CN-224229172-U - 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 fixed box and a bracket, wherein the fixed box is provided with a containing space, a damping bag is arranged in the containing space, and the bracket enters the containing space and is connected with the damping bag, so that the bracket has a damping function in the deformation range of the damping bag. The damping mechanism for the aircraft interior provided by the utility model has the advantages of good damping effect, high radial and axial rigidity, capability of being quickly disassembled and assembled and the like.

Inventors

• HE RUI
• YIN YANJIAO
• CHEN NING

Assignees

• 菲舍尔航空部件（镇江）有限公司

Dates

Publication Date

20260512

Application Date

20250603

Claims (9)

1. 1. The damping mechanism for the aircraft interior is characterized by comprising a fixed box and a bracket, wherein the fixed box is provided with a containing space, a damping bag is arranged in the containing space, and the bracket enters the containing space and is connected with the damping bag, so that the bracket has a damping function in the deformation range of the damping bag.
2. 2. A damping mechanism for aircraft interior according to claim 1, wherein the portion of the bracket that enters the receiving space is covered with the damping pack.
3. 3. A damping mechanism for aircraft interior according to claim 2, wherein the damping pack is of a composite construction.
4. 4. A damping mechanism for an aircraft interior according to claim 3, wherein the damping pack comprises a soft sleeve and a soft plug, wherein the soft sleeve has a cavity therein, and the soft plug enters the cavity.
5. 5. The damping mechanism for aircraft interior according to claim 4, wherein the soft cover has an annular groove on its periphery, and the bracket entering the accommodating space is sleeved with the annular groove.
6. 6. The damping mechanism for aircraft interior according to claim 4, wherein the soft plug entering the soft sleeve is fixedly combined with the soft sleeve through an adhesive.
7. 7. The damping mechanism for aircraft interior according to claim 5, wherein the soft cover and the soft plug are in contact with opposite surfaces of the accommodating space.
8. 8. The aircraft interior damping mechanism according to claim 5, wherein the soft cover and the soft plug are made of rubber.
9. 9. The damping mechanism for aircraft interior according to claim 1, wherein the fixing box has a first mounting position at the periphery thereof, and a second mounting position at a portion of the bracket which does not enter the accommodating space.

Description

Damping mechanism for aircraft interior trim Technical Field The utility model relates to the field of aircraft interior accessories, in particular to a damping mechanism for aircraft interior. Background The shock absorber is used as a universal part widely applied to various devices, and plays a key role in prolonging the service life of the devices and optimizing the operation conditions by weakening vibration and absorbing impact energy. The current mainstream spring damper and rubber damper can meet basic requirements, but have the common defects of complex structure, higher cost and the like, namely the spring damper has high production cost due to the nesting of multiple layers of components and is limited by the structural characteristics of the spring damper to require a larger installation space, while the traditional rubber damper is limited by material performance, has obvious short plates in the aspects of dynamic response characteristics and durability, and the technical bottlenecks seriously restrict the application expansion of the damper in precision equipment and miniaturized scenes. Disclosure of utility model The utility model aims to provide a damping mechanism for aircraft interior decoration, so as to solve the technical problems. The utility model aims to solve the technical problems, and is realized by adopting the following technical scheme: the utility model provides a damper for aircraft interior, includes fixed box, support, and wherein, fixed box has the accommodation space, and the accommodation space is equipped with the shock attenuation package in, the support get into in the accommodation space with the shock attenuation package is connected, makes the support have the shock attenuation function in the shock attenuation package deformation scope. Preferably, the portion of the bracket entering the accommodating space is sleeved with the shock absorbing bag. Preferably, the shock absorbing package is a composite structure. Preferably, the shock absorbing bag comprises a soft sleeve and a soft plug, wherein a cavity is formed in the soft sleeve, and the soft plug enters the cavity. Preferably, the soft sleeve is provided with an annular groove at the periphery, and the support entering the accommodating space is sleeved with the annular groove. Preferably, the soft plug entering the soft sleeve is fixedly combined with the soft sleeve through the viscose. Preferably, the soft cover and the soft plug are respectively contacted with two opposite surfaces in the accommodating space. Preferably, the soft sleeve and the soft plug are made of rubber. Preferably, the periphery of the fixing box is provided with a first installation position, and the part of the bracket which does not enter the accommodating space is provided with a second installation position. The beneficial effects of the utility model are as follows: 1. The damping mechanism for the aircraft interior provided by the utility model has the advantages of good damping effect, high radial and axial rigidity, capability of being quickly disassembled and assembled and the like. 2. The fixing box used for forming the damping mechanism has no physical fixing structure, and the damping bag entering the fixing box has a larger adjusting space. Drawings FIG. 1 is a schematic view of a shock absorbing mechanism for an aircraft interior; FIG. 2 is a front view of the shock absorbing mechanism shown in FIG. 1; FIG. 3 is a cross-sectional view of the shock absorbing mechanism shown in FIG. 2; FIG. 4 is a schematic structural view of a bracket; FIG. 5 is a cross-sectional view of a shock package; Reference numeral 1, a bracket, 2, a fixed box, 3, a shock absorption bag, 4, a through hole, 5, an annular groove, 31, a soft sleeve, 32 and a soft plug. Detailed Description In order that the utility model may be readily understood, a more complete description of the utility model will be rendered by reference to the appended drawings. Preferred embodiments of the present utility model are shown in the drawings. This utility model may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete. Unless defined otherwise, 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 utility model belongs. The terminology used herein in the description of the utility model is for the purpose of describing particular embodiments only and is not intended to be limiting of the utility model. Specific embodiments of the present utility model are described below with reference to the accompanying drawings. Example 1 In this embodiment, referring to fig. 1 to 5, a damping mechanism for an aircraft interior is provided, which includes a bracket 1 and a fixing case 2, wherein the bracket 1 is bent, the bent portion