Damping mechanism for aircraft interior trim

Abstract

The utility model provides a damping mechanism for an aircraft interior, which relates to the field of aircraft interior accessories and comprises a fixing box and a support, the fixing box is provided with a containing space, a damping bag is arranged in the containing space, and the support enters the containing space and is connected with the damping bag, so that the support has a damping function within the deformation range of the damping bag. The damping mechanism for the aircraft interior trim has the advantages of being good in damping effect, large in radial rigidity and axial rigidity, capable of being rapidly disassembled and assembled and the like.

Description

Technical Field

[0001] This utility model relates to the field of aircraft interior accessories, and in particular to a shock absorption mechanism for aircraft interiors. Background Technology

[0002] Vibration dampers, as general-purpose components widely used in various types of equipment, play a crucial role in extending equipment lifespan and optimizing operating conditions by reducing vibration and absorbing impact energy. While current mainstream spring and rubber vibration dampers can meet basic requirements, they share common drawbacks such as complex structures and high costs. Spring vibration dampers suffer from high production costs due to their multi-layered component nesting, and require significant installation space due to their structural characteristics. Traditional rubber vibration dampers, on the other hand, are limited by material properties, exhibiting significant shortcomings in dynamic response characteristics and durability. These technical bottlenecks severely restrict the application expansion of vibration dampers in precision equipment and miniaturized environments. Utility Model Content

[0003] The purpose of this invention is to provide a shock-absorbing mechanism for aircraft interiors to solve the aforementioned technical problems.

[0004] To solve the above-mentioned technical problems, this utility model adopts the following technical solution:

[0005] A shock-absorbing mechanism for aircraft interiors includes a fixed box and a bracket. The fixed box has a receiving space, in which a shock-absorbing bag is placed. The bracket enters the receiving space and connects to the shock-absorbing bag, so that the bracket has a shock-absorbing function within the deformation range of the shock-absorbing bag.

[0006] Preferably, the portion of the bracket that enters the accommodating space is fitted with the shock-absorbing package.

[0007] Preferably, the shock-absorbing package is a composite structure.

[0008] Preferably, the shock absorber includes a soft sleeve and a soft plug, wherein the soft sleeve has a cavity inside and the soft plug enters the cavity.

[0009] Preferably, the soft sleeve has an annular groove on its outer periphery, and the bracket that enters the accommodating space is fitted with the annular groove.

[0010] Preferably, the soft plug that enters the soft sleeve is fixedly bonded to the soft sleeve by adhesive.

[0011] Preferably, the soft sleeve and the soft plug respectively contact two opposite surfaces in the accommodating space.

[0012] Preferably, both the soft sleeve and the soft plug are made of rubber.

[0013] Preferably, the outer periphery of the fixing box has a first mounting position, and the portion of the bracket not entering the accommodating space has a second mounting position.

[0014] The beneficial effects of this utility model are:

[0015] 1. The shock-absorbing mechanism for aircraft interior proposed in this utility model has the advantages of good shock absorption effect, large radial and axial stiffness, and quick assembly and disassembly.

[0016] 2. In this utility model, the fixing box used to form the shock absorption mechanism has no physical fixing structure, and the shock absorption bag inside it has a large adjustment space. Attached Figure Description

[0017] Figure 1 This is a structural schematic diagram of a shock absorption mechanism for aircraft interiors.

[0018] Figure 2 for Figure 1 The front view of the shock absorption mechanism shown;

[0019] Figure 3 for Figure 2 A cross-sectional view of the shock absorption mechanism shown;

[0020] Figure 4 This is a schematic diagram of the support structure;

[0021] Figure 5 This is a cross-sectional view of the shock-absorbing package;

[0022] Reference numerals: 1. Bracket; 2. Fixing box; 3. Shock-absorbing bag; 4. Opening; 5. Annular groove; 31. Soft sleeve; 32. Soft plug. Detailed Implementation

[0023] To facilitate understanding of this utility model, a more complete description will be given below with reference to the accompanying drawings. Preferred embodiments of this utility model are shown in the drawings. However, this utility model can be implemented in many different forms and is not limited to the embodiments described herein. Rather, these embodiments are provided to provide a more thorough and complete understanding of the disclosure of this utility model.

[0024] 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 is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention.

[0025] The specific embodiments of this utility model are described below with reference to the accompanying drawings.

[0026] Example 1

[0027] This embodiment presents a shock-absorbing mechanism for aircraft interiors; please refer to [link / reference]. Figures 1-5The aircraft interior shock-absorbing mechanism includes a bracket 1 and a mounting box 2. The bracket 1 is bent, and the bent portion is divided into two parts along a center line. One part has a second mounting position, and the other part enters the mounting box 2. Further, the mounting box 2 has an accommodating space, and there is a first mounting position on the periphery of the mounting box 2. Additionally, a portion of the bracket 1 enters the accommodating space. Even further, the accommodating space contains a rubber shock-absorbing pad 3, which is connected to the bracket 1, enabling the bracket 1 to provide shock absorption within the deformation range of the shock-absorbing pad 3.

[0028] In this embodiment, the aforementioned shock-absorbing package 3 is a combined structure, specifically including a soft sleeve 31 and a soft plug 32, as shown below. Figure 5 As shown, the soft sleeve 31 has an internal cavity, and the soft plug 32 enters the cavity and is fixedly attached to the soft sleeve 31 with adhesive. Also, please refer to... Figures 3-5 The part of the bracket 1 that enters the accommodating space has an opening 4, and an annular groove 5 is provided on the periphery of the soft sleeve 31 to match the opening 4. The annular groove 5 engages with the opening 4, so that the bracket 1 and the shock-absorbing bag 3 form a stable connection.

[0029] The shock absorption mechanism proposed in this embodiment is suitable for vibration reduction work in areas where two components are combined and need to be frequently disassembled. The fixing box 2 can be fixed based on the first mounting position, and the bracket 1 can be fixed based on the second mounting position. After all the fixing processes are completed, the shock absorption bag 3 connected to the bracket 1 can be inserted into the accommodating space in the fixing box 2 to perform shock absorption. Of course, when maintenance is required, the combination state can be released by pulling the bracket 1 backward to pull the shock absorption bag 3 out of the fixing box 2.

[0030] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0031] The embodiments described above are merely illustrative of several implementations of this utility model, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the utility model patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this utility model, and these all fall within the protection scope of this utility model. Therefore, the protection scope of this utility model patent should be determined by the appended claims.

Claims

1. A shock-absorbing mechanism for aircraft interior, characterized in that: The device includes a fixing box and a bracket. The fixing box has a receiving space, in which a shock-absorbing bag is installed. The bracket enters the receiving space and connects to the shock-absorbing bag, so that the bracket has a shock-absorbing function within the deformation range of the shock-absorbing bag.

2. The shock absorption mechanism for aircraft interior as described in claim 1, characterized in that: The portion of the bracket that enters the accommodating space is fitted with the aforementioned shock-absorbing package.

3. A shock-absorbing mechanism for aircraft interior as described in claim 2, characterized in that: The shock-absorbing package is a composite structure.

4. A shock-absorbing mechanism for aircraft interior as described in claim 3, characterized in that: The shock absorber kit includes a soft sleeve and a soft plug. The soft sleeve has a cavity inside, and the soft plug enters the cavity.

5. A shock-absorbing mechanism for aircraft interior as described in claim 4, characterized in that: The soft sleeve has an annular groove on its outer perimeter, and the bracket that enters the accommodating space is fitted with the annular groove.

6. A shock-absorbing mechanism for aircraft interior as described in claim 4, characterized in that: The soft plug that goes inside the soft sleeve is fixed to the soft sleeve with adhesive.

7. A shock-absorbing mechanism for aircraft interior as described in claim 5, characterized in that: The soft sleeve and soft plug respectively contact two opposite surfaces in the accommodating space.

8. A shock-absorbing mechanism for aircraft interior as described in claim 5, characterized in that: Both the soft sleeve and the soft plug are made of rubber.

9. A shock-absorbing mechanism for aircraft interior as described in claim 1, characterized in that: There is a first mounting position on the outer perimeter of the fixing box, and a second mounting position on the part of the bracket that does not enter the accommodating space.

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