Aircraft cabin structure

Abstract

The utility model belongs to the technical field of aircraft cabin structure design, and particularly relates to an aircraft cabin structure which comprises an annular outer skin; the inner skin is annular and is arranged in the outer skin, and the inner skin and the two ends of the outer skin are blocked to form a heat insulation and noise reduction cavity; the heat insulation and noise reduction cavity is in a vacuum state; the multiple inter-skin supporting rods are arranged in the heat insulation and noise reduction cavity in the circumferential direction; and the multiple pairs of inter-skin vibration reduction damping blocks are connected to the two ends of each inter-skin supporting rod and are attached to the side walls of the outer skin and the inner skin.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft cabin structure design, and specifically relates to an aircraft cabin structure. Background Art

[0002] Currently, most aircraft cabins use a single-layer skin design. The single-layer skin is light in weight, but has limited effects in heat insulation, vibration reduction, and noise reduction, making it difficult to meet the needs of heat insulation, vibration reduction, and noise reduction in the aircraft cabin. In addition, the aircraft cabin is designed with a floor, and currently, the floor is mostly directly connected to the inner side of the single-layer skin, which can easily generate large vibration stress and cause structural damage.

[0003] This application is proposed in view of the above-mentioned technical defects. Utility Model Content

[0004] The purpose of the present application is to provide an aircraft cabin structure to overcome or alleviate at least one of the technical deficiencies of the prior art.

[0005] The technical solution of this application is:

[0006] An aircraft cabin structure, comprising:

[0007] The outer skin is annular;

[0008] The inner skin is annular and is arranged inside the outer skin. It is sealed with both ends of the outer skin to form a heat-insulating and noise-reducing cavity. The heat-insulating and noise-reducing cavity is in a vacuum state.

[0009] Multiple inter-skin support rods are arranged circumferentially in the heat insulation and noise reduction cavity;

[0010] Multiple pairs of inter-skin vibration damping blocks are connected to the two ends of each inter-skin support rod and are affixed to the side walls of the outer skin and inner skin.

[0011] Optionally, in the above-mentioned aircraft cabin structure, each pair of inter-skin vibration damping blocks are made of rubber material and bonded to both ends of each inter-skin support rod, as well as to the side walls of the outer skin and the inner skin.

[0012] Optionally, the above-mentioned aircraft cabin structure further includes:

[0013] Floor, set within the inner skin;

[0014] The vibration damping strips between the skin and floor are arranged around the edge of the floor and abut against the side walls of the inner skin;

[0015] A plurality of inter-skin and inter-floor support rods are arranged in the bottom support space formed between the inner skin and the floor;

[0016] Multiple pairs of vibration-damping blocks between the skin and floor panels are connected to both ends of the support rods between the skin and floor panels and are affixed to the inner skin and the side walls of the floor panels.

[0017] Optionally, in the above-mentioned aircraft cabin structure, the vibration-damping strips between the skin and the floor are made of rubber material and are bonded to the edges of the floor and to the side walls of the inner skin.

[0018] Optionally, in the above-mentioned aircraft cabin structure, each pair of vibration-damping damping blocks between the skin and floor are made of rubber material and bonded to both ends of each support rod between the skin and floor, as well as to the inner skin and the side walls of the floor.

[0019] This application has at least the following beneficial technical effects:

[0020] Provided is an aircraft cabin structure in which the skin is designed as a double-layer structure including an outer skin and an inner skin, and both ends are sealed to form a vacuum heat-insulating and noise-reducing cavity. Since sound waves cannot propagate in a vacuum and convective heat transfer cannot occur in a vacuum, the structure can provide good heat insulation and noise reduction. In addition, the inner sides of the outer skin and the inner skin are designed to have a plurality of vibration-damping support assemblies composed of inter-skin support rods and inter-skin vibration-damping damping blocks, thereby providing good vibration isolation effect and being able to well meet the requirements for heat insulation, vibration reduction and noise reduction in the aircraft cabin. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 is a schematic diagram of an aircraft cabin structure provided by an embodiment of the present application;

[0022] in:

[0023] 1-outer skin; 2-inner skin; 3-support rods between skins; 4-vibration damping blocks between skins; 5-floor; 6-vibration damping strips between skin and floor; 7-support rods between skin and floor; 8-vibration damping blocks between skin and floor.

[0024] 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

[0025] 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.

[0026] 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.

[0027] 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.

[0028] An aircraft cabin structure, such as Figure 1 Shown, including:

[0029] Outer skin 1, annular;

[0030] The inner skin 2 is annular and is arranged inside the outer skin 1. It is sealed with both ends of the outer skin 1, and can be sealed with a sealing ring to form a heat-insulating and noise-reducing cavity. The heat-insulating and noise-reducing cavity is in a vacuum state. To this end, during production, a vacuum hole can be opened on the outer skin 1, the inner skin 2 or the sealing ring to vacuum the heat-insulating and noise-reducing cavity. After the vacuum is completed, the vacuum hole is sealed to ensure the vacuum state in the heat-insulating and noise-reducing cavity.

[0031] A plurality of inter-skin support rods 3 are arranged along the circumferential direction of the heat insulation and noise reduction cavity;

[0032] A plurality of pairs of inter-skin vibration damping blocks 4 are connected to both ends of each inter-skin support rod 3 and are abutted against the side walls of the outer skin 1 and the inner skin 2 .

[0033] In the aircraft cabin structure disclosed in the above embodiment, the skin is designed to be a double-layer structure including an outer skin 1 and an inner skin 2, and both ends are sealed to construct a vacuum insulation and noise reduction cavity. Since sound waves cannot propagate in a vacuum and convective heat transfer cannot take place in a vacuum, it can have better insulation and noise reduction. In addition, the inner sides of the outer skin 1 and the inner skin 2 are designed to have multiple vibration-damping support assemblies composed of inter-skin support rods 3 and inter-skin vibration-damping damping blocks 4, which have better vibration isolation effect and can well meet the needs of aircraft cabin for insulation, vibration reduction and noise reduction.

[0034] In some optional embodiments, in the above-mentioned aircraft cabin structure, each pair of inter-skin vibration damping blocks 4 are made of rubber material and are bonded to the two ends of each inter-skin support rod 3, as well as to the side walls of the outer skin 1 and the inner skin 2, so that the connection between the structures is reliable.

[0035] In some optional embodiments, the above-mentioned aircraft cabin structure further includes:

[0036] A floor 5 is provided in the inner skin 2;

[0037] The vibration damping strip 6 between the skin and the floor is arranged around the edge of the floor 5 and abuts against the side wall of the inner skin 2 to reduce the vibration stress between the inner skin 2 and the floor 5 to avoid structural damage;

[0038] A plurality of inter-skin and inter-floor support rods 7 are provided in the bottom support space formed between the inner skin 2 and the floor 5;

[0039] Multiple pairs of vibration-damping blocks 8 between the skin and floor are connected to the two ends of each support rod 7 between the skin and floor, and are abutted against the side walls of the inner skin 2 and the floor 5 to provide vibration-damping support for the floor 5, thereby reducing the vibration stress between the inner skin 2 and the floor 5 and avoiding structural damage.

[0040] In some optional embodiments, in the above-mentioned aircraft cabin structure, the vibration-damping strip 6 between the skin and the floor is made of rubber material and is bonded to the edge of the floor 5 and to the side wall of the inner skin 2 to ensure a reliable connection between the structures.

[0041] In some optional embodiments, in the above-mentioned aircraft cabin structure, each pair of vibration-damping damping blocks 8 between the skin and floor are made of rubber material and are bonded to both ends of each support rod 7 between the skin and floor, as well as to the side walls of the inner skin 2 and the floor 5, so that the connection between the structures is reliable.

[0042] 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.

[0043] 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. An aircraft cabin structure, characterized in that: include: An outer skin (1) in a ring shape; The inner skin (2) is annular and is arranged inside the outer skin (1), and is sealed with both ends of the outer skin (1) to form a heat-insulating and noise-reducing cavity; the heat-insulating and noise-reducing cavity is in a vacuum state; A plurality of inter-skin support rods (3) are arranged circumferentially in the heat insulation and noise reduction cavity; A plurality of pairs of inter-skin vibration damping blocks (4) are connected to both ends of each inter-skin support rod (3) and are abutted against the side walls of the outer skin (1) and the inner skin (2).

2. The aircraft cabin structure according to claim 1, characterized in that: Each pair of inter-skin vibration damping blocks (4) are made of rubber material and are bonded to both ends of each inter-skin support rod (3) and to the side walls of the outer skin (1) and the inner skin (2).

3. The aircraft cabin structure according to claim 1, characterized in that: Also includes: A floor (5) is provided inside the inner skin (2); A vibration damping strip (6) between the skin and the floor is arranged around the edge of the floor (5) and abuts against the side wall of the inner skin (2); A plurality of inter-skin and inter-floor support rods (7) are arranged in a bottom support space formed between the inner skin (2) and the floor (5); A plurality of pairs of inter-skin and inter-floor vibration damping blocks (8) are connected to both ends of each inter-skin and inter-floor support rod (7) and are abutted against the side walls of the inner skin (2) and the floor (5).

4. The aircraft cabin structure according to claim 1, characterized in that: The vibration damping strip (6) between the skin and the floor is made of rubber material and is bonded to the edge of the floor (5) and to the side wall of the inner skin (2).

5. The aircraft cabin structure according to claim 1, characterized in that: Each pair of inter-skin and inter-floor vibration damping blocks (8) are made of rubber material and are bonded to both ends of each inter-skin and inter-floor support rod (7), as well as to the inner skin (2) and the side walls of the floor (5).

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