Aircraft cover sealing rubber ring

Abstract

The application provides a sealing rubber ring for an aircraft cover body, which comprises a compression part provided with a cavity; wherein during installation of the aircraft cover body on a body structure, a root skin of the aircraft cover body compresses the cavity, the cavity is elastically deformed, and then the compression part realizes sealing between the aircraft cover body and the body structure; and a connecting part connected to the compression part in an integrated structure, the connecting part being provided with an adhesive; wherein the connecting part is connected to the root skin of the aircraft cover body through the adhesive; and the application provides a sealing ring cross section shape, which does not need a pressing strip and a fastener, and can realize quick installation of the sealing ring through only the adhesive.

Description

Technical Field

[0001] This application belongs to the field of aerospace structural design and optimization technology, and in particular relates to a sealing rubber ring for an aircraft housing. Background Technology

[0002] Various functional fairings are arranged on the exterior of the aircraft fuselage, including radar fairings, ram air vents, equipment maintenance fairings, antenna fairings, and small wing-body fairings. These fairings are assembled with the fuselage skin / frame beams through various connection structures such as bolts, clamps, flange overlaps, and embedded slots.

[0003] The interface between the enclosure and the fuselage is an external aerodynamic sealing interface of the aircraft. During flight, it will continuously be subjected to: high-altitude pressure difference, alternating high and low temperatures (-55℃~120℃), rainwater, de-icing fluid, fuel water vapor, high-speed airflow scouring, and alternating vibration loads. If the interface seal fails, there will be airworthiness risks such as rainwater seeping into the equipment compartment, pressure leakage inside the compartment, corrosion of the fuselage aluminum alloy / composite material structure, excessive aerodynamic noise, and short circuit failure of electronic equipment. Therefore, a special sealing rubber ring must be installed at the docking point.

[0004] Traditional sealing rings are mostly P-shaped in cross-section, connected to the fuselage structure from one side, and require additional pressure strips and fasteners to compact them. This results in a complex sealing structure, severely impacting assembly efficiency. Summary of the Invention

[0005] Purpose of the invention: To provide a sealing ring cross-sectional shape that eliminates the need for pressure strips and fasteners, enabling rapid installation of the sealing ring solely through adhesive, thereby avoiding the alignment problems of pressure strips and sealing ring fastener holes.

[0006] This application provides a sealing rubber ring for an aircraft housing, the rubber ring comprising: The compression section has a cavity; during the installation of the aircraft canopy on the fuselage structure, the root skin of the aircraft canopy compresses the cavity, causing the cavity to undergo elastic deformation, thereby achieving a seal between the aircraft canopy and the fuselage structure. The connecting portion is integrated with the compression portion to form a single structure, and the connecting portion has an adhesive; wherein the connecting portion is connected to the root skin of the aircraft housing by the adhesive.

[0007] Preferably, the cross-sectional shape of the cavity is figure-eight shaped.

[0008] Preferably, the cross-sectional shape of the cavity is "B".

[0009] Preferably, the cross-section of the cavity includes: The first arc portion, the root skin of the aircraft canopy compresses the first arc portion; The straight section is connected to the first arc section. When the root skin of the aircraft canopy is compressed against the first arc section, the straight section is located on the outside of the aircraft canopy. The second arc portion is connected to the straight portion and the first arc portion; when the root skin of the aircraft canopy is compressed to the first arc portion, the second arc portion is located inside the aircraft canopy.

[0010] Preferably, the second arcuate portion protrudes into the cavity; the second arcuate portion is arranged opposite to the straight portion.

[0011] Preferably, the connecting portion includes: The U-shaped groove has its two sides connected to the root skin of the aircraft housing.

[0012] Preferably, the adhesive is disposed within the U-shaped groove, and the two sides of the U-shaped groove are connected to the root skin of the aircraft housing via the adhesive.

[0013] Preferably, the shape of the U-shaped groove should be able to adapt to the shape of the root skin of the aircraft housing.

[0014] The beneficial technical effects of this application are as follows: This invention designs a variable connection adaptable cross-section configuration for aircraft housing sealing rubber rings, which improves the assembly efficiency of sealing rings while simplifying the sealing structure, optimizes and eliminates common pressure strips and fastener structures, avoids process problems that may be caused by hole matching, and improves product manufacturing efficiency. Attached Figure Description

[0015] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. The drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0016] Figure 1 This is a schematic diagram of the cross-sectional shape of a sealing ring provided in an embodiment of this application; Figure 2 This is a schematic diagram illustrating the function of a sealing ring provided in an embodiment of this application. Detailed Implementation

[0017] The following is a description of the embodiments and appendices. Figure 1 -Appendix Figure 2 The present invention will be described in further detail, but the embodiments of the present invention are not limited thereto.

[0018] This application provides a sealing rubber ring for an aircraft canopy. The rubber ring includes: a compression portion having a cavity; wherein, during the installation of the aircraft canopy onto the fuselage structure, the root skin of the aircraft canopy compresses the cavity, causing elastic deformation of the cavity, thereby achieving a seal between the aircraft canopy and the fuselage structure; and a connecting portion integrated with the compression portion, the connecting portion having an adhesive; wherein, the connecting portion is connected to the root skin of the aircraft canopy via the adhesive.

[0019] This application innovatively proposes a sealing ring cross-sectional shape that eliminates the need for pressure strips and fasteners, enabling rapid installation of the sealing ring solely through adhesive.

[0020] This application enables rapid assembly of the sealing ring, simplifies the sealing structure, optimizes the removal of pressure strips and fasteners, and avoids the problem of misalignment of the holes of the pressure strips and sealing ring fasteners.

[0021] In this embodiment of the application, the cross-sectional shape and dimensions of the provided sealing ring are as follows: Figure 1 As shown.

[0022] like Figure 2 As shown, the sealing ring achieves effective sealing by compressing the upper cavity. The lower U-shaped groove is bonded to the structure with adhesive. The double-sided bonding of the U-shaped groove structure ensures that the sealing ring is firmly bonded to the structure, and even without a pressure strip, the sealing ring will not tilt to one side, thus affecting the sealing effect.

[0023] At the same time, there is considerable room for improvement in the cross-sectional shape of the U-shaped channel, which can be adapted to different structures by changing the cross-sectional shape.

[0024] This invention designs a variable connection adaptable cross-section configuration for aircraft housing sealing rubber rings, which improves the assembly efficiency of sealing rings while simplifying the sealing structure, optimizes and eliminates common pressure strips and fastener structures, avoids process problems that may be caused by hole matching, and improves product manufacturing efficiency.

[0025] This structure has been applied to a certain type of satellite communication antenna radome, effectively sealing it and preventing moisture from entering. At the same time, the sealing ring itself has a simple structure, high assembly efficiency, and improves the product's economy and the operability of the assembly process.

[0026] The above detailed embodiments are a description of the present invention. It should not be considered that the specific embodiments of the present invention are limited to these descriptions. For those skilled in the art, several simple deductions and substitutions can be made without departing from the concept of the present invention, and all of these should be considered to fall within the protection scope of the present invention.

Claims

1. A sealing rubber ring for an aircraft housing, characterized in that, The rubber ring includes: The compression section has a cavity; during the installation of the aircraft canopy on the fuselage structure, the root skin of the aircraft canopy compresses the cavity, causing the cavity to undergo elastic deformation, thereby achieving a seal between the aircraft canopy and the fuselage structure. The connecting portion is integrated with the compression portion to form a single structure, and the connecting portion has an adhesive; wherein the connecting portion is connected to the root skin of the aircraft housing via the adhesive.

2. The rubber ring according to claim 1, characterized in that, The cross-sectional shape of the cavity is "8".

3. The rubber ring according to claim 1, characterized in that, The cross-sectional shape of the cavity is "B".

4. The rubber ring according to claim 3, characterized in that, The cross-section of the cavity includes: The first arc portion, the root skin of the aircraft canopy compresses the first arc portion; The straight section is connected to the first arc section. When the root skin of the aircraft canopy is compressed against the first arc section, the straight section is located on the outside of the aircraft canopy. The second arc portion is connected to the straight portion and the first arc portion; when the root skin of the aircraft canopy is compressed to the first arc portion, the second arc portion is located inside the aircraft canopy.

5. The rubber ring according to claim 4, characterized in that, The second arc portion protrudes into the cavity; the second arc portion is arranged opposite to the straight portion.

6. The rubber ring according to claim 1, characterized in that, The connection portion includes: The U-shaped groove has its two sides connected to the root skin of the aircraft housing.

7. The rubber ring according to claim 6, characterized in that, The adhesive is disposed within the U-shaped groove, and the two sides of the U-shaped groove are connected to the root skin of the aircraft housing via the adhesive.

8. The rubber ring according to claim 7, characterized in that, The shape of the U-shaped groove should be able to adapt to the shape of the root skin of the aircraft housing.

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