Synchronous force and vibration measurement dual-mode narrow-band aeroelastic model and design method

Abstract

The invention discloses a synchronous force and vibration measurement dual-mode narrow-band aeroelastic model and a design method. The synchronous force and vibration measurement dual-mode narrow-band aeroelastic model has the characteristics that the cross section size is large, the longitudinal size is small, vibration and force measurement tests can be synchronously carried out, the synchronous force and vibration measurement dual-mode narrow-band aeroelastic model is suitable for various vibration modes, and two-order vertical bending modes can be synchronously simulated. The model comprises a core beam, a diaphragm beam, an end plate, an end constraint rigid test section coat narrow band, a rigid compensation section coat narrow band, an elastic support, a concentrated mass point, a force measurement sensor and a response measurement system, and a test section coat is connected with the core beam through the force measurement sensor to achieve the purpose of internally arranging the force measurement sensor, so that the inertia force is reduced; an equivalent theory is deduced, so that different scale ratios can be adopted in the longitudinal direction and the transverse direction, and the cross section size and the aerodynamic force on the section of the model can be improved; a rigid coat narrow band is adopted, inertia force is reduced, and meanwhile force and response signals at all longitudinal positions can be collected easily; in the design, a target vibration mode function is directly fitted, so that the model is suitable for various vibration mode forms.

Description

Technical Field

[0001] The present invention relates to the technical field of aerodynamics, and particularly relates to a synchronous force measurement and vibration measurement dual-mode narrowband aeroelastic model and a design method thereof. Background Art

[0002] In the field of structural wind engineering, there is an overlap phenomenon of wind speed lock-in regions during the prediction of high-order mode vortex-induced vibrations of slender flexible structures. Simulating the dual-mode vortex-induced vibration phenomenon in the overlapping region and completing synchronous force measurement and vibration measurement are the keys to exploring the mechanism and discrimination criteria of vortex-induced vibration in the overlapping region. Therefore, wind tunnel tests are required to study it.

[0003] In wind tunnel tests, although the full-scale aeroelastic model can simulate more natural modes, it is limited by the size of the wind tunnel test section. Usually, the geometric scale ratio is relatively small, which leads to the model being unable to accurately simulate the structural details, and the too-small size is not suitable for direct force measurement. Using a larger scale ratio often results in an overly large longitudinal dimension of the model, making it difficult to meet the test requirements in the longitudinal direction of the wind tunnel test section. Simplifying the structural vibration mode to a harmonic form can only simulate a small number of harmonic vibration mode shapes. In addition, in the existing aeroelastic model design, an integral outer skin is usually adopted, which is mainly suitable for vibration measurement tests. When performing force measurement tests, it will cause excessive inertial forces, thus failing to meet the test accuracy requirements. Summary of the Invention

[0004] The purpose of the present invention is to provide a synchronous force measurement and vibration measurement dual-mode narrowband aeroelastic model and a design method thereof, so as to solve one or more technical problems existing in the prior art, and at least provide a beneficial alternative or creative condition.

[0005] The technical solutions adopted to solve the above technical problems are as follows:

[0006] The present invention provides a design method for a synchronous force measurement and vibration measurement dual-mode narrowband aeroelastic model, including the following steps:

[0007] Step 1: Analyze the characteristics of the target structure, and equivalent it into a two-point elastic support structure, including a core beam, lumped mass points, elastic supports, and end constraints. Determine the constraint form and the relative position of the elastic supports according to the test conditions and the characteristics of the target structure;

[0008] Step 2: Suggest a finite element model according to the characteristics of the target structure and perform modal analysis to extract the modal mass m p-r * of each order of the target structure, the equivalent mass m p-r of the core beam, the modal frequency f p-r and the modal vibration mode φ p-r , where P represents the target structure and r represents the order;

[0009] Step 3: According to the requirements of wind tunnel tests, similarity principles, and equivalence theory, first perform overall geometric scaling on the finite element model of the target structure in a ratio of 1:n 1 ; on the premise of meeting equivalence and similarity, based on the overall geometric scaling, then perform local geometric scaling in a ratio of 1:n longitudinally 2 and n:1 transversely 2 to determine the final scaling ratio, where the final scaling ratio includes: longitudinal geometric scaling ratio λ L-lengthways , transverse geometric scaling ratio λ L-crosswise , frequency scaling ratio λ f , equivalent mass scaling ratio λ m , modal mass scaling ratio wind speed ratio λ v , modal vibration mode scaling ratio λ φ ;

[0010] Step 4: Extract the modal mass m p-r * , equivalent mass m of the core beam p-r , modal frequency f p-r and modal vibration mode φ p-r of each order from the finite element model of the target structure and the final scaling ratio, and calculate the equivalent mass m m2-r , modal mass modal frequency f m2-r , modal vibration mode φ m2-r , modal stiffness of each order of the narrowband aeroelastic model, where the modal stiffness is determined by the modal frequency and modal mass:

[0011] Step 5: According to the principle of continuous vibration mechanics, the equivalent mass m m2-r , modal mass modal frequency f m2-r , modal vibration mode φ m2-r , modal stiffness of each order of the narrowband aeroelastic model, the constraint form, and the relative position of the elastic support, calculate the target design parameters of the synchronous force-measuring and vibration-measuring dual-modal narrowband aeroelastic model, where the target design parameters include the target stiffness EI of the core beam, the target stiffness k i of the elastic support, the target distributed mass ρA of the core beam, and the target concentrated mass m i ; if any negative numbers appear among the four target design parameters, it is necessary to adjust the relative position of the elastic support so that all calculated values are positive;

[0012] Step 6: Design the geometric and material parameters of each component of the synchronous force-measuring and vibration-measuring dual-modal narrowband aeroelastic model according to the target design parameters, including the core beam, diaphragm beam, end plates, end constraints, outer narrowband of the rigid test section, outer narrowband of the rigid compensation section, elastic supports, concentrated mass points, force sensors, material parameters and structural forms of the response measurement system.

[0013] The beneficial effects of the present invention are:

[0014] The design method of the synchronous force-measuring and vibration-measuring dual-modal narrowband aeroelastic model capable of simulating dual vertical bending modes according to the present invention can, compared with the traditional sectional model that can only simultaneously complete the force measurement and vibration measurement of the modal vibrations of the first-order vertical bending and torsion, simultaneously complete the force measurement and vibration measurement tests of the two-order vertical bending modes; by adopting local geometric scaling in the longitudinal and transverse directions, compared with the conventional aeroelastic model, the span can be further scaled by n times, while the transverse dimension is enlarged by n times, avoiding the defect that the conventional aeroelastic model cannot measure the force due to the too small transverse scaling ratio. Therefore, the model of the present invention can simultaneously complete the force measurement and vibration measurement tests, and has practical operation for the vortex-induced vibration wind tunnel test.

[0015] As a further improvement of the above technical solution, Step 6 further includes:

[0016] Select the material of the core beam frame according to the target design parameters determined in Step 5 and the final scaling ratio, and determine its elastic modulus and density according to the selected material;

[0017] Calculate the theoretical value of the moment of inertia and the theoretical value of the area of the core beam section according to the target design parameters determined in Step 5;

[0018] Select the corresponding section form based on the theoretical value of the moment of inertia, the theoretical value of the area and the test structure requirements, and determine the design value of the moment of inertia and the design value of the area;

[0019] Establish a finite element model according to the determined elastic modulus, density, model parameters, design value of the moment of inertia and design value of the area for modal analysis and calculate the actual equivalent mass, modal mass, modal frequency, modal vibration mode, modal stiffness of each order of the target model, and compare with the equivalent mass m of each order of the narrowband aeroelastic model obtained in Step 5 m2-r modal mass modal frequency f m2-r modal vibration mode φ m2-r modal stiffness for comparison to determine whether the model design is completed.

[0020] As a further improvement of the above technical solution, a finite element model is established according to the determined elastic modulus, density, model parameters, designed value of section moment of inertia, and designed value of area for modal analysis, and the actual equivalent mass, modal mass, modal frequency, modal vibration mode, and modal stiffness of each order of the target model are calculated, and compared with the equivalent mass m of each order of the narrowband aeroelastic model obtained in step five m2-r modal mass modal frequency f m2-r modal vibration mode φ m2-r modal stiffness The steps for comparing and judging whether the model design is completed further include:

[0021] Judging according to three judgment criteria: judging whether the frequency deviation is less than the threshold, whether the equivalent mass deviation is less than the threshold, and whether the vibration modes are consistent;

[0022] If the deviations of all three judgment criteria are less than the threshold, the model design is completed;

[0023] In case there is a deviation greater than the threshold, adjust and check the deviation situation in turn according to the following five adjustment schemes: 1. Keep the designed value of area unchanged and adjust the designed value of moment of inertia; 2. Keep the designed value of moment of inertia unchanged and adjust the designed value of area; 3. Keep the elastic support value unchanged and adjust the concentrated mass value; 4. Keep the concentrated mass value unchanged and adjust the elastic support value; 5. Re-select the material;

[0024] After each adjustment, perform modal analysis to obtain the actual equivalent mass, modal mass, modal frequency, modal vibration mode, and modal stiffness of each order of the adjusted target model, and compare them with the equivalent mass m of each order of the narrowband aeroelastic model obtained in step five m2-r modal mass modal frequency f m2-r modal vibration mode φ m2-r modal stiffness for comparison, and judge according to three judgment criteria: judging whether the frequency deviation is less than the threshold, whether the equivalent mass deviation is less than the threshold, and whether the vibration modes are consistent;

[0025] Perform cyclic adjustment according to the adjustment scheme and deviation evaluation method until the deviations of all three judgment criteria are less than the threshold, then the model design is completed.

[0026] As a further improvement of the above technical solution, in step one, the target structure is equivalent to a two-point elastic support structure, the model end constraint form corresponds to the target structure, and the mass of the target structure includes the distributed mass of the core beam of the two-point elastic support structure and the simulation of concentrated mass points, and the stiffness is mainly simulated by the core beam stiffness and elastic support.

[0027] As a further improvement of the above technical solution, in step 3, two-scale-down operations are carried out according to the similarity principle, equivalent theory and test requirements. The first is the overall geometric scale-down (Full Geometry Scale), and the second is the local geometric scale-down (Part Geometry Scale) in the longitudinal and transverse directions to meet the test requirements. Note: The subscript m1 (model1) represents the model parameters after geometric scale-down, the subscript m2 (model2) represents the model parameters after local geometric scale-down, and the subscript p (prototype) represents the real bridge parameters. Determine the geometric scale ratio (1:n 1 ), select an appropriate wind speed ratio (1:n v ). The process of overall geometric scale-down is as follows:

[0028] (1) Geometric similarity:

[0029]

[0030] (2) Equivalent mass similarity:

[0031]

[0032] (3) Modal mass similarity:

[0033]

[0034] (4) Select the wind speed ratio according to the test conditions:

[0035]

[0036] (5) Frequency similarity:

[0037]

[0038] (6) Mode shape similarity:

[0039] φ m1-r =φ p-r (6)

[0040] Results of overall geometric scale-down:

[0041]

[0042] To meet the test requirements, on the basis of the overall geometric scale-down, local geometric scale-down is carried out in the longitudinal direction at 1:n 2 , and in the transverse direction at n 2 :1. The purpose of local geometric scale-down is to further reduce the longitudinal length of the model:

[0043] (1) Longitudinal scale-down:

[0044]

[0045] (2) The total mass remains unchanged, so the equivalent mass scaling ratio:

[0046]

[0047] (3) The modal mass remains consistent:

[0048]

[0049] (4) According to the similarity of lift, the lateral scaling:

[0050]

[0051] (5) The longitudinal scaling ratio is L m2 = γL m1 , then the lateral scaling is:

[0052]

[0053] (6) Frequency similarity: Ensure the same frequency by adjusting the distributed stiffness and the support stiffness;

[0054] (7) Wind speed similarity:

[0055]

[0056] (8) Mode shape similarity:

[0057]

[0058] Local geometric scaling result:

[0059]

[0060] As a further improvement of the above technical solution, according to the principle of continuous vibration mechanics, calculate the target stiffness EI of the core beam, the target stiffness k of the elastic support i , the target distributed mass ρA of the core beam and the target concentrated mass m i during the calculation, fit the mode shape data to obtain the mode shape function, and the parameters of the aeroelastic model are calculated as follows:

[0061]

[0062] As a further improvement of the above technical solution, in the sixth step, it further includes a force sensor for measuring the inertial force of the outer narrow band of the rigid test section, and the force sensor is installed between the core beam and the outer narrow band of the rigid test section.

[0063] As a further improvement of the above technical solution, in the sixth step, a diaphragm beam is provided at the central position of the narrow-band outer covering of each rigid test section and the narrow-band outer covering of the rigid compensation section, and at the position of the elastic support point.

[0064] As a further improvement of the above technical solution, in the sixth step, the concentrated mass is arranged at the position of the elastic support point.

[0065] The present invention also provides a synchronous force-measuring and vibration-measuring dual-mode narrow-band aeroelastic model, including a core beam frame and a support structure. The core beam frame includes two core beams and a plurality of diaphragm beams. The two core beams are arranged side by side, and the plurality of diaphragm beams are connected between the two core beams at intervals along the extending direction of the core beams. The core beam frame is provided with a plurality of narrow-band outer covering sections arranged at intervals along the extending direction of the core beams. The outer sides of the narrow-band outer covering sections are all wrapped with narrow-band outer coverings. The plurality of narrow-band outer covering sections include a plurality of rigid compensation sections and a plurality of rigid test sections. The rigid test sections are distributed between two adjacent rigid compensation sections; the support structure includes two end supports and at least two elastic supports. The two end supports are respectively connected to the two ends of the core beam. At least two elastic supports are arranged at intervals between the two end supports along the extending direction of the core beam. At least two elastic supports are respectively arranged between any two of the rigid compensation sections, and the elastic supports are connected to the core beam frame. Description of the Drawings

[0066] The following further describes the present invention with reference to the drawings and embodiments;

[0067] Figure 1 is a schematic structural diagram of a synchronous force-measuring and vibration-measuring dual-mode narrow-band aeroelastic model described in the embodiment;

[0068] Figure 2 is a cross-sectional view of the outer covering of the compensation section of a synchronous force-measuring and vibration-measuring dual-mode narrow-band aeroelastic model described in the embodiment;

[0069] Figure 3 is a cross-sectional view of the outer covering of the test section of a synchronous force-measuring and vibration-measuring dual-mode narrow-band aeroelastic model described in the embodiment;

[0070] Figure 4 is an elevation view of a synchronous force-measuring and vibration-measuring dual-mode narrow-band aeroelastic model described in the embodiment;

[0071] Figure 5 is a plan view of a synchronous force-measuring and vibration-measuring dual-mode narrow-band aeroelastic model described in the embodiment;

[0072] Figure 6 is a cross-sectional view of the position of the diaphragm beam of the outer covering of the test section of a synchronous force-measuring and vibration-measuring dual-mode narrow-band aeroelastic model described in the embodiment;

[0073] Figure 7 It is a cross diaphragm beam of the outer cover of the test section of a synchronous force measurement and vibration measurement dual - mode narrow - band aeroelastic model described in the embodiment.

[0074] Schematic cross - sectional view of the position;

[0075] Figure 8 It is a schematic cross - sectional view of the position of the cross diaphragm beam of the outer cover of the compensation section of a synchronous force measurement and vibration measurement dual - mode narrow - band aeroelastic model described in the embodiment;

[0076] Figure 9 It is a schematic cross - sectional view of the position of the non - cross diaphragm beam of the outer cover of the compensation section of a synchronous force measurement and vibration measurement dual - mode narrow - band aeroelastic model described in the embodiment;

[0077] Figure 10 It is a flowchart of the design method of a synchronous force measurement and vibration measurement dual - mode narrow - band aeroelastic model described in the embodiment. Detailed implementation manners

[0078] This part will describe in detail the specific embodiments of the present invention. The preferred embodiments of the present invention are shown in the drawings. The function of the drawings is to supplement the description of the text part of the specification, enabling people to intuitively and vividly understand each technical feature and the overall technical solution of the present invention. However, it should not be construed as a limitation on the protection scope of the present invention.

[0079] In the description of the present invention, it should be understood that for the orientation description, such as the orientation or positional relationship indicated by up, down, front, back, left, right, etc., is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation on the present invention.

[0080] In the description of the present invention, if there are descriptions with words such as "several", its meaning is one or more, and the meaning of multiple is more than two. Understanding greater than, less than, exceeding, etc. does not include the present number, and understanding above, below, within, etc. includes the present number.

[0081] In the description of the present invention, unless otherwise clearly defined, words such as setting, installation, connection, etc. should be understood in a broad sense. Those skilled in the art can reasonably determine the specific meanings of the above words in the present invention in combination with the specific content of the technical solution.

[0082] Referring to Figures 1 to 10 , the following embodiments are made for a synchronous force measurement and vibration measurement dual - mode narrow - band aeroelastic model and its design method of the present invention:

[0083] Design method of synchronous force-measuring and vibration-measuring dual-mode narrow-band aeroelastic model, comprising the following steps:

[0084] Step 1: Analyze the characteristics of the target structure, and equivalent it into a two-point elastic support structure, including a core beam 1, a concentrated mass point 8, an elastic support 7 and an end constraint 4, and determine the constraint form and the relative position of the elastic support 7 according to the test conditions and the characteristics of the target structure;

[0085] Step 1 further includes: Equivalent the target structure into a two-point elastic support structure, the end constraint form of the model corresponds to that of the target structure, the mass of the target structure is simulated by the distributed mass of the core beam 1 and the concentrated mass point 8 of the two-point elastic support structure, and the stiffness is simulated by the core beam stiffness and the elastic support 7.

[0086] Step 2: Establish a finite element model according to the characteristics of the target structure and perform modal analysis, and extract the modal mass m p-r * of each order of the target structure, the equivalent mass m p-r of the core beam, the modal frequency f p-r and the modal vibration mode φ p-r , where P represents the target structure and r represents the order number;

[0087] Step 3: According to the requirements of the wind tunnel test, the similarity principle and the equivalent theory, first perform overall geometric scaling on the finite element model of the target structure according to 1:n 1 ; on the premise of meeting the equivalence and similarity, then perform local geometric scaling according to 1:n 2 in the longitudinal direction and n 2 :1 in the transverse direction on the basis of the overall geometric scaling to determine the final scaling ratio, and the final scaling ratio includes: longitudinal geometric scaling ratio λ L-lengthways , transverse geometric scaling ratio λ L-crosswise , frequency scaling ratio λ f , equivalent mass scaling ratio λ m , modal mass scaling ratio λ m* , wind speed ratio λ v , modal vibration mode scaling ratio λ φ .

[0088] According to the requirements of the wind tunnel test, the similarity principle and the equivalent theory, first perform overall geometric scaling according to 1:n 1 , and then on the premise of meeting the equivalence and similarity, perform local geometric scaling according to 1:n 2 in the longitudinal direction and n 2 :1 in the transverse direction to obtain the scaling ratio: longitudinal geometric scaling ratio λ L-lengthways , transverse geometric scaling ratio λ L-crosswise , frequency scaling ratio λ f , equivalent mass scaling ratio λ m , modal mass scaling ratio λm* 、Wind speed ratio λ v 、Modal vibration mode scaling ratio λ φ 。

[0089] According to the similarity principle, equivalent theory and test requirements, two scalings are carried out. The first is overall geometric scaling (Full Geometry Scale), and the second is local geometric scaling (Part Geometry Scale) for the longitudinal and transverse directions to meet the test requirements. Note: The subscript m1 (model1) represents the model parameters after geometric scaling, the subscript m2 (model2) represents the model parameters after local geometric scaling, and the subscript p (prototype) represents the real bridge parameters. Determine the geometric scaling ratio (1:n 1 ), select an appropriate wind speed ratio (1:n v ). The overall geometric scaling process is as follows:

[0090] (1) Geometric similarity:

[0091]

[0092] (2) Equivalent mass similarity:

[0093]

[0094] (3) Modal mass similarity:

[0095]

[0096] (4) Select the wind speed ratio according to the test conditions:

[0097]

[0098] (5) Frequency similarity:

[0099]

[0100] (6) Vibration mode similarity:

[0101] φ m1-r =φ p-r (6)

[0102] Overall geometric scaling result:

[0103]

[0104] To meet the test requirements, based on the overall geometric scaling, local geometric scaling is carried out in the longitudinal direction at 1:n 2 , and in the transverse direction at n 2 :1. The purpose of local geometric scaling is to further reduce the longitudinal length of the model:

[0105] (1) Longitudinal scale factor:

[0106]

[0107] (2) If the total mass remains unchanged, then the equivalent mass scale ratio:

[0108]

[0109] (3) Modal mass remains consistent:

[0110]

[0111] (4) According to the similarity of lift, then the lateral scale:

[0112]

[0113] (5) The longitudinal scale ratio is L m2 = γL m1 , then the lateral scale is:

[0114]

[0115] (6) Frequency similarity: Ensure the same frequency by adjusting the distributed stiffness and support stiffness;

[0116] (7) Wind speed similarity:

[0117]

[0118] (8) Mode shape similarity:

[0119]

[0120] Local geometric scale results:

[0121]

[0122] Step 4: Extract the modal mass m p-r * of each order, the equivalent mass m p-r of the core beam (1), the modal frequency f p-r and the modal mode shape φ p-r and the final scale ratio, and calculate the equivalent mass m m2-r of each order, the modal mass the modal frequency f m2-r the modal mode shape φ m2-r the modal stiffness where the modal stiffness is determined by the modal frequency and modal mass:

[0123] Step Five: According to the principle of continuous vibration mechanics, the equivalent mass m of each order of the narrowband aeroelastic model m2-r , modal mass modal frequency f m2-r , modal vibration mode φ m2-r , modal stiffness constraint form and the relative position of the elastic support 7, calculate the target design parameters of the synchronous force-measuring and vibration-measuring dual-modal narrowband aeroelastic model, and the target design parameters include the core beam target stiffness EI, the elastic support target stiffness k i , the core beam target distributed mass ρA and the target concentrated mass m i . If negative numbers appear among the four target design parameters, the relative position of the elastic support 7 needs to be adjusted so that all calculated values are positive;

[0124] Specifically, it further includes: According to the principle of continuous vibration mechanics and the model modal parameters obtained in Step Four, calculate the core beam target stiffness EI, the elastic support target stiffness k i , the core beam target distributed mass ρA and the target concentrated mass m i of a synchronous force-measuring and vibration-measuring dual-modal narrowband aeroelastic model; When calculating, consider the model as a single main beam plus elastic support 7 model, with two concentrated mass points 8 distributed on the main beam, and the two elastic support 7 suspension points at the positions of the concentrated mass points 8. The whole is completely symmetrical, so the concentrated mass and the stiffness of the elastic support 7 are the same. Finally, the model uses a double main beam, and the two core beams 1 are in parallel. Then the stiffness, distributed mass, concentrated mass point 8 and the stiffness of the elastic support 7 of a single core beam 1 are half of the calculated values of the single main beam model; among them, the vibration mode function directly fits the vibration mode data of the real bridge modal analysis and is applicable to all forms of vibration modes:

[0125]

[0126] Step Six: Design the geometric and material parameters of each component of the synchronous force-measuring and vibration-measuring dual-modal narrowband aeroelastic model according to the target design parameters, including the material parameters and structural forms of the core beam 1, diaphragm beam 2, end plate 3, end constraint 4, rigid test section outer narrowband 5, rigid compensation section outer narrowband 6, elastic support 7, concentrated mass point 8, force sensor 9, and response measurement system 10.

[0127] Refer to Figure 10 , Step Six also includes:

[0128] Select the material of the core beam 1 frame according to the target design parameters determined in Step Five and the final scale ratio, and determine its elastic modulus and density according to the selected material;

[0129] Calculate the theoretical value of the cross-sectional moment of inertia and the theoretical value of the area of the core beam 1 according to the target design parameters determined in Step Five;

[0130] Select the corresponding cross-section form according to the theoretical values of the cross-section moment of inertia, the theoretical value of the area, and the test structure requirements, and determine the design values of the cross-section moment of inertia and the area design value;

[0131] Establish a finite element model according to the determined elastic modulus, density, model parameters, design value of the cross-section moment of inertia, and area design value for modal analysis, and calculate the actual equivalent mass, modal mass, modal frequency, modal vibration mode, and modal stiffness of each order of the target model, and compare them with the equivalent mass m of each order of the narrowband aeroelastic model obtained in step five m2-r and modal mass modal frequency f m2-r and modal vibration mode φ m2-r and modal stiffness Make a comparison judgment to determine whether the model design is completed. Specifically, it also includes:

[0132] Make a judgment according to three judgment criteria: judge whether the frequency deviation is less than the threshold, whether the equivalent mass deviation is less than the threshold, and whether the vibration modes are consistent;

[0133] If the deviations of all three judgment criteria are less than the threshold, the model design is completed;

[0134] If there is a situation where the deviation is greater than the threshold, adjust and check the deviation situation in turn according to the following five adjustment schemes: 1. Keep the area design value unchanged and adjust the moment of inertia design value; 2. Keep the moment of inertia design value unchanged and adjust the area design value; 3. Keep the elastic support value unchanged and adjust the concentrated mass value; 4. Keep the concentrated mass value unchanged and adjust the elastic support value; 5. Re-select the material;

[0135] After each adjustment, perform modal analysis to obtain the actual equivalent mass, modal mass, modal frequency, modal vibration mode, and modal stiffness of each order of the adjusted target model, and compare them with the equivalent mass m of each order of the narrowband aeroelastic model obtained in step five m2-r and modal mass modal frequency f m2-r and modal vibration mode φ m2-r and modal stiffness Make a comparison, and make a judgment according to three judgment criteria: judge whether the frequency deviation is less than the threshold, whether the equivalent mass deviation is less than the threshold, and whether the vibration modes are consistent;

[0136] Perform cyclic adjustment according to the adjustment scheme and deviation evaluation method until the deviations of all three judgment criteria are less than the threshold, then the model design is completed.

[0137] The more specific adjustment scheme adjustment process includes:

[0138] Judgment is made according to three judgment criteria: whether the frequency deviation is less than the threshold, whether the equivalent mass deviation is less than the threshold, and whether the vibration modes are consistent;

[0139] If the deviations are all less than the threshold, the model design is completed;

[0140] If there is a situation where the deviation is greater than the threshold, first ensure that the area design value remains unchanged and adjust the moment of inertia design value;

[0141] After adjustment, modal analysis is carried out to obtain the actual equivalent mass, modal mass, modal frequency, modal vibration mode, and modal stiffness of each order of the adjusted target model, and compare them with the equivalent mass m of each order of the narrowband aeroelastic model obtained in step five respectively m2-r modal mass modal frequency f m2-r modal vibration mode φ m2-r modal stiffness and make a comparison, and judge according to three judgment criteria: whether the frequency deviation is less than the threshold, whether the equivalent mass deviation is less than the threshold, and whether the vibration modes are consistent;

[0142] If the deviations of the three judgment criteria are all less than the threshold, the model design is completed.

[0143] If there is a situation where the deviation is greater than the threshold, ensure that the moment of inertia design value remains unchanged and adjust the area design value;

[0144] After adjustment, modal analysis is carried out to obtain the actual equivalent mass, modal mass, modal frequency, modal vibration mode, and modal stiffness of each order of the adjusted target model, and compare them with the equivalent mass m of each order of the narrowband aeroelastic model obtained in step five respectively m2-r modal mass modal frequency f m2-r modal vibration mode φ m2-r modal stiffness and make a comparison, and judge according to three judgment criteria: whether the frequency deviation is less than the threshold, whether the equivalent mass deviation is less than the threshold, and whether the vibration modes are consistent;

[0145] If the deviations of the three judgment criteria are all less than the threshold, the model design is completed.

[0146] After adjustment, modal analysis is carried out to obtain the actual equivalent mass, modal mass, modal frequency, modal vibration mode, and modal stiffness of each order of the adjusted target model, and compare them with the equivalent mass m of each order of the narrowband aeroelastic model obtained in step five respectively m2-r modal mass modal frequency f m2-r modal vibration mode φ m2-r modal stiffness Make a comparison and judge according to three judgment criteria: judge whether the frequency deviation is less than the threshold, whether the equivalent mass deviation is less than the threshold, and whether the vibration modes are consistent;

[0147] Judge the three conditions. If all meet the threshold, the model design is completed;

[0148] If there is a situation where the deviation is greater than the threshold, ensure that the lumped mass value remains unchanged and adjust the elastic support value;

[0149] After adjustment, perform modal analysis to obtain the actual equivalent mass, modal mass, modal frequency, modal vibration mode, and modal stiffness of each order of the adjusted target model, and compare them with the equivalent mass m of each order of the narrowband aeroelastic model obtained in step five respectively m2-r and modal mass modal frequency f m2-r modal vibration mode φ m2-r and modal stiffness Make a comparison and judge according to three judgment criteria: judge whether the frequency deviation is less than the threshold, whether the equivalent mass deviation is less than the threshold, and whether the vibration modes are consistent;

[0150] If the deviations of all three judgment criteria are less than the threshold, the model design is completed.

[0151] If there is still a situation where the deviation is greater than the threshold, reselect the material for design, that is, reselect the density and elastic modulus.

[0152] Specifically, according to the scale ratio, since the model is scaled down twice and the cross-sectional scale ratio is greater than the longitudinal scale ratio, using a double-core beam is beneficial to the stability of the model. The two core beams are connected by cross diaphragms to form a frame structure.

[0153] According to the target stiffness EI of the core beam, the target stiffness k of the elastic support i , the target distributed mass ρA of the core beam and the target lumped mass m i ; and the scale ratio, select steel or aluminum as the material of core beam 1. If steel is selected as the material of core beam 1, further obtain the cross-sectional dimension parameters of core beam 1 according to the model target value. In order to ensure that the balance can be stably installed on core beam 1, core beam 1 needs to be designed in a flat shape. If the cross-section of steel core beam 1 is smaller than the size of the balance base under the condition of meeting the model target value, the material of core beam 1 can be selected as aluminum, and further obtain the cross-sectional dimension parameters of core beam 1 according to the model target value. The size of the balance needs to be taken into account, and core beam 1 is selected as a flat shape. The balance can be understood as a kind of force measuring sensor.

[0154] Refer to Figure 1 、 Figure 2 、 Figure 3 and Figure 5The specific structure of the dual-mode narrow-band aeroelastic model for synchronous force and vibration measurement includes a core beam frame and an end support structure.

[0155] The core beam frame includes two core beams 1 and a plurality of transverse beams 2. The two core beams 1 are arranged side by side. The plurality of transverse beams 2 are connected between the two core beams 1 at intervals along the direction in which the core beams 1 extend. The core beam frame is provided with a plurality of outer garment narrow band sections arranged at intervals along the direction in which the core beams 1 extend. The outer sides of the outer garment narrow band sections are all wrapped with outer garment narrow bands. The plurality of outer garment narrow band sections include a plurality of rigid compensation sections and a plurality of rigid test sections. The rigid test sections are distributed between two adjacent rigid compensation sections. For ease of understanding, the rigid compensation sections are also referred to as rigid compensation section outer garment narrow bands 6 in this embodiment, and the rigid test sections are also referred to as rigid test section outer garment narrow bands 5 in this embodiment. The model outer garment adopts the form of a rigid narrow band to ensure that the test section has sufficient rigidity. While reducing the inertial force, it is also helpful to collect the force and response signals at various longitudinal positions, which is convenient for force measurement and has good practicality in wind tunnel tests.

[0156] Specifically, the outer garment narrow belt comprises a light and rigid outer skin and a light frame, wherein the light and rigid outer skin is arranged on the light frame, Figure 6 and Figure 7 The outer garment narrow belt of the rigid test section is integrally formed, a core beam frame groove is arranged at the center of the outer garment narrow belt, and the core beam frame passes through the core beam frame groove;

[0157] Reference Figure 8 and Figure 9 The outer narrow band of the rigid compensation section includes a first wrapping band and a second wrapping band covering each other. The first wrapping band and the second wrapping band are respectively arranged on both sides of the core beam frame, and the first wrapping band and the second wrapping band are detachably connected. During installation, separate the upper and lower first wrapping bands and the second wrapping bands, buckle them on the upper and lower sides of the core beam frame respectively, and then connect with bolts. The cross beam 2 is designed with the same material as the core beam 1, which is convenient for welding. The outer narrow band of the rigid compensation section is symmetrically provided with two counterweight grooves, and a counterweight plate 11 is provided in the counterweight groove, which can be made of aluminum plate;

[0158] The rigid test section is provided with two groups of force sensors 9, which are arranged between the core beam 1 and the outer garment narrow belt. By means of the built-in force sensor 9, the rigid outer garment narrow belt is connected to the core beam 1 through the force measurement system to avoid the inertial force of the whole model affecting the accuracy of force measurement;

[0159] The support structure includes two end supports and at least two elastic supports, the two end supports are respectively connected to the two ends of the core beam 1, at least two elastic supports are spaced between the two end supports along the direction in which the core beam 1 extends, at least two elastic supports are respectively arranged between any two rigid compensation sections, and the elastic supports are connected to the core beam frame. The elastic support 7 refers to the support condition of the elastic support, and the end constraint 4 refers to the constraint form of the end support. The two ends of the core beam 1 are detachably connected to the end constraint 4 through the end plate, which is convenient for the later installation of the rigid test section outer narrow band 5 and the verification of the quality of the core beam frame. Corresponding end constraints 4 are respectively arranged on the lower side of the end plate.

[0160] The present invention discloses a design method for a dual-mode narrow-band aeroelastic model capable of simulating dual vertical bending modes and synchronous force and vibration measurement. Compared with a traditional segmental model that can only simultaneously complete force and vibration measurement of first-order vertical bending and torsional modal vibrations, the present invention can simultaneously complete force and vibration measurement tests of two-order vertical bending modes. By adopting local geometric scaling in the longitudinal and lateral directions, the span can be further scaled down by n times, while the lateral dimension can be enlarged by n times, relative to conventional aeroelastic models, thereby avoiding the defect that conventional aeroelastic models cannot measure their forces due to too small lateral scaling ratios. Therefore, the model of the present invention can be simultaneously The force and vibration test is completed in one step, which is practical for vortex-vibration wind tunnel test; by directly fitting the vibration mode data into the vibration mode function, there is no need to simplify the vibration mode into a simple harmonic function, which ensures that not only the simple resonant mode but also the non-simple resonant mode can be simulated; through the method of built-in force measurement system, the rigid outer garment narrow band is connected to the core beam 1 through the force measurement system to avoid the influence of the inertia force of the whole model on the force measurement accuracy; the model outer garment adopts the form of a rigid narrow band to ensure that the test section has sufficient rigidity, which is convenient for force measurement and has good practicality in wind tunnel test. Specific embodiments

[0162] like Figure 1 As shown, a dual-mode narrow-band aeroelastic model of synchronous force and vibration measurement that can simulate dual vertical bending modes of the present invention includes the core beam 1, the diaphragm beam 2, the end plate 3, the end constraint 4, the rigid test section outer narrow band 5, the rigid compensation section outer narrow band 6, the elastic support 7, the concentrated mass point 8, the force sensor 9, and the response measurement system 10.

[0163] The design method of the aeroelastic model includes the following steps:

[0164] Step 1: Establish a finite element model of the target bridge and perform modal analysis to extract the modal masses m of each order. p-r * , Main beam equivalent mass m p-r , modal frequency f p-r and the modal vibration shape φ p-r :

[0165]

[0166] Step 2: According to the requirements of the wind tunnel test, the similarity principle and the equivalence theory, first perform an overall geometric scale-down at a ratio of 1:100:

[0167] Span scale ratio:

[0168] Width scale ratio:

[0169] Equivalent mass scale ratio:

[0170] Modal mass scale ratio:

[0171] Select the wind speed ratio according to the test conditions:

[0172] Frequency scale ratio: λ f = 100 / 3.

[0173] Overall geometric scale-down result:

[0174]

[0175] To meet the test requirements, on the basis of the overall geometric scale-down, the span is further scaled down locally at a ratio of 1:2

[0176] for local geometric scale-down. The purpose of the local geometric scale-down is to further reduce the span of the model:

[0177] Longitudinal scale ratio γ = 0.5, L d = γL m = 8.88 * 0.5 = 4.44,

[0178] If the total mass remains unchanged, then the equivalent mass: m m * L m = m d * L d ,

[0179] The modal mass remains consistent:

[0180] If the lift remains the same, the scale ratio of the model width can be deduced:

[0181] F Ls = 0.5ρU 2 (C L )B) s L s = F Lm = 0.5ρU2 (C L B) m L m ,

[0182]

[0183] Therefore, the span is shortened to L d =γL m =8.88 * 0.5 = 4.44

[0184] Then, the width is enlarged to ensure

[0185] that the frequencies remain consistent: By adjusting the distributed stiffness and the support stiffness to ensure the same frequency

[0186] The vibration modes remain consistent:

[0187] According to the scaling ratios determined in Step 2, calculate the equivalent mass m of each order, modal mass m2-r , modal mass modal frequency f m2-r modal vibration mode φ m2-r modal stiffness

[0188]

[0189] According to the principle of continuous vibration mechanics and the modal parameters of the first-order and second-order vertical bending modal models obtained above, fit the vibration modes into vibration mode functions. By adjusting the distance from the elastic support 7 to the end to 1.36 m, calculate the target stiffness EI = 169.7786 N·m of the core beam in a synchronous force-measuring and vibration-measuring dual-modal narrowband aeroelastic model that can simulate dual vertical bending modes 2 , target stiffness K of the elastic support i = 2812 N / m, target distributed mass ρA = 4.5383 kg / m of the core beam, and target concentrated mass m i = 0.0753 kg:

[0190]

[0191]

[0192] According to the target stiffness EI of the core beam, target stiffness k of the elastic support i , target distributed mass ρA of the core beam, and target concentrated mass m iAnd the scale ratio, aluminum is selected as the material of the core beam 1. Since the density and elastic modulus of the material are fixed after the material is determined and it is impossible to simultaneously meet the target stiffness and the target distributed mass, the target stiffness EI = 217.44 N·m of the core beam is optimized based on the target frequency, equivalent mass and vibration mode of the model 2 and the target stiffness k of the elastic support i = 2812 N / m. If the deviation of the key parameters of the vibration characteristics of the final model from the target value is lower than the threshold of 5%, the support model can be carried out according to step S600:

[0193]

[0194] Furthermore, according to the model parameters, the cross-sectional dimension parameters of the core beam (1) are obtained as a concave cross-section, with a thickness of 3 mm, a width of 50 mm, a length of 4.44 m, a height of 14 mm, and a cross-sectional area of 2.16e-4 m 2 .

[0195] Furthermore, according to the model parameters and the parameters of the core beam 1, the diaphragm beam 2 is determined to be a hollow thin-walled aluminum square tube, with a height of 25 mm, a width of 25 mm, a thickness of 3 mm, and a length of 0.35 m. A total of 27 outer narrow bands are designed in the model, ensuring that a diaphragm beam 2 is arranged in the middle of each outer narrow band, with a total of 27 diaphragm beams 2. In order to maintain stability, a diaphragm beam 2 is also arranged at the 7 suspension points of the elastic support, so 2 more diaphragm beams 2 are added, with a total of 29 diaphragm beams 2.

[0196] A total of 8 suspension elastic supports 7 are arranged, and the stiffness of the elastic support 7 is 2812 N / m.

[0197] According to the determined geometric and material parameters of each component of the model, a finite element model of the scaled model is established, and modal analysis is carried out. The vibration mode of the model is consistent with the target vibration mode. The deviation of the first-order vertical bending frequency of the model from the target value is 1.84%, the deviation of the second-order vertical bending frequency of the model from the target value is -1.82%, the deviation of the first-order equivalent mass of the model from the target value is 1.49%, and the deviation of the second-order equivalent mass of the model from the target value is -0.84%.

[0198] The suspension point of the elastic support 7 coincides with the position of the concentrated mass point 8, and a concentrated mass is set here, where the suspension connecting piece of the elastic support 7 also belongs to a part of the concentrated mass.

[0199] In this embodiment, when scaling the aeroelastic model, the conventional method is to perform geometric scaling, which will result in too small a cross-sectional scale ratio and too small aerodynamic force, making it inconvenient to conduct a force measurement test. In this embodiment, different scale ratios are adopted longitudinally and transversely to simultaneously meet the equivalence of vibration characteristics.

[0200] The above has specifically described the preferred embodiments of the present invention. However, the present invention is not limited to the embodiments. Those skilled in the art can also make various equivalent variations or substitutions without departing from the spirit of the present invention. These equivalent variations or substitutions are all included within the scope defined by the claims of this application.

Claims

1. A design method for a dual-mode narrow-band aeroelastic model for synchronous force and vibration measurement, characterized in that: The following steps are involved: Step 1: Analyze the characteristics of the target structure and convert it into a two-point elastic support structure, including a core beam, a concentrated mass point, an elastic support, and end constraints. Determine the constraint form and the relative position of the elastic support according to the test conditions and the characteristics of the target structure. Step 2: Establish a finite element model based on the characteristics of the target structure and perform modal analysis to extract the modal mass m of each order of the target structure. p-r * , core beam equivalent mass m p-r , modal frequency f p-r and the modal vibration shape φ p-r , where P represents the target structure and r represents the order; Step 3: According to the requirements of wind tunnel test, similarity principle and equivalent theory, the finite element model of the target structure is first scaled according to 1:n1; on the premise of meeting the equivalence and similarity, the local geometric scaling is further performed according to 1:n2 in the longitudinal direction and n2:1 in the transverse direction on the basis of the overall geometric scaling to determine the final scaling ratio, and the final scaling ratio includes: longitudinal geometric scaling ratio λ L-lengthways , lateral geometric scale ratio λ L-crosswise , frequency scaling ratio λ f , equivalent mass scale ratio λ m , modal mass scale ratio Wind speed ratio λ v , mode shape scaling ratio λ φ ; Step 4: Extract the modal mass m of each order based on the finite element model of the target structure p-r * , core beam equivalent mass m p-r , modal frequency f p-r and the modal vibration shape φ p-r and the final scale ratio, calculate the equivalent mass m of each order of the narrow-band aeroelastic model m2-r , modal mass Modal frequency f m2-r , modal vibration shape φ m2-r , modal stiffness where the modal stiffness is determined by the modal frequency and modal mass: Step 5: According to the principle of continuous vibration dynamics, the equivalent mass m of each order of the narrow-band aeroelastic model m2-r , modal mass Modal frequency f m2-r , modal vibration shape φ m2-r , modal stiffness The constraint form and the relative position of the elastic support are used to calculate the target design parameters of the dual-mode narrow-band aeroelastic model with synchronous force and vibration measurement, which include the core beam target stiffness EI, the elastic support target stiffness k i , core beam target distributed mass ρA and target concentrated mass m i , if a negative number appears in the four target design parameters, it is necessary to adjust the relative position of the elastic support so that all the calculated values ​​are positive numbers; Step six: Design the geometric and material parameters of each component of the dual-mode narrow-band aeroelastic model with simultaneous force and vibration measurement according to the target design parameters, including the core beam, diaphragm, end plate, end constraint, rigid test section outer narrow band, rigid compensation section outer narrow band, elastic support, concentrated mass point, force sensor, response measurement system material parameters and structural form.

2. The design method of a dual-mode narrow-band aeroelastic model for synchronous force and vibration measurement according to claim 1 is characterized in that: The step six also includes: Selecting the material of the core beam frame according to the target design parameters determined in step 5 and the final scale ratio, and determining the elastic modulus and density of the core beam frame according to the selected material; Calculate the theoretical value of the moment of inertia and the theoretical value of the area of ​​the core beam section according to the target design parameters determined in step 5; Select the corresponding cross-sectional form based on the theoretical value of the cross-sectional inertia moment, the theoretical value of the area and the test construction requirements, and determine the design value of the cross-sectional inertia moment and the design value of the area; According to the determined elastic modulus and density, model parameters, design value of section inertia moment, and design value of area, a finite element model is established for modal analysis and the actual equivalent mass, modal mass, modal frequency, modal vibration shape, and modal stiffness of the target model are calculated, and compared with the equivalent mass m of each order of the narrow-band aeroelastic model obtained in step 5. m2-r , modal mass Modal frequency f m2-r , modal vibration shape φ m2-r , modal stiffness Compare and judge whether the model is designed.

3. The design method of a dual-mode narrow-band aeroelastic model for synchronous force and vibration measurement according to claim 2, characterized in that: The elastic modulus and density, model parameters, section inertia design value, and area design value determined according to the above process are used to establish a finite element model for modal analysis and calculate the actual equivalent mass of each order, modal mass, modal frequency, modal vibration shape, and modal stiffness of the target model, and compare them with the equivalent mass m of each order of the narrow-band aeroelastic model obtained in step 5. m2-r , modal mass Modal frequency f m2-r , modal vibration shape φ m2-r , modal stiffness The steps of comparing and judging whether the model is designed are also as follows: The judgment is made based on three criteria: whether the frequency deviation is less than the threshold, whether the equivalent mass deviation is less than the threshold, and whether the vibration mode is consistent; If the deviations of the three judgment criteria are all less than the threshold, the model design is completed; If the deviation is greater than the threshold, the following five adjustment schemes are used to adjust and check the deviation in turn:

1. Adjust the design value of the moment of inertia while ensuring that the design value of the area remains unchanged; 2. Adjust the design value of the moment of inertia while ensuring that the design value of the moment of inertia remains unchanged; 3. Adjust the concentrated mass value while ensuring that the elastic support value remains unchanged; 4. Adjust the elastic support value while ensuring that the concentrated mass value remains unchanged; 5. Reselect the material; After each adjustment, modal analysis is performed to obtain the actual equivalent mass, modal mass, modal frequency, modal vibration shape, and modal stiffness of the adjusted target model, and these are compared with the equivalent mass m of the narrow-band aeroelastic model obtained in step 5. m2-r , modal mass Modal frequency f m2-r , modal vibration shape φ m2-r , modal stiffness Compare and judge according to three criteria: whether the frequency deviation is less than the threshold, whether the equivalent mass deviation is less than the threshold, and whether the vibration mode is consistent; The adjustment is performed cyclically according to the adjustment scheme and deviation evaluation method until the deviations of the three judgment criteria are all less than the threshold value, and the model design is completed.

4. The design method of a dual-mode narrow-band aeroelastic model for synchronous force and vibration measurement according to claim 1, characterized in that: In the step 1, the target structure is equivalent to a two-point elastic support structure, the constraint form of the model end corresponds to the target structure, the mass of the target structure includes the core beam distributed mass and the concentrated mass point simulation of the two-point elastic support structure, and the stiffness is mainly simulated by the core beam stiffness and the elastic support.

5. The design method of a synchronous force and vibration dual-mode narrow-band aeroelastic model according to claim 1 is characterized in that: In the step 3, two scalings are performed according to the similarity principle, equivalent theory and test requirements. The first is the overall geometry scaling (Full Geometry Scale), and the second is the local geometry scaling (Part Geometry Scale) in the longitudinal and transverse directions to meet the test requirements. Note: The subscript m1 (model1) represents the model parameters after geometry scaling, the subscript m2 (model2) represents the model parameters after local geometry scaling, and the subscript p (prototype) represents the actual bridge parameters. The geometry scaling ratio (1:n1) is determined, and the appropriate wind speed ratio (1:n v ), the overall geometric scaling process is as follows: (1) Geometric similarity: (2) Similar equivalent quality: (3) Similar modal quality: (4) Select wind speed ratio according to test conditions: (5) Similar frequency: (6) Similar vibration modes: f m1-r =φ p-r (6) Overall geometric scaling results: In order to meet the test requirements, on the basis of the overall geometric scaling, local geometric scaling is carried out according to 1:n2 in the longitudinal direction and n2:1 in the transverse direction. The purpose of local geometric scaling is to further reduce the longitudinal length of the model: (1) Longitudinal scale: (2) If the total mass remains unchanged, the equivalent mass scale ratio is: (3) Modal quality remains consistent: (4) Based on the similarity of lift, the lateral scaling is: (5) The longitudinal scale ratio is L m2 =γL m1 , then the horizontal scale is: (6) Similar frequency: The frequency is ensured to be the same by adjusting the distribution stiffness and support stiffness; (7) Similar wind speed: (8) Similar vibration modes: Local geometry scaling results:

6. The design method of a dual-mode narrow-band aeroelastic model for synchronous force and vibration measurement according to claim 1, characterized in that: In the step five, According to the principle of continuous vibration dynamics, the target stiffness EI of the core beam and the target stiffness k of the elastic support in the aeroelastic model are calculated. i , core beam target distributed mass ρA and target concentrated mass m i When , the vibration mode data is fitted to obtain the vibration mode function, and the aeroelastic model parameters are calculated as follows:

7. The design method of a dual-mode narrow-band aeroelastic model for synchronous force and vibration measurement according to claim 1, characterized in that: In the step six, a force sensor for measuring the inertial force of the rigid test section outer garment narrow band is also included, and the force sensor is installed between the core beam and the rigid test section outer garment narrow band.

8. The method for designing a dual-mode narrow-band aeroelastic model for synchronous force and vibration measurement according to claim 1, characterized in that: In the step six, a cross beam is provided at the center position and elastic support point position of each rigid test section outer garment narrow band and rigid compensation section outer garment narrow band.

9. The design method of a dual-mode narrow-band aeroelastic model for synchronous force and vibration measurement according to claim 1, characterized in that: In the step six, the concentrated mass is arranged at the elastic support point.

10. A dual-mode narrow-band aeroelastic model for synchronous force and vibration measurement, characterized in that: include: A core beam frame, comprising two core beams and a plurality of transverse beams, wherein the two core beams are arranged side by side, and a plurality of transverse beams are connected between the two core beams at intervals along the direction in which the core beams extend, and the core beam frame is provided with a plurality of outer garment narrow band segments arranged at intervals along the direction in which the core beams extend, and the outer sides of the outer garment narrow band segments are all wrapped with outer garment narrow bands, and the plurality of outer garment narrow band segments include a plurality of rigid compensation segments and a plurality of rigid test segments, and the rigid test segments are distributed between two adjacent rigid compensation segments; The supporting structure includes two end supports and at least two elastic supports, wherein the two end supports are respectively connected to the two ends of the core beam, at least two elastic supports are spaced between the two end supports along the direction in which the core beam extends, at least two elastic supports are respectively arranged between any two of the rigid compensation sections, and the elastic supports are connected to the core beam frame.

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