Exterior aircraft interior noise reduction observation window assembly

Abstract

The invention belongs to the technical field of aircraft interior noise reduction design, and particularly relates to an exterior aircraft interior noise reduction observation window assembly. The assembly comprises a pressing ring, the cross section of the pressing ring is in an L shape, the pressing ring comprises a first pressing plate and a second pressing plate, and a containing cavity is formed between the first pressing plate and the second pressing plate; the E-shaped soft ring sleeve is installed in the containing cavity, the E-shaped soft ring sleeve and the pressing ring are bonded and fixed through an adhesive, and two grooves are formed in the E-shaped soft ring sleeve; the double-layer transparent part is arranged in the groove of the E-shaped soft ring sleeve; wherein after the pressing ring, the E-shaped soft ring sleeve and the double-layer transparent part are assembled, the pressing ring, the E-shaped soft ring sleeve and the double-layer transparent part are installed at the end of the cylindrical observation window of the aircraft interior trim from the outer side of the aircraft interior trim, and the pressing ring and a wall plate of the cylindrical observation window of the aircraft interior trim are fixed through a fastener. Sound insulation and noise reduction of the aircraft interior observation window can be achieved, and installation is easy and convenient.

Description

Technical Field

[0001] This application belongs to the field of aircraft interior noise reduction design technology, and specifically relates to an externally mounted aircraft interior noise reduction observation window component. Background Technology

[0002] Currently, the aircraft interior observation windows used in the project are a combination of single-layer transparent parts, rubber profiles, and pressure rings. In the aircraft cabin noise test, the noise at the interior observation window is greater than that of the surrounding interior panels. If only the surrounding interior panels are noise-reducing, the interior observation window will still be a weak point in noise reduction, and the noise reduction effect will be affected.

[0003] Therefore, there is an urgent need for a technical solution to overcome or mitigate at least one of the aforementioned defects in the existing technology. Summary of the Invention

[0004] The purpose of this application is to provide an externally mounted aircraft interior noise-reducing observation window assembly to solve at least one problem existing in the prior art.

[0005] The technical solution of this application is:

[0006] An externally mounted aircraft interior noise-reducing observation window assembly, comprising:

[0007] A pressure ring with an L-shaped cross-section includes a first pressure plate and a second pressure plate, and a receiving cavity is formed between the first pressure plate and the second pressure plate.

[0008] E-shaped soft ring sleeve, the E-shaped soft ring sleeve is installed in the receiving cavity and is fixed to the pressure ring by adhesive, and the E-shaped soft ring sleeve is provided with two grooves;

[0009] A double-layer transparent component is installed in the groove of the E-shaped soft ring sleeve;

[0010] The pressure ring, the E-shaped soft ring sleeve, and the double-layer transparent component are assembled and installed from the outside of the aircraft interior to the end of the cylindrical observation window of the aircraft interior. The pressure ring is then fixed to the wall panel of the cylindrical observation window of the aircraft interior using fasteners.

[0011] In at least one embodiment of this application, the pressure ring is made of a metal material.

[0012] In at least one embodiment of this application, the pressure ring is made of a non-metallic material.

[0013] In at least one embodiment of this application, the adhesive is an epoxy resin adhesive or an acrylic adhesive.

[0014] In at least one embodiment of this application, the cross-sectional shape of the two grooves of the E-shaped soft ring matches the edge contour of the double-layer transparent piece, for clamping and cushioning the double-layer transparent piece.

[0015] In at least one embodiment of this application, the E-shaped soft ring is made of a non-metallic material with a preset compression amount and sound insulation effect.

[0016] In at least one embodiment of this application, the E-shaped soft ring is made of silicone rubber or fluororubber.

[0017] In at least one embodiment of this application, the double-layer transparent element comprises two layers of transparent elements arranged parallel to each other, with an air gap between the two layers of transparent elements.

[0018] In at least one embodiment of this application, the thickness of the double-layer transparent component and the thickness of the air interlayer are designed according to the aircraft's sound insulation and noise reduction requirements.

[0019] In at least one embodiment of this application, the double-layer transparent component is made of a rigid non-metallic material.

[0020] In at least one embodiment of this application, the double-layer transparent component is an plexiglass plate or a polycarbonate plate.

[0021] In at least one embodiment of this application, the fastener is a bolt, and the first pressure plate is provided with mounting holes for mounting the bolt.

[0022] The invention has at least the following beneficial technical effects:

[0023] The external aircraft interior noise reduction observation window assembly of this application can achieve sound insulation and noise reduction of the aircraft interior observation window. During installation, the assembly is installed on the outside of the cylindrical observation window of the aircraft interior, which is easy to install. Attached Figure Description

[0024] Figure 1 This is a schematic diagram of an externally mounted aircraft interior noise reduction observation window assembly according to one embodiment of this application;

[0025] Figure 2 This is a partial enlarged view of an externally mounted aircraft interior noise reduction observation window assembly according to one embodiment of this application.

[0026] in:

[0027] 1-Pressure ring; 2-E-shaped soft ring sleeve; 3-Double-layer transparent part. Detailed Implementation

[0028] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0029] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting the scope of protection of this application.

[0030] The following is in conjunction with the appendix Figures 1 to 2 This application will be described in further detail.

[0031] This application provides an externally mounted aircraft interior noise reduction observation window assembly, including: a pressure ring 1, an E-shaped soft ring sleeve 2, and a double-layer transparent component 3.

[0032] Specifically, the pressure ring 1 has an L-shaped cross-section and includes a first pressure plate and a second pressure plate, forming a receiving cavity between the first and second pressure plates. It is understood that the length of the first pressure plate is greater than the length of the second pressure plate to facilitate the connection between the first pressure plate and the aircraft interior cylindrical observation window panel. The length of the second pressure plate is adapted to the thickness of the aircraft interior cylindrical observation window panel to prevent an excessively long second pressure plate from obstructing the aircraft interior cylindrical observation window.

[0033] The E-shaped flexible ring 2 is installed in the receiving cavity and is bonded to the pressure ring 1 with adhesive. The E-shaped flexible ring 2 has two grooves. The double-layer transparent part 3 is installed in the groove of the E-shaped flexible ring 2.

[0034] The external aircraft interior noise reduction observation window assembly of this application is assembled by first snapping the double-layer transparent piece 3 into the groove of the E-shaped soft ring 2, then inserting the combination of the double-layer transparent piece 3 and the E-shaped soft ring 2 into the receiving cavity of the pressure ring 1, and finally bonding and fixing the E-shaped soft ring 2 to the pressure ring 1 with adhesive. After the aircraft interior noise reduction observation window assembly is assembled, it is installed from the outside of the aircraft interior into the end of the cylindrical observation window of the aircraft interior, and the pressure ring 1 is fixed to the wall panel of the cylindrical observation window of the aircraft interior with fasteners.

[0035] Depending on the actual needs, either metal or non-metal can be selected as the material for the pressure ring 1. In a preferred embodiment of this application, the adhesive used to connect the pressure ring 1 and the E-shaped flexible ring 2 is an epoxy resin adhesive or an acrylic adhesive.

[0036] In a preferred embodiment of this application, the cross-sectional shape of the two grooves of the E-shaped flexible ring 2 matches the edge contour of the double-layer transparent part 3, for clamping and cushioning the double-layer transparent part 3. The E-shaped flexible ring 2 must be made of a non-metallic material with a certain amount of compression and good sound insulation effect; preferably, the E-shaped flexible ring 2 is made of silicone rubber or fluororubber.

[0037] In a preferred embodiment of this application, the double-layer transparent component 3 comprises two layers of transparent components arranged parallel to each other, with an air gap between the two layers. The groove size on the E-shaped flexible ring 2 must match the thickness of the double-layer transparent component 3. The thickness of the air gap between the double-layer transparent components 2 is determined by the protrusion in the middle of the E-shaped flexible ring 2. The thickness of the double-layer transparent component 3 and the thickness of the air gap are designed according to the aircraft's sound insulation and noise reduction requirements. The double-layer transparent component 3 needs to be made of a rigid non-metallic material with good light transmittance and meeting strength requirements. In this embodiment, the double-layer transparent component 3 is an plexiglass plate or a polycarbonate plate.

[0038] In a preferred embodiment of this application, the fasteners used for assembling the noise reduction observation window assembly for the aircraft interior are bolts, and the first pressure plate is provided with mounting holes for mounting the bolts.

[0039] The external aircraft interior noise reduction observation window assembly of this application comprises a pressure ring 1, which is an L-shaped rotating annular body; an E-shaped soft ring sleeve 2, which is an E-shaped soft material annular structure; and a double-layer transparent component 3, which consists of two transparent layers. The double-layer transparent component 3 is snapped into the groove of the E-shaped soft ring sleeve 2, and then together with the E-shaped soft ring sleeve 2, is installed into the receiving cavity of the pressure ring 1. After assembly, it is installed from the outside of the aircraft interior cylindrical observation window at the end. This application can achieve sound insulation and noise reduction of the aircraft interior observation window. During installation, the assembly is installed on the outside of the aircraft interior cylindrical observation window, making installation simple.

[0040] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. An externally mounted aircraft interior noise-reducing observation window assembly, characterized in that, include: The pressure ring (1) has an L-shaped cross-section. The pressure ring (1) includes a first pressure plate and a second pressure plate, and a receiving cavity is formed between the first pressure plate and the second pressure plate. E-shaped soft ring sleeve (2), the E-shaped soft ring sleeve (2) is installed in the receiving cavity and is bonded and fixed to the pressure ring (1) by adhesive. The E-shaped soft ring sleeve (2) is provided with two grooves. A double-layer transparent component (3) is installed in the groove of the E-shaped soft ring sleeve (2); The pressure ring (1), the E-shaped soft ring sleeve (2) and the double-layer transparent part (3) are assembled and installed from the outside of the aircraft interior to the end of the cylindrical observation window of the aircraft interior, and the pressure ring (1) is fixed to the wall panel of the cylindrical observation window of the aircraft interior by fasteners.

2. The externally mounted aircraft interior noise reduction observation window assembly according to claim 1, characterized in that, The pressure ring (1) is made of metal.

3. The externally mounted aircraft interior noise reduction observation window assembly according to claim 1, characterized in that, The pressure ring (1) is made of non-metallic material.

4. The externally mounted aircraft interior noise reduction observation window assembly according to claim 1, characterized in that, The adhesive is an epoxy resin adhesive or an acrylic adhesive.

5. The externally mounted aircraft interior noise reduction observation window assembly according to claim 1, characterized in that, The cross-sectional shape of the two grooves of the E-shaped soft ring (2) matches the edge contour of the double-layer transparent piece (3) and is used to clamp and cushion the double-layer transparent piece (3).

6. The externally mounted aircraft interior noise reduction observation window assembly according to claim 1, characterized in that, The E-shaped soft ring (2) is made of a non-metallic material with a preset compression amount and sound insulation effect.

7. The externally mounted aircraft interior noise reduction observation window assembly according to claim 6, characterized in that, The E-shaped soft ring (3) is made of silicone rubber or fluororubber.

8. The externally mounted aircraft interior noise reduction observation window assembly according to claim 1, characterized in that, The double-layer transparent component (3) includes two layers of transparent components arranged parallel to each other, with an air gap between the two layers of transparent components.

9. The externally mounted aircraft interior noise reduction observation window assembly according to claim 8, characterized in that, The thickness of the double-layer transparent component (3) and the thickness of the air interlayer are designed according to the requirements of aircraft sound insulation and noise reduction.

10. The externally mounted aircraft interior noise-reducing observation window assembly according to claim 9, characterized in that, The double-layer transparent component (3) is made of a rigid non-metallic material.

11. The externally mounted aircraft interior noise-reducing observation window assembly according to claim 10, characterized in that, The double-layer transparent component (3) is an organic glass plate or a polycarbonate plate.

12. The externally mounted aircraft interior noise reduction observation window assembly according to claim 1, characterized in that, The fastener is a bolt, and the first pressure plate is provided with mounting holes for installing the bolt.

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