Airplane interior trimming panel structure with sound absorption and insulation functions

Abstract

The invention belongs to the field of design of aircraft interior trim structures, and particularly relates to an aircraft interior trim panel structure with sound absorption and insulation functions. The aircraft interior trimming panel structure comprises an inner skin, a first honeycomb core, a damping layer, a second honeycomb core and an outer skin which are sequentially connected into a whole through an adhesive; wherein the inner skin is provided with a hole opening area, and the hole opening area is provided with sound absorption holes. The absorption characteristic of the noise in the cabin is adjusted by adjusting the noise absorption variable; and the blocking characteristic to the noise outside the cabin is adjusted by adjusting the noise blocking variable. According to the aircraft interior trim panel structure with the sound absorption and insulation functions, the interior trim panel with the noise absorption and insulation functions is designed, the noise level in a cabin can be effectively reduced, and the noise reduction requirement in the aircraft cabin is met.

Description

TECHNICAL FIELD

[0001] The application belongs to the field of aircraft interior structure design, and particularly relates to an aircraft interior panel structure with sound absorption and insulation functions. BACKGROUND

[0002] The aircraft cabin interior panel is a composite panel located on the cabin wall, which integrates aesthetics, lightweight and functional requirements. In addition to the decoration and bearing functions, modern interior panels need to have sound insulation, weight reduction and other performances.

[0003] Current aircraft cabin noise control mainly relies on filling sound-absorbing materials behind the interior panel. This noise reduction method has a single structure, limited noise absorption effect, and is difficult to effectively block structure-borne sound. With the improvement of passenger cabin comfort requirements in civil aviation, the existing interior panel structure has been difficult to meet the increasingly stringent cabin noise reduction requirements.

[0004] Therefore, there is an urgent need for a technical solution to overcome or alleviate at least one of the above-mentioned deficiencies of the prior art. SUMMARY

[0005] The purpose of the present application is to provide an aircraft interior panel structure with sound absorption and insulation functions to solve at least one problem existing in the prior art.

[0006] The technical solution of the present application is:

[0007] An aircraft interior panel structure with sound absorption and insulation functions comprises:

[0008] The inner skin, the first honeycomb core, the damping layer, the second honeycomb core and the outer skin are connected in sequence by an adhesive to form an integrated whole. The inner skin is provided with an open area having sound absorption holes.

[0009] In at least one embodiment of the present application, the inner skin is a glass fiber prepreg.

[0010] In at least one embodiment of the present application, the inner skin adopts a hemming form and extends to the side edge of the interior panel.

[0011] In at least one embodiment of the present application, the inner skin is installed towards the cabin.

[0012] In at least one embodiment of the present application, the first honeycomb core is an aramid paper honeycomb core structure, and the aramid paper honeycomb core structure is filled with glass fiber cotton.

[0013] In at least one embodiment of the present application, the second honeycomb core is an aramid paper honeycomb core structure.

[0014] In at least one embodiment of the present application, the outer skin is a glass fiber prepreg.

[0015] In at least one embodiment of the present application, the outer skin is mounted towards the cabin exterior.

[0016] In at least one embodiment of the present application, the absorption properties to the cabin interior noise are adjusted by adjusting noise absorption variables, the noise absorption variables including the aperture of the open hole area, the perforation rate, and the glass fiber cotton filling proportion, filling density of the first honeycomb core.

[0017] In at least one embodiment of the present application, the blocking properties to the cabin exterior noise are adjusted by adjusting noise blocking variables, the noise blocking variables including the length, height of the aramid paper honeycomb core of the second honeycomb core, and the thickness, material of the damping layer.

[0018] The present application has at least the following beneficial technical effects:

[0019] The aircraft interior panel structure with sound absorption and insulation function of the present application designs the interior panel with noise absorption and insulation functions, which can effectively reduce the cabin noise level and meet the noise reduction demand of the aircraft cabin interior. BRIEF DESCRIPTION OF DRAWINGS

[0020] Figure 1 is a schematic diagram of an aircraft interior panel structure with sound absorption and insulation function according to an embodiment of the present application.

[0021] Wherein:

[0022] 1 - inner skin; 2 - first honeycomb core; 3 - damping layer; 4 - second honeycomb core; 5 - outer skin; 6 - open hole area. DETAILED DESCRIPTION

[0023] In order to make the purpose, technical scheme and advantages of the present application clearer, the technical scheme of the embodiments of the present application will be described in more detail below in combination with the drawings of the embodiments of the present application. In the drawings, the same or similar reference numerals represent the same or similar elements or elements with the same or similar functions throughout. The described embodiments are part of the embodiments of the present application, not all embodiments. The embodiments described below by reference to the drawings are exemplary and are intended to explain the present application, and cannot be understood as limiting the present application. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative labor fall within the scope of protection of the present application. The embodiments of the present application will be described in detail below in combination with the drawings.

[0024] In the description of the present application, it should be understood that the terms "center", "longitudinal", "transverse", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the scope of protection of the present application.

[0025] The accompanying drawings are referred to in the description of the present application. Figure 1 The present application is further described in detail.

[0026] The present application provides an aircraft interior panel structure with sound absorption and insulation function, comprising: an inner skin 1, a first honeycomb core 2, a damping layer 3, a second honeycomb core 4 and an outer skin 5 connected in sequence by an adhesive to form a whole; wherein the inner skin 1 is provided with an open area 6, and the open area 6 is provided with sound absorption holes.

[0027] In the preferred embodiment of the present application, each component is made of flame-retardant material. Among them, the inner skin 1 is made of glass fiber prepreg; the first honeycomb core 2 is made of aramid paper honeycomb core structure, and the aramid paper honeycomb core structure is filled with glass fiber cotton; the second honeycomb core 4 is made of aramid paper honeycomb core structure; and the outer skin 5 is made of glass fiber prepreg.

[0028] In the preferred embodiment of the present application, as shown in Figure 1 The inner skin 1 is installed towards the cabin and forms a sound absorption structure with the open area 6 and the first honeycomb core 2 to absorb the noise in the cabin. The absorption characteristics of the noise in the cabin are adjusted by adjusting the noise absorption variables, including the hole diameter of the open area 6, the perforation rate, and the filling ratio and density of the glass fiber cotton of the first honeycomb core 2.

[0029] In the preferred embodiment of the present application, the outer skin 5 is installed towards the outside of the cabin, and forms a sound insulation structure with the second honeycomb core 4 and the damping layer 3 to block the noise outside the cabin. The blocking characteristics of the noise outside the cabin are adjusted by adjusting the noise blocking variables, including the length and height of the aramid paper honeycomb core of the second honeycomb core 4, and the thickness and material of the damping layer 3.

[0030] The aircraft interior panel structure with sound absorption and insulation function of the present application can block the noise outside the cabin and absorb the noise inside the cabin, thereby reducing the noise level inside the cabin of the aircraft.

[0031] The above merely provides the specific implementation of the present application, but the protection scope of the present application is not limited to this. Any person skilled in the art can easily think of the changes or replacements within the technical range disclosed by the present application, which should be covered in the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. An aircraft interior panel structure having sound absorption and insulation functions, characterized by, Comprise: The inner skin (1), the first honeycomb core (2), the damping layer (3), the second honeycomb core (4) and the outer skin (5) are sequentially connected by adhesive to be integrated; wherein, the inner skin (1) is provided with an open area (6), and the open area (6) is provided with sound absorption holes.

2. The aircraft interior panel structure having sound absorbing and insulating functions according to claim 1, characterized by, The inner skin (1) is glass fiber prepreg.

3. The aircraft interior panel structure having sound absorption and insulation functions according to claim 2, characterized by, The inner skin (1) adopts a form of edge covering and extends to the side edge of the interior trim panel.

4. The aircraft interior panel structure having sound absorbing and insulating functions according to claim 3, characterized by, The inner skin (1) is installed towards the cabin.

5. The aircraft interior panel structure having sound absorbing and insulating functions according to claim 4, characterized by, The first honeycomb core (2) is an aramid paper honeycomb core structure, and the aramid paper honeycomb core structure is filled with glass fiber cotton.

6. The aircraft interior panel structure having sound absorbing and insulating functions according to claim 5, characterized by, The second honeycomb core (4) is an aramid paper honeycomb core structure.

7. The aircraft interior panel structure having sound absorbing and insulating functions according to claim 6, characterized by, The outer skin (5) is glass fiber prepreg.

8. The aircraft interior panel structure having sound absorbing and insulating functions according to claim 7, characterized by, The outer skin (5) is installed towards the cabin.

9. The aircraft interior panel structure having sound absorbing and insulating functions according to claim 8, characterized by, The absorption characteristics of the cabin noise are adjusted by adjusting noise absorption variables, and the noise absorption variables include the aperture of the open area (6), the perforation rate, and the filling proportion and filling density of the glass fiber cotton of the first honeycomb core (2).

10. The aircraft interior panel structure having sound absorbing and insulating functions according to claim 9, characterized by, The blocking characteristics of the cabin noise are adjusted by adjusting noise blocking variables, and the noise blocking variables include the length and height of the aramid paper honeycomb core of the second honeycomb core (4), and the thickness and material of the damping layer (3).

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