weight reduction method.

[0129] The embodiments of the present application also provide a computer readable storage medium, which stores a computer program, and the computer program is executed by the processor 130 to realize the composite stiffened panel opening weight reduction method.

[0130] In the embodiments of the present disclosure, it should be understood that the disclosed apparatus and method can also be implemented in other manners. The embodiments described above are merely schematic. For example, the flowcharts and block diagrams in the accompanying drawings show the possible implementation architectures, functions and operation of the apparatus, method and computer program product according to the embodiments of the present disclosure. In this regard, each block in the flowcharts and block diagrams can represent a module, a program segment or a part of code, which includes one or more executable instructions configured to implement the specified logic function. It should also be noted that, in some alternative implementations, the functions noted in the blocks can occur in a different order from that noted in the accompanying drawings. For example, two consecutive blocks can actually be executed substantially in parallel, and sometimes they can be executed in reverse order, depending on the functions involved. It should also be noted that each block in the block diagrams and / or flowcharts, and the combination of blocks in the block diagrams and / or flowcharts, can be implemented by a dedicated hardware-based system that performs the specified functions or actions, or can be implemented by a combination of dedicated hardware and computer instructions.

[0131] In addition, the various functional modules in the embodiments of the present disclosure can be integrated together to form a separate part, or each module can exist independently, or two or more modules can be integrated to form a separate part. When the functions are realized in the form of software functional modules and sold or used as independent products, they can be stored in a computer readable storage medium. Based on this understanding, the technical solutions of the present disclosure can be embodied in the form of a software product, and the computer software product is stored in a storage medium, including a number of instructions to make a computer device (which can be a personal computer, a server, or a network device, etc.) execute all or part of the steps of the methods described in the embodiments of the present disclosure. The aforementioned storage medium includes: a U disk, a mobile hard disk, a read-only memory (ROM, Read-Only Memory), a random access memory (RAM, Random Access Memory), a magnetic disk or an optical disk, and various media that can store program codes.

[0132] It is to be noted that the relationship terms such as first and second, and the like, are used only to differentiate one entity or action from another, and do not necessarily require or imply that there is any such actual relationship or order between these entities or actions. Moreover, the terms "comprising", "including", or any other variant thereof are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but can also include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the statement "comprising a" does not exclude the existence of additional identical elements in the process, method, article, or apparatus that includes the element.

[0133] The above merely provides various embodiments of the present application, and the protection scope of the present application is not limited thereto. Any person skilled in the art can easily think of changes or replacements within the technical scope disclosed by the present application, and all such changes or replacements should be covered within the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims. Industrial applicability

[0134] Embodiments of the present disclosure provide a composite stiffened panel opening weight reduction method and device, electronic equipment and storage medium, which can reduce the use of materials, thereby reducing the weight of large composite thin-walled structures.

Claims

1. A method for opening and lightening a composite panel, characterized in that, The method comprises: determining the target buckling load of any two target inter-stringer panels in the built large composite thin-walled structure's stiffened panel finite element model; determining the maximum deformation position of the stiffened panel in the stiffened panel finite element model, wherein the stiffened panel comprises the target inter-stringer panel; drilling holes with different preset diameters at the maximum deformation position and the center position of the stiffened panel respectively to obtain a plurality of first panels; determining the first buckling load of each first panel; obtaining each second buckling load greater than or equal to the target buckling load from each first buckling load; obtaining the first panel corresponding to the maximum buckling load from each second buckling load, and drilling holes based on the hole drilling mode of the first panel.

2. The method of claim 1, wherein, The method further comprises: determining the first diameter corresponding to the first hole of the maximum deformation position of the first panel corresponding to the maximum buckling load in each second buckling load; comparing the first diameter with the first preset diameter; when the first diameter is greater than the first preset diameter, comparing the first diameter with the second preset diameter, wherein the first preset diameter is smaller than the second preset diameter; when the first diameter is greater than the second preset diameter, strengthening the first hole.

3. The method of claim 1, wherein, The method further comprises: determining the second diameter corresponding to the second hole of the center position of the first panel corresponding to the maximum buckling load in each second buckling load; comparing the second diameter with the first preset diameter; when the second diameter is greater than the first preset diameter, comparing the second diameter with the second preset diameter, wherein the first preset diameter is smaller than the second preset diameter; when the second diameter is greater than the second preset diameter, strengthening the second hole.

4. The method according to any one of claims 1 to 3, characterized in that, The step of determining the target buckling load of any two target inter-stringer panels in the built large composite thin-walled structure's stiffened panel finite element model comprises: determining the third buckling load of any two target inter-stringer panels in the built large composite thin-walled structure's stiffened panel finite element model; determining the fourth buckling load of any two target inter-stringer panels under four-edge simply supported conditions; determining the fifth buckling load of any two target inter-stringer panels under four-edge clamped conditions; calculating the average value of the fourth buckling load and the fifth buckling load; calculating the absolute value of the difference between the third buckling load and the average value; calculating the ratio of the absolute value to the third buckling load; comparing the ratio with a preset value; when the ratio is less than or equal to the preset value, the third buckling load is taken as the target buckling load of any two target inter-stringer panels in the built large composite thin-walled structure's stiffened panel finite element model.

5. The method of claim 4, wherein, The step of determining the third buckling load of any two target inter-stringer panels in the built large composite thin-walled structure's stiffened panel finite element model comprises: determining the mechanical property parameters of the built large composite thin-walled structure's stiffened panel finite element model; determining the average strain of any two target inter-stringer panels in the built large composite thin-walled structure's stiffened panel finite element model; determining a thickness of any target inter-stringer panel among any two target inter-stringer panels; calculating a third buckling load of any two target inter-stringer panels in the finite element model of the stiffened panel of the large composite thin-walled structure based on the mechanical property parameters, the average strain, and the thickness.

6. The method of claim 5, wherein, The third buckling load satisfies the following formula: N x = E * ε * t; where N x is the third buckling load, E is the mechanical property parameter, ε is the average strain on the two target stringers, and t is the thickness.

7. The method of claim 4, wherein, The fourth bending load satisfies the following formula: The fifth bending load satisfies the following formula: where D 11 is the bending stiffness coefficient of any two of the target inter-stringer panel 11 in the direction, D 12 is the bending stiffness coefficient of any two of the target inter-stringer panel 12 in the direction, D 22 is the bending stiffness coefficient of any two of the target inter-stringer panel 22 in the direction, D 66 is the bending stiffness coefficient of any two of the target inter-stringer panel 66 in the direction, and b is the outer stringer spacing of any of the target inter-stringer panels.

8. The method according to any one of claims 1 to 7, characterized in that, The determination of the target buckling load of any two target inter-stringer panels in the finite element model of the stiffened panel of the large composite thin-walled structure includes: In the computer-aided engineering software, a finite element model of the stiffened panel of the large composite thin-walled structure is established, nonlinear analysis is performed under a compression load condition, and the buckling load of any two target inter-stringer panels in the finite element model of the stiffened panel of the large composite thin-walled structure is extracted.

9. The method of claim 8, wherein, The determination of the maximum deformation position of the stiffened panel in the finite element model includes: Based on the finite element model of the stiffened panel of the large composite thin-walled structure established in the computer-aided engineering software, the maximum deformation position of the stiffened panel in the finite element model of the stiffened panel of the large composite thin-walled structure is determined.

10. The method according to any one of claims 1 to 7, characterized in that, The maximum deformation position is provided with a 12mm hole, a 24mm hole, and a 50mm hole, and the center position of the stiffened panel is provided with a 12mm hole, a 24mm hole, and a 50mm hole.

11. The method according to any one of claims 1 to 7, characterized in that, The determination of the first buckling load of each first panel includes: The CAE software is used to perform finite element modeling on the stiffened panel after the holes are opened; Under the same compression and shear load condition as the finite element model of the stiffened panel of the large composite thin-walled structure established without opening holes, nonlinear calculation is performed on the finite element modeling of the stiffened panel after the holes are opened, strain and time data in the finite element results are extracted, and a load-strain curve graph is formed; The second buckling load is determined through the load-strain graph.

12. The method of claim 11, wherein, The second load is calculated by time, and the specific formula is as follows: F=t*F0, F is the second buckling load, t is the finite element extraction time, and F0 is the fixed load set in the compression and shear load condition. The device includes:

13. A composite panel wall framing opening weight reduction device, comprising: A determination module configured to determine a target buckling load of any two target inter-stringer panels in a finite element model of a stiffened panel of a large composite thin-walled structure established, and determine a maximum deformation position of a stiffened panel in the finite element model of the stiffened panel, wherein the stiffened panel includes a target inter-stringer panel; A hole opening module configured to open holes of different preset diameters at the maximum deformation position and the center position of the stiffened panel respectively to obtain a plurality of first panels; The determination module is further configured to determine a first buckling load of each first panel; An acquisition module configured to acquire, from each first buckling load, a second buckling load greater than or equal to the target buckling load, and acquire a first panel corresponding to a maximum buckling load from each second buckling load to open holes based on the opening mode of the first panel. ​ 14. An electronic device, comprising: A computer program product comprising a memory storing a computer program and a processor, wherein the processor implements the steps of the method according to any one of claims 1 to 12 when executing the computer program.

15. A readable storage medium, having stored thereon a computer program, characterized in that, The computer program is executed by a processor to implement the steps of the method according to any one of claims 1 to 12.

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