A reverse design method and device of a blade layup and an electronic device

Abstract

The present application relates to the technical field of wind turbine blade layup, and particularly relates to a blade layup reverse design method, device, equipment and computer readable storage medium, wherein the method comprises: obtaining a target bending stiffness distribution of a blade and a blade geometric shape, and laying a basic shell layup on the blade geometric shape; setting a beam cap on the basic shell layup with the blade shaft as a center line; calculating an initial bending stiffness of the basic shell layup without the beam cap for a blade cross section; judging whether the target bending stiffness is greater than the initial bending stiffness, if greater, starting from the first beam cap, sequentially increasing the unidirectional cloth layup layer number thereof, and calculating the bending stiffness of the current interface, until the error between the bending stiffness of the current cross section and the target bending stiffness satisfies a preset tolerance. With the target bending stiffness distribution as a direct input, the layup parameters are reversely solved through a systematic algorithm process, avoiding a large number of trial-and-error calculations and repeated adjustments depending on experience in the traditional method.

Description

Technical Field

[0001] This application relates to the field of wind turbine blade layup technology, and in particular to a reverse design method, apparatus, electronic device and computer-readable storage medium for blade layup. Background Technology

[0002] As a core component for wind energy capture and conversion, the structural design and mechanical properties of wind turbine blades directly affect the overall power generation efficiency and operational reliability of the turbine. Blades typically employ composite laminate structures, achieving the required stiffness and strength distribution through ply layup design. Among these, bending stiffness is a key indicator in blade structural design, directly impacting the blade's dynamic response, fatigue life, and aeroelastic stability.

[0003] Traditional blade layup design methods largely rely on a forward design approach, which involves calculating structural stiffness step-by-step based on material properties, layup sequence, and thickness, and then iteratively adjusting to meet the target stiffness requirements. While intuitive, this method suffers from long design cycles, high computational loads, reliance on experience, and difficulty in accurately matching the target stiffness distribution. This is especially true when dealing with complex cross-sectional shapes or multi-beam cap structures, where forward design often struggles to efficiently control the precise stiffness distribution. Furthermore, existing technologies lack a systematic reverse design method that can derive the layup scheme for each cross-section from the target bending stiffness distribution, and achieve rapid and accurate design optimization while considering process constraints (such as maximum layup thickness and material modulus selection).

[0004] Therefore, there is an urgent need for a method that can perform reverse design of blade layup based on the target bending stiffness distribution, so as to improve design efficiency, reduce trial and error costs, and ensure the accurate realization of blade structural performance. Summary of the Invention

[0005] This application aims to at least partially address one of the technical problems in the related art.

[0006] Therefore, the first objective of this application is to propose a reverse design method for blade layup to solve the problems of long design cycle, large amount of calculation, reliance on experience, and difficulty in accurately matching target stiffness distribution in existing technologies.

[0007] The second objective of this application is to provide an apparatus.

[0008] The third objective of this application is to propose an electronic device.

[0009] The fourth objective of this application is to provide a computer-readable storage medium.

[0010] To achieve the above objectives, a first aspect of this application proposes a reverse design method for blade layup, comprising:

[0011] Obtain the target bending stiffness distribution and blade geometry of the blade, and lay a basic shell layup on the blade geometry;

[0012] With the blade shaft as the center line, a beam cap is installed on the base shell ply;

[0013] For the blade section, calculate the initial bending stiffness of the foundation shell ply when there is no beam cap;

[0014] Determine whether the target bending stiffness is greater than the initial bending stiffness. If it is greater, start from the first beam cap and increase the number of unidirectional laying layers in sequence, and calculate the bending stiffness of the current interface until the error between the bending stiffness of the current section and the target bending stiffness meets the preset tolerance.

[0015] Preferably, it further includes:

[0016] If the ply thickness of a single beam cap reaches its maximum processable thickness, and the bending stiffness of the current section does not meet the preset tolerance, then the ply thickness of the beam cap remains unchanged, and the number of ply layers of the next beam cap is increased sequentially until the preset tolerance is met.

[0017] Preferably, it further includes:

[0018] If the ply thickness of the beam cap reaches its maximum processable thickness, and the bending stiffness of the current section still does not meet the preset tolerance, then replace it with a unidirectional fabric material with a higher modulus and re-lay it until the preset tolerance is met.

[0019] Preferably, it further includes:

[0020] If the same beam cap uses unidirectional fabric materials with different moduli in different sections, the material with the highest modulus shall be selected as the final material of the beam cap.

[0021] The ply thickness of the section on the beam cap that previously used a lower modulus material was modified.

[0022] Preferably, the thickness correction formula is:

[0023] hn=E0×h0 / En

[0024] Where hn is the thickness of the new beam cap section, En is the elastic modulus of the material with the highest modulus, E0 is the modulus of the material with the lowest modulus, and h0 is the current ply thickness.

[0025] Preferably, the step of setting a beam cap on the base shell ply with the blade shaft as the centerline includes:

[0026] The number and location of beam caps are determined based on the chord length of the blades and the maximum width of the beam cap fabric layer. If the total width of the beam caps required calculated based on the chord length exceeds the actual chord length, the number of beam caps is reduced.

[0027] Preferably, the formula for determining whether the target bending stiffness is greater than the initial bending stiffness is:

[0028]

[0029] Where abs is the absolute value function, EI is the current calculated bending stiffness, EId is the target bending stiffness, and D is the preset tolerance.

[0030] To achieve the above objectives, a second aspect of this application provides a reverse design apparatus for blade layup, comprising:

[0031] The data acquisition module acquires the target bending stiffness distribution and blade geometry of the blade, and lays a basic shell layer on the blade geometry.

[0032] The beam cap setting module sets a beam cap on the foundation shell layer with the blade shaft as the center line;

[0033] The initial bending stiffness calculation module calculates the initial bending stiffness of the foundation shell ply when there is no beam cap for the blade section.

[0034] The judgment module determines whether the target bending stiffness is greater than the initial bending stiffness. If it is greater, it starts from the first beam cap and sequentially increases the number of unidirectional laying layers, and calculates the bending stiffness of the current interface until the error between the bending stiffness of the current section and the target bending stiffness meets the preset tolerance.

[0035] To achieve the above objectives, a third aspect of this application provides an electronic device, including: a processor, and a memory communicatively connected to the processor;

[0036] The memory stores computer-executed instructions;

[0037] The processor executes computer execution instructions stored in the memory to implement the method described in any of the preceding descriptions.

[0038] To achieve the above objectives, a fourth aspect of this application provides a computer-readable storage medium, comprising computer-executable instructions stored therein, which, when executed by a processor, are used to implement the method described in any of the above embodiments.

[0039] This application provides a reverse design method for blade layups. Using the target bending stiffness distribution as direct input, it solves for layup parameters through a systematic algorithm, avoiding the extensive trial-and-error calculations and experience-dependent adjustments required in traditional methods. By employing a "sequential activation of beam caps" strategy, material is preferentially added to the region contributing the most to the section's moment of inertia (i.e., the main beam cap furthest from the neutral axis), thus achieving maximum stiffness improvement with minimal material increment. Through steps such as "replacing with a higher modulus material" and "thickness correction after material unification," it provides an effective solution for complex design scenarios with high stiffness requirements. It allows for the use of different materials for the same beam cap in different sections, followed by a final unification correction, demonstrating high flexibility.

[0040] Additional aspects and advantages of this application will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of this application. Attached Figure Description

[0041] The above and / or additional aspects and advantages of this application will become apparent and readily understood from the following description of the embodiments taken in conjunction with the accompanying drawings, wherein:

[0042] Figure 1 A flowchart of a first specific embodiment of a reverse design method for blade layup provided by the present invention;

[0043] Figure 2 This is a structural block diagram of a blade layup reverse design device provided in an embodiment of the present invention. Detailed Implementation

[0044] The core of this invention is to provide a reverse design method, device, electronic device and computer-readable storage medium for blade layup. Taking the target bending stiffness distribution as direct input, the layup parameters are solved in reverse through a systematic algorithm process, which improves design efficiency, reduces trial and error costs and ensures the accurate realization of blade structural performance.

[0045] To enable those skilled in the art to better understand the present invention, the invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. Obviously, the described embodiments are merely some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0046] Please refer to Figure 1 , Figure 1 A flowchart of a first specific embodiment of the reverse design method for blade layup provided by the present invention; the specific operation steps are as follows:

[0047] Step S101: Obtain the target bending stiffness distribution and blade geometry of the blade, and lay the basic shell ply on the blade geometry;

[0048] Step S102: With the blade shaft as the center line, install a beam cap on the foundation shell layer;

[0049] Step S103: For the blade section, calculate the initial bending stiffness of the foundation shell ply without a beam cap;

[0050] Step S104: Determine whether the target bending stiffness is greater than the initial bending stiffness. If it is greater, start from the first beam cap and increase the number of its unidirectional laying layers in sequence, and calculate the bending stiffness of the current interface until the error between the bending stiffness of the current section and the target bending stiffness meets the preset tolerance.

[0051] Based on the above embodiments, this embodiment will provide a detailed description of step S101:

[0052] In one embodiment, based on the target bending stiffness and blade geometry, a commonly used shell material, such as biaxial fiberglass cloth, is used for laying, with one layer on the inside and one layer on the outside, from the leading edge to the trailing edge, to ensure the basic shape of the blade cross section.

[0053] Based on the above embodiments, this embodiment will provide a detailed description of step S102:

[0054] In one embodiment, the number and position of beam caps are determined based on the chord length of the blade and the maximum width of the beam cap fabric layer. If the total width of the beam caps required calculated based on the chord length exceeds the actual chord length, the number of beam caps is reduced.

[0055] Specifically, with the blade axis as the centerline, the first beam cap is laid out. The number and position of the beam caps are determined based on the chord length and the maximum width of the beam cap layer. Multiple beam caps can be used, with the edge of the beam cap closest to the blade trailing edge being more than 60mm from the trailing edge, and the edge of the beam cap closest to the blade leading edge being more than 60mm from the leading edge. There should be no overlap between beam caps. If the chord length is insufficient, one beam cap is removed. The beam caps are laid out unidirectionally, with the width of each beam cap being the maximum width of the unidirectional layer for the layer design.

[0056] Based on the above embodiments, this embodiment will provide a detailed description of step S103:

[0057] In one embodiment, for each cross section, cross section bending stiffness analysis software or program, such as precomp, is used to calculate the bending stiffness of each cross section of the blade when there is no beam cap.

[0058] Based on the above embodiments, this embodiment will provide a detailed description of step S104:

[0059] In one embodiment, if the target bending stiffness is greater than the initial bending stiffness, the unidirectional fabric on the first beam cap is added first. After each layer is laid, the bending stiffness of the section is calculated. If the error with the target stiffness is within the preset tolerance, the fabric layer thickness is no longer increased, and the design is completed.

[0060]

[0061] Where abs is the absolute value function, EI is the current calculated bending stiffness, EId is the target bending stiffness, and D is the preset tolerance.

[0062] In one embodiment, if the ply thickness of a single beam cap reaches its maximum processable thickness and the bending stiffness of the current section does not meet the preset tolerance, then the ply thickness of the beam cap remains unchanged, and the number of ply layers of the next beam cap is sequentially increased until the preset tolerance is met.

[0063] If the ply thickness of the beam cap reaches its maximum processable thickness, and the bending stiffness of the current section still does not meet the preset tolerance, then replace it with a unidirectional fabric material with a higher modulus and re-lay it until the preset tolerance is met.

[0064] If the same beam cap uses unidirectional fabric materials with different moduli in different sections, the material with the highest modulus is selected as the final material of the beam cap; the ply thickness is adjusted for sections on the beam cap that previously used materials with lower modulus.

[0065] The thickness correction formula is:

[0066] hn=E0×h0 / En

[0067] Where hn is the thickness of the new beam cap section, En is the elastic modulus of the material with the highest modulus, E0 is the modulus of the material with the lowest modulus, and h0 is the current ply thickness.

[0068] Specifically, if the ply thickness of the beam cap reaches the maximum processable thickness but the cross-sectional bending stiffness still does not reach the target stiffness, then the thickness of the first beam cap remains unchanged, and the ply of the second beam cap is increased until the cross-sectional bending stiffness meets the requirements; if the ply thickness of the first and second beam caps reaches the maximum processable thickness but the cross-sectional bending stiffness still does not reach the target stiffness, then the thickness of the first and second beam caps remains unchanged, and the ply of the third beam cap is increased until the cross-sectional bending stiffness meets the requirements; and so on.

[0069] If the thickness of all the beam caps on the cross section reaches the maximum processable thickness, but the bending stiffness of the cross section still does not reach the target stiffness, then replace the material with a material with a higher modulus and repeat the above process until the error requirement of the target stiffness is met.

[0070] After traversing all the above sections, if a beam cap uses unidirectional fabric material with different moduli in different sections, then the beam cap is designed with the material with the highest modulus, and the thickness of the beam cap section that does not use this material is redesigned.

[0071] This embodiment provides a reverse design method for blade layups. Using the target bending stiffness distribution as direct input, it solves for layup parameters through a systematic algorithm, avoiding the extensive trial-and-error calculations and experience-based adjustments required in traditional methods. By employing a "sequential activation of beam caps" strategy, material is preferentially added to the region contributing the most to the section's moment of inertia (i.e., the main beam cap furthest from the neutral axis), thus achieving maximum stiffness improvement with minimal material increment. Through steps such as "replacing with a higher modulus material" and "thickness correction after material unification," it provides an effective solution for complex design scenarios with high stiffness requirements. It allows for the use of different materials for the same beam cap in different sections, followed by a final unification correction, demonstrating high flexibility.

[0072] Based on the above embodiments, this embodiment uses specific data to describe the reverse design method for blade layup, as follows:

[0073] A reverse layup design for an 80-meter wind turbine blade;

[0074] This embodiment uses an 80-meter-long wind turbine blade as an example, applying the reverse design method of this invention for layered design. The target bending stiffness distribution (EIdi) of the blade has been predetermined through aeroelastic and structural dynamic analysis.

[0075] S1: Model building and foundation shell installation;

[0076] Provide a complete geometric model of the 80-meter blade (including coordinates of each section, chord length, twist angle, etc.). Select biaxial fiberglass cloth (e.g., ±45° layup) as the base shell material. Lay one layer of this biaxial cloth on both the pressure and suction sides from the blade root to the blade tip, along the leading edge to the trailing edge, to form a closed shell structure, in order to initially construct and stabilize the aerodynamic shape of the blade.

[0077] S2: Install beam caps;

[0078] Using the blade's main beam axis as the centerline, and based on the chord lengths at various points along the blade's span and the maximum process width of the selected unidirectional arrangement (assumed to be 150mm), calculations determine that three beam caps are needed in most areas of the blade. The arrangement principle is as follows: the beam cap closest to the leading edge (beam cap 1) has a trailing edge side line greater than 60mm from the leading edge line; the beam cap closest to the trailing edge (beam cap 3) has a leading edge side line greater than 60mm from the trailing edge line; and there is no overlap between the three beam caps. In areas with smaller tip chord lengths, this is reduced to two beam caps based on the principle.

[0079] S3: Calculate the initial stiffness;

[0080] Ten representative sections along the blade span (i = 1–10, from blade root to blade tip) were selected. For section 5 (approximately at 50% span), the initial bending stiffness EI05 was calculated using the section stiffness analysis software PreComp when only a two-way fabric shell for the foundation was laid (without any beam caps). The calculated EI05 = 8500 kN·m. 2 The target bending stiffness of this section is EId5 = 10000 kN·m. 2 Clearly, EId5 > EI05, so an additional beam cap layer is needed.

[0081] S4: Iterative thickening of the main beam cap;

[0082] The layup is increased starting from the main beam cap (beam cap 1), which has the highest contribution efficiency. This beam cap uses an initially selected standard modulus glass fiber unidirectional fabric (modulus E1 = 40 GPa).

[0083] After laying the first layer (0.8mm thick), the current stiffness EI calculated using PreComp is 8650kN·m. 2 The relative error is calculated as follows: abs(8650-10000) / 10000 = 13.5% > 0.5%, which does not meet the requirements.

[0084] After laying the second layer, EI = 8800 kN·m 2 The error was 12.0%, which did not meet the requirements. After continuous iteration, when the 10th layer (total thickness 8mm) was laid, the calculated EI was 9980 kN·m. 2 The relative error is calculated as: abs(9980-10000) / 10000 = 0.2% ≤ 0.5%! This meets the tolerance requirement. Therefore, the number of layers for beam cap 1 in this section is set to 10.

[0085] S5: (Alternative Path): Enable subsequent beam caps;

[0086] Assuming another scenario: at a certain cross-section at the leaf root, after beam cap 1 is laid to the maximum process thickness of 15mm (approximately 18 layers), the calculated EI is 15000kN·m. 2 However, the target stiffness of this section is EId = 18000 kN·m 2 If the error is 16.7% > 0.5%, then keep the thickness of beam cap 1 unchanged and start increasing the number of layers in beam cap 2 (also using unidirectional fabric with E = 40 GPa). After adding the first layer of beam cap 2, EI = 15200 kN·m 2 The error was 15.6%. Through continuous iteration, when beam cap 2 was laid to the 5th layer, EI = 17910 kN·m. 2The error is 0.5%! Requirements are met. Design complete.

[0087] S6 (Alternative Path): Replace with high modulus material;

[0088] Assuming another, more critical section at the leaf root, even if all three beam caps are laid to their maximum process thickness (e.g., a uniform thickness of 15 mm), the calculated EI using 40 GPa material is 25000 kN·m. 2 However, it is still lower than the target stiffness EId = 26000 kN·m 2 The error was 3.8% > 0.5%. At this point, keeping the layup thickness unchanged, the material of the three beam caps was replaced with a higher modulus carbon fiber hybrid unidirectional fabric (modulus E2 = 70 GPa).

[0089] After changing the material, the stiffness is recalculated. Since stiffness is proportional to modulus (EI∝E), the new stiffness estimate is approximately 25000*(70 / 40)=43750kN·m. 2 This is much higher than the target value. This means that such a thick layer is not needed.

[0090] Therefore, process S4 needs to be repeated: starting from beam cap 1, the layup iterations are performed again using 70 GPa material. It is possible that ultimately only 6 layers of high-modulus material will be needed to achieve EI = 26050 kN·m. 2 The error is less than 0.2%, which meets the requirements. This demonstrates the effectiveness of replacing the material with a high-modulus one.

[0091] S7: Traverse all sections and unify materials.

[0092] Following the procedures in S3-S6, all 10 representative sections were traversed to complete the preliminary layer design. Inspection revealed that beam cap 1 used 40GPa material in most sections, but 70GPa material was used in the critical sections described in S6.

[0093] According to the principle of standardization: the entire beam cap 1 uses the material with the highest modulus, namely 70GPa.

[0094] For sections that originally used 40GPa material, the required thickness needs to be recalculated. For example, in section S4, the original design required 10 layers of 40GPa material (thickness h0 = 8mm). After uniformly replacing it with 70GPa material, the required thickness h0 will be... n Revised to:

[0095] h n =E0*h0 / E n = (40GPa * 8mm) / 70GPa ≈ 4.57mm

[0096] Based on the actual single-layer thickness of the fabric, the number of layers is adjusted to 6 layers (4.8mm thick) or 5 layers (4.0mm thick) + partial layers. After fine-tuning calculations, the stiffness error is ensured to still meet the requirement of ≤0.5%.

[0097] Repeat this process for all beam caps to obtain a blade layup design drawing with uniform material, continuously varying thickness, and fully meeting the target stiffness distribution requirements.

[0098] This embodiment provides a reverse design method for blade layups. Using the target bending stiffness distribution as direct input, it solves for layup parameters through a systematic algorithm, avoiding the extensive trial-and-error calculations and experience-based adjustments required in traditional methods. By employing a "sequential activation of beam caps" strategy, material is preferentially added to the region contributing the most to the section's moment of inertia (i.e., the main beam cap furthest from the neutral axis), thus achieving maximum stiffness improvement with minimal material increment. Through steps such as "replacing with a higher modulus material" and "thickness correction after material unification," it provides an effective solution for complex design scenarios with high stiffness requirements. It allows for the use of different materials for the same beam cap in different sections, followed by a final unification correction, demonstrating high flexibility.

[0099] Please refer to Figure 2 , Figure 2 A structural block diagram of a reverse design device for blade layup provided in an embodiment of the present invention; the specific device may include:

[0100] The data acquisition module 100 acquires the target bending stiffness distribution and blade geometry of the blade, and lays a basic shell layup on the blade geometry.

[0101] The beam cap setting module 200 sets a beam cap on the foundation shell layer with the blade shaft as the center line;

[0102] Initial bending stiffness calculation module 300 calculates the initial bending stiffness of the foundation shell ply when there is no beam cap for the blade section.

[0103] The judgment module 400 determines whether the target bending stiffness is greater than the initial bending stiffness. If it is greater, it starts from the first beam cap and sequentially increases the number of its unidirectional laying layers, and calculates the bending stiffness of the current interface until the error between the bending stiffness of the current section and the target bending stiffness meets the preset tolerance.

[0104] This embodiment of the blade ply reverse design device is used to implement the aforementioned blade ply reverse design method. Therefore, the specific implementation of the blade ply reverse design device can be found in the embodiment section of the blade ply reverse design method above. For example, the data acquisition module 100, the beam cap setting module 200, the initial bending stiffness calculation module 300, and the judgment module 400 are respectively used to implement steps S101, S102, S103, and S104 in the aforementioned blade ply reverse design method. Therefore, its specific implementation can be referred to the description of the corresponding embodiments, which will not be repeated here.

[0105] To implement the above embodiments, this application also proposes an electronic device, including: a processor and a memory communicatively connected to the processor; the memory stores computer execution instructions; the processor executes the computer execution instructions stored in the memory to implement the method provided in the foregoing embodiments.

[0106] To implement the above embodiments, this application also proposes a computer-readable storage medium storing computer-executable instructions, which, when executed by a processor, are used to implement the methods provided in the foregoing embodiments.

[0107] To implement the above embodiments, this application also proposes a computer program product, including a computer program that, when executed by a processor, implements the methods provided in the foregoing embodiments.

[0108] The collection, storage, use, processing, transmission, provision, and disclosure of user personal information involved in this application all comply with the provisions of relevant laws and regulations and do not violate public order and good morals.

[0109] It should be noted that personal information collected from users should be used for legitimate and reasonable purposes and should not be shared or sold outside of these legitimate uses. Furthermore, such collection / sharing should only be conducted after receiving the user's informed consent, including but not limited to notifying the user to read the user agreement / user notice and sign an agreement / authorization that includes authorization of relevant user information before the user uses the function. In addition, any necessary steps must be taken to protect and safeguard access to such personal information data and ensure that others with access to personal information data comply with their privacy policies and procedures.

[0110] This application is intended to provide an implementation scheme for users to selectively prevent the use or access to their personal information data. Specifically, this disclosure is intended to provide hardware and / or software to prevent or block access to such personal information data. Once personal information data is no longer needed, risks can be minimized by restricting data collection and deleting data. Furthermore, where applicable, such personal information is de-identified to protect user privacy.

[0111] In the foregoing descriptions of the embodiments, the terms "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to specific features, structures, materials, or characteristics described in connection with that embodiment or example, which are included in at least one embodiment or example of this application. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0112] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this application, "multiple" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0113] Any process or method description in the flowchart or otherwise herein can be understood as representing a module, segment, or portion of code comprising one or more executable instructions for implementing custom logic functions or processes, and the scope of the preferred embodiments of this application includes additional implementations in which functions may be performed not in the order shown or discussed, including substantially simultaneously or in reverse order depending on the functions involved, as should be understood by those skilled in the art to which embodiments of this application pertain.

[0114] The logic and / or steps represented in the flowchart or otherwise described herein, for example, can be considered as a sequenced list of executable instructions for implementing logical functions, and can be embodied in any computer-readable medium for use by, or in conjunction with, an instruction execution system, apparatus, or device (such as a computer-based system, a processor-included system, or other system that can fetch and execute instructions from, an instruction execution system, apparatus, or device). For the purposes of this specification, "computer-readable medium" can be any means that can contain, store, communicate, propagate, or transmit programs for use by, or in conjunction with, an instruction execution system, apparatus, or device. More specific examples (a non-exhaustive list) of computer-readable media include: an electrical connection having one or more wires (electronic device), a portable computer disk drive (magnetic device), random access memory (RAM), read-only memory (ROM), erasable and editable read-only memory (EPROM or flash memory), fiber optic devices, and portable optical disc read-only memory (CDROM). Alternatively, the computer-readable medium may be paper or other suitable media on which the program can be printed, since the program can be obtained electronically, for example, by optically scanning the paper or other medium, followed by editing, interpreting, or otherwise processing as necessary, and then stored in a computer memory.

[0115] It should be understood that various parts of this application can be implemented using hardware, software, firmware, or a combination thereof. In the above embodiments, multiple steps or methods can be implemented using software or firmware stored in memory and executed by a suitable instruction execution system. For example, if implemented in hardware as in another embodiment, it can be implemented using any one or a combination of the following techniques known in the art: discrete logic circuits having logic gates for implementing logical functions on data signals, application-specific integrated circuits (ASICs) having suitable combinational logic gates, programmable gate arrays (PGAs), field-programmable gate arrays (FPGAs), etc.

[0116] Those skilled in the art will understand that all or part of the steps of the methods in the above embodiments can be implemented by a program instructing related hardware. The program can be stored in a computer-readable storage medium, and when executed, the program includes one or a combination of the steps of the method embodiments.

[0117] Furthermore, the functional units in the various embodiments of this application can be integrated into a processing module, or each unit can exist physically separately, or two or more units can be integrated into a module. The integrated module can be implemented in hardware or as a software functional module. If the integrated module is implemented as a software functional module and sold or used as an independent product, it can also be stored in a computer-readable storage medium.

[0118] The storage medium mentioned above can be a read-only memory, a disk, or an optical disk, etc. Although embodiments of this application have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting this application. Those skilled in the art can make changes, modifications, substitutions, and variations to the above embodiments within the scope of this application.

Claims

1. A reverse design method for blade layup, characterized in that, include: Obtain the target bending stiffness distribution and blade geometry of the blade, and lay a basic shell layup on the blade geometry; With the blade shaft as the center line, beam caps are provided on the base shell ply, and the number of beam caps is multiple; For the blade section, calculate the initial bending stiffness of the foundation shell ply when there is no beam cap; Determine whether the target bending stiffness is greater than the initial bending stiffness. If it is greater, start from the first beam cap and increase the number of its unidirectional laying layers in sequence, and calculate the bending stiffness of the current section until the error between the bending stiffness of the current section and the target bending stiffness meets the preset tolerance. If the ply thickness of a single beam cap reaches its maximum processable thickness, and the error between the bending stiffness of the current section and the target bending stiffness does not meet the preset tolerance, then the ply thickness of the beam cap remains unchanged, and the number of ply layers of the next beam cap is increased sequentially until the preset tolerance is met. If the ply thickness of the beam cap reaches its maximum processable thickness, and the error between the bending stiffness of the current section and the target bending stiffness still does not meet the preset tolerance, then replace it with a unidirectional fabric material with a higher modulus and re-lay it until the preset tolerance is met. If the same beam cap uses unidirectional fabric materials with different moduli in different sections, the material with the highest modulus shall be selected as the final material of the beam cap. The ply thickness of the section on the beam cap that previously used a lower modulus material was modified.

2. The reverse design method for blade layup according to claim 1, characterized in that, The thickness correction formula is: in, For the thickness of the new beam cap section, The elastic modulus of the material with the highest modulus. For materials with currently lower modulus, This represents the current layer thickness.

3. The reverse design method for blade layup according to claim 1, characterized in that, The provision of a beam cap on the foundation shell layer with the blade shaft as the centerline includes: The number and location of beam caps are determined based on the chord length of the blades and the maximum width of the beam cap fabric layer. If the total width of the beam caps required calculated based on the chord length exceeds the actual chord length, the number of beam caps is reduced.

4. A reverse design device for blade layup, characterized in that, include: The data acquisition module acquires the target bending stiffness distribution and blade geometry of the blade, and lays a basic shell layer on the blade geometry. The beam cap setting module sets beam caps on the base shell ply with the blade shaft as the center line, and the number of beam caps is multiple. The initial bending stiffness calculation module calculates the initial bending stiffness of the foundation shell ply when there is no beam cap for the blade section. The judgment module determines whether the target bending stiffness is greater than the initial bending stiffness. If it is greater, it starts from the first beam cap and sequentially increases the number of its unidirectional laying layers, and calculates the bending stiffness of the current section until the error between the bending stiffness of the current section and the target bending stiffness meets the preset tolerance. If the ply thickness of a single beam cap reaches its maximum processable thickness, and the error between the bending stiffness of the current section and the target bending stiffness does not meet the preset tolerance, then the ply thickness of the beam cap remains unchanged, and the number of ply layers of the next beam cap is increased sequentially until the preset tolerance is met. If the ply thickness of the beam cap reaches its maximum processable thickness, and the error between the bending stiffness of the current section and the target bending stiffness still does not meet the preset tolerance, then replace it with a unidirectional fabric material with a higher modulus and re-lay it until the preset tolerance is met. If the same beam cap uses unidirectional fabric materials with different moduli in different sections, the material with the highest modulus shall be selected as the final material of the beam cap. The ply thickness of the section on the beam cap that previously used a lower modulus material was modified.

5. An electronic device, characterized in that, include: A processor, and a memory communicatively connected to the processor; The memory stores computer-executed instructions; The processor executes computer execution instructions stored in the memory to implement the method as described in any one of claims 1-3.

6. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores computer-executable instructions, which, when executed by a processor, are used to implement the method as described in any one of claims 1-3.

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