Design method, device, equipment and storage medium for composite pressure-bearing equipment

Abstract

The embodiments of the present invention disclose a design method, device, equipment and storage medium for composite pressure-bearing equipment, and relate to the field of composite material technology. The method includes: in response to the design instructions of the target pressure-bearing equipment, obtaining the inner liner geometric data of the target pressure-bearing equipment; modeling the composite plies of the target pressure-bearing equipment according to the inner liner geometric data to obtain the composite plies modeling results of the target pressure-bearing equipment; determining the strain and stress of each composite plies based on the composite plies modeling results, and determining whether the composite plies corresponding to the composite plies modeling results are safe according to the strains and stresses. The scheme of the embodiments of the present invention shortens the design time of composite pressure-bearing equipment and improves the design accuracy of composite pressure-bearing equipment.

Description

Technical Field

[0001] The present invention relates to the technical field of composite materials, and in particular to a design method, device, equipment and storage medium for composite pressure-bearing equipment. Background Art

[0002] Composite pressure equipment refers to containers or pipes made of two or more different materials, which are used to withstand internal pressure or other forms of pressure. These materials usually include fiber reinforced plastics (such as carbon fiber, glass fiber), metals, ceramics, etc. The advantage of composite materials is that they can combine the advantages of each component material, such as high strength, light weight, corrosion resistance and good processing performance.

[0003] At present, the design of composite pressure-bearing equipment needs to be completed through two different commercial software. This results in large amount of calculation, long time consumption, low precision and easy incompatibility of the two calculation results.

[0004] How to shorten the design time of composite pressure-bearing equipment and improve the design accuracy of composite pressure-bearing equipment are key research issues in the industry. Summary of the invention

[0005] The present invention provides a design method, device, equipment and storage medium for composite pressure-bearing equipment, which can shorten the design time of composite pressure-bearing equipment and improve the design accuracy of composite pressure-bearing equipment.

[0006] According to one aspect of the present invention, a design method for composite pressure-bearing equipment is provided, the method comprising:

[0007] In response to a design instruction of a target pressure-bearing device, obtaining inner liner geometric data of the target pressure-bearing device;

[0008] Modeling the composite material layup of the target pressure-bearing equipment according to the inner liner geometric data to obtain a composite material layup modeling result of the target pressure-bearing equipment;

[0009] The strain and stress of each composite material ply are determined based on the composite material ply modeling result, and whether the composite material ply corresponding to the composite material ply modeling result is safe is determined according to each strain and stress.

[0010] According to another aspect of the present invention, there is provided a design device for composite pressure-bearing equipment, the device comprising:

[0011] An inner liner geometric data acquisition module, used to obtain the inner liner geometric data of the target pressure-bearing equipment in response to the design instruction of the target pressure-bearing equipment;

[0012] A composite material layup modeling result determination module is used to model the composite material layup of the target pressure-bearing equipment according to the inner liner geometric data to obtain the composite material layup modeling result of the target pressure-bearing equipment;

[0013] A calculation module is used to determine the strain and stress of each composite material ply based on the composite material ply modeling result, and determine whether the composite material ply corresponding to the composite material ply modeling result is safe according to each strain and stress.

[0014] According to another aspect of the present invention, an electronic device is provided, the electronic device comprising:

[0015] at least one processor; and

[0016] a memory communicatively connected to the at least one processor; wherein,

[0017] 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 so that the at least one processor can execute the method for designing composite pressure-bearing equipment described in any embodiment of the present invention.

[0018] According to another aspect of the present invention, a computer-readable storage medium is provided, wherein the computer-readable storage medium stores computer instructions for enabling a processor to implement the method for designing composite pressure-bearing equipment described in any embodiment of the present invention when the computer instructions are executed.

[0019] According to another aspect of the present invention, a computer program product is provided, comprising a computer program, wherein when the computer program is executed by a processor, the method for designing a composite pressure-bearing device according to any embodiment of the present invention is implemented.

[0020] The technical solution of the embodiment of the present invention obtains the inner liner geometric data of the target pressure-bearing equipment in response to the design instructions of the target pressure-bearing equipment; models the composite material layup of the target pressure-bearing equipment according to the inner liner geometric data to obtain the composite material layup modeling result of the target pressure-bearing equipment; determines the strain and stress of each of the composite material layups based on the composite material layup modeling result, and determines whether the composite material layup corresponding to the composite material layup modeling result is safe according to each of the strains and stresses, thereby shortening the design time of the composite material pressure-bearing equipment and improving the design accuracy of the composite material pressure-bearing equipment.

[0021] It should be understood that the contents described in this section are not intended to identify the key or important features of the embodiments of the present invention, nor are they intended to limit the scope of the present invention. Other features of the present invention will become easily understood through the following description. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0023] Figure 1 is a flow chart of a design method of a composite pressure-bearing device provided according to Embodiment 1 of the present invention;

[0024] Figure 2 This is a schematic diagram of the inner liner structure of a composite material pressure-bearing device provided according to Embodiment 1 of the present invention;

[0025] Figure 3 is a structural schematic diagram of a design device for composite pressure-bearing equipment provided according to Embodiment 2 of the present invention;

[0026] Figure 4 It is a structural schematic diagram of an electronic device for implementing the design method of composite pressure-bearing equipment according to an embodiment of the present invention. DETAILED DESCRIPTION

[0027] In order to enable those skilled in the art to better understand the scheme of the present invention, the technical scheme in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work should fall within the scope of protection of the present invention.

[0028] It should be noted that the terms "first", "second", etc. in the specification and claims of the present invention and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the data used in this way can be interchanged where appropriate, so that the embodiments of the present invention described herein can be implemented in an order other than those illustrated or described herein. In addition, the terms "including" and "having" and any variations thereof are intended to cover non-exclusive inclusions, for example, a process, method, system, product or device that includes a series of steps or units is not necessarily limited to those steps or units that are clearly listed, but may include other steps or units that are not clearly listed or inherent to these processes, methods, products or devices.

[0029] Embodiment 1

[0030] Figure 1This is a flow chart of a design method for composite pressure equipment provided according to the first embodiment of the present invention. This embodiment is applicable to the case of modeling and verifying the composite material layer of the composite pressure equipment. The method can be executed by a design device for composite pressure equipment. The design device for composite pressure equipment can be implemented in the form of hardware and / or software. The design device for composite pressure equipment can be configured in electronic devices such as computers, servers or tablet computers. Figure 1 As shown, the method includes:

[0031] Step 110: In response to the design instruction of the target pressure-bearing equipment, obtain the inner liner geometric data of the target pressure-bearing equipment.

[0032] The target pressure-bearing equipment may be any composite pressure-bearing equipment, such as a Type IV hydrogen storage tank or an oxygen tank, etc., which is not limited in this embodiment.

[0033] In an optional implementation of the present embodiment, after receiving the design instructions for the target pressure-bearing equipment, the inner liner geometric data of the target pressure-bearing equipment can be further obtained according to the design instructions of the target pressure-bearing equipment; the inner liner geometric data of the target pressure-bearing equipment may include: pole hole radius, inner liner radius, and target bursting pressure, etc.

[0034] For example, Figure 2 is a schematic diagram of the inner liner structure of a composite material pressure-bearing device provided according to the first embodiment of the present invention, with reference to Figure 2 , r 0 is the radius of the polar hole, r is the radius of the gallbladder, and α is the winding angle of the spiral layer; the specific value of the target blasting pressure is Figure 2 Not shown.

[0035] Optionally, in this embodiment, in response to the design instructions of the target pressure-bearing equipment, obtaining the inner liner geometric data of the target pressure-bearing equipment may include: determining the coding rules of the design instructions of the target pressure-bearing equipment; parsing the design instructions of the target pressure-bearing equipment according to the coding rules to obtain the inner liner geometric data of the target pressure-bearing equipment.

[0036] In an optional implementation of the present embodiment, after obtaining the design instructions of the target pressure-bearing equipment, the encoding rules of the design instructions of the target pressure-bearing equipment can be further determined; further, the design instructions of the target pressure-bearing equipment can be parsed according to the encoding rules to obtain the inner liner geometric data of the target pressure-bearing equipment.

[0037] Step 120: Model the composite material layup of the target pressure-bearing equipment according to the inner liner geometric data to obtain a composite material layup modeling result of the target pressure-bearing equipment.

[0038] In this embodiment, the modeling results include: the order of each layer in the composite material layup, the total thickness of the circumferential layer and the helical layer, the thickness change of the head part of each helical layer, and the winding angle of each helical layer.

[0039] Optionally, in this embodiment, after obtaining the inner liner geometric data of the target pressure-bearing equipment, the composite material layup of the target pressure-bearing equipment can be further modeled according to the inner liner geometric data of the target pressure-bearing equipment, so as to obtain the composite material layup modeling result of the target pressure-bearing equipment; illustratively, the order of each layup in the composite material layup of the target pressure-bearing equipment, the total thickness of the annular layer and the spiral layer, the thickness change of the head part of each spiral layer, and the winding angle of each spiral layer can be obtained.

[0040] In an optional implementation of the present embodiment, the composite material layup of the target pressure-bearing equipment is modeled according to the inner liner geometric data to obtain the composite material layup modeling result of the target pressure-bearing equipment, which may include: determining the order of each layup in the composite material layup, the thickness of each target layer, and the winding angle of each spiral layer based on the pole hole radius and the inner liner radius in the inner liner geometric data.

[0041] Optionally, in this embodiment, determining the order of each ply in the composite material ply, the thickness of each ply, and the winding angle of each helical layer based on the polar hole radius and the liner radius in the liner geometry data may include: determining the thickness of each ply based on any of the following formulas: the ply includes a helical layer and a hoop layer;

[0042] t(r)=a 0 +a 1 r+a 2 r 2 +a 3 r 3 , r 0 ≤r≤r 2b ;

[0043]

[0044] Among them, a 0-3 is the fitting parameter, r 0 is the radius of the polar hole, r is the radius of the inner tank, and r 2b is the position of two bandwidths from the polar hole outward; one bandwidth is the width of a carbon fiber; m R is the number of yarns, n R is the number of layers; b is the yarn width; the winding angle of each spiral layer is determined based on the following formula:

[0045]

[0046] Wherein, r(y) is the local radius of the bottle body on the y-axis, λ represents the friction coefficient, α is the winding angle of the helical layer, r... and r... are the second-order and first-order derivatives of the local radius respectively; based on the grid theory, the total thickness of the spiral layer and the total thickness of the circumferential layer in the composite material ply are determined respectively; the number of plies in the composite material ply is determined based on the total thickness of each ply, the total thickness of the spiral layer and the total thickness of the circumferential layer, and the order of each ply is determined based on the number of plies and the winding angle of each spiral layer.

[0047] It can be understood that the spiral layer is formed by winding the ribbon fibers around the outer wall of the inner liner in a spiral manner; this winding method enables the fibers to resist axial and circumferential stresses to a certain extent; according to the inclination angle of the fibers relative to the length direction of the high-pressure container, the spiral layer can be further divided into a low spiral layer and a high spiral layer. The ribbon fibers in the low spiral layer have a smaller inclination angle, which can better cover the contraction part of the inner liner, thereby ensuring the compressive strength of the contraction part. The ribbon fibers in the high spiral layer have a larger inclination angle, which helps to improve the compressive resistance of the overall structure. The circumferential layer is formed by winding the ribbon fibers around the outer wall of the inner liner in a circumferential manner; this winding method mainly provides circumferential stress resistance, which is particularly effective in improving the compressive strength of the high-pressure container.

[0048] In an optional implementation of this embodiment, after obtaining the inner liner geometric data of the target pressure-bearing equipment, the thickness of each layer in the composite material layer can be further determined based on the polar hole radius and the inner liner radius; in this embodiment, the polar hole radius r 0 To two bandwidths r 2b The thickness of each ply in the composite material layup can be determined by the following formula:

[0049] t(r)=a 0 +a 1 r+a 2 r 2 +a 3 r 3 r 0 ≤r≤r 2b ;

[0050] Furthermore, at two bandwidths r 2b In addition, the thickness of each ply in the composite layup can be determined by the following formula:

[0051]

[0052] Where R is the diameter of the bottle.

[0053] Furthermore, the winding angle of each helical layer can be determined based on the following formula:

[0054]

[0055] Where r(y) is the local radius of the bottle on the y-axis (for example, the y-axis direction can refer to Figure 2 ), λ represents the friction coefficient, α is the winding angle of the helical layer, r″ and r′ are the second-order and first-order derivatives of the local radius, respectively. In an example of this embodiment, the winding angle of each helical layer can be 15°, 30°, 40°, 48° and 54°.

[0056] Furthermore, the total thickness of the helical layer and the total thickness of the circumferential layer in the composite material layer can be determined based on the grid theory; illustratively, the total thickness of the helical layer and the total thickness of the circumferential layer can be determined by the following formulas: Among them, t α is the total thickness of the helical layer; t θ is the total thickness of the annular layer; p is the target bursting pressure; R is the radius of the bottle body; α is the winding angle.

[0057] In a specific example of this embodiment, the composite material layup modeling results of the target pressure-bearing equipment calculated through the above steps can be: 4× circumferential layers, 8×15° spiral layers, 4×30° spiral layers, 4×40° spiral layers, 4×48° spiral layers, 4×54° spiral layers and 8× circumferential layers; wherein the layers are arranged from low to high winding angles, the inner layer is the smallest geodesic winding angle, which helps to fully cover the gas cylinder, and the circumferential layers are distributed on the inside and outside.

[0058] Step 130: Determine the strain and stress of each composite material ply based on the composite material ply modeling result, and determine whether the composite material ply corresponding to the composite material ply modeling result is safe according to each strain and stress.

[0059] In an optional implementation of the present embodiment, after obtaining the modeling results of the composite layup of the target pressure-bearing equipment, the strain and stress of each layup in the composite layup can be further determined based on the composite layup modeling results, and whether the composite layup corresponding to the composite layup modeling results of the target pressure-bearing equipment is safe can be determined based on the calculated strain and stress.

[0060] Optionally, in the present embodiment, determining the strain and stress of each of the composite material plies based on the composite material ply modeling results may include: splitting the material ply modeling results into head modeling results and body modeling results; determining the strain and stress of the head modeling results based on an analytical solution of a differential equation; and performing circumferential and meridian strain calculations on the body modeling results to obtain circumferential strain and meridian strain.

[0061] In an optional implementation of this embodiment, determining the strain and stress of the head modeling result based on the analytical solution of the differential equation may include: determining the meridian direction, meridian curvature and circumferential curvature that match the head modeling result; determining the strain and stress of the head modeling result based on the meridian direction, meridian curvature and circumferential curvature.

[0062] Correspondingly, determining the strain and stress of the head modeling result according to the meridian direction, meridian curvature and circumferential curvature may include: substituting the meridian direction, meridian curvature and circumferential curvature into the target formula to obtain the strain and stress of the head modeling result; the target formula is determined by the following formula:

[0063]

[0064]

[0065] Among them, A 11 , A 12 , A 21 , A 22 , B 11 , B 12 , B 21 , B 22 , C 11 , C 12 , C 21 and C 22 is the item of the stiffness matrix corresponding to the head modeling result; and are the meridian and annular stresses respectively under ideal conditions; ∈ s and∈ θ Represents the strain in the meridian and annular directions; s is the coordinate in the meridian direction; r1 is the meridian curvature; r2 is the curvature in the circumferential direction; r3 is the auxiliary variable for mechanical calculation.

[0066] In this embodiment, the strains in the circumferential and meridian directions of the head portion can be calculated by the above formula, thereby calculating the stress.

[0067] In another optional implementation of this embodiment, the circumferential strain and the meridian strain of the bottle body modeling result are calculated respectively to obtain the circumferential strain and the meridian strain, which may include: determining the circumferential strain of the bottle body modeling result based on the following formula:

[0068]

[0069] in, A 11 , A 12, A 21 , A 22 , B 11 , B 12 , B 21 , B 22 , C 11 , C 12 , C 21 and C 22 is the item of the stiffness matrix corresponding to the bottle modeling result; R is the bottle diameter, p is the design bursting pressure, s is the axis in the meridian direction, ∈ θ is the hoop strain;

[0070] The meridian strain of the bottle modeling result is determined based on the following formula:

[0071]

[0072] Among them, ∈ s is the strain in the meridian direction; A 11 , A 12 , B 11 and B 12 Entries of the stiffness matrix corresponding to the bottle modeling results.

[0073] In an optional implementation of this embodiment, after the strain and stress of each composite material ply are obtained, it can be further determined whether the composite material ply corresponding to the composite material ply modeling result is safe according to each strain and stress.

[0074] Optionally, in this embodiment, it can be determined whether the strain and stress of each composite ply exceeds the maximum stress or maximum strain of the material. If not, the composite ply corresponding to the composite ply modeling result is determined to be safe; otherwise, it is unsafe.

[0075] The technical solution of this embodiment obtains the inner liner geometric data of the target pressure-bearing equipment in response to the design instructions of the target pressure-bearing equipment; models the composite material layup of the target pressure-bearing equipment according to the inner liner geometric data to obtain the composite material layup modeling result of the target pressure-bearing equipment; the modeling includes: the order of each layup in the composite material layup, the thickness of each layup, and the winding angle of each spiral layer; based on the composite material layup modeling result, the strain and stress of each composite material layup are determined, and according to each strain and stress, it is determined whether the composite material layup corresponding to the composite material layup modeling result is safe, thereby shortening the design time of the composite material pressure-bearing equipment and improving the design accuracy of the composite material pressure-bearing equipment.

[0076] Embodiment 2

[0077] Figure 3Schematic diagram of the structure of a design device for composite pressure-bearing equipment according to the second embodiment of the present invention. Figure 3 As shown, the device includes: an inner liner geometry data acquisition module 310, a composite material layup modeling result determination module 320 and a calculation module 330.

[0078] The inner liner geometric data acquisition module 310 is used to obtain the inner liner geometric data of the target pressure-bearing equipment in response to the design instruction of the target pressure-bearing equipment;

[0079] A composite material layup modeling result determination module 320 is used to model the composite material layup of the target pressure-bearing equipment according to the inner liner geometric data, and obtain the composite material layup modeling result of the target pressure-bearing equipment; the modeling result includes: the order of each layup in the composite material layup, the total thickness of the circumferential layer and the spiral layer, the thickness change of the head part of each spiral layer, and the winding angle of each spiral layer;

[0080] The calculation module 330 is used to determine the strain and stress of each composite material ply based on the composite material ply modeling result, and determine whether the composite material ply corresponding to the composite material ply modeling result is safe according to each strain and stress.

[0081] The solution of this embodiment is to obtain the inner liner geometric data of the target pressure-bearing equipment in response to the design instructions of the target pressure-bearing equipment through the inner liner geometric data acquisition module; to model the composite layup of the target pressure-bearing equipment according to the inner liner geometric data through the composite layup modeling result determination module to obtain the composite layup modeling result of the target pressure-bearing equipment; the modeling includes: the order of each layup in the composite layup, the thickness of each layup, and the winding angle of each spiral layer; to determine the strain and stress of each composite layup based on the composite layup modeling result through the calculation module, and to determine whether the composite layup corresponding to the composite layup modeling result is safe according to each strain and stress, thereby shortening the design time of the composite pressure-bearing equipment and improving the design accuracy of the composite pressure-bearing equipment.

[0082] In an optional implementation of this embodiment, the liner geometry data acquisition module 310 is specifically used to determine the coding rules of the design instructions of the target pressure-bearing equipment;

[0083] Parsing the design instructions of the target pressure-bearing equipment according to the coding rules to obtain the inner tank geometry data of the target pressure-bearing equipment;

[0084] The inner liner geometric data includes: the pole hole radius, the inner liner radius and the target bursting pressure.

[0085] In an optional implementation of the present embodiment, the composite material ply modeling result determination module 320 is specifically used to determine the order of each ply in the composite material ply, the thickness of each target layer, and the winding angle of each spiral layer based on the polar hole radius and the inner liner radius in the inner liner geometry data.

[0086] In an optional implementation of this embodiment, the composite material ply modeling result determination module 320 is further specifically configured to determine the thickness of each ply based on any of the following formulas: t(r)=a 0 +a 1 r+a 2 r 2 +a 3 r 3 , for r 0 ≤r≤r 2b ;

[0087]

[0088] Among them, a 0-3 is the fitting parameter, r 0 is the radius of the polar hole, r is the radius of the inner tank, and r 2b is the position of two bandwidths from the polar hole outward; one bandwidth is the width of a carbon fiber; m R is the number of yarns, n R is the number of layers; b is the yarn width;

[0089] The winding angle of each helical layer is determined based on the following formula:

[0090]

[0091] Where r(y) is the local radius of the bottle on the y-axis, λ represents the friction coefficient, α is the winding angle of the helical layer, r″ and r′ are the second and first derivatives of the local radius, respectively;

[0092] Based on the grid theory, the total thickness of the spiral layer and the total thickness of the hoop layer in the composite material layup are determined respectively;

[0093] The number of plies in the composite material layup is determined based on the total thickness of each of the plies, the total thickness of the spiral layers and the total thickness of the hoop layers, and the order of each ply is determined based on the number of plies and the winding angle of each spiral layer.

[0094] In an optional implementation of this embodiment, the calculation module 330 is specifically used to split the material layer modeling result into a head modeling result and a bottle body modeling result;

[0095] Determine the strain and stress of the head modeling result based on analytical solution of differential equations;

[0096] The strains in the circumferential direction and the meridian direction are calculated for the modeling results of the bottle body to obtain the circumferential strain and the meridian direction strain.

[0097] In an optional implementation of this embodiment, the calculation module 330 includes: a head modeling result calculation submodule, which is used to determine the meridian direction, meridian curvature and circumferential direction curvature matching the head modeling result;

[0098] Determine the strain and stress of the head modeling result according to the meridian direction, meridian curvature and circumferential curvature;

[0099] Correspondingly, the head modeling result calculation submodule is specifically used to substitute the meridian direction, meridian curvature and circumferential curvature into the target formula to obtain the strain and stress of the head modeling result; the target formula is determined by the following formula:

[0100]

[0101] Among them, A 11 , A 12 , A 21 , A 22 , B 11 , B 12 , B 21 , B 22 , C 11 , C 12 , C 21 and C 22 is the item of the stiffness matrix corresponding to the head modeling result; and are the meridian and annular stresses respectively under ideal conditions; ∈ s and∈ θ Represents the strain in the meridian and annular directions; s is the coordinate in the meridian direction; r1 is the meridian curvature; r2 is the curvature in the circumferential direction; r3 is the auxiliary variable for mechanical calculation.

[0102] In an optional implementation of this embodiment, the calculation module 330 further includes: a bottle body modeling result calculation submodule, which is used to determine the hoop strain of the bottle body modeling result based on the following formula:

[0103]

[0104] in, A 11 , A 12 , A 21 , A 22 , B 11 , B 12 , B21 , B 22 , C 11 , C 12 , C 21 and C 22 is the item of the stiffness matrix corresponding to the bottle modeling result; R is the radius of the bottle, p is the design bursting pressure, s is the axis in the meridian direction, ∈ θ is the hoop strain;

[0105] The meridian strain of the bottle modeling result is determined based on the following formula:

[0106]

[0107] Among them, ∈ s is the strain in the meridian direction; A 11 , A 12 , B 11 and B 12 Entries of the stiffness matrix corresponding to the bottle modeling results.

[0108] The design device for composite pressure-bearing equipment provided in the embodiment of the present invention can execute the design method for composite pressure-bearing equipment provided in any embodiment of the present invention, and has the corresponding functional modules and beneficial effects of the execution method.

[0109] In the technical solution of the embodiment of the present invention, the collection, storage, use, processing, transmission, provision and disclosure of user personal information (such as facial information, voice information, etc.) are in compliance with the provisions of relevant laws and regulations and do not violate public order and good morals.

[0110] Embodiment 3

[0111] Figure 4 A schematic diagram of the structure of an electronic device 10 that can be used to implement an embodiment of the present invention is shown. The electronic device is intended to represent various forms of digital computers, such as laptop computers, desktop computers, workstations, personal digital assistants, servers, blade servers, mainframe computers, and other suitable computers. The electronic device can also represent various forms of mobile devices, such as personal digital processing, cellular phones, smart phones, wearable devices (such as helmets, glasses, watches, etc.) and other similar computing devices. The components shown herein, their connections and relationships, and their functions are merely examples and are not intended to limit the implementation of the present invention described and / or required herein.

[0112] like Figure 4As shown, the electronic device 10 includes at least one processor 11, and a memory connected to the at least one processor 11, such as a read-only memory (ROM) 12, a random access memory (RAM) 13, etc., wherein the memory stores a computer program that can be executed by at least one processor, and the processor 11 can perform various appropriate actions and processes according to the computer program stored in the read-only memory (ROM) 12 or the computer program loaded from the storage unit 18 to the random access memory (RAM) 13. 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.

[0113] A number of 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 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.

[0114] The processor 11 may be a variety of general and / or special 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 dedicated 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 executes the various methods and processes described above, such as a design method for a composite pressure-bearing device, the method comprising: in response to a design instruction of a target pressure-bearing device, obtaining the inner liner geometric data of the target pressure-bearing device; modeling the composite material layup of the target pressure-bearing device according to the inner liner geometric data, and obtaining a composite material layup modeling result of the target pressure-bearing device; the modeling result includes: the order of each layup in the composite material layup, the total thickness of the circumferential layer and the spiral layer, the thickness change of the head portion of each spiral layer, and the winding angle of each spiral layer; based on the composite material layup modeling result, the strain and stress of each composite material layup are determined, and according to each of the strains and stresses, whether the composite material layup corresponding to the composite material layup modeling result is safe.

[0115] In some embodiments, the design method of composite pressure-bearing equipment may be implemented as a computer program, which is tangibly contained in a computer-readable storage medium, such as a storage unit 18. In some embodiments, part or all of the computer program may be loaded and / or installed on the electronic device 10 via the ROM 12 and / or the communication unit 19. When the computer program is loaded into the RAM 13 and executed by the processor 11, one or more steps of the design method of composite pressure-bearing equipment described above may be performed. Alternatively, in other embodiments, the processor 11 may be configured to execute the design method of composite pressure-bearing equipment by any other appropriate means (e.g., by means of firmware).

[0116] Various implementations of the systems and techniques described above herein can be implemented in digital electronic circuit systems, integrated circuit systems, field programmable gate arrays (FPGAs), application specific integrated circuits (ASICs), application specific standard products (ASSPs), systems on chips (SOCs), load programmable logic devices (CPLDs), computer hardware, firmware, software, and / or combinations thereof. These various implementations can include: being implemented in one or more computer programs that can be executed and / or interpreted on a programmable system including at least one programmable processor, which can be a special purpose or general purpose programmable processor that can receive data and instructions from a storage system, at least one input device, and at least one output device, and transmit data and instructions to the storage system, the at least one input device, and the at least one output device.

[0117] Computer programs for implementing the methods of the present invention may be written in any combination of one or more programming languages. These computer programs may be provided to a processor of a general-purpose computer, a special-purpose computer, or other programmable data processing device, so that when the computer program is executed by the processor, the functions / operations specified in the flow chart and / or block diagram are implemented. The computer program may be executed entirely on the machine, partially on the machine, partially on the machine and partially on a remote machine as a stand-alone software package, or entirely on a remote machine or server.

[0118] In the context of the present invention, a computer-readable storage medium may be a tangible medium that may contain or store a computer program for use by or in combination with an instruction execution system, device or equipment. A computer-readable storage medium may include, but is not limited to, electronic, magnetic, optical, electromagnetic, infrared, or semiconductor systems, devices or equipment, or any suitable combination of the foregoing. Alternatively, a computer-readable storage medium may be a machine-readable signal medium. A more specific example of a machine-readable storage medium may include an electrical connection based on one or more lines, a portable computer disk, 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 disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the foregoing.

[0119] To provide interaction with a user, the systems and techniques described herein may 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 trackball) through which the user can provide input to the electronic device. Other types of devices may also be used to provide interaction with the user; for example, the feedback provided to the user may be any form of sensory feedback (e.g., visual feedback, auditory feedback, or tactile feedback); and input from the user may be received in any form (including acoustic input, voice input, or tactile input).

[0120] The systems and techniques described herein may be implemented in a computing system that includes backend components (e.g., as a data server), or a computing system that includes middleware components (e.g., an application server), or a computing system that includes frontend components (e.g., a user computer with a graphical user interface or a web browser through which a user can interact with implementations of the systems and techniques described herein), or a computing system that includes any combination of such backend components, middleware components, or frontend components. The components of the system may 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.

[0121] A computing system may include a client and a server. The client and the server are generally remote from each other and usually interact through a communication network. The client and server relationship is generated by computer programs running on the corresponding computers and having a client-server relationship with each other. The server may 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 difficult management and weak business scalability in traditional physical hosts and VPS services.

[0122] It should be understood that the various forms of processes shown above can be used to reorder, add or delete steps. For example, the steps described in the present invention can be executed in parallel, sequentially or in different orders, as long as the desired results of the technical solution of the present invention can be achieved, and this document does not limit this.

[0123] The above specific implementations do not constitute a limitation on the protection scope of the present invention. It should be understood by those skilled in the art that various modifications, combinations, sub-combinations and substitutions can be made according to design requirements and other factors. Any modification, equivalent substitution and improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A design method for composite pressure-bearing equipment, characterized in that: include: In response to a design instruction of a target pressure-bearing device, obtaining inner liner geometric data of the target pressure-bearing device; Modeling the composite material layup of the target pressure-bearing equipment according to the inner liner geometric data to obtain a composite material layup modeling result of the target pressure-bearing equipment; Determining the strain and stress of each composite material ply based on the composite material ply modeling result, and determining whether the composite material ply corresponding to the composite material ply modeling result is safe according to each strain and stress; The step of modeling the composite material layup of the target pressure-bearing equipment according to the inner liner geometric data to obtain the composite material layup modeling result of the target pressure-bearing equipment includes: Determining the order of each ply in the composite material layup, the thickness of each target layer, and the winding angle of each spiral layer based on the polar hole radius and the inner liner radius in the inner liner geometric data; The determining the strain and stress of each composite material ply based on the composite material ply modeling result includes: Splitting the material layer modeling result into a head modeling result and a bottle body modeling result; Determine the strain and stress of the head modeling result based on analytical solution of differential equations; The strains in the circumferential direction and the meridian direction are calculated for the modeling result of the bottle body to obtain the circumferential strain and the meridian direction strain; The method of determining the strain and stress of the head modeling result based on the analytical solution of the differential equation includes: Determine the meridian direction, meridian curvature and circumferential curvature that match the head modeling result; Determine the strain and stress of the head modeling result according to the meridian direction, meridian curvature and circumferential curvature; Correspondingly, the strain and stress of the head modeling result are determined according to the meridian direction, meridian curvature and circumferential curvature, including: Substituting the meridian direction, meridian curvature and circumferential curvature into the target formula to obtain the strain and stress of the head modeling result; The target formula is determined by the following formula: ； in, , , , , , , , , , , as well as is the item of the stiffness matrix corresponding to the head modeling result; and are the meridian and annular stresses respectively under ideal conditions; and Represents the strain in the meridian direction and the annular direction; s is the coordinate in the meridian direction; r1 is the meridian curvature; r2 is the curvature in the circumferential direction; r3 is the auxiliary variable for geometric calculation; The strain calculation of the bottle body modeling result in the circumferential direction and the meridian direction is performed respectively to obtain the circumferential strain and the meridian direction strain, including: The hoop strain of the bottle modeling results is determined based on the following formula: ； in, ; ; ; ; , , , , , , , , , , as well as is the item of the stiffness matrix corresponding to the bottle modeling result; R is the radius of the bottle, p is the design bursting pressure, s is the axis in the meridian direction, is the hoop strain; The meridian strain of the bottle modeling result is determined based on the following formula: ； in, is the strain in the meridian direction; , , as well as Entries of the stiffness matrix corresponding to the bottle modeling results.

2. The design method of composite pressure-bearing equipment according to claim 1, characterized in that: The step of obtaining the inner liner geometric data of the target pressure-bearing equipment in response to the design instruction of the target pressure-bearing equipment comprises: Determining a coding rule for a design instruction of the target pressure-bearing equipment; Parsing the design instructions of the target pressure-bearing equipment according to the coding rules to obtain the inner tank geometry data of the target pressure-bearing equipment; The inner liner geometric data includes: the pole hole radius, the inner liner radius and the target bursting pressure.

3. The design method of composite pressure-bearing equipment according to claim 2, characterized in that: The determining the order of each ply in the composite material ply, the thickness of each ply, and the winding angle of each spiral layer based on the polar hole radius and the inner liner radius in the inner liner geometric data includes: The thickness of each of the plies is determined based on any of the following formulas: ； ； in, is the fitting parameter, is the radius of the polar hole, r is the radius of the inner tank, It is the position of two bandwidths from the polar hole outwards; one bandwidth is the width of a carbon fiber; is the number of yarns, is the number of layers; b is the yarn width; The winding angle of each helical layer is determined based on the following formula: ； in, is the local radius of the bottle on the y-axis, represents the friction coefficient, α is the winding angle of the helical layer, and are the second and first derivatives of the local radius, respectively; Based on the grid theory, the total thickness of the spiral layer and the total thickness of the hoop layer in the composite material layup are determined respectively; The number of plies in the composite material layup is determined based on the total thickness of each of the plies, the total thickness of the spiral layers and the total thickness of the hoop layers, and the order of each ply is determined based on the number of plies and the winding angle of each spiral layer.

4. A design device for composite pressure-bearing equipment, characterized in that: include: An inner liner geometric data acquisition module, used to obtain the inner liner geometric data of the target pressure-bearing equipment in response to the design instruction of the target pressure-bearing equipment; A composite material layup modeling result determination module is used to model the composite material layup of the target pressure-bearing equipment according to the inner liner geometric data to obtain the composite material layup modeling result of the target pressure-bearing equipment; A calculation module, used to determine the strain and stress of each composite material ply based on the composite material ply modeling result, and determine whether the composite material ply corresponding to the composite material ply modeling result is safe according to each strain and stress; The composite material ply modeling result determination module is specifically used to determine the order of each ply in the composite material ply, the thickness of each target layer, and the winding angle of each spiral layer based on the polar hole radius and the inner liner radius in the inner liner geometric data; The calculation module is specifically used to split the material layer modeling result into a head modeling result and a bottle body modeling result; and determine the strain and stress of the head modeling result based on an analytical solution of a differential equation; The strains in the circumferential direction and the meridian direction are calculated for the modeling result of the bottle body to obtain the circumferential strain and the meridian direction strain; The calculation module includes: a head modeling result calculation submodule, which is used to determine the meridian direction, meridian curvature and circumferential direction curvature matching the head modeling result; Determine the strain and stress of the head modeling result according to the meridian direction, meridian curvature and circumferential curvature; The head modeling result calculation submodule is specifically used to substitute the meridian direction, meridian curvature and circumferential curvature into the target formula to obtain the strain and stress of the head modeling result; the target formula is determined by the following formula: ； in, , , , , , , , , , , as well as is the item of the stiffness matrix corresponding to the head modeling result; and are the meridian and annular stresses respectively under ideal conditions; and Represents the strain in the meridian direction and the annular direction; s is the coordinate in the meridian direction; r1 is the meridian curvature; r2 is the curvature in the circumferential direction; r3 is the auxiliary variable for geometric calculation; The calculation module further includes: a bottle body modeling result calculation submodule, which is used to determine the hoop strain of the bottle body modeling result based on the following formula: ； in, ; ; ; ; , , , , , , , , , , as well as is the item of the stiffness matrix corresponding to the bottle modeling result; R is the radius of the bottle, p is the design bursting pressure, s is the axis in the meridian direction, is the hoop strain; The meridian strain of the bottle modeling result is determined based on the following formula: ； in, is the strain in the meridian direction; , , as well as Entries of the stiffness matrix corresponding to the bottle modeling results.

5. An electronic device, characterized in that: The electronic device comprises: at least one processor; and a memory communicatively connected to the at least one processor; wherein, The memory stores a computer program executable by the at least one processor, and the computer program is executed by the at least one processor so that the at least one processor can execute the method for designing composite pressure-bearing equipment according to any one of claims 1-3.

6. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores computer instructions, and the computer instructions are used to implement the design method of composite pressure-bearing equipment according to any one of claims 1 to 3 when executed by a processor.

Images