Interior trim panel structure in aircraft cabin

Abstract

The utility model belongs to the technical field of design of interior trim panels in aircraft cabins, and particularly relates to an interior trim panel structure in an aircraft cabin. The inner-layer plate is arranged opposite to the outer-layer plate; the supporting rods are arranged between the outer layer plate and the inner layer plate; the multiple pairs of damping springs are connected to the two ends of each supporting rod and abut against the inner sides of the outer layer plate and the inner layer plate; the sealing strip is arranged along the edges of the outer-layer plate and the inner-layer plate, and a heat insulation and noise reduction cavity is formed among the sealing strip, the outer-layer plate and the inner-layer plate; and the heat insulation and noise reduction cavity is in a vacuum state.

Description

Technical Field

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

[0002] Currently, interior panels in aircraft cabins usually adopt honeycomb panel structure. Honeycomb panel structure is light in weight and high in strength, but its heat insulation, vibration reduction and noise reduction effects are limited, which makes it difficult to meet the needs of heat insulation, vibration reduction and noise reduction in aircraft cabins.

[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 interior panel structure to overcome or alleviate at least one of the existing technical deficiencies.

[0005] The technical solution of this application is:

[0006] An aircraft cabin interior panel structure, comprising:

[0007] outer panels;

[0008] An inner plate is arranged opposite to the outer plate;

[0009] A plurality of support rods are provided between the outer plate and the inner plate;

[0010] Multiple pairs of damping springs are connected to both ends of each support rod and rest against the inner side of the outer plate and the inner plate;

[0011] The sealing strips are arranged along the edges of the outer layer panels and the inner layer panels, forming a heat-insulating and noise-reducing cavity between the outer layer panels and the inner layer panels; the heat-insulating and noise-reducing cavity is in a vacuum state.

[0012] Optionally, in the above-mentioned aircraft cabin interior trim panel structure, the sealing strip is located between the outer panel and the inner panel, and is adhesively connected to the outer panel and the inner panel.

[0013] Optionally, in the above-mentioned aircraft cabin interior panel structure, there are multiple groups of outer panels and their corresponding inner panels, support rods, vibration damping springs, and sealing strips; connecting gaps are left between the edges of adjacent groups of outer panels and inner panels;

[0014] The aircraft cabin interior panel structure further includes:

[0015] A plurality of connection blocks are arranged in each connection gap;

[0016] Multiple pairs of connecting strips are connected on both sides of each connecting block and pressed tightly against the outer sides of the corresponding groups of outer and inner plates.

[0017] Optionally, in the above-mentioned aircraft cabin interior panel structure, each connecting block is made of rubber material;

[0018] Each pair of connecting strips is made of rubber material.

[0019] Optionally, in the above-mentioned aircraft cabin interior trim panel structure, each pair of connecting strips is bonded to both sides of each connecting block, and bonded to the outer sides of the corresponding group of outer panels and inner panels.

[0020] This application has at least the following beneficial technical effects:

[0021] Provided is an aircraft cabin interior panel structure, in which the interior panel structure is designed as a double-wall panel structure including an outer panel and an inner panel, and a vacuum heat-insulating and noise-reducing cavity is constructed in conjunction with sealing strips. Since sound waves cannot propagate in a vacuum and convective heat transfer cannot occur in a vacuum, the structure can achieve better heat insulation and noise reduction. In addition, the inner sides of the outer panel and the inner panel are designed to have multiple vibration-damping support assemblies composed of vibration-damping springs and support rods, which have a good vibration isolation effect and can well meet the needs of aircraft cabins for heat insulation, vibration reduction, and noise reduction. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 is a schematic diagram of an aircraft cabin interior panel structure provided by an embodiment of the present application;

[0023] Figure 2 This is a schematic diagram of the connection of the aircraft cabin interior panel structure group provided by an embodiment of the present application;

[0024] in:

[0025] 1-outer plate; 2-inner plate; 3-support rod; 4-vibration damping spring; 5-sealing strip; 6-connecting block; 7-connecting strip.

[0026] 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

[0027] 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.

[0028] 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.

[0029] 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.

[0030] An aircraft cabin interior panel structure, such as Figure 1 As shown, including:

[0031] Outer plate 1;

[0032] The inner plate 2 is arranged opposite to the outer plate 1;

[0033] A plurality of support rods 3 are provided between the outer plate 1 and the inner plate 2;

[0034] Multiple pairs of damping springs 4 are connected to both ends of each support rod 3 and rest against the inner side of the outer plate 1 and the inner plate 2;

[0035] The sealing strip 5 is arranged along the edges of the outer layer plate 1 and the inner layer plate 2, and forms a heat-insulating and noise-reducing cavity between the outer layer plate 1 and the inner layer plate 2; the heat-insulating and noise-reducing cavity is in a vacuum state. For this reason, during the production, exhaust holes can be opened on the outer layer plate 1, the inner layer plate 2 or the sealing strip 5 to evacuate the heat-insulating and noise-reducing cavity. After the exhaust is completed, the exhaust holes are blocked to ensure the vacuum state in the heat-insulating and noise-reduction cavity.

[0036] In the interior panel structure of the aircraft cabin disclosed in the above embodiment, the interior panel structure is designed as a double-wall panel structure including an outer panel 1 and an inner panel 2, and a vacuum heat insulation and noise reduction cavity is constructed in conjunction with a sealing strip 5. Since sound waves cannot propagate in a vacuum and convective heat exchange cannot take place in a vacuum, it can have better heat insulation and noise reduction. In addition, the outer panel 1 and the inner panel 2 are designed to have a plurality of vibration-damping support assemblies composed of vibration-damping springs 4 and support rods 3 on the inner side, which has a good vibration isolation effect and can well meet the needs of heat insulation, vibration reduction and noise reduction in the aircraft cabin.

[0037] In some optional embodiments, in the above-mentioned aircraft cabin interior panel structure, the sealing strip 5 is located between the outer panel 1 and the inner panel 2, and is adhesively connected to the outer panel 1 and the inner panel 2 to ensure the reliability and sealing of the connection.

[0038] In some optional embodiments, in the above-mentioned aircraft cabin interior panel structure, there are multiple groups of outer panels 1 and their corresponding inner panels 2, support rods 3, damping springs 4, and sealing strips 5; connecting gaps are left between the edges of adjacent groups of outer panels 1 and inner panels 2;

[0039] The aircraft cabin interior panel structure further includes:

[0040] A plurality of connecting blocks 6 are arranged in each connecting gap;

[0041] Multiple pairs of connecting strips 7 are connected on both sides of each connecting block 6 and pressed against the outer sides of the corresponding outer layer plates 1 and inner layer plates 2. Figure 2 As shown, it is possible to construct interior panels with larger areas.

[0042] In some optional embodiments, in the above-mentioned aircraft cabin interior panel structure, each connecting block 6 is made of rubber material;

[0043] Each pair of connecting bars 7 is made of rubber material to have a good vibration damping effect and reduce the vibration of the entire structure.

[0044] In some optional embodiments, in the above-mentioned aircraft cabin interior panel structure, each pair of connecting strips 7 is bonded to both sides of each connecting block 6, and to the outer sides of the corresponding group of outer panels 1 and inner panels 2 to ensure the reliability and sealing of the connection.

[0045] 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.

[0046] 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 interior panel structure, characterized in that: include: Outer plate (1); An inner plate (2) is arranged opposite to the outer plate (1); A plurality of support rods (3) are arranged between the outer plate (1) and the inner plate (2); Multiple pairs of damping springs (4) are connected to both ends of each support rod (3) and abut against the inner sides of the outer plate (1) and the inner plate (2); The sealing strip (5) is arranged along the edges of the outer plate (1) and the inner plate (2), and forms a heat-insulating and noise-reducing cavity between the outer plate (1) and the inner plate (2); the heat-insulating and noise-reducing cavity is in a vacuum state.

2. The aircraft cabin interior panel structure according to claim 1, characterized in that: The sealing strip (5) is located between the outer plate (1) and the inner plate (2) and is bonded to the outer plate (1) and the inner plate (2).

3. The aircraft cabin interior panel structure according to claim 1, characterized in that: There are multiple groups of outer plates (1) and their corresponding inner plates (2), support rods (3), damping springs (4), and sealing strips (5); connecting gaps are left between the edges of adjacent groups of outer plates (1) and inner plates (2); The aircraft cabin interior panel structure further includes: A plurality of connection blocks (6) are arranged in each connection gap; A plurality of pairs of connecting strips (7) are connected to both sides of each connecting block (6) and pressed against the outer sides of the corresponding groups of outer plates (1) and inner plates (2).

4. The aircraft cabin interior panel structure according to claim 3, characterized in that: The plurality of connecting blocks (6) are made of rubber material; Each pair of connecting strips (7) is made of rubber material.

5. The aircraft cabin interior panel structure according to claim 4, characterized in that: Each pair of connecting strips (7) is bonded to both sides of each connecting block (6), and is bonded to the outer sides of the corresponding group of outer layer plates (1) and inner layer plates (2).

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