A resilient cushioning aerospace bushing assembly

Abstract

This utility model discloses an elastic buffer type aviation bushing assembly, relating to the field of aviation bushing technology. It includes an outer sleeve, with a first sealing plate on one side and a second sealing plate on the other side. Multiple equidistant mounting holes are provided on the periphery of both the first and second sealing plates, which are connected to the outer sleeve via these mounting holes and bolts. This utility model utilizes the alternating arrangement of elastic filler and elastic support components to facilitate the fixing and deformation of the intermediate elastic filler, improving the axial load dispersion effect and thus achieving the function of buffering axial vibration. Furthermore, the misalignment and varying lengths of the internal and external threaded strips facilitate radial displacement within the entire bushing, improving the radial load dispersion effect and further achieving the function of buffering radial vibration. Ultimately, this solves the problems of limited buffering performance and poor buffering effect in existing devices.

Description

Technical Field

[0001] This utility model relates to the field of aviation bushing technology, and in particular to an elastic buffer aviation bushing assembly. Background Technology

[0002] The development of traditional aerospace bushing assemblies is a technological product of the aerospace industry's continuous pursuit of mechanical connection reliability, structural safety, and operational durability. Its technological evolution is closely related to the performance improvement and increased operating complexity of aerospace equipment, becoming one of the core technologies to ensure the stable operation of key aircraft components. The technological route of traditional aerospace bushing assemblies has evolved from single materials to composite structures. Early bushings used pure metal materials (such as bronze and steel bushings) and achieved low-friction fit through precision machining. However, the rigid contact between metals could not alleviate impact loads and was prone to corrosion and jamming in humid and high-temperature environments. With the advancement of materials science, metal-non-metal composite bushings have become the mainstream. This involves embedding friction-reducing materials such as graphite and polytetrafluoroethylene within a metal skeleton, or using a composite structure of elastomers such as rubber and polyurethane with metal. This retains the high strength support capacity of the metal while using non-metallic materials to achieve lubrication, buffering, or sealing functions.

[0003] Traditional aerospace bushing assemblies consist of an outer shell, a single rubber layer, a metal helical spring, and an inner sleeve. When this type of assembly is used, the metal helical spring can only buffer axial loads and has insufficient radial stiffness; the single rubber layer cannot adapt to variable load conditions and has poor high-frequency vibration isolation efficiency; the simple combination of the outer shell and inner sleeve cannot seal the entire structure, making the internal structure prone to damage. Therefore, the above problems need to be improved. Utility Model Content

[0004] The purpose of this invention is to address the shortcomings of existing technologies by proposing an elastic buffer type aviation bushing assembly.

[0005] To achieve the above objectives, the present invention adopts the following technical solution: an elastic buffer type aviation bushing assembly, including an outer sleeve, a first sealing plate on one side of the outer sleeve, and a second sealing plate on the other side of the outer sleeve, the first sealing plate and the second sealing plate having a plurality of equidistant mounting holes on their periphery, and the first sealing plate and the second sealing plate being connected to the outer sleeve through the mounting holes and bolts.

[0006] Preferably, an outer elastic support is fitted inside the outer sleeve, and the two sides of the outer elastic support abut against the first sealing plate and the second sealing plate, respectively.

[0007] Preferably, the inner wall of the external elastic support is provided with an external threaded strip, which is in the shape of a helical blade.

[0008] Preferably, the outer sleeve is provided with an inner sleeve, and an inner elastic support is installed on the outer side of the inner sleeve. The inner elastic support is placed inside the outer elastic support, and an internal threaded strip is installed on the outer side of the inner elastic support.

[0009] Preferably, the internal threaded strip is configured to cooperate with the external threaded strip.

[0010] Preferably, an elastic filler is provided between the inner elastic support and the outer elastic support.

[0011] Compared with the prior art, the beneficial effects of this utility model are as follows: This utility model, through the alternating arrangement and cooperation of elastic filler and elastic support, facilitates the fixing and deformation of the intermediate elastic filler, improves the axial load dispersion effect, and thus achieves the function of buffering axial vibration. Through the cooperation of the misalignment and different lengths of the internal and external threaded strips, the entire bushing can be radially offset, improving the radial load dispersion effect and thus achieving the function of buffering radial vibration. Furthermore, through the fixed cooperation of the first sealing plate, the second sealing plate, the mounting holes, and the bolts, the sealing and support of the entire structure are facilitated, improving the overall sealing performance of the structure and thus achieving the function of protecting the bushing assembly. Ultimately, it solves the problems of single buffering performance, poor buffering effect, and poor sealing in existing devices. Attached Figure Description

[0012] The accompanying drawings, which are included to provide a further understanding of the present invention and form part of this application, illustrate exemplary embodiments of the present invention and, together with the description thereof, serve to explain the present invention and do not constitute an undue limitation thereof. In the drawings:

[0013] Figure 1 This is a schematic diagram of the overall three-dimensional structure proposed in this utility model;

[0014] Figure 2 This is a schematic diagram of the overall cross-sectional structure proposed in this utility model;

[0015] Figure 3 This is a schematic diagram of the overall three-dimensional side structure proposed in this utility model;

[0016] Figure 4 This is a three-dimensional structural diagram of the internal elastic support member proposed in this utility model;

[0017] Figure 5 This is a three-dimensional structural diagram of the external elastic support member proposed in this utility model;

[0018] The numbers in the diagram are: 1. Outer sleeve; 2. First sealing plate; 3. Bolt; 4. Inner sleeve; 5. Inner elastic support; 6. Outer elastic support; 7. Elastic filler; 8. Second sealing plate; 9. External threaded strip; 10. Internal threaded strip; 11. Mounting hole. Detailed Implementation

[0019] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present utility model. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments.

[0020] Example: See Figures 1 to 4 This utility model discloses an elastic buffer type aviation bushing assembly, including an outer sleeve 1. The cylindrical design of the outer sleeve 1 facilitates the assembly of internal devices. A first sealing plate 2 is provided on one side of the outer sleeve 1, and a second sealing plate 8 is provided on the other side of the outer sleeve 1. The first sealing plate 2 and the second sealing plate 8 facilitate the sealing of the internal structure. Multiple equidistant mounting holes 11 are opened on the periphery of the first sealing plate 2 and the second sealing plate 8, which facilitate the installation of the sealing plates. The first sealing plate 2 and the second sealing plate 8 are connected to the outer sleeve 1 through the mounting holes 11 and bolts 3. The bolts 3 facilitate the connection and fixation of the outer sleeve 1 to the first sealing plate 2 and the second sealing plate 8.

[0021] In this utility model, an outer elastic support 6 is sleeved on the inner side of the outer sleeve 1. The two sides of the outer elastic support 6 abut against the first sealing plate 2 and the second sealing plate 8, respectively. The structure of the outer elastic support 6 facilitates the connection and support of the elastic material. An external threaded strip 9 is installed on the inner wall of the outer elastic support 6. The external threaded strip 9 is in the shape of a helical blade, which facilitates the increase of friction. An inner sleeve 4 is provided inside the outer sleeve 1, which facilitates contact with the connecting parts. An inner elastic support 5 is installed on the outer side of the inner sleeve 4, which facilitates the radial buffering of the assembly. The inner elastic support 5 is placed inside the outer elastic support 6, and an internal threaded strip 10 is installed on the outer side of the inner elastic support 5. The internal threaded strip 10 is configured to cooperate with the external threaded strip 9, which facilitates the increase of friction. An elastic filler 7 is provided between the inner elastic support 5 and the outer elastic support 6, which facilitates the increase of the overall structure's buffering effect.

[0022] The following description is made of the materials involved in this solution: The elastic filler 7 is a special rubber-metal composite material that is resistant to high and low temperatures, has stable elastic properties over a wide temperature range, and can absorb radial vibration impact.

[0023] Working principle: When using this elastic buffer aviation bushing assembly, the aviation equipment bearing is first installed inside the bushing, so that the bearing abuts against the inner sleeve 4, completing the initial assembly of the assembly and the aviation equipment bearing; then, using the multiple equidistant mounting holes 11 opened on the periphery of the first sealing plate 2 and the second sealing plate 8, the first sealing plate 2, the second sealing plate 8 and the outer sleeve 1 are connected and fixed by bolts 3, thereby achieving the sealing of the entire bushing structure. This sealing structure can effectively prevent fuel and dust from entering the elastic layer inside the bushing, while ensuring that the internal elastic units such as the inner elastic support 5, the outer elastic support 6 and the elastic filler 7 are not corroded by the outside, thus maintaining the stability of the bushing during use; when the aviation equipment vibrates during operation, the bearing will rotate and shift, and through the interference fit, the inner sleeve 4 will squeeze the elastic filler 7 located between the inner elastic support 5 and the outer elastic support 6 (wherein the elastic filler 7 is made of a special rubber-metal composite material that is resistant to high temperature and low temperature, has stable elastic performance over a wide temperature range, and can absorb radial vibration impact).

[0024] Since the inner elastic support 5 is shorter than the outer elastic support 6, the space reserved between them is just right to meet the radial vibration mitigation requirements. At this time, the elastic filler 7 plays a leading role in buffering, absorbing radial vibration energy through its own elastic deformation, thus effectively buffering radial vibration. For axial vibration, the threaded structure formed by the helical blade-shaped external threaded strip 9 installed on the inner wall of the outer elastic support 6 and the internal threaded strip 10 installed on the outer side of the inner elastic support 5 and cooperating with the external threaded strip 9, can keep the elastic filler 7 fixed between the outer elastic support 6 and the inner elastic support 5, making it difficult for it to shift. Subsequently, the axial vibration is buffered by the stretching and compressing deformation of the elastic filler 7. During this process, the rigid structure of the inner sleeve 4 and the outer sleeve 1 can ensure the overall load-bearing capacity of the component, and reasonably transfer the load buffered by the elastic filler 7, the inner elastic support 5 and the outer elastic support 6 to the relevant components, ultimately achieving vibration isolation and protection of aviation equipment, and ensuring the stable operation of aviation equipment throughout the entire operating cycle.

[0025] The above description is only a preferred embodiment of the present utility model, but the protection scope of the present utility model is not limited thereto. Any equivalent substitutions or changes made by those skilled in the art within the technical scope disclosed in the present utility model, based on the technical solution and the inventive concept of the present utility model, should be included within the protection scope of the present utility model.

Claims

1. A resilient cushioning aircraft bushing assembly, comprising an outer sleeve (1), characterized in that: The outer sleeve (1) has a first sealing plate (2) on one side and a second sealing plate (8) on the other side. The first sealing plate (2) and the second sealing plate (8) have multiple equidistant mounting holes (11) on their periphery. The first sealing plate (2) and the second sealing plate (8) are connected to the outer sleeve (1) through the mounting holes (11) and bolts (3). An outer elastic support (6) is sleeved on the inner side of the outer sleeve (1), and the two sides of the outer elastic support (6) abut against the first sealing plate (2) and the second sealing plate (8) respectively. The outer sleeve (1) is provided with an inner sleeve (4), and an inner elastic support (5) is installed on the outside of the inner sleeve (4). The inner elastic support (5) is placed inside the outer elastic support (6), and an inner threaded strip (10) is installed on the outer side of the inner elastic support (5). An elastic filler (7) is provided between the inner elastic support (5) and the outer elastic support (6).

2. The elastic buffer type aircraft bushing assembly according to claim 1, characterized in that: The inner wall of the external elastic support (6) is fitted with an external threaded strip (9), which is in the shape of a helical blade.

3. The elastic buffer type aircraft bushing assembly according to claim 2, characterized in that: The internal threaded bar (10) is configured to cooperate with the external threaded bar (9).

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