Aerodynamic flap vibration reduction device for bridges

Abstract

The application provides a kind of aerodynamic wing plate damping device for bridge, the aerodynamic wing plate damping device includes fixedly connected with the fixed support rod of bridge box girder, rotatably connected with the aerodynamic wing plate of bridge box girder, elastic member is arranged between the fixed support rod and the aerodynamic wing plate, the first frequency modulation element is arranged in the fixed support rod, two ends of the elastic member are connected with the fixed support rod and aerodynamic wing plate respectively, when the amplitude of the aerodynamic wing plate is less than first set value, the first frequency modulation element is away from the aerodynamic wing plate, when the amplitude of the aerodynamic wing plate is equal to or greater than first set value, the other end of the first frequency modulation element is automatically connected to the aerodynamic wing plate. In the aerodynamic wing plate damping device, the frequency of aerodynamic wing plate movement can be adjusted, and the amplitude of aerodynamic wing plate can be limited to avoid further amplification to avoid structural damage.

Description

[Technical Field]

[0001] This invention relates to the field of bridge engineering technology, and in particular to a pneumatic winglet vibration damping device for bridges. [Background Technology]

[0002] Long-span bridges are characterized by dense modalities, resulting in vibrations at different frequencies under varying wind conditions. Vibration damping devices designed for a single mode can only control vibrations at a specific frequency, offering limited suppression of other frequencies. Active aerodynamic vanes offer an effective solution for controlling wind-induced vibrations in long-span bridges, adjusting the control law according to different incoming wind conditions for better control range and effectiveness. However, compared to passive aerodynamic measures, active aerodynamic vanes often require external energy input. When long-span bridges are affected by extreme wind conditions such as typhoons, they face risks such as disrupted energy supply, leading to insufficient control stability and significant risks. While mechanically connecting aerodynamic vanes to the main beam can avoid additional energy supply, it cannot automatically adjust its motion according to different main beam vibration frequencies. [Summary of the Invention]

[0003] The purpose of this invention is to provide a pneumatic winglet vibration damping device for bridges, wherein the frequency of the pneumatic winglet movement is adjustable and the amplitude of the pneumatic winglet vibration is limited to avoid further structural damage.

[0004] To achieve the above-mentioned objective, the present invention provides a pneumatic wing plate vibration damping device for bridges. The pneumatic wing plate vibration damping device includes a fixed support rod fixedly connected to a bridge box girder, a pneumatic wing plate rotatably connected to the bridge box girder, an elastic element disposed between the fixed support rod and the pneumatic wing plate, and a first frequency tuning element disposed on the fixed support rod. The two ends of the elastic element are respectively connected to the fixed support rod and the pneumatic wing plate. When the amplitude of the pneumatic wing plate is less than a first set value, the first frequency tuning element moves away from the pneumatic wing plate. When the amplitude of the pneumatic wing plate is equal to or greater than the first set value, the other end of the first frequency tuning element automatically connects to the pneumatic wing plate.

[0005] As a further improvement of one embodiment of the present invention, the first frequency modulation element is a first frequency modulation spring.

[0006] As a further improvement of one embodiment of the present invention, a first magnetic support is provided at one end of the first frequency tuning component facing the aerodynamic wing plate. When the amplitude of the aerodynamic wing plate is equal to or greater than a first set value, the first magnetic support is attracted to the aerodynamic wing plate.

[0007] As a further improvement of one embodiment of the present invention, the aerodynamic wing plate vibration damping device further includes a second frequency tuning component disposed on the fixed support rod. When the amplitude of the aerodynamic wing plate is greater than a first set value and less than a second set value, the second frequency tuning component moves away from the aerodynamic wing plate. When the amplitude of the aerodynamic wing plate is equal to or greater than the second set value, the other end of the second frequency tuning component is automatically connected to the aerodynamic wing plate.

[0008] As a further improvement of one embodiment of the present invention, the second frequency modulation element is a second frequency modulation spring.

[0009] As a further improvement of one embodiment of the present invention, a second magnetic support is provided at one end of the second frequency tuning component facing the aerodynamic wing plate. When the amplitude of the aerodynamic wing plate is equal to or greater than a second set value, the second magnetic support is attracted to the aerodynamic wing plate.

[0010] As a further improvement of one embodiment of the present invention, the elastic element is a support spring.

[0011] As a further improvement of one embodiment of the present invention, a rubber support is provided between the elastic element and the aerodynamic wing plate.

[0012] Compared with the prior art, the present invention has the following beneficial effects: Because a first frequency tuning component is provided on the fixed support rod, and when the amplitude of the aerodynamic wingplate is less than a first set value, the first frequency tuning component moves away from the aerodynamic wingplate, meaning that the first frequency tuning component is not connected to the aerodynamic wingplate at this time. However, when the amplitude of the aerodynamic wingplate is equal to or greater than the first set value, the other end of the first frequency tuning component automatically connects to the aerodynamic wingplate. This ensures that when the amplitude of the aerodynamic wingplate is large, the first frequency tuning component connects to the aerodynamic wingplate to adjust the movement frequency of the aerodynamic wingplate, and can limit further amplification of the aerodynamic wingplate amplitude to avoid structural damage. In summary, the present invention provides a vibration frequency-adjustable aerodynamic wingplate vibration reduction device for bridges, thereby compensating for the shortcomings of traditional passive aerodynamic wingplates in wind vibration control of long-span bridges, and more effectively improving the multimodal wind vibration performance of long-span bridge structures. [Attached Image Description]

[0013] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort. Wherein:

[0014] Figure 1 This is a schematic diagram of a pneumatic wing plate vibration damping device for bridges, provided in a specific embodiment of this application, mounted on a bridge box girder.

[0015] Figure 2 yes Figure 1 A partially enlarged schematic diagram of the aerodynamic airfoil vibration damping device, in which the aerodynamic airfoil is not connected to the first frequency tuning component.

[0016] Figure 3 yes Figure 1 A partially enlarged schematic diagram of the aerodynamic airfoil vibration damping device, in which the aerodynamic airfoil vibrates downwards until it connects with the first frequency tuning component.

[0017] Figure 4 yes Figure 3 A schematic diagram of the aerodynamic airfoil vibration damping device. At this time, the aerodynamic airfoil is connected to the first frequency tuning component, and the aerodynamic airfoil vibrates upward.

[0018] Figure 5 yes Figure 1 A partially enlarged schematic diagram of the aerodynamic airfoil vibration damping device, in which the aerodynamic airfoil vibrates downwards until it connects with the second frequency modulation component.

[0019] Figure 6 yes Figure 5 A schematic diagram of the aerodynamic winglet vibration damping device. At this time, the aerodynamic winglet is connected to both the first and second frequency tuning components, and the aerodynamic winglet vibrates upward.

Detailed Implementation Methods

[0020] To make the above-mentioned objectives, features, and advantages of this application more apparent and understandable, the specific embodiments of this application will be described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are for illustrative purposes only and are not intended to limit the scope of this application. Furthermore, it should be noted that, for ease of description, only the parts relevant to this application are shown in the accompanying drawings, not the entire structure. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without inventive effort are within the scope of protection of this application.

[0021] The terms “comprising” and “having”, and any variations thereof, used in this application are intended to cover non-exclusive inclusion. For example, a process, method, system, product, or apparatus that includes a series of steps or units is not limited to the steps or units listed, but may optionally include steps or units not listed, or may optionally include other steps or units inherent to such process, method, product, or apparatus.

[0022] It should be noted that when a component is said to be "fixed to" another component, it can be directly attached to the other component or there may be an intervening component. When a component is said to be "connected to" another component, it can be directly connected to the other component or there may be an intervening component. The terms "vertical," "horizontal," "left," "right," and similar expressions used in this document are for illustrative purposes only.

[0023] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. The terminology used herein in the description of the invention is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. The term "and / or" as used herein includes any and all combinations of one or more of the associated listed items.

[0024] In this document, the term "embodiment" means that a particular feature, structure, or characteristic described in connection with an embodiment may be included in at least one embodiment of this application. The appearance of this phrase in various places throughout the specification does not necessarily refer to the same embodiment, nor is it a separate or alternative embodiment mutually exclusive with other embodiments. It will be explicitly and implicitly understood by those skilled in the art that the embodiments described herein can be combined with other embodiments.

[0025] Please see Figures 1 to 6 As shown in the specific embodiment of the present invention, this embodiment provides an aerodynamic wing plate vibration damping device 10 for bridges. The aerodynamic wing plate vibration damping device 10 includes a fixed support rod 14 fixedly connected to a bridge box girder 12, an aerodynamic wing plate 16 rotatably connected to the bridge box girder 12, an elastic element 18 disposed between the fixed support rod 14 and the aerodynamic wing plate 16, and a first frequency tuning element 20 disposed on the fixed support rod 14. The two ends of the elastic element 18 are respectively connected to the fixed support rod 14 and the aerodynamic wing plate 16. When the amplitude of the aerodynamic wing plate 16 is less than a first set value, the first frequency tuning element 20 moves away from the aerodynamic wing plate 16. When the amplitude of the aerodynamic wing plate 16 is equal to or greater than the first set value, the other end of the first frequency tuning element 20 is automatically connected to the aerodynamic wing plate 16.

[0026] In this specific embodiment, a first frequency tuning element 20 is provided on the fixed support rod 14. When the amplitude of the aerodynamic wing 16 is less than a first set value, the first frequency tuning element 20 moves away from the aerodynamic wing 16. That is, at this time, the first frequency tuning element 20 is not connected to the aerodynamic wing 16. However, when the amplitude of the aerodynamic wing 16 is equal to or greater than the first set value, the other end of the first frequency tuning element 20 automatically connects to the aerodynamic wing 16. This ensures that when the amplitude of the aerodynamic wing 16 is large, the first frequency tuning element 20 connects to the aerodynamic wing 16 to adjust the movement frequency of the aerodynamic wing 16 and to limit further amplification of the amplitude of the aerodynamic wing 16 to avoid structural damage.

[0027] In summary, the present invention provides a bridge aerodynamic wing plate vibration reduction device 10 with adjustable vibration frequency, thereby making up for the shortcomings of traditional passive aerodynamic wing plates in wind vibration control of long-span bridges and more effectively improving the multimodal wind vibration performance of long-span bridge structures.

[0028] Furthermore, the first frequency modulation element 20 is a first frequency modulation spring.

[0029] A first magnetic support 22 is provided at the end of the first frequency tuning component 20 facing the aerodynamic airfoil 16. When the amplitude of the aerodynamic airfoil 16 is equal to or greater than a first set value, the first magnetic support 22 is attracted to the aerodynamic airfoil 16. Of course, other automatic connection methods can also be used between the first frequency tuning component 20 and the aerodynamic airfoil 16.

[0030] Furthermore, the aerodynamic winglet vibration damping device 10 also includes a second frequency tuning component 24 disposed on the fixed support rod 14. When the amplitude of the aerodynamic winglet 16 is greater than a first set value and less than a second set value, the second frequency tuning component 24 moves away from the aerodynamic winglet 16, and there is no connection between the second frequency tuning component 24 and the aerodynamic winglet 16. However, when the amplitude of the aerodynamic winglet 16 is equal to or greater than the second set value, the other end of the second frequency tuning component 24 is automatically connected to the aerodynamic winglet 16. This arrangement ensures that when the amplitude of the aerodynamic winglet 16 is larger, the second frequency tuning component 24 is connected to the aerodynamic winglet 16 to further adjust the movement frequency of the aerodynamic winglet 16 and to limit further amplification of the amplitude of the aerodynamic winglet 16 to avoid structural damage.

[0031] In other words, when the amplitude of the aerodynamic winglet 16 is greater than or equal to the first set value and less than the second set value, the other end of the first frequency tuning component 20 is automatically connected to the aerodynamic winglet 16. At this time, the second frequency tuning component 24 is still far away from the aerodynamic winglet 16, that is, it is not connected to the aerodynamic winglet 16. When the amplitude of the aerodynamic winglet 16 is equal to or greater than the second set value, at the same time as the other end of the first frequency tuning component 20 is connected to the aerodynamic winglet 16, the other end of the second frequency tuning component 24 is also automatically connected to the aerodynamic winglet 16.

[0032] Specifically, the second frequency modulation element 24 is the second frequency modulation spring.

[0033] A second magnetic support 26 is provided at the end of the second frequency tuning component 24 facing the aerodynamic winglet 16. When the amplitude of the aerodynamic winglet 16 is equal to or greater than a second set value, the second magnetic support 26 is attracted to the aerodynamic winglet 16. Of course, other automatic connection methods can also be used between the second frequency tuning component 24 and the aerodynamic winglet 16.

[0034] In this preferred embodiment, two frequency-modulating springs are provided, namely the first frequency-modulating spring and the second frequency-modulating spring. Of course, the number of frequency-modulating springs can be increased or decreased according to the actual dynamic characteristics of the bridge. In addition, the specific stiffness setting of the frequency-modulating springs can also be changed according to the actual dynamic characteristics of the bridge.

[0035] The elastic element 18 is a support spring. Specifically, the elastic element 18 is a cylindrical helical spring, and both the first frequency tuning element 20 and the second frequency tuning element 24 are cylindrical helical springs. Furthermore, the pitch of the first frequency tuning element 20 is greater than the pitch of the elastic element 18, and the pitch of the second frequency tuning element 24 is greater than the pitch of the first frequency tuning element 20.

[0036] A rubber support 28 is provided between the elastic element 18 and the aerodynamic wing 16. This reduces the vibration between the elastic element 18 and the aerodynamic wing 16.

[0037] The above is only one specific embodiment of the present invention, and any improvements made based on the concept of the present invention shall be considered within the scope of protection of the present invention.

Claims

1. An aerodynamic flap vibration damping device for a bridge, characterized by, The aerodynamic wing plate damping device comprises a fixed support rod fixedly connected to the bridge box girder, an aerodynamic wing plate rotatably connected to the bridge box girder, an elastic member arranged between the fixed support rod and the aerodynamic wing plate, and a first frequency adjusting member arranged on the fixed support rod, two ends of the elastic member are respectively connected to the fixed support rod and the aerodynamic wing plate, when the amplitude of the aerodynamic wing plate is less than a first set value, the first frequency adjusting member is away from the aerodynamic wing plate, one end of the first frequency adjusting member facing the aerodynamic wing plate is provided with a first magnetic support, when the amplitude of the aerodynamic wing plate is equal to or greater than the first set value, the first magnetic support is adsorbed to the aerodynamic wing plate.

2. The pneumatic airfoil vibration damping apparatus of claim 1, wherein The first frequency adjusting member is a first frequency adjusting spring.

3. The pneumatic airfoil vibration damping apparatus of claim 1, wherein, The aerodynamic wing plate damping device further comprises a second frequency adjusting member arranged on the fixed support rod, when the amplitude of the aerodynamic wing plate is greater than the first set value and less than a second set value, the second frequency adjusting member is away from the aerodynamic wing plate, when the amplitude of the aerodynamic wing plate is equal to or greater than the second set value, the other end of the second frequency adjusting member is automatically connected to the aerodynamic wing plate.

4. The pneumatic airfoil vibration damping apparatus of claim 3, wherein The second frequency adjusting member is a second frequency adjusting spring.

5. The airfoil vibration damping device of Claim 3, wherein One end of the second frequency adjusting member facing the aerodynamic wing plate is provided with a second magnetic support, when the amplitude of the aerodynamic wing plate is equal to or greater than the second set value, the second magnetic support is adsorbed to the aerodynamic wing plate.

6. The aerodynamic winglet vibration damping device of claim 1, wherein, The elastic member is a support spring.

7. The pneumatic airfoil vibration reduction device of claim 1, wherein, A rubber support is arranged between the elastic member and the aerodynamic wing plate.

Images