Civil branch aircraft cabin side wall mounting structure

Abstract

The invention belongs to the technical field of aircrafts, and particularly relates to a civil branch aircraft passenger cabin side wall mounting structure which is characterized in that multiple groups of mounting structures are mounted along splicing seams of adjacent interior trim panels, and each mounting structure comprises two primary supports, a secondary support and a tertiary support; each primary support comprises a fixed end and a connecting end, the fixed end of one primary support is connected with the corresponding interior trim panel, the connecting end of the primary support is connected with the middle section of the secondary support, the fixed end of the other primary support is connected with the other interior trim panel, and the connecting end of the primary support is connected with the middle section of the secondary support; the secondary support comprises a middle section and warped ends formed by bending the two ends of the middle section in the direction away from the interior trim panel, and the warped ends are fixedly connected with the tertiary support. The tertiary support is fixedly connected with a machine body mounting frame located on the inner side of the interior trim panel by a certain distance and used for reducing vibration transmitted by a machine body to the interior trim panel.

Description

Technical Field

[0001] The present application belongs to the field of aircraft technology, and in particular relates to a cabin side wall mounting structure for a civil regional aircraft. Background Art

[0002] The interior panels of the cabin of a civil regional aircraft are connected to the fuselage mounting frame inside the wall, but the fuselage mounting frame is integrated with the aircraft. Therefore, the vibration or deformation of the aircraft fuselage is transmitted to the interior panels. A connection structure between flexibility and rigidity is required to prevent the vibration of the aircraft fuselage from being transmitted to the aircraft cabin. Summary of the invention

[0003] In order to solve the above problems, the present application provides a civil feeder aircraft cabin side wall mounting structure, wherein multiple groups of mounting structures are installed along the joints of adjacent interior panels, and each mounting structure includes:

[0004] Two primary brackets, one secondary bracket, and one tertiary bracket;

[0005] The primary bracket includes a fixed end and a connecting end, the fixed end of one primary bracket is connected to the interior trim panel, and the connecting end is connected to the middle section of the secondary bracket, and the fixed end of another primary bracket is connected to another interior trim panel, and the connecting end is connected to the middle section of the secondary bracket;

[0006] The secondary bracket includes a middle section and two ends of the middle section that are bent away from the interior trim panel to form warped ends, and the warped ends are fixedly connected to the tertiary bracket;

[0007] The tertiary bracket is fixedly connected to the fuselage mounting frame located at a certain distance inside the interior trim panel.

[0008] Preferably, a clip strip covering the joint seam is provided at the joint seam position.

[0009] Preferably, a rubber pad is provided between the primary bracket and the interior trim panel to reduce vibration transmitted from the fuselage mounting frame to the interior trim panel.

[0010] Preferably, there is a bend between the fixed end and the connecting end of the primary bracket, so that the connecting end is offset in a direction away from the interior panel. The bend allows the primary bracket to form an elastic structure, thereby reducing vibration transmitted from the fuselage mounting frame to the interior panel.

[0011] Preferably, the warped end enables the secondary bracket to form an elastic structure, thereby reducing vibration transmitted from the fuselage mounting frame to the interior trim panel.

[0012] Preferably, a vibration damper is provided between the secondary bracket and the tertiary bracket, and the vibration damper reduces vibration transmitted from the fuselage mounting frame to the interior trim panel.

[0013] Preferably, the connecting line of the two warped ends of the secondary support is parallel to the joint seam, so as to resist the tilting along the joint seam direction transmitted from the tertiary support.

[0014] Preferably, the secondary bracket is arranged along the joint seam with two connection points of the two primary brackets respectively, and when the secondary bracket is tilted along the joint seam, the two primary brackets are bent to different degrees to offset the overturning force.

[0015] Preferably, the primary bracket is connected to the interior trim panel via mounting screws and gaskets.

[0016] Preferably, the secondary bracket is fixed to the shock absorber by means of screws and washers, and the shock absorber is riveted to the tertiary bracket.

[0017] Preferably, each interior trim panel is installed with at least four sets of mounting structures.

[0018] The advantages of the present application include: the bending axis of the primary bracket is along the joint seam, and the bending axis of the secondary bracket is perpendicular to the joint seam direction, which can offset the skewness and vibration in multiple directions. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 This is a schematic diagram of a cabin side wall installation of a civil feeder aircraft in a preferred embodiment of the present application;

[0020] Figure 2 A schematic diagram of the installation of a cabin side wall connection assembly for a civil regional aircraft. DETAILED DESCRIPTION

[0021] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be further described in detail in detail and in detail in conjunction with the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design. In the absence of conflict, the embodiments in the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0022] In addition, it should be noted that, unless otherwise clearly specified and limited, the words "installed", "connected", "connected" 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, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, an indirect connection through an intermediate medium, or the internal connection of two components. Technical personnel in the field can understand their specific meanings in this application according to the specific circumstances.

[0023] like Figure 1-Figure 2 As shown, the present application provides a civil feeder aircraft cabin side wall mounting structure, wherein multiple groups of mounting structures are installed along the joint seams of adjacent interior panels 1, and each mounting structure includes:

[0024] Two primary brackets 2, one secondary bracket 6, and one tertiary bracket 4;

[0025] The primary bracket 2 includes a fixed end and a connecting end. The fixed end of one primary bracket 2 is connected to the interior panel 1, and the connecting end is connected to the middle section of the secondary bracket 6. The fixed end of another primary bracket 2 is connected to another interior panel 1, and the connecting end is connected to the middle section of the secondary bracket 6.

[0026] The secondary bracket 6 includes a middle section and two ends of the middle section that are bent away from the interior trim panel 1 to form warped ends, and the warped ends are fixedly connected to the tertiary bracket 4;

[0027] The tertiary bracket 4 is fixedly connected to the fuselage mounting frame which is located at a certain distance inside the interior trim panel 1 .

[0028] In some optional embodiments, a clip strip 10 covering the joint seam is provided at the joint seam position.

[0029] In some optional embodiments, a rubber pad 9 is provided between the primary bracket 2 and the interior trim panel 1 to reduce vibration transmitted from the fuselage mounting frame to the interior trim panel 1 .

[0030] In some optional embodiments, there is a bend between the fixed end and the connecting end of the primary bracket 2, so that the connecting end is offset in a direction away from the interior panel 1. The bend allows the primary bracket 2 to form an elastic structure, thereby reducing the vibration transmitted to the interior panel 1 by the fuselage mounting frame.

[0031] In some optional embodiments, the warped end allows the secondary bracket 6 to form an elastic structure, thereby reducing the vibration transmitted from the fuselage mounting frame to the interior trim panel 1 .

[0032] In some optional embodiments, a vibration damper 5 is provided between the secondary bracket 6 and the tertiary bracket 4, and the vibration damper 5 reduces the vibration transmitted from the fuselage mounting frame to the interior trim panel 1. The vibration damper 5 includes two metal sheets and a vibration damping block disposed between the two metal sheets.

[0033] In some optional embodiments, the connecting line of the two warped ends of the secondary bracket 6 is parallel to the joint seam, so as to resist the tilting along the joint seam direction transmitted from the tertiary bracket 4 .

[0034] In some optional embodiments, the secondary bracket 6 is arranged along the joint seam with two connection points of the two primary brackets 2 respectively. When the secondary bracket 6 is tilted along the joint seam, the two primary brackets 2 are bent to different degrees to offset the overturning force.

[0035] In some optional embodiments, the primary bracket 2 and the interior trim panel 1 are connected via mounting screws 3 and gaskets 8 .

[0036] In some optional embodiments, the secondary bracket 6 is fixed to the shock absorber 5 by means of screws 3 and washers 8 , and the shock absorber 5 is riveted to the tertiary bracket 4 .

[0037] In some optional embodiments, each interior trim panel 1 is installed with at least four sets of installation structures.

[0038] The advantages of the present application include: the bending axis of the primary bracket 2 is along the joint seam, and the bending axis of the secondary bracket is perpendicular to the joint seam direction, which can offset the skewness and vibration in multiple directions.

[0039] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A civil feeder aircraft cabin side wall mounting structure, characterized in that: A plurality of mounting structures are installed along the joints of adjacent interior panels (1), each mounting structure comprising: Two primary brackets (2), one secondary bracket (6), and one tertiary bracket (4); The primary bracket (2) comprises a fixed end and a connecting end, the fixed end of one primary bracket (2) is connected to the interior trim panel (1), and the connecting end is connected to the middle section of the secondary bracket (6), and the fixed end of another primary bracket (2) is connected to another interior trim panel (1), and the connecting end is connected to the middle section of the secondary bracket (6); The secondary bracket (6) comprises a middle section and two ends of the middle section which are bent in a direction away from the interior trim panel (1) to form warped ends, and the warped ends are fixedly connected to the tertiary bracket (4); The tertiary bracket (4) is fixedly connected to a fuselage mounting frame located at a certain distance inside the interior trim panel (1).

2. The civil feeder aircraft cabin side wall mounting structure according to claim 1, characterized in that: A clamping strip (10) covering the splicing seam is provided at the splicing seam position.

3. The civil feeder aircraft cabin side wall mounting structure according to claim 1, characterized in that: A rubber pad (9) is provided between the primary bracket (2) and the interior trim panel (1) to reduce vibration transmitted from the fuselage mounting frame to the interior trim panel (1).

4. The civil feeder aircraft cabin side wall mounting structure according to claim 1, characterized in that: There is a bend between the fixed end and the connecting end of the primary bracket (2), so that the connecting end is offset in a direction away from the interior trim panel (1). The bend enables the primary bracket (2) to form an elastic structure, thereby reducing vibration transmitted from the fuselage mounting frame to the interior trim panel (1).

5. The civil feeder aircraft cabin side wall mounting structure according to claim 1, characterized in that: The warped end enables the secondary bracket (6) to form an elastic structure, thereby reducing the vibration transmitted from the fuselage mounting frame to the interior trim panel (1).

6. The civil feeder aircraft cabin side wall mounting structure according to claim 1, characterized in that: A vibration damper (5) is provided between the secondary bracket (6) and the tertiary bracket (4), and the vibration damper (5) reduces vibration transmitted from the fuselage mounting frame to the interior trim panel (1).

7. The civil feeder aircraft cabin side wall mounting structure according to claim 1, characterized in that: The connecting line of the two tilted ends of the secondary support (6) is parallel to the joint seam, and is used to resist the tilting along the joint seam direction transmitted from the tertiary support (4).

8. The civil feeder aircraft cabin side wall mounting structure according to claim 7, characterized in that: The secondary bracket (6) is respectively arranged with two connection points of the two primary brackets (2) along the joint seam; when the secondary bracket (6) is tilted along the joint seam, the two primary brackets (2) are respectively bent to different degrees to offset the overturning force.

9. The civil feeder aircraft cabin side wall mounting structure according to claim 7, characterized in that: The primary bracket (2) and the interior trim panel (1) are connected via mounting screws (3) and gaskets (8).

10. The civil feeder aircraft cabin side wall mounting structure according to claim 6, characterized in that: The secondary bracket (6) is fixed to the vibration damper (5) by means of screws (3) and washers (8), and the vibration damper (5) is riveted to the tertiary bracket (4).

11. The civil feeder aircraft cabin side wall mounting structure according to claim 6, characterized in that: Each interior trim panel (1) is installed with at least four sets of installation structures.

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