Particle damper for vibration reduction of wing structure

Abstract

The invention provides a particle damper for vibration reduction of a wing structure, which comprises a bottom plate, a cover plate and a box body symmetrically arranged on the bottom plate, a plurality of damping particles and metal grids parallel to each other are placed in the box body, and a damping layer is attached to the inner wall of the box body. When the main beam vibrates due to external disturbance of the wing, the damping particles vibrate along with the main beam and collide and rub with the metal grating and the damping layer in the vibration process, vibration energy is effectively converted into heat energy, and therefore dissipation of the vibration energy is achieved, the vibration amplitude of the main beam of the wing is remarkably reduced under the condition that the structure of the wing is not changed, and the service life of the wing is prolonged. Not only is the influence of vibration on the performance of the wings effectively reduced, but also the purpose of noise reduction is achieved, and the mute performance and the riding comfort of the aircraft are improved.

Description

Technical Field

[0001] The invention belongs to the technical field of particle damping and vibration reduction, and in particular relates to a particle damper used for vibration reduction of a wing structure. Background Art

[0002] Vibration, as a physical phenomenon that is widely present in daily life and engineering practice, has always been an important research object that has received much attention in the field of mechanics. Its universality and complexity make vibration research not only of theoretical value, but also play a vital role in practical applications. In the discipline system of mechanics, vibration research occupies a pivotal position and is the key to exploring the laws of material motion, optimizing structural design, and improving engineering performance.

[0003] With the rapid development of modern science and technology, people's demand for vibration control and noise reduction is becoming increasingly urgent. In the fields of industrial production, transportation, aerospace, etc., vibration and noise not only affect the operating efficiency and stability of equipment, but may also have adverse effects on the environment and human health.

[0004] As an important part of an aircraft, the stability and safety of its performance are crucial to the success of the flight. However, during the flight, the wings are often affected by various factors and vibrate. These vibrations not only affect the flight performance and stability of the aircraft, but may also cause damage to the structure of the wing, thereby threatening the safety of the aircraft.

[0005] Existing methods for suppressing wing vibration include optimizing the wing aerodynamic shape and enhancing the wing stiffness. However, optimizing the wing aerodynamic shape requires full consideration and precise calculation in the design phase, which is difficult to implement. Using high-quality materials and advanced manufacturing processes to improve wing stiffness will increase the manufacturing cost of the aircraft. Summary of the invention

[0006] The purpose of the present invention is to solve the shortcomings of existing wing vibration suppression methods that are difficult or costly to implement, and to provide a particle damper for wing structure vibration reduction.

[0007] To achieve the above purpose, the technical solution provided by the present invention is:

[0008] A particle damper for wing structure vibration reduction, comprising a bottom plate, a cover plate and boxes symmetrically arranged at both ends of the top of the bottom plate, each box is filled with a plurality of damping particles, and the total mass of the damping particles in the box is equal;

[0009] The cover plate is installed on the top of the box body, used to close the box body opening, and forms a mounting through hole with the middle of the bottom plate, and the mounting through hole is used to cooperate with the wing structure for mounting;

[0010] A number of mutually parallel metal grids are arranged in the box to promote the flow of damping particles and avoid accumulation of damping particles;

[0011] A damping layer is attached to the inner wall of the box to absorb the impact of the damping particles on the box when they move.

[0012] Furthermore, the damping particles are metal particles or rubber particles.

[0013] Furthermore, the damping layer is made of rubber material and is adhered to the inner wall of the box by adhesive.

[0014] Furthermore, the metal grille is cylindrical, and has external threads at both ends of the metal grille for fixing to the side wall of the box body through nuts.

[0015] Furthermore, the bottom plate, the box body and the cover plate are all made of aluminum alloy.

[0016] A wing, comprising a main beam, on which the particle damper is arranged; the particle damper is clamped on the main beam through a mounting through hole in the middle thereof and close to the end of the main beam;

[0017] Screws and nuts are installed on the cover plate of the particle damper at a position corresponding to the top of the box body, and are used to press the cover plate against the top of the main beam when tightened.

[0018] An aircraft comprises the above-mentioned wing.

[0019] The advantages of the present invention are:

[0020] 1. The present invention provides a particle damper, which has two symmetrically arranged boxes, in which a number of damping particles and metal grids parallel to each other are placed, and a damping layer is attached to the inner wall of the box. When the wing is disturbed by external disturbances and the main beam vibrates, the damping particles vibrate accordingly, and collide and rub with the metal grid and the damping layer during the vibration process, effectively converting the vibration energy into heat energy, thereby achieving the dissipation of the vibration energy, and significantly reducing the vibration amplitude of the wing main beam without changing the structure of the wing itself, which not only effectively reduces the impact of vibration on the wing performance, but also achieves the purpose of noise reduction, and improves the quiet performance and ride comfort of the aircraft.

[0021] 2. The multiple parallel metal grids provided in the present invention can disperse the damping particles when the damping particles vibrate, reduce the accumulation effect of the damping particles, promote the collision of the damping particles, and improve the vibration reduction effect of the particle damper of this aspect at small excitation amplitudes.

[0022] 3. A damping layer is attached to the inner wall of the particle damper box, which further reduces the impact of the damping particles on the damper box and further improves the stability and durability of the particle damper of the present invention.

[0023] 4. The particle damper of the present invention has a simple structure and a small size. The height of the particle damper is slightly higher than the thickness of the wing main beam. While ensuring the damping effect, the influence on the aerodynamic shape of the wing is minimized.

[0024] 5. The particle damper of the present invention is used to reduce the vibration of the wing main beam, which has a wide range of applicable environments and low maintenance costs, and has significant innovation and invention in practical application effects.

[0025] Additional aspects and advantages of the present invention will be given in part in the following description and in part will be obvious from the following description, or will be learned through practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] The above and / or additional aspects and advantages of the present invention will become apparent and easily understood from the description of the embodiments in conjunction with the following drawings, in which:

[0027] Figure 1 It is a schematic diagram of the appearance of the particle damper of the present invention;

[0028] Figure 2 It is the internal structure diagram of the particle damper of the present invention;

[0029] Figure 3 is a schematic diagram of the installation of the particle damper of the present invention on the wing main beam structure of Example 1;

[0030] Figure 4 This is a wing model diagram of Example 2;

[0031] Figure 5 yes Figure 4 Schematic diagram of the mid-wing main beam structure;

[0032] Figure 6 The particle damper of the present invention is Figure 5 The schematic diagram of the installation on the wing main beam structure is shown;

[0033] Figure 7 This is a comparison chart of the wing main beam tip displacement without and with particle dampers.

[0034] In the figure: 1-bottom plate, 2-cover plate, 3-box body, 4-metal grille. DETAILED DESCRIPTION

[0035] Embodiments of the present invention are described in detail below. The embodiments are exemplary and intended to be used to explain the present invention, but should not be construed as limiting the present invention.

[0036] Reference Figure 1 and Figure 2This embodiment shows a particle damper for wing structure vibration reduction, including a bottom plate 1, a cover plate 2, and boxes 3 symmetrically arranged at both ends of the top of the bottom plate. Each box is filled with a number of damping particles, and a plurality of mutually parallel metal grids 4 are arranged in the box cavity. A damping layer is attached to the inner wall of the box to reduce the impact of the damping particles on the inner cavity of the box and improve the overall stability and durability of the particle damper. The damping particles and the damping layer are Figure 2 The cover plate 2 is mounted on the top of the box body 3 to close the opening of the box body.

[0037] Specifically, the gap between the two boxes and the height of the boxes are determined according to the width and height of the wing main beam, so as to ensure that the particle damper of the present invention can be snapped onto the wing main beam.

[0038] The metal grid 4 is a metal column with threads at both ends for being fixedly connected to the side wall of the box through nuts. The metal grid 4 not only enhances the structural strength of the box, but also helps the distribution and flow of damping particles in the box, reduces the accumulation effect of damping particles, promotes the collision of particles, and improves the vibration reduction effect of the particle damper at small excitation amplitudes.

[0039] The damping particles are metal particles or rubber particles, and the total mass of the damping particles in the two boxes is consistent to ensure the balance and stability of the damping effect.

[0040] The damping layer is attached to the inner wall of the box by adhesive to absorb and disperse the impact force generated by the damping particles, thereby reducing the impact of the damping particles on the cavity structure and improving the stability and durability of the damper. Preferably, the damping layer is made of rubber material.

[0041] The base plate, box body and cover plate of the particle damper are made of aluminum alloy, which can achieve lightweight design while meeting the requirements of damping and vibration reduction.

[0042] Reference Figure 3 , showing a wing main beam structure with a particle damper of the present invention attached. Two boxes and the middle part of the cover plate form a rectangular mounting through hole, which is plugged into the wing main beam and close to the end of the main beam. Specifically, the particle damper is installed at the point where the structural response is maximum on the main beam, and the damping effect is most obvious at this position; the specific installation position is determined by the thickness of the wing beam section, and is as close to the end of the main beam (the point where the structural response is maximum) as possible if the thickness permits. In addition, after the particle damper is plugged into the main beam through the mounting through hole in the middle thereof, the cover plate is pressed against the top of the main beam by tightening the screws and nuts on the cover plate 2, thereby achieving the fastening of the particle damper to the main beam and ensuring a reliable connection between the particle damper and the main beam. The symmetrical layout of the boxes on the particle damper ensures the stability and reliability of the particle damper.

[0043] Reference Figure 4-Figure 5, showing another wing structure and its variable cross-section main beam structure located on the wing, Figure 6 This is a schematic diagram of the installation of the variable cross-section main beam of the particle damper of the present invention in this example. In this example, 36 steel balls with a diameter of 5 mm are filled in each box, and the total mass of the steel balls in a single box is 18.5 g. The total mass of the particle damper is 77 g.

[0044] In order to evaluate the effect of the particle damper of the present invention, in this embodiment, the first order natural frequency of the main beam in the wing model is first calculated by finite element simulation technology, and the result is 13.79 Hz. Then, a sinusoidal excitation with an excitation amplitude of 10N and an excitation frequency of 13.79 Hz (i.e., the first order natural frequency of the beam of the wing model) is applied to the root of the main beam in the wing model without the particle damper and the root of the main beam in the wing model with the particle damper of the present invention, and the displacement of the tip of the main beam in the wing model is monitored respectively.

[0045] like Figure 7 As shown, the test comparison results show that the displacement amplitude of the tip of the main beam of the wing model without the particle damper is 5.427mm, and the displacement amplitude of the tip of the main beam in the wing model with the particle damper of the present invention is 1.238mm. After adding the particle damper of the present invention, the displacement amplitude of the tip of the main beam is reduced by 77.18%, which proves that the particle damper designed by the present invention has good damping performance and significantly reduces the influence of vibration on the wing without changing the structure of the wing itself.

[0046] The above description is only a specific implementation mode of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can easily think of various equivalent modifications or substitutions within the technical scope disclosed in the present invention, and these modifications or substitutions should be included in the protection scope of the present invention.

Claims

1. A particle damper for wing structure vibration reduction, characterized in that: It includes a bottom plate, a cover plate, and boxes symmetrically arranged at both ends of the top of the bottom plate, each box is filled with a number of damping particles, and the total mass of the damping particles in the box is equal; The cover plate is installed on the top of the box body, used to close the box body opening, and forms a mounting through hole with the middle of the bottom plate, and the mounting through hole is used to cooperate with the wing structure for mounting; A number of mutually parallel metal grids are arranged in the box to promote the flow of damping particles and avoid accumulation of damping particles; A damping layer is attached to the inner wall of the box to absorb the impact of the damping particles on the box when they move.

2. The particle damper according to claim 1, characterized in that The damping particles are metal particles or rubber particles.

3. The particle damper according to claim 2, characterized in that: The damping layer is made of rubber material and is adhered to the inner wall of the box by adhesive.

4. The particle damper according to claim 3, characterized in that The metal grille is cylindrical, and has external threads at both ends for fixing to the side wall of the box body through nuts.

5. The particle damper according to claim 1, characterized in that: The bottom plate, the box body and the cover plate are all made of aluminum alloy.

6. A wing comprising a main beam, characterized in that: The particle damper according to any one of claims 1 to 5 is provided on the main beam; the particle damper is connected to the main beam through a mounting through hole in the middle thereof and is close to the end of the main beam; Screws and nuts are installed on the cover plate of the particle damper at a position corresponding to the top of the box body, and are used to press the cover plate against the top of the main beam when tightened.

7. An aircraft, characterized in that: Comprising the wing as claimed in claim 6.

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