Vibration reduction structure between cabin door and cabin door frame of airplane

Abstract

The utility model belongs to the technical field of vibration reduction design between an aircraft cabin door and a cabin door frame, and particularly relates to a vibration reduction structure between an aircraft cabin door and a cabin door frame, which comprises a metal mounting sheet connected to the cabin door frame and matched with the cabin door frame structure; the rubber block is connected to the metal mounting sheet and is matched with the cabin door structure; and the chemical and blended fabric is embedded in the rubber block and is intensively distributed at the thicker part of the rubber block.

Description

Technical Field

[0001] The present application belongs to the technical field of vibration reduction design between aircraft cabin doors and cabin door frames, and specifically relates to a vibration reduction structure between aircraft cabin doors and cabin door frames. Background Art

[0002] When the cabin door on an airplane is closed, it collides with the door frame, making a loud collision noise and generating large vibrations, which can cause long-term damage to the door and door frame. For this reason, a vibration-damping structure is designed between the door and the door frame.

[0003] At present, rubber is mostly pasted on the door frame as a vibration-damping structure. When the door collides with the door frame when closed, it can play a buffering role between the door and the door frame, avoiding direct collision between the door and the door frame. This will reduce the collision sound and vibration between the door and the door frame, and avoid collision damage to the door and the door frame. However, the rubber is a flat strip structure and cannot adapt well to the curved structure on the door. When the door is closed and collides with the door frame, the impact force is not evenly distributed. The rubber lacks adaptive design for this and is prone to local damage.

[0004] This application is proposed in view of the above-mentioned technical defects. Utility Model Content

[0005] The purpose of the present application is to provide a vibration reduction structure between an aircraft door and a door frame, so as to overcome or alleviate at least one of the technical defects of the known ones.

[0006] The technical solution of this application is:

[0007] A vibration reduction structure between an aircraft door and a door frame, comprising:

[0008] Metal mounting plate, connected to the door frame, adapted to the door frame structure;

[0009] The rubber block is connected to the metal mounting plate and adapted to the door structure;

[0010] The chemical fiber fabric is embedded in the rubber block and concentrated in the areas where the rubber block is thicker.

[0011] Optionally, in the above-mentioned vibration reduction structure between the aircraft door and the door frame, the metal mounting plate is connected to the door frame by bolts.

[0012] Optionally, in the above-mentioned vibration reduction structure between the aircraft door and the door frame, the rubber block is connected to the metal mounting plate by a vulcanization process, or is bonded to the metal mounting plate by glue.

[0013] Optionally, in the above-mentioned vibration-damping structure between the aircraft door and the door frame, the chemical fiber fabric is nylon yarn, carbon fiber or non-woven fabric.

[0014] Optionally, in the above-mentioned vibration reduction structure between the aircraft door and the door frame, a plurality of weight-reducing and vibration-reducing grooves are distributed on the rubber block.

[0015] This application has at least the following beneficial technical effects:

[0016] Provided is a vibration reduction structure between an aircraft cabin door and a cabin door frame, in which a rubber block is designed as the main vibration reduction structure between the cabin door and the cabin door frame. The rubber block is connected to the metal mounting plate via a metal mounting plate. The rubber block and the metal mounting plate are easy to shape. The metal mounting plate and the rubber block can be easily shaped to adapt to the cabin door frame and the cabin door structure respectively. When the cabin door collides with the cabin door frame when closed, the rubber block can well adapt to the curved surface structure on the cabin door and the uneven distribution of the impact force to avoid damage. In addition, chemical fiber fabrics are concentratedly embedded in the thicker parts of the rubber block to enhance the hardness of the thicker parts of the rubber block, maintain the overall shape of the rubber block, avoid deformation, and suffer greater local extrusion damage when the cabin door collides with the cabin door frame when closed. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 is a schematic diagram of a vibration reduction structure between an aircraft door and a door frame provided by an embodiment of the present application;

[0018] in:

[0019] 1-Metal mounting plate; 2-Rubber block; 3-Chemical fiber fabric.

[0020] In order to better illustrate this embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and should not be understood as limiting this application. DETAILED DESCRIPTION

[0021] To make the technical solution and its advantages of this application more clear, the technical solution of this application will be further described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described here are only some of the embodiments of this application and are only used to explain this application, not to limit this application. It should be noted that for ease of description, only the parts relevant to this application are shown in the accompanying drawings, and other relevant parts can refer to the general design.

[0022] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should have the usual meanings understood by those skilled in the art in the field to which this application belongs. The words indicating orientation used in the description of this application are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "include" used in the description of this application means that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0023] In addition, it should be noted that, unless otherwise clearly stipulated and limited, the words "installation", "connection" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Technical personnel in the field can understand its specific meaning in this application according to the specific circumstances.

[0024] A vibration reduction structure between an aircraft door and a door frame, such as Figure 1 Shown, including:

[0025] Metal mounting plate 1, connected to the door frame and adapted to the door frame structure;

[0026] The rubber block 2 is connected to the metal mounting plate 1 and is adapted to the hatch structure;

[0027] The chemical fiber fabric 3 is embedded in the rubber block 2 and is concentrated in the thicker portion of the rubber block 2 .

[0028] In the above-mentioned vibration reduction structure between the aircraft cabin door and the cabin door frame, a rubber block 2 is designed as the main vibration reduction structure between the cabin door and the cabin door frame. The rubber block 2 is connected to the metal mounting plate 1 through the metal mounting plate 1. The rubber block 2 and the metal mounting plate 1 are easy to shape. The metal mounting plate 1 and the rubber block 2 can be easily modified to adapt to the cabin door frame and the cabin door structure respectively. When the cabin door is closed and collides with the cabin door frame, the rubber block 2 can adapt well to the curved surface structure on the cabin door and the uneven distribution of the impact force to avoid damage.

[0029] In the above-mentioned vibration damping structure between the aircraft cabin door and the cabin door frame, since the rubber block 2 is designed to adapt to the cabin door structure, it is inevitable that the thickness varies in different places, and there are areas with larger thickness. Compared with the thinner areas, the thicker areas of the rubber block 2 are less supported by the metal mounting plate 1, are relatively soft, and are prone to deformation. The chemical fiber fabric 3 is concentratedly embedded in the thicker areas of the rubber block 2 to enhance the hardness of the thicker areas of the rubber block 2, maintain the overall shape of the rubber block 2, and avoid deformation, which would cause greater local extrusion damage when the cabin door collides with the cabin door frame when closed.

[0030] In some optional embodiments, in the above-mentioned vibration reduction structure between the aircraft door and the door frame, the metal mounting plate 1 is connected to the door frame by bolts.

[0031] In some optional embodiments, in the above-mentioned vibration reduction structure between the aircraft door and the door frame, the rubber block 2 is connected to the metal mounting plate 1 by a vulcanization process, or is bonded to the metal mounting plate 1 by glue, so that the connection between the rubber block 2 and the metal mounting plate 1 is reliable.

[0032] In some optional embodiments, in the above-mentioned vibration-damping structure between the aircraft door and the door frame, the chemical fiber fabric 3 is nylon yarn, carbon fiber or non-woven fabric, or can be other fabrics that are easily available and have greater flexibility.

[0033] In some optional embodiments, in the above-mentioned vibration reduction structure between the aircraft cabin door and the cabin door frame, a plurality of weight-reducing and vibration-reducing grooves are distributed on the rubber block 2, which can reduce the overall mass of the structure on the one hand, and enhance the damping effect of the rubber block 2 on the other hand, thereby improving the vibration reduction effect of the cabin door closing and the collision with the cabin door frame.

[0034] The various embodiments in the specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the various embodiments can be referenced to each other. In the absence of conflict, the embodiments in this application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0035] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or replacements to the relevant technical features, and the technical solutions after these changes or replacements will fall within the scope of protection of the present application.

Claims

1. A vibration reduction structure between an aircraft door and a door frame, characterized in that: include: A metal mounting plate (1) is connected to the door frame and is adapted to the door frame structure; A rubber block (2) is connected to the metal mounting plate (1) and is adapted to the door structure; The chemical fiber fabric (3) is embedded in the rubber block (2) and is concentratedly distributed at the thicker portion of the rubber block (2).

2. The vibration reduction structure between an aircraft door and a door frame according to claim 1, characterized in that: The metal mounting plate (1) is connected to the door frame by bolts.

3. The vibration reduction structure between an aircraft door and a door frame according to claim 1, characterized in that: The rubber block (2) is connected to the metal mounting plate (1) by a vulcanization process, or is bonded to the metal mounting plate (1) by glue.

4. The vibration reduction structure between an aircraft door and a door frame according to claim 1, characterized in that: The chemical fiber fabric (3) is nylon yarn, carbon fiber or non-woven fabric.

5. The vibration reduction structure between an aircraft door and a door frame according to claim 1, wherein: A plurality of weight-reducing and vibration-reducing grooves are distributed on the rubber block (2).

Images