Design method and system of continuous aeroelastic model of super-high four-tube bundled self-supporting steel chimney and storage medium

Abstract

The application discloses a design method and system of a super-high four-tube cluster self-standing steel chimney continuous aeroelastic model and a storage medium, and belongs to the technical field of wind tunnel test and aeroelastic mechanics. The aeroelastic model comprises the following steps: establishing a multi-degree-of-freedom aeroelastic model similarity criterion with a similarity criterion; based on the multi-degree-of-freedom aeroelastic model similarity criterion, the stiffness of a prototype four-tube cluster section is analyzed according to a stiffness equivalence-mass compensation section design method, the target stiffness distribution of the aeroelastic model is obtained, and then the internal equivalent skeleton structure of the design model is designed through topology optimization, and a scaled finite element model is established; the scaled finite element model and the full-scale finite element model are compared according to the similarity requirements, if the comparison result does not meet the similarity requirements, the scaled finite element model is re-established until the similarity requirements are met, and the effective scaled finite element model is obtained; the model skeleton is prepared in sections through a printing technology, and the aeroelastic model is obtained; and the stiffness simulation of the special-shaped section of the steel chimney and the multi-order mode reproduction are solved.

Description

Technical Field

[0001] This application relates to the fields of wind tunnel testing and aeroelasticity, specifically to the design method, system, and storage medium for a continuous aeroelastic model of an ultra-high four-tube bundled curve self-supporting steel chimney. Background Technology

[0002] With the demands of industrial development, tall structures exceeding 200m in height are increasingly common. Among them, the four-tube bundled steel chimney, as a novel chimney form, bundles four independent exhaust pipes together through a steel platform and supporting structure. It features a small footprint, high structural height, and complex overall stiffness distribution. Under strong winds, this type of structure not only experiences downwind buffeting but is also prone to aeroelastic instability phenomena such as crosswind vortex-induced vibration and galloping. Therefore, assessing its wind-induced vibration response is crucial for structural design.

[0003] Aeroelastic wind tunnel testing, as an important means of studying the wind vibration characteristics and aerodynamic stability of structures, has been maturely applied in the fields of high-rise buildings and long-span bridges. However, for tall structures with irregular cross-sections, such as four-tube bundled steel chimneys, the design of a fully aeroelastic model still faces many challenges: First, the four-tube bundled cross-section is composed of multiple circular cylinders connected by connecting members, and its bending and torsional stiffness distribution is extremely uneven. Traditional homogeneous materials cannot accurately reproduce the stiffness characteristics of this composite cross-section; Second, there are aerodynamic interference effects between multiple chimneys, and the contribution of higher-order vibration modes of the structure to the wind vibration response is not negligible. Therefore, it is necessary to design a multi-degree-of-freedom aeroelastic model, which places higher demands on the simulation of mass distribution and stiffness distribution. Existing aeroelastic model design methods are mostly limited to single-degree-of-freedom or simplified multi-degree-of-freedom models with regular cross-sections (such as rectangles and circles), which are difficult to meet the stiffness requirements of irregular cross-sections of four-tube bundled steel chimneys and the problem of multi-mode reproduction. Summary of the Invention

[0004] The purpose of this application is to provide a design method, system and storage medium for a continuous aeroelastic model of an ultra-high four-tube clustered curve self-supporting steel chimney, in order to solve the above-mentioned defects caused by the prior art.

[0005] To achieve the above objectives, this application employs the following technical solution: In the first aspect, this application discloses a design method for a continuous aeroelastic model of an ultra-high four-tube clustered curved self-supporting steel chimney, which includes: Based on the similarity criterion of the aeroelastic model with dual constraints of aerodynamic shape and dynamic characteristics, modal analysis was performed on the prototype four-tube bundled steel chimney to establish a similarity criterion for the multi-degree-of-freedom aeroelastic model with similarity criteria. Based on the similarity criterion of the multi-degree-of-freedom aeroelastic model, and according to the cross-section design method of stiffness equivalence-mass compensation, the cross-sectional characteristics of the prototype four-tube bundle cross-section are analyzed to obtain the target stiffness distribution of the aeroelastic model. Then, the equivalent skeleton structure inside the model is designed through topology optimization to establish a scaled finite element model. The similarity requirements are compared between the scaled-down finite element model and the full-scale finite element model. If the comparison results do not meet the similarity requirements, the scaled-down finite element model is re-established until the similarity requirements are met, and an effective scaled-down finite element model is obtained. Based on the effective scaled finite element model, the model skeleton was prepared in segments using printing technology and then assembled to obtain the aeroelastic model.

[0006] A further aspect of this application is that the establishment of a multi-degree-of-freedom aeroelastic model similarity criterion with similarity criteria includes establishing a multi-degree-of-freedom aeroelastic model similarity criterion that includes fluid motion similarity and structural motion similarity. The fluid motion similarity mentioned above includes determining the geometric scaling ratio under wind tunnel test conditions. λ L and wind speed ratio λ U Furthermore, the frequency ratio is derived from the similarity of the Stolaha number. ; The structural motion similarity includes deriving the stiffness ratio based on Cauchy number similarity. And derive the quality ratio ; in, λ L For geometric scaling ratio, λ U For wind speed ratio, To derive the frequency ratio, To derive the stiffness ratio; the mass ratio is ; Density ratio; This is the speed ratio.

[0007] A further aspect of this application is that the establishment of the scaled-down finite element model includes: The distribution of bending stiffness EI and torsional stiffness GJ along the height of the prototype four-tube bundle section is obtained, and the target stiffness distribution of the aeroelastic model is obtained by scaling based on the similarity criterion of the multi-degree-of-freedom aeroelastic model. Using the outer contour geometry of the aeroelastic model as a constraint, and the target stiffness and target mass distribution as design objectives, topology optimization technology is used to iteratively design the internal support structure of the model. The objective function is to minimize stiffness error, and the constraints are the target mass and centroid position. The internal ribs of the aeroelastic model are optimized to establish a scaled-down finite element model.

[0008] A further aspect of this application involves comparing the scaled-down finite element model with the full-scale finite element model to determine similarity requirements. If the comparison results do not meet the similarity requirements, a new scaled-down finite element model is established until the similarity requirements are met, resulting in an effective scaled-down finite element model, including: Modal analysis is performed on the scaled finite element model, and its first five frequencies and mode shapes are compared with the target values ​​of the full-scale finite element model. If the errors of the first five frequencies are all within the preset values ​​and the mode shape distribution is consistent, then the scaled finite element model is effective. If the frequency or mode shape error does not meet the requirements, adjust the equivalent section design or material parameters, perform iterative correction of the topology optimization design model, and rebuild the scaled finite element model until the error of the first five frequencies is within the preset value and the mode shape distribution is consistent. Then the re-established scaled finite element model is an effective scaled finite element model.

[0009] A further aspect of this application, wherein the aeroelastic model is obtained by segmenting and assembling a model skeleton based on an effectively scaled-down finite element model using printing technology, includes: Based on the effective scaled finite element model, a multi-segment aeroelastic scaled model skeleton was fabricated in an integrated manner using high-precision 3D printing technology. The mass compensation of each segment was achieved by adjusting the thickness of each T-shaped cantilever plate in the multi-segment aeroelastic scaled model skeleton. The error between the actual mass and the theoretical mass of each segment was within the preset range. The multi-segment aeroelastic scaled model skeleton was then assembled into an aeroelastic model.

[0010] Further aspects of this application include verification of the dynamic characteristics of the aeroelastic model; The dynamic characteristic verification of the aeroelastic model includes testing the dynamic characteristics of the aeroelastic model using the hammer impact method. During the test, the free decay vibration signal is recorded by a high-frequency laser displacement meter, and the actual fundamental frequency and actual damping ratio of the model are obtained by FFT analysis and compared with the design value. If the error of the actual fundamental frequency, actual damping ratio and design value is within the specified range, the aeroelastic model is qualified; otherwise, it is unqualified.

[0011] Secondly, this application discloses a continuous aeroelastic model design system for an ultra-high four-tube clustered curved self-supporting steel chimney, which includes: The similarity criterion establishment module is used to perform modal analysis on a prototype four-tube bundled steel chimney based on the similarity criterion of the aeroelastic model under the dual constraints of aerodynamic shape and dynamic characteristics, and to establish the similarity criterion of the multi-degree-of-freedom aeroelastic model with similarity criteria. The first module is used to analyze the cross-sectional characteristics of the prototype four-tube bundle cross-section based on the similarity criteria of the multi-degree-of-freedom aeroelastic model and the cross-sectional design method of stiffness equivalence-mass compensation, to obtain the target stiffness distribution of the aeroelastic model, and then to establish a scaled finite element model by designing the equivalent skeleton structure inside the model through topology optimization. The second module is used to compare the similarity requirements between the scaled-down finite element model and the full-scale finite element model. If the comparison result does not meet the similarity requirements, the scaled-down finite element model is rebuilt until the similarity requirements are met, and an effective scaled-down finite element model is obtained. The module is used to prepare the model skeleton in segments using printing technology based on an effective scaled-down finite element model, and then assemble it to obtain the aeroelastic model.

[0012] Thirdly, this application discloses a computer-readable storage medium, characterized in that the computer-readable storage medium stores one or more programs, the one or more programs including instructions that, when executed by a computing device, cause the computing device to perform the above-described method.

[0013] The beneficial effects of this application are as follows: The multi-degree-of-freedom aeroelastic model similarity criterion, which integrates similarity criteria based on geometric shape, cross-sectional stiffness, and mass distribution, can accurately simulate the nonlinear vibration modes of a four-tube bundled steel chimney. Furthermore, in conjunction with the stiffness equivalence-mass compensation cross-section design method, stiffness analysis is performed on the prototype four-tube bundled cross-section. The similarity requirements are compared between the scaled-down finite element model and the full-scale finite element model. By iteratively optimizing the scaled-down finite element model, the target stiffness distribution is repeatedly optimized to ensure the cross-sectional stiffness requirements are met. Attached Figure Description

[0014] Figure 1 This is a logic diagram of the design method for the continuous aeroelastic model of the ultra-high four-tube cluster curve self-supporting steel chimney in the embodiments of this application. Figure 2 This is a schematic diagram of the segmented printing of the aeroelastic model in an embodiment of this application; Figure 3 This is a schematic diagram of the internal rib arrangement for topology optimization of the aeroelastic model in this embodiment of the application; Figure 4 This is a schematic diagram of mass compensation for the gas bullet model in the embodiments of this application; Figure 5 This is a schematic diagram of the verification process for the dynamic characteristics of the aeroelastic model in the embodiments of this application.

[0015] in: 101. Single chimney pipe body; 102. I-beam; 103. Cross section at a certain height; 104. Elevator shaft; 105. Metal disc base; 201. Star-shaped rib; 202. Cross-shaped X-rib; 203. Cross-shaped rib; 204. Rhomboid frame-shaped rib; 301. Mass compensation longitudinal section; 302. Mass compensation block; 401. Marked as hammer impact point; 402. High-frequency laser displacement gauge; 403. Data collection and analysis system; 404. FFT analysis result graph. Detailed Implementation

[0016] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. The following description of at least one exemplary embodiment is merely illustrative and is in no way intended to limit this application or its application or use. Example 1

[0017] like Figure 1 As shown, this application provides a design method for a continuous aeroelastic model of an ultra-high four-tube bundled curved self-supporting steel chimney. The method includes: performing modal analysis on a prototype four-tube bundled steel chimney based on aeroelastic model similarity criteria constrained by both aerodynamic shape and dynamic characteristics; establishing a multi-degree-of-freedom aeroelastic model similarity criterion based on the multi-degree-of-freedom aeroelastic model similarity criterion; performing stiffness analysis on the prototype four-tube bundled section based on a stiffness equivalence-mass compensation section design method to obtain the target stiffness distribution of the aeroelastic model; then designing the equivalent skeleton structure inside the model through topology optimization to establish a scaled finite element model; comparing the scaled finite element model with the full-scale finite element model to meet similarity requirements; if the comparison result does not meet the similarity requirements, re-establishing the scaled finite element model until the similarity requirements are met, obtaining an effective scaled finite element model; and finally, using printing technology to prepare the model skeleton in segments based on the effective scaled finite element model, and assembling them to obtain the aeroelastic model.

[0018] This application designs a similarity criterion for a multi-degree-of-freedom aeroelastic model. Based on this similarity criterion and the section design method of stiffness equivalence-mass compensation, and in conjunction with topology optimization design of the internal equivalent skeleton structure of the model, the target stiffness distribution can be updated and optimized until the similarity requirements are met between the scaled finite element model and the full-scale finite element model, thus obtaining a qualified aeroelastic model.

[0019] In some embodiments, a design method for a continuous aeroelastic model of an ultra-high four-tube bundled curved self-supporting steel chimney is specifically designed as follows. Based on the similarity criterion of aeroelastic model with dual constraints of aerodynamic shape and dynamic characteristics, and taking into account geometric shape, cross-sectional stiffness and mass distribution, a multi-degree-of-freedom aeroelastic model similarity criterion including fluid motion similarity and structural motion similarity is established. First, modal analysis was performed on the prototype four-tube bundled steel chimney to extract its first five frequencies and mode shapes. Considering that the structural wind-induced vibration response is dominated by bending modes, and to accurately simulate nonlinear modes, a multi-degree-of-freedom aeroelastic model was chosen. The similarity criteria were established by comprehensively considering both fluid motion similarity and structural motion similarity. Regarding fluid motion similarity, the geometric scaling ratio was determined based on wind tunnel test conditions. λ L and wind speed ratio λ U，Furthermore, the frequency ratio is derived from the similarity of Stolaha numbers. Regarding structural motion similarity, the stiffness ratio is derived based on Cauchy number similarity. And derive the mass ratio from the mass ratio. For Reynolds number similarity, considering the Reynolds number effect of a circular cross-section, an equivalent simulation is performed by setting an artificial roughening band on the model surface. Taking a 240m high four-tube bundled steel structure chimney as an example, the implementation process of this invention is described in detail; the geometric scaling ratio is determined based on the dimensions of the wind tunnel test section and the surrounding building layout of the chimney. λ L =1:150, wind speed ratio λ U =1:5, from which the frequency ratio is derived quality ratio Bending stiffness ratio Damping ratio λ ξ A 1:1 ratio was chosen, meaning the damping ratio of the model was consistent with that of the prototype. To simulate the Reynolds number effect, a roughening strip was applied to the model surface.

[0020] Using a stiffness-equivalent-mass-compensated section design method, precise section property analysis was performed on typical sections of the prototype four-tube bundled steel chimney to obtain its bending stiffness. EI and torsional stiffness GJ Distribution pattern along height. Based on the previously determined similarity criteria for multi-degree-of-freedom aeroelastic models, the cross-sectional stiffness of the prototype four-tube bundled steel chimney was scaled down to obtain the target stiffness distribution of the aeroelastic model. Then, using the outer contour geometry of the aeroelastic model as a constraint, and the target stiffness and target mass distribution as design objectives, topology optimization technology was used for iterative design of the internal support structure of the aeroelastic model. During the design, the minimum stiffness error was used as the objective function, and the target mass and centroid position were used as constraints to optimize the layout and size of the internal ribs (such as cross-shaped intersecting ribs, diagonal intersecting ribs, multiple intersecting ribs, star-shaped ribs, etc.). Finally, a special nylon material (elastic modulus) was selected. E 1.5×10 9 Pa, density ρ 1050 kg / m 3 (This is used as the printing material, and the preliminary design of the model is completed, resulting in a scaled-down finite element model; such as...) Figure 3 As shown, combinations of star-shaped ribs 201, cross-shaped X-ribs 202, cross-shaped ribs 203, and rhomboid frame-shaped ribs 204 can be used.

[0021] Modal analysis was performed on the scaled-down finite element model, comparing its first five frequencies and mode shapes with the target values ​​(i.e., prototype frequencies multiplied by the frequency ratio) of the full-scale model. The first five frequencies were required to have errors within 5%, and the mode shape distribution to be consistent. If the frequency or mode shape errors did not meet the requirements, the equivalent section design or material parameters were adjusted, and iterative corrections were performed until all design parameters met the similarity requirements, thus determining the effective scaled-down finite element model. After iteration, the comparison results of the first five frequencies and mode shapes in this embodiment showed the following errors: first frequency error -3.42%, second -3.42%, third -3.43%, fourth -3.43%, and fifth 0.65%, all within 5%. A multi-segment aeroelastic scaled-down model was fabricated using high-precision 3D printing technology. The effective scaled-down finite element model was printed and assembled in five segments, and subtle mass compensation for each segment was achieved by adjusting the thickness of each T-shaped cantilever plate. During model fabrication, as shown... Figure 4 As shown, mass compensation is performed. In the figure, 301 is the longitudinal section for mass compensation, showing the layered structure of the model along the height direction; 302 is the mass compensation block. By adding or removing the thickness or number of compensation blocks 302 at specific locations, mass compensation is performed by adjusting the thickness of each T-shaped cantilever plate. The error between the actual mass and the theoretical mass of each section is within 5%, thus obtaining the aeroelastic model.

[0022] Finally, the dynamic characteristics of the model were verified using the hammer impact method, the process of which is as follows: Figure 5 As shown; the high-frequency laser displacement gauge 402 is aligned with the top or key measuring points of the aeroelastic model, and the data collection and analysis system is electrically connected to the data collection and analysis system 403; a hammer impact point 401 is set at the bottom or middle of the model, and the model is excited by an impact hammer; the high-frequency laser displacement gauge 402 records the free decay vibration signal; the data collection and analysis system 403 collects and stores the signal; the FFT analysis results are shown in Figure 404; the actual fundamental frequency and damping ratio of the model are identified by Fast Fourier Transform. A metal disc base 105 is installed at the bottom and fixed to the wind tunnel turntable with screws. Based on the simulation results of the Reynolds number effect of rigid body pressure measurement, a rough strip 4mm wide and 1mm thick is pasted on the surface of the model. After assembly, the dynamic characteristics are verified by the hammer impact method: the high-frequency laser displacement gauge 402 records the free decay signal, which is then imported into the data collection and analysis system 403, and the actual fundamental frequency and damping ratio of the model are obtained by FFT analysis. The measured FFT analysis results (Figure 404) show that the actual fundamental frequency is 16.000Hz, with an error of 3.9% compared to the design fundamental frequency of 16.621Hz. The actual damping ratio is 1.31%, which is close to the specification value of 1.5%, verifying the accuracy of the model's dynamic characteristics. Example 2

[0023] Based on the same inventive concept as Embodiment 1, this application discloses a continuous aeroelastic model design system for an ultra-high four-tube clustered curve self-supporting steel chimney, which includes... The similarity criterion establishment module is used to perform modal analysis on a prototype four-tube bundled steel chimney based on the similarity criterion of the aeroelastic model under the dual constraints of aerodynamic shape and dynamic characteristics, and to establish the similarity criterion of the multi-degree-of-freedom aeroelastic model with similarity criteria. The first module is used to analyze the cross-sectional characteristics of the prototype four-tube bundle cross-section based on the similarity criteria of the multi-degree-of-freedom aeroelastic model and the cross-sectional design method of stiffness equivalence-mass compensation, to obtain the target stiffness distribution of the aeroelastic model, and then to establish a scaled finite element model by designing the equivalent skeleton structure inside the model through topology optimization. The second module is used to compare the similarity requirements between the scaled-down finite element model and the full-scale finite element model. If the comparison result does not meet the similarity requirements, the scaled-down finite element model is rebuilt until the similarity requirements are met, and an effective scaled-down finite element model is obtained. The module is used to prepare the model skeleton in segments using printing technology based on an effective scaled-down finite element model, and then assemble it to obtain the aeroelastic model. Example 3

[0024] Based on the same inventive concept as other embodiments, this embodiment introduces a computer-readable storage medium, characterized in that the computer-readable storage medium stores one or more programs, the one or more programs including instructions, which, when executed by a computing device, cause the computing device to perform the method in Embodiment 1. Those skilled in the art will understand that embodiments of the present invention can be provided as methods, systems, or computer program products. Therefore, the present invention can take the form of a completely hardware embodiment, a completely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, the present invention can take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, etc.) containing computer-usable program code.

[0025] This invention is described with reference to flowchart illustrations and / or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of the invention. It will be understood that each block of the flowchart illustrations and / or block diagrams, and combinations of blocks in the flowchart illustrations and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, special-purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, generate instructions for implementing the flowchart illustrations and / or block diagrams. Figure 1 One or more processes and / or boxes Figure 1 A device that provides the functions specified in one or more boxes.

[0026] These computer program instructions may also be stored in a computer-readable storage medium that can direct a computer or other programmable data processing device to function in a particular manner, such that the instructions stored in the computer-readable storage medium produce an article of manufacture including instruction means, which are implemented in a process Figure 1 One or more processes and / or boxes Figure 1 The function specified in one or more boxes.

[0027] These computer program instructions may also be loaded onto a computer or other programmable data processing equipment to cause a series of operational steps to be performed on the computer or other programmable equipment to produce a computer-implemented process, thereby providing instructions that execute on the computer or other programmable equipment for implementing the process. Figure 1 One or more processes and / or boxes Figure 1 The steps of the function specified in one or more boxes.

[0028] The embodiments of the present invention have been described above with reference to the accompanying drawings. However, the present invention is not limited to the specific embodiments described above. The specific embodiments described above are merely illustrative and not restrictive. Those skilled in the art can make many other forms under the guidance of the present invention without departing from the spirit and scope of the claims. All of these forms are within the protection scope of the present invention.

Claims

1. A design method for a continuous aeroelastic model of an ultra-high four-tube clustered curve self-supporting steel chimney, characterized in that, include: Based on the similarity criterion of the aeroelastic model with dual constraints of aerodynamic shape and dynamic characteristics, modal analysis was performed on the prototype four-tube bundled steel chimney to establish a similarity criterion for the multi-degree-of-freedom aeroelastic model with similarity criteria. Based on the similarity criterion of the multi-degree-of-freedom aeroelastic model, and according to the cross-section design method of stiffness equivalence-mass compensation, the cross-sectional characteristics of the prototype four-tube bundle cross-section are analyzed to obtain the target stiffness distribution of the aeroelastic model. Then, the equivalent skeleton structure inside the model is designed through topology optimization to establish a scaled finite element model. The similarity requirements are compared between the scaled-down finite element model and the full-scale finite element model. If the comparison results do not meet the similarity requirements, the scaled-down finite element model is re-established until the similarity requirements are met, and an effective scaled-down finite element model is obtained. Based on the effective scaled finite element model, the model skeleton was prepared in segments using printing technology and then assembled to obtain the aeroelastic model.

2. The design method for the continuous aeroelastic model of the ultra-high four-tube clustered curve self-supporting steel chimney according to claim 1, characterized in that, The establishment of similarity criteria for a multi-degree-of-freedom aeroelastic model includes establishing similarity criteria for a multi-degree-of-freedom aeroelastic model that incorporates both fluid motion similarity and structural motion similarity. The fluid motion similarity mentioned above includes determining the geometric scaling ratio under wind tunnel test conditions. λ L and wind speed ratio λ U Furthermore, the frequency ratio is derived from the similarity of the Stolaha number. ; The structural motion similarity includes deriving the stiffness ratio based on Cauchy number similarity. And derive the quality ratio ; in, λ L For geometric scaling ratio, λ U For wind speed ratio, To derive the frequency ratio, To derive the stiffness ratio; the mass ratio is ; Density ratio; This is the speed ratio.

3. The design method for the continuous aeroelastic model of the ultra-high four-tube clustered curve self-supporting steel chimney according to claim 1, characterized in that, The establishment of the scaled-down finite element model includes: The distribution of bending stiffness EI and torsional stiffness GJ along the height of the prototype four-tube bundle section was obtained, and the target stiffness distribution of the aeroelastic model was obtained by scaling down according to the similarity criterion of the multi-degree-of-freedom aeroelastic model. Using the outer contour geometry of the aeroelastic model as a constraint, and the target stiffness and target mass distribution as design objectives, topology optimization technology is used to iteratively design the internal support structure of the model. Among them, the internal ribs of the aeroelastic model are optimized with the minimum stiffness error as the objective function and the target mass and centroid position as constraints, and a scaled finite element model is established.

4. The design method for the continuous aeroelastic model of the ultra-high four-tube clustered curve self-supporting steel chimney according to claim 1, characterized in that, Similarity requirements are assessed using the scaled-down finite element model and the full-scale finite element model. If the comparison results do not meet the similarity requirements, a new scaled-down finite element model is established until the similarity requirements are met, resulting in an effective scaled-down finite element model, including: Modal analysis is performed on the scaled finite element model, and its first five frequencies and mode shapes are compared with the target values ​​of the full-scale finite element model. If the errors of the first five frequencies are all within the preset values ​​and the mode shape distribution is consistent, then the scaled finite element model is effective. If the frequency or mode shape error does not meet the requirements, adjust the equivalent section design or material parameters, perform iterative correction of the topology optimization design model, and rebuild the scaled finite element model until the error of the first five frequencies is within the preset value and the mode shape distribution is consistent. Then the re-established scaled finite element model is an effective scaled finite element model.

5. The design method for the continuous aeroelastic model of the ultra-high four-tube clustered curve self-supporting steel chimney according to claim 1, characterized in that, The aeroelastic model, based on an effectively scaled-down finite element model, is fabricated in segments using printing technology and then assembled to obtain the model skeleton. Based on the effective scaled finite element model, a multi-segment aeroelastic scaled model skeleton was fabricated in an integrated manner using high-precision 3D printing technology. The mass compensation of each segment was achieved by adjusting the thickness of each T-shaped cantilever plate in the multi-segment aeroelastic scaled model skeleton. The error between the actual mass and the theoretical mass of each segment was within the preset range. The multi-segment aeroelastic scaled model skeleton was then assembled into an aeroelastic model.

6. The design method for the continuous aeroelastic model of the ultra-high four-tube clustered curve self-supporting steel chimney according to claim 1, characterized in that, It also includes the verification of the dynamic characteristics of the aeroelastic model; The verification of the dynamic characteristics of the gas ball model includes testing the dynamic characteristics of the gas ball model using the hammer impact method. During the test, the free decay vibration signal is recorded by a high-frequency laser displacement meter, and the actual fundamental frequency and actual damping ratio of the model are obtained by FFT analysis and compared with the design value for verification. If the errors of the actual fundamental frequency, actual damping ratio, and design value are within the specified range, the aeroelastic model is qualified; otherwise, it is unqualified.

7. A continuous aeroelastic model design system for ultra-high four-tube clustered curve self-supporting steel chimneys, characterized in that, include: The similarity criterion establishment module is used to perform modal analysis on a prototype four-tube bundled steel chimney based on the similarity criterion of the aeroelastic model under the dual constraints of aerodynamic shape and dynamic characteristics, and to establish the similarity criterion of the multi-degree-of-freedom aeroelastic model with similarity criteria. The first module is used to analyze the cross-sectional characteristics of the prototype four-tube bundle cross-section based on the similarity criteria of the multi-degree-of-freedom aeroelastic model and the cross-sectional design method of stiffness equivalence-mass compensation, to obtain the target stiffness distribution of the aeroelastic model, and then to establish a scaled finite element model by designing the equivalent skeleton structure inside the model through topology optimization. The second module is used to compare the similarity requirements between the scaled-down finite element model and the full-scale finite element model. If the comparison result does not meet the similarity requirements, the scaled-down finite element model is rebuilt until the similarity requirements are met, and an effective scaled-down finite element model is obtained. The module is used to prepare the model skeleton in segments using printing technology based on an effective scaled-down finite element model, and then assemble it to obtain the aeroelastic model.

8. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores one or more programs, the one or more programs including instructions that, when executed by a computing device, cause the computing device to perform the method of any one of claims 1 to 6.

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