Waterproofing for aircraft separation plane

Abstract

The application relates to the waterproof technical field and discloses an aircraft separation surface waterproof sleeve. The application is applied to a separation surface between a lower cabin plane and an upper wing plane, the cabin plane comprises a first mounting port, the wing plane comprises a second mounting port, the waterproof sleeve at least comprises a first ring sleeve part and a second ring sleeve part which are connected with each other, the first ring sleeve part is in sealing connection with the edge of the first mounting port, the second ring sleeve part extends upwards and sequentially passes through the first mounting port and the second mounting port, so that water vapor on the separation surface is prevented from entering the cabin through the first mounting port. The waterproof sleeve is compact in structure, convenient to install, reusable, and can effectively prevent rainwater on the top of the cabin from penetrating.

Description

Technical Field

[0001] This application relates to the field of waterproofing technology, and in particular to a waterproof sleeve for the separation surface of an aircraft. Background Technology

[0002] In aircraft design, the separation surface area between the wing and the cockpit roof contains numerous cable penetration holes, posing a significant waterproofing challenge during long-term service. Traditional solutions primarily rely on elastic sealing rings or sealants to fill and seal the edges of the separation surface. However, in practical applications, the vibration and deformation caused by frequent takeoffs and landings can lead to fatigue cracks in the sealing materials, sealants are prone to cracking under temperature cycling, and sealing rings lose their resilience due to repeated compression, resulting in an average maintenance cycle of only 3-6 months. Furthermore, each wing overhaul requires the complete removal of old sealing material and reapplication of sealant, with each sealing operation taking 4-8 hours, severely impacting maintenance efficiency. Therefore, there is an urgent need for a new type of sealing structure that is reusable, resistant to vibration fatigue, and capable of preventing dynamic water seepage. Utility Model Content

[0003] The purpose of this application is to provide a waterproof sleeve for the separation surface of an aircraft. The waterproof sleeve of this application has a compact structure, is easy to install, is reusable, and can effectively prevent rainwater from seeping into the top of the cockpit.

[0004] To address the aforementioned technical problems, this application provides a waterproof sleeve for an aircraft separation surface, applied to the separation surface between the lower cockpit plane and the upper wing plane. The cockpit plane includes a first mounting port, and the wing plane includes a second mounting port. The waterproof sleeve includes at least a first ring portion and a second ring portion connected to each other. The first ring portion is sealed to the edge of the first mounting port, and the second ring portion extends upward and passes through the first mounting port and the second mounting port in sequence to prevent moisture from the separation surface from entering the cockpit through the first mounting port.

[0005] Optionally, the first ring portion extends from the bottom of the second ring portion toward a direction away from the first mounting port and forms a sealing structure with the cockpit plane.

[0006] Optionally, the first ring portion and the second ring portion are perpendicularly connected to each other.

[0007] Optionally, the second ring portion is inclined away from the first mounting opening and forms an acute angle with the first ring portion.

[0008] Optionally, the second mounting opening is larger than the first mounting opening to form an annular gap around the second ring sleeve.

[0009] Optionally, the second ring sleeve includes a ring portion and a serrated portion connected to the ring portion, wherein the serrated portion flips outward to form a flange structure after being pressed.

[0010] Optionally, the height of the ring portion is greater than the height of the annular gap to ensure that the serrated portion covers the annular gap after being pressed and flipped.

[0011] Optionally, the waterproof sleeve is a square sleeve.

[0012] Optionally, the acute angle ranges from 60 degrees to 85 degrees.

[0013] Optionally, the cockpit plane slopes downwards from the first mounting port outwards.

[0014] The waterproof sleeve of this application has a compact structure, is easy to install, is reusable, and can effectively prevent rainwater from seeping into the top of the cabin. Attached Figure Description

[0015] Figure 1 The diagram shows the separated state of the aircraft cockpit and wings according to an embodiment of this application.

[0016] Figure 2 The diagram shown is a bottom view of the waterproof sleeve on the separation surface of the aircraft according to an embodiment of this application;

[0017] Figure 3 The diagram shows a cross-sectional view of the aircraft separation surface waterproof sleeve in the installation state according to an embodiment of this application;

[0018] Figure 4 The diagram shows a single-side cross-sectional view of the aircraft separation surface waterproof sleeve in the installation state according to an embodiment of this application.

[0019] Figure 5 The diagram shown is a single-side cross-sectional view of the waterproof sleeve on the separation surface of the aircraft, as described in this application embodiment.

[0020] Figure 6 The diagram shows a single-side cross-sectional view of the aircraft separation surface waterproof sleeve and the cockpit plane in the adhesive state of an embodiment of this application.

[0021] Figure 7 This is a structural schematic diagram showing the installation state of the waterproof sleeve on the separation surface of the aircraft according to an embodiment of this application;

[0022] Figure 8 Displayed as Figure 7 A magnified view of the area at position E in the middle;

[0023] Figure 9 This is a single-sided cross-sectional view showing the installation state of the waterproof sleeve on the separation surface of an aircraft according to another embodiment of this application. Detailed Implementation

[0024] The following embodiments further illustrate the technical solutions of this application. It should be understood that the specific embodiments described herein are merely for explaining this application. Furthermore, it should be noted that, for ease of description, only the parts relevant to this application are shown in the accompanying drawings, not all of them.

[0025] In the description of this application, it should be noted that, unless otherwise expressly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to fixed connections or detachable connections; mechanical connections or electrical connections; direct connections or indirect connections through an intermediate medium; and internal connections between two components. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0026] In this application, unless otherwise expressly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature being directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature being directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0027] The term "aircraft" is defined as an air transport system of any size having at least one lift propeller as its propulsion source. The term "aircraft" can include both "manned" and "unmanned" air transport systems. A manned aircraft can mean an air transport system carrying one or more human passengers, none of whom have control over the aircraft. A manned aircraft can also mean an air transport system carrying one or more human passengers, some of whom, or one of whom, has partial or full control over the aircraft. An unmanned aircraft can mean an air transport system that does not carry any human passengers and flies autonomously or is remotely controlled by someone at a distance.

[0028] In this specification, "aircraft" includes manned aircraft and any unmanned vehicle, such as unmanned aerial vehicles (UAVs), unmanned aircraft, remote-controlled aircraft, unmanned aircraft systems, any aircraft classified by the International Civil Aviation Organization (ICAO) under cycle 328AN / 190, and so on. As an example, a drone can take the form of a single- or multi-rotor helicopter (such as a quadcopter) or a fixed-wing aircraft. Furthermore, certain portions of this disclosure can be used in conjunction with drones in the form of other types of unmanned vehicles (e.g., wheeled, tracked, and / or watercraft).

[0029] This application relates to a structure for preventing rainwater infiltration into the top of an aircraft cockpit. Because there are numerous cables connecting the wing and the cockpit top, cable entry holes are necessary for these cables to pass through. In windy or rainy weather, moisture can seep into the separation surface between the cockpit and the wing along the separation surface and flow into the cockpit through the cable entry holes. The waterproof sleeve on the separation surface in this application effectively prevents water accumulated inside the separation surface from flowing into the cockpit through the cable entry holes.

[0030] Embodiments of this application are described below with reference to the accompanying drawings, such as Figures 1 to 3 As shown, in this embodiment of the application, the aircraft separation surface waterproof sleeve T is applied to the separation surface C between the lower cockpit plane A and the upper wing plane B. The cockpit plane A includes a first mounting port 100, and the wing plane B includes a second mounting port 200 (the first mounting port 100 and the second mounting port 200 are located at...). Figure 3 (Illustrated by dashed lines). The first mounting port 100 and the second mounting port 200 are interconnected after the cockpit and wing are assembled to facilitate cable entry and exit. The waterproof sleeve T extends circumferentially along the edge of the first mounting port 100 on the cockpit plane A.

[0031] like Figure 4 and Figure 5 As shown, the waterproof sleeve T includes a first ring sleeve 1 and a second ring sleeve 2 that are connected to each other. The first ring sleeve 1 extends from the bottom of the second ring sleeve 2 outward, i.e. away from the first mounting port 100, and forms a sealing structure with the cabin plane A.

[0032] Specifically, the first ring sleeve 1 is sealed to the edge of the first mounting port 100, and the second ring sleeve 2 extends upward and passes through the first mounting port 100 and the second mounting port 200 in sequence to prevent water vapor on the separation surface C from entering the cabin through the wire hole (i.e., the first mounting port 100).

[0033] In one embodiment, such as Figure 5 As shown, the first ring part 1 and the second ring part 2 are perpendicularly connected to each other, forming an L-shaped cross-section structure. The first ring part 1 extends horizontally along the surface of the cabin plane A and is fixedly connected to the edge of the first mounting port 100 by sealant or a pressing structure. The second ring part 2 is inserted vertically upward into the overlapping area of ​​the first mounting port 100 and the second mounting port 200. This design ensures that water vapor at the separation surface C is effectively blocked by the second ring part 2 when flowing along the top of the cabin, and cannot enter the cabin interior through the wire hole (i.e., the first mounting port 100).

[0034] The outer diameter of the second ring sleeve 2 is smaller than the inner diameter of the first mounting port 100 and the second mounting port 200, so as to ensure that it passes smoothly through the first mounting port 100 and the second mounting port 200 and forms an effective seal with the hole wall.

[0035] In one embodiment, the surfaces of the first ring sleeve 1 and the cabin plane A can be formed into an integrated sealing structure using sealant, thereby effectively preventing loosening of the connection due to vibration or temperature changes. However, it is understood that there are no particular limitations on the specific sealing method between the first ring sleeve 1 and the cabin plane A, and those skilled in the art can set it reasonably according to the actual situation.

[0036] In one embodiment, such as Figure 6 As shown, when the waterproof sleeve T is connected to the cabin plane A with sealant, a drainage slope 12 can be formed at the intersection of the first ring part 1 and the second ring part 2. This drainage slope 12 can guide water droplets flowing down the outer surface of the second ring part 2 to slide outward, preventing water from accumulating and further seeping into the sealed connection. The surface of the drainage slope 12 is smooth and continuous, transitioning naturally with the first ring part 1 and the second ring part 2, further improving the sealing reliability.

[0037] In one embodiment, the drainage slope 12 has a chamfered structure with an inclination angle of 30 to 45 degrees. This inclination angle ensures smooth drainage while preventing a decrease in structural strength due to excessive slope. Under vibration or temperature change environments, the chamfered design of the drainage slope 12 reduces stress concentration and prevents sealant cracking, thereby improving overall waterproof performance. Through the synergistic effect of the above structures, the waterproof sleeve T provides multiple layers of protection for the cable hole area, effectively ensuring the safety and stability of the cabin's internal electrical system.

[0038] The waterproof sleeve T is made of elastic rubber material, which has good weather resistance and compression resilience, and can maintain reliable sealing under different temperature conditions, adapting to harsh high-altitude climate conditions.

[0039] The waterproof sleeve T is integrally molded, with a simple structure and low manufacturing cost. It is easy to install and remove, and suitable for most assembly scenarios.

[0040] Continue to refer to Figure 3 and Figure 4 The length of the first mounting opening 100 is M, and the length of the second mounting opening 200 is N. In this embodiment, N is greater than M. It should be noted that when the waterproof sleeve is square in this embodiment, M and N only represent the lengths of the first mounting opening 100 and the second mounting opening 200, respectively. Similarly, the width of the second mounting opening 200 is greater than the width of the first mounting opening 100, that is, the dimensions of the second mounting opening 200 are larger than those of the first mounting opening 100, so as to form an annular gap 3 surrounding the rectangle of the first mounting opening 100. This annular gap 3 provides clearance space for the second ring sleeve 2 to pass upward and facilitates compensation for alignment errors between the upper and lower structures during assembly. This improves the reliability of the sealing connection and assembly efficiency.

[0041] In another embodiment, the waterproof sleeve is circular, meaning that when the first mounting opening 100 and the second mounting opening 200 are circular, the diameter of the first mounting opening 100 is M, and the diameter of the second mounting opening 200 is N, where N is greater than M. That is, the circumference of the second mounting opening 200 is greater than the circumference of the first mounting opening 100, forming an annular gap 3 around the circular first mounting opening 100. This annular gap 3 provides clearance for the second ring sleeve 2 to pass upwards and facilitates compensation for alignment errors between the upper and lower structures during assembly. This improves the reliability of the sealing connection and assembly efficiency.

[0042] In one embodiment, such as Figure 4 As shown, the second ring sleeve 2 includes a ring 21 and a serrated portion 22 connected to the ring 21. In this embodiment, the ring 21 can be a rectangular sleeve, and the serrated portion 22 includes multiple serrated structures. After being subjected to pressure from the plane D of the equipment inside the upper wing, the serrated portion 22 flips outward to form a flange structure.

[0043] In one embodiment, the vertical height of the ring portion 21 is greater than the vertical height of the annular gap 3 to ensure that the serrated portion 22 covers the annular gap 3 after being pressed and flipped. The height of the ring portion 21 is designed to face upward towards the upper device plane D to ensure that the serrated portion 22 can effectively abut against the lower surface of the upper device plane D after being pressed and flipped, thereby enhancing the sealing reliability.

[0044] like Figure 7 and Figure 8 As shown, the tooth structure of the serrated part 22 is evenly distributed around the circumference of the ring part 21. For example, the adjacent serrations of the serrated part 22 can be spaced 1-2 mm apart, and the height of the serrated part 22 can also be reasonably set according to the height of the equipment plane D.

[0045] During assembly, the free end of the serrated portion 22 gradually folds outward under axial pressure from the second ring sleeve 2 until it completely fits against the lower surface of the equipment plane D, achieving an adaptive seal. The helical tooth structure of the serrated portion 22, after being flipped under pressure, forms multi-point contact with the lower surface of the upper equipment plane D, further improving the uniformity of the sealing pressure distribution and effectively blocking the intrusion path of water vapor. Simultaneously, the elastic design of the ring portion 21 adapts to assembly tolerances, ensuring stable sealing performance under long-term vibration conditions and further enhancing waterproof reliability.

[0046] In another embodiment, such as Figure 9 As shown, the second ring sleeve 2 is inclined outward (i.e. away from the first mounting port 100) and forms an acute angle θ with the first ring sleeve 1. This inclined structure makes it easier for the second ring sleeve 2 to expand radially outward when it is pressed during assembly, thereby reducing assembly resistance and generating a larger radial preload after being pressed against the equipment plane D.

[0047] The acute angle θ ranges from 60 degrees to 85 degrees, preferably 75 degrees, to balance structural strength and sealing surface fit.

[0048] In this embodiment, the waterproof sleeve for the aircraft separation surface is square. However, it is understood that there are no particular limitations on the specific style of the waterproof sleeve. Those skilled in the art can set it reasonably according to the actual situation. For example, in some embodiments, the waterproof sleeve for the aircraft separation surface can also be circular.

[0049] Furthermore, there are no specific limitations on the size of the waterproof sleeve on the aircraft separation surface, and those skilled in the art can set it reasonably according to the actual situation.

[0050] It should be noted that in some embodiments, the cabin plane A is not horizontally set. Instead, the cabin plane A slopes downwards from the first mounting port 100 to both sides to facilitate drainage and reduce the risk of water accumulation. At the same time, the sloped cabin plane A works in conjunction with the outward-curving serrated structure of the second ring part 2 to accelerate the detachment of the water film from the sealing interface under the assistance of gravity, further reducing the probability of water leakage.

[0051] In some embodiments, the wing plane B is not horizontally arranged; instead, the wing plane B is inclined downwards from the second mounting port 200 to both sides to accommodate the installation of the cockpit plane A.

[0052] The tilt angle between the cockpit plane A and the wing plane B can range from 3 degrees to 8 degrees, preferably 5 degrees. This tilt angle helps guide external water droplets to slide smoothly down the surface of the cockpit plane A or the wing plane B, avoiding the formation of liquid accumulation in the interface area, thereby improving the overall waterproof performance of the aircraft.

[0053] One end of the separation surface C between the cockpit plane A and the wing plane B is isolated from the interior of the cabin by a waterproof sleeve T, while the other end remains open with a small gap. Moisture at the separation surface C is effectively blocked by the waterproof sleeve T as it flows along the top of the cockpit, preventing it from entering the cabin through the wiring hole (i.e., the first mounting port 100) and forcing it to flow out from the open end. This design not only avoids pressure buildup caused by the formation of a closed cavity in the sealed area but also utilizes gravity and structural guidance to achieve natural drainage, significantly reducing the risk of moisture retention. Combined with the elastic fit of the waterproof sleeve T and the coordinated tilting layout of the cockpit plane A and the wing plane B, a multi-layered protection mechanism of "guidance-blocking-exhaustion" is formed, further enhancing the aircraft's waterproof reliability in complex weather conditions.

[0054] The waterproof sleeve of this application has a compact structure, is easy to install, and can be reused. It can effectively prevent rainwater from seeping into the top of the cabin. At the same time, the top of the second ring sleeve extends to the lower surface of the equipment plane D and is provided with a flange structure to prevent water vapor from seeping in along the edge of the installation port.

[0055] Furthermore, the waterproof sleeve is compatible with the cockpit-wing interface design of various aircraft models, possessing excellent versatility and maintainability. Actual testing has shown that it maintains a continuous seal under rain, snow, high humidity, and drastic temperature changes, meeting aviation-grade protection standards. Under extreme airflow disturbances, the flanged structure of the second ring sleeve forms a labyrinthine water-blocking path with the lower surface of the equipment plane D, effectively suppressing capillary penetration.

[0056] The above embodiments are merely illustrative of the principles and effects of this application. Any person skilled in the art can modify or alter the above embodiments without departing from the purpose of this application. Therefore, all equivalent modifications or alterations made by those skilled in the art without departing from the purpose disclosed in this application should still be covered by the claims of this application.

Claims

1. A waterproof sleeve for the separation surface of an aircraft, characterized in that, The waterproof sleeve is applied to the separation surface (C) between the lower cockpit plane (A) and the upper wing plane (B), wherein the cockpit plane (A) includes a first mounting port (100) and the wing plane (B) includes a second mounting port (200); the waterproof sleeve includes at least a first ring portion (1) and a second ring portion (2) connected to each other, wherein the first ring portion (1) is sealed to the edge of the first mounting port (100), and the second ring portion (2) extends upward and passes through the first mounting port (100) and the second mounting port (200) in sequence, so as to prevent water vapor on the separation surface (C) from entering the cockpit through the first mounting port (100).

2. The waterproof sleeve for the aircraft separation surface according to claim 1, characterized in that, The first ring sleeve (1) extends from the bottom of the second ring sleeve (2) toward the direction away from the first mounting port (100) and forms a sealing structure with the cabin plane (A).

3. The waterproof sleeve for the aircraft separation surface according to claim 1, characterized in that, The first ring part (1) and the second ring part (2) are perpendicularly connected to each other.

4. The waterproof sleeve for the aircraft separation surface according to claim 1, characterized in that, The second ring sleeve (2) is inclined in a direction away from the first mounting port (100) and forms an acute angle with the first ring sleeve (1).

5. The waterproof sleeve for the aircraft separation surface according to claim 1, characterized in that, The second mounting port (200) is larger than the first mounting port (100) to form an annular gap (3) around the second ring sleeve (2).

6. The waterproof sleeve for the aircraft separation surface according to claim 5, characterized in that, The second ring sleeve (2) includes a ring (21) and a serrated part (22) connected to the ring (21), wherein the serrated part (22) flips outward after being pressed to form a flange structure.

7. The waterproof sleeve for the aircraft separation surface according to claim 6, characterized in that, The height of the ring portion (21) is greater than the height of the annular gap (3) to ensure that the serrated portion (22) covers the annular gap (3) after being pressed and flipped.

8. The waterproof sleeve for the aircraft separation surface according to claim 1, characterized in that, The waterproof sleeve is square.

9. The waterproof sleeve for the aircraft separation surface according to claim 4, characterized in that, The acute angle ranges from 60 degrees to 85 degrees.

10. The waterproof sleeve for the aircraft separation surface according to claim 1, characterized in that, The cockpit plane (A) slopes downwards from the first mounting port (100) outwards.

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