Manufacturing method for complete aeroelastic model of special-shaped high-rise structure

Abstract

The invention discloses a method for manufacturing a complete aeroelastic model of a special-shaped high-rise structure, and the method comprises the steps: S1, determining a geometric scale ratio based on prototype parameter extraction and modal analysis and test conditions; s2, determining a similarity ratio of the model according to a geometric scale ratio and a similarity criterion, and selecting a printing material; s3, according to a similarity criterion and an equivalent design method of section stiffness, obtaining a variational progressive equivalent section of the aeroelastic model along the height; s4, establishing a reduced-scale finite element model, comparing the frequency and vibration mode of the reduced-scale finite element model and the full-scale finite element model, and confirming that the reduced-scale finite element model meets a preset similar condition; s5, preparing an equivalent aeroelastic model through a 3D printing technology; and S6, fixing and aerodynamic configuration compensation are conducted on the aeroelastic model, and the complete aeroelastic model of the special-shaped high-rise structure is manufactured. According to the manufacturing method for the complete aeroelastic model of the special-shaped high-rise structure, efficient design and manufacturing of the aeroelastic wind tunnel test high-precision model are achieved.

Description

Technical Field

[0001] This invention relates to the fields of wind tunnel testing and aeroelasticity, and in particular to a method for fabricating a fully aeroelastic model of an irregularly shaped, tall structure. Background Technology

[0002] With the rapid development of large wind turbine generators and super high-rise structures, the aeroelastic response of irregularly shaped tall structures under wind loads has become increasingly prominent. These structures are characterized by complex shapes, uneven stiffness distribution, and unique mass distribution, making them prone to significant aeroelastic effects under strong winds, which seriously affect structural safety and performance.

[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 bridge engineering and high-rise building fields. However, the design of fully aeroelastic models for irregularly shaped tall structures still faces many challenges: First, the stiffness distribution of irregular cross-sections is difficult to simulate accurately, and traditional homogeneous materials cannot reproduce the stiffness characteristics of actual structures; second, the precise control of mass distribution in three-dimensional space is difficult; third, the equivalent simulation problem of Reynolds number effect has not been effectively solved, and existing aeroelastic model design methods are mostly limited to regular cross-section structures, which are difficult to meet the testing requirements of irregularly shaped tall structures. Summary of the Invention

[0004] This invention aims to solve at least one of the technical problems existing in the prior art. To this end, this invention proposes a method for fabricating a fully aeroelastic model of an irregularly shaped tall structure. This method enables the efficient design and fabrication of a high-precision aeroelastic wind tunnel test model, solving the core industry problems of simulating aerodynamic shape, achieving stiffness and mass similarity, and achieving Reynolds number equivalence in fully aeroelastic models of irregularly shaped tall structures.

[0005] According to the method for fabricating a complete aeroelastic model of an irregularly shaped tall structure of the present invention, the steps are as follows: Step S1, determining the geometric scaling ratio based on prototype parameter extraction and modal analysis, and experimental conditions; Step S2, determining the similarity ratio of the model and selecting the printing material according to the geometric scaling ratio and similarity criteria; Step S3, obtaining the variational asymptotic equivalent section of the aeroelastic model along the height according to the similarity criteria and the equivalent design method of section stiffness; Step S4, establishing a scaled-down finite element model, comparing the frequency and mode shape of the scaled-down finite element model with the full-scale finite element model, and confirming that the scaled-down finite element model meets the preset similarity conditions; Step S5, preparing an equivalent aeroelastic model using 3D printing technology; Step S6, fixing and aerodynamically compensating the aeroelastic model to fabricate a complete aeroelastic model of an irregularly shaped tall structure.

[0006] The present invention provides a method for fabricating a fully aeroelastic model of an irregularly shaped tall structure. Through a closed-loop technical solution encompassing "design-manufacturing-debugging-verification," and relying on topology optimization design of the equivalent cross-section of the irregularly shaped tall structure and 3D high-precision printing technology, it achieves efficient design and fabrication of a high-precision aeroelastic wind tunnel test model. This method not only has a short cycle time, low cost, and high accuracy, but also takes into account the scaled similarity of the aeroelastic model for multiple modes of the irregularly shaped tall structure. It accurately obtains the wind vibration characteristics of the overall structure and key parts such as abrupt changes in cross-section and local weak stiffness areas. It successfully solves the core industry problems of simulating aerodynamic shape, achieving stiffness and mass similarity, and equivalence of Reynolds number effects in the fully aeroelastic model of irregularly shaped tall structures. Ultimately, it achieves comprehensive similarity of the model in terms of geometry, mechanics, and flow field, providing reliable and comprehensive experimental data support for the wind-resistant design of the structure.

[0007] According to some embodiments of the present invention, the similarity ratio includes: wind speed ratio, time ratio, and frequency ratio derived from fluid motion similarity; density ratio and damping ratio required based on the same dimensionless parameters; and mass ratio and stiffness ratio derived from structural motion similarity.

[0008] According to some embodiments of the present invention, the stiffness equivalent section design method includes obtaining the bending and torsional stiffness of the irregular tall structure based on composite section analysis, and obtaining the variational asymptotic equivalent section along the height of the aeroelastic model that meets the requirements of bidirectional scaled stiffness and centroid based on topology optimization equivalent section design.

[0009] According to some embodiments of the present invention, step S3 includes: step S31, performing a fine section analysis on the prototype structure based on the composite section theory to obtain the bending and torsional stiffness of the prototype structure; step S32, performing scale conversion on the stiffness and mass parameters of the prototype structure based on the similarity criterion to obtain the target stiffness and mass distribution of the aeroelastic model; step S34, based on the target stiffness and the mass distribution, iteratively adjusting the local dimensions of the section and the component division through the section topology optimization design method to obtain the variational asymptotic equivalent section of the aeroelastic model along the height.

[0010] According to some embodiments of the present invention, step S4 includes: performing modal analysis on the scaled finite element model, comparing the natural frequencies and mode shapes of the scaled finite element model with the target values ​​of the full-scale finite element model, and confirming whether the errors of the frequencies or mode shapes meet the requirements; if yes, then confirming that the preset similarity conditions are met; if no, then re-determining the similarity ratio of the model according to the geometric scaling ratio and similarity criteria and re-selecting the printing material.

[0011] According to some embodiments of the present invention, step S5 includes: step S51, preparing a physical scaled-down model using 3D printing technology; step S52, configuring counterweights in sections of the physical scaled-down model to achieve mass compensation, so as to obtain an equivalent aeroelastic model.

[0012] According to some embodiments of the present invention, step S6 includes: step S61, fixing the gas ball model, verifying the dynamic characteristics of the gas ball model by hammering, and confirming that the gas ball model meets the dynamic similarity criterion; step S62, installing skin or surface treatment on the gas ball model, and performing aerodynamic shape compensation on the gas ball model to create a complete gas ball model with an irregularly shaped tall structure.

[0013] According to some embodiments of the present invention, the aeroelastic model is fixed by a metal chassis, and the aerodynamic shape compensation includes attaching a rough strip to the surface of the model.

[0014] According to some embodiments of the present invention, the method further includes: step S7, verifying the fully aeroelastic model to confirm that the fully aeroelastic model can simultaneously meet the target requirements of aerodynamic and structural dynamic similarity in wind tunnel tests.

[0015] According to some embodiments of the present invention, the verification method includes: performing a three-dimensional scan and weighing of the complete gas ballistic model to confirm that the aerodynamic shape of the complete gas ballistic model meets preset requirements and that the total mass parameter of the complete gas ballistic model meets preset values.

[0016] Additional aspects and advantages of the invention 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 the invention. Attached Figure Description

[0017] Figure 1 This is a flowchart of a method for fabricating a complete aeroelastic model of an irregularly shaped tall structure according to an embodiment of the present invention; Figure 2 This is a flowchart of step S3 according to an embodiment of the present invention; Figure 3 This is a flowchart of step S5 according to an embodiment of the present invention; Figure 4 This is a flowchart of step S6 according to an embodiment of the present invention; Figure 5 This is a schematic diagram of the internal rib arrangement for topology optimization of an aeroelastic model according to an embodiment of the present invention; Figure 6 This is a schematic diagram of the internal rib arrangement for topology optimization of an aeroelastic model according to another embodiment of the present invention; Figure 7 This is a schematic diagram of the internal rib arrangement for topology optimization of an aeroelastic model according to another embodiment of the present invention; Figure 8 This is a schematic diagram of the internal rib arrangement for topology optimization of an aeroelastic model according to another embodiment of the present invention. Detailed Implementation

[0018] Embodiments of the present invention are described in detail below. Examples of these embodiments are illustrated in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain the present invention, and should not be construed as limiting the present invention.

[0019] The following is for reference. Figures 1-8 A method for fabricating a fully aeroelastic model of an irregularly shaped tall structure according to an embodiment of the present invention is described.

[0020] like Figures 1-4 As shown, according to the first aspect of the present invention, a method for fabricating a complete aeroelastic model of an irregularly shaped tall structure is provided. Step S1 determines the geometric scaling ratio based on prototype parameter extraction, modal analysis, and experimental conditions. Prototype parameter extraction mainly includes: geometric feature parameters, such as dimensional parameters and profile curve parameters; stiffness characteristic parameters, such as the overall axial stiffness, bending stiffness, and torsional stiffness distribution of the structure, as well as the local stiffness values ​​of key components; and mass and inertia parameters, such as the total mass of the structure and the mass linear density distribution along the height direction. Modal analysis is mainly used for core parameters of the prototype structure, such as natural frequencies, mode shapes, and damping ratios. Experimental conditions refer to the experimental environment and technical capabilities that the wind tunnel laboratory can provide, which determines the selectable range of the geometric scaling ratio. Therefore, it can be understood that step S1 first extracts the core feature benchmarks of the structure based on the prototype parameters, and then, combined with the boundary constraints of the experimental conditions, calculates and selects the optimal geometric scaling ratio.

[0021] Step S2: Determine the similarity ratio of the model and select the printing material based on the geometric scaling ratio and similarity criteria. The similarity criteria are complete similarity criteria that consider both aerodynamic shape and structural dynamic characteristics.

[0022] Step S3: Obtain the variational asymptotic equivalent cross-section of the aeroelastic model along its height based on similarity criteria and equivalent design methods for cross-sectional stiffness. Since the stiffness and mass of the irregularly shaped tall structure vary gradually along its height, the variational asymptotic beam section method is introduced to transform the spanwise stiffness distribution of the full-scale prototype into a continuous equivalent cross-section of the model along its height. This allows the mechanical properties of the model's cross-section to change gradually with height, effectively avoiding aeroelastic response distortion caused by abrupt changes in local stiffness. Furthermore, this ensures that the dynamic characteristics of the model under wind loads are highly similar to those of the prototype.

[0023] Step S4: Establish a scaled-down finite element model, compare the frequencies and mode shapes of the scaled-down finite element model with those of the full-scale finite element model, and confirm that the scaled-down finite element model meets the preset similarity conditions. The preset similarity conditions are: the cross-sectional stiffness and mass of the scaled-down finite element model and the full-scale finite element model are completely equivalent.

[0024] Step S5 involves fabricating an equivalent aeroelastic model using 3D printing technology. 3D printing is a relatively simple technology with high precision, short production cycle, and relatively low cost. Therefore, fabricating an equivalent aeroelastic model using 3D printing can reduce the time and cost of model fabrication.

[0025] Step S6 involves fixing and aerodynamically compensating the aeroelastic model to create a complete aeroelastic model of an irregularly shaped, tall structure. Fixing and aerodynamically compensating the aeroelastic model are primarily used to ensure that the boundary conditions of the aeroelastic model are similar to those of the prototype structure. It should be noted that fixing the aeroelastic model ensures that it meets the equivalent constraint conditions of the prototype after fixing. Aerodynamic compensation can be achieved in various ways, such as attaching a roughening strip to the model surface.

[0026] For example, when a fully aeroelastic model needs to be prepared, firstly, based on prototype parameter extraction and modal analysis, a complete similarity criterion that comprehensively considers aerodynamic shape and structural dynamic characteristics is established to obtain geometric similarity ratio, wind speed ratio, frequency ratio, stiffness ratio, mass ratio, etc.; then, based on the determined geometric shape, the internal cross-rib structure is designed through the variable cross-section topology optimization method, and a suitable printing material is selected to complete the preliminary design of the model; then, a scaled-down finite element model is established, and the frequencies and mode shapes are compared with the full-scale finite element model to ensure that the cross-sectional stiffness and mass of the scaled-down finite element model are completely equivalent; finally, an equivalent aeroelastic model is prepared using high-precision 3D printing technology, and then the aeroelastic model is installed on a metal fixed base, and a roughening strip is pasted on the model surface to complete aerodynamic shape compensation and system assembly, thereby realizing the preparation of a fully aeroelastic model of an irregularly shaped tall structure.

[0027] It should be noted that in step S2 above, based on the geometric scaling ratio, the Stolaha number (St) similarity is strictly satisfied to determine the time and frequency scale; in step S3, the stiffness scaling relationship derived from Cauchy number (Ca) similarity is followed; for Reynolds number similarity, which is difficult to achieve, the design adopts the method of critical Reynolds number judgment and artificially setting roughness bands for equivalent simulation after the solid model is made; for Froude number similarity, it can be reasonably ignored based on the judgment that gravity is a secondary factor in wind-induced response; finally, the damping ratio is made consistent with the prototype by fixing the model. Thus, the complex multi-parameter similarity problem can be simplified to the precise control of core elements such as geometry, stiffness, mass distribution, damping ratio, and Reynolds number equivalence, thereby ensuring the simulation accuracy of aeroelastic response, while avoiding the engineering infeasibility caused by pursuing full criterion similarity, making the complete aeroelastic model preparation scheme feasible.

[0028] The present invention provides a method for fabricating a fully aeroelastic model of an irregularly shaped tall structure. Through a closed-loop technical solution encompassing "design-manufacturing-debugging-verification," and relying on topology optimization design of the equivalent cross-section of the irregularly shaped tall structure and 3D high-precision printing technology, it achieves efficient design and fabrication of a high-precision aeroelastic wind tunnel test model. This method not only has a short cycle time, low cost, and high accuracy, but also takes into account the scaled similarity of the aeroelastic model for multiple modes of the irregularly shaped tall structure. It accurately obtains the wind vibration characteristics of the overall structure and key parts such as abrupt changes in cross-section and local weak stiffness areas. It successfully solves the core industry problems of simulating aerodynamic shape, achieving stiffness and mass similarity, and equivalence of Reynolds number effects in the fully aeroelastic model of irregularly shaped tall structures. Ultimately, it achieves comprehensive similarity of the model in terms of geometry, mechanics, and flow field, providing reliable and comprehensive experimental data support for the wind-resistant design of the structure.

[0029] According to some embodiments of the present invention, similarity ratios include: wind speed ratio, time ratio, and frequency ratio derived from fluid motion similarity; density ratio and damping ratio required based on the same dimensionless parameters; and mass ratio and stiffness ratio derived from structural motion similarity.

[0030] Specifically, the similarity in fluid motion is as follows: the air in the flow field of the irregularly shaped, towering structure is a low-speed, incompressible, Newtonian viscous flow, and its fluid motion equation is:

[0031] Among them, u i (i = 1, 2, 3) represent the fluid velocity components in the x(x1), y(x2), and z(x3) directions of the rectangular coordinate system, respectively; f iLet x(x1), y(x2), z(x3) be the fluid external forces in the Cartesian coordinate system; ρ be the air density; P be the pressure; ν be the dynamic viscosity of air, ν=μ / ρ; x(x1), y(x2), z(x3) are the three principal axes of the Cartesian coordinate system, respectively.

[0032] Reference symbols λ X Representing the model X m Same prototype X p The ratio, that is λ X =X m / X p ,in X m For model variables X The value, X p prototype variable X The values ​​of the variables are as follows: variables with the subscript 'm' are model variables, and variables with the subscript 'p' are prototype variables. λ t , λ l , λ u , λ f , λ v 、 λ ρ Let these be the ratios of time, geometry, velocity, additional external force, dynamic viscosity, and density, respectively, and all be constants; then the relationship between the physical quantities of the prototype and the model, and the equation of motion of the fluid, can be expressed by the following equation: t=λ t t m ，x i =λ l x im ，u i =λ u u im P=λ P P m f=λ f f m v=λ vv m , ρ=λ ρ ρ m ，

[0033] Multiply all terms in the above formula by λ l / λ u 2 have to:

[0034] To ensure the similarity of fluid motion between the prototype and the model, the ratio of physical quantities must satisfy the following:

[0035] Therefore, the dimensionless parameter of the fluid motion similarity criterion for aeroelastic wind tunnel tests of irregularly shaped tall structures is: Right now

[0036] Among them, S t The Stora number is the number of the flow. If the Stora numbers of two flows are equal, then the unsteady inertial forces of the fluids are similar; for periodic unsteady flows, it reflects their periodic similarity. Right now

[0037] Where Re is the Reynolds number; if the Reynolds numbers of the two flows are equal, then the viscous forces of the fluids are similar; for turbulent flows with a large Reynolds number, inertial forces play a dominant role, while viscous forces are relatively small; Right now

[0038] Where Fr is the Froude number; If the Froude numbers for the two flows are equal, it indicates that the gravitational forces acting on the flows are similar, reflecting the effect of gravity on the fluid; if the fluid experiences only gravity as a mass force, ... f=f m =g ,but, Right now

[0039] Where Eu is the Euler number.

[0040] According to some embodiments of the present invention, the stiffness equivalent section design method includes obtaining the bending and torsional bidirectional stiffness of the irregular tall structure based on composite section analysis, and obtaining the variational asymptotic equivalent section along the height of the aeroelastic model that meets the requirements of bidirectional scaled stiffness and centroid based on topology optimization equivalent section design.

[0041] Among them, the composite section analysis method can directly link the cross-sectional geometric dimensions and material performance parameters through analytical formulas, thereby achieving refined extraction of bidirectional stiffness, which can provide a high-precision benchmark for subsequent scaling conversion; the topology optimization equivalent section design takes the achievement of bidirectional scaling stiffness and centroid position matching as dual objective functions, and adopts a density-based topology optimization algorithm to optimize the material distribution in the design space. That is, through sensitivity analysis, the influence of local cross-sectional dimensions and component division method on stiffness and centroid is quantified, and the structural connectivity and morphology are iteratively adjusted. This ensures that the distribution law of model stiffness along the height is consistent with the prototype, and achieves precise alignment of cross-sectional centroid with the prototype, thereby solving the technical contradiction of difficulty in synchronizing stiffness and centroid in traditional design.

[0042] According to some embodiments of the present invention, such as Figure 2 As shown, step S3 includes: step S31, based on the composite section theory, performing a fine section analysis on the prototype structure to obtain the bending and torsional stiffness of the prototype structure; step S32, based on the similarity criterion, performing scale conversion on the stiffness and mass parameters of the prototype structure to obtain the target stiffness and mass distribution of the aeroelastic model; step S34, based on the target stiffness and mass distribution, iteratively adjusting the local dimensions of the section and the component division through the section topology optimization design method to obtain the variational asymptotic equivalent section of the aeroelastic model along the height.

[0043] Specifically, firstly, the variational progressive beam section method or composite section theory is used to perform a detailed section analysis on the prototype structure to obtain its bending and torsional stiffness. Then, based on the similarity criterion, the above stiffness and mass characteristics are scaled down to obtain the target stiffness and mass distribution of the aeroelastic model. Finally, with this as the objective, under the constraints of the model's shape, topology optimization technology is used for iterative design. That is, with the minimum stiffness error as the objective function and the target mass and centroid position as constraints, the internal material layout of the section is automatically optimized, thereby designing the variable stiffness equivalent section with the best stiffness characteristics under a given shape and mass.

[0044] Therefore, it can be understood that step S3 solves the technical pain point of difficulty in accurately reproducing the stiffness and mass of aeroelastic models of irregular tall structures through closed-loop logic of prototype accurate analysis, similar equivalent conversion and topology iteration optimization. This ensures the dynamic similarity between the model and the prototype, thereby ensuring the reliability and accuracy of subsequent wind tunnel test results and providing high-quality test data support for the wind-resistant design of the structure.

[0045] According to some embodiments of the present invention, such as Figure 1 As shown, step S4 includes: performing modal analysis on the scaled-down finite element model, comparing the natural frequencies and mode shapes of the scaled-down finite element model with the target values ​​of the full-scale finite element model, and confirming whether the errors of the frequencies or mode shapes meet the requirements; if yes, then confirm that the preset similarity conditions are met; if no, then re-determine the similarity ratio of the model according to the geometric scaling ratio and similarity criteria and re-select the printing material.

[0046] Specifically, firstly, based on the initial similarity criterion and equivalent cross-section design scheme, a scaled-down finite element model is established, and modal analysis is performed on it. The natural frequencies and mode shapes are compared with the target values ​​of the full-scale finite element model. If the frequency or mode shape errors meet the requirements, the preset similarity conditions are confirmed, and the next step of fabrication can proceed. If the errors do not meet the requirements, the process must return to the design stage, and the similarity criterion and equivalent cross-section design must be readjusted until the design parameters meet all similarity requirements. This further improves the accuracy of subsequent model fabrication, thereby enhancing the accuracy of wind tunnel testing.

[0047] According to some embodiments of the present invention, such as Figure 3 As shown, step S5 includes: step S51, preparing a physical scaled-down model using 3D printing technology; step S52, configuring counterweights in sections of the physical scaled-down model to achieve mass compensation, thereby obtaining an equivalent aeroelastic model. This ensures that the model's mass, moment of inertia, and dynamic characteristics all meet the error limits of the similarity criterion, ultimately achieving a high degree of fidelity in the dynamic characteristics of the prototype structure.

[0048] According to some embodiments of the present invention, such as Figure 4 As shown, step S6 includes: step S61, fixing the gas bullet model, verifying the dynamic characteristics of the gas bullet model through a hammer impact method, and confirming that the gas bullet model meets the dynamic similarity criterion; step S62, installing skin or surface treatment on the gas bullet model, and performing aerodynamic shape compensation on the gas bullet model to create a complete gas bullet model with an irregularly shaped, towering structure. The gas bullet model is fixed using a metal chassis, and the aerodynamic shape compensation includes attaching a roughening strip to the model surface.

[0049] Specifically, since the aerodynamic shape reproduction and assembly begin with the realization of boundary conditions, after printing the physical scaled-down model, the model is first fixed with a rigid metal base to simulate the actual constraints of the prototype. Then, the dynamic characteristics of the model are verified by the hammer impact method, which is a common method in the laboratory to quickly obtain dynamic characteristic parameters such as the natural frequency, mode shape, and damping ratio of the model. This confirms that the aeroelastic model meets the dynamic similarity criterion. After that, skinning or surface treatment is installed on the verified model to strictly ensure that its geometric shape is consistent with the scaled-down prototype. In addition, to compensate for the Reynolds number effect, a rough strip of a specific specification is precisely pasted in the key areas of surface flow separation according to the similarity criterion.

[0050] According to some embodiments of the present invention, such as Figure 1 As shown, the method further includes: step S7, verifying the fully aeroelastic model to confirm that the fully aeroelastic model can simultaneously meet the target requirements of aerodynamic and structural dynamic similarity in wind tunnel testing. The verification method includes: performing a three-dimensional scan and weighing of the fully aeroelastic model to confirm that the aerodynamic shape of the fully aeroelastic model meets the preset requirements and that the total mass parameters of the fully aeroelastic model meet the preset values.

[0051] In other words, after all components are installed, the assembled complete aeroelastic model is subjected to a three-dimensional scan and final weighing to verify the accuracy of its aerodynamic shape and total mass. This ensures that the aerodynamic shape of the complete aeroelastic model meets the preset requirements and that the total mass parameters of the complete aeroelastic model meet the preset values. This ensures that the model can simultaneously meet all the requirements for aerodynamic and structural dynamic similarity in wind tunnel tests, thereby improving the accuracy of wind tunnel implementation.

[0052] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," and "circumferential" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0053] 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 one or more of that feature. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified.

[0054] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection, an electrical connection, or a communication connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0055] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. 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.

[0056] Although embodiments of the invention have been shown and described, those skilled in the art will understand that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.

Claims

1. A method for making a full aeroelastic model of a complex high-rise structure, characterized in that, The method comprises: Step S1, determining a geometric scale ratio based on prototype parameter extraction and modal analysis and test conditions; Step S2, determining a similarity ratio of the model and selecting a printing material according to the geometric scale ratio and similarity criteria; Step S3, obtaining a variational asymptotic equivalent section of the aeroelastic model along a height according to the similarity criteria and a cross-section stiffness equivalent design method; Step S4, establishing a scaled finite element model, comparing frequencies and vibration modes of the scaled finite element model and a full-scale finite element model, and confirming that the scaled finite element model meets preset similarity conditions; Step S5, preparing an equivalent aeroelastic model through 3D printing technology; Step S6, fixing the aeroelastic model and performing aerodynamic shape compensation to produce a complete aeroelastic model of the special-shaped high-rise structure.

2. The method of claim 1, wherein the method further comprises: The similarity ratio comprises a wind speed ratio, a time ratio and a frequency ratio derived according to fluid motion similarity, a density ratio and a damping ratio required according to the same dimensionless parameter, and a mass ratio and a stiffness ratio derived according to structure motion similarity.

3. The method of claim 1, wherein the method further comprises: The stiffness equivalent section design method comprises obtaining bending and torsional bidirectional stiffness of the special-shaped high-rise structure based on composite section analysis, and obtaining a variational asymptotic equivalent section of the aeroelastic model along the height which meets bidirectional scaled stiffness and centroid requirements through a topological optimization equivalent section design.

4. The method of claim 3, wherein the method further comprises: The step S3 comprises: Step S31, performing fine section analysis on the prototype structure based on composite section theory to obtain bending and torsional stiffness of the prototype structure; Step S32, performing scaled conversion on stiffness and mass parameters of the prototype structure based on the similarity criteria to obtain target stiffness and mass distribution of the aeroelastic model; Step S34, iteratively adjusting local section sizes and component division through a section topological optimization design method based on the target stiffness and the mass distribution to obtain a variational asymptotic equivalent section of the aeroelastic model along the height.

5. The method of claim 1, wherein the method further comprises: The step S4 comprises: Performing modal analysis on the scaled finite element model, comparing inherent frequencies and vibration modes of the scaled finite element model with target values of the full-scale finite element model, and confirming whether errors of the frequencies or the vibration modes meet requirements; If yes, it is confirmed that the preset similarity conditions are met; If no, the similarity ratio of the model is determined again and the printing material is selected again according to the geometric scale ratio and the similarity criteria.

6. The method of claim 1, wherein the method further comprises: The step S5 comprises: Step S51, preparing a physical scaled model through 3D printing technology; Step S52, achieving mass compensation by segmentally configuring counterweights on the physical scaled model to obtain an equivalent aeroelastic model.

7. The method of claim 1, wherein the method further comprises: The step S6 comprises: Step S61, fixing the aeroelastic model, verifying dynamic characteristics of the aeroelastic model through a hammering method, and confirming that the aeroelastic model meets dynamic similarity criteria; Step S62, installing a skin or surface treating the aeroelastic model, and performing aerodynamic shape compensation on the aeroelastic model to produce a complete aeroelastic model of the special-shaped high-rise structure.

8. The method of claim 7, wherein the method further comprises: The aeroelastic model is fixed through a metal base plate, and the aerodynamic shape compensation comprises pasting rough tapes on a surface of the model.

9. The method of claim 1, wherein the method further comprises: Further comprising: Step S7, verifying the complete aeroelastic model, and confirming that the complete aeroelastic model can meet target requirements of aerodynamic and structural dynamic similarity in a wind tunnel test.

10. The method of claim 9, wherein the method further comprises: The method for checking includes: performing three-dimensional scanning and weighing on the complete aeroelastic model to confirm that the aerodynamic shape of the complete aeroelastic model meets preset requirements and the total mass parameter of the complete aeroelastic model meets a preset value.

Images